Draft revision to CAR Section 6 - Aircraft Engine Emissions Certification - Standards and Procedures.

CIVIL AVIATION REQUIREMENTS SECTION 6 – DESIGN STANDARDS AND TYPE CERTIFICATION SERIES ‘C’ PART I AIRCRAFT ENGINE EMISSIONS CERTIFICATION – STANDARDS AND PROCEDURES ISSUE II (Revision 1) July 2020 Director General of Civil Aviation OFFICE OF THE DIRECTOR GENERAL OF CIVIL AVIATION TECHNICAL CENTRE, OPP. SAFDARJUNG AIRPORT, NEW DELRECORD OF REVISION This CAR has been issued to formulate regulations towards engine emissions certification based on International Civil Aviation Organization’s International Standards and Recommended Practices (SARPs) as contained in Annex-16, Environmental Protection, Volume-II “Aircraft Engine Emissions”. The CAR was initially developed and issued on 10th January’ 2011 and becomes effective forthwith. Thereafter, the CAR has continuously undergone revisions due to amendments from the recommendations of the meeting of the Committee on Aviation Environmental Protection (CAEP). The Record of Revisions to the aforesaid CAR is as follows: Sl. Issue Revision Date Remarks No. Number Number 1. Issue – I Revision – 0 10/01/2011 Initial issue of CAR to adopt engine emissions standards as contained in Annex-16, Volume-II including Amendment 6. 2. Issue – I Revision – 1 December Revisions due to Amendment 7. 2011 3. Issue – I Revision – 2 October Revisions due to Amendment 8. 2014 4. Issue – II Revision – 0 November Rewritten due to revisions due to 2017 Amendment 9. 5. Issue-II Revision – 1 xx/07/2020 Revisions due to Amendment 10 to ICAO Annex-16, Volume-II. 1INTRODUCTION Rule 49 of the Aircraft Rules, 1937 stipulates requirements for a Type Certificate (TC) in respect of a new type of aeronautical products such as aircraft, engine and propeller or change in type design in case of its derived version, designed and manufactured in India. The Type Certificate Data Sheet (TCDS), which forms the part of the Type Certificate, contains the certification basis in respect of that aircraft and the applicable certification basis as mentioned in CAR 21.17 and environmental protection requirements as mentioned in CAR 21.18. With the objective of compliance with the above mentioned rules, CAR, Section-6, Series-C, Part-II has been developed based on the International Standards and Recommended Practices (SARPs) contained in ICAO Annex-16, Volume-II. This CAR is issued under the provisions of Rule 133A of the Aircraft Rules, 1937, for information, guidance and compliance by all such organizations who intend to design and develop aeronautical products including Auxiliary Power Unit (APU) in India for which a Type Certificate is to be issued by DGCA under the provisions mentioned in CAR 21 The requirements contained in this CAR are in-line with the requirements as mentioned in ICAO Annex-16, Volume-II. It prescribes applicability, measurement of reference pressure ratio, smoke emission evaluation, measurement points, Instrumentation and measurement techniques for gaseous emissions, specification for HC analyser, CO and CO analysers, NOx analyser, calibration and test gases, calculation of the emissions 2 parameters, specifications for additional data, specification for fuel to be used in aircraft turbine engine emission testing, Instrumentation and measurement techniques for gaseous emissions from afterburning gas turbine engines, and compliance procedure for gaseous emissions and smoke along with relevant calculations for different category of engines fitted on aeroplanes for demonstrating compliance to the above requirements. This CAR supersedes earlier issued CAR, Issue-II, Revision-0 November, 2017. (Arun Kumar) Director General of Civil Aviation 2 Issue-II, Rev- 1, July 2020CONTENTS ENGINE EMISSIONS CERTIFICATION PROCEDURES FOR AIRCRAFT Sl. No SUBPART TOPIC 1. SUBPART – A Prevention of Intentional Fuel Venting. 2. SUBPART – B Emissions Certification. 3. SUBPART – C Turbojet and Turbofan Engines Intended for Propulsion only at Subsonic Speeds. 4. SUBPART – D Turbojet and Turbofan Engines Intended for Propulsion at Supersonic Speeds. 5. SUBPART – E Particulate Matter Emissions 6. SUBPART – F Non-Volatile Particulate Matter Assessment for Inventory Purposes. 7. APPENDIX – I Definitions. 8. APPENDIX – II Symbols. ********* 3 Issue-II, Rev- 1, July 2020SUBPART – A: PREVENTION OF INTENTIONAL FUEL VENTING. 1. APPLICABILITY: . 1.1 The provision of this CAR shall apply to all turbine engine powered aircraft intended for operation in India manufactured after 18 February, 1982. 2. GENERAL REQUIREMENTS: 2.1 Certification related to the prevention of intentional fuel venting shall be granted by DGCA on the basis of satisfactory evidence that either the aircraft or the aircraft engines comply with requirements of paragraph 2.5 of this subpart. 2.2 The certification document relating to fuel venting may be issued by DGCA as a separate fuel venting certificate, if required. 