cfr_sections
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| section_id ▼ | title_number | title_name | chapter | subchapter | part_number | part_name | subpart | subpart_name | section_number | section_heading | agency | authority | source_citation | amendment_citations | full_text |
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| 14:14:1.0.1.3.19.1.283.1 | 14 | Aeronautics and Space | I | C | 34 | PART 34—FUEL VENTING AND EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES | A | Subpart A—General Provisions | § 34.1 Definitions. | FAA | [Doc. No. 25613, 55 FR 32861, Aug. 10, 1990; 55 FR 37287, Sept. 10, 1990, as amended by Amdt. 34-3, 64 FR 5558, Feb. 3, 1999; Amdt. 34-5, 77 FR 76849, Dec. 31, 2012; Amdt. 34-5A, 78 FR 63016, Oct. 23, 2013; Amdt. 34-7, 89 FR 31085, Apr. 24, 2024] | As used in this part, all terms not defined herein shall have the meaning given them in the Clean Air Act, as amended (42 U.S.C. 7401 et. seq.): Act means the Clean Air Act, as amended (42 U.S.C. 7401 et. seq.). Administrator means the Administrator of the Federal Aviation Administration or any person to whom he has delegated his authority in the matter concerned. Administrator of the EPA means the Administrator of the Environmental Protection Agency and any other officer or employee of the Environmental Protection Agency to whom the authority involved may be delegated. Aircraft as used in this part means any airplane as defined in 14 CFR part 1 for which a U.S. standard airworthiness certificate or equivalent foreign airworthiness certificate is issued. Aircraft engine means a propulsion engine which is installed in, or which is manufactured for installation in, an aircraft. Aircraft gas turbine engine means a turboprop, turbofan, or turbojet aircraft engine. Characteristic level has the meaning given in Appendix 6 of ICAO Annex 16 as of July 2008 (incorporated by reference, see § 34.4). The characteristic level is a calculated emission level for each pollutant based on a statistical assessment of measured emissions from multiple tests. Class TP means all aircraft turboprop engines. Class TF means all turbofan or turbojet aircraft engines or aircraft engines designed for applications that otherwise would have been fulfilled by turbojet and turbofan engines except engines of class T3, T8, and TSS. Class T3 means all aircraft gas turbine engines of the JT3D model family. Class T8 means all aircraft gas turbine engines of the JT8D model family. Class TSS means all aircraft gas turbine engines employed for propulsion of aircraft designed to operate at supersonic flight speeds. Commercial aircraft engine means any aircraft engine used or intended for use by an “air carrier” (including those engaged in “intrastate air transportation”) or a “commercial operator” (including those engaged in “in… | |||
| 14:14:1.0.1.3.19.1.283.2 | 14 | Aeronautics and Space | I | C | 34 | PART 34—FUEL VENTING AND EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES | A | Subpart A—General Provisions | § 34.2 Abbreviations. | FAA | [Doc. No. FAA-2023-2434, Amdt. 34-7, 89 FR 31085, Apr. 24, 2024] | The abbreviations used in this part have the following meanings in both upper and lower case: CO 2 Carbon dioxide CO Carbon monoxide EPA United States Environmental Protection Agency FAA Federal Aviation Administration, United States Department of Transportation g Gram(s) HC Hydrocarbon(s) HP Horsepower hr Hour(s) H 2 O Water kg Kilogram(s) kJ Kilojoule(s) kN Kilonewton(s) kW Kilowatt(s) lbf Pound force LTO Landing and takeoff m Meter(s) mg Milligram(s) µg Microgram(s) min Minute(s) MJ Megajoule(s) NO X Oxides of nitrogen nvPM Non-volatile particulate matter nvPM mass Non-volatile particulate matter mass nvPM MC Non-volatile particulate matter mass concentration nvPM num Non-volatile particulate matter number Pa Pascal(s) rO Rated output rPR Rated pressure ratio sec Second(s) SP Shaft power SN Smoke number T Temperature in degrees Kelvin TIM Time in mode °C Degrees Celsius % Percent | |||
