Draft revision to CAR Section 2 Series I Part V - FLIGHT DATA RECORDERS, COMBINATION RECORDERS, DATALINK RECORDERS, AIRBORNE IMAGE RECORDERS, AIRBORNE IMAGE RECORDING SYSTEM AND AIRCRAFT DATA RECORDING SYSTEM

GOVERNMENT OF INDIA OFFICE OF DIRECTOR GENERAL OF CIVIL AVIATION TECHNICAL CENTRE, OPP SAFDARJANG AIRPORT, NEW DELHI CIVIL AVIATION REQUIREMENTS SECTION 2 - AIRWORTHINESS SERIESI PART V ISSUE III, 30th October 2018 EFFECTIVE: FORTHWITH F.No. DGCA-25012(07)/5/2021-AW SUBJECT: FLIGHT DATA RECORDERS, COMBINATION RECORDERS, DATALINK RECORDERS, AIRBORNE IMAGE RECORDERS, AIRBORNE IMAGE RECORDING SYSTEMAND AIRCRAFT DATARECORDING SYSTEM 1. PURPOSE: Rule 57 of Aircraft Rules, 1937 requires that every aircraft shall be fitted and equipped with instruments and equipment, including radio apparatus and special equipment as may be specified according to the use and circumstances under which the flight is to be conducted. This part of Civil Aviation Requirement lays down the requirements for fitment of Flight Data Recorders, Combination Recorders, Data link Recorders, Airborne Image Recorders, Airborne Image Recording System and Aircraft Data Recording System on aircraft registered in India. All aircraft imported/ purchased or leased for operation in India shall meet the applicability requirements laid down in this CAR. This CAR has been issued under the provisions of Rule 29C of the Aircraft Rules, 1937. 2. DEFINITIONS: Flight Recorder: Any type of recorder installed in the aircraft for the purpose of complementing accident/incident investigation. Automatic deployable flight recorder (ADFR): A combination flight recorder installed on the aircraft which is capable of automatically deploying from the aircraft. Commercial Operation: An aircraft operation involving the transport of passengers, Rev. 1, 27th August 2021 1CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 cargo or mail for remuneration or hire. General Aviation: An aircraft operation other than a commercial air transport operation or an aerial work operation. 3. FLIGHT RECORDER COMPOSITION: 3.1 Crash protected flight recorders comprise one or more of the following Systems: a flight data recorder (FDR), a cockpit voice recorder (CVR), an airborne image recorder (AIR), a data link recorder (DLR). Image and data link information may be recorded on either the CVR or the FDR. When image or data link information is required to be recorded on a crash- protected flight recorder, it is permissible to record it on either the CVR or the FDR. 3.2 Light weight flight recorders comprise one or more of the following: An aircraft data recording system (ADRS), a cockpit audio recording system (CARS), an airborne image recording system (AIRS), a data link recording system (DLRS). When image or data link information is required to be recorded on a lightweight flight recorder, it is permissible to record it on either the CARS or the ADRS. Note 1- For aeroplanes / helicopters for which the application for type certification is submitted before 1 January 2016, specifications applicable to cash protected flight recorders may be found in EUROCAE ED- 112, ED-56A, ED-55, Minimum Operational Performance Specifications (MOPS), or earlier equivalent documents. Note 2- For aeroplanes / helicopters for which the application for type certificationis submitted on or after 1 January 2016, specifications applicable to cash protected flight recorders may be found in EUROCAE ED-112A, Minimum Operational Performance Specification (MOPS), or equivalent documents. Note 3 - Specifications applicable to lightweight flight recorders may be found inEUROCAE ED 155, Minimum Operational Performance Specification (MOPS), or equivalent documents. Note 4- Detailed requirements on flight data recorders are contained in Appendix-I. Rev. 2, 13th October 2022 2CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 4 Applicability 4.1 Aeroplane– Commercial Air Transport 4.1.1 Allturbine–enginedaeroplanes, for which the individual certificate of airworthiness was first issued before 1 January 1987, with a maximum certificated take-off mass of over 27000kg that are of types of which the prototype was certificated by the appropriate national authority after 30 September, 1969 should be equipped with an FDR which should record, in addition to the first 5 parameters listed in table 1 of Appendix I, such additional parameters as are necessary to meet the objective of determining: a) the attitude of the aeroplane in achieving its flight path; and b) the basic forces acting upon the aero plane resulting in the achieved flight path and the origin of such basic forces. 4.1.2 All turbine-engined aeroplanes, for which the individual certificate of airworthiness was first issued on or after 1 January 1987 but before 1 January 1989, with a maximum certificated take-off mass of over 27000kg that are of types of which the prototype was certificated by the appropriate national authority after 30 September, 1969 shall be equipped with an FDR which shall record at least first 16 parameters listed in table 1 of Appendix I. 4.1.3 All turbine-engined aeroplanes, for which the individual certificate of airworthiness was first issued on or after 1 January 1987 but before 1 January 1989, with a maximum certificated take-off mass of over 5700kg, except those in 4.1.2 should be equipped with an FDRwhich should record at least the first 9 parameters listed in table 1 of Appendix I. 4.1.4 All aeroplanes of a maximum certificated take-off mass of over 27000kg for which the individual certificate of airworthiness is first issued on or after 1January 1989 shall be equipped with an FDR which shall record at least the first 32 parameters listed in table 1 of Appendix I. 4.1.5 All aeroplanes of a maximum certificated take-off mass of over 5700kg, up to and including 27000kg, for which the individual certificate of Airworthiness is first issued on or after 1 January 1989, shall be equipped with an FDR which shall record at least the first 16 parameters listed in table 1 of Appendix I. 4.1.6 All aeroplanes of a maximum certificated take-off mass of over 5700kg for which the individual certificate of airworthiness is first issued after 1 Rev. 2, 13th October 2022 3CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 January 2005 shall be equipped with an FDR which shall record at least the first 78 parameters listed in table 1 of Appendix I. 4.1.7 All multi-engined turbine powered aeroplanes of a maximum certificated take-off mass of 5700kg or less for which the individual Certificate of airworthiness is first issued on or after 1 January 1990, should be equipped with an FDR which should record at least the first 16 parameters listed in table 1 of Appendix I. 4.1.8 All turbine-engined aeroplanes, for which the individual certificate of airworthiness was first issued before 1 January 1989, with a maximum certificated take-off mass of over 5 700 kg, except those in 4.1.2, shall be equipped with an FDR which shall record at least the first 5 parameters listed in table 1 of Appendix I. 4.1.9 All turbine-engined aeroplanes of a maximum certificated take-off mass of 5700kg or less for which the application for type certification is submitted on or after 1 January 2016 shall be equipped with: a) an FDR which shall record at least the first 16 parameters listed in Table 1 of Appendix I; or b) a Class C AIR or AIRS which shall record at least the flight path and speed parameters displayed to the pilot(s), as defined in 2.1.2.3 of Appendix I; or c) an ADRS which shall record at least the first 7 parameters defined listed in Table-4 of Appendix I. Note(1)- “The application for type certification is submitted refers to the date of application of the original “Type Certificate” for the aero plane type, not the date of certification of particular aeroplane variants or derivative models. Note(2)- AIR or AIRS classification is defined in 6.6.2. 