2.3 DGCA shall recognize fuel venting certificate issued/granted by the certificating authority of another State provided the requirements towards the certification are equivalent to the provision of this Subpart. 2.4 All civil aeroplanes, operating in India for which a type certificate is to be issued by DGCA or imported through validation or type acceptance, shall have a valid emissions certificate for the engine installed in the aeroplane in accordance with the provisions contained in CAR 21.16 (A). 2.5 Aircraft shall be so designed and constructed so as to prevent the intentional discharge into the atmosphere of liquid fuel from the fuel nozzle manifolds resulting from the process of engine shutdown following normal flight or ground operations. ********* 4 Issue-II, Rev- 1, July 2020SUBPART – B: EMISSIONS CERTIFICATION. 1. APPLICABILITY: 1.1 The provisions of 1.2 to 1.5 of this subpart shall apply to all engines and their derivative versions included in the classifications defined for emission certification purposes in subparts C, D and E where such engines are fitted to aircraft engaged in operations. 1.2 Emissions certification shall be granted by DGCA on the basis of satisfactory evidence that the engine complies with requirements of this subpart. Compliance with the emissions levels of subparts C, D and E of this CAR shall be demonstrated using the procedure described in Appendix-6 of ICAO Annex- 16, Volume-II. 1.3 The document relating to emissions certification may be issued by DGCA as a separate emissions certificate, if required. 1.4 The emissions certification document for each individual engine shall include the following information: a) Name of certificating authority, b) Manufacturer’s type and model designation, c) Statement of any additional modifications incorporated for the purpose of compliance with the applicable emissions certification requirements, d) Rated thrust, e) Reference pressure ratio, f) A statement indicating compliance with Smoke Number requirements, g) A statement indicating compliance with gaseous pollutant requirements, and h) A statement indicating compliance with particulate matter requirements. 1.5 DGCA shall recognize emissions certificate issued/granted by the certificating authority of another State provided that the requirements towards the certification are equivalent to the provisions of this subpart. 1.6 DGCA shall recognize an engine exemptions granted by certificating the competent authority of another Contracting State, having jurisdiction over the organization responsible for production of the engine, provided that an acceptable process was used for an engine production cut-off requirement. However, the exemptions granted shall be in accordance with the process and criteria defined in the Environmental Technical Manual (Doc 9501),Volume II — Procedures for the Emissions Certification of Aircraft Engines. 5 Issue-II, Rev- 1, July 20201.7 Unless otherwise specified in this volume of the Annex, the date to be used by Contracting States in determining the applicability of the Standards in this Annex shall be the date when the application for a Type Certificate for engines of a type or model was submitted to the State of Design, or the date of submission under an equivalent application procedure prescribed by the certificating authority of the State of Design. 1.8 An application for a Type Certificate for engines of a type or model shall be effective for the period specified in the designation of the airworthiness regulations appropriate to the engine of a type or model, except in special cases where the certificating authority accepts an extension of this period. When this period of effectivity is exceeded and an extension is approved, the date to be used in determining the applicability of the Standards in this Annex shall be the date of issue of the Type Certificate or approval of the change in the type design, or the date of issue of approval under an equivalent procedure prescribed by the State of Design, less the period of effectivity. ********* 6 Issue-II, Rev- 1, July 2020SUBPART – C: TURBOJET AND TURBOFAN ENGINES INTENDED FOR PROPULSION ONLY AT SUBSONIC SPEEDS 1. APPLICABILITY: 1.1 The provisions specified in paragraph 5 and 6 of this subpart shall apply to all turbojet and turbofan engines, intended for propulsion only at subsonic speeds, except in the case where exemptions have been issued by DGCA or the competent authority having jurisdiction over the organization responsible for production of the engine for the following: a) Specific engine types and derivative versions of such engines for which the Type Certificate of the first basic type was issued before 1st January, 1965; and b) A limited number of engines for the manufacturing of the individual engine, over a specific period of time beyond the dates of applicability. 