| 14:14:1.0.1.3.19.1.283.3 | 14 | Aeronautics and Space | I | C | 34 | PART 34—FUEL VENTING AND EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES | A | Subpart A—General Provisions | § 34.3 General requirements. | FAA | [Doc. No. FAA-2023-2434, Amdt. 34-7, 89 FR 31085, Apr. 24, 2024] | (a) This part provides for the approval or acceptance by the Administrator or the Administrator of the EPA of testing and sampling methods, analytical techniques, and related equipment not identical to those specified in this part. Before either approves or accepts any such alternate, equivalent, or otherwise nonidentical procedures or equipment, the Administrator or the Administrator of the EPA shall consult with the other in determining whether or not the action requires rulemaking under sections 231 and 232 of the Clean Air Act, as amended, consistent with the responsibilities of the Administrator of the EPA and the Secretary of Transportation under sections 231 and 232 of the Clean Air Act. (b) Under section 232 of the Act, the Secretary of Transportation issues regulations to ensure compliance with 40 CFR part 1031. This authority has been delegated to the Administrator of the FAA in accordance with 49 CFR 1.47. (c) This part applies to civil airplanes that are powered by aircraft gas turbine engines of the classes specified herein and that have U.S. standard airworthiness certificates. (d) Pursuant to the definition of “aircraft” in 40 CFR 1031.205, this regulation applies to civil airplanes that are powered by aircraft gas turbine engines of the classes specified herein and that have foreign airworthiness certificates that are equivalent to U.S. standard airworthiness certificates. This regulation applies only to those foreign civil airplanes that, if registered in the United States, would be required by applicable regulations to have a U.S. standard airworthiness certificate in order to conduct the operations intended for the airplane. Pursuant to 40 CFR 1031.5, this regulation does not apply where it would be inconsistent with an obligation assumed by the United States to a foreign country in a treaty, convention, or agreement. (e) Reference in this regulation to 40 CFR part 1031 refers to title 40 of the Code of Federal Regulations, chapter I—Environmental Protection Agency, part 1031, Control of Ai… | |||
| 14:14:1.0.1.3.19.1.283.4 | 14 | Aeronautics and Space | I | C | 34 | PART 34—FUEL VENTING AND EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES | A | Subpart A—General Provisions | § 34.4 Incorporation by Reference. | FAA | [Doc. No. FAA-2023-2434, Amdt. 34-7, 89 FR 31086, Apr. 24, 2024] | Certain material is incorporated by reference into this part with the approval of the Director of the Federal Register under 5 U.S.C. 552(a) and 1 CFR part 51). All approved material is available for inspection at the FAA and at the National Archives and Records Administration (NARA). Contact the FAA Office of Rulemaking (ARM), 800 Independence Avenue SW, Washington, DC 20590 (telephone 202-267-9677) For information on the availability of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or email fr.inspection@nara.gov. (a) The material may be obtained from the following source: International Civil Aviation Organization (ICAO): Document Sales Unit, 999 University Street, Montreal, Quebec H3C 5H7, Canada, phone + 1 514-954-8022, or www.icao.int. (1) Annex 16 to the Convention on International Civil Aviation: Environmental Protection, Volume II—Aircraft Engine Emissions, Third Edition, July 2008 (ICAO Annex 16); in §§ 34.1 and 34.60. (2) Annex 16 to the Convention on International Civil Aviation: Environmental Protection, Volume II—Aircraft Engine Emissions, Fourth Edition, July 2017 (ICAO Annex 16, Volume II), in §§ 34.71 and 34.73. (b) [Reserved] | |||
| 14:14:1.0.1.3.19.1.283.5 | 14 | Aeronautics and Space | I | C | 34 | PART 34—FUEL VENTING AND EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES | A | Subpart A—General Provisions | § 34.5 Special test procedures. | FAA | The Administrator or the Administrator of the EPA may, upon written application by a manufacturer or operator of aircraft or aircraft engines, approve test procedures for any aircraft or aircraft engine that is not susceptible to satisfactory testing by the procedures set forth herein. Prior to taking action on any such application, the Administrator or the Administrator of the EPA shall consult with the other. | ||||