4.1.10 All turbine-engined aeroplanes of a maximum certificated take-off mass of 5700kg or less for which the individual certificate of airworthiness is first issued on or after 1 January 2016 should be equipped with: a) an FDR which should record at least the first 16 parameters listed in Table 1 of Appendix I; or b) a Class C AIR or AIRS which should record at least the flight path and speed parameters displayed to the pilot(s), as defined in 2.1.2.3 of Rev. 2, 13th October 2022 4CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 Appendix I; or c) an ADRS which should record at least the first 7 parameters listed in table 4 of Appendix I. 4.1.11 All aeroplanes of a maximum certificated take-off mass of over 5 700 kg for which the application for type certification is submitted on or after 1stJanuary,2023 shall be equipped with an FDR capable of recording at least the 82 parameters listed in Table-1 of Appendix-I. 4.1.12All aeroplanes of a maximum certificated take-off mass of over 5700 kg for which the individual certificate of airworthiness is first issued on or after 1stJanuary,2023 shall be equipped with an FDR capable of recording at least the 82 parameters listed in Table-1 of Appendix-I 4.2 Aeroplane- General Aviation 4.2.1 All aeroplanes of a maximum certificated take-off mass of over 5700 kg for which the individual certificate of airworthiness is first issued on or after 1st January, 2005 shall be equipped with an FDR which shall record at least first 78 parameters listed in Table I of Appendix I. 4.2.2 All aeroplanes of a maximum certificated take-off mass of over 27000 kg for which the individual certificate of airworthiness is first issued on or after 1stJanuary, 1989 shall be equipped with an FDR which shall record at least first 32 parameters listed in Table I of Appendix I. 4.2.3 All aeroplanes of a maximum certificated take-off mass of over 5700 kg, up to and including 27000 kg, for which the individual certificate of airworthiness is first issued on or after 1st January, 1989, should be equipped with an FDR which shall record at least first 16 parameters listed in Table I of Appendix I. 4.2.4 All multi-engined turbine powered aeroplanes of a maximum certificated takeoff mass of 5700kg or less for which the individual certificate of airworthiness is first issued on or after 1st January, 1990, should be equipped with an FDR which should record at least the first 16 parameters listed in Table 1 of Appendix I. 4.2.5 All turbine-engined aeroplanes with a seating configuration of more than five passenger seats and a maximum certificated take-off mass of 5700 kg or less for which the individual certificate of airworthiness is first issued on or after 1 January 2016 should be equipped with: a) an FDR which should record at least the first 16 parameters in Table- 1 of Appendix-I; or Rev. 2, 13th October 2022 5CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 b) a Class C AIR or AIRS which should record at least the flight path and speed parameters displayed to the pilot(s), as defined in 2.1.2.2 of Appendix-I; or c) an ADRS which should record at least first 7parameters listed in Table-4 of Appendix-I. Note-AIR or AIRS classification is defined in Para 6.6. 4.2.6 All aeroplanes of a maximum certificated take-off mass of over 5 700 kg for which the application for type certification is submitted to a DGCA on or after1st January, 2023 shall be equipped with an FDR capable of recording at least the 82 parameters listed in Table-1 of Appendix-I. 4.2.7 All aeroplanes of a maximum certificated take-off mass of over 5700 kg for which the individual certificate of airworthiness is first issued on or after 1st January,2023 should be equipped with an FDR capable of recording at least the 82 parameters listed in Table-1 of Appendix-I. Note“The application for type certification that is submitted to a contracting state” refers to the date of application of the original “Type Certificate” for the aero plane type, not the date of certification of particular aeroplane variants or derivative models. 4.3 Helicopter- Commercial Air Transport & General Aviation 4.3.1 All helicopters of a maximum certificated take-off mass of over 7000kg,or having a passenger seating configuration of more than nineteen, for which the individual certificate of airworthiness is first issued on or after 1st January,1989 shall be equipped with an FDR which shall record at least the first 30 parameters in Table-2 of Appendix I. 4.3.2 All helicopters of a maximum certificated take-off mass of over 3175 kg, upto and including 7000kg, for which the individual certificate of airworthiness is first issued on or after 1 January 1989, shall be equipped with a FDR which should record at least the first 15 parameters in Table-2 of Appendix I; 4.3.3 All helicopters of a maximum certificated take-off mass of over 3175kg for which the individual certificate of airworthiness is first issued on or after 1January 2016 shall be equipped with an FDR which shall record at least the first 48 parameters listed in Table-2 of Appendix I. 4.3.4 All turbine-engined helicopters of a maximum certificated take-off mass of over 2250 kg, up to and including 3175 kg for which the application for type Rev. 2, 13th October 2022 6CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 certification was submitted to a contracting state on or after 1 January 2018 shall be equipped with: a) an FDR which shall record at least the first 48 parameters in Table-2 of Appendix I; or b) a Class C AIR or AIRS which shall record at least the flight path and speed parameters displayed to the pilot(s), as defined in Table 5 of Appendix I; or c) an ADRS which shall record the first 7 parameters listed in Table 5 of Appendix I. Note - The “application for type certification was submitted to a contracting state refers to the date of application of the original “Type Certificate” for the helicopter type, not the date of certification of particular helicopter variants or derivative models. 4.3.5 All helicopters of a maximum certificated take-off mass of 3175 kg or less for which the individual certificate of airworthiness is first issued on or after 1stJanuary 2018 should be equipped with: a) an FDR which should record at least the first 48 parameters listed in Table-2 of Appendix I; or b) a Class C AIR or AIRS which should record at least the flight path and speed parameters displayed to the pilot(s), as defined in Table 5 of Appendix I; or c) an ADRS which should record the first 7 parameters listed in Table 5 of Appendix I; Note. AIR or AIRS classification is defined in Para 6.6. 4.3.6 All helicopters of a maximum certificated take-off mass of over 3175kgfor which the application for type certificate is submitted to a contracting state on or after1stJanuary 2023 shall be equipped with an FDR capable of recording at least the first 53 parameters listed in table 2 of Appendix I. 4.3.7 All helicopters of a maximum certificated take-off mass of over 3175kg for which the individual certificate of airworthiness is first issued on or after 1stJanuary, 2023 shall be equipped with an FDR capable of recording at least the first 53 parameters listed in table 2 of Appendix I. 4.4 Recording Technology FDRs, ADRS, AIRs or AIRS shall not use engraving metal foil, frequency modulation (FM), photographic film or magnetic tape. Rev. 2, 13th October 2022 7CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 4.5 Duration 4.5.1 All FDRs (installed on aeroplanes) shall retain the information recorded during at least the last 25 hours of their operation with the exception of those installed on aeroplane referred in 4.1.7 for which the FDR shall retain the information recorded during at least the last 30 minutes of its operations and in addition sufficient information from the preceding take off for calibration purpose. 4.5.2 All FDRs (installed on helicopters) shall retain the information recorded during at least the last 10 hours of their operation. 5. COMBINATION RECORDERS 5.1 Combination recorders (FDR/CVR) may be used to meet the flight recorder equipage requirements in this CAR. 5.2 All aeroplanes of a maximum certificated take-off mass of over 5700kg for which the application for type certification is submitted to a contracting state on or after 1 January 2016, and which are required to be equipped with both a CVR and an FDR, should be equipped with two combination recorders (FDR/CVR). 5.3 All aeroplanes of a maximum certificated take-off mass of over 15000kg for which the application for type certification is submitted to a contracting state on or after 1 January 2016, and which are required to be equipped with both a CVR and an FDR, shall be equipped with two combination recorders (FDR/CVR). One recorder shall be located as close to the cockpit as practicable and the other recorder located as far aft as practicable. 5.4 All aeroplanes of a maximum certificated take-off mass over 5700kg, required to be equipped with an FDR and a CVR, may alternatively be equipped with two combination recorders (FDR/CVR). Note- The requirement of 5.1 5.2, 5.3 and 5.4 may be satisfied by equipping the aeroplanes with two combination recorders (one forward and one aft) or separate devices. 5.5 All multi- engined turbine –powered aeroplanes of a maximum certificated take-off mass of 5700kg or less, required to be equipped with an FDR and a CVR, may alternatively be equipped with one combination recorder(FDR/CVR). Rev. 2, 13th October 2022 8CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 5.6 Automatic Deployable Flight Recorder (ADFR) The following requirements shall apply to an ADFR: - deployment shall take place when the aeroplane structure has been significantly deformed; - deployment shall take place when an aeroplane sinks in water; - ADFR shall not be capable of manual deployment; - the ADFR shall be able to float on water; - the ADFR deployment shall not compromise the safe continuation of the flight; - the ADFR deployment shall not significantly reduce the chance of survival of the recorder and of successful transmission by its ELT; - the ADFR deployment shall not release more than one piece; - an alert shall be made to the flight crew when the ADFR is no longer captive tothe aircraft. - the flight crew shall have no means to disable ADFR deployment when the aircraft is airborne; - the ADFR shall contain an integrated ELT, which shall activate automatically during the deployment sequence. Such ELT may be of a type that is activated inflight and provides information from which a position can be determined; and - the integrated ELT of an ADFR shall satisfy the same requirements as an ELT required to be installed on an aeroplane. The integrated ELT shall at least have the same performance as the fixed ELT to maximize detection of the transmitted signal. Note 1 - Refer to the Manual on Location of Aircraft in Distress and Flight Recorder Data Recovery (Doc 10054) for more information on ADFR. Note 2 - If an integrated ELT of a type that is activated in flight is used within an ADFR it could be a means to comply with requirements of Location of Aircraft in Distress (Doc 10054). 