1.2 In case, an exemption certificate is issued by DGCA or the competent authority having jurisdiction over the organization responsible for production of the engines, the identification plates on the engines shall be marked “Exempt New” or “Exempt Spare”. The certificating authority or the competent authority having jurisdiction over the organization responsible for production of the engines shall take into account the numbers of exempted engines that will be produced and their impact on the environment. Such exemptions shall be reported by engine serial number and noted in the engine record. 1.3 The provisions of this subpart shall also apply to all those engines which are designed for applications that otherwise would have been fulfilled by turbojet and turbofan engines. 1.4 While granting exemptions, DGCA shall take into account the numbers of such engines to be produced under such exemptions and their impact on the environment. However, DGCA may impose a time limit on the production of such engines for installation on new aircraft. Further guidance on issuing such exemptions is provided in the Environmental Technical Manual (Doc 9501), Volume II — Procedures for the Emissions Certification of Aircraft Engines. 1.5 The provisions of this chapter shall also apply to engines designed for applications that otherwise would have been fulfilled by turbojet and turbofan engines and which are designed as an integrated propulsive power plant and certified with a rated thrust. 7 Issue-II, Rev- 1, July 20201.6 Further guidance on issuing such exemptions is provided in the Environmental Technical Manual (Doc 9501), Volume II — Procedures for the Emissions Certification of Aircraft Engines. 2. Emissions involved: 2.1 The following emissions shall be considered for certification of aircraft engines: a) Smoke, b) Gaseous emissions, i) Unburned hydrocarbons (HC), ii) Carbon monoxide (CO), and iii) Oxides of nitrogen (NOx). 3. Units of measurement: 3.1 The smoke emission shall be measured and reported in terms of Smoke Number (SN). 3.2 The mass (Dp) of the gaseous pollutant HC, CO, or NOx emitted during the reference emissions landing and take-off (LTO) cycle, defined in paragraph 4.2 and 4.3 of this subpart, shall be measured and reported in grams. 4. Reference Conditions: 4.1 Atmospheric conditions: The reference atmospheric conditions for engine performance shall be ISA at sea level or the reference absolute humidity shall be 0.00634 kg water/kg dry air. 4.2 Thrust settings: The engine shall be tested at sufficient thrust settings to define the gaseous and smoke emissions of the engine so that mass emission rates and Smoke Numbers can be determined at the following specific percentages of rated thrust as agreed by DGCA: LTO operating mode Thrust setting Take-off 100 per cent F ∞ Climb 85 per cent F ∞ Approach 30 per cent F ∞ Taxi/ground idle 7 per cent F ∞ 8 Issue-II, Rev- 1, July 20204.3 Reference emissions landing and take-off (LTO) cycle: The reference emissions LTO cycle for the calculation and reporting of gaseous emissions shall be represented by the following: LTO operating mode Time in operating mode, minutes Take-off 0.7 Climb 2.2 Approach 4.0 Taxi/ground idle 26.0 4.4 Fuel specifications: The fuel used during tests shall meet the following specifications unless a deviation and any necessary corrections have been agreed upon by DGCA. The fuel shall not contain any additives for smoke suppression (such as organometallic compounds, etc): Property Allowable range of values Density kg/m3 at 15°C 780 – 820 Distillation temperature, °C 10% boiling point 155 – 201 Final boiling point 235 – 285 Net heat of combustion, MJ/kg 42.86 – 43.50 Aromatics, volume % 15 – 23 Naphthalenes, volume % 1.0 – 3.5 Smoke point, mm 20 – 28 Hydrogen, mass % 13.4 – 14.3 Sulphur, mass % less than 0.3% Kinematic viscosity at –20°C, mm2/s 2.5 – 6.5 4.5 Test conditions: a) The tests shall be made with the engine on its test bed. b) The engine shall be representative of the certificated configuration off-take bleeds and accessory loads other than those necessary for the engine’s basic operation shall not be simulated. c) When test conditions differ from the reference atmospheric conditions as mentioned at paragraph 4.1 of this subpart, the gaseous emissions test results shall be corrected to the reference atmospheric conditions by the methods given in Appendix-3 of ICAO Annex-16, Volume-II. 5. Smoke: 5.1 Applicability: 9 Issue-II, Rev- 1, July 20205.1.1 The provisions of paragraph 5.2 of this subpart shall apply: a) To engines whose date of manufacture is on or after 1st January, 1983 and before 1 January 2023; and. b) To engines with a maximum rated thrust of less than or equal to 26.7 kN whose date of manufacture is on or after 1 January 2023. 