DRAFT CAR Section 9 SERIES D - Part II, Aeronautical Telecommunications - Radio Navigation Aids

GOVERNMENT OF INDIA OFFICE OF DIRECTOR GENERAL OF CIVIL AVIATION TECHNICAL CENTRE, OPP SAFDARJANG AIRPORT, NEW DELHI CIVIL AVIATION REQUIREMENTS SECTION 9 – AIR SPACE AND AIR TRAFFIC MANAGEMENT SERIES 'D', PART II ISSUE V, 06th JANUARY 2026 EFFECTIVE: FORTHWITH F. No. AV. 21048/12/2018-ANS

Subject : Aeronautical Telecommunications – Radio Navigation Aids INTRODUCTION In pursuant to Article 28 of the Convention on International Civil Aviation each contracting State undertakes to provide in its territory, air navigation facilities to facilitate air navigation and also adopt and put into operation the appropriate standard systems for communication procedures, codes, markings, signals etc., in accordance with standards which may be recommended or established from time to time, pursuant to the Convention. International Civil Aviation Organization adopts and amends from time to time, as may be necessary, international standards and recommended practices and procedures for Aeronautical Telecommunications – Radio Navigation Aids in Annex 10 Volume I.

This CAR is issued under the provisions of Rule 29C and Rule 133A of the Aircraft Rules, 1937 for the requirements to be followed in respect of Aeronautical Telecommunications – Radio Navigation Aids.

This CAR is issued in supersession of CAR Section 4 Series ‘D’ Part II issue III dated 20TH SEPTEMBER 2022.

Applicability: This CAR is applicable to Air Navigation Service Provider(s) in India.

1. DEFINITIONS Note 1.: All references to "Radio Regulations” are to the Radio Regulations published by the International Telecommunication Union (ITU). Radio Regulations are amended from time to time by the decisions embodied in the Final Acts of World Radio communication Conferences held normally every two to three years. Further information on the ITU processes as they relate to aeronautical radio system frequency use is contained in the Handbook on Radio Frequency Spectrum Requirements for Civil Aviation including statement of approved ICAO policies (Doc 9718).

1CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note 2.: Intentionally left blank Note 3.: The terminology used in this CAR to refer to instrument approach operations is based on a previous version of the Annex 6 classification of instrument approach and landing operations. It can be mapped to the Annex 6 definitions as follows:

Performance requirements in support of instrument approach operations Annex 6 method - Annex 10 system performance Approach operation category

(1) Non-precision approach (NPA) 2D-Type A Approach with vertical guidance (2) 3D-Type A

(APV) Category I, DH equal to or greater than 75 m (250 ft)

(3) 3D-Type A Category I, DH equal to or greater than 60 m (200 ft) and less than 75 m (250 ft) (3) 3D-Type B - CAT I Precision approach (PA) Category II 3D-Type B - CAT II Category III 3D-Type B - CAT III

(1) Without vertical guidance.

(2) With barometric or SBAS vertical guidance.

(3) With ILS, MLS, GBAS or SBAS vertical guidance.

When the following terms are used in this CAR, they have the following meanings:

Altitude: The vertical distance of a level, a point or an object considered as a point, measured from mean sea level (MSL).

Area navigation (RNAV). A method of navigation which permits aircraft operation on any desired flight path within the coverage of ground- or space-based navigation aids or within the limits of the capability of self-contained aids, or a combination of these.

Effective acceptance bandwidth: The range of frequencies with respect to the assigned frequency for which reception is assured when all receiver tolerances have been taken into account.

Effective adjacent channel rejection: The rejection that is obtained at the 2CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 appropriate adjacent channel frequency when all relevant receiver tolerances have been taken into account.

Elevation: The vertical distance of a point or a level, on or affixed to the surface of the earth, measured from mean sea level.

Fan marker beacon: A type of radio beacon, the emissions of which radiate in a vertical fan-shaped pattern.

Height: The vertical distance of a level, a point or an object considered as a point, measured from a specified datum.

Human Factors principles: Principles which apply to design, certification, training, operations and maintenance and which seek safe interface between the human and other system components by proper consideration to human performance.

Mean power (of a radio transmitter). The average power supplied to the antenna transmission line by a transmitter during an interval of time sufficiently long compared with the lowest frequency encountered in the modulation taken under normal operating conditions.

Note: A time of 1/10 second during which the mean power is greatest will be selected normally.

Navigation Specification. A set of aircraft and flight crew requirements needed to support performance-based navigation operations within a defined airspace. There

are two kinds of navigation specifications:

Required navigation performance (RNP) specification. A navigation specification based on area navigation that includes the requirement for performance monitoring and alerting, designated by the prefix RNP, e.g. RNP 4, RNP APCH.

Area navigation (RNAV) specification. A navigation specification based on area navigation that does not include the requirement for performance monitoring and alerting, designated by the prefix RNAV, e.g. RNAV 5, RNAV 1.

Note.1.: The Performance-based Navigation (PBN) Manual (Doc 9613), Volume II, contains detailed guidance on navigation specifications.

Note 2.: The term RNP as previously defined as “a statement of the navigation performance, necessary for operation within a defined airspace”, has been removed from this Annex as the concept of RNP has been overtaken by the concept of PBN. The term RNP in this Annex is now solely used in context of navigation specifications that require performance monitoring and alerting, e.g. RNP 4 refers to the aircraft and operating requirements, including a 4 NM lateral performance with on-board performance monitoring and alerting that are detailed in the PBN Manual (Doc 9613).

Performance-based navigation (PBN). Area navigation based on performance requirements for aircraft operating along an ATS route, on an instrument approach procedure or in a designated airspace.

3CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.: Performance requirements are expressed in navigation specifications (RNAV specification, RNP specification) in terms of accuracy, integrity, continuity and functionality needed for the proposed operation in the context of a particular airspace concept. Availability of a global navigation satellite system signal in space (GNSS SIS) or some other NAVAID infrastructure is considered within the airspace concept in order to enable the navigation application.

Pressure-altitude: An atmospheric pressure expressed in terms of altitude which corresponds to that pressure in the Standard Atmosphere.

Protected service volume: A part of the facility coverage where the facility provides a particular service in accordance with relevant SARPs and within which the facility is afforded frequency protection.

Touchdown: The point where the nominal glide path intercepts the runway.

4CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Global navigation satellite system (GNSS)

1.1 A standard aid to navigation shall be the global navigation satellite system

(GNSS) conforming to the Standards contained in Chapter 2, 2.

Note 1.: It is intended that any change in, or addition to, Standards in Chapter 2, 2 that will require the replacement of GNSS equipment can become applicable on the basis of a six-year advance notice.

Note 2.: GNSS is expected to support all phases of flight and aerodrome surface operations, however, present SARPs provide for en-route, terminal and approach and landing operations down to Category I precision approach.

1.2 It shall be permissible to terminate a GNSS satellite service provided by one of its elements (Chapter 2, 2.2) on the basis of at least a six-year advance notice by a service provider.

1.3 Recording and retention of GNSS data

1.3.1 Recommendation. Service providers for GNSS-based operations should ensure that GNSS data relevant to those operations are recorded.

Note 1.: These recorded data are primarily intended for use in accident and incident investigations. They may also support periodic confirmation that accuracy, integrity, continuity and availability are maintained within the limits required for the operations approved.

Note 2.: Guidance material on the recording of GNSS parameters is contained in Attachment D, 11.

1.3.2 Recommendation. Recordings should be retained for a period of at least fourteen days. When the recordings are pertinent to accident and incident investigations, they should be retained for longer periods until it is evident that they will no longer be required.

5CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

2. General Provisions For Radio Navigation Aids

2.1. Standard radio navigation aids

2.1.1. The standard radio navigation aids shall be: a) the instrument landing system (ILS) b) the VHF Omni-directional radio range (VOR) c) the global navigation satellite system (GNSS) confirming to the Standards contained in Chapter 3.3.7 d) the non-directional beacon (NDB) e) the distance measuring equipment (DME) f) the en-route VHF marker beacon Note1: Since radio navigation is essential for the final stages of approach and landing, the installation of non-visual aids does not obviate the need for visual aids to approach and landing in conditions of low visibility.

2.1.2. Differences in radio navigation aids in any respect of provisions in para 3 of this CAR shall be published in an Aeronautical Information Publication

(AIP).

2.1.3. Wherever there is installed a radio navigation aid that is not an ILS but which may be used in whole or in part with aircraft equipment designed for use with the ILS, full details of parts that may be so used shall be published in an Aeronautical Information Publication (AIP).

Note.: This provision is to establish requirement for promulgation of relevant information rather than to authorize such installation

2.1.4 GNSS-specific provisions

2.1.4.1 It shall be permissible to terminate a GNSS satellite service provided by one of its elements (Chapter 3, 3.7.2) on the basis of at least a six-year advance notice by a service provider.

2.1.4.2 The service provider shall ensure that GNSS data relevant to the provision of GNSS services for GNSS operations are recorded.

Note 1.: The recorded data are primarily intended for use in accident and incident investigations. They may also support periodic confirmation that accuracy, integrity, continuity and availability are maintained within the limits required for the operations approved.

Note 2.: Guidance material on the recording of GNSS parameters is contained in Attachment D,11 and 12

2.1.4.3 Recordings should be retained for a period of at least 14 days. When the 6CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 recordings are pertinent to accident and incident investigations, they should be retained for longer periods until it is evident that they will no longer be required.

2.1.5 Intentionally left blank.

2.1.5.1 Intentionally left blank.

2.1.5.2 The SRE may be installed and operated without the PAR for: a) The assistance of air traffic control in handling aircraft intending to use a radio navigation aid, or for; b) Surveillance radar approaches and departures.

2.1.6 When a radio navigation aid is provided to support precision approach and landing it should be supplemented by a source of guidance information which, when used in conjunction with appropriate procedures, will provide effective guidance to the desired reference path.

Note.: VOR, NDB, DME, GNSS and aircraft navigation systems have been established for purposes mentioned above.

2.2 Ground and flight-testing:

2.2.1 Radio navigation aids of the types covered by the specifications in Chapter 3 and available for use by aircraft engaged in international air navigation are subject of periodic ground and flight tests.

Note.: NDB shall not be subjected to periodic flight tests.

2.3 Provision of information on the operational status of radio navigation aids

2.3.1 Aerodrome control towers and units providing approach control service shall be provided without delay with information on the operational status of radio navigation aids essential for approach, landing and take-off at the aerodrome(s) with which they are concerned.

2.4 Power supply for radio navigation aids and communication systems

2.4.1 Radio navigation aids and ground elements of communication systems shall be provided with suitable power supplies and means to ensure continuity of service consist with the use of the service(s) involved.

2.5 Human Factors considerations

2.5.1 Human Factors principles should be observed in the design and certification of radio navigation aids.

7CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.: Guidance material on Human Factors principles can be found in the Human Factors Training Manual (Doc 9683) and Circular 249 (Human Factors Digest No. 11— Human Factors in CNS/ATM Systems).

3 Specifications For Radio Navigation Aids

3.1. Specification for ILS

3.1.1. Definitions

Angular displacement sensitivity: The ratio of measured DDM to the corresponding angular displacement from the appropriate reference line.

Back course sector: The course sector which is situated on the opposite side of the localizer from the runway.

Course line: The locus of the points nearest to the runway centre line in any horizontal plane at which the DDM is zero.

Course sector: A sector in a horizontal plane containing the course line and limited by the loci of points nearest to the course line at which the DDM is 0.155.

DDM-Difference in depth of modulation: The percentage modulation depth of larger signal minus the percentage modulation depth of the smaller signal, divided by 100.

Displacement sensitivity (localizer): The ratio of measured DDM to the corresponding lateral displacement from the appropriate reference line.

Facility performance Category I - ILS: An ILS which provides guidance information from the coverage limit of the ILS to the point at which the localizer course line intersects the ILS glide path at a height of 60m(200ft) or less above the horizontal plane containing the threshold.

Facility Performance Category II – ILS: An ILS which provides guidance information from the coverage limit of the ILS to the point at which the localizer course line intersects the ILS glide path at a height of 15m (50 ft ) or less above the horizontal plane containing the threshold.

Facility Performance Category III – ILS: An ILS which, with the aid of ancillary equipment where necessary, provides guidance information from the coverage limit of the facility to, and along, the surface of the runway.

Front course sector: The course sector which is situated on the same side of the localizer as the runway.

Half course sector: The sector. In a horizontal place containing the course line and limited by the loci of points nearest to the course line at which the DDM is 0.0775.

Half ILS glide path sector: The sector in the vertical plane containing the 8CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 ILS glide path and limited by the loci of points nearest to the glide path at which the DDM is 0.0875.

ILS continuity of service: That quality which relates to the rarity of radiated signal interruptions. The level of continuity of service of the localizer or the glide path is expressed in terms of the probability of not losing the radiated guidance signals.

ILS glide path: That locus of points in the vertical plane containing the runway centre line at which the DDM is zero, which, of all such loci, is the closest to the horizontal plane.

ILS glide path angle: The angle between a straight line which represents the mean of the ILS glide path and the horizontal.

ILS glide path sector: The sector in the vertical plane containing the ILS glide path and limited by the loci of points nearest to the glide path at which the DDM is 0.175.

Note.: The ILS glide path sector is located in the vertical plane containing the runway centre line, and is divided by the radiated glide path in two parts called upper sector and lower sector, referring respectively to the sectors above and below the glide path.

ILS integrity: That quality which relates to the trust which can be placed in the correctness of the information supplied by the facility. The level of integrity of the localizer or the glide path is expressed in terms of the probability of not radiating false guidance signals.

ILS Point “A”: A point on the ILS glide path measured along the extended runway centre line in the approach direction a distance of 7.5 km (4 NM) from the threshold.

ILS Point “B”: A point on the ILS glide path measured along the extended runway centre line in the approach direction a distance of 1 050m (3500ft) from the threshold.

ILS point “C”: A Point through which the downward extended straight portion of the nominal ILS glide path passes at a height of 30m (100ft) above the horizontal plane containing the threshold.

ILS Point “D”: A point 4m (12ft) above the runway centre line and 900m

(3000ft) from the threshold in the direction of localizer.

ILS Point “E”: A point 4m (12ft) above the runway centre line and 600m

(2000ft) from the stop end of the runway in the direction of the threshold.

ILS Reference Datum (Point “T”): A point at a specified height located above the intersection of the runway centre line and the threshold and through which the downward extended straight portion of the ILS glide path passes (See figure 1).

9CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

Two Frequency glide path system: An ILS glide path in which coverage is achieved by the use of two independent radiation field patterns spaced on separate carrier frequencies within the particular glide path channel.

Two-frequency localizer system: A localizer system in which coverage is achieved by the use of two independent radiation field patterns spaced on separate carrier frequencies within the particular localizer VHF channel.

Figure 1

3.1.2. Basic requirements

3.1.2.1 The ILS shall comprise the following basic components: a) VHF localizer equipment, associated monitor system, remote control and indicator equipment; b) UHF glide path equipment, associated monitor system, remote control and indicator equipment;

c) VHF marker beacons, or a distance measuring equipment (DME) in accordance with para 3.5, together with associated monitor system and remote control and status indicator equipment.

3.1.2.1.1 Facility performance Categories I, II, and III- ILS shall provide indications at designated remote control points of the operational status of all ILS ground system components, as follows a) For all Category II and Category III ILS, the air traffic services unit involved in the control of the aircraft on the final approach shall be one of the designated remote control points and shall receive information on the operational status of the ILS, with a delay commensurate with the requirements of the operational environment.

10CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 b) For a Category I ILS, if that ILS provides an essential radio navigation service, the air traffic services unit involved in the control of aircraft on the final approach shall be one of the designated remote control points and shall receive information on the operational status of the ILS, with a delay commensurate with the requirements of the operational environment.

Note 1.: The indications required by this Standard are intended as a tool to support air traffic management functions, and the applicable timeliness requirements are sized accordingly (consistently with 2.8.1). Timeliness requirements applicable to the ILS integrity monitoring functions that protect aircraft from ILS malfunctions are specified in 3.1.3.11.3.1 and 3.1.5.7.3.1.

Note 2.: It is intended that the air traffic system is likely to call for additional provisions which may be found essential for the attainment of full operational Category III capability, e.g. to provide additional lateral and longitudinal guidance during the landing roll-out, and taxiing, and to ensure enhancement of the integrity and reliability of the system.

3.1.2.1.2 If one or more VHF marker beacons are used to provide distance to threshold information, the equipment shall conform to the specifications in

3.1.7. If DME is used in lieu of marker beacons, the equipment shall conform to the specifications in 3.1.7.6.5.

Note.: Guidance material relative to the use of DME and/or other standard radio navigation aids as an alternative to the marker beacon is contained in Attachment C.

3.1.2.2 The ILS shall be constructed and adjusted so that, at a specified distance from the threshold, similar instrumental indications in the aircraft represent similar displacement from the course line or ILS glide path as appropriate, irrespective of the particular ground installations in use.

3.1.2.3 The localizer and glide path components specified in 3.2.1. a) And b) above which form part of a facility Performance Category I – ILS shall comply at least with the provisions in para 3.1.3 and 3.1.5 below respectively, excepting those in which application to Facility Performance Category II – ILS is prescribed.

3.1.2.4 The localizer and glide path components specified in 3.1.2.1 a) and b) above which form part of a facility Performance Category II- ILS shall comply with the standards applicable to these components in a Facility performance Category I – ILD, as supplemented or amended by the provisions in para 3.1.3 and 3.1.5 below in which application to facility Performance Category II – ILS is prescribed.

3.1.2.5 The localizer and glide path components and ancillary equipment specified in 3.1.2.1.1 above, which form part of a Facility Performance Category III – ILS, shall otherwise comply with the provisions applicable to these components in Facility Performance Categories I and II – ILS, except as 11CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 supplemented by the Standards specified is of a high value, consistent with category of operational performance.

3.1.2.6 To ensure an adequate level of safety, the ILS shall be so designed and maintained that the probability of operation with the performance requirements specified is of a high value, consistent of operational performance concerned.

3.1.2.6.1 For Facility Performance Category II and III localizers and glide paths, the level of integrity and continuity of service shall be at least Level 3, as defined in 3.1.3.12.4 (localizer) and 3.1.5.8.4 (glide path).

Note.: The specifications for Facility Performance Categories II and III — ILS are intended to achieve the highest degree of system integrity, reliability and stability of operation under the most adverse environmental conditions to be encountered. Guidance material to achieve this objective is given in 2.8 of Attachment C.

3.1.2.7 At those locations where two separate ILS facilities serve opposite ends of a single runway, an interlock shall ensure that only the localizer serving the approach direction in use shall radiate, except where the localizer in operational use is Facility Performance Category I – ILS and no operationally harmful interference results.

3.1.2.7.1 At those locations where two separate ILS facilities serve opposite ends of a single runway and where a facility performance Category I – ILS is to be used for auto coupled approaches and landing in visual conditions, an interlock shall ensure that only the localizer serving the approach direction in use radiates providing the other localizer is not required for simultaneous operational use.

3.1.2.7.2 At locations where ILS facilities serving opposite ends of the same runway or different runways at the same airport use the same paired frequencies, an interlock shall ensure that only on facility shall radiate at a time. When switching from one ILS facility to another, radiation from both shall be suppressed for not less than 20 seconds.

3.1.2.8 At those locations where an ILS facility and a GBAS facility serve opposite approach directions to the same runway, when the approach direction in use is not the direction served by the ILS, the localizer shall not radiate when GBAS low visibility operations that require GAST D are being conducted.

3.1.3. VHF localizer and associated monitor The provisions of 3.1.3 cover ILS localizers providing wither positive guidance information over 360 degrees of azimuth, or providing such guidance only with a specified portion of the front coverage (see para

3.1.3.7.4 below). Where ILS localizers providing positive guidance information in a limited sector are installed, information from some suitably 12CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 located navigation aid, together with appropriate procedures, will generally be required to ensure that any misleading guidance information outside the sector is not operationally significant.

3.1.3.1 General

3.1.3.1.1 The radiation from the localizer antenna system shall produce a composite field pattern which is amplitude modulated by a 90 Hz and a 150 Hz tone.

The radiation field pattern shall produce a course sector with one tone predominating on one side of the course and with the other tone predominating on the opposite side.

3.1.3.1.2 When an observer faces the localizer from the approach end of a runway, the depth of modulation of the radio frequency carrier due to the 150 Hz tone shall predominate on his right hand and that due to the 90 Hz tone shall predominate on his left hand.

3.1.3.1.3 All horizontal angles employed in specifying the localizer field patterns shall originate from the centre of the localizer antenna system which provides the signals used the front course sector.

3.1.3.2 Radio frequency

3.1.3.2.1 The localizer shall operate in the band 108 MHz to 111.975 MHz Where a single radio frequency carrier is used, the frequency tolerance shall not exceed plus or minus 0.005 per cent. Where two radio frequency carriers are used, the frequency tolerance shall not exceed 0.002 per cent and the nominal band occupied by the carriers shall be symmetrical about the assigned frequency, the all tolerances applied, the frequency separation between the carriers shall not be less than 5 KHz nor more than 14 KHz.

3.1.3.2.2 The emission from the localizer shall be horizontally polarized. The vertically polarized component of the radiation on the course line shall not exceed that which corresponds to a DDM error of 0.016 when an aircraft is positioned on the course line and is in a roll attitude of 20 degrees from the horizontal.

3.1.3.2.2.1 For Facility Performance Category II localizers, the vertically polarized Component of the radiation on the course line shall not exceed that which corresponds to a DDM error 0.008 when an aircraft is positioned on the course line and is in a roll attitude of 20 degrees from the horizontal.

3.1.3.2.2.2 For Facility Performance Category III localizers, the vertically polarized component of the radiation within in sector bounded by 0.02 DDM either side of the course line shall not exceed that which corresponds to a DDM error of 0.005 when an aircraft is in a roll attitude of 20 degrees from the horizontal.

3.1.3.2.2.3 For Facility Performance Category III localizers, the signals emanating 13CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 from the transmitter shall contain no components which result in a apparent course line fluctuation of more than 0.005 DDM peak to peak in the frequency band 01.01 Hz to 10 Hz.

3.1.3.3 Coverage

3.1.3.3.1 The Localizer shall provide signals sufficient to allow satisfactory operation of typical aircraft installation within the localizer and glide path coverage sectors. The localizer coverage sector shall extend form the centre of the

localizer antenna system to distances of: a) 46.3 km (25NM) within plus or minus 10 degrees from the front course line; b) 31.5 km (17NM) between 10 degrees and 35 degrees from the front course line; c) 18.5 km (10 NM) outside of plus or minus 35 degrees from the front course line if coverage is provided;

except that, where topographical features dictate or operation requirements permit, the limits may be reduced down to 33.3 km (18NM) within the plus or minus 10 degree sector and 18.5 km (10NM) within the remainder of the coverage when alternative navigational means provide satisfactory coverage within the intermediate approach area. The localizer signals shall be receivable at the distances specified at and above a height of 600 m

(2000ft) above the elevation the threshold, or 300m (1000ft) above the elevation of the highest point within the intermediate and final approach areas, whichever is the higher, except that, where needed to protect ILS performance and if operational requirements permit, the lower limit of coverage at angles beyond 15 degrees from the front course line shall be raised linearly from its height at 15 degrees to as high as 1350m (4500 ft) above the elevation of the threshold at 35 degrees from the front course line.

Such signals shall be receivable, to the distances specified, up to a surface extending outward from the localizer antenna and inclined at 7 degrees above the horizontal.

Note.: Where intervening obstacles penetrate the lower surface, it is intended that guidance need not be provided at less than line –of-sight heights.

3.1.3.3.2 In all parts of the coverage volume specified in 3.1.3.3.1 above, other than as specified in 3.1.3.3.2.1, 3.1.3.3.2.2 and 3.1.3.3.2.3 below, the field 2 strength shall be not less than 50 micro volts per meter (minus 114dbW/m ).

This field strength is required to permit satisfactory operational usage of ILS localizer facilities.

3.1.3.3.2.1 For Facility Performance Category I localizers, the minimum field strength on the ILS glide path and within the localizer course sector from a distance 14CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 of 18.5 km (10 NM) to a height of 60m (200ft) above the horizontal place containing the threshold shall be not less than 90 micro volts per meter 2 (minus 107 db W/ m ).

3.1.3.3.2.2 For facility performance Category II localizers, the minimum field strength on the ILS glide path and within the localizer course sector shall be not less 2 than 100 microvolt per meter (minus 106 dB W/m ) at a distance of 18.5 km (10NM) increasing to not less than 200 µ volts per meter (minus 100 dB 2 W/m ) at height of 15m (50 ft) above the horizontal plane containing the threshold. This field strength is necessary to provide the signal to noise ration required for improve integrity.

3.1.3.3.2.3 For Facility Performance Category III localizers, the minimum field strength on the ILS glide path and within the localizer course sector shall be not less 2 than 100 µ volts per meter (minus 106 dB W/m ) at a distance of 18.5km (10 NM), increasing to not less than 200 µ volts per meter (minus 100 dB 2 W/m ) at 6 m (20ft) above the horizontal plane containing the threshold.

From this point to a further point 4 m (12 ft) above the runway centre line, and 300m (1000ft) from the threshold in the direction of the localizer, and thereafter at height of 4m (12ft) along the length of the runway in the direction of the localizer, the field strength shall be not less than 100 µ volts 2 per meter (minus 106 dB W/m ). This field strength is necessary to provide the signal to noise ratio required for improved integrity.

15CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Figure 2 Localizer Coverage with respect to azimuth Figure 2A Reduced Localizer Coverage with respect to azimuth 16CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Figure 3.

Figure 3A Reduced Localizer Coverage with respect to elevation Note.: Because of the siting problems and terrain limitations, some localizers may not meet the standard coverage area described above. In such cases approach plate design will assure aircraft remain within areas of adequate signal coverage and such information will be duly annotated on the approach plate.

3.1.3.3.3 Above 7 degrees, the signals should be reduced to as low as practicable.

3.1.3.3.4 When coverage is achieved by a localizer using two radio frequency carriers, one carrier providing a radiation field pattern in the front course sector and the other providing a radiation field pattern outside that sector, the ratio of the two carrier signal strengths in space within the front course sector to the coverage limits specified at 3.1.3.3.1 above shall not be less than 10 dB.

17CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.3.3.4.1 For facility performance Category III localizers, the ratio of the two carrier signal strengths in space within the front course sector should not be less than 16 dB.

3.1.3.4 Course structure

3.1.3.4.1 For Facility Performance Category I localizers, bends in the course line shall

not have amplitudes which exceed the following:

Zone Amplitude (DDM) (95% Probability) Outer limit of coverage to ILS point “A” 0.031 ILS point “A” to 0.031 at ILS Point “A” ILS Point “B” decreasing at a linear rate to

0.015 at ILS point “B” ILS Point “B” to ILS Point “C” 015

3.1.3.4.2 For Facility Performance Categories II and III localizers, bends in the course

line shall not have amplitudes which exceed the following:

Zone Amplitude (DDM) (95% Probability) Outer limit of coverage to ILS point “A” 0.031 ILS point “A” to 0.031 at ILS Point “A” ILS Point “B” decreasing at a linear rate to

0.005 at ILS point “B” ILS point “B” to ILS reference datum 0.005 and, for Category ILS reference datum to ILS Point “D” 0.005 ILS Point “D” to ILS 0.005 at ILS Point “D” increasing at a linear rate to 0.010 at ILS Point “E” 18CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Figure 4

3.1.3.5 Carrier modulation

3.1.3.5.1 The nominal depth of modulation of the radio frequency carrier due to each of the 90 Hz and 150 Hz tones shall be 20 per cent along the course line.

3.1.3.5.2 The depth of modulation of the radio frequency carrier due to each of the 90 Hz and 150 Hz tones shall be within the limits of 18 and 22 per cent.

3.1.3.5.3 The following tolerances shall be applied to frequencies of the modulating

tones: a) The modulating tones shall be 90 Hz and 150 Hz within plus or minus

2.5 per cent; b) The modulating tones shall be 90 Hz and 150Hz within plus or minus

1.5 per cent for facility performance category II installations; c) The modulating tones shall be 90 Hz and 150Hz within plus or minus 1 per cent for facility performance category III installations; d) The total harmonic content of the 90 Hz tone shall not exceed 10 per cent; additionally, for facility performance category III localizers, the second harmonic of the 90 Hz tone shall not exceed 5 per cent;

e) The total harmonic content of the 150 Hz tone shall not exceed 10 per cent 19CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.3.5.3.1 For facility performance category I – ILS, the modulating tones should be 90 Hz and 150 Hz within plus or minus 1.5 per cent where practicable.

3.1.3.5.3.2 For facility performance category III localizers, the depth of amplitude modulation of the radio frequency carrier at the power supply frequency or its harmonics, or by other unwanted components, shall not exceed 0.5 per cent. Harmonics of the supply, or other unwanted noise components that may inter modulate with the 90 Hz and 150 Hz navigational tones or their harmonics to produce fluctuations in the course line, shall not exceed 0.05 per cent modulation depth of the radio frequency carrier.

3.1.3.5.3.3 The modulation tones shall be phase-locked so that within the half course sector, the demodulation 90 Hz and 150 Hz wave forms pass through zero in

the same direction within: a) for Facility Performance Categories I and II localizers: 20 degrees; and b) for Facility Performance Category III localizers: 10 degrees, c) of phase relative to the 150 Hz component, every half cycle of the combined 90 Hz and 150 Hz wave form.

3.1.3.5.3.4. With two-frequency localizer systems, 3.1.3.5.3.3 above shall apply to each carrier. In addition, the 90 Hz modulating tone of one carrier shall be phase locked to the 90 Hz modulating tone of the other carrier so that the

demodulated wave forms pass through zero in the same direction within: a) for categories I and II localizers: 20 degrees; and b) for category III localizers: 10 degrees, of phase relative to 90 Hz.

Similarly, the 150 Hz tones of the two carriers shall be phase locked so that the demodulated wave forms pass through zero in the same

direction within:

1) for categories I and II localizers: 20 degrees; and

2) for categories III localizers: 10 degrees of phase relative to 150 Hz.

3.1.3.5.3.5. Alternative two-frequency localizer systems that employ audio phasing different from the normal in phase conditions described in 3.1.3.5.3.4 above shall be permitted. In this alternative system, the 90 Hz to 90 Hz phasing and the 150 Hz to 150 Hz phasing shall be adjusted to their nominal values to within limits equivalent to those stated in 3.1.3.5.3.4 above.

20CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

Note: This is to ensure correct airborne receiver operation in the region away from the course line where the two carrier signal strengths are approximately equal.

3.1.3.5.3.6. The sum of the modulations depths of the radio frequency carrier due to the 90 Hz and 150 Hz tones should not exceed 60 per cent or be less than 30 per cent within the required coverage.

3.1.3.5.3.6.1.For equipment first installed after 1 January 2000, the sum of the modulation depths of the radio frequency carrier due to the 90 Hz and 150 Hz tones shall not exceed 60 per cent or be less than 30 percent within the required coverage.

Note 1: If the sum of the modulation depths is greater than 60 percent for Facility Performance Category 1 localizers, the nominal displacement sensitivity may be adjusted as provided for in 3.1.3.7.1 to achieve the above modulation limit.

Note 2: For two-frequency systems, the standard for maximum sum of modulation depths does not apply at or near azimuths where the course and clearance carrier signal levels are equal in amplitude (i.e. at azimuths where both transmitting systems have a significant contribution to the total modulation depth) Note 3: The standard for minimum sum of modulation depths is based on the malfunctioning alarm level being set as high as 30 per cent.

21CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Figure 5 ILS Wave forms illustrating relative audio phasing of the 90 Hz & 150 Hz tones.

3.1.3.5.3.7. When utilizing a localizer for radiotelephone communications, the sum of the modulation depths of the radio frequency carrier due to the 90 Hz and 150 Hz tones shall not exceed 65 percent with 10 degrees of the course line and shall not exceed 78 percent at any other point around the localizer.

3.1.3.5.4. Undesired frequency and phase modulation on ILS localizer radio frequency carriers that can affect the displayed DDM values in localizer receivers should be minimized to the extent practical.

3.1.3.6 Course alignment accuracy

3.1.3.6.1 The mean course line shall be adjusted and maintained within limits equivalent to the following displacements from the runway centre line at

the ILS reference datum:

22CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 a) for Facility Performance Category I localizers: plus or minus 10.5m

(35ft), or the linear equivalent of 0.015 DDM, whichever is less; b) for Facility Performance Category II localizers: plus or minus 7.5m (25ft); c) for Facility Performance Category III localizers: plus or minus 3 m (10 ft)

3.1.3.6.2 For Facility Performance Category II localizers, the mean course line should be adjusted and maintained within limits equivalent to plus or minus 4.5m (15ft) displacement from runway centre line at the ILS reference datum.

3.1.3.7 Displacement sensitivity

3.1.3.7.1 The normal displacement sensitivity within the half course sector shall be the equivalent of 0.00145 DDM/m 0.00044 DDM/ft) at the ILS reference datum except that for Category I localizers, where the specified nominal displacement sensitivity cannot be met, the displacement sensitivity shall be adjusted as near as possible to the value. For facility Performance Category I localizers on runway codes 1 and 2, the nominal displacement sensitivity shall be achieved at the ILS point “B”. The maximum course sector angle shall not exceed 6 degrees.

3.1.3.7.2 The lateral displacement sensitivity shall be adjusted and maintained within

the limits of plus or minus: a) 17 per cent of the nominal value for Facility Performance Categories I and II; b) 10 per cent of the nominal value for Facility Performance Category III.

3.1.3.7.3 For Facility Performance Category II –ILS, displacement sensitivity should be adjusted and maintained with the limits of plus or minus 10 percent where practicable.

Note.: The figures given in 3.1.3.7.1, 3.1.3.7.2 & 3.1.3.7.3 above are based up on a nominal sector width of 210m (700 feet) at the appropriate time i.e. ILS point “B” on runway codes 1&2 and the ILS reference datum on other runways.

23CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Figure 6 Difference in depth of modulation and displacement sensitivity

3.1.3.7.4 The increase of DDM shall be substantially linear with respect to angular displacement from the front course line (where DDM is zero) up to an angle on either side of the front course line where the DDM is 0.180. From that angle to plus or minus 10 degrees, the DDM shall not be less that

0.180. From plus or minus 10 degrees to plus or minus 35 degrees, the DDM shall not be less than 0.155. Where coverage is required outside of the plus or minus 35 degrees sector, The DDM in the area of the coverage, except in the back course sector shall not be less than 0.155.

Note 1.: The linearity of change of DDM with respect to angular displacement is particularly important in the neighborhood of the course line.

Note 2.: The above DDM in the 10-35 degree sector is to be considered a minimum requirement of the use of ILS as a landing aid. Wherever practicable a higher DDM, e.g. 0.180, is advantageous to assist high speed aircraft to execute large angle intercepts a operationally desirable distances provided that limits on modulation percentage given in 3.1.3.5.3.6 are met.

Note 3.: Wherever practicable, the localizer capture level of automatic flight control systems is to be set at or below 0.175 DDM in order to prevent false localizer captures.

3.1.3.8 Voice

3.1.3.8.1 Facility Performance Categories I and II localizers may provide a ground- to- air radiotelephone communication channel to be operated simultaneously with the navigation and identification signals, provided that such operation shall not interfere in any way with the basic localizer function.

3.1.3.8.2 Category III localizers shall not provide such a channel, except where extreme care has been taken in the design and operation of the facility to ensure that there is no possibility of interference with the navigational 24CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 guidance.

25CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.3.8.3 If the channel is provided, it shall conform with the following standards:

3.1.3.8.3.1 The channel shall be on the same radio frequency carrier or carriers as used for the localizer function and the radiation shall be horizontally polarized. Where to carriers are modulated with speech, the relative phases of the modulations on the two carriers shall be such as to avoid the occurrence of nulls within the coverage of the localizer.

3.1.3.8.3.2 The peak modulation depth of the carrier of carriers due to the radiotelephone communications shall not exceed 50 per cent bust shall be

adjusted so that: a) The ratio of peak modulation depth due to the radiotelephone communications to that due to identification signal is approximately 9:1; b) The sum of modulation components due to use of the radiotelephone channel, navigational signals and identification signals shall not exceed 95 per cent.

3.1.3.8.3.3 The audio frequency characteristics of the radiotelephone channel shall be flat to with 3 dB relative to the level at 1000 Hz over the range 300 Hz to 3000 Hz

3.1.3.9 Identification

3.1.3.9.1 The localizer shall provide for the simultaneous transmission of an identification signal, specific to the runway and approach direction, on the same radio frequency carrier of carriers as used for the localizer function.

The transmission of the identification signal shall not interfere in any way with the basic localizer function.

3.1.3.9.2 The identification signal shall be produced by Class A2A modulation of the radio frequency carrier or carriers using a modulation tone of 1020 Hz within plus or minus 50 Hz. The depth of modulation shall be between the limits of 5 and 15 per cent except that, where a radiotelephone communication channel is provided, the depth of modulation shall be adjusted so that the ratio of peak modulation depth due to radiotelephone communications to that due to the identification signal modulation is approximately 9:1 (see

3.1.3.8.3.2 above). The emissions carrying the identification signal shall be horizontally polarized. Where two carriers are modulated with identification signals, the relative phase of the modulations shall be such as to avoid the occurrence of nulls within the coverage of the localizer.

3.1.3.9.3 The identification signal shall employ the International Morse Code and consist of two or three letters. It may be preceded by the International Morse Code signal of the letter “I”, followed by a short pause where it is necessary to distinguish the ILS facilities from other navigational facilities in the immediate area.

26CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.3.9.4 The identification signal shall be transmitted by dots and dashes at a speed corresponding to approximately seven words per minute, and shall be repeated at approximately equal intervals, not less than six times per minute, at all times during which the localizer is available for operational use. When the transmission of the localizer is not available for operational use, as, for example, after removal of navigational components, or during maintenance or test transmissions, the identification signal shall be suppressed. The dots shall have a duration of 0.1 second to 0.160 second.

The dash duration shall be typically three times the duration of a dot. The interval between dots and/or dashes shall be equal to that of one dot plus or minus 10 percent. The interval between letters shall not be less than the duration of three dots.

3.1.3.10 Siting

3.1.3.10.1 For Facility Performance Categories II and III the localizer antenna system shall be located on the extension of the centre line of the runway at the stop end, and the equipment shall be adjusted so that the course lines will be in a vertical plane containing the centre line of the runway served. The antenna height and location shall be consistent with safe obstruction clearance practices.

3.1.3.10.2 For Facility Performance Category I, the localizer antenna system shall be located and adjusted as in 3.1.3.10.1, unless site constraints dictate that the antenna be offset from the centre line of the runway.

3.1.3.10.2.1 The offset localizer system shall be located and adjusted in accordance with the offset ILS provisions of the PANS-OPS (Doc 8168), Volume II, and the localizer standards shall be referenced to the associated fictitious threshold point.

3.1.3.11 Monitoring

3.1.3.11.1 The automatic monitor system shall provide a warning to the designated control points and cause one of the following to occur, within the period specified in 3.1.3.11.3.1 below, if any of the conditions stated in 3.1.3.11.2

below persists: a) radiation to cease b) removal of navigation and identification components from the carrier;

3.1.3.11.2 The condition requiring monitor action shall be the following; a) for Category I localizers, a shift of the mean course line from the runway center line equivalent to more than 10.5m (35ft), or the linear equivalent to 0.015 DDM, whichever is less, at the ILS reference datum;

27CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 b) for Facility Performance Category II localizer, a shift of mean course line from the runway centre line equivalent to more than 7.5 m (25 ft) at the ILS reference datum.

c) for facility Performance Category III localizer, a shift of the mean course line from the runway center line equivalent to more than 6m

(20ft) at the ILS reference datum ; d) in the case of localizer in which the basic functions are provided by the use of a single-frequency system, a reduction of power output to a level such that any of the requirements of 3.1.3.3, 3.1.3.4 or 3.1.3.5 are no longer satisfied, or to a level that is less than 50 percent of the normal level (whichever comes first) e) in the case of localizers in which the basic functions are provided by the use of a two-frequency system, a reduction of power output for either carrier to less than 80 per cent of normal, except that a greater reduction to between 80 per cent and 50 per cent of normal may be permitted, provided the localizer continues to meet the requirements of 3.1.3.3, 3.1.3.4 and 3.1.3.5 above.

Note.: It is important to recognize that frequency change resulting in a loss of the frequency difference specified in 3.1.3.2.1 above may produce hazardous condition. This problem of greater operational significance for Categories II and III installations as necessary this problem can be dealt with through special monitoring provisions or highly reliable circuitry.

a) change of displacement sensitivity to a value differing by more than 17 per cent from the nominal value for the localizer facility.

Note.: In selecting the power reduction figure to be employed in monitoring referred to in 3.1.3.11.2 e) above, particular attention is directed to vertical and horizontal lobe structure (vertical lobbing due to different antenna heights) of the combined radiation systems when two carriers are employed. Large changes in the power ratio between carriers may results in low clearance areas and false courses in the off-course areas to the limits of the vertical coverage requirements specified in 3.1.3.3.1 above.

3.1.3.11.2.1 In the case of localizers in which the basic functions are provided by the use of a two-frequency system, the conditions requiring initiation of monitor action should include the case when the DDM in the required coverage beyond plus or minus 10 degrees from the front course line, except in the back course sector, decreases below 0.155.

3.1.3.11.3 The total period of radiation, including period(s) of zero radiation, outside the performance limits specified in a), b), c), d) , e) and f) of 3.1.3.11.2 above shall be as short as practicable, consistent with the need for avoiding interruptions of the navigation service provided by the localizer.

3.1.3.11.3.1 The total period referred to under 3.1.3.11.3 shall not exceed under any 28CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

circumstances:

10 seconds for Category I localizers;

5 seconds for Category II localizers;

2 seconds for Category III localizers.

Note 1.: The total time periods specified are never-to-be-exceeded limits and are intended to protect aircraft in the final stages of approach against prolonged or repeated periods of localizer guidance outside the monitor limits. For this reason, they include not only the initial period of outside tolerance operation but also the total of any or all periods of outside tolerance radiation including periods(s) of zero radiation, and time required to remove the navigation and identification component from the carrier, which might occur during action to restore service, for example, in the course of consecutive monitor functioning and consequent change-over(s) to localizer equipment or elements thereof.

Note 2.: From an operational point of view, the intention is that no guidance outside the monitor limits be radiated after the time periods given, and that no further attempts be made to restore service until a period in the order of 20 seconds has elapsed.

3.1.3.11.3.2 Where practicable, the total period under 3.1.3.11.3.1 should be reduced so as not to exceed two seconds for Category II localizers and one second for Category III localizers.

3.1.3.11.4 Design and operation of the monitor system shall be consistent with the requirement that navigation guidance and identification will be removed and a warning provided at the designated remote control points in the event of failure of the monitor system itself.

3.1.3.12 Integrity and continuity of service levels and requirements.

3.1.3.12.1 A localizer shall be assigned a level of integrity and continuity of service as given in 3.1.3.12.2 to 3.1.3.12.5.

Note.: Levels are used to provide the necessary information for the determination of the category of operation and associated minima, which are a function of the Facility Performance Category, the (separate) integrity and continuity of service level, and a number of operational factors (e.g. aircraft and crew qualification, meteorological conditions, and runway features). If a localizer does not meet its required integrity and continuity of service level, some operational use may still be possible, as stated in the Manual of All-Weather Operations (Doc 9365), Appendix C on ILS facility classification and downgrading. Similarly, if a localizer exceeds the minimum integrity and continuity of service level, more demanding operations may be possible.

3.1.3.12.2 The localizer level shall be Level 1 if either:

29CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 a) the localizer’s integrity of service or its continuity of service, or both, are not demonstrated; or b) the localizer’s integrity of service and its continuity of service are both demonstrated, but at least one of them does not meet the requirements of Level 2.

3.1.3.12.2.1 The probability of not radiating false guidance signals should not be less than 1 – 1.0 × 10–7 in any one landing for Level 1 localizers.

3.1.3.12.2.2 The probability of not losing the radiated guidance signal should exceed 1 – 4 × 10 -6 in any period of 15 seconds for Level 1 localizers (equivalent to 1 000 hours mean time between outages)

3.1.3.12.2.3 In the event that the integrity value for a Level 1 localizer is not available or cannot be readily calculated, a detailed analysis should be performed to assure proper monitor fail-safe operation.

3.1.3.12.3 The localizer level shall be Level 2 if: a) the probability of not radiating false guidance signals is not less than 1 – 1.0 x 10–7 in any one landing; and b) the probability of not losing the radiated guidance is greater than 1 – 4 × 10–6 in any period of 15 seconds (equivalent to 1 000 hours mean time between outages).

3.1.3.12.4 The localizer level shall be Level 3 if: a) the probability of not radiating false guidance signals is not less than 1 – 0.5 × 10–9 in any one landing; and b) the probability of not losing the radiated guidance is greater than 1 – 2 × 10–6 in any period of 15 seconds (equivalent to 2 000 hours mean time between outages).

3.1.3.12.5 The localizer level shall be Level 4 if: a) the probability of not radiating false guidance signals is not less than 1 – 0.5 × 10–9 in any one landing; and b) the probability of not losing the radiated guidance is greater than 1 – 2 × 10–6 in any period of 30 seconds (equivalent to 4 000 hours mean time between outages).

3.1.4 Interference immunity performance for ILS localizer receiving system.

3.1.4.1 The ILS localizer receiving system shall provide adequate immunity to interference from two-signal, third-order inter-modulation products caused

by VHF FM broadcast signals having levels in accordance with the following:

30CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 2N1+N2+72 ≤ 0 for VHF FM sound broadcasting signals in the range 107.7-108.0 MHz and 2N +N +3(24-20log Δf/0.4) ≤ 0 1 2 for VHF FM sound broadcasting signals below 107.7 MHz, where the frequencies of the two VHF FM sound broadcasting signals procedure, within the receiver, a two-signal, third-order inter-modulation product on the desired ILS localizer frequency.

N and N are the levels (dBm) of the two VHF FM sound broadcasting 1 2 signals at the ILS localizer receiver input. Neither level shall exceed the desensitization criteria set forth in 3.1.4.2.

F=108.1-f1, where f1 is the frequency of N1, the VHF FM sound broadcasting signal closer to 108.1 MHz

3.1.4.2 The ILS localizer receiving system shall not be desensitized in the presence of VHF FM broadcast signals having levels in accordance with the following

table:

Frequency Maximum level of unwanted (MHz) signal at receiver input

(dBm) 88-102 +15 104 +10 106 + 5

107.9 -10

3.1.4.3 Intentionally left blank.

3.1.5 UHF glide path equipment and associated monitor.

Note.: θ is used in this paragraph to denote the nominal glide path angle.

3.1.5.1 General The radiation from the UHF glide path antenna system shall produce a composite field pattern which is amplitude modulated by a 90 Hz and a 150 Hz tone. The pattern shall be arranged to provide a straight line descent path in the vertical plane containing the centre line of the runway, with 31CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 the150 Hz tone predominating below the path and the 90 Hz tone predominating above the path to at least an angle equal to 1.75 θ.

3.1.5.1.1 The ILS glide path angle should be 3 degrees. ILS glide path angles in excess of 3 degrees should not be used except where alternative means of satisfying obstruction clearance requirements are impracticable.

3.1.5.1.1.1 The glide path angle shall be adjusted and maintained within: a) 0.075 θ from θ for Facility Performance Categories I and II – ILS glide paths; b) 0.04 θ from θ for Facility Performance Category III- ILS glide paths.

3.1.5.1.2 The downward extended straight portion of the ILS glide path shall pass through the ILS reference datum at a height ensuring safe guidance over obstructions and also safe and efficient use of the RWY served.

3.1.5.1.3 The height of the ILS reference datum for facility performance categories II and III – ILS shall be 15 m (50ft). A tolerance of plus 3 m (10ft) is permitted.

3.1.5.1.4 The height of the ILS reference datum for facility performance category I - ILS should be 15 m (50 Feet). A tolerance of plus 3m (10) feet is permitted.

3.1.5.1.5 The height of the ILS reference datum for facility performance category I - ILS used on short precision approach RWY codes 1 and 2 should be 12m

(40ft). A tolerance of plus 6m (20ft) is permitted.

3.1.5.2 Radio Frequency

3.1.5.2.1 The glide path equipment shall operate in the bank 328.6 MHz to 335.4 MHz. Where a single radio frequency carrier is used, the frequency tolerance shall not exceed 0.005 percent. Where two carrier glide path systems are used, the frequency tolerance shall not exceed 0.002 percent and the nominal band occupied by the carriers shall be symmetrical about the assigned frequency. With all tolerances applied, the frequency separation between the carriers shall not be less than 4 KHz more than 32 KHz.

3.1.5.2.2 The emission from the glide path equipment shall be horizontally polarized.

32CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.5.2.3 For facility performance category III—ILS glide path equipment signals emanating from the transmitter shall contain no components which result in apparent glide path fluctuations of more than 0.02 DDM peak to peak in the frequency band 0.01 Hz to 10 Hz.

3.1.5.3 Coverage

3.1.5.3.1 The glide path equipment shall provide signals sufficient to allow satisfactory operation of a typical aircraft installation in sectors of 8 degrees in azimuth on each side of the centre line of the ILS glide path, to a distance of at least 18.5 km (10nm) up to 1.75 θ and down to 0.45 θ above the horizontal or to such lower angle, down to 0.30 θ as required to safeguard the promulgated glide path intercept procedure.

3.1.5.3.2 In order to provide the coverage for glide path performance specified in above, the minimum field strength within this coverage sector shall be 400 µ volts per metre (minus 95 dbW/meter square). For facility performance category I glide paths, this field strength shall be provided down to a height of 30m (100ft) above the horizontal plane containing the threshold. For facility performance categories II and III glide paths, this field strength shall be provided down to a height of 15 m (50ft) above the horizontal plane containing the threshold.

Figure 7 Note.: Because of the siting problems and terrain limitations, some glide paths may not meet the standard coverage area described above. The information regarding such glide paths shall be published in AIP for each 33CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 specific system.

3.1.5.4 ILS Glide Path Structure

3.1.5.4.1 For facility performance category I—ILS glide paths, bends in the glide path

shall not have amplitudes which exceed the following:

Zone Amplitude (DDM) (95% probability) Outer limit of coverage to ILS point “C” 0.035

3.1.5.4.2 For facility performance categories II and III, ILS glide paths, bends in the glide path shall not have amplitudes which exceed the following.

Zone Amplitude (DDM) (95% probability) Outer limit of coverage ILS point “A” 0.035 ILS point “A” to ILS point “B” 0.035 at ILS point “A” decreasing at a linear rate to 0.023 at ILS point “B” ILS point “B” to the ILS reference datum 0.023

3.1.5.5 Carrier modulation

3.1.5.5.1 The nominal depth of modulation of the radio frequency carrier due to each of the 90 Hz and 150 Hz tones shall be 40 percent along the ILS glide path.

The depth of modulation shall not deviate outside the limits of 37.5 percent to 42.5 percent.

3.1.5.5.2 The following tolerances shall be applied to the frequencies of the modulating tones. a) The modulating tones shall be 90 Hz and 150 Hz within 2.5 percent for facility performance category I – ILS.

b) The modulating tones shall be 90 Hz and 150 Hz within 1.5 percent for facility performance category II – ILS. c) The modulating tones shall be 90 Hz and 150 Hz within 1 percent for facility performance category III – ILS.

d) The total harmonic content of the 90 Hz tone shall not exceed 10 percent. Additionally, for facility performance category III equipment, the second harmonic of the 90 Hz tone shall not exceed 5 percent.

34CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 e) The total harmonic content of the 150 Hz tone shall not exceed 10 percent.

3.1.5.5.2.1 For facility performance category I—ILS the modulating tones should be 90 Hz and 150 Hz within plus or minus 1.5 percent where practicable.

3.1.5.5.2.2 For facility performance category III glide path equipment, the depth of amplitude modulation of the radio frequency carrier at the power supply frequency or harmonics, or at other noise frequencies, shall not exceed 1 percent.

3.1.5.5.3 The modulation shall be phase-locked so that within the ILS half glide path sector, the demodulated 90 Hz and 150 Hz wave forms pass through zero in the same direction within. a) For facility performance categories I and II ILS glide paths 20 degrees.

b) For facility performance category III ILS glide path: 10 degrees of phase relative to the 150 Hz components, every half cycle of the combined 90 Hz and 150 Hz wave form. (refer fig C-6 above)

3.1.5.5.3.1 With two frequency glide path systems, 3.1.5.5.3 above shall apply to each carrier. In addition, the 90 Hz modulating tone of one carrier shall be phase- locked to the 90 Hz modulating tone of the other carrier so that the demodulated wave forms pass through zero in the same direction within.

a) For cat I and II ILS glide paths 20 degrees. b) For cat III ILS glide paths 10 degrees. of phase relative to 90 Hz. Similarly, 150 Hz tones of the two carriers shall be phased locked so that the demodulated waveforms pass through zero in the same direction, within;

1) for Category I and II - ILS glide paths: 20 degrees;

2) for Category III ILS Glide paths: 10 degrees off phase relative to 150 Hz.

3.1.5.5.3.2 Alternative two-frequency glide path systems that employ audio phasing different from the normal in phase condition described in 3.1.5.5.3.1 above shall be permitted. In these alternative systems, the 90 Hz to 90 Hz phasing and the 150 Hz to 150 Hz phasing shall be adjusted to their nominal values to within limits equivalent to those stated 3.1.5.5.3.1 above.

3.1.5.6 Displacement sensitivity:

3.1.5.6.1 For facility performance CAT I ILS glide paths, the nominal angular 35CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 displacement sensitivity shall correspond to a DDM of 0.0875 at angular displacements above and below the glide path between 0.07 θ and 0.14 θ.

3.1.5.6.2 For facility performance CAT I ILS glide paths, the nominal angular displacement sensitivity should correspond to a DDM of 0.0875 at angular displacement below the glide path of 0.12 θ with a tolerance of plus or minus

0. 02 θ. The upper and lower sectors should be as symmetrical as practicable within the limits specified in 3.1.5.6.1 above.

3.1.5.6.3 For facility performance CAT II ILS glide paths, the angular displacement sensitivity shall be as symmetrical as practicable. The nominal angular displacement sensitivity shall correspond to a DDM of 0.0875 at an angular

displacement of: a) 0.12 θ below path with a tolerance of plus or minus 0.02 θ. b) 0.012 θ above path with a tolerance of plus 0.02 θ and minus 0.05 θ.

3.1.5.6.4 For facility performance CAT III ILS glide paths, the nominal angular displacement sensitivity shall correspond to a DDM of 0.0875 at angular displacements above and below the glide path 0.12 θ with a tolerance of plus or minus 0.02 θ.

3.1.5.6.5 The DDM below the ILS glide path shall increase smoothly for decreasing angle until a value of 0.22 DDM is reached. This value shall be achieved at an angle not less than 0.30 θ above the horizontal. However, if it is achieved at an angle above 0.45 θ the DDM value shall not be less than 0.22 at least down to 0.45 θ or to such lower angle, down to 0.30 θ as required to safeguard the promulgated glide path intercept procedure.

3.1.5.6.6 For facility performance CAT I ILS glide paths, the angular displacement sensitivity shall be adjusted and maintained within plus or minus 25 percent of the nominal value selected.

3.1.5.6.7 For facility performance CAT II ILS glide paths, the angular displacement sensitivity shall be adjusted and maintained within plus or minus 20 percent of the nominal value selected.

3.1.5.6.8 For facility performance CAT III ILS glide paths, the angular displacement sensitivity shall be adjusted and maintained within plus or minus 15 percent of the nominal value selected.

3.1.5.7 Monitoring

3.1.5.7.1 The automatic monitor system shall provide a warning to the designated control points and cause radiation to cease within the periods specified in

3.1.5.7.3.1 if any of the following conditions persist: a) Shift of the mean ILS glide path angle equivalent to more than minus 0.075 deg to plus 0.10 deg from deg.

36CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 b) In the case of ILS glide paths in which the basic functions are provided by the use of a single-frequency system, a reduction of power output to less than 50 percent of normal provided the glide path continues to meet the requirements of 3.1.5.3, 3.1.5.4 and 3.1.5.5.

c) In the case of ILS glide paths in which the basic functions are provided by the use of two-frequency systems, a reduction of power output for either carrier to less than 80 percent of normal, except that a greater reduction to between 80 percent and 50 percent of normal may be permitted, provided the glide path continues to meet the requirements of 3.1.5.3, 3.1.5.4 and 3.1.5.5.

d) For facility performance CAT I ILS glide paths, a change of the angle between the glide path and the line below the glide path (150 Hz predominating) at which a DDM of 0.0875 is realized by more than the

greater of: i) plus or minus 0.0375 deg or ii) an angle equivalent to a change of displacement sensitivity to a value differing by 25 per cent from the nominal value. e) For facility performance CAT II and III ILS glide paths, a change of displacement sensitivity to a value differing by more than 25 percent from the nominal value.

f) Lowering of the line beneath the ILS glide path at which a DDM of

0.0875 is realized to less than 0.7475 deg from horizontal. g) A reduction of DDM to less than 0.175 within the specified coverage below the glide path sector.

37CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Figure 8] Note 1.: The value of 0.7475 θ from horizontal is intended to ensure adequate obstacle clearance. This value was derived from other parameters of the glide path and monitor specification. Since the measuring accuracy to four significant figures is not intended, the value of 0.75 θ may be used as a monitor limit for this purpose.

Note 2.: Sub paragraphs f) and g) are not intended to establish a requirement for a separate monitor to protect against deviation of the lower limits of the half- sector below 0.7475 θ from horizontal.

Note 3.: At glide path facilities where the selected nominal angular displacement sensitivity corresponds to an angle below the ILS glide path which is close to or at the maximum limits specified in 3.1.5.6 it may be necessary to adjust the monitor operating limits to protect against sec to protect against sector deviations below 0.7475 θ from horizontal.

3.1.5.7.2 Monitoring of the ILS glide path characteristics to smaller tolerances should be arranged in those cases where operational penalties would otherwise exist.

38CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.5.7.3 The total period of radiation, including periods of zero radiation, outside the performance limits specified in 3.1.5.7.1 shall be as short as practicable, consistent with the need for avoiding interruptions of the navigation service

provided by the ILS glide path.

3.1.5.7.3.1 The total period referred to under 3.1.5.7.3 shall not exceed under any

circumstances:

6 seconds for CAT I ILS glide paths 2 seconds for CAT II and III ILS glide paths.

Note 1.: The total time periods specified are never-to-be exceeded limits and are intended to protect aircraft in the final stages of approach against prolonged or repeated periods of ILS glide path guidance outside the monitor limits.

For this reason, they include not only the initial period of outside tolerance operation but also the total of any or all periods of outside tolerance radiation, including periods of zero radiation, which might occur during action to restore service, for example, in the course of consecutive monitor functioning and consequent changeover to glide path equipment or elements thereof.

Note 2.: From an operational point of view, the intention is that no guidance outside the monitor limits be radiated after the time periods given, and that no further attempts be made to restore service until a period in the order of 20 seconds has elapsed.

3.1.5.7.3.2 Where practicable, the total period specified under 3.1.5.7.3.1 above for categories II and III ILS glide paths should not exceed 1 second.

3.1.5.7.4 Design and operation of the monitor system shall be consistent with the Requirement that radiation shall cease and warning shall be provided at the designated remote control points in the event of failure of the monitor system itself.

3.1.5.8 Integrity and continuity of service levels and requirements

3.1.5.8.1 A glide path shall be assigned a level of integrity and continuity of service as given in 3.1.5.8.2 to 3.1.5.8.4.

Note.: Levels are used to provide the necessary information for the determination of the category of operation and associated minima, which are a function of the Facility Performance Category, the (separate) integrity and continuity of service level, and a number of operational factors (e.g. aircraft and crew qualification, meteorological conditions, and runway features). If a glide path does not meet its required integrity and continuity of service level, some operational use may still be possible, as stated in the Manual of All- Weather Operations (Doc 9365), Appendix C on ILS facility classification and downgrading. Similarly, if a glide path exceeds the minimum integrity 39CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 and continuity of service level, more demanding operations may be possible.

3.1.5.8.2 The glide path level shall be Level 1 if either: a) the glide path’s integrity of service or its continuity of service, or both, are demonstrated; or b) the glide path’s integrity of service and its continuity of service are both demonstrated, but at least one of them does not meet the requirements of Level 2.

3.1.5.8.2.1 The probability of not radiating false guidance signals should not be less than 1 – 1.0 × 10–7 in any one landing for Level 1 glide paths.

3.1.5.8.2.2 The probability of not losing the radiated guidance signal should exceed 1 – 4 × 10–6 in any period of 15 seconds for Level 1 glide paths (equivalent to 1 000 hours mean time between outages).

3.1.5.8.2.3 In the event that the integrity value for a Level 1 glide path is not available or cannot be readily calculated, a detailed analysis should be performed to assure proper monitor fail-safe operation.

3.1.5.8.3 The glide path level shall be Level 2 if: a) the probability of not radiating false guidance signals is not less than 1 – 1.0 x 10–7 in any one landing; and b) the probability of not losing the radiated guidance is greater 1 – 4 × 10–6 in any period of 15 seconds (equivalent to 1000 hours mean time between outages).

3.1.5.8.4 The glide path level shall be Level 3 or 4 if: a) the probability of not radiating false guidance signals is not less than 1 – 0.5 × 10–9 in any one landing; and b) the probability of not losing the radiated guidance is greater than 1 – 2 × 10–6 in any period of 15 seconds (equivalent to 2 000 hours mean time between outages).

Note 1.: The requirements for glide path Level 3 and Level 4 are the same. The declaration of the glide path integrity and continuity of service levels should match the declaration of the localizer (i.e. the glide path is declared as Level 4 if the localizer is meeting Level 4).

40CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.6 Localizer and glide path frequency pairing

3.1.6.1 The pairing of the runway localizer and glide path transmitter frequencies of instrument landing system shall be taken from the following list in accordance with the provisions of Volume V, Chapter 4.4.2:

3.1.7 VHF Marker beacons

3.1.7.1 General a) There shall be two market beacons in each installation except as

provided in 3.1.7.6.5. A third marker beacon may be added whenever, in the opinion of the Competent Authority, an additional beacon is required because of operational procedures at particular site. b) The marker beacons shall conform to the requirements prescribed in

3.1.7. When the installation comprises only two market beacons, the requirements applicable to the middle marker and to the outer marker shall be complied with. c) The marker beacons shall produce radiation patterns to indicate predetermined distance from the threshold along the ILS glide path.

3.1.7.1.1 When a marker beacon is used in conjunction with the back course of localizer, it shall conform to the marker beacon characteristics specified

3.1.7.

3.1.7.1.2 Identification signals of marker beacons used in conjunction with the back 41CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 course of localizer shall be clearly distinguishable from the inner, middle and outer marker beacon identifications, as prescribed in 3.1.7.5.1.

3.1.7.2 Radio frequency

3.1.7.2.1 The marker beacons shall operate at 75 MHz with a frequency tolerance of plus or minus 0.005 per cent and shall utilize horizontal polarization.

3.1.7.3 Coverage

3.1.7.3.1 The marker beacon system shall be adjusted to provide coverage over the following distances, measured on the ILS glide path and localizer course

line: a) Inner marker: (where installed): 150 m plus of minus 50 m (500 ft plus or minus 160ft) b) Middle marker: 300 m plus or minus 100m ( 1000ft plus of minus 325 ft) c) Outer marker: 600m plus or minus 200m (2000ft plus or minus 650ft).

3.1.7.3.2 The field strength at the limits of coverage specified in 3.1.7.3.1 shall be 1.5 millivolts per metre (minus 82 dB W/m2). In addition, the field strength within the coverage area shall rise to at least 3.0 millivolts per metre (76 dB W/m2).

Note 1: Satisfactory operation of typical airborne marker installation will be obtained if the sensitivity is so adjusted that visual indication will be obtained when 2 the field strength is 1.5 millivolts per metre (minus 82 dB W/m ).

3.1.7.4 Modulation

3.1.7.4.1 The modulation frequencies shall be as follows: a) Inner marker: (when installed): 3000Hz b) Middle marker: 1300 Hz: c) Outer marker: 400 Hz The frequency tolerance of the above frequencies shall be plus of minus 2.5 per cent and the total harmonic content of each of the frequencies shall not exceed 15 per cent.

3.1.7.4.2 The depth of modulation of the markers shall be 95 per cent plus or minus 4 per cent.

42CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.7.5 Identification

3.1.7.5.1 The carrier energy shall not be interrupted. The audio frequency modulation

shall be keyed as follows: a) Inner marker: (when installed): 6 dots per second continuously; b) Middle marker: a continuous series of alternate dots and dashes, the dashes keyed at the rate of 2 dashes per second, and the dots at the rate of 6 dots per second;

c) Outer marker: 2 dashes per second continuously.

These keying rates shall be maintained to within plus or minus 15 per cent.

3.1.7.6 Siting

3.1.7.6.1 The inner marker, when installed, shall be located so as to indicate in low visibility conditions the imminence of arrival at the runway threshold.

3.1.7.6.1.1 If the radiation pattern is vertical, the inner marker, when installed, should be located between 75 m (250ft) and 450 m (1500 ft) from the threshold and at not more than 30 m (100ft) from the extended centre line of the runway.

3.1.7.6.1.2 If the radiation pattern is other than vertical, the equipment should be located so as to produce a field within the course sector and ILS glide path sector that is substantially similar to that produced by an antenna radiating a vertical pattern and located as prescribed in 3.1.7.6.1.1

3.1.7.6.2 The middle marker shall be located so as to indicate the imminence, in low visibility conditions, of visual approach guidance.

3.1.7.6.2.1 If the radiation pattern is vertical, the middle marker should be located 1050m (3500ft) plus or minus 150 m (500ft), from the landing threshold at the approach end of the runway and at not more than 75 m (250 ft) from the extended centre line of the runway.

3.1.7.6.2.2 If the radiation pattern is other than vertical, the equipment should be located so as to produce a field with the course sector and ILS glide path sector that is substantially similar to that produced by an antenna radiating a vertical pattern and located as prescribed in 3.1.7.6.2.1

3.1.7.6.3 The outer marker shall be located so as to provide height, distance and equipment functioning checks to aircraft on intermediate and final approach.

3.1.7.6.3.1 The outer marker should be located 7.2 km (3.9NM) from the threshold except that, where for topographical or operational reasons this distance is 43CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 not practicable, the outer marker may be located between 6.5 and 11.1 km (3.5 and 6 NM) from the threshold.

3.1.7.6.4 If the radiation pattern is vertical, the outer marker should be not more than 75 m (250 ft) from the extended centre line of the runway. If the radiation pattern is other than vertical, the equipment should be located so as to produce a field within the course sector and ILS glide path sector that is substantially similar to that produced by an antenna radiating a vertical pattern.

3.1.7.6.5 The positions of marker beacons, or where applicable, the equivalent distance(s) indicated by the DME when used as an alternative to part or all of the market beacon component of the ILS, shall be published in accordance with the provisions of CAR Section 4 Series ‘X’ Part II.

3.1.7.6.5.1 When so used, the DME shall provide distance information operationally equivalent to that furnished by Marker Beacons.

3.1.7.6.5.2 When used as an alternative for the Middle Marker, the DME shall be frequency paired with ILS Localizer and sited so as to minimize the error in distance information.

3.1.7.6.5.3 The DME in 3.1.7.6.6 above shall conform to the specification in 3.5 below.

3.1.7.7 Monitoring

3.1.7.7.1 Suitable equipment shall provide signals for the operation of an automatic monitor. The monitor shall transmit a warning to a control point if either of

the following conditions arise: a) Failure of the modulation or keying; b) reduction of power output to less than 50 per cent of normal

3.1.7.7.2 For each marker beacon, suitable monitoring equipment should be

provided which will indicate at the appropriate location a decrease of the modulation depth below 50 per cent.

3.2 Specification For Precision Approach Radar System

3.2.1 Intentionally left blank 44CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.2.2 Intentionally left blank

3.2.3 Intentionally left blank

3.2.4 The Surveillance Radar element (SRE)

3.2.4.1 A Surveillance Radar used as SRE of a Precision Approach Radar System shall satisfy at least the following broad performance requirements.

3.2.4.2 Coverage

3.2.4.2.1 The SRE shall be capable of detecting aircraft of 50 m square echoing area and larger, which are in light of sight of the antenna within a volume

described as follows:

The rotation through 360 degrees about the antenna of vertical plane surface bounded by a line at an angle of 1.5 degrees above the horizontal plane of the antenna, extending from the antenna to 37 Km (20 NM); by a vertical line at 37 Km (20 NM) from the intersection with the 1.5 line up to 2004 m (8000 ft) above the level of antenna; by a horizontal line at 2004 m (8000 ft) from 37 Km (20 NM) back towards the antenna to the intersection with a line from the antenna at 20 º above the horizontal plane of the antenna, and by a 20 º line from the intersection with the 2004 m (8000 ft) line to the antenna.

3.2.4.2.2 Efforts should be made in development to increase the coverage on an aircraft of 50 m square echoing area to at least the volume obtained by amending 3.2.4.2.1 above with the following substitution.

-- for 1.5 º, read 0.5 º -- for 37 Km (20 NM), read 46.3 Km (20 NM) -- for 2400 m (8000 ft), read 3000 m (10000 ft) -- for 20 º, read 30 º

3.2.4.3 Accuracy

3.2.4.3.1 Azimuth Accuracy: The indication of position in azimuth shall be within plus or minus 2 degrees of the true position. It shall be possible to resolve the position of two aircraft which are at 4 º of azimuth of one another.

3.2.4.3.2 Distance Accuracy: The error in distance indication shall not exceed 5 percent of true distance or 150 m, whichever is the greater. It shall be possible to resolve the position of two aircraft that are separated by a distance of 1 percent of the true distance from the point of observation or 230 m whichever is greater.

45CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.2.4.3.2.1 The error in distance indication should not exceed 3 percent of the true distance of 150 m, whichever is the greater.

3.2.4.4 The equipment shall be capable of completely renewing the information concerning the distance and azimuth of any aircraft within the coverage of the equipment at least once every 4 seconds.

3.2.4.5 Efforts should be made to reduce, as far as possible, the disturbance caused by ground echoes.

3.3 Specification for VHF Omni Directional Radio Range (VOR)

3.3.1 General

3.3.1.1 The VOR shall be constructed and adjusted so that similar instrumental indications in aircraft represent equal clockwise angular deviations

(bearing), degree for degree from magnetic North as measured from the location of the VOR.

3.3.1.2 The VOR shall radiate a radio frequency carrier with which are associated two separate 30 Hz modulations, one of these modulations shall be such that its phase is independent of the azimuth of the point of observation (reference phase). The other modulation (Variable phase) shall be such that its phase at the point of observation differs from that of the reference phase by an angle equal to the bearing of the point of observation with respect to the VOR.

3.3.1.3 The reference and variable phase modulations shall be in phase along the reference magnetic meridian through the station.

Note.: The reference and variable phase modulations are in phase when the maximum value of the sum of the radio frequency carrier and the sideband energy due to the variable phase modulation occurs at the same time as the highest instantaneous frequency of the reference phase modulation

3.3.2 Radio Frequency

3.3.2.1 The VOR shall operate in the band 111.975 MHZ to 117.975 MHZ. The channel separation shall be in increments of 50 KHZ. The frequency tolerance of the radio frequency carrier where 50 KHz channel spacing is in 117.950 MHz. The channel separation shall be in increments of 50 KHz referred to the highest assignable frequency. In areas where 100 KHz channel spacing is in general use, the frequency tolerance of the radio frequency is in general use, the frequency tolerance of the radio frequency carrier shall be plus or minus 0.005 percent.

3.3.2.2 The frequency tolerance of the radio frequency carrier of all installations in India where 50 KHz channel spacing is in use shall be plus or minus 0.002 percent.

46CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.3.2.3 In areas where new VOR installations are implemented and are assigned frequencies spaced at 50 KHz from existing VORs in the same area, priority shall be given to ensuring that the frequency tolerance of the radio frequency carrier of the existing VORs is reduced to plus or minus 0.002 percent.

3.3.3 Polarization and pattern accuracy:

3.3.3.1 The emission from the VOR shall be horizontally polarized. The vertically polarized component of the radiation shall be as small as possible.

3.3.3.2 The ground station contribution to the error in the bearing information conveyed by the horizontally polarized radiation from the VOR for all elevations angles between 0 to 40 degrees, measured from the center of the VOR antenna system, shall be within plus or minus 2 degrees.

3.3.4 Coverage

3.3.4.1 The VOR shall provide signals such as to permit satisfactory operation of a typical aircraft installation at the levels and distances required for operational reasons, and up to an elevation angle of 40 degrees.

3.3.4.2 The field strength or power density in space of VOR signals required to permit satisfactorily operation of a typical aircraft installation at the minimum service level at the maximum specified service radius should be 90 micro volt per meter or minus 107 db W/m square.

3.3.5 Modulation of navigational signals:

3.3.5.1 The radio frequency carrier as observed at any point in space shall be

amplitude modulated by two signals as described below: a) a sub carrier of 9960 Hz of constant amplitude, frequency modulated at 30 Hz r)

1) For the conventional VOR, the 30 Hz component of this FM sub carrier is fixed without respect to azimuth and is termed the “reference phase” and shall have a deviation ratio of 16 plus or minus 1 (i.e. 15 to 17);

2) For the Doppler VOR, the phase of the 30 Hz component varies with azimuth and is termed the “variable phase” and shall have a deviation ratio of 16 plus or minus 1 (i.e. 15 to 17) when observed at any angle of elevation up to 15 degrees, with a minimum deviation ratio of 11 when observed at any angle of elevation above 15 degrees and up to 40 degrees.

b) A 30 Hz amplitude modulation component:

47CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

1) For the conventional VOR, this component results from a rotating field pattern, the phase of which varies with azimuth, and is termed the “variable phase”.

2) For the Doppler VOR, this component, of constant phase with relation to azimuth and constant amplitude, is radiated omni directionally and is termed the “reference phase”.

3.3.5.2 The nominal depth of modulation of the radio frequency carrier due to the 30 Hz signal or sub carrier of 9960 Hz shall be within the limits of 28 percent and 32 percent.

3.3.5.3 The depth of modulation of the radio frequency carrier due to the 30 Hz, as observed at any angle of elevation up to 5 degrees, shall be within 25 to 35 percent. The depth of modulation of the radio frequency carrier due to the 9960 Hz signal, as observed at any angle of elevation up to 5 degrees, shall be within the limits of 20 to 55 per cent on facilities without voice modulation and within the limits of 20 to 35 per cent on facilities with voice modulation.

Note.: When modulation is measured during flight testing under strong dynamic multipath conditions, variations in the received modulation percentages are to be expected. Short-term variations beyond these values may be acceptable. Doc 8071 contains additional information on application of airborne modulation tolerances.

3.3.5.4 The variable and reference phase modulation frequencies shall be 30 Hz within plus or minus 1 percent.

3.3.5.5 The sub carrier modulation mid-frequency shall be 9960 Hz within plus or minus 1 percent.

3.3.5.6 a) For the conventional VOR, the percentage of amplitude modulation of the 9960 Hz sub carrier shall not exceed 5 percent. b) For the Doppler VOR, the percentage of amplitude modulation of the 9960 Hz subcarrier shall not exceed 40 percent when measured at a point at least 300 m (1000ft) from the VOR.

3.3.5.7 Where 50 KHz VOR channel spacing is implemented, the sideband level of the harmonics of the 9960 Hz component in the radiated signal shall not exceed the following levels referred to the level of the 9960 Hz sideband:

Subcarrier Level 9960Hz 0 dB reference 2nd Harmonics - 30 dB 3rd Harmonics -50 dB 4th Harmonics & above -60 dB 48CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.3.6 Voice and Identification

3.3.6.1 If the VOR provides a simultaneous communication channel ground to air, it shall be on the same radio frequency carrier as used for the navigational function. The radiation on this channel shall be horizontally polarized.

3.3.6.2 The peak modulation depth of the carrier on the communication channel shall not be greater than 30 percent.

3.3.6.3 The audio frequency characteristics of the speech channel shall be within 3dB relative to the level 1000Hz over the range 300Hz to 3000Hz.

3.3.6.4 The VOR shall provides for the simultaneous transmission of a signal of identification on the same radio frequency carrier as that used for the navigational function .The identification signal radiation shall be horizontally polarized.

3.3.6.5 The identification signal shall employ the International Morse code and consist of two or three letters. It shall be sent at a speed corresponding to approximately 7 words per minutes. The signal shall be repeated at least once every 30 seconds and the Modulation tone shall be 1020Hz within plus or minus 50Hz.

3.3.6.5.1 The identification signal should be transmitted at least three times each 30 seconds, spaced equally within that time period. One of these identification signals may take the form of voice identification.

3.3.6.6 The depth to which the radio frequency carrier is modulated by the code identification signal shall be close to, but not in excess of 10 percent except that where a communication channel is not provided, it shall be permissible to increase the modulation by the code identification signal to a value not exceeding to 20 percent.

3.3.6.6.1 If the VOR provide the simultaneous communication channel ground to air, the modulation depth of the code identification signal should be 5 plus or minus 1 percent in order to provide a satisfactory voice quality.

3.3.6.7 The transmission of speech shall not interfere in any way with the basic navigational function. When speech is being radiated the code identification shall not be suppressed.

3.3.6.8 The VOR receiving function shall permit positive identification of the wanted signal under signal conditions encountered within the specified coverage limits, and with the modulation parameters specified at 2.6.5, 2.6.7 and

2.6.9 above

3.3.7 Monitoring

3.3.7.1 Suitable equipment located in the radiation field shall provide signals for the operation of an automatic monitor. The monitor shall transmit to a control 49CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 point and either remove the identification and navigational components from the carrier or cause radiation to cease if any one or a combination of

the following deviations from established arises: a) A change in excess of 1 degree at the monitor of the bearing information transmitted by the VOR. b) A reduction of 15 percent in the modulation components of the radio frequency signals voltage level at the monitor of either the sub carrier, or 30 Hz amplitude modulation signals or both.

Note.: Where it is not possible to provide status indication to a control point, the same shall be published in AIP.

3.3.7.2 Failure of Monitor itself shall transmit a warning to a control point and either: a) By removing the identification and navigations components from the carrier; or b) Cause radiation to cease.

3.3.8 Interference Immunity Performance for VOR receiving systems

3.3.8.1 The VOR receiving system shall provide adequate immunity to interference from two signals, third order inter-modulation products caused by VHF FM

broadcast signals having levels in accordance with the following:

2N +N + 72 ≤ 0 1 2 for VHF FM sound broadcasting signals in the range 107.7 – 108.0 MHz and 2N + N + 3 (24 – 20 log Δ f / 0.4) ≤ 0 1 2 for VHF FM sound broadcasting signals below 107.7 MHz, where the frequencies of the two VHF FM sound broadcasting signals produced, within the receiver, at two signal, third order inter-modulation product on the desired VOR frequency.

N and N are the levels (dBm) of the two VHF FM sound broadcasting 1 2 signals at the VOR receiver input. Neither level shall exceed the desensitization criteria set forth in 3.3.8.2 below. Δ f = 108.1 – f , where f is the frequency of N , the VHF FM sound 1 1 1 broadcasting signal closure to 108.1 MHz

3.3.8.2 The VOR receiving system shall not desensitized in the presence of VHF FM broadcast signals having levels in accordance with the following table.

50CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Frequency (MHz) Maximum level of unwanted signal at receiver input 88 – 102 + 15 dBm 104 + 10 dBm 106 + 5 dBm

107.9 - 10 dBm Note.: The relationship is linear between adjacent points designated by the above frequencies.

3.4 Specification for non-directional Radio beacon (NDB)

3.4.1 Definitions:

Average Radius of rated coverage: The radius of a circle having the same areas as the rated coverage.

Effective Coverage: The area surrounding an NDB within which bearings can be obtained with accuracy sufficient for the nature of the operation concerned.

Locator: An LF/MF NDB used an aid to final approach.

Note.: A locator usually has an average radius of rated coverage of between 18.5 and 46.3 km (10 and 25 NM).

Rated coverage: The area surrounding an NDB within which the strength of the vertical field of the ground wave exceeds the minimum value specified for the geographical area in which the radio beacon is situated.

Note.: The above definition is intended to establish a method of rating radio beacons on the normal coverage to be expected in the absence of sky wave transmission and/or anomalous propagation from the radio beacon concerned or interference from other LF/MF facilities, but taking into account the atmospheric noise in the geographical area concerned,

3.4.2 Coverage:

3.4.2.1 The minimum value of field strength in the rated coverage of an NDB should be 70 micro volts per meter.

Note.: The selection of locations and times at which the field strength is measured is important in order to avoid abnormal results for the locality concerned; locations on air routes in the area around the beacon are operationally most significant.

3.4.2.2 All notifications or promulgations of NDBs shall be based upon the average radius of the rated coverage.

51CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note 1.: In classifying radio beacons in areas where substantial variations in rated coverage may occur diurnally and seasonally, such variations should be taken into account.

Note 2.: Beacons having an average radius of rated coverage of between 46.3 and 278 km (25 and 150NM) may be designated by the nearest multiple of 46.3 km (25NM) to the average radius of rated coverage, and beacons of rated coverage over 278 km (150NM) to the nearest multiple of 92.7 km (50NM).

3.4.2.3 Where the rated coverage of an NDB is materially different in various operationally significant factors, its classifications should be expressed in terms of the average radius of rated coverage and the angular limits of each sector as follows.

Radius of coverage of sector/angular limits of sector expressed as magnetic bearing clockwise from the beacon.

Where it is desirable to classify an NDB in such a manner, the number of sectors should be kept to a minimum and preferably should not exceed two.

3.4.3 Limitations in radiated power The power radiated from an NDB shall not exceed by more than 2dB that necessary to achieve its agreed rated coverage, except that this power may be increased if coordinated regionally or if no harmful interference to other facilities will result.

3.4.4 Radio Frequencies

3.4.4.1.1 The radio frequencies assigned to NDBs shall be selected from those available in that portion of the spectrum between 190 kHz and 1750 kHz.

3.4.4.2 The frequency tolerance applicable to NDBs shall be 0.01 per cent except that, for NDBs of antenna power above 200 W using frequencies of 1 606.5 kHz and above, the tolerance shall be 0.005 per cent.

3.4.4.3 Where two locators are used as supplements to an ILS, the frequency separation between the carriers of the two should be not less than 15KHZ to ensure correct operation of the radio compass and preferably not more than 25KHZ in order to permit a quick tuning shift in cases where an Aircraft has only one radio compass.

3.4.4.4 Where locators associated with ILS facilities serving opposite ends of a single runway are assigned a common frequency, provision shall be made to ensure that the facility not in operational use cannot radiate.

3.4.5 Identification

3.4.5.1 Each NDB shall be individually identified by a two-or three-letter 52CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 International Morse Code group transmitted at a rate corresponding to approximately 7 words per minute.

3.4.5.2 The complete identification shall be transmitted at least once every 30 seconds, except where the beacon identification is effected by the on/off keying of the carrier. In this latter case, the identification shall be at approximately I-minute intervals, except that a shorter interval may be used at particular NDB stations where this is found to be operationally desirable.

3.4.5.3 Except for those cases where the beacon identification is effected by on/off keying of the carrier, the identification signal should be transmitted at least three times each 30 seconds, spaced equally within that time period.

3.4.5.4 For NDBs with an average radius of rate coverage of 92.7 km (50 NM) or less that are primarily approach and holding aids in the vicinity of an aerodrome, the identification shall be transmitted at least three times each 30 seconds, spaced equally within that time period.

3.4.5.5 The frequency of the modulating tone used from identification shall be 1020 Hz plus or minus 50 Hz or 400 Hz plus or minus 25 Hz.

3.4.6 Characteristics of emissions:

Note.: The following specifications are not intended to preclude employment of modulations or types of modulations that may be utilized in NDBs in addition to those specified for identification, including simultaneous identification and voice modulation, provided that these additional modulations do not materially affect the operational performance of the NDBs in conjunctions with currently used airborne direction finders, and provided their use does not cause harmful interference to other NDB services.

3.4.6.1 Except as provided in 3.4.6.1.1, all NDBs shall radiate an uninterrupted carrier and be identified by on/off keying of amplitude modulating tone (NON/A2A).

3.4.6.1.1 NDBs other than those wholly or partly serving as holding approach and landing aids or those having an average radius of rated coverage of less than 92.7 km (50NM), may be identified by on/off keying of the un modulated carrier (NON/AIA) if they are in areas of high beacon density and/or where

the required rated coverage is not practicable of achievement because of : a) Radio interference from radio stations; b) High atmospheric noise; c) Local conditions.

Note.: In selecting the types of emission, the possibility of confusion, arising from an aircraft tuning from a NON/A2A facility to a NON/AIA facility without 53CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 changing the radio compass from “MCW” to “CW” operation, will need to be kept in mind.

3.4.6.2 For each NDB identified by on/off keying of an audio modulating tone, the depth of modulation shall be maintained as near to 95 per cent as practicable.

3.4.6.3 For each NDB identified by on/off keying of an audio modulating tone, the characteristics of emission during identification shall be such as to ensure satisfactory identification at the limit of its rated coverage.

Note.: The foregoing requirement necessitates as high a percentage modulation as practicable, together with maintenance of an adequate radiated carrier power during identification.

3.4.6.4 The carrier power of an NDB with NON/A2A emissions should not fall when the identify signal is being radiated except that, in the case of an NDB having an average radius of rated coverage exceeding 92.7 km (50 NM), a fall of not more than 1.5 dB may be accepted.

3.4.6.5 Unwanted audio frequency modulations shall total less than 5 per cent of the amplitude of the carrier.

Note.: Reliable performance of airborne automatic direction finding equipment

(ADF) may be seriously prejudiced if the beacon emission contains modulation by an audio frequency equal or close to the loop switching frequency or its second harmonic. The loop switching frequencies in currently used equipment lie between 30 Hz and 120 Hz.

3.4.6.6 The bandwidth of emissions and the level of spurious emissions shall be kept at the lowest value that the state of technique and the nature of the service permit.

3.4.7 Siting of Locators

3.4.7.1 Where locators are used as a supplement to the ILS, they should be located at the sites of the outer and middle marker beacons. Where only one locator is used as a supplement to the ILS, preference should be given to location at the site of the outer marker beacon. Where locators are employed as an aid to final approach in the absence of an ILS, equivalent location to those applying when an ILS is installed should be selected, taking into account the relevant obstacle clearance provisions of the ICAO Doc 8168 – Procedures for Air Navigation Services (Aircraft Operations)

3.4.7.2 Where locators are installed at both the middle and outer marker positions, they should be located, where practicable, on the same side of the extended centre line of the runway in order to provide a track between the locators which will be more nearly parallel to the centre line of the runway.

54CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.4.8 Monitoring:

3.4.8.1 For each NDB, suitable means shall be provided to enable detection of any

of the following conditions at an appropriate location: a) a decrease in radiated carrier power of more than 50 per cent below that required for the rated coverage. b) Failure to transmit the identification signal;

c) Malfunctioning or failure of the means of monitoring itself.

3.4.8.2 When an NDB is operated from a power source having a frequency which is close to airborne ADF equipment switching frequencies, and where the design of the NDB is such that the power supply frequency is likely to appear as a modulation product on the emission, the means of monitoring should be capable of detecting such power supply modulation on the carrier in excess of 5 per cent.

3.4.8.3 During the hours of service of a locator, the means of monitoring shall provide for a locator, the means of monitoring shall provide for a continuous check on the functioning of the locator as prescribed in 3, 4.8.1 (a) (b) and

(c) above.

3.4.8.4 During the hours of service of an NDB other than a locator, the means of monitoring should provide for a continuous check on the functioning of the NDB as prescribed in 3.4.8.1 (a), (b), and (c).

3.5 Specification for UHF distance measuring equipment (DME) Note 1.: In the following section, provision is made for two type of DME facility:

DME/N for general application and DME/P as outlined in 3.11.3 below.

3.4.9 Definition Control motion noise (CMN): That portion of the guidance signal error which causes control surface, wheel and column motion and could affect aircraft attitude angle during coupled flight, but does not cause aircraft displacement from the desired course and/or glide path (See 3.11 below)

DME dead time: A period immediately following the decoding of a valid interrogation during which a received interrogation will not cause a reply to be generated. (dead time is intended to prevent the transponder from replying to echoes resulting from multipath effects.) DME/N: Distance measuring equipment, primarily serving operational needs of enroute of TMA navigation, where the “N” stands for narrow spectrum characteristics.

DME/P. The distance measuring element of the MLS, where the “P” stands for precise distance measurement. The spectrum characteristics are those 55CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 of DME/N.

Equivalent Isotropically Radiated Power (E.I.R.P.): The product of the power supplied to the antenna and the antenna gain in a given direction relative to an isotropic antenna (absolute or isotropic gain).

Key down time: The time during which a dot or dash or a Morse character is being transmitted.

Mode W, X, Y, Z, A Method of coding DME transmission by time spacing pulses of a pulse pair, so that each frequency can be used more than once.

Partial rise time: The time as measured between the 5 and 30 per cent amplitude points on the leading edge of the pulse envelope, i.e. between points hand I on Figure 3-1 and 3-2.

Path following error (PFE): That portion of the guidance signal error which could cause aircraft displacement from the desired course and/or glide path.(See 3.11 below).

Pulse amplitude: The maximum voltage of the pulse envelope, i.e. A in Figure 3-1.

Pulse decay time: The time as measured between the 90 and 10 per cent amplitude points on the trailing edge of the pulse envelope, i.e. between point e and g on Figure 3-1.

Pulse code: The method differentiating between W, X, Y and Z modes and between FA and IA modes.

Pulse duration: The time interval between the 50 per cent amplitude point on leading and trailing edges of the pulse envelope, i.e. between points b and f on Figure 3-1.

Pulse rise time: The time as measured between the 10 and 90 per cent amplitude points on the leading edge of the pulse envelope, i.e. between points a and c on Figure 3-1.

Reply efficiency: The ratio of replies transmitted by the transponder to the total of received valid interrogations.

Search: The condition which exists when the DME interrogator is attempting to acquire and lock on to the response to its own interrogations from the selected transponder.

System efficiency: The ratio of valid replies processed by the interrogator to the total of its own interrogations.

Track: The condition which exists when the DME interrogator has locked onto replies in response to its own interrogations, and is continuously providing a distance measurement.

56CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

Transmission rate: The average number of pulse pairs transmitted from the transponder per second.

Virtual Origin: The point at which the straight line through the 30 per cent and 5 per cent amplitude points on the pulse leading edge intersects the 0 per cent amplitude axis (see Figure 3-2) Figure 3 - 1 Figure 3 – 2 57CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.2 General

3.5.2.1 The DME system shall provide for continuous and accurate indication in the cockpit of the slant range distance of an equipped aircraft from an equipped ground reference point.

3.5.2.2 The system shall comprise two basic components, one fitted in the aircraft, the other installed on the ground. The aircraft component shall be referred to as the interrogator and the ground component as the transponder.

3.5.2.3 In operation, interrogators shall interrogate transponders which shall, in turn transmit to the interrogator replies synchronized with the interrogations, thus providing means for accurate measurement of distance.

3.5.2.4 Intentionally left blank

3.5.2.5 When a DME associated with either an ILS or VOR for the purpose of constituting a single facility, they shall be considered to be associated in a manner complying with para 2.2.2 only when : a) they shall be operated on a standard frequency pairing in accordance with 3.5.3.3.5 below;

b) they shall be Collocated within the limits prescribed for associated facilities in 3.5.2.6 below; c) they shall comply with the identification provisions of 3.5.3.6.4 below.

3.5.2.6 Collocation limits for a DME facility associated with an ILS. MLS or VOR facility

3.5.2.6.1 Associated VOR and DME facilities shall be collocated in accordance with

following: a) for those facilities used in terminal areas for approach purpose or other procedures where the highest position fixing accuracy of system capability is required, the separation of the VOR and DME antennas does not exceed 80m (260ft) b) for purposes other than those indicated in a) the separation of the VOR and DME antennas does not exceed 600m (2000ft).

3.5.2.6.2 Association of DME with ILS

3.5.2.6.2.1 When DME is used as an alternative to ILS marker beacons, the DME should be located on the airport so that the zero range indication will be a point near the Runway.

3.5.2.6.2.2 In order to reduce the triangulation error, the DME should be sited to ensure a small angle (less than 20 degrees) between the approach path and the 58CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 direction to the DME at points where the distant information is required.

3.5.2.6.2.3 The use of DME as an alternative to the Middle Marker beacon assumes a DME system accuracy of 0.37 km (0.2NM) or better and resolution of the air bore indication such as to allow this accuracy to be attained.

3.5.2.6.2.4 When DME is used as an alternative for the outer marker, frequency pairing is preferred to simplify pilot operation and to enable aircraft with two ILS receivers to use both receivers on the ILS channels.

3.5.2.6.2.5 When the DME is frequency paired with the localizer, the DME transponder identification should be obtained by the “associated” signal from the frequency paired localizer

3.5.2.7 The Standards in 3.5.3, 3.5.4 and 3.5.5 denoted by ‡ shall apply only to DME equipment first installed after 1 January 1989.

3.5.3 System characteristics

3.5.3.1 Performance

3.5.3.1.1 Range: The system shall provide a means of measurement of slant range distance from an aircraft to a selected transponder to the limit of coverage prescribed by the operational requirements for the selected transponder.

3.5.3.1.2 Coverage:

3.5.3.1.2.1 The DME/N shall provide signals such as to permit satisfactory operation of a typical aircraft installation at the levels and distances required for operational reasons, and up to an elevation angle of at least 40 degrees.

Note.: Guidance to support performance-based navigation as described in the Performance- based Navigation (PBN) Manual (Doc 9613) is provided in Attachment C, 7.2.1.3.

3.5.3.1.2.2 When associated with a VOR, DME/N coverage shall be at least that of the VOR to the extent practicable.

3.5.3.1.2.3. When associated with an ILS, DME/N coverage shall be at least that of the ILS localizer coverage sector within plus or minus 10 degrees, as defined in Chapter 3, 3.1.3.3.1 Note.: Guidance relating to ILS-associated DME/N is provided in Attachment C,

7.1.6.3.

3.5.3.1.2.4 DME/P coverage or DME/N coverage when associated with an MLS shall be at 59CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 least that provided by the MLS azimuth angle guidance coverage sectors.

Note.: Guidance relating to ILS-associated DME/N is provided in Attachment C,

7.1.6.3.

3.5.3.1.3 Accuracy

3.5.3.1.3.1 System accuracy: The accuracy standards specified in 3.5.3.1.3.4,

3.5.4.5 and 3.5.5.4 shall be met on at 95 percent probability basis.

3.5.3.2 Radio frequencies and polarization: The system shall operate with vertical polarization in the frequency band 960 MHz to 1215 MHz. The interrogation and reply frequencies shall be assigned with 1 MHz spacing between channels.

3.5.3.3 Channeling

3.5.3.3.1 DME operating channels shall be formed by pairing interrogation and reply frequencies and by pulse coding on the paired frequencies.

3.5.3.3.2 Intentionally left blank

3.5.3.3.3 DME operating channels shall be chosen from Table A of 352 channels in which the channel numbers, frequencies, and pulse codes are assigned.

3.5.3.3.4 Channel pairing: When a DME transponder is intended to operate in association with a single VHF navigation facility in the 108 MHz to 117.95 MHz frequency band and the DME operating channel shall be paired with the VHF channel as given in table A.

3.5.3.4 Interrogation pulse repetition frequency

3.5.3.4.1 DME/N The interrogator average pulse repetition frequency (PRF) shall not exceed 30 pairs of pulses per second, based on the assumption that at least 95 percent of the time is occupied for tracing.

3.5.3.4.2 DME/N: If it is desired to decrease the time of search, the PRF may be increased during search but shall not exceed 150 airs of pulses per second.

3.5.3.4.3 DME/N: After 15000 pairs of pulses have been transmitted without acquiring indication of distance, the PRF should not exceeds 60 pairs of pulses per second thereafter, until a change in operating channel is made or successful search is completed.

3.5.3.4.4 DME/N: When, after a time period of 30 seconds, tracking has not been established the pulse pair repetition frequency shall not exceed 30 pulse pairs per second thereafter.

3.5.3.5 Aircraft handling capacity of the system 60CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.3.5.1 The aircraft handling capacity of transponders in an area shall be adequate for the peak traffic of the area of 100 aircraft, whichever is the lesser.

3.5.3.5.2 Where the peak traffic in an area exceeds 100 aircraft, the transponder should be capable of handling that peak traffic.

3.5.3.6 Transponder identification

3.5.3.6.1 All transponders shall transmit an identification signal in one of the following forms as required by 3.5.3.6.5 below: a) An “independent” identification consisting of coded (international Morse Code) identity pulses which can be used with all transponders.

b) An “associated” signal which can be used for transponders specifically associated with a VHF navigation facility which itself transmits an identification signal.

3.5.3.6.2 Both systems of identification shall use signals, which shall consist of the transmission for an appropriate period of a series of paired pulses transmitted at a repetition rate of 1350 pulse pairs per second, and shall temporarily replace all reply pulses that would normally occur at that time except as in 3.5.3.6.2.2 below. These pulses shall have similar characteristics to the other pulses of the reply signals.

3.5.3.6.2.1 DME/N Reply pulses shall be transmitted between key down times.

3.5.3.6.2.2 DME/N: If it is desired to preserve a constant duty cycle, an equalizing pair of pulses having the same characteristics as the identification pulse pairs, should be transmitted 100 microseconds plus or minus 10 microseconds after each identity pair.

3.5.3.6.3 The characteristics of the “independent” identification signal shall be as

follows: a) the identity signal shall consist of the transmission of the beacon code in the form of dots and dashes (International Morse code) of identity pulses at least once every 40 seconds at a rate of at least 6 words per

minute: and b) the identification code characteristic and letter rate for the DME transponder shall conform to the following to ensure that the maximum total key down time does not exceed 5 seconds per identification code group. The dots shall be a time duration of 0.1 second to 0.160 second, the dashes shall be typically 3 times the duration of the dots. The duration between dots and/or dashes shall be equal to that of one dot plus or minus 10 per cent. The time duration between letters or numerals shall not be less than three dots. The total period for transmission of an identification code group shall not exceed 10 seconds.

61CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.: The tone identification signal is transmitted at a repetition rate of 1350 pps.

This frequency may be used directly in the airborne equipment as an aural output for the pilot, or other frequencies may be generated at the option of the interrogator designer (see 3.5.3.6.2 above)

3.5.3.6.4 The characteristics of the “associated” signal shall be as follows: a) when associated with a VHF facility, the identification shall be transmitted in the form of dots and dashes (international Morse code) as in 3.5.3.6.3 above and shall be synchronized with the VHF facility

identification code: b) each 40 second interval shall be divided into four or more equal periods, with the transponder identification transmitted during one period only and the associated VHF facility identification, where these are provided, transmitted during the remaining periods:

3.5.3.6.5 Identification implementation

3.5.3.6.5.1 The “independent” identification code shall be employed wherever a transponder is not specifically associated with a VHF navigational facility.

3.5.3.6.5.2 Wherever a transponder is specifically associated with a VHF navigational facility identification shall be provided by the “associated” code.

3.5.3.6.5.3 When voice communications are being radiated on an associated VHF navigational facility, an “associated” signal from the transponder shall not be suppressed.

3.5.4 Detailed technical characteristics of transponder and associated monitor

3.5.4.1 Transmitter

3.5.4.1.1 Frequency of operation: The transponder shall transmit on the reply frequency appropriate to the assigned DME channel ( see 3.5.3.3.3 above).

3.5.4.1.2 Frequency stability: The radio frequency of operation shall not vary more than plus or minus 0.002 per cent from the assigned frequency.

3.5.4.1.3 Pulse shape and spectrum: The following shall apply to all radiated

pulses: a) Pulse rise time: DME/N shall not exceed 3 microseconds. b) Pulse duration shall be 3.5 microseconds plus or minus 0.5 microseconds.

62CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 c) Pulse decay time shall nominally be 2.5 microseconds but shall not exceed 3.5 microseconds. d) The instantaneous amplitude of the pulse shall not, at any instant between the point of the leading edge which is 95 per cent of maximum amplitude and the point of the trailing edge which is 95 per cent of the maximum amplitude, fall below a value which is 95 per cent of the maximum voltage amplitude of the pulse.

e) For DME/N the spectrum of the pulse modulated signal shall be such that during the pulse the E.I.R.P contained in a 05 MHz band centered on frequencies 0.8 MHz above and 0.8 MHz below the nominal channel frequency in each case shall not exceed 200 mW, and the E.I.R.P contained in a 05 MHz band centered on frequencies 2 MHz above and 2 MHz below the nominal channel frequency in each case shall not exceed 2mW.The E.I.R.P contained within any 0.5 MHz band shall decrease monotonically as the band center frequency moves away from the nominal channel frequency.

f) To ensure proper operation of the thresholding techniques, the instantaneous magnitude of any pulse turn on transients which occur in time prior to the virtual origin shall be less than one per cent of the pulse peak amplitude. Initiation of the turn-on process shall not commence sooner than 1 microseconds prior to the virtual origin.

Note 1.: The time “during the pulse” encompasses the total interval from the beginning of pulse transmission to its end. For practical reasons this interval may be measured between the 5 per cent points on the leading and trailing edges of the pulse envelope.

Note 2.: The power contained in the frequency bands specified in 3.5.4.1.3 e) is the average power during the pulse. Average power in a given frequency band is the energy contained in this frequency band divided by the time of pulse transmission as above.

3.5.4.1.4 Pulse spacing

3.5.4.1.4.1 The spacing of the constituent pulses of transmitted pulse pairs shall be as given in the table in 3.5.4.4.1.

3.5.4.1.4.2 DME/N The tolerance on the pulse spacing shall be plus or minus 0.25 microsecond.

3.5.4.1.4.3 DME/N The tolerance on the DME/N pulse spacing should be plus or minus

01.10 microsecond.

3.5.4.1.4.4 Intentionally left blank

3.5.4.1.4.5 The pulse spacing shall be measured between the half voltage points on the leading edges of the pulses.

63CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.4.1.5 Peak power output

3.5.4.1.5.1 DME/N The E.I.R.P power should not be less than that required to ensure 2 a peak pulse power density of minus 89 dBw/m under all l operational weather conditions at any point within coverage specified in 3.5.3.1.2 above.

3.5.4.1.5.2 DME / N. The peak equivalent isotropically radiated power shall not be less than that required to ensure peak pulse power density of minus 89 dBW / m2 under all operational weather condition at any point with in coverage specified in 3.5.3.1.2 above.

Note.: Although the Standard 3.5.4.1.5.2 above implies an improved interrogator receiver sensitivity, it is intended that the power density specified in

3.5.4.1.5.1 above be available at the maximum specified service range and level.

3.5.4.1.5.3 Intentionally left blank

3.5.4.1.5.4 The peak power of the constituent pulses of any pair of pulses shall not differ by more than 1 dB.

3.5.4.1.5.5 The reply capability of the transmitter should be such that the transponder should be capable of continuous operation at a transmission rate of 2700 plus or minus 90 pulse pairs per second (if 100 aircraft are to be served).

3.5.4.1.5.6 The transmitter shall operate at a transmission rate, including randomly distributed pulse pairs and distance reply pulse pairs, of not less than 700 pulse pairs per seconds except during identity. The minimum transmission rate shall be as close as practicable to 700 pulse pairs per seconds.

3.5.4.1.6 Spurious radiation: During intervals between transmission of individual pulses, the spurious power received and measured in a receiver having the same characteristics as a transponder receiver, but tuned to any DME interrogation or reply frequency, shall be more than 50 dB below the peak pulse power received and measured in the same receiver tuned to the reply frequency in use during the transmission of the required pulses. This provision refers to all spurious transmissions, including modulator and electrical interference.

3.5.4.1.6.1 DME/N The spurious power level specified in 3.5.4.1.6 above shall be more than 80 dB below the peak pulse power level.

3.5.4.1.6.2 Intentionally left blank

3.5.4.1.6.3 Out of band spurious radiation: At all frequencies from 10 to 1800 MHz but excluding the band of frequencies from 960 to 1215 MHz, the spurious output of the DME transponder transmitter shall not exceed minus 40 dBm in any one kHz of receiver bandwidth.

64CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.4.1.6.4 The equivalent isotropically radiated power of any CW harmonic of the carrier frequency on any DME operating channel shall not exceed minus 10 dBm.

3.5.4.2 Receiver

3.5.4.2.1 Frequency of operation: The receiver center frequency shall be the interrogation frequency appropriate to the assigned DME operating channel (see 3.5.3.3.3 above)

3.5.4.2.2 Frequency stability: The centre frequency of the receiver shall not vary more than plus or minus 0.002 percent from the assigned frequency.

3.5.4.2.3 Transponder sensitivity

3.5.4.2.3.1 In the absence of all interrogation pulse pairs, with the exception of those necessary to perform the sensitivity measurement interrogation pulse pairs with the correct spacing and nominal frequency shall trigger the transponder if the peak power density at the transponder antenna is at least minus103 2 dBW/m for DME/N.

3.5.4.2.3.2 The minimum power densities specified in 3.5.4.2.3.1 above shall cause the transponder to reply with an efficiency of at least 70 percent for DME/N.

3.5.4.2.3.3 DME/N dynamic range: The performance of the transponder shall be maintained when the power density of the interrogation signal at the transponder antenna has any value between the minimum specified in

3.5.4.2.3.1 above up to a maximum of minus 22 dBW/m2 when installed with ILS and minus 35 dBW/m2 when installed for other applications.

3.5.4.2.3.4 Intentionally left blank

3.5.4.2.3.5 The transponder sensitivity level shall not vary by more than 1 dB for transponder loadings between 0 and 90 percent of its maximum transmission rate.

3.5.4.2.3.6 DME/N .When the spacing of an interrogator pulse pair varies from the nominal value by up to plus or minus 1 microsecond, the receiver sensitivity shall not be reduced by more than 1 Db.

3.5.4.2.4 Load limiting:

3.5.4.2.4.1 DME/N: When transponder loading exceeds 90 percent of the maximum transmission rate, the receiver sensitivity should be automatically reduced in order to limit the transponder replies, so as to ensure that the maximum permissible transmission rate is not exceeded. (The available range of sensitivity reduction should be at least 50 Db.

65CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.4.2.5 Noise: When the receiver is interrogated at the power densities specified in

3.5.4.2.3.1 above to produce a transmission rate equal to 90 percent of the maximum, the noise generated pulse pairs shall not exceed 5 per cent of the maximum transmission rate.

3.5.4.2.6 Band width

3.5.4.2.6.1 The minimum permissible bandwidth of the receiver shall be such that the transponder sensitivity level shall not deteriorate by more then 3dB when the total receiver drift is added to an incoming interrogation frequency drift of plus or minus 100 kHz.

3.5.4.2.6.2 DME/N. The receiver bandwidth shall be sufficient to allow compliance with

3.5.3.1.3 above when the input signals are those specified in 3.5.5.1.3 below.

3.5.4.2.6.3 Intentionally left blank

3.5.4.2.6.4 3.5.4.2.6.4Intentionally left blank

3.5.4.2.6.5 Signals greater than 900 kHz removed from the desired channel nominal frequency and having power densities up to the values specified in

3.5.4.2.3.3 for DME/N shall not trigger the transponder. Signals arriving at the intermediate frequency shall be suppressed at least 80dB. All other spurious response or signals within the 9mmhz to 1215 MHz band and image frequencies shall be suppressed at least 75 dB.

3.5.4.2.7 Recovery time. Within 8 micro second of the reception of a signal between 0db and 60db above minimum sensitivity level, the minimum sensitivity level of the transponder to a desired signal shall be within 3db of the value obtained in the absence of signals. This requirement shall be met with echo suppression circuits, if any rendered in operative. The 8 microseconds are to be measured between the half voltage points on the leading edges of the two signals, both of which conform in shape, with the specifications in 3.5.1.3 below.

3.5.4.2.8 Spurious Radiations: Radiation from any part of the receiver or allied circuits shall meet the requirements stated in 3.5.4.1.6 above.

3.5.4.2.9 CW and echo suppression: CW and echo suppression should be adequate for the sites at which the transponder will be used.

Note.: In this connection, echoes mean undesired signals caused by multi path transmission (reflection, etc).

3.5.4.2.10 Protection against interference: Protection against interference outside the DME frequency band should be adequate for the sites at which the transponders will be used.

66CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.4.3 Decoding

3.5.4.3.1 The transponder shall include a decoding circuit such that the transponder can be triggered only by pairs of received pulses having pulse duration and pulse spacing appropriate to interrogator signals as described in 3.5.5.1.3 and3.5.5.1.4 below.

3.5.4.3.2 The decoding circuit performance shall not be affected by signals arriving before, between, or after the constituent pulses of a pair of the correct spacing.

3.5.4.3.3 DME/N- Decoder rejection: An interrogation pulse pair with a spacing of plus or minus 2 microseconds , or more from the nominal value specified in

3.5.4.2.3.3. shall be rejected such that the transmission rate does not exceed the value obtained when interrogations are absent.

3.5.4.4 Time delay

3.5.4.4.1 When a DME is associated only with a VHF facility, the time delay shall be the interval from the half voltage point on the leading edge of the second constituent pulse of the interrogation pair and half voltage point on the reply transmission. This delay shall be consistent with the following table, when it is desired that aircraft interrogations are to indicate distance from transponder site.

Pulse pair spacing Time delay (micro µs) (micro µs) Channel Operating Interr. Reply 1st pulse 2nd Pulse Suffix mode timing timing X DME/N 12 12 50 50 Y DME/N 36 30 56 50

3.5.4.4.2 Intentionally left blank

3.5.4.4.3 For the DME/N the transponder time delay should be capable of being set to an appropriate value between the nominal value of the time delay minus 15 micro-seconds and the nominal value of the time delay, to permit aircraft interrogations to indicate zero distance at a specific point remote from the transponder site.

Note.: Modes not allowing for the full 15 microseconds range of adjustment in transponder time delay may only be adjustable to the limits given by the transponder circuit delay and recovery time

3.5.4.4.3.1 DME/N. the time delay shall be the interval from the half voltage point on 67CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 the leading edge of the first constituent pulse of the interrogation pair and the half voltage point on the leading edge of the first constituent pulse of the reply transmission.

3.5.4.4.4 DME/N. Transponders should be sited as near to the point at which zero indication is required as is practicable.

Note.: It is desirable that the radius of the sphere at the surface of which zero indication is given be kept as small as possible in order to keep the zone of ambiguity to a minimum.

3.5.4.5 Accuracy

3.5.4.5.1 DME/N. The transponder shall not contribute more than plus or minus 1 microsecond (150 m (500ft) to the over-all system error.

3.5.4.5.1.1 DME/N..— The contribution to the total system error due to the combination of the transponder errors, transponder location co-ordinate errors, propagation effects and random pulse interference effects should be not greater than plus or minus 340 m (0.183 NM) plus 1.25 per cent of distance measure.

Note.: This error contribution limit includes errors from all causes except the airborne equipment, and assumes that the airborne equipment measures time delay based on the first constituent pulse of a pulse pair.

3.5.4.5.1.2 DME/N. The combination of the transponder errors, transponder location coordinate errors, propagation effects and random pulse interference effects shall not contribute more than plus or minus 185 m (0.1 NM) to the overall system error.

Note.: This error contribution limit includes errors from all causes except the airborne equipment, and assumes that the airborne equipment measures tie delay based on the first constituent pulse of a pulse pair.

3.5.4.5.2 DME/N. A transponder associated with a landing aid shall not contribute more than plus or minus 0.5 micro-second (75m (250ft) to the over-all system error.

3.5.4.6 Efficiency

3.5.4.6.1 The transponder reply efficiency shall be at least 70 per cent for DME/N at all values of transponder loading up to the loading corresponding to 3.5.3.5 above and at the minimum sensitivity level specified in 3.5.4.2.3.1 and

3.5.4.2.3.5 above.

Note.: When considering the transponder reply efficiency value, account is to be taken of the DME dead time and of the loading introduced by the monitoring function.

68CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.4.6.2 Transponder dead time: The transponder shall be rendered inoperative for a period normally not to exceed 60 microseconds after a valid interrogation decode has occurred. In extreme cases when the geographical site of the transponder is such as to produce undesirable reflection problems, the dead time may be increased but only by the minimum amount necessary to allow the suppression of echoes for DME/N.

3.5.4.7 Monitoring and control

3.5.4.7.1 Means shall be provided at each transponder site for the automatic monitoring and control of the transponder in use.

3.5.4.7.2 DME/N monitoring action

3.5.4.7.2.1 In the event that any of the conditions specified in 3.5.4.7.2.2 below occur,

the monitor shall cause the following action to take place: a) a suitable indication shall be given at a control point; b) the operating transponder shall be automatically switched off; and c) the standby transponder, if provided, shall be automatically placed in operation.

Note.: Where it is not possible to provide status indication to a control point, the same shall be published in AIP.

3.5.4.7.2.2 The monitor shall cause the actions specified in 3.5.4.7.2.1 above if: a) the transponder delay differs from the assigned value by 1 microseconds(75m(500ft)or more; b) in the case of a DME/N associated with a landing aid, the transponder delay differs from the assigned value by 0.5 microseconds(75m(250ft) or more;

3.5.4.7.2.3 The monitor should cause the action specified in 3.5.4.7.2.1 above if the spacing between the first and second pulse of the transponder pulse pair differs from the nominal value specified in the table following 3.5.4.4.1 above by 1 microsecond or more.

3.5.4.7.2.4 The monitor should also cause suitable indication to be given at a control

point if any of the following conditions arise: a) a fall of 3dB or more in transponder transmitted power output; b) a fall of 6dB or more in the minimum transponder receiver sensitivity 69CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 (provided that this is not due to the action of the receiver automatic gain reduction circuits);

c) the spacing between the first and second pulse of the transponder reply pulse pair differs from the normal value specified in 3.5.4.1.4 above by 1 microsecond or more; d) Variation of the transponder receiver and transmitter frequencies beyond the control range of the reference circuits (if the operating frequencies are not directly crystal controlled).

3.5.4.7.2.5 Means shall be provided so that any of the conditions and malfunctioning enumerated in 3.5.4.7.2.2, 3.5.4.7.2.3., and 3.5.4.7.2.4 above which are monitored can persist for a certain period before the monitor takes the action. This period shall be as low as practicable, but shall not exceed 10 seconds, consistent with the need for avoiding interruption, due to transient effects, of the service provided by the transponder.

3.5.4.7.2.6 The transponder shall not be triggered more than 120 times per second for either monitoring or automatic frequency control purposes, or both.

3.5.4.7.3 DME/P monitoring action

3.5.4.7.3.1 Intentionally left blank

3.5.4.7.3.2 Intentionally left blank

3.5.4.7.3.3 Intentionally left blank

3.5.4.7.3.4 Intentionally left blank

3.5.4.7.3.5 DME/N monitor failure: Failure of any part of the monitor itself shall automatically produce the same results as the malfunctioning of the element being monitored.

3.5.5 Technical characteristics of interrogator

Note: The following sub paragraph specifies only those interrogator parameters

which must be defined to ensure that the interrogator: a) does not jeopardize the effective operation of the DME system, e.g.by increasing transponder loading abnormally; and b) is capable of giving accurate distance readings.

3.5.5.1 Transmitter

3.5.5.1.1 Frequency of operation: The interrogator shall transmit on the interrogation frequency appropriate to the assigned DME channel (see 3.5.3.3.3 above)

3.5.5.1.2 Frequency stability. The radio frequency of operation shall not vary more than plus or minus 100 kHz from the assigned value.

70CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.5.1.3 Pulse shape and spectrum. The following shall apply to all radiated pulses: a) Pulse rise time for DME/N shall not exceed 3 micro seconds. b) Pulse duration shall be 3.5 microseconds plus or minus 0.5 microseconds.

c) Pulse decay time shall normally be 2.5 microseconds, but shall not exceed 3.5 microseconds. d) The instantaneous amplitude of the pulse shall not, at any instant between the point of the leading edge which is 95 percent of maximum amplitude and the point of trailing edge which id 95 percent of the maximum amplitude, fall below a value which is 95 percent of the maximum voltage amplitude of the pulse.

e) The spectrum of the pulse modulated signal shall be such that at least 90 percent of the energy in each pulse shall be within 0.5 MHz in a band centered on the nominal channel frequency. f) To ensure proper operation of the thresh holding techniques, the instantaneous magnitude of any pulse turn-on transients which occur in time prior to the virtual origin shall be less than one percent of the pulse peak amplitude. Initiation of the turn on process shall not commence sooner than 1 microsecond prior to the virtual origin.

3.5.5.1.4 Pulse spacing

3.5.5.1.4.1 The spacing of the constituent pulses of transmitted pulse pairs shall be as given in the table in 3.5.4.4.1 above.

3.5.5.1.4.2 DME/N. The tolerance on the pulse spacing shall be plus or minus 0.5 microseconds.

3.5.5.1.4.3 DME/N The tolerance on the pulse spacing should be plus or minus 0.25 microseconds.

3.5.5.1.4.4 Intentionally left blank

3.5.5.1.4.5 The pulse spacing shall be measured between the half voltage points on the leading edges of the pulses.

3.5.5.1.5 Pulse repetition frequency

3.5.5.1.5.1 The pulse repetition frequency shall be as specified in 3.5.3.4 above.

3.5.5.1.5.2 The variation in time between successive pairs of interrogation pulses shall be sufficient to prevent false lock-on.

3.5.5.1.6 Spurious radiation. During intervals between transmission of individual 71CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 pulses, the spurious pulse power received and measured in a receiver having the same characteristics of a DME transponder receiver, but tuned to any DME interrogation or reply frequency, shall be more than 50 dB below the peak pulse power received and measured in the same receiver tuned to the interrogation frequency in use during the transmission of the required pulses. This provision shall apply to all spurious pulse transmissions. The spurious CW power radiated from the interrogator on any DME interrogation or reply frequency shall not exceed 20 microwatts (minus 47 dBw).

Note: Although spurious CW radiation between pulses is limited to levels not exceeding minus 47 dBw, service providers are cautioned that where DME interrogators and secondary surveillance radar transponders are applied in the same aircraft, it may be necessary to provide protection to airborne SSR in the band 1 015 MHz to 1 045 MHz. This protection may be provided by limiting conducted and radiated CW to a level of the order of minus 77 dBW.

Where this level cannot be achieved, the required degree of protection may be provided in planning the relative location of the SSR and DME aircraft antennas. It is to be noted that only a few of these frequencies are utilized in the VHF/DME pairing plan.]

3.5.5.1.7 The spurious pulse power received and measured under the condition stated in 3.5.5.1.6 above should be 80 dB below the required peak pulse power received.

Note: Reference 3.5.5.1.6 and 3.5.5.1.7 above—although limitation of spurious CW radiation between pulses to levels not exceeding 80 dB below the peak pulse power received is recommended, service providers are cautioned that where users employ airborne secondary surveillance radar transponder in the same aircraft, it may be necessary to limit direct and radiated CW to not more than 0.02 microwatt in the frequency band 1 015 MHz to 1 045 MHz. It is to be noted that only a few of these frequencies are utilized in the VHF/DME pairing plan.

3.5.5.2 Time delay

3.5.5.2.1 The time delay shall be consistent with the table in 3.5.4.4.1 above.

3.5.5.2.2 DME/N. The time delay shall be the interval between the time of the half voltage point on the leading edge of the second constituent interrogation pulse and the time at which the distance circuits reach the condition corresponding to zero distance indication.

3.5.5.2.3 DME/N. The time delay shall be the interval between the time of the half voltage point on the leading edge of the first constituent interrogation pulse and the time at which the distance circuits reach the condition corresponding to zero distance indication.

3.5.5.3 Receiver 72CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.5.3.1 Frequency of operation. The receiver centre frequency shall be the transponder frequency appropriate to the assigned DME operating channel (see 3.5.3.3.3 above).

3.5.5.3.2 Receiver sensitivity

3.5.5.3.2.1 DME/N. The airborne equipment sensitivity shall be sufficient to acquire and provide distance information to the accuracy specified in 3.5.5.4 below for the signal power density specified in 3.5.4.1.5.2 above.

3.5.5.3.2.2 Intentionally left blank

3.5.5.3.2.3 DME/N. The performance of the interrogator shall be maintained when the power density of the transponder signal at the interrogator antenna is between the minimum values given in 3.5.4.1.5 above and a maximum of 2 minus18 dBW/m .

3.5.5.3.3 Bandwidth

3.5.5.3.3.1 DME/N. The receiver bandwidth shall be sufficient to allow compliance with

3.5.3.1.3, when the input signals are those specified in 3.5.4.1.3.

3.5.5.3.4 Interference rejection

3.5.5.3.4.1 When there is a ratio of desired to undesired co-channel DME signals of at least 8 dB at the input terminals of the airborne receiver, the interrogator shall display distance information and provide unambiguous identification from the stronger signal.

Note.: Co-channel refers to those reply signals that utilize the same frequency and the same pulse pair spacing.

3.5.5.3.4.2 DME/N. DME signals greater than 900 KHz removed from the desired channel nominal frequency and having amplitudes up to 42 dB above the threshold sensitivity shall be rejected.

3.5.5.3.5 Decoding

3.5.5.3.5.1 The interrogator shall include a decoding circuit such that the receiver can be triggered only by pairs of received pulses having pulse duration and pulse spacing appropriate to transponder signals as described in 3.5.4.1.4.

3.5.5.3.5.2 DME/N Decoder rejection: A reply pulse pair with a spacing of plus or minus 2 micro seconds, or more, from the nominal value and with any signal level up to 42 dB above the receiver sensitivity shall be rejected.

3.5.5.4 Accuracy 73CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.5.4.1 DME/N The interrogator shall not contribute more than plus or minus 315m (plus or minus 0.17NM) or 0.25 per cent of indicated range, whichever is greater to overall system error.

3.6 Intentionally left blank

3.7 Requirements for the Global Navigation Satellite System (GNSS)

3.7.1 Definitions Aircraft-based augmentation system (ABAS). An augmentation system that augments and/or integrates the information obtained from the other GNSS elements with information available on board the aircraft.

Advanced receiver autonomous integrity monitoring (ARAIM). An ABAS function making use of ISD.

Alert. An indication provided to other aircraft systems or annunciation to the pilot to identify that an operating parameter of a navigation system is out of tolerance.

Alert limit. For a given parameter measurement, the error tolerance not to be exceeded without issuing an alert.

Antenna port. A point where the received signal power is specified. For an active antenna, the antenna port is a fictitious point between the antenna elements and the antenna pre-amplifier. For a passive antenna, the antenna port is the output of the antenna itself.

Axial ratio. The ratio, expressed in decibels, between the maximum output power and the minimum output power of an antenna to an incident linearly polarized wave as the polarization orientation is varied over all directions perpendicular to the direction of propagation.

BeiDou Navigation Satellite System (BDS). The satellite navigation system operated by China.

BDS Open Service (BDS OS). The specified level of positioning, velocity and timing accuracy that is available to any BDS user on a continuous, worldwide basis.

Channel of standard accuracy (CSA). The specified level of positioning, velocity and timing accuracy that is available to any GLONASS user on a continuous, worldwide basis.

Core satellite constellation(s). The core satellite constellations are GPS, GLONASS, Galileo and BDS.

GAGAN: GPS Aided GEO Augmented Navigation, An Indian SBAS Galileo. The satellite navigation system operated by the European Union and its Member States.

Galileo Open Service (Galileo OS). The specified level of positioning, 74CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 velocity and timing accuracy that is available to any Galileo user on a continuous, worldwide basis.

Global navigation satellite system (GNSS). A worldwide position and time determination system that includes one or more satellite constellations, aircraft receivers and system integrity monitoring, augmented as necessary to support the required navigation performance for the intended operation.

Global navigation satellite system (GLONASS). The satellite navigation system operated by the Russian Federation.

Global positioning system (GPS). The satellite navigation system operated by the United States.

GNSS position error. The difference between the true position and the position determined by the GNSS receiver.

Ground-based augmentation system (GBAS). An augmentation system in which the user receives augmentation information directly from a ground- based transmitter.

Integrity. A measure of the trust that can be placed in the correctness of the information supplied by the total system. Integrity includes the ability of a system to provide timely and valid warnings to the user (alerts).

Integrity support data (ISD). A set of parameters that characterize the signal-in-space (SIS) integrity performance for each specific core satellite constellation and ARAIM service type.

Integrity support message (ISM). A dedicated core satellite constellation broadcast navigation message that contains ISD parameters which may improve ARAIM performance compared to the default ISD values.

Note.: The broadcast ISD may be contained in one or more ISMs.

Ionosphere-free pseudo-range. A pseudo-range in which the first order ionosphere effect on signal propagation has been removed by a linear combination of pseudo-range measurements from signals on two distinct frequencies from the same satellite.

ISM generator (ISMG). Entity which determines the values of the ISD parameters transmitted in the ISM for ARAIM for a given core satellite constellation.

Pseudo-range. The difference between the time of transmission by a satellite and reception by a GNSS receiver multiplied by the speed of light in a vacuum, including bias due to the difference between a GNSS receiver and satellite time reference.

Satellite-based augmentation system (SBAS). A wide coverage augmentation system in which the user receives augmentation information from a satellite-based transmitter.

75CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Standard positioning service (SPS). The specified level of positioning, velocity and timing accuracy that is available to any global positioning system (GPS) user on a continuous, worldwide basis.

Time-to-alert. The maximum allowable time elapsed from the onset of the navigation system being out of tolerance until the equipment enunciates the alert.

3.7.2 General

3.7.2.1 Functions

3.7.2.1.1 The GNSS shall provide position and time data to the aircraft.

Note: these data are derived from pseudo-range measurements between an aircraft equipped with a GNSS receiver and various signal sources on satellites or on the ground.

3.7.2.2 GNSS elements

3.7.2.2.1 The GNSS navigation service shall be provided using various combinations of the following elements installed on the ground, on satellites and/or on

board the aircraft: a) Global Positioning System (GPS) that provides the Standard Positioning Service (SPS) as defined in 3.7.3.1; b) Global Navigation Satellite System (GLONASS) that provides the Channel of Standard Accuracy (CSA) navigation signal as defined in

3.7.3.2 c) aircraft-based augmentation system (ABAS) as defined in 3.7.3.3; d) satellite-based augmentation system (SBAS) as defined in 3.7.3.4; e) ground-based augmentation system (GBAS) as defined in 3.7.3.5;

f) Intentionally Left Blank g) Aircraft GNSS receiver as defined in 3.7.3.6

3.7.2.3 Space and time reference

3.7.2.3.1 Space reference. The position information provided by the GNSS to the user shall be expressed in terms of the World Geodetic System — 1984 (WGS-

84) geodetic reference datum.

Note 1.: SARPs for WGS-84 are contained in Annex 4, Chapter 2, Annex 11, Chapter 2, Annex 14, Volumes I and II,Chapter 2 and Annex 15, Chapter 3.

Note 2.: If GNSS elements using other than WGS-84 coordinates are employed, appropriate conversion parameters are to be applied. Time reference. The time data provided by the GNSS to the user shall be expressed in a time scale that takes the Universal Time Coordinated (UTC) as reference.