6. DATA LINK RECORDERS 6.1 Applicability 6.1.1 All aeroplanes and helicopters for which the individual certificate of airworthiness are first issued on or after 1 January 2016, which use any of the data link communications applications referred to in para 6.4.2 and are required to carry a CVR, shall record the data link communications messages Rev. 2, 13th October 2022 9CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 on a crash protected flight recorder. 6.1.2 All aeroplanes and helicopter for which the individual certificate of airworthiness was first issued before 1 January 2016, that are required to carry a CVR and are modified on or after 1 January 2016 to use any of the data link communications applications referred to in para 6.4.2 and shall record the data link communication messages on a crash protected flight recorder unless the installed data link communications equipment is compliant with a type certificate issued or aircraft modification first approved prior to 1 January 2016. Note 1- A Class B AIR (Airborne Image Recorder) could be a means for recording data link communications applications messages to and from the aeroplanes/ helicopters where it is not practical or is prohibitively expensive to record those data link communications applications messages on FDR or CVR. Note 2.— The “aircraft modifications” refer to modifications to install the data link communications equipment on the aircraft (e.g. structural, wiring). 6.1.3 All aeroplanes and helicopters for which the individual certificate of airworthiness was first issued before 1 January 2016, that are required to carry a CVR and are modified on or after 1 January 2016 to use any of the data link communications applications referred to in para 6.4.2 should record the data link communications messages on a crash-protected flight recorder. 6.2Duration The minimum recording duration shall be equal to the duration of the CVR. 6.3 Correlation Data link recording shall be able to be correlated to the recorded cockpit audio. 6.4 Applications to be recorded 6.4.1 Where the aircraft/helicopter flight path is authorized or controlled through the use of data link messages, all data link messages, both uplinks (to the aircraft/helicopter) and downlinks (from the aircraft/helicopter), shall be recorded on the aircraft/helicopter. As far as practicable, the time the messages were displayed to the flight crew and the time of the responses shall be recorded. Rev. 2, 13th October 2022 10CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 6.4.2 Messages applying to the applications listed at Table-3 of Appendix-I shall be recorded. Applications without the asterisk (*) are mandatory applications which shall be recorded regardless of the system complexity. Applications with an (*) shall be recorded only as far as is practicable given the architecture of the system. Note-Sufficient information to derive the content of the data link communications message and the time the messages were displayed to the flight crew is needed to determine an accurate sequence of events on board the aircraft/helicopter. 6.5 Flight Crew-Machine Interface Recordings 6.5.1 Applicability 6.5.1.1 All aeroplanes of a maximum take-off mass of over 27 000 kg for which the application for type certification is submitted on or after 1 January 2023 shall be equipped with a crash-protected flight recorder which shall record the information displayed to the flight crew from electronic displays, as well as the operation of switches and selectors by the flight crew as defined in Para 6.6. 6.5.1.2 All aeroplanes of a maximum take-off mass of over 5700 kg, up to and including 27 000 kg, for which the application for type certification is submitted on or after 1 January 2023 should be equipped with a crash- protected flight recorder which should record the information displayed to the flight crew from electronic displays, as well as the operation of switches and selectors by the flight crew, as defined in Para 6.6. 6.5.2 Duration The minimum flight crew-machine interface recording duration shall be at least for the last two hours. 6.5.3 Correlation Flight crew-machine interface recordings shall be able to be correlated to the recorded cockpit audio. 6.6 Start and stop logic Rev. 2, 13th October 2022 11CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 6.6.1The Airborne Image Recorder (AIR) and Airborne Image Recording System (AIRS) shall start to record prior to the aeroplane/ helicopter moving under its own power and record continuously until the termination of the flight when the aeroplane/ helicopter is no longer capable of moving under its own power. In addition, depending on the availability of electrical power, the AIR or AIRS shall start to record as early as possible during the cockpit checks prior to engine start at the beginning of the flight until the cockpit checks immediately following engine shutdown at the end of the flight. 6.6.2 Classes 6.6.2.1 A Class “A” AIR or AIRS captures the general cockpit area in order to provide data supplemental to conventional flight recorders. 6.6.2.2 A Class “B” AIR or AIRS captures data link message displays. 6.6.2.3 A Class “C” AIR or AIRS captures instruments and control panels. Note 1-There are no provisions for Class “A” AIRs or AIRS in this CAR. Note2- A Class C AIR or AIRS may be considered as a means for recording flight data where it is not practical or is prohibitively expensive to record on an FDR or an ADRS or where an FDR is not required. Note3- To respect crew privacy, the cockpit area view may be designed as far as practical to exclude the head and shoulders of crew members whilst seated in their normal operating position. 6.7 Applications to be recorded 6.7.1 The operation of switches and selectors and the information displayed to the flight crew from electronic displays shall be captured by sensors or other electronic means. 6.7.2 The recording of operation of switches and selectors by the flight crew shall include the following: — any switch or selector that will affect the operation and the navigation of the aircraft; and — selection of normal and alternate systems. 6.7.3 The recording of the information displayed to the flight crew from electronic Rev. 2, 13th October 2022 12CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 displays shall include the following: — primary flight and navigation displays; — aircraft system monitoring displays; — engine indication displays; — traffic, terrain, and weather displays; — crew alerting systems displays; — stand-by instruments; and — installed EFB to the extent it is practical. 6.7.4 If image sensors are used, the recording of such images shall not capture the head and shoulders of the flight crew members whilst seated in their normal operating position 7.Flight Recorder Data Recovery 7.1 All aeroplanes of a maximum certificated take-off mass of over 27000 kg and authorized to carry more than nineteen passengers for which the application for type certification is submitted to a Contracting State on or after 1 January 2021, shall be equipped with a means approved by the State of the Operator, to recoverflight recorder data and make it available in a timely manner. 7.2 In approving the means to make flight recorder data available in a timely manner, the State of the Operator shall take into account the following: a) the capabilities of the operator; b) overall capability of the aeroplane and its systems as certified by the State of Design; c) the reliability of the means to recover the appropriate CVR channels and appropriate FDR data; and d) specific mitigation measures. Note— Guidance on approving the means to make flight recorder data available in a timely manner is contained in the Manual on Location of Aircraft in Distress and Flight Recorder Data Recovery (Doc 10054). 8. FLIGHT RECORDERS — GENERAL 8.1Construction and Installation 8.1.1 Flight recorders shall be constructed, located and installed so as to provide maximum practical protection for the recordings in order that the recorded Rev. 2, 13th October 2022 13CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 information may be preserved, recovered and transcribed. Flight recorders shall meet the prescribed crashworthiness and fire protection specifications. 8.2 Operation 8.2.1 Flight recorders shall not be switched off during flight time. 8.2.2 To preserve flight recorder records, flight recorders shall be deactivated upon completion of flight time following an accident or incident. The flight recorders shall not be reactivated before their disposition as determined in accordance with the instructions issued by DGCA. Note1 - The need for removal of the flight recorder records from the aircraft will be determined by DGCA with due regard to the seriousness of an occurrence and the circumstances, including the impact on the operation. Note2 - The operator’s responsibilities regarding the retention of flight recorder records are contained in 8.5. 