5.2 Regulatory Smoke Number: 5.2.1 The Smoke Number shall be measured and computed in accordance with the procedures given at Appendix-2 of ICAO Annex-16, Volume-II and converted to a characteristic level by the procedures of Appendix-6 of ICAO Annex-16, Volume-II. However, the Smoke Number at any of the four LTO operating mode thrust settings shall not exceed the level determined from the following formula: −0.274 Regulatory Smoke Number = 83.6 (F ) or a value of 50, whichever is lower. ∞ 6. Gaseous emissions: 6.1 Applicability: 6.1.1 The provisions of paragraph 6.2 of this subpart shall apply to engines whose rated thrust is greater than 26.7 kN and whose date of manufacture is on or after 1st January, 1986 and as specified for oxides of nitrogen. 6.2 Regulatory Levels: 6.2.1 Gaseous emission levels shall be measured and computed in accordance with the procedures of Appendix-3 of ICAO Annex-16, Volume-II and converted to characteristic levels by the procedures of Appendix-6 of ICAO Annex-16, Volume-II. However, gaseous emission levels shall not exceed the regulatory levels determined from the following formulas: Hydrocarbons (HC): Dp /F = 19.6 ∞ Carbon monoxide (CO): Dp /F = 118 ∞ Oxides of nitrogen (NOx): a) for engines of a type or model for which the date of manufacture of the first individual production model was before 1 January 1996 and for which the date of manufacture of the individual engine was before 1 January 2000. Dp /F = 40 + 2π ∞ ∞ b) for engines of a type or model for which the date of manufacture of the first individual production model was on or after 1 January 1996 or for 10 Issue-II, Rev- 1, July 2020which the date of manufacture of the individual engine was on or after 1 January 2000. Dp /F = 32 + 1.6π ∞ ∞ c) For engines of a type or model for which the date of manufacture of the first individual production model was on or after 1st January, 2004: 1) For engines with a pressure ratio of 30 or less: i) For engines with a maximum rated thrust of more than 89.0 kN: Dp /F = 19 + 1.6π ∞ ∞ ii) For engines with a maximum rated thrust of more than 26.7 kN but not more than 89.0 kN: Dp /F = 37.572 + 1.6π – 0.2087F ∞ ∞ ∞ 2) For engines with a pressure ratio of more than 30 but less than 62.5: i) For engines with a maximum rated thrust of more than 89.0 kN: Dp /F = 7 + 2.0π ∞ ∞ ii) For engines with a maximum rated thrust of more than 26.7 kN but not more than 89.0 kN: Dp /F = 42.71 + 1.4286π – 0.4013F + 0.00642π × F ∞ ∞ ∞ ∞ ∞ 3) For engines with a pressure ratio of 62.5 or more: Dp /F = 32 + 1.6π ∞ ∞ d) For engines of a type or model for which the date of manufacture of the first individual production model was on or after 1st January, 2008 or for which the date of manufacture of the individual engine was on or after 1st January, 2013: 1) For engines with a pressure ratio of 30 or less: i) For engines with a maximum rated thrust of more than 89.0 kN: Dp /F = 16.72 + 1.4080π ∞ ∞ ii) For engines with a maximum rated thrust of more than 26.7 kN but not more than 89.0 kN: Dp /F = 38.5486 + 1.6823π – 0.2453F – 0.00308π F ∞ ∞ ∞ ∞ ∞ 2) For engines with a pressure ratio of more than 30 but less than 82.6: i) For engines with a maximum rated thrust of more than 89.0 kN: Dp /F = –1.04 + 2.0π ∞ ∞ 11 Issue-II, Rev- 1, July 2020ii) For engines with a maximum rated thrust of more than 26.7 kN but not more than 89.0 kN: Dp /F = 46.1600 + 1.4286π – 0.5303F + 0.00642π F ∞ ∞ ∞ ∞ ∞ 3) For engines with a pressure ratio of 82.6 or more: Dp /F = 32 + 1.6π ∞ ∞ e) For engines of a type or model for which the date of manufacture of the first individual production model was on or after 1st January, 2014 and for which an application for a Type Certificate was submitted before 1 January 2023: 1) For engines with a pressure ratio of 30 or less: i) For engines with a maximum rated thrust of more than 89.0 kN: Dp /F = 7.88 + 1.4080π ∞ ∞ ii) For engines with a maximum rated thrust of more than 26.7 kN but not more than 89.0 kN: Dp /F = 40.052 + 1.5681π – 0.3615F – 0.0018π F ∞ ∞ ∞ ∞ ∞ 2) For engines with a pressure ratio of more than 30 but less than 104.7: i) For engines with a maximum rated thrust of more than 89.0 kN: Dp /F = –9.88 + 2.0π ∞ ∞ ii) For engines with a maximum rated thrust of more than 26.7 kN but not more than 89.0 kN: Dp /F = 41.9435 + 1.505π – 0.5823F + 0.005562π F ∞ ∞ ∞ ∞ ∞ 3) For engines with a pressure ratio of 104.7 or more: Dp /F = 32 + 1.6π ∞ ∞ f) For engines of a type or model for which an application for a Type Certificate was submitted on or after 1 January 2023: 1) For engines with a pressure ratio of 30 or less: i) For engines with a maximum rated thrust of more than 89.0 kN: Dp /F = 7.88 + 1.4080πoo ∞ ii) For engines with a maximum rated thrust of more than 26.7 kN but not more than 89.0 kN: Dp /F = 40.052 + 1.5681π – 0.3615F – 0.0018π F ∞ ∞ ∞ ∞ ∞ 12 Issue-II, Rev- 1, July 20202) For engines with a pressure ratio of more than 30 but less than 104.7: i) For engines with a maximum rated thrust of more than 89.0 kN: Dp /F = –9.88 + 2.0π ∞ ∞ ii) for engines with a maximum rated thrust of more than 26.7 kN but not more than 89.0 kN: Dp /F = 41.9435 + 1.505π – 0.5823F + 0.005562π F ∞ ∞ ∞ ∞ ∞ 3) For engines with a pressure ratio of 104.7 or more: Dp /F = 32 + 1.6π ∞ ∞ 7. Information required: 7.1 The information required is divided into three groups: 1) general information to identify the engine characteristics, the fuel used and the method of data analysis; 2) the data obtained from the engine test(s), and 3) the results derived from the test data. 7.2 General information: 7.2.1 The following information shall be provided for each engine type for which emissions certification is sought: a) Engine identification, b) Rated thrust (in kilo-newton), c) Reference pressure ratio, d) Fuel specification reference, e) Fuel hydrogen/carbon ratio, f) The methods of data acquisition, g) The method of making corrections for ambient conditions, and h) The method of data analysis. 