[Title 40 CFR 87]
[Code of Federal Regulations (annual edition) - July 1, 1996 Edition]
[Title 40 - PROTECTION OF ENVIRONMENT]
[Chapter I - ENVIRONMENTAL PROTECTION AGENCY (CONTINUED)]
[Part 87 - CONTROL OF AIR POLLUTION FROM AIRCRAFT AND AIRCRAFT ENGINES]
[From the U.S. Government Publishing Office]
40
PROTECTION OF ENVIRONMENT
9
1996-07-01
1996-07-01
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CONTROL OF AIR POLLUTION FROM AIRCRAFT AND AIRCRAFT ENGINES
87
PART 87
PROTECTION OF ENVIRONMENT
ENVIRONMENTAL PROTECTION AGENCY (CONTINUED)
PART 87--CONTROL OF AIR POLLUTION FROM AIRCRAFT AND AIRCRAFT ENGINES--Table of Contents
Subpart A--General Provisions
Sec.
87.1 Definitions.
87.2 Abbreviations.
87.3 General requirements.
87.4 [Reserved]
87.5 Special test procedures.
87.6 Aircraft safety.
87.7 Exemptions.
Subpart B--Engine Fuel Venting Emissions (New and In-Use Aircraft Gas
Turbine Engines)
87.10 Applicability.
87.11 Standard for fuel venting emissions.
Subpart C--Exhaust Emissions (New Aircraft Gas Turbine Engines)
87.20 Applicability.
87.21 Standards for exhaust emissions.
Subpart D--Exhaust Emissions (In-Use Aircraft Gas Turbine Engines)
87.30 Applicability.
87.31 Standards for exhaust emissions.
Subparts E-F--[Reserved]
Subpart G--Test Procedures for Engine Exhaust Gaseous Emissions
(Aircraft and Aircraft Gas Turbine Engines)
87.60 Introduction.
87.61 Turbine fuel specifications.
87.62 Test procedure (propulsion engines).
87.63 [Reserved]
87.64 Sampling and analytical procedures for measuring gaseous exhaust
emissions.
87.65--87.70 [Reserved]
87.71 Compliance with gaseous emission standards.
Subpart H--Test Procedures for Engine Smoke Emissions (Aircraft Gas
Turbine Engines)
87.80 Introduction.
87.81 Fuel specifications.
87.82 Sampling and analytical procedures for measuring smoke exhaust
emissions.
87.83--87.88 [Reserved]
87.89 Compliance with smoke emission standards.
Authority: Secs. 231, 301(a), Clean Air Act, as amended (42 U.S.C.
7571, 7601(a)), unless otherwise noted.
Source: 47 FR 58470, Dec. 30, 1982, unless otherwise noted.
Subpart A--General Provisions
Sec. 87.1 Definitions.
(a) As used in this part, all terms not defined herein shall have
the meaning given them in the Act:
Act means the Clean Air Act, as amended (42 U.S.C. 7401 et seq.).
Administrator means the Administrator of the Environmental
Protection Agency and any other officer or employee of the Environmental
Protection Agency to whom authority involved may be delegated.
Aircraft means any airplane 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.
Class TP means all aircraft turboprop engines.
Class TF means all turbofan or turbojet aircraft 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 ``intrastate air transportation'') as these
terms are defined in the Federal Aviation Act and the Federal Aviation
Regulations.
Commercial aircraft gas turbine engine means a turboprop, turbofan,
or turbojet commercial aircraft engine.
Emission measurement system means all of the equipment necessary to
transport and measure the level of emissions. This includes the sample
system and the instrumentation system.
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Engine Model means all commercial aircraft turbine engines which are
of the same general series, displacement, and design characteristics and
are usually approved under the same type certificate.
Exhaust emissions means substances emitted to the atmosphere from
the exhaust discharge nozzle of an aircraft or aircraft engine.
Fuel venting emissions means raw fuel, exclusive of hydrocarbons in
the exhaust emissions, discharged from aircraft gas turbine engines
during all normal ground and flight operations.
In-use aircraft gas turbine engine means an aircraft gas turbine
engine which is in service.
New aircraft turbine engine means an aircraft gas turbine engine
which has never been in service.
Power setting means the power or thrust output of an engine in terms
of kilonewtons thrust for turbojet and turbofan engines and shaft power
in terms of kilowatts for turboprop engines.