8.3 Continued Serviceability Operational checks and evaluations of recordings from the flight recorder systems shall be conducted to ensure the continued serviceability of the recorders. Note- Procedure for inspection of flight recorder systems are given in Appendix-I. 8.4 Flight Recorder Electronic Documentation It is recommended that the documentation requirement concerning FDR and ADRS parameters provided by operators to accident investigation authorities should be in electronic format and take account of industry specifications. Note- Industry specification for documentation concerning flight recorder parameters may be found in the ARINC 647A, Flight Recorder Electronic Documentation, or equivalent document. 8.5 Flight Recorder Records The pilot in-command, and/or owner/operator, shall ensure, to the extent possible, in the event the aeroplane/ helicopter becomes involved in an accident or incident, the preservation of all related flight recorder records and, if necessary, the associated flight recorders, and their retention in safe custody pending their disposition in accordance with instruction issued by DGCA. Rev. 2, 13th October 2022 14CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 (Arun Kumar) Director General of Civil Aviation Rev. 2, 13th October 2022 15CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 APPENDIX- I GUIDANCE ON FLIGHT RECORDERS 1. GENERAL REQUIREMENTS 1.1 Non-deployable flight recorder containers shall be painted a distinctive orange colour. 1.2 Non-deployable crash-protected flight recorder containers shall: a) carry reflective material to facilitate their location; and b) have securely attached an automatically activated underwater locating device operating at a frequency of 37.5 kHz. At the earliest practicable date but not later than 1 January 2018, this device shall operate for a minimum of 90 days. 1.3 Automatic deployable flight recorder containers shall: a) be painted a distinctive orange colour, however the surface visible from outside the aircraft may be of another colour; b) carry reflective material to facilitate their location; and c) have an integrated automatically activated ELT. 1.4 The flight recorder systems shall be installed so that: a) the probability of damage to the recordings is minimized; b) there is an aural or visual means for pre-flight checking that the flight recorder systems are operating properly; and c) if the flight recorder systems havean erasure device, the installation shall be designedto prevent operation of the device during flight time or crash impact; and d) for aeroplanes for which the individual certificate of airworthiness is first issued on or after 1 January 2023, a flight crew-operated erase function shall be provided onthe flight deck which, when activated, modifies the recording of a CVR and AIR so that it cannot be retrieved using normal replay or copying techniques. The installation shall be designed to prevent activation during Rev. 2, 13th October 2022 16CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 flight. In addition, the probability of an inadvertent activation of an erase function during an accident shall also be minimized. Note— The erase function is intended to prevent access to CVR and AIR recordings by normal replay or copying means, but would not prevent accident investigation authorities access to such recordings by specialized replay or copying techniques. 1.5 The crash protected flight recorders shall be installed so that they receive electrical power from a bus that provides the maximum reliability for operation of the flight recorders without jeopardizing service to essential or emergency loads. 1.6 The lightweight flight recorders shall be connected to a power source having the characteristics which ensure proper and reliable recording in the operational environment. 1.7 The flight recorder systems, when tested by methods approved by the appropriate certificating authority, shall be demonstrated to be suitable for the environmental extremes over which they are designed to operate. 1.8 Means shall be provided for an accurate time correlation between the flight recorder systems recordings. 1.9 The Flight recorder system manufacturer shall provide the appropriate certificating authority with the following information in respect of the flight recorder systems: a) manufacturer’s operating instructions, equipment limitations and installation procedures; b) parameter origin or source and equations which relate counts to units of measurement; and c) manufacturer’s test reports and d) detailed information to ensure the continued serviceability of the flight recorder system 1.10 The holder of the airworthiness approval for the installation design of the flight recorder system shall make available the relevant continuing airworthiness information to the operator of the aeroplane to be incorporated in the continuing airworthiness maintenance programme. This continuing airworthiness information shall cover in detail all the tasks required to ensure the continued serviceability of the flight recorder system. Note 1.— The flight recorder system is composed of the flight recorder as well as any dedicated sensors, hardware and software that provide information required per this Appendix. Note 2.— Conditions related to the continued serviceability of a flight recorder system are defined in Section 6 of this Appendix. The Manual Rev. 2, 13th October 2022 17CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 on Flight Recorder System Maintenance (FRSM) (Doc 10104) provides guidance on maintenance tasks associated with flight recorder systems. 2. FLIGHT DATA RECORDER (FDR) AND AIRCRAFT DATA RECORDINGSYSTEMS (ADRS) 2.1 Aeroplane:- 2.1.1 Start and stop logic The FDR or ADRS shall start to record prior to the aeroplane moving under its own power and record continuously until the termination of the flight when the aeroplane is no longer capable of moving under its own power. 2.1.2 Parameters to be recorded 2.1.2.1 The parameters that satisfy the requirements for FDRs are listed in the table 1 below. The number of parameters to be recorded shall depend on aero plane complexity. The parameters without an asterisk (*) are mandatory parameters which shall be recorded regardless of aeroplane complexity. In addition, the parameters designated by an asterisk (*) shall be recorded if an information data source for the parameter is used by aeroplane systems or the flight crew to operate the aeroplane. However, other parameters may be substituted with due regard to the aeroplane type and the characteristics of the recording equipment. 2.1.2.2 If further FDR recording capacity is available, recording of the following additional information shall be considered: a) Operational information from electronic display systems, such as electronic flight instrument systems (EFIS), electronic centralized aircraft monitor (ECAM) and engine indication and crew alerting system (EICAS). Use the following order of priority: 1) parameters selected by the flight crew relating to the desired flight path, e.g. barometric pressure setting, selected altitude, selected airspeed, decision height, and auto flight system engagement and mode indications if not recorded from another source; 2) display system selection/status, e.g. SECTOR, PLAN, ROSE, NAV, WXR, COMPOSITE, COPY, ETC.; 3) warnings and alerts; and Rev. 2, 13th October 2022 18CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 4) the identity of displayed pages for emergency procedures and checklists; and b) retardation information including brake application for use in the investigation of landing overruns and rejected take-offs. 2.1.2.3The parameters that satisfy the requirements for flight path and speed as displayed to the pilot(s) are listed below. The parameters without an (*) are mandatory parameters which shall be recorded. In addition, the parameters designated by an (*) shall be recorded if an information source for the parameter is displayed to the pilot and is practicable to record: — Pressure altitude — Indicated airspeed or calibrated airspeed — Heading (primary flight crew reference) — Pitch attitude — Roll attitude — Engine thrust/power — Landing-gear status* — Total or outside air temperature* — Time* — Navigation data*: drift angle, wind speed, wind direction, latitude/longitude — Radio altitude* 2.1.2.4 The parameters that satisfy the requirements for ADRS are listed in Table 4. 2.1.2.5The measurement range, recording interval and accuracy of parameters on installed equipment shall be verified by methods approved by the appropriate certificating authority. 2.1.2.6 Documentation concerning parameter allocation, conversion equations, periodic calibration and other serviceability/maintenance information shall be maintained by the operator. The documentation needs to be sufficient to ensure that accident investigation authorities have the necessary information to read out the data in engineering units. 