7.3 Test information: 7.3.1 The following information shall be provided for each engine tested for certification purposes at each of the thrust settings specified in paragraph 4.2 of this subpart. The information shall be provided after correction to the reference ambient conditions where applicable: a) Fuel flow (kilograms/second), b) Emission index (grams/kilogram) for each gaseous pollutant, and c) Measured Smoke Number. 7.4 Derived information: 13 Issue-II, Rev- 1, July 20207.4.1 The following derived information shall be provided for each engine tested for certification purposes: a) Emission rate, i.e. emission index X fuel flow, (grams/second) for each gaseous pollutant, b) Total gross emission of each gaseous pollutant measured over the LTO cycle (grams), c) Values of Dp /F for each gaseous pollutant (grams/kilo newton), and ∞ d) Maximum Smoke Number. 7.4.2 The characteristic Smoke Number and gaseous pollutant emission levels shall be provided for each engine type for which emissions certification is sought. ********* 14 Issue-II, Rev- 1, July 2020SUBPART – D: TURBOJET AND TURBOFAN ENGINES INTENDED FOR PROPULSION AT SUPERSONIC SPEEDS RESERVED. ********* 15 Issue-II, Rev- 1, July 2020SUBPART – E: PARTICULATE MATTER EMISSIONS 1. APPLICABILITY: 1.1 The provisions of this subpart shall apply to all aircraft engines, as further specified in 4, intended for propulsion only at subsonic speeds, for which an application for type certification is submitted to DGCA. 1.2 Specific provisions for the relevant engine categories shall apply as detailed in paragraph 4 of this subpart, except when the certificating authority or the competent authority having jurisdiction over the organization responsible for production of the engines grants exemptions for a limited number of engines over a specific period of time beyond the dates of applicability specified in 4 for the manufacture of the individual engine. 1.3 In such cases, an exemption document shall be issued by the certificating authority or the competent authority having jurisdiction over the organization responsible for production of the engines, the identification plates on the engines shall be marked “EXEMPT” and the grant of exemption shall be noted in the permanent engine record. The certificating authority or the competent authority having jurisdiction over the organization responsible for production of the engines shall take into account the number of exempted engines that will be produced and their impact on the environment. Exemptions shall be reported by engine serial number and made available via an official public register. 1.4 When such an exemption is granted, the certificating authority or the competent authority having jurisdiction over the organization responsible for production of the engines should consider imposing a time limit on the production of such engines. 1.5 Emissions involved: The purpose of this section is to control non-volatile particulate matter mass (nvPM mass) emissions. 1.6 Units of measurement: The concentration of nvPM mass shall be reported in μg micrograms/m3. 1.7 The nvPM mass emitted during the reference emissions landing and take-off (LTO) cycle, defined in 2.2 (LTOmass), shall be measured and reported in milligrams. 1.8 The nvPM number emitted during the reference emissions landing and take-off (LTO) cycle, defined in 2.2 (LTOnum), shall be measured and reported in number of particles. 2. Reference conditions: 16 Issue-II, Rev- 1, July 20202.1 Atmospheric conditions: The reference atmospheric conditions for the reference standard engine shall be ISA at sea level or the reference absolute humidity shall be 0.00634 kg water/kg dry air. 2.2 Reference emissions landing and take-off (LTO) cycle: The engine shall be tested at sufficient thrust settings to define the nvPM emissions of the engine so that nvPM mass emission indices (EI ) and nvPM number mass emission indices (EI ) can be determined at the following specific num percentages of rated thrust the reference emissions LTO cycle thrust settings and at thrusts producing maximum nvPM mass concentration, maximum EI and maximum EI as agreed by DGCA. mass num For the calculation and reporting of nvPM emissions, the reference emissions LTO cycle shall be represented by the following thrust setting and time in each following operating mode: LTO operating mode Thrust setting Time in Operating per cent F Mode Minutes ∞ Take-off 100 per cent F 0.7 ∞ Climb 85 per cent F 2.2 ∞ Approach 30 per cent F 4.2 ∞ Taxi/ground idle 7 per cent F 26.0 ∞ 2.3 Fuel Specifications: The fuel used during tests shall meet the specifications as specified at paragraph 4.4 of Subpart-C of this CAR. 3. Test conditions: 3.1 The tests shall be made with the engine on its test bed. 3.2 The engine shall be representative of the certificated configuration, off take bleeds and accessory loads other than those necessary for the engine’s basic operation shall not be simulated. 