| 14:14:1.0.1.3.19.1.283.6 | 14 | Aeronautics and Space | I | C | 34 | PART 34—FUEL VENTING AND EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES | A | Subpart A—General Provisions | § 34.6 Aircraft safety. | FAA | [Docket No. 25613, 55 FR 32861, Aug. 10, 1990, as amended by Amdt. No. 34-7, 89 FR 31086, Apr. 24, 2024] | (a) The provisions of this part will be revised if at any time the Administrator determines that an emission standard cannot be met within the specified time without creating a safety hazard. (b) Consistent with 40 CFR part 1031, if the FAA Administrator determines that any emission control regulation in this part cannot be safely applied to an aircraft, that provision may not be adopted or enforced against that aircraft by any state or political subdivision thereof. | |||
| 14:14:1.0.1.3.19.1.283.7 | 14 | Aeronautics and Space | I | C | 34 | PART 34—FUEL VENTING AND EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES | A | Subpart A—General Provisions | § 34.7 Exemptions. | FAA | [Doc. No. 25613, 55 FR 32861, Aug. 10, 1990, as amended by Amdt. 34-5, 77 FR 76850, Dec. 31, 2012; Amdt. 34-7, 89 FR 31087, Apr. 24, 2024] | Notwithstanding part 11 of the Federal Aviation Regulations (14 CFR part 11), all petitions for rulemaking involving either the substance of an emission standard or test procedure prescribed by the EPA that is incorporated in this FAR, or the compliance date for such standard or procedure, must be submitted to the EPA. Information copies of such petitions are invited by the FAA. Petitions for rulemaking or exemption involving provisions of this FAR that do not affect the substance or the compliance date of an emission standard or test procedure that is prescribed by the EPA, and petitions for exemptions under the provisions for which the EPA has specifically granted exemption authority to the Secretary of Transportation are subject to part 11 of the Federal Aviation Regulations (14 CFR part 11). Petitions for rulemaking or exemptions involving these FARs must be submitted to the FAA. (a) Exemptions based on flights for short durations at infrequent intervals. The emission standards of this part do not apply to engines which power aircraft operated in the United States for short durations at infrequent intervals. Such operations are limited to: (1) Flights of an aircraft for the purpose of export to a foreign country, including any flights essential to demonstrate the integrity of an aircraft prior to a flight to a point outside the United States. (2) Flights to a base where repairs, alterations or maintenance are to be performed, or to a point of storage, or for the purpose of returning an aircraft to service. (3) Official visits by representatives of foreign governments. (4) Other flights the Administrator determines, after consultation with the Administrator of the EPA, to be for short durations at infrequent intervals. A request for such a determination shall be made before the flight takes place. (b) Exemptions for very low production engine models. The emissions standards of this part do not apply to engines of very low production after the date of applicability. For the purpose of this part, “very… | |||
| 14:14:1.0.1.3.19.1.283.8 | 14 | Aeronautics and Space | I | C | 34 | PART 34—FUEL VENTING AND EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES | A | Subpart A—General Provisions | § 34.9 Exceptions. | FAA | [Doc. No. FAA-2012-1333, 77 FR 76850, Dec. 31, 2012] | (a) Spare engines. Certain engines that meet the following description are excepted: (1) This exception allows production of an engine for installation on an in-service aircraft. A spare engine may not be installed on a new aircraft. (2) Each spare engine must be identical to a sub-model previously certificated to meet all applicable requirements. (3) A spare engine may be used only when the emissions of the spare do not exceed the certification requirements of the original engine, for all regulated pollutants. (4) No separate approval is required to produce spare engines. (5) The record for each engine excepted under this paragraph (c) must indicate that the engine was produced as an excepted spare engine. (6) Engines produced under this exception must be labeled “EXCEPTED SPARE” in accordance with § 45.13 of this chapter. (b) On and after July 18, 2012, and before August 31, 2013, a manufacturer may produce up to six Tier 4 compliant engines that meet the NO X standards of paragraph (d)(1)(vi) of this section rather than § 34.23(a)(2). No separate approval is required to produce these engines. Engines produced under this exception are to be labeled “COMPLY” in accordance with § 45.13 of this chapter. | |||