2.2 Helicopters 2.2.1 Start and stop logic The FDR or ADRS shall start to record prior to the helicopter moving under its own power and record continuously until the termination of the flight when the helicopter is no longer capable of moving under its own power. Rev. 2, 13th October 2022 19CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 2.2.2 Parameters to be recorded 2.2.2.1The parameters that satisfy the requirements for FDRs, are listed in Table 2.The number of parameters to be recorded shall depend on helicopter complexity. The parameters without an asterisk (*)are mandatory parameters which shall be recorded regardless of helicopter complexity. In addition, the parameters designated by an asterisk (*) shall be recorded if an information data source for the parameter is used by helicopter systems or the flight crew to operate the helicopter. However, other parameters may be substituted with due regard to the helicopter type and the characteristics of the recording equipment. 2.2.2.2 The following parameters shall satisfy the requirements for flight path and speed: — Pressure altitude — Indicated airspeed — Outside air temperature — Heading — Normal acceleration — Lateral acceleration — Longitudinal acceleration (body axis) — Time or relative time count — Navigation data*: drift angle, wind speed, wind direction, latitude/longitude — Radio altitude*. 2.2.2.3 If further FDR recording capacity is available, recording of the following additional information shall be considered: a) additional operational information from electronic displays, such as electronic flight instrument systems (EFIS), electronic centralized aircraft monitor (ECAM) and engine indication and crew alerting system (EICAS); and b) additional engine parameters (EPR, N1, fuel flow, etc.). 2.2.2.4The parameters that satisfy the requirements for ADRS are listed in Table 5. 2.2.2.5The measurement range, recording interval and accuracy of parameters on installed equipment is usually verified by methods approved by the appropriate certificating authority. 2.2.2.6 Documentation concerning parameter allocation, conversion equations, periodic calibration and other serviceability/maintenance information Rev. 2, 13th October 2022 20CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 shall be maintained by the operator/owner. The documentation shall be sufficient to ensure that accident investigation authorities have the necessary information to read out the data in engineering units 3. RECORDING INTERVAL The flight recorders shall start to record prior to the aeroplane/helicopter moving under its own power and record continuously until the termination of the flight when the aeroplane/helicopter is no longer capable of moving under its own power. 4. INSPECTION OF FLIGHT RECORDER SYSTEM 4.1 Prior to the first flight of the day, the built-in test features for the flight recorders and flight data acquisition unit (FDAU), when installed, shall be monitored by manual and/or automatic checks. 4.2 FDR systems or ADRS and AIR systems or AIRS shall have recording inspection intervals of one year; subject to the approval from the appropriate regulatory authority, this period may be extended to two years provided these systems have demonstrated a high integrity of serviceability and self- monitoring. DLR systems or DLRS shall have recording inspection intervals of two years; subject to the approval from the appropriate regulatory authority, this period may be extended to four years provided these systems have demonstrated high integrity of serviceability and self-monitoring. 4.3 Recording inspections shall be carried out as follows: a) an analysis of the recorded data from the flight recorders shall ensure that the recorder operates correctly for the nominal duration of the recording; b) The FDR or ADRS recording from a complete flight shall be examined in engineering units to evaluate the validity of all recorded parameters. Particular attention shall be given to parameters from sensors dedicated to the FDR or ADRS. Parameters taken from the aircraft’s electrical bus system need not be checked if their serviceability can be detected by other aircraft systems; c) the readout facility shall have the necessary software to accurately convert the recorded values to engineering units and to determine the status of discrete signals; d) an examination of the recorded signal on the CVR or the CARS shall be carried out by replay of the CVR or CARS recording. While installed in the aircraft, the CVR or CARS shall record test signals from each aircraft source Rev. 2, 13th October 2022 21CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 and from relevant external sources to ensure that all required signals meet intelligibility standards; e) where practicable, during the examination, a sample of in-flight recordings of the CVR or CARS shall be examined for evidence that the intelligibility of the signal is acceptable; and f) an examination of the recorded images on the AIR or AIRS shall be carried out by replay of the AIR or AIRS recording. While installed in the aircraft, the AIR or AIRS shall record test images from each aircraft source and from relevant external sources to ensure that all required images meet recording quality standards. g) an examination of the recorded messages on the DLR or DLRS shall be carried out by replay of the DLR or DLRS recording. 4.4 A flight recorder system shall be considered unserviceable if there is a significant period of poor quality data, unintelligible signals, or if one or more of the mandatory parameters is not recorded correctly. 4.5 A report of the recording system inspection shall be made available on request to DGCA for monitoring purposes. 4.6 Calibration of the FDR system: a) for those parameters which have sensors dedicated only to the FDR and are not checked by other means, recalibration shall be carried out at least every five years or in accordance with the recommendations of the sensor manufacturer to at an interval determined by the continuing airworthiness information for the FDR system. In the absence of such information, a recalibration shall be carried out at least every five years. The recalibration shall determine any discrepancies in the engineering conversion routines for the mandatory parameters and to ensure that parameters are being recorded within the calibration tolerances; and b) When the parameters of altitude and airspeed are provided by sensors that are dedicated to the FDR system, there shall be a recalibration performed at an interval determined by the continuing airworthiness information for the FDR system. In the absence of such information, a recalibration shall be carried out at least every two years.as recommended by the sensor manufacturer, or at least every two years. Rev. 2, 13th October 2022 22CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 Appendix - I Table-1 PARAMETER CHARACTERISTICS FOR FLIGHT DATA RECORDERS AEROPLANES Maximum Accuracy limits sampling and (sensor input Serial Measurement Recording Parameter Applicability recording compared number range resolution interval to FDR read- (seconds) out) 1 Time (UTC when available, 24 hours 4 ±0.125% /h 1s otherwise relative time count or GNSS time sync) 2 Pressure-altitude –300 m (–1 1 ±30 m to ±200 m 1.5 m (5 ft) 000 ft) to (±100 ft to ±700 maximum ft) certificated altitude of aircraft +1 500 m (+5 000 ft) 3 Indicated airspeed or 95 km/h (50 kt) 1 ±5% 1 kt (0.5 kt calibrated airspeed to max ±3% recommended) VSo (Note 1) VSoto 1.2 VD (Note 2) 4 Heading (primary flight 360° 1 ±2° 0.5° crew reference) 5 Normal acceleration Application for –3 g to +6 g 0.125 ±1% of maximum 0.004 g (Note8) type certification range excluding is submitted on or datum error of before 1 January ±5% 2016 Application for –3 g to +6 g 0.0625 ±1% of maximum 0.004 g type certification range excluding is submitted on or datum error of after 1 January ±5% 2016 6 Pitch attitude ±75° or usable 0.25 ±2° 0.5° range whichever is greater 7 Roll attitude ±180° 0.25 ±2° 0.5° 8 Radio transmission keying On-off (one 1 discrete) 9 Power on each engine Full range 1 (per ±2% 0.2% of full (Note 4 -3) engine) range or the resolution required to operate the aircraft 10* Trailing edge flap and Full range or 2 ±5% or as pilot’s 0.5% of full cockpit each indicator range or the control selection discrete resolution position required to operate the aircraft 11* Leading edge flap and Full range or 2 ±5% or as pilot’s 0.5% of full cockpit each indicator range or the control selection discrete resolution position required to operate the aircraft 12* Thrust reverser position Stowed, in 1 (per transit, engine Rev. 2, 13th October 2022 23CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 Maximum Accuracy limits sampling and (sensor input Serial Measurement Recording Parameter Applicability recording compared number range resolution interval to FDR read- (seconds) out) and reverse 13* Ground spoiler/speed brake Full range or 1 ±2% unless 0.2% of full selection (selection and each higher accuracy range position) discrete uniquely required position 14 Outside air temperature Sensor range 2 ±2°C 0.3°C 15* Autopilot/auto A suitable 1 throttle/AFCS combination mode and engagement of discretes status 16 Longitudinal acceleration Application for ±1 g 0.25 ±0.015 g 0.004 g (Note 8) type certification excluding a submitted before