14 C.F.R. Subpart G—Test Procedures for Engine Exhaust Gaseous Emissions (Aircraft and Aircraft Gas Turbine Engines)
Title 14 - Aeronautics and Space
Title 14: Aeronautics and Space
PART 34—FUEL VENTING AND EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES
Browse Previous |
Browse Next
Subpart G—Test Procedures for Engine Exhaust Gaseous Emissions (Aircraft and Aircraft Gas Turbine Engines)
§ 34.60 Introduction.
(a) Except as provided under §34.5, the procedures described in this subpart shall constitute the test program used to determine the conformity of new aircraft gas turbine engines with the applicable standards set forth in this part.
(b) The test consists of operating the engine at prescribed power settings on an engine dynamometer (for engines producing primarily shaft power) or thrust measuring test stand (for engines producing primarily thrust). The exhaust gases generated during engine operation must be sampled continuously for specific component analysis through the analytical train.
(c) The exhaust emission test is designed to measure concentrations of hydrocarbons, carbon monoxide, carbon dioxide, and oxides of nitrogen, and to determine mass emissions through calculations during a simulated aircraft landing-takeoff cycle (LTO). The LTO cycle is based on time in mode data during high activity periods at major airports. The test for propulsion engines consists of at least the following four modes of engine operation: taxi/idle, takeoff, climbout, and approach. The mass emission for the modes are combined to yield the reported values.
(d) When an engine is tested for exhaust emissions on an engine dynamometer or test stand, the complete engine (with all accessories which might reasonably be expected to influence emissions to the atmosphere installed and functioning), shall be used if not otherwise prohibited by §34.62(a)(2). Use of service air bleed and shaft power extraction to power auxiliary, gearbox-mounted components required to drive aircraft systems is not permitted.
(e) Other gaseous emissions measurement systems may be used if shown to yield equivalent results and if approved in advance by the Administrator or the Administrator of the EPA.
[Doc. No. 25613, 55 FR 32861, Aug. 10, 1990, as amended by Amdt. 34–3, 64 FR 5559, Feb. 3, 1999]
§ 34.61 Turbine fuel specifications.
For exhaust emission testing, fuel that meets the specifications listed in this section shall be used. Additives used for the purpose of smoke suppression (such as organometallic compounds) shall not be present.
Specification for Fuel To Be Used in Aircraft Turbine Engine Emission Testing------------------------------------------------------------------------ Property Allowable range of values------------------------------------------------------------------------Density at 15 °C...................... 780-820.Distillation Temperature, °C 10% 155-201. Boiling Point.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 %.......................... 13.4-14.1.Sulfur Mass %............................. Less than 0.3%.Kinematic viscosity at_20 °C, mm \2\ / 2.5-6.5. sec.------------------------------------------------------------------------
|
[Doc. No. FAA–1999–5018, 64 FR 5559, Feb. 3, 1999] § 34.62 Test procedure (propulsion engines).
(a)(1) The engine shall be tested in each of the following engine operating modes which simulate aircraft operation to determine its mass emission rates. The actual power setting, when corrected to standard day conditions, should correspond to the following percentages of rated output. Analytical correction for variations from reference day conditions and minor variations in actual power setting should be specified and/or approved by the Administrator:
|
------------------------------------------------------------------------ Class Mode ----------------------------------- TP TF, T3, T8 TSS------------------------------------------------------------------------Taxi/idle........................... (*) (*) (*)Takeoff............................. 100 100 100Climbout............................ 90 85 65Descent............................. NA NA 15Approach............................ 30 30 34------------------------------------------------------------------------*See paragraph (a) of this section.
|
(2) The taxi/idle operating modes shall be carried out at a power setting of 7% rated thrust unless the Administrator determines that the unique characteristics of an engine model undergoing certification testing at 7% would result in substantially different HC and CO emissions than if the engine model were tested at the manufacturers recommended idle power setting. In such cases the Administrator shall specify an alternative test condition.
(3) The times in mode (TIM) shall be as specified below:
|
------------------------------------------------------------------------ Class Mode ----------------------------------- TP TF, T3, T8 TSS------------------------------------------------------------------------Taxi/idle........................... 26.0 Min. 26.0 Min. 26.0 Min.Takeoff............................. 0.5 0.7 1.2Climbout............................ 2.5 2.2 2.0Descent............................. N/A N/A 1.2Approach............................ 4.5 4.0 2.3------------------------------------------------------------------------
|
(b) Emissions testing shall be conducted on warmed-up engines which have achieved a steady operating temperature.
[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] § 34.63 [Reserved]
§ 34.64 Sampling and analytical procedures for measuring gaseous exhaust emissions.
The system and procedures for sampling and measurement of gaseous emissions shall be as specified in Appendices 3 and 5 to the International Civil Aviation Organization (ICAO) Annex 16, Environmental Protection, Volume II, Aircraft Engine Emissions, Second Edition, July 1993, effective March 20, 1997. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. This document can be obtained from the International Civil Aviation Organization (ICAO), Document Sales Unit, P.O. Box 400, Succursale: Place de L'Aviation Internationale, 1000 Sherbrooke Street West, Suite 400, Montreal, Quebec, Canada H3A 2R2. Copies may be reviewed at the FAA Office of the Chief Counsel, Rules Docket, Room 916, Federal Aviation Administration Headquarters Building, 800 Independence Avenue, SW., Washington, DC, or at the FAA New England Regional Office, 12 New England Executive Park, Burlington, Massachusetts, or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.php.
[Doc. No. FAA–1999–5018, 64 FR 5559, Feb. 3, 1999; Amdt. 34–3, 64 FR 60336, Nov. 5, 1999; 69 FR 18803, Apr. 9, 2004] §§ 34.65-34.70 [Reserved]
§ 34.71 Compliance with gaseous emission standards.
Compliance with each gaseous emission standard by an aircraft engine shall be determined by comparing the pollutant level in grams/kilonewton/thrust/cycle or grams/kilowatt/cycle as calculated in §34.64 with the applicable emission standard under this part. An acceptable alternative to testing every engine is described in Appendix 6 to ICAO Annex 16, Environmental Protection, Volume II, Aircraft Engine Emissions, Second Edition, July 1993, effective July 26, 1993. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. This document can be obtained from, and copies may be reviewed at, the respective addresses listed in §34.64. Other methods of demonstrating compliance may be approved by the FAA Administrator with the concurrence of the Administrator of the EPA.
[Doc. No. FAA–1999–5018, 64 FR 5559, Feb. 3, 1999; Amdt. 34–3, 64 FR 60336, Nov. 5, 1999]
Browse Previous |
Browse Next
|