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3.7.2.4 Signal-in-space performance

3.7.2.4.1 The combination of GNSS elements and a fault-free GNSS user receiver shall meet the signal-in-space requirements defined in Table 3.7.2.4-1 Note.: The concept of a fault-free user receiver is applied only as a means of defining the performance of combinations of different GNSS elements. The fault-free receiver is assumed to be a receiver with nominal accuracy and time-to-alert performance. Such a receiver is assumed to have no failures that affect the integrity, availability and continuity performance.

Table 3.7.2.4-1 Signal-in-space performance requirements Accuracy Accuracy horizontal vertical 95% 95% Time-to- (Notes 1 and (Notes 1 and Integrity alert Continuity Availability Typical Operation 3) 3) (Note 2) (Note 3) (Note 4) (Note 5) NOTES-

1. The 95th-percentile values for GNSS position errors are those required for the intended operation at the lowest height above threshold (HAT), if applicable. Detailed requirements are specified in Appendix B and guidance material is given in Attachment D. 3.2.

2. The definition of the integrity requirement includes an alert limit against which the 77CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 requirement can be assessed. For Category I precision approach, a vertical alert limit

(VAL) greater than 10 m for a specific system design may only be used if a system- specific safety analysis has been completed. Further guidance on the alert limits is

provided in Attachment D. 3.3.6 to 3.3.10. These alert limits are:

3. The accuracy and time-to-alert requirements include the nominal performance of a fault-free receiver.

4. Ranges of values are given for the continuity requirement for en-route, terminal, initial approach, NPA and departure operations, as this requirement is dependent upon several factors including the intended operation, traffic density, complexity of airspace and availability of alternative navigation aids. The lower value given is the minimum requirement for areas with low traffic density and airspace complexity. The higher value given is appropriate for areas with high traffic density and airspace complexity (see Attachment D. 3.4.2). Continuity requirements for APV and Category I operations apply to the average risk (over time) of loss of service, normalized to a 15-second exposure time (see Attachment D. 3.4.3).

5. A range of values is given for the availability requirements as these requirements are dependent upon the operational need which is based upon several factors including the frequency of operations, weather environments, the size and duration of the outages, availability of alternate navigation aids, radar coverage, traffic density and reversionary operational procedures. The lower values given are the minimum availabilities for which a system is considered to be practical but are not adequate to replace non-GNSS navigation aids. For en-route navigation, the higher values given are adequate for GNSS to be the only navigation aid provided in an area. For approach 78CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 and departure, the higher values given are based upon the availability requirements at airports with a large amount of traffic assuming that operations to or from multiple runways are affected but reversionary operational procedures ensure the safety of the operation (see Attachment D, 3.5).

6. A range of values is specified for Category I precision approach. The 4.0 m (13 feet) requirement is based upon ILS specifications and represents a conservative derivation from these specifications (see Attachment D, 3.2.7).

7. GNSS performance requirements for Category II and III precision approach operations are under review and will be included at a later date.

8. The terms APV-I and APV-II refer to two levels of GNSS approach and landing operations with vertical guidance (APV) and these terms are not necessarily intended to be used operationally.

3.7.3 GNSS elements specifications

3.7.3.1 Core constellations

3.7.3.1.1 GPS Standard Positioning Service (SPS) (L1, L5) Note.: Unless otherwise specified, the performance standards in 3.7.3.1.1.1 to

3.7.3.1.1.7 below apply to single-frequency ranging, using the L1 coarse acquisition (C/A) code signal or the L5 signal (I5 code or Q5 code), and to dual-frequency ranging using the combination of L1 and L5 signals. In addition, they only apply to current and consistent ephemeris and clock data within the respective curve fit intervals.

3.7.3.1.1.1 Space and control segment accuracy Note.: The following accuracy standards apply only for healthy GPS SPS signal-in- space (SIS), during normal operations as described in Attachment D, 4.1.1.9, and do not include atmospheric or receiver errors as described in Attachment D, 4.1.1.2. GPS SPS SIS health conditions can be found in the United States Department of Defense, Global Positioning System – Standard Positioning Service – Performance Standard, 5th Edition, April 2020 (hereinafter referred to as “GPS SPS PS”), 2.3.2.

3.7.3.1.1.1.1 Positioning accuracy. The single-frequency L1 C/A code position errors

shall not exceed the following limits:

79CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.7.3.1.1.2 Time transfer accuracy. The GPS SPS time transfer errors shall not exceed 30 nanoseconds 95 per cent of the time.

3.7.3.1.1.1.3 Range domain accuracy. The range domain error shall not exceed

the following limits: a) Range error of any satellite —30m (100 ft) with reliability specified in

3.7.3.1.1.3 th b) 95 percentile range rate error of any satellite —0.006m (0.02ft) per second;(global average ); th c) 95 percentile range acceleration error of any satellite —0.002m (0.006ft) per second-squared(global average ); and th d) 95 percentile range error for any satellites over all time differences between time of data generation and time of use of data 7.8m (26 ft ) (global average ).

3.7.3.1.1.2 Availability. The GPS SPS availability shall be as follows: ≥99 per cent horizontal service availability, average location (15 m 95 per cent threshold) ≥99 per cent vertical service availability, average location (33 m 95 per cent threshold) ≥90 per cent horizontal service availability, worst-case location (15 m 95 per cent threshold) ≥90 per cent vertical service availability, worst-case location (33 m 95 per cent threshold)

3.7.3.1.1.3 Reliability. The GPS SPS reliability shall be within the following limits: a) Reliability — at least 99.94 per cent (global average); and b) Reliability — at least 99.79 per cent (worst single point average).

80CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.7.3.1.1.4 Probability of major service failure.

Note.: The different alert indications are described in the United States Department of Defense, Global Positioning System - Standard Positioning Service - Performance Standard, 4th Edition, September 2008, Section 2.3.4.

3.7.3.1.1.4.1 Satellite major service failure onset rate (Rsat). The probability that the instantaneous user range error (URE) of any satellite will exceed 4.42 times the relevant integrity assured user range accuracy (IAURA) value broadcast by that satellite without an alert received at the user receiver antenna within 10 seconds shall not exceed 1×10-5 per hour.

3.7.3.1.1.4.2 Probability of a satellite major service failure condition (Psat). The probability at any given instant that the instantaneous URE of any satellite will exceed 4.42 times the relevant IAURA value broadcast by that satellite without an alert received at the user receiver antenna within 10 seconds shall not exceed 1×10-5.

3.7.3.1.1.4.3 Probability of a common-cause major service failure condition (Pconst).

The probability at any given instant that the instantaneous URE of two or more satellites will exceed 4.42 times the relevant IAURA broadcast by each satellite due to a common fault without an alert received at the user receiver antenna within 10 seconds shall not exceed 1×10-8.

3.7.3.1.1.5 Continuity. The probability of losing GPS SPS signal-in-space (SIS) availability from a slot of the nominal 24-slot constellation due to -4 unscheduled interruption shall not exceed 2x10 per hour

3.7.3.1.1.6 Coverage. The GPS SPS shall cover the surface of the earth up to an altitude of 3000 kilometers.

Note.: Guidance material on GPS accuracy, availability, reliability and coverage is given in Attachment D, 4.1

3.7.3.1.1.7 Constellation availability. The probability that 21 or more of the 24 slots will be occupied by either a satellite broadcasting a trackable and healthy L1 C/A signal in the baseline slot configuration or by a pair of satellites each broadcasting a trackable and healthy L1 C/A signal in the expanded slot configurations, shall be at least 0.98. The probability that 20 or more of the 24 slots will be occupied by either a satellite broadcasting a trackable and healthy L1 C/A signal in the baseline slot configuration or by a pair of satellites each broadcasting a trackable and healthy L1 C/A signal in the expanded slot configurations, shall be at least 0.99999.

Note.: There is currently no corresponding standard for the L5 signal or for the combined L1 C/A and L5 signals since older satellites in the constellation do not have the capability to broadcast an L5 signal.

81CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.7.3.1.1.8 Radio frequency (RF) characteristics Note.: Detailed RF characteristics are specified in NAVSTAR GPS Space Segment/Navigation User Segment Interfaces, IS No. IS-GPS-200, Rev K (hereinafter referred to as “IS-GPS-200K”) for L1 and NAVSTAR GPS Space Segment/User Segment L5 Interfaces, IS No. IS-GPS-705, Rev F (hereinafter referred to as “IS-GPS-705F”); selected characteristics are specified in Appendix B, 3.1.1.1.1 for L1 and Appendix B, 3.1.1.1.4 for L5.

3.7.3.1.1.8.1 L1 carrier frequency. Each GPS satellite shall broadcast an SPS ranging signal at the carrier frequency of 1 575.42 MHz (GPS L1) using code division multiple access (CDMA).

3.7.3.1.1.8.2 L5 carrier frequency. Some GPS satellites shall, in addition, broadcast an SPS ranging signal at the carrier frequency of 1 176.45 MHz (GPS L5) using CDMA.

3.7.3.1.1.8.3 Signal spectrum. The L1 and L5 signal power shall be contained within ±12 MHz bands centred on the respective carrier frequencies: 1 563.42 –1 587.42 MHz for L1 and 1 164.45 – 1 188.45 for L5.

3.7.3.1.1.8.4 Polarization. The transmitted L1 and L5 RF signals shall be right-hand circularly polarized.

3.7.3.1.1.8.5 Signal structure. The L1 C/A signal shall consist of one carrier component. The L5 signal shall consist of two carrier components: an in- phase component (I5) and a quadrature component lagging the in-phase component by 90 degrees (Q5).

3.7.3.1.1.8.6 Signal power level. Each GPS satellite shall broadcast SPS navigation signals with sufficient power such that, at all unobstructed locations near the ground from which the satellite is observed at an elevation angle of 5 degrees or higher, the level of the received RF signal at the antenna port of a 3 dBi linearly-polarized antenna is within the following ranges for all

antenna orientations orthogonal to the direction of propagation: –158.5 dBW to –153 dBW for L1 C/A and –157.9 dBW to –150 dBW for each of the I5 and Q5 channels on L5.

3.7.3.1.1.8.7 Modulation. Each SPS L1 and L5 signal shall be bipolar phase shift key

(BPSK) modulated with a pseudo random noise (PRN) code. The C/A code on L1 shall have a rate of 1.023 megachips per second. The codes on I5 and Q5 shall have a rate of 10.23 megachips per second.

3.7.3.1.1.8.7.1 The C/A, I5, and Q5 code sequences shall be repeated each millisecond.

3.7.3.1.1.8.7.2 The transmitted code sequence on L1 shall be the Modulo-2 addition of a 50-bit-per-second legacy navigation (LNAV) message and the C/A code.

82CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.7.3.1.1.8.7.3 The transmitted code sequence on I5 shall be the Modulo-2 addition of a 50-bit-per-second civil navigation (CNAV) message (rate 1/2 convolution encoded into a 100 symbol per second stream), a 10-bit Neuman-Hofman overlay code clocked at 1 kbps, and the I5 code. The transmitted code sequence on Q5 shall be the Modulo-2 addition of a 20 bit Neuman- Hofman overlay code clocked at 1 kbps and the Q5 code. Note.— The Q5 signal is not modulated with navigation data.

3.7.3.1.1.8.7.4 Signal coherence. All transmitted signals for any satellite shall be coherently derived from the same on board frequency standard. On the L5 channel, the chip transitions of the two modulating signals, I5 and Q5, shall be such that the average time difference between them does not exceed 10 nanoseconds.

3.7.3.1.1.9 GPS time. GPS time shall be referenced to UTC (as maintained by the U.S.

Naval Observatory).

3.7.3.1.1.10 Coordinate system. The GPS coordinate system shall be WGS-84.

3.7.3.1.1.11 Navigation information. The navigation data transmitted by the satellites

shall include the necessary information to determine: a) satellite time of transmission; b) satellite position; c) satellite health; d) satellite clock correction; e) propagation delay effects; f) time transfer to UTC; and g) constellation status.

Note.: Structure and contents of data are specified in Appendix B,

3.1.1.1.2 and 3.1.1.1.3 for L1, and 3.1.1.1.5 and

3.1.1.1.6 for L5.

3.7.3.1.2 GLONASS Channel of Standard Accuracy (CSA) (L1) Note. : The GLONASS signals for CSA are broadcast in two frequency bands identified as L1 and L3. In the L1 band, two types of signals are broadcast:

L1OF with frequency division multiple access (FDMA) and L1OC with code division multiple access (CDMA). In the L3 band, only CDMA signals (L3OC) are broadcast. Except where otherwise specified, the term GLONASS refers to all satellites in the constellation transmitting either FDMA or CDMA signals 83CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.7.3.1.2.1 Space and control segment accuracy Note. : The single-frequency accuracy Standards do not include atmospheric or receiver errors; ionosphere errors are included for dual-frequency combinations, as described in Attachment D, 4.1.2.2.

3.7.3.1.2.1.1 Positioning accuracy. The GLONASS CSA position errors shall not exceed

the following limits:

3.7.3.1.2.1.2 Time transfer accuracy. The GLONASS CSA time transfer errors shall not exceed 700 nanoseconds 95 per cent of the time.

3.7.3.1.2.1.3 Range domain accuracy. The range domain error shall not exceed the

following limits:

3.7.3.1.2.2 Availability. The GLONASS CSA availability shall be as follows 84CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.7.3.1.2.3 Reliability. The GLONASS CSA reliability shall be within the following

limits:

3.7.3.1.2.4

3.7.3.1.2.5 Probability of major service failure. The probability that the user range error (URE) of any satellite will exceed the following tolerance without an alert received at the user receiver antenna within 10 seconds shall not

exceed the following probability:

3.7.3.1.2.6 Continuity. The probability of losing GLONASS CSA healthy signal availability from a slot of the nominal 24-slot constellation due to

unscheduled interruption shall not exceed the following limit:

3.7.3.1.2.7 Coverage. The GLONASS CSA shall cover the surface of the earth up to 85CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 an altitude of 2 000 km.

Note.: Guidance material on GLONASS accuracy, availability, reliability and coverage is given in Attachment D, 4.1.2.

3.7.3.1.2.8 L1OF RF characteristics Note.: Detailed RF characteristics are specified in Appendix B, 3.1.2.1.1.

3.7.3.1.2.8.1 Carrier frequency. Each GLONASS satellite shall broadcast CSA navigation signal at its own carrier frequency in the L1 (1.6 GHz) frequency band using frequency division multiple access (FDMA).

Note 1.: GLONASS satellites may have the same carrier frequency but in this case they are located in antipodal slots of the same orbital plane.

Note 2.: GLONASS-M satellites will broadcast an additional ranging code at carrier frequencies in the L2 (1.2 GHz) frequency band using FDMA.

3.7.3.1.2.8.2 Signal spectrum. GLONASS CSA signal power shall be contained within a ±5.75 MHz band centred on each GLONASS carrier frequency.

3.7.3.1.2.8.3 Polarization. The transmitted RF signal shall be right-hand circularly polarized.

3.7.3.1.2.8.4 Signal power level. Each GLONASS satellite shall broadcast CSA navigation signals with sufficient power such that, at all unobstructed locations near the ground from which the satellite is observed at an elevation angle of 5 degrees or higher, the level of the received RF signal at the antenna port of a 3 dBi linearly polarized antenna is within the range of –161 dBW to –155.2 dBW for all antenna orientations orthogonal to the direction of propagation.

Note 1.: The power limit of 155.2 dBW is based on the predetermined characteristics of a user antenna, atmospheric losses of 0.5 dB and an error of an angular position of a satellite that does not exceed one degree (in the direction causing the signal level to increase).

Note 2.: GLONASS-M satellites will also broadcast a ranging code on L2 with sufficient power such that, at all unobstructed locations near the ground from which the satellite is observed at an elevation angle of 5 degrees or higher, the level of the received RF signal at the output of a 3 dBi linearly polarized antenna is not less then –167 dBW for all antenna orientations orthogonal to the direction of propagation.

3.7.3.1.2.8.5 Modulation

3.7.3.1.2.8.5.1.1 Each GLONASS satellite shall transmit at its carrier frequency the navigation RF signal using a BPSK modulated binary train. The 86CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 phase shift keying of the carrier shall be performed at π-radians with the maximum error ±0.2 radian. The pseudo-random code sequence shall be repeated each millisecond.

3.7.3.1.2.8.5.1.2 The modulating navigation signal shall be generated by the Modulo-2

addition of the following three binary signals: a) ranging code transmitted at 511 kbits/s; b) navigation message transmitted at 50 bits/s; and c) 100 Hz auxiliary meander sequence.

3.7.3.1.2.9 L3OC RF characteristics Note.: Detailed RF characteristics are specified in Appendix B, 3.1.2.1.5.

3.7.3.1.2.9.1 Carrier frequency. GLONASS L3OC navigation signals shall be broadcast at the carrier frequency of 1 202.025 MHz using code division multiple access (CDMA).

3.7.3.1.2.9.2 Signal spectrum. GLONASS CSA L3OC signal power shall be contained within the 1 190.35 – 1 212.23 МHz band.

3.7.3.1.2.9.3 Polarization. The transmitted L3OC signal shall be right-hand circularly polarized.

3.7.3.1.2.9.4 Signal power level. GLONASS L3OC navigation signals shall be broadcast with sufficient power such that, at all unobstructed locations near the ground from which the satellite is observed at an elevation angle of 5 degrees or higher, the level of the received RF signal at the antenna port of a 3 dBi linearly polarized antenna is within the range of 158.5 dBW to –

155.2 dBW for all antenna orientations orthogonal to the direction of propagation.

Note.: The power limit of 155.2 dBW is based on the predetermined characteristics of a user antenna, atmospheric losses of 0.5 dB and an error of an angular position of a satellite that does not exceed one degree (in the direction causing the signal level to increase).

3.7.3.1.2.9.5 Modulation Note.: Additional information concerning the modulation is given in the GLONASS CDMA ICD Open Service Navigation Signal in L3 frequency band (Edition 1.0), dated 2016 (hereinafter referred to as “GLONASS CDMA ICD L3 band”).

3.7.3.1.2.9.5.1 GLONASS L3OC navigation signals shall contain two components using the same BPSK (10)-modulated binary train: an in-phase data component and a quadrature-phase pilot component identified as 87CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 L3OCd and L3OCp, respectively. The pilot component leads the data component by 𝜋/2 radians.

3.7.3.1.2.9.5.2 The L3OCd signal component shall be generated by the Modulo-2

addition of the following three binary signals: a) ranging code with length N=10230, period T=1 ms, clock rate

10.23 MHz; b) 100 bits/s navigation message encoded using a convolutional encoder with constraint length 7 and code rate 1/2 to yield 200 symbols per second; and c) overlay code “00010” with period T=5 ms.

3.7.3.1.2.9.5.3 The L3OCp signal component shall be generated by the Modulo-2

addition of the following two binary signals: a) ranging code with length N=10230, period T=1 ms, clock rate

10.23 MHz; and b) overlay code ”0000110101” with period T=10 ms.

3.7.3.1.2.10 L1OC RF characteristics Note.: Detailed RF characteristics are specified in Appendix B, 3.1.2.1.5.

3.7.3.1.2.10.1 Carrier frequency. GLONASS L1OC navigation signals shall be broadcast at the carrier frequency of 1600.995 MHz using code division multiple access (CDMA).

3.7.3.1.2.10.2 Signal spectrum. GLONASS CSA L1OC signal power shall be contained within the 1 592.9 – 1 610 MHz band.

3.7.3.1.2.10.3 Polarization. The transmitted L1OC signal shall be right-hand circularly polarized.

3.7.3.1.2.10.4 Signal power level. GLONASS L1OC navigation signals shall be broadcast with sufficient power such that, at all unobstructed locations near the ground from which the satellite is observed at an elevation angle of 5 degrees or higher, the level of the received RF signal at the antenna port of a 3 dBi linearly polarized antenna is within the range of 158.5 dBW to –155.2 dBW for all antenna orientations orthogonal to the direction of propagation.

Note.: The power limit of 155.2 dBW is based on the predetermined characteristics of a user antenna, atmospheric losses of 0.5 dB and an error of an angular position of a satellite that does not exceed one degree (in the direction causing the signal level to increase).

3.7.3.1.2.10.5 Modulation 88CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.: Additional information concerning the modulation is given in the GLONASS CDMA ICD Open Service Navigation Signal in L1 frequency band (Edition 1.0), dated 2016 (hereinafter referred to as “GLONASS CDMA ICD L1 band”).

3.7.3.1.2.10.5.1 GLONASS L1OC navigation signals shall contain two components: a data component and a pilot component identified as L1OCd and L1OCp, respectively. Both components shall be at one phase quadrature using time division multiplexing. L1OCd shall be modulated using binary phase-shift keying BPSK (1), while L1OCp shall be modulated by binary offset carrier BOC (1,1) modulation.

3.7.3.1.2.10.5.2 The L1OCd signal component shall be generated by the Modulo-2

addition of the following three binary signals: a) ranging code with length N=1023, period T=2 ms, clock rate

0.5115 MHz; b) 125 bits/s navigation message encoded using a convolutional encoder with constraint length 7 and code rate 1/2 to yield 250 symbols per second; and c) overlay code “01” with period T=4 ms.

3.7.3.1.2.10.5.3 The L1OCp signal component shall be generated by the Modulo-2

addition of the following two binary signals: a) ranging code with length N=4092, period T=8 ms, clock rate

0.5115 MHz; and b) meander sequence “0101” with clock rate 2.046 MHz.

3.7.3.1.2.11 GLONASS time. GLONASS time shall be referenced to UTC(SU) (as maintained by the National Time Service of Russia).

3.7.3.1.2.12 Coordinate system. The GLONASS coordinate system shall be PZ-

90.

Note.: Conversion from the PZ-90 coordinate system used by GLONASS to the WGS-84 coordinates is defined in Appendix B, 3.2.5.2.

3.7.3.1.2.13 Navigation information. The navigation data transmitted by the

satellite shall include the necessary information to determine: a) satellite time of transmission; b) satellite position; c) satellite health;

89CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 d) satellite clock correction; e) time transfer to UTC; and f) constellation status. g) ionospheric delay effects (L1OC, L3OC only); and h) satellite orientation in umbra (L1OC, L3OC only).

Note.: Structure and contents of data are specified in Appendix B, 3.2.1.2 and

3.2.1.3, respectively.

3.7.3.1.3 Galileo Open Service (Galileo OS) (E1, E5) Note 1.: The Galileo signals for Galileo OS are broadcast in two frequency bands identified as E1 and E5. In the E5 band, two types of signals are broadcast with code division multiple access (CDMA): E5a and E5b. For aviation purposes, the Galileo single-frequency OS is based on either E1 or E5a signals; and the Galileo dual-frequency OS is based on a combination of E1 and E5a signals.

Note 2.: The E5b signal component is described in this Annex since it is a subset of the overall Galileo signal modulated on the E5 frequency carrier.

However, there is currently no intention that the E5b signal be used by aviation receivers.

Note 3.: The following performance standards only apply if “healthy” signals-in- space are used (see Appendix B, 3.1.3.1.3.4).

Note 4.: The following performance standards do not include atmospheric or receiver errors such as ionosphere, troposphere, interference, receiver noise or multipath.

Note 5.: Guidance material on Galileo OS accuracy, availability, continuity, probability of satellite/constellation failure and coverage, is given in Attachment D, 4.1.3.

3.7.3.1.3.1 Positioning accuracy. The Galileo position errors shall not exceed the

following limits:

90CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.7.3.1.3.2 Time determination accuracy. The Galileo UTC time determination error shall not exceed 30 nanoseconds, 95 per cent of the time.

3.7.3.1.3.3 Range domain accuracy. The Galileo range domain error shall not exceed

the following limits:

Note 1.: The ranging accuracy considers only healthy Galileo OS SIS above a minimum elevation angle of 5 degrees.

Note 2.: Single-frequency (E1 or E5a) ranging accuracy includes broadcast group delay (BGD) errors. BGD definition is specified in Attachment D, 4.1.3.3.2.

3.7.3.1.3.4 Availability. The Galileo OS availability shall be as follows:

91CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.7.3.1.3.5 Galileo integrity support data Note.: Galileo integrity support data is specified for measurements derived from Galileo signals received above a 5-degree elevation angle

3.7.3.1.3.5.1 Probability of satellite failure (Psat). The probability that one satellite of Galileo operational core constellation provides an instantaneous SIS range error higher than k times the Galileo user range accuracy (Galileo URA) and no notification is given to the user, shall not exceed 3×10-5.

Note 1.: A change in the SIS health status is notified through the flags contained in the navigation message. The mapping between Galileo SIS status and flags contained in the navigation data message is specified in Appendix B,

3.1.3.1.3.4.

Note 2.: Galileo URA corresponds either to σURA,DF for dual-frequency users or to σURA,SF for single-frequency users as specified in 3.7.1.3.5.3 and

3.7.1.3.5.4.

Note 3.: Psat definition is further specified in Attachment D, 4.1.3.6.1.

3.7.3.1.3.5.2 Probability of constellation failure (Pconst). The probability that, due to a common cause, any subset of two or more satellites within Galileo operational constellation provides an instantaneous SIS range error higher than k times the Galileo URA and no notification is given to the user, shall not exceed 2×10-4.

Note 1.: A change in the SIS health status is notified through the flags contained in the navigation message. The mapping between Galileo SIS status and flags contained in the navigation data message is specified in Appendix B,

3.1.3.1.3.4.

Note 2.: Galileo URA corresponds either to σURA,DF for dual-frequency users or to σURA,SF for single-frequency users. as specified in 3.7.1.3.5.3 and

3.7.1.3.5.4.

Note 3.: Pconst definition is further specified in Attachment D, 4.1.3.6.2.

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3.7.3.1.3.5.3 Galileo URA for dual-frequency (σ ). Galileo σ shall not exceed URA,DF URA,DF 6 m.

Note 1.: σURA,DF applies to a dual-frequency E1-E5a signal combination.

Note 2.: σURA,DF is defined in Attachment D, 4.1.3.6.3.

3.7.3.1.3.5.4 Galileo URA for single-frequency (σ ). Galileo σ shall not URA,SF URA,SF exceed 6.5 m for E1 and 7.5 m for E5a. σ is defined in Attachment D, 4.1.3.6.4.

URA,SF

3.7.3.1.3.5.5 Galileo σ . Galileo σ shall not exceed 2.5 m for both E1 and E5a.

BGD BGD Note.: Galileo σ is defined in Attachment D, 4.1.3.6.5 BGD .

3.7.3.1.3.5.6 Galileo fault rates R and R . Galileo R shall not exceed 2×10-5/h sat const sat and Galileo R shall not exceed 1×10-4/h. const Note.: Fault rates are defined in Appendix B, 3.4.1.1.2.

3.7.3.1.3.6 Continuity. The probability of losing Galileo OS SIS availability from a slot of the nominal 24-slot constellation due to unscheduled interruption, shall

not exceed the following limit:

3.7.3.1.3.7 Coverage. The Galileo OS shall cover the surface of the earth up to an altitude of 30.48 km.

3.7.3.1.3.8 Radio frequency (RF) characteristics. All Galileo satellites shall broadcast Galileo OS signals E1, E5a and E5b.

Note 1.: E5a and E5b signals are multiplexed together through an AltBOC scheme and transmitted at the E5 carrier frequency centred at 1191.795 MHz.

AltBOC modulation allows E5a signal components and E5b signal components to be recovered separately by using a QPSK receiver centred on the individual E5a and E5b frequencies.

Note 2.: AltBOC modulation is specified in Appendix B, 3.1.3.1.1.3.13.

Note 3.: Detailed Galileo signals RF characteristics are specified in Appendix B,

3.1.3.1.1.

3.7.3.1.3.8.1 E1 radio frequency (RF) characteristics 93CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.7.3.1.3.8.1.1 E1 carrier frequency. Each Galileo satellite shall broadcast E1 signal at the carrier frequency of 1575.420 MHz using CDMA.

3.7.3.1.3.8.1.2 E1 signal spectrum. The Galileo signal power on E1 shall be contained within a 24.552 MHz band centred on the E1 frequency.

3.7.3.1.3.8.1.3 E1 signal polarization. The transmitted E1 RF signal shall be right-hand circularly polarized.

3.7.3.1.3.8.1.4 E1 minimum signal power level. Each Galileo satellite shall broadcast an E1 navigation signal with sufficient power such that, at all unobstructed locations near the ground from which the satellite is observed at an elevation angle of 5 degrees or higher, the level of the received RF signal at the antenna port of a 3 dBi linearly-polarized antenna shall not be less than –157.9 dBW for all antenna orientations orthogonal to the direction of propagation.

3.7.3.1.3.8.1.5 E1 maximum signal power level. Each Galileo satellite shall broadcast an E1 navigation signal such that the level of the received RF signal at the antenna port of a 3 dBi linearly-polarized antenna shall not exceed –151.45 dBW.

3.7.3.1.3.8.1.6 E1 signal modulation. The E1 signal shall be a composite binary offset carrier (CBOC) generated by multiplexing a wideband binary offset carrier (BOC) signal BOC(6,1) with a narrowband signal BOC(1,1) in such a way that 1/11 of the power is allocated, in average, to the high frequency component.

Note. : CBOC modulation is specified in Appendix B, 3.1.3.1.1.2.7.

3.7.3.1.3.8.2 E5a radio frequency (RF) characteristics Note.: Additional information concerning the overall E5 signal modulation is given in the European GNSS (Galileo) Open Service Signal-In-Space Interface Control Document (Issue 2.0), dated January 2021 (hereinafter referred to as “Galileo OS SIS ICD”).

3.7.3.1.3.8.2.1 E5a carrier frequency. Each Galileo satellite shall broadcast E5a signal at the carrier frequency of 1 176.45 MHz using CDMA.

3.7.3.1.3.8.2.2 E5a signal spectrum. The Galileo signal power on E5a shall be contained within a 20.460 MHz band centred on the E5a frequency.

3.7.3.1.3.8.2.3 E5a signal polarization. The transmitted E5a RF signal shall be right- hand circularly polarized.

3.7.3.1.3.8.2.4 E5a minimum signal power level. Each Galileo satellite shall broadcast an E5a navigation signal with sufficient power such that, at all unobstructed locations near the ground from which the satellite is observed at an elevation angle of 5 degrees or higher, the level of the received RF signal at the antenna port of a 3 dBi linearly-polarized 94CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 antenna shall not be less than –155.90 dBW for all antenna orientations orthogonal to the direction of propagation.

3.7.3.1.3.8.2.5 E5a maximum signal power level. Each Galileo satellite shall broadcast an E5a navigation signal such that the level of the received RF signal at the antenna port of a 3 dBi linearly-polarized antenna shall not exceed –149.45 dBW.

3.7.3.1.3.8.2.6 E5a signal modulation. The E5a signal shall be generated from Modulo- 2 addition of the E5a navigation data stream with the 10.23 megachips per second E5a data channel ranging code (E5a-I), and the 10.23 megachips per second E5a pilot channel ranging code (E5a-Q).

3.7.3.1.3.8.3 E5b radio frequency (RF) characteristics Note.: Additional information concerning the overall E5 signal modulation is given in Galileo OS SIS ICD.

3.7.3.1.3.8.3.1 E5b carrier frequency. Each Galileo satellite shall broadcast E5b signal at the carrier frequency of 1207.14 MHz using CDMA.

3.7.3.1.3.8.3.2 E5b signal spectrum. The Galileo signal power on E5b shall be contained within a 20.460 MHz band centred on the E5b frequency.

3.7.3.1.3.8.3.3 E5b signal polarization. The transmitted E5b RF signal shall be right- hand circularly polarized.

3.7.3.1.3.8.3.4 E5b minimum signal power level. Each Galileo satellite shall broadcast an E5b navigation signal with sufficient power such that, at all unobstructed locations near the ground from which the satellite is observed at an elevation angle of 5 degrees or higher, the level of the received RF signal at the antenna port of a 3 dBi linearly-polarized antenna shall not be less than –155.90 dBW for all antenna orientations orthogonal to the direction of propagation.

3.7.3.1.3.8.3.5 E5b maximum signal power level. Each Galileo satellite shall broadcast an E5b navigation signal such that the level of the received RF signal at the antenna port of a 3 dBi linearly-polarized antenna shall not exceed –149.45 dBW.

3.7.3.1.3.8.3.6 E5b signal modulation. The E5b signal shall be generated from Modulo- 2 addition of the E5b navigation data stream with the 10.23 megachips per second E5b data channel ranging code (E5b-I), and the 10.23 megachips per second E5b pilot channel ranging code (E5b-Q).

3.7.3.1.3.9 Galileo system time. Galileo system time (GST) shall be referenced to UTC BIPM (UTC as coordinated by the International Bureau of Weights and Measures).

Note.: Further details on GST are specified in Appendix B, 3.1.3.4.1.

95CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.7.3.1.3.10 Coordinate system. The Galileo coordinate system shall be Galileo Terrestrial Reference Frame (GTRF).

Note.: GTRF details are specified in Appendix B, 3.1.3.5.2.

3.7.3.1.3.11 Navigation information. The navigation data transmitted by the

satellites shall include the necessary information to determine: a) satellite time of transmission; b) satellite position; c) satellite health; d) satellite clock correction; e) ionospheric delay effects;

f) time transfer to UTC; and g) constellation status.

Note.: Structure and contents of data are specified in Appendix B, 3.1.3.1.2 and 3.1.3.1.3, respectively.

3.7.3.1.4 BDS Open Service (BDS OS) (B1I, B1C, B2a) Note 1.: The BDS OS signals are broadcast in three frequency bands identified as B1I, B1C and B2a. The single-frequency BDS OS is based on any one of the B1I, B1C or B2a signals. The dual-frequency BDS OS is based on a combination of the B1C and B2a signals.

Note 2.: BDS OS signals B1I, B1C and B2a are broadcast by all BDS-3 (BDS third- phase) medium earth orbit (MEO) and inclined geosynchronous orbit (IGSO) satellites.

Note 3.: All requirements specified in this section are based on the BDS-3 constellation configuration of 24 MEO and 3 IGSO satellites.

3.7.3.1.4.1 Space and control segment accuracy Note. ; The following accuracy standards do not include atmospheric or receiver errors as described in Attachment D, 4.1.4.2. They only apply under the condition that the aircraft receiver uses healthy satellites.

3.7.3.1.4.1.1 Positioning accuracy. The BDS position errors shall not exceed the

following limits:

96CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.7.3.1.4.1.2 Time transfer accuracy. The BDS OS time transfer error shall not exceed 50 nanoseconds, 95 per cent of the time.

3.7.3.1.4.1.3 Range domain accuracy. The BDS range domain error shall not exceed

the following limits:

3.7.3.1.4.2 Availability. The BDS OS availability shall be as follows:

97CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.: Availability applies under the condition that the aircraft receiver uses healthy satellites.

3.7.3.1.4.3 Reliability. The BDS OS reliability relative to the 15 m range error requirement in 3.7.3.1.4.2 shall be within the following limits: a) reliability — at least 99.94 per cent (global average); and b) reliability — at least 99.79 per cent (worst single point average).

Note. : Reliability applies under the condition that the satellite is broadcasting a healthy indication.

3.7.3.1.4.4 Probability of major service failure Note.: The standards apply under the condition that the satellite is broadcasting a healthy indication.

3.7.3.1.4.4.1 Probability of a satellite major service failure condition (Psat). The probability that the BDS OS SIS user range error of any satellite will exceed the not-to-exceed (NTE) tolerance without an alert received at the user receiver antenna within 300 seconds, shall not exceed 1×10-5.

3.7.3.1.4.4.2 Probability of a common-cause major service failure condition (Pconst).

The probability that the BDS OS SIS user range error of two or more satellites will exceed the NTE tolerance due to a common fault without an alert received at the user receiver antenna within 300 seconds, shall not exceed 6×10-5.

Note 1.: For B1I signals, the NTE tolerance is defined to be 4.42 times the upper bound 98CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 of the URA range corresponding to the URA index (URAI) value being broadcast in D1 navigation messages, as described in Appendix B, 3.1.4.1.3.1.2.

Note 2.: For B1C and B2a signals, the NTE tolerance is defined to be 4.42 times the signal-in-space accuracy (SISA) value calculated as described in Appendix B,

3.1.4.2.5.

Note 3. The mapping between BDS B1I SIS status and BDS B1I flags contained in the navigation data message is specified in Appendix B, 3.1.4.1.3.1.3. The mapping between BDS B1C and B2a SIS status and BDS B1C and B2a flags contained in the navigation data message is specified in Appendix B, 3.1.4.1.3.2.7.2.

3.7.3.1.4.5 Continuity. The probability of losing BDS OS SIS availability from a slot of the nominal 27-slot constellation due to unscheduled interruption, shall not

exceed the following limits:

Note.: Continuity applies under the condition that the satellite is broadcasting a healthy indication.

3.7.3.1.4.6 Coverage. BDS OS shall cover the surface of the earth up to an altitude of 1000 km.

3.7.3.1.4.7 Radio frequency (RF) characteristics Note.: Detailed BDS OS signals RF characteristics are specified in Appendix B, 3.1.4.1.1.

3.7.3.1.4.8 B1I radio frequency (RF) characteristics

3.7.3.1.4.8.1 B1I carrier frequency. Each BDS-3 MEO or IGSO satellite shall broadcast a BDS B1I OS signal at the carrier frequency of 1 561.098 MHz using code division multiple access (CDMA).

3.7.3.1.4.8.2 B1I signal spectrum. The BDS OS B1I signal power shall be contained within a ±2.046 MHz band (1 559.052 – 1 563.144 MHz) centred on the 1 561.098 MHz frequency.

3.7.3.1.4.8.3 B1I signal polarization. The transmitted B1I RF signal shall be right- hand circularly polarized.

3.7.3.1.4.8.4 B1I signal power levels

3.7.3.1.4.8.4.1 Each BDS-3 MEO satellite shall broadcast a B1I navigation signal with sufficient power such that, at all unobstructed locations near the ground 99CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 from which the satellite is observed at an elevation angle of 5 degrees or higher, the level of the received RF signal at the antenna port of a 3 dBi linearly-polarized antenna is within the range of –163 dBW to 154.8 dBW for all antenna orientations orthogonal to the direction of propagation.

3.7.3.1.4.8.4.2 Each BDS-3 IGSO satellite shall broadcast a B1I navigation signal with sufficient power such that, at all unobstructed locations near the ground from which the satellite is observed at an elevation angle of 5 degrees or higher, the level of the received RF signal at the antenna port of a 3 dBi linearly-polarized antenna is within the range of –163 dBW to 156.5 dBW for all antenna orientations orthogonal to the direction of propagation.

3.7.3.1.4.8.5 B1I signal modulation. The BDS OS B1I signal shall be binary phase shift key (BPSK) modulated.

3.7.3.1.4.9 B1C radio frequency (RF) characteristics

3.7.3.1.4.9.1 B1C carrier frequency. Each BDS-3 MEO or IGSO satellite shall broadcast a BDS OS B1C signal at the carrier frequency of 1 575.42 MHz using CDMA.

3.7.3.1.4.9.2 B1C signal spectrum. The BDS OS signal power on B1C shall be contained within a 32.736 MHz band centred on the B1C frequency.

3.7.3.1.4.9.3 B1C signal polarization. The transmitted B1C RF signal shall be right- hand circularly polarized.

3.7.3.1.4.9.4 B1C signal power levels

3.7.3.1.4.9.4.1 Each BDS-3 MEO satellite shall broadcast a B1C navigation signal with sufficient power such that, at all unobstructed locations near the ground from which the satellite is observed at an elevation angle of 5 degrees or higher, the level of the received RF signal at the antenna port of a 3 dBi linearly-polarized antenna is within the range of –159 dBW to 152.5 dBW for all antenna orientations orthogonal to the direction of propagation.

3.7.3.1.4.9.4.2 Each BDS-3 IGSO satellite shall broadcast a B1C navigation signal with sufficient power such that, at all unobstructed locations near the ground from which the satellite is observed at an elevation angle of 5 degrees or higher, the level of the received RF signal at the antenna port of a 3 dBi linearly-polarized antenna is within the range of –161 dBW to 153.5 dBW for all antenna orientations orthogonal to the direction of propagation.

3.7.3.1.4.9.5 B1C signal modulation. The B1C signal shall comprise two components, known as B1C data component and B1C pilot component.

The B1C data component shall be sine-phased binary offset carrier

(BOC) modulated with the Modulo-2 addition of the ranging code and 100CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 the navigation data. The B1C pilot component shall be quadrature multiplexed BOC (QMBOC) modulated with the ranging code. Ranging codes on B1C data component and B1C pilot component shall have the same chipping rate of 1.023 megachips per second.

Note.: Additional information concerning B1C modulation is given in the BeiDou Navigation Satellite System Signal In Space Interface Control Document Open Service Signal B1C (Version 1.0), dated December 2017 (hereinafter referred to as “BDS OS B1C ICD”), 4.2.

3.7.3.1.4.10 B2a radio frequency (RF) characteristics

3.7.3.1.4.10.1 B2a carrier frequency. Each BDS-3 MEO and IGSO satellite shall broadcast a BDS OS B2a signal at the carrier frequency of 1 176.45 MHz using CDMA.

3.7.3.1.4.10.2 B2a signal spectrum. The BDS OS signal power on B2a shall be contained within a 20.46 MHz band centred on the B2a frequency.

3.7.3.1.4.10.3 B2a signal polarization. The transmitted B2a RF signal shall be right- hand circularly polarized.

3.7.3.1.4.10.4 B2a signal power levels

3.7.3.1.4.10.4.1 Each BDS-3 MEO satellite shall broadcast a B2a navigation signal with sufficient power such that, at all unobstructed locations near the ground from which the satellite is observed at an elevation angle of 5 degrees or higher, the level of the received RF signal at the antenna port of a 3 dBi linearly-polarized antenna is within the range of –156 dBW to -148.5 dBW for all antenna orientations orthogonal to the direction of propagation.

3.7.3.1.4.10.4.2 Each BDS-3 IGSO satellite shall broadcast a B2a navigation signal with sufficient power such that, at all unobstructed locations near the ground from which the satellite is observed at an elevation angle of 5 degrees or higher, the level of the received RF signal at the antenna port of a 3 dBi linearly-polarized antenna is within the range of –158 dBW to -150.5 dBW for all antenna orientations orthogonal to the direction of propagation.

3.7.3.1.4.10.5 B2a signal modulation. The B2a signal shall comprise two components, known as B2a data component and B2a pilot component. The B2a data component shall be BPSK modulated with the Modulo-2 addition of the ranging code and the navigation data. The B2a pilot component shall be BPSK modulated with the ranging code. Ranging codes on B2a data component and B2a pilot component shall have the same chipping rate of 10.23 megachips per second.

Note. : Additional information concerning B2a modulation is given in the BeiDou Navigation Satellite System Signal In Space Interface Control Document Open Service Signal B2a (Version 1.0), dated December 2017 (hereinafter 101CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 referred to as “BDS OS B2a ICD”), 4.2.

3.7.3.1.4.11 BDS time. BDS time (BDT) shall be referenced to UTC as maintained by the National Time Service Center (NTSC), Chinese Academy of Sciences.

Note.: BDT details are specified in Appendix B, 3.1.4.4.

3.7.3.1.4.12 Coordinate system. The BDS coordinate system shall be BeiDou Coordinate System (BDCS).

Note.: BDCS details are specified in Appendix B, 3.1.4.5.

3.7.3.1.4.13 Navigation information. The navigation data transmitted by the satellites

shall include the necessary information to determine: a) satellite time of transmission; b) satellite position; c) satellite health; d) satellite clock correction; e) ionospheric delay effects; f) time transfer to UTC; and g) constellation status.

3.7.3.2 Reserved.

3.7.3.3 Aircraft-based augmentation system (ABAS)

3.7.3.3.1 Performance. The ABAS function combined with one or more of the core satellite constellations and both a fault-free GNSS receiver and fault-free aircraft system used for the ABAS function shall meet the requirements for accuracy, integrity, continuity and availability as stated in 3.7.2.4.

Note.: For GNSS receivers supporting the ABAS function, the requirements to be resistant to interference, as specified in 3.7.4, apply

3.7.3.3.2 Advanced receiver autonomous integrity monitoring (ARAIM). If the ABAS function implements ARAIM using integrity support data (ISD), the function shall meet the requirements in Appendix B, 3.4.1.

3.7.3.4 Satellite-based augmentation system (SBAS)- GAGAN

3.7.3.4.1 Performance. GAGAN combined with one or more of the other GNSS 102CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 elements and a fault-free receiver shall meet the requirements for system accuracy, integrity, continuity and availability for the intended operation as stated in 3.7.2.4.

Note.: GAGAN complements the core satellite constellation(s) by increasing accuracy, integrity, continuity and availability of navigation provided within a service area, typically including multiple aerodromes

3.7.3.4.1.1 GAGAN combined with one or more of the other GNSS elements and a fault-free receiver shall meet the requirements for signal-in-space integrity as stated in 3.7.2.4, throughout the GAGAN coverage area.

Note.: Message Types 27 or 28 is used to comply with the integrity requirements in the coverage area. See Appendix B, 3.5.7.4.7. Additional guidance on the rationale and interpretation of this requirement is provided in Attachment D,

3.3.

3.7.3.4.2 Functions. GAGAN shall perform one or more of the following functions: a) Intentionally left Blank b) GNSS satellite status: determine and transmit the GNSS satellite health status (Appendix B, 3.5.7.3);

c) Basic differential correction: provide GNSS satellite ephemeris and clock corrections (fast and long-term) to be applied to the pseudo- range measurements from satellites (Appendix B, 3.5.7.4); and d) Precise differential correction: determine and transmit the Ionospheric corrections (Appendix B, 3.5.7.5).

3.7.3.4.2.1 Intentionally left blank

3.7.3.4.3 Intentionally left blank

3.7.3.4.4 Service area. The GAGAN service area shall be a defined area where GAGAN meets the requirements of 3.7.2.4 and supports the corresponding approved operations.

Note 1.: The coverage area is that area within which the SBAS broadcast can be received (e.g. the geostationary satellite footprints).

Note 2.: SBAS coverage and service areas are discussed in Attachment D, 6.2.

3.7.3.4.5 RF characteristics Note.: Detailed RF characteristics are specified in Appendix B, 3.5.2.

3.7.3.4.5.1 Carrier frequency. The carrier frequency shall be 1575.42 MHz.

103CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.7.3.4.5.2 Signal spectrum. At least 95 per cent of the broadcast power shall be contained within a ±12 MHz band centred on the L1 frequency. The bandwidth of the L1 signal transmitted by an SBAS satellite shall be at least

2.2 MHz.

3.7.3.4.5.3 Signal power level

3.7.3.4.5.3.1 Each GAGAN satellite shall broadcast navigation signals with sufficient power such that, at all unobstructed locations near the ground from which the satellite is observed at an elevation angle of 5 degrees or higher, the level of the received RF signal at the output of a 3 dBi linearly polarized antenna is within the range of –161 dBW to –153 dBW for all antenna orientations orthogonal to the direction of propagation.

3.7.3.4.5.3.2 Each SBAS satellite broadcasting an SBAS L1 signal placed in orbit after 31 December 2013 shall comply with broadcast navigation signals with sufficient power such that, at all unobstructed locations near the ground from which the satellite is observed at or above the minimum elevation angle for which a trackable GEO signal needs to be provided, the level of the received RF signal at the output of the antenna specified in Appendix B, Table B-87 is at least –164.0 dBW.

3.7.3.4.5.4 Polarization. The broadcast signal on L1 shall be right-hand circularly polarized.

3.7.3.4.5.5 Modulation. The transmitted sequence on L1 shall be the Modulo-2 addition of the navigation message at a rate of 500 symbols per second and the 1 023 bit pseudo-random noise code. It shall then be BPSK-modulated onto the carrier at a rate of 1.023 megachips per second.

3.7.3.4.5.6 Minimum elevation angle. The minimum elevation angle used to determine GEO coverage shall not be less than 5 degrees for a user near the ground.

3.7.3.4.5.7 The level of a received GAGAN RF signal at the output of a 0 dBic antenna located near the ground shall not exceed –152.5 dBW.

3.7.3.4.6 GAGAN network time (GNT). The difference between GNT and GPS time shall not exceed 50 nanoseconds.

3.7.3.4.7 Navigation information. The navigation data transmitted by the

satellites shall include the necessary information to determine: a) GAGAN satellite time of transmission; b) GAGAN satellite position; c) Corrected satellite time for all satellites; d) Corrected satellite position for all satellites;

e) Ionospheric propagation delay effects;

104CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 f) User position integrity; g) Time transfer to UTC; and h) Service level status.

Note.: Structure and contents of data are specified in Appendix B, 3.5.3 and

3.5.4, respectively.

3.7.3.5 Ground-based augmentation system (GBAS) and ground-based regional augmentation system (GRAS)

Note: Except where specifically annotated, reference to approach with vertical guidance (APV) means APV-I and APV-II.

3.7.3.5.1 Performance. GBAS combined with one or more of the other GNSS elements and a fault-free GNSS receiver shall meet the requirements for system accuracy, continuity, availability and integrity for the intended operation as stated in 3.7.2.4.

Note: GBAS is intended to support all types of approach, landing, departure and surface operations and may support en-route and terminal operations. The following SARPs are developed to support Category I precision approach, approach with vertical guidance, and a GBAS positioning service. In order to achieve interoperability and enable efficient spectrum utilization, it is intended that the data broadcast is the same for all operations.

3.7.3.5.2 Functions. GBAS shall perform the following functions: a) provide locally relevant pseudo-range corrections; b) provide GBAS-related data; c) provide final approach segment data when supporting precision approach;

d) provide predicted ranging source availability data; and e) provide integrity monitoring for GNSS ranging sources.

3.7.3.5.3 Coverage

3.7.3.5.3.1 Category I precision approach and approach with vertical guidance. The GBAS coverage to support each Category I precision approach or approach with vertical guidance shall be as follows, except where topographical features dictate and operational requirements

permit:

3.7.3.5.3.1.1 laterally, beginning at 140 m (450 ft) each side of the landing threshold 105CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 point/fictitious threshold point (LTP/FTP) and projecting out ±35 degrees either side of the final approach path to 28 km (15 NM) and ±10 degrees either side of the final approach path to 37 km (20 NM);

and

3.7.3.5.3.1.2 vertically, within the lateral region, up to the greater of 7 degrees or 1.75 promulgated glide path angle (GPA) above the horizontal with an origin at the glide path interception point (GPIP) and 0.45 GPA above the horizontal or to such lower angle, down to 0.30 GPA, as required, to safeguard the promulgated glide path intercept procedure. This coverage applies between 30 m (100 ft) and 3 000 m (10 000 ft) height above threshold (HAT).

Note.: LTP/FTP and GPIP are defined in Appendix B, 3.6.4.5.1.

3.7.3.5.3.1.1 Recommendation.: For Category I precision approach, the data broadcast as specified in 3.7.3.5.4 should extend down to 3.7 m (12 ft) above the runway surface.

3.7.3.5.3.1.3 Recommendation.: The data broadcast should be omni-directional when required to support the intended applications.

Note.: Guidance material concerning coverage for Category I precision approach and APV is provided in Attachment D, 7.3.

3.7.3.5.3.2 Approach services supporting autoland and guided take-off. The minimum additional GBAS service volume to support approach operations that include automatic landing and roll-out, including during guided take-off, shall be as follows, except where operational

requirements permit: a) Horizontally, within a sector spanning the width of the runway beginning at the stop end of the runway and extending parallel with the runway centre line towards the LTP to join the minimum service volume as described in 3.7.3.5.3.1.

b) Vertically, between two horizontal surfaces one at 3.7 m (12 ft) and the other at 30 m (100 ft) above the runway centre line to join the minimum service volume as described in 3.7.3.5.3.1.

Note.: Guidance material concerning the approach service volume is provided in Attachment D, 7.3.

3.7.3.5.3.3 GBAS positioning service. The service volume for the GBAS positioning service shall be where the data broadcast can be received and the positioning service meets the requirements of 3.7.2.4 and supports the corresponding approved operations 106CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.7.3.5.4 Note.: Guidance material concerning the positioning service volume is

provided in Attachment D, 7.3.Data broadcast characteristics

Note: RF characteristics are specified in Appendix B, 3.6.2.

3.7.3.5.4.1 Carrier frequency. The data broadcast radio frequencies used shall be selected from the radio frequencies in the band 108 to 117.975 MHz.

The lowest assignable frequency shall be 108.025 MHz and the highest assignable frequency shall be 117.950 MHz. The separation between assignable frequencies (channel spacing) shall be 25 kHz.

Note: Guidance material on ILS/VOR/GBAS frequency assignments and geographical separation criteria is given Attachment D, 7.2.1 in the Handbook on Radio Frequency Spectrum Requirements for Civil Aviation (Doc 9718, Volume II).

3.7.3.5.4.2 Access technique. A time division multiple access (TDMA) technique shall be used with a fixed frame structure. The data broadcast shall be assigned one to eight slots.

Note.: Two slots is the nominal assignment. Some GBAS facilities that use multiple VHF data broadcast (VDB) transmit antennas to improve VDB coverage may require assignment of more than two time slots.

Guidance on the use of multiple antennas is given in Attachment D,

7.12.4;

3.7.3.5.4.3 Modulation. GBAS data shall be transmitted as 3-bit symbols, modulating the data broadcast carrier by D8PSK, at a rate of 10 500 symbols per second.

3.7.3.5.4.4 Data broadcast RF field strength and polarization Note.: GBAS can provide a VHF data broadcast with either horizontal (GBAS/H) or elliptical (GBAS/E) polarization that employs both horizontal polarization (HPOL) and vertical polarization (VPOL) components. Aircraft using a VPOL component will not be able to conduct operations with GBAS/H equipment. Relevant guidance material is provided in Attachment D, 7.1.

3.7.3.5.4.4.1 GBAS/H

3.7.3.5.4.4.1.1 A horizontally polarized signal shall be broadcast.

107CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.7.3.5.4.4.1.2 The effective radiated power (ERP) shall provide for a horizontally polarized signal with a minimum field strength of 215 microvolts per metre (–99 dBW/m2) and a maximum field strength of 0.350 volts per metre (–35 dBW/m2) within the GBAS coverage volume. The field strength shall be measured as an average over the period of the synchronization and ambiguity resolution field of the burst. The RF phase offset between the HPOL and any VPOL components shall be such that the minimum signal power defined in Appendix B, 3.6.8.2.2.3 is achieved for HPOL users throughout the coverage volume.

3.7.3.5.4.4.1.3 GBAS/E Recommendation.—An elliptically polarized signal should be broadcast whenever practical.

3.7.3.5.4.4.1.4 When an elliptically polarized signal is broadcast, the horizontally polarized component shall meet the requirements in 3.7.3.5.4.4.1.2, and the effective radiated power (ERP) shall provide for a vertically polarized signal with a minimum field strength of 136 microvolts per metre (–103 dBW/m2) and a maximum field strength of 0.221 volts per metre (–39 dBW/m2) within the GBAS coverage volume. The field strength shall be measured as an average over the period of the synchronization and ambiguity resolution field of the burst. The RF phase offset between the HPOL and VPOL components, shall be such that the minimum signal power defined in Appendix B, 3.6.8.2.2.3 is achieved for HPOL and VPOL users throughout the coverage volume.

Note.: The minimum and maximum field strengths in 3.7.3.5.4.4.1.2 and

3.7.3.5.4.4.2.2 are consistent with a minimum receiver sensitivity of – 87 dBm and minimum distance of 200 m (660 ft) from the transmitter antenna for a coverage range of 43 km (23 NM).

3.7.3.5.4.5 Power transmitted in adjacent channels. The amount of power during transmission under all operating conditions when measured over a 25 kHz bandwidth centered on the ith adjacent channel shall not exceed the values shown in Table 3.7.3.5-1.

108CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 NOTES.:

1. The maximum power applies if the authorized transmitter power exceeds 150 W.

2. The relationship is linear between single adjacent points designated by the adjacent channels identified above.

3.7.3.5.4.6 Unwanted emissions. Unwanted emissions, including spurious and out- of- band emissions, shall be compliant with the levels shown in Table 3.7.3.5-

2. Total power in any VDB harmonic or discrete signal shall not be greater than –53 dBm.

NOTES. —

1. The maximum unwanted emission level (absolute power) applies if the authorized transmitter power exceeds 150 W.

2. The relative unwanted emission level is to be computed using the same bandwidth for desired and unwanted signals. This may require conversion of the measurement for unwanted signals done using the bandwidth indicated in the maximum unwanted emission level column of this table.

3. This value is driven by measurement limitations. Actual performance is expected to be better.

4. The relationship is linear between single adjacent points designated by the adjacent channels identified above.

109CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.7.3.5.5 Navigation information. The navigation data transmitted by GBAS shall

include the following information: a) pseudo-range corrections, reference time and integrity data; b) GBAS-related data; c) final approach segment data when supporting precision approach; and d) predicted ranging source availability data.

Note.: Structure and contents of data are specified in Appendix B, 3.6.3.

3.7.3.6 Aircraft GNSS receiver

3.7.3.6.1 The aircraft GNSS receiver shall process the signals of those GNSS elements that it intends to use as specified in , Appendix B, 3.1 (for GPS), Appendix B, 3.2 (for GLONASS), Appendix B, 3.3 (for combined GPS and GLONASS), Appendix B, 3.5 (for GAGAN) and Appendix B, 3.6 (for GBAS).

3.7.4 Resistance to interference

3.7.4.1 GNSS shall comply with performance requirements defined in 3.7.2.4 and Appendix B, 3.7 in the presence of the interference environment defined in Appendix B, 3.7.

Note.: GPS and GLONASS operating in the frequency band 1559 – 1610 MHz are classified by the ITU as providing a radio navigation satellite service

(RNSS) and aeronautical radio navigation service (ARNS) and are afforded special spectrum protection status for RNSS. In order to achieve the performance objectives for precision approach guidance to be supported by the GNSS and its augmentations, RNSS/ARNS is intended to remain the only global allocation in the 1 559 –1 610 MHz band and emissions from systems in this and adjacent frequency bands are intended to be tightly controlled by national and/or international regulation.

3.7.5 Database Note.: SARPs applicable to aeronautical data are provided in relevant CARS for Aeronautical charts, Air Traffic Management, Aerodrome and Ground Aids and Aeronautical Information Service.

3.7.5.1 Aircraft GNSS equipment that uses a database shall provide a means to: a) Update the electronic navigation database; and 110CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 b) Determine the Aeronautical Information Regulation and Control

(AIRAC) effective dates of the aeronautical database.

Note.: Guidance material on the need for a current navigation database in aircraft GNSS equipment is provided in Attachment D, 11.

3.8 Intentionally left blank

3.9 System characteristics of airborne ADF receiving systems

3.9.1 Accuracy of bearing indication

3.9.1.1 The bearing given by the ADF system shall not be in error by more than plus or minus 5 degrees with a radio signal from any direction having a field strength of 70 microvolts per metre or more radiated from an LF/MF NDB and in the presence also of an unwanted signal from a direction 90 degrees

from the wanted signal and: a) on the same frequency and 15 dB weaker; or b) plus or minus 2 kHz away and 4 dB weaker; or c) plus or minus 6 kHz or more away and 55 dB stronger.

Note.: The above bearing error is exclusive of aircraft magnetic compass error.

Sd/- (Vir Vikram Yadav) Director General of Civil Aviation 111CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Table A. DME/VOR and DME/ILS channeling and pairing Channel pairing DMR Parameters Interrogation Reply DME VHF Frequenc Pulse code Frequency Pulse Chann Frequenc y MHz DME/N MHz codes el y MHz Micro Sec Micro Sec Numbe r *1X - 1025 12 962 12 **1Y - 1025 36 1088 30 *2X - 1026 12 963 12 **2Y - 1026 36 1089 30 *3X - 1027 12 964 12 **3Y - 1027 36 1090 30 *4X - 1028 12 965 12 **4Y - 1028 36 1091 30 *5X - 1029 12 966 12 **5Y - 1029 36 1092 30 *6X - 1030 12 967 12 **6Y - 1030 36 1093 30 *7X - 1031 12 968 12 **7Y - 1031 36 1094 30 *8X - 1032 12 969 12 **8Y - 1032 36 1095 30 *9X - 1033 12 970 12 **9Y - 1033 36 1096 30 *10X - 1034 12 971 12 **10Y - 1034 36 1097 30 *11X - 1035 12 972 12 **11Y - 1035 36 1098 30 *12X - 1036 12 973 12 **12Y - 1036 36 1099 30 *13X - 1037 12 974 12 **13Y - 1037 36 1100 30 *14X - 1038 12 975 12 **14Y - 1038 36 1101 30 *15X - 1039 12 976 12 **15Y - 1039 36 1102 30 *16X - 1040 12 977 12 **16Y - 1040 36 1103 30 17X 108.00 1041 12 978 12 17Y 108.05 1041 36 1104 30 18X 108.10 1042 12 979 12 18Y 108.15 1042 36 1105 30 19X 108.20 1043 12 980 12 19Y 108.25 1043 36 1106 30 112CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Channel pairing DMR Parameters Interrogation Reply DME VHF Frequenc Pulse code Frequency Pulse Chann Frequenc y MHz DME/N MHz codes el y MHz Micro Sec Micro Numbe Sec r 20X 108.30 1044 12 981 12 20Y 108.35 1044 36 1107 30 21X 108.40 1045 12 982 12 21Y 108.45 1045 36 1108 30 22X 108.50 1046 12 983 12 22Y 108.55 1046 36 1109 30 23X 108.60 1047 12 984 12 23Y 108.65 1047 36 1110 30 24X 108.70 1048 12 985 12 24Y 108.75 1048 36 1111 30 25X 108.80 1049 12 986 12 25Y 108.85 1049 36 1112 30 26X 108.90 1050 12 987 12 26Y 108.95 1050 36 1113 30 27X 109.00 1051 12 988 12 27Y 109.05 1051 36 1114 30 28X 109.10 1052 12 989 12 28Y 109.15 1052 36 1115 30 29X 109.20 1053 12 990 12 29Y 109.25 1053 36 1116 30 30X 109.30 1054 12 991 12 30Y 109.35 1054 36 1117 30 31X 109.40 1055 12 992 12 31Y 109.45 1055 36 1118 30 32X 109.50 1056 12 993 12 32Y 109.55 1056 36 1119 30 33X 109.60 1057 12 994 12 33Y 109.65 1057 36 1120 30 34X 109.70 1058 12 995 12 34Y 109.75 1058 36 1121 30 35X 109.80 1059 12 996 12 35Y 109.85 1059 36 1122 30 36X 109.90 1060 12 997 12 36Y 109.95 1060 36 1123 30 37X 110.00 1061 12 998 12 37Y 110.05 1061 36 1124 30 38X 110.10 1062 12 999 12 38Y 110.15 1062 36 1125 30 113CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Channel pairing DMR Parameters Interrogation Reply DME VHF Frequenc Pulse code Frequency Pulse Chann Frequenc y MHz DME/N MHz codes el y MHz Micro Sec Micro Sec Numbe r 39X 110.20 1063 12 1000 12 39Y 110.25 1063 36 1126 30 40X 110.30 1064 12 1001 12 40Y 110.35 1064 36 1127 30 41X 110.40 1065 12 1002 12 41Y 110.45 1065 36 1128 30 42X 110.50 1066 12 1003 12 42Y 110.55 1066 36 1129 30 43X 110.60 1067 12 1004 12 43Y 110.65 1067 36 1130 30 44X 110.70 1068 12 1005 12 44Y 110.75 1068 36 1131 30 45X 110.80 1069 12 1006 12 45Y 110.85 1069 36 1132 30 46X 110.90 1070 12 1007 12 46Y 110.95 1070 36 1133 30 47X 111.00 1071 12 1008 12 47Y 1110.5 1071 36 1134 30 48X 111.10 1072 12 1009 12 48Y 111.15 1072 36 1135 30 49X 111.20 1073 12 1010 12 49Y 111.25 1073 36 1136 30 50X 111.30 1074 12 1011 12 50Y 111.35 1074 36 1137 30 51X 111.40 1075 12 1012 12 51Y 111.45 1075 36 1138 30 52X 111.50 1076 12 1013 12 52Y 111.55 1076 36 1139 30 53X 111.60 1077 12 1014 12 53Y 111.65 1077 36 1140 30 54X 111.70 1078 12 1015 12 54Y 111.75 1078 36 1141 30 55X 111.80 1079 12 1016 12 55Y 111.85 1079 36 1142 30 56X 111.90 1080 12 1017 12 56Y 111.95 1080 36 1143 30 57X 112.00 1081 12 1018 12 57Y 112.05 1081 36 1144 30 114CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Channel pairing DMR Parameters Interrogation Reply DME VHF Frequenc Pulse code Frequency Pulse Chann Frequenc y MHz DME/N MHz codes el y MHz Micro Sec Micro Sec Numbe r 58X 112.10 1082 12 1019 12 58Y 112.15 1082 36 1145 30 59X 112.20 1083 12 1020 12 59Y 112.25 1083 36 1146 30 **60X - 1084 12 1021 12 **60Y - 1084 36 1147 30 **61X - 1085 12 1022 12 **61Y - 1085 36 1148 30 **62X - 1086 12 1023 12 **62Y - 1086 36 1149 30 **63X - 1087 12 1024 12 **63Y - 1087 36 1150 30 **64X - 1088 12 1151 12 **64Y - 1088 36 1025 30 **65X - 1089 12 1152 12 **65Y - 1089 36 1026 30 **66X - 1090 12 1153 12 **66Y - 1090 36 1027 30 **67X - 1091 12 1154 12 **67Y - 1091 36 1028 30 **68X - 1092 12 1155 12 **68Y - 1092 36 1029 30 **69X - 1093 12 1156 12 **69Y - 1093 36 1030 30 70X 112.30 1094 12 1157 12 **70Y 112.35 1094 36 1031 30 71X 112.40 1095 12 1158 12 **71Y 112.45 1095 36 1032 30 72X 112.50 1096 12 1159 12 **72Y 112.55 1096 36 1033 30 73X 112.60 1097 12 1160 12 **73Y 112.65 1097 36 1034 30 74X 112.70 1098 12 1161 12 **74Y 112.75 1098 36 1035 30 75X 112.80 1099 12 1162 12 **75Y 112.85 1099 36 1036 30 76X 112.90 1100 12 1163 12 **76Y 112.95 1100 36 1037 30 115CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Channel pairing DMR Parameters Interrogation Reply DME VHF Frequenc Pulse code Frequency Pulse Chann Frequenc y MHz DME/N MHz codes el y MHz Micro Sec Micro Sec Numbe r 77X 113.00 1101 12 1164 12 **77Y 113.05 1101 36 1038 30 78X 113.10 1102 12 1165 12 **78Y 113.15 1102 36 1039 30 79X 113.20 1103 12 1166 12 **79Y 113.25 1103 36 1040 30 80X 113.30 1104 12 1167 12 80Y 113.35 1104 36 1041 30 81X 113.40 1105 12 1168 12 81Y 113.45 1105 36 1042 30 82X 113.50 1106 12 1169 12 82Y 113.55 1106 36 1043 30 83X 113.60 1107 12 1170 12 83Y 113.65 1107 36 1044 30 84X 113.70 1108 12 1171 12 84Y 113.75 1108 36 1045 30 85X 113.80 1109 12 1172 12 85Y 113.85 1109 36 1046 30 86X 113.90 1110 12 1173 12 86Y 113.95 1110 36 1047 30 87X 114.00 1111 12 1174 12 87Y 114.05 1111 36 1048 30 88X 114.10 1112 12 1175 12 88Y 114.15 1112 36 1049 30 89X 114.20 1113 12 1176 12 89Y 114.25 1113 36 1050 30 90X 114.30 1114 12 1177 12 90Y 114.35 1114 36 1051 30 91X 114.40 1115 12 1178 12 91Y 114.45 1115 36 1052 30 92X 114.50 1116 12 1179 12 92Y 114.55 1116 36 1053 30 93X 114.60 1117 12 1180 12 93Y 114.65 1117 36 1054 30 94X 114.70 1118 12 1181 12 94Y 114.75 1118 36 1055 30 95X 114.80 1119 12 1182 12 95Y 114.85 1119 36 1056 30 116CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Channel pairing DMR Parameters Interrogation Reply DME VHF Frequenc Pulse code Frequency Pulse Chann Frequenc y MHz DME/N MHz codes el y MHz Micro Sec Micro Sec Numbe r 96X 114.90 1120 12 1183 12 96Y 114.95 1120 36 1057 30 97X 115.00 1121 12 1184 12 97Y 115.05 1121 36 1058 30 98X 115.10 1122 12 1185 12 98Y 115.15 1122 36 1059 30 99X 115.20 1123 12 1186 12 99Y 115.25 1123 36 1060 30 100X 115.30 1124 12 1187 12 100Y 115.35 1124 36 1061 30 101X 115.40 1125 12 1188 12 101Y 115.45 1125 36 1062 30 102X 115.50 1126 12 1189 12 102Y 115.55 1126 36 1063 30 103X 115.60 1127 12 1190 12 103Y 115.65 1127 36 1064 30 104X 115.70 1128 12 1191 12 104Y 115.75 1128 36 1065 30 105X 115.80 1129 12 1192 12 105Y 115.85 1129 36 1066 30 106X 115.90 1130 12 1193 12 106Y 115.95 1130 36 1067 30 107X 116.00 1131 12 1194 12 107Y 116.05 1131 36 1068 30 108X 116.10 1132 12 1195 12 108Y 116.15 1132 36 1069 30 109X 116.20 1133 12 1196 12 109Y 116.25 1133 36 1070 30 110X 116.30 1134 12 1197 12 110Y 116.35 1134 36 1071 30 111X 116.40 1135 12 1198 12 111Y 116.45 1135 36 1072 30 112X 116.50 1136 12 1199 12 112Y 116.55 1136 36 1073 30 113X 116.60 1137 12 1200 12 113Y 116.65 1137 36 1074 30 114X 116.70 1138 12 1201 12 114Y 116.75 1138 36 1075 30 117CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 DMR Parameters Channel pairing Interrogation Reply DME VHF Frequenc Pulse code Frequency Pulse Chann Frequenc y MHz DME/N MHz codes el y MHz Micro Sec Micro Sec Numbe r 115X 116.80 1139 12 1202 12 115Y 116.85 1139 36 1076 30 116X 116.90 1140 12 1203 12 116Y 116.95 1140 36 1077 30 117X 117.00 1141 12 1204 12 117Y 117.05 1141 36 1078 30 118X 117.10 1142 12 1205 12 118Y 117.15 1142 36 1079 30 119X 117.20 1143 12 1206 12 119Y 117.25 1143 36 1080 30 120X 117.30 1144 12 1207 12 120Y 117.35 1144 36 1081 30 121X 117.40 1145 12 1208 12 121Y 117.45 1145 36 1082 30 122X 117.50 1146 12 1209 12 122Y 117.55 1146 36 1083 30 123X 117.60 1147 12 1210 12 123Y 117.65 1147 36 1084 30 124X 118.70 1148 12 1211 12 **124Y 117.75 1148 36 1085 30 125X 117.80 1149 12 1212 12 **125Y 117.85 1149 36 1086 30 126X 117.90 1150 12 1213 12 **126Y 117.95 1150 36 1087 30 *These channels are reserved exclusively for national allotments.

**These channels may be used for national allotment on a secondary basis.

118CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Appendix - A Appendix – A - Intentionally left blank 119CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 APPENDIX B. TECHNICAL SPECIFICATIONS FOR THE GLOBAL NAVIGATION SATELLITE SYSTEM (GNSS) 1 DEFINITIONS GBAS/E. A ground-based augmentation system transmitting an elliptically-polarized VHF data broadcast.

GBAS/H. A ground-based augmentation system transmitting a horizontally- polarized VHF data broadcast.

Receiver. A subsystem that receives GNSS signals and includes one or more sensors.

Reserved (bits/words/fields). Bits/words/fields that are not allocated, but which are reserved for a particular GNSS application.

S Maximum desired VHF data broadcast signal power at the VHF data broadcast max. receiver input. This power at the receiver input is computed from the maximum RF field strength defined in Chapter 3, 3.7.3.5.4.4 for the desired VHF data broadcast signal as received by an ideal isotropic antenna minus the minimum aircraft implementation loss. It is used to determine the VHF data broadcast interference immunity to adjacent channel signals (3.6.8.2.2.6) and to signals from sources outside the 108.000 – 117.975 MHz band (3.6.8.2.2.8).

Spare (bits/words/fields). Bits/words/fields that are not allocated or reserved, and which are available for future allocation.

Note.: All spare bits are set to zero.

2 GENERAL Note.: The following technical specifications supplement the provisions of

Chapter 3, 3.7.

3 GNSS ELEMENTS

3.1 Core constellations

3.1.1 GLOBAL POSITIONING SYSTEM (GPS) STANDARD POSITIONING SERVICE (SPS) (L1 AND L5)

3.1.1.1 NON-AIRCRAFT ELEMENTS

3.1.1.1.1 L1 coarse acquisition (c/a) signal radio frequency (rf) characteristics

3.1.1.1.1.1 Carrier phase noise. The carrier phase noise spectral density of the unmodulated L1 carrier shall be such that a phase locked loop of 10 Hz one-sided noise bandwidth is able to track the carrier to an accuracy of 0.1 radian (1 sigma).

3.1.1.1.1.2 Spurious emissions. In-band spurious emissions shall be at least 40 dB below the unmodulated L1 carrier over the allocated channel bandwidth.

120CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.1.1.1.3 Correlation loss. The loss in the recovered signal power due to imperfections in the L1 C/A signal modulation and waveform distortion shall not exceed 0.6 dB for all GPS-II satellite generations and 0.3 dB for all GPS-III satellite generations.

Note.: The loss in signal power is the difference between the broadcast power in an allocated bandwidth and the signal power recovered by a noise-free, loss-free receiver with 1-chip correlator spacing and the same bandwidth.

3.1.1.1.1.4 L1 C/A code generation and timing. Each C/A code pattern Gi(t) shall be formed by the Modulo-2 sum of two 1 023-bit linear patterns, G1 and G2i.

The G2i sequence shall be formed by effectively delaying the G2 sequence by an integer number of chips. The G1 and G2 sequences shall be generated by 10-stage shift registers having the following polynomials

as referred to in the shift register input: a) G1: X10 + X3 + 1; and b) G2: X10 + X9 + X8 + X6 + X3 + X2 + 1.

The initialization vector for the G1 and G2 sequences shall be “1111111111”. The G1 and G2 registers shall be clocked at a 1.023 MHz rate. Timing relationships related to the C/A code shall be as shown in Figure B-1.

Note.: Additional information on code phase assignments is given in IS-GPS- 200K.

3.1.1.1.2 L1 data structure. The legacy navigation (LNAV) message shall be formatted as shown in Figure B-2. Each page, as shown in Figure B-6, shall utilize a basic format of a 1 500-bit-long frame with up to 5 subframes, each of 300 bits in length. All words shall be transmitted most significant bit (MSB) first.

Note.: The bit allocations depicted for subframes 4 and 5 in Figure B-6 apply only to satellites broadcasting PRN codes 1 – 32. See IS-GPS-200K for the bit allocations of subframes 4 and 5 for satellites broadcasting PRN codes 33 – 63.

3.1.1.1.2.1 Subframe structure. Each subframe and/or page of a subframe shall start with a telemetry (TLM) word followed by a handover word (HOW). The HOW shall be followed by 8 data words. Each word in each frame shall contain 6 parity bits. The TLM word and HOW formats shall be as shown in Figures B-3 and B-4, respectively.

3.1.1.1.2.2 End/start of week. At the end/start of week:

121CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 a) the cyclic paging of subframes 1 through 5 shall restart with subframe 1 regardless of which subframe was last transmitted prior to the end/start of week; and b) the cycling of 25 pages of subframes 4 and 5 shall restart with page 1 of each of the subframes, regardless of which page was transmitted prior to the end/start of week. All upload and page cutovers shall occur on frame boundaries (i.e. Modulo 30 seconds relative to the end/start of week).

Note.: New data in subframes 4 and 5 may start to be transmitted with any of the 25 pages of these subframes.

3.1.1.1.2.3 Data parity. Words 1 through 10 of subframes 1 through 5 shall each contain 6 parity bits as their least significant bits (LSBs). In addition, two non-information bearing bits shall be provided as bits 23 and 24 of words 2 and 10 for parity computation purposes.

3.1.1.1.2.4 Telemetry (TLM) word. Each TLM word shall be 30 bits long, occur every 6 seconds in the data frame and be the first word in each subframe. The TLM format shall be as shown in Figure B-3. Each TLM word shall begin with a preamble, followed by 16 reserved bits and 6 parity bits.

3.1.1.1.2.5 Handover word (HOW). The HOW shall be 30 bits long and shall be the second word in each subframe/page, immediately following the TLM word.

A HOW shall occur every 6 seconds in the data frame. The HOW format and content shall be as shown in Figure B-4. The full time-of-week (TOW) count shall consist of the 19 LSBs of the 29-bit Z-count (3.1.1.1.2.6). The HOW shall begin with the 17 MSBs of the TOW count. These 17 bits shall correspond to the TOW count at the 1.5-second epoch that occurs at the start (leading edge) of the next following subframe.

3.1.1.1.2.5.1 Bit 18. On satellites designed by configuration code 001, bit 18 shall be an “alert” flag. When this flag is raised (bit 18 is a “1”), it shall indicate to the user that the satellite user range accuracy (URA) may be worse than indicated in subframe 1 and that use of the satellite is at the user’s risk.

3.1.1.1.2.5.2 Bit 19. Bit 19 shall be reserved.

3.1.1.1.2.5.3 Bits 20, 21 and 22. Bits 20, 21 and 22 of the HOW shall provide the identification (ID) of the subframe in which that particular HOW is the second word. The ID code shall be as defined below:

122CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.1.1.2.6 Satellite Z-count. Each satellite shall internally derive a 1.5-second epoch that shall contain a convenient unit for precisely counting and communicating time. Time stated in this manner shall be referred to as a Z-count. The Z-count shall be provided to the user as a 29-bit binary number consisting of two parts as follows.

3.1.1.1.2.6.1 Time-of-week (TOW) count. The binary number represented by the 19 LSBs of the Z-count shall be referred to as the TOW count and is defined as being equal to the number of 1.5-second epochs that have occurred since the transition from the previous week. The count shall be short- cycled such that the range of the TOW count is from 0 to 403 199 1.5 second epochs (equaling one week) and shall be reset to zero at the end of each week. The TOW count’s zero state shall be the 1.5- second epoch that is coincident with the start of the present week. A truncated version of the TOW count, consisting of its 17 MSBs, shall be contained in the HOW of the L1 downlink data stream. The relationship between the actual TOW count and it’s truncated HOW version shall be as indicated in Figure B-5.

Note.: The above-mentioned epoch occurs at (approximately) midnight Saturday night/Sunday morning, where midnight is defined as 0000 hours on the UTC scale which is nominally referenced to the Greenwich Meridian.

3.1.1.1.2.6.2 Week count. The 10 MSBs of the Z-count shall be a binary representation of the sequential number assigned to the present GPS week (Modulo

1024). The range of this count shall be from 0 to 1 023. Its zero state shall be that week which starts with the 1.5-second epoch occurring at

(approximately) the UTC zero time point (3.1.4). At the expiration of GPS week number 1 023, the GPS week number shall roll over to zero. The previous 1 024 weeks in conversions from GPS time to a calendar date shall be accounted for by the user.

3.1.1.1.3 L1 DATA CONTENT 123CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.1.1.3.1 Subframe 1 — satellite clock and health data. The content of words 3 through 10 of subframe 1 shall contain the clock parameters and other data as indicated in Table B-1. The parameters in a data set shall be valid during the interval of time in which they are transmitted and shall remain valid for an additional period of time after transmission of the next data set has started.

3.1.1.1.3.1.1 Week number. The 10 MSBs of word 3 shall contain the 10 MSBs of the 29-bit Z-count and shall represent the number of the current GPS week at the start of the data set transmission interval with all zeros indicating week “zero.” The GPS week number shall increment at each end/start of week epoch.

3.1.1.1.3.1.2 User range accuracy (URA). Bits 13 through 16 of word 3 provide a URA index, which prescribes the predicted satellite URA as shown in Table B-

2. The integrity assured URA (IAURA) shall be the upper bound URA value corresponding to the URA index, as shown in the last column of Table B-

2.

Note 1.: The URA does not include error estimates due to inaccuracies of the single-frequency ionospheric delay model.

Note 2.: The URA is a statistical indicator of the contribution of the apparent clock and ephemeris prediction accuracies to the ranging accuracies obtainable with a specific satellite based on historical data.

Note 3.: The nominal URA value for each URA index is also shown in Table B-

2. The nominal URA is suitable for use as a prediction of the RMS signal-in-space pseudo-range errors for accuracy-related purposes.

124CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.1.1.3.1.3 Health. The transmitting satellite 6-bit health indication shall be provided by bits 17 through 22 of word 3. The MSB shall indicate a summary of the health of the navigation data, where:

a) 0 = all navigation data are valid; and b) 1 = some of the navigation data are not valid.

The 5 LSBs shall indicate the health of the signal components in accordance with Table B-3. The health indication shall be provided relative to the capabilities of each satellite as designated by the configuration code

provided in page 25 of subframe 4. Any satellite that does not have a certain capability shall be indicated as “healthy” if the lack of this capability is inherent in its design or it has been configured into a mode which is normal from a receiver standpoint and does not require that capability.

Additional health data shall be given in subframes 4 and 5.

Note.: The data given in subframe 1 may differ from that shown in subframes 4 and/or 5 of other satellites since the latter may be updated at a different time.

125CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.1.1.3.1.4 Issue of data, clock (IODC). Bits 23 and 24 of word 3 in subframe 1 shall be the 2 MSBs of the 10-bit IODC term. Bits 1 through 8 of word 8 in subframe 1 shall contain the 8 LSBs of the IODC. The IODC shall indicate the issue number of data set. The transmitted IODC shall be different from any value transmitted by the satellite during the preceding 6 hours.

Note.: The relationship between the IODC and the Issue of Data, Ephemeris

(IODE) terms is defined in 3.1.1.1.3.2.2.

3.1.1.1.3.1.5 Estimated group delay differential. Bits 17 through 24 of word 7 shall contain the correction term, TGD, to account for the effect of satellite group delay differential.

Note.: TGD does not include any C/A to P(Y) code relative group delay error.

3.1.1.1.3.1.6 Satellite clock correction parameters. Bits 9 through 24 of word 8, bits 1 through 24 of word 9, and bits 1 through 22 of word 10 shall contain the parameters needed by the users for apparent satellite clock correction (toc, af2, af1 and af0).

3.1.1.1.3.1.7 Reserved data fields. Reserved data fields shall be as indicated in Table B-4. All reserved data fields shall support valid parity within their respective words.

3.1.1.1.3.2 Subframes 2 and 3 — satellite ephemeris data. Subframes 2 and 3 shall contain the ephemeris representation of the transmitting satellite.

126CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.1.1.3.2.1 Ephemeris parameters. The ephemeris parameters shall be as indicated in Table B-5. For each parameter in subframe 2 and 3, the number of bits, the scale factor of the LSB, the range, and the units shall be as specified in Table B-6.

3.1.1.1.3.2.2 Issue of data, ephemeris (IODE). The IODE shall be an 8-bit number equal to the 8 LSBs of the 10-bit IODC of the same data set. The IODE shall be

provided in both subframes 2 and 3 for the purpose of comparison with the 8 LSBs of the IODC term in subframe 1. Whenever these three terms do not match, as a result of a data set cutover, new data shall be collected.

The transmitted IODE shall be different from any value transmitted by the satellite during the preceding six hours (Note 1). Any change in the subframe 2 and 3 data shall be accomplished in concert with a change in both IODE words. Change to new data sets shall occur only on hour boundaries except for the first data set of a new upload. Additionally, the toe value, for at least the first data set transmitted by a satellite after an upload, shall have a small negative offset relative to the nominal location on an hour boundary (midpoint of the curve fit interval) (Note 2).

127CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 128CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note 1. The IODE/IODC terms provide the receiver with a means for detecting any changes in the ephemeris/clock representation parameters.

Note 2. The first data set may change (3.1.1.1.2.2) at any time during the hour and therefore may be transmitted by the satellite for less than 1 hour.

3.1.1.1.3.2.3 Curve fit intervals. Bit 17 in word 10 of subframe 2 shall be a “fit interval” flag which indicates the curve-fit interval used in determining the ephemeris parameters, as follows:

0 = 4 hours, 1 = greater than 4 hours.

A fit interval flag of zero (0) shall indicate the satellite is undergoing normal operations. A fit interval flag of one (1) shall indicate the satellite is undergoing short- or long-term extended operations.

3.1.1.1.3.3 Subframes 4 and 5 — support data. Both subframes 4 and 5 shall be sub commutated 25 times each. With the possible exception of “reserved” 129CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 pages and explicit repeats, each page shall contain different data in words 3 through 10. Subframes 4 and 5 shall contain the data listed in Table B-

7.

Note.: Subframes 4 and 5 from satellites broadcasting PRN codes 1 – 32 contain almanac and health data for 32 satellites. Subframes 4 and 5 from satellites broadcasting PRN codes 33 – 63 contain almanac and health data for only 31 satellites. See IS-GPS-200K for full details on the content and bit allocations of the data in subframes 4 and 5.

3.1.1.1.4 L5 SIGNAL RADIO FREQUENCY (RF) CHARACTERISTICS

3.1.1.1.4.1 Carrier phase noise. The carrier phase noise spectral density of the unmodulated L5 carrier shall be such that a phase locked loop of 10 Hz one-sided noise bandwidth can track the carrier to an accuracy of 0.1 radians RMS.

3.1.1.1.4.2 Spurious emissions. In-band spurious emissions shall be at least 40 dB below the unmodulated L5 carrier over the allocated channel bandwidth.

3.1.1.1.4.3 Correlation loss. The loss in the recovered signal power due to imperfections in the L5 signal modulation and waveform distortion shall not exceed 0.6 dB.

Note.: The loss in signal power is the difference between the broadcast power in an allocated bandwidth and the signal power recovered by a noise-free, loss-free receiver with 1-chip correlator spacing and the same bandwidth.

130CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.1.1.4.4 L5 carrier components. L5 shall have two carrier components modulated

by separate bit trains: the I5-code and the Q5-code (see Table B-8).

3.1.1.1.4.4.1 The I5 and Q5 carriers shall be in phase quadrature (within ±100 milliradians) and the Q5 carrier shall be lagging the I5 carrier by 90 degrees.

3.1.1.1.4.5 Code generation. The I5 and Q5 code patterns I5(t) and Q5(t) shall each i i be formed by the Modulo-2 sum of two extended bit patterns clocked at a

10.23 MHz rate, XA(t) and XBI(nIi, t) or XA(t) and XBQ(nQi, t), where nI i i i and nQ are the initial states of XBI and XBQ for satellite i. i i i

3.1.1.1.4.5.1 The XA code shall be a code of length 8 190 with initial condition of all “ones” that is short-cycled 1 chip before its natural ending and restarted to run over a period of 1 millisecond (synchronized with the L1 frequency C/A code) for a total of 10 230 chips.

3.1.1.1.4.5.2 The XBI and XBQ codes shall be codes of length 8 191 with initial i i conditions that are specified in ISGPS-705F, Tables 3-Ia and Ib. The XBI i and XBQ codes shall not be short-cycled and shall be restarted to run over i a period of 1 millisecond for a total of 10 230 chips.

3.1.1.1.4.5.3 The generating polynomials for the XA and XBI and XBQ codes shall be: i i a) XA: X13 + X12 + X10 + X9 + 1; and b) XBI and XBQ: X13 + X12 +X8 + X7 + X6 + X4 + X3 + X + 1. i i Note.: Additional details on code phase assignments are specified in the GPS Interface Specification, IS-GPS-705F.

131CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.1.1.4.6 Navigation data modulation. The L5 navigation data (CNAV) bit train shall be encoded at a rate of 2 symbols per bit using a convolution code with a constraint length of 7 to yield 100 symbols per second (sps). The 100 sps symbols shall then be modulated (Modulo-2 addition) with the 10-bit Neuman-Hofman code “0000110101” clocked at 1 kHz. The resulting symbol sequence shall be Modulo-2 added with the I5 PRN code and used to modulate the L5 in-phase carrier.

3.1.1.1.4.7 Signal timing. The XA code shall be synchronized with the L1 frequency C/A code. The XBIi and XBQi codes shall be synchronized with the XA code.

3.1.1.1.4.8 Group delay differential. The absolute value of the mean differential delay between the radiated L1 and L5 signals shall not exceed 30.0 nanoseconds. The total variation about the mean (random plus non- random variations) shall not exceed 3.0 nanoseconds (95 per cent probability).

Note.: Inter-signal corrections (ISCs) are provided in the navigation data, to correct for the bias component of the differential delay.

3.1.1.1.5 L5 DATA STRUCTURE

3.1.1.1.5.1 Forward error correction. The L5 CNAV bit train shall be rate 1/2 convolution encoded with a forward error correction (FEC) code of constraint length 7.

3.1.1.1.5.2 Navigation data structure. The L5 CNAV data shall be provided in a set of six-second 300-bit long messages.

3.1.1.1.5.2.1 Each message shall contain a cyclic redundancy check (CRC) parity block of 24 bits protecting the entire 300-bit message.

3.1.1.1.5.2.2 Each message shall be composed of the following ordered fields: an 8-bit preamble (“10001011”), the 6- bit PRN number of the transmitting satellite, a 6-bit message type ID (range 0 to 63), the 17-bit message time-of-week

(TOW) count, a 1-bit alert flag (bit 38), the data field (238 bits), and the 24- bit CRC parity block.

3.1.1.1.5.2.3 The TOW count multiplied by 6 shall provide the satellite time in seconds at the start of the next 6-second message.

3.1.1.1.5.2.4 Bit 38 shall be an “alert flag” where the value “1” indicates that the signal URA components may be worse than indicated in the associated message types and that use of the signal is at the user’s risk.

132CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.1.1.6 L5 (CNAV) DATA CONTENT

3.1.1.1.6.1 CNAV message types. The CNAV data broadcasted on L5 shall contain the message types listed in Table B-9.

Note.: See IS-GPS-705F for details on the content and application of the data contained in each message type.

3.1.1.1.6.2 Message Type 10 shall contain the elevation-dependent (ED) component of the user range accuracy (URAED) index corresponding to the maximum elevation-dependent error expected for the current ephemeris curve fit for the worst-case location within the satellite footprint.

Note.: At the best location within the satellite footprint (i.e. nominally directly below the satellite along its nadir vector), the corresponding URAED is zero (see Table B-10).

3.1.1.1.6.3 Message Types 30 to 37 shall contain the non-elevation-dependent (NED)

URA component indices: URA index, URA index, and URA NED0 NED1 NED2 index, respectively, for the transmitting satellite.

The URA value shall be related to the URA index according to NED0 NED0 133CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Table B-11.

The URA value shall be related to the URA index as:

NED1 NED1 where N = 14 + URA index NED1

The URA value shall be related to the URA index as:

NED2 NED2 where N = 14 + URA index NED2 Note.: URAED, URANED0, URANED1 and URANED2 are used to compute the integrity assured URA (IAURA).

134CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 135CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 136CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.1.2 DEFINITIONS OF PROTOCOLS FOR DATA APPLICATION Note.: This section defines the inter-relationships of the data broadcast message parameters. It provides definitions of parameters that are not transmitted, but are used by either or both non-aircraft and aircraft elements, and that define terms applied to determine the navigation 137CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 solution and its integrity.

3.1.1.2.1 GPS PROTOCOLS FOR SINGLE-FREQUENCY L1 USERS

3.1.1.2.1.1 Parity algorithm. GPS parity algorithms are defined as indicated in Table B-12.

3.1.1.2.1.2 Satellite clock correction parameters. GPS system time t is defined as: t = t – (Δt ) sv sv L1 where t = GPS system time (corrected for beginning and end-of-week crossovers); t = effective satellite PRN code phase time at transmission of the message;

sv (Δt ) = the satellite PRN code phase offset for the L1 C/A signal; sv L1 (Δt ) = Δt - T sv L1 sv GD where Δt = a + a (t – t ) + a (t – t )2+ Δt; sv f0 f1 oc f2 oc r TGD is contained in subframe 1; a , a and a and t , are contained in subframe 1; and f0 f1 f2 oc Δt = the relativistic correction term (seconds) r 138CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Δt = Fe √A sin E r k where e and A are contained in subframes 2 and 3;

Ek is defined in Table B-13; and where μ = WGS-84 universal gravitational parameter (3.986005 × 1014 m3/s2) c = the speed of light in a vacuum (2.99792458 × 108 m/s) Note.: The value of t is intended to account for the beginning or end-of-week crossovers. That is, if the quantity t-toc is greater than 302 400 seconds, subtract 604 800 seconds from t. If the quantity t-toc is less than –302 400 seconds, add 604 800 seconds to t.

3.1.1.2.1.3 Satellite position. The current satellite position (X , Y , Z ) is defined as k k k shown in Table B-13.

3.1.1.2.1.4 Ionospheric correction. The ionospheric correction (T ) is defined as: iono, L1 where 139CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.1.2.1.4.1 The terms used in computation of ionospheric delay are as follows: a) Satellite transmitted terms α = the coefficients of a cubic equation representing the amplitude n of the vertical delay (4 coefficients = 8 bits each) obtained from page 18 of subframe 4 β = the coefficients of a cubic equation representing the period of n the model (4 coefficients = 8 bits each) obtained from page 18 of subframe 4 b) Receiver generated terms E = elevation angle between the user and satellite (semi-circles) A = azimuth angle between the user and satellite, measured clockwise positive from the true North (semi-circles) ϕ = user geodetic latitude (semi-circles) WGS-84 u λ = user geodetic longitude (semi-circles) WGS-84 u GPS time = receiver computed system time c) Computed terms x = phase (radians) 140CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 F = obliquity factor (dimensionless) t = local time (seconds) ϕ = geomagnetic latitude of the earth projection of the ionospheric m intersection point (mean ionospheric height assumed 350 km) (semi- circles) λ = geomagnetic longitude of the earth projection of the ionospheric i intersection point (semi-circles) ϕ = geomagnetic latitude of the earth projection of the ionospheric i intersection point (semi-circles) ψ = earth’s central angle between user position and earth projection of ionospheric intersection point (semi-circles) 141CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.1.2.2 GPS PROTOCOLS FOR SINGLE-FREQUENCY (L5) AND DUAL- FREQUENCY (L1/L5) USERS

3.1.1.2.2.1 Parity algorithm. The CNAV CRC word shall be calculated in the forward direction using a seed of 0. The sequence of 24 bits (p1, p2,..., p24) shall be generated from the sequence of information bits (m1, m2,..., m276)

using the following generating polynomial:

142CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 where g = 1 for 0, 1, 3, 4, 5, 6, 7, 10, 11, 14, 17, 18, 23, 24, and i 0 otherwise.

Note.: See IS-GPS-705F for full details on the CNAV parity algorithm.

3.1.1.2.2.2 Satellite clock correction. GPS system time t shall be as follows: t = t – Δt sv sv where Δt is computed using the equations defined in 3.1.1.2.1.2 and sv parameters from CNAV message Types 10 and 11 (for the relativistic correction term) and 30 through 37.

Note.: Additional terms apply to the satellite clock correction for single- frequency L5 users. Section 3.1.1.2.2.5 shows the satellite PRN code phase offset for the single frequency L5 I5 and L5 Q5 users, and t = t – (Δt )L5 I5 or t = t – (Δt ) L5 Q5.

sv sv sv sv

3.1.1.2.2.3 Satellite position. The current satellite position (X , Y , Z ) shall be k k k calculated as shown in Table B-14.

Note.: The ephemeris parameters: toe, ΔA, Ȧ, Δn0, Δṅ0, M0-n, en, ωn, Ω0- n, ΔΩ̇ , i0-n, i0-̇n,Cis-n, Cic-n, Crs-n, Crc-n, Cus-n, and Cucn, are

provided in CNAV message Types 10 and 11.

3.1.1.2.2.4 Integrity assured user range accuracy (IAURA)

3.1.1.2.2.4.1 Composite IAURA. The composite IAURA value shall be the RSS of an elevation-dependent (ED) component and a non-elevation-dependent

(NED) component.

3.1.1.2.2.4.2 Elevation-dependent (ED) accuracy estimate. An adjusted ED IAURA value (in metres) shall be computed from the upper bound value of the URAED obtained from message Type 10, Table B-10, and the equation:

where E is the satellite elevation angle in degrees (E ≥ 0)

3.1.1.2.2.4.3 Non-elevation-dependent (NED) accuracy estimate. The non-elevation- dependent IAURA value (in metres) shall be computed using the upper bound value of URANED0 and the equation:

143CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 when t – t + 604,800×(WN – WN ) ≤ 93,600 seconds op op and when t – t + 604,800×(WN – WN ) > 93,600 seconds op op where t = GPS system time WN, WN , t , URA , URA , URA are obtained from message op op NED0 NED1 NED2 Types 10, 30 to 37, and Table B-11.

3.1.1.2.2.5 Estimated L5 group delay differential for single-frequency users.

Note.: Inter-signal biases for L1/L5 dual-frequency users are corrected via the ionosphere-free pseudo-range described in 3.1.1.2.2.7.

3.1.1.2.2.5.1 For the single-frequency L5 I5 user, the satellite clock time, corrected for the L1/L5 inter-signal bias, shall be as follows:

3.1.1.2.2.5.2 For the single-frequency L5 Q5 user, the satellite clock time, corrected for the L1/L5 inter-signal bias, shall be as follows:

Note.:TGD, ISCL5I5 and ISCL5Q5 are provided in CNAV message Type 30.

3.1.1.2.2.6 Ionospheric correction. For L5, the single-frequency ionospheric correction defined in 3.1.1.2.1.4 shall be multiplied by ɣ , (T = 15 iono, L5 ɣ T ), where ɣ = (f /f )2 = (1 575.42/1 176.45)2 = (154/115)2.

15 iono, L1 15 L1 L5

3.1.1.2.2.7 L1/L5 ionospheric correction for dual-frequency users.

3.1.1.2.2.7.1 The ionosphere-free pseudo-range for the dual-frequency (L1 C/A and L5 I5) user shall be as follows: where PR = pseudo-range corrected for ionospheric effects, 144CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 PRi = pseudo-range measured on the channel indicated by the subscript, ISCi = inter-signal correction for the channel indicated by the subscript, provided in CNAV message Type 30, T = L1 P(Y) and L2 P(Y) inter-signal correction, provided in CNAV message GD Type 30, c = speed of light, and ɣ = (f /f )2 = (1 575.42/1 176.45)2 = (154/115)2.

15 L1 L5

3.1.1.2.2.7.2 The ionosphere-free pseudo-range for the dual-frequency (L1 C/A and L5 Q5) user shall be as follows: where PR, PRi, ISCi, T , c and ɣ are as defined above.

GD 15 145CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 146CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.1.3 AIRCRAFT ELEMENTS

3.1.1.3.1 GPS RECEIVER

3.1.1.3.1.1 Reserved.

3.1.1.3.1.2 Satellite tracking. The receiver shall provide the capability to continuously track a minimum of four satellites and generate a position solution based upon those measurements.

3.1.1.3.1.3 Doppler shift. The receiver shall be able to compensate for dynamic Doppler shift effects on nominal SPS signal carrier phase and C/A code measurements. The receiver shall compensate for the Doppler shift that is unique to the anticipated application.

3.1.1.3.1.4 Resistance to interference. The receiver shall meet the requirements for resistance to interference as specified in Chapter 3, 3.7.

3.1.1.3.1.5 Application of clock and ephemeris data. The receiver shall ensure that it is using the correct ephemeris and clock data before providing any position solution. For LNAV data, the receiver shall monitor the IODC and IODE values, and shall update ephemeris and clock databased upon a detected change in one or both of these values. For CNAV data, the receiver shall monitor the toe, toc and top values and shall update ephemeris and clock data based upon a detected change in any of these values.

3.1.1.4 TIME GPS time shall be referenced to a UTC (as maintained by the U.S. Naval Observatory) zero time-point defined as midnight on the night of 5 January 1980/morning of 6 January 1980. The largest unit used in stating GPS time shall be 1 week, defined as 604 800 seconds. The GPS time scale shall be maintained to be within 1 microsecond of UTC (Modulo 1 second) after correction for the integer number of leap seconds difference. The navigation data shall contain the requisite data for relating GPS time to UTC.

3.1.2 Global navigation satellite system (GLONASS) channel of standard accuracy (CSA) (L1/L3) Note.:— In this section, the term GLONASS refers to all satellites in the constellation. Standards relating only to GLONASSM satellites are qualified accordingly.

3.1.2.1 NON-AIRCRAFT ELEMENTS

3.1.2.1.1 L1OF (L1 OPEN SERVICE FDMA) RF CHARACTERISTICS 147CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.:Additional information on the L1OF RF characteristics is given in the GLONASS Navigational radio signal in bands L1, L2 Interface Control Document (Edition 5.1), dated 2008 (hereinafter referred to as “GLONASS FDMA ICD”).

3.1.2.1.1.1 Carrier frequencies. The nominal values of L1 carrier frequencies shall

be as defined by the following expressions: f = f + kΔf k1 01 1 where k = –7, …, 0, 1, …, 6 are carrier numbers (frequency channels) of the signals transmitted by GLONASS satellites in the L1 sub-band;

f = 1 602 MHz; and 01 Δf = 0.5625 MHz.

1 Carrier frequencies shall be coherently derived from a common on-board time/frequency standard. The nominal value of frequency, as observed on the ground, shall be equal to 5.0 MHz. The carrier frequency of a GLONASS satellite shall be within ±2 × 10–11 relative to its nominal value fk.

Note 1.— The nominal values of carrier frequencies for carrier numbers k are given in Table B-15.

Note 2.— For GLONASS-M satellites, the L2 channel of standard accuracy (CSA) navigation signals will occupy the 1 242.9375–1 251.6875 MHz ±0.511 MHz bandwidth as defined by the following expressions: f = f + kΔf , k2 02 2 f = 1 246 MHz; Δf = 0.4375 MHz.

02 2 For any given value of k the ratio of carrier frequencies of L1 and L2 sub-bands will be

equal to:

148CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.2.1.1.2 Carrier phase noise. The phase noise spectral density of the unmodulated carrier shall be such that a phase locked loop of 10 Hz one-sided noise bandwidth provides the accuracy of carrier phase tracking not worse than

0.1 radian (1 sigma).

3.1.2.1.1.3 GLONASS pseudo-random code generation. The pseudo-random ranging code shall be a 511-bit sequence that is sampled at the output of the seventh stage of a 9-stage shift register. The initialisation vector to generate this sequence shall be “11111111”. The generating polynomial that corresponds to the 9-stage shift register shall be:

G(x) = 1 + x5 + x9.

3.1.2.1.1.4 Spurious emissions. The power of the transmitted RF signal beyond the GLONASS allocated bandwidth shall not be more than –40 dB relative to the power of the unmodulated carrier.

Note 1.— GLONASS satellites launched during 1998 to 2005 and beyond use filters limiting out-of-band emissions to the harmful interference limit contained in Recommendation ITU R RA.769 for the 1 660 – 1 670 MHz band.

149CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note 2.— GLONASS satellites launched beyond 2005 use filters limiting out-of- band emissions to the harmful interference limit contained in Recommendation ITU-R RA.769 for the 1 610.6 – 1 613.8 MHz and 1 660 – 1 670 MHz bands.

3.1.2.1.1.5 Correlation loss. The loss in the recovered signal power due to imperfections in the signal modulation and waveform distortion shall not exceed 0.8 dB.

Note.: The loss in signal power is the difference between the broadcast power in a 1.022 MHz bandwidth and the signal power recovered by a noise-free, loss-free receiver with 1-chip correlator spacing and a

1.022 MHz bandwidth.

3.1.2.1.2 L1OF (L1 OPEN SERVICE FDMA) DATA STRUCTURE Note.: Additional information concerning the data structure is given in the GLONASS FDMA ICD.

3.1.2.1.2.1 General. The navigation message shall be transmitted as a pattern of digital data which are coded by Hamming code and transformed into relative code. Structurally, the data pattern shall be generated as continuously repeating superframes. The superframe shall consist of the frames and the frames shall consist of the strings. The boundaries of strings, frames and superframes of navigation messages from different GLONASS satellites shall be synchronized within 2 milliseconds.

3.1.2.1.2.2 Superframe structure. The superframe shall have a 2.5-minute duration and shall consist of 5 frames. Within each superframe a total content of non-immediate information (almanac for 24 GLONASS satellites) shall be transmitted.

Note.:Superframe structure with indication of frame numbers in the superframe and string numbers in the frames is shown in Figure B-7.

3.1.2.1.2.3 Frame structure. Each frame shall have a 30-second duration and shall consist of 15 strings. Within each frame the total content of immediate information (ephemeris and time parameters) for given satellite and a part of nonimmediate information (almanac) shall be transmitted. The frames 1 through 4 shall contain the part of almanac for 20 satellites (5 satellites per frame) and frame 5 shall contain the remainder of almanac for 4 satellites. The almanac for one satellite shall occupy two strings.

Note.:Frame structures are shown in Figures B-8 and B-9.

3.1.2.1.2.4 String structure. Each string shall have a 2-second duration and shall contain binary chips of data and time mark. During the last 0.3 second within this 2-second interval (at the end of each string) the time mark shall 150CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 be transmitted. The time mark (shortened pseudo-random sequence) shall consist of 30 chips with a time duration for each chip of 10 milliseconds

and having the following sequence:

1 1 1 1 1 0 0 0 1 1 0 1 1 1 0 1 0 1 0 0 0 0 1 0 0 1 0 1 1 0.

During the first 1.7 seconds within this 2-second interval (in the beginning of each string) 85 bits of data (each data bit of a 20 milliseconds duration) shall be transmitted in bi-binary format. The numbers of bits in the string shall be increased from right to left. Along with information bits (bit positions 9 through 84) the check bits of Hamming code (KX) (bit positions 1 through 8) shall be transmitted. The Hamming code shall have a code length of 4. The data of one string shall be separated from the data of adjacent strings by time mark (MB). The words of the data shall be registered by MSB ahead. In each string bit position, 85 shall be an idle chip (“0”) and be transmitted first.

3.1.2.1.2.4.1 Strings 1 through 4. The information contained in strings 1 through 4 of each frame shall correspond to the satellite from which it is transmitted.

This information shall not be changed within the superframe.

3.1.2.1.2.4.2 Strings 5 through 15. Strings 5 through 15 of each frame shall contain GLONASS almanac for 4 or 5 satellites. The information contained in the fifth string shall be repeated in each frame of the superframe.

Note.:— String structure is given in Figure B-10.

3.1.2.1.3 L1OF (L1 OPEN SERVICE FDMA) DATA CONTENT Note.:Additional information concerning the data content is given in the GLONASS FDMA ICD.

3.1.2.1.3.1 Ephemeris and time parameters. The ephemeris and time parameters

shall be as follows:

M = the string number within the frame; t = the time referenced to the beginning of the frame within the k current day. It is calculated according to the satellite time scale.

The integer number of hours elapsed since the beginning of the current day is registered in the 5 MSBs. The integer number of minutes elapsed since the beginning of the current hour is registered in the next 6 bits. The number of 30-second intervals elapsed since the beginning of the current minute is registered in the one LSB. The beginning of the day according to the satellite time scale coincides with the beginning of the recurrent superframe;

t = the time interval within the current day according to UTC(SU) + b 151CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 03 hours 00 min. The immediate data transmitted within the frame are referred to the middle of t . Duration of the time b interval and therefore the maximum value of tb depends on the value of the flag P1;

γ (t ) = the relative deviation of predicted carrier frequency value of n- n b satellite from the nominal value at the instant t , i.e. b where f = the nominal value of frequency of n-satellite clocks;

Hn 𝜏 (t ) = the correction to the n-satellite time tn relative to GLONASS time n b tc at an instant tb, i.e. 𝜏 (t ) = t (t ) – tn(t ); n b c b b x (t ), y (t ), z (t ) = the coordinates of n-satellite in PZ-90 coordinate n b n b n b system at an instant tb;

ẋ (t ), ẏ (t ), ż (t ) = the velocity vector components of n-satellite in PZ-90 n b n b n b coordinate system at an instant tb; ẍ (t ), ÿ (t ), z̈ (t ) = the acceleration components of n-satellite in PZ-90 n b n b n b coordinate system at an instant tb, which are caused by effect of sun and moon;

E = an indication of the “age” of the immediate information, i.e. a time n interval elapsed since the instant of its calculation (uploading) until the instant tb for n-satellite;

B = the health flag. Values greater than 3 indicate the fact of malfunction n of given satellite;

P1 = a flag indicating the time interval between the current and previous

value of the tb parameters in minutes as shown:

P2 = a flag indicating whether the value of tb is odd or even. A value of “1” indicates a 30-minute interval of service information transmit (t = 1, 3, 5 b …), a value of “0” indicates a 60-minute interval of service information transmit (t = 2, 6, 10 …);

b 152CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 P3 = a flag indicating the number of satellites for which an almanac is transmitted within a given frame. “1” corresponds to 5 satellites and “0” corresponds to 4 satellites; and Δ𝜏 = the time difference between the navigation RF signal transmitted in n L2 sub-band and navigation RF signal transmitted in L1 sub-band by given

satellite: Δ𝜏 = t – t n f2 f1 where t , t are the equipment delays in L1 and L2 sub-bands respectively, expressed f1 f2 in units of time.

3.1.2.1.3.2 Ephemeris and time parameters. The ephemeris and time parameters shall be as indicated in Table B-16. For the words for which numeric values may be positive or negative, the MSB shall be the sign bit. The chip “0” shall correspond to the “+” sign and the chip “1” shall correspond to the ”-” sign.

3.1.2.1.3.3 Arrangement of the ephemeris and time parameters. Arrangements of the ephemeris and time parameters within a frame shall be as indicated in Table B-17.

3.1.2.1.3.4 Almanac parameters. The almanac parameters shall be as follows:

A = an index showing relation of this parameter with the almanac;

MA = an index of the modification of nA-satellite: “00” indicates n GLONASS satellite, and “01” indicates GLONASSM satellite; τ = the GLONASS time scale correction to UTC(SU) time. The c correction τ is given at the instant of day NA;

c NA = the calendar day number within the 4-year period beginning since the leap year. The correction τ and other almanac data (almanac of c orbits and almanac of phases) relate to this day number; nA = the slot number occupied by n-satellite;

HA = the channel number of a carrier frequency of nA-satellite (Table n B-15); λA = the longitude of the first (within the NA-day) ascending node of nA- n satellite orbit in PZ-90 coordinate system; t A = the time of the first ascending node passage of nA-satellite within λ n NA-day;

153CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 154CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 ΔiA = the correction to the mean value of inclination of nA-satellite at n instant of t A (mean value of inclination is equal to 63 degrees);

λ n ΔTA = the correction to the mean value of Draconian period of the nA- n satellite at the instant of t A (mean value of Draconian period T is equal λ n to 43 200 seconds); ΔT˙A = the rate of change of Draconian period of nA-satellite;

n εA = the eccentricity of nA-satellite at instant of tλAn; n ωA = the argument of perigee of nA-satellite at the instant of tλAn; n 𝜏A = the coarse value of nA-satellite time correction to GLONASS time n at instant of t A ;

λ n CA = a generalized “unhealthy flag” of nA-satellite at instant of almanac n upload almanac of orbits and phases. When C = 0, this indicates that n n-satellite is non-operational. When C = 1, this indicates that n-satellite n is operational.

155CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.2.1.3.5 Partition and coding of almanac parameters. The GLONASS almanac, transmitted within the superframe, shall be partitioned over the superframe, as indicated in Table B-21. The numeric values of almanac parameters shall be positive or negative. The MSB shall be the sign bit, the chip “0” shall correspond to the “+” sign, and the chip “1” shall correspond to the “–” sign. The almanac parameters shall be coded as indicated in Table B-18.

3.1.2.1.3.6 Arrangement of the almanac parameters. Arrangement of the almanac words within the frame shall be as indicated in Table B-19.

3.1.2.1.4 CONTENT AND STRUCTURE OF ADDITIONAL DATA TRANSMITTED BY GLONASS-M SATELLITES IN L1OF (L1 OPEN SERVICE FDMA) Note.: Additional information concerning the data content and structure is given in the GLONASS FDMA ICD.

3.1.2.1.4.1 Letter designation of additional data. In addition to the GLONASS data, GLONASS-M satellites shall transmit the following additional data as indicated in Table B-20: n – an index of the satellite transmitting the given navigation signal: it corresponds to a slot number within GLONASS constellation;

ln – health flag for n-th satellite: “0” indicates the n-th satellite is healthy, “1” indicates the malfunction of the n-th satellite;

B1 – coefficient to determine ΔUT1: it is equal to the difference between UT1 and UTC at the beginning of the day (NA), expressed in seconds;

B2 – coefficient to determine ΔUT1: it is equal to the daily change of the difference ΔUT1 (expressed in seconds for a mean sun day).

These coefficients shall be used to transform between UTC(SU) and UT1: ΔUT1= UTC(SU) – UT1, where UT1 – Universal Time referenced to the Mean Greenwich Meridian (taking account of Pole motion), UTC(SU) – Coordinated Universal Time of the Russian Federation State Standard, ΔUT1= B1 + B2 × (N – NA), T KP – notification of a forthcoming leap second correction of UTC (±1 s) as

shown:

156CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.: GLONASS system timescale correction is usually performed once a year at midnight 00 hours 00 minutes 00 seconds in accordance with the early notification of the International Time Bureau (BIH/BIPM) at

the end of a quarter: from 31 December to 1 January – first quarter, from 31 March to 1 April – second quarter, from 30 June to 1 July – third quarter, from 30 September to 1 October – fourth quarter.

N – current date, calendar number of the day within the four-year interval T starting from 1 January in a leap year;

Note.: An example of NT transformation into the common form of current data information (dd/mm/yy) is presented in Attachment D, 4.1.2.7.1.

N – four-year interval number starting from 1996;

4 F – a parameter that provides the predicted satellite user range accuracy at T time tb. Coding is as indicated in Table B-19;

M – type of satellite transmitting the navigation signal. 00 refers to a GLONASS satellite; 01 refers to a GLONASS-M satellite;

P4 – flag to show that updated ephemeris parameters are present. “1” indicates that an updated ephemeris or frequency/time parameters have been uploaded by the control segment;

Note.: Updated ephemeris or frequency/time information is transmitted in the next interval after the end of the current interval tb.

P – technological parameter of control segment indicating the satellite operation

mode in respect of time parameters:

00 – 𝜏 parameter relayed from control segment, 𝜏 parameter relayed from c GPS control segment;

01 – 𝜏 parameter relayed from control segment, 𝜏 parameter calculated on- c GPS board the GLONASS-M satellite;

10 – 𝜏 parameter calculated on-board the GLONASS-M satellite; 𝜏 c GPS parameter relayed from control segment;

11 – 𝜏 parameter calculated on-board the GLONASS-M satellite; 𝜏 c GPS parameter calculated on-board the GLONASS-M satellite; 𝜏 – correction to GPS time relative to GLONASS time:

GPS T – T = ΔT + 𝜏 , GPS GL GPS 157CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 where ΔT is the integer part, and 𝜏 is the fractional part of the difference between GPS the system timescales expressed in seconds.

Note.: The integer part ΔT is determined from the GPS navigation message by the user receiver.

MA – type of satellite nA: coding “00” indicates a GLONASS satellite, coding n “01” indicates a GLONASS-M satellite.

3.1.2.1.4.2 Additional data parameters. Additional data parameters are defined in Tables B-18 to B-20.

3.1.2.1.4.3 Location of additional data words within GLONASS-M navigation message. The required location of additional data words within the GLONASS-M navigation message is defined in Table B-20.

158CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 159CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 160CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 161CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.2.1.5 L1OC, L3OC RF CHARACTERISTICS Note.: Additional information concerning the RF characteristics is given in the GLONASS CDMA ICD General Description of CDMA Signal System, Edition 1.0, dated 2016 (hereinafter referred to as “GLONASS CDMA ICD General Description”); in the GLONASS CDMA ICD L1 band; and in the GLONASS CDMA ICD L3 band.

3.1.2.1.5.1 The L1OC signal shall contain L1OCd data and L1OCp pilot components of equal power levels. These components shall be obtained by chip-by- chip time-division multiplexing of two pseudo random noise sequences.

The L1OC signal shall be in phase quadrature with the L1SC signal. L1OC leads L1SC by 𝜋/2 radians as shown in Figure B-11A.

Note.: The L1SC signal is a CDMA secured service navigation signal in the L1 frequency band and is not used in aviation.

162CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.2.1.5.2 The L3OC signal shall contain L3OCd data and L3OCp pilot components of equal power levels. These components shall occupy phase quadratures I and Q, respectively. L3OCd leads L3OCp by π/2 radians as shown in Figure B-11A.

3.1.2.1.5.3 Carrier phase noise. The phase noise spectral density of the unmodulated carrier shall be such that a phase locked loop of 10 Hz one-sided noise bandwidth shall be able to track the carrier to accuracy no worse than 0.01 radians rms.

3.1.2.1.5.4 Spurious emissions. The power of the transmitted RF signal beyond the GLONASS allocated bandwidth shall not be more than –40 dB relative to the power of the unmodulated carrier.

Note 1.: The GLONASS allocated bandwidths are L1 (1 592.9 – 1 610 MHz), L2 (1 237.8 – 1 256.8 MHz) and L3 (1 190.35 – 1 212.23 MHz).

Note 2.: GLONASS satellites use filters limiting out-of-band emissions to the harmful interference limit contained in Recommendation ITU-R RA.769 for the 1 610.6 – 1 613.8 MHz and 1 660 – 1 670 MHz bands.

3.1.2.1.5.5 Correlation loss. The loss in the recovered signal power due to imperfections in the signal modulation and waveform distortion shall not exceed 0.6 dB.

Note.: The loss in signal power is the difference between the broadcast power in the specified bandwidth and the signal power recovered by a noise-free, loss-free receiver with 1-chip correlator spacing and an RF front-end with the same bandwidth.

3.1.2.1.6 L1OC, L3OC DATA STRUCTURE Note.: Additional information concerning the data structure is given in the GLONASS CDMA ICD General Description; in the GLONASS CDMA ICD L1 band; and in the GLONASS CDMA ICD L3 band.

3.1.2.1.6.1 General. The GLONASS CDMA navigation message shall be transmitted as a variable sequence of strings. Strings shall comprise service and data fields (separate bits or groups of bits containing specific parameters).

Note.: A pseudoframe is a set of strings of immediate and non-immediate data starting with the three strings of ephemeris and clock data (immediate data). The remaining strings of a pseudoframe contain non-immediate data.

3.1.2.1.6.2 Service fields. The structure of a service section shall be the same for each type of signal and include preamble, type of the string, time of the beginning of the string (TS), satellite ID number, signal parameters and cyclic redundancy check (CRC) bits to check the integrity of the string data.

163CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.2.1.6.3 Data fields. The structure of data fields shall depend on the string type.

Each type of string shall contain a complete individual block of data with the exception of orbit and clock data, which occupies three types of strings and shall be transmitted as a continuous packet.

Note.: The message design may evolve together with future evolutions of GLONASS. This evolution may involve the inclusion of additional new string types, which can either contain new data types or modify the existing string types.

3.1.2.1.6.4 L1OC message characteristics

3.1.2.1.6.4.1 The L1OCd navigation message shall be transmitted at 125 bits/s. The message shall consist of 250-bit strings of 2-second duration as well as of 125- and 375-bit anomalous strings of 1- and 3-second duration, respectively.

3.1.2.1.6.4.2 L1OCd nominal string structure. Each L1OCd nominal string shall consist of 50-bit service fields, a 184- bit data field and a 16-bit CRC service field as shown in Figure B-11B. Transmission of a string shall start with bit 1 (the first bit of the preamble and end with bit 250 (last bit of CRC)).

3.1.2.1.6.4.3 L1OCd service fields shall be as shown in Table B-24.

164CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.2.1.6.4.4 L1OCd anomalous strings. Anomalous strings shall be indicated by string Types 1 and 2. Strings of Type 1 shall be used to indicate the leap second corrections of L1OCd signal time when a day’s length is reduced by 1 s.

Strings of Type 1 shall consist of 50-bit service fields, a 59-bit data field and a 16-bit CRC service field as shown in Figure B-11C. Strings of Type 2 shall be used to indicate the leap second corrections of L1OCd signal 165CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 time when a day’s length is increased by 1 s. Strings of Type 2 shall consist of 50-bit service fields, a 301-bit data field and a 24-bit CRC service field as shown in Figure B-11D.

3.1.2.1.6.4.5 L1OCd nominal strings CRC. The CRC (250,234) generator polynomial

shall have the following form: g(X) = 1+ X+ X5+ X6+ X8+ X9+ X10+ X11+ X13+ X14+ X16.

A 234-bit data block shall be delivered to the encoder’s input (starting with the 1st bit of the preamble and ending with the 184th bit of the data field). At the encoder’s output, a 250-bit encoded block shall be generated by adding 16 check bits.

3.1.2.1.6.4.6 L1OCd anomalous string Type 1 CRC. CRC (125,109) shall be used in L1OCd Type 1 strings. It shall be generated similarly to code (250,234) except for the number of bits delivered to the input (109 instead of 234).

3.1.2.1.6.4.7 L1OCd anomalous strings Type 2 CRC. CRC (375,351) shall be used in L1OCd Type 2 strings. The CRC (375,351) generator polynomial shall

have the following form: g(X) = 1+ X+ X3+ X4+ X5+ X6+ X7+ X10+ X11+ X14+ X18+ X23+ X24.

A 351-bit data block shall be delivered to the encoder’s input (starting with the 1st bit of the preamble and ending with the 301st bit of the data field). At the encoder’s output, a 375-bit encoded block shall be generated by adding 24 check bits.

3.1.2.1.6.5 L3OC message characteristics

3.1.2.1.6.5.1 The L3OCd navigation message shall be transmitted at 100 bits/s. The message shall consist of 300-bit strings of 3-second duration as well as of 200- and 400-bit anomalous strings of 2- and 4-second duration, respectively.

3.1.2.1.6.5.2 L3OCd strings structure. Each L3OCd nominal string shall consist of 57-bit service fields, a 219-bit long data field and 24-bit long CRC service field, as shown in Figure B-12A. Transmission of a string shall start with bit 1 (the first bit of the preamble) and end with bit 300 (the last bit of CRC).

3.1.2.1.6.5.3 L3OCd service fields shall be as shown in Table B-25.

166CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.2.1.6.5.4 L3OCd anomalous strings. Anomalous strings shall be indicated by strings Types 1 and 2. Strings of Type 1 shall be used to indicate the leap second corrections of L3OCd signal time when a day’s length is reduced by 1 s. Strings of Type 1 shall consist of 57-bit service fields, a 119-bit data field and a 24-bit CRC service field, as shown in Figure B-12B.

Strings of Type 2 shall be used to indicate the leap second corrections of 167CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 L3OCd signal time when a day’s length is increased by 1 s. Strings of Type 2 shall consist of 57+20-bit service fields, a 299-bit data field and a 24-bit CRC service field as shown in Figure B-12C.

3.1.2.1.6.5.5 L3OCd nominal strings CRC. The CRC (300,276) generator polynomial

shall have the following form: g(X) = 1+ X+ X3+ X4+ X5+ X6+ X7+ X10+ X11+ X14+ X17+ X18+ X23+ X24.

A 276-bit data block shall be delivered to the encoder’s input (starting with the 1st bit of the preamble and ending with the 219th bit of the data field). At the encoder’s output, a 300-bit encoded block shall be generated by adding 24 check bits.

3.1.2.1.6.5.6 L3OCd anomalous string Type 1 CRC. CRC (200,176) shall be used in L3OCd Type 1 strings. It shall be generated similarly to code (300,276) except for the number of bits delivered to the input (176 instead of 276).

3.1.2.1.6.5.7 L3OCd anomalous string Type 2 CRC. CRC (400,376) shall be used in L3OCd Type 2 strings. It shall be generated similarly to code (300,276) except for the number of bits delivered to the input (376 instead of 276).

3.1.2.1.7 L1OC, L3OC DATA CONTENT Note.: Additional information concerning the data content is given in the GLONASS CDMA ICD General Description; in the GLONASS CDMA ICD L1 band; and in the GLONASS CDMA ICD L3 band.

3.1.2.1.7.1 L1OCd navigation messages shall contain the data in accordance with the list of string types shown in Table B-26.

Note.: Additional information concerning the data content of the L1OCd service and data fields is given in the GLONASS CDMA ICD L1 band.

168CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.2.1.7.2 L3OCd navigation messages shall contain the data in accordance with the list of string types shown in Table B-27.

Note.:— Additional information concerning the data content of the L3OCd service and data fields is given in the GLONASS CDMA ICD L3 band.

3.1.2.1.7.3 Accuracy factor fields FE, FT. Fields FE and FT shall contain equivalent pseudo-range errors (σ) related to the ephemeris and clock of transmitting satellite. Table B-28 shows values of FE and FT and the corresponding errors.

169CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.2.1.7.4 The maximum interval of updating immediate data (string Types 10, 11 and 12) shall be 30 minutes. Considering that various types of non- immediate data are updated at various intervals, the maximum update interval for all non-immediate data shall be 48 hours.

Note.: Long-term dynamic model parameters enable the usage of immediate data to propagate the orbit for a 4-hour interval.

3.1.2.2 DEFINITIONS OF PROTOCOLS FOR DATA APPLICATION Note.: This section defines the inter-relationships of the data broadcast message parameters. It provides definitions of parameters that are not transmitted, but are used by either or both non-aircraft and aircraft elements, and that define terms applied to determine the navigation solution and its integrity.

170CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.2.2.1 Parity checking algorithm for FDMA data verification. The algorithm shown in Table B-29 and as detailed below is used to detect and correct an error of 1 bit within the string and to detect an error of 2 or more bits within a string.

171CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.2.2.1.1 Each string includes the 85 data bits where the 77 MSBs are data chips (b , b , …, b , b ), and the 8 LSBs are the check bits of Hamming code 85 84 10 9 length of 4 (β , β , …, β , β ).

8 7 2 1

3.1.2.2.1.2 To correct 1-bit errors within the string the following checksums are

generated: (c , c , …, c ), and to detect 2-bit errors (or more-even-number- 1 2 7 of-bits errors) a checksum c is generated, as shown in Table B-29. The Σ

following is used for correcting single errors and detecting multiple errors: a) A string is considered correct if all checksums (c , ..., c , and c ) are 1 7 Σ equal to “0”, or if only one of the checksums (c , ..., c ) is equal to “1” 1 7 and c is equal to “1”.

Σ b) If two or more of the checksums (c , ..., c ) are equal to “1” and c is 1 7 Σ equal to “1”, then character “b ” is corrected to the opposite character icor

in the following bit position: “i ”= c c c c c c c + 8–K, provided that “i ” ≤ 85, cor 7 6 5 4 3 2 1 cor where “c c c c c c c ” is a binary number generated from the 7 6 5 4 3 2 1 checksums (c , ..., c ) with c being the LSB and c being the MSB. K is 1 7 1 7 the ordinal number of the most significant checksum not equal to “0”.

If i > 85, then there is an odd number of multiple errors, and the data cor shall be rejected. c) If at least one of the checksums (c , ..., c ) is equal to “1” and c is equal 1 7 Σ to “0”, or if all checksums (c , ..., c ) are equal to “0” but c is equal to 1 7 Σ “1”, then there are multiple errors and the data shall be rejected.