3.3 When test conditions differ from the reference atmospheric conditions as mentioned in paragraph 2.1 of this Subpart, EI and EI shall be mass num corrected to the engine combustor inlet temperature under the reference atmospheric conditions by the method given in Appendix-7 of ICAO Annex-16, Volume-II. 3.4 The maximum nvPM mass concentration shall be corrected for dilution and thermophoretic losses in the Collection Part of the sampling system in accordance with the procedures of Appendix 7 of ICAO Annex-16, 17 Issue-II, Rev- 1, July 2020Volume-II. and The EI and EI shall be corrected for thermophoretic mass num losses in the Collection Part of the sampling system and fuel composition by the method given in Appendix-7 of ICAO Annex-16, Volume-II. 4. Non-Volatile Particulate Matter Emissions 4.1 Applicability: 4.1.1 The provision further specified in paragraphs 4.2 and 4.3 of this subpart shall apply to all turbofan and turbojet engines of a type or model, and their derivative versions, with a rated thrust greater than 26.7 kN and whose date of manufacture of the individual engine is on or after 1 January 2020. 4.2 Regulatory Levels: 4.2.1 Maximum nvPM mass concentration: For an engine whose date of manufacture of the individual engine is on or after 1 January 2020, the maximum nvPM mass concentration measured in μg/m3 obtained from measurement at sufficient thrust settings, in such a way that the mission maximum can be determined, and computed in accordance with the procedures of Appendix 7 of ICAO Annex-16, Volume-II and converted to characteristic levels by the procedures of Appendix 6 of ICAO Annex-16, Volume-II, or equivalent procedures as agreed by DGCA shall not exceed the regulatory level determined from the following formula: Regulatory limit concentration of nvPM mass concentration = 10 (3 + 2.9 𝐹 −0.274 ) ∞ 4.2.2 nvPM mass and nvPM number emitted during the reference LTO cycle: The nvPM mass and nvPM number emission levels when measured and computed in accordance with the procedures of Appendix 7 of ICAO Annex-16, Volume-II and converted to characteristic levels by the procedures of Appendix 6 of ICAO Annex-16, Volume-II, or equivalent procedures as agreed by the certificating authority, shall not exceed the regulatory levels determined from the following formulas: a) LTO : mass 1) For engines of a type or model for which the date of manufacture of the individual engine was on or after 1 January 2023: i) For engines with a maximum rated thrust of more than 200 kN: LTO /F = 347.5 mass ∞ 18 Issue-II, Rev- 1, July 2020ii) for engines with a maximum rated thrust of more than 26.7 kN but not more than 200 kN: LTO /F = 4646.9 – 21.497F mass ∞ ∞ 2) For engines of a type or model for which an application for a Type Certificate was submitted on or after 1 January 2023: i) For engines with a maximum rated thrust of more than 150 kN: LTO /F = 214.0 mass ∞ ii) For engines with a maximum rated thrust of more than 26.7 kN but not more than 150 kN: LTO /F = 1251.1 – 6.914F mass ∞ ∞ b) LTO : num 1) For engines of a type or model for which the date of manufacture of the individual engine was on or after 1 January 2023: i) For engines with a maximum rated thrust of more than 200 kN: LTO /F = 4.170 x 1015 num ∞ ii) For engines with a maximum rated thrust of more than 26.7kN but not more than 200 kN: LTO /F = 2.669x 1016 – 1.126 x 1014F num ∞ ∞ 2) For engines of a type or model for which an application for a Type Certificate was submitted on or after 1 January 2023: i) For engines with a maximum rated thrust of more than 150 kN: LTO /F = 2.780 x 1015 num ∞ ii) For engines with a maximum rated thrust of more than 26.7 kN but not more than 150 kN: LTO /F = 1.490 x 1016 – 8.080 x 1013F num ∞ ∞ 4.3 Reporting Requirement: 4.3.1 The manufacturer shall report the following values of nvPM emissions measured and computed in accordance with the procedures of Appendix- 7 of ICAO Annex-16, Volume-II, or any equivalent procedures as agreed by DGCA: a) Characteristic level for the maximum nvPM concentration (μg/m3), mass b) Fuel flow (kg/s) at each thrust setting of the LTO cycle, 19 Issue-II, Rev- 1, July 2020c) EI (mg/kg of fuel) at each thrust setting of the LTO cycle, mass d) EI (particles/kg of fuel) at each thrust setting of the LTO cycle, num e) a) Maximum EI (mg milligrams/kg