| 14:14:1.0.1.3.19.2.283.1 | 14 | Aeronautics and Space | I | C | 34 | PART 34—FUEL VENTING AND EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES | B | Subpart B—Engine Fuel Venting Emissions (New and In-Use Aircraft Gas Turbine Engines) | § 34.10 Applicability. | FAA | [Doc. No. FAA-2012-1333, 77 FR 76850, Dec. 31, 2012] | (a) The provisions of this subpart are applicable to all new aircraft gas turbine engines of classes T3, T8, TSS, and TF equal to or greater than 36 kN (8,090 lb) rated output, manufactured on or after January 1, 1974, and to all in-use aircraft gas turbine engines of classes T3, T8, TSS, and TF equal to or greater than 36 kN (8,090 lb) rated output manufactured after February 1, 1974. (b) The provisions of this subpart are also applicable to all new aircraft gas turbine engines of class TF less than 36 kN (8,090 lb) rated output and class TP manufactured on or after January 1, 1975, and to all in-use aircraft gas turbine engines of class TF less than 36 kN (8,090 lb) rated output and class TP manufactured after January 1, 1975. | |||
| 14:14:1.0.1.3.19.2.283.2 | 14 | Aeronautics and Space | I | C | 34 | PART 34—FUEL VENTING AND EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES | B | Subpart B—Engine Fuel Venting Emissions (New and In-Use Aircraft Gas Turbine Engines) | § 34.11 Standard for fuel venting emissions. | FAA | [Docket No. 25613, 55 FR 32861, Aug. 10, 1990, as amended by Amdt. No. 34-7, 89 FR 31087, Apr. 24, 2024] | (a) No liquid fuel venting emissions shall be discharged into the atmosphere from any new or in-use aircraft gas turbine engine subject to the subpart. This paragraph is directed at the elimination of intentional discharge to the atmosphere of fuel drained from fuel nozzle manifolds after engines are shut down and does not apply to normal fuel seepage from shaft seals, joints, and fittings. (b) Conformity with the standard set forth in paragraph (a) of this section shall be determined by inspection of the method designed to eliminate these emissions. (c) As applied to an airframe or an engine, any manufacturer or operator may show compliance with the liquid fuel venting and emissions requirements of this section that were effective beginning February 1, 1974 or January 1, 1975, by any means that prevents the intentional discharge of fuel from fuel nozzle manifolds after the engines are shut down. Acceptable means of compliance include one of the following: (1) Incorporation of an FAA-approved system that recirculates the fuel back into the fuel system. (2) Capping or securing the pressurization and drain valve. (3) Manually draining the fuel from a holding tank into a container. | |||
| 14:14:1.0.1.3.19.3.283.1 | 14 | Aeronautics and Space | I | C | 34 | PART 34—FUEL VENTING AND EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES | C | Subpart C—Exhaust Emissions (New Aircraft Gas Turbine Engines) | § 34.20 Applicability. | FAA | The provisions of this subpart are applicable to all aircraft gas turbine engines of the classes specified beginning on the dates specified in § 34.21. | ||||
| 14:14:1.0.1.3.19.3.283.2 | 14 | Aeronautics and Space | I | C | 34 | PART 34—FUEL VENTING AND EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES | C | Subpart C—Exhaust Emissions (New Aircraft Gas Turbine Engines) | § 34.21 Standards for exhaust emissions. | FAA | [Doc. No. 25613, 55 FR 32861, Aug. 10, 1990; 55 FR 37287, Sept. 10, 1990, as amended by Amdt. 34-3, 64 FR 5559, Feb. 3, 1999; Amdt. 34-4, 74 FR 19127, Apr. 28, 2009; Amdt. 34-5, 77 FR 76851, Dec. 31, 2012; Amdt. No. 34-7, 89 FR 31087, Apr. 24, 2024] | (a) Exhaust emissions of smoke from each new aircraft gas turbine engine of class T8 manufactured on or after February 1, 1974, shall not exceed a smoke number (SN) of 30. (b) Exhaust emissions of smoke from each new aircraft gas turbine engine of class TF and of rated output of 129 kN (29,000 lb) thrust or greater, manufactured on or after January 1, 1976, shall not exceed SN = 83.6 (rO) −0.274 (rO is in kN). (c) Exhaust emission of smoke from each new aircraft gas turbine engine of class T3 manufactured on or after January 1, 1978, shall not exceed a smoke number (SN) of 25. (d) Gaseous exhaust emissions from each new aircraft gas turbine engine shall not exceed: (1) For Classes TF, T3, T8 engines greater than 26.7 kN (6,000 lb) rated output: (i) Engines manufactured on or after January 1, 1984: Hydrocarbons: 19.6 g/kN rO. (ii) Engines manufactured on or