3.1.2.2.2 SATELLITE CLOCK CORRECTION PARAMETERS

3.1.2.2.2.1 GLONASS system time shall be determined using FDMA data as: t = t + 𝜏 (t ) – γ (t )(t – t ) GLONASS k n b n b k b where t , 𝜏 (t ), γ (t ) are parameters described in 3.1.2.1.3.1. k n b n b

3.1.2.2.2.2 GLONASS system time shall be determined using CDMA data as: where 𝑇 𝑗 is the signal time of received signal from satellite j and 𝜏𝑗(𝑡 ), 𝑆𝑇{𝑠𝑖𝑔𝑛𝑎𝑙} 𝑏 𝛾𝑗(𝑡 ), 𝛽𝑗(𝑡 ), 𝜏 (𝑡 ), 𝜏̇ (𝑡 ) are parameters transmitted in CDMA signals 𝑏 𝑏 𝑐 𝑏 𝑐 𝑏 172CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 within string of Types 10, 11 and 12 as shown in Table B-26 and Table B-

27.

3.1.2.2.2.3 GLONASS system time offset to National Time Service of Russia (UTC(SU)) shall be determined using FDMA data as: t = t + 𝜏 – 03 hours 00 minutes UTC(SU) GLONASS 𝑐 where 𝜏 is a parameter described in 3.1.2.1.3.4 and 𝑐 03 hours 00 minutes is continuous time shift caused by difference between Moscow time and Greenwich time.

3.1.2.2.2.4 GLONASS system time offset to UTC(SU) shall be determined using

CDMA data as: where 𝜏 (𝑡 ), 𝜏̇ (𝑡 ) , are parameters transmitted in CDMA signals within 𝑐 𝑏 𝑐 𝑏 string of Types 10, 11 and 12 as shown in Table B-26 and Table B-27; and 10 800 seconds is the continuous time shift caused by the difference between Moscow time and Greenwich time.

3.1.2.2.3 SATELLITE POSITION

3.1.2.2.3.1 The current satellite centre of mass position shall be defined using ephemeris parameters from GLONASS navigation, as indicated in Table B-16 for GLONASS FDMA signals, in Table B-26 for L1OC and in Table B-27 for L3OC.

3.1.2.2.3.2 Recalculation of ephemeris from instant tb to instant ti within the interval (|τi| = |ti – tb| ≤ 15 minutes) is performed using a technique of numeric integration of differential equations describing the motion of the satellites. In the righthand parts of these equations the accelerations are determined using the gravitational constant μ and the second zonal harmonic of the geopotential J2 which defines polar flattening of the 0 earth, and accelerations due to luni-solar perturbation are taken into account. The equations are integrated in the PZ-90 (3.2.5) coordinate system by applying the Runge-Kutta technique of fourth order, as

indicated below:

173CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Where r = √x2+y2+z2; μ = earth’s universal gravitational constant (398 600.4418 × 109 m3/s2); ae = major semi-axis (6 378 136 m);

J2 = second zonal harmonic of the geopotential (1 082 625.75 × 10–9);

0 and ω = earth’s rotation rate (7.2921151467 × 10–5 radians/s).

Coordinates x (t ), y (t ), z (t ), and velocity vector components ˙x (t ) = n b n b n b n b V , ˙y (t ) = V , ˙z (t ) = V are initial conditions for the integration. x n b y n b z Accelerations due to luni-solar perturbation ¨x (t ), ¨y (t ), ¨z (t ) are n b n b n b constant on the integration interval ±15 minutes.

3.1.2.2.3.3 Recalculation of ephemeris from instant tb to instant ti within the interval (|𝜏i| = |t – t | ≤ 4 hours) for CDMA signals shall be performed as in i b

3.1.2.2.3.2, except that this model includes additional accelerations modelled by a fourth-degree polynomial to accommodate the extended

interval as described below:

174CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Coordinates, velocity vector components at the time tb, and perturbing accelerations x¨, y¨, z¨ shall be transmitted in CDMA signals within string of Types 10, 11 and 12.

The long-term dynamic model parameters for the fourth-degree polynomials, accelerations 𝑎 , 𝑎 , and 𝑎 , shall be transmitted in CDMA signals in strings of Types 𝑥 𝑦 𝑧 31 and 32.

3.1.2.2.4 ALGORITHM FOR DETERMINATION OF SATELLITE ANTENNA PHASE CENTRE POSITION

3.1.2.2.4.1 For high-precision pseudo-range measurements, an algorithm for computing antenna phase centre position in the PZ-90 coordinate system based on the satellite centre of mass position and data transmitted in CDMA signals within string Type 16 shall be used.

Note.: Additional information concerning a suitable algorithm is given in Appendix R of the GLONASS CDMA ICD General Description.

3.1.2.2.5 IONOSPHERIC CORRECTION

3.1.2.2.5.1 The ionospheric correction for a single-frequency receiver shall be

defined as:

175CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 where f is the signal carrier frequency, in GHz;

I is the total electron content (TEC) integrated along the signal e propagation path, 1×1016m-2; and 𝐼̇ is the rate of change of TEC integrated along the signal 𝑒 propagation path, 1×1016 m-2s-1.

Note.: Additional information concerning two suitable algorithms for computing TEC integrated along the signal propagation path based on data transmitted within strings of Type 25 is given in Appendix Q of the GLONASS CDMA ICD General Description. The first algorithm is a universal algorithm for terrestrial and space users. It is more complex, accurate, and has wider application. The second algorithm is intended for terrestrial users only. It is easier to implement but it results in larger errors of TEC at less than 30° elevation angles.

Residual ionosphere correction errors of the second algorithm do not exceed 4 m (0.95 probability).

3.1.2.3 AIRCRAFT ELEMENTS

3.1.2.3.1 GLONASS RECEIVER

3.1.2.3.1.1 Reserved.

3.1.2.3.1.2 Satellite tracking. The receiver shall provide the capability to continuously track a minimum of four satellites and generate a position solution based upon those measurements.

3.1.2.3.1.3 Doppler shift. The receiver shall be able to compensate for dynamic Doppler shift effects on nominal GLONASS signal carrier phase and standard code measurements. The receiver shall compensate for the Doppler shift that is unique to the anticipated application.

3.1.2.3.1.4 Resistance to interference. The receiver shall meet the requirements for resistance to interference as specified in 3.7.

3.1.2.3.1.4.1 Intrasystem interference. When receiving an FDMA navigation signal with frequency channel k = n, the interference created by a navigation signal with frequency channel number k = n – 1 or k = n + 1 shall not be more than -48 dBc with respect to the minimum specified satellite power 176CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 at the surface of the earth provided that the satellites transmitting these signals are simultaneously located in user’s visibility zone.

Note.: The intrasystem interference is the intercorrelation properties of the ranging pseudo-random signal with regard to frequency division multiple access.

3.1.2.3.1.4.2 For CDMA signals, multiple access interference shall be defined by the intercorrelation properties of ranging codes and will depend on the number of elementary symbols N in the periods of these codes. Multiple access interference power in relation to the power of the L1OCd signal shall not exceed the level of –30 dB. Multiple access interference power in relation to the power of the L1OCp signal shall not exceed the level of –36 dB. Multiple access interference power in relation to the power of the L3OC signal shall not exceed the level of –40 dB.

3.1.2.3.1.5 Application of clock and ephemeris data. The receiver shall ensure that it is using the correct ephemeris and clock data before providing any position solution.

3.1.2.3.1.6 Leap second correction. Upon GLONASS time leap second correction (see 3.1.2.1.3.1, tb) the GLONASS receiver shall be capable of: a) generating a smooth and valid series of pseudo-range measurements; and b) resynchronizing the data string time mark without loss of signal tracking.

3.1.2.3.1.6.1 After GLONASS time leap second correction the GLONASS receiver

shall utilize the UTC time as follows: a) utilize the old (prior to the correction) UTC time together with the old ephemeris (transmitted before 00 hours 00 minutes 00 seconds UTC); and b) utilize the updated UTC time together with the new ephemeris (transmitted after 00 hours 00 minutes 00 seconds UTC).

Note.: Additional information concerning the specific aspects of receiver operation during scheduled corrections of GLONASS time and Moscow time in the specified situations is given in Appendix E of the GLONASS CDMA ICD General Description.

3.1.2.4 TIME 177CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.2.4.1 For the GLONASS-M satellites, the navigation message shall contain the data necessary to relate UTC(SU) time to UT1. GLONASS time shall be maintained to be within 1 millisecond of UTC(SU) time after correction for the integer number of hours due to GLONASS control segment

specific features: | t – (UTC + 03 hours 00 minutes) | < 1 ms GLONASS The navigation data shall contain the requisite data to relate GLONASS time to UTC time (as maintained by the National Time Service of Russia, UTC (SU)) within 1 microsecond.

Note 1. — The timescales of GLONASS satellites are periodically compared with central synchronizer time. Corrections to the timescales of GLONASS satellites relative to GLONASS time and UTC(SU) time are computed at the GLONASS ground based control complex and uploaded to the satellites twice per day.

Note 2. — There is no integer-second difference between GLONASS time and UTC time. The GLONASS timescale is periodically corrected to integer number of seconds simultaneously with UTC corrections which are performed according to the Bureau International de l’Heure

notification (leap second correction). These corrections are performed at 00 hours 00 minutes 00 seconds UTC time at midnight at the end of a quarter of the year. Upon the GLONASS leap second correction the time mark within navigation message changes its position (in a continuous timescale) to become synchronized with 2 second epochs of corrected UTC timescale. GLONASS users are notified in advance on these planned corrections. For the GLONASSM satellites, notification of these corrections is provided to users via the navigation message parameter KP.

3.1.2.4.2 Accuracy of mutual satellite timescales synchronization shall be 20 nanoseconds (1 sigma) for GLONASS satellites and 8 nanoseconds (1 sigma) for GLONASS-M satellites.

3.1.2.4.3 The correction to GPS time relative to GLONASS time (or difference between these timescales) broadcast by the GLONASS-M satellites, τGPS, shall not exceed 30 nanoseconds (1 sigma).

Note.: The accuracy of τGPS (30 ns) is determined with reference to the GPS SPS coarse acquisition signal and may be refined upon completion of trials of the GLONASS system using GLONASS-M satellites.

3.1.2.4.4 Signal time shall be generated and maintained by an on-board clock based on atomic frequency standard, shall be synchronized with GLONASS time and shall be distributed in radio navigation signals.

178CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note 1: Signal time differs from on-board clock time by the group delay value.

Thus, signal time corrections in string Types 10, 11 and 12 include group delay values.

Note 2.: Additional information concerning signal time is given in the GLONASS CDMA ICD General Description.

3.1.2.4.4.1 Navigation data for any GLONASS CDMA signal shall contain the estimated parameters of the polynomial model for relating signal time broadcast in this signal to GLONASS time as well as for relating a pilot component of this signal to its data component.

3.1.2.4.4.2 When GLONASS time is corrected for ±1 s during scheduled leap second corrections of UTC(SU), simultaneous correction of signal time for all satellites shall be carried out through changing the time stamps of the pulse sequence representing seconds.

Note.: Navigation data provides advance notifications to users of the day and the sign of the correction.

3.1.2.5 COORDINATE SYSTEM

3.1.2.5.1 PZ-90 (Parameters of common terrestrial ellipsoid and gravitational field of the earth 1990). The GLONASS broadcast ephemeris shall describe a position of transmitting antenna phase centre of a given satellite in the PZ-90 earth-centred earth-fixed reference frame.

3.1.2.5.2 CONVERSION BETWEEN PZ-90 AND WGS-84

3.1.2.5.2.1 Recommendation. — The following conversion parameters should be used to obtain position coordinates in WGS-84 (version G1674) from position coordinates in PZ-90 (Version PZ-90.11):

Note 1.: X, Y and Z are expressed in metres. The difference between versions WGS-84 (G1674) and PZ-90 (PZ-90.11) is not significant with respect to operational requirements.

Note 2.: Guidance material on conversion between PZ-90 and WGS-84 is

provided in Attachment D, 4.1.2.9.3.

3.1.3 Galileo Open Service (Galileo OS)

3.1.3.1 NON-AIRCRAFT ELEMENTS 179CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.3.1.1 GALILEO RF CHARACTERISTICS

3.1.3.1.1.1 E1 and E5 common requirements

3.1.3.1.1.1.1 Carrier phase noise. The carrier phase noise spectral density of the unmodulated carrier on E5 and E1 shall be such that a second-order phase locked loop of 10 Hz one-sided noise bandwidth is able to track the carrier to an accuracy of 0.04 radian root mean square (RMS).

3.1.3.1.1.1.2 Spurious emissions. In-band spurious emissions shall be at least 35 dB below the unmodulated E1 and E5 carriers over the allocated channel bandwidth.

3.1.3.1.1.1.3 Correlation loss. The loss in the recovered signal power due to imperfections in the signal modulation and waveform distortion shall not exceed 0.6 dB for each signal (E1, E5a and E5b).

Note.: The loss in signal power is the difference between the broadcast power in the specified bandwidth and the signal power recovered by a noise-free, loss-free receiver with 1-chip correlator spacing and the same bandwidth.

3.1.3.1.1.1.4 Code/data coherence. The edge of each data symbol shall be aligned with the edge of the corresponding ranging code chip. The start of the periodic ranging code shall be aligned with the start of a data symbol.

The edge of each secondary code chip shall be aligned with the edge of a primary code chip. The start of a primary code chip shall be aligned with the start of a secondary code chip.

3.1.3.1.1.2 E1 RF characteristics

3.1.3.1.1.2.1 E1 signal components. The E1 signal shall comprise two signal

components: E1-B navigation data component with a navigation data symbol rate of 250 symbols per second and E1-C pilot component.

3.1.3.1.1.2.2 E1 signal power split. The E1 signal power shall be equally split between the E1-B and E1-C signal components.

3.1.3.1.1.2.3 E1-B ranging code (CE1-B). The E1-B ranging code shall be a 1.023 megachips per second ranging code repeated every 4 milliseconds, derived from a primary ranging code of 4 092 chips.

Note.: Additional information concerning the E1-B ranging codes is given in Galileo OS SIS ICD, Chapter 3 and Annex C.

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3.1.3.1.1.2.4 E1-C ranging code (CE1-C). The E1-C ranging code shall be a 1.023 megachips per second ranging code repeated every 100 milliseconds, derived from the Modulo-2 addition of a primary ranging code of 4 092 chips and a secondary code of 25 chips.

Note.: Additional information concerning the E1-C ranging codes is given in Galileo OS SIS ICD, Chapter 3 and Annex C.

3.1.3.1.1.2.5 E1-B data component generation. The E1-B data component shall be generated from the E1 navigation data stream (DE1-B) and the E1-B ranging code (CE1-B), modulated with two in-phase CBOC subcarriers of 1.023 MHz and 6.138 MHz, respectively, as shown in Figure B-13.

Note.: The subcarrier-free component of the E1 navigation data component – that is, before CBOC modulation – is denoted as eE1-B. Additional information concerning eE1-B generation is given in Galileo OS SIS ICD, 2.3.3.

3.1.3.1.1.2.6 E1-C pilot component generation. The E1-C pilot component shall be generated from the E1-C ranging code (CE1-C) modulated with two anti- phase CBOC subcarriers of 1.023 MHz and 6.138 MHz, respectively, as shown in Figure B-13.

Note.: The subcarrier-free component of the E1 pilot component – that is, before CBOC modulation – is denoted as eE1-C. Additional information concerning eE1-C generation is given in Galileo OS SIS ICD, 2.3.3.

3.1.3.1.1.2.7 E1 signal modulation. The E1-B/C composite binary signal shall be generated from the CBOC modulation of the binary signal components, eE1-B and eE1-C, and the subcarriers, as illustrated in Figure B-13.

Note.: Additional information concerning E1-B/C generation is given in Galileo OS SIS ICD, 2.3.3. 3.1.3.1.1.3

3.1.3.1.1.3 E5a and E5b RF characteristics

3.1.3.1.1.3.1 E5a signal components. The E5a signal shall comprise two signal

components: E5a-I navigation data component with a navigation data symbol rate of 50 symbols per second and E5a-Q pilot component.

3.1.3.1.1.3.2 E5a signal power split. The E5a signal power shall be equally split between the E5a-I and E5a-Q components.

3.1.3.1.1.3.3 E5a-I ranging code (CE5a-I). The E5a-I ranging code sequence shall be a 10.230 megachips per second ranging code repeated every 20 181CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 milliseconds, derived from the Modulo-2 addition of a primary ranging code of 10 230 chips and a secondary code of 20 chips.

Note.: Additional information concerning E5a-I ranging codes is given in Galileo OS SIS ICD, Chapter 3 and Annex C.

3.1.3.1.1.3.4 E5a-Q ranging code (CE5a-Q). The E5a-Q ranging code shall be a

10.230 megachips per second ranging code repeated every 100 milliseconds, derived from the Modulo-2 addition of a primary ranging code of 10 230 chips and a secondary code of 100 chips.

Note.: Additional information concerning E5a-Q ranging codes is given in Galileo OS SIS ICD, Chapter 3 and Annex C.

3.1.3.1.1.3.5 E5a-I data component generation. The E5a data component shall be generated from the E5a navigation data stream (DE5a-I) and the E5a-I ranging code (CE5a-I).

Note.: The subcarrier-free component of the E5a navigation data component – that is, before AltBOC modulation – is denoted as eE5a-I.

3.1.3.1.1.3.6 E5a-Q pilot component generation. The E5a pilot component shall be generated from the E5a-Q ranging code (CE5a-Q).

Note.: The subcarrier-free component of the E5a pilot component – that is, before AltBOC modulation – is denoted as eE5a-Q.

3.1.3.1.1.3.7 E5b signal components. The E5b signal shall comprise two signal

components: E5b-I navigation data component with a navigation data symbol rate of 250 symbols per second and E5b-Q pilot component.

3.1.3.1.1.3.8 E5b signal power split. The E5b signal power shall be equally split between the E5b-I and E5b-Q components.

3.1.3.1.1.3.9 E5b-I ranging code (CE5b-I). The E5b-I ranging code shall be a 10.230 megachips per second ranging code repeated every 4 milliseconds, derived from the Modulo-2 addition of a primary ranging code of 10 230 chips and a secondary code of 4 chips.

Note. Additional information concerning E5b-I ranging codes is given in Galileo OS SIS ICD, Chapter 3 and Annex C.

3.1.3.1.1.3.10 E5b-Q Ranging code (CE5b-Q). The E5b-Q ranging code shall be a 10.230 megachips per second ranging code repeated every 100 milliseconds, derived from the Modulo-2 addition of a primary ranging code of 10 230 chips and a secondary code of 100 chips.

182CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.: Additional information concerning E5b-Q ranging codes is given in Galileo OS SIS ICD, Chapter 3 and Annex C.

3.1.3.1.1.3.11 E5b-I data component generation. The E5b data component shall be generated from the E5b navigation data stream (DE5b-I) and the ranging code (CE5b-I).

Note.: The subcarrier-free component of the E5b navigation data component – that is, before AltBOC modulation – is denoted as eE5b-I.

3.1.3.1.1.3.12 E5b-Q pilot component generation. The E5b pilot component shall be generated from the ranging code (CE5b-Q).

Note.: The subcarrier-free component of the E5b pilot component – that is, before AltBOC modulation – is denoted as eE5b-Q.

3.1.3.1.1.3.13 E5 signal modulation. The wideband E5 signal shall be generated with the AltBOC modulation of sideband subcarrier of 15.345 MHz (15 ×

1.023 MHz) with the binary signal components eE5a-I, eE5a-Q, eE5b-I and eE5b-Q, as illustrated in Figure B-14.

Note 1.: E5a and E5b signals can be processed independently by the user receiver as though they were two separate QPSK signals with a carrier frequency of 1176.45 MHz and 1207.14 MHz, respectively.

Note 2.: Additional information concerning E5 generation is given in Galileo OS SIS ICD, 2.3.1.

3.1.3.1.1.3.14 Code assignments to satellites

3.1.3.1.1.3.14.1 Primary ranging code assignment to satellites. The E5a-I, E5a-Q, E1-B and E1-C primary code number n shall be allocated to the space vehicle IDs (SVID) number n (with n=1 to 36).

3.1.3.1.1.3.14.2 Secondary ranging code assignment to satellites. The E5a-Q secondary code shall be assigned according to the SVID number n (with n=1 to 36). E5a-I and E1-C secondary codes shall be constant regardless of the SVID.

3.1.3.1.2 DATA STRUCTURE Note.: Additional information concerning the data structure is given in Galileo OS SIS ICD.

3.1.3.1.2.1 E5a-I message (F/NAV) characteristics 183CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.3.1.2.1.1 The E5a-I message shall be transmitted as a sequence of frames as indicated in Figure B-15. The period of each frame shall be 600 seconds.

Each frame shall consist of 12 subframes of period 50 seconds per subframe. Each subframe shall consist of five pages of period 10 seconds per page.

3.1.3.1.2.1.2 Page structure. Each page structure shall contain the following elements structured as indicated in Table B-30:  12 synchronization block symbols  488 interleaved message block symbols

3.1.3.1.2.1.3 Synchronization block. The first element of each page shall be a 12- symbol synchronization sequence. The synchronization sequence shall be “101101110000” with the MSB transmitted first, and it shall be added to the beginning of the 488 interleaved message block symbols field after the interleaving procedure described in paragraph 3.1.3.1.2.1.6.

3.1.3.1.2.1.4 F/NAV message word. The message word shall contain 244 bits consisting of a 6-bit page type, a 208-bit data field, a 24-bit CRC and a 6-bit tail field. The 6-bit tail field shall be “000000”.

Note.: Additional information concerning the message words is given in Galileo OS SIS ICD.

3.1.3.1.2.1.5 F/NAV FEC encoding. The 25-bit-per-second data stream shall be encoded at a rate of two symbols per bit using a convolution code with a constraint length of seven to yield 50 symbols per second. The convolution encoder logic arrangement shall be as illustrated in Figure B- 16 with the G1 output selected for the first half of each 40-millisecond data bit period resulting in 488 symbols per page where S1 is the first symbol and S488 is the last symbol.

3.1.3.1.2.1.6 E5a-I interleaving procedure. The E5a-I message block symbols shall be interleaved using a 61-column, 8-row matrix, where each entry is one symbol. The message block symbols shall be written into each column 184CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 and ordered for transmission, row by row, starting at the upper left corner of the matrix as indicated in Table B-31.

3.1.3.1.2.2 E1-B message (I/NAV) characteristics

3.1.3.1.2.2.1 The E1-B message shall be transmitted as a sequence of frames as indicated in Figure B-17. The period of each frame shall be 720 seconds.

Each frame shall consist of 24 subframes of period 30 seconds per subframe. Each subframe consist of 15 nominal pages of period 2 seconds per page. Each page shall consist of two subpages each of period one second.

Note 1.: The two subpages in a page are known as the even page and the odd page.

Note 2.: I/NAV message structure is indicated in Figure B-17.

3.1.3.1.2.2.2 Page type. There shall be two types of pages, a nominal page and an alert page. The nominal page shall contain the nominal data word.

Note.: The alert page is reserved for future applications.

3.1.3.1.2.2.3 Nominal page. A nominal page shall consist of two parts (even and odd) transmitted sequentially over the same frequency and structured as indicated in Table B-33. The nominal page shall contain 240 bits so that the first 120 bits shall be in the even nominal subpage, and the second 120 bits shall be in the odd nominal subpage.

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3.1.3.1.2.2.4 Nominal data word. The nominal E1-B data word shall contain 128 bits consisting of a 6-bit word type and a 122-bit data field.

3.1.3.1.2.2.5 Subpage structure. Each subpage structure shall contain the following elements, structured as indicated in Table B-32: a) 10 synchronization block symbols; and b) 240 interleaved message block symbols.

3.1.3.1.2.2.6 Synchronization block. The first element of each subpage shall be a 10- symbol synchronization sequence. The synchronization sequence shall be “0101100000”, with the MSB transmitted first, and shall be added to the beginning of the 240 interleaved message block symbols field after the interleaving procedure described in paragraph 3.1.3.1.2.2.10.

3.1.3.1.2.2.7 Even subpage. The even subpage shall contain a bit denoting which part (even or odd) of the subpage is being transmitted, a type bit to indicate that this is a nominal page, the first 112 bits of the nominal data word and a 6-bit tail field, as indicated in Table B-33. The tail field shall be “000000”.

3.1.3.1.2.2.8 Odd subpage. The odd subpage shall contain a bit denoting which part (even or odd) of the subpage is being transmitted, a type bit to indicate that this is a nominal page, the last 16 bits of the nominal data word, a 40-bit “reserved 1” field, 22 bits for search and rescue (SAR) data, a 2- bit spare field, a 24-bit CRC, an 8-bit “reserved 2” field and a 6-bit tail field, as indicated in Table B-33. The tail field shall be “000000”.

Note.: Galileo provides enhanced distress localization and call features for the provision of a SAR service interoperable with the COSPAS- SARSAT system. Galileo SAR service is out of the scope of Annex

10.

186CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note 1.: Even/odd field (1 bit) indicates the part of the page (0=even/1=odd) that is broadcast.

Note 2.: Page type field (1 bit) equal to 0 indicates the nominal page type.

Note 3.: Data field consists of a nominal data word (described in

3.1.3.1.2.2.4) of 128 bits (comprising 112 bits of data (1/2) and 16 bits of data (2/2)).

3.1.3.1.2.2.9 I/NAV FEC encoding. The 125-bit-per-second data in the even and odd subpages shall be encoded at a rate of two symbols per bit using a convolutional code with a constraint length of seven to yield 250 symbols per second. The convolutional encoder logic arrangement shall be as illustrated in Figure B-18 with the G1 output selected for the first half of each 8-millisecond data bit period resulting in 240 symbols per page, where S1 is the first symbol and S240 is the last symbol.

3.1.3.1.2.2.10 E1-B interleaving procedure. The E1-B message block symbols shall be interleaved using a 30 column by an eight-row matrix, where each entry is one symbol. The message block symbols shall be written into each column and ordered for transmission row by row starting at the upper left corner of the matrix, as indicated in Table B-34.

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3.1.3.1.2.2.11 Transmission sequence of nominal pages on E1. The pages shall be transmitted on E1-B such that the even subpage of any word shall be transmitted before the odd subpage of the same word.

3.1.3.1.3 DATA CONTENT Note 1.: Additional information concerning Galileo OS navigation data content and parameters is given in Galileo OS SIS ICD, Chapters 4 and 5.

Note 2. — Galileo ISM is defined in the Galileo OS SIS ICD Issue 2.1.

3.1.3.1.3.1 The contents of F/NAV E5a-I page types shall be according to Table B-

35.

Note 1.: The odd numbered subframes contain page type 5 and the even numbered subframes contain page type 6. This allows transmission of the almanacs for three satellites within two successive subframes (100 seconds).

Note 2.: The parameter k is a designator for “satellite number 1”, k+1 is a designator for “satellite number 2”, etc. It is not a navigation data parameter. k is set by the Galileo control system. The complete F/NAV frame layout (12 subframes) can transmit the almanacs for 18 satellites, sequenced as indicated in Galileo OS SIS ICD, 4.2.3.

Note 3.: Additional information concerning the bit allocation of the different F/NAV page types is given in Galileo OS SIS ICD, 4.2.4.

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3.1.3.1.3.2 The contents of I/NAV E1-B word types shall be according to Table B-36.

Note 1.: Additional information concerning I/NAV nominal subframe layout is given in Galileo OS SIS ICD, 4.3.3.

Note 2.: The parameter k changes every two subframes (i.e. subframes 1 and 2 have the same k, subframes 3 and 4 have the next, etc.). The complete I/NAV frame layout (24 subframes) can transmit the almanacs for 36 satellites, sequenced as indicated in Galileo OS SIS ICD, 4.3.4.

Note 3.: Additional information concerning the bit allocations of the different I/NAV word types is given in Galileo OS SIS ICD, 4.3.5.

189CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Table B-36. I/NAV E1-B word types content Word Type Word Content 0 Spare word 1 IODnav and ephemeris (1/4) 2 IODnav and ephemeris (2/4) 3 IODnav and ephemeris (3/4) 4 IODnav, SVID, ephemeris (4/4) and clock correction 5 Ionospheric correction, BGD, SHS, GST and DVS 6 GST-UTC conversion and TOW 7 IODa, almanac for satellite k (part 1), almanac reference time and almanac reference week number 8 IODa, almanac for satellite k (part 2) and satellite k+1 (part 1) 9 IODa, almanac reference time, almanac reference week number, almanac for satellite k+1 (part 2) and satellite k+2 (part 1) 10 IODa, almanac for satellite k+2 (part 2) and GST-GPS conversion parameters 16 Reduced clock and ephemeris data (CED) parameters 17, 18, 19, 20 FEC2 Reed-Solomon for clock and ephemeris data (CED) 22 Integrity support message (ISM) *Note 1.: Receivers are not required to process this word type for GNSS air navigation applications.

**Note 2.: Galileo ISM is defined in the Galileo OS SIS ICD Issue 2.1 and it contains ISD information supporting ARAIM as described in 3.4.1.

3.1.3.1.3.3 Ephemeris parameters shall be provided in both I/NAV and F/NAV messages transmitted by each Galileo satellite. A single ephemeris shall be applicable to all signals of a specific satellite.

Note.: The ephemeris is computed with respect to the antenna apparent phase centre common to every frequency.

3.1.3.1.3.4 The Galileo OS SIS status shall take one of the following three values:  SIS “healthy”: the SIS is expected to meet the minimum performance requirements.  SIS “unhealthy”: the SIS is out of service or under test.

 SIS “marginal”: the SIS is in neither of the two previous states.

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3.1.3.1.3.4.1 The status of the SIS shall be encoded within the navigation message

through three SIS status flags: the signal health status (SHS) flag, the data validity status (DVS) flag and the SIS accuracy index (SISA).

Note.: Additional information concerning the position of the Galileo SIS status flags within the navigation message is given in Galileo OS SIS ICD, 5.1.9.3 and 5.1.12.

3.1.3.1.3.4.2 SISA. The SISA shall be encoded as shown in Table B-37.

3.1.3.1.3.4.3 SISA shall be coded as shown in Table B-38.

3.1.3.1.3.4.4 Signal health status (SHS). The SHS index shall be encoded according to the values stated in Table B-39.

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3.1.3.1.3.4.5 Data validity status (DVS). The DVS index shall be encoded according to the values in Table B-40.

3.1.3.1.3.4.6 The mapping between the values of the SIS status flags shall be as presented in Table B-41.

Note.: Additional information concerning Galileo flags is given in the European GNSS (Galileo) Open Service Definition Document (Issue

1.1), dated May 2019 (hereinafter referred to as “Galileo OS SDD”).

3.1.3.1.3.5 Almanac. F/NAV and I/NAV messages shall contain the almanac data for a constellation of up to 36 satellites. The almanac data shall be a reduced-precision subset of the clock and ephemeris parameters of the active Galileo satellites in orbit. Also, a predicted satellite health status shall be provided for each of these satellites, giving indications on the satellite’s signal components health and navigation data health.

3.1.3.1.3.6 Dummy messages. If no valid F/NAV or I/NAV data can be transmitted, then the satellite shall transmit a dummy page with a message ID of 63 in the respective F/NAV or I/NAV signals.

Note.: Additional information concerning the dummy page is given in Galileo OS SIS ICD, 4.2.5 and 4.3.6.

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3.1.3.1.3.7 Issue of data (IOD). The Galileo satellite shall broadcast the navigation parameters in data sets. Every set of navigation data broadcast by a Galileo satellite shall be identified by an IOD value.

Note.: Two independent IODs are defined for the ephemeris, satellite clock correction parameters and SISA (“IODnav”) and the almanacs (“IODa”).

3.1.3.1.3.7.1 The IODnav value broadcast by a Galileo satellite in a set of navigation data (ephemeris and clock corrections) shall be unique with respect to any other IODnav broadcast by the same Galileo satellite in the previous 240 minutes.

3.1.3.1.3.8 Navigation data validity time. In nominal operations, each navigation message data set shall be superseded before its expiration at four hours by the broadcast of a new navigation message data set.

Note.: The nominal period of ephemeris and clock corrections update ranges from 10 minutes to three hours.

3.1.3.1.3.9 Galileo time of week (TOW). The TOW shall cover an entire week from 0 to 604 799 seconds and shall be reset to zero at the end of each week.

Note.: The TOW is defined as the number of seconds that have occurred since the transition from the previous week.

3.1.3.1.3.10 Galileo week number (WN). The WN shall consist of 12 bits, which covers 4 096 weeks. The counter shall be reset to zero to cover an additional period Modulo 4 096.

Note.: The WN is an integer counter that gives the sequential week number from the GST start epoch.

3.1.3.2 DEFINITIONS OF PROTOCOLS FOR DATA APPLICATION

3.1.3.2.1 Parity check algorithm. For the F/NAV and the I/NAV data, a CRC of 24 bits shall be generated from the following generator polynomial G(X): 𝐺(𝑋) = (1 + 𝑋) 𝑃(𝑋) where 𝑃(𝑋) = 𝑋23 + 𝑋17 + 𝑋13+𝑋12+𝑋11 + 𝑋9 + 𝑋8+𝑋7+𝑋5+𝑋3 + 1 Note.: The CRC code is calculated in accordance with 3.9 of this Appendix.

3.1.3.2.1.1 The F/NAV CRC information field, M(X), shall be computed using the

equation:

193CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 M(X) shall be formed from the 6-bit E5a-I page type identifier and the 208-bit data field.

Bits shall be arranged in the order transmitted from the Galileo satellite, such that m1 corresponds to the first transmitted bit of the page type identifier, and m214 corresponds to bit 208 of the data field.

3.1.3.2.1.2 The I/NAV nominal page CRC information field, M(X), shall be

computed using the equation:

M(x) shall be formed from the even (e)/odd (0) fields, page type fields, data word fields (1/2 and 2/2), reserved 1 field, SAR (on E1-B only) and spare fields. In nominal mode the CRC shall be computed for the even and odd subpages of the same frequency and shall always be broadcast in the odd subpage.

3.1.3.2.2 Satellite clock correction parameters. The predicted offset of the physical satellite signal time of transmission (TOT) relative to the satellite signal TOT in GST shall be computed for the dual-frequency signal combination

using the following formula:

TOT (X) = TOT (X) ‒ Δt (X) c m SV where  (X)=(f1,f2) is the dual-frequency combination f1 and f2 used for the clock model;  TOT (X) is the corrected satellite TOT in GST for the signal combination X;

C  TOT (X) is the physical satellite TOT for the signal combination X retrieved m through pseudo-range measurements; and  Δt (X) is the satellite time correction for the signal combination X computed SV by means of the time correction data retrieved from the navigation message,

as follows: Δt (X)=a (X)+a (X)[t-t (X)]+a (X)[t-t (X)]2+Δt SV f0 f1 0C f2 0C r where  a (X), a (X), a (X) and t (X) are parameters transmitted in F/NAV signals f0 f1 f2 0c page Type 1 and I/NAV signals word Type 4 as indicated in 3.1.3.1.3;

 t0c(X) is the reference time for the clock correction;  t is the GST time in seconds; and 194CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026  Δ , expressed in seconds, is a relativistic correction term, given by Δ =F e tr tr A1/2 sin(E) where the orbital parameters (e, A1/2) are transmitted in F/NAV signals page Type 2 and I/NAV signals word Type 1 as indicated in 3.1.3.1.3, E is the calculated eccentric anomaly and F = -2μ1/2/c2 = -4.442807309 × 10- 10 s/m1/2.

3.1.3.2.2.1 A single-frequency user receiver processing pseudo-ranges from the frequency f1 shall apply the following correction to the satellite clock correction ΔtSV defined in paragraph 3.1.3.2.2: Δt (𝑓 ) = Δ𝑡 (𝑓 , 𝑓 ) − 𝐵𝐺𝐷(𝑓 , 𝑓 ) 𝑆𝑉 1 𝑆𝑉 1 2 1 2 where BGD(f1,f2) is the broadcast group del y transmitted in F/NAV signals page Type 1 and I/NAV signals word Type 5 as indicated in 3.1.3.1.3 and defined as follows:

where  f and f denote the carrier frequencies of E1 and E5a, 1 2 respectively; and  TR and TR are the group delays of the signals whose 1 2 carrier frequencies are respectively f and f .

1 2

3.1.3.2.2.2 A single-frequency user receiver processing pseudo-ranges from the frequency f shall apply the following correction to the satellite clock 2 correction Δt defined in paragraph 3.1.3.2.2:

SV

3.1.3.2.3 GST-UTC conversion algorithm and parameters. The UTC time t shall UTC be computed through three different cases depending on the epoch of a possible leap second adjustment (scheduled future or recent past) given by the day number (DN), the day at the end of which the leap second becomes effective, and the week number (WNLSF) to which DN is referenced. “Day one” of DN shall be the first day relative to the end/start of week and the WNLSF value shall consist of eight bits, which are a Modulo 256 binary representation of the Galileo week number to which the DN is referenced. The following three cases shall apply:

Case A:

Whenever the leap second adjustment time indicated by WNLSF and 195CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 DN is not in the past (relative to the user’s present time), and the user’s present time does not fall in the time span which starts six hours prior to the effective time, and ends six hours after the effective time, tUTC

shall be computed as follows: 𝑡 = (𝑡 − Δ𝑡 )[Modulo 86400] 𝑈𝑇𝐶 𝐸 𝑈𝑇𝐶 where Δ𝑡 = Δ𝑡 + 𝐴 + 𝐴 (𝑡 – 𝑡 + 604800(𝑊𝑁 – 𝑊𝑁 )) 𝑈𝑇𝐶 𝐿𝑆 0 1 𝐸 0𝑡 0t

Case B:

Whenever the user’s current time falls within the time span of six hours prior to the leap second adjustment time to six hours after the djustment time, tUTC shall be computed as follows (ΔtUTC as defined in Case A):

𝑡 = 𝑊 [Modulo (86400 + Δ𝑡 − Δ𝑡 )] 𝑈𝑇𝐶 𝐿𝑆𝐹 𝐿𝑆 where 𝑊 = (𝑡𝐸 − Δ𝑡𝑈𝑇𝐶 − 43200) [Modulo 86400] + 43200

Case C:

Whenever the leap second adjustment time is in the “past” (relative to the user’s current time), and the user’s present time does not fall in the time span which starts six hours prior to the leap second adjustment time, and ends six hours after the adjustment time, tUTC shall be computed

as follows: 𝑡 = (𝑡𝐸 − Δ𝑡 ) [Modulo 86400] 𝑈𝑇𝐶 𝑈𝑇𝐶 where Δ𝑡 = Δ𝑡 + 𝐴 + 𝐴 (𝑡 − 𝑡 + 604800(𝑊𝑁 − 𝑊𝑁 )) 𝑈𝑇𝐶 𝐿𝑆𝐹 0 1 𝐸 0𝑡 0𝑡  A , A , Δt , t , WN , WN , DN and Δt are GST to UTC time 0 1 LS 0t 0t LSF LSF conversion parameters transmitted in F/NAV signals page Type 4 and I/NAV signals word Type 6 as indicated in 3.1.3.1.3;

 t is the GST as estimated by the user through its GST E determination algorithm; and  WN is the week number to which t is referenced.

E

3.1.3.2.4 Satellite position. The Earth-Centred, Earth-Fixed (ECEF) coordinates of the satellite antenna phase centre position at GST time t shall be

computed using the following equations:

196CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 x = x'cos(Ω) - y'cos(i)sin(Ω) y = x'sin(Ω) + y'cos(i)cos(Ω) z = y'sin(i)

3.1.3.2.5 Ionospheric correction.

Note.: Receivers operating in single-frequency mode can use the single- frequency ionospheric correction algorithm described in document 197CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 EUROCAE ED-259 Minimum Operational Performance Standard for Galileo/Global Positioning System/Satellite-based Augmentation System Airborne Equipment, Appendix J (any version).

3.1.3.3 AIRCRAFT ELEMENTS

3.1.3.3.1 GALILEO RECEIVER

3.1.3.3.1.1 Satellite tracking. The receiver shall provide the capability to continuously track a minimum of four Galileo satellites and generate a position solution based upon those measurements.

3.1.3.3.1.2 Doppler shift. The receiver shall be able to compensate for dynamic Doppler shift effects on nominal Galileo signal carrier phase and OS code measurements. The receiver shall compensate for the Doppler shift that is unique to the anticipated application.

3.1.3.3.1.3 Resistance to interference. The receiver shall meet the requirements for resistance to interference as specified in 3.7.

3.1.3.3.1.4 Application of clock and ephemeris data. The receiver shall monitor the IODnav value and update ephemeris and clock data based upon a detected change in this parameter. To compute position and clock corrections, receivers shall use for each satellite, IODnav-tagged parameters corresponding to the same IODnav value. These parameters shall be retrieved from the most recent navigation data set received.

Note.: IODnav values are not necessarily incremented in steps of one. An IODnav with higher value does not necessarily mean that it tags more recent data. The only valid comparison between IODnav values is whether they are equal or not. For positioning, users can combine SIS from different satellites with different IODnav values,

provided that the navigation parameters derived from each satellite are tagged by a unique IODnav value.

3.1.3.3.1.5 Navigation data validity duration. The receiver shall only use the ephemeris and clock corrections from a set of navigation data during a period of time no longer than four hours from the reference time of ephemeris (t0e). The receiver shall not rely on performance commitments in Chapter 3, 3.7.3.1.3, if the age of t0e exceeds four hours.

Note.: See Attachment D, 4.1.3.11 for guidance material on the age of t0e.

3.1.3.4 TIME

3.1.3.4.1 Galileo system time (GST). The GST shall be a continuous timescale based on the definition of the second (according to the International 198CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 System of Units, SI) whose origin/reference epoch (GST (T0)) shall be defined as 13 seconds before 1999-08-22 00:00:00 UTC. The Galileo navigation message shall contain all necessary parameters to convert between GST and UTC.

Note.: See Attachment D, 4.1.3.9 for GST guidance material.

3.1.3.5 COORDINATE SYSTEM

3.1.3.5.1 The Galileo OS broadcast ephemeris shall determine the position of the transmitting antenna phase centre of a given satellite in the Galileo Terrestrial Reference Frame (GTRF) ECEF reference frame.

3.1.3.5.2 The GTRF difference from the latest physical realization of the International Terrestrial Reference Frame (ITRF) shall not exceed 3 cm 95 per cent globally.

Note 1.: WGS-84 and GTRF are both realizations of ITRF. The difference between GTRF and WGS 84 used in GPS, is considered insignificant for aviation.

Note 2.: See Attachment D, 4.1.3.10 for additional information on GTRF.

3.1.4 BeiDou Navigation Satellite System (BDS) Open Service (OS) (B1I, B1C and B2a)

3.1.4.1 NON-AIRCRAFT ELEMENTS

3.1.4.1.1 3.1.4.1.1 BDS RF CHARACTERISTICS Note.: This section describes RF characteristics of the BDS B1I, B1C and B2a signals transmitted by BDS-3 MEO and IGSO satellites.

3.1.4.1.1.1 B1I, B1C and B2a common requirements

3.1.4.1.1.1.1 Carrier phase noise. The carrier phase noise spectral density of the unmodulated carrier on B1I, B1C and B2a shall be such that a third-order phase locked loop of 10 Hz one-sided noise bandwidth is able to track the carrier to an accuracy of 0.1 radian root mean square (RMS).

3.1.4.1.1.1.2 Spurious emissions. In-band spurious emissions shall be at least 50 dB below the unmodulated B1I, B1C and B2a carrier over the allocated channel bandwidth.

Note.: The allocated channel bandwidth for the B1I signal is 4.096 MHz.

The allocated channel bandwidth for the B1C signal is 32.736 MHz.

The allocated channel bandwidth for the B2a signal is 20.46 MHz.

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3.1.4.1.1.1.3 Data/code coherence. The edge of each data symbol shall be aligned with the edge of the corresponding ranging code chip, and the start time of the first chip of the periodic ranging code shall be aligned with the start time of the data symbol bit. The edges of each secondary code chip shall be aligned with the edges of the primary code chip and the primary code first chip start time shall be aligned with the starting time of the secondary code chip.

3.1.4.1.1.2 B1I RF characteristics

3.1.4.1.1.2.1 B1I correlation loss. The correlation loss due to payload distortions shall not exceed 0.6 dB on B1I.

3.1.4.1.1.2.2 B1I ranging code. The chipping rate of the B1I ranging code shall be

2.046 megachips per second, and the length shall be 2 046 chips. The B1I ranging code (hereinafter referred to as CB1I) shall be a balanced Gold code truncated with the last one chip. The Gold code shall be generated by means of Modulo-2 addition of G1 and G2 sequences, which are respectively derived from two 11-bit linear shift registers. The generator of CB1I shall be as shown in Figure B-19.

Note.: Additional information concerning the B1I ranging code is given in the BeiDou Navigation Satellite System Signal In Space Interface Control Document Open Service Signal B1I (Version 3.0), dated February 2019 (hereinafter referred to as “BDS OS B1I ICD”),

section 4.3.

3.1.4.1.1.3 B1C RF characteristics

3.1.4.1.1.3.1 B1C correlation loss. The correlation loss due to payload distortions shall not exceed 0.3 dB on B1C.

3.1.4.1.1.3.2 B1C signal generation. The B1C signal shall comprise two components, known as B1C data component and B1C pilot component.

3.1.4.1.1.3.3 B1C signal power split. The B1C signal power shall be 1:3 split between the B1C data component and the B1C pilot component.

3.1.4.1.1.3.4 B1C data ranging code (CBIC_ ). The B1C data ranging code data sequence shall be a 10 230-chip length primary code repeated every 10 milliseconds.

Note.: Additional information concerning the B1C data primary code is given in BDS OS B1C ICD, section 5.2.1.

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3.1.4.1.1.3.5 B1C pilot ranging code (CBIC_ ). The B1C pilot ranging code sequence pilot shall be the Modulo-2 addition of a 10 230-chip length primary code repeated every 10 milliseconds and a 1 800-chip length secondary code repeated every 18 000 milliseconds.

Note.: Additional information concerning the B1C pilot primary code and secondary code is given in BDS OS B1C ICD, sections 5.2.1 and

5.2.2.

3.1.4.1.1.3.6 B1C data component (SBIC_ ) generation. The B1C data component data shall be generated from the navigation message data (DBIC_data) and the ranging code (CBIC_ ) modulated with the sine-phased BOC(1,1) data subcarrier SCB1C_ .

data

3.1.4.1.1.3.7 B1C pilot component (SBIC_ ) generation. The B1C pilot component pilot shall be generated from the ranging code (CBIC_ ) modulated with the pilot QMBOC(6, 1, 4/33) subcarrier SCB1C_ . The subcarrier shall be pilot composed of a BOC(1, 1) subcarrier and a BOC(6, 1) subcarrier, which shall be in phase quadrature with each other and have a power ratio of 29:4.

Note.: Additional information concerning B1C modulation is given in BDS OS B1C ICD, section 4.2.

3.1.4.1.1.4 B2a RF characteristics

3.1.4.1.1.4.1 B2a correlation loss. The correlation loss due to payload distortions shall not exceed 0.6 dB on B2a.

3.1.4.1.1.4.2 B2a signal generation. The B2a signal shall comprise two components known as B2a data component and B2a pilot component.

3.1.4.1.1.4.3 B2a signal power split. The B2a signal power shall be equally split between the B2a data component and the B2a pilot component.

3.1.4.1.1.4.4 B2a data ranging code (CB2a_ ). The B2a data ranging code data sequence shall be the Modulo-2 addition of a 10 230-chip length primary code repeated every 1 millisecond and a 5-chip length secondary code repeated every 5 milliseconds.

Note.: Additional information concerning B2a_data primary code and secondary code is given in BDS OS B2a ICD, sections 5.2.1 and

5.2.2.

3.1.4.1.1.4.5 B2a pilot ranging code (CB2a_ ). The B2a pilot ranging code sequence pilot shall be the Modulo-2 addition of a 10 230-chip length primary code 201CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 repeated every 10 millisecond and a 100-chip length secondary code repeated every 100 milliseconds.

Note.: Additional information concerning B2a_pilot primary code and secondary code is given in BDS OS B2a ICD, sections 5.2.1 and

5.2.2.

3.1.4.1.1.4.6 B2a data component (SB2a_ ) generation. The B2a data component data shall be BPSK(10) modulated from the navigation message data (DB2a_data) and the ranging code (CB2a_ ). data

3.1.4.1.1.4.7 B2a pilot component (SB2a_pilot) generation. The B2a pilot component shall be BPSK(10) modulated from the ranging code CB2a_ (t) only. pilot Note.: Additional information concerning B2a modulation is given in BDS OS B2a ICD, section 4.2.

3.1.4.1.2 DATA STRUCTURE

3.1.4.1.2.1 B1I D1 message characteristics

3.1.4.1.2.1.1 General. The B1I navigation message broadcast by BDS-3 MEOs and IGSOs B1I signals (“D1 navigation message”) shall be modulated with 1 kbps secondary Neuman-Hofman (NH) code. The D1 navigation message shall be structured into superframes, frames and subframes.

The frame structure of the D1 navigation message shall be as shown in Figure B-20.

Note.: Additional information concerning the NH code is given in BDS OS B1I ICD, section 5.2.1.

3.1.4.1.2.1.2 Superframe. Every superframe shall contain 36 000 bits. Every superframe shall be composed of 24 frames (24 pages).

3.1.4.1.2.1.3 Frame. Every frame shall contain 1 500 bits. Every frame shall be composed of 5 subframes.

3.1.4.1.2.1.4 Subframe. Every subframe shall contain 300 bits. Every subframe shall be composed of 10 words. Every word shall contain 30 bits. Every word shall consist of navigation message data and parity bits.

3.1.4.1.2.1.5 Data parity. Word 1 of each subframe shall contain 26 information bits and 4 parity bits in the least significant bits (LSBs), and words 2 through 10 shall contain 22 information bits and 8 parity bits in the LSBs. Bose- Chaudhuri- Hocquenghem (BCH)(15,11,1) encoding shall be used for error control and interleaving.

202CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.: Additional information concerning BCH(15,11,1) encoding is given in BDS OS B1I ICD, section 5.1.3.

3.1.4.1.2.1.6 Preamble. Bits 1 through 11 of every subframe shall contain a preamble consisting of the sequence of bits “11100010010”.

3.1.4.1.2.1.7 Subframe identification. Bits 16 through 18 of every subframe shall contain the subframe identification, encoded as follows:

3.1.4.1.2.1.8 Seconds-of-week (SOW). Bits 19 through 26 and bits 31 through 42 of each subframe of the D1 navigation message shall contain the 20-bit seconds-of-week (SOW), which is defined as the number of seconds that have occurred since the last Sunday, 00:00:00 BDT. The SOW count shall occur at the leading edge of the first preamble bit (MSB) of the subframe.

3.1.4.1.2.1.9 Reserved bits. Bits 12 through 15 of every subframe or page of a subframe shall be reserved.

3.1.4.1.2.2 B1C message characteristics

3.1.4.1.2.2.1 General. The B1C navigation message (B-CNAV1 navigation message) shall be broadcast as a sequence of frames. Each frame shall contain 1 800 symbols with a symbol rate of 100 symbols per second. Each frame shall consist of three subframes with the basic frame structure shown in Figure B-21.

3.1.4.1.2.2.2 Subframe 1. Subframe 1 shall contain 14 bits before BCH error correction encoding. After BCH (21,6) + BCH (51,8) encoding, its length shall be 72 symbols.

Note.: Additional information concerning BCH(21,6)+BCH(51,8) encoding is given in BDS OS B1C ICD, section 6.2.2.1.

3.1.4.1.2.2.3 Subframe 2. Subframe 2 shall contain 600 bits before low-density parity check (LDPC) encoding. The 576 MSBs of subframe 2 shall be included in the CRC calculation, and the 24 LSBs shall be the corresponding CRC bits. After 64- ary LDPC (200, 100) encoding, its length shall be 1 200 symbols.

Note.: Additional information concerning 64-ary LDPC (200, 100) encoding is given in BDS OS B1C ICD, section 6.2.2.2.

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3.1.4.1.2.2.4 Subframe 3. Subframe 3 shall contain 264 bits before LDPC encoding.

The 6 MSBs shall be the page type (PageID), the 24 LSBs shall be CRC bits, and the remaining 234 bits shall be message data. PageID and message data shall be included in the CRC calculation. After 64-ary LDPC (88,44) encoding, its length shall be 528 symbols. The frame structure of subframe 3 shall be as shown in Figure B-22.

Note.: Additional information concerning 64-ary LDPC (88,44) encoding is given in BDS OS B1C ICD, section 6.2.2.3.

3.1.4.1.2.2.5 Interleaving. After encoding, subframe 2 and subframe 3 shall be combined and interleaved using a block interleaver.

Note.: Additional information concerning interleaving is given in BDS OS B1C ICD, section 6.2.2.4.

3.1.4.1.2.3 B2a message characteristics

3.1.4.1.2.3.1 General. The B2a navigation message (“B-CNAV2 navigation message”) shall be broadcast as a sequence of frames. Each frame shall contain 600 symbols with a symbol rate of 200 symbols per second. The B- CNAV2 basic frame structure shall be as shown in Figure B-23.

3.1.4.1.2.3.2 Frame structure. Each frame shall consist of a 24-symbol preamble and a 288-bit navigation message before error correction encoding. After encoding by 64-ary LDPC (96,48), its length shall be 1 200 symbols.

Note. Additional information concerning 64-ary LDPC (96,48) encoding is given in BDS OS B2a ICD, section 6.2.2.

3.1.4.1.2.3.2.1 Preamble. Each frame shall contain a preamble consisting of the sequence of bits “111000100100110111101000”.

3.1.4.1.2.3.2.2 Navigation message. Each frame shall contain 288 bits before LDPC encoding, including the 6-bit PRN code, 6-bit message type, 18- bit SOW, 234-bit message data and 24-bit CRC. PRN, message type, SOW, and message data shall be included in the CRC calculation. After 64-ary LDPC(96, 48) encoding, the frame length shall be 576 symbols.

3.1.4.1.3 DATA CONTENT Note.: A full description of the data content of the words being transmitted is given in BDS OS B1I ICD, BDS OS B1I ICD and BDS OS B2a ICD.

3.1.4.1.3.1 B1I data content 204CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.4.1.3.1.1 The B1I D1 navigation data shall contain the information listed in Table B-42.

Note.: Additional information concerning B1I D1 content and application of the data is given in BDS OS B1I ICD, section 5.2.4.

3.1.4.1.3.1.2 User range accuracy index (URAI). Bits 49 through 52 of subframe 1 of the D1 message shall contain the URAI. The range of URAI shall be from 0 to 15. The user range accuracy (URA) shall be used to describe the signal-in-space accuracy (SISA) in metres. The relationship between URAI and URA shall be as shown in Table B-43.

Note.: Additional information concerning URAI is given in BDS OS B1I ICD,

section 5.2.4.5 and section 5.2.3, Figure 5-8.

205CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.4.1.3.1.3 Autonomous satellite health flag (SatH1). Bit 43 of subframe 1 of the D1 message shall provide SatH1. A value of “0” shall indicate that the broadcasting satellite is healthy and a value of “1” shall indicate that the broadcasting satellite is unhealthy.

Note.: Additional information concerning SatH1is given in BDS OS B1I ICD,

section 5.2.4.6 and section 5.2.3, Figure 5-8.

3.1.4.1.3.1.4 Satellite clock correction parameter t shall be broadcast in the D1 oc navigation message. The value of t shall monotonically increase over oc the week and shall change if any of the clock parameters change.

Note.:The update of the clock parameters always starts at the beginning of a superframe.

3.1.4.1.3.1.5 Satellite ephemeris parameter toe shall be broadcast in the D1 navigation message. The value of toe shall monotonically increase over the week and shall change if any of the ephemeris parameters change. If toe changes, then toc shall also change.

Note.: The update of the ephemeris parameters always starts at the beginning of a superframe.

206CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.4.1.3.1.6 Page number (Pnum). Both subframe 4 and subframe 5 shall have 24 pages which shall be identified through the page number (Pnum) contained in bits 44 through 50 of the subframes.

3.1.4.1.3.1.7 Identification of expanded almanacs (AmEpID). Bits 291 through 292 of pages 1 through 24 of subframe 4 and pages 1 to 6 of subframe 5 shall contain AmEpID. A binary value of “11” of AmEpID shall indicate that pages 11 through 23 of subframe 5 are used to broadcast the almanac parameters for SV ID 31 through 63, and page 24 of subframe 5 is used to broadcast the satellite health information for SV ID 31 through 63.

Otherwise, pages 11 through 24 of subframe 5 shall be reserved.

3.1.4.1.3.1.8 Identification of time-sharing broadcasting (AmID). Bits 291 through 292 of pages 11 through 23 of subframe 5 and bits 216 through 217 of page 24 of subframe 5 shall provide AmID. AmID shall be used combining with AmEpID and Pnum to indicate the PRN of the satellite transmitting the almanac parameters in the Pnum page. AmID shall only be used when AmEpID has a binary value of “11”. The broadcasting scheme for the almanac parameters of SV ID 31 through 63 shall be as shown in Table B-44.

3.1.4.1.3.2 B1C and B2a data content

3.1.4.1.3.2.1 The B-CNAV1 data broadcasted on B1C shall contain the information listed in Table B-45. The B-CNAV2 data broadcasted on B2a shall contain the message types and data content listed in Table B-46.

Note 1.: Additional information concerning B-CNAV1 data content and application of the data is given in BDS OS B1C ICD, section 7.

Note 2.: Additional information concerning B-CNAV2 data content and application of the data is given in BDS OS B2a ICD, section 7.

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3.1.4.1.3.2.2 Page type. Page ID shall be used to identify the page types of subframe 3 in B CNAV1. It shall be a 6-bit unsigned integer. Its definition shall be as shown in Table B-47.

3.1.4.1.3.2.3 Message type (MesType). Message type shall be used to identify the message types of the B-CNAV2 frames. It shall be a 6-bit unsigned integer. Its definition shall be as shown in Table B-48.

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3.1.4.1.3.2.4 Issue of data Note 1.: Additional information concerning B1C issue of data is given in BDS OS B1C ICD, section 7.4.1, Table 7-3 and section 7.4.2, Table 7-4.

Note 2.: Additional information concerning B2a issue of data is given in BDS OS B2a ICD, section 7.4.1, Table 7-3 and section 7.4.2, Table 7-4.

3.1.4.1.3.2.4.1 Issue of data, ephemeris (IODE). IODE shall indicate the issue number of a set of ephemeris parameters. The IODE value shall be updated when any ephemeris parameter is updated. The IODE values shall indicate the range of the ephemeris data age. The ephemeris data age shall be defined as the offset between the ephemeris parameters reference time (toe) and the last measured time for generating the ephemeris parameters. The values of IODE shall not be repeated within any 24 hours. The relationship between the IODE values and the ephemeris data age shall be as in Table B-49.

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3.1.4.1.3.2.4.2 Issue of data, clock (IODC). IODC shall indicate the issue number of a set of clock correction parameters. The IODC value shall be updated when any clock correction parameter is updated. The IODC values shall indicate the range of the clock correction data age. The clock correction data age shall be defined as the offset between the clock correction parameters reference time (toc) and the last measured time for generating the clock correction parameters. The range of the clock correction data age shall be defined by the 2 MSBs of IODC together with the 8 LSBs of IODC. The values of IODC shall not be repeated within any 24 hours. The relationship between the IODC values and the clock correction data age shall be as in Table B-50.

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3.1.4.1.3.2.5 Satellite health status. Satellite health status (SHS) shall indicate the health status of the transmitting satellite. The definitions of the SHS parameter shall be as shown in Table B-51.

Note 1.: Additional information concerning B1C SHS is given in BDS OS B1C ICD,

section 7.14, Table 7-22.

Note 2.: Additional information concerning B2a SHS is given in BDS OS B2a ICD,

section 7.14, Table 7-22.

3.1.4.1.3.2.6 Satellite integrity status. The satellite integrity status shall be conveyed

by two parameters: data integrity flag (DIF) and signal integrity flag (SIF).

Each of them shall occupy 1 bit and their definitions shall be as shown in Table B-52.

Note 1.: Additional information concerning the B1C satellite integrity status flag is given in BDS OS B1C ICD, section 7.15, Table 7-23.

Note 2.: Additional information concerning the B2a satellite integrity status flag is given in BDS OS B2a ICD, section 7.15, Table 7-23.

3.1.4.1.3.2.7 Satellite signal-in-space health status (SISHS)

3.1.4.1.3.2.7.1 BDS OS signal-in-space health status (SISHS) shall take one of the

three states: a) healthy: the signal meets the minimum service performance specified in this document;

212CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 b) unhealthy: the signal is not providing services or is being tested; and c) marginal: the signal is neither of the two previous states.

3.1.4.1.3.2.7.2 The B1C and B2a SISHS shall be indicated by the combination of four

SIS flags: HS, SIF and DIF. The mapping between the values of the three flags and B1C/B2a SISHS shall be as shown in Table B-53.

3.1.4.1.3.2.8 Signal-in-space accuracy (SISA) indices. The SISA shall describe the predictive accuracy of the orbital parameters and clock correction parameters broadcast in the navigation message. It shall comprise the along-track and cross-track accuracy of the satellite orbit (SISA ) as oe well as the satellite orbital radius and satellite clock correction accuracy (SISA ). The SISA index parameters listed below shall be oc used to calculate SISAoe and SISAoc and shall be broadcast in B- CNAV1 Subframe 3 for B1C and B CNAV2 message Type 40 for B2a,

respectively: a) SISAIoe which is a signed, two’s complement integer in the range of +15 to -16 shall indicate the combined satellite along-track and cross-track orbit accuracy as shown in Table B-54; b) SISAIocb which is a signed, two’s complement integer in the range of +15 to -16 shall indicate the combined satellite orbit radial and satellite clock bias accuracy as shown in Table B-55;

c) SISAIoc1 with an integer value in the range of 0 to 7 shall indicate the satellite clock drift accuracy; d) SISAIoc2 with an integer value in the range of 0 to 7 shall indicate the satellite clock drift rate accuracy; and e) top shall indicate the time of week for data prediction.

213CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note 1.: Additional information concerning the SISA index parameters is given in BDS OS B1C ICD, section 7.16.

Note 2.: Additional information concerning the SISA index parameters is given in BDS OS B2a ICD, section 7.16.

214CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 215CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 216CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.4.2 DEFINITIONS OF PROTOCOLS FOR DATA APPLICATION Note.: This section defines the inter-relationships of the data broadcast message parameters. It provides definitions of parameters that are not transmitted but are used by either or both non-aircraft and aircraft elements, and that define terms applied to determine the navigation solution and its integrity.

3.1.4.2.1 Parity algorithms.

3.1.4.2.1.1 The D1 message uses BCH(15,11,1) encoding as parity algorithms as indicated in 3.1.4.1.2.1.5.

3.1.4.2.1.2 The B-CNAV1 message and the B-CNAV2 message use a 24-bit CRC.

The CRC shall be calculated in accordance with 3.7, with the following

generator polynomial:

217CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

where:

G = 1 for 0, 1, 3, 4, 5, 6, 7, 10, 11, 14, 17, 18, 23, 24 and i 0 otherwise.

3.1.4.2.2 Satellite clock correction parameters.

3.1.4.2.2.1 BDS system time t shall be computed as follows: t = t – Δt sv sv

where: t = BDT in seconds at time of signal transmission; t = the effective satellite ranging code phase time in seconds at time of sv signal transmission; and Δt = the offset of satellite ranging code phase time in seconds defined sv as:

Δt = a + a (t – t ) + a (t – t )2 + Δt sv 0 1 oc 2 oc r

where: a , a and a and t are parameters transmitted in D1 navigation 0 1 2 oc message subframe 1, in B CNAV1 subframe 2 and BCNAV2 message Types 30, 31, 32, 33 and 34; and Δt is the relativistic effect correction r

term defined as: Δt, = F ∙ e ∙ √A ∙ sin E , r k

where: e, √𝐴, E , are parameters that can get from D1 navigation message k subframe 2 and subframe 3, from B-CNAV1 subframe 2 and B-CNAV2 message Types 10 and 11;

F = -2μ1/2/c2; μ = 3.986004418×1014 m3/s2 is the value of the earth’s universal gravitational constant; and c = 2.99792458×108 m/s is the speed of light.

3.1.4.2.2.2 BDS system time related to UTC (NTSC) time. BeiDou system time offset with respect to UTC shall be determined by using B1I data, B1C data or B2a data.

Note.: Additional information concerning time parameters and algorithms relating BeiDou system time to UTC is given in section 5.2.4.18, BDS OS B1I ICD; section 7.12, BDS OS B1C ICD; and section 7.12, BDS OS B2a ICD.

3.1.4.2.3 Satellite position.

3.1.4.2.3.1 B1I satellite position solution. The current satellite position shall be computed as shown in Table B-56.

218CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note 1. : The current satellite position is defined using ephemeris parameters.

The ephemeris parameters (toe, √𝐴, e, ω, Δn, M0, Ω0, 𝛺̇, i0, IDOT, Cuc, Cus, Crc, Crs, Cic, Cis) used in the B1I satellite position solution are parameters transmitted by D1 navigation message subframe 2 and subframe 3.

Note 2.: Additional information concerning ephemeris parameters and algorithms is given in BDS OS B1I ICD, section 5.2.4.12.

219CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.4.2.3.2 B1C and B2a satellite position solution. The current satellite position shall be computed as shown in Table B-57.

Note 1.: The current satellite position is defined using ephemeris parameters.

The ephemeris parameters (toe, SatType, ΔA, 𝐴̇, Δn0, Δ𝑛0 ̇ , M0, e, ω, Ω0, i0, 𝛺̇, 𝑖̇0 , Cis, Cic, Crs, Crc, Cus, Cuc) used in the B1C and B2a satellite position solution are parameters transmitted by B- CNAV1 navigation message subframe 2 and 3, or by B-CNAV2 navigation message Type 10 and message Type 11.

Note 2.: Additional information concerning ephemeris parameters and algorithms is given in BDS OS B1C ICD, section 7.7, and in BDS OS B2a ICD, section 7.7.

220CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.4.2.4 Ionospheric delay correction.

3.1.4.2.4.1 B1I ionospheric delay correction. The B1I ionospheric delay correction shall be computed as shown in Table B-58.

221CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.: Additional information concerning B1I ionospheric delay correction parameters and user algorithms is given in BDS OS B1I ICD, section

5.2.4.7.

3.1.4.2.4.2 3.1.4.2.4.2 B1C and B2a ionospheric delay correction.

3.1.4.2.4.2.1 Single-frequency ionospheric delay correction. The B1C or B2a ionospheric delay correction shall be computed as shown in Table B-59.

222CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 223CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 224CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.: Additional information concerning ionospheric delay correction model parameters broadcast on B1C and B2a and the user algorithms are given in BDS OS B1C ICD, section 7.8.2, Table 7-12, and in BDS OS B2a ICD, section 7.8.2, Table 7-12.

3.1.4.2.4.2.2 Dual-frequency ionospheric delay correction For the dual-frequency user applying the B1C and B2a signals, the effect of the ionospheric delay shall be corrected by using the dual-frequency ionosphere-free pseudo-range.

The dual-frequency ionosphere-free pseudo-range from the B1C pilot component and the B2a pilot component (PR ) shall be computed B1Cp- B2ap

as follows:

The dual-frequency pseudo-range from the B1C pilot component and the B2a data component (PR ) shall be computed as follows:

B1Cp-B2ad The dual-frequency pseudo-range from the B1C data component and the B2a pilot component (PR ) shall be computed as follows:

B1Cd-B2ap 225CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.1.4.2.4.2.3 The dual-frequency pseudo-range from the B1C data component and the B2a data component (PR ) shall be computed as follows:

B1Cd-B2ad where , is the factor associated with frequency; 𝑃𝑅 is the measured pseudo-range of the B1C pilot component B1Cp (corrected by the clock correction but not corrected by T );

GDB1Cp 𝑃𝑅 is the measured pseudo-range of the B1C data component B1Cd (corrected by the clock correction but not corrected by T and GDB1Cp ISC );

B1Cd 𝑃𝑅 is the measured pseudo-range of the B2a pilot component B2ap (corrected by the clock correction but not corrected by T );

GDB2ap 𝑃𝑅 is the measured pseudo-range of the B2a data component B2ad (corrected by the clock correction but not corrected by T and GDB2ap ISC );

B2ad T is the group delay differential of the B1C pilot component;

GDB1Cp T is the group delay differential of the B2a pilot component;

GDB2ap ISC is the group delay differential between the B1C data component B1Cd and the B1C pilot component;

ISC is the group delay differential between the B2a data component B2ad and the B2a pilot component; c = 2.99792458×108 m/s is the speed of light.

Note 1.: Additional information concerning B1C ionospheric delay model parameters is given in BDS OS B1C ICD, section 7.8.

Note 2.: Additional information concerning B2a ionospheric delay model parameters is given in BDS OS B2a ICD, section 7.8.

3.1.4.2.5 SISA calculation for B1C and B2a.

The signal-in-space accuracy (SISA) for integrity use shall be calculated as: 𝑆𝐼𝑆𝐴 = √(𝑆𝐼𝑆𝐴 × sin14°)2 + 𝑆𝐼𝑆𝐴 2 𝑜𝑒 𝑜𝑒 226CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 where SISAoe is the upper bound value corresponding to the SISAoe index “N” as broadcast in B-CNAV1 Subframe 3 for B1C and in B- CNAV2 message Types 34 and 40 for B2a, respectively (defined in 3.1.4.1.3.2.8) as shown in Table B-54.

SISA shall be calculated with the following equations (in metres): oc where SISA is the upper bound value corresponding to the ocb SISA index “N” as broadcast in B-CNAV1 Subframe 3 for ocb B1C and in B-CNAV2 message Types 34 and 40 for B2a, respectively (defined in 3.1.4.1.8) as shown in Table B-55;

SISAoc1 is the satellite clock drift accuracy in metres per second derived from SISAIoc1 (defined in 3.1.4.1.3.2.8) as

follows: 𝑆𝐼𝑆𝐴 = 2−(𝑆𝐼𝑆𝐴𝐼𝑜𝑐1 +14) 𝑜𝑐1 SISAoc2 is the satellite clock drift rate accuracy in metres per square second derived from SISAIoc2 (defined in

3.1.4.1.3.2.8) as follows: 𝑆𝐼𝑆𝐴 = 2−(𝑆𝐼𝑆𝐴𝐼𝑜𝑐2 +28) 𝑜𝑐2 where t is the BDS system time in second; t is the time of week for data prediction in second op broadcast in B-CNAV1 subframe 3 for B1C and in B CNAV2 message Types 34 and 40 for B2a, respectively.

3.1.4.3 AIRCRAFT ELEMENTS

3.1.4.3.1 BDS RECEIVER

3.1.4.3.1.1 Satellite tracking. The receiver shall provide the capability to continuously track a minimum of four BDS satellites and generate a position solution based upon those measurements.

3.1.4.3.1.2 Doppler shift. The receiver shall be able to compensate for dynamic Doppler shift effects on nominal BDS OS signal carrier phase and ranging code measurements. The receiver shall compensate for the Doppler shift that is unique to the anticipated application.

3.1.4.3.1.3 Resistance to interference. The receiver shall meet the requirements for resistance to interference as specified in 3.7.

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3.1.4.3.1.4 Application of clock and ephemeris data. The receiver shall ensure that it is using the correct ephemeris and clock data before providing any position solution. For B1I, the receiver shall monitor the parameters toc and toe to update clock and ephemeris data based upon the detected change in these parameters. For B1C and B2a, the receiver shall monitor the parameters IODC and IODE to update clock and ephemeris data based upon the detected change in these parameters.

3.1.4.4 TIME The time reference for BDS shall be the BeiDou Navigation Satellite System Time (BDT). BDT shall adopt the International System of Units

(SI) seconds, and shall accumulate continuously without leap seconds.

The start epoch of BDT shall be 00:00:00 on 1 January 2006 of Coordinated Universal Time (UTC). BDT shall connect with UTC via UTC

(NTSC), and the deviation of BDT to UTC shall be maintained within 50 nanoseconds (Modulo 1 second). The leap seconds shall be broadcast in the navigation (NAV) message.

3.1.4.5 COORDINATE SYSTEM

3.1.4.5.1 BeiDou Coordinate System. The BDS broadcast ephemeris shall describe the position of the transmitting antenna phase centre of a given satellite in the BeiDou Coordinate System (BDCS).

3.1.4.5.2 The difference between the latest physical realization of ITRF and BDCS shall not exceed 3 cm (95 per cent).

Note 1.: WGS-84 and BDS terrestrial reference frame BDCS are both realizations of ITRF. The difference between BDCS and WGS-84 used in GPS is considered insignificant for aviation.

Note 2.: Additional information on the BDCS is in Attachment D, 4.1.4.9.

3.2 (Reserved)

3.3 Use of multiple core satellite constellations

3.3.1 AIRCRAFT ELEMENTS

3.3.1.1 Multi-constellation GNSS receiver. The multi-constellation GNSS receiver shall process signals from two or more core satellite constellations in accordance with the requirements specified in 3.1.1.3.1, GPS receiver,

3.1.2.3.1, GLONASS receiver, 3.1.3.3.1, Galileo receiver and 3.1.4.3.1, BDS receiver.

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3.3.1.1.1 Resistance to interference. The multi-constellation GNSS receiver shall meet the individual requirements for the core satellite constellations processed as specified in 3.7.

3.3.1.2 Antenna(e). Core satellite constellation signals shall be received through one or more antennae.

Note.: Performance characteristics of GNSS receiver antennae are defined in 3.8.

3.3.1.3 Position information provided by a multi-constellation GNSS receiver shall be expressed in WGS-84 earth coordinates.

3.3.1.4 When combining measurements from core satellite constellations, the difference among each core satellite constellation reference time shall be taken into account.

3.3.1.4.1 Multi-constellation GNSS receivers shall solve for the time offset between the core constellations as an additional unknown parameter in the navigation solution and not only rely on the time offset broadcast in the navigation messages.

3.4 Aircraft-based augmentation system (ABAS) Note.: Guidance on ABAS and associated signal processing is given in Attachment D, section 5.

3.4.1 Advanced Receiver Autonomous Integrity Monitoring (ARAIM) ARAIM shall consist of a non-aircraft subsystem and an aircraft subsystem. The non- aircraft subsystem shall provide, for each core satellite constellation supported, fault characteristics of the constellation, fault characteristics of the satellites and ranging error models. The aircraft subsystem shall apply the data

provided by the non-aircraft subsystem, complemented as appropriate by fault characteristics and ranging error models of the aircraft subsystem components, to meet the requirements as specified in Chapter 3, 3.7.3.3.1.

Note 1.: The non-aircraft subsystem performs its function by providing integrity support data (ISD as specified below) either through broadcast navigation data or through default values stored in receiver memory. Broadcast navigation data for ARAIM can be contained either in dedicated navigation data messages (ISM as defined below) or in other navigation data messages from core satellite constellations.

Note 2.: For GNSS receivers using ARAIM, ranging error models include ionosphere, troposphere, multipath, antenna bias and receiver noise.

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3.4.1.1 Integrity support data (ISD) data content

3.4.1.1.1 ISD general information. The ISD general information shall be as follows:

Validity time: this field shall specify when ISD can be applied by the GNSS receiver using ARAIM.

Applicable core satellite constellation: this field shall identify to which core satellite constellation the ISD applies.

ARAIM service type: this field shall indicate the performance level supported by the ISD parameters.

ARAIM service type A: the ISD supports horizontal positioning for typical operations of en-route, terminal, initial approach, intermediate approach, non-precisions approach and departure in accordance with Chapter 3,

3.7.3.3.1.

ARAIM service type B: reserved.

Note 1.: Aircraft manufacturers may integrate ARAIM with other ABAS system elements to support additional applications, subject to approval by the appropriate regulatory authority.

Note 2.: There may be multiple active sets of ISD per constellation (i.e. different data sets supporting different service types).

Note 3.: ARAIM service type B performance is expected to support typical operations of approach with vertical guidance through Category I precision approach.

3.4.1.1.2 Constellation-specific ISD parameters. The constellation-specific ISD shall

be as follows:

Satellite mask: this field shall indicate to which satellite (within the given core satellite constellation) the ISD parameters apply.

Note.: The interpretation of the satellite mask by the ISMG and the aircraft receiver is specified in 3.4.1.2.2.2 and 3.4.1.3.3.2, respectively.

P : the probability that two or more satellites within a core satellite const constellation have faulted signals concurrently due to a common cause.

P : the probability that a satellite has a faulted signal, where the faulted sat signal occurs only on one satellite or has independent causes if occurring on more than one satellite.

R : the rate at which two or more satellites within a core satellite const constellation have faulted signals concurrently due to a common cause.

230CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 R : the rate at which individual satellites have a faulted signal, where the sat faulted signal occurs only on one satellite or has independent causes if occurring on more than one satellite.

MFD : the mean duration of faulted signals of two or more satellites const within a core satellite constellation due to a common cause.

MFD : the mean duration of individual satellites having a faulted signal. sat σ : the overbounding integrity range error model parameter to be applied URA for a given satellite signal. σ : the accuracy and continuity range error model parameter to be URE applied for a given satellite signal.

b : the overbounding bias term for a given satellite signal. nom Note 1. — A faulted signal and the associated fault event occurs when one or more signals indicated as healthy from a given satellite are in fact faulted as described in 3.4.1.2.2.1 and Attachment D, 5.3.1.3. A faulted signal ends through action by the core satellite constellation, either by removal of the cause of the fault or by indication that the affected satellite or satellites are not healthy.

Note 2. — ISD parameters apply to healthy signals.

Note 3. — Some core satellite constellation providers may use the term “mean time to notify” (MTTN or MTN) interchangeably with MFD.

Note 4. — More detailed explanations of the terms σ , σ and b , URA URE nom are given in 3.4.1.2.2.1 and Attachment D, 5.3.1.4.

3.4.1.2 ARAIM non-aircraft elements

3.4.1.2.1 ISD broadcast and application requirements Note.: These requirements determine how ISD are broadcast to the user by the core satellite constellations.

3.4.1.2.1.1 The broadcast ISD shall be defined by the applicable core satellite constellation providers in interface specifications.

Note 1.: The interface specifications define on which signals and in which messages the ISD parameters are encoded.

Note 2.: For GPS, σ and σ are specified in IS-GPS-705F (message type 10 URA URE and message types 30 through 37) and in IS-GPS-200K (subframe 1).

231CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note 3.: ISM interface specifications for GPS, GLONASS and BDS are under development.

3.4.1.2.1.2 ARAIM augmented satellite signals The ISD parameters shall apply to core satellite constellation signals as

specified below:  For GPS: GPS L1 C/A signal (3.1.1 and Chapter 3, 3.7.3.1.1.8) and GPS L5 signal (3.1.1 and Chapter 3, 3.7.3.1.1.8).  For GLONASS: GLONASS L1OF signal (3.1.2 and Chapter 3,

3.7.3.1.2.8), GLONASS L1OC signal (3.1.2 and Chapter 3,

3.7.3.1.2.10) and GLONASS L3OC signal (3.1.2 and Chapter 3,

3.7.3.1.2.9).  For Galileo: Galileo E1 signal (3.1.3.1.1 and Chapter 3, 3.7.3.1.3.11.1) and Galileo E5a signal (3.1.3.1.1 and Chapter 3, 3.7.3.1.3.11.2).  For BDS: BDS B1C signal (3.1.4 and Chapter 3, 3.7.3.1.4.7) and BDS B2a signal (3.1.4 and Chapter 3, 3.7.3.1.4.7).

3.4.1.2.1.3 ISD and ISM timing

3.4.1.2.1.3.1 When a core satellite constellation broadcasts ISD, the core satellite constellation shall transmit and disseminate worldwide a complete set of broadcast ISD at a minimum broadcast rate(maximum repeat interval) of 15 minutes.

Note.: A complete set of broadcast ISD includes both the entire set of ISD within ISM(s) for a given service type, for all supported satellites and any associated ISD not contained in ISM (e.g. in other navigation data messages). This does not imply a requirement to broadcast ISD for all satellites of a specific core satellite constellation.

3.4.1.2.1.3.2 The validity time, as defined in 3.4.1.1.1, shall: a) indicate the start time of ISD applicability; or b) indicate a start time and an expiration time.

3.4.1.2.1.3.2.1 When no expiration time is provided, the ISMG shall update the broadcast ISD to maintain compliance with 3.4.1.2.2.1.

Note.: The core satellite constellation interface specifications for broadcast ISD (3.4.1.2.1.1) define the associated protocols for data application, including ISD updating.

3.4.1.2.1.3.3 For a default ISD as specified in 3.4.1.3.3.3, the validity time shall not expire as long as the data remains present in a receiver.

Note.: Default ISD values are based on core satellite constellation minimum 232CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 performance commitments. They can only be modified by a change to these performance commitments. Airborne equipment maintenance action would be necessary to update these ISD parameters.

3.4.1.2.2 ISM generator requirements (data content) Note.: The ISM generator (ISMG) is an entity separate from core satellite constellation provider and performing an air navigation service provider function limited to ARAIM. It is expected that close cooperation will exist between the two entities. Further guidance is contained in the Global Navigation Satellite System (GNSS) Manual (Doc 9849).

3.4.1.2.2.1 Overbounding

3.4.1.2.2.1.1 The ISMG shall ensure that default and broadcast ISD parameters are

provided such that the fault-free ranging signal errors are left- and right- overbounded over an interval limited by a not-to-exceed (NTE) threshold, [-NTE, NTE] by the following: a) for integrity: a gaussian distribution N(-b , σ ) for left side nom URA overbounding and N(b , σ ) for right side overbounding;

nom URA b) for accuracy and continuity (false alert or failed exclusion): a gaussian distribution N(0, σ ).

URE

3.4.1.2.2.1.2 The ISMG shall ensure that P and R provide an upper bound of the sat sat probability and rate that an individual satellite broadcasts signals that cause ranging signal errors outside the interval [-NTE, NTE].

3.4.1.2.2.1.3 The ISMG shall ensure that P and R provide an upper bound of the sat sat probability and rate that more than one satellite concurrently broadcast signals due to a common cause that cause ranging signal errors outside the interval [-NTE, NTE].

Note 1.: Faulted signals are signals with ranging errors outside the interval [-NTE, NTE]. Fault-free signals are signals with ranging errors within the interval [-NTE, NTE]. ARAIM accounts for errors due to faulted signals through P and R and for errors due to fault-free signals through σ and const const URA σ . Further guidance is provided in Attachment D, 5.3.1.3 to 5.3.1.5.

URE Note 2.: Core satellite constellation service providers distinguish between fault-free and faulted ranging signals using a predefined core satellite constellation service provider NTE. By this definition, all signals with errors below the threshold are considered fault-free signals and all signals with errors that are above the threshold are considered faulted signals. Fault-free signals include ranging errors due to system-inherent properties as well as any faults characterized by a limited amplitude and frequency which maintain 233CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 compliance with the overbounding conditions. The ISMG can use this definition to determine the overbounding parameters. However, the ISMG may consider errors below the core satellite constellation service provider NTE as faulted to improve σ , provided that P , P , R and R URA sat const sat const still meet the requirement in 3.4.1.2.2.1.2 and 3.4.1.2.2.1.3.

Note 3.: For consistency with the Gaussian overbounding of fault-free signals, the NTE value is typically set to k × σ where k corresponds to the inverse URA of the normal cumulative distribution function of P /2. For example, for sat GPS and P of 10-5, the corresponding NTE is specified as 4.42 × σ sat URA and 4.42 corresponds to the inverse of the normal cumulative distribution function of a probability of 0.5 × 10-5. The division by two is because the fault magnitude can be positive or negative. Alternatively, the NTE can be a fixed value.

Note 4.: The ARAIM airborne algorithm will achieve the intended integrity risk when b and σ bound the fault-free distribution and P , R , P and nom URA sat sat const R characterize the faulted distributions for both single and dual const frequency signal processing. The ARAIM airborne algorithm does not explicitly use NTE.

3.4.1.2.2.2 Satellite mask. The ISM generator shall ensure that all satellites set to valid in the ISD satellite mask meet the requirements in section 3.4.1.2.2.1 for the associated ISD content.

3.4.1.2.2.3 R , P , and MFD . If multiple ISM are provided for a given const const const constellation and ARAIM service type, the R , P and MFD for a const const const given validity time shall be the same.

3.4.1.2.2.4 Relationship between ISD values and core satellite constellation provider minimum service commitments. For Service Type A, broadcast ISD values as defined in 3.4.1.1 shall always be set to indicate a performance that is equal to or better than the default values specified in 3.4.1.3.3.3.

3.4.1.2.3 ISD parameter integrity requirements

3.4.1.2.3.1 The ISMG shall generate ISD for ARAIM service type A such that GNSS receivers using ARAIM can perform monitoring to meet a 10-7/hour integrity risk using both single and dual frequency signal processing.

3.4.1.2.3.2 Procedures shall be put in place by the ISMG such that the integrity assurance process mitigates the effects of internal faults, to a level consistent with the supported ARAIM service type.

3.4.1.2.4 ISM transmission / data integrity requirements

3.4.1.2.4.1 The data integrity of the ISM parameters shall be maintained throughout the data chain from origination by the ISMG, handover to and broadcast to 234CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 the user by the core satellite constellation to a level consistent with the supported ARAIM service type.

Note.: Further guidance on ISD parameter data integrity is provided in Attachment D, 5.3.1.7.

3.4.1.2.4.2 A core satellite constellation using cyclic redundancy checks (CRC) for ISM data integrity shall calculate the CRC in accordance with the requirements in 3.9.

Note.: Detailed user implementation guidance is provided in core satellite constellation interface documentation as specified in 3.4.1.2.1.1.

3.4.1.2.5 Receiver design constraint assumptions for ISD generation

3.4.1.2.5.1 The ISMG shall validate broadcast ISD assuming that the GNSS receiver using ARAIM is compliant with the following constraints when processing L1, L5, E1, E5a, B1C and B2a signals: a) 3 dB bandwidth between 12 and 24 MHz centred around 1575.42 MHz and around 1176.45 MHz;

b) differential group delay not greater than 150 ns; c) early minus late discriminator; d) L1/E1/B1C correlator spacing between 0.08 and 0.12 chips; e) L5/E5a/B2a correlator spacing between 0.9 chips and 1.1 chips;

f) frequency dependent gain roll-off of at least 24 dB per octave in the transition band until reaching a minimum attenuation to meet the performance objectives in the presence of interfering signals at the interference thresholds specified in 3.7;

g) maintain the minimum attenuation to meet the performance objectives in the presence of interfering signals at the out-of-band interference thresholds specified in 3.7; h) filter centre frequencies around 1575.42 MHz and 1176.45 MHz within ±10% of the 3 dB bandwidth as specified in a).

Note.: The 0 dB level corresponds to the filter’s normalized peak in-band response.

235CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.4.1.2.5.2 The ISMG shall validate broadcast ISD assuming that the GNSS receiver using ARAIM is compliant with the following constraints when processing L1OC and L3OC signals: a) 3 dB radio frequency / intermediate frequency bandwidth between 12 and 24 MHz centred around 1600.995 MHz and around

1202.025 MHz; b) differential group delay not greater than 150 ns; c) early minus late discriminator; d) L1OC correlator spacing between 0.08 and 0.12 L1 chips; e) L3OC correlator spacing between 0.9 chips and 1.1 L5 chips;

f) frequency dependent gain roll-off of at least 24 dB per octave in the transition band until reaching a minimum attenuation to meet the performance objectives in the presence of interfering signals at the interference thresholds specified in 3.7;

g) maintain the minimum attenuation to meet the performance objectives in the presence of interfering signals at the out-of-band interference thresholds specified in 3.7; h) filter centre frequencies around 1600.995 MHz and 1202.025 MHz within ±10% of the 3 dB bandwidth as specified in a).

Note.: The 0 dB level corresponds to the filter’s normalized peak in-band response.

3.4.1.2.5.3 The ISMG shall validate broadcast ISD assuming that the GNSS receiver using ARAIM is compliant with the constraints in Table D-23 when processing L1OF signals.

3.4.1.2.6 ISD provision requirements

3.4.1.2.6.1 ISMG shall provide one of the following sets of ISD parameters: – R , P ; or sat sat – R , MFD ; or sat sat – P , R , MFD . sat sat sat Note.: When P is not provided, it can be derived from the following relationship:

sat probability of fault = rate of fault × mean fault duration.

3.4.1.2.6.2 ISMG shall provide one of the following sets of ISD parameters: – R , P ; or const const 236CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 – R , MFD ; or const const – P , R , MFD .

const const const Note.: When P is not provided, it can be derived from the following const

relationship: probability of fault = rate of fault × mean fault duration.

3.4.1.2.6.3 ISMG shall provide all ISD as defined in 3.4.1.1 to support the applicable ARAIM service type except as specified in 3.4.1.2.6.1 and 3.4.1.2.6.2.

Note.: ISD are provided either through core satellite constellation navigation data broadcast (as defined in 3.4.1.2.1.1) or as defaults as shown in 3.4.1.3.3.3.

3.4.1.2.6.4 The default and broadcast ISD parameters shall be valid for satellite elevation angles between 5 and 90 degrees, inclusive. When core satellite constellations identify a valid minimum elevation angle smaller than 5 degrees, the default and broadcast ISD parameters shall be valid from the minimum specified elevation angle to 90 degrees, inclusive. The elevation angle validity range shall be documented in the interface specifications as defined in 3.4.1.2.1.1.

3.4.1.3 ARAIM aircraft elements

3.4.1.3.1 General receiver processing requirements:

3.4.1.3.1.1 When a GNSS receiver using ARAIM processes core satellite constellation signals, it shall process the signals following the requirements as specified in 3.1.1.3.1 (GPS receiver) and/or 3.1.2.3.1 (GLONASS receiver) and/or

3.1.3.3.1 (Galileo receiver) and/or 3.1.4.3.1 (BDS receiver).

3.4.1.3.1.2 When a GNSS receiver using ARAIM processes core satellite constellation signals, it shall apply the protocols for data application as specified in

3.1.1.2 (GPS) and/or 3.1.2.2 (GLONASS) and/or 3.1.3.2 (Galileo) and/or

3.1.4.2 (BDS).

Note.: GNSS receivers using ARAIM only use core satellite constellation signals that indicate a healthy status.

3.4.1.3.2 Design constraints for GNSS receivers using ARAIM

3.4.1.3.2.1 GNSS receivers using ARAIM shall comply with the design constraints listed in section 3.4.1.2.5.

Note.: Future development may provide more flexibility on receiver design constraints.

3.4.1.3.3 Application of ISD in ARAIM processing algorithms 237CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.4.1.3.3.1 When processing broadcast ISD, GNSS receivers using ARAIM shall process ISD as specified in 3.4.1.2.1.1.

3.4.1.3.3.2 When processing ISM, GNSS receivers using ARAIM shall apply ISD consistent with its service type, validity time and applicable satellite mask.

3.4.1.3.3.3 Default ISD. GNSS receivers using ARAIM shall store the following default

ISD:

Note 1.: These values correspond to the core satellite constellation commitments (as shown in Attachment D, 5.3.2). They can only be modified by a change to these performance commitments.

Note 2.: Default ISD values have been validated using the receiver design assumptions listed in 3.4.1.2.5.

Note 3.: When CNAV data is available (GPS dual-frequency and L5-only, single- frequency modes), the IAURA is defined in Appendix B, 3.1.1.2.2.4.1, and the nominal URA is defined in IS-GPS-705F sections 20.3.3.1.1.4 (elevation dependent) and 20.3.3.2.4 (non-elevation dependent). If CNAV data is not available (L1-only, single-frequency mode), the IAURA and nominal URA are defined in Appendix B, 3.1.1.1.3.1.2.

Note 4.: Guidance information is provided in Attachment D, 5.3.2.3.

3.4.1.3.3.4 Mixing satellites from the same constellation with default and broadcast ISD 238CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.4.1.3.3.4.1 When GNSS receivers using ARAIM apply default ISD to some satellites and broadcast ISD to other satellites from the same core satellite constellation, the receiver shall use default ISD (3.4.1.3.3.3) for the parameters defined in 3.4.1.2.6.2 for all satellites from the corresponding core satellite constellation.

3.5 Satellite-based augmentation system (SBAS)

3.5.1 GENERAL Note.: Geodetic parameters in this section are defined in WGS-84.

3.5.1.1 SBAS system and service description. SBAS shall consist of a non-aircraft subsystem and an aircraft subsystem. The SBAS non-aircraft subsystem shall provide data and corrections for the GNSS ranging signals over one or two GNSS frequencies broadcast from a satellite to the aircraft subsystem. The SBAS non-aircraft subsystem shall broadcast on the L1 frequency to support the L1 SBAS service and/or on the L5 frequency to support the DFMC SBAS service.

Note.: The SBAS non-aircraft subsystem may provide a single-frequency ranging signal on the SBAS L1 frequency or a dual-frequency ranging signal as a combination of the signals transmitted on the SBAS L1 and SBAS L5 frequencies.

3.5.1.2 SBAS pseudo-range definition.

3.5.1.2.1 Carrier smoothing. Carrier smoothing shall be defined by the following

filter:

P = αP + (1 – α)P CSC,k meas proj P = (P + Δ ) proj CSC,k-1 carrier_range where P = the carrier smoothed code pseudo-range at time k;

CSC,k P = the previous carrier smoothed code pseudo-range at time CSC,k–1 k-1;

P = the measured pseudo-range as defined below; meas Δ = the change in carrier range as defined below, and carrier_range α = the filter weighting function equal to the sample interval divided by the smoothing time constant.

239CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 where P = the raw pseudo-range of frequency n at time k; and n,k γ = the square of the ratio of frequency 1 to frequency 2;

12 where φ = the accumulated carrier in metres for frequency n at time k; and n,k φ = the accumulated carrier in metres for frequency n at time k-1. n,k-1

3.5.1.2.2 Corrected pseudo-range. The corrected pseudo-range for a given satellite

i at time t is:

PR = P + TC + b i,corrected CSC,i i i where P = the smoothed pseudo-range (defined in 3.5.1.1);

CSC,i TC = the tropospheric correction (defined in 3.5.5.3 for SBAS); and i b = the clock correction. i

3.5.2 SBAS L1 RF CHARACTERISTICS

3.5.2.1 Carrier frequency stability. The short-term stability of the carrier frequency (square root of the Allan Variance) at the output of the satellite transmit antenna shall be better than 5 × 10–11 over 1 to 10 seconds.

3.5.2.2 Carrier phase noise. The phase noise spectral density of the unmodulated carrier shall be such that a phase locked loop of 10 Hz one-sided noise bandwidth is able to track the carrier to an accuracy of 0.1 radian (1 sigma).

3.5.2.3 Spurious emissions. Spurious emissions shall be at least 40 dB below the unmodulated carrier power over all frequencies.

3.5.2.4 Code/carrier frequency coherence. The short-term (less than 10 seconds) fractional frequency difference between the code phase rate and the carrier frequency shall be less than 5 × 10–11 (standard deviation). Over the long term (less than 100 seconds), the difference between the change in the broadcast code phase, converted to carrier cycles by multiplying the number of code chips by 1 540, and the change in the broadcast carrier phase, in cycles, shall be within one carrier cycle (standard deviation).

Note.: This applies to the output of the satellite transmit antenna and does not include code/carrier divergence due to ionospheric refraction in 240CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 the downlink propagation path.

3.5.2.5 Correlation loss. The loss in the recovered signal power due to imperfections in the signal modulation and waveform distortion shall not exceed 1 dB.

Note.: The loss in signal power is the difference between the broadcast power in a 2.046 MHz bandwidth and the signal power recovered by a noise-free, loss-free receiver with 1-chip correlator spacing and a

2.046 MHz bandwidth.

3.5.2.6 Maximum code phase deviation. The maximum uncorrected code phase of the L1 broadcast signal shall not deviate from the equivalent SBAS network time (SNT) for L1 SBAS by more than ±2–20 seconds.

3.5.2.7 Code/data coherence. Each 2-millisecond symbol shall be synchronous with every other code epoch.

3.5.2.8 Message synchronization. The leading edge of the first symbol that depends on the first bit of the current message shall be broadcast from the SBAS satellite synchronous with a 1-second epoch of SNT for L1 SBAS.

3.5.2.9 Convolutional encoding. A 250-bit-per-second data stream shall be encoded at a rate of 2 symbols per bit using a convolutional code with a constraint length of 7 to yield 500 symbols per second. The convolutional encoder logic arrangement shall be as illustrated in Figure B-24 with the G3 output selected for the first half of each 4-millisecond data bit period.

3.5.2.10 Pseudo-random noise (PRN) codes. Each PRN code shall be a 1 023-bit Gold code which is itself the Modulo-2 addition of two 1 023-bit linear patterns, G1 and G2. The G2 sequence shall be formed by delaying the i i G2 sequence by the associated integer number of chips as illustrated in Table B-61. Each of the G1 and G2 sequences shall be defined as the output of stage 10 of a 10-stage shift register, where the input to the shift register is the Modulo-2 addition of the following stages of the shift register:

a) G1: stages 3 and 10; and b) G2: stages 2, 3, 6, 8, 9 and 10.

The initial state for the G1 and G2 shift registers shall be “1111111111”.

241CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 242CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.3 DATA STRUCTURE ON SBAS L1 SIGNAL Note.: Messages broadcast on SBAS L1 signal are independent of those broadcast on SBAS L5 signal. Information broadcast on SBAS L1 signal is used only for the L1 SBAS service using GPS L1 C/A and GLONASS L1OF (FDMA signal).

3.5.3.1 Format summary. All messages shall consist of a message type identifier, a preamble, a data field and a cyclic redundancy check as illustrated in Figure B-25.

3.5.3.2 Preamble. For L1, the preamble shall consist of the sequence of bits “01010011 10011010 11000110”, distributed over three successive blocks. The start of every other 24-bit preamble shall be synchronous with a 6-second GPS subframe epoch.

3.5.3.3 Message type identifier. The L1 message type identifier shall be a 6-bit value identifying the message type (Types 0 to 63) as defined in Table B-

62. The message type identifier shall be transmitted MSB first.

3.5.3.4 Data field. The L1 data field shall be 212 bits as defined in 3.5.6. Each data field parameter shall be transmitted MSB first.

3.5.3.5 Cyclic redundancy check (CRC). The SBAS message CRC code on L1 shall be calculated in accordance with 3.9.

3.5.3.5.1 The length of the CRC code shall be k = 24 bits.

243CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.3.5.2 The CRC generator polynomial shall be:

G(x) = x24 + x23 + x18 + x17 + x14 + x11 + x10 + x7 + x6 + x5 + x4 + x3 + x + 1 Note.: L1 messages (Table B-62) are for use with L1 SBAS service and L5 messages (Table B-98) are for use with DFMC SBAS service. Types 0, 62 and 63 messages are used independently by both L1 SBAS and DFMC SBAS services and their contents only apply to their service.

244CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.3.5.3 The CRC information field, M(x), shall be:

3.5.3.5.4 M(x) shall be formed from the 8-bit SBAS message preamble, 6-bit message type identifier, and 212-bit data field. Bits shall be arranged in the order transmitted from the SBAS satellite, such that m1 corresponds to the first transmitted bit of the preamble, and m226 corresponds to bit 212 of the data field.

3.5.3.5.5 The CRC code r-bits shall be ordered such that r1 is the first bit transmitted and r24 is the last bit transmitted.

3.5.4 L1 SBAS DATA CONTENT

3.5.4.1 PRN mask parameters. PRN mask parameters shall be as follows:

PRN code number: a number that uniquely identifies the satellite PRN code and related assignments as shown in Table B-63.

PRN mask: 210 PRN mask values that correspond to satellite PRN code numbers. The mask shall set up to 51 of the 210 PRN mask values.

Note.: The first transmitted bit of the PRN mask corresponds to PRN code number 1.

PRN mask value: a bit in the PRN mask indicating whether data are

provided for the associated satellite PRN code number (1 to 210).

Coding: 0 = data not provided 1 = data provided

PRN mask number: the sequence number (1 to 51) of the mask values set in the PRN mask.

245CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.: The PRN mask number is “1” for the lowest satellite PRN number for which the PRN mask value is “1”.

Issue of data — PRN (IODP): an indicator that associates the correction data with a PRN mask.

Note.: Parameters are broadcast in the following messages: a) PRN mask (consisting of 210 PRN mask values) in Type 1 message; b) PRN mask number in Type 24, 25 and 28 messages; c) PRN code number in Type 17 message; and d) IODP in Type 1 to 5, 7, 24, 25 and 28 messages.

3.5.4.2 Geostationary orbit (GEO) ranging function parameters. GEO ranging

function parameters shall be as follows: t : the reference time for the GEO ranging function data, expressed as the time 0,GEO after midnight of the current day. [𝑋 𝑌 𝑍 ]: the position of the GEO at time t .

𝐺 𝐺 𝐺 0,GEO [𝑋˙ 𝑌˙ 𝑍˙ ]: the velocity of the GEO at time t . 𝐺 𝐺 𝐺 0,GEO [𝑋¨ 𝑌¨ 𝑍¨ ]: the acceleration of the GEO at time t . 𝐺 𝐺 𝐺 0,GEO a : the time offset of the GEO clock with respect to SNT for L1 SBAS, Gf0 defined at t .

0,GEO a : the drift rate of the GEO clock with respect to SNT for L1 SBAS.

Gf1 User range accuracy (URA): an indicator of the root-mean-square ranging error, excluding atmospheric effects, as described in Table B-64.

Note.: All parameters are broadcast in Type 9 message.

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3.5.4.3 GEO almanac parameters. GEO almanac parameters shall be as follows:

PRN code number: see 3.5.4.1.

Health and status: an indication of the functions provided by the SBAS.

The service provider identifiers are shown in Table B-65.

247CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 [𝑋 𝑌 𝑍 ]: the position of the GEO at time t . 𝐺,𝐴 𝐺,𝐴 𝐺,𝐴 almanac [𝑋˙ 𝑌˙ 𝑍˙ ]:the velocity of the GEO at time t .

𝐺,𝐴 𝐺,𝐴 𝐺,𝐴 almanac t : the reference time for the GEO almanac data, expressed as the almanac time after midnight of the current day.

Note.: All parameters are broadcast in Type 17 message.

3.5.4.4 SATELLITE CORRECTION BROADCAST PARAMETERS

3.5.4.4.1 Long-term correction parameters shall be as follows:

Issue of data (IODi): an indicator that associates the long-term corrections for the ith satellite with the ephemeris data broadcast by that satellite.

Note 1.: For GPS, the IODi matches the IODE and 8 LSBs of the IODC (3.1.1.3.1.4 and 3.1.1.3.2.2).

Note 2.: For GLONASS, the IODi indicates a period of time that GLONASS data are to be used with SBAS data. It consists of two fields as shown in Table B-66. 𝛿 : for satellite i, the ephemeris correction for the x axis.

𝑥𝑖 𝛿 : for satellite i, the ephemeris correction for the y axis. 𝑦𝑖 𝛿 : for satellite i, the ephemeris correction for the z axis. 𝑧𝑖 𝛿 ,𝑓0: for satellite i, the ephemeris time correction. 𝑎𝑖 𝛿𝑥̇ : for satellite i, ephemeris velocity correction for x axis.

𝑖 𝛿𝑦̇ : for satellite i, ephemeris velocity correction for y axis. 𝑖 𝛿𝑧̇ : for satellite i, ephemeris velocity correction for z axis. 𝑖 𝛿 : for satellite i, rate of change of the ephemeris time correction.

𝑎𝑖,𝑓1 t : the time of applicability of the parameters δx, δy, δz, δa , δx˙, δy˙, i,LT i i i i,f0 i i δz˙ and δ , expressed in seconds after midnight of the current day. i ai,f1

Velocity code: an indicator of the message format broadcast (Table B-86 and Table B-87).

Note.: All parameters are broadcast in Type 24 and 25 messages.

248CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Table B-65. SBAS service provider identifiers Identifier Service Provider 0 WAAS 1 EGNOS 2 MSAS 3 GAGAN 4 SDCM 5 BDSBAS 6 KASS 7 ANGA 8 SouthPAN 9 Reserved for SBAS 10 PAK-SBAS 11 to 13 Reserved for SBAS 14, 15 Reserved 16 to 31 Reserved for SBAS provider supporting DFMC SBAS only Note 1.: A service provider ID of 14 is used for GBAS and is not applicable to SBAS.

Note 2.: Service provider IDs of 16 to 31 cannot be coded in the L1 SBAS message.

3.5.4.4.2 Fast correction parameters shall be as follows:

Fast correction (FCi): for satellite i, the pseudo-range correction for rapidly varying errors, other than tropospheric or ionospheric errors, to be added to the pseudo-range after application of the long-term correction.

Note.: The user receiver applies separate tropospheric corrections (3.5.8.4.2 and 3.5.8.4.3).

249CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

Fast correction type identifier: an indicator (0, 1, 2, 3) of whether the Type 24 message contains the fast correction and integrity data associated with the PRN mask numbers from Type 2, Type 3, Type 4 or Type 5 messages, respectively.

Issue of data-fast correction (IODFj): an indicator that associates UDREIis with fast corrections. The index j shall denote the message type (j = 2 to 5) to which IODFj applies (the fast correction type identifier +2).

Note.: The fast correction type identifier is broadcast in Type 24 messages.

The FCi are broadcast in Type 2 to 5, and Type 24 messages. The IODFj are broadcast in Type 2 to 6, and Type 24 messages.

3.5.4.5 Fast and long-term correction integrity parameters. Fast and long-term

correction integrity parameters shall be as follows:

UDREI: an indicator that defines the σ2,UDRE for satellite i as described i i in Table B-67.

Model variance of residual clock and ephemeris errors (σ𝑖,𝑈𝐷𝑅𝐸 2 ): the variance of a normal distribution associated with the user differential range errors for satellite i after application of fast and long-term corrections, excluding atmospheric effects and used in horizontal protection level/vertical protection level computations (3.5.5.6).

Note.: All parameters are broadcast in Type 2 to 6, and Type 24 messages.

3.5.4.6 Ionospheric correction parameters. Ionospheric correction parameters

shall be as follows:

IGP mask: a set of 11 ionospheric grid point (IGP) band masks defined in Table B-68.

IGP band mask: a set of IGP mask values which correspond to all IGP locations in one of the 11 IGP bands defined in Table B-68.

250CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

IGP mask value: a bit indicating whether data are provided within that IGP band for the associated IGP.

Coding: 0 = data are not provided 1 = data are provided

Number of IGP bands: the number of IGP band masks being broadcast.

IGP band identifier: the number identifying the ionospheric band as defined in Table B-68.

IGP block identifier: the identifier of the IGP block. The IGP blocks are defined by dividing into groups of 15 IGPs the sequence of IGPs within an IGP band mask which have IGP mask values of “1”. The IGP blocks are 251CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 numbered in an order of IGP mask value transmission, starting with “0”.

Validity interval (V): the time interval for which the GLONASS ephemeris data are applicable (coded with an offset of 30 s) as described in Table B-

69.

Latency time (L): the time interval between the time the last GLONASS ephemeris has been received by the ground segment and the time of transmission of the first bit of the long-term correction message at the GEO(tltc) as described in Table B-30.

IODIk: an indication of when the kth IGP band mask changes.

IGP vertical delay estimate: an estimate of the delay induced for a signal at 1 575.42 MHz if it traversed the ionosphere vertically at the IGP.

Coding: The bit pattern “111111111” indicates “Do Not Use”.

GIVEIi: an indicator that defines the σ2 as described in Table B-71. i,GIVE Model variance of residual ionospheric errors (σ2 ): the variance of a i,GIVE normal distribution associated with the residual ionospheric vertical error at the IGP for an L1 signal.

Note.: All parameters are broadcast in Type 18 and Type 26 messages.

252CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 253CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 254CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 255CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.4.7 Degradation parameters. Degradation parameters, whenever used, shall

be as follows:

Fast correction degradation factor indicator (aii): an indicator of the fast correction degradation factor (ai) for the ith satellite as described in Table B-72.

Note.: The aii is also used to define the time-out interval for fast corrections, as described in 3.5.8.1.2.

System latency time (t ): the time interval between the origin of the fast lat correction degradation and the user differential range estimate indicator

(UDREI) reference time.

B : a parameter that bounds the noise and round-off errors when rrc computing the range rate correction degradation as in 3.5.5.6.2.2.

C : the maximum round-off error due to the resolution of the orbit and ltc_lsb clock information.

C : the velocity error bound on the maximum range rate difference of ltc_v1 missed messages due to clock and orbit rate differences.

256CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 I : the update interval for long-term corrections if velocity code = 1 ltc_v1 (3.5.4.4.1).

C : a parameter that bounds the difference between two consecutive ltc_v0 long-term corrections for satellites with a velocity code = 0.

I : the minimum update interval for long-term messages if velocity code ltc_v0 = 0 (3.5.4.4.1).

C : the maximum round-off error due to the resolution of the orbit and GEO_lsb clock information.

C : the velocity error bound on the maximum range rate difference of GEO_v missed messages due to clock and orbit rate differences.

I : the update interval for GEO ranging function messages.

GEO C : the bound on the residual error associated with using data beyond the er precision approach/approach with vertical guidance time-out.

257CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 C : the bound on the difference between successive ionospheric grid iono_step delay values.

I : the minimum update interval for ionospheric correction messages. iono

C ramp: the rate of change of the ionospheric corrections. iono

RSS : the root-sum-square flag for fast and long-term correction UDRE residuals.

Coding: 0 = correction residuals are linearly summed 1 = correction residuals are root-sum-squared

RSS : the root-sum-square flag for ionospheric residuals. iono

Coding: 0 = correction residuals are linearly summed 1 = correction residuals are root-sum-squared C : the term which is used to compensate for quantization effects covariance when using the Type 28 message.

Note 1.: The parameters ai and tlat are broadcast in Type 7 message. All other parameters are broadcast in Type 10 message.

Note 2.: If message Type 28 is not broadcast, C is not applicable. covariance

3.5.4.8 Time parameters. Time parameters, whenever used, shall be as follows:

UTC standard identifier: an indication of the UTC reference source as defined in Table B-73.

GPS time-of-week count: the number of seconds that have passed since the transition from the previous GPS week (similar to the GPS parameter in 3.1.1.2.6.1 but with a 1-second resolution).

Table B-73. UTC standard identifier UTC standard UTC standard identifier 0 UTC as operated by the National Institute of Information and Communication Technology, Tokyo, Japan 1 UTC as operated by the U.S. National Institute of Standards and Technology 2 UTC as operated by the U.S. Naval Observatory 3 UTC as operated by the Observatoire de Paris 4 Reserved for UTC as operated by a European laboratory 5 UTC as operated by the National Time Service Center, Chinese Academy of Sciences 6 Reserved 7 UTC not provided 8 to 15 Reserved for DFMC SBAS only 258CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.: UTC standard identifiers of 8 to 15 cannot be coded in the L1 SBAS message.

GPS week number (week count): see 3.1.1.2.6.2.

GLONASS indicator: a flag indicating if GLONASS time parameters are

provided.

Coding: 0 = GLONASS time parameters are not provided 1 = GLONASS time parameters are provided GLONASS time offset L1 (δai,GLONASS): A parameter broadcast on L1 that represents the stable part of the offset between the L1 GLONASS time and the L1 SBAS network time.

Note.: If L1 SBAS does not support GLONASS, δai,GLONASS is not applicable.

UTC parameters: A , A , t , WN, Δt , WN , DN and Δt are as 1SNT 0SNT 0t t LS LSF LSF described in 3.1.1.3.3.6, with the exception that the SBAS parameters relate SNT to UTC time, rather than GPS time.

Note.: All parameters are broadcast in Type 12 message.

3.5.4.9 Service region parameters. Service region parameters shall be as follows:

Issue of data, service (IODS): an indication of a change of the service

provided in the region.

Number of service messages: the number of different Type 27 SBAS service messages being broadcast. (Value is coded with an offset of 1.)

Service message number: a sequential number identifying the message within the currently broadcast set of Type 27 messages (from 1 to number of service messages, coded with an offset of 1).

Number of regions: the number of service regions for which coordinates are broadcast in the message.

Priority code: an indication of a message precedence if two messages define overlapping regions. The message with a higher value of priority code takes precedence. If priority codes are equal, the message with the lower δUDRE takes precedence.

δUDRE indicator-inside: an indication of regional UDRE degradation factor (δUDRE) applicable at locations inside any region defined in the message, in accordance with Table B-74.

259CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 δUDRE indicator-outside: an indication of regional UDRE degradation factor (δUDRE) applicable at locations outside all regions defined in all current Type 27 messages, in accordance with Table B-74.

Coordinate latitude: the latitude of one corner of a region.

Coordinate longitude: the longitude of one corner of a region.

Region shape: an indication of whether a region is a triangle or quadrangle.

Coding: 0 = triangle 1 = quadrangle Note 1.: Coordinate 3 has Coordinate 1 latitude and Coordinate 2 longitude. If region is a quadrangle, Coordinate 4 has Coordinate 2 latitude and Coordinate 1 longitude. Region boundary is formed by joining coordinates in the sequence 1 2-3-1 (triangle) or 1-3-2-4-1

(quadrangle). Boundary segments have either constant latitude, constant longitude, or constant slope in degrees of latitude per degree of longitude. The change in latitude or longitude along any boundary segment between two coordinates is less than ±180 degrees.

Note 2.: All parameters are broadcast in Type 27 message.

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3.5.4.10 Clock-ephemeris covariance matrix parameters. Clock-ephemeris

covariance matrix parameters shall be as follows:

PRN mask number: see 3.5.4.1.

Scale exponent: A term to compute the scale factor used to code the Cholesky factorization elements.

Cholesky factorization elements (E ): Elements of an upper triangle matrix i,j which compresses the information in the clock and ephemeris covariance matrix. These elements are used to compute the user differential range estimate (UDRE) degradation factor (δUDRE) as a function of user position.

3.5.5 DEFINITIONS OF PROTOCOLS FOR L1 SBAS DATA APPLICATION Note.: This section provides definitions of parameters used by the non- aircraft or aircraft elements that are not transmitted. These 261CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 parameters, necessary to ensure interoperability of SBAS, are used to determine the navigation solution and its integrity (protection levels).

3.5.5.1 GEO POSITION AND CLOCK

3.5.5.1.1 GEO position estimate. The estimated position of a GEO at any time t is: k

3.5.5.1.2 GEO clock correction. The clock correction for a SBAS GEO satellite i is

applied in accordance with the following equation: t = t – Δt G G where t = SBAS network time; t = GEO code phase time at transmission of message; and G Δt = GEO code phase offset.

G

3.5.5.1.2.1 GEO code phase offset (Δt ) at any time t is:

G Δt = a + a (t – t ) G Gf0 Gf1 0,GEO where (t – t ) is corrected for end-of-day crossover.

0,GEO

3.5.5.2 LONG-TERM CORRECTIONS

3.5.5.2.1 GPS clock correction. The clock correction for a GPS satellite i is applied in

accordance with the following equation: t = t – [(Δt )L1 + δΔt ] SV,i SV,i SV,i where t = SBAS network time; t = the GPS satellite time at transmission of message;

SV,i (Δ ) = the satellite PRN code phase offset as defined in 3.1.2.2; and tSV,i L1 δΔt = the code phase offset correction.

SV,i

3.5.5.2.1.1 The code phase offset correction (δΔt ) for a GPS or SBAS satellite i SV,i at any time-of-day t is: k δΔt = δa + δ (t – t ) SV,i i,f0 ai,f1 k i,LT 262CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.5.2.2 GLONASS clock correction. The clock correction for a GLONASS satellite

i is applied in accordance with the following equation: where The code phase offset correction δΔtSV,i for a GLONASS satellite i is: where (t – t ) is corrected for end-of-day crossover. If the velocity code = 0, then i,LT δa = 0.

i,f1

3.5.5.2.3 Satellite position correction. The SBAS-corrected vector for a core satellite constellation(s) or SBAS satellite i at time t is: where (t – t ) is corrected for end-of-day crossover; and i,LT [x y z]T = the core satellite constellation(s) or SBAS satellite position vector i i i as defined in 3.1.2.3, 3.2.2.3 and 3.5.5.1.1.

If the velocity code = 0, then [δx˙ δy˙ δz˙] =[0 0 0]T. i i i T

3.5.5.3 Pseudo-range corrections. The corrected pseudo-range at time t for

satellite i is:

PR = PR + FC + RRC (t – t ) + IC + TC i,corrected i i i i,0f i i where PR = the measured pseudo-range after application of the satellite clock i correction;

FC = the fast correction; i RRC = the range rate correction; i IC = the ionospheric correction; i TC = the tropospheric correction (negative value representing the i troposphere delay); and 263CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 t = the time of applicability of the most recent fast corrections, which is i,0f the start of the epoch of the SNT second that is coincident with the transmission at the SBAS satellite of the first symbol of the message block.

3.5.5.4 Range rate corrections (RRC). The range rate correction for satellite i is: where FC = the most recent fast correction; i,current FC = a previous fast correction; i,previous t = the time of applicability of FC ;

i,0f i,current t = the time of applicability of FC ; and i,0f_previous i,previous a = fast correction degradation factor (see Table B-72). i

3.5.5.5 BROADCAST IONOSPHERIC CORRECTIONS

3.5.5.5.1 Location of ionospheric pierce point (IPP). The location of an IPP is defined to be the intersection of the line segment from the receiver to the satellite and an ellipsoid with constant height of 350 km above the WGS-84 ellipsoid. This location is defined in WGS-84 latitude (ϕ ) and longitude pp (λ ).

pp

3.5.5.5.2 Ionospheric corrections. The ionospheric correction for satellite i is: where Note.: For GLONASS satellites, the ionospheric correction (ICi) is to be multiplied by the square of the ratio of the GLONASS to the GPS frequencies (fGLONASS/fGPS)2.

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3.5.5.5.3 Interpolated vertical ionospheric delay estimate. When four points are used for interpolation, the interpolated vertical ionospheric delay estimate at latitude ϕ and longitude λ is: pp pp where 𝜏 : the broadcast grid point vertical delay values at the kth corner of the vk IGP grid, as shown in Figure B-26.

3.5.5.5.3.1 For IPPs between N85° and S85°: where λ = longitude of IGPs west of IPP;

1 λ = longitude of IGPs east of IPP;

2 ϕ = latitude of IGPs south of IPP; and 1 ϕ = latitude of IGPs north of IPP.

2 Note.: If λ1 and λ2 cross 180 degrees of longitude, the calculation of xpp must account for the discontinuity in longitude values.

3.5.5.5.3.2 For IPPs north of N85° or south of S85°: where λ = longitude of the second IGP to the east of the IPP;

1 λ = longitude of the second IGP to the west of the IPP;

2 λ = longitude of the closest IGP to the west of the IPP; and 3 λ = longitude of the closest IGP to the east of the IPP.

4 265CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 When three points are used for interpolation, the interpolated vertical

ionospheric delay estimated is:

3.5.5.5.3.3 For points between S75° and N75°: where

3.5.5.5.3.4 x and y are calculated as for four-point interpolation, except that λ and pp pp 1 ϕ are always the longitude and latitude of IGP , and λ and ϕ are the 1 2 2 2 other longitude and latitude. IGP is always the vertex opposite the 2 hypotenuse of the triangle defined by the three points, IGP has the same 1 longitude as IGP , and IGP has the same latitude as IGP (an example is 2 3 2 shown in Figure B-27).

3.5.5.5.3.5 For points north of N75° and south of S75°, three-point interpolation is not supported.

3.5.5.5.4 Selection of ionospheric grid points (IGPs). The protocol for the selection

of IGPs is: a) For an IPP between N60° and S60°:

1) if four IGPs that define a 5-degree-by-5-degree cell around the IPP are set to “1” in the IGP mask, they are selected; else,

2) if any three IGPs that define a 5-degree-by-5-degree triangle that circumscribes the IPP are set to “1” in the IGP mask, they are selected; else,

3) if any four IGPs that define a 10-degree-by-10-degree cell around the IPP are set to “1” in the IGP mask, they are selected; else,

4) if any three IGPs that define a 10-degree-by-10-degree triangle that circumscribes the IPP are set to “1” in the IGP mask, they are selected; else,

5) an ionospheric correction is not available. b) For an IPP between N60° and N75° or between S60° and S75°:

1) if four IGPs that define a 5-degree-latitude-by-10-degree longitude cell around the IPP are set to “1” in the IGP mask, they are selected; else, 266CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

2) if any three IGPs that define a 5-degree-latitude-by-10-degree longitude triangle that circumscribes the IPP are set to “1” in the IGP mask, they are selected; else,

3) if any four IGPs that define a 10-degree-by-10-degree cell around the IPP are set to “1” in the IGP mask, they are selected; else,

4) if any three IGPs that define a 10-degree-by-10-degree triangle that circumscribes the IPP are set to “1” in the IGP mask, they are selected; else,

5) an ionospheric correction is not available. c) For an IPP between N75° and N85° or between S75° and S85°:

1) if the two nearest IGPs at 75° and the two nearest IGPs at 85° (separated by 30° longitude if Band 9 or 10 is used, separated by 90° otherwise) are set to “1” in the IGP mask, a 10-degree-by-10- degree cell is created by linearly interpolating between the IGPs at 85° to obtain virtual IGPs at longitudes equal to the longitudes of the IGPs at 75°; else,

2) an ionospheric correction is not available. d) For an IPP north of N85°:

1) if the four IGPs at N85° latitude and longitudes of W180°, W90°, 0° and E90° are set to “1” in the IGP mask, they are selected; else, 2) an ionospheric correction is not available. e) For an IPP south of S85°:

1) if the four IGPs at S85° latitude and longitudes of W140°, W50°, E40° and E130° are set to “1” in the IGP mask, they are selected; else,

2) an ionospheric correction is not available.

Note.: This selection is based only on the information provided in the mask, without regard to whether the selected IGPs are monitored, “Not Monitored”, or “Do Not Use”. If any of the selected IGPs is identified as “Do Not Use”, an ionospheric correction is not available. If four IGPs are selected, and one of the four is identified as “Not Monitored”, then three-point interpolation is used if the IPP is within the triangular region covered by the three corrections that are provided.

3.5.5.6 Protection levels. The horizontal protection level (HPL) and the vertical protection level (VPL) are:

267CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 where where where s = the partial derivative of position error in the x-direction with respect to x,i pseudo-range error on the ith satellite;

s = the partial derivative of position error in the y-direction with respect to y,i pseudo-range error on the ith satellite; s = the partial derivative of position error in the vertical direction with respect to V,i pseudo-range error on the ith satellite; and The variances (σ2i, and σ2 ) are defined in 3.5.5.6.2 and 3.5.5.6.3.1. The flt i,UIRE parameters (σ2 and σ2 ) are determined by the aircraft element (3.5.8.4.2 i,air i,tropo and 3.5.8.4.3).

The x and y axes are defined to be in the local horizontal plane, and the v axis represents local vertical.

For a general least-squares position solution, the projection matrix S is:

268CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 where El = the elevation angle of the ith ranging source (in degrees); i Az = the azimuth of the ith ranging source taken counter-clockwise from the x i axis in degrees; and w = the inverse weight associated with satellite i = σ2.

i i Note 1. — To improve readability, the subscript i was omitted from the protection matrix’s equation.

Note 2.— For an unweighted least-squares solution, the weighting matrix is an identity matrix (wi = 1).

3.5.5.6.1 Definition of K values. The K values are:

3.5.5.6.2 Definition of fast and long-term correction error model. If fast corrections and long-term correction/GEO ranging parameters are applied, and

degradation parameters are applied: where if using message Type 27, δ is a region-specific term as defined in 3.5.4.9, UDRE if using message Type 28, δ is a satellite-specific term as defined in UDRE

3.5.5.6.2.5, if using neither message, δ = 1 (see Attachment D, 6.5.7).

UDRE 269CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.: With the requirement to broadcast either a Type 27 message or a Type 28 message in section 3.5.7.4.7, user equipment no longer needs to set δUDRE =1 and can instead wait for broadcast data.

If fast corrections and long-term corrections/GEO ranging parameters are applied, but

degradation parameters are not applied:

3.5.5.6.2.1 Fast correction degradation. The degradation parameter for fast correction

data is: where t = the current time; t = (UDREI reference time): if IODF ≠ 3, the start time of the SNT 1- u i j second epoch that is coincident with the start of the transmission of the message block that contains the most recent UDREI data (Type 2 to 6, i or Type 24 messages) that matches the IODF of the fast correction being j used. If IODF = 3, the start time of the epoch of the SNT 1-second epoch j that is coincident with the start of transmission of the message that contains the fast correction for the ith satellite; and t = (as defined in 3.5.4.7).

lat Note.: For UDREs broadcast in Type 2 to 5, and Type 24 messages, tu equals the time of applicability of the fast corrections since they are in the same message. For UDREs broadcast in Type 6 message and if the IODF = 3, tu also equals the time of applicability of the fast corrections (t0f). For UDREs broadcast in Type 6 message and IODF ≠ 3, tu is defined to be the time of transmission of the first bit of Type 6 message at the GEO.

3.5.5.6.2.2 Range rate correction degradation

3.5.5.6.2.2.1 If the RRC = 0, then ε = 0. rrc

3.5.5.6.2.2.2 If the RRC ≠ 0 and IODF ≠ 3, the degradation parameter for fast

correction data is:

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3.5.5.6.2.2.3 If RRC ≠ 0 and IODF = 3, the degradation parameter for range rate data is:

Where t = the current time;

IODF = IODF associated with most recent fast correction; current IODF = IODF associated with previous fast correction; previous Δt = ti,0f – ti,0f_previous; and I = the user time-out interval for fast corrections.

fc

3.5.5.6.2.3 Long-term correction degradation

3.5.5.6.2.3.1 Core satellite constellation(s)

3.5.5.6.2.3.1.1 For velocity code = 1, the degradation parameter for long-term

corrections of satellite i is:

3.5.5.6.2.3.1.2 For velocity code = 0, the degradation parameter for long-term

corrections is:

Where t = the current time; t = the time of transmission of the first bit of the long-term correction message ltc at the GEO; and 271CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 [x] = the greatest integer less than x.

3.5.5.6.2.3.2 GEO satellites. The degradation parameter for long-term corrections is: where t = the current time.

Note.:When long-term corrections are applied to a GEO satellite, the long-term correction degradation is applied and the GEO navigation message degradation is not applied.

3.5.5.6.2.4 Degradation for en-route through non-precision approach

3.5.5.6.2.5 UDRE degradation factor calculated with message Type 28 data. The δUDRE is: where

3.5.5.6.3 Definition of ionospheric correction error model 272CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.5.6.3.1 Broadcast ionospheric corrections. If SBAS-based ionospheric corrections are applied, σ2UIRE is: where using the same ionospheric pierce point weights (Wn) and grid points selected for the ionospheric correction (3.5.5.5).

If degradation parameters are used, for each grid point: where t = the current time; t = the time of transmission of the first bit of the ionospheric correction iono message at the GEO; and [x] = the greatest integer less than x.

If degradation parameters are not used, for each grid point:

Note.: For GLONASS satellites, both σGIVE and ɛiono parameters are to be multiplied by the square of the ratio of the GLONASS to the GPS frequencies (fGLONASS/fGPS)2.

3.5.5.6.3.2 Ionospheric corrections. If SBAS-based ionospheric corrections are not applied, σ2UIRE is: where 273CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 T = the ionospheric delay estimated by the chosen model (GPS correction or iono other model);

F = (as defined in 3.5.5.5.2); pp

3.5.6 L1 SBAS MESSAGE TABLES Each SBAS message shall be coded in accordance with the corresponding message format defined in Tables B-75 through B-91. All signed parameters in these tables shall be represented in two’s complement, with the sign bit occupying the MSB.