of fuel), mass f) b) Maximum EI (particles/kg of fuel), num 5. Information required: The information required is divided into three groups: 1) general information to identify the engine characteristics, the fuel used and the method of data analysis; 2) the data obtained from the engine test(s); and 3) the results derived information from the test data. 5.1 General information: The following information shall be provided for each engine type for which emissions certification is sought: a) Engine identification, b) Rated output (in kN), c) Reference pressure ratio, d) Fuel specification reference, e) Fuel hydrogen/carbon ratio, f) The methods of data acquisition, g) The method of making corrections for thermophoretic losses in the Collection Part of the sampling system, and h) g) The method of data analysis. 5.2 Test information: 5.2.1 The following information shall be provided for each engine tested for certification purposes For each test the following information shall be reported: a) Fuel net heat of combustion (MJ/kg), b) Fuel hydrogen content (mass %), c) Fuel total aromatics content (volume %), d) Fuel naphthalene content (volume %), and e) Fuel sulphur content (ppm by mass %). 20 Issue-II, Rev- 1, July 20205.2.2 The following information, as measured and computed in accordance with the procedures of Appendix 7 of ICAO Annex-16, Volume-II, or any equivalent procedures as agreed by the certificating authority, shall be provided for each engine tested for certification purposes: a) Fuel flow (kg/s) at each thrust setting of the LTO cycle; b) EI (milligrams/kg of fuel) at each thrust setting of the LTO cycle; mass c) EI (particles/kg of fuel) at each thrust setting of the LTO cycle. num 5.3 Derived information: 5.3.1 The following derived information shall be provided for each engine tested for certification purposes: a) Emission rate, i.e. EI x fuel flow, (milligrams/s) for nvPM mass; mass b) Emissions rate, i.e. EI x fuel flow, (particles/s) for nvPM number; num c) Total gross emission of nvPM mass measured over the LTO cycle (milligrams); d) Total gross emission of nvPM number measured over the LTO cycle (particles); e) Values of LTO / F (milligrams/kN); mass ∞ f) Values of LTO / F (particles/kN); and num ∞ g) Maximum nvPM mass concentration (micrograms/m3). 5.3.2 The characteristic levels shall be provided for the maximum nvPM mass concentration, the LTO /F and the LTO /F for each engine type for which mass ∞ num ∞ emissions certification is sought. ******** 21 Issue-II, Rev- 1, July 2020SUBPART – F: NON-VOLATILE PARTICULATE MATTER ASSESSMENT FOR INVENTORY PURPOSES 1. The purpose of this subpart is to provide Standards and Recommended Practices guidance on how to calculate the nvPM mass and number correction factors for the nvPM system losses other than the Collection Part thermophoretic losses. The nvPM sampling and measurement system, the Collection Part and the thermophoretic losses calculation are described in Appendix 7 of ICAO Annex-16, Volume-II. 2. The nvPM mass and number system loss correction factors permit an estimation of the concentration of the nvPM mass and number at the exhaust of the aircraft engine from the nvPM mass and number concentration obtained following the procedures described in Appendix 7 of ICAO Annex-16, Volume-II. 3. For engines of a type or model subject to Part III, Chapter 4, and for which the date of manufacture of the individual engine was on or after 1 January 2023, the nvPM mass and nvPM number system loss correction factors (kSL and mass kSL ), and EI and EI corrected for system losses shall be reported to num mass num DGCA or competent authority as designated by the State in accordance with the procedures of Appendix 8 of ICAO Annex-16, Volume-II, or equivalent procedures as agreed by DGCA. 4. For inventory and modelling purposes, the turbine engine manufacturers should determine the nvPM mass and nvPM number system loss correction factors (k and k ) using the methodology described in Appendix 8 of ICAO SLmass SLnum Annex-16, Volume-II and should report these factors to DGCA. 5. For inventory and modelling purposes, the nvPM mass and nvPM number concentration emissions obtained following the procedures described in Appendix 7 of ICAO Annex-16, Volume-II should be corrected for system losses using the methodology described in Appendix 8 of ICAO Annex-16, Volume-II. 22 Issue-II, Rev- 1, July 2020APPENDIX -I 1. Afterburning: A mode of engine operation wherein a combustion system fed (in whole or part) by vitiated/exhaust air is used. 2. Approach phase: The operating phase defined by the time during which the engine is operated in the approach operating mode. 3. Climb phase: The operating phase defined by the time during which the engine is operated in the climb operating mode. 4. Date of manufacture: The date of issue of the document attesting that the individual aircraft or engine as appropriate conforms to the requirements of the type or the date of an analogous document. 