after July 7, 1997: Carbon Monoxide: 118 g/kN rO. (iii) Engines of a type or model of which the date of manufacture of the first individual production model was on or before December 31, 1995, and for which the date of manufacture of the individual engine was on or before December 31, 1999 (Tier 2): Oxides of Nitrogen: (40 + 2(rPR)) g/kN rO. (iv) Engines of a type or model of which the date of manufacture of the first individual production model was after December 31, 1995, or for which the date of manufacture of the individual engine was after December 31, 1999 (Tier 2): Oxides of Nitrogen: (32 + 1.6(rPR)) g/kN rO. (v) The emission standards prescribed in paragraphs (d)(1)(iii) and (iv) of this section apply as prescribed beginning July 7, 1997. (vi) The emission standards of this paragraph apply as prescribed after December 18, 2005. For engines of a type or model of which the first individual production model was manufactured after December 31, 2003 (Tier 4): (A) That have a rated pressure ratio of 30 or less and a maximum rated output greater than 89 kN: Oxides of Nitrogen: (19 + 1.6(rPR)) g/kN rO. (B) That have a rated pressure ratio of… | |||
| 14:14:1.0.1.3.19.3.283.3 | 14 | Aeronautics and Space | I | C | 34 | PART 34—FUEL VENTING AND EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES | C | Subpart C—Exhaust Emissions (New Aircraft Gas Turbine Engines) | § 34.23 Exhaust Emission Standards for Engines Manufactured on and after July 18, 2012. | FAA | [Doc. No. 34-5, 77 FR 76851, Dec. 31, 2012, as amended by Amdt. 34-5A, 78 FR 63017, Oct. 23, 2013; 78 FR 65554, Nov. 1, 2013; Amdt. No. 34-7, 89 FR 31087, Apr. 24, 2024] | The standards of this section apply to aircraft engines manufactured on and after July 18, 2012, unless otherwise exempted or excepted. Where a gaseous emission standard is specified by a formula, calculate and round the standard to three significant figures or to the nearest 0.1 g/kN (for standards at or above 100 g/kN). Where a smoke standard is specified by a formula, calculate and round the standard to the nearest 0.1 SN. Engines comply with an applicable standard if the testing results show that the engine type certificate family's characteristic level does not exceed the numerical level of that standard, as described in § 34.60. (a) Gaseous exhaust emissions from each new aircraft gas turbine engine shall not exceed: (1) [Reserved] (2) Except as provided in §§ 34.9(b) and 34.21(c), for Classes TF, T3 and T8 engines manufactured on and after July 18, 2012, and for which the first individual production model was manufactured on or before December 31, 2013 (Tier 6): Tier 6 Oxides of Nitrogen Emission Standards for Subsonic Engines (3) Engines exempted from paragraph (a)(2) of this section produced on or before December 31, 2016 must be labeled “EXEMPT NEW” in accordance with § 45.13 of this chapter. No exemptions to the requirements of paragraph (a)(2) of this section will be granted after December 31, 2016. (4) For Class TSS Engines manufactured on and after July 18, 2012: Gaseous Emission Standards for Supersonic Engines 1 rO is the rated output with afterburning applied. (b) Gaseous exhaust emissions from each new aircraft gas turbine engine shall not exceed: (1) For Classes TF, T3 and T8 engines of a type or model of which the first individual production model was manufactured after December 31, 2013 (Tier 8): Tier 8 Oxides of Nitrogen Emission Standards for Subsonic Engines (c) Engines (including engines that are determined to be derivative engines for the purposes of emission certification) type certificated with characteristic levels at or below the NO X standards of § 34.21(d)(1)(vi) of t… | |||
| 14:14:1.0.1.3.19.3.283.4 | 14 | Aeronautics and Space | I | C | 34 | PART 34—FUEL VENTING AND EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES | C | Subpart C—Exhaust Emissions (New Aircraft Gas Turbine Engines) | § 34.25 Non-volatile particulate emissions standards (nvPM). | FAA | [Doc. No. FAA-2023-2434, Amdt. No. 34-7, 89 FR 31087, Apr. 24, 2024, as amended by Amdt. No. 34-7A, 89 FR 37972, May 7, 2024] | The standards of this section apply to an aircraft engine of Class TF, T3, or T8 with a rated output greater than 26.7 kN that is manufactured after January 1, 2023. Where a maximum nvPM MC standard is expressed as a formula, calculate and round the standard to the nearest 1.0 µg/m 3 . Where an nvPM mass