datum error of 1 January 2016 ±0.05 g Application for ±1 g 0.0625 ±0.015 g 0.004 g type certification excluding a submitted on or datum error of after 1 January ±0.05 g 2016 17 Lateral acceleration (Note 3 Application for ±1 g 0.25 ±0.015 g 0.004 g 8) type certification excluding a submitted to a datum error of Contracting State ±0.05 g before 1 January 2016 Application for ±1 g 0.0625 ±0.015 g 0.004 g type certification excluding a submitted to a datum error of Contracting State ±0.05 g on or after 1 January 2016 18 Pilot input and/or control Application for Full range 0.25 ±2° unless higher 0.2% of full surface position-primary type certification accuracy range or as controls (pitch, roll, yaw) submitted before uniquely required installed (Notes 4 and 8) 1 January 2016 Application for Full range 0.125 ±2° unless higher 0.2% of full type certification accuracy range or as submitted on or uniquely required installed after 1 January 2016 19 Pitch trim position Full range 1 ±3% unless 0.3% of full higher accuracy range or as uniquely required installed 20* Radio altitude –6 m to 750 m 1 ±0.6 m (±2 ft) or 0.3 m (1 ft) (–20 ft to 2 500 ±3% below 150 m ft) whichever is (500 ft) 0.3 m (1 greater below 150 ft) + 0.5% of full m range above 150 (500 ft) and ±5% m (500 ft) above 150 m (500 ft) 21* Vertical beam deviation Signal range 1 ±3% 0.3% of full (ILS/ GNSS/GLS glide range path, MLS elevation, IRNAV/IAN vertical deviation) 22* Horizontal beam deviation Signal range 1 ±3% 0.3% of full (ILS/GNSS/GLS localizer, range MLS azimuth, IRNAV/IAN lateral deviation) 23 Marker beacon passage Discrete 1 24 Master warning Discrete 1 Rev. 2, 13th October 2022 24CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 Maximum Accuracy limits sampling and (sensor input Serial Measurement Recording Parameter Applicability recording compared number range resolution interval to FDR read- (seconds) out) 25 Each NAV receiver Full range 4 As installed frequency selection (Note5) 26* DME 1 and 2 distance 0 – 370 km 4 As installed 1 852 m (1 NM) (includes Distance to (0 – 200 NM) runway threshold (GLS) and Distance to missed approach point (IRNAV/IAN)) (Notes 5 and 6) 27 Air/ground status Discrete 1 28* GPWS/TAWS/GCAS Discrete 1 status (selection of terrain display mode including pop-up display status) and (terrain alerts, both cautions and warnings, and advisories) and (on/off switch position) 29* Angle of attack Full range 0.5 As installed 0.3 % of full range 30* Hydraulics, each system Discrete 2 0.5% of full (low pressure) range 31* Navigation data As installed 1 As installed (latitude/longitude, ground speed and drift angle) (Note 7) 32* Landing gear and gear Discrete 4 As installed selector position 33* Groundspeed As installed 1 Data should be 1 kt obtained from the most accurate system 34 Brakes (left and right brake (Maximum 1 ±5% 2% of full range pressure, left and right metered brake brake pedal position) range, discretes or full range) 35* Additional engine Engine fuel As installed Each engine As installed 2% of full range parameters (EPR, N1, metering valve each second indicated vibration level, position: N2, EGT, fuel flow, fuel Application for cut-off lever position, N3, type certification engine fuel metering valve is submitted on or position) after 1 January 2023 36* TCAS/ACAS (traffic alert Discrete 1 As installed and collision avoidance system) 37* Wind shear warning Discrete 1 As installed 38* Selected barometric setting As installed 64 As installed 0.1 mb (0.01 in- (pilot, co-pilot) Hg) 39* Selected altitude (all pilot As installed 1 As installed Sufficient to selectable modes of determine crew operation) selection 40* Selected speed (all pilot As installed 1 As installed Sufficient to selectable modes of determine crew operation) selection 41* Selected Mach (all pilot As installed 1 As installed Sufficient to selectable modes of determine crew operation) selection 42* Selected vertical speed (all As installed 1 As installed Sufficient to Rev. 2, 13th October 2022 25CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 Maximum Accuracy limits sampling and (sensor input Serial Measurement Recording Parameter Applicability recording compared number range resolution interval to FDR read- (seconds) out) pilot selectable modes of determine crew operation) selection 43* Selected heading (all pilot As installed 1 As installed Sufficient to selectable modes of determine crew operation) selection 44* Selected flight path (all 1 As installed pilot selectable modes of operation) (course/DSTRK, path angle, final approach path (IRNAV/IAN)) 45* Selected decision height As installed 64 As installed Sufficient to determine crew selection 46* EFIS display format (pilot, Discrete(s) 4 As installed co-pilot) 47* Multi-function/engine/alerts Discrete(s) 4 As installed display format 48* AC electrical bus status Discrete(s) 4 As installed 49* DC electrical bus status Discrete(s) 4 As installed 50* Engine bleed valve position Discrete(s) 4 As installed 51* APU bleed valve position Discrete(s) 4 As installed 52* Computer failure Discrete(s) 4 As installed 53* Engine thrust command As installed 2 As installed 54* Engine thrust target As installed 4 As installed 2% of full range 55* Computed centre of gravity As installed 64 As installed 1% of full range 56* Fuel quantity in CG trim As installed 64 As installed 1% of full range tank 57* Head up display in use As installed 4 As installed 58* Para visual display on/off As installed 1 As installed 59* Operational stall protection, As installed 1 As installed stick shaker and pusher activation 60* Primary navigation system As installed 4 As installed reference (GNSS, INS, VOR/DME, MLS, Loran C, localizer glideslope) 61* Ice detection As installed 4 As installed 62* Engine warning each As installed 1 As installed engine vibration 63* Engine warning each As installed 1 As installed engine over temperature 64* Engine warning each As installed 1 As installed engine oil pressure low 65* Engine warning each As installed 1 As installed engine over speed 66* Yaw trim surface position Full range 2 ±3% unless 0.3% of full higher accuracy range uniquely required 67* Roll trim surface position Full range 2 ±3% unless 0.3% of full higher accuracy range uniquely required 68* Yaw or sideslip angle Full range 1 ±5% 0.5° 69* De-icing and/or anti-icing Discrete(s) 4 systems selection 70* Hydraulic pressure (each Full range 2 ±5% 100 psi system) 71* Loss of cabin pressure Discrete 1 72* Cockpit trim control input Full range 1 ±5% 0.2% of full range position, Pitch or as installed 73* Cockpit trim control input Full range 1 ±5% 0.2% of full position, Roll range or as Rev. 2, 13th October 2022 26CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 Maximum Accuracy limits sampling and (sensor input Serial Measurement Recording Parameter Applicability recording compared number range resolution interval to FDR read- (seconds) out) installed 74* Cockpit trim control input Full range 1 ±5% 0.2% of full position, Yaw range or as installed 75* All cockpit flight control Full range 1 ±5% 0.2% of full input forces (control wheel, (±311 N (±70 range or as control column, rudder lbf), ± 378 N installed pedal) (±85 lbf), ± 734 N (±165 lbf)) 76* Event marker Discrete 1 77* Date 365 days 64 78* ANP or EPE or EPU As installed 4 As installed 79* Cabin pressure altitude Application for As installed (0 1 As installed 100 ft type certification ft to submitted to on or 40 000 ft after 1 January recommended) 2023 80* Aeroplane computed Application for As installed 64 As installed 1% of full range weight type certification submitted on or after 1 January 2023 81* Flight director command Application for Full range 1 ± 2° 0.5° type certification submitted on or after 1 January 2023 82* Vertical speed Application for As installed 0.25 As installed 16 ft/min type certification (32 ft/min submitted on or recommended) after 1 January 2023 Notes.— 1. VSostalling speed or minimum steady flight speed in the landing configuration is in Section “Abbreviations and Symbols”. 2. VD design diving speed. 3. Record sufficient inputs to determine power. 4. For aeroplanes with control systems in which movement of a control surface will back drive the pilot’s control, ‘‘or’’ applies. For aeroplanes with control systems in which movement of a control surface will not back drive the pilot’s control, ‘‘and’’ applies. In aeroplanes with split surfaces, a suitable combination of inputs is acceptable in lieu of recording each surface separately. In aeroplanes with independent pilot input on primary controls, each pilot input on primary controls needs to be recorded separately. 5. If signal available in digital form. 6. Recording of latitude and longitude from INS or other navigation system is a preferred alternative. 7. If signals readily available. 