5. Derivative version: An aircraft gas turbine engine of the same generic family as an originally type-certificated engine and having features which retain the basic core engine and combustor design of the original model and for which other factors, as judged by the certificating authority, have not changed. 6. Exhaust nozzle: In the exhaust emissions sampling of gas turbine engines where the jet effluxes are not mixed (as in some turbofan engines for example) the nozzle considered is that for the gas generator (core) flow only. Where, however, the jet efflux is mixed the nozzle considered is the total exit nozzle. 7. Gas concentration: The volume fraction of the component of interest in the gas mixture — expressed as volume percentage or as parts per million. 8. Non-Volatile Particulate Matter (nvPM): Emitted particles that exists at gas turbine engine exhaust nozzele exit plane that do not volatilise when heated to a temperature of 350 °C. 9. Oxides of nitrogen: The sum of the amounts of the nitric oxide and nitrogen dioxide contained in a gas sample calculated as if the nitric oxide were in the form of nitrogen dioxide. 10. Parts per million (ppm): The unit volume gas concentration of a gas per million unit volume of the gas mixture of which it is a part. 11. Parts per million carbon (ppmC): The mole fraction of hydrocarbon multiplied by 106 measured on a methane-equivalence basis. Thus, 1 ppm of methane is indicated as 1 ppmC. To convert ppm concentration of any hydrocarbon to an equivalent ppmC value, multiply ppm gas concentration by the number of carbon atoms per molecule of the gas. For example, 1 ppm propane translates as 3 ppmC hydrocarbon; 1 ppm hexane as 6 ppmC hydrocarbon. 12. Rated thrust: For engine emissions purposes, the maximum take-off thrust approved by the certificating authority for use under normal operating conditions at ISA sea level static conditions, and without the use of water injection. Thrust is expressed in kilo-newton. 23 Issue-II, Rev- 1, July 202013. Reference gas: A mixture of gases of specified and known composition used as the basis for interpreting instrument response in terms of the gas concentration of the gas to which the instrument is responding. 14. Reference pressure ratio: The ratio of the mean total pressure at the last compressor discharge plane of the compressor to the mean total pressure at the compressor entry plane when the engine is developing take-off thrust rating in ISA sea level static conditions. 15. Response: The change in instrument output signal that occurs with change in sample gas concentration. 16. Type Certificate: A document issued by a Contracting State to define the design of an aircraft, engine or propeller type and to certify that this design meets the appropriate airworthiness requirements of that State. 17. Smoke: The carbonaceous materials in exhaust emissions which obscure the transmission of light. 18. Smoke Number: The dimensionless term quantifying smoke emissions. 19. State of Design: The State having jurisdiction over the organization responsible for the type design. 20. Take-off phase: The operating phase defined by the time during which the engine is operated at the rated thrust. 21. Taxi/ground idle: The operating phases involving taxi and idle between the initial starting of the propulsion engine(s) and the initiation of the take-off roll and between the time of runway turn-off and final shutdown of all propulsion engine(s). 22. Unburned hydrocarbons: The total of hydrocarbon compounds of all classes and molecular weights contained in a gas sample, calculated as if they were in the form of methane. ********* 24 Issue-II, Rev- 1, July 2020APPENDIX -II NOMENCLATURE: SYMBOLS AND UNITS Following is the list of definitions and symbols used in this CAR. Many of the following definitions and symbols are specific to aircraft noise certification. Some of the definitions and symbols may also apply to purposes beyond aircraft noise certification. CO Carbon monoxide Dp The mass of any gaseous pollutant emitted during the reference emissions landing and take-off cycle EI nvPM mass emission index corrected for thermophoretic losses, mass in mg/kg fuel EI nvPM number emission index corrected for thermophoretic num losses, in number/kg fuel Fn Thrust in International Standard Atmosphere (ISA), sea level conditions, for the given operating mode F Rated thrust ∞ F* Rated thrust with afterburning applied ∞ HC Unburned hydrocarbons k mass nvPM mass system loss correction factor SL k num nvPM numbersystem loss correction factor SL NO Nitric oxide NO Nitrogen dioxide 2 NOx Oxides of nitrogen nvPM Non-volatile particulate matter nvPM nvPM mass concentration at instrument STP condition, mass corrected for dilution and thermophoretic losses in the collection section of the sampling system in μg/m3 SN Smoke Number Π Reference pressure ratio ∞ 25 Issue-II, Rev- 1, July 2020********* 26 Issue-II, Rev- 1, July 2020