Note.: The range for the signed parameters is smaller than indicated, as the maximum positive value is constrained to be one value less (the indicated value minus the resolution).

274CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 275CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 276CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

Notes: -

1. All parameters are defined in 3.5.4.7.

2. The valid range for Iltc_vo and Iiono is 1 to 511. The value of 0 is not valid and receivers will use a value of 1 in place of a transmitted value of 0.

277CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 278CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 279CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 280CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 281CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.7 L1 SBAS NON-AIRCRAFT ELEMENTS Note 1.: Depending on the level of service offered by a particular SBAS, different functions can be implemented as described in Chapter 3, 3.7.3.4.2.

Note 2.: The parameters that are referred to in this section are defined in 3.5.4.

3.5.7.1 GENERAL

3.5.7.1.1 Required data and broadcast intervals. SBAS shall broadcast the data required for the supported functions as shown in Table B-92. If the SBAS broadcasts data that are not required for a particular function, the requirements for that data supporting other functions shall apply. The maximum interval between broadcasts for all data of each data type

provided shall be as defined in Table B-92.

3.5.7.1.2 SBAS radio frequency monitoring. The SBAS shall monitor the SBAS satellite parameters shown in Table B-93 and take the indicated action.

Note.: SBAS may broadcast null messages (Type 63 messages) in each time slot for which no other data are broadcast.

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3.5.7.1.3 “Do Not Use”. SBAS shall broadcast a “Do Not Use” message (Type 0 message) when necessary to inform users not to use the SBAS satellite ranging function and its broadcast data.

3.5.7.1.4 The Doppler shift in the GEO satellite signal seen at any fixed location within the GEO footprint for any GEO shall not exceed ±450 Hz.

Note.: This maximum Doppler shift corresponds approximately to the maximum GEO satellite orbit inclination that can be supported by the coding ranges for Type 9 and Type 17 messages.

3.5.7.1.5 Geostationary orbit (GEO) ranging function parameters. Each SBAS satellite shall broadcast geostationary orbit (GEO) ranging function parameters (defined in 3.5.4.2).

Note.: It is necessary to broadcast geostationary orbit ranging function parameters even when a ranging function is not provided, so that airborne receivers may implement a positive identification of the broadcasting SBAS satellite. When ranging is not provided, the accuracy of the Type 17 data (and Type 9 data) only needs to support the acquisition of the satellite.

3.5.7.1.5.1 The error in the Doppler shift of a GEO satellite derived from any Type 9 message that has not timed out, with respect to the true GEO Doppler shift seen at any fixed location within the GEO footprint, shall not exceed ±210 Hz.

3.5.7.1.6 Almanac data. Each SBAS satellite shall broadcast almanac data (defined in 3.5.4.3) for all SBAS satellites of the same service provider.

3.5.7.1.6.1 The error in the estimated position of the satellite derived from any Type 17 message broadcast within the previous 15 minutes, with respect to the true satellite position, shall not exceed 3 000 km.

3.5.7.1.6.2 The separation distance between the estimated position of the satellite derived from any Type 17 message broadcast within the previous 15 minutes and the position of the satellite derived from the GEO ranging parameters in any Type 9 message that has not timed out shall not exceed 200 km.

3.5.7.1.6.3 The error in the Doppler shift of a GEO satellite derived from any Type 17 message broadcast within the previous 15 minutes, with respect to the true GEO Doppler shift seen at any fixed location within the GEO footprint, shall not exceed ±210 Hz.

3.5.7.1.6.4 SBAS shall not broadcast almanac data for any SBAS satellite from a different service provider for which the position estimated from the almanac data broadcast within the previous 15 minutes would be within 283CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 200 km of the position of any of its own GEOs as derived from the GEO ranging parameters from any Type 9 message that has not timed out.

3.5.7.1.6.5 Where the estimated position of a GEO satellite providing a ranging function, derived from the Type 17 message broadcast within the previous 15 minutes, is within 200 km of the position of another GEO satellite of the same service provider, derived from a Type 9 message for this GEO that has not timed out, the GEO UDRE value shall be set sufficiently large to account for the possibility that a user could misidentify the PRN of the GEO providing the ranging function.

3.5.7.1.6.6 The health and status parameter shall indicate the satellite status and the service provider identifier, as defined in 3.5.4.3.

3.5.7.1.6.7 Unused almanac slots in Type 17 messages shall be coded with a PRN code number of “0”.

3.5.7.1.6.8 The service provider shall ensure the correctness of the service provider ID broadcast in any almanac.

3.5.7.2 Ranging function. If an SBAS provides an L1 SBAS ranging function, it shall comply with the requirements contained in this section in addition to the requirements of 3.5.7.1.

3.5.7.2.1 Performance requirements Note.: See Chapter 3, 3.7.3.4.3.

3.5.7.2.2 Ranging function data. SBAS shall broadcast ranging function data such that the SBAS satellite position error projected on the line-of-sight to any user in the satellite footprint is less than 256 metres. Each SBAS satellite shall broadcast a URA representing an estimate of the standard deviation of the ranging errors referenced to SNT for L1 SBAS.

3.5.7.3 GNSS satellite status function. If an SBAS provides a satellite status function, it shall also comply with the requirements contained in this

section.

Note.: An SBAS may be able to provide integrity on some GPS satellites that are designated either marginal or unhealthy.

3.5.7.3.1 Performance of satellite status functions. Given any valid combination of active data, the probability of a horizontal error exceeding the HPLSBAS (as defined in 3.5.5.6) for longer than 8 consecutive seconds shall be less than 10–7 in any hour, assuming a user with zero latency.

284CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.: Active data is defined to be data that have not timed out per 3.5.8.1.2. This requirement includes core satellite constellation(s) and SBAS failures.

3.5.7.3.2 PRN mask and Issue of data – PRN (IODP). SBAS shall broadcast a PRN mask and IODP (Type 1 message). The PRN mask values shall indicate whether or not data are being provided for each GNSS satellite. The IODP shall change when there is a change in the PRN mask. The change of IODP in Type 1 messages shall occur before the IODP changes in any other message. The IODP in Type 2 to 5, 7, 24, 25 and 28 messages shall equal the IODP broadcast in the PRN mask message (Type 1 message) used to designate the satellites for which data are provided in that message.

Table B-92. Data broadcast intervals and supported functions Maximum Precise Associated broadcast GNSS satellite Basic differential differential message Data type interval Ranging status correction correction types Clock-ephemeris covariance 120s R R R 28 matrix (see Note 5) (see Note 5) (see Note 5) SBAS in test mode 6s 0 PRN mask 120s R R R 1 UDREI 6s R* R R 2 to 6, 24 Fast corrections I /2 R* R R 2 to 5, 24 fc (see Note 4) Long-term corrections 120s R* R R 24, 25 GEO ranging function data 120s R R R R 9 Fats correction degradation 120s R* R R 7 Degradation parameters 120s R 10 Ionospheric grid mask 300s R 18 Ionospheric corrections, 300s R 26 GIVEI Timing data 300s R R R R 12 (see Note 3) (see Note 3) (see Note 3) (see Note 3) Almanac data 300s R R R R 17 Service level 300s R R R 27 (see Note 5) (see Note 5) (see Note 5) Notes. -

1. “R” indicates that the data must be broadcast to support the function.

2. “R*” indicates special coding as described in 3.5.7.3.3.

3. Type 12 messages are only required if data are provided for GLONASS satellites.

4. Ifc refers to the PA/APV time-out interval for fast corrections, as defined in Table B-57.

5. Either a Type 27 message or Type 28 message is to be broadcast as required in 3.5.7.6.2.

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3.5.7.3.2.1 Recommendation. – When the PRN mask is changed, SBAS should repeat the Type 1 message several times before referencing it in other messages to ensure that users receive the new mask.

3.5.7.3.3 Integrity data. If SBAS does not provide the basic differential correction function, it shall transmit fast corrections, long-term corrections and fast correction degradation parameters coded to zero for all visible satellites indicated in the PRN mask.

3.5.7.3.3.1 If SBAS does not provide the basic differential correction function, SBAS shall indicate that the satellite is unhealthy (“Do Not Use”) if the pseudo- range error exceeds 150 metres.

3.5.7.3.3.2 If SBAS does not provide the basic differential correction function, SBAS shall indicate that the satellite is “Not Monitored” if the pseudo-range error cannot be determined.

3.5.7.3.3.3 If SBAS does not provide the basic differential correction function, SBAS shall transmit a UDREIi of 13 if the satellite is not “Do Not Use” or “Not Monitored”.

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3.5.7.3.3.4 The IODFj parameter in Type 2 to 5, 6 or 24 messages shall be equal to

3.

3.5.7.4 Basic differential correction function. If an SBAS provides a basic differential correction function, it shall comply with the requirements contained in this section in addition to the GNSS satellite status function requirements defined in 3.5.7.3.

3.5.7.4.1 Performance of basic differential correction function. Given any valid combination of active data, the probability of a horizontal error exceeding the HPLSBAS (as defined in 3.5.5.6) for longer than 8 consecutive seconds shall be less than 10-7 in any hour, assuming a user with zero latency.

Note.: Active data is defined to be data that has not timed out per 3.5.8.1.2. This requirement includes core satellite constellation(s) and SBAS failures.

3.5.7.4.2 Long-term corrections. Except for SBAS satellites from the same service provider, SBAS shall determine and broadcast long-term corrections for each visible GNSS satellite (see Note) indicated in the PRN mask (PRN mask value equal to “1”). The long-term corrections shall be such that the core satellite constellation(s) satellite position error projected on the line- of-sight to any user in the satellite footprint after application of these long- term corrections is less than 256 metres. For each GLONASS satellite, SBAS shall translate satellite coordinates into WGS-84 as defined in

3.1.2.5.2 prior to determining the long-term corrections. For each GPS satellite, the broadcast IOD shall match both the GPS IODE and 8 LSBs of IODC associated with the clock and ephemeris data used to compute the corrections (3.1.1.3.1.4 and 3.1.1.3.2.2). Upon transmission of a new ephemeris by a GPS satellite, SBAS shall continue to use the old ephemeris to determine the fast and long-term error corrections for at least 2 minutes and not more than 4 minutes. For each GLONASS satellite, SBAS shall compute and broadcast an IOD that consists of a latency and a validity interval as defined in 3.5.4.4.1.

Note.: The criteria for satellite visibility include the locations of reference stations and the achieved mask angle at those locations.

3.5.7.4.2.1 Recommendation. – To ensure accurate range rate corrections, SBAS should minimize discontinuities in the satellite ephemerides after application of long-term corrections.

3.5.7.4.3 Fast corrections. SBAS shall determine fast corrections for each visible GNSS satellite indicated in the PRN mask (PRN mask value equal to “1”).

Unless the IODF = 3, each time any fast correction data in Type j (j = 2, 3, 4 or 5) message changes, the IODFj shall sequence “0, 1, 2, 0, ...”.

287CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.: If there is an alarm condition, the IODFj may equal 3 (see 3.5.7.4.5).

3.5.7.4.4 Timing data. If data are provided for GLONASS, SBAS shall broadcast the timing message (Type 12 message) including GLONASS time offset as defined in Table B-82.

3.5.7.4.5 Integrity data. For each satellite for which corrections are provided, SBAS shall broadcast integrity data (UDREIi and either a, Type 27 or 28 message data to calculate δUDRE) such that the integrity requirement in 3.5.7.4.1 is met.

If the fast corrections or long-term corrections exceed their coding range, SBAS shall indicate that the satellite is unhealthy (“Do Not Use”). If 𝜎2 i,UDRE cannot be determined, SBAS shall indicate that the satellite is “Not Monitored”.

If Type 6 message is used to broadcast 𝜎2 , then: i,UDRE a) the IODFj shall match the IODFj for the fast corrections received in Type j message to which the 𝜎2 apply; or i,UDRE b) the IODFj shall equal 3 if the 𝜎2 apply to all valid fast corrections i,UDRE received in Type j message which have not timed out.

3.5.7.4.6 Degradation data. SBAS shall broadcast degradation parameters (Type 7 message) to indicate the applicable time out interval for fast corrections and ensure that the integrity requirement in 3.5.7.4.1 is met.

3.5.7.4.7 SBAS shall broadcast service indication data as specified in 3.5.7.6.2 (Type 27 message) orclock-ephemeris covariance matrix data as specified in 3.5.7.6.3 (Type 28 message) to comply throughout the SBAS coverage area with the signal-in-space integrity requirements stated in Chapter 3,

3.7.2.4.

3.5.7.5 Precise differential correction function. If SBAS provides a precise differential correction function, it shall comply with the requirements contained in this section in addition to the basic differential correction function requirements in 3.5.7.4.

3.5.7.5.1 Performance of precise differential correction function. Given any valid combination of active data, the probability of an out-of-tolerance condition for longer than the relevant time-to-alert shall be less than 2 × 10–7 during any approach, assuming a user with zero latency. The time-to-alert shall be 5.2 seconds for an SBAS that supports precision approach operations, and 8 seconds for an SBAS that supports APV or NPA operations. An out- of-tolerance condition shall be defined as a horizontal error exceeding the 288CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 HPLSBAS or a vertical error exceeding the VPLSBAS (as defined in

3.5.5.6). When an out-of-tolerance condition is detected, the resulting alert message (broadcast in a Type 2 to 5 and 6, 24, 26 or 27 messages) shall be repeated three times after the initial notification of the alert condition for a total of four times in 4 seconds.

Note 1.: Active data is defined to be data that has not timed out per 3.5.8.1.2. This requirement includes core satellite constellation(s) and SBAS failures.

Note 2.: Subsequent messages can be transmitted at the normal update rate.

3.5.7.5.2 Ionospheric grid point (IGP) mask. SBAS shall broadcast an IGP mask and IODIk (up to 11 Type 18 messages, corresponding to the 11 IGP bands).

The IGP mask values shall indicate whether or not data are being provided for each IGP.

If IGP Band 9 is used, then the IGP mask values for IGPs north of 55°N in Bands 0 through 8 shall be set to “0”. If IGP Band 10 is used, then the IGP mask values for IGPs south of 55°S in Bands 0 through 8 shall be set to “0”. The IODI shall change when there is a change of IGP mask values in the kth k band. The new IGP mask shall be broadcast in a Type 18 message before it is referenced in a related Type 26 message. The IODI in Type 26 k message shall equal the IODI broadcast in the IGP mask message (Type k 18 message) used to designate the IGPs for which data are provided in that message.

3.5.7.5.2.1 Recommendation. – When the IGP mask is changed, SBAS should repeat the Type 18 message several times before referencing it in a Type 26 message to ensure that users receive the new mask. The same IODI k should be used for all bands.

3.5.7.5.3 Ionospheric corrections. SBAS shall broadcast ionospheric corrections for the IGPs designated in the IGP mask (IGP mask values equal to “1”).

3.5.7.5.4 Ionospheric integrity data. For each IGP for which corrections are

provided, SBAS shall broadcast GIVEI data such that the integrity requirement in 3.5.7.5.1 is met. If the ionospheric correction or 𝜎2 i,UDRE exceed their coding range, SBAS shall indicate the status “Do Not Use” (designated in the correction data, 3.5.4.6) for the IGP. If 𝜎2 cannot i,UDRE be determined, SBAS shall indicate that the IGP is “Not Monitored” (designated in the GIVEI coding).

3.5.7.5.5 Degradation data. SBAS shall broadcast degradation parameters (Type 10 message) such that the integrity requirement in 3.5.7.5.1 is met.

3.5.7.6 OPTIONAL FUNCTIONS 289CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.7.6.1 Timing data. If UTC time parameters are broadcast, they shall be as defined in 3.5.4.8 (Type 12 message).

3.5.7.6.2 Service indication. If service indication data are broadcast, they shall be as defined in 3.5.4.9 (Type 27 message) and Type 28 messages shall not be broadcast. The IODS in all Type 27 messages shall increment when there is a change in any Type 27 message data.

3.5.7.6.2.1 If service indication data are broadcast, the δUDRE indicator-inside parameter in Type 27 message shall be equal to 0.

Note.: This requirement ensures compatibility with equipment developed according to RTCA/DO-229. Further information is available in Attachment D, section 6.5.7.

3.5.7.6.3 Clock-ephemeris covariance matrix. If clock-ephemeris covariance matrix data are broadcast, they shall be broadcast for all monitored satellites as defined in 3.5.4.10 (Type 28 message) and Type 27 messages shall not be broadcast.

3.5.7.7 MONITORING

3.5.7.7.1 SBAS radio frequency monitoring. The SBAS shall monitor the SBAS satellite parameters shown in Table B-53 and take the indicated action.

Note.: In addition to the radio frequency monitoring requirements in this section, it will be necessary to make special provisions to monitor pseudo-range acceleration specified in Chapter 3, 3.7.3.4.3.5, and carrier phase noise specified in 3.5.2.2 and correlation loss in 3.5.2.5, unless analysis and testing shows that these parameters cannot exceed the stated limits.

3.5.7.7.2 Data monitoring. SBAS shall monitor the satellite signals to detect conditions that will result in improper operation of differential processing for airborne receivers with the tracking performance defined in Attachment D, 8.11.

3.5.7.7.2.1 The ground subsystem shall use the strongest correlation peak in all receivers used to generate the pseudo range corrections.

3.5.7.7.2.2 The ground subsystem shall also detect conditions that cause more than one zero crossing for airborne receivers that use the Early-Late discriminator function as defined in Attachment D, 8.11.

3.5.7.7.2.3 The monitor action shall be to set UDRE to “Do Not Use” for the satellite.

3.5.7.7.2.4 SBAS shall monitor all active data that can be used by any user within the service area.

3.5.7.7.2.5 SBAS shall raise an alarm within 5.2 seconds if any combination of active data and GNSS signals-in-space results in an out-of-tolerance condition 290CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 for precision approach (3.5.7.5.1).

3.5.7.7.2.6 SBAS shall raise an alarm within 8 seconds if any combination of active data and GNSS signals-in-space results in an out-of-tolerance condition for en-route through APV I (3.5.7.4.1).

Note.: The monitoring applies to all failure conditions, including failures in core satellite constellation(s) or SBAS satellites. This monitoring assumes that the aircraft element complies with the requirements of RTCA/DO-229D with Change 1, except as superseded by 3.5.8 and Attachment D, 8.11.

3.5.7.7.3 IOD monitoring. SBAS shall monitor the GPS IODE values for possible invalid transmissions of values used previously for a different set of ephemeris parameters within the time interval(s) specified in 3.1.1.3.2.2, and take appropriate action to ensure the integrity of its broadcast corrections, if such an invalid use is detected.

Note 1.: The IOD uniqueness is granted by design in the case of SBAS augmenting GLONASS satellites.

Note 2.: The GPS IODC (as per 3.1.1.3.1.4) is not currently used in the processing of GPS L1 navigation messages in an SBAS receiver mode. Therefore, monitoring is not specifically required.

3.5.7.7 Robustness to core satellite constellation(s) failures. Upon occurrence of a core satellite constellation(s) satellite anomaly, SBAS shall continue to operate normally using the available healthy satellite signals that can be tracked.

3.5.8 L1 SBAS AIRCRAFT ELEMENTS Note 1.: The parameters that are referred to in this section are defined in 3.5.4.

Note 2.: Some of the requirements of this section may not apply to equipment that integrates additional navigation sensors, such as equipment that integrates SBAS with inertial navigation sensors.

3.5.8.1 SBAS-capable GNSS receiver. Except as specifically noted, the SBAS- capable GNSS receiver shall process the signals of the SBAS and meet the requirements specified in 3.1.3.1 (GPS receiver) and/or 3.2.3.1 (GLONASS receiver). Pseudo-range measurements for each satellite shall be smoothed using carrier measurements and a smoothing filter which deviates less than 0.25 metre within 200 seconds after initialization, relative to the steady-state response of the filter defined in 3.6.5.1 in the presence of drift between the code phase and integrated carrier phase of up to 0.018 metre per second.

3.5.8.1.1 GEO satellite acquisition. The receiver shall be able to acquire and track 291CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 GEO satellites for which a stationary receiver at the user receiver location would experience a Doppler shift as large as ±450 Hz.

3.5.8.1.2 Conditions for use of data. The receiver shall use data from an SBAS message only if the CRC of this message has been verified. Reception of a Type 0 message from an SBAS satellite shall result in deselection of that satellite for at least one minute and all data from that satellite shall be discarded, except that there is no requirement to discard data from Type 12 and Type 17 messages. For GPS satellites, the receiver shall apply long-term corrections only if the IOD matches both the IODE and 8 least significant bits of the IODC. For GLONASS satellites, the receiver shall apply long-term corrections only if the time of reception (tr) of the GLONASS ephemeris is inside the following IOD validity interval, as defined in 3.5.4.4.1:

t – L – V ≤ t ≤ t – L LT r LT Note 1.: For SBAS satellites, there is no mechanism that links GEO ranging function data (Type 9 message) and long-term corrections.

Note 2.: This requirement does not imply that the receiver has to stop tracking the SBAS satellite.

3.5.8.1.2.1 SBAS satellite identification. Upon acquisition or re-acquisition of an SBAS satellite, the receiver shall not use SBAS satellite data unless the calculated separation between the satellite position derived from its GEO ranging function parameters and the satellite position derived from the almanac message most recently received from the same service provider within the last 15 minutes is less than 200 km.

Note.: This check ensures that a receiver will not mistake one SBAS satellite for another due to cross-correlation during acquisition or re-acquisition.

3.5.8.1.2.2 The receiver shall use integrity or correction data only if the IODP associated with that data matches the IODP associated with the PRN mask.

3.5.8.1.2.3 The receiver shall use SBAS-provided ionospheric data (IGP vertical delay estimate and GIVEIi) only if the IODIk associated with that data in a Type 26 message matches the IODIk associated with the relevant IGP band mask transmitted in a Type 18 message.

3.5.8.1.2.4 The receiver shall use the most recently received integrity data for which the IODF equals 3 or the IODF matches the IODF associated with the fast j j j correction data being applied (if corrections are provided).

3.5.8.1.2.5 The receiver shall apply any regional degradation to the 𝜎2i,UDRE as defined by a Type 27 service message. If a Type 27 message with a new IODS indicates a higher δUDRE for the user location, the higher δUDRE 292CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 shall be applied immediately.A lower δUDRE in a new Type 27 message shall not be applied until the complete set of messages with the new IODS has been received.

3.5.8.1.2.6 The receiver shall apply satellite-specific degradation to the 𝜎2i,UDRE as defined by a Type 28 clock-ephemeris covariance matrix message. The δUDRE derived from a Type 28 message with an IODP matching that of the PRN mask shall be applied immediately.

3.5.8.1.2.7 In the event of a loss of four successive SBAS messages during an SBAS-based approach operation with a HAL of 40 m or a VAL of 50 m or less, the receiver shall invalidate all UDREI data from that SBAS satellite.4 3.5.8.1.2.8 The receiver shall not use a broadcast data parameter after it has timed out as defined in Table B-94.

3.5.8.1.2.9 The receiver shall not use a fast correction if Δt for the associated RRC exceeds the time-out interval for fast corrections, or if the age of the RRC exceeds 8Δt.

3.5.8.1.2.10 The calculation of the RRC shall be reinitialized if a “Do Not Use” or “Not Monitored” indication is received for that satellite.

3.5.8.1.2.11 For SBAS-based precision approach or APV operations, the receiver shall only use satellites with elevation angles at or above 5 degrees.

3.5.8.1.2.12 The receiver shall no longer support SBAS-based precision approach or APV operation using a particular satellite if the UDREIi received is greater than or equal to 12.

293CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.8.2 Ranging function

3.5.8.2.1 Precision approach and APV operations. The root-mean-square (1 sigma) of the total airborne error contribution to the error in a corrected pseudo- range for an SBAS satellite at the minimum received signal power level (Chapter 3, 3.7.3.4.4.3) under the worst interference environment as defined in 3.7 shall be less than or equal to 1.8 metres, excluding multipath effects, tropospheric and ionospheric residual errors.

Note.: The aircraft element will bound the errors caused by multipath and troposphere (3.5.8.4.1). For the purpose of predicting service, the multipath error is assumed to be less than 0.6 metres (1 sigma).

294CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.8.2.2 Departure, en-route, terminal, and non-precision approach operations.

The root-mean-square (1 sigma) of the total airborne contribution to the error in a corrected pseudo-range for an SBAS satellite at the minimum received signal power level (Chapter 3, 3.7.3.4.5.3) under the worst interference environment as defined in 3.7 shall be less than or equal to 5 metres, excluding multipath, tropospheric and ionospheric errors.

3.5.8.2.3 SBAS satellite position

3.5.8.2.3.1 Position computation. The receiver shall decode Type 9 message and determine the code phase offset and position (XG, YG, ZG) of the SBAS satellite.

3.5.8.2.3.2 SBAS satellite identification. The receiver shall discriminate between SBAS satellites.

Note.: This requirement applies to false acquisition of a satellite due to cross- correlation.

3.5.8.2.4 Almanac data

3.5.8.2.4.1 Recommendation. – The almanac data provided by the SBAS should be used for acquisition.

Note.: Health and status information provided in the GEO almanac data does not override or invalidate data provided in other SBAS messages. The use of bits 0 to 2 by airborne equipment is optional; there are no requirements covering their usage.

3.5.8.3 GNSS satellite status function. The receiver shall exclude satellites from the position solution if they are identified as “Do Not Use” by SBAS. If SBAS-provided integrity is used, the receiver shall not be required to exclude GPS satellites based on the GPS-provided ephemeris health flag as required in 3.1.3.1.1 or to exclude GLONASS satellites based on GLONASS-provided ephemeris health flag as required in 3.2.3.1.1.

Note 1.: In the case of a satellite designated marginal or unhealthy by the core satellite constellation(s) health flag, SBAS may be able to broadcast ephemeris and clock corrections that will allow the user to continue using the satellite.

Note 2.: If satellites identified as “Not Monitored” by SBAS are used in the position solution, integrity is not provided by SBAS. ABAS or GBAS may be used to provide integrity, if available.

3.5.8.4 BASIC AND PRECISE DIFFERENTIAL FUNCTIONS

3.5.8.4.1 Core satellite constellation(s) ranging accuracy. The root-mean-square (1 sigma) of the total airborne contribution to the error in a corrected pseudo- 295CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 range for a GPS satellite at the minimum and maximum received signal power level (Chapter 3, 3.7.3.1.1.8.6) under the worst interference environment as defined in 3.7 shall be less than or equal to 0.36 metres for minimum signal level and 0.15 metres for maximum signal level, excluding multipath effects, tropospheric and ionospheric residual errors.

The RMS of the total airborne contribution to the error in a corrected pseudo-range for a GLONASS satellite at the minimum received signal power level (Chapter 3, 3.2.5.4) under the worst interference environment as defined in 3.7 shall be less than or equal to 0.8 metres, excluding multipath effects, tropospheric and ionospheric residual errors.

3.5.8.4.2 Precision approach and APV operations

3.5.8.4.2.1 The receiver shall obtain correction and integrity data for all satellites in the position solution from the same SBAS signal (PRN code).

3.5.8.4.2.2 The receiver shall compute and apply long-term corrections, fast corrections, range rate corrections and the broadcast ionospheric corrections. For GLONASS satellites, the ionospheric corrections received from the SBAS shall be multiplied by the square of the ratio of GLONASS to GPS frequencies (f /f )2.

GLONASS GPS

3.5.8.4.2.3 The receiver shall use a weighted-least-squares position solution.

3.5.8.4.2.4 The receiver shall apply a tropospheric model such that residual pseudo- range errors have a mean value (μ) less than 0.15 metres and a 1 sigma deviation less than 0.07 metres.

Note.: A model was developed that meets this requirement. Guidance is provided in Attachment D, 6.5.4.

3.5.8.4.2.5 The receiver shall compute and apply horizontal and vertical protection levels defined in 3.5.5.6. In this computation, σ shall be: i,tropo where θ is the elevation angle of the ith satellite.

i In addition, σ shall satisfy the condition that a normal distribution with i,air zero mean and a standard deviation equal to σ bounds the error i,air distribution for residual aircraft pseudo-range errors as follows:

296CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 where f(x) = probability density function of the residual aircraft pseudo-range i error and Note.: The standard allowance for airborne multipath defined in 3.6.5.5.1 may be used to bound the multipath errors.

3.5.8.4.2.6 The parameters that define the approach path for a single precision approach or APV shall be contained in the FAS data block.

Note 1.: The FAS path is a line in space defined by the landing threshold point/fictitious threshold point (LTP/FTP), flight path alignment point

(FPAP), threshold crossing height (TCH) and glide path angle (GPA). The local level plane for the approach is a plane perpendicular to the local vertical passing through the LTP/FTP (i.e. tangent to the ellipsoid at the LTP/FTP). Local vertical for the approach is normal to the WGS-84 ellipsoid at the LTP/FTP. The glide path intercept point (GPIP) is where the final approach path intercepts the local level plane.

Note 2.: For SBAS, FAS data blocks are stored in airborne databases. The format of the data for validation of a cyclic redundancy check is shown in Attachment D, 6.6. It differs from the GBAS FAS data block in 3.6.4.5.

3.5.8.4.2.6.1 L1 SBAS FAS data block parameters shall be as follows (see Table B-

96):

Note 1.: See 3.5.15.3.5 for the definitions of operation type, SBAS service provider ID and approach performance designator applicable to DFMC SBAS receivers.

Note 2.: “L1 SBAS receivers” refers to receivers that meet the specifications of RTCA/DO-229.

Operation type: straight-in approach procedure or other operation types applicable to L1 SBAS receivers.

Coding: 0 = straight-in approach procedure 297CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 1 to 15 = spare

SBAS service provider ID: shall indicate the service provider associated with this FAS data block.

Coding: 0-13 = Table B-65.

14 = FAS data block is to be used with GBAS only.

15 = FAS data block can be used with any SBAS service provider.

Airport ID: the three- or four-letter designator used to designate an airport.

Coding: Each character is coded using the lower 6 bits of its IA-5 representation. For each character, b1 is transmitted first, and 2 zero bits are appended after b6, so that 8 bits are transmitted for each character.

Only upper-case letters, numeric digits and IA-5 “space” are used. The rightmost character is transmitted first. For a three-character airport ID, the rightmost (first transmitted) character shall be IA-5 “space”.

Runway number: the runway orientation, point-in-space final approach course, or SBAS circling only procedure course rounded to the nearest 10 degrees and truncated to two characters.

Coding: 01 to 36 = runway number Note.: For heliport operations, the runway number value is the integer nearest to one tenth of the final approach course, except when that integer is zero, in which case the runway number is 36.

Runway letter: the one-letter designator used, as necessary, to differentiate between parallel runways.

Coding: 0 = no letter 1 = R (right) 2 = C (centre) 3 = L (left)

Approach performance designator: this field shall not be used by L1 SBAS receivers.

298CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

Route indicator: a “blank” or the one-letter identifier used to differentiate between multiple procedures to the same runway end.

Note.: Procedures are considered to be different even if they only differ by the missed approach segment.

Coding: The letter is coded using bits b1 through b5 of its IA-5 representation. Bit b1 is transmitted first. Only upper-case letters, excluding “I” and “O”, or IA-5 “space” (blank) are used. Blank indicates that there is only one procedure to the runway end. For multiple procedures to the same runway end, the route indicator is coded using a letter starting from Z and moving backward in the alphabet for additional procedures.

Reference path data selector (RPDS): this field is not used by SBAS.

299CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Reference path identifier (RPI): four characters used to uniquely designate the reference path. The four characters consist of three alphanumeric characters plus a blank or four alphanumeric characters.

Note.: The best industry practice matches the 2nd and 3rd character encoding to the encoded runway number. The last character is a letter starting from A or a “blank.”

Coding: Each character is coded using bits b1 through b6 of its IA- 5 representation. For each character, b1 is transmitted first, and 2 zero bits are appended after b6 so that 8 bits are transmitted for each character.

Only upper-case letters, numeric digits and IA-5 “space” are used. The rightmost character is transmitted first. For a three-character reference path identifier, the rightmost (first transmitted) character shall be IA-5 “space”.

Note.: The LTP/FTP is a point over which the FAS path passes at a height above the LTP/FTP height specified by the TCH.

LTP/FTP latitude: the latitude of the LTP/FTP point in arc seconds.

Coding: positive value denotes north latitude. negative value denotes south latitude.

LTP/FTP longitude: the longitude of the LTP/FTP point in arc seconds.

Coding: positive value denotes east longitude. negative value denotes west longitude.

LTP/FTP height: the height of the LTP/FTP above the WGS-84 ellipsoid.

Coding: This field is coded as an unsigned fixed-point number with an offset of –512 metres. A value of zero in this field places the LTP/FTP 512 metres below the earth ellipsoid.

Note.: The FPAP is a point at the same height as the LTP/FTP that is used to define the alignment of the approach. The origin of angular deviations in the lateral direction is defined to be 305 metres (1 000 ft) beyond the FPAP along the lateral FAS path. For an approach aligned with the runway, the FPAP is at or beyond the stop end of the runway.

300CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 ΔFPAP latitude: the difference of latitude of the runway FPAP from the LTP/FTP in arc seconds.

Coding: Positive value denotes the FPAP latitude north of LTP/FTP latitude.

Negative value denotes the FPAP latitude south of the LTP/FTP latitude. ΔFPAP longitude: the difference of longitude of the runway FPAP from the LTP/FTP in arc seconds.

Coding: Positive value indicates the FPAP longitude east of LTP/FTP longitude.

Negative value indicates the FPAP longitude west of LTP/FTP longitude.

Approach TCH: the height of the FAS path above the LTP/FTP defined in either feet or metres as indicated by the TCH units selector.

Approach TCH units selector: the units used to describe the TCH.

Coding: 0 = feet 1 = metres Glide path angle (GPA): the angle of the FAS path with respect to the horizontal plane tangent to the WGS-84 ellipsoid at the LTP/FTP.

Course width: the lateral displacement from the path defined by the FAS at the LTP/FTP at which full-scale deflection of a course deviation indicator is attained.

Coding: This field is coded as an unsigned fixed-point number with an offset of 80 metres. A value of zero in this field indicates a course width of 80 metres at the LTP/FTP.

301CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 ΔLength offset: the distance from the stop end of the runway to the FPAP.

Coding: 1111 1111 = not provided

HAL: Horizontal alert limit to be used during the approach in metres.

VAL: Vertical alert limit to be used during the approach in metres.

Final approach segment CRC: the 32-bit CRC appended to the end of each FAS data block in order to ensure approach data integrity. The 32- bit final approach segment CRC shall be calculated in accordance with

3.9. The length of the CRC code shall be k = 32 bits.

The CRC generator polynomial shall be:

G(x) = x32 + x31 + x24 + x22 + x16 + x14 + x8 + x7 + x5 + x3 + x + 1 The CRC information field, M(x), shall be:

M(x) shall be formed from all bits of the associated FAS data block, excluding the CRC. Bits shall be arranged in the order transmitted, such that m1 corresponds to the LSB of the operation type field, and m288 corresponds to the MSB of the Vertical Alert Limit (VAL) field. The CRC shall be ordered such that r1 is the LSB and r32 is the MSB.

3.5.8.4.2.6.2 For precision approach and APV operations, the service provider ID broadcast Type 17 message shall be identical to the service provider ID in the FAS data block, except if ID equals 15 in the FAS data block.

302CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.: If the service provider ID in the FAS data block equals 15, then any service provider can be used. If the service provider ID in the FAS data block equals 14, then SBAS precise differential corrections cannot be used for the approach.

3.5.8.4.2.6.3 SBAS FAS data points accuracy. The survey error of all the FAS data points, relative to WGS-84, shall be less than 0.25 metres vertical and 1 metre horizontal.

3.5.8.4.3 Departure, en-route, terminal, and non-precision approach operations

3.5.8.4.3.1 The receiver shall compute and apply long-term corrections, fast corrections and range rate corrections.

3.5.8.4.3.2 The receiver shall compute and apply ionospheric corrections.

Note.: Two methods of computing ionospheric corrections are provided in 3.1.2.4 and 3.5.5.5.2.

3.5.8.4.3.3 The receiver shall apply a tropospheric model such that residual pseudo- range errors have a mean value (μ) less than 0.15 metres and a standard deviation less than 0.07 metres.

Note.: A model was developed that meets this requirement. Guidance is provided in Attachment D, 6.5.4.

3.5.8.4.3.4 The receiver shall compute and apply horizontal and vertical protection levels as defined in 3.5.5.6. In this computation, σtropo shall be obtained either from the formula in 3.5.8.4.2.5, which can be used for elevation angles not less than 4 degrees, or from the alternate formula below, which can be used for elevation angles not less than 2 degrees:

where θ is the elevation angle of the ith satellite. i In addition, σi,air shall satisfy the condition that a normal distribution with zero mean and standard deviation equal to σi,air bounds the error distribution for residual aircraft pseudo-range errors as follows:

303CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 where f(x) = probability density function of the residual aircraft pseudo-range i error and Note.: The standard allowance for airborne multipath defined in 3.6.5.5.1 may be used to bound the multipath errors.

3.5.8.4.4 Recommendation. – For departure, en-route, terminal, and non-precision approach operations, the receiver should use the broadcast ionospheric corrections, when available, and a tropospheric model with performance equal to that specified in 3.5.8.4.3.

3.5.9 SBAS L5 RF CHARACTERISTICS

3.5.9.1 Carrier frequency stability. The short-term stability of the L5 carrier frequency (square root of the Allan variance) at the output of the satellite transmit antenna shall be better than 6.7 × 10-11 over 1 to 10 seconds.

3.5.9.2 Carrier phase noise. The phase noise spectral density of the unmodulated carrier shall be such that a phase locked loop of 10 Hz one-sided noise bandwidth is able to track the carrier to an accuracy of 0.1 radian (1 sigma).

3.5.9.3 Spurious emissions. Spurious emissions shall be at least 40 dB below the unmodulated carrier power over all frequencies.

3.5.9.4 Code/carrier frequency coherence

3.5.9.4.1 For L5, the rate of change of code minus carrier shall be less than 0.5 metres/second.

3.5.9.4.2 For DFMC SBAS ranging satellites:

Note.: See 3.5.1.1 and 3.5.1.2 for a description of the smoothing filters to be used for the requirements below.

304CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.9.4.2.1 The root-mean-square (RMS) value over 3 600 seconds of the difference between the L5 code pseudo-range and the L5 code pseudo-range smoothed using a 10-second carrier smoothing of the code based pseudo- range shall be less than 0.200 metres.

3.5.9.4.2.2 The RMS value over 86 400 seconds of the difference between the L5 code pseudo-range and the L5 code pseudo-range smoothed using a 100- second carrier smoothing of the code based pseudo-range shall be less than 0.255 metres.

3.5.9.4.2.3 The RMS value over 3 600 seconds of the difference between the L1 code pseudo-range and the L1 code pseudo-range smoothed using a 10- second carrier smoothing of the code based pseudo-range shall be less than 0.15 metres.

3.5.9.4.2.4 The RMS value over 86 400 seconds of the difference between the L1 code pseudo-range and the L1 code pseudo-range smoothed using a 100- second carrier smoothing of the code based pseudo-range shall be less than 0.19 metres.

3.5.9.4.2.5 L1 and L5 short-term fractional code/carrier frequency coherence. For L1 and L5 signals broadcast by an SBAS ranging satellite, the RMS value over 3 600 seconds of the difference between the ionosphere-free pseudo- range and the ionosphere-free pseudo-range smoothed using a 10 second carrier smoothing of the L1/L5 ionosphere-free pseudo-range combination shall be less than 0.29 metres.

3.5.9.4.2.6 L1 and L5 long-term fractional code/carrier frequency coherence. For L1 and L5 signals broadcast by an SBAS ranging satellite, the RMS value over 86 400 seconds of the difference between the ionosphere-free pseudo-range and the ionosphere-free pseudo-range smoothed using a 100 seconds carrier smoothing of the L1/L5 ionosphere-free pseudo-range combination shall be less than 0.37 metres.

3.5.9.5 Correlation loss. The loss in the recovered signal power due to imperfections in the signal modulation and waveform distortion shall not exceed 1 dB.

Note.: The correlation loss is defined as the ratio of output powers from a perfect

correlator for two cases: a) the actual received SBAS L5 signal correlated against a perfect unfiltered pseudo-random noise reference; and b) a perfect unfiltered pseudo-random noise signal normalized to the same total power as the SBAS signal in case a), correlated against a perfect unfiltered pseudo-random noise reference.

305CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.9.6 Maximum code phase deviation. The L5 broadcast signal shall not deviate from the equivalent SBAS network time (SNT) for DFMC SBAS by more than ±2-10 seconds.

3.5.9.7 Code/data coherence. Each 2-millisecond symbol shall be synchronous with every other code epoch.

3.5.9.8 Message synchronization. The leading edge of the first symbol that depends on the first bit of the current message shall be broadcast from the SBAS satellite synchronous with a 1-second epoch of SNT for DFMC SBAS.

Note.: The SNT time reference is provided by the Type 37 message as described in 3.5.11.5.

3.5.9.9 Convolutional and bi-binary encoding

3.5.9.9.1 Convolution encoding. A 250-bit-per-second data stream shall be encoded at a rate of 2 symbols per bit using a convolutional code with a constraint length of 7 to yield 500 symbols per second. The convolutional encoder logic arrangement shall be as illustrated in Figure B-24 with the G3 output selected for the first half of each 4-millisecond data bit period.

3.5.9.9.2 Bi-binary encoding. In addition to the convolution coding detailed in paragraph 3.5.9.9.1, the convolution encoded 500 symbols per second data channel shall be further bi-binary encoded such that a “0” symbol becomes a “01” pair and a “1” symbol becomes a “10” pair resulting in a data channel operating at a 1 kHz rate.

Note.: See Attachment D, 6.4.4.

3.5.9.10 Pseudo-random noise (PRN) codes for L5. Each PRN code shall be a 10 230-bit code and be added Modulo-2 with the navigation message data stream generated in 3.5.9.9.2.

Note.: Additional information on the PRN code is given in IS-GPS-705F.

The initial state for the XA shift register shall be “1111111111111”, and the initial state for the XBi register shall be as illustrated in Table B-97.

306CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 307CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.10 DATA STRUCTURE ON SBAS L5 SIGNAL Note.: Messages broadcast for use under DFMC SBAS service are independent from those broadcast for use under L1 SBAS service. Information broadcast on SBAS L5 signal is used only for DFMC SBAS service solutions using dual-frequency measurements from core constellations.

308CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.10.1 Format summary. All messages shall consist of a preamble, a message type identifier, a data field and a cyclic redundancy check as illustrated in Figure B-28.

3.5.10.2 Preamble. For L5, the preamble shall consist of the sequence of bits “0101 1100 0110 1001 0011 1010”, distributed over six successive blocks. The start of every 24-bit preamble shall be synchronous with SNT time of day in seconds Modulo 6 seconds.

3.5.10.3 Message type identifier. The L5 message type identifier shall be a 6-bit value identifying the message type as defined in Table B-98. The message type identifier shall be transmitted MSB first.

3.5.10.4 Data field. The L5 data field shall be 216 bits as defined in 3.5.13. Each data field parameter shall be transmitted MSB first.

309CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.10.5 Cyclic redundancy check (CRC). The SBAS message CRC code on L5 shall be calculated in accordance with 3.9.

3.5.10.5.1 The length of the CRC code shall be k = 24 bits.

3.5.10.5.2 The CRC generator polynomial shall be:

G(x) = x24 + x23 + x18 + x17 + x14 + x11 + x10 + x7 + x6 + x5 + x4 + x3 + x + 1

3.5.10.5.3 The CRC information field, M(x), shall be:

3.5.10.5.4 M(x) shall be formed from the 4-bit SBAS message preamble, 6-bit message type identifier, and 216-bit data field. Bits shall be arranged in the order transmitted from the SBAS satellite, such that m1 corresponds to the first transmitted bit of the preamble, and m226 corresponds to bit 216 of the data field.

3.5.10.5.5 The CRC code r-bits shall be ordered such that r1 is the first bit transmitted and r24 is the last bit transmitted.

3.5.11 DFMC SBAS DATA CONTENT

3.5.11.1 Satellite mask parameters. The satellite mask parameters shall be as

follows:

SBAS satellite mask: the satellite mask shall be a set of 214 bits such that each bit represents one specific satellite as shown in Table B-99 and the value of that bit shall indicate whether augmentation is, or is not, provided for that satellite. It shall be broadcast in the Type 31 message.

Note.: The satellite mask can set up to 92 satellites from the 214 possible satellites available for augmentation.

Satellite slot number: a unique number representing a specific slot in the SBAS satellite mask (slots numbers range from 1 to 214) assigned to a specific satellite for which augmentation can be provided.

Note 1.: The first transmitted bit of the satellite mask corresponds to GPS PRN code number 1.

Note 2.: This parameter is also broadcast in Type 32 messages to identify the satellite to which the corrections apply.

310CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

SBAS augmented satellite signals: the DFMC SBAS standards shall allow the augmentation of the ionosphere-free combination of the following

signal per core constellation: a) for GPS: the GPS L1 C/A signal (as described in Chapter 3,

3.7.3.1.1.8 and 3.1.1.1.1) and the GPS L5-Q signal (as described in

Chapter 3, 3.7.3.1.8 and 3.1.1.1.4). The LNAV data on GPS L1C/A shall be used in DFMC SBAS position solution; b) for GLONASS: the GLONASS L1 OC signal (as described in Chapter 3, 3.7.3.1.2.10 and 3.1.2.1.5) and the GLONASS L3 OC signal (as described in Chapter 3, 3.7.3.1.2.9 and 3.1.2.1.5). The data on GLONASS L1 OC shall be used in DFMC SBAS position solution;

c) for Galileo: the Galileo E1-C signal (as described in Chapter 3,

3.7.3.1.3.11 and 3.1.3.1.1.2) and the Galileo E5a-Q signal (as described in Chapter 3, 3.7.3.1.3.11 and 3.1.3.1.1.3). The FNAV data on Galileo E5a-I shall be used in DFMC SBAS position solution; d) for BDS: the BDS B1C signal (as described in Chapter 3,

3.7.3.1.4.9 and 3.1.4.1.1.3) and the BDS B2a signal (as described in

Chapter 3, 3.7.3.1.4.10 and 3.1.4.1.1.4). The B-CNAV2 data on BDS B2a shall be used in DFMC SBAS position solution; and 311CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 e) for SBAS: the SBAS L1 signal (as described in 3.5.2) and SBAS L5 signal (as described in 3.5.9). The data broadcast on SBAS L5 shall be used in DFMC SBAS position solution.

Satellite slot value: binary indication per satellite slot to indicate whether correction and integrity data are provided for the satellite.

Coding: 0 = data not provided 1 = data provided

Augmented slot index: a number in the sequence of the satellite slot values set to “1” (1 up to 92) in the SBAS satellite mask.

Note.: The augmented slot index is “1” for the lowest satellite slot number for which the satellite slot value is “1”.

Issue of data mask (IODM): an indicator provided in Types 31, 34, 35 and 36 messages that links the integrity data provided in Types 34, 35 and 36 messages with the augmented slot indexes in the Type 31 message with the same IODM.

3.5.11.2 Satellite clock-ephemeris corrections and covariance matrix parameters.

The clock-ephemeris corrections and covariance matrix function

parameters shall be as follows:

Satellite slot number: see 3.5.11.1.

Issue of data navigation (IODN): a 10-bit indicator broadcast in Type 32 messages that associates the clock and ephemeris corrections of a satellite with the ephemeris data broadcast by that satellite. The IODN for a given satellite matches with the following information (IODs) broadcast

by the same satellite: a) for GPS: IODC parameter (3.1.1.1.3.1.4) in the L1 LNAV message; b) for GLONASS: tb parameter (3.1.2.1.3.1) in strings Type 10, 31, 32 of L1OC navigation message; c) for Galileo: IOD parameter (3.1.3.1.3.7) in the F/NAV message;

d) for BDS: IODC parameter (3.1.4.1.3.2.4.2) in the B-CNAV2 message; and e) for SBAS: IODG parameter (3.5.11.5) in the Type 39/40 messages.

Orbit and clock parameters corrections: The orbit parameters shall be

defined as follows: δx : ephemeris correction for the X-axis in WGS84 ECEF coordinates;

(ECEF) 312CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 δy : ephemeris correction for the Y-axis in WGS84 ECEF coordinates;

(ECEF) δz : ephemeris correction for the Z-axis in WGS84 ECEF coordinates;

(ECEF) δB : clock offset error correction expressed in metres;

(ECEF) δẋ : ephemeris velocity correction for the X-axis in WGS84 ECEF

(ECEF) coordinates; δẏ : ephemeris velocity correction for the Y-axis in WGS84 ECEF

(ECEF) coordinates; δż : ephemeris velocity correction for the Z-axis in WGS84 ECEF

(ECEF) coordinates; δḂ : clock drift error correction expressed in metres per second; and

(ECEF) t : time of applicability of the parameters δx, δy, δz, δB, δẋ, δẏ, δż and δḂ D expressed in seconds of the day (see Attachment D, 6.7.11).

Scale exponent: a term to compute the scale factor used to code the Cholesky factorization elements.

Cholesky factorization elements (Ei,j): elements of an upper triangle matrix which compresses the information in the clock and ephemeris covariance matrix. These elements are used to compute the user location factor (δ ) as a function of user position (see 3.5.12.4.1).

DFRE Dual-frequency range error indicator (DFREI): a 4-bit indicator of the dual- frequency range error (DFRE) value, with range from 0 to 15, with value 15 corresponding to “Do Not Use for SBAS”.

Note 1.: For other values (from 0 to 14), the table defining the correspondence between the DFREI values and the standard deviation (σDFRE, in metres) is given in 3.5.11.4.

Note 2.: The broadcast standard deviation values (within the allowed ranges as defined in 3.5.11.4) are SBAS-dependent. δR : the first order degradation parameter multiplier.

CORR Note.: All parameters are broadcast in the Type 32 message.

3.5.11.3 Integrity message parameters. The integrity message parameters shall

consist of:

Dual-frequency range error change indicator (DFRECI): a 2-bit indicator that denotes the integrity status of a specific satellite identified by its augmented slot index (see 3.5.11.1), as specified in Table B-100.

313CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Issue of data mask (IODM): see 3.5.11.1.

Dual-frequency range error indicator (DFREI): see 3.5.11.2.

Note.: Parameters are broadcast using one or more the following message types: a) Type 34 message providing DFRECI for all augmented satellites, DRFEI for up to 7 augmented satellites and IODM; and b) Types 35 and 36 messages broadcasting IODM and DFREIs for a maximum set of 53 and 39 augmented satellites, respectively.

3.5.11.4 Degradation parameters and DFREI scale table parameters. The old but active data (OBAD) parameters and DFREI scale table parameters shall

be as follows:

Common OBAD parameters: a set of parameters common to all augmented satellites where

(IVALID) is the Type 32 message validity interval;

32

(IVALID) is the Types 39 and 40 messages validity interval;

39/40 C is the step degradation parameter for en-route through non-precision ER approach applications;

C is the clock-ephemeris covariance degradation COVARIANCE parameter; and Degradation equation selector indicates how the degradation terms combine for the dual-frequency residual error model variance.

Coding: 0 = δ only multiplies σ , correction residuals are DFRE DFRE 314CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 root-sum squared 1 = δ multiplies the linear sum of σ and the degradation DFRE DFRE parameters

Specific OBAD parameter: a set of parameters linked to a given core constellation used to account for the degradation of corrections that are old but still valid, where:

I is the time interval for application of CCORR;

CORR C is the step degradation parameter for precision approach CORR applications; and R is the first order degradation parameter.

CORR

Time reference identifier: a parameter that specifies the GNSS constellation on which the SNT for DFMC SBAS is aligned, where “0” is GPS; “1” is GLONASS; “2” is Galileo; “3” is BDS; “4” is reserved; and “5”, “6” and “7” are spare.

DFREI scale table: provides the mapping between the DFREI parameter (see 3.5.11.2) and σDFRE as specified in Table B-101. σ is the standard deviation of the residual ionosphere-free clock and DFRE ephemeris range error following the application of the DFMC SBAS clock and ephemeris corrections (Type 32 message) or of the SBAS satellite clock and ephemeris (Type 39/40 message).

315CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.: All parameters are broadcast in the Type 37 message.

3.5.11.5 SBAS satellite clock, ephemeris and covariance matrix parameters. The broadcasting SBAS satellite clock, ephemeris and covariance data shall

be as follows:

Issue of data GEO (IODG): an issue of data indicator that links Type 39 and 40 messages.

Note.: Each message of a paired Type 39/40 message set contains the same 2- bit IODG.

SBAS service provider ID: identifies the SBAS service provider responsible for the signal broadcast by the SBAS satellite, as defined in Table B-65.

Keplerian parameters: the ephemeris information to determine the ionosphere-free dual-frequency L1/L5 antenna phase centre location is:

C is the amplitude of cosine harmonic correction terms to the argument uc of latitude;

C is the amplitude of sine harmonic correction terms to the argument of us latitude;

I is the rate of inclination angle; dot a is the semi-major axis;

316CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 ω is the argument of perigee; Ω is longitude of ascending node of orbital plane at te;

0 M is the mean anomaly at te;

0 I is the inclination at te; and e is the eccentricity;

Satellite slot delta: identifies the broadcasting SBAS satellite in Table B-

102.

Note.: A satellite slot delta of 0 is used in the Type 47 message to indicate that no almanac data follows.

SBAS ephemeris time te: time of applicability of the ephemeris message in seconds of day;

clock parameters: provided for ionosphere-free position as follows: a : clock offset; and Gf0 a : clock rate;

Gf1

scale exponent: see 3.5.11.2;

covariance matrix: see 3.5.11.2; dual-frequency range error indicator (DFREI): see 3.5.11.2; and δ : see 3.5.11.2.

RCORR Note.: All parameters are broadcast in combined Type 39 and Type 40 messages.

3.5.11.6 GNSS time offsets parameters. The GNSS time parameters shall be as

follows:

The common UTC parameters are:

A : drift coefficient of the SNT scale for DFMC SBAS relative to UTC;

1SNT 317CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 A : bias coefficient of the SNT scale for DFMC SBAS relative to UTC 0SNT time scale; t : time data reference time of week;

0t WN: data reference week number; t Δt : current or past leap second count;

LS

WN : leap second reference week number;

LSF DN: leap second reference day number; Δt : current or future leap second count; and LSF UTC standard identifier (defined in 3.5.4.8).

The validity model parameters of the SNT-to-UTC offset model are:

TOW : start time in time of week of the validity period of the app information broadcast in the common UTC parameter field;

WN : week number associated to the TOW defining the validity period app app of the information broadcast in the common UTC parameter field. WN app set to 0 means that the WN = WN-1. WN set to 1 means that the app t app WN =WN;

app t VP: identifies the validity period (time-out) duration according to Table B-104 for the common UTC information; and

UTC offset status: SNT-to-UTC offset validity status defined according to Table B-103.

318CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 The time-out for the SNT-to-UTC offset information (noted TO42 below)

shall be defined as follows: a) if VP is set to 0: TO42 = Type 42 message received time + 86 400 s; b) if VP is set to a value different from 0: TO42 = start time in seconds (defined by TOWapp and WNapp) + (VP duration) × 3 600.

Note 1.: All parameters are broadcast in a Type 42 message.

Note 2.: It is not intended that Type 42 messages be used for positioning services with integrity, as no integrity budget is defined in SBAS system for the time offset parameters.

3.5.11.7 SBAS satellite parameters. The SBAS satellite parameters shall be as

follows:

satellite slot delta: see 3.5.11.5;

SBAS service provider ID: see 3.5.11.5;

broadcast indicator: when set to 1, it identifies the almanac data of the broadcasting satellite. It shall be set to 0 otherwise;

almanac parameters: broadcast using Keplerian parameters, where: a is the semi-major axis; e is the eccentricity;

I is the inclination; ω is the argument of perigee; Ω is the longitude of ascending node of orbital plane at beginning of week;

0 Ω̇ is the rate of right ascension of the ascending node;

M is the mean anomaly at t ; and 0 a 319CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 t is SBAS almanac time (the almanac reference epoch in seconds of day); a week number rollover count (WNRO ): the number of week number count rollovers already elapsed for the GNSS constellation identified by the time reference identifier at the almanac reference time, ta, broadcast in the SBAS I Keplerian parameters block of the Type 47 message (see Table B-102). WNRO value of 15 shall be used to indicate that the parameter count is not valid and will be updated. The starting time per constellation with

respect to UTC shall be: a) for GPS: midnight between 5 January 1980 and 6 January 1980 (see

3.1.1.4); b) for GLONASS: midnight between 31 December 1995 and 1 January 1996 (see 3.1.2.4); c) for Galileo: 13 seconds before midnight between 21 August 1999 and 22 August 1999 (see 3.1.3.4); and d) for BDS: midnight between 31 December 2005 and 1 January 2006 (see 3.1.4.4).

Note 1.: All parameters are broadcast in a Type 47 message.

Note 2.: The Type 47 message provides the capacity to transmit the SBAS almanacs parameters of 2 SBAS satellites.

3.5.12.1 DEFINITIONS OF PROTOCOLS FOR DFMC SBAS DATA APPLICATIONS Note.: This section provides the definitions of parameters used by SBAS (non- aircraft and aircraft elements) that are needed to compute the navigation solution and associated integrity (protection levels).

3.5.12.1 General information for DFMC SBAS data protocol The conventional values to be used for the computation of the earth-fixed

coordinates of the SBAS space vehicle antenna phase centre shall be: π = 3.1415926535898 (ratio of a circle’s circumference to its diameter); μ = 3.986005 x 1014 m3/s2 (earth’s gravitational parameter);

Ω’ = 7.2921151467 x 10-5 rad/s (earth’s rotation rate); and 𝑒 c = 299 792 458 m/s (speed of light in a vacuum).

Note.: The values of these parameters are not broadcast by SBAS but use of the correct values is necessary to ensure interoperability between different 320CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 SBAS implementations.

When computing a time difference (t-t ) where the reference time t0 is 0 expressed in the SNT (such as t broadcast in Type 32 message, te D broadcast in Type 40, ta broadcast in Type 47 message), the time t used in 3.5.12 shall be expressed in the same time frame considering the conversion elements in Table B-105.

3.5.12.2 Determination of SBAS satellite position based on its almanac.

The following parameters described in 3.5.11.7 shall be used in the

computation of the SBAS satellite position based on its almanac: t : SBAS almanac time (the reference epoch of the almanac (s) as a time a of day); a: semi-major axis (m); e: eccentricity (dimensionless);

M : mean anomaly (rad) at ta;

0 ω: argument of perigee (rad);

I: inclination angle (rad); Ω : longitude of ascending node of orbital plane at beginning of week (rad);

0 and Ω̇ : rate of right ascension of the ascending node (rad/s).

321CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 The computation of the SBAS satellite position shall be made for the epoch t, expressed in the SNT frame for DFMC SBAS. The “almanac reference epoch” shall be broadcast as a time of day through ta. The SBAS users shall account for the truncated nature of the t parameter.

a

3.5.12.2.1 Computation of the mean anomaly (Mt) The mean anomaly (Mt) at the epoch t shall be computed as:

M = M + n Δ t 0 0 t where Note.: The SBAS user needs to ensure that t and ta have the same time reference when computing Δt. Since the broadcast parameter ta is a time of day, conversion is needed to account for day or week changes.

3.5.12.2.2 Computation of the eccentric anomaly (Et) The eccentric anomaly (Et) for epoch t shall be computed solving the

equation:

M = E − e sin(E) t t t Note.: This equation may be solved by iteration.

3.5.12.2.3 Computation of the argument of latitude (Φ) t The argument of latitude (Φ) for epoch t shall be computed as: t ϕ = v + ω t t

where v is the true anomaly at epoch t: t

3.5.12.2.4 Computation of the coordinates in the orbital plane (x’; y’) t t The coordinates in the orbital plane (x’; y’) for epoch t shall be computed t t as:

322CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

where rt is the orbit radius at epoch t: rt = a × [1 − (e × cosE)] t

3.5.12.2.5 Computation of the space vehicle fixed earth’s coordinates (x; y; z) t t t The space vehicle fixed earth’s coordinates (x; y; z) for epoch t shall be t t t

computed as: where Ω is the corrected longitude of the ascending node at epoch t: t and t is t expressed in seconds as a time of week (or elapsed time aTOW a since the beginning of the almanac week).

3.5.12.3 Determination of SBAS satellite position based on its ephemeris The following parameters, described in 3.5.11.5, shall be used in the

computation of the SBAS satellite position based on its ephemeris: t : SBAS ephemeris time (the reference epoch of the ephemeris (s) as a e time of day); a: semi-major axis (m); e: eccentricity (dimensionless);

M : mean anomaly (rad) at te;

0 ω: argument of perigee (rad);

I: inclination angle at te (rad);

I : rate of inclination angle (rad/s); dot Ω : longitude of the ascending node of orbital plane at te (rad);

0 C : amplitude of the cosine harmonic correction to the argument of latitude uc

(rad); and C : amplitude of the sine harmonic correction to the argument of latitude us

(rad).

The computation of the SBAS satellite position shall be made for the epoch 323CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 t, expressed in the SNT frame for DFMC SBAS. The “ephemeris reference epoch” shall be broadcast as a time of day through t . The SBAS users e shall account for the truncated nature of the t parameter.

e

3.5.12.3.1 Computation of the mean anomaly (Mt) The mean anomaly (Mt) at the epoch t shall be computed as:

M = M + n Δ t 0 0 t where Note.: The SBAS user needs to ensure that t and te have the same time reference when computing Δt. Since the broadcast parameter te is a time of day, a conversion is needed to account for day or week changes.

3.5.12.3.2 Computation of the eccentric anomaly (E) t The eccentric anomaly (Et) for epoch t shall be computed solving the

equation:

M = E − esin(E) t t t Note.: This equation may be solved by iteration.

3.5.12.3.3 Computation of the argument of latitude (Φ) t The eccentric anomaly (Φt) for epoch t shall be computed as: ϕ = v + ω t t

where v is the true anomaly at epoch t: t

3.5.12.3.4 Computation of the corrected argument of latitude (u) t The corrected argument of latitude (ut) for epoch t shall be computed as: u = ϕ + δu t t t 324CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 where δu is the argument of latitude second harmonic perturbation at t

epoch t: δu = [C sin(2ϕ)] + [C cos(2ϕ)] t us t us t

3.5.12.3.5 Computation of the coordinates in the orbital plane (x’; y’) t t The coordinates in the orbital plane (x’; y’) for epoch t shall be computed t t as:

where r is the orbit radius at epoch t: t r = a[1-(ecosE)] t t

3.5.12.3.6 Computation of the space vehicle fixed earth’s coordinates (x; y; z) t t t The space vehicle fixed earth’s coordinates (xt; yt; zt) for epoch t shall be

computed as: where Ω is the corrected longitude of the ascending node at epoch t: t Ω = Ω − (Ω̇ Δ ) 𝑡 0 𝑒 𝑡

and i is the corrected inclination for epoch t: t i = I + (I Δ) t dot t Note 1.: The Sagnac correction (earth’s rotation) needs to be taken into account.

Note 2.: The rate of right ascension of the ascending node is assumed to be zero.

3.5.12.4 SBAS DFMC navigation solution Note.: 3.5.12.4 provides formulas for the SBAS DFMC navigation solution of an SBAS system augmenting two core constellations, Constellation 1 (C1) and Constellation 2 (C2). When the number N of constellations being augmented is different from 2 (N=1, 3 or 4), the size of G and of X will need to vary accordingly. Additional information is available in Attachment D,

6.7.12.

The weighted least square navigation solution takes the following form:

325CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Where a) X̂ is the weighted least square estimate of the error in the estimated

location of the user about which the linearization has been made: where t is the clock bias of the receiver in seconds with respect to Constellation C1 1 reference time; and t is the time difference observed by the receiver in seconds between C1-C2 the reference constellation 2 and the constellation 1, namely t = t – C1-C2 C2 t ;

C1 Note.: This is one possible implementation. A second implementation is described in Attachment D, 6.7.12. b) Y is the P-dimensional vector containing the corrected ionosphere- free pseudo-range measurements PRi,corrected, minus the expected ranging values based on the location of the satellites and the estimated location of the user (X), where P is the number of satellites used in the navigation solution;

PR is the corrected ionosphere-free pseudo-range measurement i,corrected for the satellite i computed as specified in 3.5.1.2 with the parameters as

follows: 𝑏, defined in 3.5.1.2, is SBAS corrected clock: 𝑖 δΔt is the time error estimate at time t computed with the parameters SV,I described in 3.5.11.2 as follows: Δt is the satellite time correction described in 3.5.15.1.1.2; and SV,i t is the reference time of the corrections.

D The satellite position error correction vector [δx(t), δy(t), δz(t)] shall be expressed in the WGS-84 ECEF coordinate frame as follows and shall be added to the satellite coordinate vector [x(t), y(t), z(t)]:

326CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 with δx, δy, δz, 𝛿𝑥̇ 𝛿𝑦̇ and 𝛿𝑧̇ defined in 3.5.11.2.

Note 1.: The SBAS user needs to ensure that t and tD have the same time reference when computing t-tD. Since the broadcast parameter tD is a time of day, a conversion is needed to account for day or week changes.

Note 2.: In case of SBAS ranging, for the SBAS ionosphere-free measurements of the SBAS providing the correction and integrity information, the time error estimate 𝛿Δ𝑡𝑆𝑉 is zero as there is no correction provided for this satellite.

c) G is the observation matrix: where El is the elevation for satellite i after correction of its position using the i parameters described in 3.5.11.2;

Az is the azimuth for satellite i after correction of its position using the i parameters transmitted described in 3.5.11.2.

The positive azimuth is defined clockwise from North; and n is “1” if satellite is part of reference constellation C2 or “0” if it is part of i C1.

For SBAS ranging satellite: ni is “0” if C1 is GPS and ni is “1” if C2 is GPS.

Note 1.: The DFMC SBAS standards have no provisions for the augmentation of DFMC SBAS ranging signals from other service providers.

Note 2.: If SBAS ranging is provided by the SBAS and if the SBAS is not augmenting GPS, the SBAS range time offset needs to be solved by introducing an additional unknown in the observation matrix as explained in Attachment D, 6.7.12.1.

d) W is the weighting matrix:

327CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 where σ2 is the model variance for the residual error associated to SBAS i,DFC corrections for satellite i, as defined in 3.5.12.4.1;

σ2 is the model variance for the troposphere residual error for satellite i,tropo i, as defined in 3.5.8.4.2.4 and 3.5.8.4.2.5; σ2 is the model variation for the combined measurement noise and i,air_DF multipath residual errors applicable to the ionosphere-free combination of dual-frequency range measurements (see 3.5.15.3.4.1) for satellite i; and σ2 is the model variance for the ionosphere-free residual error for i,iono satellite i, as defined in 3.5.15.3.4.2.

3.5.12.4.1 Computation of the model variance for the residual error associated to SBAS corrections 𝜎2 . 𝐷𝐹𝐶 Note.: The following calculations are done for each satellite. For convenience, the index i used in 3.5.12.4 was removed from the equations.

The user location factor (δ ) shall be obtained via the clock-ephemeris DFRE

covariance matrix C as follows:

C=RTR where then where I is the 4-D line of sight vector from the user to the satellite in the WGS- 84 coordinate frame where the first three components are the unit vector from the user to the satellite and the fourth component is 1;

ε is derived from CCOVARIANCE (defined in 3.5.11.4) as:

C εC = C × 2scale exponent−5; and COVARIANCE 328CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 scale exponent is defined in 3.5.11.2 and is transmitted through Type 32 messages for core constellation satellites and Type 40 messages for SBAS satellites.

The model variance for the residual error associated to SBAS corrections (σ2 ) at the time t shall be computed using the SBAS corrections DFC parameters described in 3.5.11.2 (for core constellations satellites) and

3.5.11.5 (for SBAS satellite) associated to the OBAD parameters described in 3.5.11.4 based on the broadcast degradation equation

selector as follows: where σ is the standard deviation of the residual ionosphere-free clock and DFRE ephemeris range error as defined in 3.5.11.4; ε is the degradation parameter for corrections;

CORR ε is the degradation parameter for en-route through non-precision er approach applications. It shall be equal to 0 if the corrections have not timed out for approach applications (APV-I or Category I). It shall be equal to Cer (see 3.5.11.4) if any of the corrections or the DFREI/DFRECI (i.e. information broadcast in a valid Types 32, 34, 35, 36, 39 and 40 messages) have timed out for approach application but are still valid for en-route through non-precision approach applications;

t is the time of applicability (the start of the epoch of the SNT second CORR that is coincident with the transmission by SBAS of the first bit of the message block) of the latest satellite or SBAS clock-ephemeris correction information received mapping with the satellite ephemeris;

I is the time interval for application of C (see 3.5.11.4);

CORR CORR C is the step degradation parameter for precision approach CORR applications (see 3.5.11.4); (R ) is the satellite specific degradation factor computed from 𝑅 CORR SV 𝐶𝑂𝑅𝑅 (see 3.5.11.4) and 𝛿𝑅 as in 3.5.11.2 (for the augmented satellites) or 𝐶𝑂𝑅𝑅 in 3.5.11.5 (for SBAS):

if t - t ≤ I , then (𝑅 ) = 𝑅 ×𝛿𝑅 CORR CORR 𝐶𝑂𝑅𝑅 SV 𝐶𝑂𝑅𝑅 𝐶𝑂𝑅𝑅 329CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 if t - t > I , then (𝑅 ) = 𝑅 ; and CORR CORR 𝐶𝑂𝑅𝑅 SV 𝐶𝑂𝑅𝑅 ⌊x⌋ is the greatest integer less than or equal to x.

3.5.12.5 Protection level calculation For a general least-squares position solution, the projection matrix S shall

be defined as: where G is the observation matrix defined in 3.5.12.4; and W is the weighting matrix defined in 3.5.12.4.

3.5.12.5.1 Horizontal protection level (HPL) The horizontal protection level (HPL) shall be computed as follows:

HPL=K d H major where d is the error uncertainty along the semi-major axis of the error ellipse major defined as where d2 is the variance of model distribution that overbounds the true error east

distribution in the east axis: d2 is the variance of model distribution that overbounds the true error north

distribution in the north axis:

330CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

d is the covariance of model distribution in the east and north axis:

EN s is the partial derivative of position error in the east direction with (east,i) respect to the pseudo-range error on the ith satellite; s is the partial derivative of position error in the north direction with (north,i) respect to the pseudo-range error on the ith satellite;

σi is defined in 3.5.12.4.

3.5.12.5.2 Vertical protection level (VPL) The vertical protection level (VPL) shall be computed as follows: where K =5.33;

V,PA d2 is the variance of model distribution that overbounds the non- nt,U

tropospheric true error distribution in the vertical axis defined as: where s is the partial derivative of position error in the vertical direction with U,I respect to the pseudo-range error on the ith satellite; and σ2 is given by:

nt,i (sigma terms defined in 3.5.12.4) d2 is given by: tropo, U d2 is the square root of the model variance for the troposphere tropo, U residual error for satellite i, as defined in 3.5.8.4.2.5;

3.5.13 DFMC SBAS MESSAGE TABLES 331CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Each SBAS message shall be coded in accordance with the corresponding message format defined in Tables B-92 through B 104.

All signed parameters in these tables shall be represented in two’s complement, with the sign bit occupying the MSB.

Note 1.: The value of every parameter contained in a DFMC message is computed as follows, considering that fieldvalue is the decimal value of the binary number, after two’s complement transformation if specified in the

description column of the table: • if the parameter is coded as two’s complement: parameter = field *scale ; and value factor • if the parameter is not coded as two’s complement: parameter = offset + field *scale , where the offset being specified in the value factor comment column if different from the effective range minimum.

Note 2.: Reserved bits in DFMC messages can take any value.

Note 1.: This message is the equivalent of the L1 SBAS Type 0 message but with application for the messages broadcast on DFMC SBAS service only.

Note 2.: When this message is broadcast, it indicates that the signal does not support safety-of-life operation. SBAS may broadcast the data field of any message type in each Type 0 message.

332CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 333CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.: All parameters are defined in 3.5.11.1.

334CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note 1.: This message contains the correction parameters for a single satellite identified by the satellite slot parameter.

Note 2.: All parameters are defined in 3.5.11.2.

Note 1.: DFREI is defined in 3.5.11.2.

335CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note 2.: IODM is defined in 3.5.11.1.

Note 3: DFRECI is defined in 3.5.11.3.

Note 4.: See Attachment D, 6.7.14 for further guidance.

Note 1.: DFREI is defined in 3.5.11.2.

Note 2.: IODM is defined in 3.5.11.1.

Note 1.: DFREI is defined in 3.5.11.2.

Note 2.: IODM is defined in 3.5.11.1.

Note 3.: See Attachment D, 6.7.14 for further guidance.

336CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 337CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.: All information is defined in 3.5.11.4.

338CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note 1.: All information is defined in 3.5.11.5.

Note 2.: 3.5.9.6 limits aGf0 to ±292 766.07 m.

339CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note 1.: DFREI and δRCORR are defined in 3.5.11.2.

Note 2.: All other information is defined in 3.5.11.5.

340CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 341CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 342CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note 1. — SBAS service provider identifiers are defined in 3.5.11.5.

Note 2. — All other parameters are defined in 3.5.11.7.

Note.:— The null message is used as a filler message if no other message is available for broadcast for the one-second time slot.

Table B-119. L5 message data time-out intervals En-route, Precision Associated Maximum update terminal, NPA approach, APV Data message types interval time-out time-out “Do Not Use” 0 6 s N/A N/A Satellite mask 31 120 s 600 s 600 s DFREI or DFRECI 32 6 s 18 s 12 s 34 6 s 18 s 12 s 35 6 s 18 s 12 s 36 6 s 18 s 12 s 40 6 s 18 s 12 s Satellite clock-ephemeris 32 0.5x(I ) s per 1.5x(I ) (I ) valid 32 valid 32 valid 32 corrections and covariance matrix corrected satellite SBAS satellite clock, ephemeris 39 0.5x(I ) s 1.5x(I ) (I ) valid 39/40 valid 39/40 valid 39/40 and covariance matrix 40 Degradation parameters 37 120 s 600 s 600 s DFREI scale table 37 120 s 600 s 600 s Time reference identifier 37 120 s 600 s 600 s SBAS service provider identifier 39 120 s N/A 600 s 47 120 s N/A 600 s SNT-to-UTC offset 42 240 s Note 3 Note 3 Note1.-The time-out intervals are defined from the time of arrival at the receiver’s antenna port of the last bit of the message.

Note 2.-There is no time-out requirement for other parameters of the Type 47 message than those listed above.

Note 3.-The SNT-to-UTC offset information in the Type 42 message times out as defined in 3.5.11.6 taking account the parameters WNapp, TOWapp and VP.

343CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.14 DFMC SBAS NON-AIRCRAFT ELEMENTS Note.: The parameters that are referred to in this section are defined in 3.5.11.

3.5.14.1 General

3.5.14.1.1 Required data and broadcast intervals. SBAS shall broadcast the data required for the supported functions described in Chapter 3, 3.7.3.4.2 as shown in Table B-120.

Note.: SBAS may broadcast null messages (Type 63 messages) in each time slot for which no other data are broadcast.

3.5.14.1.1.1 All data broadcast by SBAS, whether required or not for a particular function, shall meet the update requirements in Table B-120.

3.5.14.1.2 SBAS radio frequency monitoring. The SBAS shall monitor the SBAS satellite parameters shown in Table B-121 and take the indicated action.

344CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.14.1.3 “Do Not Use”. SBAS shall broadcast a “Do Not Use” message (Type 0 message) when necessary to inform users not to use the SBAS satellite broadcast data on L5 and dual-frequency ranging function.

3.5.14.1.4 Doppler shift in SBAS satellite. The Doppler shift in the SBAS satellite signal seen at any fixed location within the footprint for any satellite shall

not exceed: a) ±337 Hz for GEO satellite signal; and b) ±7 kHz for non-GEO satellite signal.

3.5.14.1.5 SBAS ephemeris parameters. When broadcasting ephemeris parameters, each SBAS satellite shall broadcast ephemeris parameters for itself as defined in 3.5.11.5.

3.5.14.1.5.1 The SBAS service provider shall ensure that the SBAS ephemeris time parameter te in the Type 40 message is set within -43 200 s and +43 199 s of the broadcast time and adjusted for day crossovers.

345CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.: t is encoded as a time of day and the applicable day/week complies with e the [-43 200 s; +43 199 s] time window.

3.5.14.1.6 Almanac data. Each SBAS satellite shall broadcast almanac data as defined in 3.5.11.7 for all SBAS satellites of the same service provider.

Note.: Additional information for certain SBAS orbits is given in Attachment D,

6.7.5.

3.5.14.1.6.1 The error in the estimated position of the satellite derived from any Type 47 message broadcast within the previous 15 minutes, with respect to the true satellite position, shall not exceed 3 000 km.

3.5.14.1.6.2 The error in the predicted Doppler shift computed from the Type 47 message shall not exceed ± 337Hz for a period of seven days after the broadcast of the Type 47 message.

Note.: SBAS receivers can expect this almanac accuracy for seven days from reception of the almanac message. The receiver needs to account for day and week crossovers since the almanac reference time is only in seconds of day.

3.5.14.1.6.3 If only one SBAS satellite almanac is provided in the Type 47 message, the bits from 118 to 225 assigned to the second SBAS satellite almanac shall be coded with “0”.

3.5.14.1.6.4 SBAS shall set the broadcast indicator to “1” for the SBAS satellite broadcasting the Type 47 message, and set the broadcast indicator to “0” for all other SBAS satellites.

3.5.14.1.6.5 SBAS service provider shall ensure the correctness of the SBAS service provider ID using the value allocated to the SBAS service provider as per Table B-65 in any Type 47 message.

3.5.14.1.6.6 SBAS service provider shall ensure that the SBAS almanac time parameter ta in the Type 47 message is set within -43 200 s and +43 199 s of the broadcast time and adjusted for day crossovers.

Note.: t is encoded as a time of day and the applicable day/week complies with a the [-43 200 s; +43 199 s] time window.

3.5.14.2 Ranging function. If an SBAS provides a DFMC SBAS ranging function, it shall also comply with the requirements contained in this section.

3.5.14.2.1 Performance requirements Note.: See Chapter 3, 3.7.3.4.3.

3.5.14.2.2 Ranging function data. SBAS shall broadcast the ephemeris parameters, covariance matrix and DFREI value only for the broadcasting SBAS satellite through Type 39 and Type 40 messages both linked by their 346CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 IODG.

3.5.14.2.3 Active IODG. SBAS shall have no more than three active IODG. An active IODG corresponds to an IODG parameter broadcast in Types 39 or 40 messages, which have not timed out as per Table B-119.

3.5.14.3 Ionosphere-free differential correction function. If an SBAS provides an ionosphere-free differential correction function, it shall also comply with the requirements contained in this section.

3.5.14.3.1 Performance of the ionosphere-free differential correction.

3.5.14.3.1.1 For en-route, terminal and non-precision approach, given any valid combination of active data, the probability of a horizontal error exceeding the HPL (as defined in 3.5.12.5) for longer than eight consecutive seconds shall be less than 10-7 in any hour, assuming a user with zero latency.

3.5.14.3.1.2 Given any valid combination of active data, the probability of an out of tolerance condition (e.g. horizontal error exceeding the HPL or vertical error exceeding the VPL, as defined in 3.5.12.5), for longer than 5.2 consecutive seconds time-to-alert shall be less than 2 × 10–7 during any approach, assuming a user with zero latency.

3.5.14.3.1.3 When SBAS detects that the probability of error exceeding the protection level is above the integrity risk requirement for one of the SBAS operations, the resulting alert information (set DFRE to a larger value or to “Do Not Use for SBAS”), broadcast in Types 32, 34, 35, 36 or 40 messages, shall be repeated three times in a row after the initial notification of the alert condition for a total of four times in four seconds.

Note 1.: A Type 0 message can also be sent four times in a row to indicate an alert condition. See Attachment D, 6.7.4 for additional guidance.

Note 2.: Active data is defined as data that has not timed out per 3.5.15.1.4.2. This requirement includes core satellite constellation(s) and SBAS failures.

Note 3.: Subsequent messages can be transmitted at the normal update rate.

3.5.14.3.2 SBAS satellite mask and issue of data mask (IODM). SBAS shall broadcast an SBAS satellite mask and IODM (Type 31 message). The satellite slot values shall indicate whether or not data are being provided for each GNSS satellite.

3.5.14.3.2.1 SBAS shall change the IODM when there is a change in the SBAS satellite mask by increasing by 1 the IODM Modulo-4 from the latest transmitted value.

3.5.14.3.2.2 The IODM in Type 34, 35 and 36 messages shall equal the IODM broadcast in the satellite mask message (Type 31 message) used to designate the satellites for which data are provided in those messages..

347CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.14.3.2.3 SBAS shall have no more than two active IODMs. An active IODM corresponds to a satellite mask broadcast in a Type 31 message, which has not timed out as per Table B-119.

3.5.14.3.3 Satellite corrections and covariance matrix data.

3.5.14.3.3.1 Except for the broadcasting SBAS satellite, SBAS shall broadcast clock and ephemeris corrections and covariance matrix (Type 32 message) for any satellite in the SBAS satellite mask (i.e. with satellite slot value equal to “1”) when SBAS sets a DFREI between 0 and 14.

Note.: The Type 39/40 message from the broadcasting satellite does not require further correction and therefore SBAS broadcasting satellite will not send correction data for itself.

3.5.14.3.3.2 SBAS shall broadcast clock and ephemeris correction and covariance matrix data with an issue of data navigation (IODN) matching to the clock and ephemeris data from GNSS satellites being corrected (IODs). The IODN value shall be derived from the IODs of GNSS satellite clock and ephemeris data as described in 3.5.11.2.

3.5.14.3.3.3 In order to enable all SBAS users to acquire the new GNSS data upon transmission of new valid clock and ephemeris data from the GNSS satellites, the SBAS shall continue to broadcast corrections and covariance matrix with respect to the old clock and ephemeris data for a

period of time of: a) 120 to 240 seconds for GPS; b) 150 to 320 seconds for GLONASS; c) 150 to 350 seconds for Galileo; and d) 120 to 300 seconds for BDS.

Note.: “Valid clock and ephemeris data” means that the information broadcast by the GNSS satellites is in line with its signal interface control document

(ICD), performance standard and SARPs.

3.5.14.3.3.4 For any non-SBAS satellite, SBAS shall only broadcast a Type 32 message when SBAS has continuously monitored that satellite’s ephemeris and clock data for at least 300 seconds.

Note.: IOD is defined in 3.5.11.2 and includes a comparison of the GPS LNAV IODE with the 8 LSB of the GPS LNAV IODC. Ephemeris and clock data is derived from the core constellation navigation message being augmented by DFMC SBAS as mentioned in 3.5.11.1.

3.5.14.3.3.5 SBAS service provider shall ensure that the correction time of applicability parameter t in the Type 32 message is set within -43 200 s and +43 199 D s of the broadcast time and adjusted for day crossovers 348CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.: t is encoded as a time of day and the applicable day/week complies with D the [-43 200 s; +43 199 s] time window.

3.5.14.3.4 Integrity data. For each satellite set in the SBAS satellite mask, SBAS shall broadcast DFREI information using DFREI or DFRECI parameters, covariance matrix, scale exponent and degradation parameters such that the integrity requirement in 3.5.14.3.1 is met. If the corrections exceed their coding range or if σ2DFC (as described in 3.5.12.4.1) cannot bedetermined, SBAS shall indicate that the satellite is not appropriate for SBAS position (“Do Not Use for SBAS”).

Note.: The SBAS receiver will apply the DFRECI to its current active DFREI which can be any active broadcast DFREI.

3.5.14.3.4.1 SBAS shall provide DFREI information, directly via DFREI parameter or indirectly via DFRECI parameter, allowing the computation of σ (as DFRE defined in 3.5.11.4) for the satellite set in the satellite mask and monitored by SBAS using Types 34, 35 or 36 messages at least every six seconds.

3.5.14.3.4.1.1 When using a Type 34 message, the SBAS shall transmit at most seven DFRECIs set to “1”.

Note 1.: Instead of transmitting updated DFREI values in the Type 34 message, the SBAS can set some DFRECI values to “2” or “3” to change DFREIs on more than seven satellites and still use the Type 34 message. Types 35 or 36 message can also be used instead of Type 34 messages to provide more DFREI value updates.

Note 2.: The DFRECIs are in augmented slot index order derived from the Type 31 message with a matching IODM.

3.5.14.3.4.1.2 When using a Type 34 message with DFRECI set to “1”, the SBAS shall broadcast the new DFREI values in the order corresponding to the order of DFRECI set to “1” across the DFRECI field. The new DFREI value shall apply to the augmented slot index of the corresponding DFRECI value set to “1”.

3.5.14.3.4.2 SBAS shall set to “15” any DFREI value in the associated data field of Types 35 and 36 messages, which corresponds to satellite slot number not set in the mask.

3.5.14.3.4.2.1 When using a Type 34 message, SBAS shall set DFRECI value to “3” for DFRECI slots exceeding the maximum augmented slot index.

3.5.14.3.4.2.2 If in a given Type 34 message, the number N of DFRECI set to “1” is below seven, the last 7-N DFREI values of the Type 34 message shall be set to “15”.

3.5.14.3.4.3 When using a Type 34 message, SBAS shall transmit a DFRECI of “3” (“Do Not Use for SBAS”) instead of transmitting a DFRECI of “2” (“DFREI increased by one”) when the most recent active DFREI was set to “14” and 349CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 the corresponding DFRE value is no longer adequate to ensure integrity as per 3.5.14.3.1.

3.5.14.3.4.4 SBAS shall send (IVALID)32 and (IVALID)39/40 in the Type 37 messages corresponding to the time intervals during which the integrity data of Type 32 and Type 39/40 messages can be used.

Note.: These time intervals are measured from the time of arrival of the last bit of Type 32 or the last bit of the last message in the paired Type 39/40 messages being received at the antenna port of the SBAS receiver.

3.5.14.3.4.5 The integrity requirement in 3.5.14.3.1 shall apply throughout the update of parameters in a Type 37 message.

Note.: It is expected that change in the DFREI scale table will be a rare event in the lifetime of an SBAS.

3.5.14.3.4.5.1 For each DFREI, the σ value shall always be greater than the σ DFRE DFRE value specified for lower DFREI in the scale table in the Type 37 message.

3.5.14.3.5 Old but active data (OBAD). SBAS shall broadcast OBAD parameters (Type 37 message) such that the integrity requirement in 3.5.14.3.1 is met.

3.5.14.3.6 Timing data

3.5.14.3.6.1 SBAS shall indicate on which reference time the SNT for DFMC SBAS is aligned through the time reference identifier field of the Type 37 message.

3.5.14.3.6.2 If an SBAS provides the WNROcount information with a parameter not permanently set to “15”, the SBAS shall monitor the week number rollover by updating the week number rollover count (WNROcount) in the Type 47 message for the GNSS constellation identified by the time reference identifier in the Type 37 message.

Note.: The week number rollover count is used to solve the possible ambiguity of the week number value transmitted through the GNSS navigation data.

Information on the reference time per constellation to compute the WNROcount can be found in 3.5.11.7.

3.5.14.3.6.3 If a Type 42 message is broadcast, SBAS shall provide information to derive the SNT-to-UTC offset in line with the information set in the VP parameter.

Note.: The UTC offset status parameter can be used by the SBAS to time-out previously broadcast information.

3.5.14.3.6.4 If a Type 42 message is broadcast and if a SNT-to-UTC offset cannot be broadcast by SBAS, SBAS shall broadcast all parameters in common parameter field with all bits coded to zero except the UTC standard identifier set to “7”.

350CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.14.4 Monitoring

3.5.14.4.1 SBAS radio frequency monitoring. The SBAS shall monitor the SBAS satellite parameters shown in Table B-121 and take the indicated action.

Note.: In addition to the radio frequency monitoring requirements in this section, it will be necessary to make special provisions to monitor the pseudo-range acceleration specified in Chapter 3, 3.7.3.4.3.5, carrier phase noise specified in 3.5.9.2, and correlation loss in 3.5.9.5, unless analysis and testing shows that these parameters cannot exceed the stated limits.

3.5.14.4.2 Data monitoring. The SBAS shall monitor GNSS ranging signals to ensure that active data meets the requirements of 3.5.14.3.1.

3.5.14.4.2.1 The ground subsystem shall lock on main correlation peaks of the tracked signals used for the SBAS augmentation.

3.5.14.4.2.2 The ground subsystem shall ensure that broadcast data bound the residual error for airborne receivers according to DFMC SBAS receiver design constraints defined in 3.5.15.1.1.3 when exposed to GNSS signal distortions defined in Attachment D, 8.

Note.: SBAS receiver locks on the main correlation peak of the tracked signal following the requirement in 3.5.15.1.5.

3.5.14.4.2.3 The monitor action shall be to set DFRE to a larger value or to “Do Not Use for SBAS” for the satellite.

3.5.14.4.2.4 SBAS shall monitor all active data that can be used by any user within the coverage area.

3.5.14.4.2.5 SBAS shall raise an alert within 5.2 seconds if any combination of active data and GNSS signals-in-space results in a horizontal or vertical position error exceeding respectively the HPL or VPL (as per 3.5.14.3.1).

Note.: The monitoring applies to all failure conditions, including failures in core satellite constellation(s) or SBAS satellites. This monitoring assumes that the aircraft element complies with the requirements of 3.5.15.

3.5.14.4.3 IOD monitoring. SBAS shall take appropriate action to ensure integrity of the broadcast information when the active IODN as described in 3.5.11.2 can be linked to more than one valid ephemeris.

Note 1.: Active data is defined as data that has not timed out as per Table B-119.

This requirement includes core satellite constellation(s) and SBAS failures.

Note 2.: Additional information on the application of SBAS corrections by an SBAS receiver is provided in 3.5.15.1.4.8 and can be used to assess the time during which a mismatch of IODN and core constellation can be 351CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 considered by SBAS.

3.5.14.5 Robustness to core constellation(s) failures. SBAS shall continue to provide SBAS services after removal of one or several satellites, including a complete core constellation.

Note.: SBAS systems are expected to maintain operation in the presence of failures or anomalies on one or several satellites or failure of a complete core constellation. The level of supported service degrades as more satellites are removed. Removal of a failed or unhealthy satellite does not impact the ability to monitor and correct other satellites.

3.5.15 DFMC SBAS AIRCRAFT ELEMENTS Note 1.: The parameters that are referred to in this section are defined in 3.5.11.

Note 2.: Whereas all SBAS receivers process signals from SBAS GEO satellites, processing non-GEO SBAS signals is optional.

3.5.15.1 DFMC SBAS-capable GNSS receiver.

3.5.15.1.1 DFMC SBAS-capable GNSS receiver. Except as specifically noted, the DFMC SBAS-capable GNSS receiver shall process the signals of the SBAS and meet the requirements applicable to the core constellations it tracks as specified in 3.1.1.3.1 (GPS receiver), and/or 3.1.2.3.1 (GLONASS receiver), and/or 3.1.3.3.1 (Galileo receivers), and/or 3.1.4.3.1 (BDS receivers). Pseudo-range measurements for each satellite shall be smoothed using carrier measurements and the filter identified in 3.5.1.1 with the following pseudo-range observables:

P is the L1 C/A or L1OCd or E1-C or B1C_pilot or SBAS L1 raw pseudo- 1,k range measurement in metres; P2,k is the L5-Q or L3OCd or E5a-Q or B2a_pilot or SBAS L5 raw pseudo-range measurement in metres; φ is the accumulated L1 C/A or L1OCd or E1-C or B1C_pilot or SBAS 1,k L1 raw carrier phase measurement in metres;

φ is the accumulated L5-Q or L3OCd or E5a-Q or B2a_pilot or SBAS L5 2,k raw carrier phase measurement in metres; is the square frequency ratio, where f1 is L1 C/A or L1OCd or E1-C or B1C_pilot or SBAS L1 and f2 is L5-Q or L3OCd or E5a-Q or B2a_pilot or SBAS L5; and α is the filter weighting function defined as follows: after 100 seconds have elapsed since filter initialization, α shall be equal to the sample interval in 352CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 seconds divided by the time constant of 100 seconds. In the first 100 seconds since filter initialization, α shall be equal to the sample interval in seconds divided by the time in seconds since filter initialization.

3.5.15.1.1.1 The receiver shall process the augmented signals as follows: a) for GPS: the receiver shall use a BPSK (1) replica for L1 C/A signal and a BPSK(10) replica for L5-Q signal. The satellite position and satellite clock shall be based on ephemeris in LNAV message on L1.

Group delay correction from LNAV message on L1 shall be applied; b) for GLONASS: the receiver shall use a BPSK (1) replica for L1OCd and a BPSK(10) replica for L3OCd signal. The satellite position and satellite clock shall be based on ephemeris in strings 10, 11 and 12 of L1OCd or L3OCd;

c) for Galileo: the receiver shall use a BOC (1,1) replica for E1-C signal and a BPSK (10) replica for E5a-Q signal. The satellite position and satellite clock shall be based on ephemeris in F/NAV message on E5a; and d) for BDS: the receiver shall use a BOC (1,1) replica for B1C_pilot signal and a BPSK (10) replica for B2a_pilot signal. The satellite position and satellite clock shall be based on ephemeris in B CNAV2 message on B2a.

Note.: The equivalent specific ionosphere-free computation is described in BDS- SIS-ICD-B2a (V1.0), 7.8.3 taking into account the group delays broadcast in B-CNAV2 message.

3.5.15.1.1.2 The satellite time correction (Δ𝑡 ) for satellite i, defined in 3.5.12.4, 𝑆𝑉,𝑖

shall be computed using the following information: a) for GPS: the satellite clock correction Δt shall be (Δt ) , 𝑆𝑉,𝑖 𝑆𝑉 L1 computed as described in 3.1.1.2.1.2 taking into account the group delay correction broadcast in the LNAV message;

b) for GLONASS: the satellite clock correction Δt shall be computed 𝑆𝑉,𝑖 as described in 3.1.2.2.2; c) for Galileo: the satellite clock correction Δt shall be computed as 𝑆𝑉,𝑖 described in 3.1.3.2.2;

d) for BDS: the satellite clock correction Δt shall be computed as 𝑆𝑉,𝑖 described in 3.1.4.2.2.1; and e) for SBAS ranging satellite: the satellite clock correction Δt shall be 𝑆𝑉,𝑖 computed as Δ𝑡 = 𝛼 + 𝛼 Δ𝑡 with a and a broadcast in the 𝑆𝑉,𝑖 𝐺𝑓0 𝐺𝑓1 Gf0 Gf1 Type 39 message and 𝛥𝑡 defined in 3.5.12.3.1.

353CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.15.1.1.3 DFMC SBAS aircraft element design constraints.

3.5.15.1.1.3.1 For processing of L1, L5, E1, E5a, B1C and B2a signals, the aircraft

element shall comply with the following constraints: a) 3 dB bandwidth between 12 and 24 MHz centred around 1 575.42 MHz and around 1 176.45 MHz; b) differential group delay not greater than 150 ns; c) early minus late discriminator;

d) L1/E1/B1C correlator spacing between 0.08 and 0.12 L1 chips; e) L5/E5a/B2a correlator spacing between 0.9 chips and 1.1 L5 chips; f) frequency roll-off of at least 24 dB per octave until reaching a minimum attenuation to meet the performance objectives in the presence of interfering signals at the interference thresholds specified in 3.7;

g) maintain the minimum attenuation to meet the performance objectives in the presence of interfering signals at the interference thresholds specified in 3.7; and h) filter centre frequencies around 1 575.42 MHz and 1 176.45 MHz within ±10% of the 3 dB bandwidth specified in a).

Note 1.: This requirement constrains the entire aircraft implementation of the DFMC SBAS capability and not only the DFMC SBAS receiver.

Note 2.: The 0 dB level corresponds to the filter’s normalized peak in-band response.

3.5.15.1.1.3.2 For processing of L1OC and L3OC signals, the aircraft element shall

comply with the following constraints: a) 3 dB bandwidth between 12 and 24 MHz centred around 1 600.995 MHz and around 1 202.025 MHz; b) differential group delay not greater than 150 ns; c) early minus late discriminator;

d) L1OC correlator spacing between 0.08 and 0.12 L1 chips; e) L3OC correlator spacing between 0.9 chips and 1.1 L5 chips; f) frequency roll-off of at least 24 dB per octave until reaching a minimum attenuation to meet the performance objectives in the presence of interfering signals at the interference thresholds specified in 3.7;

354CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 g) maintain the minimum attenuation to meet the performance objectives in the presence of interfering signals at the interference thresholds specified in 3.7; and h) filter centre frequencies around 1 600.995 MHz and 1 202.025 MHz within ±10% of the 3 dB bandwidth specified in a).

Note 1.: This requirement constrains the entire aircraft implementation of the DFMC SBAS capability and not only the DFMC SBAS receiver.

Note 2.: The 0 dB level corresponds to the filter’s normalized peak in-band response.

3.5.15.1.2 GEO SBAS satellite acquisition on L5. The receiver shall be able to acquire and track GEO satellites for which a stationary receiver at the user receiver location would experience a Doppler shift as large as ±337 Hz.

3.5.15.1.3 Non-GEO SBAS satellite acquisition on L5. The non-GEO SBAS capable receiver shall be able to acquire and track non-GEO satellites for which a stationary receiver at the user receiver location would experience a Doppler shift as large as ±7 kHz.

Note.: Information on non-GEO Doppler range is available in Attachment D,

6.7.5.

3.5.15.1.4 Conditions of use of data on L5.

3.5.15.1.4.1 The receiver shall use data from an SBAS message only if the CRC of this message has been verified.

3.5.15.1.4.2 The receiver shall use the information transmitted in DFMC messages only within the time-out period, defined in Table B-119, starting from the reception of the last bit of the message.

3.5.15.1.4.3 Upon reception of a Type 0 message, the receiver shall cease using all data received from this signal that have defined time-out intervals in Table B-119, except for the SBAS service provider identifier which can be used only for the SBAS acquisition process.

3.5.15.1.4.4 The receiver shall only apply integrity data for which Type 34, 35 or 36 messages IODM matches an active Type 31 message IODM.

3.5.15.1.4.5 The reception of new DFREI shall replace the old DFREI.

3.5.15.1.4.6 DFRECI requirements.

3.5.15.1.4.6.1 The receiver shall treat the reception of a DFRECI = 0 or a DFRECI = 2 as though it had received a new copy of the most recent, active DFREI previously received through Type 32, 34, 35, 36 or 40 messages.

355CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.15.1.4.6.2 Upon reception of a DFRECI = 2, the equipment shall use the most recent, active DFREI received through Types 32, 34, 35, 36 or 40 messages and use the σ corresponding to the active DFREI increased DFRE by one.

Note.: The effect of the reception of a DFRECI = 2 (“value increase of 1”) is not cumulative.

3.5.15.1.4.6.3 Upon reception of a DFRECI = 3, the receiver shall set the DFREI to “15” (“Do Not Use for SBAS”) and exclude the satellite from the SBAS position solution.

3.5.15.1.4.6.4 Upon reception of a DFRECI = 1, the receiver shall update the DFREI value by decoding the corresponding DFREI slot in the order of a Type 34 message DFRECI set to “1” across the DFRECI field.

3.5.15.1.4.7 The receiver shall use the DFREI table through the latest decoded Type 37 message for the computation of σ based on received DFREI.

DFRE

3.5.15.1.4.8 Upon reception of the initial valid Type 32 message applicable to a given non-SBAS satellite, the receiver shall invalidate for this satellite any retained clock/ephemeris data set containing at least one parameter received for the last time more than 5 minutes before the reception of the initial valid Type 32 message.

Note.: The “initial valid Type 32 message” is the first Type 32 message received when there is no active Type 32 message from the SBAS L5 signal in use.

3.5.15.1.4.9 The receiver shall apply the ephemeris and clock parameters, the covariance matrix parameters, the OBAD parameters and the integrity parameters as described in 3.5.12.4 and 3.5.12.5.

3.5.15.1.4.10 The receiver shall use the content of Types 39 and 40 messages, only when Types 39 and 40 messages with the same IODG have been received and have not timed out.

3.5.15.1.4.11 The receiver shall correctly account for the day and week rollover change when observed after the last received Type 47 message.

3.5.15.1.4.12 The receiver shall only use SBAS augmented satellite ranges from satellites with elevation angles at or above 5 degrees in the DFMC SBAS position computation.

3.5.15.1.4.13 The receiver shall only use correction, integrity and other data obtained from a single SBAS satellite L5 signal, designated by its PRN code, for all satellites used in the position solution.

Note.: When using additional SBAS satellites for ranging, the receiver uses the clock and ephemeris parameters in the Type 39/40 message from the ranging SBAS satellite(s), and the covariance and integrity parameters (e.g. DFREI, delta_RCORR) in the Type 32 message from the SBAS 356CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 satellite being used for corrections.

3.5.15.1.4.14 Prior to use, the receiver shall verify that the tracked SBAS PRN code matches the PRN code derived from the satellite slot delta field within the almanac data upon reception of the Type 47 message with the broadcast indicator set to “1” or derived from the satellite slot delta field in an active Type 39 message.

3.5.15.1.4.15 In the event of a loss of four successive SBAS messages, the receiver shall invalidate all DFREIs and DFRECIs previously received from this SBAS PRN.

3.5.15.1.4.16 The receiver shall check that the tD parameter in Type 32 message, as well as te and aGf0 parameters in Type 39/40 message, are within the effective range indicated in the message tables under 3.5.13. If the effective range check fails, the message shall be discarded.

Note.: Message bits or fields marked as “Reserved” or “Spare” may take any value during the operational lifetime of the SBAS service.

3.5.15.1.5 The SBAS receiver shall lock on main correlation peak of each of the tracked signals augmented by the SBAS and used in the SBAS position solution.

3.5.15.2 SBAS satellite position

3.5.15.2.1 Position computation with ephemeris. When using SBAS ranging, the receiver shall decode Type 39/40 messages and determine the position (XG, YG, ZG) of the SBAS satellite using the protocol described in

3.5.12.3.

3.5.15.2.2 Position computation with almanac. When computing the SBAS satellite position using a Type 47 message, the receiver shall determine the position (XG, YG, ZG) of the SBAS satellite using the protocol described in 3.5.12.2.

3.5.15.3 Ionosphere-free differential functions

3.5.15.3.1 GNSS satellite status function. The receiver shall exclude satellites from the SBAS position solution if they are identified as “Do Not Use for SBAS”.

Note 1.: In the case of a satellite designated marginal or unhealthy by the core satellite constellation(s) health flags, SBAS may broadcast ephemeris and clock corrections that will allow the user to continue using the satellite as long as performance requirements in 3.5.14.3.1 are met.

Note 2.: If satellites identified as “Do Not Use for SBAS” by SBAS are used in the position solution, integrity is not provided by SBAS.

3.5.15.3.2 Core satellite constellation(s) ranging accuracy for precision approach.

The RMS (1 sigma) of the total airborne contribution in steady state to the 357CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 error in a corrected ionosphere-free pseudo-range shall be less than or equal to the value in Table B-122 at minimum and maximum power levels.

3.5.15.3.3 The receiver shall use the protocol described in 3.5.12.4 for the SBAS position solution and for the constellation time difference if more than one constellation is augmented by the SBAS.

3.5.15.3.4 The receiver shall compute the SBAS horizontal and vertical protection levels as defined in 3.5.12.5.

3.5.15.3.4.1 The airborne receiver error variance 𝜎2 for satellite i shall be 𝑎𝑖𝑟,𝐷𝐹

computed as follows: where 𝜎2 2 [𝑖] is defined in 3.5.15.3.2; 𝑛𝑜𝑖𝑠𝑒 𝜎2 , the multipath and antenna group delay variation error model 𝑀𝑃&𝐴𝐺𝐷𝑉,𝐷𝐹 for ionosphere-free dual-frequency 100-second smoothed measurements, described by a normal distribution with zero mean and a

standard deviation of: for GPS, Galileo, GLONASS and BDS: 𝜎 [𝑖] = 0.34 + 0.4 𝑀𝑃&𝐴𝐺𝐷𝑉,𝐷𝐹 𝑒𝑥𝑝(−𝐸𝑙 [𝑖]/14°) (in metres); and 𝑑𝑒𝑔 where 𝐸𝑙 [𝑖] is the elevation angle of satellite i (in degrees).

𝑑𝑒𝑔 Note.: The models are valid when the receiver is in a steady state.

3.5.15.3.4.2 For ionosphere-free dual-frequency measurements, the residual

ionospheric uncertainty shall be defined as: where 𝐸𝑙 [𝑖] is the elevation angle (in degrees) of satellite i. 𝑑𝑒𝑔

3.5.15.3.5 The parameters in the SBAS FAS data block applicable to DFMC SBAS 358CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 receivers shall be as described in 3.5.8.4.2.6 with the exception of the operation type and the approach performance designator as described

below:

Operation type: straight-in approach procedure or other operation types applicable to DFMC SBAS receivers.

Coding: 0 = straight-in approach procedure with SPID from 0 to 13 1 to 7 = spare 8 = straight-in approach procedure with SPID from 16 to 31 9 to 15 = spare Approach performance designator (APD): shall indicate the SBAS service supporting the requirements in accordance withTable 3.7.2.4-1 for the approach defined by the FAS data block, including the completion of a system-specific safety analysis for Category 1 if the vertical alert limit

(VAL) in the FAS data block is greater than 10 m.

Coding: 0 = DFMC SBAS or L1 SBAS service 1 = DFMC SBAS service augmenting one or more constellations (L1 SBAS not supported) 2 = DFMC SBAS service augmenting at least two constellations (L1 SBAS not supported) 3 to 4 = Spare 5 = DFMC SBAS service augmenting one or more constellations (L1 SBAS with reduced continuity/availability) 6 = DFMC SBAS service augmenting at least two constellations (L1 SBAS with reduced continuity/availability) 7 = Spare Note 1.: The different APD coding values are intended to communicate potential performance differences available from the SBAS services at the approach location based on the number of GNSS frequencies and the number of augmented constellations used. Only DFMC SBAS airborne receivers use the APD to select the appropriate airborne receiver mode to support the operation. Further information can be found in Attachment D, 6.6.5.

Note 2.: “L1 SBAS not supported” means that, for a Category I approach, the L1 SBAS service in the approach region does not meet the system-specific safety assessment for the published VAL. See also the guidance in Attachment D, 3.3.9 and 6.6.5.

359CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note 3.: “L1 SBAS service with reduced continuity/availability” means that the L1 SBAS service in the approach region does not meet the availability or continuity requirements for the approach. Additional aircraft element integration may be used to satisfy availability and continuity requirements for the approach. The determination of the SBAS-based position domain NSE availability and continuity, using additional aircraft element system integration, and the assessment of the suitability of that availability and continuity for the approach, is the responsibility of the aircraft element. For a Category 1 approach, the L1 SBAS service does meet the system- specific safety assessment for the published VAL, following the guidance in Attachment D, 3.3.9 and 6.6.5.

3.5.15.3.5.1 For operations defined by a FAS data block, the receiver shall determine the operational SBAS service provider identifier (SPID) applicable to the

operation as follows: if the operation type is 0, the operational SPID shall be the value of the FAS data block SPID; if the operation type is 8, the operational SPID shall the sum of 16 and the value of the FAS data block SPID.

3.5.15.3.5.2 For operations defined by a FAS data block and the operational SPID is not 15, the receiver shall select SBAS signals with an active SPID decoded from a received Type 47 message that matches the operational SPID determined from the FAS data block (see 3.5.15.3.5.1).

3.5.15.3.5.3 For operations defined by a FAS data block, the receiver shall use the APD to determine the acceptable combination of SBAS navigation service (i.e. DFMC SBAS and/or L1 SBAS) and the number of constellations required to support the intended operation (see Attachment D, 6.6.5).

3.5.15.3.5.4 For operations defined by a FAS data block with an operational SPID of 15 and an APD of two or six, the receiver shall select SBAS satellites that augment two or more constellations that can be used by the receiver.

Note.:If the operational SPID is 15 and the APD is not two or six, the receiver can select any operational SBAS (not broadcasting MT0).

3.5.15.4 Ranging function

3.5.15.4.1 DFMC SBAS satellite ranging accuracy. The root-mean-square (1 sigma) of the total airborne contribution in steady state to the error in a corrected ionosphere-free pseudo-range for a dual-frequency SBAS ranging satellite under the worst interference environment as defined in 3.7, excluding multipath effects, tropospheric and ionospheric residual errors, shall be less than or equal to 0.8 metres at the minimum received signal power level or equal to 0.6 metres at the maximum received signal power level (Chapter 3, 3.7.3.4.6.3).

3.5.15.5 Timing function 360CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.5.15.5.1 If a UTC time is derived from an SBAS receiver through a Type 42 message, the receiver shall time-out previously received SNT-to-UTC information if the receiver decodes a UTC offset status set to 1.

3.5.15.5.2 If a UTC time is derived from an SBAS receiver through a Type 42 message, the receiver shall not apply the content of the received Type 42 message if the UTC standard identifier is set to 7.

Note.: The receiver may still use previously received information if not timed-out and if the UTC offset status is set to 0 in the received Type 42 message.

3.5.16 INTERFACE BETWEEN SBAS Note.: Guidance material on the interface between different SBAS service providers is given in Attachment D, 6.3.

3.6 Ground-based augmentation system (GBAS) and ground-based regional augmentation system (GRAS)

3.6.1 GENERAL The GBAS shall consist of a ground subsystem and an aircraft subsystem.

The GBAS ground subsystem shall provide data and corrections for the GNSS ranging signals over a digital VHF data broadcast to the aircraft subsystem. The GRAS ground subsystem shall consist of one or more GBAS ground subsystems.

Note 1.: Guidance material is provided in Attachment D, 7.1.

Note 2.: GBAS SARPs have not yet been updated to support dual-frequency multi- constellation (DFMC) use. These SARPs are applicable to GPS L1 C/A and GLONASS L1OF only. Throughout the GBAS SARPs (Appendix B,

3.6) and in the GBAS sections of Attachment D, the term GLONASS should be understood to refer to GLONASS L1OF signals and services only, and the term GPS should be understood to refer to GPS L1 C/A signals and services only.

3.6.1.1 GBAS service types. A GBAS ground subsystem shall support either the positioning service, approach service or both types of service.

Note 1.: Service types refers to a matched set of ground and airborne functional and performance requirements that ensure that quantifiable navigation performance is achieved by the airborne equipment. Guidance material concerning service types is given in Attachment D, 7.1.

Note 2.: GBAS ground facilities are characterized by a GBAS facility classification

(GFC). Many GBAS performance and functional requirements depend on the GFC. These SARPs are organized according to which requirements apply for a given facility classification element (i.e. the facility approach service type (FAST) letter, the facility polarization, etc.). Guidance material 361CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 concerning facility classifications is given in Attachment D, 7.1.4.1.

3.6.1.2 All GBAS ground subsystems shall comply with the requirements of 3.6.1,

3.6.2, 3.6.3, 3.6.4, 3.6.6 and 3.6.7, unless otherwise stated. A FAST D ground subsystem shall comply with all FAST C requirements in addition to the specific FAST D requirements.

3.6.2 RF CHARACTERISTICS

3.6.2.1 Carrier frequency stability. The carrier frequency of the data broadcast shall be maintained within ±0.0002 per cent of the assigned frequency.

3.6.2.2 Bit-to-phase-change encoding. GBAS messages shall be assembled into symbols, each consisting of 3 consecutive message bits. The end of the message shall be padded by 1 or 2 fill bits if necessary to form the last 3- bit symbol of the message. Symbols shall be converted to D8PSK carrier phase shifts (ΔΦ𝑘) in accordance with Table B-123.

Note.: The carrier phase for the kth symbol (ɸk) is given by: ɸk = ɸk-1 + Δɸk. The D8PSK signal may be produced as shown in Figure B-29 by combining two quadrature RF signals which are independently suppressed-carrier amplitude-modulated by base band filtered impulses. A positive increase in Δ𝛷𝑘 represents a counterclockwise rotation in the complex I-Q plane of Figure B-29.

3.6.2.3 Modulation wave form and pulse shaping filters. The output of differential phase encoder shall be filtered by a pulse shaping filter whose output, s(t),

is described as follows: where h = the impulse response of the raised cosine filter; ɸ = (as defined in 3.6.2.2); k t = time; and T = the duration of each symbol = 1/10 500 second.

This pulse shaping filter shall have a nominal complex frequency response of a raised-cosine filter with α = 0.6. The time response, h(t), and frequency response, H(f), of the base band filters shall be as

follows:

362CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 The output s(t) of the pulse shaping filter shall modulate the carrier.

3.6.2.4 Error vector magnitude. The error vector magnitude of the transmitted signal shall be less than 6.5 per cent root-mean- square (1 sigma).

3.6.2.5 RF data rate. The symbol rate shall be 10 500 symbols per second ±0.005 per cent, resulting in a nominal bit rate of 31 500 bits per second.

3.6.2.6 Emissions in unassigned time slots. Under all operating conditions, the maximum power over a 25 kHz channel bandwidth, centred on the assigned frequency, when measured over any unassigned time slot, shall not exceed –105 dBc referenced to the authorized transmitter power.

Note.:— The –105 dBc may not protect reception of emissions in a slot assigned to 363CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 another desired transmitter for receivers within 80 metres from the undesired transmitting antenna.

3.6.3 DATA STRUCTURE

3.6.3.1 TRANSMITTER TIMING

3.6.3.1.1 Data broadcast timing structure. The time division multiple access

(TDMA) timing structure shall be based on frames and time slots. Each frame shall be 500 milliseconds in duration. There shall be 2 such frames contained in each 1 second UTC epoch. The first of these frames shall start at the beginning of the UTC epoch and the second frame shall start

0.5 seconds after the beginning of the UTC epoch. The frame shall be time division multiplexed such that it shall consist of 8 individual time slots (A to H) of 62.5-millisecond duration.

3.6.3.1.2 Bursts. Each assigned time slot shall contain at most 1 burst. To initiate the use of a time slot, the GBAS shall broadcast a burst in that time slot in each of 5 consecutive frames. For each time slot in use, the ground subsystem shall broadcast a burst in at least 1 frame of every 5 consecutive frames.

Note 1.— Bursts contain one or more messages and may be of variable length up to the maximum allowed within the slot as required by 3.6.3.2.

Note 2.— During time slot initiation, the airborne receiver may not receive the first 4 bursts.

3.6.3.1.3 Timing budget for bursts

3.6.3.1.3.1 Each burst shall be contained in a 62.5-millisecond time slot.

3.6.3.1.3.2 The beginning of the burst shall occur 95.2 microseconds after the beginning of the time slot with a tolerance of ±95.2 microseconds.

3.6.3.1.3.3 For GBAS/E equipment, the start of the synchronization and ambiguity resolution portion of the burst, transmitted with horizontal polarization

(HPOL), shall occur within 10 microseconds of the start of the burst transmitted with vertical polarization (VPOL).

Note.:— Table B-124 illustrates the burst timing.

3.6.3.1.4 Ramp-up and transmitter power stabilization. The transmitter shall ramp up to 90 per cent of the steady-state power level within 190.5 microseconds after the beginning of the burst (2 symbols). The transmitter shall stabilize at the steadystate power within 476.2 microseconds after the beginning of the burst (5 symbols).

364CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.:— The transmitter power stabilization period may be used by the aircraft receiver to settle its automatic gain control.

3.6.3.1.5 Ramp-down. After the final information symbol is transmitted in an assigned time slot, the transmitter output power level shall decrease to at least 30 dB below the steady-state power within 285.7 microseconds (3 symbols).

3.6.3.2 Burst organization and coding. Each burst shall consist of the data elements shown in Table B-125. Encoding of the messages shall follow

the sequence: application data formatting, training sequence forward error correction (FEC) generation, application FEC generation and bit scrambling.

3.6.3.2.1 Synchronization and ambiguity resolution. The synchronization and ambiguity resolution field shall consist of the 48-bit sequence shown below, with the rightmost bit transmitted first:

010 001 111 101 111 110 001 100 011 101 100 000 011 110 010 000 365CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.6.3.3 SCRAMBLED DATA CONTENT

3.6.3.3.1 Station slot identifier (SSID). The SSID shall be a numeric value corresponding to the letter designation A to H of the first time slot assigned to the GBAS ground subsystem, where slot A is represented by 0, B by 1, C by 2, … and H by 7. The identifier is transmitted LSB first.

3.6.3.3.2 Transmission length. The transmission length shall indicate the total number of bits in both application data and application FEC. The transmission length is transmitted LSB first.

3.6.3.3.3 Training sequence FEC. The training sequence FEC shall be computed over the SSID and transmission length fields, using a (25, 20) block code,

in accordance with the following equation: [P1, ..., P5] = [SSID1, …, SSID3, TL1, …, TL17] HT where Pn = the nth bit of the training sequence FEC (P1 shall be transmitted first);

SSIDn = the nth bit of the station slot identifier (SSID1 = LSB);

TLn = the nth bit in the transmission length (TL1 = LSB); and HT = the transpose of the parity matrix, defined below:

366CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.:— This code is capable of correcting all single bit errors and detecting 75 of 300 possible double bit errors.

3.6.3.3.4 Application data. The application data shall consist of one or more message blocks, as defined in 3.6.3.4. The message blocks shall be mapped directly into the application data with no additional overhead of intervening layers.

3.6.3.3.5 Application FEC. The application FEC shall be calculated using the application data by means of a systematic, fixed-length, Reed-Solomon (R-S) (255, 249) code.

3.6.3.3.5.1 The field-defining primitive, p(x), of the R-S code shall be: p(x) = x8 + x7 + x2 + x + 1

3.6.3.3.5.2 The generator polynomial of the R-S code, g(x), shall be: where α is a root of p(x) used for construction of the Galois Field of size 28, GF(256), and 𝛼𝑖 is the ith primitive element in GF(256).

3.6.3.3.5.3 In generating the application FEC, the data to be encoded, m(x), shall be grouped into 8-bit R-S symbols. All data fields in the message blocks that define the application data shall be ordered such as specified in Tables B-59 and B-60, and in the message tables in 3.6.6. However, since the R-S code is a block code, application data blocks shorter than 249 bytes (1 992 bits) shall be extended to 249 bytes by virtual fill bits set to zero and appended to the application data. These virtual fill bits shall not be transferred to the bit scrambler. The data to be encoded, m(x), shall be

defined by: m(x) = a248x248 + a247x247 + .... + a248-length+1 x248-length+1 + a248-length x248-length + .... + a1x+a0 where 367CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 length represents the number of 8-bit bytes in the application data block;

a248 represents the message block identifier, with the rightmost bit defined as the LSB and the first bit of the application data sent to the bit scrambler; a248-length+1 represents the last byte of the message block CRC, with the leftmost bit defined as the MSB and the last bit of the application data sent to the bit scrambler; and a248-length, ..., a1, a0 are the virtual fill bits (if any).

3.6.3.3.5.4 The 6 R-S check symbols (bi) shall be defined as the coefficients of the remainder resulting from dividing the message polynomial x6m(x) by the generator polynomial g(x):

3.6.3.3.5.5 The 8-bit R-S check symbols shall be appended to the application data.

Each 8-bit R-S check symbol shall be transmitted MSB first from b0 to b5, i.e. the first application FEC bit transferred to the bit scrambler shall be the MSB of b0 and the last application FEC bit transferred to the bit scrambler shall be the LSB of b5.

Note 1.— This R-S code is capable of correcting up to 3 symbol errors.

Note 2.— The order of the transmitted 8-bit R-S check symbols of the appended application FEC differs from the VHF data link (VDL) Mode 2. Moreover, for VDL Mode 2 each R-S check symbol is transmitted LSB first.

Note 3. — Example results of application FEC encoding are given in Attachment D,

7.15.

368CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.6.3.3.6 Bit scrambling

3.6.3.3.6.1 The output of a pseudo-noise scrambler with a 15-stage generator register shall be exclusive OR’ed with the burst data starting with the SSID and ending with the application FEC. Bit scrambling of the fill bits is optional and the set value of the fill bits is optional.

Note.:— The fill bits are not used by the aircraft receiver and their values have no impact on the system.

3.6.3.3.6.2 The polynomial for the register taps of the scrambler shall be 1 + x + x15.

The register content shall be rotated at the rate of one shift per bit. The initial status of the register, prior to the first SSID bit of each burst, shall be “1101 0010 1011 001”, with the leftmost bit in the first stage of the register. The first output bit of the scrambler shall be sampled prior to the first register shift.

Note.:— A diagram of the bit scrambler is given in Attachment D, 7.4.

3.6.3.4 Message block format. The message blocks shall consist of a message block header, a message and a 32-bit CRC. Table B-126 shows the construction of the message block. All signed parameters shall be two’s complement numbers and all unsigned parameters shall be unsigned fixed point numbers. The scaling of the data shall be as shown in the message tables in 3.6.6. All data fields in the message block shall be transmitted in the order specified in the message tables, with the LSB of each field transmitted first.

Note.:All binary representations reading left to right are MSB to LSB.

3.6.3.4.1 Message block header. The message block header shall consist of a message block identifier, a GBAS identifier (ID), a message type identifier and a message length, as shown in Table B-127.

Message block identifier: the 8-bit identifier for the operating mode of the GBAS message block.

369CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 All other values are reserved.

GBAS ID: the four-character GBAS identification to differentiate between GBAS ground subsystems.

Coding: Each character is coded using bits b1 through b6 of its International Alphabet No. 5 (IA-5) representation. For each character, bit b1 is transmitted first and six bits are transmitted for each character.

Only upper case letters, numeric digits and IA-5 “space” are used. The rightmost character is transmitted first. For a three-character GBAS ID, the rightmost (first transmitted) character shall be IA-5 “space”.

Note.:The GBAS ID is normally identical to the location indicator at the nearest airport. Assignment of GBAS IDs will be coordinated as appropriate to avoid conflicts.

Message type identifier: the numeric label identifying the content of the message (Table B-128).

Message length: the length of the message in 8-bit bytes including the 6- byte message block header, the message and the 4 byte message CRC code.

3.6.3.4.2 Cyclic redundancy check (CRC). The GBAS message CRC shall be calculated in accordance with 3.9.

3.6.3.4.2.1 The length of the CRC code shall be k = 32 bits.

3.6.3.4.2.2 The CRC generator polynomial shall be:

G(x) = x32 + x31 + x24 + x22 + x16 + x14 + x8 + x7 + x5 + x3 + x + 1

3.6.3.4.2.3 The CRC information field, M(x), shall be:

3.6.3.4.2.4 M(x) shall be formed from the 48-bit GBAS message block header and all bits of the variable-length message, excluding the CRC. Bits shall be arranged in the order transmitted, such that m1 corresponds to the first transmitted bit of the message block header, and mn corresponds to the last transmitted bit of the (n-48) message bits.

370CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.6.3.4.2.5 The CRC shall be ordered such that r1 is the first bit transmitted and r32 is the last bit transmitted.

3.6.4 DATA CONTENT

3.6.4.1 Message types. The message types that can be transmitted by GBAS shall be as in Table B-128.

3.6.4.2 TYPE 1 MESSAGE — PSEUDO-RANGE CORRECTIONS

3.6.4.2.1 The Type 1 message shall provide the differential correction data for individual GNSS ranging sources (Table B-138). The message shall

contain three sections: a) message information (time of validity, additional message flag, number of measurements and the measurement type); b) low-frequency information (ephemeris decorrelation parameter, satellite ephemeris CRC and satellite availability information); and c) satellite data measurement blocks.

Note 1. — Transmission of the low-frequency data for SBAS ranging sources is optional.

Note 2.— All parameters in this message type apply to 100-second carrier-smoothed pseudo-ranges.

3.6.4.2.2 Each Type 1 message shall include ephemeris decorrelation parameter, ephemeris CRC and source availability duration parameters for one satellite ranging source. The ephemeris decorrelation parameter, ephemeris CRC and source availability duration shall apply to the first ranging source in the message.

3.6.4.2.3 Pseudo-range correction parameters shall be as follows:

Modified Z-count: the indication of the time of applicability for all the parameters in the message.

Coding: the modified Z-count resets on the hour (xx:00), 20 minutes past the hour (xx:20) and 40 minutes past the hour (xx:40) referenced to GPS time.

Additional message flag: an identification of whether the set of measurement blocks in a single frame for a particular measurement type is contained in a single Type 1 message or a linked pair of messages.

Coding: 0 = All measurement blocks for a particular measurement type are contained in one Type 1 message.

371CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 1 = This is the first transmitted message of a linked pair of Type 1 messages that together contain the set of all measurement blocks for a particular measurement type.

2 = Spare 3 = This is the second transmitted message of a linked pair of Type 1 messages that together contain the set of all measurement blocks for a particular measurement type.

Note.: When a linked pair of Type 1 messages is used for a particular measurement type, the number of measurements and low-frequency data are computed separately for each of the two individual messages.

Number of measurements: the number of measurement blocks in the message.

Measurement type: the type of ranging signal from which the corrections have been computed.

372CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

Coding: 0 = C/A or CSA code L1 1 = reserved 2 = reserved 3 = reserved 4 to 7 = spare Ephemeris decorrelation parameter (P): a parameter that characterizes the impact of residual ephemeris errors due to decorrelation for the first measurement block in the message.

For a SBAS geostationary satellite, the ephemeris decorrelation parameter, if transmitted, shall be coded as all zeros. For GBAS ground subsystems that do not broadcast the additional data block 1 in the Type 2 message, the ephemeris decorrelation parameter shall be coded as all zeros.

Ephemeris CRC: the CRC computed with the ephemeris data used to determine corrections for the first measurement block in the message.

The ephemeris CRC for core satellite constellation(s) ranging sources shall be calculated in accordance with 3.9. The length of the CRC code shall be k = 16 bits. The CRC generator polynomial shall be:

G(x) = x16 + x12 + x5 + 1 The CRC information field, M(x), for a given satellite shall be:

For a GPS satellite, M(x) shall be of length n = 576 bits. M(x) for a GPS satellite shall be calculated using the first 24 bits from each of words 3 to S10 of subframes 1, 2 and 3 of the data transmission from that satellite, ANDed with the GPS satellite ephemeris mask of Table B-129. M(x) shall be arranged in the order that bytes are transmitted by the GPS satellite, but with each byte ordered LSB first, such that m1 corresponds to bit 68 of subframe 1, and m576 corresponds to bit 287 of subframe 3.

Note.:M(x) for a GPS satellite does not include word 1 (TLM) or word 2 (HOW), which start each subframe, or the 6 parity bits at the end of each word.

373CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 For a GLONASS satellite, M(x) shall be of length n = 340 bits. M(x) for a GLONASS satellite shall be calculated using strings 1, 2, 3 and 4 of the data transmission from that satellite, ANDed with the GLONASS satellite ephemeris mask of Table B-130.Bits shall be arranged in transmission

order such that m1 corresponds to bit 85 of string 1, and m340 corresponds to bit 1 of string 4.

For a SBAS geostationary satellite, the ephemeris CRC, if transmitted shall be coded as all zeros.

The CRC shall be transmitted in the order r9, r10, r11...., r16, r1, r2, r3...r8, where ri is the ith coefficient of the remainder R(x) as defined in

3.9.