standard is expressed as a formula, calculate and round the standard to three significant figures or to the nearest 0.1 mg/kN. Where an nvPM num standard is expressed as a formula, calculate and round the standard to three significant figures. Engines comply with an applicable standard if the test results show that the engine type certificate family's characteristic level does not exceed the numerical level of the nvPM standard when tested as described in subpart H of this part. (a) Except as provided in paragraph (b) or (c) of this section; (1) The characteristic level for the maximum nvPM MC expressed in units of µg/m 3 must not exceed the following: nvPM MC = 10 (3+2.9 r0 -0.274 ) and (2) The characteristic level for nvPM mass expressed in [mg/kN] and for nvPM number expressed in [particles/kN] must not exceed the following: Table 1 to Paragraph ( a )(2) (b) For a change in type design by the type design holder, when the application for an amended type certificate is filed after January 1, 2023: (1) If the engine qualifies as a derivative engine in accordance with § 34.48 of this part, no testing is required for the engine to use the same nvPM certificated parameters (nvPM mass , nvPM num , and maximum nvPM MC ) as the engine it is derived from; or (2) If the engine does not qualify as a derivative engine in accordance with § 34.48 of this part, the applicant must demonstrate compliance with each requirement in paragraph (a) of this section. (c) For issuance of an original type certificate when an application for type certification is filed after January 1, 2023, the applicant must demonstrate that the engine does not exceed: (1) For maximum nvPM MC : as prescribed in paragraph (a)(1) of thi… | |||
| 14:14:1.0.1.3.19.4.283.1 | 14 | Aeronautics and Space | I | C | 34 | PART 34—FUEL VENTING AND EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES | D | Subpart D—Exhaust Emissions (In-use Aircraft Gas Turbine Engines) | § 34.30 Applicability. | FAA | The provisions of this subpart are applicable to all in-use aircraft gas turbine engines certificated for operation within the United States of the classes specified, beginning on the dates specified in § 34.31. | ||||
| 14:14:1.0.1.3.19.4.283.2 | 14 | Aeronautics and Space | I | C | 34 | PART 34—FUEL VENTING AND EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES | D | Subpart D—Exhaust Emissions (In-use Aircraft Gas Turbine Engines) | § 34.31 Standards for exhaust emissions. | FAA | [Doc. No. FAA-2012-1333, 77 FR 76852, Dec. 31, 2012] | (a) Exhaust emissions of smoke from each in-use aircraft gas turbine engine of Class T8, beginning February 1, 1974, shall not exceed a smoke number (SN) of 30. (b) Exhaust emissions of smoke from each in-use aircraft gas turbine engine of Class TF and of rated output of 129 kN (29,000 lb) thrust or greater, beginning January l, 1976, shall not exceed SN = 83.6(rO) −0.274 (rO is in kN). (c) The standards set forth in paragraphs (a) and (b) of this section refer to exhaust smoke emission emitted during operation of the engine as specified in the applicable sections of subpart G of this part, and measured and calculated in accordance with the procedures set forth in subpart G. | |||
| 14:14:1.0.1.3.19.5.283.1 | 14 | Aeronautics and Space | I | C | 34 | PART 34—FUEL VENTING AND EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES | E | Subpart E—Certification Provisions | § 34.48 Derivative engines for emissions certification purposes. | FAA | [Doc. No. 34-5, 77 FR 76852, Dec. 31, 2012, as amended by Amdt. No. 34-7, 89 FR 31088, Apr. 24, 2024] | (a) General. A type certificate holder may request from the FAA a determination that an engine configuration is considered a derivative engine for emissions certification purposes (all gaseous emissions and either nvPM or smoke number as applicable). To be considered a derivative engine for emissions certification purposes under this part, the configuration must have been derived from the original engine that was certificated to the requirements of part 33 of this chapter and one of the following: (1) The FAA has determined that a safety issue exists that requires an engine modification. (2) Emissions from the derivative engines are determined to be similar. In general, this means the emissions must meet the criteria specified in paragraph (b) of this section. The FAA may amend the criteria of paragraph (b) in