8. It is not intended that aeroplanes issued with an individual certificate of airworthiness before 1 January 2016 be modified to meet the measurement range, maximum sampling and recording interval, accuracy limits or recording resolution description detailed in this Appendix. Table-2 PARAMETER CHARACTERISTICS FOR FLIGHT DATA RECORDERS - HELICOPTER Maximum Accuracy limits sampling and (sensor input Serial Measurement Recording Parameter Applicability recording compared number range resolution interval to FDR read- (seconds) out) 1 Time (UTC when 24 hours 4 ±0.125% /h 1 s available, Rev. 2, 13th October 2022 27CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 Maximum Accuracy limits sampling and (sensor input Serial Measurement Recording Parameter Applicability recording compared number range resolution interval to FDR read- (seconds) out) otherwise relative time count or GNSS time sync) 2 Pressure-altitude –300 m (–1000 1 ±30 m to ±200 m 1.5 m (5 ft) ft) to (±100 ft to ±700 maximum ft) certificated altitude of aircraft +1500 m (+5 000 ft) 3 Indicated airspeed As installed 1 ±3% 1 kt (0.5 kt pilot display recommended) measuring system 4 Heading 360° 1 ±2° 0.5° 5 Normal acceleration –3 g to +6 g 0.125 ±0.09 g excluding 0.004 g (Note8) a datum error of ±0.05g 6 Pitch attitude ±75° or 100% of 0.5 ±2° 0.5° usable range whichever is greater 7 Roll attitude ±180° 0.5 ±2° 0.5° 8 Radio transmission On-off (one 1 keying discrete) 9 Power on each engine Full range 1 (per ±2% 0.1% of full (Note 4 -3) engine) range 10 Main Rotor Main Rotor Speed 50-130% 0.51 ±2% 0.3% of full range Rotor Brake Discrete 11 Pilot input and/or Full range 0.5 (0.25 ±2% unless 0.5% of control surface recommended) higher accuracy operating range – primary uniquely required controls (collective pitch, longitudinal cyclic pitch, lateral cyclic pitch, tail rotor pedal) 12 Hydraulics, each system Discrete 1 (low pressure and selection) 13 Outside air temperature Sensor range 2 ±2°C 0.3°C 14* Autopilot/auto A suitable 1 throttle/AFCS combination mode and engagement of discretes status 15* Stability Augmentation Discrete 1 System Engagement 16* Main Gearbox Oil As installed 1 As installed 6.895 kN/m2 (1 Pressure psi) 17* Main Gearbox Oil As installed 2 As installed 1oC Temperature 18 Yaw Rate ±400o /second 0.25 ±1.5% maximum ±2o /s range excluding datum error of ±5% 19* Sling Load Force 0 to 200% of 0.5 ±3% of maximum 0.5% for Rev. 2, 13th October 2022 28CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 Maximum Accuracy limits sampling and (sensor input Serial Measurement Recording Parameter Applicability recording compared number range resolution interval to FDR read- (seconds) out) Certified Load range maximum certified load 20 Longitudinal ±1 g 0.25 ±0.015 g 0.004 g acceleration excluding a datum error of ±0.05 g 21 Lateral acceleration ±1 g 0.25 ±0.015 g 0.004 g (Note 8) excluding a datum error of ±0.05 g 22* Radio altitude –6 m to 750 m 1 ±0.6 m (±2 ft) or 0.3 m (1 ft) (–20 ft to 2500 ±3% whichever is below 150 m ft) greater below (500 ft) 0.3 m (1 150 m ft) + 0.5% of full (500 ft) and ±5% range above 150 above 150 m(500 m (500 ft) ft) 23* Vertical beam deviation Signal range 1 ±3% 0.3% of full range 24* Horizontal beam Signal range 1 ±3% 0.3% of full deviation range 25 Marker beacon passage Discrete 1 26 Warnings Discrete (s) 1 27 Each Navigation Sufficient to 4 As installed receiver frequency determine selection selected frequency 28* DME 1 and 2 distances 0 – 370 km 4 As installed 1 852 m (1 NM) (0 – 200 NM) 29* Navigation data As installed 2 As installed As installed (latitude/longitude, ground Speed, drift angle, wind speed, wind direction) 30* Landing gear and gear Discrete 4 selector position 31* Engine Exhaust Gas As installed 1 As installed Temperature (T) 4 32* Turbine Inlet As installed As installed Temperature (TIT/ITT) 33* Fuel Contents As installed 4 As installed 34* Altitude Rate As installed 1 As installed 35* Ice Detection As installed 4 As installed 36* Helicopter Health and As installed As installed Usage Monitor System 37 Engine Control Modes Discrete 1 38* Selected barometric As installed 64 (4 As installed 0.1 mb (0.01 in- setting (pilot, co-pilot) recommended) Hg) 39* Selected altitude (all As installed 1 As installed Sufficient to pilot selectable modes determine crew of operation) selection 40* Selected speed (all pilot As installed 1 As installed Sufficient to selectable modes of determine crew operation) selection 41* Selected Mach (all pilot As installed 1 As installed Sufficient to selectable modes of determine crew operation) selection 42* Selected vertical speed As installed 1 As installed Sufficient to (all pilot selectable determine crew modes of operation) selection 43* Selected heading (all As installed 1 As installed Sufficient to Rev. 2, 13th October 2022 29CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 Maximum Accuracy limits sampling and (sensor input Serial Measurement Recording Parameter Applicability recording compared number range resolution interval to FDR read- (seconds) out) pilot selectable modes determine crew of operation) selection 44* Selected flight path (all As installed 1 As installed Sufficient to pilot selectable modes determine crew of operation) selection 45* Selected decision height As installed 4 As installed Sufficient to determine crew selection 46* EFIS display format Discrete(s) 4 (pilot, co-pilot) 47* Multi- Discrete(s) 4 function/engine/alerts display format 48* Event Marker Discrete 1 49* GPWS/TAWS/GCAS Application Discrete(s) 1 As installed status ( selection of for Type terrain display modes Certification including pop-up is submitted display status) and to a (Terrain Alerts, both contracting cautions and warnings, state on or and advisories) and after 1 (on/off switch position) January, and (Operational Status) 2023) 50* TCAS/ACAS (Traffic Application Discrete(s) 1 As installed Alert and Collision for Type Avoidance System) and Certification (Operational Status) is submitted on or after 1 January, 2023 51* Primary Flight Application Full range 0.125 (0.0625 ±3% unless 0.5% of controls - Pilot input for type recommended) higher accuracy is operating range forces certification uniquely required is submitted on or after 1 January 2023 52* Computed Centre of Application As installed 64 As installed 1% of full range Gravity for type certification is submitted on or after 1 January 2023 53* Helicopter Computed Application As installed 64 As installed 1% of full range Weight for type certification is submitted on or after 1 January 2023 Rev. 2, 13th October 2022 30CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 Table-3 DESCRIPTION OF APPLICATIONS FOR DATA LINK RECORDERS Item Application type Application description Recoding No. content 1. Data link Initiation This includes any applications used to logon toor C initiate data link service. In FANS-1/A andATN, these are ATS Facilities Notification (AFN)and Context Management (CM) respectively. 2. Controller/Pilot This includes any application used to C Communication exchangerequests, clearances, instructions and reportsbetween the flight crew and controllers on theground. In FANS-1/A and ATN, this includes theCPDLC application.It also includes applications used for theexchange of oceanic (OCL) and departureclearances (DCL) as well as data link delivery of taxi clearances. 3. Addressed This includes any surveillance application inwhich C Surveillance the ground sets up contracts for deliveryof surveillance data.In FANS-1/A and ATN, this includes theAutomatic Dependent Surveillance - contract (ADS-C)application. Where parametric data are reportedwithin the message they shall be recordedunless data from the same source are recordedon the FDR. 4. Flight Information This includes any service used for delivery offlight C information to specific aircraft. This includes, for example, data link aviation weather report service (D- METAR), data link-automatic terminal service (D- ATIS), digital Notice to Airmen (D-NOTAM) and other textual data link services 5. Aircraft Broadcast This includes Elementary and EnhancedSurveillance M* Surveillance Systems, as well as automatic dependent surveillance- broadcast (ADS-B) outputdata. Where parametric data sent by thehelicopter are reported within the message theyshall be recorded unless data from the same source are recorded on the FDR. 6. Aeronautical This includes any application transmitting orreceiving M* Operational Control data used for aeronautical operational control Data purposes (per the ICAO definition of operational control). Key: C:Complete contents recorded. M: Information that enables correlation to any associated records stored separately fromthe helicopter. *:Applications that are to be recorded only as far as is practicable given the architectureof the system. Rev. 2, 13th October 2022 31CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 Table-4 PARAMETER CHARACTERISTICS FOR AIRCRAFT DATA RECORDING SYSTEMS - AEROPLANES Maximum Minimum Minimum Minimum recording No. Parameter name recording recording recording Remarks interval in range accuracy resolution seconds 1 Heading a) Heading ±180º 1 ±2° 0.5° Heading is (Magnetic or True) preferred, if not available, yaw rate shall be recorded b) Yaw rate ±300º/s 0.25 ±1% + drift 2°/s of 360°/h 2 a) Pitch attitude ±90º 0.25 ±2º 0.5° Pitch attitude is preferred, if not available, pitch rate shall be recorded b) Pitch rate ±300º/s 0.25 ±1% + drift 2°/s of 360°/h 3 a) Roll attitude ±180º 0.25 ±2º Roll attitude is 0.5° preferred, if not available, roll rate shall be recorded b) Roll rate ±300º/s 0.25 ±1% + drift 2°/s of 360°/h 4 Positioning system a) Time 24 hours 1 ±0.5 s 0.1 s UTC time preferred where