Source availability duration: the predicted duration for which corrections for the ranging source are expected to remain available, relative to the modified Z-count for the first measurement block.

Coding: 1111 1110 = The duration is greater than or equal to 2 540 seconds.

1111 1111 = Prediction of source availability duration is not provided by this ground subsystem.

3.6.4.2.4 The measurement block parameters shall be as follows:

Ranging source ID: the identity of the ranging source to which subsequent measurement block data are applicable.

374CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

Coding: for GPS, IOD = GPS IODE parameter (3.1.1.3.2.2) for GLONASS, IOD = GLONASS “tb” parameter (see 3.2.1.3.1) for SBAS, IOD = 1111 1111 Note.:For GLONASS insert 0 in the MSB of the IOD.

Pseudo-range correction (PRC): the correction to the ranging source pseudo-range.

Range rate correction (RRC): the rate of change of the pseudo-range correction. 𝜎pr_gnd: the standard deviation of a normal distribution associated with the signal-in-space contribution of the pseudo-range error at the GBAS reference point (3.6.5.5.1, 3.6.5.5.2 and 3.6.7.2.2.4).

Coding: 1111 1111 = Ranging source correction invalid.

B1 through B4: are the integrity parameters associated with the pseudo- range corrections provided in the same measurement block. For the ith ranging source these parameters correspond to Bi,1 through Bi,4 (3.6.5.5.1.2, 3.6.5.5.2.2 and 3.6.7.2.2.4). During continuous operation, the indices “1-4” correspond to the same physical reference receiver for every epoch transmitted from a given ground subsystem with the

following exception: the physical reference receiver tied to any of the indices 1 to 4 can be replaced by any other physical reference receiver (including a previously removed one) that has not been used for transmissions during the last 5 minutes.

Coding: 1000 0000 = Reference receiver was not used to compute the pseudo-range correction.

375CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note 1.— A physical reference receiver is a receiver with an antenna at a fixed location.

Note 2.- Some airborne inertial integrations may expect a largely static correspondence of the reference receivers to the indices. Refer to RTCA/DO-253D, Appendix L.

3.6.4.3 Type 2 message — GBAS-related data. Type 2 message shall identify the location of the GBAS reference point at which the corrections

provided by the GBAS apply and shall give other GBAS-related data (Table B-69). GBAS-related data parameters shall be as follows:

Note.:— Additional data blocks may be included in the Type 2 message. Additional data block 1 and additional data block 2 are defined. In the future, other additional data blocks may be defined. Data blocks 2 through 255 are variable length and may be appended to the message after additional data block 1 in any order.

GBAS reference receivers: the number of GNSS reference receivers installed in this GBAS ground subsystem.

Coding: 0 = GBAS installed with 2 reference receivers 1 = GBAS installed with 3 reference receivers 2 = GBAS installed with 4 reference receivers 3 = The number of GNSS reference receivers installed in this GBAS ground subsystem is not applicable

Ground accuracy designator letter: the letter designator indicating the minimum signal-in-space accuracy performance provided by GBAS (3.6.7.1.1).

Coding: 0 = accuracy designation A 1 = accuracy designation B 2 = accuracy designation C 3 = spare GBAS continuity/integrity designator (GCID): numeric designator indicating the operational status of the GBAS.

Coding: 0 = spare 1 = GCID 1 2 = GCID 2 376CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 3 = GCID 3 4 = GCID 4 5 = spare 6 = spare 7 = unhealthy Note 1.— The values of GCID 2, 3 and 4 are specified in order to ensure compatibility of equipment with future GBAS.

Note 2.— The value of GCID 7 indicates that all approach services supported by the ground facility are unavailable.

Local magnetic variation: the published magnetic variation at the GBAS reference point.

Coding: Positive value denotes east variation (clockwise from true north), Negative value denotes west variation (counterclockwise from true north) 100 0000 0000 = Precision approach procedures supported by this GBAS are published based on true bearing.

Note.:Local magnetic variation is chosen to be consistent with procedure design and is updated during magnetic epoch years. σvert_iono_gradient: the standard deviation of a normal distribution associated with the residual ionospheric uncertainty due to spatial decorrelation (3.6.5.4).

Refractivity index (Nr): the nominal tropospheric refractivity index used to calibrate the tropospheric correction associated with the GBAS ground subsystem (3.6.5.3).

Coding: This field is coded as two’s complement number with an offset of +400. A value of zero in this field indicates a refractivity index of 400.

Scale height (h0): a scale factor used to calibrate the tropospheric correction and residual tropospheric uncertainty associated with the GBAS ground subsystem (3.6.5.3).

Refractivity uncertainty (σn): the standard deviation of a normal distribution associated with the residual tropospheric uncertainty (3.6.5.3).

Latitude: the latitude of the GBAS reference point defined in arc seconds.

377CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

Coding: Positive value denotes north latitude.

Negative value denotes south latitude.

Longitude: the longitude of the GBAS reference point defined in arc seconds.

Coding: Positive value denotes east longitude.

Negative value denotes west longitude.

Reference point height: the height of the GBAS reference point above the WGS-84 ellipsoid.

3.6.4.3.1 Additional data block 1 parameters. Additional data block 1 parameters

shall be as follows:

REFERENCE STATION DATA SELECTOR (RSDS): the numerical identifier that is used to select the GBAS ground subsystem.

Note.:— The RSDS is different from every other RSDS and every reference path data selector (RPDS) broadcast on the same frequency by every GBAS ground subsystem within the broadcast region.

Coding: 1111 1111 = GBAS positioning service is not provided MAXIMUM USE DISTANCE (Dmax): the maximum distance (slant range) from the GBAS reference point within which pseudorange corrections are applied by the aircraft element.

Note.:— This parameter does not indicate a distance within which VHF data broadcast field strength requirements are met.

Coding: 0 = distance limitation GPS EPHEMERIS MISSED DETECTION PARAMETER, GBAS Positioning Service (Kmd_e_POS,GPS): the multiplier for computation of the ephemeris error position bound for the GBAS positioning service derived from the probability of missed detection given that there is an ephemeris error in a GPS satellite.

For GBAS ground subsystems that do not broadcast corrections for GPS ranging sources or that do not provide the GBAS positioning service, this parameter shall be coded as all zeros.

GPS EPHEMERIS MISSED DETECTION PARAMETER, GBAS approach service types A, B or C (Kmd_e,GPS): the multiplier for computation of the ephemeris error position bound for GBAS approach 378CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 service types A, B and C derived from the probability of missed detection given that there is an ephemeris error in a GPS satellite.

For GBAS ground subsystems that do not broadcast corrections for GPS ranging sources, this parameter shall be coded as all zeros.

GLONASS EPHEMERIS MISSED DETECTION PARAMETER, GBAS Positioning Service (Kmd_e,_POS,GLONASS): the multiplier for computation of the ephemeris error position bound for the GBAS positioning service derived from the probability of missed detection given that there is an ephemeris error in a GLONASS satellite.

For GBAS ground subsystems that do not broadcast corrections for GLONASS ranging sources or that do not provide positioning service, this parameter shall be coded as all zeros.

GLONASS EPHEMERIS MISSED DETECTION PARAMETER, GBAS approach service types A, B or C (Kmd_e_,GLONASS): the multiplier for computation of the ephemeris error position bound for GBAS approach service types A, B and C derived from the probability of missed detection given that there is an ephemeris error in a GLONASS satellite.

For GBAS ground subsystems that do not broadcast corrections for GLONASS ranging sources, this parameter shall be coded as all zeros.

3.6.4.3.2 Additional data blocks. For additional data blocks other than additional data block 1, the parameters for each data block shall be as follows:

ADDITIONAL DATA BLOCK LENGTH: the number of bytes in the additional data block, including the additional data block length and additional data block number fields.

ADDITIONAL DATA BLOCK NUMBER: the numerical identifier of the type of additional data block.

Coding: 0 to 1 = reserved 2 = additional data block 2, GRAS broadcast stations 3 = additional data block 3, GAST D parameters 4 = additional data block 4, VDB authentication parameters 5 to 255 = spare

ADDITIONAL DATA PARAMETERS: the set of data defined in accordance with the additional data block number.

3.6.4.3.2.1 GRAS broadcast stations 379CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Parameters for additional data block 2 shall include data for one or more broadcast stations as follows (Table B-131):

CHANNEL NUMBER: the channel number, as defined in 3.6.5.7, associated with a GBAS broadcast station.

Note.:— The channel number in this field refers to a frequency and an RSDS. ΔLATITUDE: the difference of latitude of a GBAS broadcast station, measured from the latitude provided in the latitude parameter of Type 2 message.

Coding: Positive value denotes that the GBAS broadcast station is north of the GBAS reference point.

Negative value denotes that the GBAS broadcast station is south of the GBAS reference point. ΔLONGITUDE: the difference of longitude of a GBAS broadcast station, measured from the longitude provided in the longitude parameter of Type 2 message.

Coding: Positive value denotes that the GBAS broadcast station is east of the GBAS reference point.

Negative value denotes that the GBAS broadcast station is west of the GBAS reference point.

Note.: Guidance material concerning additional data block 2 is provided in Attachment D, 7.17.

3.6.4.3.2.2 GAST D parameters Parameters for additional data block 3 shall include parameters (Table B-132) to be used when the active service type is GAST D as follows:

Kmd_e_D,GLONASS (Kmd_e_D,GLONASS): is the multiplier for computation of the ephemeris error position bound for GAST D derived from the probability of missed detection given that there is an ephemeris error in a GLONASS satellite. For GBAS ground subsystems that do not broadcast corrections for GLONASS ranging sources, this parameter is coded as all zeros.

Note.:— This parameter, Kmd_e_D,GLONASS, may be different than the ephemeris decorrelation parameter Kmd_e_GLONASS provided in additional data block 1 of the Type 2 message. Additional information regarding the difference in these parameters is given in Attachment D,

7.5.6.1.2 and 7.5.6.1.3.

380CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Kmd_e_D,GPS (Kmd_e_D,GPS): is the multiplier for computation of the ephemeris error position bound for GAST D derived from the probability of missed detection given that there is an ephemeris error in a GPS satellite. For GBAS ground subsystems that do not broadcast corrections for GPS ranging sources, this parameter is coded as all zeros.

Note.:— This parameter, Kmd_e_D,GPS, may be different than the ephemeris decorrelation parameter Kmd_e_GPS provided in additional data block 1 of the Type 2 message. Additional information regarding the difference in these parameters is given in ttachment D, 7.5.6.1.2 and 7.5.6.1.3.

Sigma_vert_iono_gradient_D (𝜎𝑣𝑒𝑟𝑡_𝑖𝑜𝑛𝑜_𝑔𝑟𝑎𝑑𝑖𝑒𝑛𝑡_𝐷): is the standard deviation of a normal distribution associated with the residual ionospheric uncertainty due to spatial decorrelation. This parameter is used by airborne equipment when its active approach service type is D.

Note.:— This parameter, Sigma_vert_iono_gradient_D, may be different than the ionospheric decorrelation parameter Sigma_vert_iono_gradient provided in the Type 2 message. Additional information regarding the difference in these parameters is given in Attachment D, 7.5.6.1.2 and 7.5.6.1.3.

YEIG: is the maximum value of EIG at zero distance from the GBAS reference point. This parameter is used by airborne equipment when its active approach service type is D.

MEIG: is the slope of maximum EIG versus distance from the GBAS reference point. This parameter is used by airborne equipment when its active approach service type is D.

381CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.6.4.3.2.3 VDB authentication parameters Additional data block 4 includes information needed to support VDB authentication protocols (Table B-133).

Slot group definition: This 8-bit field indicates which of the 8 slots (A-H) are assigned for use by the ground station. The field is transmitted LSB first. The LSB corresponds to slot A, the next bit to slot B, and so on. A “1” in the bit position indicates the slot is assigned to the ground station.

A “0” indicates the slot is not assigned to the ground station.

3.6.4.4 TYPE 3 MESSAGE — NULL MESSAGE

3.6.4.4.1 The Type 3 message is a variable length “null message” which is intended to be used by ground subsystems that support the authentication protocols (see 3.6.7.4).

3.6.4.4.2 The parameters for the Type 3 message shall be as follows:

Filler: a sequence of bits alternating between “1” and “0” with a length in bytes that is 10 less than the value in the message length field in the message header.

3.6.4.5 Type 4 message — Final approach segment (FAS). Type 4 message shall contain one or more sets of FAS data, each defining a single precision approach (Table B-143). Each Type 4 message data set shall

include the following:

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Data set length: the number of bytes in the data set. The data set includes the data set length field and the associated FAS data block, FAS vertical alert limit (FASVAL)/approach status and FAS lateral alert limit

(FASLAL)/approach status fields.

FAS data block: the set of parameters to identify an approach and define its associated approach path.

Coding: See 3.6.4.5.1 and Table B-134.

Note.: Guidance material for FAS path definition is contained in Attachment D,

7.11. FASVAL/approach status: the value of the parameter FASVAL as used in 3.6.5.6.

Coding: 1111 1111 = Do not use vertical deviations.

Note.:— The range and resolution of values for FASVAL depend upon the approach performance designator in the associated FAS data block.

FASLAL/approach status: the value of the parameter FASLAL as used in

3.6.5.6.

Coding: 1111 1111 = Do not use approach.

Note.:— The Procedures for Air Navigation Services — Aircraft Operations (PANS- OPS) (Doc 8168), Volume II, specifies conventions to be used by procedure designers when applying the FAS data block definitions and codings below to encode procedures.

3.6.4.5.1 FAS data block. The FAS data block shall contain the parameters that define a single GAST A, B, C or D approach. The FAS path is a line in space defined by the landing threshold point/fictitious threshold point (LTP/FTP), flight path alignment point (FPAP), threshold crossing height

(TCH) and glide path angle (GPA). The local level plane for the approach is a plane perpendicular to the local vertical passing through the LTP/FTP (i.e. tangent to the ellipsoid at the LTP/FTP).

Local vertical for the approach is normal to the WGS-84 ellipsoid at the LTP/FTP. The glide path intercept point (GPIP) is where the final approach path intercepts the local level plane. FAS data block

parameters shall be as follows:

Operation type: straight-in approach procedure or other operation types.

Coding: 0 = straight-in approach procedure 1 to 15 = spare Note.:— Offset procedures are straight-in procedures and coded as “0”.

383CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

SBAS service provider ID: indicates the service provider associated with this FAS data block.

Coding: See Table B-65.

14 = FAS data block is to be used with GBAS only.

15 = FAS data block can be used with any SBAS service provider.

Note.:— This parameter is not used for approaches conducted using GBAS or GRAS pseudo-range corrections.

Airport ID: the three- or four-letter designator used to designate an airport.

384CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

Coding: Each character is coded using the lower 6 bits of its IA-5 representation. For each character, bi is transmitted first, and 2 zero bits are appended after b6, so that 8 bits are transmitted for each character.

Only upper case letters, numeric digits and IA-5 “space” are used. The rightmost character is transmitted first. For a three-character airport ID, the rightmost (first transmitted) character shall be IA-5 “space”.

Runway number: the approach runway number.

Coding: 1 to 36 = runway number Note.:— For heliport and point-in-space operations, the runway number value is the integer nearest to one tenth of the final approach course, except when that integer is zero, in which case the runway number is 36.

Runway letter: the one-letter designator used, as necessary, to differentiate between parallel runways.

Coding: 0 = no letter 1 = R (right) 2 = C (centre) 3 = L (left)

Approach performance designator: the general information about the approach design.

Coding:

0 = GAST A or B 1 = GAST C 2 = GAST C and GAST D 3 = GAST C, GAST D and an additional approach service type to be defined in the future 4 = GAST C, GAST D and two additional approach service types to be defined in the future 5 to 7 = spare Note.:— Some airborne equipment designed for Category I performance is insensitive to the value of the APD. It is intended that airborne equipment designed for Category I performance accepts APD values of at least 1-4 as valid to accommodate future extensions to higher performance types 385CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 using the same FAS data block.

Route indicator: the one-letter identifier used to differentiate between multiple approaches to the same runway end.

Coding: The letter is coded using bits b1 through b5 of its IA-5 representation. Bit b1 is transmitted first. Only upper case letters, excluding “I” and “O”, or IA-5 “space” are used.

Reference path data selector (RPDS): the numeric identifier that is used to select the FAS data block (desired approach).

Note.:— The RPDS for a given FAS data block is different from every other RPDS and every reference station data selector (RSDS) broadcast on the same frequency by every GBAS within the broadcast region.

Reference path identifier (RPI): the three or four alphanumeric characters used to uniquely designate the reference path.

Coding: Each character is coded using bits b1 through b6 of its IA-5 representation. For each character, b1 is transmitted first, and 2 zero bits are appended after b6 so that 8 bits are transmitted for each character.

Only upper case letters, numeric digits and IA-5 “space” are used. The rightmost character is transmitted first. For a three-character reference path identifier, the rightmost (first transmitted) character shall be IA-5 “space”.

Note.: The LTP/FTP is a point over which the FAS path passes at a relative height specified by the TCH. LTP is normally located at the intersection of the runway centre line and the threshold.

LTP/FTP latitude: the latitude of the LTP/FTP point in arc seconds.

Coding: Positive value denotes north latitude.

Negative value denotes south latitude.

LTP/FTP longitude: the longitude of the LTP/FTP point in arc seconds.

Coding: Positive value denotes east longitude.

Negative value denotes west longitude.

LTP/FTP height: the height of the LTP/FTP above the WGS-84 ellipsoid.

Coding: This field is coded as an unsigned fixed-point number with an offset of –512 metres. A value of zero in this field places the LTP/FTP 512 metres below the earth ellipsoid.

386CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.:— The FPAP is a point at the same height as the LTP/FTP that is used to define the alignment of the approach. The origin of angular deviations in the lateral direction is defined to be 305 metres (1 000 ft) beyond the FPAP along the lateral FAS path. For an approach aligned with the runway, the FPAP is at or beyond the stop end of the runway.

ΔFPAP latitude: the difference of latitude of the runway FPAP from the LTP/FTP in arc seconds.

Coding: Positive value denotes the FPAP latitude north of LTP/FTP latitude.

Negative value denotes the FPAP latitude south of the LTP/FTP latitude. ΔFPAP longitude: the difference of longitude of the runway FPAP from the LTP/FTP in arc seconds.

Coding: Positive value indicates the FPAP longitude east of LTP/FTP longitude.

Negative value indicates the FPAP longitude west of LTP/FTP longitude.

Approach TCH: the height of the FAS path above the LTP/FTP defined in either feet or metres as indicated by the TCH units selector.

Approach TCH units selector: the units used to describe the TCH.

Coding: 0 = feet 1 = metres Glide path angle (GPA): the angle of the FAS path with respect to the horizontal plane tangent to the WGS-84 ellipsoid at the LTP/FTP.

Course width: the lateral displacement from the path defined by the FAS at the LTP/FTP at which full-scale deflection of a course deviation indicator is attained.

Coding: This field is coded as an unsigned fixed-point number with an offset of 80 metres. A value of zero in this field indicates a course width of 80 metres at the LTP/FTP. ΔLength offset: the distance from the stop end of the runway to the FPAP.

Coding: 1111 1111 = not provided

Final approach segment CRC: the 32-bit CRC appended to the end of each FAS data block in order to ensure approach data integrity. The 32- 387CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 bit final approach segment CRC shall be calculated in accordance with

3.9. The length of the CRC code shall be k = 32 bits.

The CRC generator polynomial shall be:

G(x) = x32 + x31 + x24 + x22 + x16 + x14 + x8 + x7 + x5 + x3 + x + 1 The CRC information field, M(x), shall be:

M(x) shall be formed from all bits of the associated FAS data block, excluding the CRC. Bits shall be arranged in the order transmitted, such that m1 corresponds to the LSB of the operation type field, and m272 corresponds to the MSB of the Δlength offset field. The CRC shall be ordered such that r1 is the LSB and r32 is the MSB. The CRC information field,

3.6.4.6 Type 5 message — predicted ranging source availability. When used, the Type 5 message shall contain rising and setting information for the currently visible or soon to be visible ranging sources. Predicted ranging

source availability parameters shall be as follows:

Modified Z-count: indicates the time of applicability of the parameters in this message.

Coding: Same as modified Z-count field in Type 1 message (3.6.4.2).

Number of impacted sources: the number of sources for which duration information applicable to all approaches is provided.

Coding: 0 = Only specified obstructed approaches have limitations.

1 to 31 = The number of ranging sources impacted.

Ranging source ID: as for Type 1 message (3.6.4.2).

Source availability sense: indicates whether the ranging source will become available or cease to be available.

Coding: 0 = Differential corrections will soon cease to be provided for the associated ranging source.

1 = Differential corrections will soon start to be provided for the associated ranging source.

388CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

Source availability duration: the predicted minimum ranging source availability duration relative to the modified Z-count.

Coding: 111 1111 = The duration is greater than or equal to 1 270 seconds.

Number of obstructed approaches: the number of approaches for which the corrections will be reduced due to approach unique constellation masking.

Reference path data selector: an indication of the FAS data block to which the source availability data applies (3.6.4.5.1).

Number of impacted sources for this approach: the number of sources for which duration information applicable only to this approach is

provided.

3.6.4.7 TYPE 6 MESSAGE Note.: Type 6 message is reserved for future use to provide the information required for Category II/III precision approaches.

3.6.4.8 TYPE 7 MESSAGE Note.: Type 7 message is reserved for national applications.

3.6.4.9 TYPE 8 MESSAGE Note.: Type 8 message is reserved for local and regional test applications.

3.6.4.10 TYPE 101 MESSAGE — GRAS PSEUDO-RANGE CORRECTIONS

3.6.4.10.1 The Type 101 message shall provide the differential correction data for individual GNSS ranging sources (Table B-139). The message shall

contain three sections: a) message information (time of validity, additional message flag, number of measurements and the measurement type); b) low-frequency information (ephemeris decorrelation parameter, satellite ephemeris CRC and satellite availability information); and c) satellite data measurement blocks.

Note.:— All parameters in this message type apply to 100-second carrier-smoothed pseudo-ranges.

3.6.4.10.2 Each Type 101 message shall include ephemeris decorrelation parameter, ephemeris CRC and source availability duration parameters 389CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 for one satellite ranging source. The ephemeris decorrelation parameter, ephemeris CRC and source availability duration shall apply to the first ranging source in the message.

3.6.4.10.3 Pseudo-range correction parameters shall be as follows:

Modified Z-count: as defined in 3.6.4.2.3.

Additional message flag: as defined in 3.6.4.2.3 except applicable to Type 101 messages.

Number of measurements: as defined in 3.6.4.2.3.

Measurement type: as defined in 3.6.4.2.3.

Ephemeris decorrelation parameter (P): as defined in 3.6.4.2.3.

Ephemeris CRC: as defined in 3.6.4.2.3.

Source availability duration: as defined in 3.6.4.2.3.

Number of B parameters: an indication of whether the B parameters are included in the measurement block for each ranging source.

Coding: 0 = B parameters are not included 1 = 4 B parameters per measurement block

3.6.4.10.4 The measurement block parameters shall be as follows:

Ranging source ID: as defined in 3.6.4.2.4.

Issue of data (IOD): as defined in 3.6.4.2.4.

Pseudo-range correction (PRC): as defined in 3.6.4.2.4.

Range rate correction (RRC): as defined in 3.6.4.2.4. σpr_gnd: as defined in 3.6.4.2.4, with the exception of the range of values and resolution.

B1 through B4: as defined in 3.6.4.2.4.

Note.:— Inclusion of the B parameters in the measurement block is optional for Type 101 messages.

3.6.4.11 TYPE 11 MESSAGE – PSEUDO-RANGE CORRECTIONS – 30- SECOND SMOOTHED PSEUDO-RANGES 390CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.6.4.11.1 The Type 11 message shall provide the differential correction data for individual GNSS ranging sources (Table B-140) with 30-second carrier- smoothing applied. The message shall contain three sections:

a) message information (time of validity, additional message flag, number of measurements and the measurement type); b) low-frequency information (ephemeris decorrelation parameter); and c) satellite data measurement blocks.

Note.: Transmission of the low-frequency data for SBAS ranging sources is optional.

3.6.4.11.2 Each Type 11 message shall include the ephemeris decorrelation parameter for one satellite ranging source.

The ephemeris decorrelation parameter shall apply to the first ranging source in the message.

Note.: The ephemeris CRC and source availability duration parameters are not included in the Type 11 message because they are provided in the Type 1 message.

3.6.4.11.3 Pseudo-range correction parameters for the Type 11 message shall be

as follows:

Modified Z-count: as defined in 3.6.4.2.3.

Additional message flag: an identification of whether the set of measurement blocks in a single frame for a particular measurement type is contained in a single Type 11 message or a linked pair of messages.

Coding: 0 = All measurement blocks for a particular measurement type are contained in one Type 11 message.

1 = This is the first transmitted message of a linked pair of Type 11 messages that together contain the set of all measurement blocks for a particular measurement type.

2 = Spare 3 = This is the second transmitted message of a linked pair of Type 11 messages that together contain the set of all measurement blocks for a particular measurement type.

Number of measurements: the number of measurement blocks in the message.

391CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

Measurement type: as defined in 3.6.4.2.3.

Ephemeris decorrelation parameter D (PD): a parameter that characterizes the impact of residual ephemeris errors due to decorrelation for the first measurement block in the message.

Note.:— This parameter, PD, may be different than the ephemeris decorrelation parameter P provided in the Type 1 message. Additional information regarding the difference in these parameters is given in Attachment D,

7.5.6.1.3 and 7.5.6.1.4.

For an SBAS geostationary satellite, the ephemeris decorrelation parameter, if transmitted, shall be coded as all zeros.

3.6.4.11.4 The measurement block parameters shall be as follows:

Ranging source ID: as defined in 3.6.4.2.3.

Pseudo-range correction (PRC30): the correction to the ranging source pseudo-range based on 30-second carrier-smoothing.

Range rate correction (RRC30): the rate of change of the pseudo-range correction based on 30-second carrier-smoothing.

Sigma_PR_gnd_D (σpr_gnd_D): the standard deviation of a normal distribution associated with the signal in-space contribution of the pseudo-range error in the 100-second smoothed correction in the Type 1 message at the GBAS reference point (3.6.5.5.1 and 3.6.7.2.2.4).

Note.:— The parameter σpr_gnd_D differs from σpr_gnd for the corresponding measurement in the Type 1 message in that σpr_gnd_D should include no inflation to address overbounding of decorrelated ionospheric errors.

Coding: 1111 1111 = Ranging source correction invalid.

Sigma_PR_gnd_30 (σpr_gnd_30): the standard deviation of a normal distribution that describes the nominal accuracy of corrected pseudo- range smoothed with a time constant of 30 seconds at the GBAS reference point.

Note.:— The normal distribution N(0, σpr_gnd_30) is intended to be an appropriate description of the errors to be used in optimizing the weighting used in a weighted least-squares-position solution. The distribution need not bound the errors as described in 3.6.5.5.1 and 3.6.7.2.2.4.

Coding: 1111 1111 = Ranging source correction invalid.

3.6.5 DEFINITIONS OF PROTOCOLS FOR DATA APPLICATION 392CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.:— This section defines the inter-relationships of the data broadcast message parameters. It provides definitions of parameters that are not transmitted, but are used by either or both non-aircraft and aircraft elements, and that define terms applied to determine the navigation solution and its integrity.

3.6.5.1 Measured and carrier smoothed pseudo-range. The broadcast correction is applicable to carrier smoothed code pseudo-range measurements that have not had the satellite broadcast troposphere and ionosphere corrections applied to them. The carrier smoothing is defined by the

following filter: where PCSCn = the smoothed pseudo-range;

PCSCn–1 = the previous smoothed pseudo-range;

P = the raw pseudo-range measurement where the raw pseudo-range measurements are obtained from a carrier driven code loop, first order or higher and with a one-sided noise bandwidth greater than or equal to

0.125 Hz; λ = the L1 wavelength; ϕn = the carrier phase; ϕn–1 = the previous carrier phase; and α = the filter weighting function equal to the sample interval divided by the smoothing time constant. For GBAS pseudo-range corrections in message Type 1 and message Type 101, the smoothing time constant is 100 seconds, except as specified in 3.6.8.3.5.1 for airborne equipment.

For GBAS pseudo-range corrections in message Type 11, the smoothing time constant is 30 seconds.

3.6.5.2 Corrected pseudo-range. The corrected pseudo-range for a given

satellite at time t is:

PRcorrected = PCSC + PRC + RRC × (t − tz − count) + TC + c × (Δtsv)L1 where PCSC = the smoothed pseudo-range (defined in 3.6.5.1);

393CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 PRC = the pseudo-range correction from the appropriate message: a) for 100-second smoothed pseudo-ranges, PRC is taken from message Type 1 or Type 101 defined in 3.6.4.2; and b) for 30-second smoothed pseudo-ranges, PRC is PRC30 taken from message Type 11 defined in 3.6.4.11;

RRC = the pseudo-range correction rate from the appropriate message: a) for 100-second smoothed pseudo-ranges, RRC is taken from message Type 1 or Type 101 defined in 3.6.4.2; and b) for 30-second smoothed pseudo-ranges, RRC is RRC30 taken from message Type 11 defined in 3.6.4.11;

t = the current time; tz-count = the time of applicability derived from the modified Z-count of the message containing PRC and RRC;

TC = the tropospheric correction (defined in 3.6.5.3); and c and (Δtsv)L1 are as defined in 3.1.2.2 for GPS satellites.

3.6.5.3 TROPOSPHERIC DELAY

3.6.5.3.1 The tropospheric correction for a given satellite is: where Nr = refractivity index from the Type 2 message (3.6.4.3); Δh = height of the aircraft above the GBAS reference point;

Eli = elevation angle of the ith satellite; and h0 = troposphere scale height from the Type 2 message.

3.6.5.3.2 The residual tropospheric uncertainty is:

394CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 where σn = the refractivity uncertainty from the Type 2 message (3.6.4.3).

3.6.5.4 Residual ionospheric uncertainty. The residual ionospheric uncertainty

for a given satellite is: σiono = Fpp × σvig × (xair + 2 × 𝜏 × vair) where Fpp = the vertical-to-slant obliquity factor for a given satellite (3.5.5.5.2); σvig = is dependent on the active GAST.

For GAST A, B or C, σvig = σvert_iono_gradient (as defined in 3.6.4.3);

For GAST D, σvig = σvert_iono_gradient_D (as defined in 3.6.4.3.2.2); xair = the distance (slant range) in metres between current aircraft location and the GBAS reference point indicated in the Type 2 message;

𝜏 = is dependent on the active GAST.

For GAST A, B or C, τ =100 seconds (time constant used in 3.6.5.1); and For GAST D, the value of τ depends on whether σiono is applied in measurement weighting or in integrity bounding. τ = 100 seconds when σiono is used for integrity bounding (per 3.6.5.5.1.1.1) and 𝜏 = 30 seconds when σiono is used for measurement weighting (per

3.6.5.5.1.1.2); vair = the aircraft horizontal approach velocity (metres per second).

3.6.5.5 PROTECTION LEVELS

3.6.5.5.1 Protection levels for all GBAS approach service types. The signal-in- space vertical and lateral protection levels (VPL and LPL) are upper confidence bounds on the error in the position relative to the GBAS

reference point defined as:

VPL = MAX {VPLHO, VPLH1} LPL = MAX {LPLHO, LPLH1}

3.6.5.5.1.1 Normal measurement conditions

3.6.5.5.1.1.1 The vertical protection level (VPLH0) and lateral protection level

(LPLH0), assuming that normal measurement conditions (i.e. no faults) exist in all reference receivers and on all ranging sources, is calculated as:

395CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 VPLH0 = Kffmdσvert +DV LPLH0 = Kffmdσlat +DL where and σpr_gnd,i is dependent on the active GAST.

For GAST A, B or C: σpr_gnd,i = σpr_gnd for the ith ranging source as defined in 3.6.4.2;

For GAST D: σpr_gnd,i = σpr_gnd_D for the ith ranging source (3.6.4.11); σ2tropo,I, σ2pr_air,I and σ2iono,I are as defined in 3.6.5.5.1.1.2;

Kffmd = the multiplier derived from the probability of fault-free missed detection; s_verti = sv,i + sx,i × tan (GPA); s_lati = sy,i; sx,i = the partial derivative of position error in the x-direction with respect to pseudo-range error on the ith satellite;

sy,i = the partial derivative of position error in the y-direction with respect to pseudo-range error on the ith satellite; sv,i = the partial derivative of position error in the vertical direction with respect to pseudo-range error on the ith satellite;

GPA = the glidepath angle for the final approach path (3.6.4.5.1);

396CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 N = the number of ranging sources used in the position solution; and i = the ranging source index for ranging sources used in the position solution;

DV = an airborne determined parameter depending on the active GAST.

For GAST A, B or C: DV = 0;

For GAST D: DV is calculated as the magnitude of the vertical projection of the difference between the 30-second and 100-second position solutions;

DL = an airborne determined parameter depending on the active GAST.

For GAST A, B or C: DL = 0;

For GAST D: DL is calculated as the magnitude of the lateral projection of the difference between the 30-second and 100-second position solutions.

Note 1.— The airborne 30-second and 100-second position solutions, DV and DL are defined in RTCA MOPS DO-253D.

Note 2. — The coordinate reference frame is defined such that x is along track positive forward, y is crosstrack positive left in the local level tangent plane and v is the positive up and orthogonal to x and y.

3.6.5.5.1.1.2 For a general-least-squares position solution, the projection matrix S is

defined as: where 397CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 where where σpr_gnd,i = is dependent on the active GAST.

For GAST A, B or C or the GBAS positioning service: σpr_gnd,i = σ pr_gnd for the ith ranging source as defined in (3.6.4.2);

For GAST D: σpr_gnd,i = σpr_gnd_30 for the ith ranging source (3.6.4.11); σtropo,i = the residual tropospheric uncertainty for the ith ranging source (3.6.5.3); σiono,i = the residual ionospheric delay (due to spatial decorrelation) uncertainty for the ith ranging source (3.6.5.4); and σpr_air,i = √σ2receiver(Eli) + σ2multipath(Eli), the standard deviation of the aircraft contribution to the corrected pseudo range error for the ith ranging source. The total aircraft contribution includes the receiver contribution (3.6.8.2.1) and a standard allowance for airframe multipath;

where σmultipath(Eli) = 0.13 + 0.53e–Eli/10 deg, the standard model for the contribution of airframe multipath (in metres);

Eli = the elevation angle for the ith ranging source (in degrees); and Azi = the azimuth for the ith ranging source taken counterclockwise for the x axis (in degrees).

Note.:— To improve readability, the subscript i was omitted from the projection matrix’s equation.

3.6.5.5.1.2 Faulted measurement conditions. When the Type 101 message is broadcast without B parameter blocks, the values for VPLH1 and LPLH1 are defined as zero. Otherwise, the vertical protection level (VPLH1) and lateral protection level (LPLH1), assuming that a latent fault exists in one, and only one reference receiver, are:

VPLH1 = max [VPLj] + DV LPLH1 = max [LPLj] + DL where VPLj and LPLj for j = 1 to 4 are 398CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 VPLj = |B_vertj| + Kmd σvert,H1 ; and LPLj = |B_latj| + Kmd σlat,H1 ;

DV = an airborne determined parameter depending on the active GAST (3.6.5.5.1.1.1);

DL = an airborne determined parameter depending on the active GAST (3.6.5.5.1.1.1); and Note.: A latent fault includes any erroneous measurement(s) that is not immediately detected by the ground subsystem, such that the broadcast data are affected and there is an induced position error in the aircraft subsystem.

3.6.5.5.1.3 Definition of K multipliers for GBAS approach services. The multipliers are given in Table B-135.

399CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.6.5.5.2 GBAS positioning service. The signal-in-space horizontal protection level is an upper confidence bound on the horizontal error in the position

relative to the GBAS reference point defined as:

HPL = MAX{HPLH0,HPLH1,HEB}

3.6.5.5.2.1 Normal measurements conditions. The horizontal protection level

(HPLH0), assuming that normal measurement conditions (i.e. no faults) exist in all reference receivers and on all ranging sources, is calculated as:

HPLH0 = Kffmd, POSdmajor

where: sx,i = the partial derivative of position error in the x-direction with respect to pseudo-range error on the ith satellite sy,i = the partial derivative of position error in the y-direction with respect to pseudo-range error on the ith satellite Kffmd,POS = the multiplier derived from the probability of fault-free missed detection N = the number of ranging sources used in the position solution i = the ranging source index for ranging sources used in the position solution σi = the pseudo-range error term as defined in 3.6.5.5.1.1 Note.:— For the GBAS positioning service, the x and y axes define an arbitrary orthogonal basis in the horizontal plane.

3.6.5.5.2.2 Faulted measurement conditions. When the Type 101 message is broadcast without B parameter blocks, the value for HPLH1 is defined as 400CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 zero. Otherwise, the horizontal protection level (HPLH1), assuming that a latent fault exists in one and only one reference receiver, is:

HPLH1 = max [HPLj] where HPLj for j = 1 to 4 is: and Bi,j = the broadcast differences between the broadcast pseudo-range corrections and the corrections obtained excluding the jth reference receiver measurement for the ith ranging source.

Kmd_POS = the multiplier derived from the probability of missed detection given that the ground subsystem is faulted.

Note.: For the GBAS positioning service, the x and y axes define an arbitrary orthogonal basis in the horizontal plane.

401CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Mi = the number of reference receivers used to compute the pseudo- range corrections for the ith ranging source (indicated by the B values).

Ui = the number of reference receivers used to compute the pseudo- range corrections for the ith ranging source, excluding the jth reference receiver.

Note.: A latent fault includes any erroneous measurement(s) that is not immediately detected by the ground subsystem, such that the broadcast data are affected and there is an induced position error in the aircraft subsystem.

3.6.5.5.2.3 Definition of K multipliers for GBAS positioning service. The multiplier Kffmd_POS is equal to 10.0 and the multiplier Kmd_POS, is equal to 5.3.

3.6.5.6 ALERT LIMITS Note 1.— Guidance concerning the calculation of alert limits, including approaches associated with channel numbers 40 000 to 99 999, is provided in Attachment D, 7.13.

Note 2. — Computation of alert limits depends on the active service type.

3.6.5.6.1 GAST C and D alert limits. The alert limits are defined in Tables B-136 and B-137. For aircraft positions at which the lateral deviation exceeds twice the deviation at which full-scale lateral deflection of a course deviation indicator is achieved, or vertical deviation exceeds twice the deviation at which full-scale fly-down deflection of a course deviation indicator is achieved, both the lateral and vertical alert limits are set to the maximum values given in the tables.

3.6.5.6.2 GAST A and B alert limits. The alert limits are equal to the FASLAL and FASVAL taken from the Type 4 message for approaches with channel numbers in the range of 20 001 to 39 999. For approaches with channel numbers in the range 40 000 to 99 999, the alert limits are stored in the on-board database.

3.6.5.7 Channel number. Each GBAS approach transmitted from the ground subsystem is associated with a channel number in the range of 20 001 to 39 999. If provided, the GBAS positioning service is associated with a separate channel number in the range of 20 001 to 39 999. The channel

number is given by:

Channel number = 20 000 + 40(F – 108.0) + 411(S) 402CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 where F = the data broadcast frequency (MHz) S = RPDS or RSDS and RPDS = the reference path data selector for the FAS data block (as defined in 3.6.4.5.1) RSDS = the reference station data selector for the GBAS ground subsystem (as defined in 3.6.4.3.1) For channel numbers transmitted in the additional data block 2 of Type 2 message (as defined in 3.6.4.3.2.1), only RSDS are used.

Note 1.— When the FAS is not broadcast for an approach supported by GAST A or B, the GBAS approach is associated with a channel number in the range 40 000 to 99 999.

Note 2. — Guidance material concerning channel number selection is provided in Attachment D, 7.7.

3.6.5.8 EPHEMERIS ERROR POSITION BOUND 403CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.:— Ephemeris error position bounds are computed only for core satellite constellation ranging sources used in the position solution (j index) and not for other types of ranging sources (SBAS satellites or pseudolites) that are not subject to undetected ephemeris failures. However, the calculations of these position bounds use information from all ranging sources used in the position solution (i index).

3.6.5.8.1 GBAS approach. The vertical and lateral ephemeris error position

bounds are defined as:

The vertical and lateral ephemeris error position bounds for the jth core satellite constellation ranging source used in the position solution are

given by:

where:

DV = an airborne determined parameter depending on the active GAST (3.6.5.5.1.1.1);

DL = an airborne determined parameter depending on the active GAST (3.6.5.5.1.1.1); s_verti or j is defined in 3.6.5.5.1.1; s_lati or j is defined in 3.6.5.5.1.1; xair is defined in 3.6.5.4;

N is the number of ranging sources used in the position solution; σi is defined in 3.6.5.5.1.1;

404CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Pej is the broadcast ephemeris decorrelation parameter for the jth ranging source. The source of this parameter depends on the active

GBAS approach service type:

GAST A, B or C: Pej = P from the Type 1 or Type 101 Message corresponding to the jth ranging source (3.6.4.2.3);

GAST D: Pej = PD from the Type 11 Message corresponding to the jth ranging source (3.6.4.11.3);

Kmd_e,j is the broadcast ephemeris missed detection multiplier for GAST A-C associated with the satellite constellation for the jth ranging source. The source of this parameter depends on the active GBAS

approach service type:

GAST A, B or C: Kmd_e,j = Kmd_e,GPS or Kmd_e,GLONASS as obtained from the Type 2 Message Additional Data block 1 (3.6.4.3.1);

GAST D: Kmd_e,j = Kmd_e_D,GPS or Kmd_e_D,GLONASS as obtained from the Type 2 Message Additional Data block 3 (3.6.4.3.2.2).

3.6.5.8.2 GBAS positioning service. The horizontal ephemeris error

position bound is defined as:

The horizontal ephemeris error position bound for the jth core satellite

constellation ranging source used in the position solution is given by:

where: sx,j is as defined in 3.6.5.5.2.1 sy,j is as defined in 3.6.5.5.2.1 xair is defined in 3.6.5.4 Pj is the broadcast ephemeris decorrelation parameter for the jth ranging source. The source of this parameter does not depend on the active GBAS approach service type. In all cases, Pj=P from the Type 1 or Type 101 Message (3.6.4.2.3) corresponding to the jth ranging source.

405CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Kmd_e_POS is the broadcast ephemeris missed detection multiplier for the GBAS positioning service associated with the satellite constellation for the jth ranging source (Kmd_e_POS,GPS or Kmd_e_POS,GLONASS) dmajor is as defined in 3.6.5.5.2.1

3.6.5.9 Ionospheric gradient error The maximum undetected 30-second smoothed corrected pseudo-range error due to an ionospheric gradient (EIG) is calculated based on the broadcast parameters YEIG and MEIG, as:

EIG = YEIG + MEIG×DEIG where YEIG = maximum value of EIG (metres) in the Type 2 message;

MEIG = slope of maximum EIG (m/km) in the Type 2 message;

DEIG = the distance in kilometres between the LTP location for the selected approach broadcast in the Type 4 Message and the GBAS reference point in the Type 2 message.

3.6.6 MESSAGE TABLES Each GBAS message shall be coded in accordance with the corresponding message format defined in Tables B-138 through B-144.

Note.:— Message type structure is defined in 3.6.4.1.

406CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 407CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 408CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 409CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.:— Multiple additional data blocks may be appended to a Type 2 message.

Note.:— The number of bytes in the filler field is 10 less than the message length field in the message header as defined in 3.6.3.4.

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3.6.7 NON-AIRCRAFT ELEMENTS

3.6.7.1 PERFORMANCE

3.6.7.1.1 Accuracy

3.6.7.1.1.1 The root-mean-square (RMS) (1 sigma) of the ground subsystem contribution to the corrected 100-second smoothed pseudo-range

accuracy for GPS and GLONASS satellites shall be: where M = the number of GNSS reference receivers, as indicated in the Type 2 message parameter (3.6.4.3), or, when this parameter is coded to indicate “not applicable”, the value of M is defined as 1;

n = nth ranging source; θn = elevation angle for the nth ranging source; and a0, a1, a2, and θ0 = parameters defined in Tables B-72 and B-73 for each of the defined ground accuracy designators (GADs).

Note 1.— The GBAS ground subsystem accuracy requirement is determined by the GAD letter and the number of reference receivers.

Note 2.— The ground subsystem contribution to the corrected 100-second smoothed pseudo-range error specified by the curves defined in Tables B-72 and B- 73 and the contribution to the SBAS satellites do not include aircraft noise and aircraft multipath.

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3.6.7.1.1.2 The RMS of the ground subsystem contribution to the corrected 100- second smoothed pseudo-range accuracy for SBAS satellites shall be: where M is as defined in 3.6.7.1.1.1.

Note.: GAD classifications for SBAS ranging sources are under development.

3.6.7.1.2 Integrity

3.6.7.1.2.1 GBAS ground subsystem integrity risk

3.6.7.1.2.1.1 Ground subsystem integrity risk for GBAS approach services

3.6.7.1.2.1.1.1 Ground subsystem signal-in-space integrity risk for GBAS approach service types A, B or C. For a GBAS ground subsystem classified as FAST A, B or C, the integrity risk shall be less than 1.5 × 10–7 per approach.

Note 1. — The integrity risk assigned to the GBAS ground subsystem is a subset of the GBAS signal-in-space integrity risk, where the protection level integrity risk (3.6.7.1.2.2.1) has been excluded and the effects of all other GBAS, SBAS and core satellite constellations failures are included. The GBAS ground subsystem integrity risk includes the integrity risk of satellite signal monitoring required in 3.6.7.3.3.

Note 2. — GBAS signal-in-space integrity risk is defined as the probability that the ground subsystem provides information which when processed by a fault- free receiver, using any GBAS data that could be used by the aircraft in the service volume, results in an out-of-tolerance lateral or vertical relative position error without annunciation for a period longer than the maximum signal-in-space time-to-alert. An out-of-tolerance lateral or vertical relative position error is defined as an error that exceeds the GBAS approach 413CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 services protection level and, if additional data block 1 is broadcast, the ephemeris error position bound.

3.6.7.1.2.1.1.2 Ground subsystem signal-in-space integrity risk for GBAS approach service type D. For a GBAS ground subsystem classified as FAST D, the integrity risk for all effects other than errors induced by anomalous ionospheric conditions shall be less than 1.5 × 10–7 per approach.

Note 1. — The integrity risk assigned to the GBAS ground subsystem classified as FAST D is a subset of the GBAS signal-in-space integrity risk, where the protection level integrity risk (3.6.7.1.2.2.1) has been excluded and the effects of all other GBAS, SBAS and core satellite constellations failures are included.

Note 2.— For GAST D, the GBAS signal-in-space integrity risk is defined as the probability that the ground subsystem provides information which when processed by a fault-free receiver, using any GBAS data that could be used by the aircraft in the service volume, in the absence of an ionospheric anomaly, results in an out-of-tolerance lateral or vertical relative position error without annunciation, for a period longer than the maximum signal- in-space time-to-alert. An out-of-tolerance lateral or vertical relative position error is defined as an error that exceeds the GBAS approach services protection level and the ephemeris error position bound. For GAST D, out-of-tolerance conditions caused by anomalous ionospheric errors are excluded from this integrity risk as the risk due to ionospheric anomalies has been allocated to and is mitigated by the airborne segment.

3.6.7.1.2.1.1.3 Ground subsystem integrity risk for GAST D. For a GBAS ground subsystem classified as FAST D, the probability that the ground subsystem internally generates and transmits non-compliant information for longer than 1.5 seconds shall be less than 1 × 10–9 in any one landing.

Note 1. — This additional integrity risk requirement assigned to FAST D GBAS ground subsystems is defined in terms of the probability that internal ground subsystem faults generate non-compliant information. Non- compliant information in this context is defined in terms of the intended function of the ground subsystem to support landing operations in Category III minima. For example, non-compliant information includes any broadcast signal or broadcast information that is not monitored in accordance with the standard.

Note 2. — Environmental conditions (anomalous ionosphere, troposphere, radio frequency interference, GNSS signal multipath, etc.) are not considered faults; however, faults in ground subsystem equipment, used to monitor for or mitigate the effects of these environmental conditions, are included in this requirement. Similarly, the core satellite constellation ranging source faults are excluded from this requirement; however, the ground subsystem’s capability to provide integrity monitoring for these ranging 414CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 sources is included. Monitoring requirements for ranging source faults and ionosphere environmental conditions are separately specified in

3.6.7.3.3.2, 3.6.7.3.3.3 and 3.6.7.3.4.

Note 3. — Faults that occur in ground receivers used to generate the broadcast corrections are excluded from this requirement if they occur in any one, and only one, ground receiver at any time. Such faults are constrained by the requirement in 3.6.7.1.2.2.1.2 and the associated integrity risk requirements in 3.6.7.1.2.2.1 and 3.6.7.1.2.2.1.1.

3.6.7.1.2.1.2 Ground subsystem time-to-alert for GBAS approach services

3.6.7.1.2.1.2.1 Maximum time-to-alert for approach services

3.6.7.1.2.1.2.1.1 For a ground segment classified as FAST A, B, C or D, the GBAS ground subsystem maximum timeto- alert shall be less than or equal to 3 seconds for all signal-in-space integrity requirements (see Appendix B,

3.6.7.1.2.1.1.1, 3.6.7.1.2.1.1.2, 3.6.7.1.2.2.1) when Type 1 messages are broadcast.

Note 1. — The ground subsystem time-to-alert above is the time between the onset of the out of tolerance lateral or vertical relative position error and the transmission of the last bit of the message that contains the integrity data that reflects the condition (see Attachment D, 7.5.14).

Note 2. — For FAST D ground subsystems, additional range domain monitoring requirements apply as defined in 3.6.7.3.3.2, 3.6.7.3.3.3 and 3.6.7.3.4. In these sections, time limits are defined for the ground system to detect and alert the airborne receiver of out-of-tolerance differential pseudo-range errors.

3.6.7.1.2.1.2.1.2 For a ground segment classified as FAST A, the GBAS ground subsystem maximum signal-in-space time-to-alert shall be less than or equal to 5.5 seconds when Type 101 messages are broadcast.

3.6.7.1.2.1.3 Ground subsystem FASLAL and FASVAL

3.6.7.1.2.1.3.1 For message Type 4 FAS data blocks with APD coded as 1, 2, 3 or 4, the value FASLAL for each FAS block, as defined in the FAS lateral alert limit field of the Type 4 message shall be no greater than 40 metres, and the value FASVAL for each FAS block, as defined in the FAS vertical alert limit field of the Type 4 message, shall be no greater than 10 metres.

3.6.7.1.2.1.3.2 For message Type 4 FAS data blocks with APD coded as zero, the value FASLAL and FASVAL shall be no greater than the lateral and vertical alert limits given in Annex 10, Volume I, 3.7.2.4 for the intended operational use.

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3.6.7.1.2.1.4 Ground subsystem signal-in-space integrity risk for GBAS positioning service. For GBAS ground subsystem that provides the GBAS positioning service, integrity risk shall be less than 9.9 × 10–8 per hour.

Note 1. — The integrity risk assigned to the GBAS ground subsystem is a subset of the GBAS signal in-space integrity risk, where the protection level integrity risk (3.6.7.1.2.2.2) has been excluded and the effects of all other GBAS, SBAS and core satellite constellations failures are included. The GBAS ground subsystem integrity risk includes the integrity risk of satellite signal monitoring required in 3.6.7.3.3.

Note 2. — GBAS signal-in-space integrity risk is defined as the probability that the ground subsystem provides information which when processed by a fault- free receiver, using any GBAS data that could be used by the aircraft, results in an out-of-tolerance horizontal relative position error without annunciation for a period longer than the maximum time-to-alert. An out- of-tolerance horizontal relative position error is defined as an error that exceeds both the horizontal protection level and the horizontal ephemeris error position bound.

3.6.7.1.2.1.4.1 Time-to-alert for GBAS positioning service. The GBAS ground subsystem maximum time-to-alert shall be less than or equal to 3 seconds when Type 1 messages are broadcast and less than or equal to

5.5 seconds when Type 101 messages are broadcast.

Note.: The time-to-alert above is the time between the onset of the out-of- tolerance horizontal relative position error and the transmission of the last bit of the message that contains the integrity data that reflects the condition.

3.6.7.1.2.2 Protection level integrity risk

3.6.7.1.2.2.1 For a GBAS ground subsystem that provides GBAS approach services, the protection level integrity risk shall be less than 5 × 10–8 per approach.

Note.: For approach services, the protection level integrity risk is the integrity risk due to undetected errors in the 100- second smoothed position solution relative to the GBAS reference point greater than the associated protection

levels under the two following conditions: a) normal measurement conditions defined in 3.6.5.5.1.1 with DV and DL set to zero; and b) faulted measurement conditions defined in 3.6.5.5.1.2 with DV and DL set to zero.

Note.: The ground subsystem bounding of the 100-second smoothed GAST D position solution will ensure that the 30 smoothed GAST D position solution is bounded.

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3.6.7.1.2.2.1.1 Additional bounding requirements for FAST D ground subsystems. The σvert (used in computing the protection level VPLH0) and σlat (used in computing the protection level LPLH0) for GAST D formed, based on the broadcast parameters (defined in 3.6.5.5.1.1.1) and excluding the airborne contribution, shall satisfy the condition that a normal distribution with zero mean and a standard deviation equal to σvert and σlat bounds the vertical and lateral error distributions of the combined differential

correction errors as follows: where fn(x) = probability density function of the differential vertical or lateral position error excluding the airborne contribution, and The σvert,H1 (used in computing the protection level VPLH1) and σlat,H1 (used in computing the protection level LPLH1) for GAST D formed, based on the broadcast parameters (defined in 3.6.5.5.1.2) and excluding the airborne contribution, shall bound the combined differential correction errors (as defined above) formed by all possible subsets with one reference receiver excluded.

Note 1. — The airborne contribution is addressed in 3.6.8.3.2.1 in combination with the use of the standard airborne multipath model defined in 3.6.5.5.1.1.2.

Note 2.— The combined differential correction errors refer to code-carrier-smoothed corrections based on 100-second smoothing time constant.

3.6.7.1.2.2.1.2 For a GBAS ground subsystem classified as FAST D, the rate of faulted measurements from any one, and only one, reference receiver shall be less than 1 × 10–5 per 150 seconds.

Note.: Faulted measurements can occur from faults within the receiver or from environmental conditions unique to a single reference receiver location.

3.6.7.1.2.2.2 For a GBAS ground subsystem that provides the positioning service, protection level integrity risk shall be less than 10–9 per hour.

417CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.:— The GBAS positioning service protection level integrity risk is the integrity risk due to undetected errors in the horizontal position relative to the GBAS reference point greater than the GBAS positioning service protection level

under the two following conditions: a) normal measurement conditions defined in 3.6.5.5.2.1; and b) faulted measurement conditions defined in 3.6.5.5.2.2.

3.6.7.1.3 Continuity of service

3.6.7.1.3.1 Continuity of service for approach services. The GBAS ground subsystem continuity of service shall be greater than or equal to 1 – 8.0 × 10–6 per 15 seconds.

Note.:— The GBAS ground subsystem continuity of service is the average probability per 15-second period that the VHF data broadcast transmits data in tolerance, VHF data broadcast field strength is within the specified range and the protection levels are lower than the alert limits, including configuration changes that occur due to the space segment. This continuity of service requirement is the entire allocation of the signal-in- space continuity requirement from Chapter 3, Table 3.7.2.4-1, and therefore all continuity risks included in that requirement must be accounted for by the ground subsystem provider.

3.6.7.1.3.2 Additional continuity of service requirements for FAST D. The probability of a GBAS ground subsystem failure or false alert, excluding ranging source monitoring, causing an unscheduled interruption of service for a period equal to or greater than 1.5 seconds shall not exceed 2.0 × 10−6 during any 15 second interval. The probability that the ground subsystem excludes any individual fault-free ranging source from the Type 1 or Type 11 corrections due to a false detection by the ground integrity monitors shall not exceed 2.0 × 10−7 during any 15 second interval.

Note 1. — Loss of service includes failures resulting in loss of the VHF data broadcast, failure to meet the VHF data broadcast field strength, failures resulting in transmission of out-of-tolerance VHF broadcast data, and alert due to an integrity failure. Guidance material on the potential causes of loss of service and monitor false detections are contained in Attachment D, 7.6.2.1.

Note 2. — Continuity for FAST D is defined as the probability that the ground subsystem continues to provide the services associated with the intended ground subsystem functions. Total aircraft continuity of navigation system performance in the position domain must be evaluated in the context of a specific satellite geometry and aeroplane integration. Evaluation of position domain navigation service continuity is the responsibility of the airborne user for GAST D. Additional information regarding continuity is given in Attachment D, 7.6.2.1.

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3.6.7.1.3.3 Continuity of service for positioning service Note.: For GBAS ground subsystems that provide the GBAS positioning service, there may be additional continuity requirements depending on the intended operations.

3.6.7.2 FUNCTIONAL REQUIREMENTS

3.6.7.2.1 General

3.6.7.2.1.1 Data broadcast requirements.

3.6.7.2.1.1.1 A GBAS ground subsystem shall broadcast message types as defined in Table B-147 according to the service types supported by the ground subsystem.

3.6.7.2.1.1.2 Each GBAS ground subsystem shall broadcast Type 2 messages with additional data blocks as required to support the intended operations.

Note.: Guidance material concerning usage of the Type 2 message additional data blocks is provided in Attachment D, 7.17.

3.6.7.2.1.1.3 Each GBAS ground subsystem which supports GBAS approach service type (GAST) B, C or D shall broadcast FAS blocks in Type 4 messages for these approaches. If a GBAS ground subsystem supports any approach using GAST A or B and does not broadcast FAS blocks for the corresponding approaches, it shall broadcast additional data block 1 in the Type 2 message.

Note.: FAS blocks for APV procedures may be held within a database on board the aircraft. Broadcasting additional data block 1 allows the airborne receiver to select the GBAS ground subsystem that supports the approach procedures in the airborne database. FAS blocks may also be broadcast to support operations by aircraft without an airborne database. These procedures use different channel numbers as described in Attachment D,

7.7.

3.6.7.2.1.1.4 When the Type 5 message is used, the ground subsystem shall broadcast the Type 5 message at a rate in accordance with Table B-148.

Note.: When the standard 5-degree mask is not adequate to describe satellite visibility at either the ground subsystem antennas or at an aircraft during a specific approach, the Type 5 message may be used to broadcast additional information to the aircraft.

3.6.7.2.1.1.5 Data broadcast rates. For all message types required to be broadcast, messages meeting the field strength requirements of Chapter 3,

3.7.3.5.4.4.1.2 and 3.7.3.5.4.4.2.2 and the minimum rates shown in Table B-148 shall be provided at every point within the service volume. The 419CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 total message broadcast rates from all antenna systems of the ground subsystem combined shall not exceed the maximum rates shown in Table B-148.

Note.:— Guidance material concerning the use of multiple antenna systems is

provided in Attachment D, 7.12.4.

3.6.7.2.1.2 Message block identifier. The MBI shall be set to either normal or test according to the coding given in 3.6.3.4.1.

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3.6.7.2.1.3 VDB authentication

3.6.7.2.1.3.1 Recommendation. — All GBAS ground subsystems should support VDB authentication (see 3.6.7.4).

3.6.7.2.1.3.2 All ground subsystems classified as FAST D shall support VDB authentication (see 3.6.7.4).

3.6.7.2.2 Pseudo-range corrections

3.6.7.2.2.1 Message latency. The time between the time indicated by the modified Z-count and the last bit of the broadcast Type 1, Type 11 or Type 101 message shall not exceed 0.5 seconds.

3.6.7.2.2.2 Low-frequency data. Except during an ephemeris change, the first ranging source in the Type 1, Type 11 or Type 101 message shall sequence so that the low-frequency data (as defined in 3.6.4.2.1 for Type 1 message, 3.6.4.11.1 for Type 11 message and 3.6.4.10.1 for Type 101 message) for each core satellite constellation’s ranging source are transmitted at least once every 10 seconds. During an ephemeris change, the first ranging source shall sequence so that the low-frequency data for each core satellite constellation’s ranging source are transmitted at least once every 27 seconds. When new ephemeris data are received from a core satellite constellation’s ranging source, the ground subsystem shall use the previous ephemeris data from each satellite until the new ephemeris data have been continuously received for at least 2 minutes but shall make a transition to the new ephemeris data before 3 minutes have passed. When this transition is made to using the new ephemeris data for a given ranging source, the ground subsystem shall broadcast the new ephemeris CRC and associated low-frequency 421CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 information, notably P and PD for all occurrences of that ranging source in the low-frequency information of Type 1, Type 11 or Type 101 message in the next 3 consecutive frames. For a given ranging source, the ground subsystem shall continue to transmit data corresponding to the previous ephemeris data until the new CRC ephemeris is transmitted in the low-frequency data of Type 1, Type 11 or Type 101 message (see Note). If the ephemeris CRC changes and the IOD does not, the ground subsystem shall consider the ranging source invalid.

Note.:— The delay before the ephemeris transition allow sufficient time for the aircraft subsystem to collect new ephemeris data.

3.6.7.2.2.2.1 Recommendation. — The ephemeris decorrelation parameter and the ephemeris CRC for each core satellite constellation’s ranging source should be broadcast as frequently as possible.

3.6.7.2.2.3 Broadcast pseudo-range correction. Each broadcast pseudo-range correction shall be determined by combining the pseudo-range correction estimates for the relevant ranging source calculated from each of the reference receivers.

For each satellite, the measurements used in this combination shall be obtained from the same ephemeris data. The corrections shall be based on smoothed code pseudo-range measurements for each satellite using the carrier measurement from a smoothing filter and the approach service type specific smoothing parameters in accordance with Appendix B,

3.6.5.1.

3.6.7.2.2.4 Broadcast signal-in-space integrity parameters. The ground subsystem shall provide σpr_gnd and B parameters for each pseudo-range correction in Type 1 message such that the protection level integrity risk requirements defined in 3.6.7.1.2.2 for GAST A, B, and C are satisfied.

At least two B values that are not using the special coding (as defined in

3.6.4.2.4) shall be provided with each pseudo-range correction. The ground subsystem shall provide σpr_gnd and, if necessary, B parameters for each pseudo-range correction in Type 101 message such that the protection level integrity risk requirements defined in 3.6.7.1.2.2 are satisfied.

Note.:— Broadcast of the B parameters are optional for Type 101 messages.

Guidance material regarding the B parameters in Type 101 messages is contained in Attachment D, 7.5.11.

3.6.7.2.2.4.1 Broadcast signal-in-space integrity parameters for FAST D ground subsystems. Ground subsystems that support GAST D shall provide Sigma_PR_gnd_D in the Type 11 message and B parameters for each 422CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 pseudo-range correction in the Type 1 message, such that the protection level integrity risk requirement defined in 3.6.7.1.2.2.1 is satisfied.

3.6.7.2.2.4.2 For FAST D systems broadcasting the Type 11 message, if σpr_gnd is coded as invalid in the Type 1 message, then the Sigma_PR_gnd_D for the associated satellite in the Type 11 message shall also be coded as invalid.

3.6.7.2.2.5 Recommendation.— Reference receiver measurements should be monitored. Faulted measurements or failed reference receivers should not be used to compute the pseudo-range corrections.

3.6.7.2.2.6 Repeated transmission of Type 1, Type 2, Type 11 or Type 101 messages. For a given measurement type and within a given frame, all broadcasts of Type 1, Type 2, Type 11 or Type 101 messages or linked pairs from all GBAS broadcast stations that share a common GBAS identification, shall have identical data content.

3.6.7.2.2.7 Issue of data. The GBAS ground subsystem shall set the IOD field in each ranging source measurement block to be the IOD value received from the ranging source that corresponds to the ephemeris data used to compute the pseudo-range correction.

3.6.7.2.2.8 Application of signal error models. Ionospheric and tropospheric corrections shall not be applied to the pseudo-ranges used to calculate the pseudo-range corrections.

3.6.7.2.2.9 Linked pair of Type 1, Type 11 or Type 101 messages. If a linked pair of Type 1, Type 11 or Type 101 messages is transmitted then, a) the two messages shall have the same modified Z-count; b) the minimum number of pseudo-range corrections in each message shall be one;

c) the measurement block for a given satellite shall not be broadcast more than once in a linked pair of messages; d) the two messages shall be broadcast in different time slots; e) the order of the B values in the two messages shall be the same;

f) for a particular measurement type, the number of measurements and low-frequency data shall be computed separately for each of the two individual messages; g) in the case of FAST D, when a pair of linked Type 1 messages are transmitted, there shall also be a linked pair of Type 11 messages; and 423CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 h) if linked message types of Type 1 or Type 11 are used, the satellites shall be divided into the same sets and order in both Type 1 and Type 11 messages.

Note.: Type 1 messages may include additional satellites not available in Type 11 messages, but the relative order of those satellites available in both messages is the same in Type 1 and Type 11 messages. Airborne processing is not possible for satellites included in the Type 11 message, but also not included in the associated Type 1 message.

3.6.7.2.2.9.1 Recommendation. — Linked messages should only be used when there are more pseudo-range corrections to transmit than will fit in one Type 1 message.

3.6.7.2.2.10 Modified Z-count requirements

3.6.7.2.2.10.1 Modified Z-count update. The modified Z-count for Type 1, Type 11 or Type 101 messages of a given measurement type shall advance every frame.

3.6.7.2.2.10.2 If message Type 11 is broadcast, the associated Type 1 and Type 11 messages shall have the same modified Z-count.

3.6.7.2.2.11 Ephemeris decorrelation parameters

3.6.7.2.2.11.1 Ephemeris decorrelation parameter for approach services. For ground subsystems that broadcast the additional data block 1 in the Type 2 message, the ground subsystem shall broadcast the ephemeris decorrelation parameter in the Type 1 message for each core satellite constellation ranging source such that the ground subsystem integrity risk of 3.6.7.1.2.1.1.1 is met.

3.6.7.2.2.11.2 Ephemeris decorrelation parameter for GAST D. Ground subsystems classified as FAST D shall broadcast the ephemeris decorrelation parameter in the Type 11 message for each core satellite constellation ranging source such that the ground subsystem signal-in-space integrity risk of 3.6.7.1.2.1.1.2 is met.

3.6.7.2.2.11.3 GBAS positioning service. For ground subsystems that provide the GBAS positioning service, the ground subsystem shall broadcast the ephemeris decorrelation parameter in the Type 1 message for each core satellite constellation’s ranging source such that the ground subsystem signal-in-space integrity risk of 3.6.7.1.2.1.4 is met.

3.6.7.2.3 GBAS-related data

3.6.7.2.3.1 Tropospheric delay parameters. The ground subsystem shall broadcast a refractivity index, scale height, and refractivity uncertainty in a Type 2 424CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 message such that the protection level integrity risk requirements defined in 3.6.7.1.2.2 are satisfied.

3.6.7.2.3.2 GCID indication

3.6.7.2.3.2.1 GCID indication for FAST A, B or C. If the ground subsystem meets the requirements of 3.6.7.1.2.1.1.1, 3.6.7.1.2.2.1, 3.6.7.1.3.1, 3.6.7.3.2 and

3.6.7.3.3.1 but not all of 3.6.7.1.2.1.1.2, 3.6.7.1.2.1.1.3, 3.6.7.1.2.2.1.1, and 3.6.7.1.3.2 the GCID shall be set to 1, otherwise it shall be set to 7.

Note.: Some of the requirements applicable to FAST D are redundant with the FAST A, B and C requirements. The phrase “not all of” refers to the condition where a ground subsystem may meet some of the requirements applicable to FAST D but not all of them. Therefore, in that condition, the GCID would be set to 1, indicating that the ground subsystem meets only FAST A, B or C.

3.6.7.2.3.2.2 GCID indication for FAST D. If the ground subsystem meets the requirements of 3.6.7.1.2.1.1.1, 3.6.7.1.2.1.1.2, 3.6.7.1.2.1.1.3,

3.6.7.1.2.2.1.1, 3.6.7.1.2.2.1, 3.6.7.1.3.1, 3.6.7.1.3.2, 3.6.7.3.2 and

3.6.7.3.3, the GCID shall be set to 2, otherwise it shall be set in accordance with 3.6.7.2.3.2.1.

3.6.7.2.3.2.3 GCID values of 3 and 4 are reserved for future service types and shall not be used.

3.6.7.2.3.3 GBAS reference antenna phase centre position accuracy. For each GBAS reference receiver, the reference antenna phase centre position error shall be less than 8 cm relative to the GBAS reference point.

3.6.7.2.3.4 Recommendation.— GBAS reference point survey accuracy. The survey error of the GBAS reference point, relative to WGS-84, should be less than 0.25 m vertical and 1 m horizontal.

Note.:— Relevant guidance material is given in Attachment D, 7.16.

3.6.7.2.3.5 Ionospheric uncertainty estimate parameter

3.6.7.2.3.5.1 Ionospheric uncertainty estimate parameter for all ground subsystems.

The ground subsystem shall broadcast an ionospheric delay gradient parameter in the Type 2 message such that the protection level integrity risk requirements defined in 3.6.7.1.2.2 are satisfied.

3.6.7.2.3.5.2 Ionospheric uncertainty estimate parameter for FAST D ground subsystems. The ground subsystem shall broadcast an ionospheric delay gradient parameter in the Type 2 message, additional data block 3, such that the protection level integrity risk requirements defined in

3.6.7.1.2.2 are satisfied.

425CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.:— Guidance material concerning FAST D position domain error bounding for ionospheric errors may be found in Attachment D, 7.5.6.1.3 and 7.5.6.1.4.

3.6.7.2.3.6 For ground subsystems that provide the GBAS positioning service, the ground subsystem shall broadcast the ephemeris error position bound parameters using additional data block 1 in the Type 2 message.

3.6.7.2.3.7 Recommendation. — All ground subsystems should broadcast the ephemeris error position bound parameters using additional data block 1 in the Type 2 message.

3.6.7.2.3.8 For ground subsystems that broadcast additional data block 1 in the Type 2 message, the following requirements shall apply:

3.6.7.2.3.8.1 Maximum use distance. The ground subsystem shall provide the maximum use distance (Dmax). When the positioning service is provided the ground subsystem integrity risk in 3.6.7.1.2.1.4 and the protection level integrity risk in 3.6.7.1.2.2.2 shall be met within Dmax. When approach service is provided, the maximum use distance shall at least encompass all approach service volumes supported.

3.6.7.2.3.8.2 Ephemeris missed detection parameters. The ground subsystem shall broadcast the ephemeris missed detection parameters for each core satellite constellation such that the ground subsystem integrity risk of

3.6.7.1.2.1 is met.

3.6.7.2.3.8.3 GBAS positioning service indication. If the ground subsystem does not meet the requirements of 3.6.7.1.2.1.4 and 3.6.7.1.2.2.2, the ground subsystem shall indicate using the RSDS parameter that the GBAS positioning service is not provided.

3.6.7.2.3.9 If the VHF data broadcast is transmitted at more than one frequency within the GRAS service area, each GBAS broadcast station within the GRAS ground subsystem shall broadcast additional data blocks 1 and 2.

3.6.7.2.3.9.1 Recommendation. — The VHF data broadcast should include additional data block 2 parameters to identify channel numbers and locations of adjacent and nearby GBAS broadcast stations within the GRAS ground subsystem.

3.6.7.2.4 Final approach segment data

3.6.7.2.4.1 FAS data points accuracy. The relative survey error between the FAS data points and the GBAS reference point shall be less than 0.25 metres vertical and 0.40 metres horizontal.

426CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.6.7.2.4.2 Recommendation. — The final approach segment CRC should be assigned at the time of procedure design, and kept as an integral part of the FAS data block from that time onward.

3.6.7.2.4.3 Recommendation. — The GBAS should allow the capability to set the FASVAL and FASLAL for any FAS data block to “1111 1111” to limit the approach to lateral only or to indicate that the approach must not be used, respectively.

3.6.7.2.4.4 LTP/FTP for FAST D. For an approach that supports GAST D, the LTP/FTP point in the corresponding FAS definition shall be located at the intersection of the runway centre line and the landing threshold.

Note.: Airborne systems may compute the distance to the landing threshold using the LTP/FTP. For GAST D approaches, the LTP/FTP is to be at the threshold so that these distance-to-go computations reliably reflect the distance to the threshold.

3.6.7.2.4.5 FPAP location for FAST D. For an approach that supports GAST D, the FPAP point in the corresponding FAS definition shall be located on the extended runway centre line and the ΔLength offset parameter shall be coded to correctly indicate the stop end of the runway.

3.6.7.2.5 Predicted ranging source availability data Note.: Ranging source availability data are optional for FAST A, B, C or D ground subsystems and may be required for possible future operations.

3.6.7.2.6 General functional requirements on augmentation

3.6.7.2.6.1 Recommendation. — GBAS ground subsystems classified as FAST C or FAST D should provide augmentation based on GPS at a minimum.

3.6.7.2.6.2 Recommendation. — Ground subsystems classified as FAST C should be able to process and broadcast corrections for at least 12 satellites of each core constellation for which differential corrections are provided.

3.6.7.2.6.3 Ground subsystems classified as FAST D shall be able to process and broadcast differential corrections for at least 12 satellites of one core constellation.

Note.: Technical validation has only been completed for GAST D when applied to GPS.

3.6.7.2.6.4 Recommendation. — Whenever possible, differential corrections for all visible satellites with an elevation greater than 5 degrees above the local horizontal plane tangent to the ellipsoid at the ground subsystem reference location should be provided for each core constellation for which augmentation is provided.

427CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.:— The phrase “whenever possible” in this context means whenever meeting another requirement in these SARPs (e.g. 3.6.7.3.3.1) does not preclude providing a differential correction for a particular satellite.

3.6.7.3 MONITORING

3.6.7.3.1 RF monitoring

3.6.7.3.1.1 VHF data broadcast monitoring. The data broadcast transmissions shall be monitored. The transmission of the data shall cease within 0.5 seconds in case of continuous disagreement during any 3-second period between the transmitted application data and the application data derived or stored by the monitoring system prior to transmission. For FAST D ground subsystems, the transmission of Type 11 messages shall cease within 0.5 seconds in case of continuous disagreement during any 1- second period between the transmitted application data and the application data derived or stored by the monitoring system prior to transmission.

Note.: For ground subsystems that support authentication, ceasing the transmission of data means ceasing the transmission of Type 1 messages and/or Type 11 messages if applicable or ceasing the transmission of Type 101 messages. In accordance with 3.6.7.4.1.3, the ground subsystem must still transmit messages such that the defined percentage or more of every assigned slot is occupied. This can be accomplished by transmitting Type 2, Type 3, Type 4 and/or Type 5 messages.

3.6.7.3.1.2 TDMA slot monitoring. The risk that the ground subsystem transmits a signal in an unassigned slot and fails to detect an out-of-slot transmission, which exceeds that allowed in 3.6.2.6, within 1 second, shall be less than 1 × 10–7 in any 30-second period. If out-of-slot transmissions are detected, the ground subsystem shall terminate all data broadcast transmissions within 0.5 seconds.

3.6.7.3.1.3 VDB transmitter power monitor. The probability that the horizontally or elliptically polarized signal’s transmitted power increases by more than 3 dB from the nominal power for more than 1 second shall be less than 2.0 × 10–7 in any 30-second period.

Note.:— The vertical component is only monitored for GBAS/E equipment.

3.6.7.3.2 Data monitoring

3.6.7.3.2.1 Broadcast quality monitor. The ground subsystem monitoring shall comply with the time-to-alert requirements given in 3.6.7.1.2.1. The

monitoring action shall be one of the following:

428CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 a) to broadcast Type 1 (and Type 11 if broadcast) or Type 101 messages with no measurement blocks; or b) to broadcast Type 1 (and Type 11 if broadcast) or Type 101 messages with the σpr_gnd,i (and σpr_gnd_D,I if broadcast) field set to indicate the ranging source is invalid for every ranging source included in the previously transmitted frame; or c) to terminate the data broadcast.

Note.:— Monitoring actions a) and b) are preferred to c) if the particular failure mode permits such a response, because actions a) and b) typically have a reduced signal-in-space time-to-alert.

3.6.7.3.3 Integrity monitoring for GNSS ranging sources

3.6.7.3.3.1 The ground subsystem shall monitor the satellite signals to detect conditions that will result in improper operation of differential processing for airborne receivers complying with the tracking constraints in Attachment D, 8.11. The monitor time-to-alert shall comply with 3.6.7.1.2.

The monitor action shall be to set σpr_gnd to the bit pattern “1111 1111” for the satellite or to exclude the satellite from the Type 1, Type 11 or Type 101 message.

3.6.7.3.3.1.1 The ground subsystem shall use the strongest correlation peak in all receivers used to generate the pseudorange corrections. The ground subsystem shall also detect conditions that cause more than one zero crossing for airborne receivers that use the early-late discriminator function as described in Attachment D, 8.11.

3.6.7.3.3.2 For FAST D ground subsystems, the probability that the error at the landing threshold point (LTP) of any runway for which the ground subsystem supports GAST D, |Er|, on the 30-second smoothed corrected pseudo-range (see 3.6.5.2) caused by a ranging source fault, is not detected and reflected in the broadcast Type 11 message within 1.5 s shall fall within the region specified in Table B-149. Ranging source faults

for which this requirement applies are: a) signal deformation (Note 1.); b) code/carrier divergence; c) excessive pseudo-range acceleration, such as a step or other rapid change; and d) erroneous broadcast of ephemeris data from the satellite.

Note 1.— Refer to Attachment D, 8.11 for further information on GAEC-D avionics 429CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 relating to signal deformation fault.

Note 2.— Upon detection, a ranging source fault may be reflected in the Type 11

message by either: a) removing the correction for the associated satellite from the Type 11 message; or b) marking the satellite as invalid using the coding of σpr_gnd_D (see

3.6.4.11.4).

Note 3. — The acceptable probability of a missed detection region is defined with respect to differentially corrected pseudorange error. The differentially corrected pseudo-range error, |Er|, includes the error resulting from a single ranging source fault, given the correct application of GBAS ground subsystem message Type 11 broadcast corrections (i.e. pseudo-range correction and range rate corrections defined in 3.6.4.11) by the aircraft avionics as specified within 3.6.8.3. Evaluation of Pmd performance includes GBAS ground subsystem fault-free noise. The growth of |Er| with time should consider the data latency of the ground subsystem, but not the airborne latency, as described in Attachment D, 7.5.14.

Note 4.— Additional information regarding the ranging source fault conditions and monitoring requirements for FAST D ground subsystems may be found in Attachment D, 7.5.14. Missed messages do not need to be considered as part of compliance with this requirement.

3.6.7.3.3.3 For FAST D ground subsystems, the probability that an error at the landing threshold point (LTP) of any runway for which the ground subsystem supports GAST D, |Er|, greater than 1.6 metres on the 30- second smoothed corrected pseudo-range (see 3.6.5.2), caused by a ranging source fault, is not detected and reflected in the broadcast Type 11 message within 1.5 seconds shall be less than 1 × 10−9 in any one landing when multiplied by the prior probability (Papriori). Ranging source

faults for which this requirement applies are: a) signal deformation (Note 1); b) code/carrier divergence;

430CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 c) excessive pseudo-range acceleration, such as a step or other rapid change; and d) erroneous broadcast of ephemeris data from the satellite.

Note 1. — Refer to Attachment D, 8.11 for further information on GAEC-D avionics relating to signal deformation fault.

Note 2. — It is intended that the prior probability of each ranging source fault

(Papriori) be the same value that is used in the analysis to show compliance with error bounding requirements for FAST C and D (see Appendix B, 3.6.5.5.1.1.1).

Note 3.— Upon detection, a ranging source fault may be reflected in the Type 11

message by either: a) removing the faulty satellite correction from the Type 11 message; or b) marking the satellite as invalid using the coding of σ _gnd_D (see pr

3.6.4.11.4).

Note 4. — Additional information regarding the ranging source fault conditions and monitoring requirements for FAST D ground subsystems may be found in Attachment D, 7.5.14. Missed messages do not need to be considered as part of compliance with this requirement.

3.6.7.3.4 Ionospheric gradient mitigation For FAST D ground subsystems, the probability of an error (|Er|) in the 30-second smoothed corrected pseudo-range at the landing threshold point (LTP) for every GAST D supported runway that: a) is caused by a spatial ionospheric delay gradient, b) is greater than the EIG value computed from a broadcast Type 2 message, and c) is not detected and reflected in the broadcast Type 11 message within 1.5 seconds shall be less than 1 × 10−9 in any one landing. The FAST D ground subsystem shall limit the Type 2 broadcast parameters to ensure that the maximum EIG at every LTP supporting GAST D operations shall not exceed 2.75 metres, except when operational requirements are demonstrated to permit it.

Note 1. — The total probability of an undetected delay gradient includes the prior probability of the gradient and the monitor(s) probability of missed detection.

Note 2. — Validation guidance for ionospheric gradient mitigation can be found in

7.5.6.1.8.

Note 3.— To roadcast Type 2 parameters such that EIG exceeds 2.75 m for a specific LTP supporing GAST D operations, a tailored analysis will 431CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 demonstrate that the resulting GST D continuity and availability supports the intended operation. Guidance for assessing acceptability of EIG exceeding 2.75 m can be found in 7.5.13.1.

3.6.7.4 FUNCTIONAL REQUIREMENTS FOR AUTHENTICATION PROTOCOLS

3.6.7.4.1 Functional requirements for ground subsystems that support authentication

3.6.7.4.1.1 The ground system shall broadcast the additional data block 4 with the Type 2 message with the slot group definition field coded to indicate which slots are assigned to the ground station.

3.6.7.4.1.2 The ground subsystem shall broadcast every Type 2 message only in one of a set of slots defined as the MT 2 sanctioned slots. The first slot in the group of MT 2 sanctioned slots corresponds to the SSID coding for the ground subsystem. Slot A is represented by SSID = 0, B by 1, C by 2, and H by 7. The group of MT 2 sanctioned slots then also includes the next slot after the slot corresponding to the station SSID if it exists in the frame. If there is not an additional slot before the end of the frame, only the SSID is included in the set.

Note.: For example, the MT 2 sanctioned slot group for SSID = 0 would include slots {A, B} while the MT 2 sanctioned slot group for SSID = 6 would include slots {G, H}. The MT 2 sanctioned slot group for SSID = 7 includes slot {H} only.

3.6.7.4.1.2.1 The set of slots assigned to a ground station shall include at a minimum all the slots in the MT 2 sanctioned slots as described in 3.6.7.4.1.2.

3.6.7.4.1.3 Assigned slot occupancy. The ground subsystem shall transmit messages such that 89 per cent or more of every assigned slot is occupied. If necessary, Type 3 messages may be used to fill unused space in any assigned time slot.

Note 1. — More information on the calculation of the slot occupancy is provided in Attachment D, 7.21.

Note 2. — The requirement applies to the aggregate transmissions from all transmitters of a GBAS ground subsystem. Due to signal blockage, not all of those transmissions may be received in the service volume.

3.6.7.4.1.4 Reference path identifier coding. Every reference path identifier included in every final approach segment data block broadcast by the ground subsystem via the Type 4 messages shall have the first letter selected to indicate the SSID of the ground subsystem in accordance with the following coding.

432CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

Coding: A = SSID of 0 X = SSID of 1 Z = SSID of 2 J = SSID of 3 C = SSID of 4 V = SSID of 5 P = SSID of 6 T = SSID of 7

3.6.7.4.2 Functional requirements for ground subsystems that do not support authentication

3.6.7.4.2.1 Reference path identifier coding. Characters in this set: {A X Z J C V P T} shall not be used as the first character of the reference path identifier included in any FAS block broadcast by the ground subsystem via the Type 4 messages.

3.6.8 AIRCRAFT ELEMENTS

3.6.8.1 GNSS receiver. The GBAS-capable GNSS receiver shall process signals of GBAS in accordance with the requirements specified in this section as well as with requirements in 3.1.3.1 and/or 3.2.3.1 and/or 3.5.8.1.

Note.:— In order to ensure the required performance and functional objectives for GAST D are achieved, it is necessary for the airborne equipment to meet defined performance and functional standards. The relevant minimum operational performance standards are detailed in RTCA DO-253D.

3.6.8.2 PERFORMANCE REQUIREMENTS

3.6.8.2.1 GBAS aircraft receiver accuracy

3.6.8.2.1.1 The RMS of the total aircraft receiver contribution to the error for GPS

and GLONASS shall be: where n = the nth ranging source;

433CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 θn = the elevation angle for the nth ranging source; and a0, a1, and θ0 = as defined in Table B-150 for GPS and Table B-151 for GLONASS.

3.6.8.2.1.2 The RMS of the total aircraft receiver contribution to the error for SBAS satellites shall be as defined in 3.5.8.2.1 for each of the defined aircraft accuracy designators.

Note.: The aircraft receiver contribution does not include the measurement error induced by airframe multipath.

3.6.8.2.2 VHF data broadcast receiver performance

3.6.8.2.2.1 VHF data broadcast tuning range. The VHF data broadcast receiver shall be capable of tuning frequencies in the range of 108.000 – 117.975 MHz in increments of 25 kHz.

3.6.8.2.2.2 VHF data broadcast capture range. The VHF data broadcast receiver shall be capable of acquiring and maintaining lock on signals within ±418 Hz of the nominal assigned frequency.

Note.:— The frequency stability of the GBAS ground subsystem, and the worst- case doppler shift due to the motion of the aircraft, are reflected in the above requirement. The dynamic range of the automatic frequency control should also consider the frequency-stability error budget of the aircraft VHF data broadcast receiver.

434CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.6.8.2.2.3 VHF data broadcast message failure rate. The VHF data broadcast receiver shall achieve a message failure rate less than or equal to one failed message per 1 000 full-length (222 bytes) application data messages, within the range of the RF field strength defined in Chapter 3,

3.7.3.5.4.4 as received by the airborne antenna. This requirement shall apply when the variation in the average received signal power between successive bursts in a given time slot does not exceed 40 dB. Failed messages include those lost by the VHF data broadcast receiver system or which do not pass the CRC after application of the FEC.

Note 1. — An aircraft VHF data broadcast receiving antenna can be horizontally or vertically polarized. Due to the difference in the signal strength of horizontally and vertically polarized components of the broadcast signal, the maximum total aircraft implementation loss for horizontally polarized receiving antennas is 4 dB higher than the maximum loss for vertically polarized receiving antennas. For guidance in determining aircraft implementation loss see Attachment D, 7.2.

Note 2. — It is acceptable to exceed the signal power variation requirement in limited parts of the service volume when operational requirements permit. Refer to Attachment D, 7.12.4.1 for guidance.

3.6.8.2.2.4 VHF data broadcast time slot decoding. The VHF data broadcast receiver shall meet the requirements of 3.6.8.2.2.3 for all message types required (see 3.6.8.3.1.2.1) from the selected GBAS ground subsystem. These requirements shall be met in the presence of other GBAS transmissions in any and all time slots respecting the levels as indicated in 3.6.8.2.2.5.1 b).

Note.: Other GBAS transmissions may include: a) other message types with the same SSID, and b) messages with different SSIDs.

3.6.8.2.2.5 Co-channel rejection

3.6.8.2.2.5.1 VHF data broadcast as the undesired signal source. The VHF data broadcast receiver shall meet the requirements specified in 3.6.8.2.2.3 in the presence of an undesired co-channel VHF data broadcast signal that

is either: a) assigned to the same time slot(s) and 26 dB below the desired VHF data broadcast signal power at the receiver input or lower; or b) assigned different time slot(s) and no more than 72 dB above the minimum desired VHF data broadcast signal field strength defined in

3.7.3.5.4.4 .

3.6.8.2.2.5.2 VOR as the undesired signal. The VHF data broadcast receiver shall meet the requirements specified in 3.6.8.2.2.3 in the presence of an 435CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 undesired co-channel VOR signal that is 26 dB below the desired VHF data broadcast signal power at the receiver input.

3.6.8.2.2.5.3 ILS localizer as the undesired signal. The VHF data broadcast receiver shall meet the requirements specified in 3.6.8.2.2.3 in the presence of an undesired co-channel ILS localizer signal that is 26 dB below the desired VHF data broadcast signal power at the receiver input.

3.6.8.2.2.6 Adjacent channel rejection. The level of ILS localizer or VOR undesired signals shall be measured as the power in the RF carrier.

Note.: Even though Smax is the maximum desired VHF data broadcast signal power, it is also used to limit the maximum adjacent channel undesired signal power at the receiver input.

3.6.8.2.2.6.1 First adjacent 25 kHz channels (±25 kHz). The VHF data broadcast receiver shall meet the requirements specified in 3.6.8.2.2.3 in the presence of an undesired signal with power levels at the receiver input up to Smax offset by 25 kHz on either side of the desired channel that is

either: a) 18 dB above the desired signal power at the receiver input when the undesired signal is another VHF data broadcast signal assigned to the same time slot(s); or b) equal in power at the receiver input when the undesired signal is VOR; or c) equal in power at the receiver input when the undesired signal is ILS localizer.

3.6.8.2.2.6.2 Second adjacent 25 kHz channels (±50 kHz). The VHF data broadcast receiver shall meet the requirements specified in 3.6.8.2.2.3 in the presence of an undesired signal with power levels at the receiver input up to Smax offset by 50 kHz on either side of the desired channel that is

either: a) 43 dB above the desired signal power at the receiver input when the undesired signal is another VHF data broadcast source assigned to the same time slot(s); or b) 34 dB above the desired signal power at the receiver input when the undesired signal is VOR; or c) 34 dB above the desired signal power at the receiver input when the undesired signal is ILS localizer.

3.6.8.2.2.6.3 Third up to thirty-ninth adjacent 25 kHz channels (±75 kHz to ±975 kHz).

The VHF data broadcast receiver shall meet the requirements specified in 3.6.8.2.2.3 in the presence of an undesired signal with the power levels 436CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 at the receiver input up to Smax offset by 75 kHz to 975 kHz on either

side of the desired channel that is either: a) 46 dB above the desired signal power at the receiver input when the undesired signal is another VHF data broadcast signal assigned to the same time slot(s); or b) 46 dB above the desired signal power at the receiver input when the undesired signal is VOR; or c) 46 dB above the desired signal power at the receiver input when the undesired signal is ILS localizer.

3.6.8.2.2.6.4 Fortieth and beyond adjacent 25 kHz channels (±1 MHz or more). The VHF data broadcast receiver shall meet the requirements specified in

3.6.8.2.2.3 in the presence of an undesired signal offset by 1 MHz or

more on either side of the desired channel that is either: a) 46 dB above the desired signal power at the receiver input when the undesired signal with power levels at the receiver input up to Smax is another VHF data broadcast signal assigned to the same time slot(s); or b) 46 + ΔP dB above the desired signal power at the receiver input when the undesired signal is a VOR with power levels at the receiver input up to Smax – ΔP dB and ΔP ranges from 0 to 14 dB; or c) 46 + ΔP dB above the desired signal power at the receiver input when the undesired signal is an ILS localizer with power levels at the receiver input up to Smax – ΔP dB and ΔP ranges from 0 to 14 dB.

Note 1.— ΔP equals Smax minus the undesired signal power at the receiver input with the following two constraints. ΔP equals 0 dB when the undesired power reaches Smax. ΔP equals 14 dB when the undesired power is 14 dB or more below Smax.

Note 2.— The requirements in items b) and c) accommodate a third order intermodulation between the undesired signal and the local oscillator in the first mixer of the RF front-end of the VDB receiver; it is similar to the FM intermodulation immunity in 3.6.8.2.2.8.3 where N1 is the undesired signal and N2 is the local oscillator.

3.6.8.2.2.6.5 Receiver recovery from short-term excess undesired signal power. The VHF data broadcast receiver shall meet the requirements specified in

3.6.8.2.2.3 within 187.5 milliseconds (equivalent duration of three VDB slots) after encountering an adjacent channel interference signal (ILS localizer or VOR) whose power is above Smax for no more than 2.5 seconds and by no more than 9 dB at the receiver input.

437CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note 1.— This requirement supports brief excessive power received during ILS localizer and VOR overflight. The duration of the excess power is limited by the continuity of the operation, e.g. the opportunity to receive three Type 1 messages in every 3.5 second window (refer to 3.6.8.3.4.1) without excess power for GAST C. For GAST D, no excess power is allowed when the timeout is 1.5 seconds (refer to 3.6.8.3.4.3). A VDB undesired signal never exceeds the maximum allowed field strength of the desired VDB signal within the service volume.

Note 2.— Figure B-30 shows a graphical representation of the VDB receiver regions of operation in the presence of an undesired ILS localizer or VOR signal in the fortieth or beyond adjacent 25 kHz channel, as a function of D/U and undesired signal power.

3.6.8.2.2.7 Rejection of off-channel signals from sources inside the 108.000 –

117.975 MHz band. With no on-channel VHF data broadcast signal present, the VHF data broadcast receiver shall not output data from an undesired VHF data broadcast signal on any other assignable channel.

3.6.8.2.2.8 Rejection of signals from sources outside the 108.000 – 117.975 MHz band

3.6.8.2.2.8.1 VHF data broadcast interference immunity. The VHF data broadcast receiver shall meet the requirements specified in 3.6.8.2.2.3 in the presence of one or more signals having the frequency and total interference levels specified in Table B-152.

3.6.8.2.2.8.2 Desensitization. The VHF data broadcast receiver shall meet the requirements specified in 3.6.8.2.2.3 in the presence of VHF FM broadcast signals with signal levels shown in Tables B-153 and B-154.

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3.6.8.2.2.8.3 VHF data broadcast FM intermodulation immunity. The VHF data broadcast receiver shall meet the requirements specified in 3.6.8.2.2.3 in the presence of interference from two-signal, third-order intermodulation products of two VHF FM broadcast signals having levels in accordance

with the following:

2N1 + N2 + 3 [23 − Smax] ≤ 0 for VHF FM sound broadcasting signals in the range 107.7 – 108.0 MHz and 2N1 + N2 + 3 [23 - Smax − 20 Log (Δf / 0.4)] ≤ 0 for VHF FM sound broadcasting signals below 107.7 MHz where the frequencies of the two VHF FM sound broadcasting signals produce, within the receiver, a two signal, third-order intermodulation product on the desired VDB frequency.

N1 and N2 are the levels (dBm) of the two VHF FM sound broadcasting signals at the VHF data broadcast receiver input. Neither level shall exceed the desensitization criteria set forth in 3.6.8.2.2.8.2.

Δf = 108.1 – f1, where f1 is the frequency of N1, the VHF FM sound broadcasting signal closer to 108.1 MHz.

Smax is the maximum desired VHF data broadcast signal power at the receiver input.

440CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.: The FM intermodulation immunity requirements are not applied to a VHF data broadcast channel operating below 108.1 MHz, hence frequencies below 108.1 MHz are not intended for general assignments. Additional information is provided in Attachment D, 7.2.1.2.

3.6.8.3 AIRCRAFT FUNCTIONAL REQUIREMENTS Note.:— Unless otherwise specified, the following requirements apply to all GBAS airborne equipment classifications as described in Attachment D, 7.1.4.3.

3.6.8.3.1 Conditions for use of data

3.6.8.3.1.1 The receiver shall use data from a GBAS message only if the CRC of that message has been verified.

3.6.8.3.1.2 The receiver shall use message data only if the message block identifier is set to the bit pattern “1010 1010”.

3.6.8.3.1.2.1 GBAS message processing capability. The GBAS receiver shall at a minimum process GBAS message types in accordance with Table B-155.

3.6.8.3.1.2.2 Airborne processing for forward compatibility Note.: Provisions have been made to enable future expansion of the GBAS Standards to support new capabilities. New message types may be defined, new additional data blocks for message Type 2 may be defined and new data blocks defining reference paths for inclusion within message Type 4 may be defined. To facilitate these future expansions, all equipment should be designed to properly ignore all data types that are not recognized.

3.6.8.3.1.2.2.1 Processing of unknown message types. The existence of messages unknown to the airborne receiver shall not prevent correct processing of the required messages.

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3.6.8.3.1.2.2.2 Processing of unknown Type 2 extended data blocks. The existence of message Type 2 additional data blocks unknown to the airborne receiver shall not prevent correct processing of the required messages.

3.6.8.3.1.2.2.3 Processing of unknown Type 4 data blocks. The existence of message Type 4 data blocks unknown to the airborne receiver shall not prevent correct processing of the required messages.

Note.: While the current SARPs include only one definition of a data block for inclusion within a Type 4 message, future GBAS Standards may include other reference path definitions.

3.6.8.3.1.3 The receiver shall use only ranging source measurement blocks with matching modified Z-counts.

3.6.8.3.1.4 If Dmax is broadcast by the ground subsystem, the receiver shall only apply pseudo-range corrections when the distance to the GBAS reference point is less than Dmax.

3.6.8.3.1.5 The receiver shall only apply pseudo-range corrections from the most recently received set of corrections for a given measurement type. If the number of measurement fields in the most recently received message types (as required in Appendix B, 3.6.7.2.1.1.1 for the active service type) indicates that there are no measurement blocks, then the receiver shall not apply GBAS corrections for that measurement type.

3.6.8.3.1.6 Validity of pseudo-range corrections

3.6.8.3.1.6.1 When the active service type is A, B or C, the receiver shall exclude from the differential navigation solution any ranging sources for which σpr_gnd in the Type 1 or Type 101 messages is set to the bit pattern “1111 1111”.

3.6.8.3.1.6.2 If the active service type is D, the receiver shall exclude from the differential navigation solution any ranging source for which σpr_gnd_D in the Type 11 message or σpr_gnd in the Type 1 message is set to the bit pattern “1111 1111”.

3.6.8.3.1.7 The receiver shall only use a ranging source in the differential navigation solution if the time of applicability indicated by the modified Z-count in the Type 1, Type 11 or Type 101 message containing the ephemeris decorrelation parameter for that ranging source is less than 120 seconds old.

3.6.8.3.1.8 Conditions for use of data to support approach services

3.6.8.3.1.8.1 During the final stages of an approach, the receiver shall use only measurement blocks from Type 1, Type 11 or Type 101 messages that were received within the last 3.5 seconds.

442CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.:— Guidance concerning time-to-alert is given in Attachment D, 7.5.14.

3.6.8.3.1.8.2 GCID indications

3.6.8.3.1.8.2.1 When the active service type is A, B or C, the receiver shall use message data from a GBAS ground subsystem for guidance only if the GCID indicates 1, 2, 3 or 4 prior to initiating the final stages of an approach.

3.6.8.3.1.8.2.2 When the active service type is D, the receiver shall use message data from a GBAS ground subsystem for guidance only if the GCID indicates 2, 3 or 4 prior to initiating the final stages of an approach.

3.6.8.3.1.8.3 The receiver shall ignore any changes in GCID during the final stages of an approach.

3.6.8.3.1.8.4 The receiver shall not provide approach vertical guidance based on a particular FAS data block transmitted in a Type 4 message if the FASVAL received prior to initiating the final stages of the approach is set to “1111 1111”.

3.6.8.3.1.8.5 The receiver shall not provide approach guidance based on a particular FAS data block transmitted in a Type 4 message if the FASLAL received prior to initiating the final stages of the approach is set to “1111 1111”.

3.6.8.3.1.8.6 Changes in the values of FASLAL and FASVAL data transmitted in a Type 4 message during the final stages of an approach shall be ignored by the receiver.

3.6.8.3.1.8.7 The receiver shall use FAS data only if the FAS CRC for that data has been verified.

3.6.8.3.1.8.8 The receiver shall only use messages for which the GBAS ID (in the message block header) matches the GBAS ID in the header of the Type 4 message which contains the selected FAS data or the Type 2 message which contains the selected RSDS.

3.6.8.3.1.8.9 Use of FAS data

3.6.8.3.1.8.9.1 The receiver shall use the Type 4 messages to determine the FAS for precision approach.

3.6.8.3.1.8.9.2 The receiver shall use the Type 4 messages to determine the FAS for approaches which are supported by GBAS approach service type

(GAST) A or B associated with a channel number between 20 001 and 39 999.

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3.6.8.3.1.8.9.3 The receiver shall use the FAS held within the on-board database for approaches which are supported by GBAS approach service type

(GAST) A associated with a channel number between 40 000 and 99

999.

3.6.8.3.1.8.10 When the GBAS ground subsystem does not broadcast the Type 4 message and the selected FAS data are available to the receiver from an airborne database, the receiver shall only use messages from the intended GBAS ground subsystem.

3.6.8.3.1.9 Conditions for use of data to provide the GBAS positioning service

3.6.8.3.1.9.1 The receiver shall only use measurement blocks from Type 1 messages that were received within the last 7.5 seconds.

3.6.8.3.1.9.2 The receiver shall only use measurement blocks from Type 101 messages that were received within the last 5 seconds.

3.6.8.3.1.9.3 The receiver shall only use message data if a Type 2 message containing additional data block 1 has been received and the RSDS parameter in this block indicates that the GBAS positioning service is provided.

3.6.8.3.1.9.4 The receiver shall only use messages for which the GBAS ID (in the message block header) matches the GBAS ID in the header of the Type 2 message which contains the selected RSDS.

3.6.8.3.2 Integrity

3.6.8.3.2.1 Bounding of aircraft errors. For each satellite used in the navigation solution, the receiver shall compute a σreceiver such that a normal distribution with zero mean and a standard deviation equal to σreceiver bounds the receiver contribution to the corrected pseudo-range error as

follows: where f(x) = probability density function of the residual aircraft pseudo-range error and 444CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.6.8.3.2.2 Use of GBAS integrity parameters. The aircraft element shall compute and apply the vertical, lateral and horizontal protection levels described in 3.6.5.5. If a Bi,j parameter is set to the bit pattern “1000 0000” indicating that the measurement is not available, the aircraft element shall assume that Bi,j has a value of zero. For any active service type, the aircraft element shall verify that the computed vertical and lateral protection levels are no larger than the corresponding vertical and lateral alert limits defined in 3.6.5.6.

3.6.8.3.3 Use of satellite ephemeris data

3.6.8.3.3.1 IOD check. The receiver shall only use satellites for which the IOD broadcast by GBAS in the Type 1 or Type 101 message matches the core satellite constellation IOD for the clock and ephemeris data used by the receiver.

3.6.8.3.3.2 CRC check. The receiver shall compute the ephemeris CRC for each core satellite constellation’s ranging source used in the position solution.

The computed CRC shall be validated against the ephemeris CRC broadcast in the Type 1 or Type 101 messages prior to use in the position solution and within one second of receiving a new broadcast CRC. The receiver shall immediately cease using any satellite for which the computed and broadcast CRC values fail to match.

3.6.8.3.3.3 Ephemeris error position bounds

3.6.8.3.3.3.1 Ephemeris error position bounds for GBAS approach services. If the ground subsystem provides additional data block 1 in the Type 2 messages, the aircraft element shall compute the ephemeris error position bounds defined in 3.6.5.8.1 for each core satellite constellation’s ranging source used in the approach position solution within 1s of receiving the necessary broadcast parameters. The aircraft element shall verify that the computed vertical and lateral ephemeris error position bounds (VEBj and LEBj) are no larger than the corresponding vertical and lateral alert limits defined in 3.6.5.6.

3.6.8.3.3.3.2 Ephemeris error position bound for the GBAS positioning service. The aircraft element shall compute and apply the horizontal ephemeris error position bound (HEBj) defined in 3.6.5.8.2 for each core satellite constellation’s ranging source used in the positioning service position solution.

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3.6.8.3.4 Message loss

3.6.8.3.4.1 For airborne equipment operating with GAST C as the active service type, the receiver shall provide an appropriate alert if no Type 1 message was received during the last 3.5 seconds.

3.6.8.3.4.2 For airborne equipment operating with GAST A or B as the active service type, the receiver shall provide an appropriate alert if no Type 1 and no Type 101 message was received during the last 3.5 seconds.

3.6.8.3.4.3 For the airborne equipment operating with GAST D as the active service type, the receiver shall provide an appropriate alert or modify the active

service type if any of the following conditions are met: a) The computed position solution is less than 200 ft above the LTP/FTP for the selected approach and no Type 1 message was received during the last 1.5 seconds.

b) The computed position solution is less than 200 ft above the LTP/FTP for the selected approach and no Type 11 message was received during the last 1.5 seconds. c) The computed position solution is 200 ft or more above the LTP/FTP of the selected approach and no Type 1 message was received during the last 3.5 seconds.

d) The computed position solution is 200 ft or more above the LTP/FTP of the selected approach and no Type 11 message was received during the last 3.5 seconds.

3.6.8.3.4.4 For the GBAS positioning service using Type 1 messages, the receiver shall provide an appropriate alert if no Type 1 message was received during the last 7.5 seconds.

3.6.8.3.4.5 For the GBAS positioning service using Type 101 messages, the receiver shall provide an appropriate alert if no Type 101 message was received during the last 5 seconds.

3.6.8.3.5 Airborne pseudo-range measurements

3.6.8.3.5.1 Carrier smoothing for airborne equipment. Airborne equipment shall utilize the standard 100-second carrier smoothing of code phase measurements defined in 3.6.5.1. During the first 100 seconds after filter start-up, the value of shall be either:

a) a constant equal to the sample interval divided by 100 seconds; or 446CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 b) a variable quantity defined by the sample interval divided by the time in seconds since filter start-up.

3.6.8.3.5.2 Carrier smoothing of airborne equipment operating with GAST D as the active service type. Airborne equipment operating with GAST D as the active service type shall utilize 30-second carrier smoothing of code phase measurements as defined in 3.6.5.1.

Note.: For equipment that supports GAST D, two sets of smoothed pseudo- ranges are used. The form of the smoothing filter given in 3.6.5.1 is the same for both sets, and only the time constant differs (i.e. 100 seconds and 30 seconds). Guidance concerning carrier-smoothing for GAST D is given in Attachment D, 7.19.3.

3.6.8.3.6 Service type specific differential position solution requirements. The airborne equipment shall compute all position solutions in a manner that is consistent with the protocols for application of the data (see

3.6.5.5.1.1.2).

Note.: The general form for the weighting used in the differential position solution is given in 3.6.5.5.1.1.2. Exactly which information from the ground subsystem is used in the differential position solution depends on the type of service (i.e. positioning service vs. approach service) and the active approach service type. The specific requirements for each service type are defined in RTCA DO 253D. Additional information concerning the normal processing of position information is given in Attachment D, 7.19.

3.7 Resistance to interference

3.7.1 PERFORMANCE OBJECTIVES Note 1. — For GNSS receivers not using differential corrections from an augmentation system, the resistance to interference is measured with respect to the following core satellite constellation performance

parameters:

447CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note 2. — This tracking error neither includes contributions due to signal propagation such as multipath, tropospheric and ionospheric effects nor ephemeris and GPS, GLONASS, Galileo and BDS satellite clock errors.

Note 3. — For SBAS receivers, the resistance to interference is measured with respect to parameters specified in 3.5.8.2.1, 3.5.8.4.1 and 3.5.15.3.2.

Note 4. — For GBAS receivers, the resistance to interference is measured with respect to parameters specified in 3.6.7.1.1 and 3.6.8.2.1.

Note 5. — The signal levels specified in this section are defined at the antenna port.

Assumed maximum aircraft antenna gain in the lower hemisphere is –10 dBic.

Note 6. —The performance requirements are to be met in the interference environments defined below. This defined interference environment is relaxed during initial acquisition of GNSS signals when the receiver cannot 448CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 take advantage of a steady-state navigation solution to aid signal acquisition.

Note 7. — If not specified, the equipment performance objectives and requirements specified for a particular constellation apply whether the equipment supports only that constellation (single constellation equipment) or that constellation and other constellation(s) (multiple constellation equipment).

3.7.2 CONTINUOUS WAVE (CW) INTERFERENCE

3.7.2.1 GPS L1 AND SBAS L1 RECEIVERS Note.: Less interference power is tolerated by the interference thresholds for GPS L1 and SBAS L1 receivers than for the dual-frequency L1/L5 receivers in the band 1 480 – 1 565 MHz described in 3.7.2.3.

3.7.2.1.1 After steady-state navigation has been established, GPS L1 and SBAS L1 receivers shall meet the performance objectives with CW interfering signals present with a power level at the antenna port equal to the interference thresholds specified in Table B-156 and shown in Figure B-31 and with a desired GPS L1 and SBAS L1 level of –164 dBW at the antenna port.

3.7.2.1.2 During initial acquisition of the GPS L1 and SBAS L1 signals prior to steady- state navigation, GPS L1 and SBAS L1 receivers shall meet the performance objectives with interference thresholds 6 dB less than those specified in Table B-156.

3.7.2.2 GLONASS RECEIVERS

3.7.2.2.1 After steady-state navigation has been established, GLONASS FDMA signals receivers in L1 band (except those identified in 3.7.2.2.1.1) shall meet the performance objectives with CW interfering signals present with a power level at the antenna port equal to the interference thresholds specified in Table B-157 and shown in Figure B-32 and with a desired signal level –166.5 dBW at the antenna port.

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3.7.2.2.1.1 After steady-state navigation has been established, GLONASS FDMA signals receivers in L1 band used for all phases of flight (excluding those used for the precision approach phase of flight) and put into operation before 1 January 2017 shall meet the performance objectives with CW interfering signals present with a power level at the antenna port 3 dB less than the interference thresholds specified in Table B-157 and shown in Figure B-32 and with a desired signal level of –166.5 dBW at the antenna port.

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3.7.2.2.1.2 After steady-state navigation has been established, GLONASS CDMA signals receivers in L1 and L3 bands shall meet the performance objectives with CW interfering signals present with a power level at the antenna port equal to the interference thresholds specified in Tables B- 158 and B-159 and shown in Figures B-33 and B-34 and with a desired signal level of –161.5 dBW at the antenna port.

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3.7.2.2.2 During initial acquisition of the GLONASS FDMA signals in L1 band prior to steady-state navigation, GLONASS receivers shall meet the performance objectives with interference thresholds 6 dB less than those specified in Table B-157.

3.7.2.2.2.1 During initial acquisition of the GLONASS CDMA signals in L1 and L3 bands prior to steady-state navigation, GLONASS receivers shall meet the performance objectives with interference thresholds 6 dB less than those specified in Tables B-158 and B-159.

3.7.2.3 GPS L1/L5, GALILEO E1/E5A AND DFMC SBAS receivers

3.7.2.3.1 During initial L5/E5a acquisition prior to steady-state navigation, and after steady-state navigation has been established, DFMC SBAS receivers processing signals centred on L1/E1 and L5/E5a frequencies shall meet the performance objectives with CW interfering signals present with a power level at the antenna port equal to the interference thresholds specified in Table B-160 and shown in Figure B-35, and with a desired SBAS L5 signal level of –162.5 dBW, with a desired GPS L5 signal level of –159.4 dBW, and with a desired Galileo E5a signal level of –160.4 dBW at the antenna port.

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3.7.2.3.2 After steady-state navigation has been established, DFMC SBAS receivers processing signals centred on L1/E1 and L5/E5a frequencies shall meet the performance objectives with CW interfering signals present with a power level at the antenna port equal to the interference thresholds specified in Table B-160 and shown in Figure B-35, and with a desired GPS L1 and SBAS L1 signal level of –163 dBW and with a desired Galileo E1 signal level of –162.25 dBW at the antenna port. During initial L1/E1 acquisition, DFMC SBAS receivers shall meet the performance objectives with interference levels that are 6 dB below what is specified in Table B-160.

Note.:— CW interference thresholds for DMFC SBAS receivers determine the interference power levels applicable for the frequency ranges defined in Table B-160.

3.7.2.4 BDS RECEIVERS 453CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.7.2.4.1 After steady-state navigation has been established, BDS B1I receivers shall meet the performance objectives with CW interfering signals present with a power level at the antenna port equal to the interference thresholds specified in Table B-161 and shown in Figure B-36A and with a desired BDS signal level of –164.5 dBW at the antenna port. During initial acquisition prior to steady state navigation, BDS B1I receivers shall meet the performance objectives with 6 dB less than those specified in Table B-161.

3.7.2.4.2 After steady-state navigation has been established, BDS B1C/B2a receivers shall meet the performance objectives with a power level at the antenna port equal to the interference thresholds specified in Table B-162 and shown in Figure B-36B and with desired BDS signal levels of –163.5 dBW for B1C and –160.5 dBW for B2a at the antenna port. During initial acquisition prior to steady state navigation, BDS B1C/B2a receivers shall meet the performance objectives with 6 dB less than those specified in Table B-162.

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3.7.3 BAND-LIMITED NOISE-LIKE INTERFERENCE

3.7.3.1 GPS L1 AND SBAS L1 RECEIVERS

3.7.3.1.1 After steady-state navigation has been established, GPS L1 and SBAS L1 receivers shall meet the performance objectives with noise-like interfering signals present in the frequency range of 1 575.42 MHz ±Bwi/2 and with power levels at the antenna port equal to the interference thresholds specified in Table B-169 and shown in Figure B-37 and with the desired signal level of –164 dBW at the antenna port.

Note.: Bwi is the equivalent noise bandwidth of the interference signal.

3.7.3.1.2 During initial acquisition of the GPS L1 and SBAS L1 signals prior to steady- state navigation, GPS L1 and SBAS L1 receivers shall meet the 455CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 performance objectives with interference thresholds 6 dB less than those specified in Table B-83.

3.7.3.2 GLONASS RECEIVERS

3.7.3.2.1 After steady-state navigation has been established, GLONASS FDMA signals receivers in L1 band (except those identified in 3.7.3.2.1.1) shall meet the performance objectives while receiving noise-like interfering signals in the frequency band fk ±Bwi/2, with power levels at the antenna port equal to the interference thresholds specified in Table B-170 and shown in Figure B-38 and with a desired signal level of –166.5 dBW at the antenna port.

3.7.3.2.1.1 After steady-state navigation has been established, GLONASS FDMA signals receivers in L1 band used for all phases of flight (excluding those used for the precision approach phase of flight) and put into operation before 1 January 2017 shall meet the performance objectives while receiving noise-like interfering signals in the frequency band fk ±Bwi/2, with power levels at the antenna port 3 dB less than the interference thresholds specified in Table B-170 and shown in Figure B-38 and with a desired signal level of –166.5 dBW at the antenna port.

Note.: fk is the centre frequency of a GLONASS channel with fk = 1 602 MHz + k × 0.5625 MHz and k = –7 to + 6 as defined in Table B-15 and Bwi is the equivalent noise bandwidth of the interference signal.

3.7.3.2.1.2 After steady-state navigation has been established, GLONASS CDMA signals receivers in L1 and L3 bands shall meet the performance objectives while receiving noise-like interfering signals in the frequency band fk ±Bwi/2, with power levels at the antenna port equal to the interference thresholds specified in Tables B-163 and B-164 and shown in Figures B-39 and B-40 and with a desired signal level of –161.5 dBW at the antenna port.

3.7.3.2.2 During initial acquisition of the GLONASS FDMA signals receivers in L1 band prior to steady-state navigation, GLONASS receivers shall meet the performance objectives with interference thresholds 6 dB less than those specified in Table B-170.

3.7.3.2.2.1 During initial acquisition of the GLONASS CDMA signals in L1 and L3 bands prior to steady-state navigation, GLONASS receivers shall meet the performance objectives with interference thresholds 6 dB less than those specified in Tables B-163 and B-164.

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3.7.3.3 GPS L1/L5, GALILEO E1/E5A AND DFMC SBAS RECEIVER

3.7.3.3.1 During initial L5/E5a acquisition prior to steady-state navigation, and after steady-state navigation has been established, GPS L1/L5, Galileo E1/E5a and DFMC SBAS receivers processing signals centred on L1/E1 and L5/E5a frequencies shall meet the performance objectives with noise-like interfering signals present in the frequency range of 1 176.45 MHz ±Bwi/2 and with power levels at the antenna port equal to the interference thresholds specified in Table B-165 and shown in Figure B-41 and with a desired SBAS L5 signal level of –162.5 dBW, with a desired GPS L5 level of –159.4 dBW and with a desired Galileo E5a level of –160.4 dBW at the output of the antenna.

Note.: Bwi is the equivalent noise bandwidth of the interference signal.

3.7.3.3.2 After steady-state navigation has been established, GPS L1/L5, Galileo E1/E5a and DFMC SBAS receivers processing signals centred on L1/E1 and L5/E5a frequencies shall meet the performance objectives with noise- like interfering signals present in the frequency range of 1 575.42 MHz ±Bwi/2 and with power levels at the antenna port equal to the interference thresholds specified in Table B-169 and shown in Figure B-37 and with the desired GPS and SBAS L1 signal levels of –163 dBW and with the desired Galileo E1 signal level of –162.25 dBW at the antenna port. During initial 457CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 L1/E1 acquisition, DFMC SBAS receivers shall meet the performance objectives with interference thresholds 6 dB less than those specified in Table B-83.

Note.:— Bwi is the equivalent noise bandwidth of the interference signal.

3.7.3.4 BDS RECEIVERS

3.7.3.4.1 After steady-state navigation has been established, BDS B1I receivers shall meet the performance objectives with noise like interfering signals present in the frequency range of 1561.098 MHz ±Bwi/2 and with power levels at the antenna port equal to the interference thresholds specified in Table B-166 and shown in Figure B-42A and with a desired B1I signal level of –164.5 dBW at the output of the antenna. During initial acquisition of the BDS B1I signals prior to steady-state navigation, BDS receivers shall meet the performance objectives with interference thresholds 6 dB less than those specified in Table B-166.

Note.: Bwi is the equivalent noise bandwidth of the interference signal.

3.7.3.4.2 After steady-state navigation has been established, BDS B1C receivers shall meet the performance objectives with noise-like interfering signals present in the frequency range of 1 575.42 MHz ±Bwi/2 and with power levels at the antenna port equal to the interference thresholds specified in Table B-167 and shown in Figure B-42B and with a desired B1C signal level of –163.5 dBW at the output of the antenna. During initial acquisition of the BDS B1C signals prior to steady-state navigation, BDS receivers shall meet the performance objectives with interference thresholds 6 dB less than those specified in Table B-167.

Note.: Bwi is the equivalent noise bandwidth of the interference signal.

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3.7.3.4.3 After steady-state navigation has been established, BDS B2a receivers shall meet the performance objectives with noise-like interfering signals present in the frequency range of 1 176.45 MHz ±Bwi/2 and with power levels at the antenna port equal to the interference thresholds specified in Table B-168 and shown in Figure B-42C and with a desired B2a signal level of –160.5 dBW at the output of the antenna. During initial acquisition of the BDS B2a signals prior to steady-state navigation, BDS receivers shall meet the performance objectives with interference thresholds 6 dB less than those specified in Table B-168.

Note.: Bwi is the equivalent noise bandwidth of the interference signal.

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3.7.3.5 Pulsed interference. After steady-state navigation has been established, the GNSS receiver shall meet the performance objectives while receiving pulsed interference signals with characteristics according to Table B-171 where the interference threshold is defined at the antenna port.

3.7.3.6 GNSS receivers shall not output misleading information in the presence of interference including interference levels above those specified in 3.7.

Note.: Guidance material on this requirement is given in Attachment D, 10.5.

3.8 GNSS aircraft satellite receiver antenna

3.8.1 Antenna coverage. The GNSS antenna shall meet the performance requirements for the reception of GNSS satellite signals from 0 to 360 degrees in azimuth and from 0 to 90 degrees in elevation relative to the horizontal plane of an aircraft in level flight.

3.8.2 Antenna gain. The minimum passive antenna element gain for single-frequency antennas shall not be less than that shown in Table B-172 for the specified elevation angle above the horizon. For these antennas, the maximum passive antenna element gain shall not exceed +4 dBic for elevation angles above 5 degrees. The minimum passive antenna element gains at both frequencies for dual-frequency antennas shall comply with Table B-173 for the specified elevation angles above the horizon. For these antennas, the maximum passive antenna element gain shall be limited to +4 dBic for elevation angles above 75 degrees.

3.8.3 Polarization. The GNSS antenna polarization shall be right-hand circular (clockwise with respect to the direction of propagation).

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3.8.3.1 Axial ratio. For single-frequency antennas, the axial ratio shall not exceed

3.0 dB as measured at boresight. For dual-frequency antennas, the axial ratio shall be less than or equal to 3 dB over the operating frequency range as measured in a region extending from boresight down to 40 degrees off boresight across all azimuth angles.

3.9 Cyclic redundancy check Each CRC shall be calculated as the remainder, R(x), of the Modulo-2 division of

two binary polynomials as follows:

Where k = the number of bits in the particular CRC;

M(x) = the information field, which consists of the data items to be protected by the particular CRC represented as a polynomial;

G(x) = the generator polynomial specified for the particular CRC;

Q(x) = the quotient of the division; and R(x) = the remainder of the division, contains the CRC:

461CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 462CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 463CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 464CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 465CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 466CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 467CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 468CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 469CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 470CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 471CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 472CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 473CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 474CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 475CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 476CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 477CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 478CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 479CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 480CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 481CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 482CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 483CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 484CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 485CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 486CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 487CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 488CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 489CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 490CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 491CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 492CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 493CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 494CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 495CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 496CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 497CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 498CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 499CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 500CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 501CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 502CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 503CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 504CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 505CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 506CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 507CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 508CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 509CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Attachment – A Intentionally left blank 510CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Attachment – B Intentionally left blank 511CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 ATTACHMENT C. INFORMATION AND MATERIAL FOR GUIDANCE IN THE APPLICATION OF THE STANDARDS AND RECOMMENDED PRACTICES FOR ILS, VOR, PAR, 75 MHz MARKER BEACONS (EN-ROUTE), NDB AND DME

1. Introduction The material in this Attachment is intended for guidance and clarification purposes and is not to be considered as part of the specifications or as part of the Standards and Recommended Practices contained in Volume I.

For the clarity of understanding of the text that follows and to facilitate the ready exchange of thoughts on closely associated concepts, the following definitions are included.

Definitions relating to the Instrument Landing System (ILS) Note.:: The terms given here are in most cases capable of use either without prefix or in association with the prefix “indicated”. Such usages are intended to

convey the following meanings:

No prefix: the achieved characteristics of an element or concept.

The prefix “indicated”: the achieved characteristics of an element or concept, as indicated on a receiver (i.e. including the errors of the receiving installation).

2. Material concerning ILS installations

2.1 Operational objectives, design and maintenance objectives, and definition of course structure for Facility Performance Categories

2.1.1 The Facility Performance Categories defined in Chapter 3, 3.1.1 have operational objectives as defined by Category I, II or III operations.

Definitions of such operations are given in Annex 6.

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2.1.2 Capabilities. Relevant to these objectives will be the type of aircraft using the ILS and the capabilities of the aircraft flight guidance system(s). Modern aircraft fitted with equipment of appropriate design are assumed in these objectives. In practice, however, operational capabilities may extend beyond the specific objectives given at 2.1.1.

2.1.2.1 Equipage for additional objectives. The availability of fail-passive and fail-operational flight guidance systems in conjunction with an ILS ground system which provides adequate guidance with an appropriate level of continuity of service and integrity for the particular case can permit the attainment of operational objectives which do not coincide with those described at 2.1.1.

2.1.2.2 Advanced operations. For modern aircraft fitted with automatic approach and landing systems, the routine use of such systems is being encouraged by aircraft operating agencies in conditions where the progress of the approach can be visually monitored by the flight crew. For example, such operations may be conducted on Facility Performance Category I — ILS where the guidance quality and coverage exceeds basic requirements given at Chapter 3, 3.1.3.4.1 and extends down to the runway.

2.1.2.3 ILS classification system. In order to fully exploit the potential benefits of modern aircraft automatic flight control systems, there is a related need for a method of describing ground-based ILS more completely than can be achieved by reference solely to the Facility Performance Category. This is achieved by the ILS classification system using the three designated characters. It provides a description of those performance aspects which are required to be known from an operations viewpoint in order to decide the operational applications which a specific ILS could support.

2.1.2.4 The ILS classification scheme provides a means to make known the additional capabilities that may be available from a particular ILS ground facility, beyond those associated with the facilities defined in

Chapter 3, 3.1.1. These additional capabilities can be exploited in

order to permit operational use according to 2.1.2.1 and 2.1.2.2 to be approved down to and below the values stated in the operational objectives described in 2.1.1.

2.1.2.5 An example of the classification system is presented in 2.14.3.

Note.:: The following guidance material is intended to assist States when they are evaluating the acceptability of ILS localizer courses and glide paths having bends. Although, by definition, course bends and glide path bends are related to the nominal positions of the localizer course and glide path respectively, the evaluation of high frequency aberrations is based on the deviations from the mean course or path. The material in 2.1.5 and Figure 513CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 C-2 regarding the evaluation of bends indicates how the bends relate to the mean position of the course and path. Aircraft recordings will normally be in this form.

2.1.3 Course bends. Localizer course bends should be evaluated in terms of the course structure specified in Chapter 3, 3.1.3.4. With regard to landing and roll-out, this course structure is based on the desire to provide adequate guidance for manual and/or automatic operations along the runway in low visibility conditions. With regard to Facility Performance Category I in the approach phase, this course structure is based on the desire to restrict aircraft deviations, due to course bends (95 per cent probability basis) at the 30 m (100 ft) height, to lateral displacement of less than 10 m (30 ft). With regard to Facility Performance Categories II and III in the approach phase, this course structure is based on the desire to restrict aircraft deviations due to course bends (95 per cent probability basis) in the region between ILS Point B and the ILS reference datum (Facility Performance Category II) or Point D (Facility Performance Category III), to less than 2 degrees of roll and pitch attitude and to lateral displacement of less than 5 m (15 ft).

Note 1: Course bends are unacceptable when they preclude an aircraft under normal conditions from reaching the decision height in a stable attitude and at a position, within acceptable limits of displacement from the course line, from which a safe landing can be effected. Automatic and semi- automatic coupling is affected to a greater degree than manual coupling by the presence of bends. Excessive control activity after the aircraft has settled on an approach may preclude it from satisfactorily completing an approach or landing. Additionally, when automatic coupling is used, there may be an operational requirement to continue the approach below the decision height. Aircraft guidance can be satisfied if the specification for course structure in Chapter 3, 3.1.3.4, is met.

Note 2.: Bends or other irregularities that are not acceptable will normally be ascertained by flight tests in stable air conditions requiring precision flight check techniques.

2.1.4 ILS glide path bends. Bends should be evaluated in terms of the ILS glide path structure specified in Chapter 3,3.1.5.4. With regard to Facility Performance Category I, this glide path structure is based on the desire to restrict aircraft deviations due to glide path bends (95 per cent probability basis) at the 30 m (100 ft) height, to vertical displacements of less than 3 m (10 ft). With regard to Facility Performance Categories II and III, this glide path structure is based on the desire to restrict aircraft deviations due to path bends (95 per 514CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 cent probability basis) at the 15 m (50 ft) height, to less than 2 degrees of roll and pitch attitude and to vertical displacements of less than 1.2 m (4 ft).

Note 1.: Path bends are unacceptable when they preclude an aircraft under normal conditions from reaching the decision height in a stable attitude and at a position, within acceptable limits of displacement from the ILS glide path, from which a safe landing can be effected.

Automatic and semi-automatic coupling is affected to a greater degree than manual coupling by the presence of bends. Additionally, when automatic coupling is used, there may be an operational requirement to continue the approach below the decision height. Aircraft guidance can be satisfied if the specification for ILS glide path structure in

Chapter 3, 3.1.5.4, is met.

Note 2.: Bends or other irregularities that are not acceptable will normally be ascertained by precision flight tests, supplemented as necessary by special ground measurements.