unusual circumstances, for individual cases, consistent with good engineering judgment. (3) All of the regulated emissions from the derivative engine are lower than the original engine. (b) Emission similarity (1) The type certificate holder must demonstrate that the proposed derivative engine model's emissions meet the applicable standards and differ from the original model's emission rates within the following ranges and values: (i) ±3.0 g/kN for NO X . (ii) ±1.0 g/kN for HC. (iii) ±5.0 g/kN for CO. (iv) ±2.0 SN for smoke (where applicable). (v) The following values apply for maximum nvPM MC , nvPM mass , and nvPM num (where applicable): (A) maximum nvPM MC : ( 1 ) ±200 µg/m3 if the characteristic level of maximum nvPM MC is below 1,000 µg/m 3 ; or ( 2 ) ±20% of the characteristic level if the characteristic level for maximum nvPM MC is at or above 1,000 µg/m 3 . (B) nvPM mass : ( 1 ) 80 mg/kN if the characteristic level for nvPM mass emissions is below 400 mg/kN; or ( 2 ) ±20% of the characteristic level if the characteristic level for nvPM mass emissions is greater than or equal to 400 mg/kN. (C) nvPM num : ( 1 ) 4 × 10 14 particles/kN if the characteristic level for nvPM n… | |||
| 14:14:1.0.1.3.19.7.283.1 | 14 | Aeronautics and Space | I | C | 34 | PART 34—FUEL VENTING AND EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES | G | Subpart G—Test Procedures for Engine Exhaust Gaseous Emissions (Aircraft and Aircraft Gas Turbine Engines) | § 34.60 Introduction. | FAA | [Doc. No. FAA-2012-1333, 77 FR 76853, Dec. 31, 2012, as amended by Doc. No. FAA-2018-0119, Amdt. 34-6, 83 FR 9170, Mar. 5, 2018; Doc. No. FAA-2023-2434; Amdt. No. 34-7, 89 FR 31088, Apr. 24, 2024] | (a) Use the equipment and procedures specified in Appendix 3, Appendix 5, and Appendix 6 of ICAO Annex 16, as applicable, to demonstrate whether engines meet the applicable gaseous emission standards specified in subpart C of this part. Measure the emissions of all regulated gaseous pollutants. Use the equipment and procedures specified in Appendix 2 and Appendix 6 of ICAO Annex 16 to determine whether engines meet the applicable smoke standard specified in subpart C of this part. The compliance demonstration consists of establishing a mean value from testing the specified number of engines, then calculating a “characteristic level” by applying a set of statistical factors that take into account the number of engines tested. Round each characteristic level to the same number of decimal places as the corresponding emission standard. For turboprop engines, use the procedures specified for turbofan engines, consistent with good engineering judgment. (b) Use a test fuel that meets the specifications described in Appendix 4 of ICAO Annex 16. The test fuel must not have additives whose purpose is to suppress smoke, such as organometallic compounds. (c) Prepare test engines by including accessories that are available with production engines if they can reasonably be expected to influence emissions. The test engine may not extract shaft power or bleed service air to provide power to auxiliary gearbox-mounted components required to drive aircraft systems. (d) Test engines must reach a steady operating temperature before the start of emission measurements. (e) In consultation with the EPA, the FAA may approve alternative procedures for measuring emissions, including testing and sampling methods, analytical techniques, and equipment specifications that differ from those specified in this part. Manufacturers and operators may request approval of alternative procedures by written request with supporting justification to the FAA and to the Designated EPA Program Officer. To be approved, one of the following conditions must… | |||
| 14:14:1.0.1.3.19.7.283.2 | 14 | Aeronautics and Space | I | C | 34 | PART 34—FUEL VENTING AND EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES | G | Subpart G—Test Procedures for Engine Exhaust Gaseous Emissions (Aircraft and Aircraft Gas Turbine Engines) | §§ 34.61-34.71 [Reserved] | FAA | |||||