available. b) Latitude:±90° 2 As installed 0.00005° Latitude/longitude Longitude:±180° (1 if (0.00015° available) recommended) c) Altitude –300 m (–1 000 2 As installed 1.5 m (5 ft) ft) to maximum (1 if (±15 m (±50 certificated available) ft) altitude of recommended) aeroplane +1 500 m (5 000 ft) d) Ground speed 0–1 000 kt 2 As installed 1 kt (1 if (±5 kt available) recommended) e) Track 0–360º 2 As installed 0.5° (1 if (± 2º available) recommended) f) Estimated error Available range 2 As installed As installed Shall be recorded (1 if if readily available) available 5 Normal –3 g to + 6 g (*) 0.25 (0.125 As installed (± 0.004 g acceleration if available) 0.09 g excluding a datum error of ±0.45 g recommended) 6 Longitudinal ±1 g (*) 0.25 (0.125 As installed 0.004 g acceleration if available) (±0.015 g excluding a Rev. 2, 13th October 2022 32CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 Maximum Minimum Minimum Minimum recording No. Parameter name recording recording recording Remarks interval in range accuracy resolution seconds datum error of ±0.05 g recommended) 7 Lateral ±1 g (*) 0.25 (0.125 As installed 0.004 g acceleration if available) (±0.015 g excluding a datum error of ±0.05 g recommended) 8 External static 34.4 mb (3.44 1 As installed 0.1 mb (0.01 in- pressure (or in-Hg) to 310.2 (±1 mb (0.1 Hg) or 1.5 m (5 pressure altitude) mb (31.02 in- in-Hg) or ft) Hg) or available ±30 m (±100 sensor range ft) to ±210 m (±700 ft) recommended) 9 Outside air –50° to +90°C 2 As installed 1°C temperature (or or available (±2°C total air sensor range recommended) temperature) 10 Indicated air speed As the installed 1 As installed 1 kt (0.5 kt pilot display (±3 % recommended) measuring recommended) system or available sensor range 11 Engine RPM Full range Each engine As installed 0.2% of full including each second range overspeed condition 12 Engine oil pressure Full range Each engine As installed 2% of full range each second (5% of full range recommended) 13 Engine oil Full range Each engine As installed 2% of full range temperature each second (5% of full range recommended) 14 Fuel flow or Full range Each engine As installed 2% of full range pressure each second 15 Manifold pressure Full range Each engine As installed 0.2% of full each second range 16 Engine Full range Each engine As installed 0.1% of full * Sufficient thrust/power/torque each second range parameters e.g. parameters EPR/N1 or required to torque/Np as determine appropriate to the propulsive particular engine thrust/power* shall be recorded to determine power in both normal and reverse thrust. A margin for possible overspeed should be provided. 17 Engine gas 0-150% Each engine As installed 0.2% of generator speed each second full range (Ng) 18 Free power turbine 0-150% Each engine As installed 0.2% of speed (Nf) each second full range Rev. 2, 13th October 2022 33CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 Maximum Minimum Minimum Minimum recording No. Parameter name recording recording recording Remarks interval in range accuracy resolution seconds 19 Coolant Full range 1 As installed 1° C temperature (±5°C recommended) 20 Main voltage Full range Each engine As installed 1 Volt each second 21 Cylinder head Full range Each As installed 2% of temperature cylinder full range each second 22 Flaps position Full range or 2 As installed 0.5° each discrete position 23 Primary flight Full range 0.25 As installed 0.2 % of control surface full range position 24 Fuel quantity Full range 4 As installed 1% of full range 25 Exhaust gas Full range Each engine As installed 2% of temperature each second full range 26 Emergency voltage Full range Each engine As installed 1 Volt each second 27 Trim surface Full range or 1 As installed 0.3% of full position each discrete range position 28 Landing gear Each discrete Each gear As installed * Where position position* every two available, record seconds up-and- locked and down-and- locked position 29 Novel/unique As required As required As required As required aircraft features Table - 5 Rev. 2, 13th October 2022 34CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 PARAMETER CHARACTERISTICS FOR AIRCRAFT DATA RECORDING SYSTEMS - HELICOPTERS Maximum Minimum Minimum Minimum recording No. Parameter name recording recording recording Remarks interval in range accuracy resolution seconds 1 Heading a) Heading ±180º 1 ±2° 0.5° * Heading is (Magnetic or True) preferred, if not available, yaw rate shall be recorded b) Yaw rate ±300º/s 0.25 ±1% + drift 2°/s of 360°/h 2 Pitch a) Pitch attitude ±90º 0.25 ±2º 0.5° *Pitch altitude is preferred, if not available, pitch rate shall be recorded b) Pitch rate ±300º/s 0.25 ±1% + drift 2°/s of 360°/h 3 Roll a) Roll attitude ±180º 0.25 ±2º 0.5° * Roll attitude is prefereed, if not available, roll rate shall be recorded b) Roll rate ±300º/s 0.25 ±1% + drift 2°/s of 360°/h 4 Positioning system: a) Time 24 hours 1 ±0.5 s 0.1 s UTC time preferred where available. b) Latitude Latitude:±90° 2 (1 if As installed 0.00005° /longitude Longitude:±180° available) (0.00015° recommended) c) Altitude –300 m (–1 000 2 (1 if As installed 1.5 m (5 ft) ft) to maximum available) (±15 m (±50 certificated ft) altitude of recommended) aeroplane +1500 m (5 000 ft) d) Ground speed 0–1 000 kt 2 (1 if As installed 1 kt available) (±5 kt recommended) e) Track 0–360º 2 (1 if As installed 0.5° available) (± 2º recommended) f) Estimated error Available range 2 (1 if As installed As installed Shall be available) recorded if readily available 5 Normal –3 g to + 6 g 0.25 (0.125 As installed (± 0.004 g acceleration if available) 0.09 g excluding a datum error of ±0.05 g Rev. 2, 13th October 2022 35CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 Maximum Minimum Minimum Minimum recording No. Parameter name recording recording recording Remarks interval in range accuracy resolution seconds recommended) 6 Longitudinal ±1 g 0.25 (0.125 As installed 0.004 g acceleration if available) (±0.015 g excluding a datum error of ±0.05 g recommended) 7 Lateral ±1 g 0.25 (0.125 As installed 0.004 g acceleration if available) (±0.015 g excluding a datum error of ±0.05 g recommended) 8 External static 34.4 hPa (1.02 1 As installed 0.1 hPa (0.03 in- pressure (or in -Hg) to 310.2 (±1 hPa (0.3 Hg) or 1.5 m (5 pressure altitude) hPa (9.16 in-Hg) in-Hg) or ft) or available ±30 m (±100 sensor range ft) to ±210 m (±700 ft) recommended) 9 Outside air –50° to +90°C 2 As installed 1°C temperature (or or available (±2°C total air sensor range recommended) temperature) 10 Indicated air speed As the installed 1 As installed 1 kt (0.5 kt pilot display (±3 % recommended) measuring recommended) system or available sensor range 11 Main rotor speed 50% to 130% or 0.5 As installed 0.3% of full (Nr) available sensor range range 12 Engine RPM (*) Full range Each engine As installed 0.2% of full * for pistion- including each second range engined overspeed helicopters condition 13 Engine oil pressure Full range Each engine As installed 2% of full range each second (5% of full range recommended) 14 Engine oil Full range Each engine As installed 2% of full range temperature each second (5% of full range recommended) 15 Fuel flow or Full range Each engine As installed 2% of full range pressure each second 16 Manifold pressure Full range Each engine As installed 0.2% of full * for pistion- (*) each second range engined helicopters 17 Engine Full range Each engine As installed 0.1% of full * Sufficient thrust/power/torque each second range parameters e.g. parameters EPR/N1 or required to torque/Np as determine Appropriate to propulsive the particular thrust/power* engine shall be recorded to determine power. A margin for possible overspeed Rev. 2, 13th October 2022 36CIVIL AVIATION REQUIREMENTS SECTION 2 SERIES I PART V 30th October, 2018 Maximum Minimum Minimum Minimum recording No. Parameter name recording recording recording Remarks interval in range accuracy resolution seconds should be provided. Only for turbine- engined helicopters 18 Engine gas 0-150% Each engine As installed 0.2% of * Only for generator speed each second full range turbine- (Ng) (*) engined helicopters 19 Free power turbine 0-150% Each engine As installed 0.2% of * Only for speed (Nf)(*) each second full range turbine- engined helicopters 20 Collective Pitch Full range 0.5 As installed 0.1% of full range 21 Coolant Full range 1 As installed 1° C * Only for temperature (±5°C piston-engined recommended) helicopters 22 Main voltage Full range Each engine As installed 1 Volt each second 23 Cylinder head Full range Each As installed 2% of * Only for temperature (*) cylinder full range piston-engined each second helicopters 24 Fuel quantity Full range 4 As installed 1% of full range 25 Exhaust gas Full range Each engine As installed 2% of temperature each second full range 26 Emergency voltage Full range Each engine As installed 1 Volt each second 27 Trim surface Full range or 1 As installed 0.3% of full position each discrete range position 28 Landing gear Each discrete Each gear As installed * Where position position* every two available, seconds record up-and- locked and down-and- locked position 29 Novel/unique As required As required As required As required aircraft features *** Rev. 2, 13th October 2022 37