2.1.5 Application of localizer course/glide path bend amplitude Standard. In applying the specification for localizer course structure (Chapter 3,

3.1.3.4) and ILS glide path structure (Chapter 3, 3.1.5.4), the following

criteria should be employed: — Figure C-1 shows the relationship between the maximum (95 per cent probability) localizer course/glide path bend amplitudes and distances from the runway threshold that have been specified for Facility Performance Categories I, II and III ILS.

— If the bend amplitudes are to be evaluated in any region of the approach, the flight recordings, corrected for aircraft angular position error, should be analysed for a time interval of plus or minus 20 seconds about the midpoint of the region to be evaluated. The foregoing is based on an aircraft ground speed of 195 km/h (105 knots) plus or minus 9 km/h (5 knots).

The 95 per cent maximum amplitude specification is the allowable percentage of total time interval in which the course/path bend amplitude must be less than the amount specified in Figure C-1 for the region being evaluated. Figure C-2 presents a typical example of the method that can be employed to evaluate the course/path bend amplitude at a particular facility. If the sum of the time intervals t1, t2, t3, where the given specification is exceeded, is equal to or less than 5 per cent of the total time T, the region that is being evaluated is acceptable. Therefore:

515CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Analysis of ILS glide path bends should be made using as a datum the mean glide path and not the downward extended straight line. The extent of curvature is governed by the offset displacement of the ground equipment glide path antenna system, the distance of this antenna system from the threshold, and the relative heights of the ground along the final approach route and at the glide path site (see 2.4).

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2.1.6 Measurements filter. Owing to the complex frequency components present in the ILS beam bend structures, measured values of beam bends are dependent on the frequency response of the airborne receiving and recording equipment. It is intended that beam bend measurements be obtained by using a low-pass filter corner frequency (radians per second) for the receiver DDM output circuits and associated recording equipment of V/92.6, where V is the velocity in km/h of the aircraft or ground vehicle as appropriate.

2.1.7 Monitor systems. Available evidence indicates that performance stability within the limits defined in Chapter 3, 3.1.3.6, 3.1.3.7 and 3.1.5.6, i.e. well within the monitor limit, can readily be achieved.

2.1.7.1 The choice of monitor limits is based on judgement, backed by knowledge of the safety requirements for the category of operation. However, the specifications of such monitoring limits do not indicate the magnitude of the normal day-to-day variations in performance which result from setting- up errors and equipment drift. It is necessary to investigate and take corrective action if the day-to-day performance frequently drifts beyond the limits specified in Chapter 3, 3.1.3.6, 3.1.3.7 and 3.1.5.6. The causes of

such drifts should be eliminated: a) to reduce greatly the possibility of critical signal parameters hovering near the specified monitor limits;

517CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 b) to ensure a high continuity of ILS service.

2.1.7.2 Following are some general guidelines for the design, operation and maintenance of monitor systems to meet the requirements in Chapter 3,

3.1.3.11 and 3.1.5.7.

1) Great care should be exercised to ensure that monitor systems respond to all those variations of the ground facility which adversely affect the operation of the airborne system during ILS approach.

2) Monitor systems should not react to local conditions which do not affect the navigational information as seen by airborne systems.

3) Drifts of the monitor system equipment should not appreciably reduce or increase the monitoring limits specified.

4) Special care must be taken in the design and operation of the monitor system with the aim of ensuring that the navi gational components will be removed or radiation cease in the event of a failure of the monitor system itself.

5) Some monitors rely on devices which sample the signal in the vicinity of the transmitter antenna system. Experience has shown that such

monitor systems require special attention in the following aspects: a) where large-aperture antenna systems are used, it is often not possible to place the monitor sensors in such a position that the phase relationship observed in the far field on the course exists at the sensing point. Nevertheless, the monitor system should also detect antenna and associated feeder system changes which significantly affect the course in the far field;

b) changes in effective ground level caused by snow, flooding, etc., may affect glide path monitor systems, and the actual course in space differently, particularly when reliance is placed on the ground plane to form the desired glide path pattern;

c) attention should be paid to other causes which may disturb the monitor sensing of the radiated signal, such as icing and birds; d) in a system where monitoring signals are used in a feedback loop to correct variations of the corresponding equipment, special care should be taken that extraneous influence and changes in the monitor system itself do not cause course or ILS glide path variations outside the specified limits without alarming the monitor.

6) One possible form of monitor is an integral monitor in which the contribution of each transmitting antenna element to the far-field 518CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 course signal is measured at the antenna system. Experience has shown that such monitoring systems, properly designed, can give a close correlation between the monitor indication and the radiated signal in the far field. This type of monitor, in certain circumstances, overcomes the problem outlined in 5) a), b) and c).

2.1.7.3 It will be realized that the DDM measured at any one point in space is a function of displacement sensitivity and the position of the course line or ILS glide path. This should be taken into account in the design and operation of monitor systems.

2.1.8 Radiation by ILS localizers not in operational use. Severe interference with operational ILS localizer signals has been experienced in aircraft carrying out approaches to low levels at runways equipped with localizer facilities serving the reciprocal direction to the approach. Interference in aircraft overflying this localizer antenna system is caused by cross modulation due to signals radiated from the reciprocal approach localizer. Such interference, in the case of low level operations, could seriously affect approach or landing, and may prejudice safety. Chapter 3, 3.1.2.7 and

3.1.2.7.1 specify the conditions under which radiation by localizers not in operational use may be permitted.

2.1.8.1 At those locations where an ILS facility and a GBAS facility serve opposite approach directions to the same runway, there is a possibility of interference to the reception of the GBAS VDB signals in the region where the aircraft overflies the localizer. Localizer signals that do not support compliance with the requirements in Appendix B, 3.6.8.2.2.5 and

3.6.8.2.2.6 defining the desired to undesired signal ratios and the maximum adjacent channel power tolerable by the GBAS VDB receiver, can result in excessive missed messages and cause a loss of continuity of GBAS guidance. The interference is likely to be higher when the localizer is sited close to the runway threshold. Chapter 3, 3.1.2.8 specifies the conditions under which radiation by localizers not in operational use should not be allowed. Additional information is contained in Attachment D,

7.2.3.3.

2.1.9 ILS multipath interference Note 1.: This guidance material reflects how new larger aeroplanes (NLA) may impact the size of the ILS critical and sensitive areas. It also documents established engineering practices for determining critical and sensitive area dimensions, outlines the associated operational trade-offs, and presents indicative examples of the resulting sizes of the areas. In practice, however, the size of critical and sensitive areas at an aerodrome may need to be determined by specific assessments at that aerodrome.

Note 2.: This guidance material is not intended to create a need to review 519CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 established critical and sensitive area dimensions which have been demonstrated to be satisfactory at a particular aerodrome, unless the operational environment has evolved significantly (such as through the introduction of NLA operations at the aerodrome or the construction of new buildings) or the ILS installation has been changed in a way that may affect the dimensions of the areas.

2.1.9.1 ILS environmental effects. Large reflecting objects within the ILS coverage volume, whether fixed objects or vehicles, including aircraft, can potentially cause degradation of the signal-in-space, through signal blockage and/or multipath interference, with the consequence that the signal-in-space tolerances defined in Chapter 3, 3.1 may be exceeded. The amount of degradation is a function of the location, size and orientation of the reflecting surfaces, and of the ILS antenna characteristics. The objective of identifying critical and sensitive areas (see 2.1.9.2) and associated management procedures is to prevent such degradation and ensure that aircraft using the ILS can rely on the signal-in-space meeting the requirements of Chapter 3, 3.1.

2.1.9.2 ILS critical and sensitive areas. States differ in the way they choose to identify ILS protection areas. Practices also differ in how vehicle movement restrictions are managed. One method is to identify critical

areas and sensitive areas as follows: a) the ILS critical area is an area of defined dimensions about the localizer and glide path antennas where vehicles, including aircraft, are excluded during all ILS operations. The critical area is protected because the presence of vehicles and/or aircraft inside its boundaries will cause unacceptable disturbance to the ILS signal-in-space;

b) the ILS sensitive area is an area where the parking and/or movement of vehicles, including aircraft, is controlled to prevent the possibility of unacceptable interference to the ILS signal during ILS operations.

The sensitive area is protected against interference caused by large moving objects outside the critical area but still normally within the airfield boundary.

Note 1.: In some States, the term “critical area” is used to describe an area that combines the critical and sensitive areas identified in this guidance material. In cases where the critical area overlaps operational areas, specific operational management procedures are required to ensure protection of aircraft using the ILS for intercept and final approach guidance.

Note 2.: It is expected that at sites, where ILS and MLS are to be collocated, the 520CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 MLS might be located within ILS critical areas in accordance with guidance material in Attachment G, 4.1.

2.1.9.3 Technical and operational logic associated with critical and sensitive areas. Ideally, the critical area is enforced during all ILS operations with protection afforded down to at least the Category I decision height. A critical area disturbance would normally impact all aircraft using the ILS signal at a given time (entire approach). The critical area is typically safeguarded through marked boundaries, limiting access to the area or through procedural means if there are overlaps into operational areas.

From an operational perspective, the sensitive area would ideally protect aircraft operations at least from the Category I decision height down to the runway, and be activated during low visibility conditions only (e.g.

Category II and III). A sensitive area disturbance would normally be of a transient nature, and produce a local disturbance affecting a single aircraft only. However, at many locations, it may not be possible to achieve this ideal situation, and corresponding technical and operational mitigations will be required.

Note.: Guidance on operational procedures for the protection of critical and sensitive areas is provided in ICAO EUR DOC 013, “European Guidance Material on All Weather Operations at Aerodromes”.

2.1.9.4 Technical determination of critical and sensitive area dimensions. Critical and sensitive areas are normally calculated in the planning stage, prior to ILS installation, using computer simulation. A similar process is used when there are changes to the installation or to the environment. When using computer simulations, it is necessary to allocate the protection of individual parts of the approach to either the critical or sensitive area. It is desirable to ensure that the combined critical and sensitive areas protect the entire approach. However, this may not be possible in all cases. Furthermore, if the logic described in 2.1.9.3 is used, this may lead to restrictively large critical areas. Some States have found that a reasonable compromise can be achieved using a different logic, whereby the critical area protects the segment from the edge of coverage down to 2 NM from the runway threshold, while the sensitive area protects the approach from 2 NM down to the runway. In this case, a sensitive area for Category I operations will exist and may require operational mitigation. Depending on the operational environment (such as timing between leading aircraft on runway roll-out and trailing aircraft on final approach), no particular measures may be needed. There may not necessarily be a direct link between the approach allocation used in simulations to determine critical and sensitive areas, and their operational management. It is a State’s responsibility to define the relevant areas. If different disturbance acceptance criteria or different flight segment protections are to be applied, they must be validated through a safety analysis. The safety analysis must take all relevant factors into account, including the aerodrome configuration, traffic density and any operational issues or capacity restrictions.

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2.1.9.5 Factors impacting the sizes of critical and sensitive areas. Localizer and glide path antennas with optimized radiation patterns, especially when combined with two-frequency transmitters, can be very effective in reducing the potential for signal disturbance and hence the sizes of the critical and sensitive areas. Other factors affecting the sizes of the areas include the category of approach and landing operation to be supported, the amount of static disturbance, locations, sizes and orientations of aircraft and other vehicles (particularly of their vertical surfaces), runway and taxiway layout, and antenna locations. In particular, the maximum heights of vertical aircraft tail surfaces likely to be encountered must be established, together with all possible orientations at a given location, which may include non-parallel or non-perpendicular orientations with respect to the runway. While critical and sensitive areas are evaluated in a two-dimensional (horizontal) context, protection should actually be extended to volumes, as departing aircraft and/or manoeuvring helicopters/aircraft can also cause disturbances to the ILS signals. The vertical profiles of the protection volumes depend on the vertical patterns of the transmitting arrays.

2.1.9.6 Allocation of multipath error budget. It is convenient to consider disturbances caused by mobile objects such as aircraft and other vehicles separately from the static disturbances caused by fixed objects such as buildings and terrain. Once the static multipath is known, the remainder can be allocated to dynamic disturbances. If measurements indicate that the real static multipath is significantly different from that assumed in the simulations, the allocation may need to be revised. In most cases, the root sum square combination of the disturbances due to fixed and mobile objects gives a more statistically valid representation of the total disturbance than an algebraic sum. For example, a limit of plus or minus 5μA for localizer course structure would be respected with plus or minus 3μA of disturbance due to static objects and an allowance of plus or minus 4μA for dynamic objects:

2.1.9.7 Site study and computer simulations. Normally, a site specific study is conducted for a particular airport installation. The study will take into account different assumptions for the static multipath environment, airport topography, types and effective heights of ILS arrays, and orientations of manoeuvring aircraft, such as runway crossings, 180° turns at threshold or holding orientations other than parallel or perpendicular. Simulation models can be employed to calculate the probable location, magnitude and duration of ILS disturbances caused by objects, whether by structures or by aircraft of various sizes and orientation at different locations. Air navigation service providers (ANSPs) will need to ensure that simulation models used have been validated by direct comparison with ground and flight measurements for a variety of specific situations and environments, and that the subsequent application of such models is conducted by personnel with appropriate engineering knowledge and judgement to take 522CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 into account the assumptions and limitations of applying such models to specific multipath environments.

2.1.9.8 Changes in airport environment. Should major changes in the airport environment cause an increase in the static disturbances of the localizer and/or glide path, the sizes of the critical and sensitive areas may need to be redefined, with potential impact on airport efficiency or capacity. This is particularly significant when considering the location, size and orientation of proposed new buildings within or outside the airport boundary. It is recommended that suitable safeguarding criteria be employed to protect the ILS operations.

Note.:: Example guidance can be found in ICAO EUR DOC 015 “European Guidance Material on Managing Building Restricted Areas”.

2.1.9.9 Typical examples of critical and sensitive areas. Figures C-3 and C-4 (including associated Tables C-1, C-2A and C-2B) show examples of critical and sensitive areas for the different categories of operations and for different classes of vehicle/aircraft heights and several localizer and glide path antenna types. The calculation of these examples has been done with a simulation model using an exact method of resolution of ILS propagation equations applied to a 3D model of corresponding aircraft.

The dimensions are based on assumptions of flat terrain, 3.0° glide path, allocations of 60 per cent of applicable tolerances for static multipath and 80 per cent for dynamic multipath, an approaching aircraft at 105 knots, i.e. with a 2.1 rad/s low-pass filter and an omnidirectional receiving antenna pattern. The examples consider typical orientations of reflecting surfaces of taxiing, holding and manoeuvring aircraft/large ground vehicles. The tail heights for the ground vehicles/small aircraft, medium, large and very large aircraft categories correspond to Annex 14 aerodrome reference code letters A, B/C, D/E and F, respectively, as detailed within FAA Advisory Circular 150/5300-13. In case of uncertainty about which category an aircraft belongs to for the purposes of critical and sensitive areas assessment, the tail height is the determining feature.

2.1.9.10 Purpose and correct application of typical examples. Since it will be rare that an actual installation fits exactly the assumptions used in these examples, adaptation to local conditions will be required. The examples serve to provide a rough order of magnitude indication of critical and sensitive area sizes, depending on how much local conditions differ from assumptions used in these examples. The example tables may also be used to assess the tools used in simulations, using the listed assumptions.

In many installations, airports have established critical and sensitive areas which are different from those listed in these examples, through a combination of further technical optimizations, operational mitigations, experience, and safety assessments applicable to the particular operational environment. In the case of new airport construction projects, 523CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 potential conflicts of the example areas provided here with planned operational uses should lead to further evaluations, and may lead to implementing more advanced ILS antenna systems, for example wider aperture localizer antennas, including advanced designs such as very large aperture arrays. The typical examples provided here do not take such specific optimized systems into account. The tables differ slightly between the localizer and the glide path in terms of how different aircraft orientations are considered. These details are explained in the notes to Tables C-1 (note 9), C-2A and C-2B (note 8). In accordance with these notes, in some glide path cases the half-wingspan of aircraft needs to be added to ensure that no portion of the aircraft enters the critical or sensitive areas.

2.1.9.9.2 Limits of multipath assumptions used in example simulations. The allocation of 60 per cent for static and 80 per cent for dynamic multipath used in 2.1.9.6 represents a conservative approach which is suitable in locations where both types of multipath coincide. A different allocation may be appropriate for the glide path, especially in the case of flat terrain, as in that case the static multipath will be very small. In locations where static and dynamic multipath do not coincide, due to the specific layout of the airport, the full tolerance can be consumed by the dynamic multipath. A simulation tool able to model the complete environment (static and dynamic reflection sources) and to compute the combined effect may avoid having to apply the root sum square approximation. This may lead to an optimization of the critical and/or sensitive area dimensions.

2.1.9.9.3 Flight segment protection allocations used in example simulations. The examples given in Figure C-3 for the localizer use a 2 NM transition point as described in 2.1.9.4. The examples given in Figure C-4 for the glide path use a 0.6 NM transition point (corresponding to the Category I decision height). Depending on local operations, other transition points may be more suitable.

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2.1.10 Reducing localizer bends and areas with insufficient difference in depth of modulation (DDM)

2.1.10.1 Introduction. Owing to site effects at certain locations, it is not always possible to produce, with simple standard ILS installations, localizer courses that are sufficiently free from troublesome bends or irregularities.

If this is the case, it is highly preferable to use two radio frequency carriers to provide the standard coverage and signal characteristics. Additional guidance on two radio frequency carrier coverage is provided in 2.7. If standard coverage requirements still cannot be met, reducing radiation in the direction of objects and accepting an increase of the lower vertical coverage boundaries as permitted in Chapter 3, 3.1.3.3.1 may be employed.

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2.1.10.2 Reducing standard localizer coverage. When using the coverage reduction option defined in Chapter 3, 3.1.3.3.1, care needs to be taken to ensure that the reduced coverage volume is consistent with the minimum altitudes published for the instrument approach procedure. Additionally, normal vectoring operations should not be terminated and a clearance to intercept the localizer should not be issued until within the promulgated coverage area. This is sometimes referred to as the operational service volume.

2.1.10.2.1 Operational considerations from an air traffic management perspective.

Instrument approach procedures must be designed to take into account any reduction in localizer coverage permitted by the Standard in Chapter 3, 3.1.3.3.1. This can be done either by ensuring that the procedure remains within localizer coverage or by providing alternative means to navigate. Consequently, a significant portion (3.7 km (2 NM) minimum) of the initial segment must be within localizer coverage. Localizer coverage needs to be available sufficiently in advance of the area where controllers usually give the approach or intercept clearance to permit pilots to verify the Morse code identification (IDENT).

2.1.10.2.2 Operational considerations from a pilot/aircraft perspective. For aircraft equipped with automatic flight control systems (AFCS), localizer coverage needs to be available prior to the activation of the AFCS intercept mode (manual or automatic flight) and sufficiently in advance of the area where controllers usually give the approach or intercept clearance to permit checking the IDENT signal. When flying manually or when using an AFCS, pilots normally check the IDENT of the ILS facility and then wait to arm the mode enabling localizer intercept turn initiation and capture until after receiving the approach or intercept clearance. Ideally, additional aids (if included in the approach procedure) should permit a determination of the relationship between the aircraft position and the localizer front course line by the pilot.

2.2 ILS airborne receiving equipment

2.2.1 To ensure that the required operational objectives are achieved, it is necessary for the airborne receiving equipment to meet defined performance standards.

Note.: The relevant minimum operational performance standards for ILS receivers are detailed in RTCA DO-195 (1986) and EUROCAE ED-46B (including Amendments Nos. 1 and 2) for the localizer, in RTCA DO-143

(1970) and EUROCAE 1/WG 7/70 for the marker beacon, and in RTCA DO-192 (1986) and EUROCAE ED-47B (including Amendment No. 1) for the glide path receivers.

2.2.2 Immunity performance of ILS localizer receiving systems to interference from VHF FM broadcast signals 529CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

2.2.2.1 With reference to Note 2 of 3.1.4.2, Chapter 3, the immunity performance defined there must be measured against an agreed measure of degradation of the receiving system’s normal performance, and in the presence of, and under standard conditions for the input wanted signal.

This is necessary to ensure that the testing of receiving equipment on the bench can be performed to a repeatable set of conditions and results and to facilitate their subsequent approval. Tests have shown that FM interference signals may affect both course guidance and flag current, and their effects vary depending on the DDM of the wanted signal which is applied. Additional information can be found in ITU Recommendation ITU- R SM.1140, Test procedures for measuring receiver characteristics used for determining compatibility between the sound-broadcasting service in the band of about 87–108 MHz and the aeronautical services in the band 108–118 MHz.

2.2.2.2 Commonly agreed methodology and formulae should be used to assess potential incompatibilities to receivers meeting the general interference immunity criteria specified in Chapter 3, 3.1.4. The formulae provide clarification of immunity interference performance of spurious emission (type A1) interference, out-of-band channel (type A2) interference, two- signal and three-signal third order (type B1) interference, and overload/desensitization (type B2) interference. Additional information can be found in ITU Recommendation ITU-R SM.1009-1, Compatibility between the sound-broadcasting service in the band of about 87–108 MHz and the aeronautical services in the band 108–137 MHz.

2.2.3 Localizer and glide path antenna polarization

2.2.3.1 Over the localizer and glide path frequency bands, respectively, the reception of vertically polarized signals from the forward direction with respect to the localizer and glide path antenna should be at least 10 dB below the reception of horizontally polarized signals from the same direction.

2.3 Alarm conditions for ILS airborne equipment

2.3.1 Ideally, a receiver alarm system such as a visual flag should warn a pilot of any unacceptable malfunctioning conditions which might arise within either the ground or airborne equipments. The extent to which such an ideal may be satisfied is specified below.

2.3.2 The alarm system is actuated by the sum of two modulation depths and, therefore, the removal of the ILS course modulation components from the radiated carrier should result in the actuation of the alarm. 2.3.3 The alarm system should indicate to the pilot and to any other airborne system which may be utilizing the localizer and glide path data, the existence of any of

the following conditions:

530CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 a) the absence of any RF signal as well as the absence of simultaneous 90 Hz and 150 Hz modulation; b) the percentage modulation of either the 90 Hz or 150 Hz signal reduction to zero with the other maintained at its normal 20 per cent and 40 per cent modulation respectively for the localizer and glide path;

Note.: It is expected that the localizer alarm occur when either the 90 Hz or 150 Hz modulation is reduced to 10 per cent with the other maintained at its normal 20 per cent. It is expected that the glide path alarm occur when either the 90 Hz or 150 Hz modulation is reduced to 20 per cent with the other maintained at its normal 40 per cent.

2.3.3.1 The alarm indication should be easily discernible and visible under all normal flight deck conditions. If a flag is used, it should be as large as practicable commensurate with the display.

2.4 Guidance for the siting, elevation, adjustment and coverage of glide path equipment

2.4.1 Lateral placement. The lateral placement of the glide path antenna system with respect to the runway centre line is normally not less than 120 m (400 ft). In deciding the lateral placement of the glide path antenna, account should be taken of the appropriate provisions of Annex 14 with regard to obstacle clearance surfaces and objects on strips for runways.

2.4.2 ILS glide path curvature. In many cases, the ILS glide path is formed as a conic surface originating at the glide path aerial system. Owing to the lateral placement of the origin of this conic surface from the runway centre line, the locus of the glide path in the vertical plane along the runway centre line is a hyperbola. Curvature of the glide path occurs in the threshold region and progressively increases until touchdown. To limit the amount of curvature, the glide path antenna should not be located at an excessive lateral distance from the runway centre line.

2.4.3 Procedure design. Chapter 3, 3.1.5.1 provides Standards and Recommended Practices for the glide path angle and the height of the ILS reference datum. The longitudinal position of the glide path antenna with respect to the runway threshold is established in order to provide the selected glide path angle and desired ILS reference datum height for the precision approach procedure designed for that runway. The precision approach procedure design may be modified to meet obstacle clearance requirements or to account for technical siting constraints for the glide path antenna (for example, crossing runways or taxiways). The procedure designer will take into account the acceptable glide path angle, threshold crossing height and runway length available as they relate to the type of aircraft expected to use the precision approach procedure.

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2.4.4 Longitudinal placement. Assuming that the reflecting surface in the beam forming area can be approximated by a planar surface with appropriate lateral and longitudinal slopes, the required longitudinal position of the glide path antenna is then a function of the ILS reference datum above the runway threshold and of the projection of the glide path reflection plane along the runway centre line . This situation is described pictorially in Figure C-5. In this figure, the line OP is defined by the intersection between the glide path reflection plane and the vertical plane along the runway centre line, and point O is at the same longitudinal distance from the threshold as the glide path antenna. Depending on the height and orientation of the reflection plane, point O may be above or below the runway surface. For a planar reflecting surface, the longitudinal position of

the glide path antenna is then calculated as follows:

Where D = the horizontal distance between O and P (equivalent to the longitudinal distance from the glide path antenna to the runway threshold);

H = the nominal height of the ILS reference datum above the runway threshold;

Y = the vertical height of the runway threshold above P'; θ = the nominal ILS glide path angle; α = the longitudinal downslope of the glide path reflection plane.

Note.: In the above formula α is to be taken as positive in the case of a downslope from the antenna towards the threshold. Y is taken as positive if the threshold is above the reflection plane intersection line.

2.4.5 The foregoing guidance material is based on the approximation of the reflecting surface by an appropriately oriented plane. Actual siting characteristics, such as significant lateral slope or an irregular rather than planar reflection surface, may require a more rigorous approach if the design goal for the height of the ILS reference datum is to be closely met.

In challenging cases, mathematical modelling predictions of the effects of the siting conditions may be appropriate.

2.4.6 Typically, the glide path has some irregularities. The mean ILS glide path angle can be ascertained only by flight tests; the mean observed position of that part of the glide path between ILS Points A and B being represented as a straight line, and the ILS glide path angle being the angle measured between that straight line and its vertical projection on the horizontal plane.

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2.4.7 It is important to recognize that the effect of glide path irregularities if averaged within the region between the middle marker and the threshold will likely tend to project a reference datum which is actually different from the ILS reference datum. This reference datum, defined here as the achieved ILS reference datum, is considered to be of important operational significance. The achieved ILS reference datum can only be ascertained by flight check, i.e. the mean observed position of that portion of the glide path typically between points 1 830 m (6 000 ft) and 300 m (1 000 ft) from the threshold being represented as a straight line and extended to touchdown. The point at which this extended straight line meets the line drawn vertically through the threshold at the runway centre line is the achieved ILS reference datum.

Note.: Further guidance on the measurement of the glide path angle and the achieved ILS reference datum is given in Doc 8071.

2.4.8 To reduce multipath interference to Facility Performance Category III glide paths and to reduce siting requirements and sensitive areas at these sites, it is desirable that the signals forming the horizontal radiation pattern from the Facility Performance Category III — ILS glide path antenna system be reduced to as low a value as practicable outside the azimuth coverage limits specified in Chapter 3, 3.1.5.3. Another acceptable method is to 533CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 rotate in azimuth the glide path antennas away from multipath sources thus reducing the amount of radiated signals at specific angles while still maintaining the azimuth coverage limits.

2.4.9 Chapter 3, 3.1.5.3.1 indicates the glide path coverage to be provided to allow satisfactory operation of a typical aircraft installation. The operational procedures promulgated for a facility must be compatible with the lower limit of this coverage. It is usual for descents to be made to the intercept altitude and for the approach to continue at this altitude until a flydown signal is received. In certain circumstances a cross-check of position may not be available at this point. Automatic flight control systems will normally start the descent whenever a fly-up signal has decreased to less than about 10 microamperes.

2.4.10 The objective is, therefore, to provide a fly-up signal prior to intercepting the glide path. Although under normal conditions, approach procedures will be accomplished in such a way that glide path signals will not be used below 0.45 θ, or beyond 18.5 km (10 NM) from the runway, it is desirable that misleading guidance information should not be radiated in this area.

Where procedures are such that the glide path guidance may be used below 0.45 θ, adequate precautions must be taken to guard against the radiation of misleading guidance information below 0.45 θ, under both normal conditions and during a malfunction, thus preventing the final descent being initiated at an incorrect point on the approach. Some precautions which can be employed to guard against the radiation of misleading guidance include the radiation of a supplementary clearance signal such as provided for in Chapter 3, 3.1.5.2.1, the provision of a separate clearance monitor and appropriate ground inspection and setting-up procedures.

2.4.11 To achieve satisfactory monitor protection against below-path out-of- tolerance DDM, depending on the antenna system used, the displacement sensitivity monitor as required in Chapter 3, 3.1.5.7.1 e) may not be adequate to serve also as a clearance monitor. In some systems, e.g.

those using multi-element arrays without supplementary clearance, a slight deterioration of certain antenna signals can cause serious degradation of the clearance with no change or only insignificant changes within the glide path sector as seen by the deviation sensitivity monitor. It is important to ensure that monitor alarm is achieved for any or all possible deteriorated antenna and radiated signal conditions, which may lead to a reduction of clearance to 0.175 DDM or less in the below-path clearance coverage.

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2.6 Deployment of ILS frequencies Note.: Guidance material on deployment of ILS frequencies is given in the Handbook on Radio Frequency Spectrum Requirements for Civil Aviation (Doc 9718, Volume II), Chapter 3.

2.7 Localizers and glide paths achieving coverage with two radio frequency carriers

2.7.1 Localizer and glide path facilities may achieve their coverage requirements by using two radiation field patterns, commonly known as the “course” and “clearance” patterns, transmitted using separate carrier frequencies spaced within the frequency channel. The course field pattern gives accurate course and displacement indications; the clearance field pattern provides displacement indications at angles beyond the limits of the course field pattern . Discrimination between signals is obtained in airborne receivers by the stronger signal capturing the receiver. Effectiveness of capture depends on the type of detector used but, in general, if the ratio of the two signals is of the order of 10 dB or more, the smaller signal does not cause significantly large errors in demodulated output. For optimum performance within the front course sector, the following guidance material should be applied in the operation of two carrier frequency localizer systems.

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2.7.2 The localizer should be designed and maintained so that the ratio of the two radiated signals-in-space within the front course sector does not fall below 10 dB. Particular attention should be directed to the vertical lobe structure produced by the two antenna systems which may be different in height and separated in distance, thus resulting in changes in ratio of signal strengths during approach.

2.7.3 Due to the 6 dB allowance for the receiver pass-band filter ripple, localizer receiver response variations can occur as the clearance frequency is displaced from the course frequency. To minimize this effect, particularly for Category III operations, the course-to-clearance signal ratio needs to be increased from 10 dB to 16 dB.

2.7.4 To minimize further the risk of errors if the ratio of the two radiated signals falls below 10 dB within the front course sector, the difference in alignment of the radiation field patterns of the two signals should be kept as minimal as practicable.

2.7.5 Glide paths which employ two carriers are used to form a composite radiation field pattern on the same radio frequency channel. Special configurations of antennas and the distribution of antenna currents and phasing may permit siting of glide path facilities at locations with particular terrain conditions which may otherwise cause difficulty to a single- frequency system. At such sites, an improvement is obtained by reducing the low angle radiation. The second carrier is employed to provide coverage in the region below the glide path.

2.7.6 Monitoring dual frequency systems. The dual frequency monitoring requirements in Chapter 3, 3.1.3.11.2 e) and 3.1.5.7.1 c) specify monitor action for a power output of less than 80 per cent of normal, except that reductions can be accepted to 50 per cent of normal if certain performance requirements are met.

2.7.6.1 Monitoring the course and clearance transmitters for a 20 per cent reduction in power (approximately –1 dB) can be challenging if environmental and other effects such as large ambient temperature variations exist at the site. For example, temperature variations cause normal transmitter power output to vary and coaxial cable insertion losses to change. Even assuming no failure occurs in the transmitting system, the alarm limit occasionally may be exceeded, and this in turn may compromise continuity.

2.7.6.2 The alternative of monitoring at power reductions of up to 50 per cent appears very attractive, but must be used cautiously. Monitoring each transmitter independently at a 50 per cent reduction can allow a large change from the nominal power ratio between the two transmitters if uncorrelated failures occur. This in turn may compromise the capture effect in the receiver, thus increasing structure errors or reducing 540CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 clearance indications.

2.7.6.3 One solution is to use a monitoring scheme that limits the difference between the power output of the transmitters to approximately 1 dB (i.e.

80 per cent), while allowing both to decrease up to 3 dB (i.e. 50 per cent) if they change together. This method provides a greater tolerance for common mode effects such as cable loss changes due to temperature, and therefore increases continuity of service.

2.8 Integrity and continuity of service — ILS ground equipment

2.8.1 Introduction

2.8.1.1 This material is intended to provide clarification of the integrity and continuity of service objectives of ILS localizer and glide path ground equipment and to provide guidance on engineering design and system characteristics of this equipment. Integrity is needed to ensure that an aircraft on approach will have a low probability of receiving false guidance;

continuity of service is needed to ensure that an aircraft in the final stages of approach will have a low probability of being deprived of a guidance signal. Integrity and continuity of service are both key safety factors during the critical phase of approach and landing. The integrity and continuity of service must of necessity be known from an operational viewpoint in order to decide the operational application which an ILS could support.

2.8.1.2 It is generally accepted, irrespective of the operational objective, that the average rate of a fatal accident during landing, due to failures or shortcomings in the whole system, comprising the ground equipment, the aircraft and the pilot, should not exceed 1 × 10–7. This criterion is frequently referred to as the global risk factor.

2.8.1.3 In the case of Category I operations, responsibility for assuring that the above objective is not exceeded is vested more or less completely in the pilot. In Category III operations, the same objective is required but must now be inherent in the whole system. In this context it is of the utmost importance to endeavour to achieve the highest level of integrity and continuity of service of the ground equipment.

2.8.1.4 The requirements for integrity and high continuity of service require highly reliable systems to minimize the probability of failure which may affect any characteristic of the total signal-in-space. It is suggested that States endeavour to achieve reliability with as large a margin as is technically and economically reasonable. Reliability of equipment is governed by basic construction and operating environment. Equipment design should employ the most suitable engineering techniques, materials and components, and rigorous inspection should be applied in manufacture. Equipment should be operated in environmental conditions appropriate to the manufacturers’ design criteria.

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2.8.2 Achievement and retention of integrity service levels

2.8.2.1 An integrity failure can occur if radiation of a signal which is outside specified tolerances is either unrecognized by the monitoring equipment or the control circuits fail to remove the faulty signal. Such a failure might constitute a hazard if it results in a gross error.

2.8.2.2 Clearly not all integrity failures are hazardous in all phases of the approach. For example, during the critical stages of the approach, undetected failures producing gross errors in course width or course line shifts are of special significance whereas an undetected change of modulation depth, or loss of localizer and glide slope clearance and localizer identification would not necessarily produce a hazardous situation. The criterion in assessing which failure modes are relevant must however include all those deleterious fault conditions which are not unquestionably obvious to the automatic flight system or pilot.

2.8.2.3 The highest order of protection is required against the risk of undetected failures in the monitoring and associated control system. This would be achieved by careful design to reduce the probability of such occurrences to a low level and provide fail-safe operations compliant with the Standards of Chapter 3, 3.1.3.11.4 and 3.1.5.7.4, and by carrying out maintenance checks on the monitor system performance at intervals which are determined by a design analysis.

2.8.2.4 A design analysis can be used to calculate the level of integrity of the system in any one landing. The following formula applies to certain types of ILS and provides an example of the determination of system integrity, I, from a calculation of the probability of transmission of undetected erroneous radiation, P.

(1) I = 1 – P Where I = integrity P = the probability of a concurrent failure in transmitter and monitor systems resulting in erroneous undetected radiation M1 = transmitter mean time between failures (MTBF) M2 = MTBF of the monitoring and associated control system 1/𝛼1= ratio of the rate of failure in the transmitter resulting in the radiation of an erroneous signal to the rate of all transmitter failures 542CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 1/α2 = ratio of the rate of failure in the monitoring and associated control system resulting in inability to detect an erroneous signal to the rate of all monitoring and associated control system failures T1 = period of time (in hours) between transmitter checks T2 = period of time (in hours) between checks on the monitoring and associated control system When T1 ≥ T2 the monitor system check may also be considered a transmitter check. In this case, therefore T1 = T2 and the formula would be:

2.8.2.5 Since the probability of occurrence of an unsafe failure within the monitoring or control equipment is extremely remote, to establish the required integrity level with a high degree of confidence would necessitate an evaluation period many times that needed to establish the equipment MTBF. Such a protracted period is unacceptable and therefore the required integrity level can only be predicted by rigorous design analysis of the equipment.

2.8.2.6 Protection of the integrity of the signal-in-space against degradation which can arise from extraneous radio interference falling within the ILS frequency band or from re-radiation of ILS signals must also be considered. Measures to prevent the latter by critical and sensitive area protection are given in general terms at 2.1.9. With regard to radio interference it may be necessary to confirm periodically that the level of interference does not constitute a hazard.

2.8.2.7 In general, monitoring equipment design is based on the principle of continuously monitoring the radiated signals in- space at specific points within the coverage volume to ensure their compliance with the Standards specified at Chapter 3, 3.1.3.11 and 3.1.5.7. Although such monitoring provides to some extent an indication that the signal-in-space at all other points in the coverage volume is similarly within tolerance, this is largely inferred. It is essential therefore to carry out rigorous flight and ground inspections at periodic intervals to ensure the integrity of the signal-in- space throughout the coverage volume.

2.8.3 Achievement and retention of continuity of service levels

2.8.3.1 A design analysis should be used to predict the MTBF and continuity of service of the ILS equipment. Before assignment of a level of continuity of service and introduction into service, the mean time between outages

(MTBO) of the Level 2, 3 or 4 ILS should be confirmed by evaluation in an operational environment. In this evaluation, an outage is defined as any unanticipated cessation of signal-in-space. This evaluation takes into 543CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 account the impact of operational factors, i.e. airport environment, inclement weather conditions, power availability, quality and frequency of maintenance. MTBO is related to MTBF, but is not equivalent, as some equipment failures, such as a failure of a transmitter resulting in the immediate transfer to a standby transmitter may not necessarily result in an outage. For continuity of service Level 2, 3 or 4, the evaluation period should be sufficient to determine achievement of the required level with a high degree of confidence. One method to demonstrate that continuity standards are met is the sequential test method. If this method is used, the

following considerations apply: a) the minimum acceptable confidence level is 60 per cent. To achieve the confidence level of 60 per cent, the evaluation period has to be longer than the required MTBO hours as stated in Table C-4.

Typically, these minimal evaluation periods for new and subsequent installations are for Level 2, 1 600 operating hours, for Level 3, 3 200 hours and for Level 4, 6 400 hours. To assess the seasonal influence of the environment, a minimal evaluation period of one year is typically required for a new type of installation in a particular environment. It may be possible to reduce this period in cases where the operating environment is well controlled and similar to other proven installations. Where several identical systems are being operated under similar conditions, it may be possible to base the assessment on the cumulative operating hours of all the systems;

this will result in a reduced evaluation period. Once a higher confidence level is obtained for a type of installation, subsequent installation of the same type of equipment under similar operational and environmental conditions may follow shorter evaluation periods;

b) during the evaluation period, it should be decided for each outage if it is caused by a design failure or if it is caused by a failure of a component due to its normal failure rate. Design failures are, for instance, operating components beyond their specification (overheating, overcurrent, overvoltage, etc. conditions). These design failures should be dealt with such that the operating condition is brought back to the normal operating condition of the component or that the component is replaced with a part suitable for the operating conditions. If the design failure is treated in this way, the evaluation may continue and this outage is not counted, assuming that there is a high probability that this design failure will not occur again. The same applies to outages due to any causes which can be mitigated by permanent changes to the operating conditions.

2.8.3.2 An assigned continuity of service level should not be subject to frequent change. A suitable method to assess the behaviour of a particular installation is to keep the records and calculate the average MTBO over the last five to eight failures of the equipment. This weighs the MTBO for continuity of service purposes to be more relevant to the next approach, rather than computing MTBO over the lifetime of the equipment. If 544CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 continuity of service deteriorates, the assigned designation should be reduced until improvements in performance can be effected.

2.8.3.3 Additional detailed guidance. Several States have published continuity of service policies and procedures. The following documents may be

consulted for additional guidance and details: a) European Guidance Material on Continuity of Service Evaluation in Support of the Certification of ILS & MLS Ground Systems, EUR DOC 012; and b) Instrument Landing System Continuity of Service Requirements and Procedures, Order 6750.57A, United States Federal Aviation Administration.

2.8.4 The following configuration is an example of a redundant equipment arrangement that is likely to meet the objectives for integrity and continuity of service Levels 3 and 4. The localizer and glide path facilities each consist of two continuously operating transmitters, one connected to the antenna and the standby connected to a dummy load. With these transmitters is associated a monitor system performing the following

functions: a) confirming proper operation within the specified limits of the main transmitter and antenna system by means of majority voting among redundant monitors; b) confirming operation of the standby equipment.

2.8.4.1 Whenever the monitor system rejects one of the equipments the facility continuity of service level will be reduced because the probability of cessation of signal consequent on failure of other equipment will be increased. This change of performance must be automatically indicated at remote locations.

2.8.4.2 An identical monitoring arrangement to the localizer is used for the glide path facility.

2.8.4.3 To reduce mutual interference between the main and standby transmitters any stray radiation from the latter is at least 50 dB below the carrier level of the main transmitter measured at the antenna system.

2.8.4.4 In the above example, the equipment would include provision to facilitate monitoring system checks at intervals specified by the manufacturer, consequent to the design analysis, to ensure attainment of the required integrity level. Such checks, which can be manual or automatic, provide the means to verify correct operation of the monitoring system including the control circuitry and changeover switching system. The advantage of adopting an automatic monitor integrity test is that no interruption to the operational service provided by the localizer or glide path is necessary. It 545CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 is important when using this technique to ensure that the total duration of the check cycle is short enough not to exceed the total period specified in

Chapter 3, 3.1.3.11.3 or 3.1.5.7.3.

2.8.4.5 Interruption of facility operation due to primary power failures is avoided by the provision of suitable standby supplies, such as batteries or “no- break” generators. Under these conditions, the facility should be capable of continuing in operation over the period when an aircraft may be in the critical stages of the approach. Therefore, the standby supply should have adequate capacity to sustain service for at least two minutes.

2.8.4.6 Warnings of failures of critical parts of the system, such as the failure of the primary power supply, must be given at the designated control points.

2.8.4.7 In order to reduce failure of equipment that may be operating near its monitor tolerance limits, it is useful for the monitor system to include provision to generate a pre-alarm warning signal to the designated control point when the monitored parameters reach a limit equal to a value in the

order of 75 per cent of the monitor alarm limit.

2.8.4.8 An equipment arrangement similar to that at 2.8.4, but with no transmitter redundancy, would normally be expected to achieve the objectives for continuity of service Level 2.

2.8.5 Guidance relating to localizer far field monitors is given below.

2.8.5.1 Far field monitors are provided to monitor course alignment but may also be used to monitor course sensitivity. A far field monitor operates independently from integral and near field monitors. Its primary purpose is to protect against the risk of erroneous setting-up of the localizer, or faults in the near field or integral monitors. In addition, the far field monitor system will enhance the ability of the combined monitor system to respond to the effects of physical modification of the radiating elements or variations in the ground reflection characteristics. Moreover, multipath effects and runway area disturbances not seen by near field and integral monitors, and some occurrences of radio interferences may be substantially monitored by using a far field monitoring system built around a suitable receiver(s), installed under the approach path. 2.8.5.2 A far field monitor is generally considered essential for Category III operations, while for Category II it is generally considered to be desirable. Also for Category I installations, a far field monitor has proved to be a valuable tool to supplement the conventional monitor system.

2.8.5.3 The signal received by the far field monitor will suffer short-term interference effects caused by aircraft movements on or in the vicinity of the runway and experience has shown that it is not practical to use the far field monitor as an executive monitor. When used as a passive monitor, means must be adopted to minimize such temporary interference effects and to reduce the occurrence of nuisance downgrade indications; some 546CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 methods of achieving this are covered in 2.8.5.4. The response of the far field monitor to interference effects offers the possibility of indicating to the air traffic control point when temporary disturbance of the localizer signal is present. However, experience has shown that disturbances due to aircraft movements may be present along the runway, including the touchdown zone, and not always be observed at the far field monitor. It must not be assumed, therefore, that a far field monitor can provide comprehensive surveillance of aircraft movements on the runway.

2.8.5.3.1 Additional possible applications of the far field monitor are as follows: b) it can be a useful maintenance aid to verify course and/or course deviation sensitivity in lieu of a portable far field monitor;

c) it may be used to provide a continuous recording of far field signal performance showing the quality of the far field signal and the extent of signal disturbance.

2.8.5.4 Possible methods of reducing the occurrence of nuisance downgrade

indications include: b) incorporation of a time delay within the system adjustable from 30 to 240 seconds; c) the use of a validation technique to ensure that only indications not affected by transitory disturbances are transmitted to the control system;

d) use of low pass filtering.

2.8.5.5 A typical far field monitor consists of an antenna, VHF receiver and associated monitoring units which provide indications of DDM, modulation sum, and RF signal level. The receiving antenna is usually of a directional type to minimize unwanted interference and should be at the greatest height compatible with obstacle clearance limits. For course line monitoring, the antenna is usually positioned along the extended runway centre line. Where it is desired to also monitor displacement sensitivity, an additional receiver and monitor are installed with antenna suitably positioned to one side of the extended runway centre line. Some systems utilize a number of spatially separated antennas.

2.9 Localizer and glide path displacement sensitivities

2.9.1 Although certain localizer and glide path alignment and displacement sensitivities are specified in relation to the ILS reference datum, it is not intended to imply that measurement of these parameters must be made at this datum.

547CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

2.9.2 Localizer monitor system limits and adjustment and maintenance limits given in Chapter 3, 3.1.3.7 and 3.1.3.11 are stated as percentage changes of displacement sensitivity. This concept, which replaces specifications of angular width in earlier editions, has been introduced because the response of aircraft guidance systems is directly related to displacement sensitivity. It will be noted that angular width is inversely proportional to displacement sensitivity.

2.10 Siting of ILS markers

2.10.1 Considerations of interference between inner and middle markers, and the minimum operationally acceptable time interval between inner and middle marker light indications, will limit the maximum height marked by the inner marker to a height on the ILS glide path of the order of 37 m (120 ft) above threshold for markers sited within present tolerances in Annex 10. A study of the individual site will determine the maximum height which can be marked, noting that with a typical airborne marker receiver a separation period of the order of 3 seconds at an aircraft speed of 140 kt between middle and inner marker light indications is the minimum operationally acceptable time interval.

2.10.2 2.10.2 In the case of ILS installations serving closely spaced parallel runways, e.g. 500 m (1 650 ft) apart, special measures are needed to ensure satisfactory operation of the marker beacons. Some States have found it practical to employ a common outer marker for both ILS installations. However, special provisions, e.g. modified field patterns, are needed in the case of the middle markers if mutual interference is to be avoided, and especially in cases where the thresholds are displaced longitudinally from one another.

2.11 Use of DME and/or other standard radio navigation aids as an alternative to ILS marker beacons

2.11.1 When DME is used as an alternative to ILS marker beacons, the DME should be located on the airport so that the zero range indication will be a point near the runway. If the DME associated with ILS uses a zero range offset, this facility has to be excluded from RNAV area navigation solutions.

2.11.1.1 In order to reduce the triangulation error, the DME should be sited to ensure a small angle (e.g. less than 20 degrees) between the approach path and the direction to the DME at the points where the distance information is required.

2.11.1.2 The use of DME as an alternative to the middle marker beacon assumes a DME system accuracy of 0.37 km (0.2 NM) or better and a resolution of the airborne indication such as to allow this accuracy to be attained.

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2.11.1.3 While it is not specifically required that DME be frequency paired with the localizer when it is used as an alternative for the outer marker, frequency pairing is preferred wherever DME is used with ILS to simplify pilot operation and to enable aircraft with two ILS receivers to use both receivers on the ILS channel.

2.11.1.4 When the DME is frequency paired with the localizer, the DME transponder identification should be obtained by the “associated” signal from the frequency-paired localizer.

2.11.2 In some locations, the Competent Authority may authorize the use of other means to provide fixes as detailed in the Procedures for Air Navigation Services — Aircraft Operations (PANS-OPS) (Doc 8168), such as NDB, VOR or GNSS. This may be useful in particular in locations where aircraft user equipage with DME is low, or if the DME is out of service.

2.12 The use of supplementary sources of orientation guidance in association with ILS

2.12.1 Aircraft beginning an ILS approach may be assisted by guidance information provided by other ground referenced facilities such as VORs, surveillance radar or, where these facilities cannot be provided, by a locator beacon.

2.12.2 When not provided by existing terminal or en-route facilities, a VOR, suitably sited, will provide efficient transition to the ILS. To achieve this purpose the VOR may be sited on the localizer course or at a position some distance from the localizer course provided that a radial will intersect the localizer course at an angle which will allow smooth transitions in the case of auto coupling. The distance between the VOR site and the desired point of interception must be recognized when determining the accuracy of the interception and the airspace available to provide for tracking errors.

2.12.3 Where it is impracticable to provide a suitably sited VOR, a compass locator or an NDB can assist transition to the ILS. The facility should be sited on the localizer course at a suitable distance from the threshold to provide for optimum transition.

2.13 The use of Facility Performance Category I — ILS for automatic approaches and landings in visibility conditions permitting visual monitoring of the operation by the pilot 2.13.1 Facility Performance Category I — ILS installations of suitable quality can be used, in combination with aircraft flight control systems of types not relying solely on the guidance information derived from the ILS sensors, for automatic approaches and automatic landings in visibility conditions permitting visual monitoring of the operation by the pilot.

2.13.2 To assist aircraft operating agencies with the initial appraisal of the suitability of individual ILS installations for such operations, provider States 549CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

are encouraged to promulgate: a) the differences in any respect from Chapter 3, 3.1; b) the extent of compliance with the provisions in Chapter 3, 3.1.3.4 and

3.1.5.4, regarding localizer and glide path beam structure; and c) the height of the ILS reference datum above the threshold.

2.13.3 To avoid interference which might prevent the completion of an automatic approach and landing, it is necessary that local arrangements be made to protect, to the extent practicable, the ILS critical and sensitive areas.

2.14 ILS classification — supplementary ILS description method with objective to facilitate operational utilization

2.14.1 The classification system given below, in conjunction with the current facility performance categories, is intended to provide a more comprehensive method of describing an ILS.

2.14.2 The ILS localizer classification is defined by using three characters as

follows: a) I, II or III: this character indicates conformance to Facility Performance Category in Chapter 3, 3.1.3. b) A, B, C, T, D or E: this character defines the ILS points to which the localizer structure conforms to the course structure given at Chapter 3, 3.1.3.4.2, except the letter T, which designates the runway threshold. The points are defined in Chapter 3, 3.1.1.

c) 1, 2, 3 or 4: this number indicates the level of integrity and continuity of service of the localizer as defined in Chapter 3, 3.1.3.12 and summarized in Table C-4.

2.14.3 The ILS glide path classification is defined by using three characters as

follows: a) I, II or III: this character indicates conformance to Facility Performance Category in Chapter 3, 3.1.3 and 3.1.5. b) A, B, C or T: this character defines the ILS points to which the glide path structure conforms to the path structure given at Chapter 3,

3.1.5.4.2, except the letter T, which designates the runway threshold.

The points are defined in Chapter 3, 3.1.1. c) 1, 2, 3 or 4: this number indicates the level of integrity and continuity of service of the glide path as defined in Chapter 3, 3.1.5.8 and summarized in Table C-4.

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2.14.4 Examples

2.14.4.1 As an example, a Facility Performance Category II — localizer which meets the localizer course structure criteria appropriate to a Facility Performance Category III — localizer down to ILS point “D” and conforms to the integrity and continuity of service objectives of Level 3 would be described as class II/D/3.

2.14.4.2 As an example, a Facility Performance Category I — glide path which meets the glide path structure criteria appropriate to a Facility Performance Category III — glide path down to ILS point “T” and conforms to the integrity and continuity of service objectives of Level 3 would be described as class I/T/3.

2.14.5 ILS classes are appropriate only to the ground ILS element. Consideration of operational categories must also include additional factors such as operator capability, critical and sensitive area protection, procedural criteria and ancillary aids, such as transmissometers and lights.

2.15 ILS carrier frequency and phase modulation

2.15.1 In addition to the desired 90 Hz and 150 Hz AM modulation of the ILS RF carriers, undesired frequency modulation (FM) and/or phase modulation

(PM) may exist. This undesired modulation can cause centring errors in ILS receivers due to slope detection by ripple in the intermediate frequency

(IF) filter pass-band.

2.15.2 For this to occur, the translated RF carrier frequency must fall on an IF frequency where the pass-band has a high slope. The slope converts the undesired 90 Hz and 150 Hz frequency changes to AM of the same frequencies. Similarly, any difference in FM deviation between the undesired 90 Hz and 150 Hz components is converted to DDM, which in turn produces an offset in the receiver. The mechanism is identical for PM as for FM, since PM causes a change in frequency equal to the change in phase (radians) multiplied by the modulating frequency.

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2.15.3 The effect of the undesired FM and/or PM is summed by vector addition to the desired AM. The detected FM is either in phase or anti-phase with the AM according to whether the pass-band slope at the carrier’s IF is positive or negative. The detected PM is in quadrature with the AM, and may also be positive or negative according to the pass-band slope.

2.15.4 Undesired FM and/or PM from frequencies other than 90 Hz and 150 Hz, but which pass through the 90 Hz and 150 Hz tone filters of the receiver, can also cause changes to the desired 90 Hz and 150 Hz AM modulation of the ILS RF carrier, resulting in a DDM offset error in the receiver. Thus, it is essential that when measuring undesired FM and PM levels, audio band-pass filters with a pass-band at least as wide as that of the tone filters of ILS receivers be used. These filters are typically inserted in commercial modulation meter test equipment between the demodulation and metering circuits, to ensure that only spectral components of interest to ILS applications are measured. To standardize such measurements, the filter

characteristics are recommended as shown below:

2.15.5 The preferred maximum limits, as shown below, are derived from ILS receiver centring error limits specified in EUROCAE documents ED-46B 552CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 and ED-47B, based on the worst-case-to-date observed correlation

between undesired modulation levels and centring errors:

Note 1.: This column applies to the peak frequency or phase deviation as measured with the 90 Hz tone filter specified in 2.15.4.

Note 2.: This column applies to the peak frequency or phase deviation as measured with the 150 Hz tone filter specified in 2.15.4.

Note 3.: This column applies to the difference in peak frequency deviation between the separate measurements of the undesired 90 Hz FM (or equivalent PM) and the 150 Hz FM (or equivalent PM) obtained with the filters specified in the table in 2.15.4. The equivalent deviation for 90 Hz and 150 Hz measured PM values is calculated by multiplying each peak PM measurement in radians by its corresponding modulating frequency in Hz.

3. Material concerning VOR/DVOR

3.1 Guidance relating to VOR/DVOR equivalent isotropically radiated power

(EIRP) and coverage Note.:— Unless specifically mentioned, all guidance material provided below applies to VOR and DVOR signals.

3.1.1 The field strength specified at Chapter 3, 3.3.4.2, is based on the following

consideration:

The power required of minus 110 dBW is obtained at 118 MHz with a power density of minus 107 dBW/m2; minus 107 dBW/m2 is equivalent to 90 microvolts per metre, i.e. plus 39 dB referenced to 1 microvolt per metre.

553CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.:: The power density for the case of an isotropic antenna may be computed

in the following manner:

Where Pd = power density in dBW/m2;

Pa = power at receiving point in dBW; λ = wavelength in metres.

3.1.2 The necessary EIRP to achieve a field strength of 90 microvolts per metre (minus 107 dBW/m2) is given in Figure C-13. The field strength is directly proportional to the antenna elevation pattern. The actual radiation patterns of the antennas depend on a number of factors such as height of the antenna phase centre above ground level (AGL), surface roughness, terrain form and conductivity of ground and counterpoise. However, to account for lowest EIRP in notches between the lobes of the real elevation antenna pattern, a conservative value has been provided. Whenever more precise system data are available, a more precise estimation of range is permissible. Further guidance may be found in the Handbook on Radio Frequency Spectrum Requirements for Civil Aviation including statement of approved ICAO policies (Doc 9718).

3.2 Guidance in respect of siting of VOR

3.2.1 VOR is susceptible to multipath interference from surrounding terrain, buildings, trees and power lines. The effect of this should therefore be considered when selecting a site for a new facility, and when considering the acceptability of proposed developments in the vicinity of established sites. Doppler VOR is more resistant to multipath interference than conventional VOR and may be used to provide acceptable performance on more challenging multipath sites.

Note.:: Guidance on siting of VOR is given in documents EUROCAE ED-52 (including Amendment No. 1), United States Federal Aviation Administration Order 6820.10 and ICAO EUR DOC 015 (First Edition).

3.2.2 The impact of wind farm developments on VOR is an increasing problem in many States due to the growth of interest in alternative energy sources.

The impact of wind farms on VOR is difficult to assess for several reasons,

including:

554CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 a) the cumulative effect of a group of turbines may be unacceptable even though the effect of each of the turbines may be acceptable individually;

b) worst-case errors may be experienced when the turbine blades are stationary (due to either high or low wind speeds). The actual error is a function of the orientation of the turbine and position of the turbine blades when stationary;

c) worst-case errors are likely to be experienced at the limit of coverage and at low elevation angles; and d) it is unlikely that the worst-case errors can be confirmed by flight inspections due to the factors listed above.

3.2.3 Computer simulations can be used to assess the effect of wind farms on VOR using worst-case assumptions, as outlined above.

Note 1.: The curves are based on the IF-77 propagation model with a 4/3 Earth radius which has been confirmed by measurements.

555CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note 2.: The guidance provided assumes that the VOR/DVOR counterpoise height above ground level (AGL) that defines the antenna pattern is at 3 m (10 ft) AGL over flat terrain. Terrain shielding will reduce the achievable range.

Note 3.: The transmitted power required to achieve an EIRP value as shown depends upon transmitting antenna gain and cable losses. As an example, an EIRP of 25 dBW can be achieved by a VOR with an output power of 100 W, a cable loss of 1 dB and an antenna gain of 6 dBi.

3.3 [Reserved]

3.4 Criteria for geographical separation of VOR type facilities Note.: Guidance material on criteria for geographical separation of VOR type facilities is given in the Handbook on Radio Frequency Spectrum Requirements for Civil Aviation (Doc 9718, Volume II), Chapter 4.

3.5 Criteria for geographical separation of VOR/ILS facilities Note.: Guidance material on criteria for geographical separation of VOR/ILS facilities is given in the Handbook on Radio Frequency Spectrum Requirements for Civil Aviation (Doc 9718, Volume II), Chapter 4.

3.6 Receiving function

3.6.1 Sensitivity. After due allowance has been made for aircraft feeder mismatch, attenuation loss and antenna polar diagram variation, the sensitivity of the receiving function should be such as to provide on a high percentage of occasions the accuracy of output specified in 3.6.2, with a signal having a field strength of 90 microvolts per metre or minus 107 dBW/m2.

3.6.2 Accuracy. The error contribution of the airborne installation should not exceed plus or minus 3 degrees with a 95 per cent probability.

Note 1.: The assessment of the error contribution of the receiver will need to take

account of:

1) the tolerance of the modulation components of the ground VOR facility as defined in Chapter 3, 3.3.5;

2) variation in signal level and carrier frequency of the ground VOR facility;

3) the effects of unwanted VOR and ILS signals.

Note 2.: The airborne VOR installation is not considered to include any special 556CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 elements which may be provided for the processing of VOR information in the aircraft and which may introduce errors of their own (e.g. radio magnetic indicator (RMI).).

3.6.3 Flag alarm operation. Ideally, the flag alarm should warn a pilot of any unacceptable malfunctioning conditions which might arise within either the ground or airborne equipments. The extent to which such an ideal might be satisfied is specified below.

3.6.3.1 The flag alarm movement is actuated by the sum of two currents which are derived from the 30 Hz and 9 960 Hz elements of the VOR bearing component signal and, therefore, the removal of these elements from the radiated carrier results in the appearance of the flags. Since the VOR ground monitor interrupts the bearing components when any unacceptable condition prevails on the ground, there will be an immediate indication within an aircraft when the system is unusable.

3.6.3.2 The flag alarm movement current is also dependent upon the AGC characteristics of the airborne equipment and any subsequent gain following the receiver’s second detector. Thus, if with a correctly adjusted airborne receiver the flag is just out of view when receiving a VOR signal conforming to the modulation characteristics specified in Chapter 3, 3.3.5, the flags will again become visible in the event of a decrease in the receiver’s overall gain characteristics.

Note.: Certain types of receivers employ warning indications other than mechanical flags to perform the functions described here.

3.6.4 VOR receiver susceptibility to VOR and localizer signals Note.: Guidance material on VOR receiver susceptibility to VOR and localizer signals is given in the Handbook on Radio Frequency Spectrum Requirements for Civil Aviation (Doc 9718, Volume II), Chapter 4.

3.6.5 Immunity performance of VOR receiving systems to interference from VHF FM broadcast signals Note.: Guidance material on VOR receiving systems to interference from VHF FM broadcast signals is given in the Handbook on Radio Frequency Spectrum Requirements for Civil Aviation (Doc 9718, Volume II), Chapter

4.

3.7 VOR system accuracy Note.: Guidance material on the determination of VOR system performance values is also contained in Annex 11, Attachment A.

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3.7.1 Purpose. The following guidance material is intended to assist in the use of VOR systems. It is not intended to represent lateral separation standards or minimum obstacle clearances, although it may of course provide a starting point in their determination. The setting of separation standards or minimum obstacle clearances will necessarily take account of many factors not covered by the following material.

3.7.1.1 There is, however, a need to indicate a system use accuracy figure for the guidance of States planning VOR systems.

3.7.2 Explanation of terms. The following terms are used with the meanings

indicated: a) VOR radial signal error. The difference between the nominal magnetic bearing to a point of measurement from the VOR ground station and the bearing indicated by the VOR signal at that same point. The VOR radial signal error is made up of certain stable elements, such as course displacement error and most site and terrain effect errors, and certain random variable errors. The VOR radial signal error is associated with the ground station only and excludes other error factors, such as airborne equipment errors and pilotage element.

b) VOR radial variability error. That part of the VOR radial signal error which can be expected to vary about the essentially constant remainder. The radial variability error is the sum of the variable errors.

c) VOR radial displacement error. That part of the VOR radial signal error which is stable and may be considered as fixed for long periods of time. d) VOR airborne equipment error. That error attributable to the inability of the equipment in the aircraft to translate correctly the bearing information contained in the radial signal. This error includes the contributions of the airborne receiver and the instrumentation used to present the information to the pilot.

e) VOR aggregate error. The difference between the magnetic bearing to a point of measurement from the VOR ground station and the bearing indicated by airborne VOR equipment of stated accuracy.

More simply put, this is the error in the information presented to the pilot, taking into account not only the ground station and propagation path errors, but also the error contributed by the airborne VOR receiver and its instrumentation. The entire VOR radial signal error, both fixed and variable, is used.

558CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 f) VOR pilotage element. The error in the use of VOR navigation attributable to the fact that the pilot cannot or does not keep the aircraft precisely at the centre of the VOR radial or bearing indicated by the equipment.

g) VOR system use error. The square root of the sum of the squares

(RSS) of VOR aggregate error and the pilotage element. This combination may be used to determine the probability of an aircraft remaining within specified limits when using VOR.

3.7.3 Calculation of VOR system use accuracy

3.7.3.1 The VOR system use accuracy is derived by considering the following

error elements: a) VOR radial signal error (Eg). This element consists of the radial displacement error and the radial variability error. It is determined by considering such factors as fixed radial displacement, monitoring, polarization effects, terrain effects and environment changes.

b) VOR airborne equipment error (Ea). This element embraces all factors in the airborne VOR system which introduces errors (errors resulting from the use of compass information in some VOR displays are not included).

c) VOR pilotage element (Ep). The value taken for this element is that used in PANS-OPS (Doc 8168) for pilot tolerance.

Note.: A measurement error also exists, but in a generalized discussion of errors may be considered to be absorbed in the other error values.

3.7.3.2 Since the errors in a), b), and c), when considered on a system basis (not any one radial) are independent variables, they may be combined on a root-sum-square method (RSS) when the same probability level is given to each element. For the purpose of this material, each element is considered to have a 95 per cent probability.

Therefore, the following formulae are derived:

3.7.3.3 The following examples will derive only the VOR system use error but calculations can also be made to determine VOR aggregate error, if desired. By use of these formulae, the impact on the system of improvement or degradation of one of more error elements can be 559CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 assessed.

Note.: All figures for VOR radial signal error are related to radials for which no restrictions are published.

3.7.3.4 Subject to the qualifications indicated in 3.7.1, it is considered that a VOR system use accuracy of plus or minus 5 degrees on a 95 per cent probability basis is a suitable figure for use by States planning the application of the VOR system (see, however, 3.7.3.5). This figure

corresponds to the following component errors:

VOR radial signal error: plus or minus 3° (95 per cent probability), a value readily achieved in practice.

VOR airborne equipment error: plus or minus 3° (95 per cent probability), system characteristics value (see

3.6.2).

VOR pilotage element: plus or minus 2.5° (95 per cent probability), in accordance with PANS-OPS (see also 3.7.3.8).

3.7.3.5 While the figure of plus or minus 5 degrees on a 95 per cent probability basis is a useful figure based on broad practical experience and used by many States, it must be noted that this figure may be achieved only if the error elements which make it up remain within certain tolerances. It is clear that, if the errors attributable to the VOR system elements are larger than the amounts noted, the resulting VOR system use error will also be larger.

Conversely, where any or all of the VOR system error elements are smaller than those used in the above computation, the resulting VOR system use error will also be smaller.

3.7.3.6 The following examples, also derived from practical experience, provide

additional planning guidance for States:

A.— VOR radial signal error: plus or minus 3.5° (95 per cent probability), used by some States as the total ground system error.

VOR airborne equipment error: plus or minus 4.2° (95 per cent probability), recognized in some States as the minimum performance figure for some classes of operations.

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VOR pilotage element: plus or minus 2.5° (95 per cent probability), in accordance with PANS-OPS (see also 3.7.3.8).

Calculated VOR system use accuracy: plus or minus 6° (95 per cent probability).

B. — VOR radial signal error: plus or minus 1.7° (95 per cent probability), based on extensive flight measurements conducted in one State on a large number of VORs.

VOR airborne equipment error: plus or minus 2.7° (95 per cent probability), achieved in many airline operations.

VOR pilotage element: plus or minus 2.5° (95 per cent probability), in accordance with PANS-OPS (see also 3.7.3.8).

Calculated VOR system use accuracy:

3.7.3.7 More realistic application of the VOR system may be achieved by assessing the errors as they actually exist in particular circumstances, rather than by using all-embracing generalizations which may give unduly optimistic or pessimistic results. In individual applications, it may be possible to utilize a system use accuracy value less than plus or minus 5 degrees if one or more of the error elements are smaller than the values used to compute the plus or minus 5 degrees. Conversely, a system use accuracy value greater than plus or minus 5 degrees will be necessary where it is known that radials are of poor quality or significant site errors exist, or for other reasons. However, in addition to this advice a warning is also essential regarding the use of lower values of individual elements in the system (for example, the radial signal error) on the assumption that an overall improvement in system accuracy will occur. There is considerable evidence that this may not be the case in some circumstances and that lower system accuracy values should not be applied without other confirmation (e.g. by radar observation) that an actual improvement in overall performance is being achieved.

3.7.3.8 It is to be noted that in angular systems such as the VOR, the pilotage element error, expressed in angular terms, will be greater as the aircraft nears the point source. Thus, while ground system and airborne error 561CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 contributions, expressed in angular terms, are for all practical purposes constant at all ranges, it is necessary when considering the overall system use accuracy figures to take into account the larger pilotage element error occurring when the aircraft is near the VOR. However, these larger pilotage element errors do not result in large lateral deviations from course when near the facility.

3.8 Changeover points for VORs Guidance on the establishment of changeover points on ATS routes defined by VORs is contained in Annex 11, Attachment A.

4. Precision approach radar system Figures C-14 to C-18 illustrate certain of the Standards contained in

Chapter 3, 3.2.

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5. Specification for 75 MHz marker beacons (en-route)

5.1 Marker beacon antenna arrays

5.1.1 General. The following describes types of marker antenna arrays that are frequently used in current practice. These types are the simplest forms meeting normal requirements; in special cases, arrays having a better performance (see Note to 5.1.4) may be required.

5.1.2 Marker beacons a) Radiating system. A radiating system consisting of two horizontal dipole arrays crossed at right angles, each comprising two co-linear half-wave radiating elements with centres spaced approximately a half wavelength apart and mounted one-quarter wavelength above the counterpoise. The currents in the dipoles and their respective

elements are adjusted so that:

1) the current in one set of dipole arrays relative to that in the other set is equal but differs in time phase by 90 degrees;

2) the currents in the radiating elements of a particular dipole array are equal and in time phase. b) Counterpoise. A square counterpoise with minimum dimensions of 9 m × 9 m, usually elevated about 1.8 m (6 ft) above the ground and, if 564CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 fabricated from wire mesh, with the dimension of the mesh not exceeding 7.5 cm × 7.5 cm.

5.1.3 Fan marker beacons for use only at low altitudes (low power fan marker beacons). A radiating system capable of providing the field strengths indicated in Chapter 3, 3.1.7.3.2.

5.1.4 Fan marker beacons for general use (high power fan marker beacons) a) Radiating system. A radiating system consisting of four horizontal co- linear half-wave (approximate) radiating elements mounted approximately one-quarter wavelength above the counterpoise. The current in each of the antenna elements should be in phase and should have a current ratio of 1:3:3:1.

Note.: The current distribution between elements and their height above the counterpoise may be altered to provide patterns for specific operational requirements. Improved vertical patterns for certain operational needs may be achieved by adjusting the height of the dipole arrays above the counterpoise to a value of one-quarter wavelength or greater, but less than a half wavelength.

b) Counterpoise. A rectangular counterpoise with minimum dimensions of 6 m × 12 m, usually elevated about 1.8 m (6 ft) above the ground and, if fabricated from wire mesh, with the dimension of the mesh not exceeding 7.5 cm × 7.5 cm.

5.2 Identification coding for fan marker beacons associated with a four-course radio range

5.2.1 Fan marker beacons located on the legs of a four-course radio range do not normally require an identification signal relating to a particular geographic location, but only a signal that will indicate the leg with which they are associated.

5.2.2 In the case of a four-course radio range having not more than one marker on any leg, it is current practice to identify a marker by a single dash if on the leg bearing true north or nearest to north in a clockwise direction (east), and to identify a marker on other legs by two, three or four dashes according to whether the leg with which it is associated is the second, third or fourth leg from north in a clockwise direction. Where more than one fan marker beacon is associated with one leg of a fourcourse radio range, the marker nearest to the station is identified by dashes only, the next nearest by two dots preceding the dashes, and the third by three dots preceding the dashes, and so on.

Note.: In certain special circumstances, the above coding system may lead to ambiguities due to two markers associated with the legs of different but 565CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 overlapping radio ranges being geographically close together. In such cases, it is desirable to use a distinctive identification coding with one of the marker beacons.

6. Material concerning NDB

6.1 Guidance material on NDB field strength requirements in latitudes between 30°N and 30°S

6.1.1 In order to obtain a satisfactory service within the rated coverage of an NDB located in latitudes between 30°N and 30°S, a minimum value of field strength of 120 microvolts per metre would be required, except where practical experience in the operation of NDBs over several years has revealed that a minimum field strength of 70 microvolts per metre would be adequate to meet all the operational needs. In some specific areas, field strength values considerably in excess of 120 microvolts per metre would be required. Such areas are:

a) Indonesia and Papua New Guinea, Myanmar, Malay Peninsula, Thailand, Lao People’s Democratic Republic, Democratic Kampuchea, Viet Nam and Northern Australia; b) Caribbean and northern parts of South America;

c) Central and South Central Africa.

6.1.2 The field strength of 120 microvolts per metre is based upon practical experience to date and is a compromise between what is technically desirable and what it is economically possible to provide.

6.2 Guidance material on meaning and application of rated and effective coverage

6.2.1 Rated coverage

6.2.1.1 The rated coverage as defined in Chapter 3, 3.4.1, is a means of designating actual NDB performance, in a measurable way, which is dependent on the frequency, the radiated power, and the conductivity of the path between the NDB and a point on the boundary where the minimum value of field strength is specified.

6.2.1.2 The rated coverage has been found to be a useful means of facilitating regional planning and, in some instances, may be related to effective coverage.

6.2.1.3 The application of rated coverage to frequency planning is governed by

the following criteria:

566CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

6.2.1.3.1 Frequencies should be deployed having regard to the rated coverage of the NDBs concerned, so that the ratio of the signal strength of any NDB at the boundary of its rated coverage to the total field strength due to co- channel stations and adjacent channel stations (with an appropriate allowance for the selectivity characteristics of a typical airborne receiver) is not less than 15 dB by day.

6.2.1.3.2 The figures set forth in Attachment B to Volume V of Annex 10 should be applied, as appropriate, in determining the allowance to be made for the attenuation of adjacent channel signals.

6.2.1.4 It follows from the application of rated coverage to frequency deployment planning that, unless otherwise specified, protection against harmful interference can only be ensured within the rated coverage of an NDB and, then, only if the radiated power of the NDBs is adjusted to provide within reasonably close limits the field strength required at the limit of the rated coverage. In areas where the density of NDBs is high, any NDB providing a signal at the limit of its rated coverage materially in excess of that agreed in the region concerned will give rise, in general, to harmful interference within the rated coverages of cochannel or adjacent channel NDBs in the area concerned, and will limit the number of NDBs which can be installed in the region within the available spectrum. It is important, therefore, that increases in radiated power beyond that necessary to provide the rated coverage, particularly at night when sky wave propagation may give rise to interference over long distances, should not be made without coordination with the authorities of the other stations likely to be affected (see Chapter 3, 3.4.3).

6.2.1.5 Frequency planning is considerably facilitated if a common value of minimum field strength within the desired coverage is used.

6.2.1.6 Extensive experience has shown that in relatively low noise level areas, such as Europe, the figure of 70 microvolts per metre is satisfactory.

6.2.1.6.1 Experience has also shown that the figure of 120 microvolts per metre is generally satisfactory for higher noise level areas but will be inadequate in areas of very high noise. In such areas, the information given in 6.3 may be used for general guidance.

6.2.2 Relationship to effective coverage

6.2.2.1 Rated coverage may have a close correlation to effective coverage under

the following conditions: a) when the minimum field strength within the rated coverage is such that, for most of the time, it exceeds the field strength due to atmospheric and other noise sufficiently to ensure that the latter will not distort the information presented in the aircraft to the extent that it is unusable;

567CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 b) when the ratio of the strength of the wanted signal to that of interfering signals xceeds the minimum required value at all points within the coverage, in order to ensure that interfering signals will also not distort the information presented in the aircraft to the extent that it is unusable.

6.2.2.2 Since, normally, the lowest signal within the coverage will occur at its boundary, these conditions imply that at the boundary the field strength should be such that its ratio to atmospheric noise levels would ensure usable indications in the aircraft for most of the time and that, in respect of the boundary value, overall planning should ensure that the ratio of its value to that of interfering signals exceeds the required value for most of the time.

6.2.2.3 Although the value of 70 microvolts per metre used for frequency deployment has been found successful in Europe (i.e. north of 30° latitude) in giving coverage values which closely approximate to effective coverage most of the time, experience is too limited to prove the suitability of the 120 microvolts per metre value for general application in areas of high noise. It is to be expected that rated coverages in high noise based on a boundary value of 120 microvolts per metre will, on many occasions, be substantially greater than the effective coverage achieved. In such areas, in order to secure a better correlation between rated coverage and an average of the achieved effective coverage, it may be advisable to choose a boundary value based more closely on the proportionality of noise in that area to the noise in areas where a boundary value has been satisfactorily established (e.g. Europe), or to determine an appropriate value from a statistical examination of achieved effective coverages in respect of an NDB in the area of known performance.

6.2.2.4 It is important to appreciate, however, that minimum values of field strength based on a simple comparison of noise levels in different areas may be insufficient, because factors such as the frequency of occurrence of noise, its character and effect on the airborne receiver and the nature of the air operation involved may all modify ratios determined in this way.

6.2.2.5 Values of diurnal and seasonal noise in various parts of the world have been published in Report 322 of the former CCIR of the ITU.

6.2.2.5.1 Correlation of these values to actual local conditions and the derivation of required signal-to-noise ratios for effective operational use of ADF equipment is not yet fully established.

6.2.3 Effective coverage

6.2.3.1 Effective coverage as defined in Chapter 3, 3.4.1, is the area surrounding an NDB, within which useful information to the operator concerned can be obtained at a particular time. It is, therefore, a measure of NDB 568CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 performance under prevailing conditions.

6.2.3.2 The effective coverage is limited by the ratio of the strength of the steady (non-fading) signal received from the NDB to the total noise intercepted by the ADF receiver. When this ratio falls below a limiting value, useful bearings cannot be obtained. It should also be noted that the effective coverage of an NDB may in some cases be limited to the range of the usable identification signal.

6.2.3.3 The strength of signal received from the NDB is governed by: a) the power supplied to the antenna of the NDB; b) the radiation efficiency of the antenna, which varies according to the height of the antenna and other characteristics of the radiating system;

c) the conductivity of the path between the NDB and the receiver, which may vary considerably as between one site and another, and is always less over land than over seawater; d) the operating radio frequency.

6.2.3.4 The noise admitted by the receiver depends on: a) the bandwidth of the receiver; b) the level of atmospheric noise, which varies according to the geographical area concerned, with the time of day and the season of the year, and which may reach very high levels during local thunderstorms;

c) the level of the interference produced by other radio emissions on the same or on adjacent frequencies, which is governed to a large extent by the NDB density in the area concerned and the effectiveness of regional planning;

d) the level of noise due to electrical noise in the aircraft or to industrial noise (generated by electric motors, etc.), when the coverage of the NDB extends over industrial areas.

6.2.3.4.1 It has to be noted that the effect of noise depends on characteristics of the ADF receiver and the associated equipment, and also on the nature of the noise (e.g. steady noise, impulsive noise).

6.2.3.5 A further factor which limits the effective coverage of an NDB is present at night when interaction occurs between components of the signal which are propagated respectively in the horizontal plane (ground wave propagation) and by reflection from the ionosphere (sky wave propagation). When there is interaction between these components, which arrive at the ADF receiver 569CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 with a difference of phase, bearing errors are introduced (night effect).

6.2.3.6 It will thus be seen that the effective coverage of an NDB depends on so many factors, some of which are variable, that it is impossible to specify the effective coverage of an NDB in any simple manner. The effective coverage of any NDB, in fact, varies according to the time of day and the season of the year.

6.2.3.6.1 Hence any attempt to specify an effective coverage, which would be obtainable at any time throughout the day or throughout the year, would result either in a figure for coverage which would be so small (since this would be the coverage obtained under the worst conditions of atmospheric noise, etc.) as to give quite a misleading picture of the effectiveness of the NDB, or would involve such high power and costly antenna systems (to provide the required coverage under the worst conditions), that the installation of such an NDB would usually be precluded by considerations of initial and operating costs. No specific formula can be given in determining what rated coverage would be equivalent to a desired effective coverage and the relation must be assessed regionally.

6.2.3.7 Those concerned with the operational aspects of NDB coverage will normally consider requirements in terms of a desired operational coverage and, in regional planning, it will usually be necessary to interpret such requirements in terms of a rated coverage from which may be derived the essential characteristics of the NDB required and which will also define the area to be protected against harmful interference. No specific formula can be given in determining what rated coverage would be equivalent to a desired operational coverage and the relation must be assessed regionally.

6.2.3.8 Some States have recorded data on NDBs and their effective coverage; and collection of similar information would be a practical way of obtaining an assessment of effective coverage in terms of rated coverage of facilities in a given area. This information would also be useful for future regional planning. In order to reduce the number of factors involved in assessing effective coverage, it would be desirable to establish criteria for determining the limit of useful coverage in terms of the reaction of the bearing indicator. The data referred to previously, together with measurements of actual field strength within the coverage of the NDB, would also permit determination of the effectiveness of existing installations and provide a guide to improvements that may be necessary to achieve a desired effective coverage.

6.3 Coverage of NDBs

6.3.1 Introduction

6.3.1.1 The following studies have been based on the latest propagation and noise data available to the ITU. They are included in this Attachment as general 570CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 guidance in respect of NDB planning. Attention is called particularly to the assumptions made.

6.3.1.2 When applying the material, the validity of the assumptions in respect of the particular conditions under consideration should be carefully examined and, in particular, it should be noted that the assumed signal-to-noise ratios require considerable further study before they can be accepted as representative of the ratios limiting useful reception.

6.3.2 Assumptions

1. Operating frequency — 300 kHz.

Reference is made, however, where appropriate, to frequencies of 200 kHz and 400 kHz.

2. a) Average soil conductivity: (σ = 10–13 e.m.u.) b) Average seawater conductivity: (σ = 4.10–11 e.m.u.)

3. The level of atmospheric noise (RMS) which is likely to prevail: 1) by day, 2) by night, over land masses, within the belts of latitude mentioned. [The values of expected noise have been derived from Recommendation ITU-R P.372-6 and have been taken as the average noise by day and by night during equinox periods, i.e. the values which are likely to be exceeded 20–25 per cent of the year.]

4. Input powers to the antenna of the NDB of: a) 5 kW b) 1 kW c) 500 W d) 100 W e) 50 W f) 10 W

5. The following average values of radiation efficiencies of antennas, i.e.

the ratio of:

571CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 i) The figure for a) is included because it is possible to realize this efficiency by the use of a more elaborate antenna system than is usually employed.

ii) The figure for h) is included because many low power NDBs use very inefficient antennas.

6. An admittance band of the ADF receiver of 6 kHz.

7. Required ratios of signal-(median) to-noise (RMS) of: a) 15 dB by day; b) 15 dB by night.

6.3.3 Results of studies A.— Minimum field strengths required at the boundary of the rated

coverage:

A star shown against a figure indicates that a higher value of field strength — probably 2 or 3 times the values shown (plus 6 to plus 10 dB) — may be necessary in the presence of high aircraft noise and/or industrial noise.

B.— Coverage of NDBs (expressed in terms of the radius of a circle, in kilometres, with the NDB at the centre) which may be expected under the

assumptions made:

572CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

6.3.3.1 In all of the above tables, it has to be noted that: a) the distances are given in kilometres, in accordance with ITU practice; b) the figures in the final columns, with the heading 10 W, are calculated on the assumption that the low power NDB uses a very inefficient antenna (see 6.3.2, assumption 5 h));

573CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 c) a star shown against a figure indicates that the coverage may be limited by aircraft and industrial noises.

6.3.3.2 It has also to be noted that: a) if a frequency of 200 kHz were used in place of 300 kHz, this would not appreciably affect the coverage of low power short range NDBs, but the coverage of the higher power, longer range beacons (for example, those with a range of 150 km or more) would be increased, as compared with those shown in the tables, by about 20 per cent;

b) if a frequency of 400 kHz were used in place of 300 kHz this would not appreciably affect the coverage of low power short range NDBs, but the coverage of the higher power, longer range beacons (for example, those with a range of 150 km or more) would be decreased, as compared with those shown in the tables, by about 25 per cent;

c) use of an ADF receiver with a narrower band would, other things being equal, provide wider coverage for the same radiated power of the NDB or, for the same coverage, an improved effective signal-to- noise ratio.

For example, if an admittance band of 1 kHz instead of 6 kHz were used, the coverage might be increased by as much as 30 per cent for the same radiated power or, alternatively, the effective signal-to-noise ratio might be increased by as much as 8 dB;

d) if a sector of the coverage of an NDB is over seawater, a greater

coverage may be expected within that sector due to:

1) better ground wave propagation over seawater than over land;

2) the noise level, which is highest over land, often drops fairly steeply with increasing distance from the land. It might be assumed, therefore, that the distances shown in the tables could be increased by about 30 per cent by day, and by about 20 per cent by night, when the path is over seawater;

e) if, however, the beacon is sited on an island remote from land masses (for example, in mid-Pacific or mid-Atlantic, but not in the Caribbean), the coverage of the beacon is likely to be much greater, particularly in tropical latitudes, than is indicated in the tables; and in such cases figures for coverage similar to those shown for latitudes more than 350N and S may be assumed for all latitudes, due to the much lower level of atmospheric noise which prevails in midocean as compared with that experienced over, or in proximity to, land masses.

6.3.4 Limitation of coverage of a beacon at night due to “night effect”.

574CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 a) The distances, at night, at which the ground wave and sky wave

components of the received field are likely to be equal are as follows:

Frequency Over land Over sea 200 kHz 500 km 550 km 300 kHz 390 km 520 km 400 kHz 310 km 500 km b) The distances, at night, at which the ground wave component of the received field is likely to exceed the sky wave component by 10 dB

are as follows:

Frequency Over land Over sea 200 kHz 300 km 320 km 300 kHz 230 km 300 km 400 kHz 200 km 280 km c) It is, therefore, unlikely that reliable bearings can be obtained, at night, due to interaction of the two components of the received field, at much greater distances than those shown in 6.3.4 b). These distances are independent of the power of the NDB.

d) It has to be noted, moreover, that, while with overland paths of good conductivity, night effect will only be serious at somewhat greater distances than those indicated over paths of poor conductivity, night effect may become pronounced at much shorter ranges. This will also depend to some extent upon the characteristics of the radiation system.

6.4 Considerations affecting operations of NDBs

6.4.1 Depth of modulation

6.4.1.1 In specifying that the depth of modulation should be maintained as near to 95 per cent as is practicable, it must be noted that, at the frequencies used for NDBs, the small antennas generally in use can affect the effective modulation depth of the NDB system due to attenuation of the sidebands.

6.4.1.2 At this order of frequency, the antennas are normally only a small fraction of a wavelength long; they are therefore highly reactive and tend to have a high Q.

6.4.1.3 The effect is illustrated in Figure C-19, which was compiled from measurements made by one State. The modulating frequency in these measurements was 1 020 Hz. If a lower modulating frequency were used, the effect would be less.

575CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

6.4.1.4 In order to reduce the attenuation, attempts should be made to reduce the Q of the antenna. This can be done in two ways, by increasing either its capacity or resistance.

6.4.1.5 Inserting additional resistance in an antenna wastes power, whereas increasing the capacity does not. Additionally, the effect of increasing the capacity is to reduce the voltage across the system and hence to reduce the insulation problems.

6.4.1.6 For these reasons, it is considered desirable to increase antenna capacity by the use of a top load as, for example, in the so-called umbrella top capacity.

6.4.2 Earth systems Frequency planning is done on the assumption that the field strength will be maintained at the correct value. If the earth resistance is high (i.e. an insufficient earth system), not only will the radiation efficiency be low but the power radiated will be sensitive to changes in climatic conditions and other factors affecting the earth loss. In all cases, the earth system needs to be the best possible, taking into account all local circumstances.

576CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

6.5 Considerations affecting the choice of the modulating frequency for NON/A2A NDBs Recognition of the fact that modern narrow band ADF receivers have improved selectivity characteristics requires consideration of the fact that, in so far as attenuation of the audio sidebands by these receivers results in a reduction of the effective depth of modulation of the signal, the distance at which satisfactory identification is obtained is consequently reduced. In such circumstances, it is considered that 400 Hz would provide a better identification service than 1 020 Hz. There is some evidence, however, that under conditions of high atmospheric noise, the higher frequency of 1 020 Hz may provide a more easily readable signal.

7. Material concerning DME

7.1 Guidance material concerning both DME/N and DME/P 577CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

7.1.1 System efficiency

7.1.1.1 System efficiency is the combined effect of down-link garble, ground transponder dead time, up-link garble, and interrogator signal processor efficiency. Since each of these efficiency components are statistically independent, they can be computed individually and then combined to yield the system efficiency. The effect of a single component is defined as the percentage ratio of valid replies processed by the interrogator in response to its own interrogations assuming all other components are not present. The system efficiency is then the product of the individual components.

7.1.1.2 In computing system efficiency, the number of missing replies as well as the accuracy of the range measurement made with the received replies should be considered. Missing replies may result from signal interference due to garble or from interrogations being received at the transponder during a dead time period. Replies which contain significant errors large enough to be rejected by the interrogator signal processing also should be treated as missing replies when computing the efficiency component.

7.1.1.3 The interference rate due to garble is dependent upon the channel assignment plan, traffic loading, and the ground transponder and interrogator receiver bandwidths. Because the FA mode has a wider receiver bandwidth than the IA mode, it is more susceptible to interference.

These factors were accommodated in the DME/P system definition and normally do not require special consideration by the operating authority.

7.1.2 Down-link garble Down-link garble occurs when valid interrogations at the ground transponder are interfered with by coincident interrogations from other aircraft and results in loss of signal or errors in time-of-arrival measurement. This undesired air-to ground loading is a function of the number of interrogating aircraft in the vicinity of the serving transponder and the corresponding distribution of interrogation frequencies and signal amplitudes received at the transponder.

Note.: Transponder to transponder garbling is controlled by the channel assignment authorities.

7.1.3 Up-link garble Up-link garble occurs when valid replies at the interrogator are interfered with by other transponders and results in loss of signal or errors in pulse time-of-arrival measurement. The garble can be interference from any transponder whose frequency is within the bandwidth of the interrogator, including those on the same frequency, but with different pulse coding.

This undesired ground-to-air loading is a function of the number of 578CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 transponders in the vicinity of the interrogator and the corresponding distribution of reply frequencies and signal amplitudes received at the interrogator.

7.1.4 Interrogator processor efficiency The interrogator signal processor efficiency is the ratio of the number of replies processed by the interrogator to the number of interrogations in the absence of garble and transponder dead time effects. This efficiency depends on the reply pulse threshold level and the receiver noise level.

7.1.5 Relationship between aircraft served and transmission rate

7.1.5.1 Specification of the maximum transponder transmission rate establishes the maximum average transmitter power level. Chapter 3, 3.5.4.1.5.5 recommends that the transponder have a transmission rate capability of 2 700 pulse pairs per second if 100 aircraft are to be served. This represents typical transponder loading arising from 100 aircraft. To determine the actual transmission rate capability that should be accommodated at a given facility during peak traffic conditions requires that the maximum number of interrogators be estimated. To compute the interrogation loading on the transponder, the following should be considered:

a) the number of aircraft that constitutes the peak traffic load; b) the number of interrogators in use on each aircraft; c) the distribution of operating modes of the interrogators in use (e.g. search, initial approach, final approach, ground test);

d) the appropriate pulse repetition frequency as given in Chapter 3,

3.5.3.4.

7.1.5.2 Given the interrogation loading which results from the peak traffic as well as the reply efficiency of the transponder in the presence of this load, the resulting reply rate can be computed, thereby establishing the required transmitter capability. This reply rate is the level that, when exceeded, results in a reduction in receiver sensitivity (as specified in Chapter 3,

3.5.4.2.4) in order to maintain the reply rate at or below this maximum level.

7.1.6 Siting of DME associated with ILS or MLS

7.1.6.1 The DME should, where possible, provide to the pilot an indicated zero range at touchdown in order to satisfy current operational requirements.

7.1.6.2 The optimum site for a DME transponder is dependent upon a number of technical and operational factors. DME/N may be installed with ILS or MLS where operational requirements permit. DME/P, which provides higher 579CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 accuracy and coverage throughout the entire runway region, is required to support the more flexible and advanced operations that are available with MLS.

7.1.6.3 In the case of DME/N, the provision of zero range indication may be achieved by siting the transponder as close as possible to the point at which zero range indication is required. Alternatively, the transponder time delay can be adjusted to permit aircraft interrogators to indicate zero range at a specified distance from the DME antenna. If this is done, a resulting disadvantage is that such facilities will not be usable to support performance-based navigation as described in 7.2.3. When the indicated DME zero range has a reference other than the DME antenna or the DME provides only sectorial coverage, consideration should be given to publishing this information.

7.1.6.4 In the case of DME/P, in order to meet accuracy and coverage requirements, particularly in the runway region, it is recommended that the DME/P be sited as closely as possible to the MLS azimuth facility, consistent with obstacle clearance criteria. For aircraft equipped with a full MLS capability, the desired zero range indication can then be obtained by utilizing MLS basic data. Note that the DME/P transponder time delay must not be adjusted for this purpose.

7.1.6.5 It is desirable that all users obtain indicated zero range at touchdown irrespective of the airborne equipment fitted. This would necessitate location of the DME/P abeam the runway at the touchdown point. In this case accuracy requirements for DME/P would not be met on the runway.

It must be noted that MLS Basic Data Word 3 only permits the coding of DME/P coordinates within certain limits.

7.1.6.6 If an MLS/DME/P and an ILS/DME/N serve the same runway, an aircraft equipped with a minimum MLS capability can have a zero range indication at the MLS approach azimuth site when operating on MLS and a zero range indication at the touchdown point when operating on ILS. As this is considered to be operationally unacceptable, specifically from an ATC point of view, and if ILS/MLS/DME frequency tripling to prevent the relocation of the DME/N is not possible, the implementation of DME/P is to be postponed until the DME/N is withdrawn.

7.1.6.7 The nominal location of the zero range indication provided by a DME/N interrogator needs to be published.

7.1.6.8 In considering DME sites, it is also necessary to take into account technical factors such as runway length, profile, local terrain and transponder antenna height to assure adequate signal levels in the vicinity of the threshold and along the runway, and also to assure the required coverage volume (circular or sector). Care is also to be taken that where distance information is required in the runway region, the selected site is not likely to cause the interrogator to lose track due to excessive rate of change of 580CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 velocity (i.e. the lateral offset of the DME antenna must be chosen with care).

7.1.7 Geographical separation criteria Note.: Guidance material on DME geographical separation criteria is given in the Handbook on Radio Frequency Spectrum Requirements for Civil Aviation (Doc 9718, Volume II), Chapter 5.

7.1.8 Desired to undesired (D/U) signal ratios at the airborne receiver Note.: Guidance material on desired to undesired (D/U) signal ratios at the airborne DME receiver is given in the Handbook on Radio Frequency Spectrum Requirements for Civil Aviation (Doc 9718, Volume II), Chapter

5.

7.1.9 Special considerations for DME Y and Z channel assignments The channel assignment plan for DME is such that the transponder reply frequency for each Y or Z channel is the same as the interrogation frequency of another DME channel. Where the reply frequency of one DME matches the interrogation frequency of a second DME, the two transponders should be separated by a distance greater than the radio horizon distance between them. The radio horizon distance is calculated taking into account the elevations of the two transponder antennas.

7.1.10 Special considerations for DME/P associated with ILS

7.1.10.1 For those runways where it is intended to install DME associated with ILS and where early MLS/RNAV area navigation operations are planned, installation of DME/P is preferred.

7.1.10.2 When it is intended to use the DME/P ranging information throughout the terminal area, interrogation pulse pairs with the correct spacing and nominal frequency must trigger the transponder if the peak power density at the trans-ponder antenna is at least minus 93 dBW/m2. This sensitivity level is based on the values contained in Chapter 3, 3.5.4.2.3.1 and it is applied to DME/P IA mode, where at this level DME/P IA mode is intended to comply with DME/N reply efficiency and at least DME/N accuracy.

7.1.11 Considerations for the universal access transceiver (UAT)

7.1.11.1 Frequency planning criteria to ensure compatibility between DME and the UAT are contained in Part II of the Manual on the Universal Access Transceiver (UAT) (Doc 9861).

7.2 Guidance material concerning DME/N only

7.2.1 Coverage of DME/N 581CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

7.2.1.1 Whether a particular installation can provide the required frequency, protected coverage volume can be determined by using Figure C-20. The propagation loss for paths without obstructions uses the IF-77 propagation model.

7.2.1.2 Whenever a DME that provides coverage using either a directional or bi- directional DME antenna, the antenna pattern in azimuth and elevation has to be taken into account to achieve the full benefit of the reduced separation requirements outside the antennas main lobe. The actual radiation patterns of the antennas depend on a number of factors, including height of the antenna phase centre, height of the DME counterpoise above ground level (AGL), terrain surface roughness, terrain form, site elevation above mean sea level (MSL), and conductivity of ground and counterpoise. For coverage under difficult terrain and siting conditions, it may be necessary to make appropriate increases in the equivalent isotropically radiated power (EIRP). Conversely, practical experience has shown, that under favourable siting conditions, and under the less pessimistic conditions often found in actual service, satisfactory system operation is achieved with a lower EIRP. However, to account for lowest EIRP in notches between the lobes of the real elevation antenna pattern, the values in Figure C-20 are recommended.

Note.: Further guidance may be found in the Handbook on Radio Frequency Spectrum Requirements for Civil Aviation including statement of approved ICAO policies (Doc 9718, Volume II).

7.2.1.3 When providing coverage to support performance-based navigation as described in the Performance-based Navigation (PBN) Manual (Doc 9613) and in 7.2.3, the following should be considered: a) although aircraft approved for PBN based on DME are able to tune to a DME up to a range of 160 NM, automatic DME station tuning by aircraft generally favours more nearby stations. Thus, in airspace volumes served by many DME/N facilities, these facilities may not be used by many aircraft at extended range. Therefore, in such areas served by many DMEs (providing a high level of multi-DME position fixing redundancy), use of extended DME coverage ranges may bring little or no performance benefit, while potentially imposing restrictions on the assignment of frequencies;

b) in airspace volumes served by few DMEs, the coverage for multi- DME position fixing may be improved by the use of extended coverage ranges for individual DMEs. Due to different logic applied in various avionics implementations, the values, coded in navigation database fields could unnecessarily limit the usable coverage range of DMEs for multi-DME position fixing. For example, in ARINC 424 coding the Figure of Merit (FOM), the DME Operational Service 582CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Volume (D-OSV) and the coverage field of the NAVAID class can all limit DME usable range in some avionics implementations. To avoid this, coordination with concerned aircraft operators and navigation database providers may be necessary.

7.2.2 EIRP of DME/N facilities

7.2.2.1 The power density figure prescribed in Chapter 3, 3.5.4.1.5.2 is based on

the following example:

Airborne receiver sensitivity –120 dBW Transmission line loss, mismatch loss, antenna polar pattern variation with respect to an isotropic antenna +9 dB Power required at antenna –111 dBW Minus 111 dBW at the antenna corresponds to minus 89 dBW/ m2 at the id-band frequency.

7.2.2.2 Nominal values of the necessary EIRP to achieve a power density of minus 89 dBW/m2 are given in Figure C-20. For coverage under difficult terrain and siting conditions it may be necessary to make appropriate increases in the EIRP. Conversely, under favourable siting conditions, the stated power density may be achieved with a lower EIRP.

583CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note1.: The curves are based on the IF-77 propagation model with a 4/3 Earth radius which has been confirmed by measurements.

Note2.: The radio horizon in Figure C-20 is for a DME antenna located 5 m (17 ft) AGL over flat terrain. Terrain shielding will reduce the achievable range.

Note3.: If the antenna is located significantly higher than the assumed reference antenna, the radio horizon and power density will increase.

7.2.3 DME-DME RNAV area navigation

7.2.3.1 There is an increasing use of DME to support area navigation (RNAV) operations. Although the use of DME to support RNAV area navigation operations does not impose any additional technical requirements on the DME system, it does raise some additional issues compared with the traditional use of DME with VOR to support conventional operations.

These are examined briefly below.

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7.2.3.2 DME/DME positioning is based on the aircraft RNAV area navigation system triangulating position from multiple DME ranges from DME facility locations in the aircraft database. The resulting accuracy of the position solution depends on the range to the DMEs and their relative geometry.

Some additional measures are therefore necessary to ensure that the DME infrastructure is adequate to support the RNAV area navigation operation, i.e. that sufficient DMEs are available and that their location provides adequate geometry to meet the accuracy requirements. For approach and departure procedures, it is also necessary to confirm that there is adequate signal strength and that there are no false locks or unlocks due to multipath. When ensuring there are sufficient DMEs, it is also important to identify any critical DMEs (i.e. those which must be operational for the necessary performance to be assured).

7.2.3.3 Errors in published DME facility locations will result in RNAV area navigation position errors. It is therefore important that DME positions are correctly surveyed and that adequate procedures are in place to ensure that the location data are correctly published. For DME facilities collocated with VOR, the DME position should be separately surveyed and published if the separation distance exceeds 30 m (100 ft).

Note.: Specifications concerning data quality and publication of DME location information are contained in PANS-AIM (Doc 10066), Appendix 1.

7.2.3.4 When using DME to support RNAVarea navigation, scanning DME aircraft receivers usually do not check the DME identification. As a consequence, removing the identification of a DME during tests and maintenance operations does not guarantee that the signals will not be used operationally. Maintenance actions that may provide misleading information should be minimized.

Note1.: Further guidance on flight inspection of DME-DME RNAV area navigation procedures is given in Doc 8071.

Note2.: Further guidance on navigation infrastructure assessment to support RNAV area navigation procedures is given in EUROCONTROL-GUID- 0114 (available at http://www.eurocontrol.int) and on the performance- based navigation (PBN) page of the ICAO website at

http://www.icao.int/pbn.

7.3 Guidance material concerning DME/P only

7.3.1 DME/P system description

7.3.1.1 The DME/P is an integral element of the microwave landing system described in Chapter 3, 3.11. The DME/P signal format defines two 585CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 operating modes, initial approach (IA) and final approach (FA). The IA mode is compatible and interoperable with DME/N and is designed to provide improved accuracies for the initial stages of approach and landing.

The FA mode provides substantially improved accuracy in the final approach area. Both modes are combined into a single DME/P ground facility and the system characteristics are such that DME/N and DME/P functions can be combined in a single interrogator. The IA and FA modes are identified by pulse codes which are specified in Chapter 3, 3.5.4.4. In the MLS approach sector, the DME/P coverage is at least 41 km (22 NM) from the ground transponder. It is intended that the interrogator does not operate in the FA mode at ranges greater than 13 km (7 NM) from the transponder site, although the transition from the IA mode may begin at 15 km (8 NM) from the transponder. These figures were selected on the assumption that the transponder is installed beyond the stop end of the runway at a distance of approximately 3 600 m (2 NM) from the threshold.

7.3.1.2 A major potential cause of accuracy degradation encountered in the final phases of the approach and landing operation is multipath (signal reflection) interference. DME/P FA mode minimizes these effects by using wideband signal processing of pulses having fast rise time leading edges, and by measuring the time of arrival at a low point on the received pulse where it has not been significantly corrupted by multipath. This is in contrast to the slower rise time pulses and higher thresholding at the 50 per cent level used in DME/N.

7.3.1.3 Because the FA mode is used at ranges less than 13 km (7 NM), the transmitter can provide an adequate signal level to meet the required accuracy without the fast rise time pulse violating the transponder pulse spectrum requirements. Use of the 50 per cent threshold and a narrow receiver bandwidth in the IA mode permits an adequate but less demanding performance to the coverage limits. The transponder determines the interrogation mode in use by the interrogation code in order to time the reply delay from the proper measurement reference. The IA mode is interoperable with DME/N permitting a DME/N interrogator to be used with a DME/P transponder to obtain at least the accuracy with a DME/N transponder. Similarly, a DME/P interrogator may be used with a DME/N transponder.

7.3.2 DME/P system accuracy requirements

7.3.2.1 DME/P accuracy requirements

7.3.2.1.1 When considering the DME/P accuracy requirement, the operations that can be performed in the service volume of the final approach mode tend to fall into one of two groups. This has led to two accuracy standards being

defined for the final approach mode: a) accuracy standard 1: this is the least demanding and is designed to cater for most CTOL operations;

586CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 b) accuracy standard 2: this gives improved accuracy that may be necessary for VTOL and STOL operations, CTOL flare manoeuvres using MLS flare elevation guidance and CTOL high-speed turnoffs.

7.3.2.1.2 Table C-7 shows applications of DME and typical accuracy requirements.

This will assist in selecting the appropriate accuracy standard to meet the operational requirement. The calculations are based on a distance of 1 768 m (5 800 ft) between the DME antenna and the runway threshold. The following paragraphs refer to Table C-7.

7.3.2.1.3 It is intended that the DME/P accuracy approximately corresponds to the azimuth function PFE at a distance of 37 km (20 NM) from the MLS reference datum both along the extended runway centre line and at an azimuth angle of 40 degrees. The CMN is the linear equivalent of the plus or minus 0.1 degree CMN specified for the azimuth angle function.

7.3.2.1.4 PFE corresponds to azimuth angular error; CMN is approximately the linear equivalent of the plus or minus 0.1 degree CMN specified for the azimuth angle system.

7.3.2.1.5 The plus or minus 30 m (100 ft) PFE corresponds to a plus or minus 1.5 m (5 ft) vertical error for a 3-degree elevation angle.

7.3.2.1.6 Flare initiation begins in the vicinity of the MLS approach reference datum;

MLS elevation and DME/P provide vertical guidance for automatic landing when the terrain in front of the runway threshold is uneven.

7.3.2.1.7 Sensitivity modification or autopilot gain scheduling requirements are not strongly dependent on accuracy.

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7.3.2.1.8 It is intended that this specification applies when vertical guidance and sink rate for automatic landing are derived from the MLS flare elevation and the DME/P.

Note.: Although the standard has been developed to provide for MLS flare elevation function, this function is not implemented and is not intended for future implementation.

7.3.2.1.9 It indicates to the pilot if the aircraft is landing beyond the touchdown region.

7.3.2.1.10 The roll-out accuracy requirement reflects system growth potential. In this application the roll-out PFE would be dictated by the possible need to optimize roll-out deceleration and turnoff so as to decrease runway 588CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 utilization time.

7.3.2.1.11 It is intended to assure the pilot that the aircraft is over the landing pad before descending.

7.3.2.1.12 It may be desirable to translate the MLS coordinates from one origin to another when the antennas are not installed in accordance with Chapter 3, 3.11.5.2.6 or 3.11.5.3.5. The figures in the table are typical of a VTOL application; actual values will depend on the geometry of the installation.

7.3.3 DME/P error budgets Example error budgets for DME/P accuracy standards 1 and 2 are shown in Table C-8. If the specified error components are not individually exceeded in practice, it can be expected that the overall system performance, as specified in Chapter 3, 3.5.3.1.4, will be achieved. A garbling contribution to the system error is computed by taking the root sum square (RSS) of the errors obtained in the specified down-link environment with those obtained in the specified up-link environment and removing, on an RSS basis, the error obtained in a non-garbling environment.

Note1.: The figures for “non-specular multipath” and for “garble” are the totals of the up-link and down-link components.

Note2.: PFE contains both bias and time varying components. In the above table the time varying components and most site related errors are assumed to be essentially statistically independent. The bias components may not conform to any particular statistical distribution. In considering these error budgets, caution is to be exercised when combining the individual components in any particular mathematical manner.

Note3.: The transmitter wave form is assumed to have a 1 200 nanosecond rise time.

7.3.4 System implementation 589CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

7.3.4.1 While the DME/P may be implemented in various ways, the instrumental and propagation errors assumed are typical of those obtainable with equipment designs which provide internal time delay drift compensation and which establish timing reference points by thresholding on the leading

edge of the first pulse of a pulse pair using the following techniques: a) IA mode. A conventional technique which thresholds at the 50 per cent amplitude point; b) FA mode. A delay-attenuate-and-compare (DAC) technique which thresholds between the 5 per cent and 30 per cent amplitude points.

7.3.4.2 Accuracy standard 1 can be achieved using a delay of 100 nanoseconds and an attenuation of 5 to 6 dB. It is also required that the threshold amplitude point of both the delayed pulse and the attenuated pulse lie within the partial rise time region.

7.3.4.3 The example above does not preclude time of arrival measurement techniques other than the DAC from being used, but it is necessary in any case that threshold measurements take place during the pulse partial rise time.

7.3.5 DME/P interrogator signal processing

7.3.5.1 During acquisition a) The interrogator acquires and validates the signal within 2 seconds before transitioning to track mode even in the presence of squitter and random pulse pairs from adjacent channels, which result in a 50 per cent system efficiency.

b) After loss of the acquired signal in either the IA or FA mode, the interrogator provides a warning output within 1 second, during which time the guidance information continues to be displayed. After loss of signal, the interrogator returns to the search condition in the IA mode in order to re-establish track.

7.3.5.2 During track When track is established, the receiver output consists of valid guidance information before removing the warning. The validation process continues to operate as long as the interrogator is in track. The interrogator remains in track as long as the system efficiency is 50 per cent or greater. While in track, the receiver provides protection against short duration, large amplitude erroneous signals.

7.3.5.3 Range date filter 590CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 The accuracy specifications in Chapter 3, 3.5.3.1.4, as well as the error budgets discussed in 7.3.3, assume that the higher frequency noise contributions are limited by a low pass filter with a corner frequency of qw s specified in Figure C-21. Depending upon the user’s application, additional filtering for noise reduction can be used provided that the induced phase delay and amplitude variation do not adversely affect the aircraft flight control system’s dynamic response. The following sections recommend additional features which should be incorporated into the data filter.

7.3.5.4 Velocity memory The data filter may require a velocity memory in order to achieve the specified accuracies in Chapter 3, 3.5.3.1.4 with a system efficiency of 50 per cent. It should be noted that low system efficiencies can occur in the IA mode during identification transmissions.

7.3.5.5 Outlier rejection Range estimates which are significantly different from previous filtered range estimates, because they cannot be the result of aircraft motion, should be assumed to be in error. Such data should be rejected at the input to the data filter.

7.3.6 DME/P error measurement methods

7.3.6.1 System errors

7.3.6.1.1 The DME/P system accuracies are specified in Chapter 3, 3.5.4.1.4 in terms of path following error (PFE) and control motion noise (CMN). These parameters describe the interaction of the DME/P guidance signal with the aircraft in terms directly related to aircraft position errors and flight control system design.

7.3.6.1.2 For the purposes of determining compliance with the accuracy standard, the PFE and CMN components are evaluated over any T second interval (where T = 40 seconds in the IA mode and 10 seconds in the FA mode) of the flight error record taken within the DME/P coverage limits. The 95 per cent probability requirement is interpreted to be satisfied if the PFE and CMN components do not exceed the specified error limits for a total period that is more than 5 per cent of the evaluation time interval. This is illustrated in Figure C-21. To evaluate the PFE and CMN components of the DME/P guidance data, the true aircraft position, as determined by a suitable position reference, is subtracted from the guidance data to form an error signal. This error signal is then filtered by the PFE and CMN filters, where the outputs provide suitable estimates of the PFE and CMN components, respectively. These filters are defined in Figure C-21.

7.3.6.1.3 These filters can be utilized to determine the transponder instrumentation 591CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 error components specified in Chapter 3, 3.5.4.5.3 and 3.5.4.5.4. Similarly, the interrogator instrumentation error components, specified in Chapter 3,

3.5.5.4, can be determined.

7.3.7 Multipath effects

7.3.7.1 Under the multipath conditions likely to exist, the accuracy specifications of the DME/P assume that the performance is not degraded beyond a certain limit and that this degradation is equally applied to both interrogator and transponder receiver.

7.3.7.2 To ensure that the equipment is working according to the specifications,

the following should apply to FA mode operation of the system: a) if a signal of sufficient power to make thermal noise contributions insignificant is applied to the receivers, a second signal delayed between 0 and 350 nanoseconds with respect to the first, with an amplitude 3 dB or more below the first and with a scalloping frequency between 0.05 and 200 Hz should not produce errors in the receiver output of more than plus or minus 100 nanoseconds (15 m);

b) for delays more than 350 nanoseconds the error contribution will be reduced considerably. A typical value will be plus or minus 7 nanoseconds (1 m).

7.3.7.3 The airborne DME antenna should be located so as to preclude antenna gain reductions in the forward direction with the aircraft in the landing configuration. Any such antenna gain reductions could enhance the multipath error component when the aircraft is on approach and landing phases when highest DME accuracies are required.

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7.3.8 DME/P power budget

7.3.8.1 Tables C-9 and C-10 are an example of CTOL air-to-ground and ground- to-air power budgets. The permitted peak ERP value is based on a pulse shape which meets the spectral constraints in Chapter 3, 3.5.4.1.3 e).

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7.3.8.2 In the power budget calculations, it is assumed that the aircraft antenna is not shielded by the aircraft structure including the landing gear when extended.

7.3.8.3 The video power signal-to-noise ratio is related to the IF power signal-to-

noise ratio in the following manner:

Note1.: The distances are measured from the transponder antenna.

Note2.: Frequency dependent parameters were calculated for 1 088 MHz.

7.3.9 DME/P monitor time delay measurement The required time delay measurement can be accomplished by measuring the output of a PFE filter and making a control decision within 1 second.

However, since the transponder PFE is a slowly varying error component, an equivalent measurement is to average the unfiltered time delay samples for 1 second.

9. Material concerning power supply switch-over times

8.1 Power supply switch-over times for ground-based radio aids used in the vicinity of aerodromes The power supply switch-over times for radio navigation aids and ground elements of communications systems are dependent on the type of runway and aircraft operations to be supported.

Table C-11 indicates representative switch-over times which may be met by power supply systems currently available.

595CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 596CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 ATTACHMENT D. INFORMATION AND MATERIAL FOR GUIDANCE IN THE APPLICATION OF THE GNSS STANDARDS AND RECOMMENDED PRACTICES

1. DEFINITIONS Bi-binary. Bi-binary is known as “Manchester Encoding”. It is sometimes referred to as “Differential Manchester Encoding”. Using this system, it is the transition of the edge that determines the bit.

Chip. A single digital bit of the output of a pseudo-random bit sequence.

Gold code. A class of unique codes used by GPS, which exhibit bounded cross-correlation and off-peak auto-correlation values.

Selective availability (SA). A set of techniques for denying the full accuracy and selecting the level of positioning, velocity and time accuracy of GPS available to users of the standard positioning service signal.

Note.: GPS SA was discontinued at midnight on 1 May 2000.

2. GENERAL Standards and Recommended Practices for GNSS contain provisions for the elements identified in Chapter 3, 3.7.2.2. Additional implementation guidance is provided in the Global Navigation Satellite System (GNSS) Manual (Doc 9849).

Note.: Except where specifically annotated, GBAS guidance material applies to GRAS.

3. NAVIGATION SYSTEM PERFORMANCE REQUIREMENTS

3.1 Introduction

3.1.1 Navigation system performance requirements are defined in the Performance-based Navigation (PBN) Manual (Doc 9613) for a single aircraft and for the total system which includes the signal-in-space, the airborne equipment and the ability of the aircraft to fly the desired trajectory. These total system requirements were used as a starting point to derive GNSS signal-in-space performance requirements. In the case of GNSS, degraded configurations which may affect multiple aircraft are to be considered. Therefore, certain signal-in-space performance requirements are more stringent to take into account multiple aircraft use 597CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 of the system.

3.1.2 Two types of approach and landing operations with vertical guidance

(APV), APV-I and APV-II, use vertical guidance relative to a glide path, but the facility or navigation system may not satisfy all of the requirements associated with precision approach. These operations combine the lateral performance equal to that of a Facility Performance Category I localizer with different levels of vertical guidance. Both APV-I and APV-II provide access benefits relative to a non-precision approach, and the service that is provided depends on the operational requirements and the SBAS infrastructure. APV-I and APV-II exceed the requirements (lateral and vertical) for current RNAV area navigation approaches using barometric altimetry, and the relevant on-board equipment will therefore be suitable for the conduct of barometric VNAV APV and RNAV area navigation non- precision approaches.

3.2 Accuracy

3.2.1 GNSS position error is the difference between the estimated position and the actual position. For an estimated position at a specific location, the probability should be at least 95 per cent that the position error is within the accuracy requirement.

3.2.2 Stationary, ground-based systems such as VOR and ILS have relatively repeatable error characteristics, so that performance can be measured for a short period of time (e.g. during flight inspection) and it is assumed that the system accuracy does not change after the test. However, GNSS errors change over time. The orbiting of satellites and the error characteristics of GNSS result in position errors that can change over a period of hours. In addition, the accuracy itself (the error bound with 95 per cent probability) changes due to different satellite geometries. Since it is not possible to continually measure system accuracy, the implementation of GNSS demands increased reliance on analysis and characterization of errors. Assessment based on measurements within a sliding time window is not suitable for GNSS.

3.2.3 The error for many GNSS architectures changes slowly over time, due to filtering in the augmentation systems and in the user receiver. This results in a small number of independent samples in periods of several minutes.

This issue is very important for precision approach applications, because it implies that there is a 5 per cent probability that the position error can exceed the required accuracy for an entire approach. However, due to the changing accuracy described in 3.2.2, this probability is usually much lower.

3.2.4 The 95 per cent accuracy requirement is defined to ensure pilot acceptance, since it represents the errors that will typically be experienced. The GNSS accuracy requirement is to be met for the worst- case geometry under which the system is declared to be available.

Statistical or probabilistic credit is not taken for the underlying probability 598CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 of particular ranging signal geometry.

3.2.5 Therefore, GNSS accuracy is specified as a probability for each and every sample, rather than as a percentage of samples in a particular measurement interval. For a large set of independent samples, at least 95 per cent of the samples should be within the accuracy requirements in

Chapter 3, Table 3.7.2.4-1. Data is scaled to the worst-case geometry in

order to eliminate the variability in system accuracy that is caused by the geometry of the orbiting satellites.

3.2.6 An example of how this concept can be applied is the use of GPS to support performance required for non-precision approach operations.

Assume that the system is intended to support non-precision approaches hen the horizontal dilution of precision (HDOP) is less than or equal to 6.

To demonstrate this performance, samples should be taken over a long period of time (e.g. 24 hours). The measured position error g for each sample i is denoted gi. This error is scaled to the worst-case geometry as 6 × gi/HDOP. Ninety-five per cent of the scaled errors must be less than 220 m for the system to comply with the non-precision accuracy requirement under worst-case geometry conditions. The total number of samples collected must be sufficient for the result to be statistically representative, taking into account the decorrelation time of the errors.

3.2.7 A range of vertical accuracy values is specified for Category I precision approach operations which bounds the different values that may support an equivalent operation to ILS. A number of values have been derived by different groups, using different interpretations of the ILS standards. The lowest value from these derivations was adopted as a conservative value for GNSS; this is the minimum value given for the range. Because this value is conservative, and because GNSS error characteristics are different from ILS, it may be possible to achieve Category I operations using larger values of accuracy within the range. The larger values would result in increased availability for the operation. The maximum value in the range has been proposed as a suitable value, subject to validation.

3.2.7.1 Requirements for position domain accuracy to support precision approach operations below Category I are not defined in the SARPs. GBAS service types intended to support operations with lower than Category I minima are required to meet the SIS accuracy requirements for Category I at a minimum. In addition, specific pseudo-range accuracy requirements apply to support the assessment of adequate performance during aircraft certification. The additional requirements on pseudorange accuracy may be combined with geometry screening to ensure the resulting position domain accuracy is adequate for a given aeroplane design to achieve suitable landing performance. See 7.5.13.

3.2.8 The GPS SPS position error (Chapter 3, 3.7.3.1.1.1.1) accounts for the contribution of the space and control segment to position errors (satellite clock and ephemeris errors) only; it does not include the contributions of ionospheric and tropospheric delay model errors, errors due to multipath 599CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 effects, and receiver measurement noise errors (see 4.1.2). These errors are addressed in the receiver standards. The user positioning error at the output of ABAS-capable equipment is mainly driven by the GNSS receiver used.

3.2.8.1 For Basic GNSS receivers, the receiver qualification standards require demonstration of user positioning accuracy in the presence of interference and a model of selective availability (SA) to be less than 100 m (95 per cent of time) horizontally and 156 m (95 per cent of time) vertically. The receiver standards do not require that a Basic GNSS receiver applies the ionospheric correction described in Appendix B, 3.1.1.2.1.4.

Note.: The term “Basic GNSS receiver” designates the GNSS avionics that at least meet the requirements for a GPS receiver as outlined in Annex 10, Volume I and the specifications of RTCA/DO-208 as amended by United States Federal Aviation Administration (FAA) TSO-C129A, or EUROCAE ED-72A (or equivalent).

3.2.8.2 Since the discontinuation of SA, the representative user positioning accuracy of GPS has been conservatively estimated to be as shown in Table D-1. The numbers provided assume that the worst two satellites of a nominal 24 GPS satellite constellation are out of service. In addition, a 7 m (1 σ) ionospheric delay model error, a 0.25 m (1 σ) residual tropospheric delay error, and a 0.80 m (1 σ) receiver noise error are assumed. After discontinuation of SA (see section 1.), the dominant pseudo-range error for users of the GPS Standard Positioning Service is the ionospheric error that remains after application of the ionospheric corrections. This error is also highly variable and depends on conditions such as user geomagnetic latitude, level of solar activity (i.e. point of the solar cycle that applies), level of ionospheric activity (i.e. whether there is a magnetic storm, or not), elevation angle of the pseudo-range measurement, season of the year, and time of day. The ionospheric delay model error assumption reflected in Table D-1 is generally conservative; however, conditions can be found under which the assumed 7 m (1 σ) error during solar maximum would be inadequate.

3.2.9 SBAS and GBAS receivers will be more accurate, and their accuracy will be characterized in real time by the receiver using standard error models, as described in Chapter 3, 3.5, for SBAS and Chapter 3, 3.6, for GBAS.

600CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note1.: The term “SBAS receiver” designates the GNSS avionics that at least meet the requirements for an SBAS receiver as outlined in Annex 10, Volume I and the specifications of RTCA/DO-229D with Change 1 (or equivalent) or the specification of the EUROCAE/ED-259 (or equivalent).

Note2.: The term “GBAS receiver” designates the GNSS avionics that at least meet the requirements for a GBAS receiver as outlined in Annex 10, Volume I and the specifications of the RTCA documents covering the applicable performance types, amended by United States FAA TSO (or equivalent).

3.3 Integrity

3.3.1 Integrity is a measure of the trust that can be placed in the correctness of the information supplied by the total system. Integrity includes the ability of a system to provide timely and valid warnings to the user (alerts) when the system must not be used for the intended operation (or phase of flight).

3.3.2 To ensure that the position error is acceptable, an alert limit is defined that represents the largest position error allowable for a safe operation. The position error cannot exceed this alert limit without annunciation. This is analogous to ILS in that the system can degrade so that the error is larger than the 95th percentile but within the monitor limit.

3.3.3 The integrity requirement of the navigation system for a single aircraft to support en-route, terminal, initial approach, non-precision approach and departure is assumed to be 1 – 1 × 10–5 per hour.

3.3.4 For satellite-based navigation systems, the signal-in-space in the en-route environment simultaneously serves a large number of aircraft over a large area, and the impact of a system integrity failure on the air traffic management system will be greater than with traditional navigation aids.

The performance requirements in Chapter 3, Table 3.7.2.4-1, are therefore more demanding.

3.3.5 For APV and precision approach operations, integrity requirements for GNSS signal in space requirements of Chapter 3, Table 3.7.2.4-1, were selected to be consistent with ILS requirements.

3.3.6 Alert limits for typical operations are provided in Note 2 to Table 3.7.2.4-1.

A range of vertical alert limits (VAL) from 10 m (33 ft) to 35 m (115 ft) is specified for Category I precision approach operations, reflecting potential differences in system design that may affect the operation. The derivation of the range values is explained in 3.3.7 and 3.3.8. When using a VAL greater than 10 m (33 ft), a system-specific analysis must determine which value in the 10 m (33 ft) to 35 m (115 ft) range s appropriate to ensure suitable guidance quality. The analysis must take into account the system monitor design and other factors relevant to system implementation (i.e.

601CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 additional mechanisms which prevent exposure to significant vertical biases). In the case of SBAS, this analysis is normally done by the augmentation system service provider, supported by the system designer and accepted by the appropriate safety oversight authority. Additionally, regardless of the VAL used, local implementation- and procedure-specific safety cases are normally conducted separately from the system-specific safety case. These are conducted by the local air navigation service provider, taking into account information provided by the augmentation system service provider (see 3.3.9 and 3.3.10).

3.3.7 The range of values for VAL reflects the different characteristics of GNSS integrity monitoring as compared to ILS integrity monitoring. In ILS, monitor thresholds for key signal parameters are standardized, and the monitors themselves have very low measurement uncertainty on the parameter that is being monitored. With differential GNSS, some system monitors have comparably large measurement uncertainty whose impact must be considered on the intended operation. In all cases, the effect of the alert limit is to restrict the satellite-user geometry to one where the monitor performance (typically in the pseudo-range domain) is acceptable when translated into the position domain. The smallest (most stringent) precision approach vertical alert limit (VAL) value (10 m (33 ft)) was derived based on the monitor performance of ILS as it could affect the glide slope at a nominal decision altitude of 60 m (200 ft) above the runway threshold, without taking into account the specific characteristics of GNSS integrity monitoring which could potentially enable the use of a less stringent VAL. By applying the 10 m (33 ft) VAL, the GNSS error, under faulted conditions, can be directly compared to an ILS error under faulted conditions, such that the GNSS errors are less than or equal to the ILS errors. For those faulted conditions with comparably large measurement uncertainty in GNSS, this results in monitor thresholds which are more stringent than ILS. When using a 10 m (33 ft) VAL no further analysis of navigation system error distribution is required.

3.3.8 The largest precision approach VAL value (35 m (115 ft)) was derived to ensure obstacle clearance equivalent to ILS for those error conditions which can be modelled as a bias during the final approach, taking into account that the aircraft decision altitude is independently derived from barometric pressure. An assessment has been conducted of the worst- case effect of a latent bias error equal to the alert limit of 35 m (115 ft), concluding that adequate obstacle clearance protection is provided on the approach and missed approach (considering the decision altitude would be reached early or late, using an independent barometric altimeter). It is important to recognize that this assessment only addressed obstacle clearance and is limited to those error conditions which can be modelled as bias errors. Analysis has shown 35 m (115 ft) bias high and low conditions can be tolerated up to the approach speed category (Categories A through D) glide path angle limits in the Procedures for Air Navigation Services — Aircraft Operations (PANS-OPS, Doc 8168) without impinging on the ILS obstacle clearance surfaces during the instrument segment of 602CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 the approach. However, it is important to note that GNSS systems using a VAL greater than 10 m (33 ft) will not produce sustained bias errors of such magnitude. Instead, the increased VAL is used in conjunction with additional system monitors to produce guidance quality equivalent to or better than ILS. When using a VAL greater than 10 m (33 ft), additional characterization of navigation system error distribution is required to ensure that position errors, in both the instrument and visual segments of the approach, are sufficiently small to ensure obstacle clearance and acceptable touchdown performance.

3.3.9 When conducting the system-specific safety assessment to support the use of a VAL greater than 10 m (33 ft), the factors discussed below should be considered.

3.3.9.1 When a visual contact with approach/runway lighting or marking is established and the pilot takes a decision to land, the instrument phase ends and the flight continues with a visual reference. In the presence of a vertical navigation system error (VNSE), pilots may not be able to recognize a navigation error during the transition from the instrument to the visual segment. As a consequence of the VNSE, the decision altitude may be reached either above or below the nominal flight path, such that there might be a necessity to manually align the aircraft with reference to visual cues in order to cross the runway threshold at a height suitable for landing. Such actions, in a very late phase of flight, could lead to a destabilization of the approach or a go-around from inside the visual segment. Although possible consequences of the exposure to a VNSE depend on various contributors, such as flight technical error (FTE), aircraft velocity, wind speed, glide path angle, visibility, runway lighting and human performance, the magnitude of the VNSE is the most relevant factor for assessing the safety of the navigation system.