| 14:14:1.0.1.3.19.8.283.1 | 14 | Aeronautics and Space | I | C | 34 | PART 34—FUEL VENTING AND EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES | H | Subpart H—Test Procedures and Compliance Demonstration for Non-Volatile Particulate Matter Emissions | § 34.71 Non-volatile particulate matter (nvPM) test procedures. | FAA | For each Class TF, T3, or T8 engine manufactured after January 1, 2023, that has a rated output greater than 26.7 kN, the test procedures for measuring each required nvPM parameter are as follows: (a) Measure the emissions of all nvPM parameters required in this part, as applicable. (b) Collect data from at least three engine tests, with each test conducted at the reference LTO time/thrust combinations shown in paragraph (h) of this section. (c) For the engines referenced in paragraph (b) of this section, all emissions certification tests may be conducted on one or more engines of the same type design. (d) Use a test fuel that meets the specifications described in Appendix 4 of ICAO Annex 16, Volume II (incorporated by reference, see § 34.4). The test fuel must not have any additive whose purpose is to suppress nvPM emissions. (e) (1) When conducting test measurements in accordance with paragraphs (a) through (c) of this section, use the equipment and procedures specified in Appendix 1, Appendix 4, Appendix 6, and Appendix 7 of ICAO Annex 16, Volume II (incorporated by reference, see § 34.4), when demonstrating whether an engine meets the applicable nvPM limit specified in § 34.25 of this part. (2) An applicant that seeks to use a procedure or equipment that differs from any specified in this part must request FAA approval in writing with supporting justification before the alternative procedure or equipment may be used to demonstrate compliance. The FAA will consult with the EPA on any such request. The FAA may approve the requested alternative for measuring nvPM, including testing and sampling methods, analytical techniques, and equipment specifications. Each request must meet one of the following conditions: (i) The engine cannot be tested using a specified procedure; or (ii) The alternative procedure is shown to be equivalent to, or more accurate or precise than, the specified procedure. (f) Any engine accessory included in a type design that may reasonably be expected to influence either nvPM emissi… | ||||
| 14:14:1.0.1.3.19.8.283.2 | 14 | Aeronautics and Space | I | C | 34 | PART 34—FUEL VENTING AND EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES | H | Subpart H—Test Procedures and Compliance Demonstration for Non-Volatile Particulate Matter Emissions | § 34.73 Demonstration of compliance for nvPM emissions. | FAA | (a) Each compliance demonstration by an applicant requires: (1) Establishing a mean value from tests conducted on one or more engines; (2) Calculating a “characteristic level” by applying a set of statistical factors that take into account the number of engines tested in accordance with § 34.71(b) of this part; and (3) Rounding each characteristic level to the same number of decimal places as the corresponding emission limit. (b) In demonstrating compliance with this subpart, an applicant must use the nvPM measurements collected in accordance with § 34.71 as follows: (1) An engine complies with an applicable standard when the engine type certificate family's characteristic level does not exceed any nvPM limit described in § 34.25 of this part; and (2) A compliance demonstration consists of: (i) Determining the maximum nvPM MC , and the mean value for nvPM mass and nvPM num from the data collected in accordance with paragraph § 34.71(f) of this part; (ii) Correcting each data point to standard temperature and pressure conditions; (iii) Applying the appropriate statistical factor shown in Table 6-1 of Appendix 6 of ICAO Annex 16, Volume II (incorporated by reference, see § 34.4) to account for the number of engines tested; and (iv) Rounding each characteristic level to the same number of decimal places as the corresponding nvPM limit in § 34.25 of this part. (c) (1) In determining maximum nvPM MC , an applicant must use one of the following evaluation methods for all engines measured in accordance with § 34.71(c) of this par and using the thrust settings given in § 34.71(h) of this part. An applicant may choose to measure additional thrust settings; while there is no restriction on the number of thrust settings measured, the same thrust settings must be used on each engine tested. A dataset consists of nvPM MC measurements made at each thrust setting across the thrust range chosen by the applicant for each engine. Plot all nvPM MC measurements versus thrust setting. (i) Method 1— (A) Average the in… |
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