3.3.9.2 The following values of the VNSE should be considered in the design of

the augmentation system: a) VNSE of 4 m (13 ft) or less. This is considered as an equivalent to ILS Category I with acceptable touchdown performance and a standard number of missed approaches due to visibility conditions.

b) VNSE higher than 4 m (13 ft) but not higher than 10 m (33 ft). Either a safe landing with an acceptable touchdown performance or a go- around can be expected. c) VNSE higher than 10 m (33 ft) but not higher than 15 m (50 ft). The touchdown performance may be affected and flight crew workload may be increased.

d) VNSE higher than 15 m (50 ft). The safety margin would be significantly reduced under some operational configurations.

603CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

3.3.9.3 In considering the values above, one acceptable means to manage the risks in the visual segment is for the system to comply with the following

criteria: a) the fault-free accuracy is equivalent to ILS at ILS point B. This includes system 95 per cent VNSE less than 4 m (13 ft), and a fault- free system VNSE exceeding 10 m (33 ft) with a probability less than 10-7 per approach for each location where the operation is to be approved. This assessment is performed over all environmental and operational conditions under which the service is declared available;

b) under system failure conditions, the system design is such that the probability of an error greater than 15 m (50 ft) is lower than 10-5, so that the likelihood of occurrence is remote. The fault conditions to be taken into account are those affecting either the core constellations or the GNSS augmentation under consideration. This probability is to be understood as the combination of the occurrence probability of a given failure with the probability of detection for applicable monitor(s).

Typically, the probability of a single fault is large enough that a monitor is required to satisfy this condition.

3.3.9.4 In case these criteria are applied, the service provider could declare the Category I service area considering where Category I integrity is available, for a given VAL in the 10 m (33 ft) to 35 m (115 ft) range, in accordance with the system analysis showing where the additional conditions a) and b) described above are met.

Note.: Further guidance on the technical interpretation of these requirements is given in the Global Navigation Satellite System (GNSS) Manual (Doc 9849, SBAS Operations, 4.3.3.3).

3.3.10 For GBAS, a technical provision has been made to broadcast the alert limit to aircraft. For SBAS, technical provisions have been made to specify the alert limit through an updatable database (see Attachment C).

3.3.10.1 For GBAS approach service type D (see 7.1.2.1) additional lower level performance and functional requirements are introduced in order to achieve a total system capable of supporting aircraft landing operations.

This service type also supports guided take-off operations.

3.3.11 The approach integrity requirements apply in any one landing and require a fail-safe design. If the specific risk on a given approach is known to exceed this requirement, the operation should not be conducted. One of the objectives of the design process is to identify specific risks that could cause misleading information and to mitigate those risks through redundancy or monitoring to achieve a fail safe design. For example, the ground system may need redundant correction processors and to be capable of shutting down automatically if that redundancy is not available 604CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 due to a processor fault.

3.3.12 A unique aspect of GNSS is the time-varying performance caused by changes in the core satellite geometry. A means to account for this variation is included in the SBAS and GBAS protocols through the protection level equations, which provide a means to inhibit use of the system if the specific integrity risk is too high.

3.3.13 GNSS performance can also vary across the service volume as a result of the geometry of visible core constellation satellites. Spatial variations in system performance can further be accentuated when the ground system operates in a degraded mode following the failure of system components such as monitoring stations or communication links. The risk due to spatial variations in system performance should be reflected in the protection level equations, i.e. the broadcast corrections.

3.3.14 GNSS single-frequency augmentations are also subject to several atmospheric effects, particularly due to the ionosphere. Spatial and temporal variations in the ionosphere will affect mostly single-frequency navigation because they can cause local or regional ionospheric delay errors that cannot be corrected within the L1 SBAS or GBAS architectures due to the definition of the message protocols and the sparse sampling of augmentation systems. Such events are rare and their likelihood varies by region, but they are not expected to be negligible. The resulting errors can be of sufficient magnitude to cause misleading information and should be mitigated in the system design through accounting for their effects in the broadcast parameters (e.g. σ iono_vert in GBAS), and monitoring for excessive conditions where the broadcast parameters are not adequate.

The likelihood of encountering such events should be considered when developing any system monitor. SBAS dual-frequency augmentations use ionosphere-free pseudo-ranges in order to remove the first order ionosphere delay in the position computation. The dual-frequency protection level includes a small error allocation to bound the residual ionosphere errors and greatly reduce the impact of local and temporal variations in ionospheric delays on the navigation solution.

3.3.15 Another environmental effect that should be accounted for in the ground system design is the errors due to multipath at the ground reference receivers, which depend on the physical environment of monitoring station antennas as well as on satellite elevations and times in track.

3.3.16 SBAS needs to assure the integrity of its broadcast corrections as required in Chapter 3, 3.7.2.4, throughout its coverage area. This requirement also applies outside the intended service area, where user receivers could navigate using either an SBAS navigation solution, if available, or L1 fault detection and exclusion (FDE) navigation solution that combines satellites with SBAS corrections and satellites without SBAS corrections. DFMC SBAS corrections are not intended for use in an FDE navigation solution.

The L1 SBAS contributions to a single-frequency FDE navigation solution 605CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 are limited to assuring the integrity of the transmitted corrections. SBAS systems have to comply with all the integrity requirements for all typical operations from En-route to Category I, defined in Chapter 3, Table

3.7.2.4-1, in the coverage area when, for a given operation, the horizontal and vertical protection levels are lower than the corresponding alert limits.

This is of particular importance for vertically guided operations using SBAS that are not controlled by FAS data block.

3.4 Continuity of service

3.4.1 Continuity of service of a system is the capability of the system to perform its function without unscheduled interruptions during the intended operation.

3.4.2 En-route

3.4.2.1 For en-route operations, continuity of service relates to the capability of the navigation system to provide a navigation output with the specified accuracy and integrity throughout the intended operation, assuming that it was available at the start of the operation. The occurrence of navigation system alerts, either due to rare fault-free performance or to failures, constitute continuity failures. Since the durations of these operations are variable, the continuity requirement is specified as a probability on a per- hour basis.

3.4.2.2 The navigation system continuity requirement for a single aircraft is 1 – 1 × 10–4 per hour. However, for satellite based systems, the signal-in-space may serve a large number of aircraft over a large area. The continuity requirements in Chapter 3, Table 3.7.2.4-1, represent reliability requirements for the GNSS signal-in-space, i.e. they derive mean time between outage (MTBO) requirements for the GNSS elements.

3.4.2.3 A range of values is given in Chapter 3, Table 3.7.2.4-1, for the signal-in- space continuity requirement for enroute operations. The lower value is the minimum continuity for which a system is considered to be practical. It is appropriate for areas with low traffic density and airspace complexity. In such areas, the impact of a navigation system failure is limited to a small number of aircraft, and there is, therefore, no need to increase the continuity requirement significantly beyond the single aircraft requirement (1 – 1 × 10–4 per hour). The highest value given (i.e. 1 – 1 × 10–8 per hour) is suitable for areas with high traffic density and airspace complexity, where a failure will affect a large number of aircraft. This value is appropriate for navigation systems where there is a high degree of reliance on the system for navigation and possibly for dependent surveillance. The value is sufficiently high for the scenario based on a low probability of a system failure during the life of the system.Intermediate values of continuity (e.g. 1 – 1 × 10–6 per hour) are considered to be appropriate for areas of high traffic density and complexity where there is a high degree of reliance on the navigation system but in which mitigation for navigation 606CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 system failures is possible. Such mitigation may be through the use of alternative navigation means or the use of ATC surveillance and intervention to maintain separation standards. The values of continuity performance are determined by airspace needs to support navigation where GNSS has either replaced the existing navigation aid infrastructure or where no infrastructure previously existed.

3.4.3 Approach and landing

3.4.3.1 For approach and landing operations, continuity of service relates to the capability of the navigation system to provide a navigation output with the specified accuracy and integrity during the approach and landing, given that it was available at the start of the operation. In particular, this means that loss of continuity events that can be predicted and for which NOTAMs have been issued do not have to be taken into account when establishing compliance of a given system design against the SARPs continuity requirement. The occurrence of navigation system alerts, either due to rare fault-free performance or to failures, constitutes a loss of continuity event.

In this case, the continuity requirement is stated as a probability for a short exposure time.

3.4.3.2 The continuity requirements for approach and landing operations represent only the allocation of the requirement between the aircraft receiver and the non-aircraft elements of the system. In this case, no increase in the requirement is considered necessary to deal with multiple aircraft use of the system. The continuity value is normally related only to the risk associated with a missed approach and each aircraft can be considered to be independent. However, in some cases, it may be necessary to increase the continuity values since a system failure has to be correlated between both runways (e.g. the use of a common system for approaches to closely-spaced parallel runways).

3.4.3.3 For GNSS-based APV and Category I approaches, missed approach is considered a normal operation, since it occurs whenever the aircraft descends to the decision altitude for the approach and the pilot is unable to continue with visual reference. The continuity requirement for these operations applies to the average risk (over time) of loss of service, normalized to a 15-second exposure time. Therefore, the specific risk of loss of continuity for a given approach could exceed the average requirement without necessarily affecting the safety of the service provided or the approach. A safety assessment performed for one system led to the conclusion that, in the circumstances specified in the assessment, continuing to provide the service was safer than withholding it.

3.4.3.4 For those areas where the system design does not meet the average continuity risk specified in the SARPs, it is still possible to publish procedures. However, specific operational mitigations should be put in place to cope with the reduced continuity expected. For example, flight planning may not be authorized based solely on a GNSS navigation means 607CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 with such a high average continuity risk.

3.5 Availability

3.5.1 The availability of GNSS is characterized by the portion of time the system is to be used for navigation during which reliable navigation information is presented to the crew, autopilot, or other system managing the flight of the aircraft.

3.5.2 When establishing the availability requirements for GNSS, the desired level of service to be supported should be considered. If the satellite navigation service is intended to replace an existing en-route navigation aid infrastructure, the availability of the GNSS should be commensurate with the availability provided by the existing infrastructure. An assessment of the operational impact of a degradation in service should be conducted.

3.5.3 Where GNSS availability is low, it is still possible to use the satellite navigation service by restricting the navigation operating times to those periods when it is predicted to be available. This is possible in the case of GNSS since unavailability due to insufficient satellite geometry is repeatable. Under such restrictions, there remains only a continuity risk associated with the failure of necessary system components between the time the prediction is made and the time the operation is conducted.

3.5.4 En-route

3.5.4.1 Specific availability requirements for an area or operation should be based

upon: a) traffic density and complexity; b) alternate navigation aids; c) primary/secondary surveillance coverage; d) air traffic and pilot procedures; and e) duration of outages.

3.5.4.2 For this reason, the GNSS SARPs specify a range of values for availability requirements. The requirements support GNSS sole-means operations in airspace with various levels of traffic and complexity. The lower end of the range is only sufficient for providing sole means of navigation in a low traffic density and complexity airspace.

3.5.4.3 While augmentations can reduce the dependency of the GNSS on a particular core element, they do not provide usable service without the core elements. The requirement for the availability of a particular augmentation in an area should account for potential degradation in the GNSS core 608CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 elements (i.e. the minimum constellation of core elements (number and diversity of satellites) that is expected). Operational procedures should be developed in case such a degraded configuration occurs.

3.5.5 Approach

3.5.5.1 Specific requirements for an area should be based upon: a) traffic density and complexity; b) procedures for filing and conducting an approach to an alternate airport; c) navigation system to be used for an alternate airport;

d) air traffic and pilot procedures; e) duration of outages; and f) geographic extent of outages.

3.5.5.2 When developing operating procedures for GNSS approach systems, the duration of an outage and its impact on the alternate airport should be considered. Although GNSS outages can occur which affect many approaches, the approach service can be restored without any maintenance because of the orbiting of the satellites.

3.5.6 Determining GNSS availability Note.: Additional guidance material pertaining to reliability and availability of radio communications and navigation aids is contained in Attachment F.

3.5.6.1 The availability of GNSS is complicated by the movement of satellites relative to a coverage area under consideration and the potentially long time needed to restore a satellite in the event of a failure. Accurately measuring the availability would require many years to allow for a measurement period longer than the MTBF and repair times. The availability of GNSS should be determined through design, analysis and modelling, rather than measurement. The availability model should account for the ionospheric, tropospheric and receiver error models used by the receiver to verify integrity (e.g. HPL, LPL and VPL calculations). The availability specified in Chapter 3, 3.7.2.4, applies to the design availability.

3.5.6.2 The availability of ABAS, GBAS and SBAS must be evaluated by comparing the augmented performance to the operational requirements of

Chapter 3, 3.7.2.4. The availability of ABAS, GBAS and SBAS does not directly relate to the core constellation service availability standards in

Chapter 3. Availability analysis is based on the number of usable satellites 609CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 from the core constellation(s) and the performance of the augmentation system(s). Information on the operational satellites/slots is given in the satellite/slot/constellation availability standards or guidance material for each core constellation.

4.1.1 GPS Note.: Additional information concerning GPS can be found in the GPS SPS PS IS-GPS-200K, and IS-GPS-705F.

4.1.1.1 The L1 C/A code performance standards are based upon the assumption that a representative standard positioning service (SPS) receiver is used.

A representative receiver has the following characteristics: a) designed in accordance with IS-GPS-200K; b) tracking the SF L1 C/A code SPS SIS from all satellites in view above a 5-degree masking angle;

c) accomplishes satellite position and geometric range computations in the most current realization of the World Geodetic System 1984 (WGS-84) Earth-Centred, Earth-Fixed (ECEF) coordinate system; d) generates a position and time solution from data broadcast by all satellites in view transmitting PRNs 1-32;

e) compensates for dynamic Doppler shift effects on nominal SPS ranging signal carrier phase and C/A code measurements; f) excludes marginal and unhealthy satellites from the position solution; g) uses up-to-date and internally consistent ephemeris and clock data within the respective curve fit intervals for all satellites it is using in its position solution; and h) loses track in the event that a GPS satellite stops transmitting a trackable signal. The time transfer accuracy applies to the data in the broadcast navigation message, which relates GPS SPS time to UTC as maintained by the United States Naval Observatory. A 12-channel receiver will meet performance requirements specified in Chapter 3,

3.7.3.1.1.1.1 and 3.7.3.1.1.2. A receiver that is able to track four satellites only (Appendix B, 3.1.1.3.1.2) will not get the full position domain accuracy and availability performance.

Note1.: No user position domain performance standards are available at this time for L5-only operation because there are no SIS availability or continuity performance standards defined yet for the L5 signals. Availability and continuity performance standards for the L5 signals will be provided in 610CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 advance of any declaration for an enhanced SPS which includes the L5 service. The performance standards for the L5 signals (range domain accuracy, reliability, major service failure) are at the SIS level and do not require the notion of a user receiver. However, it may be helpful when considering the accuracy and integrity standards for the L5 signals to consider that a user receiver would need to be designed to process the L5 signals in a manner analogous to how it processes the L1 signals;

particularly by processing those signals in accordance with IS-GPS- 705, continuously monitoring the L5 SIS health, using up-to-date and internally consistent navigation data (CNAV), and using only satellites designated as healthy during normal GPS operations.

Note2.: Conditions indicating that a satellite is “healthy”, “marginal” or “unhealthy” can be found in the GPS SPS PS, Section 2.3.2.

4.1.1.2 Position domain accuracy. The position domain accuracy is measured with a representative receiver and a measurement interval of 24 hours for any point within the coverage area. The positioning and timing accuracy are for the signalin- space (SIS) only and do not include such error sources as: ionosphere, troposphere, interference, receiver noise or multipath. In

order to maintain backwards compatibility, the position domain accuracy standard will be met with a representative SPS receiver tracking only PRNs 1 through 32.

4.1.1.3 Range domain accuracy. The range domain accuracy standard applies to normal operations, which implies that updated navigation data is uplinked to the satellites on a regular basis. Range domain accuracy is conditioned by the satellite transmitting a healthy status and transmitting C/A code and does not account for satellite failures outside of the normal operating characteristics. Range domain accuracy limits can be exceeded during satellite failures or anomalies while uploading data to the satellite. The range rate error limit is the maximum for any satellite measured over any 3-second interval for any point within the coverage area. The range acceleration error limit is the maximum for any satellite measured over any 3-second interval for any point within the coverage area. Under nominal conditions, all satellites are maintained to the same standards, so it is appropriate for availability modelling purposes to assume that all satellites have a 43.6-metre RMS SIS user range error (URE). The standards are restricted to range domain errors allocated to space and control segments.

4.1.1.4 Availability. The availability standard applies to normal operations, which implies that updated navigation data is uplinked to the satellites on a regular basis. Availability is the percentage of time over any 24-hour interval that the predicted 95 per cent positioning error (due to space and control segment errors) is less than its threshold, for any point within the coverage area. It is based on a 15-metre horizontal 95 per cent threshold;

a 33-metre vertical 95 per cent threshold; using a representative receiver;

611CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 and operating within the coverage area over any 24-hour interval. The service availability assumes a constellation that meets the criteria in

Chapter 3, 3.7.3.1.1.7. As noted for position domain accuracy, in order to maintain backwards compatibility, the availability standard will be met with a representative SPS receiver tracking only PRNs 1 through 32.

4.1.1.5 Reliability. Reliability is the percentage of time over a specified time interval that the instantaneous SPS SIS URE is maintained within the range error limit, at any given point within the coverage area, for all healthy GPS satellites. The reliability standard is based on a measurement interval of one year and the average of daily values within the coverage area. The worst single point average reliability assumes that the total service failure time of 18 hours will be over that particular point (3 failures each lasting 6 hours).

4.1.1.6 Major service failure.

4.1.1.6.1 A major service failure is defined to be a condition over a time interval during which a trackable and healthy GPS satellite’s instantaneous ranging signal error (excluding atmospheric and receiver errors) exceeds the range error limit of 4.42 times the integrity assured user range accuracy

(IAURA) broadcast by a satellite for longer than the allowable time-toalert (10 seconds). A major service failure occurs only if no alert is issued within the 10 second time to alert. Events when the instantaneous user range error (URE) exceeds 4.42 times the IAURA for a total duration of less than 10 seconds are not counted as major service failures. Once an alert has been issued, the major service failure event ceases to have any impact on SPS SIS integrity.

4.1.1.6.2 The instantaneous SIS URE will depend upon the combination of SIS components used. The major service failure standards apply for both single-frequency and dual-frequency users using these SIS component combinations in Table D-2.

4.1.1.6.3 For SIS component combinations using LNAV data, the IAURA is equal to the upper bound on the URA value corresponding to the URA index “N” currently broadcast by the satellite in subframe 1. This URA is specific to 612CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 the broadcasting satellite. For SIS component combinations using CNAV data, the IAURA is the root sum square (RSS) of an elevation dependent function of the upper bound value of the URAED component and a non- elevation-dependent function of the upper bound value of the URANED component currently broadcast by the satellite in MT-10 and MT-3x respectively. This IAURA is also specific to the broadcasting satellite. The IAURA for a marginal SPS SIS is not defined and there is no IAURA for an unhealthy SPS SIS. Since the URAs and IAURAs vary with time, a validity period for each is specified in the GPS interface specifications.

4.1.1.6.4 The onset rate, Rsat, is defined as the probability of a major service failure on any particular satellite over any hour, given that the maximum SPS SIS instantaneous URE did not exceed 4.42 times the IAURA at the start of the hour. The mean fault duration is one hour and the worst-case duration is six hours.

4.1.1.6.5 The probabilities of a single satellite major service failure (Psat) for a particular satellite and a common-cause, multi-satellite major service failure (Pconst) are instantaneous state probabilities equivalent to the fraction of time when the SPS SIS instantaneous URE exceeds 4.42 times the IAURA for more than 10 seconds without an alert issued within those 10 seconds.

4.1.1.6.6 The probability of 1×10-5 in Chapter 3, 3.7.3.1.1.4 corresponds to a maximum of 3 major service failures, with one-hour duration, for the entire constellation per year assuming a maximum constellation of 32 satellites.

4.1.1.7 Continuity. Continuity for a healthy GPS satellite is the probability that the SPS SIS will continue to be healthy without unscheduled interruption over a specified time interval. Scheduled interruptions which are announced at least 48 hours in advance do not contribute to a loss of continuity.

4.1.1.8 Coverage. The SPS supports the terrestrial coverage area, which is from the surface of the earth up to an altitude of 3 000 km.

4.1.1.9 Normal operations. In normal operations mode, the satellites are uploaded with fresh navigation (NAV) message data by the control segment on a regular basis. The SPS SIS indicates when the satellite is in the normal operations mode by way of the C/A code signal LNAV data stream fit interval flag being set to “0” (zero) in accordance with IS-GPS-200K. When the fit interval flag is set to “1” (one), the satellite is operating in the extended operations mode. Special SPS SIS accuracy standards apply for the extended operations mode. See IS-GPS-200K for further details on the fit interval flag.

Note1.: There is no equivalent “normal operations mode” flag (fit interval flag) in the CNAV data stream on the I5-code signal 613CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note2.: Additional information concerning normal operations is given in the GPS SPS PS, Sections A.4.3.2 and A.4.3.3.

4.1.2 GLONASS Note.: Additional information is given in the GLONASS FDMA ICD and in the GLONASS CDMA ICD General Description.

4.1.2.1 Assumptions. The performance standard is based upon the assumption that a representative channel of standard accuracy (CSA) receiver is used.

A representative receiver has the following characteristics: designed in accordance with GLONASS ICD; uses a 5-degree masking angle; accomplishes satellite position and geometric range computations in the most current realization of the PZ-90 and uses PZ-90 – WGS-84 transformation parameters as indicated in Appendix B, 3.1.2.5.2;

generates a position and time solution from data broadcast by all satellites in view; compensates for dynamic Doppler shift effects on nominal CSA ranging signal carrier phase and standard accuracy signal measurements;

excludes GLONASS unhealthy satellites from the position solution; uses up-to-date and internally consistent ephemeris and clock data for all satellites it is using in its position solution; and loses track in the event that a GLONASS satellite stops transmitting standard accuracy code. The time transfer accuracy applies to a stationary receiver operating at a surveyed location.

4.1.2.2 Accuracy. Accuracy is measured with a representative receiver and a measurement interval of 24 hours for any point within the coverage area.

The positioning and timing accuracy of single-frequency solutions are for the signal-in-space (SIS) only and do not include such error sources as: ionosphere, troposphere, interference, receiver noise or multipath. Dual frequency solution accuracy characteristics include ionosphere residual errors. The accuracy is derived based on the worst two of 24 satellites being removed from the constellation and a 6-metre constellation RMS SIS user range error (URE).

4.1.2.3 Range domain accuracy. Range domain accuracy is conditioned by the satellite indicating a healthy status and transmitting standard accuracy code and does not account for satellite failures outside of the normal operating characteristics. Range domain accuracy limits can be exceeded during satellite failures or anomalies while uploading data to the satellite.

Exceeding the range error limit constitutes a major service failure as described in 4.1.2.6. The range rate error limit is the maximum for any satellite measured over any 3-second interval for any point within the coverage area. The range acceleration error limit is the maximum for any satellite measured over any 3-second interval for any point within the coverage area. The range error accuracy over all satellites is the 95 per cent threshold of the URE of all satellites over any 24-hour interval for any 614CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 point within the coverage area. The range error accuracy for any satellite is calculated over a 30-day interval. Under nominal conditions, all satellites are maintained to the same standards, so it is appropriate for availability modelling purposes to assume that all satellites have a 6-metre RMS SIS URE. The standards are restricted to range domain errors allocated to space and control segments.

4.1.2.4 Availability. Availability is the percentage of time over any 24-hour interval that the predicted 95 per cent positioning error (due to space and control segment errors) is less than its threshold, for any point within the coverage area. It is based on a 12 metre (40-foot) horizontal 95 per cent threshold and a 25-metre (80-foot) vertical 95 per cent threshold, using a representative receiver and operating within the coverage area over any 24-hour interval. The service availability assumes the worst combination of two satellites out of service.

4.1.2.4.1 Satellite/constellation availability. Twenty-four operational satellites are available in orbit with 0.95 probability (averaged over any day), where a satellite is defined to be operational if it is capable of, but is not necessarily transmitting, a usable ranging signal. At least 21 satellites in the 24 nominal plane/slot positions must be set healthy and must be transmitting a navigation signal with 0.98 probability (yearly averaged).

4.1.2.5 Reliability. Reliability is the percentage of time over a specified time interval that the instantaneous CSA SIS URE is maintained within the range error limit, at any given point within the coverage area, for all healthy GLONASS satellites. The reliability standard is based on a measurement interval of one year and the average of daily values within the coverage area. The single point average reliability assumes that the total service failure time of 18 hours will be over that particular point (three failures each lasting six hours).

4.1.2.6 Major service failure. A major service failure is defined as a condition over a time interval during which a single healthy GLONASS satellite’s ranging signal error (excluding atmospheric and receiver errors) exceeds the range error limit of 70 m (as defined in Chapter 3, 3.7.3.1.2.4).

4.1.2.7 Constellation fault. Constellation fault is defined as a condition over a time interval during which more than one healthy GLONASS satellite’s ranging signal error (excluding atmospheric and receiver errors) exceeds the range error limit of 70 m due to a common cause (as defined in Chapter 3,

3.7.3.1.2.5).

4.1.2.8 Continuity. Continuity for a healthy GLONASS satellite is the probability that the GLONASS SIS will continue to be healthy without unscheduled interruption over a specified time interval. Scheduled interruptions, which are announced at least 48 hours in advance, do not contribute to a loss of continuity.

615CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

4.1.2.9 Coverage. The GLONASS CSA supports the terrestrial coverage area, which is from the surface of the earth up to an altitude of 2 000 km.

4.1.2.10 GLONASS time. GLONASS time is generated based on GLONASS Central Synchronizer time. Daily instability of the Central Synchronizer hydrogen clock is not worse than 5 × 10–14. The difference between GLONASS time and UTC(SU) is within 1 millisecond. The navigation message contains the requisite data to relate GLONASS time to UTC(SU) within 0.7 microsecond.

4.1.2.11 Transformation of GLONASS-M current data information into common form. A satellite navigation message contains current data information in NT parameter. It could be transformed into the common form by the

following algorithm: a) Current year number J in the four-year interval is calculated:

If 1 ≤ NT ≤ 366; J = 1;

If 367 ≤ NT ≤ 731; J = 2;

If 732 ≤ NT ≤ 1 096; J = 3;

If 1 097 ≤ NT ≤ 1 461; J = 4. b) Current year in common form is calculated by the following formula:

Y = 1 996 + 4 (N4 – 1) + (J – 1). c) Current day and month (dd/mm) are extracted from the reference table stored in user equipment ROM. The table interrelates NT parameter and common form dates.

4.1.2.11.1 GLONASS coordinate system. The GLONASS coordinate system is PZ- 90 as described in Parameters of Earth, 1990 (PZ-90), published by the Topographic Service, Russian Federation Ministry of Defence, Moscow.

4.1.2.11.2 PZ-90 parameters include fundamental geodetic constants, dimensions of the common terrestrial ellipsoid, the characteristics of the gravitational field of the earth, and the elements of the Krasovsky ellipsoid (coordinate system 1942) orientation relative to the common terrestrial ellipsoid.

4.1.2.11.3 By definition, the coordinate system PZ-90 is a geocentric Cartesian space system whose origin is located at the centre of the earth’s body. The Z- axis is directed to the Conventional Terrestrial Pole as recommended by the International Earth Rotation Service. The X-axis is directed to the point of intersection of the earth’s equatorial plane and zero meridian established by the Bureau International de l’Heure. The Y-axis completes the right-handed coordinate system.

4.1.2.11.4 Geodetic reference systems WGS-84 and PZ-90 are maintained consistent with the International Terrestrial Reference Frame (ITRF).

616CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 While the current conversion parameters from PZ-90 to WGS 84 are

provided in Appendix B, 3.1.2.5.2, the application of previous versions of these parameters is also appropriate as long as performance requirements of Chapter 3, Table 3.7.2.4-1 for intended operation are met.

4.1.3 Galileo Note.: Additional information concerning the Galileo Open Service is given in the Galileo OS SIS ICD and Galileo OS SDD.

4.1.3.1 Assumptions. The Galileo Open Service (OS) performance standard is based upon the assumption that a representative OS receiver is used. A

representative receiver has the following characteristics: a) designed in accordance with Galileo OS SIS ICD; b) uses a 5-degree masking angle; c) accomplishes satellite position and geometric range computations in the most current realization of the Galileo Terrestrial Reference Frame (GTRF);

d) generates a position and time solution from data broadcast by all satellites in view; e) excludes Galileo non-healthy signals from the position solution; f) uses up-to-date and internally consistent ephemeris and clock data for all satellites it is using in its position solution; and g) navigation data (ephemeris, satellite clock correction and SISA parameters) is not used beyond the maximum validity time of 4 hours.

4.1.3.2 Position domain accuracy

4.1.3.2.1 Position domain accuracy for single-frequency Galileo OS. The horizontal/vertical position domain accuracy is measured with a representative receiver and a measurement interval of 30 days for any point within the coverage area. The position is computed using single- frequency “healthy” SIS. The positioning and timing accuracy are for the SIS only (including BGD errors) and do not include such error sources as:

ionosphere, troposphere, interference, receiver noise or multipath.

4.1.3.2.2 Position domain accuracy for dual-frequency Galileo OS. The horizontal/vertical position domain accuracy is measured with a representative receiver and a measurement interval of 30 days for any point within the coverage area. The position is computed using dual- frequency “healthy” SIS. The positioning and timing accuracy are for the 617CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

SIS only and do not include such error sources as: ionosphere, troposphere, interference, receiver noise or multipath.

4.1.3.3 Range domain accuracy. The Galileo ranging accuracy is defined as a statistical measure of the SIS range error time series. It is only measured for time periods during which the transmitted SIS is healthy. Galileo ranging accuracy is evaluated over all age of data (AOD) values, i.e. the SIS range error time series will consider the navigation message at the age of data when it was observed. It is computed for both single-frequency and dual-frequency users. The range rate error limit is the maximum for any satellite measured over any 3-second interval for any point within the coverage area. The 95th percentile SIS range error accuracy for any satellite is calculated over a 30-day interval. The 99.9th percentile SIS range error accuracy for any satellite is normalized annually.

4.1.3.3.1 SIS accuracy. The SIS accuracy is a prediction of the minimum standard deviation (1 sigma) of the unbiased Gaussian distribution which over bounds the predictable distribution of SIS range error for all possible user locations within the satellite coverage area. The SISA parameter, broadcast in Galileo SIS navigation message, provides the user with an indication of the SIS accuracy according to Appendix B, 3.1.3.1.3.4.2. The SISA parameter can assume 255 values. Nevertheless, when it is used as one of the means for determining the SIS status of a Galileo satellite, it must be considered as a binary indicator with its only meaningful values being “no accuracy prediction available” (NAPA) when SISA=255 or “not NAPA” when SISA≠255. SISA values from 126 to 254 are described as spare, and should be considered as “not NAPA”.

4.1.3.3.2 Galileo BGD. Galileo BGD is the estimate of the group delay between the different frequencies of a specific Galileo satellite. It is provided as part of the Galileo broadcast navigation data as specified in Appendix B,

3.1.3.1.3.1 and 3.1.3.1.3.2.

4.1.3.4 Galileo UTC time determination accuracy. The Galileo UTC time determination accuracy depends on both the instantaneous GST determination error and on the error in the broadcast GST-UTC conversion parameters. This second component is defined as the Galileo SIS UTC time dissemination accuracy.

4.1.3.4.1 Galileo SIS UTC time dissemination accuracy. The Galileo SIS UTC time dissemination accuracy is defined as the 95th percentile of the broadcast GST/UTC conversion parameters error. Galileo SIS UTC time dissemination accuracy is the SIS component of the overall user UTC time determination, which is driven by the accuracy of the broadcast GST-UTC parameters. It does not contain effects that are not under the control of the Galileo operator such as user local contributions depending on the receivers or due to atmospheric effects.

4.1.3.5 Service availability. Service availability is the percentage of time over a 30- 618CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 day interval that the predicted 95 per cent positioning error (due to space and control segment errors) is less than its threshold, for any point within the coverage area. It is based on a 10-metre horizontal 95 per cent threshold; a 16-metre vertical 95 per cent threshold; using a representative receiver; and operating within the coverage area over the 30-day interval.

The service availability assumes a constellation that meets the criteria in

4.1.3.5.1.

4.1.3.5.1 SIS per-slot/constellation availability. The probability that an operational slot in the Galileo constellation is occupied by a satellite transmitting healthy SIS is higher than 0.95 (normalized annually). For the Galileo baseline configuration, the probability that at least 21 satellites in the nominal 24-slot positions are set healthy and are transmitting a navigation signal, is higher than 0.97 (normalized annually). The SIS constellation availability can be derived from the SIS per-slot availability by means of a binomial model.

4.1.3.6 Probability of failure

4.1.3.6.1 P t. P is the probability that the instantaneous ranging signal error of a sa sat healthy Galileo satellite (excluding atmospheric and receiver errors) exceeds k times the Galileo user range accuracy (Galileo URA). Galileo URA in P definition corresponds to σ or to σ for dual- sat URA,DF URA,SF frequency or single-frequency users, respectively. k is the number of standard deviations from the mean corresponding to a probability of P in sat a normal distribution. For instance, a k factor of 4.17, corresponds to a 3 × 10-5 P value. P applies at any given time and at any location in the sat sat satellite visibility area to both single-frequency and dual-frequency users.

4.1.3.6.2 P . P . is the probability that the instantaneous ranging signal errors const const of two or more healthy Galileo satellites (excluding atmospheric and receiver errors) exceeds k times the Galileo user range accuracy (Galileo URA) due to a common failure. Galileo URA in the P . definition const corresponds to σ or to σ for dual-frequency or single-frequency URA,DF URA,SF users, respectively. P . applies at any given time and at any location in const the respective visibility areas of the affected satellites to both single- frequency and dual-frequency users.

4.1.3.6.3 σ . Galileo σ is defined as the standard deviation of a zero-mean URA,DF URA,DF normal distribution which overbounds the actual distribution of SIS range errors more probable than P . Galileo σ applies to any user location sat URA,DF and to a healthy SIS dual-frequency combination E1/E5a.

4.1.3.6.4 σ . Galileo σ is defined as the standard deviation of a zero-mean URA,SF URA,SF normal distribution which overbounds the actual distribution of SIS range errors more probable than P . Galileo σ applies to any user location sat URA,SF and to a healthy SIS single-frequency user (E1 or E5a). σ considers URA,SF the Galileo σ and can be derived from the following expression:

BGD 619CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 where 𝛾𝑓 69ndrepresents the frequency inflation factor equal to 𝑓𝐸1 2 /𝑓𝐸5𝑎 2 for E5a users and to 1 for E1 users.

The same expression applies between Galileo σ and σ . The URE,SF URE,DF σ and σ are defined in Appendix B, section 3.4.1.1.2. This URE,SF URE,DF expression can also be used by Galileo receiver to compute the σ URE,SF and σ from broadcast σ and σ in Galileo I/NAV word Type URE,SF URE,DF URE,DF

22.

4.1.3.6.5 σ . Galileo σ is defined as the standard deviation of a zero-mean BGD BGD normal distribution, which overbounds the actual distribution of BGD residual errors such that the probability of unbounded errors is negligible with respect to P . BGD residual errors are the remaining errors after sat applying Galileo BGD corrections broadcast in the navigation message.

4.1.3.7 Continuity. Continuity for a healthy Galileo satellite is the probability that the Galileo OS SIS will continue to be healthy without unscheduled interruption over the next hour. Scheduled interruptions which are announced at least 48 hours in advance do not contribute to a loss of SIS continuity.

4.1.3.8 Coverage. The Galileo OS supports the terrestrial coverage area, which is from the surface of the earth up to 30.48 km.

4.1.3.9 Galileo system time (GST). The GST is a continuous timescale based on the definition of the second (according to the International System of units, SI) whose origin/reference epoch GST (t0) is defined as 13 seconds before 1999-08-22 00:00:00 UTC. The time synchronization information disseminated in the Galileo SIS (e.g. satellite clock offsets) is referenced to GST. This information allows the Galileo OS users to estimate their local time referenced to the GST realization computed by the Galileo OS receiver. In order to better support timing applications based on UTC, the Galileo OS data message includes additional parameters which enable the Galileo OS users to obtain a realization of the UTC time by applying a correction to the GST.

4.1.3.10 Galileo terrestrial reference frame (GTRF). The GTRF is a highly accurate independent realization of the International Terrestrial Reference System

(ITRS) based on the estimated coordinates of each of the Galileo sensor station (GSS) sites. The Galileo system uses the geodetic input information to produce navigation data (e.g. satellite ephemeris) referenced to the GTRF. Accordingly, the user position coordinates derived from Galileo position solutions are referenced to GTRF. Due to the good alignment of GTRF to ITRF both reference frames are understood to be equivalent for aviation. The GTRF is regularly aligned if new ITRF 620CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 realizations are published. To obtain the position in any reference frame different from ITRF, Galileo OS user equipment needs to apply the appropriate valid transformation parameters between the latest ITRF and the desired reference frame. This transformation is under full control and responsibility of the Galileo OS user. Concerning the interoperability between GPS and Galileo, the GPS terrestrial reference frame WGS-84 and the GTRF are both realizations of the ITRF. Therefore, for most Galileo OS applications, a high level of interoperability is provided between the spatial positions obtained with GPS and those obtained with Galileo, without further activity by the user equipment.

4.1.3.11 Age of ephemeris. The age of ephemeris is the time elapsed between the reference t0e (set at the beginning of each navigation data set) and the time of usage of the ephemeris by a receiver.

Note.: Details on how to compute the age of ephemeris can be found in Galileo OS SDD, Annex C, section 4.4.1.

4.1.3.12 Age of data (AOD). The age of data (AOD) is the elapsed time between the generation of a navigation message by the ground segment and its usage at user level. Aging of data (characterized by AOD) impacts the accuracy of the orbit and clock models. The accuracy of their prediction inevitably degrades with higher ages.

4.1.4 BDS

4.1.4.1 Assumptions. The performance standard is based upon the assumption that a representative BDS Open Service (BDS OS) receiver is used. A

representative receiver has the following characteristics: it is designed in accordance with BDS ICDs; uses a 5-degree masking angle for MEO satellites and a 12-degree masking angle for IGSO satellites;

accomplishes satellite position and geometric range computations in the most current realization of the BDCS (which is equivalent to WGS-84); compensates for dynamic Doppler shift effects on nominal BDS OS ranging signal carrier phase and ranging code measurements; excludes BDS unhealthy or marginal satellites from the position solution; uses up- to-date and internally consistent ephemeris and clock data for all satellites it is using in its position solution; and loses track in the event that a BDS satellite stops transmitting ranging code. The time transfer accuracy applies to a stationary receiver operating at a surveyed location.

4.1.4.2 Accuracy. Position domain accuracy is measured with a representative receiver and a measurement interval of 168 hours (seven sidereal days) for any point within the coverage area. The positioning and timing accuracy

are for the SIS only and do not include such error sources as: ionosphere, troposphere, interference, receiver noise or multipath. The accuracy is derived based on the worst two of all operational satellites being removed from the constellation and a 4.6-metre 95th percentile user range error of 621CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 any satellite.

4.1.4.2.1 Time transfer accuracy. Time transfer accuracy is the 95 per cent statistical deviation between the BDS OS timing receiver output and Coordinated Universal Time (UTC) maintained by NTSC in China. It can be used to evaluate the timing performance of a navigation satellite system.

4.1.4.3 Range domain accuracy. Range domain accuracy is measured with a representative receiver and a measurement interval of 168 hours. Range domain accuracy is conditioned by the satellite indicating a healthy status and transmitting BDS OS ranging code and does not account for satellite failures outside of the normal operating characteristics. Range domain accuracy limits can be exceeded during satellite failures or anomalies while uploading data to the satellite. Exceedance of the range error limit constitutes a major service failure as described in 4.1.4.5. The range rate error limit is the maximum for any satellite measured over any 3-second interval for any point within the coverage area. The range acceleration error limit is the maximum for any satellite measured over any 3-second interval for any point within the coverage area. Under nominal conditions, all satellites are maintained to the same standards, so it is appropriate for availability modelling purposes to assume that all satellites have a 4.6- metre 95th percentile user range error. The standards are restricted to range domain errors allocated to space and control segments.

4.1.4.4 Availability. Availability is the percentage of time over any 168-hour interval that the predicted 95 per cent positioning error (due to space and control segment errors) is less than its threshold, for any point within the coverage area. It is based on a 15-metre horizontal 95 per cent threshold and a 22- metre vertical 95 per cent threshold; using a representative receiver and operating within the coverage area over any 168-hour interval. The service availability assumes the worst combination of two out-of-service satellites.

4.1.4.4.1 Satellite/constellation availability. At least 24 satellites in the 27 nominal plane/slot positions must be set healthy and must be transmitting a navigation signal with a 0.998 probability (yearly averaged). At least 21 satellites in the 27 nominal plane/slot positions must be set healthy and must be transmitting a navigation signal with a 0.99999 probability (yearly averaged).

4.1.4.5 Major service failure

4.1.4.5.1 The single satellite major service failure is the condition that the SIS ranging error (excluding atmospheric and receiver errors) of any satellite exceeds the not-to-exceed (NTE) tolerance without an alert to users. For B1I signals, the NTE tolerance is defined to be 4.42 times the upper bound of the URA range corresponding to the URA index (URAI) value being broadcast in D1 navigation messages, as described in Appendix B,

3.1.4.1.3.1.2. For B1C and B2a signals, the NTE tolerance is defined to be

4.42 times the signal-in-space accuracy (SISA) value calculated as 622CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 described in Appendix B, 3.1.4.2.5. The Psat of 1 × 10-5 in Chapter 3,

3.7.3.1.4.4.1 corresponds to a maximum of three major service failures for each BDS OS signal per year assuming a maximum constellation of 30 satellites. The Mean Time to Notify (MTN) is 60 minutes.

4.1.4.5.2 The common-cause major service failure is a condition that the BDS OS SIS user range error of two or more satellites will exceed the NTE tolerance due to a common fault without an alert received at the user receiver antenna. For B1I signals, the NTE tolerance is defined to be 4.42 times the upper bound of the URA range corresponding to the URA index

(URAI) value being broadcast in D1 navigation messages, as described in Appendix, 3.1.4.1.3.1.2. For B1C and B2a signals, the NTE tolerance is defined to be 4.42 times the SISA value calculated as described in Appendix B, 3.1.4.2.5. The Pconst of 6 × 10-5 in Chapter 3, 3.7.3.1.4.4.2 corresponds to a maximum of 0.5 commonly caused major service failures for the entire constellation per year. The MTN is 60 minutes.

4.1.4.6 Continuity. Continuity for a healthy BDS satellite is the probability that the BDS OS SIS will continue to be healthy without unscheduled interruption over a specified time interval. Scheduled interruptions, which are announced at least 24 hours in advance, do not contribute to a loss of continuity.

4.1.4.7 Coverage. The BDS OS supports the terrestrial coverage area which is from the surface of the earth up to an altitude of 1 000 km.

4.1.4.8 BDS time. The time reference for the BDS uses the BeiDou Navigation Satellite System Time (BDT), as described in Appendix B, 3.1.4.4.

4.1.4.9 BDS coordinate system. BDS uses the BeiDou Coordinate System

(BDCS).

4.1.4.9.1 BDCS origin, axis and scale. The origin is located at the earth’s centre of mass; the Z axis is the direction of the IERS (International Earth Rotation and Reference System Service) Reference Pole (IRP); the X-axis is the intersection of IERS Reference Meridian (IRM) and the plane passing through the origin and normal to the Z-axis; the Y-axis, together with the Z-axis and the X-axis, constitute a right-handed orthogonal coordinate system. The length unit is the international system of units (SI) metre.

4.1.4.9.2 BDCS Ellipsoid. The geometric centre of the BDCS Ellipsoid coincides with the earth’s centre of mass, and the rotation axis of the BDCS Ellipsoid is the Z-axis. The parameters of BDCS Ellipsoid are defined as:

Semi-major axis: a = 6 378 137.0 m Geocentric gravitational constant (mass of the earth’s atmosphere included): μ = 3.986004418×1014 m3/s2

Flattening: f = 1/298.257222101 623CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

Earth rotation rate: Ωe ̇ = 7.2921150×10-5 rad/s

4.2 Dilution of precision Dilution of precision (DOP) factors express how ranging accuracy is scaled by a geometry effect to yield position accuracy. The optimal geometry (i.e. the lowest DOP values) for four satellites is achieved when three satellites are equally spaced on the horizon, at minimum elevation angle, and one satellite is directly overhead. The geometry can be said to “dilute” the range domain accuracy by the DOP factor.

4.3 GNSS antenna and receiver

4.3.1 The antenna specifications in Appendix B, 3.8.3.1, determine the axial ratio performance of the antennas. The specifications for the single- frequency only antennas do not control the antenna axial ratio except at boresight.

4.3.2 Linear polarization should be assumed for the airborne antenna for SBAS GEO signals received at low-elevation angles. For instance, when receiving an SBAS GEO signal that needs to be provided at a minimum elevation angle of 5 degrees, single-frequency antennas should be presumed to be linearly polarized with −2.5 dBil (−5.5 dBic) gain. This should be taken into account in the SBAS GEO satellite link budget in order to ensure that the minimum received RF signal at the antenna port meets the requirements of Chapter 3, 3.7.3.4.5.3.2 and 3.7.3.4.6.3.

4.3.3 The failures caused by the receiver can have two consequences on navigation system performance which are the interruption of the information provided to the user or the output of misleading information.

Neither of these events are accounted for in the signal-in-space requirement.

4.3.4 The nominal error of the GNSS aircraft element is determined by receiver noise, interference, and multipath and tropospheric model residual errors.

Specific receiver noise requirements for both the SBAS airborne receiver and the GBAS airborne receiver include the effect of any interference below the protection mask specified in Appendix B, 3.7. The required performance has been demonstrated by receivers that apply narrow correlator spacing or code smoothing techniques.

4.3.5 The method for the search of the in-band, near-band and out-of-band maximum non-aeronautical interference tolerable power consists, for each interference bandwidth BWi, in computing the largest value of the Spectral Separation Coefficient (SSC) for all PRNs and for all central frequencies fci = fcL1orL5 +/- max(BWGNSS/2, BWi/2), where BWGNSS = 20 MHz.

For all GNSS signals’ modulations (BPSK and MBOC) considered in the SARPs, this process results in an in-band, near-band maximum tolerable power monotonously increasing with BWi. The out-of-band maximum 624CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 tolerable power is evaluated for BWi = 1 kHz.

4.3.6 Following Note 5 in Table B-171 of Appendix B, Table B-171 does not describe non aeronautical pulsed interferences in the environment to be considered for the L5 channel in an L1/L5 receiver as their impact is negligible compared to DME/TACAN and JTIDS/MIDS impact considered in the environment.

5. AIRCRAFT-BASED AUGMENTATION SYSTEM (ABAS)

5.1 Introduction

5.1.1 ABAS augments the information obtained from core satellite constellations with additional receiver processing and/or with information available from other sensors on board the aircraft in order to ensure operation according to the values specified in Chapter 3, 3.7.2.4.

5.1.2 ABAS includes processing schemes that provide: a) integrity monitoring for the position solution using redundant information (e.g. multiple range measurements). The monitoring

scheme generally consists of two functions: fault detection and fault exclusion. The goal of fault detection is to detect the presence of a positioning failure. Upon detection, proper fault exclusion determines and excludes the source of the failure (without necessarily identifying the individual source causing the problem), thereby allowing GNSS navigation to continue without interruption. There are two general

classes of integrity monitoring: receiver autonomous integrity monitoring (RAIM), which uses GNSS information exclusively, and aircraft autonomous integrity monitoring (AAIM), which uses information from additional on-board sensors (e.g. barometric altimeter, clock and inertial navigation system (INS));

b) continuity aiding for the position solution using information of alternative sources, such as INS, barometric altimetry and external clocks; c) availability aiding for the position solution (analogous to the continuity aiding); and d) accuracy aiding through filtering techniques and/or estimation of remaining errors in determined ranges.

5.1.3 Non-GNSS information can be integrated with GNSS information in two

ways: a) integrated within the GNSS solution algorithm (an example is the modelling of altimetry data as an additional satellite measurement); and 625CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 b) external to the basic GNSS position calculation (an example is a comparison of the altimetry data for consistency with the vertical GNSS solution with a flag raised whenever the comparison fails).

5.1.4 Each scheme has specific advantages and disadvantages, and it is not possible to present a description of all potential integration options with specific numerical values of the achieved performance. The same applies to the situation when several GNSS elements and/or multiple frequency signals are combined.

5.2 Receiver autonomous integrity monitoring (RAIM)

5.2.1 RAIM has been implemented using GPS L1 C/A (“GPS RAIM”) and fixed values for constellation performance.

5.2.2 In contrast with ARAIM (section 5.3), GPS RAIM relies on GPS constellation performance using the the broadcast URA values and a satellite fault probability of Psat = 1 x 10-5 or lower. Furthermore, it assumes that only one satellite fault occurs at a given time and that any bias-like errors are small enough to be overbounded by a zero-mean gaussian distribution.

5.2.3 GPS RAIM can be combined with AAIM and other augmentations including ARAIM.

5.3 Advanced RAIM (ARAIM)

5.3.1 Introduction

5.3.1.1 ARAIM refers to an implementation of GNSS-receiver based ABAS other than GPS RAIM, including single or dual frequency, and single or multiple constellation modes. ARAIM includes the provision of integrity support data (ISD). ISD is either generated by or verified by an entity referred to as the ISM generator (ISMG). There is one ISMG per core constellation.

In comparison to GPS RAIM, which can be thought of as using “static ISD”, ARAIM enables dynamic ISD where integrity parameters can be adapted to actual core satellite constellation performance and available performance history.

5.3.1.2 ISD will be broadcast in core satellite constellation navigation data messages. Messages containing ISD are called integrity support messages (ISM). Some ISD could also be sent outside of ISM, as part of other navigation data messages (such as IAURA for GPS).

5.3.1.3 The ISD contains parameters that describe a Gaussian overbound of the fault-free ranging signal errors as well as parameters describing the likelihood that the satellite signal is faulted and may not be adequately characterized by the fault-free Gaussian overbounds. The ARAIM 626CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 algorithm uses the ISD to perform fault monitoring and integrity tests and to calculate the protection level(s) to achieve a target integrity risk performance in accordance with operational requirements. The ARAIM algorithm assumes that the fault events characterized by the ISD are independent. It is not necessary to monitor all possible combinations of satellite and constellation faults, as many of these combinations have very small contributions to the integrity risk. The ARAIM algorithm accounts for the integrity risk of the fault-free position and missed detections of monitored and unmonitored fault modes.

5.3.1.4 The ISD parameters σURA and σURE characterize the fault-free ranging signal errors caused by clock and ephemeris errors and the noise-like error contributions from antenna biases, signal deformations, inter-frequency biases, code-carrier coherence. The bnom term characterizes bias-like errors that can be bounded in magnitude. These are due to antenna biases, signal deformations, inter-frequency biases, nominal code-carrier incoherence, nominal range error variation over the satellite terrestrial footprint (due to antenna anisotropy) or other quasi-static/correlated error sources. The bnom term can also be used to bound asymmetry and non- unimodality in the observed clock and ephemeris error distributions.

Flexibility is given to the ISMG when determining a Gaussian overbound described by bnom and σURA as long as the overbounding criteria in Appendix B, 3.4.1.2.2.1 are satisfied. Several overbounding methods are available. bnom, σURA and σURE are not accounting for errors caused by signal propagation through the troposphere and ionosphere. 33

5.3.1.5 The ISD parameters fault rate (Rsat, Rconst) and fault probability (Psat, Pconst) describe the likelihood that the signal is faulted. If a mean fault duration is provided together with a fault rate, the corresponding fault probability can be derived by the receiver. The fault rate is a conservative estimate of the number of faults per hour. The ISMG can provide ISD values equivalent to the default values. However, if justified based on analysis and observed performance, the ISMG may set the broadcast fault parameters such that fault rate and fault probability are lower than default commitments. The ISMG will need to update the broadcast ISD if observed behaviour no longer supports the lower parameters. The ISMG may provide margin in the broadcast ISD by artificially inflating the observed faults by one or more to ensure that ISM updating does not become time critical.

5.3.1.6 If a core satellite constellation that does not provide an ISM in its navigation data messages is used in ARAIM, then default ISD values are used in the receiver as specified in Appendix B, 3.4.1.3.3.3. Further details about default ISD are provided in 5.3.2.

5.3.1.7 The ARAIM SARPs allow for some flexibility in the detailed assignment of responsibility for ISD parameter data integrity. For example, an ISMG could assemble or code an ISM, generate an associated CRC and then hand-over the complete message to the core satellite constellation 627CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 provider for broadcasting. Alternatively, the ISMG could transmit the values to be broadcast to the core satellite constellation provider, who would then assemble or code the ISM, and generate a CRC (or other suitable mechanism) as part of its normal message packaging. Whichever approach is chosen, procedures by the ISMG and the relevant core satellite constellation service provider mitigate the risk of data corruption at any stage of the entire process (Appendix B, 3.4.1.2.4). This is based on a thorough analysis of the overall system architecture. The resulting data quality assurance processes will be consistent with the supported ARAIM service type.

5.3.1.8 ARAIM may be combined with RAIM, AAIM and other augmentations.

5.3.1.9 Additional guidance material on ARAIM is provided in the Global Navigation Satellite System (GNSS) Manual (Doc 9849).

5.3.2 Default ISD and traceability to core satellite constellation definitions

5.3.2.1 Default ISD can be used by GNSS receivers to process satellites for which no ISM is broadcast by the core satellite constellation. Table D-3 provides justification of the values in Appendix B, 3.4.1.3.3.3 by referencing the corresponding sections in the core satellite constellation standards.

628CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note 1.: SF refers to single frequency processing and DF to dual frequency.

Note 2.: See Appendix B, 3.4.1.3.3.3, Note 3, for interface control document references. 35 Note 3.: As indicated in 4.1.3.6.4 for the Galileo σURA,SF, the Galileo single frequency σURA, SF and σURE, SF are linked to the Galileo dual frequency σURA, DF and σURE, DF by the following equation:

𝜎𝑆𝐹2=𝜎𝐷𝐹2+𝛾𝑓2∙𝜎𝐵𝐺𝐷2 with 𝛾𝑓=𝑓𝐸12𝑓𝐸5𝑎2𝑓𝑜𝑟 𝐸5𝑎, 𝛾𝑓=1 𝑓𝑜𝑟 𝐸1 𝑎𝑛𝑑 𝜎𝐵𝐺𝐷= 2.5 𝑚 .

5.3.2.2 Some ISD parameters (Psat, Pconst, Rsat, Rconst) are specified with a 629CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 “≤” sign. This means that core satellite constellation providers are free to further improve their minimum service commitments (which may or may not be reflected in future amendments to this Annex). However, any such future improvements will likely not be implemented in the default ISD values used by ARAIM receivers already installed in aircraft at that time.

5.3.2.3 The Galileo ARAIM service provision scheme is based on commitments made regarding the fault probabilities (Psat and Pconst) and fault rates (Rsat and Rcont). Those parameters, when complemented by σURA ,σURE and bnom, are sufficient to run the airborne integrity monitoring algorithm under ARAIM augmentation. Galileo MFD is not specified. The users should not assume any MFD values from the Galileo commitments on Psat, Pconst, Rsat and Rconst, since those parameters include margin on top of the actual performance that the user may experience and therefore MFD values derived from them may not be representative of the Galileo system.

6. SATELLITE-BASED AUGMENTATION SYSTEM (SBAS)

6.1 SBAS may provide an L1 SBAS service augmenting GPS and/or GLONASS constellations, a dual-frequency, multiconstellation (DFMC) SBAS service augmenting one or more (up to four) constellations, or both services. The L1 SBAS service uses the L1 message data to support single-frequency service. The DFMC SBAS service uses the L5 message data to support DFMC SBAS service. The SBAS messages and data content of the L1 SBAS and DFMC SBAS services are independent and users can only apply the data from the data channel associated with the specific service. In addition, when the SBAS supports ranging, the SBAS satellite may be used as a single-frequency ranging source on L1 using the L1 data, or a dual-frequency ranging source combining both L1 and L5 pseudo-ranges using the L5 data. An SBAS is made up of three distinct

elements: a) the ground infrastructure; b) the SBAS satellites; and c) the SBAS airborne receiver.

6.1.1 The ground infrastructure includes the monitoring and processing stations that receive the data from the navigation satellites and compute integrity, corrections and ranging data which form the SBAS signal-in-space. The SBAS satellites relay the data relayed from the ground infrastructure to the SBAS airborne receivers that determine position and time information using core satellite constellation(s) and SBAS satellites. The SBAS airborne receivers acquire the ranging and correction data and apply these data to determine the integrity and improve the accuracy of the derived position.

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6.1.2 The SBAS ground network measures the pseudo-range between the ranging source and an SBAS receiver at the known locations and provides separate corrections for ranging source ephemeris errors, clock errors and, in addition for the L1 SBAS service, ionospheric delays and errors.

The user applies a tropospheric delay model.

6.1.3 The ranging source ephemeris error and slow moving clock error are the primary basis for the corrections provided in DFMC SBAS service and

provided in the long-term correction in L1 SBAS. The ranging source clock error is adjusted for the long-term correction and tropospheric error and is the primary basis for the fast correction provided in L1 SBAS service. The ionospheric errors among many ranging sources are combined into vertical ionospheric errors at predetermined ionospheric grid points. These errors are the primary basis for ionospheric corrections provided in L1 SBAS service. No fast corrections are provided in DFMC SBAS service as a result of the slow clock drift performance of GNSS core constellations.

No ionospheric corrections are provided in DFMC SBAS service as DFMC SBAS corrections are provided for ranging derived from the ionosphere- free combination of satellite signals, which removes almost all ionospheric delay from the ranging measurements.

6.2 SBAS coverage area and service areas

6.2.1 It is important to distinguish between the coverage area and service areas for an SBAS. A coverage area typically corresponds to the union of SBAS satellite footprint areas and comprises one or more service areas. Service areas are declared by SBAS service providers or by the State or group of States managing the SBAS, for the typical operations defined in Table

3.7.2.4-1 (e.g. En-route, APV-I, Category I) where the corresponding accuracy, integrity and continuity requirements are met with a certain availability (e.g. 99 per cent). Some SBAS service providers publish service areas of their systems (e.g. WAAS Performance standard, EGNOS Service Definition Document and AIPs). The service area for En-route may be larger than the service area for APV-I. DFMC SBAS can provide service areas that can be larger than service areas provided by L1 SBAS for the same service levels. For the GNSS receiver, the SIS is usable whenever the protection levels are lower than the alert limits for the intended operation (VPL<VAL and HPL<HAL), irrespective of whether or not the GNSS receiver is inside the corresponding service area defined by the SBAS service provider. SBAS systems support operations based on some or all of the SBAS functions defined in Chapter 3, 3.7.3.4.2. These

functions can be related to the operations that are supported as follows: a) Ranging: SBAS can provide a single-frequency ranging source on L1. L1 ranging can be used in the SBAS solution or for other augmentation(s) (ABAS, GBAS or other SBAS); SBAS can provide a dual-frequency ranging source using L1 and L5 frequencies suitable for a DFMC SBAS position derived from the broadcasting SBAS system.

631CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 b) Satellite status and basic differential corrections: L1 SBAS provides en-route, terminal, and non precision approach service. Different operations (e.g. performance-based navigation (PBN) operations) may be supported in different service areas;

c) Precise differential corrections: L1 SBAS provides APV and precision approach service (i.e. APV-I and Category I precision approach may be supported in different service areas); d) Ionosphere-free differential correction: DFMC SBAS provides en- route, terminal, non precision approach, APV and precision approach service (i.e. APV-I and Category I precision approach). Different operations (e.g. PBN operations) may be supported in different service areas.

6.2.2 Satellite-based augmentation services are provided by the Wide Area Augmentation System (WAAS) (North America), the European Geostationary Navigation Overlay Service (EGNOS) (Europe and Africa), the Michibiki Satellite based Augmentation Service (MSAS) (Japan) and the GPS-aided Geo-augmented Navigation (GAGAN) (India). The System for Differential Correction and Monitoring (SDCM) (Russia), the BeiDou Satellite-based Augmentation System (BDSBAS) (China), the Korea Augmentation Satellite System (KASS) (Republic of Korea), the Augmented Navigation for Africa (ANGA) (ASECNA) and the Southern Positioning Augmentation Network (SouthPAN) (Australia and New Zealand) are also under development to provide these services.

6.2.3 An SBAS may provide accurate and reliable service outside the defined service area(s). The ranging, satellite status, basic differential corrections and ionosphere-free differential correction functions are usable throughout the entire coverage area. The performance of these functions may be technically adequate to support en-route, terminal and non-precision approach operations by providing monitoring and integrity data for core satellite constellations and/or SBAS satellites. L1 SBAS mitigates errors which cannot be monitored by its ground network through message Type 27 or message Type 28. DFMC SBAS mitigates errors that cannot be monitored by its ground network through message Type 32.

6.2.4 Each State is responsible for approving SBAS-based operations within its airspace. In some cases, States will field SBAS ground infrastructure linked to an SBAS. In other cases, States may approve service areas and SBAS-based operations using available SBAS signals. In either case, each State is responsible for ensuring that SBAS meets the requirements of Chapter 3, 3.7.2.4, within its airspace, and that appropriate operational status reporting and NOTAMs are provided for its airspace.

6.2.5 Before approving SBAS-based operations, a State must determine that the proposed operations are adequately supported by one or more SBASs.

632CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 This determination should focus on the practicality of using SBAS signals, taking into account the relative location of the SBAS ground network. This could involve working with the State(s) or organization(s) responsible for operating the SBASs. For an airspace located relatively far from an SBAS ground network, the number of visible satellites for which that SBAS provides status and basic corrections would be reduced. Since L1 SBAS receivers are able to use data from two SBASs simultaneously, and to use autonomous fault detection and exclusion when necessary, availability may still be sufficient for approval of operations. Unlike the L1 SBAS service that can only provide ionospheric delay estimate near the SBAS reference network, the ionosphere-free differential corrections will provide a valid solution in airspace located relatively far from the SBAS reference network. In most cases, there will be overlap of DFMC services from neighbouring SBAS systems and users will be able to transition directly from one SBAS system to another. There is no benefit from the combination of ranging sources corrected by two or more SBAS services, but there would be additional error bounding to account for potential differences among SBAS services. Therefore, the use of multiple SBAS is not permitted when using dual-frequency service.

6.2.6 Before publishing procedures based on SBAS signals, a State is expected to provide a status monitoring and NOTAM system. To determine the effect of a system element failure on service, a mathematical service volume model is to be used. The State can either obtain the model from the SBAS operator or develop its own model. Using the current and forecast status data of the basic system elements, and the locations where the State has approved operations, the model would identify airspace and airports where service outages are expected, and it could be used to originate NOTAMs.

The system element status data (current and forecast) required for the model could be obtained via a bilateral arrangement with the SBAS service provider, or via connection to a real time “broadcast” of the data if the SBAS service provider chooses to provide data in this way.

6.2.7 Participating States or regions will coordinate through ICAO to ensure that SBAS provides seamless global coverage, taking into account Recommendation 2.2/2 b) of the Thirteenth Air Navigation Conference, which calls for States to avoid, in principle, prohibiting the use of available GNSS elements if they perform according to ICAO SARPs and can meet all safety and regulatory requirements for the intended operations.

6.2.8 As the SBAS satellite coverages (footprints) overlap, it will be necessary for SBAS equipment to handle selection and transition mechanisms among the SBASs. As a minimum, the SBAS airborne receivers must be able to operate within the coverage of any SBAS. It is possible for an L1- only SBAS provider to monitor and send integrity and correction data for a geostationary orbit satellite that belongs to another SBAS service provider.

For L1 SBAS, augmenting ranging SBAS satellites can improve availability by adding ranging sources for user receivers that can track additional SBAS satellites. This improvement does not require any interconnection 633CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 between SBAS systems and should be accomplished by all SBAS service providers. For DFMC SBAS, the ranging signal from the SBAS PRN in use may be used. Ranging signal from other SBAS satellite(s) from the same provider may be used with Type 32 message augmentation. Ranging signal from other SBAS providers cannot be used.

6.2.9 Other levels of integration can be implemented using a unique connection between the SBAS networks (e.g. separate satellite communication). In this case, SBASs can exchange either raw satellite measurements from one or more reference stations or processed data (corrections or integrity data) from their master stations. This information can be used to improve system robustness and accuracy through data averaging, or integrity through a cross check mechanism. Availability will also be improved within the service areas, and the technical performance will meet the GNSS SARPs throughout the entire coverage (i.e. monitoring of satellites ephemeris would be improved). Finally, SBAS control and status data could be exchanged to improve system maintenance.

6.3 Integrity

6.3.1 The provisions for integrity are complex, as some attributes are determined within the SBAS ground network and transmitted in the signal- in-space, while other attributes are determined within the SBAS equipment on the aircraft. For the satellite status, basic corrections functions and ionosphere-free differential corrections functions, an error uncertainty for the ephemeris and clock corrections is determined by the SBAS ground network. This uncertainty is modelled by the variance of a zero-mean, normal distribution that describes the user differential range error (UDRE) or dual-frequency range error (DFRE) for each ranging source after application of fast (L1 SBAS) and long-term (L1 and DFMC SBAS) corrections and excluding atmospheric effects and receiver errors.

6.3.2 For the precise differential function, an error uncertainty for the ionospheric correction is determined. This uncertainty is modelled by the variance of a zero-mean, normal distribution that describes the L1 residual user ionospheric range error (UIRE) for each ranging source after application of ionospheric corrections. This variance is determined from an ionospheric model using the broadcast grid ionospheric vertical error

(GIVE).

6.3.3 There is a finite probability that an SBAS receiver would not receive an SBAS message. In order to continue navigation in that case, the SBAS broadcasts degradation parameters in the signal-in-space. These parameters are used in a number of mathematical models that characterize the additional residual error from basic, precise and ionosphere-free differential corrections induced by using old but active data. These models are used to modify the UDRE/DFRE variance and the UIRE variance as appropriate.

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6.3.4 The individual error uncertainties described above are used by the receiver to compute an error model of the navigation solution. This is done by projecting the pseudo-range error models to the position domain. The horizontal protection level (HPL) provides a bound on the horizontal position error with a probability derived from the integrity requirement.

Similarly, the vertical protection level (VPL) provides a bound on the vertical position. If the computed HPL exceeds the horizontal alert limit

(HAL) for a particular operation, SBAS integrity is not adequate to support that operation. The same is true for precision approach and APV operations, if the VPL exceeds the vertical alert limit (VAL).

6.3.5 One of the most challenging tasks for an SBAS provider is to determine UDRE/GIVE or DFRE variances so that the protection level integrity requirements are met without having an impact on availability. The performance of an individual SBAS depends on the network configuration, geographical extent and density, the type and quality of measurements used and the algorithms used to process the data. General methods for determining the model variance are described in section 14.

6.3.6 Residual clock and ephemeris error (σUDRE). The residual clock error is well characterized by a zero-mean, normal distribution since there are many receivers that contribute to this error. The residual ephemeris error depends upon the user location. For the precise differential function, the SBAS provider will ensure that the residual error for all users within a defined service area is reflected in the σUDRE. For the basic differential function, the residual ephemeris error should be evaluated and may be determined to be negligible.

6.3.7 Ionosphere-free residual clock and ephemeris error (σDFRE). The residual clock error is well characterized by a zero-mean, normal distribution since there are many receivers that contribute to this error. The residual ephemeris error depends upon the user location. For the ionosphere-free differential correction function, the SBAS provider will ensure that the residual error for all users within a coverage area is reflected in the σDFRE. The residual error needs to account for the increased noise in the ionosphere-free dual-frequency combination.

6.3.8 Vertical ionospheric error (σGIVE). The residual ionospheric error is well represented by a zero-mean, normal distribution since there are many receivers that contribute to the ionospheric estimate. Errors come from the measurement noise, the ionospheric model and the spatial decorrelation of the ionosphere. The position error caused by ionospheric error is mitigated by the positive correlation of the ionosphere itself. In addition, the residual ionospheric error distribution has truncated tails, i.e. the ionosphere cannot create a negative delay, and has a maximum delay.

6.3.9 Aircraft element errors. The combined multipath and receiver contribution is bounded as described in section 14. This error can be divided into multipath and receiver contribution as defined in Appendix B, 3.6.5.5.1, 635CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 and the standard model for multipath described in Appendix B,

3.6.5.5.1.1.2 may be used. The receiver contribution can be taken from the accuracy requirement (Appendix B, 3.5.8.2, 3.5.8.4.1 and 3.5.15.3.2) and extrapolated to typical signal conditions. Specifically, the aircraft can be assumed to have σ2 air = σ2 receiver + σ2 multipath, where it is assumed that σreceiver is defined by the RMSpr_air specified for GBAS Airborne Accuracy Designator A equipment, and σmultipath is defined in Appendix B, 3.6.5.5.1 for L1 SBAS equipment and 3.5.15.3.4.1 for DFMC SBAS equipment. The aircraft contribution to multipath includes the effects of reflections from the aircraft itself. Multipath errors resulting from reflections from other objects are not included. If experience indicates that these errors are not negligible, they must be accounted for operationally. The standard multipath model in Appendix B, 3.5.15.3.4.1 accounts for multipath error in the ionosphere-free combination.

6.3.10 Tropospheric error. The receiver must use a model to correct for tropospheric effects. The residual error of the model is constrained by the maximum bias and variance defined in Appendix B, 3.5.8.4.2, 3.5.8.4.3 and 3.5.15.3.4. The effects of this mean must be accounted for by the ground subsystem. The airborne user applies a specified model for the residual tropospheric error (σtropo).

6.4 RF characteristics

6.4.1 Minimum SBAS L1 GEO signal power level. The minimum aircraft equipment (e.g. RTCA/DO-229D with Change 1) is required to operate with a minimum signal strength of –164 dBW at the antenna port in the presence of non-RNSS interference (Appendix B, 3.7) and an aggregate RNSS noise density of –172.8 dBm/Hz. In the presence of interference, receivers may not have reliable tracking performance for a signal strength at the antenna port below –164 dBW (e.g. with GEO satellites placed in orbit prior to 2014). A GEO that delivers a signal power below –164 dBW at the receiving antenna port at 5 degree elevation on the ground can be used to ensure signal tracking in a service area contained in a coverage area defined by a minimum elevation angle that is greater than 5 degrees (e.g. 10 degrees). In this case, advantage is taken from the gain characteristic of the minimum standard (e.g. RTCA/DO-301) antenna to perform a trade-off between the GEO signal power and the size of the service area in which a trackable signal needs to be ensured. When planning for the introduction of new operations based on SBAS, States are expected to conduct an assessment of the signal power level as compared to the level interference from RNSS and non-RNSS sources. If the outcome of this analysis indicates that the level of interference is adequate to operate, then operations can be authorized.

6.4.2 Minimum SBAS L5 signal power level. The minimum aircraft equipment is required to operate with a minimum signal strength of –158 dBW at the antenna port in the presence of non-RNSS interference (Appendix B, 3.7) and an aggregate RNSS noise density of –171.4 dBm/Hz. An SBAS 636CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 satellite that delivers a signal power below –158 dBW at the receiving antenna port at 5 degree elevation on the ground can be used to ensure signal tracking in a service area contained in a coverage area defined by a minimum elevation angle that is greater than 5 degrees (e.g. 10 degrees). In this case, advantage is taken from the gain characteristic of the standard antenna to perform a trade-off between the SBAS satellite power and the size of the service area in which a trackable signal needs to be ensured. When planning for the introduction of new operations based on SBAS, States are expected to conduct an assessment of the signal power level as compared to the level of interference from RNSS and non- RNSS sources. If the outcome of this analysis indicates that the level of interference is adequate to operate, then operations can be authorized.

6.4.3 SBAS network time. SBAS network time is a time reference maintained by SBAS for the purpose of defining corrections. When using corrections, the user’s solution for time is relative to the SBAS network time rather than core satellite constellation system time. In L1 SBAS only, if corrections are not applied, the position solution will be relative to a composite core satellite constellation/SBAS network time depending on the satellites used and the resulting accuracy will be affected by the difference among them.

Mix of uncorrected and SBAS corrected measurement is not allowed in DFMC SBAS. L1 SBAS and DFMC SBAS services are independent. The SBAS network time used for L1 SBAS and that used for DFMC SBAS may be different. In DFMC SBAS, a time reference identifier parameter is broadcast in Type 37 message to inform DFMC user about the core constellation time reference used to steer the SBAS network time in DFMC SBAS (see Chapter 3, 3.7.3.4.7.2 which specifies the maximum time difference between SNT and core constellation reference time). It refers to the time reference of a GNSS constellation, which will be assumed to be the constellation of reference when computing SBAS user position and estimating time offset for other constellation augmented by the SBAS system.

6.4.4 SBAS convolutional and bi-binary encoding. Information on the convolutional coding and decoding of L1 SBAS messages can be found in RTCA/DO-229D with Change 1, Appendix A. Information on the convolutional coding and decoding of DFMC SBAS messages can be found in EUROCAE/ED-259, Appendix A. The SBAS L5 signals use bi- binary (Manchester) encoding (see section 1). SBAS L5 signals without bi- binary encoding are suitable for testing and validation purposes only.

Figure D-19 shows the convention of the bi-binary encoding, where a “0” is expressed by a low-to-high transition (“0” during the first half of the bit period and “1” during the second half) and where a “1” is expressed by a high-to-low transition (“1” during the first half of the bit period and “0” during the second half).

6.4.5 Message timing. The users’ convolutional decoders will introduce a fixed delay that depends on their respective algorithms (usually 5 constraint lengths, or 35 bits), for which they must compensate to determine SBAS 637CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 network time (SNT) from the received signal.

6.4.6 SBAS signal characteristics. Differences between the relative phase and group delay characteristics of SBAS signals, as compared to GPS signals, can create a relative range bias error in the receiver tracking algorithms.

The SBAS service provider is expected to account for this error, as it affects receivers with tracking characteristics within the tracking constraints in Attachment D, 8.11 and Appendix B, 3.5.15.1.1.3. For GEOs supporting L1 SBAS ranging for which the on-board RF filter characteristics have been published in RTCA/DO-229D with Change 1, Appendix T, the SBAS service providers are expected to ensure that the UDREs bound the residual errors including the maximum range bias errors specified in RTCA/DO-229D with Change 1. For other SBAS satellites supporting L1 SBAS ranging or DFMC SBAS ranging, the SBAS service providers are expected to work with equipment manufacturers in order to determine, through analysis, the maximum range bias errors that can be expected from existing receivers when they process these specific satellites. This effect can be minimized by ensuring that the satellites have a wide transmission bandwidth and small group delay across the pass band. Additionally, the DFMC SBAS tracking error in Appendix B,

3.5.15.4.1 is developed with the presumption that the SBAS L1 signal supporting DFMC SBAS ranging is a wideband signal. SBAS service providers are expected to ensure that the DFREs bound the residual errors including tracking bias errors for the DFMC SBAS ranging signals.

6.4.7 SBAS pseudo-random noise (PRN) codes. Receivers compliant with RTCA DO-229D with Change 1 and earlier versions only search for PRN codes in the range 120 to 138 only (out of the full 120 to 158 range in Table B-21), and therefore will not acquire and track SBAS L1 signals identified by a PRN code in the range 139 to 158. Receivers compliant with DO- 229E and subsequent versions can acquire and track SBAS L1 signals identified by all PRN codes in Table B-21. EUROCAE/ED-259, Appendix A, provides a method for SBAS L5 PRN code generation.

6.4.8 SBAS L5 carrier phase noise. A practical way to comply with the SBAS L5 code carrier noise requirement would be to comply with the following table

specification:

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6.4.9 Cross-correlation loss. Cross-correlation loss is defined as the ratio of the

following two correlation outputs: (1) the actual received signal correlated against a perfect unfiltered reference signal; and (2) a perfect unfiltered signal normalized to the same total power as the signal in case (1), correlated against a perfect unfiltered reference signal. The correlation

loss can be calculated as indicated in the equation below: where “CXX” is the value resulting from correlation of the unfiltered reference signal with itself, “CYY” is the value resulting from correlation of the actual received signal with itself, and “CXY” is the value resulting from correlation of the actual received signal with the unfiltered reference signal when these two signals are optimally aligned for maximal cross correlation.

The bracketed term above is the correlation coefficient between the actual received signal and the unfiltered reference signal.

6.5 Data characteristics on SBAS L1 signal

6.5.1 SBAS messages. Due to the limited bandwidth, SBAS L1 signal data is encoded in messages that are designed to minimize the required data throughput. RTCA/DO-229D with Change 1, Appendix A, provides detailed specifications for SBAS messages.

6.5.2 Data broadcast intervals. The maximum broadcast intervals between L1 SBAS messages are specified in Appendix B, Table B-92. These intervals are such that a user entering the L1 SBAS service broadcast area is able to output a corrected position along with SBAS-provided integrity information in a reasonable time. For en-route, terminal and NPA operations, all needed data will be received within 2 minutes, whereas for 639CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 precision approach operations, it will take a maximum of 5 minutes. The maximum intervals between broadcasts do not warrant a particular level of accuracy performance as defined in Chapter 3, Table 3.7.2.4-1. In order to ensure a given accuracy performance, each service provider will adopt a set of broadcast intervals taking into account different parameters such as the type of constellations (e.g. GPS with SA, GPS without SA) or the ionospheric activity.

6.5.3 Time-to-alert. Figure D-2 provides explanatory material for the allocation of the total time-to-alert defined in Chapter 3, Table 3.7.2.4-1. The time-to- alert requirements in Appendix B, 3.5.7.3.1, 3.5.7.4.1 and 3.5.7.5.1 (corresponding to the GNSS satellite status, basic differential correction and precise differential correction functions, respectively) include both the ground and space allocations shown in Figure D-2.

6.5.4 Tropospheric function. Because tropospheric refraction is a local phenomenon, users will compute their own tropospheric delay corrections.

A tropospheric delay estimate for precision approach is described in RTCA/DO-229D with Change 1, although other models can be used.

6.5.5 Multipath considerations. Multipath is one of the largest contributors to positioning errors for L1 SBAS affecting both ground and airborne elements. For SBAS ground elements, emphasis should be placed on reducing or mitigating the effects of multipath as much as possible so that the signal-in-space uncertainties will be small. Many mitigation techniques have been studied from both theoretical and experimental perspectives.

The best approach for implementing SBAS reference stations with minimal

multipath errors is to: a) ensure that an antenna with multipath reduction features is chosen; b) consider the use of ground plane techniques; c) ensure that the antenna is placed in a location with low multipath effects; and d) use multipath-reducing receiver hardware and processing techniques.

6.5.6 GLONASS issue of data. Since the existing GLONASS design does not provide a uniquely defined identifier for sets of ephemeris and clock data, L1 SBAS will use a specific mechanism to avoid any ambiguity in the application of the broadcast corrections. This mechanism is explained in Figure D-3. The definitions of the latency time and validity interval along with the associated coding requirements can be found in Appendix B,

3.5.4. The user can apply the long-term corrections received only if the set of GLONASS ephemeris and clock data used on board have been received within the validity interval.

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6.5.7 δUDRE indicator inside the service area. Equipment built to RTCA/DO- 229 standards will apply δUDRE = 1 until receipt of the complete Type 27 service area messages. Since the δUDRE indicator inside the service area is set to 0 as required in Appendix B, 3.5.7.6.2.1, SBAS user equipment operating inside the service area will generate the correct integrity bound in the transient phase, using a δUDRE = 1, before reception of the complete set of Type 27 messages.

6.5.8 Day crossover considerations. The parameters t0,GEO, talmanac and ti,LT are expressed in seconds of day. Equipment standard assumes that those parameters are adjusted by SBAS for day crossover. SBAS needs to set those parameters to mitigate misinterpretation by SBAS equipment.

6.6 SBAS final approach segment (FAS) data block

6.6.1 The SBAS final approach segment (FAS) data block for a particular approach procedure is as shown in Appendix B, 3.5.8.4.2.6.1 and Table B-96, with additional description of fields used by DFMC SBAS user equipment in Appendix B, 3.5.15.3.5. The format is the same as the GBAS FAS data block defined in Appendix B, 3.6.4.5.1 and Table B-134, with the following exceptions. The SBAS FAS data block also contains the HAL and VAL to be used for the approach procedure as described in 6.3.4.

SBAS user equipment interprets certain fields differently from GBAS user equipment and DFMC SBAS user equipment uses two fields not used by L1 SBAS user equipment. The new fields have been defined such that existing FAS data blocks designed for the L1 SBAS service are compatible for use with DFMC SBAS user equipment. FAS data blocks that have APD codings other than 0 are only for use by and should only be installed on aircraft with DFMC SBAS user equipment.

6.6.2 FAS data blocks for SBAS and some GBAS approaches are held within a common on-board database supporting both SBAS and GBAS. Within this database, channel assignments must be unique for each approach and coordinated with civil authorities. States are responsible for providing the FAS data for incorporation into the database.

6.6.3 An example of the coding of FAS data block for SBAS is provided in Table D-4. This example illustrates the coding of the various application parameters, including the cyclic redundancy check (CRC). The engineering values for the message parameters in the table illustrate the message coding process.

6.6.4 DFMC SBAS user equipment uses the operation type field from the FAS data block to determine the required SBAS service provider identifier

(SPID) for the approach. The DFMC SBAS service broadcasts a 5-bit SPID while the FAS data block only supports a 4-bit SPID. To differentiate the additional 16 SPID values, the DFMC SBAS user equipment looks for the operation type field. User equipment that receives an operation type of 0 or does not read the operation type field will interpret the SPID as 641CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 published with values between 0 and 15. User equipment that receives an operation type of 8 will add 16 to the value of the SPID from the FAS data block, resulting in a range from 16 to 31. This expanded range can only be broadcast on the DFMC SBAS service and is intended for use by SBAS systems that only provide a DFMC SBAS service.

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6.6.5 DFMC SBAS user equipment uses the approach performance designator

(APD) field to identify which of the SBAS services provide adequate performance to support the procedure identified in the FAS data block. The service modes are the L1 SBAS service, the DFMC SBAS when one or more augmented constellations are usable, and the DFMC SBAS service when two or more augmented constellations are usable. Constellations are usable when the SBAS provides augmentation and the user equipment can use the augmentation. For procedures using APV performance level, the user equipment can check the computed protection level(s) against the associated alert limit(s) to determine suitability of the navigation. For procedures using the Category 1 performance level, the integrity referred to in Chapter 3, Table 3.7.2.4.-1, Note 2 requires a system-specific safety analysis when the VAL is set to be greater than 10 m. This includes a performance assessment that the SBAS service provider makes, which the ANSP can use to support the decision on the APD coding for published procedures. Since the DFMC SBAS service will have a significantly larger service volume than the L1 SBAS service, ANSPs will be able to publish approach procedures based on DFMC SBAS services that an associated L1 SBAS service cannot fully support. In some circumstances,the L1 SBAS service might not meet the availability or continuity for the approach but would otherwise meet the performance requirements and could be used, if available. ANSPs can then publish the procedure with APD codings of 5 or 6 based on the L1 SBAS service performance provided by the SBAS service provider. In some circumstances, when the L1 SBAS service does not meet the criteria in 3.3.9 or when the ANSP determines that the L1 SBAS service is not suitable for use, ANSPs can then publish procedures with APD codings of 1 or 2. The table below provides an indication of when the different APD codings are appropriate. ANSPs code 644CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 DFMC SBAS procedure with an APD of 1 or 2 when there is no L1 SBAS service deemed to be available in support of flying the published approach.

6.6.6 User equipment not designed to process DFMC SBAS (e.g. compliant with RTCA/DO-229 standards) is not required to use the APD field (see

Chapter 3, Appendix B, 3.5.8.4.2.6.1) whereas DFMC SBAS equipment uses this field. SBAS procedures developed for L1 SBAS service use an APD coded as 0. The 0 coding is therefore retained for procedures supported by both L1 SBAS and DFMC SBAS. SBAS user equipment not designed to process DFMC SBAS (e.g. compliant with RTCA/DO-229 standards) should only be used in combination with FAS data blocks with APD set to 0.

6.7 DFMC SBAS considerations

6.7.1 Data broadcast intervals. The maximum broadcast intervals between DFMC SBAS messages are specified in Appendix B, Table B-119. These intervals are such that a user entering the DMFC SBAS coverage area is 645CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 able to output a corrected position along with SBAS-provided integrity information in a reasonable time. For en-route, terminal, NPA and precision approach operations, all needed data will be received within 3 minutes considering a maximum of 92 satellites set in the DFMC SBAS mask. The maximum intervals between broadcasts do not warrant a particular level of accuracy performance as defined in Chapter 3, Table

3.7.2.4-1. In order to ensure a given accuracy performance, each service provider will adopt a set of broadcast intervals taking into account different parameters such as the number of constellations augmented and the number of SBAS satellites used by the service provider.

6.7.2 DFMC SBAS mask

6.7.2.1 SBAS mask parameters. Appendix B, Table B-99, provides the mapping between the DFMC SBAS satellite mask and GNSS satellites. It was decided to define specific satellites per constellation that could be augmented in DFMC SBAS. It concerns the GPS PRN numbers 1 to 32 and 120 to 158 (SBAS PRN), GLONASS ID number 1 to 37, Galileo SVID 1 to 36 and BDS ranging code number 1 to 37. If any constellation broadcasts a signal from a satellite identified with a parameter exceeding the ranges specified, this satellite is not eligible for DFMC SBAS augmentation. DFMC SBAS mask broadcast in Type 31 message is independent from the L1 SBAS mask broadcast in Type 1 message even if both services are delivered by an SBAS provider.

6.7.2.2 SBAS mask transition. The Standard does not specify the means to conduct a mask transition, therefore SBAS providers might choose different mask transition strategies. The user requires a valid mask to decode the integrity messages sent every six seconds in the Type 34, 35 or 36 messages. The user needs to receive a valid integrity message at least every 12 seconds in order to continue vertical operations, since the integrity parameters time out after 12 seconds. The satellite mask message (Type 31) is valid for 360 seconds. Therefore, one method for mask transitions would be to start the transition with the broadcast of a new Type 31 message while continuing to reference the old Type 31 in the integrity messages. After the second (or third) transmission of the new Type 31, the SBAS would transition the integrity messages to use the new satellite mask message. Users should be able to receive the new satellite mask with two or three transmissions and, in the meantime, would continue to operate normally. Other satellite mask transition options could be used

such as: broadcast two integrity messages per cycle, one using the old satellite mask and one using the new satellite mask. SBAS providers need to assess the impact on continuity of service associated with the selected mechanism for SBAS mask transition when the user misses some messages.

6.7.3 DFMC SBAS almanac and ephemeris generation. The DFMC SBAS ephemeris and almanac messages were designed to provide a set of Keplerian parameters. This design enables using SBAS satellites whose 646CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 orbits are not geostationary ones. The DFMC SBAS ephemeris and almanac messages enable the broadcast of satellites in MEO, HEO, IGSO and GEO orbital position. For some special case orbits, like low-inclination

(geostationary) orbits or circular, zero eccentricity orbits, some of the Keplerian parameters are not well defined and therefore are not unique.

Valid sets of Keplerian parameters exist and the user will be able to properly determine the satellite position provided the SBAS creates a valid set of parameters. SBAS providers can set the problematic parameters to constant values and the resulting ephemeris or almanac fit will converge to a good solution. The SBAS calculation removed the rate of right ascension of ascending node (RAAN) since the validity time of the ephemeris is short. Proper selection of the harmonic correction to argument of latitude can correct the error introduced by the removal of rate of RAAN for the geostationary satellite case. For the case of inclined orbits, the error is still not negligible and the compensation needs to include IDOT in combination with Cus and Cuc. These correction parameters were chosen in general as they allow for (roughly) along-track (Cus, Cuc) and cross-track (IDOT) corrections. Since the elimination of rate of RAAN is addressed by other parameters, a long parameter fitting interval may degrade accuracy of SBAS satellite position.

6.7.4 Integrity considerations

6.7.4.1 General. While the SBAS corrections remove the observable error, there remains some uncertainty on the residual error. The SBAS ground segment selects DFREs to broadcast to provide protection level bounding of the user’s residual position errors after the application of SBAS corrections. The SBAS ground segment should account for the growth of the uncertainty in the nominal error that occurs when the user applies any received augmentation data that remains valid (has not timed out). The SBAS ground segment can choose and broadcast the associated degradation parameters to help maintain this bounding. This ensures that alerts will not be necessary under normal conditions over the validity period of the corrections and the DFREs. As the uncertainty increases, the SBAS can increase the DFREs to maintain adequate bounding. Provided that the degradation parameters add sufficient bounding to meet the integrity requirements of Appendix B, 3.5.14.3, an increase in the current DFREs to cover nominal behaviour will not require an alert to protect users still applying older active values. As specified in Appendix B, 3.5.14.4.2, the SBAS system is required to monitor for satellite ranging faults and applicability of active SBAS data. During this monitoring, the SBAS is required to maintain integrity. For some monitored behaviours, like a clock run-off, if the errors are consistent with the SBAS system design and integrity analysis and the errors continue to be bounded by the active previously broadcast DFREs in combination with the degradation parameters, the SBAS should not broadcast an alert in order to maintain continuity. If the SBAS determines that old but active data with the degradations applied will not meet the integrity requirement, then the SBAS will broadcast an alert for that satellite. The alert could be in the form 647CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 of larger DFREIs, up to and including the value indicating “Do Not Use in SBAS Mode”. For other monitored cases, like detection of abnormal signal quality, the SBAS may be better served to broadcast an alert for the satellite directly to “Do Not Use in SBAS Mode”.

6.7.4.2 Mechanism. There are several means to provide an alert. The alert sequence consists of a broadcast of at least four consecutive instances of data that will mitigate the misleading information. For individual satellites, it is often sufficient to broadcast larger DFREs to bound the error. This provides protection for all satellite data including that with longer time-out periods. Through this use of DFREs to alert, once the alerting condition has cleared, the nominal performance can be restored quickly by broadcasting nominal DFREs. The SBAS should expect that the user will miss messages and could be using any data that was previously broadcast that has not yet reached its time-out. When sending larger DFRE data to mitigate the misleading information, the SBAS sends the new DFRE in at least four consecutive messages. Since the DFRE terms are found in several different messages, it is possible to mix messages to achieve this repetition, such as four consecutive Type 32 messages or four consecutive Type 34/35/36 messages, or a combination of four consecutive Type 32 and integrity messages.

6.7.4.3 Use of Type 0 message for alerts. If necessary, to remove active data from the user receiver, SBAS can broadcast Type 0 messages. If the active data results in misleading information, the SBAS may use Type 0 message as an alert and send it in four consecutive messages. The reception of Type 0 messages will result in users dropping L5 data sent by the broadcasting satellite on the respective link. The use of Type 0 messages to alert individual satellites is generally not necessary as the use of larger DFREIs can provide for satellite alerts with less impact to the SBAS service.

6.7.4.4 Missed messages and use of Type 0 messages. Since the alert is required to be sent four times, a receiver might miss an alert if it misses four consecutive messages. For safety during approach operations, when the receiver misses four messages, it is required to invalidate all DFREIs/DFRECIs (see Appendix B, 3.5.15.1.4.15). The receiver could resume using correction data upon reception of an appropriate set of DFREIs with no other changes, as might occur with the reception of a Type 35 or Type 36 message. The SBAS should consider the possibility that the user receiver missed an alert sequence and should continue to broadcast DFREIs or DFRECIs consistent with the alerted value for all correction data that remains valid. This is also true following broadcast of a Type 0 message. If the user misses four or more messages, the user will only time out the DFREIs/DFRECIs and not remove other data. Therefore, the SBAS should consider how to resume nominal broadcast sequence following a Type 0 message alert sequence. The SBAS could continue to broadcast Type 0 messages or make impacted satellites unavailable until the misleading broadcast data has timed out. Transition from alerting through 648CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Type 0 messages to alerting through “Do Not Use for SBAS” may permit the receiver to use new SBAS data sooner.

6.7.5 Integrity data

6.7.5.1 Integrity messages. The DFMC SBAS concept defined three message types to provide integrity information with a repetition not to exceed six seconds. DFMC SBAS will broadcast integrity data for all satellites set in the satellite mask (Type31 message), and can use any combination of these messages. The integrity messages are Types 34, 35 and 36. The Type 35message provides DFREI information for the first 53 satellites in the Type 31 mask message and can be the sole message used when the SBAS augments 53 or fewer satellites. The Type 36 message is similar to the Type 35 message and is used together with the Type 35 message to broadcast DFREI information for satellites 54 to 92. Using a paired Type 35/36 message doubles the number of integrity messages being sent and might reduce the ability to send other information (e.g. correction information) more frequently compare to the minimum required. The Type 34 message is an option to provide integrity information for up to 92 satellites in a single SBAS message.

6.7.5.2 Use of the integrity message. The Type 34 message gives a means to provide integrity information for up to 92 satellites in a single message through the use of a 2-bit DFRE change indicator (DFRECI) instead of a 4-bit DFREI for each satellite. The Type 32 message provides the actual DFREI. For most operations, the DFREI will stay the same or only change by one increment during the time-out period of the DFREI. Therefore, the two-bit indicator has only four states indicating the following: 1) no change in DFREI, used to indicate that all broadcast, valid DFREIs remain valid;

2) increase the DFREI byone step (bump); 3) the Type 34 message will provide a new DFREI in one of seven slots allocated for DFREI updates in the message; or 4) indicate that the satellite is “Do Not Use for SBAS”. The user could apply the indicator to the last received DFREI that has not timed out. The SBAS system design accounts for the user missing prior broadcast DFREI and/or DFRECI values. The SBAS cannot expect the user to have the most recent DFREI and monitors all old but active data transmitted to comply with the integrity requirement in Appendix B,

3.5.14.3.1. The SBAS can provide seven DFREIs in the Type 34 message.

If the SBAS provider needs to increase more than seven DFREIs by more than one DFREI value, then the SBAS provider has two options, either set satellites that cannot be coded in the DFREI field to “Do Not Use for SBAS”, or provide DFREIs using the Type 35 or Type 36 message. The SBAS provider can broadcast a DFRECI set to 0 corresponding to an existing higher DFREI value when a lower one could be broadcast. The DFRECI bump is not cumulative and can apply to any broadcast DFREI that could still be valid. Each Type 32 satellite correction message contains a DFREI. Any DFREI sent in a Type 32 message is valid until its time-out unless a new DFREI has been sent in multiple consecutive Types 34, 35 or 36 messages. When SBAS sends a new DFREI in all integrity 649CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 messages broadcast during the DFREI validity period, SBAS can consider that the user will have the new DFREI and that the DFREI value broadcast in the previous Type 32 message has been replaced.

6.7.5.3 Use of DFMC SBAS integrity message for alerting. When an SBAS augments 53 or fewer satellites or uses the Type 34 message, the SBAS can send an alarm sequence using consecutive Type 34 or Type 35 messages and meet the alarm requirement. When an SBAS augments more than 53 satellites and chooses to use the Type 35/36 message pair, the alert logic becomes more complex. If all the satellites for which an alert needs to be sent are in the same message type, then that message type could be broadcast multiple times to meet the alert requirement. If the satellites that require an alert are contained across both the Type 35 and Type 36 messages, then it will be necessary to transition to use the Type 34 message or a Type 0 message to alert these satellites. The use of the Type 34 message is the preferred option to limit service disruption since the use of Type 0 message requires recovery of all SBAS data.

6.7.6 DFREI scale table update. The Type 37 message contains integrity related parameters which are used in the DFMC SBAS HPL and VPL equations.

In particular, the Type 37 message contains a DFREI scale table which provides the link between broadcast DFREI values and the associated dual-frequency range error sigma value to use in the protection level computation. Since the Type 37 message content is related to SBAS design, the expectation is that the Type 37 message parameters will change rarely. However, when the Type 37 message content does change, the SBAS provider will need to ensure that SBAS receivers maintain integrity during the change. The SBAS provider can achieve this through the broadcast of Type 0 message to clear SBAS receivers of the old Type 37 message data, through the inflation of broadcast DFREI values for all satellites, by alerting specific satellites that might not maintain integrity, or with no change if SBAS receivers will maintain integrity when using any valid broadcast Type 37 message data.

6.7.7 Time-to-alert. Figure D-2 also provides explanatory material in the frame of DFMC SBAS for the allocation of the total time-to-alert defined in

Chapter 3, Table 3.7.2.4-1. 6.7.8 Tropospheric function. A tropospheric delay estimate for precision approach is described in 6.5.4.

6.7.9 Multipath considerations. Multipath is the largest contributors to positioning errors for DFMC SBAS affecting both ground and airborne elements in particular due to ionosphere-free combination of SBAS corrected dual- frequency measurements. Mitigation techniques for SBAS ground elements, described in 6.5.5, are also valid in DFMC SBAS.

6.7.10 Week number rollover. The week number rollover count (WNROcount) value of 15 indicates that parameter is not valid. The DFMC SBAS receiver may use the WNROcount parameter to solve the possible ambiguity of the truncated week number value (WNx) transmitted through the GNSS 650CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 navigation data if the SBAS broadcast a WNROcount between 0 and 14.

In this case, the WNROcount is processed as follows: • If the current truncated week number (WNx) of the GNSS constellation designated by a Type 37 message is equal to the maximum value ̅𝑊̅̅̅𝑁̅ − 1 , and the current day number of week is 7 and the reference time ta corresponds to day number of week 1 in the GNSS constellation reference time, the total number of weeks

(WN) elapsed since the beginning of the GNSS reference time is

given by: • If the current truncated week number (WNx) of the GNSS constellation designated by a Type 37 message is 0, and the current day number of week is 1 and the reference time ta corresponds to day number of week 7 in the GNSS constellation reference time, the total number of weeks (WN) elapsed since the beginning of the

GNSS constellation reference time is given by:

6.7.11 Day crossovers considerations. The parameters td, ta and te are expressed in seconds of day, adjusted for day crossovers. The following mechanism can be used at the user level to determine the reference day for a td, ta or te parameter received in a message broadcast at epoch t.

Taking the case of a td parameter, with t and td expressed in seconds of

day: • If –43 200 ≤(td -t) ≤43 199, td is expressed in seconds of the message broadcast day; • If (td -t) < –43 200, td is expressed in seconds of the next day of the message broadcast day; and • If (td -t) > 43 199, td is expressed in seconds of the previous day of the message broadcast day;

The previous mechanism can be applied to ta and te, replacing td by ta or te.

6.7.12 Position computation in DFMC SBAS. Appendix B, 3.5.12.4 provides the protocol to compute SBAS position out of two augmented constellations by an SBAS. Assuming that an SBAS augments N number of constellations, N being equal to three or more, the linearized weighted 651CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 least square estimate X includes N - 2 additional elements for the time offsets between the additional constellation and the reference constellation

1. In addition, the observation matrix G, described in Appendix B, 3.5.12.4 c), is modified to integrate N - 2 additional columns of time parameters.

Those time parameters equal 1 for all satellites of this specific constellation when setting the parameter for the column number corresponding to the time offset column of this constellation in X. Those time parameters equal 0 otherwise.

6.7.12.1 Alternative observation matrix G. The DFMC SBAS navigation solution can be computed with the following observation matrix G as an alternative to the one defined in Appendix B, 3.5.12.4:

6.7.13 Dual PRNs from one SBAS satellite

6.7.13.1 Assignment of SBAS PRN codes to satellites. For vertically-guided approach operations, the system safety analysis expects user equipment to track two different satellites (as identified by PRN code), if available, to improve continuity of the operation. The broadcast of two PRNs from the same SBAS satellite introduces the SBAS satellite as a common failure between the two SBAS PRNs and might not provide the same level of continuity for these operations.

6.7.13.2 Multiple SBAS range from the same satellite. A concern with the broadcast of two ranging PRNs from the same SBAS satellite is that user equipment 652CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 will use both ranging sources as if they were independent. If there are two ranging PRNs from the same SBAS satellite, the DFMC SBAS mask can prohibit use of both ranging signals in the same position solution for the DFMC SBAS user since the DFMC SBAS user is required to use all information from a single SBAS PRN. Therefore, an SBAS should preclude use of the second SBAS ranging signal from the same satellite by ensuring that the second ranging SBAS PRN satellite slot number is not set to “1” in the satellite mask received from the first SBAS PRN signal and vice- versa.

6.7.14 Test operations. Prior to certification for aviation use, SBAS broadcasts a Type 0 Do Not Use message. Aviation equipment will process this Type 0 message by clearing SBAS data received from that SBAS satellite. During pre-operational testing when the SBAS is able to compute valid data, some SBAS providers can broadcast valid data in the Type 0 message. Non- safety of life receivers might decide to use this data to calculate SBAS position solutions. For the L1 messages, some SBAS providers populated the Type 0 message with Type 2 data content. For the L5 message, SBAS providers may populate the Type 0 message with the content of Type 34, Type 35 or Type 36 messages. To identify which of these three integrity messages content is broadcast under Type 0 message, SBAS providers can use bits 222 and 223, with the following convention:

“00” No integrity data. “01” Type 34 data content. “10” Type 35 data content. “11” Type 36 data content.

SBAS providers may choose a different coding of Type 0 messages in test operation.

6.7.15 Non-geostationary satellite consideration. There are several considerations for non-geostationary satellites. With higher satellite eccentricity, the deviations in power and Doppler shift require more consideration from the SBAS provider. Based on analysis, when the eccentricity exceeds 0.15, then the power differential from the orbit will exceed 3 dB and require some onboard power control function. The range change in the orbit will cause a constant power satellite bus to have broadcast power outside of either the maximum or minimum required power at some point during the orbit. When the eccentricity is above 0.3, the satellite Doppler shift at perigee will exceed the maximum specified Doppler shift. Some user equipment might no longer be able to track this satellite at perigee. Generally, highly eccentric orbits are used to increase satellite dwell time over a particular region during the apogee portion of the orbit. Therefore, the inability of user equipment to track the satellite around perigee might not impact the intended SBAS service. The Doppler 653CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 shift for non-GEO SBAS is set to ± 7 kHz in Appendix B, 3.5.14.1.4, in line with these analyses.

6.7.16 SNT-to-UTC conversion

6.7.16.1 Users compute the time referenced in SNT at each epoch by solving the DFMC SBAS navigation solution. The optional Type 42 message provides the parameters to convert the time referenced in SNT into time referenced in UTC.

6.7.16.2 SNT is aligned on the core constellation time identified by the SBAS time reference identifier broadcast in the Type 37 message. The core constellation broadcasts parameters to convert the core constellation time into UTC, without an associated validity period. An SBAS service provider can broadcast a Type 42 message with UTC conversion parameters corresponding to the ones broadcast by the reference core constellation, without guarantee on the validity period by setting the validity period parameter to “000”. SBAS service providers can broadcast a Type 42 message with other validity period values to provide a more accurate UTC conversion service (see Appendix B, 3.5.11.6).

6.7.16.3 Under nominal operation, the UTC conversion parameters broadcast in the Type 42 message are valid during a period of time equal to the validity period parameter. The UTC offset status parameter provides a mechanism to invalidate parameters broadcast in the previous Type 42 message and for which the validity period (VP) has not timed out. In that case, users should discard the UTC conversion parameters from the previous Type 42 message and start using the parameters contained in the latest received Type 42 message, if any provided (i.e. UTC standard identifier not set to

7).

7. GROUND-BASED AUGMENTATION SYSTEM (GBAS) AND GROUND- BASED REGIONAL AUGMENTATION SYSTEM (GRAS) Note.: In this section, except where specifically annotated, reference to approach with vertical guidance (APV) means APV-I and APV-II.

7.1 System description

7.1.1 GBAS consists of ground and aircraft elements. A GBAS ground subsystem typically includes a single active VDB transmitter and broadcast antenna, referred to as a broadcast station, and multiple reference receivers. A GBAS ground subsystem may include multiple VDB transmitters and antennas that share a single common GBAS identification (GBAS ID) and frequency as well as broadcast identical data. The GBAS ground subsystem can support all the aircraft subsystems within its service volume providing the aircraft with approach data, corrections and integrity 654CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 information for GNSS satellites in view. GBAS ground and aircraft elements are classified according to the types of service they support (as defined in 7.1.2).

7.1.2 GBAS systems may provide two types of services: approach services and the GBAS positioning service. The approach service provides deviation guidance for FASs within the approach service volume. The GBAS positioning service provides horizontal position information to support RNAV area navigation operations within the positioning service volume.

The two types of services are also distinguished by different performance requirements associated with the particular operations supported (see Table 3.7.2.4-1) including different integrity requirements as discussed in

7.5.1.

7.1.2.1 GBAS approach services are further differentiated into multiple types referred to as GBAS approach service types (GAST). A GAST is defined as the matched set of airborne and ground performance and functional requirements that are intended to be used in concert in order to provide approach guidance with quantifiable performance. Four types of approach service, GAST A, GAST B, GAST C and GAST D are currently defined.

GAST A, B and C are intended to support typical APV I, APV II and Category I operations, respectively. GAST D has been introduced to support landing and guided take-off operations in lower visibility conditions including Category III operations. Note that provisions for a separate service type to support Category II operations, but not Category I nor Category III, have not been made. Since equipment supporting GAST D will function the same when supporting Category II minima as when supporting Category III minima, GAST D provides one means of supporting Category II operations. Category II operations may potentially be supported using GAST C in conjunction with an appropriate aeroplane level integration. A relevant analogy is the authorization in at least one State of lower than Category I minima based on guidance from a facility performance Category I ILS used in conjunction with a head-up display

(HUD). Requirements for the approval of Category II operations using GBAS will be defined by the airworthiness and operational approval authorities within States.

7.1.2.1.1 A GBAS ground subsystem may support multiple service types simultaneously. There are two types of ground subsystems, those that support multiple types of approach service and those that do not.

Equipment designed in compliance with earlier versions of these SARPs may only support a single type of approach service, GAST C. Equipment designed in compliance with these SARPs may or may not support multiple types of service on one or more runway ends. The type of services supported for each approach are indicated in the approach performance designation field in a FAS data block within the Type 4 message. The GBAS continuity/integrity designator (GCID) parameter in the Type 2 message indicates whether a GBAS ground subsystem is currently supporting multiple types of approach service. Airborne equipment that 655CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 can support multiple service types will first check the GCID to determine if the ground segment supports multiple types of service. If it does, the equipment will then check the approach performance designator (APD) field of the selected FAS data block within the Type 4 message to determine which types of service are supported by the ground segment for the approach selected (using the channel selection scheme described in

7.7 below). The airborne equipment will then determine which approach service to select based on APD, the current status of GCID and the airborne equipment type. Operators should understand that the available operations may be restricted by many factors including pilot qualifications or temporary ANSP limitations which are not reflected in the APD value.

Therefore, APD should not be interpreted as an indication of the availability of any operational use, only as an indication of the service types that are supported for the given runway.

7.1.2.1.2 GBAS airborne equipment may attempt to automatically select the highest type of service supported by both the airborne equipment and the ground segment for the selected approach (as indicated in APD). If the desired type of service is not available, the airborne equipment may select the next lower available type of service and annunciate this appropriately.

Therefore, during a GBAS operation, there is the selected service type

(SST) and the active service type (AST). The SST is the service type that the airborne equipment would use if it were available, and can be no higher than the highest type of service offered by the ground segment for the selected approach. The AST is the service type that the airborne equipment is actually using at a particular time. The AST may differ from the SST if the SST is unavailable for some reason. The airborne equipment annunciates both the SST and AST so that proper action (e.g.

annunciations) may be taken in the context of the airborne integration and operational procedures.

7.1.2.1.3 Service providers should give consideration to what service type or types are actually required for each runway given the planned operations and encode the availability of the appropriate service types in the APD field of the associated FAS block.

7.1.2.1.4 When the ground subsystem is no longer capable of meeting FAST D requirements there are several options, depending upon which requirements are not met. If the ground subsystem cannot meet all of the FAST D integrity requirements (Appendix B, 3.6.7.1.2.1.1.2,

3.6.7.1.2.1.1.3, and 3.6.7.1.2.2.1.1, 3.6.7.3.2) FAST D needs to be removed within the time-toalert defined in Appendix B, 3.6.7.1.2.1.1.3. If it is still capable of meeting FAST C integrity requirements, the ground subsystem should only remove FAST D and continue to broadcast in FAST C mode. The procedure for removing FAST D includes two options for reflecting this in the corrections (Appendix B, 3.6.7.3.2.1).

7.1.2.1.4.1 When downgrading from FAST D to C, the GCID in the Type 2 message (Appendix B, 3.6.7.2.3.2) also needs to change. A FAST D ground 656CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 subsystem normally broadcasts a GCID of 2, indicating it supports FAST C and FAST D. When the ground subsystem can no longer support FAST D, but can still support FAST C, the GCID should change to 1. Note that it is assumed here that a FAST D ground subsystem would downgrade to FAST C only, and not to FAST A or B.

7.1.2.1.4.2 Another condition that could result in the ground subsystem no longer being capable of supporting FAST D would be a failure such that FAST D continuity (Appendix B, 3.6.7.1.3.1 and 3.6.7.1.3.2) cannot be met (e.g.

failure of redundant components). If FAST D integrity requirements are still met, the ground subsystem is not required to remove the corrections in the Type 11 messages. However, the GCID needs to change to 1.

Communicating the change in GCID nominally would take 10 seconds, as the minimum update rate for Type 2 messages is 10 seconds. It may take as long as one minute. A change in FAST should be reflected in the next scheduled broadcast of the Type 2 message. In addition, changes to GCID are ignored by the airborne equipment when the aircraft is in the final stages of the approach. Therefore, GCID changes only affect the FAST for aircraft outside of the final stages of the approach.

7.1.3 A significant distinguishing feature for GBAS ground subsystem configurations is whether additional ephemeris error position bound parameters are broadcast. This feature is required for the positioning service, but is optional for some approach services. If the additional ephemeris error position bound parameters are not broadcast, the ground subsystem is responsible for assuring the integrity of ranging source ephemeris data without reliance on the aircraft calculating and applying the ephemeris bound as discussed in 7.5.9.

7.1.4 GBAS configurations. There are multiple configurations possible of GBAS ground subsystems conforming to the GNSS Standards, examples of such

configurations are: a) a configuration that supports GAST C only; b) a configuration that supports GAST A, GAST B, GAST C, and also broadcasts the additional ephemeris error position bound parameters; c) a configuration that supports only GAST C and GAST D, and the GBAS positioning service, while also broadcasting the ephemeris error position bound parameters referred to in b); and d) a configuration that supports only GAST A and the GBAS positioning service, and is used within a GRAS.

7.1.4.1 GBAS facility classification (GFC). A GBAS ground subsystem is classified according to key configuration options. A GFC is composed of the following

elements:

657CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 a) facility approach service type (FAST); b) ranging source types; c) facility coverage; and d) polarization.

7.1.4.1.1 Facility approach service type (FAST). The FAST is a collection of letters from A to D indicating the service types that are supported by the ground subsystem. For example, FAST C denotes a ground subsystem that meets all the performance and functional requirements necessary to support GAST C. As another example, a FAST ACD designates a ground subsystem that meets the performance and functional requirements necessary to support service types A, C and D.

Note.: The facility classification scheme for GBAS includes an indication of which Service Types the ground subsystem can support. This means the ground subsystem meets all the performance requirements and functional requirements such that a compatible airborne user can apply the information from the ground subsystem and have quantifiable performance at the output of the processing. It does not necessarily mean that the ground subsystem supports all service types on every runway end. Which GBAS approach service types are supported on a given runway end is indicated in the Type 4 message and is included as part of the approach facility designation defined in 7.1.4.2.

7.1.4.1.2 Ranging source types: The ranging source type designation indicates what ranging sources are augmented by the ground subsystem. The coding for

this parameter is as follows:

G1 - GPS G2 - SBAS G3 - GLONASS G4 - Reserved for Galileo G5+ - Reserved for future ranging sources

7.1.4.1.3 Facility coverage: The facility coverage designation indicates positioning service capability and maximum use distance. The facility coverage is coded as 0 for ground facilities that do not provide the positioning service.

For other cases, the facility coverage indicates the radius of Dmax expressed in nautical miles.

Note.: The service volume for specific approaches is defined as part of the approach facility designations defined in 7.1.4.2.

7.1.4.1.4 Polarization: The polarization designation indicates the polarization of the 658CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 VHF data broadcast (VDB) signal. E indicates elliptical polarization and H indicates horizontal polarization.

7.1.4.1.5 GBAS facility classification examples. The facility classification for a specific facility is specified by a concatenated series of codes for the elements described in 7.1.4.1 through 7.1.4.1.4. The general form of the

facility classification is:

GFC = Facility Approach Service Type/Ranging Source Type /Facility Coverage/Polarization.

For example, a facility with the designation of GFC – C/G1/50/H, denotes a ground subsystem that meets all the performance and functional requirements necessary to support service type C on at least one approach, using GPS ranges only, with the GBAS positioning service available to a radius of 50 NM from the GBAS reference position and a VDB that broadcasts in Horizontal polarization only. Similarly, GFC – CD/G1G2G3G4/0/E denotes a ground subsystem that supports at least one approach with a service type of C and D, provides corrections for GPS, SBAS, GLONASS and Galileo satellites, does not support the positioning service and broadcasts on elliptical polarization.

7.1.4.2 Approach facility designations. A GBAS ground subsystem may support many approaches to different runway ends at the same airport or even runways at adjacent airports. It is even possible that a GBAS will support multiple approaches to the same runway end with different types of service (intended, for example, to support different operational minima). Each approach provided by the ground system may have unique characteristics and in some sense may appear to the user to be a separate facility.

Therefore, in addition to the GBAS facility classification, a system for classifying or designating the unique characteristics of each individual approach path is needed. For this purpose, a system of approach facility designations is defined. Figure D-4 illustrates the relationship between GBAS facility classifications and approach facility designations. The classification is intended to be used for pre-flight planning and published in the AIP.

7.1.4.2.1 Approach facility designation elements. Each approach supported by a GBAS can be characterized by an approach facility designation (AFD).

The AFD is composed of the following elements:

GBAS identification: Indicates the GBAS facility identifier that supports the approach (4-character GBAS ID).

Approach identifier: This is the approach identifier associated with the approach in the message Type 4 data block. It is 4 characters and must be unique for each approach within radio range of the GBAS facility.

Channel number: This is the channel number associated with the 659CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 approach selection. It is a 5 digit channel number between 20001 and 39999.

Approach service volume: Associated with each published approach, indicates the service volume either by a numerical value in feet corresponding to the minimum decision height (DH) or by the GBAS points as defined below (i.e. GBAS Points A, B, C, T, D, E, or S).

Supported service types: Designates the GBAS service types (A-D) that are supported for the approach by the ground subsystem. This field can never be given a value greater than the facility approach service type for the GBAS ground subsystem that supports the approach.

The GBAS points A, B, C, T, D and E define the same locations relative to the runway as the ILS Points in Attachment C, Figure C-1 used to define the ILS localizer course and glide path bend amplitude limits. Point S is a new point defining the stop end of the runway. For GBAS, the points are used to indicate the location along the nominal approach and/or along the runway for which GBAS performance for the supported service type(s) has been verified. When a decision height is used instead to define the approach service volume, the service volume is provided to a height of half the DH as defined in Chapter 3,

3.7.3.5.3.1. The choice of coding using a DH or GBAS points depends upon the intended operational use of the runway. For example, if the approach identifier corresponds to a Category I instrument approach procedure from which automatic landings are authorized, the approach service volume element is intended to indicate at what point along the runway the performance has been verified. The point definitions are given below:

GBAS Point “A”. A point on a GBAS final approach segment measured along the extended runway centre line in the approach direction a distance of 7.5 km (4 NM) from the threshold.

GBAS Point “B”. A point on the GBAS final approach segment measured along the extended runway centre line in the approach direction a distance of 1 050 m (3 500 ft) from the threshold.

GBAS Point “C”. A point through which the downward extended straight portion of the nominal GBAS final approach segment passes at a height of 30 m (100 ft) above the horizontal plane containing the threshold.

GBAS Point “D”. A point 3.7 m (12 ft) above the runway centre line and 900 m (3 000 ft) from the threshold in the direction of the GNSS 660CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 azimuth reference point (GARP).

GBAS Point “E”. A point 3.7 m (12 ft) above the runway centre line and 600 m (2 000 ft) from the stop end of the runway in the direction of the threshold.

GBAS Point “S”. A point 3.7 m (12 ft) above the runway centre line at the stop end of the runway.

GBAS reference datum (Point “T”). A point at a height specified by TCH located above the intersection of the runway centre line and the threshold.

7.1.4.2.2 Approach facility designation examples The approach facility designation consists of the concatenation of the parameters defined in 7.1.4.2.1 as:

GBAS ID/approach ID/ranging sources/approach service volume/required service type. An example application of this concept to a particular approach at the US Washington, DC Ronald Reagan International Airport is:

“KDCA/XDCA/21279/150/CD”

where:

KDCA − indicates the approach is supported by the GBAS installation at DCA XDCA − indicates the approach ident (echoed to the pilot on approach selection) for this specific approach is “XDCA” 21279 − is the 5-digit channel number used to select the approach 150− indicates the GBAS coverage has been verified to be sufficient to support a DH as low as 150 ft.

CD − indicates that GBAS approach service types C and D are supported by the ground subsystem for the approach Another example application of this concept to a particular approach at

Boeing Field is: “KBFI/GBFI/35789/S/C”

where:

KBFI- indicates the approach is supported by the GBAS installation at BFI (with GBAS Station identifier KBFI) GBFI − indicates the approach ident (echoed to the pilot on approach selection) for this specific approach is “GBFI” 35789 − is the 5-digit channel number used to select the approach.

S − indicates the GBAS service volume extends along the approach and the length of the runway surface (i.e. 12 ft above 661CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 the runway to the stop end).

C − indicates that GBAS approach service type C is supported by the ground subsystem for this FAS.

7.1.4.3 GBAS airborne equipment classification (GAEC)

7.1.4.3.1 GBAS airborne equipment may or may not support multiple types of approach service that could be offered by a specific ground subsystem.

The GBAS airborne equipment classifications (GAEC) specifies which subsets of potentially available services types the airborne equipment can support. The GAEC includes the following elements:

Airborne approach service type (AAST): The AAST designation is a series of letters in the range from A to D indicating which GASTs are supported by the airborne equipment. For example, AAST C denotes airborne equipment that supports only GAST C. Similarly, AAST ABCD indicates the airborne equipment can support GASTs A, B, C & D.

Note.: For airborne equipment, designating only the highest GBAS approach service type supported is insufficient as not all airborne equipment is required to support all service types. For example, a particular type of airborne equipment may be classified as AAST CD, meaning the airborne equipment supports GAST C and D (but not A or B).

Ranging source types: This field indicates which ranging sources can be used by the airborne equipment. The coding is the same as for the ground facility classification (see 7.1.4.1.2)

7.1.4.3.2 Multiple service type capable equipment. Ground and airborne equipment designed and developed in accordance with previous versions of these SARPs (Amendment 80) and RTCA DO-253A will only support GAST C.

The current version of the Standards has been designed such that legacy GBAS airborne equipment will still operate correctly when a ground subsystem supports multiple types of service. Also, airborne equipment which can support multiple types of service will operate correctly when operating with a ground subsystem that supports only GAST C.

7.1.4.3.3 GBAS airborne equipment classification examples. GBAS airborne equipment classifications consist of a concatenated series of codes for the parameters defined in 7.1.4.3. The general form of the GAEC is:

GAEC = (airborne approach service type)/(ranging source type) For

example:

GAEC of C/G1 – denotes airborne equipment that supports only GAST C and uses only GPS ranges.

Similarly:

662CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 GAEC of ABC/G1G4 - denotes airborne equipment that supports all GASTs except GAST D and can use both GPS and Galileo ranging sources.

GAEC of ABC/G1G3 – denotes airborne equipment that supports all GASTs except GAST D and can use both GPS and GLONASS ranging sources.

Finally:

GAEC – CD/G1G2G3G4 – denotes airborne equipment that supports GASTs C and D and uses GPS, SBAS, GLONASS and Galileo ranging sources.

7.1.5 GRAS configurations. From a user perspective, a GRAS ground subsystem consists of one or more GBAS ground subsystems (as described in 7.1.1 through 7.1.4), each with a unique GBAS identification, providing the positioning service and one or more approach service types where required. By using multiple GBAS broadcast stations, and by broadcasting the Type 101 message, GRAS is able to support en-route operations via the GBAS positioning service, while also supporting terminal, departure, and operations supported by GAST A or B over a larger coverage region than that typically supported by GBAS. In some GRAS applications, the corrections broadcast in the Type 101 message may be computed using data obtained from a network of reference receivers distributed in the coverage region.

7.1.6 VDB transmission path diversity. All broadcast stations of a GBAS ground subsystem broadcast identical data with the same GBAS identification on a common frequency. The airborne receiver need not and cannot distinguish between messages received from different broadcast stations of the same GBAS ground subsystem. When within coverage of two such broadcast stations, the receiver will receive and process duplicate copies of messages in different time division multiple access (TDMA) time slots.

7.1.7 Interoperability of the GBAS ground and aircraft elements compatible with RTCA/DO-253() is addressed in Appendix B, 3.6.8.1. GBAS receivers compliant with RTCA/DO-253A will not be compatible with GRAS ground subsystems broadcasting Type 101 messages. However, GRAS and GBAS receivers compliant with RTCA/DO-310 GRAS MOPS, will be compatible with GBAS ground subsystems. SARPs-compliant GBAS receivers may not be able to decode the FAS data correctly for GAST A transmitted from GBAS ground subsystems (i.e. a FAS data block with APD coded as “0”). These receivers will apply the FASLAL and FASVAL as if the active service type is GAST C. ANSPs should be cognizant of this fact and relevant operational restrictions may have to be applied to ensure the safety of the operation. For GBAS ground subsystems providing GAST D, APD in the FAS data blocks may be coded as values of 1 or 2 (Appendix B, 3.6.4.5.1). SARPs compliant GBAS receivers developed in accordance 663CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 with SARPs prior to Amendment 91 may not be able to use FAS data blocks with APD equal to 2 or above.

7.1.8 The GBAS VDB transmits with either horizontal or elliptical polarization (GBAS/H or GBAS/E). This allows service providers to tailor the broadcast to their operational requirements and user community.

7.1.9 The majority of aircraft will be equipped with a horizontally-polarized VDB receiving antenna, which can be used to receive the VDB from both GBAS/H and GBAS/E equipment. A subset of aircraft will be equipped with a vertically polarized antenna due to installation limitations or economic considerations. These aircraft are not compatible with GBAS/H equipment and are, therefore, limited to GBAS-based operations supported by GBAS/E.

7.1.10 GBAS service providers must publish the signal polarization (GBAS/H or GBAS/E), for each GBAS facility in the aeronautical information publication

(AIP). Aircraft operators that use vertically polarized receiving antenna will have to take this information into account when managing flight operations, including flight planning and contingency procedures.

7.1.11 Availability considerations for GBAS. A single GBAS ground subsystem may provide multiple types of service to multiple users and service for multiple runway ends simultaneously. These different types of service may have different availability and consequently one type of service may be available when another is not. Furthermore, as some elements of GBAS are optional (e.g. augmentation of multiple constellations or use of SBAS ranging sources), the capabilities of different users will vary. For this reason, it is not practical for the service provider to predict if a given user will find a specific service type to be available at any given time. All that can be known by the service provider is the status of the ground subsystem and satellite constellation. An assessment can be made as to whether the ground subsystem is meeting the allocated requirements for some target service type and further, the availability of service can be predicted based on an assumed level of performance and a nominal user. The definition of the nominal user includes which elements of GNSS are used (core satellite systems, SBAS ranges etc.) and within that, which subset of satellites are used in the position solution. For GBAS supporting GAST D this is further complicated by the fact that certain parameters (e.g. geometry screening thresholds) may be adjusted by the airframe designer to ensure adequate landing performance given the characteristics of the specific aircraft type.

ANSPs and air space designers should be cognizant of the fact that availability of service for GNSS augmentation systems in general is less predictable than conventional navigation aids. Variations in user capabilities will result in times where service may be available to some users and unavailable to others.

7.2 RF characteristics

7.2.1 Frequency coordination 664CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

7.2.1.1 Performance factors Note.: Guidance material on VOR and GBAS performance factors that must be considered when determining the geographical separation for the purpose of frequency coordination between a candidate GBAS station, a candidate VOR station and existing VOR or GBAS installations is given in the Handbook on Radio Frequency Spectrum Requirements for Civil Aviation (Doc 9718, Volume II), Chapters 4 (VOR) and 6 (GBAS).

7.2.1.1.2 Nominal link budgets for VDB are shown in Table D-6. The first example in Table D-6 assumes a user receiver height of 3 000 m (10 000 ft) MSL and a transmit antenna designed to suppress ground illumination in order to limit the fading losses to a maximum of 10 dB at VDB coverage edge.

In the case of GBAS/E equipment, the 10 dB also includes any effects of signal loss due to interference between the horizontal and vertical components. The second example in Table D--6 provides a link budget for longer range positioning service. It is for a user receiver height sufficient to maintain radio line-of-sight with a multi-path limiting transmitting antenna. No margin is given in Table D-6 for fading as it is assumed that the receiver is at low elevation angles of radiation and generally free from significant null for the distances shown in the table (greater than 50 NM).

In practice, installations will experience a fade margin that will be dependent on many parameters including aircraft altitude, distance from transmit antenna, antenna type/design and ground reflectors.

7.2.1.2 FM immunity Note.: Guidance material on GBAS FM immunity is given in the Handbook on Radio Frequency Spectrum Requirements for Civil Aviation (Doc 9718, Volume II), Chapter 6.

7.2.1.3 Geographic separation methodologies Note.: Guidance material on GBAS geographic separation methodologies is given in the Handbook on Radio Frequency Spectrum Requirements for Civil Aviation (Doc 9718, Volume II), Chapter 6.

7.2.2 The geographical separation criteria for GBAS/ILS and GBAS/VHF communications are given in the Handbook on Radio Frequency Spectrum Requirements for Civil Aviation (Doc 9718, Volume II), Chapters 2 and 6.

7.2.3 Compatibility with ILS.

7.2.3.1 Inter-airport compatibility. The minimum geographical separation based on a minimum frequency separation of 75 kHz between ILS localizer and GBAS ground station deployed at different airports is 3 NM between the undesired transmitter antenna location and the edges of the coverage of 665CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 the desired service that are assumed to be at minimum signal power.

Smaller necessary separation distance values may be obtained by taking into account additional information such as the actual desired service field strength and actual undesired service transmit antenna radiation patterns.

Note.: The coverage of the ILS localizer is standardized in Chapter 3, 3.1.3.3 and the GBAS service volume is standardized in Chapter 3, 3.7.3.5.3, respectively.

7.2.3.2 Same-airport compatibility.

When applying international frequency assignment planning rules, incompatibility with existing ILS or VOR at or near the same airport may lead to an unsuccessful frequency assignment for a given GBAS VDB. In such a case applying ‘same-airport compatibility’ assessment may still lead to a compatible GBAS VDB frequency. Guidance on same-airport compatibility assessment is contained in Appendix H of EUROCAE ED114B change 1.

7.2.3.3 At those locations where an ILS facility and a GBAS facility serve opposite approach directions to the same runway, there is a possibility of interference to the GBAS VDB signals in the region where the aircraft overflies the localizer. The interference can result in exceedance of the message failure rate requirement (Appendix B, 3.6.8.2.2.3) and cause a loss of continuity of GBAS guidance. The condition of unacceptable interference is when the ILS localizer signal does not support compliance with the requirements in Appendix B, 3.6.8.2.2.5 and 3.6.8.2.2.6, defining the desired to undesired signal ratios and the maximum adjacent channel power tolerable by the GBAS VDB receiver. The interference is likely to be higher when the localizer is sited close to the runway threshold. Chapter 3, 3.1.2.8 specifies the conditions under which radiation by localizers not in operational use should not be allowed. Compliance with 3.1.2.8 will ensure there is no interference by the ILS localizer to GBAS during low visibility operations that require GAST D. Generally, this should not be an issue for GAST C operations due to the 3.5 seconds window allowed to receive three Type 1 messages, when the aircraft overflies the localizer.

However, there may be conditions during GAST C operations where the VDB signal power does not support the D/U, or the maximum ILS localizer power is incompatible with recovery from short term excess undesired signal power (Appendix B, 3.6.8.2.2.6.5), and that would require the localizer to be turned off.

7.2.4 Compatibility with VHF communications.

Note.: Guidance material on GBAS compatibility with VHF communications is given in the Handbook on Radio Frequency Spectrum Requirements for Civil Aviation (Doc 9718, Volume II), Chapters 2 and 6.

666CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

7.2.5 For a GBAS ground subsystem that only transmits a horizontally-polarized signal, the requirement to achieve the power associated with the minimum sensitivity is directly satisfied through the field strength requirement. For a GBAS ground subsystem that transmits an elliptically-polarized component, the ideal phase offset between HPOL and VPOL components is 90 degrees. In order to ensure that an appropriate received power is maintained throughout the GBAS service volume during normal aircraft manoeuvres, transmitting equipment should be designed to radiate HPOL and VPOL signal components with an RF phase offset of 90 degrees. This phase offset should be consistent over time and environmental conditions.

Deviations from the nominal 90 degrees must be accounted for in the system design and link budget, so that any fading due to polarization loss does not jeopardize the minimum receiver sensitivity. System qualification and flight inspection procedures will take into account an allowable variation in phase offset consistent with maintaining the appropriate signal level throughout the GBAS service volume. One method of ensuring both horizontal and vertical field strength is to use a single VDB antenna that transmits an elliptically-polarized signal, and flight inspect the effective field strength of the vertical and horizontal signals in the service volume.

7.3 Service volume

7.3.1 The minimum GBAS service volume to support approach services is depicted in Figure D-5. Where practical, it is operationally advantageous to provide valid guidance along the visual segment of an approach. The lateral approach service volume may be different (larger) than the vertical approach service volume. When the additional ephemeris error position bound parameters are broadcast, differential corrections may only be used within the Maximum Use Distance (D ) defined in the Type 2 message.

max It is also allowable for D to extend beyond an approach service volume. max Reasons why this may be desirable include providing pilots with situational awareness and GBAS status information prior to intercepting the approach procedure, and improving GBAS course capture at the limits of the service volume. In such cases, the potential for reduced protection level, ephemeris bound, and VDB continuity outside the approach service volume should be considered especially when broadcasting large or unlimited values of D .

max

7.3.1.1 If a GBAS installation supports multiple approach service volumes, use of a single omnidirectional data broadcast covering all intended service volumes should be considered to limit complexity, if geographically feasible.

7.3.1.2 In addition, autoland or guided take-off may be used at facilities or runways not intended to support or not currently supporting Category II or III operations using GBAS. Even in Category I or better visual conditions, use of an approved autoland system with GAST C can aid pilots in achieving stabilized approaches and reliable touchdown performance, for Category 667CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 II or III training, to exercise the airborne system to ensure suitable performance, and for maintenance checks. Use of this capability may also provide pilot workload relief. Similarly, use of an approved guided take-off system will also provide operational benefits. Autoland and guided take-off service volume requirements are contained in Chapter 3, 3.7.3.5.3.2. VDB reception on the runway surface is significantly affected by the transmit antenna design and its installed height as well as the geography of the airport. Service along all runways at an airport using a single VDB antenna/transmitter location may be difficult. However, where practical, service to support autoland and guided take-off operations should be

provided at suitable runways supporting any precision approach. The approach service volume element of the approach facility designation allows this information to be contained in the AIP (refer to 7.1.4.2.1). A useful autoland capability may be achievable for some aircraft even when the requirements of Chapter 3, 3.7.3.5.3.2 are not entirely met. Similarly, some aircraft may not be able to conduct automatic landings with only the minimum service volume provided. For approaches with a FAS data path not aligned with the runway centre line, autoland service volume is not required.

7.3.2 An increased signal power (-62.5 dBm) from 36 ft and above, compared to the minimum requirement set for the GBAS service volume at 12 ft above the ground (-72 dBm), is required above the runway surface to accommodate various implementations of airborne VDB antenna. Indeed, VDB antenna height and aircraft implementation loss might not be suitable to meet adequate continuity for autoland under Category III conditions and guided take-off if:

a) aircraft VDB antenna height located above 12 ft may induce more than the expected 15 dB aircraft implementation loss; and b) aircraft VDB antenna height located below 12 ft may receive a signal power that is below the minimum required value of -72 dBm.

7.3.2.1 To mitigate a lack of adequate VDB link budget, actual aircraft implementation loss (including type of antenna and location of antenna on the fuselage, antenna gain, mismatch loss, cable loss, etc.) and actual receiver sensitivity may be balanced to achieve the expected link budget.

The need for additional operational mitigations might be identified and implemented during the aircraft approval process in case of potential loss of VDB along the flight path. It is common practice that a verification flight test is performed by a candidate operator to perform autoland under Category III conditions on a given runway.

7.3.2.2 It is not practical to measure the signal strength at 36 ft. Therefore, two

example means of verification are identified below: • Simplified analysis method: Measure the signal at 12 ft and estimate the signal strength at 36 ft using mathematical tools;

668CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 • Complex analysis method: Model the airport configuration and simulate, using a mathematical tool, the signal strength at 12 ft and 36 ft.

Note 1.: There exists an upper limit in the autoland service volume above the runway surface set at 100 ft.

Note 2.: Verification of minimum signal strength at 36 ft is sufficient to ensure compliance above 36 ft.

7.3.2.3 Simplified analysis method.

In order to apply this method, it is assumed the following: • VDB transmitter antennas are installed above a planar ground with line-of-sight to runways in the desired GBAS service volume as mentioned in 7.12.3.

• The analysis methodology consists of: • Ground subsystem manufacturers and/or service providers perform a generic (non-airport specific) analysis to show that signal strength requirements at both 12 ft and 36 ft can be met based on distance from and height of the VDB antenna at their specific location. Studies have shown that signal strength will increase from the signal strength measured at 12 ft in various airport configurations. When verifying compliance for a specific installation, an acceptable means of compliance is to measure the signal strength at 12 ft and estimate

the signal strength by using the following formula:

To estimate the power PhdBm (in dBm) at a height h (in metres) from the power𝑃ℎ0𝑑𝐵𝑚 at a height h0 (in metres), one can use the following

expression:

Where • d is the horizontal distance to the transmitter antenna in metres • ha is the height of the transmitter antenna phase centre in metres 669CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 • λ=c / f is the wavelength in metres • f is the frequency in Hertz • c is the speed of light 𝜆𝑑 The applicability of the above-mentioned formula at different heights above the runway surface may vary with the distance between the VDB transmitter antenna and the intended path on the runway surface, and the VDB transmitter antenna height. Some siting constraints may be needed to verify the minimum signal strength is met in the service volume above the runway surface.

7.3.2.4 Complex analysis method.

This method assumes that: • Airport configuration is so complex that “noise like multipath” (multipath reflections from buildings or aircraft standing or moving) cannot be easily accounted for and must be addressed in the analysis; and/or • Line-of-sight between the VDB antenna and runway cannot be maintained.

The analysis methodology consists of: • The airport configuration includes relevant surfaces such as buildings and metallic fences, and topology of the ground surface is modeled with their electromagnetic characteristics. Radiation pattern of the VDB transmitter antenna is also modeled.

• Signal powers at 12 ft and 36 ft are estimated by simulating radio propagation. One of the acceptable means of the simulation is the 670CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 ray-tracing method based on geometric optics. Such simulation is available with commercially available software with an intuitive human-machine interface to the airport modeling.

• Effects of small-scale (less than 5-10 wavelengths) structures limit the accuracy of simulation by the ray-tracing method. Therefore, an additional margin to represent such effects may need to be added to the simulation results.

• The signal power at 12 ft is measured and compared with the simulated one. If the measured and simulated signal powers at 12 ft match well, the simulation can be regarded as being able to model the signal powers at different heights over the runway.

• The simulated signal power and the minimum requirement at 36 ft are compared to verify the compliance of the VDB coverage over the runway.

7.3.3 The service volume required to support the GBAS positioning service is dependent upon the specific operations intended. The optimal service volume for this service is intended to be omnidirectional in order to support operations using the GBAS positioning service that are performed outside of the approach service volume. Each State is responsible for defining a service volume for the GBAS positioning service and ensuring that the requirements of Chapter 3, 3.7.2.4 are satisfied. When making this determination, the characteristics of the fault-free GNSS receiver should be considered, including the reversion to ABAS-based integrity in the event of loss of GBAS positioning service.

7.3.4 The limit on the use of the GBAS positioning service information is given by the Maximum Use Distance (D ). D however does not delineate max max the coverage area where field strength requirements specified in Chapter 3, 3.7.3.5.4.4 are necessarily met nor matches this area. Accordingly, operations based on the GBAS positioning service can be predicated only in the service volume(s) (where performance requirements are met) within the D range.

max

7.3.5 As the desired service volume of a GBAS positioning service may be greater than that which can be provided by a single GBAS broadcast station, a network of GBAS broadcast stations can be used to provide the service. These stations can broadcast on a single frequency and use different time slots (8 available) in neighbouring stations to avoid interference or they can broadcast on different frequencies. Figure D-5A details how the use of different time slots will allow a single frequency to be used without interference subject to guard time considerations noted under Table B-57. For a network based on different VHF frequencies, guidance material in 7.17 should be considered.

7.4 Data structure 671CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 A bit scrambler/descrambler is shown in Figure D-6.

Note.: Additional information on the data structure of the VHF data broadcast is given in RTCA/DO-246E, GNSS Based Precision Approach Local Area Augmentation System (LAAS) — Signal-in-Space Interface Control Document (ICD).

7.5 Integrity

7.5.1 Different levels of integrity are specified for precision approach operations and operations based on the GBAS positioning service. The signal-in- space integrity risk for approach services is 2 × 10-7 per approach. GBAS ground subsystems that are also intended to support other operations through the use of the GBAS positioning service have to also meet the signal in- space integrity risk requirement specified for terminal area operations, which is 1 × 10-7/hour (Chapter 3, Table 3.7.2.4-1). Therefore additional measures are necessary to support these more stringent requirements for positioning service. The signal in- space integrity risk is allocated between the ground subsystem integrity risk and the protection level integrity risk. The ground subsystem integrity risk allocation covers failures in the ground subsystem as well as core constellation and SBAS failures such as signal quality failures and ephemeris failures. For GAST A, B, and C the protection level integrity risk allocation covers rare fault- free position domain performance risks and the case of failures in one of the reference receiver measurements. In both cases the protection level equations ensure that the effects of the satellite geometry used by an aircraft fault-free receiver are taken into account. This is described in more detail in the following paragraphs. For GAST D, the position domain integrity is delegated to the aircraft and a FAST D ground subsystem provides additional data and ranging source monitoring for aircraft using this service type.

7.5.1.1 Additional integrity requirements apply for GAST D, which is intended to support precision approach and automatic landing in low visibility conditions with minima less than Category I. The same requirements for bounding the position solution within a protection level that is compared to an alert limit apply, for all error sources except single ground reference receiver faults and errors induced by ionospheric anomalies. Single ground reference receiver faults are mitigated as described in 7.5.11. The responsibility for some errors induced by anomalous ionospheric conditions has been allocated to the airborne equipment. Mitigation of errors due to ionospheric anomalies is described in 7.5.6.1.6. Additional monitoring requirements and design assurance requirements are needed to allow a FAST D GBAS ground subsystem to provide a service that can provide equivalent safety to Category III ILS operations. Some additional monitoring requirements are allocated to the ground subsystem (see

7.5.6.1 to 7.5.6.1.7) and some are allocated to the airborne equipment.

672CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 The additional monitoring performance requirements for the ground subsystem can be found in Appendix B, 3.6.7.3.3.

7.5.1.2 The ground subsystem integrity risk requirement for GAST D (Appendix B,

3.6.7.1.2.1.1.3) limits the probability of a ground subsystem failure resulting in the transmission of erroneous data during a minimum exposure time of “any one landing.” Typically the critical period of exposure to failures for vertical guidance in Category III operations is taken to be the period between the Category I Decision Height (200 ft) and the threshold (50 ft height). This is nominally 15 seconds, depending upon the aircraft approach speed. The critical period of exposure to failures for lateral guidance in Category III operations is taken to be the period between the Category I Decision Height and completion of the roll-out, which occurs when the aircraft decelerates to a safe taxi speed (typically less than 30 knots). This is nominally 30 seconds, again depending upon the aircraft approach speed and rate of deceleration. The term “any one landing” is used to emphasize that the time period where faults could occur extends prior to the critical period of exposure. The reason for this is that the fault may develop slowly over time; it could occur earlier in the landing phase and become a hazard during the critical period of exposure.

7.5.1.3 The critical period of exposure to failure for lateral guidance during a guided take-off in low visibility conditions is nominally 60 seconds.

Erroneous or loss of guidance during a guided take-off being less critical than for Category III landings, it does not introduce any changes to the ground subsystem integrity requirements.

7.5.2 The GBAS ground subsystem defines a corrected pseudo-range error uncertainty for the error relative to the GBAS reference point (σpr_gnd) and the errors resulting from vertical (σtropo) and horizontal (σiono) spatial decorrelation. These uncertainties are modelled by the variances of zero- mean, normal distributions which describe these errors for each ranging source.

7.5.3 The individual error uncertainties described above are used by the receiver to compute an error model of the navigation solution. This is done by projecting the pseudo-range error models to the position domain. General methods for determining that the model variance is adequate to guarantee the protection level integrity risk are described in section 14. The lateral protection level (LPL) provides a bound on the lateral position error with a probability derived from the integrity requirement. Similarly, the vertical protection level (VPL) provides a bound on the vertical position. For approach services, if the computed LPL exceeds the lateral alert limit (LAL) or the VPL exceeds the vertical alert limit (VAL), integrity is not adequate to support the selected service type . For the positioning service the alert limits are not defined in the standards, with only the horizontal protection level and ephemeris error position bounds required to be computed and applied. The alert limits will be determined based on the operation being conducted. The aircraft will apply the computed protection level and 673CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 ephemeris bounds by verifying they are smaller than the alert limits. Two protection levels are defined, one to address the condition when all reference receivers are fault-free (H0 – Normal Measurement Conditions), and one to address the condition when one of the reference receivers contains failed measurements (H1 – Faulted Measurement Conditions).

Additionally an ephemeris error position bound provides a bound on the position error due to failures in ranging source ephemeris. For approach services, a lateral ephemeris error bound (LEB) and a vertical ephemeris error bound (VEB) are defined. For the positioning service a horizontal ephemeris error bound (HEB) is defined.

7.5.3.1 The GBAS signal-in-space integrity risk (Appendix B, 3.6.7.1.2.1.1) is defined as the probability that the ground subsystem provides information which when processed by a fault-free receiver, using any combination of GBAS data allowed by the protocols for data application (Appendix B,

3.6.5), results in an out-of-tolerance lateral or vertical relative position error without annunciation for a period longer than the maximum time-to-alert.

An out-of-tolerance lateral or vertical relative position error is defined as an error that exceeds the GBAS approach services protection level and, if additional data block 1 is broadcast, the ephemeris error position bound.

Hence it is the responsibility of the ground subsystem to provide a consistent set of data including the differential corrections, and all parameters that are used by the protocols for data application (e.g, σ _ pr gnd and the B values as defined in the Type 1 message), so that the protection levels bound the position error with the required integrity risk. This error bounding process must be valid for any set of satellites that the user might be using. To ensure the computed protection levels actually bound the error with the required probability, it may in some cases be necessary to inflate or otherwise manipulate one or more of the parameters that are used by the protocols for data application. For example, to address the impact of anomalous ionospheric effects one strategy that has been used is to inflate σ _ and σ _ to ensure that airborne equipment pr gnd vert iono_gradient that complies with the protocols for data application will be adequately protected.

7.5.4 Ground system contribution to corrected pseudo-range error (σ _ ). pr gnd Error sources that contribute to this error include receiver noise, multipath, and errors in the calibration of the antenna phase centre. Receiver noise has a zero-mean, normally distributed error, while the multipath and antenna phase centre calibration can result in a small mean error.

7.5.5 Residual tropospheric errors. Tropospheric parameters are broadcast in Type 2 messages to model the effects of the troposphere, when the aircraft is at a different height than the GBAS reference point. This error can be well-characterized by a zero-mean, normal distribution.

7.5.5.1 Tropospheric parameters. Because tropospheric refraction is a local phenomenon, the tropospheric parameters will be determined by the GBAS provider based on local meteorological data or empirical models.

674CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Tropospheric delay is proportional to the refractivity integrated over a height interval from the GBAS ground subsystem to the airborne subsystem. The tropospheric delay consists of the dry and wet (water vapor) air components.

7.5.5.2 Tropospheric scale height. Tropospheric scale height accounts for the dependence of the tropospheric correction and residual tropospheric uncertainty on the height difference between the GBAS ground and airborne subsystems. The height variations of the refractivity of the dry and wet components are different. Because only one scale height can be broadcast in message Type 2, the broadcast scale height should account for the height variation of the total tropospheric refractivity including dry and wet components. One of the acceptable means of modeling the scale height is described below.

7.5.5.2.1 Total scale height. Using ℎ0 to estimate 𝑇𝐶 and 𝜎𝑡𝑟𝑜𝑝𝑜 as described in Appendix B, 3.6.5.3.1 and 3.6.5.3.2 is equivalent to approximating the height profile of the tropospheric refractivity by a function decaying exponentially from the refractivity at the ground surface level (ℎ𝑆). The total refractivity (𝑁𝑟) is the sum of the dry refractivity (𝑁𝑑𝑟𝑦) and wet refractivity (𝑁𝑤𝑒𝑡). The dry and wet components have different scale heights (ℎ0,𝑑𝑟𝑦, ℎ0,𝑤𝑒𝑡). As long as the height difference is much smaller than the scale heights, the total scale height can be described as follows:

7.5.5.2.2 Dry and wet scale heights. The height variations of the dry and wet components of the refractivity can be found in literature. According to one of the models (Hopfield, 1971), as long as the height difference is much smaller than the scale heights, the dry and wet scale heights can be

described as follows: where 𝑔 is the gravitational acceleration, 𝛼 the temperature lapse rate by height, and 𝑅 the gas constant for unit mass of air. ℎ𝑑 and ℎ𝑤 are respectively the empirically determined equivalent heights where the modelled dry and wet refractivities become zero. For 𝜇=4 corresponding to 𝛼=6.7 K/km, Hopfield (1971) obtained the following set of equations to

best fit radiosonde measurements:

675CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 As these expressions were obtained to best fit the observations, estimated 𝑇𝐶 would be valid even for the standard atmosphere (𝛼=6.5 K/km). For 𝛼 values other than 6.7 K/km (i.e. 𝜇 other than 4), ℎ𝑑 and ℎ𝑤 must be determined for the specific 𝛼 value. The tropospheric scale height is different for locations and seasons due to variations of the temperature, temperature lapse rate, dry and wet mixing ratio, and so on. The scale height should be determined to account for the statistics of local meteorological conditions. The error in 𝑇𝐶 associated with the scale height and the other tropospheric parameters must be bounded by a Gaussian distribution with zero mean and a standard deviation of 𝜎𝑡𝑟𝑜𝑝𝑜.

7.5.5.3 Determination of tropospheric parameters. One of the acceptable means to determine the tropospheric parameters is to use a dataset observed at a meteorological station near the GBAS reference point. The dataset should consist of at least the surface pressure, temperature and relative humidity. The meteorological station should be located within the same climatological conditions as the GBAS reference point. It is necessary to correct effects of a difference in altitude on the tropospheric parameters. If certain local and characteristic meteorological phenomena such as the sea breeze are known, they may also need to be considered in selecting the meteorological station. The period of the dataset should at least be over one year to account for the seasonal variation of the meteorological phenomena. Year-to-year and longer-term variations of the tropospheric parameters should be considered. Refractivity index (Nr) is the sum of dry refractivity (𝑁𝑑𝑟𝑦) and wet refractivity (𝑁𝑤𝑒𝑡) as described in 7.5.5.2.1.

𝑁𝑑𝑟𝑦 can be obtained from averaged values for surface pressure and temperature during the period. 𝑁𝑤𝑒𝑡 can be calculated from the surface temperature and partial pressure of the water vapor which can be derived from the surface temperature and relative humidity. The refractivity uncertainty (𝜎𝑛) can be calculated by taking the standard deviation of the Nr to overbound the dataset. This overbounding will account for the year- to-year and longer-term variations. As long as it is determined to overbound the observed dataset, periodic recomputation of the tropospheric parameters is not necessary. The scale height (h0) can be derived from the averaged surface temperature, Nr, 𝑁𝑑𝑟𝑦 and 𝑁𝑤𝑒𝑡 according to the equations in 7.5.5.2.1 and 7.5.5.2.2.

7.5.5.4 Other considerations related to the troposphere. The horizontal variation in the tropospheric delay is not considered in the tropospheric correction.

However, the tropospheric delay is not necessarily horizontally homogeneous. If a service provider determines that the horizontal gradient is not negligible, the horizontal variation in the tropospheric delay should be accounted for. One of the acceptable means is to include the 676CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 uncertainty in the tropospheric delay associated with its horizontal variation in 𝜎𝑣𝑒𝑟𝑡_𝑖𝑜𝑛𝑜_𝑔𝑟𝑎𝑑𝑖𝑒𝑛𝑡 because it is a parameter which can account for errors proportional to the distance between the GBAS reference point and the aircraft.

7.5.6 Residual ionospheric errors. An ionospheric parameter is broadcast in Type 2 messages to model the effects of the ionosphere between the GBAS reference point and the aircraft. This error can be well-characterized y a zero-mean, normal distribution during nominal conditions.

7.5.6.1 Ionospheric anomalies. Small scale structures in the ionosphere can result in non-differentially corrected errors in the GBAS position. Such phenomena are typically associated with solar storm activity and may be characterized by steep gradients in the ionospheric delay over a relatively short distance (e.g. a few tens of kilometres). The errors that may be induced by these phenomena result when the airborne receiver and ground subsystem are receiving satellite signals that have different propagation delays. Also, since GBAS uses code-carrier smoothing with a relatively long time constant, biases build up in these filters that are a function of the rate of change of ionospheric delay. If the ground subsystem and airborne receivers experience significantly different delays and rates of change of the ionospheric delays, the biases that build up in these filters will not match and will not be cancelled by the differential processing.

7.5.6.1.1 Ionospheric anomaly mitigation. Ionospheric anomalies can produce position errors which are significant (i.e. tens of metres) in the context of approach operations. To mitigate these errors, different strategies are used depending on the GBAS approach service type.

7.5.6.1.2 Ionospheric anomaly mitigation for GAST A, B and C. For GAST A, B or C, the ground subsystem is responsible for mitigating the potential impact of ionospheric anomalies. This may be handled through various monitoring schemes (e.g. far-field monitors or integration with a wide area ground network supporting SBAS) which detect the presence of ionosphere anomalies and deny service if the resulting user position errors would be unacceptable. One means to deny service is to inflate some combination

of the broadcast integrity parameters: σ _ , σ _ _gradient, the pr gnd vert iono ephemeris decorrelation parameter (P), the ephemeris missed detection parameters K _ GPS and K _ _,GLONASS such that any geometry md e, md e that could be used by an airborne user will not be subjected to intolerably large errors (given the intended operational use). This inflation scheme could also be used without the complexity of monitoring the ionosphere during operations by assuming ionosphere anomalies are present. In this case, a model of the possible ionosphere conditions that could occur is used to determine the proper values of the broadcast integrity parameters.

Since the extremes of ionosphere conditions vary significantly through the world, the model is location dependent. Such an inflation scheme results in a reduction in availability because it inflates the values even when 677CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 anomalies are not present.

7.5.6.1.3 Ionospheric anomaly mitigation for GAST D. Requirements for monitoring and geometry screening in the airborne equipment have been introduced for GAST D to mitigate the potential impact of ionospheric anomalies. The airborne monitoring consists of monitoring the code-carrier divergence continuously in order to detect large gradients in the ionosphere. In addition, the airborne equipment will screen geometries to ensure that an unacceptably large amplification of residual pseudo-range errors (i.e.

errors that may exist after airborne monitoring has been applied) will not occur. Another factor which is useful for the mitigation of errors induced by ionospheric anomalies is the use of the 30-second carrier smoothed pseudoranges in a position solution. (The shorter time constant smoothing is inherently less susceptible to filter bias mismatch errors.) Finally, GAST

D includes parameters: K _ , K _ , PD and md e_D,GLONASS md e_D,GPS σ _ _ _ , which are intended to be used in place of the vert iono gradient D parameters , and σ , respectively, Kmd_e,GLONASS, Kmd_e,GPS, P vert_iono_gradient when the active service type is GAST D. This is done so that if the ground subsystem employs inflation of the parameters K _ , md e_D,GLONASS K _ , P and σ _ _gradient to mitigate the effects of ionospheric md e_D,GPS vert iono anomalies for GAST A, B or C, the GAST D user can be provided with non- inflated parameters for use in GAST D where airborne monitoring is employed to address the ionospheric anomaly errors. This enables GAST D service to have improved availability.

7.5.6.1.4 Bounding of ionospheric anomaly errors. As stated above, ionospheric

anomalies may be addressed by inflating one or more of the parameters: σ , the ephemeris decorrelation parameter (P), the pr_gnd, σvert_iono_gradient ephemeris missed detection parameters K and K . The md_e,GPS md_e,GLONASS ground subsystem is responsible for providing values in these parameters such that the error is appropriately bounded by the VPL and HPL computations at the output of a fault free receiver. In GAST D, responsibility for mitigation of errors due to anomalous ionospheric conditions has been divided between the airborne subsystem and the ground subsystem. Although GAST D still requires the protection levels to bound the errors (as described in 7.5.3.1), they are not required to bound the errors that result from an anomalous ionospheric event as is the case for GAST C. Hence, the protection levels as computed with PD, , , and σ _ must bound the error for Kmd_e_D,GLONASS Kmd_e_D,GPS vert iono_gradient_D all error sources as discussed in 3.6.7.1.2.1.1.2 except for the errors due to anomalous ionospheric conditions. The protections level computations must bound the nominal ionospheric errors.

7.5.6.1.5 Dual solution ionospheric gradient monitoring. Another component of the airborne mitigation of errors induced by ionospheric anomalies is by the use of dual position solutions computed simultaneously with two different carrier smoothing time constants (see 7.19.3). This dual solution computation has two purposes. Firstly, taking the difference of two corrected pseudo-range measurements as detection statistics allows the 678CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 filter build-up errors on each satellite, due to large differences in ionospheric gradients between the ground measurements and airborne measurements, to be directly observable. Hence a threshold can be applied to these detection statistics in order to detect a large portion of the ionospheric anomalies. The second application of the dual solutions is to compute a bound for the 30-second smoothed position (excluding the impact of ionospheric anomalies). The data provided by the ground segment allows a protection level bound to be computed for the 100- second solution. By adding the direct observation of the magnitude of the difference between the 30-second smoothed position and the 100-second smoothed position, to the protection level computation, a protection level is obtained, which is guaranteed to bound the 30-second position solution with the required 1x10-7/approach. This allows airborne equipment, with an active service type of D to provide equivalent bounding performance, as required for approaches to Category I minima even though the 30- second solution is used to develop the guidance.

7.5.6.1.6 Requirements for FAST D ground subsystems to support mitigation of errors caused by ionospheric anomalies. Although much of the responsibility for mitigation of ionospheric errors is allocated to the airborne segment, there is a requirement for FAST D ground subsystems that is necessary to support mitigation of such effects. Appendix B,

3.6.7.3.4 specifies that the ground subsystem is responsible for ensuring mitigation of ionospheric spatial delay gradients. The ground subsystem ensures that the value of the maximum corrected pseudo-range error

(EIG) computed from the Type 2 data does not exceed 2.75 metres at all LTPs associated with runways that support GAST D procedures. One option available to the manufacturer is to restrict the distance between the GBAS reference point and the LTP. It may, in some cases, be desirable to allow GAST D service at LTPs where EIG exceeds 2.75 m. This could have an impact on the availability of the GAST D service for that particular approach. The service provider should then evaluate whether the expected performance is adequate for the intended service. See 7.5.13.1 for guidance on how availability assessment can be done.

7.5.6.1.7 Ionospheric anomaly threat models used for GAST D validation. As discussed above, the mitigation of errors that could be induced by ionospheric anomalies is accomplished through a combination of airborne and ground system monitoring. The effectiveness of the required monitoring has been demonstrated through simulation and analysis and the maximum errors at the output of the monitoring have been shown to be consistent with airworthiness certification criteria for a range of anomalies described below. This range of anomalies is described in terms of a “standard threat space” consisting of an ionospheric anomaly model which defines physical attributes of the ionospheric anomaly. The model described in 7.5.6.1.7.1 is a conservative rendition of the model developed for the continental United States. This model has been shown to bound the ionospheric threat evaluated in several other mid-latitude regions, relative to the magnetic equator. Recent data collected in some low- 679CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 latitude regions, relative to the magnetic equator, has shown ionospheric conditions associated with local ionospheric density depletion (“plasma bubbles”) that exceed this threat model. Research has resulted, for example, in a reference low latitude threat model for the Asia-Pacific Region by a dedicated Ionospheric Studies Task Force (APAC ISTF). The threat models define an ionospheric environment for which the standardized monitoring is known to produce acceptable performance on a per-pseudo-range basis. Each service provider should evaluate whether the standard threat space model described below is appropriate for the ionospheric characteristics in the region where GBAS is intended to support GAST D service. This evaluation should always be performed, regardless of the latitudes involved. If a service provider determines that the ionospheric behaviour is not adequately characterized by this threat model (e.g. for a region of uniquely severe ionospheric behaviour), that service provider must take appropriate action to ensure the users will not be subjected to ionospheric anomalies with characteristics outside the range of the standard threat space. The service provider may elect to:

1. alter the characteristics of its ground subsystem; and/or

2. introduce additional monitoring (internal or external to the GBAS); and/or

3. introduce other operational mitigations that limit users’ exposure to the extreme ionospheric conditions.

Potential ground subsystem changes which could achieve this risk reduction include tighter siting constraints (see 7.5.6.1.6) and improved ground subsystem monitoring performance (Appendix B, 3.6.7.3.4).

Another mitigation strategy is monitoring of space weather (external to the GBAS system) in conjunction with operational limitations on the use of the system during predicted periods of severely anomalous ionospheric activity. Combinations of these strategies may be used to ensure that the GAST D user is not subjected to ionospheric anomalies outside the standard threat space.

7.5.6.1.7.1 Ionosphere anomaly model: moving wedge. This models a severe ionospheric spatial gradient as a moving wedge of constant, linear change in slant ionosphere delay, as shown in Figure D-7. The key parameters of this model are the gradient slope (g) in mm/km, the width (w) of the wedge in km, the amplitude of the change in delay (D) in m, and the speed (v) at which the wedge moves relative to a fixed point on the ground. These values are assumed to remain (approximately) constant over the period in which this wedge affects the satellites tracked by a single aircraft completing a GAST D approach. While the width of the wedge is small, the “length” of the wedge in the East-North coordinate frame (i.e. how far the “ionospheric front” containing the wedge extends) is not constrained. In this model, the upper bound on g is dependent on wedge speed as specified in Table D-9. This value is not dependent on satellite elevation 680CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 angle. Because g is expressed in terms of slant delay, no “obliquity” correction from zenith delay is needed. The width w can vary from 25 to 200 km. The maximum value of D is 50 m. Note that, to make the model consistent, D must equal the product of slope g and width w. In cases where slope and width each fall within their allowed ranges, but their product D exceeds the 50-metre bound, that combination of slope and width is not a valid point within the threat model. For example, both g = 400 mm/km and w = 200 km are individually allowed, but their product equals 80 metres. Since this violates the constraint on D, a wedge with g = 400 mm/km and w = 200 km is not included in this threat model.

Note.: In the GAST D validation, it was assumed that each simulated wedge model is applied to the two ranging sources that produced the worst-case position errors. However, the numbers of wedges and impacted ranging sources depend on the ionospheric characteristics in the region where GBAS is intended to support GAST D service.

7.5.6.1.8 Ionosphere gradient mitigation validation

7.5.6.1.8.1 Because the mitigation responsibility for spatial ionosphere gradients is shared between the airborne and ground subsystems, this section includes guidance for modeling the critical airborne components (e.g.

aircraft motion and monitoring) which will enable a ground manufacturer to validate the mitigation of spatial ionosphere gradients from a total system perspective. The validation can take into account the combination of ground and airborne monitors for the detection of gradients. When accounting for the combination of monitors, the correlation or independence between the monitors needs to be considered. Monitor performance should also consider the effective time between independent samples of each monitor’s test statistic. Modeling of the ionosphere monitoring should include re admittance criteria for an excluded satellite, as appropriate per the ground subsystem design and DO-253D.

7.5.6.1.8.2 This section also includes test scenario guidance to help ensure all possible airborne position, ground reference point, approach direction, and gradient direction orientations are considered during validation.

7.5.6.1.8.3 Airborne monitor implementation

Validation may account for the following airborne monitors:

681CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 a) airborne code carrier divergence filtering as described in 2.3.6.11 of DO-253D; b) differential RAIM used for satellite addition as described in 2.3.9.6.1 of DO-253D; and c) dual solution pseudo-range ionospheric gradient monitoring as described in 2.3.9.7 of DO-253D.

7.5.6.1.8.3.1 In assessing the probability of missed detection, the contribution of all noise sources to the test statistic used for the airborne code carrier divergence monitor, excluding the effects of the ionosphere, can be assumed to have a normal distribution with a zero mean and a standard deviation of 0.002412 m/s.

7.5.6.1.8.3.2 In assessing the probability of missed detection, the contribution of all noise sources to the test statistic used for the dual solution pseudo-range ionospheric gradient monitor can be assumed to have a normal distribution with a zero mean and a standard deviation of 0.1741 m.

7.5.6.1.8.3.3 Note that the prior probability of the gradient that can be utilized during validation of 3.6.7.3.4 applies for these airborne monitors as well.

7.5.6.1.8.4 Modeling airborne positioning and speed The airborne speed and position can be modeled working backward from the threshold crossing time using

the following four values: a) speed at landing; b) amount of time at landing speed; c) deceleration rate; and d) speed at start of deceleration.

7.5.6.1.8.4.1 Figure D-8 illustrates how these four values are used to define a speed profile and Table D-10 shows the values that define the family of curves to be used in determination of GAST D broadcast parameters for a specific IGM design.

682CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Note.: Modeling aircraft altitude is not necessary.

7.5.6.1.8.4.2 Figure D-9 shows the approach speed profiles based on the values in Table D-10 in terms of ground speed versus time until the aircraft reaches the landing threshold point.

7.5.6.1.8.5 Gradient, airborne position, ground reference point, and approach direction considerations

7.5.6.1.8.5.1 Figure D-10 illustrates the basic anomalous ionospheric scenarios (A-D) that constitute a threat. For a given ground station installation, the ground manufacturer should demonstrate valid mitigation for any ionosphere gradient/airborne/approach orientations corresponding to that particular installation.

7.5.6.1.8.5.2 Validation test scenarios should also address the timing component for each orientation. For example, for a given scenario, an approach should be executed at least at one minute intervals.

7.5.7 Aircraft receiver contribution to corrected pseudo-range error. The receiver contribution is bounded as described in section 14. The maximum contribution, used for analysis by the GBAS provider, can be taken from the accuracy requirement, where it is assumed that σreceiver equals RMSpr_air for GBAS Airborne Accuracy Designator A equipment.

7.5.8 Airframe multipath error. The error contribution from airframe multipath is defined in Appendix B, 3.6.5.5.1. Multipath errors resulting from reflections from other objects are not included. If experience indicates that these errors are not negligible, they must be accounted for operationally or through inflation of the parameters broadcast by the ground (e.g. σ ).

pr_gnd

7.5.9 Ephemeris error uncertainty. Pseudo-range errors resulting from ephemeris errors (defined as a discrepancy between the true satellite position and the satellite position determined from the broadcast data) are spatially decorrelated and will therefore be different for receivers in different locations. When users are relatively close to the GBAS reference point, the residual differential error due to ephemeris errors will be small and both the corrections and uncertainty parameters σ sent by the pr_gnd ground subsystem will be valid to correct the raw measurements and 683CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 compute the protection levels. For users further away from the GBAS reference point, protection against ephemeris failures can be ensured in

two different ways: a) the ground subsystem does not transmit the additional ephemeris error position bound parameters. In this case, the ground subsystem is responsible for assuring integrity in case of satellite ephemeris failures without reliance on the aircraft calculating and applying the ephemeris bound. This may impose a restriction on the distance between the GBAS reference point and the decision altitude/height depending upon the ground subsystem means of detecting ranging source ephemeris failures. One means of detection is to use satellite integrity information broadcast by SBAS;

or b) the ground subsystem transmits the additional ephemeris error position bound parameters which enable the airborne receiver to compute an ephemeris error bound. These

parameters are: coefficients used in the ephemeris error position bound equations (Kmd_e_(), where the subscript () means either “GPS”, “GLONASS”, “POS, GPS” or “POS, GLONASS”), and the ephemeris decorrelation parameters

(P). The ephemeris decorrelation parameter (P) in the Type 1 or Type 101 message characterizes the residual error as a function of distance between the GBAS reference point and the aircraft. The value of P is expressed in m/m. The values of P are determined by the ground subsystem for each satellite. One of the main factors influencing the values of P is the ground subsystem monitor design. The quality of the ground monitor will be characterized by the smallest ephemeris error that it can detect. The relationship between the P parameter and the smallest detectable error ɛephdet for a particular satellite, i, can be approximated by Pi = ɛ ephdet /R where R is the smallest of the predicted ranges from the i i ground subsystem reference receiver antenna(s) for the period of validity of Pi. Since Ri varies with time, the P parameters values are time dependent as well. However, it is not a requirement for the ground subsystem to dynamically vary P. Static P parameters can be sent if they properly ensure integrity. In this latter case, the availability would be slightly degraded. Generally, as ɛephdet becomes smaller, overall GBAS availability improves.

7.5.10 Ephemeris error/failure monitoring. There are several types of monitoring approaches for detecting ephemeris errors/failures. They include: a) Long baseline. This requires the ground subsystem to use receivers separated by large distances to detect ephemeris errors that are not 684CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 observable by a single receiver. Longer baselines translate to better performance in smallest detectable error;

b) SBAS. Since SBAS augmentation provides monitoring of satellite performance, including ephemeris data, integrity information broadcast by SBAS can be used as an indication of ephemeris validity. SBAS uses ground subsystem receivers installed over very long baselines, therefore this provides optimum performance for ephemeris monitoring and thus makes small errors detectable;

c) Ephemeris data monitoring. This approach involves comparing the broadcast ephemeris over consecutive satellite orbits. This monitoring assumes that the only threat of failure is due to a failure in the ephemeris upload from the constellation ground control network so that the ephemeris is inconsistent with previously broadcast ephemeris; and d) Delta-V (change in velocity) monitoring. This monitoring covers the cases of uncommanded satellite manoeuvres out of view with unchanged ephemeris.

7.5.10.1 The monitor design (for example, its smallest detectable error) is to be based upon the integrity risk requirements and the failure model the monitor is intended to protect against. A bound on the GPS ephemeris failure rate can be determined from the reliability requirements defined in

Chapter 3, 3.1.7.3.1.4, since such an ephemeris error would constitute a major service failure.

7.5.10.2 The GLONASS control segment monitors the ephemeris and time parameters, and in case of any abnormal situation it starts to input the new and correct navigation message. The ephemeris and time parameter failures do not exceed 70 m of range errors. The failure rate of GLONASS satellite including the ephemeris and time parameter failures does not exceed 4 × 10-5 per satellite per hour.

7.5.11 Ground reference receiver faults. A typical GBAS ground subsystem processes measurements from 2 to 4 reference receivers installed in the immediate vicinity of the reference point. For GAST A, B, C and D, the aircraft receiver is protected against a large error or fault condition in a single reference receiver by computing a protection level based on the B parameters from the Type 1 or Type 101 message and comparing that protection level to the alert limit. Ground subsystem compliance with the GAST A, B, C and D integrity risk (Appendix B, 3.6.7.1.2.2.1) is demonstrated taking into account the protocols required of the airborne subsystem (Appendix B, 3.6.5.5.1.2) and explicit monitoring required in the airborne subsystem. Alternative system architectures with sufficiently high redundancy in reference receiver measurements may employ processing algorithms capable of identifying a large error or fault in one of the receivers. This may apply for a GRAS network with receivers distributed 685CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 over a wide area and with sufficient density of ionospheric pierce points to separate receiver errors from ionospheric effects. The integrity can then be achieved using only the protection levels for normal measurement conditions (VPLH0 and LPLH0), with appropriate values for Kffmd and σ . This can be achieved using the Type 101 message with the B pr_gnd parameters excluded.

7.5.11.1 GAST D ground reference receiver faults. For GAST D, there is an additional standardized monitor implemented in the airborne receiver used to maintain the single reference receiver faulted measurement condition integrity regardless of the satellite geometry used in the aircraft. The aircraft receiver computes a position error estimate based on the B parameters and compares that error estimate directly to a threshold set as low as possible consistent with acceptable continuity risk. Although the monitor is mechanized in the airborne subsystem, the ground subsystem must meet specific requirements for the monitor to provide the required protection. The integrity performance depends on the assumed a priori failure rate (Appendix B, 3.6.7.1.2.2.1.2) and the probability of missed detection of the monitor. The a priori rate of a single reference receiver providing faulted measurements is required to be less than 1 × 10-5 per 150 seconds. The rate per individual receiver is dependent upon the number of reference receivers in the ground subsystem. For example, with four reference receivers the rate per receiver would be required to be less than 2.5 × 10-6 per 150 seconds. This a priori rate is achieved through a combination of receiver design requirements and proper reference receiver siting and operational constraints. Because conditions during system operation vary, ground subsystems may monitor receiver outputs to verify continued compliance with the requirement. The integrity performance also depends on the probability of missed detection (P ) md performance of the monitor implemented in the airborne equipment. The P performance of this monitor in turn depends on the characteristics of md the errors that confound the observability of a reference failure. This is also true for the existing protection level integrity risk equations associated with faulted measurement conditions. The ground subsystem is required to broadcast integrity parameters that bound the errors such that a normal distribution can sufficiently characterize the errors and the P can be md estimated (Appendix B, 3.6.7.1.2.2.1.1 and 3.6.7.2.2.4.1).

7.5.11.2 GAST D ground reference receiver fault magnitude bounding. Because the airborne subsystem implements the monitor as defined in the MOPS, it is possible to compute the size of the largest error that can result from the failure of a single reference receiver with a probability of greater than 1 × 10-9. The calculated maximum size of the error will depend on the assumed a priori failure rate (Appendix B, 3.6.7.1.2.2.1.1) and the probability of missed detection of the monitor. The monitor Pmd is dependent on the monitor threshold which is computed by the airborne equipment as a function of the geometry and the error distribution associated with the H1 hypothesis.

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7.5.12 Range domain monitoring requirements for GAST D. To support equivalent safety of Category II/III operations, requirements beyond the basic “signal-in-space” requirements defined for GAST A, B and C are necessary. These requirements include performance requirements for monitors implemented to detect pseudo-range errors. Two requirements apply to the post monitoring error in the corrected pseudo-range due to specific ranging source failures (Appendix B, 3.6.7.3.3.2 and 3.6.7.3.3.3).

In both cases, the requirement applies to the probability of missed detection as a function of the size of an error due to the failure in the 30- second smoothed pseudo-range after the correction is applied.

1) The first requirement constrains the Pmd performance of the specified ranging source failures without regard for the a priori probability of the ranging source failure. The bound for a ground subsystem’s monitor performance defined in Appendix B, 3.6.7.3.3.2 is illustrated in Figure D-11. GAEC- D equipment will use the 30-second differential corrections to form the position solution used for deviation guidance. The limits of the constraint region define the minimum Pmd that the ground subsystem must ensure for any single ranging source failure condition.

Note.: The example compliant Pmd in Figure D-11 is based on a hypothetical monitor with a threshold set to 0.8 m and monitor noise of 0.123 m. The curve is for illustration purposes only and does not represent the performance of any specific monitor design.

2) The second requirement constrains the conditional probability of the P performance of the specified ranging md source given the a-priori failure probability for the specific ranging source failure. The conditional probability bound, P md × P , for a ground subsystem’s monitor performance apriori defined in Appendix B, 3.6.7.3.3.3 is illustrated in Figure D-

12. The prior probability of each ranging source failure (P ), used to evaluate compliance, should be the same apriori value that is used in the analysis to show compliance with the bounding requirements for FAST C and D (see 7.5.3.1).

7.5.12.1 Verification of ground subsystem compliance with range domain monitoring requirements Verifying that a ground system design complies with the monitor requirements provided in Appendix B, 3.6.7.3.3.2 and

3.6.7.3.3.3 is achieved by a combination of testing and analysis. The requirements take the form of a constraint on the probability of missed detection as a function of the size of an error in the corrected pseudo- range. The general process that may be used to verify that a specific monitor, included as part of a ground subsystem design, meets the

specified performance is as follows:

687CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 • Identify the threat space for each fault mode to be considered. (The requirements in Appendix B, 3.6.7.3.3 apply to four specific fault modes). These fault modes (i.e. the threat space), which may be used for evaluating compliance with a ground subsystem design, are

provided in 7.5.12.1.3.1 through 7.5.12.1.3.4. These fault modes and fault combinations constitute the threat space. These threat space definitions represent what at least one State has found acceptable as an assumed threat space for each fault mode.

• Identify the airborne configuration space. The airborne system requirements introduce constraints on the design and performance of airborne equipment. These constraints define the range of critical airborne parameters of the configuration space for each fault mode and/or monitor that must be protected by the ground subsystem. For example, the bandwidth and correlator spacing of a compliant airborne receiver will conform to the requirements in 8.11.4 through

8.11.7.1. These are two of the critical parameters of the airborne configuration space for the satellite signal deformation fault mode. A critical airborne parameter directly influences how each point in the threat space translates to an error in the differentially corrected pseudo-range.

• An error analysis is done considering the specific monitor design under consideration given the full range of fault characteristics that comprise the threat space. For each characterized fault, the error that would be induced in the corrected pseudo-range (using the 30- second smoothed pseudo-ranges and pseudo-range corrections) is computed given the full range of critical airborne parameters that comprise the airborne configuration space.

• When assessing the compliance of a ground subsystem design, the performance is characterized by relevant statistical measures. Any monitor is subject to noise and therefore the performance may be characterized by the false detection rate and the missed detection probability. Both of these performance metrics are specified in the ground requirements in Appendix B by means of a not-to-exceed constraint. The missed detection probability performance is constrained by the requirements in Appendix B, 3.6.7.3.3.2 and

3.6.7.3.3.3. The false detection rate performance is constrained by the continuity requirements given in Appendix B, 3.6.7.1.3.2. It should be understood that the ground subsystem must meet all requirements in the Standards. It is possible that the performance of individual monitors may be further constrained by other requirements, such as the ground subsystem integrity risk requirement in Appendix B, 3.6.7.1.2.1.1.1. Ground station accuracy performance may have an impact on airborne and ground monitor performance. In the validation of requirement feasibility a GAD C4 performance was assumed to account for instance for single reference receiver faults. Use of lower performance categories may 688CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 have an availability or continuity impact and should be investigated in the design process.

7.5.12.1.1 Compliance of ground subsystem monitoring with continuity requirements.

The compliance with the false detection rate (continuity) may be established based on collected real data combined with analysis and/or simulation. The required number of truly independent samples should be sufficient to adequately characterize the cumulative distribution function

(CDF) of the monitor discriminator, which is compared to the threshold set for the monitor. The fault free noise CDF must be such that for the threshold set in the monitor the false detection probability is smaller than that required to support continuity. An allocation of the continuity to each monitor must be done with consideration given to the overall specified probability of false detection (Appendix B, 3.6.7.1.3.2). The achieved probability of false detection is determined by extrapolation of the observed trends in the measured CDF. Additionally, detection events in the ground system may be logged and if, over time, the false detection rates are not maintained at the required levels, thresholds may be adjusted as the result of a maintenance action to correct the problem.

7.5.12.1.2 Compliance of ground subsystem monitoring with integrity requirements.

The compliance with the missed detection probability (integrity risk) is typically established based on simulation and analysis. (Given the low allowed probability of observing actual faults, collection of enough real data to establish that the probability is met with any statistical significance is impossible.) The threat space for the fault mode is divided into discrete intervals across the relevant parameters that define the fault behavior. The total space of potential faults is represented by a multidimensional grid of discrete points that span the threat space. The airborne configuration space is also discretized i.e. represented by a multidimensional grid of discrete (critical parameter) points. A simulation is used to compute the expected pseudo-range error performance for each point in the threat space, each possible airborne configuration and the ground receiver function with the monitors. The worst case error in the corrected pseudo- range is computed as a function of the discriminator value for the monitor addressing the threat (assuming no noise at this point). This also makes it possible to determine the discriminator value as a function of the worst- case error in the corrected pseudo-range (the inverse mapping). The missed detection probability is obtained by superimposing noise based on a conservative noise model (using an over bound of the CDF that was generated by the real data), on the discriminator determined from the worst-case differential range. This can be done either analytically or by simulation. The mapping from discriminator to worst-case error in the corrected pseudo-range and the noise levels applied may have further dependencies (for instance satellite elevation), and the established missed detection probability is therefore also a function of a set of parameters that constitute the detection parameter space which is divided into discrete intervals as well, i.e. represented by a multidimensional grid of discrete (detection parameter) points. The final missed detection probability is 689CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 obtained by searching for the worst case when evaluating all the grid points in the detection parameter space.

7.5.12.1.3 Threat space and relevant airborne configuration space for each fault mode

7.5.12.1.3.1 Code carrier divergence threat

7.5.12.1.3.1.1 The code carrier divergence threat is a fault condition in a GPS satellite that causes the code and carrier of the broadcast signal to diverge excessively.

7.5.12.1.3.1.2 A code carrier divergence fault may cause a differential ranging error in

one or both of the following cases:

(1) the aircraft and ground filter designs are not identical, and (2) the aircraft and ground filters start at different times. Both of these cases can result in a difference between the transient responses of the filters in the presence of a CCD event. The critical airborne

parameters are: — The time of initialization of the airborne smoothing filter relative to the fault onset. — The smoothing filter type (fixed time constant 30 seconds or adjustable time constant equal to time from initialization up to 30 seconds and thereafter fixed).

— The carrier code divergence rate monitoring required in airborne system for GAST D and the associated fault reaction. — The time period from initialization of the airborne smoothing filter to the incorporation of the measurement in the position solution.

7.5.12.1.3.2 Excessive acceleration threat The excessive acceleration threat is a fault condition in a GPS satellite that causes the carrier (and code in unison) of the broadcast signal to accelerate excessively. The threat space is one-dimensional and corresponds to all possible accelerations including ramps and steps.

7.5.12.1.3.3 Ephemeris error threat The ephemeris error threat is a fault condition that causes the broadcast ephemeris parameters to yield excessive satellite position errors perpendicular to the ground subsystem’s line of sight to the satellite. The resultant differential range error is the satellite position error (true compared to broadcast ephemeris) multiplied by the distance between ground subsystem and airborne and scaled by the inverted distance to the 690CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 satellite. It is bounded by the product of the P parameter (see 7.5.9) and the distance between the user and the ground subsystem. The critical airborne parameter for the ephemeris error threat is therefore the distance between the user and the ground subsystem. Satellite ephemeris faults are categorized into two types, A and B, based upon whether or not the fault is associated with a satellite manoeuvre. There are two subclasses of the type A fault, A1 and A2.

7.5.12.1.3.3.1 Ephemeris error threat type B

7.5.12.1.3.3.1.1 The type B threat occurs when the broadcast ephemeris data is anomalous, but no satellite manoeuvre is involved.

7.5.12.1.3.3.1.2 The GBAS ground subsystem can monitor against such faults by comparing current and prior ephemerides. One example of a type B fault: no manoeuvre occurs, an incorrect upload is sent to a satellite, and the satellite subsequently broadcasts an erroneous ephemeris.

7.5.12.1.3.3.2 Ephemeris error threat type A1

7.5.12.1.3.3.2.1 The type A1 threat occurs when the broadcast ephemeris data is anomalous following an announced and intentional satellite manoeuvre.

7.5.12.1.3.3.2.2 Prior ephemerides are of limited use in the detection of type A1 failures because of the intervening manoeuvre. The GBAS ground subsystem will need to monitor ranging data directly as part of ephemeris validation.

One example of a type A1 fault: a satellite is set unhealthy, a manoeuvre is executed, an incorrect upload is sent to the satellite, the satellite is reset to healthy and subsequently broadcasts an erroneous ephemeris.

7.5.12.1.3.3.3 Ephemeris error threat type A2

7.5.12.1.3.3.3.1 The type A2 threat occurs when the broadcast ephemeris data is anomalous following an unannounced or unintentional satellite manoeuvre.

7.5.12.1.3.3.3.2 Prior ephemerides are of limited use in the detection of type A2 failures because of the intervening manoeuvre. The GBAS ground subsystem will need to monitor ranging data directly as part of ephemeris validation.

One example of a type A2 fault: a satellite is set healthy, an intentional manoeuvre or unintentional thruster firing occurs, and the satellite continues to broadcast the pre-manoeuvre (now erroneous) ephemeris.

7.5.12.1.3.4 Signal deformation threat

7.5.12.1.3.4.1 The signal deformation threat is a fault condition in the GPS satellite that causes the broadcast C/A code to be distorted so that the correlation peaks used for tracking in the airborne system and the ground system are deformed. The extent of the deformation depends on the receiver 691CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 bandwidth and the resulting tracking error depends on where the correlator points used for code tracking are located (along the correlator peak).

7.5.12.1.3.4.2 The signal deformation monitoring threat space is defined in section 8.

There are three fault types A, B, C.

7.5.12.1.3.4.3 Most satellites naturally show some degree of correlator peak deformation and these are referred to as natural (correlator measurement) biases. These natural biases may vary over time.

7.5.12.1.3.4.4 A fault condition (onset) will appear as a step in the raw (unfiltered) code measurement both in the airborne system and in the ground. If both system had exactly the same front end (RF and IF filtering, sampling method), correlator type and correlator spacing the error would be the same in ground and air and no differential error would occur. But typically that is not the case.

7.5.12.1.3.4.5 The step is filtered by the smoothing algorithm in the ground and in the airborne systems and the steady state differential error will gradually manifest itself in a 60 – 90 second time frame when using corrections from message Type 11 (or 200 – 300 seconds for message Type 1).

7.5.12.1.3.4.6 If a fault (A, B or C) occurs in a satellite it will take about 60 – 90 seconds before the steady state for the error and the monitor discriminator is reached. In essence the fault onset starts a race between the increasing differential error and the monitor discriminator as it moves towards the threshold. This is referred to as the transient state. If the range error reaches the limit that must be protected while the discriminator is not yet past the threshold with sufficient margin to guarantee the required detection probability, the requirement is not met. Both the steady state and the transient state performance must be evaluated.

7.5.12.1.3.4.7 The critical airborne parameters for the signal deformation threat are: • The time period from initialization of the airborne smoothing filter to incorporation of the measurement in the position solution.

• The parameters that have constraints defined in the GAST D standard (Attachment B) including: o Correlator type Early-Late (EL) or Double Delta (DD) o Correlator spacing o GPS signal bandwidth (from reception at antenna through RF, IF, and A/D conversion) • Group delay (from reception at antenna through RF, IF, and A/D 692CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 conversion).

7.5.12.1.3.4.8 Apart from the discrete choice of EL versus DD the configuration space is two-dimensional (correlator spacing and bandwidth). The filters implemented in the airborne system may be of different types (Butterworth, Chebychev, Elliptical, etc.). The group-delay constraints will exclude some of these filters. However the possible variation in receiver design introduces additional dimensions that the ground subsystem manufacturer must consider. The filter types are part of the configuration space to be considered.

7.5.13 Ground subsystem requirements and airworthiness performance assessment. Airworthiness certification of autoland systems, for use in Category II/III operations, requires an assessment of landing performance under fault-free and faulted conditions. More information, describing how the technical standards can be used to support an assessment, may be found in RTCA document DO-253D, “Minimum Operational Performance Requirements for Airborne Equipment using the Local Area Augmentation System”, Appendix J.

7.5.13.1 Estimating availability. It may, in some cases, be necessary to estimate the expected availability for an airport or a runway end. Examples are cases where the mask angles are high or EIG exceeds 2.75 m. When the maximum value of 2.75 m is established for the EIG, this is based on availability simulations where conservative assumptions are used for the constellation and aircraft performance, and the target is to provide the GAST D service with an availability of 0.999 for Category III airports around the world. Therefore, the EIG limit of 2.75 m guarantees an availability that is higher than 0.999 under the worst-case assumptions, when only the residual ionospheric component is considered. However, for many locations, the availability may still be within this limit for EIG > 2.75 m. Also,

Chapter 3, Table 3.7.2.4-1 specifies a range of availability requirements, and the service provider must assess which availability is needed for the operation in question. In case GAST D service is provided to an LTP where EIG exceeds 2.75 m, no assumptions can be made on availability, and the service provider is then responsible for estimating the availability according to the guidance outlined below, making assumptions on airborne performance. The maximum allowable undetected airborne error in the position domain (MaxE , MaxE ) as derived from the touchdown v L airworthiness requirements, can be assumed to be 10 m or higher.

7.5.13.2 In general, availability at a given approach can be estimated by taking into account the ground station parameters transmitted under normal conditions, to compute airborne VEB/LEB and VPL/LPL and to compare against VALs/LALs for a particular approach. The result of the airborne geometry screening is a separate component of the availability. For cases where EIG exceeds 2.75 m, it is sufficient to consider the availability resulting from airborne geometry screening, which will drive availability rather than protection levels.

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7.5.13.3 At a minimum, the duration of the simulation must consider all constellation states (24 hours for GPS). When taking additional probabilistic considerations into account, e.g. scintillation probability, longer simulation durations may be required.

7.5.13.4 VPL/LPL should be compared against VAL/LAL at 200 ft (or at the threshold if that is further away from the GBAS reference point).

7.5.13.5 VEB/LEB should be compared against VAL/LAL at 23 NM or wherever the approach is intended to start.

7.5.13.6 The constellation to be used is the standard expandable (27 SV) constellation, as defined in the GPS Standard Positioning Service (SPS) Performance Standard, Fourth Edition with N-1 and N-2 state probabilities as given in Table D-11.

7.5.13.7 If the availability requirement is met under these conditions, no further analysis is required. If additional analysis is needed, a less conservative constellation can be used, e.g. a contemporary Yuma almanac. The same constellation state probabilities may be used, or, if possible, probabilities applicable to that constellation.

7.5.13.8 The ground station parameters are those transmitted by the particular ground subsystem.

7.5.13.9 The assumptions for airborne parameters are: • AAD B; • aircraft speed: 160 kts; • σdivg : 0 (assumes smoothing filter steady state); • σnoise : 0.15 (worst-case within AAD B); • MaxEv, MaxEL: 10 m;

• MaxSvert = MaxEv / ER; • MaxSLat = MaxEL / ER; • MaxSvert2 = MaxEv / max (EIG);

694CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 • MaxSLat2 = MaxEL / max (EIG); • ER is the maximum undetected pseudo-range error for the GAST D approach, either 1.6 m or EIG for the approach, whichever is larger;

and • the airborne receiver is capable of simultaneously tracking and continuously decoding the associated navigation data for at least 12 ranging sources.

7.5.14 GBAS signal-in-space time-to-alert. The GBAS signal-in-space time-to- alert (SIS TTA) is defined below within the context of GBAS based upon the TTA definition in Chapter 3, 3.7.1. The GBAS SIS TTA is the maximum allowable time elapsed from the onset of an out-of-tolerance condition at the output of the fault-free aircraft GBAS receiver until the aircraft GBAS receiver annunciates the alert. This time is a never-to-be-exceeded limit and is intended to protect the aircraft against prolonged periods of guidance outside the lateral or vertical alert limits.

7.5.14.1 There are two allocations made to support the GBAS SIS TTA in the Standards.

1) The first allocation, the ground subsystem TTA for SIS requirements, limits the time it takes the ground subsystem to provide an indication that it has detected an out-of-tolerance situation considering the output of a fault-free GBAS receiver. The indication to the aircraft

element is either: a) to broadcast Type 1 (and Type 11 if broadcast) or Type 101 messages indicating the condition (in accordance with Appendix B, 3.6.7.3.2.1), or b) terminate all VDB transmissions. The ground subsystem is allocated 3 seconds to take either action. For airborne receivers using GAST C, at least one Type 1 message signaling the out-of-tolerance condition must be received by a fault- free airborne receiver within the message time out to meet the SIS TTA. For airborne receivers using GAST D at least one of each (Type 1 and Type 11) message with the same applicable modified z-count (and the same set of satellites) must be received by a fault-free airborne receiver within the message time out to meet the SIS TTA.

Because shutting down the VDB may result in an exposure time longer than the SIS TTA for satellite faults, this option is recommended only under conditions where the VDB transmission does not meet its associated performance requirements (reference Appendix B, 3.6.7.3.1.1.).

In addition, for ground subsystems that support GAST D monitoring performance requirements, the ground subsystem is allocated only

1.5 seconds to detect a condition producing out-of-tolerance errors in 30-second corrected pseudo-ranges and to either exclude the ranging source measurements from the broadcast or mark them as 695CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 invalid. This time-to-detect and broadcast is similar in definition, but not equivalent in function to the ground subsystem TTA, as an out- of-tolerance condition in a single ranging source does not necessarily lead to out-of tolerance guidance information.

2) The second allocation for the GBAS signal-in-space time-to-alert provides for the possible temporary loss of message reception.

Airborne equipment operating with GAST C active will generate an alert if a Type 1 message is not received within 3.5 seconds when on the final stages of approach. When the airborne equipment is below 200 ft height above the runway threshold (HAT), airborne equipment operating with GAST D active will generate an alert or change the active service type if a set of Type 1 and Type 11 messages with the same modified z-count are not received within 1.5 seconds. Note that these time-outs will also dictate the achieved signal-in-space time to- alert when the ground subsystem ceases VDB transmissions instead of broadcasting messages as an alert to the airborne equipment.

Requirements on how quickly the receiver outputs must be invalidated (so annunciating an alert), as well as additional conditions requiring the outputs to be indicated as invalid, are contained in RTCA DO-253D. For example, there is a requirement for the aircraft GBAS receiver position determination function to use the most recently received message content and reflect the message content in its outputs within 400 ms. The SIS TTA is defined by start and stop events at the same point in the aircraft. Any processing that is common to generating outputs under both normal conditions and alert conditions will not change the achieved SIS TTA. That is, this common period acts like a lag to both the start event and end event and does not affect the total exposure time to the aircraft. Within the GBAS receiver, the outputs under both of these conditions must meet the same latency requirement, so large differences are not expected.

SIS TTA will differ from ground subsystem TTA by a value equal to the difference between receiver processing time and receiver time to invalidate outputs.

7.5.14.2 Table D-12 summarizes the time periods that contribute to the GBAS SIS TTA and the range of achieved TTA that can be expected.

7.5.14.3 Figure D-13 illustrates the nominal case with no missed messages and Figure D-14 illustrates the effect of missed messages for GAST D below 200 ft. Above 200 ft, the situation is similar, but the aircraft has a longer missed message allocation, as described above.

7.5.14.3.1 Figure D-14 illustrates the effect on the SIS TTA due to missed messages (upper half) and VDB termination (lower half) using the example of GAST D requirements below 200 ft. The upper time-line shows just two messages being missed, but the third is received, so operations can continue, unless the third message is indicating a fault condition that 696CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 results in an alert from the receiver. The lower time-line shows the effect of the VDB terminating. The aircraft receiver invalidates its outputs after three messages are missed. The SIS TTA combines the ground TTA and the missed message allocation (See Table D-10), but it is now displaced by the aircraft receiver processing time. Above 200 ft, the situation is similar, but the aircraft has a longer allocation, as described in RTCA DO- 253D.

7.5.14.3.2 For SIS integrity, the diagram indicates that the SIS TTA starting point is where the fault-free airborne receiver outputs out-of-tolerance data. The SIS TTA end event is also at the output of the airborne receiver.

7.5.14.3.3 The start event of the ground subsystem’s time-to-alert or time-to-detect and broadcast is the last bit of the first message (Type 1 and Type 11 message pair for GAST D) including the out-of-tolerance data. For ground equipment failures or termination of the VDB signal, this is the first message the ground subsystem broadcasts containing correction, integrity or path information that does not conform to the applicable integrity requirement (e.g. SIS integrity, ground subsystem integrity). For satellite failures, the requirements are out-of-tolerance once differential pseudo- range errors exceed the performance metrics detailed within a certain requirement (e.g. Ranging Source Monitoring). Their end event is the last bit of the first message (message pair for GAST D) removing the out-of- tolerance data or flagging it invalid.

7.5.14.3.4 It should be noted that, while the Figure D-13 indicates that the SIS and ground subsystem TTAs reference different start and end points in time, an ANSP may assume that they are the same. A ground subsystem should be evaluated and certified with no credit or penalty for airborne receiver variations due to a specific, approved aircraft implementation. From the ground subsystem perspective, all received messages are assumed to be instantaneously applied or acted upon by the airborne receiver. This effectively results in equivalent SIS and ground subsystem TTA reference points from the ground subsystem’s point of view.

7.5.15 Ground subsystem integrity risk for GAST D. Appendix B, 3.6.7.1.2.1.1.3 specifies a new ground subsystem integrity requirement relating to fail- safe design criteria. This integrity method will ensure that failures within the ground subsystem that might affect the stations functions and result in erroneous information are extremely improbable. The intent of this requirement is to specify the allowable risk that the ground subsystem would internally generate and cause erroneous information to be broadcast. Other requirements specify the required performance of the ground subsystem with respect to detection and mitigation of faults originating outside the ground subsystem (such as ranging source failures). This requirement relates to the probability that the ground subsystem fails to meet the intended function. The intended function for GBAS is defined in Chapter 3, 3.7.3.5.2. The functions listed in that section and their associated performance requirements characterize the intended 697CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 function of the system.

Note 1.: These ground subsystem TTA requirements apply to a ground subsystem transmitting Type 1 messages. Ground subsystems transmitting Type 101 messages have a 5.5 s TTA as standardized in Appendix B,

3.6.7.1.2.1.2.1.2.

Note 2.: These times apply to excluding all ranging sources, marking all ranging sources as invalid in message Type 1 or the cessation of VDB transmission. When a single ranging source is marked invalid or excluded, it may or may not cause the aircraft receiver to generate an alert, depending on the role of that ranging source in the aircraft’s position solution.

Note 3.: This design requirement applies to the integrity of internal ground subsystem functions (excluding single reference receiver failures). This includes the ground subsystem ranging source monitoring capability. The table illustrates the exposure time for ground equipment failures that result in the transmission of non-compliant information and that are enunciated to the aircraft using the VDB transmission.

Note 4.: These requirements apply to the integrity monitoring for GNSS ranging sources. When a single ranging source is marked invalid or excluded, it may or may not cause the aircraft receiver to generate an alert, depending on the role of that ranging source in the aircraft’s position solution. The times listed in the table assume the ranging source was critical to determining the position solution.

Note 5.: The missed message time-out allocation starts with the last received message and not with the first missed message, so is 0.5 s longer than time added 698CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 to the SIS time-to-alert.

Note 6.: If transmissions continue and there are no missed messages, the “nominal” column is relevant. This value includes the maximum ground subsystem contribution.

Note 7.: The maximum SIS TTA includes the maximum ground subsystem contribution and the possible temporary loss of message reception. When VDB transmissions cease, the maximum SIS TTA is relevant. This time is computed by adding the ground subsystem TTA and the airborne message time out minus 0.5 s (see Note 5).

Note 8.: Although these sections are related to FAST D and the maximum TTA values are larger than those historically associated with Category II/III operations, the TTA values in this line are not relevant for integrity to support Category II/III. These TTA values apply to the bounding conditions (see 7.5.3.1) and therefore are related to the total risk of fault-free error sources and faults exceeding the protection levels. For GAST D, the effects of malfunctions are addressed by the additional requirements in Appendix B,

3.6.7.1.2.1.1.3, Appendix B, 3.6.7.3.3 and additional airborne requirements as provided in RTCA DO-253D, for example the reference receiver fault monitor. These additional requirements are more constraining and enforce a shorter TTA that is appropriate for Category II/III operations. The existence of the longer TTA values in this line should not be interpreted to imply that errors near or exceeding the alert limit for up to these longer exposure times can occur with a probability greater than 1 x 10-9 in any landing.

Note 9.: This is “time to detect and broadcast”; the other ground system requirements apply in addition.

7.5.15.1 Verification of compliance with subsystem integrity risk for GAST D.

Verification that a ground subsystem meets the integrity risk requirements of Appendix B, 3.6.7.1.2.1.1.3 would typically be accomplished through a combination of analysis and appropriate safety-related design practices/processes. The overall process must ensure that failures within the ground subsystem that might affect the stations intended functions and result in erroneous information are extremely improbable. All ground subsystem component failure conditions must be shown to be sufficiently mitigated through either direct monitoring or through use of an acceptable design assurance development process (such as RTCA/DO-178 and RTCA/DO-254). The methodology should provide assurance of mitigation of component (HW, SW) failures. The integrity method of design assurance, applied in conjunction with fail-safe design concepts and other assurance actions (such as those in SAE ARP 4754) to detect and remove systematic errors in the design, provides safety assurance of the GAST D ground system. Some States have used safety assurance guidance from ICAO’s Safety Management Manual (SMM) (Doc 9859).

7.6 Continuity of service 699CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

7.6.1 GBAS continuity /integrity designator. The GBAS continuity/integrity designator (GCID) provides an indication of the current capability of GBAS ground subsystems. The ground subsystem meets the performance and functional requirements of GAST A, B or C when GCID is set to 1. The ground subsystem meets the performance and functional requirements of GAST A, B, C and D when GCID is set to 2. GCID of 3 and 4 are intended to support future operations with an associated service type that has requirements that are more stringent than GAST D. The GCID is intended to be an indication of ground subsystem status to be used when an aircraft selects an approach. It is not intended to replace or supplement an instantaneous integrity indication communicated in a Type 1 or Type 101 message. GCID does not provide any indication of the ground subsystem capability to support the GBAS positioning service.

7.6.2 Ground subsystem continuity of service. GBAS ground subsystems are required to meet the continuity of service specified in Appendix B to

Chapter 3, 3.6.7.1.3 in order to support GAST A, B and C. GBAS ground subsystems that are also intended to support other operations through the use of the GBAS positioning service should support the minimum continuity required for terminal area operations, which is 1–10-4/hour (Chapter 3, Table 3.7.2.4-1). When the GAST A, B or C required continuity (1–8 × 10-6/15 seconds) is converted to a per hour value it does not meet the 1–10-4/hour minimum continuity requirement. Therefore, additional measures are necessary to meet the continuity required for other operations. One method of showing compliance with this requirement is to assume that airborne implementation uses both GBAS and ABAS to provide redundancy and that ABAS provides sufficient accuracy for the intended operation.

7.6.2.1 Ground subsystem continuity of service for GAST D. A ground segment that supports GAST D must meet the SIS continuity requirement (1-8.0 × 10-6/15 seconds) for a GAST A, B and C system but must also meet the continuity requirements specific to GAST D as defined in Appendix B,

3.6.7.1.3.2. The ground subsystem continuity is defined by two requirements. One is the continuity of the ground subsystem that includes failures of all components necessary for the VDB broadcast, including the reference receivers. It also includes loss of service due to integrity failures in the ground subsystem that result in alerts and monitor false alerts. The other allocation is the continuity associated with monitor fault-free detections. The reason for defining the ranging source monitor detections as a separate requirement is because the VDB broadcast portion includes all failures that result in the loss of the SIS, whereas the monitor contribution is related only to exclusion of individual satellites from the broadcast corrections. This does not necessarily result in a loss of the SIS by the airborne receiver. The requirement is defined on a per ranging source basis so that the ground design does not need to account for the actual number of satellites in view or the number considered critical to the user for a specific approach. It is the responsibility of the airborne user to 700CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 demonstrate the overall continuity achieved when considering the contribution of the satellites and the airborne monitors.

7.7 GBAS channel selection

7.7.1 Channel numbers are used in GBAS to facilitate an interface between aircraft equipment and the signal-in-space that is consistent with interfaces for ILS and MLS. The cockpit integration and crew interface for GBAS may be based on entry of the 5-digit channel number. An interface based on approach selection through a flight management function similar to current practice with ILS is also possible. The GBAS channel number may be stored in an on-board navigation database as part of a named approach.

The approach may be selected by name and the channel number can automatically be provided to the equipment that must select the appropriate GBAS approach data from the broadcast data. Similarly, the use of the GBAS positioning service may be based on the selection of a 5-digit channel number. This facilitates conducting operations other than the approaches defined by the FAS data. To facilitate frequency tuning, the GBAS channel numbers for neighbouring GBAS ground subsystems supporting positioning service may be provided in the Type 2 message additional data block 2.

7.7.2 A channel number in the range from 20 001 to 39 999 is assigned when the FAS data are broadcast in the Type 4 message. A channel number in the range from 40 000 to 99 999 is assigned when the FAS data associated with a GAST A service type are obtained from the on-board database.

7.7.3 Every FAS data block uplinked in a Type 4 message will be associated with a single 5-digit channel number regardless of whether or not the approach is supported by multiple approach service types. For approaches that are supported by multiple approach service types, the approach performance designator field in the Type 4 message is used to indicate the most demanding approach service type supported by the ground subsystem for any specific approach.

7.8 Reference path data selector and reference station data selector A mapping scheme provides a unique assignment of a channel number to each GBAS approach. The channel number consists of five numeric characters in the range 20 001 to 39 999. The channel number enables the GBAS airborne subsystem to tune to the correct frequency and select the final approach segment (FAS) data block that defines the desired approach. The correct FAS data block is selected by the reference path data selector (RPDS), which is included as part of the FAS definition data in a Type 4 message. Table D-13 shows examples of the relationship between the channel number, frequency and RPDS. The same mapping scheme applies to selection of the positioning service through the reference station data selector (RSDS). The RSDS is broadcast in the Type 2 message and allows the selection of a unique GBAS ground 701CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 subsystem that provides the positioning service. For GBAS ground subsystems that do not provide the positioning service and broadcast the additional ephemeris data, the RSDS is coded with a value of 255. All RPDS and RSDS broadcast by a ground subsystem must be unique on the broadcast frequency within radio range of the signal. The RSDS value must not be the same as any of the broadcast RPDS values.

7.9 Assignment of RPDS and RSDS by service provider RPDS and RSDS assignments are to be controlled to avoid duplicate use of channel numbers within the protection region for the data broadcast frequency. Therefore, the GBAS service provider has to ensure that an RPDS and RSDS are assigned only once on a given frequency within radio range of a particular GBAS ground subsystem. Assignments of RPDS and RSDS are to be managed along with assignments of frequency and time slots for the VHF data broadcast.

7.10 GBAS identification The GBAS identification (ID) is used to uniquely identify a GBAS ground subsystem broadcasting on a given frequency within the VDB coverage of the GBAS. The aircraft will navigate using data broadcast from one or more GBAS broadcast stations of a single GBAS ground subsystem (as identified by a common GBAS identification).

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7.11 Final approach segment (FAS) path

7.11.1 FAS path is a line in space defined by the landing threshold point/fictitious threshold point (LTP/FTP), flight path alignment point (FPAP), threshold crossing height (TCH) and glide path angle (GPA). These parameters are determined from data provided in a FAS data block within a Type 4 message or in the on-board database. The relationship between these parameters and the FAS path is illustrated in Figure D-15.

7.11.1.1 FAS data blocks for SBAS and some GBAS approaches are held within a common onboard database supporting both SBAS and GBAS. States are responsible for providing the FAS data to support APV procedures when the Type 4 message is not broadcast. These data comprise the parameters contained within the FAS block, the RSDS, and associated broadcast frequency. The FAS block for a particular approach procedure is described in Appendix B, 3.6.4.5.1 and Table B-134.

7.11.2 FAS path definition

7.11.2.1 Lateral orientation. The LTP/FTP is typically at or near the runway threshold. However, to satisfy operational needs or physical constraints, the LTP/FTP may not be at the threshold. The FPAP is used in conjunction with the LTP/FTP to define the lateral reference plane for the approach.

For a straight-in approach aligned with the runway, the FPAP will be at or beyond the stop end of the runway. The FPAP is not placed before the stop end of the runway.

7.11.2.2 ΔLength offset. The Δlength offset defines the distance from the end of the runway to the FPAP. This parameter is provided to enable the aircraft equipment to compute the distance to the end of the runway. If the Δlength offset is not set to appropriately indicate the end of the runway relative to the FPAP, the service provider should ensure the parameter is coded as “not provided”.

7.11.2.3 Vertical orientation. Local vertical for the approach is defined as normal to the WGS-84 ellipsoid at the LTP/FTP and may differ significantly from the local gravity vector. The local level plane for the approach is defined as a plane perpendicular to the local vertical passing through the LTP/FTP (i.e.

tangent to the ellipsoid at the LTP/FTP). The datum crossing point (DCP) is a point at a height defined by TCH above the LTP/FTP. The FAS path is defined as a line with an angle (defined by the GPA) relative to the local level plane passing through the DCP. The GPIP is the point where the final approach path intercepts the local level plane. The GPIP may actually be above or below the runway surface depending on the curvature of the runway.

7.11.3 “ILS look-alike” deviation computations. For compatibility with existing aircraft designs, it is desirable for aircraft equipment to output guidance 703CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 information in the form of deviations relative to a desired flight path defined by the FAS path. The Type 4 message includes parameters that support the computation of deviations that are consistent with typical ILS installations.

7.11.3.1 Lateral deviation definition. Figure D-15 illustrates the relationship between the FPAP and the origin of the lateral angular deviations. The course width parameter and FPAP are used to define the origin and sensitivity of the lateral deviations. By adjusting the location of the FPAP and the value of the course width, the course width and sensitivity of a GBAS can be set to the desired values. They may be set to match the course width and sensitivity of an existing ILS or MLS. This may be necessary, for example, for compatibility with existing visual landing aids.

7.11.3.1.1 Lateral deviation reference. The lateral deviation reference plane is the plane that includes the LTP/FTP, FPAP and a vector normal to the WGS- 84 ellipsoid at the LTP/FTP. The rectilinear lateral deviation is the distance of the computed aircraft position from the lateral deviation reference plane.

The angular lateral deviation is a corresponding angular displacement referenced to the GNSS azimuth reference point (GARP). The GARP is defined to be beyond the FPAP along the procedure centre line by a fixed offset value of 305 m (1 000 ft).

7.11.3.1.2 Lateral displacement sensitivity. The lateral displacement sensitivity is determined by the aircraft equipment from the course width provided in the FAS data block. The service provider is responsible for setting the course width parameter to a value that results in the appropriate angle for full scale deflection (i.e. 0.155 DDM or 150 μA) taking into account any operational constraints.

7.11.3.2 Vertical deviations. Vertical deviations are computed by the aircraft equipment with respect to a GBAS elevation reference point (GERP). The GERP may be at the GPIP or laterally offset from the GPIP by a fixed GERP offset value of 150 m. Use of the offset GERP allows the glide path deviations to produce the same hyperbolic effects that are normal characteristics of ILS and MLS (below 200 ft). The decision to offset the GERP or not is made by the aircraft equipment in accordance with requirements driven by compatibility with existing aircraft systems. Service providers should be aware that users may compute vertical deviations using a GERP which is placed at either location. Sensitivity of vertical deviations is set automatically in the aircraft equipment as a function of the GPA. The specified relationship between GPA and the full scale deflection

(FSD) of the vertical deviation sensitivity is: FSD = 0.25*GPA. The value

0.25 is the same as for MLS (Attachment G, 7.4.1.2) and differs slightly from the nominal value of 0.24 recommended for ILS (Chapter 3,

3.1.5.6.2). However, the value specified is well within the tolerances recommended for ILS (0.2 to 0.28). Therefore the resulting sensitivity is equivalent to the glide path displacement sensitivity provided by a typical ILS.

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7.11.4 Approaches not aligned with the runway. Some operations may require the definition of a FAS path that is not aligned with the runway centre line as illustrated in Figure D-16. For approaches not aligned with the runway, the LTP/FTP may or may not lie on the extended runway centre line. For this type of approach Δlength offset is not meaningful and should be set to “not

provided”.

7.11.5 SBAS service provider. A common format is used for FAS data blocks to be used by both GBAS and SBAS. The SBAS service provider ID field identifies which SBAS system(s) may be used by an aircraft that is using the FAS data during an approach. The GBAS service provider may inhibit use of the FAS data in conjunction with any SBAS service. For precision approaches based on GBAS this field is not used, and it can be ignored by aircraft GBAS equipment.

7.11.6 Approach identifier. The service provider is responsible for assigning the approach identifier for each approach. The approach identification should be unique within a large geographical area. Approach identifications for multiple runways at a given aerodrome should be chosen to reduce the potential for confusion and misidentification. The approach identification should appear on the published charts that describe the approach. The first letter of the approach identifier is used in the authentication protocols for GBAS. Ground stations that support the authentication protocols must encode the first character of the identifier for all approaches supported from the set of letters {A X Z J C V P T} as described in Appendix B,

3.6.7.4.1.4. This enables airborne equipment (that supports the authentication protocols) to determine which slots are assigned to the ground station and therefore to subsequently ignore reception of data broadcast in slots not assigned to the selected ground station. For ground stations that do not support the authentication protocols, the first character of the approach identifier may be assigned any character except those in the set {A X Z J C V P T}.

7.12 Airport siting considerations

7.12.1 The installation of a GBAS ground subsystem involves special considerations in choosing prospective sites for the reference receiver antennas and the VDB antenna(s). In planning antenna siting, Annex 14 obstacle limitation requirements must be met.

7.12.2 Locating reference receiver antennas. The site should be selected in an area free of obstructions, so as to permit the reception of satellite signals at elevation angles as low as possible. In general, anything masking GNSS satellites at elevation angles higher than 5 degrees will degrade system availability.

7.12.2.1 The antennas for the reference receivers should be designed and sited to limit multipath signals that interfere with the desired signal. Mounting 705CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 antennas close to a ground plane reduces long-delay multipath resulting from reflections below the antenna. Mounting height should be sufficient to prevent the antenna being covered by snow, or being interfered with by maintenance personnel or ground traffic. The antenna should be sited so that any metal structures, such as air vents, pipes and other antennas are outside the near-field effects of the antenna.

7.12.2.2 Besides the magnitude of the multipath error at each reference receiver antenna location, the degree of correlation must also be considered.

Reference receiver antennas should be located in places that provide independent multipath environments.

7.12.2.3 The installation of each antenna should include a mounting that will not flex in winds or under ice loads. Reference receiver antennas should be located in an area where access is controlled. Traffic may contribute to error due to multipath or obstruct view of satellites from the antennas.

7.12.3 Locating the VDB transmitter antenna. The VDB transmitter antenna must be located to comply with the minimum and maximum field strength requirements within the service volume(s) as defined in Chapter 3,

3.7.3.5.4.4. Compliance with the minimum field strength for approach services can generally be met if the VDB transmitter antenna is located so that an unobstructed line-of-sight exists from the antenna to any point within the service volume for each supported FAS. Consideration should also be given to ensuring the minimum VDB transmitter antenna-to-aircraft antenna separation so that the maximum field strength is not exceeded.

For the nominal link budget, typically, an 80 m separation is required to avoid exceedance of the maximum field strength requirement. Though it is desirable to apply the separation criteria to any location where an aircraft may operate (including taxiways, ramp areas and gates), it is only necessary to meet the maximum field strength in the service volume(s) (see 3.7.3.5.3 for service volume definitions). If the minimum separation cannot be met for all operating aircraft (including taxiways, ramp areas and gates) it must be ensured that the airborne receiver is protected from burn- out in accordance with the RTCA/DO-253 D MOPS. This typically requires a minimum separation of 20 m from the VDB antenna to the aircraft antenna. In order to provide the required coverage for multiple FASs at a given airport, and in order to allow flexibility in VDB antenna siting, the actual coverage around the transmitter antenna may need to be considerably larger than that required for a single FAS. The ability to provide this coverage is dependent on the VDB antenna location with respect to the runway and the height of the VDB antenna. Generally speaking, increased antenna height may be needed to provide adequate signal strength to users at low altitudes, but may also result in unacceptable multipath nulls within the desired coverage. A suitable antenna height trade-off must be made based on analysis, to ensure the signal strength requirements are met within the entire coverage.

Consideration should also be given to the effect of terrain features and buildings on the multipath environment.

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7.12.3.1 In order to ensure that the maximum field strength requirements defined in

Chapter 3, 3.7.3.5.4.4 are not violated, VDB transmitter antennas should not be located any closer than 80 m to where aircraft are approved to operate based on published procedures using GBAS or ILS guidance information. This applies to aircraft on final approach, departure, and on runways. The 80-metre separation applies to the slant range distance between VDB transmitter antennas and the aircraft antenna position. For aircraft on the runway the maximum deviation from the centre line can be assumed to be 19 m. In regions prior to runway thresholds, the maximum lateral course angular deviation from the extended centre line on final approach is plus and minus one sixth of the full course width, which is nominally 210 m (±105 m (±350 ft)) at threshold. The origin of the lateral course should be assumed to be the GBAS GARP, or the ILS localizer, as appropriate. The maximum vertical deviation is one half of the full scale deflection from the glide path, where full scale deflection is calculated as ±0.25 times the glide path angle. The origin of the glide path should be assumed to be the GPIP. See 7.11.3 for further guidance on lateral and vertical course width deviation sensitivity.

7.12.4 Use of multiple transmit antennas to improve VDB coverage. For some GBAS installations, constraints on antenna location, local terrain or obstacles may result in ground multipath and/or signal blockage that make it difficult to provide the specified field strength at all points within the service volume. Some GBAS ground facilities may make use of one or more additional antenna systems, sited to provide signal path diversity such that collectively they meet the service volume requirements.

7.12.4.1 Whenever multiple antenna systems are used, the antenna sequence and message scheduling must be arranged to provide broadcasts at all points within the service volume that adhere to the specified minimum and maximum data broadcast rates, considering the receiver’s ability to adapt to transmission-to-transmission variations in signal strength in a given slot.

Exceedance of the signal power variation requirement in Appendix B,

3.6.8.2.2.3 is acceptable for limited areas within the service volume,

provided it can be shown based on receiver behaviour as described, for example in RTCA DO-253D and the assumptions listed below, that the resulting performance is acceptable.

7.12.4.1.2 Message transmission and reception rate requirements, and time-to-alert requirements prevent Type 1 and Type 11 messages from being alternated between antennas in the same slot from frame to frame. Only Type 2 and 4 messages (and Type 3 messages as a filler message) are candidates for being alternated. Continuity is maintained as long as a Type 2 message is received at least once per minute. The receiver does not verify repeated reception of Type 4 messages during the final stages of an approach.

7.12.4.1.3 While the signal power variation requirement in Appendix B, 3.6.8.2.2.3 707CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 applies on the input port of the receiver, the situation for a specific site has to be assessed in the field strength domain. Therefore, the potential variation in aircraft antenna gain must be taken into account. If the area where the signal power variation requirement may be exceeded is so large that it may take one minute or more for an approaching aircraft to pass through it, it may be necessary to address the potential message loss from a probabilistic point of view. In these cases the multiple VDB antenna set- up should be limited so that in case alternation of messages in the same slot from frame to frame is applied, the alternating pattern should only involve two transmitter antennas, with a scheduled burst in every frame, and the transmission should alternate between the antennas every frame, in order to resemble the situation for which the receiver has been tested.

This is necessary in order to be able to make assumptions on receiver message failure rates (MFR).

7.12.4.1.4 When analysing the probability of lost messages, the following basic

assumptions apply:

1. If all received signal levels are between the receiver minimum design input power (S ) and maximum design input power (Smax), and min they are within 40 dB of each other, then the analysis can assume 10-3 message failure rate (MFR).

2. If all received signals are below S , then the analysis must assume min a MFR of 100 per cent.

3. If any signal exceeds Smax it must be assumed that reception in all slots in that frame and any number of subsequent frames is adversely affected (not only those where Smax is exceeded), as no receiver recovery time is specified for these conditions.

Furthermore, in the case of a dual antenna set-up with messages alternating in each frame, the following assumptions can be made:

4. If one signal is below S (S - Δ) and the second signal is within min min 40 dB (i.e., S - Δ + 40 dB or less), then the analysis must assume min that the MFR for the signal below S is 100 per cent and the MFR min for the stronger signal is 10-3.

5. If both signals are within S to Smax, but the variation between the min signals is greater than 40 dB, then the analysis must assume a MFR of 60 per cent.

6. If one signal is below S (S - Δ) and the second is above Smin, min min and exceeds 40 dB variation (S - Δ + 40 dB + ε or more), then the min analysis must assume that the MFR for the signal below S is 100 min per cent and the MFR for the stronger signal is 60 per cent.

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7.12.4.1.5 The resulting probability of no Type 2 messages being received for a duration of one minute should be assessed against the applicable continuity requirement.

Note.: The analysis may have to consider up to 15 dB variation for the aircraft VDB antenna gain variation depending upon the scenario, such that the 40 dB power variation ≤ SIS power variation + up to 15 dB aircraft antenna gain variation.

To avoid receiver processing issues concerning lost or duplicated messages, all transmissions of the Type 1, Type 11 or Type 101 message, or linked pairs of Type 1, Type 11 or Type 101 messages for a given measurement type within a single frame need to provide identical data content.

7.12.4.2 One example of the use of multiple antennas is a facility with two antennas installed at the same location but at different heights above the ground plane. The heights of the antennas are chosen so that the pattern from one antenna fills the nulls in the pattern of the other antenna that result from reflections from the ground plane. The GBAS ground subsystem alternates broadcasts between the two antennas, using one, two or three assigned slots of each frame for each antenna. Type 1, Type 11 or Type 101 messages as appropriate for the service type supported are broadcast once per frame, per antenna. This allows for reception of one or two Type 1, Type 11 or Type 101 messages per frame, depending on whether the user is located within the null of one of the antenna patterns. Type 2 and 4 messages are broadcast from the first antenna in one frame, then from the second antenna in the next frame. This allows for reception of one each of the Type 2 and 4 messages per one or two frames, depending on the user location.

7.13 Definition of lateral and vertical alert limits

7.13.1 The lateral and vertical alert limits when the active service type is C or D are computed as defined in Appendix B, Tables B-138 and B-139. In these computations the parameters D and H have the meaning shown in Figure D-17.

7.13.2 The vertical alert limit when the active service type is C or D is scaled from a height of 60 m (200 ft) above the LTP/FTP. For a procedure designed with a decision height of more than 60 m (200 ft), the VAL at that decision height will be larger than the broadcast FASVAL.

7.13.3 The lateral and vertical alert limits for procedures supported by GAST A service type associated with channel numbers 40 001 to 99 999 are computed in the same manner as SBAS as given in 6.6.

7.14 Monitoring and maintenance actions 709CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

7.14.1 Specific monitoring requirements or built-in tests may be necessary in addition to the monitors defined in Appendix B, 3.6.7.3 and should be determined by individual States. Since the VDB signal is critical to the operation of the GBAS broadcast station, any failure of the VDB to successfully transmit a usable signal within the assigned slots and over the entire service volume is to be corrected as soon as possible. Therefore, it is recommended that the following conditions be used as a guide for

implementing a VDB monitor: a) Power. A significant drop in power is to be detected within an appropriate time period. b) Loss of message type. The failure to transmit any scheduled message type(s). This could be based on the failure to transmit a unique message type in succession, or a combination of different message types.

c) Loss of all message types. The failure to transmit any message type for an appropriate time period will be detected.

The appropriate time periods for these monitors depend on the FAST and on whether a back-up transmitter is provided. Where a back-up transmitter is provided, the objective is to switch to the back-up transmitter quickly enough to avoid an alert being generated in the airborne equipment. This means that the appropriate time periods are a maximum of 3 seconds for FAST C and a maximum of 1.5 seconds for FAST D ground systems in

order to be consistent with the aircraft equipment message loss requirements. If longer periods than this are implemented, the changeover to the back-up transmitter will cause an alert and must therefore be considered to be a continuity failure. If no back-up transmitter is provided, the time periods for these monitors are not critical.

7.14.2 Upon detection of a failure, and in the absence of a back-up transmitter, termination of the VDB service should be considered if the signal cannot be used reliably within the service volume to the extent that aircraft operations could be significantly impacted. Appropriate actions in operational procedures are to be considered to mitigate the event of the signal being removed from service. These would include dispatching maintenance specialists to service the GBAS VDB or special ATC procedures. Additionally, maintenance actions should be taken when possible for all built-in test failures to prevent loss of GBAS service.

7.14.3 The use of a back-up transmitter also applies to the VDB monitoring requirements defined in Appendix B,

3.6.7.3.1. The time to switch over to the back-up needs to be taken into account while remaining compliant with the time to detect and terminate transmissions defined in Appendix B, 3.6.7.3.1.1 and 3.6.7.3.1.2.

710CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

7.15 Examples of VDB messages

7.15.1 Examples of the coding of VDB messages are provided in Tables D-14 through D-21. The examples illustrate the coding of the various application parameters, including the cyclic redundancy check (CRC) and forward error correction (FEC) parameters, and the results of bit scrambling and D8PSK symbol coding. The engineering values for the message parameters in these tables illustrate the message coding process, but are not necessarily representative of realistic values.

7.15.2 Table D-14 provides an example of a Type 1 VDB message. The additional message flag field is coded to indicate that this is the first of two Type 1 messages to be broadcast within the same frame. This is done for illustration purposes; a second Type 1 message is not typically required, except to allow broadcast of more ranging source corrections than can be accommodated in a single message.

7.15.3 Table D-15 provides an example of a Type 101 VDB message. The additional message flag field is coded to indicate that this is the first of two Type 101 messages to be broadcast within the same frame. This is done for illustration purposes; a second Type 101 message is not typically required, except to allow broadcast of more ranging source corrections than can be accommodated in a single message.

7.15.4 Table D-16 provides examples of a Type 1 VDB message and a Type 2 VDB message coded within a single burst (i.e. two messages to be broadcast within a single transmission slot). The additional message flag field of the Type 1 message is coded to indicate that it is the second of two Type 1 messages to be broadcast within the same frame. The Type 2 message includes additional data block 1. Table D-17 provides an example of Type 1 and Type 2 messages with additional data blocks 1 and

2.

7.15.4.1 Table D-18 provides an example of Type 2 messages with additional data blocks 1, 3 and 4 coded within a single burst with a Type 3 message that is used to fill the rest of the time slot.

7.15.5 Table D-19 provides an example of a Type 4 message containing two FAS data blocks.

7.15.6 Table D-20 provides an example of a Type 5 message. In this example, source availability durations common to all approaches are provided for two ranging sources. Additionally, source availability durations for two

individual approaches are provided: the first approach has two impacted ranging sources and the second approach has one impacted ranging source.

7.15.7 Table D-21 provides an example of a Type 11 message.

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7.16 GBAS survey accuracy The standards for the survey accuracy for NAVAIDs are contained in Annex 14 — Aerodromes. In addition, the Manual of the World Geodetic System 1984 (WGS-84) (Doc 9674) provides guidance on the establishment of a network of survey control stations at each aerodrome and how to use the network to establish WGS-84 coordinates. Until specific requirements are developed for GBAS, the Annex 14 survey accuracy requirements for NAVAIDs located at the aerodrome apply to GBAS. The recommendation contained in Appendix B to Chapter 3,

3.6.7.2.3.4, for the survey accuracy of the GBAS reference point is intended to further reduce the error in the WGS-84 position calculated by an airborne user of the GBAS positioning service to a value smaller than that established by the requirements of Appendix B to Chapter 3,

3.6.7.2.4.1 and 3.6.7.2.4.2, in the GBAS standards and to enhance survey accuracy compared to that specified in Annex 14. The integrity of all aeronautical data used for GBAS is to be consistent with the integrity requirements in Chapter 3, Table 3.7.2.4-1.

7.17 Type 2 message additional data blocks

7.17.1 The Type 2 message contains data related to the GBAS facility such as the GBAS reference point location, the GBAS continuity and integrity designator (GCID) and other pertinent configuration information. A method for adding new data to the Type 2 message has been devised to allow GBAS to evolve to support additional service types. The method is through the definition of new additional data blocks that are appended to the Type 2 message. In the future, more additional data blocks may be defined. Data blocks 2 through 255 have variable length and may be appended to the message after additional data block 1 in any order.

7.17.2 Type 2 message additional data block 1 contains information related to spatial decorrelation of errors and information needed to support selection of the GBAS positioning service (when provided by a given ground station).

7.17.3 Type 2 message additional data block 2 data may be used in GRAS to enable the GRAS airborne subsystem to switch between GBAS broadcast stations, particularly if the GBAS broadcast stations utilize different frequencies. Additional data block 2 identifies the channel numbers and locations of the GBAS broadcast station currently being received and other adjacent or nearby GBAS broadcast stations.

7.17.4 Type 2 message additional data block 3 contains information necessary to support GAST D. All FAST D ground subsystems are required to transmit a Type 2 message with additional data block 3 properly populated so that the bounding requirements are met.

7.17.5 Type 2 message additional data block 4 contains information necessary 712CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 for a ground station that supports the authentication protocols. It includes a single parameter which indicates which slots are assigned to the ground station for VDB transmissions. Airborne equipment that supports the authentication protocols will not use data unless it is transmitted in the slots indicated by the slot group definition field in the MT 2 ADB 4.

713CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 714CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 715CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 716CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 717CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 718CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 719CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 720CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 721CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 722CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 723CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 724CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 725CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 726CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 727CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 728CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

7.18 Type 101 message Type 101 message is an alternative to Type 1 message developed to fit the specific needs of GRAS systems. The primary difference in the contents and application of these two message types is two-fold: (a) Type 101 message has a larger available range for σpr_gnd values and (b) ground subsystem time-to-alert is larger for a system broadcasting Type 101 messages. The first condition would typically occur in a system where a broadcast station covers a large area, such that decorrelation errors increase the upper limit of the pseudo-range correction errors. The second condition may be typical for systems where a central master station processes data from multiple receivers dispersed over a large area.

7.19 Airborne processing for GBAS approach service types Note.: In order to ensure the required performance and functional objectives for GAST D are achieved, it is necessary for the airborne equipment to meet defined performance and functional standards. The relevant minimum operational performance standards (MOPS) are detailed in RTCA DO- 253D.

7.19.1 Differential position solution for the GBAS positioning service. The position solution used to provide position, velocity and time outputs is based on 100-second smoothed pseudo-ranges corrected with corrections obtained from message Type 1 or message Type 101.

7.19.2 Differential position solution for approach service GAST A, B and C. When the active approach service type is A, B or C, the position solution used to generate deviations is based on 100 second smoothed pseudo-ranges corrected with corrections obtained from message Type 1 or message Type 101. The projection matrix, S, used to compute the position solution (Appendix B, 3.6.5.5.1.1.2) is computed based on σi computed using σ _ [i] from message Type 1 or message Type 101 and σ based on pr gnd iono,i σ from message Type 2.

vert_iono_gradient

7.19.3 Differential position solutions for approach service GAST D. When GAST D is the active approach service type, the airborne equipment will compute two different position solutions, one based on 30-second smoothed pseudo-ranges and the other based on 100-second smoothed pseudo- ranges. The following characterizes the standard processing required by

the MOPS: a) the position solution used to develop deviations is based on 30- second smoothed pseudo-ranges corrected with corrections obtained from message Type 11; b) the projection matrix, S, used for both position solutions is computed based on σw,i computed using σpr_gnd_30s from message Type 11 729CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 and σiono,i based on σvert_iono_gradient_D from message Type 2 Additional Data Block 3;

c) a second position solution is computed using the projection matrix from b) and the 100-second smoothed pseudoranges corrected with corrections obtained from message Type 1; and d) both position solutions are based on the same set of satellites as used for the position solution defined in a) above. Additional information regarding the intended use of these dual position solutions is given in 7.5.6.1 of this attachment.

7.20 Type 11 message A Type 11 message is required for FAST D ground subsystems. The Type 11 message contains differential corrections derived from pseudo-range data that has been carrier smoothed with a time constant of 30 seconds.

The Type 11 message also includes alternative parameters for integrity bounding and for optimal weighting of measurements. Additional information regarding the standard processing of parameters in the Type 11 message is given in 7.19.

7.21 Slot occupancy The slot occupancy requirement in Appendix B, 3.6.7.4.1.3 is for ground subsystems that support authentication. The slot occupancy is the length of a burst divided by the length of a single time slot. In more detail and

expressed in number of bits: slot occupancy = (88 bits + up to 1 776 bits application data + 57 to 59 bits for application FEC, fill bits and ramp down) / 1 968.75 bits The numerator in the formula sums all bits that are included in a single burst of the ground subsystem. These are the first 88 bits from ramp up to training sequence FEC, up to 1 776 application data bits, 48 application FEC bits, 0 to 2 fill bits and 9 bits for ramp down. For the denominator 1

968.75 bits are the calculated number of bits that can be transmitted in

62.5 ms (Appendix B, 3.6.3.1) using the data rate of 31 500 bits/s (Appendix B, 3.6.2.5).

8. SIGNAL QUALITY MONITOR (SQM) DESIGN

8.1 The objective of the signal quality monitor (SQM) is to detect satellite signal anomalies in order to prevent aircraft receivers from using misleading information (MI). MI is an undetected aircraft pseudo-range differential error greater than the maximum error (MERR) that can be tolerated. For GAST D equipment, additional requirements are in place to assure detection before the differential pseudo-range error reaches a specified value (see Appendix B, 3.6.7.3.3). These large pseudo-range errors are 730CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 due to code correlation peak distortion caused by satellite payload failures.

If the reference receiver used to create the differential corrections and the aircraft receiver have different measurement mechanizations (i.e. receiver bandwidth and tracking loop correlator spacing), the signal distortion affects them differently. The SQM must protect the aircraft receiver in cases when mechanizations are not similar. SQM performance is further defined by the probability of detecting a satellite failure and the probability of incorrectly annunciating a satellite failure.

8.2 The signal effects that might cause a GBAS or SBAS to output MI can be categorized into three different effects on the correlation function as

follows: a) Dead zones: If the correlation function loses its peak, the receiver’s discriminator function will include a flat spot or dead zone. If the reference receiver and aircraft receiver settle in different portions of this dead zone, MI can result.

b) False peaks: If the reference receiver and aircraft receiver lock to different peaks, MI could exist. c) Distortions: If the correlation peak is misshapen, an aircraft that uses a correlator spacing other than the one used by the reference receivers may experience MI.

8.3 The threat model proposed for use in assessment of SQM has three parts that can create the three correlation peak pathologies listed above.

8.4 Threat Model A consists of the normal code signal except that all the positive chips, and positive/negative sub-carrier chips for Galileo E1-C signal and BDS B1C_pilot signal, have a falling edge that leads or lags relative to the correct end-time for that chip. This threat model is associated with a failure in the navigation data unit (NDU), the digital partition of a satellite. The occurrences of Threat Model A on GPS L1 C/A and on GPS L5 Q5 signals are independent events. If overlapping in time, the signs and sizes of leads and lags may be different on L1 C/A and L5 Q5 signals.

8.4.1 Threat Model A for GPS has a single parameter Δ, which is the lead (Δ <

0) or lag (Δ > 0) expressed in microseconds. The range for this parameter is ‒ 0.12 ≤ Δ ≤ 0.12 for the L1 C/A code signal. The range for this parameter is ‒ 0.1 ≤ Δ ≤ 0.1 for the GPS L5 Q5 signal. Threat Model A for GLONASS has a single parameter Δ, which is the lead (Δ < 0) or lag (Δ > 0) expressed in microseconds. The range for this parameter is ‒ 0.22 ≤ Δ ≤ 0.22 for GLONASS L1OF signal. The range for this parameter is ‒ 0.1 ≤ Δ ≤ 0.1 for GLONASS L1OC signal and ‒ 0.1 ≤ Δ ≤ 0.1 for GLONASS L3OC. Threat Model A for Galileo has a single parameter Δ, which is the lead (Δ < 0) or lag (Δ > 0) expressed in microseconds. The range for this parameter is ‒

0.12 ≤ Δ ≤ 0.12 for Galileo E1-C signal. The range for this parameter is ‒ 731CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

0.1 ≤ Δ ≤ 0.1 for Galileo E5a-Q signal. Threat Model A for BDS has a single parameter Δ, which is the lead (Δ < 0) or lag (Δ > 0) expressed in microseconds. The range for this parameter is ‒ 0.05 ≤ Δ ≤ 0.05 for BDS B1C_pilot signal. The range for this parameter is ‒ 0.05 ≤ Δ ≤ 0.05 for BDS B2a_pilot signal.

8.4.2 Within this range, threat Model A generates the dead zones described above. (Waveforms with lead need not be tested, because their correlation functions are simply advances of the correlation functions for lag; hence, the MI threat is identical.)

8.5 Threat Model B introduces amplitude modulation and models degradations in the analog section of the core constellation satellite. More specifically, it consists of the output from a second order system when the nominal code baseband signal is the input. Threat Model B assumes that the degraded satellite subsystem can be described as a linear system dominated by a pair of complex conjugate poles. These poles are located at σ ± j2πfd, where σ is the damping factor in 106 nepers/second and fd is the resonant frequency with units of 106 cycles/second.

8.5.1 The unit step response of a second order system is given by:

8.5.2 Threat Model B for GPS corresponding to second order anomalies uses the following ranges for the parameters Δ, fd and σ:

The occurrence of Threat Model A on the GPS L5 Q5 signal and the occurrence of Threat Model B on the GPS L5 Q5 signal are independent events. The parameters characterizing the leads, lags, ringing frequency fd, and decay parameter σ are not constrained to be the same size or sign on GPS L1 C/A and GPS L5 Q5 signals.

Threat Model B for GLONASS corresponding to second order anomalies

uses the following ranges for the parameters defined above:

Threat Model B for Galileo corresponding to second order anomalies uses

the following ranges for the parameters defined above:

732CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 Threat Model B for BDS corresponding to second order anomalies uses

the following ranges for the parameters defined above:

8.5.3 Within these parameter ranges, Threat Model B generates distortions of the correlation peak as well as false peaks.

8.6 Threat Model C introduces both lead/lag and amplitude modulation.

Specifically, it consists of outputs from a second order system when the C/A code signal at the input suffers from lead or lag. This waveform is a combination of the two effects described above.

8.6.1 Threat Model C for GPS includes parameters Δ, fd and σ with the following

ranges:

Threat Model C for GLONASS includes parameters Δ, fd and σ with the

following ranges:

Threat Model C for Galileo includes parameters Δ, fd and σ with the

following ranges:

Threat Model C for BDS includes parameters Δ, fd and σ with the following

ranges:

8.6.2 Within these parameter ranges, threat Model C generates dead zones, distortions of the correlation peak and false peaks.

8.7 Unlike core constellation signals, the SBAS ranging signal is commissioned and controlled by the service provider. Moreover, the service provider also monitors the quality of the signal from the SBAS. To this end, the threat model will be specified and published by the service provider for each SBAS satellite. The SBAS SQM will be designed to protect all avionics that comply with Table D-23. Publication of the threat 733CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 model is required for those cases where a service provider chooses to allow the SBAS L1 ranging signal from a neighbouring service provider to be used for precision approach by SBAS or GBAS. In these cases, the service provider will monitor the SBAS ranging signal from the neighbouring satellite.

8.8 In order to analyse the performance of a particular monitor design, the monitor limit must be defined and set to protect individual satellite pseudo- range error relative to the protection level, with an allocation of the ground subsystem integrity risk. The maximum tolerable error (denoted as MERR) for each ranging source i can be defined in GBAS, L1 SBAS and DFMC

SBAS as: for SBAS, and in particular for L1 SBAS APV and precision approach where min {𝜎i,UDRE2 } is the minimum possible value for any user, MERR is evaluated at the output of a fault-free user receiver and varies with satellite elevation angle and ground subsystem performance.

8.9 The SQM is designed to limit the worst differential error to values below the MERR in the case of a satellite anomaly. Typically, the SQM measures various correlation peak values and generates spacing and ratio metrics that characterize correlation peak distortion. Figure D-18 illustrates typical points at the top of a fault-free, unfiltered correlation peak.

8.9.1 A correlator pair is used for tracking. All other correlator values are measured with respect to this tracking pair.

8.9.2 Two types of test metrics are formed: early-minus-late metrics (D) that are indicative of tracking errors caused by peak distortion, and amplitude ratio metrics (R) that measure slope and are indicative of peak flatness or close- in, multiple peaks.

8.9.3 It is necessary that the SQM has a precorrelation bandwidth that is sufficiently wide to measure the narrow spacing metrics, so as not to cause significant peak distortion itself and not to mask the anomalies caused by the satellite failure. Typically, the SQM receiver must have a precorrelation bandwidth of at least 16 MHz for GPS L1 and at least 24 MHz for L5, at least 15 MHz for GLONASS, at least 24 MHz for Galileo and at least 24 MHz for BDS.

8.9.4 The test metrics are smoothed using low-pass digital filters. The time constant of these filters are to be shorter than those used jointly by the 734CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 reference receivers for deriving differential corrections and by the aircraft receiver for smoothing pseudo-range measurements (and standardized at 100 seconds). The smooth metrics are then compared to thresholds. If any one of the thresholds is exceeded, an alarm is generated for that satellite.

8.9.5 The thresholds used to derive performance are defined as minimum detectable errors (MDEs) and minimum detectable ratios (MDRs). Fault- free false detection probability and missed detection probability are used to derive MDEs and MDRs. The noise in metrics (D) and (R), as denoted σ and σ below, is dominated by multipath errors. Note that the D,test R,test metric test can also have a mean value (μtest) caused by SQM receiver filter distortion. Threshold tests must also account for the mean values.

8.9.6 The MDE and MDR values used in the SQM performance simulations are

calculated based on the following equations: where Kffd = 5.26 is a typical fault-free detection multiplier representing a false detection probability of 1.5 × 10–7 per test. The false detection probability may be allocated to each metric used in the SQM depending on the number of metrics implemented;

Kmd = 3.09 is a typical missed detection multiplier representing a missed detection probability of 10–3 per test. The allocation of the missed detection probability can be further optimised considering the probability of integrity risk induced by each distortion (given its differential bias) and the probability of integrity failure allocated to the signal distortion event;

σ is the standard deviation of measured values of difference test metric D,test D; and σ is the standard deviation of measured values of ratio test metric R.

R,test

8.9.7 If multiple independent SQM receivers are used to detect the failures, the sigma values can be reduced by the square root of the number of independent monitors.

8.9.8 A failure is declared if for any of the tests performed, where μ is the mean value of the test X X,test that accounts for fault-free SQM receiver filter distortion, as well as correlation peak distortion associated with the specific code. (Code correlation peaks can have different slopes across different codes within the same code family. In a simulation environment, however, this code 735CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 distortion can be ignored, and a perfect correlation peak can be used, except for simulated filter distortion.)

8.10 The standard deviations of the test statistics, σD,test and σR,test can be determined via data collection on a multicorrelator receiver in the expected operating environment. The data collection receiver utilizes a single tracking pair of correlators and additional correlation function measurement points which are slaved to this tracking pair, as illustrated in Figure D-18 for GPS and GLONASS and in Figure D-19 for Galileo and BDS. Data is collected and smoothed for all available measurement points in order to compute the metrics. The standard deviation of these metrics define σ . It is also possible to compute these one sigma test statistics D,test if a multipath model of the installation environment is available.

8.10.1 The resulting σ is highly dependent on the multipath environment in D,test which the data are collected. The deviation due to multipath can be an

order of magnitude greater than that which would result from noise even at minimum carrier-to-noise level. This aspect illustrates the importance of the antenna design and siting criteria which are the primary factors in determining the level of multipath that will enter the receiver. Reducing multipath will significantly decrease the resulting MDEs and thus improve the SQM capabilities.

8.10.2 Mean values μD,test and μR,test, on the other hand, are determined in a relatively error-free environment, such as through the use of core constellation satellite signal simulator as input. These mean values model the nominal SQM receiver’s filter distortion of the autocorrelation peak, including the effects of distortion due to adjacent minor autocorrelation peaks. The mean values can differ for the various PRNs based on these properties.

8.10.3 The presence of nominal signal deformation biases may cause the distribution of the monitor detectors to have non-zero mean. These biases can be observed by averaging measurements taken from a real-world data collection. Note that the nominal biases may depend on elevation and they typically change slowly over time. For example, nominal GPS deformations are leads and lags that are present in unfaulted conditions and thus may exist all the time. The nominal GPS deformation is in the range – 0.01 μs ≤ Δ ≤ +0.01 μs.

8.10.4 The SQM for SBAS is validated for the signal distortions defined by the GPS, GLONASS, Galileo and BDS TMA/ B/C threat space only for a vertical alert limit greater or equal to 35 m.

8.11 In order for the ground monitor to protect users against the different threat models described above, it is necessary to assume that aircraft receivers have specific characteristics. If no such constraints were assumed, the complexity of the ground monitor would be unnecessarily high. Evolution in the technology may lead to improved detection capability in the aircraft 736CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 receiver and may alleviate the current constraints.

8.11.1 For double-delta correlators, the aircraft receiver tracks the strongest correlation peak over the full code sequence for every ranging source used in the navigation solution.

8.11.2 For double-delta correlators, the precorrelation filter rolls off by at least 30 dB per octave in the transition band. For GBAS receivers, the resulting attenuation in the stop band is required to be greater than or equal to 50 dB (relative to the peak gain in the pass band).

8.11.3 The following parameters are used to describe the tracking performance

specific to each type of satellite: a) the instantaneous correlator spacing is defined as the spacing between a particular set of early and late samples of the correlation function; b) the average correlator spacing is defined as a one-second average of the instantaneous correlator spacing. The average applies over any one-second time frame;

c) the discriminator Δ is based upon an average of early-minus-late samples with spacings inside the specified range, or is of the type Δ = 2Δd1 – Δ2d1, with both d1 and 2d1 in the specified range. Either a coherent or non-coherent discriminator is used;

d) the differential group delay applies to the entire aircraft system prior to the correlator, including the antenna. The differential group delay

is defined as: where fc is the precorrelation band pass filter centre frequency; f is any frequency within the 3dB bandwidth of the precorrelation filter; ϕ is the combined phase response of precorrelation band pass filter and antenna; and ω is equal to 2πf.

8.11.4 For aircraft receivers supporting single-frequency L1 using early-late correlators and tracking GPS L1 C/A satellites signal, the precorrelation bandwidth of the installation, the correlator spacing and the differential group delay are within the ranges defined in Table D-22, except as noted 737CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 below.

8.11.4.1 For GBAS airborne equipment using early-late correlators and tracking GPS L1 C/A satellites signal, the precorrelation bandwidth of the installation, the correlator spacing and the differential group delay (including the contribution of the antenna) are within the ranges defined in Table D-22, except that the region 1 minimum bandwidth will increase to 4 MHz and the average correlator spacing is reduced to an average of 0.21 chips or instantaneous of 0.235 chips.

8.11.4.2 For GBAS airborne equipment class D (GAEC D) receivers using early- late correlators and tracking GPS satellites, the precorrelation bandwidth of the installation, the correlator spacing and the differential group delay are within the ranges defined in Table D-22, regions 2, 3 or 4 only. In addition, in region 2 the range of average correlator spacing is 0.045 –

0.12 chips, and the instantaneous correlator spacing is 0.04 – 0.15 chips.

8.11.4.3 For SBAS airborne equipment using early-late correlators and tracking GPS L1 C/A satellites signal, the precorrelation bandwidth of the installation, the correlator spacing and the differential group delay (including the contribution of the antenna) are within the ranges of the first three regions defined in Table D-22 for L1 signal.

8.11.5 For aircraft receivers supporting single-frequency L1 using early-late correlators and tracking GLONASS satellites, the precorrelation bandwidth of the installation, the correlator spacing, and the differential group delay are within the ranges as defined in Table D-23.

8.11.5.1 For GBAS airborne equipment class D (GAEC D) aircraft receivers using early-late correlators and tracking GLONASS satellites, the precorrelation bandwidth of the installation, the correlator spacing, and the differential group delay are within the ranges as defined in Table D-23, regions 2 and 3 only. In addition, in region 2 the range of average correlator spacing is

0.05 – 0.1 chips, and the instantaneous correlator spacing is 0.045 – 0.11 chips.

8.11.6 For aircraft receivers supporting single-frequency L1 using double-delta correlators and tracking GPS L1 C/A satellites signal, the precorrelation bandwidth of the installation, the correlator spacing and the differential group delay are within the ranges defined in Tables D-24 and D-27.

8.11.6.1 For GBAS airborne equipment class D (GAEC D) receivers using double- delta correlators and tracking GPS satellites, the precorrelation bandwidth of the installation, the correlator spacing and the differential group delay are within the ranges defined in Table D-27, regions 2 and 3 only.

8.11.7 For aircraft receivers supporting single-frequency L1 and using the early- late or double-delta correlators and tracking SBAS L1 satellites, the precorrelation bandwidth of the installation, the correlator spacing and the 738CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 differential group delay are within the ranges defined in Table D-28.

8.11.7.1 For GBAS airborne equipment class D (GAEC D) receivers using the early- late or double-delta correlators and tracking SBAS satellites, the precorrelation bandwidth of the installation, the correlator spacing and the differential group delay are within the ranges defined in Table D-28, region 2 only. In addition, for GAEC D receivers using early-late correlators and tracking SBAS satellites, the average correlator spacing is 0.045 – 0.12 chips, and the instantaneous correlator spacing is 0.04 – 0.15 chips.

8.11.8 For aircraft receivers designed for DFMC SBAS, the L5 (or L3) signal tracking precorrelation bandwidth of the installation, the correlator spacing and the differential group delay are within the ranges defined in Table D- 25 using the early late correlators and tracking the GPS, Galileo, GLONASS, BDS or SBAS L5 signals identified in Attachment B, 3.5.11.1.

8.11.9 For aircraft receivers designed for DFMC SBAS, the L1 signal tracking precorrelation bandwidth of the installation, the correlator spacing and the differential group delay are within the ranges defined in Table D-26 using the early late correlators and tracking the GPS, Galileo, GLONASS, BDS or SBAS L1 signals identified in Attachment B, 3.5.11.1.

8.11.10 The instantaneous correlator spacing may be larger than the average correlator spacing range provided in Table D-25 and Table D-26 accounting for noise or jitter in the correlator spacing.

9. STATUS MONITORING AND NOTAM

9.1 System status

9.1.1 Degradation of GBAS usually has local effects and affects mainly approach operations. System degradation of GBAS is to be distributed as approach-related information.

9.1.2 Degradation of core satellite constellation(s) or SBAS can be limited to local effects affecting mainly approach operations, but can also impact a wider area, and may directly affect en-route operations in the SBAS service area(s). System degradation impacting en-route or wider area SBAS operations is to be distributed as area-related information. An example is an ionosphere storm that removes all vertically-guided approach capability. System degradation impacting limited approaches can be distributed as approach-related information.

9.1.3 Degradation of GRAS may have local effects and/or wide area effects.

Therefore, if the degradation has only local effects, GRAS system degradation information is to be distributed in accordance with 9.1.1. If the degradation has wide area effects, GRAS system degradation information is to be distributed in accordance with 9.1.2.

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9.1.4 Information is to be distributed to indicate the inability of GNSS to support a defined operation. For example, GPS/SBAS may not support a precision approach operation on a particular approach. This information can be generated automatically or manually based upon models of system performance.

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9.2 Information on type of degradation

The following information is to be distributed: a) non-availability of service; b) downgrade of service, if applicable; and c) time and expected duration of degradation.

9.3 Timing of notification For scheduled events, notification should be given to the NOTAM authority at least 72 hours prior to the event. For unscheduled events, notification to the NOTAM authority should be given within 15 minutes. Notification should be given for events of 15-minute, or longer, duration.

10. INTERFERENCE 742CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026

10.1 Potential for interference Satellite radio navigation systems such as GPS, GLONASS, Galileo and BDS feature relatively weak received signal power, meaning that an interference signal could cause loss of service. In order to maintain service, it will be necessary to ensure that the maximum interference levels specified in the SARPs are not exceeded.

10.2 In-band interference sources A potential source of in-band harmful interference is Fixed Service operation in certain States. There is a primary allocation to the fixed service for point-to-point microwave links in certain States in the frequency band used by GPS, GLONASS, Galileo and BDS.

10.3 Out-of-band interference sources Potential sources of out-of-band interference include harmonics and spurious emissions of aeronautical VHF and UHF transmitters. Out-of- band noise, discrete spurious products and intermodulation products from radio and TV broadcasts can also cause interference problems.

10.4 Aircraft generated sources

10.4.1 The potential for harmful interference to GPS, GLONASS, Galileo and BDS on an aircraft depends on the type of aircraft, its size and the transmitting equipment installed. The GNSS antenna location should take into account the possibility of on-board interference (mainly SATCOM).

10.4.2 GNSS receivers that are used on board aircraft with SATCOM equipment must have a higher interference threshold in the frequency range between 1 610 MHz and 1 626.5 MHz than receivers on board aircraft without SATCOM equipment. Therefore, specifications for the interference threshold discriminate between both cases.

Note.: Limits for radiated SATCOM aircraft earth stations are given in Annex 10, Volume III, Part I, Chapter 4, 4.2.3.5.

10.4.3 The principal mitigation techniques for on-board interference include shielding, filtering, receiver design techniques, and, especially on larger aircraft, physical separation of antennas, transmitters and cabling.

Receiver design techniques include the use of adaptive filters and interference cancellation techniques that mitigate against narrow in-band interference. Antenna design techniques include adaptive null steering antennas that reduce the antenna gain in the direction of interference sources without reducing the signal power from satellites.

10.5 Integrity in the presence of interference 743CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 The requirement that GNSS receivers do not output misleading information in the presence of interference is intended to prevent the output of misleading information under unintentional interference scenarios that could arise. It is not intended to specifically address intentional interference. While it is impossible to completely verify this requirement through testing, an acceptable means of compliance can be found in the appropriate receiver Minimum Operational Performance Standards published by RTCA and EUROCAE.

11. RECORDING OF GNSS PARAMETERS

11.1 In order to be able to conduct post-incident/accident investigations (Chapter 2, 2.1.4.2 and 2.1.4.3), it is necessary to record GNSS information both for the augmentation system and for the appropriate GNSS core system constellation used for the operation. The parameters to be recorded are dependent on the type of operation, augmentation system and core elements used. All parameters available to users within a given service area should be recorded at representative locations in the service area.

11.2 The objective is not to provide independent assurance that the GNSS is functioning correctly, nor is it to provide another level of system monitoring for anomalous performance or input data for a NOTAM process. The recording system need not be independent of the GNSS service and may be delegated to other States or entities. In order to enable future reconstruction of position, velocity and time indications provided by specific GNSS configurations, it is recommended to log data continuously, generally at a 1 Hz rate.

11.3 For GNSS core systems the following monitored items should be recorded

for all satellites in view: a) observed satellite carrier-to-noise density (C/N0); b) observed satellite raw pseudo-range code and carrier phase measurements; c) broadcast satellite navigation messages, for all satellites in view; and d) relevant recording receiver status information.

11.4 For SBAS the following monitored items should be recorded for all SBAS satellites in view in addition to the GNSS core system monitored items

listed above: a) observed SBAS satellite carrier-to-noise density (C/N0); b) observed SBAS satellite raw pseudo-range code and carrier phase 744CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 measurements;

c) broadcast SBAS data messages; and d) relevant receiver status information.

11.5 For GBAS the following monitored items should be recorded in addition to the GNSS core system and SBAS monitored items listed above (where appropriate): a) VDB power level; b) VDB status information; and c) broadcast GBAS data messages.

12. GNSS PERFORMANCE ASSESSMENT

12.1 GNSS performance assessment is a periodic offline activity that may be performed by a State or delegated entity, aiming to verify that GNSS performance parameters conform to the relevant Annex 10 Standards.

This activity can be done for the core constellation, the augmentation system or a combination of both.

Note.: Additional guidance material on GNSS performance assessment is

provided in the Global Navigation Satellite System (GNSS) Manual (Doc

9849).

12.2 The data described in section 11 may also support GNSS performance assessment.

13. GNSS AND DATABASE Note.: Provisions relating to aeronautical data are contained in Annex 11,

Chapter 2, and Annex 15, Chapter 3.

13.1 The database is to be current with respect to the effective AIRAC cycle, which generally means that a current database be loaded into the system approximately every 28 days. Operating with out-of-date navigation databases has to be avoided.

13.2 In certain situations, operations using an expired database can be conducted safely by implementing a process and/or using procedures to ensure that the required data is correct. These processes and/or procedures need prior approval by the State.

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13.2.1 These procedures should be based on one of the following methods: a) require the crew to check, prior to the operation, critical database information against current published information. (This method increases workload and would not be practical for all applications.);

or b) waive the requirement for a current database and frequent checks by the crew of the database information. This waiver can only be applied to very specific cases where aircraft are operated in a strictly limited geographical area and where that area is controlled by a single regulatory agency or multiple agencies that coordinate this process;

or c) use another approved method that ensures an equivalent level of safety.

14. MODELLING OF RESIDUAL ERRORS

14.1 Application of the integrity requirements for SBAS and GBAS requires that a model distribution be used to characterize the error characteristics in the pseudo-range. The HPL/LPL and VPL models (see 7.5.3) are constructed based on models of the individual error components (in the pseudo-range domain) that are independent, zero-mean, normal distributions. The relationship between this model and the true error distribution must be defined.

14.2 One method of ensuring that the protection level risk requirements are met is to define the model variance (σ ), such that the cumulative error 2

distribution satisfies the conditions:

14.3 This method can be directly applied when the error components have zero- mean, symmetrical and unimodal probability density functions. This is the case for the receiver contribution to corrected pseudo-range error, since the aircraft element is not subjected to low-frequency residual multipath errors.

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14.4 This method can be extended to address non-zero-mean, residual errors by inflating the model variance to compensate for the possible effect of the mean in the position domain.

14.5 Verification of the pseudo-range error models must consider a number of

factors including: a) the nature of the error components; b) the sample size required for confidence in the data collection and estimation of each distribution; c) the correlation time of the errors; and d) the sensitivity of each distribution to geographic location and time.

Figure D-1. Reserved 747CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 748CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 749CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 750CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 751CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 752CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 753CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 754CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 755CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 756CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 757CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 758CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 759CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 760CIVIL AVIATION REQUIREMENTS SECTION 9 SERIES D PART-II 06th JANUARY 2026 761