Rated output (rO) means the maximum power/thrust available for
takeoff at standard day conditions as approved for the engine by the
Federal Aviation Administration, including reheat contribution where
applicable, but excluding any contribution due to water injection.
Rated pressure ratio (rPR) means the ratio between the combustor
inlet pressure and the engine inlet pressure achieved by an engine
operating at rated output.
Sample system means the system which provides for the transportation
of the gaseous emission sample from the sample probe to the inlet of the
instrumentation system.
Secretary means the Secretary of Transportation and any other
officer or employee of the Department of Transportation to whom the
authority involved may be delegated.
Shaft power means only the measured shaft power output of a
turboprop engine.
Smoke means the matter in exhaust emissions which obscures the
transmission of light.
Smoke number (SN) means the dimensionless term quantifying smoke
emissions.
Standard day conditions means standard ambient conditions as
described in the United States Standard Atmosphere, 1976, (i.e.,
Temperature =15 deg.C, specific humidity =0.00 kg/ H2O/kg dry air,
and pressure =101325 Pa.)
Taxi/idle (in) means those aircraft operations involving taxi and
idle between the time of landing roll-out and final shutdown of all
propulsion engines.
Taxi/idle (out) means those aircraft operations involving taxi and
idle between the time of initial starting of the propulsion engine(s)
used for the taxi and turn on to duty runway.
[47 FR 58470, Dec. 30, 1982, as amended at 49 FR 31875, Aug. 9, 1984]
Sec. 87.2 Abbreviations.
The abbreviations used in this part have the following meanings in
both upper and lower case:
FAA Federal Aviation Administration, Department of Transportation.
HC Hydrocarbon(s).
hr. Hour(s).
LTO Landing takeoff
min. Minute(s).
rO Rated output.
rPR Rated pressure ratio.
sec. Seconds.
SP Shaft power.
SN Smoke number.
T Temperature, degrees Kelvin.
TIM Time in mode.
W Watt(s).
deg. Degree.
% Percent.
[47 FR 58470, Dec. 30, 1982, as amended at 49 FR 31875, Aug. 9, 1984]
Sec. 87.3 General requirements.
(a) This part provides for the approval or acceptance by the
Administrator or the Secretary 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 Secretary 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 Administrator's
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and the Secretary's responsibilities under sections 231 and 232 of the
Act. (42 U.S.C. 7571, 7572).
(b) Under section 232 of the Act, the Secretary issues regulations
to insure compliance with this part.
(c) With respect to aircraft of foreign registry, these regulations
shall apply in a manner consistent with any obligation assumed by the
United States in any treaty, convention or agreement between the United
States and any foreign country or foreign countries.
Sec. 87.4 [Reserved]
Sec. 87.5 Special test procedures.
The Administrator or the Secretary 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
Secretary shall consult with the other.
Sec. 87.6 Aircraft safety.
The provisions of this part will be revised if at any time the
Secretary determines that an emission standard cannot be met within the
specified time without creating a safety hazard.
Sec. 87.7 Exemptions.
(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 its 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, and flights for the purpose
of returning an aircraft to service.
(3) Official visits by representatives of foreign governments.
(4) Other flights the Secretary determines, after consultation with
the Administrator, 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 models. The emissions
standards of this part do not apply to engines of very low total
production after the date of applicability. For the purpose of this
part, ``very low production'' is limited to a maximum total production
for United States civil aviation applications of no more than 200 units
covered by the same type certificate after January 1, 1984.
(1) A maximum annual production rate after January 1, 1984 of 20
units covered by the same type certificate; and
(2) A maximum total production after January 1, 1984 of 200 units
covered by the same type certificate.
(c) Exemptions for New Engines in Other Categories. The emissions
standards of this part do not apply to engines for which the Secretary
determines, with the concurrence of the Administrator, that application
of any standard under Sec. 87.21 is not justified, based upon
consideration of:
(1) Adverse economic impact on the manufacturer.
(2) Adverse economic impact on the aircraft and airline industries
at large.
(3) Equity in administering the standards among all economically
competing parties.
(4) Public health and welfare effects.
(5) Other factors which the Secretary, after consultation with the
Administrator, may deem relevant to the case in question.
(d) Time Limited Exemptions for In Use Engines. The emissions
standards of this part do not apply to aircraft or aircraft engines for
time periods which the Secretary determines, with the concurrence of the
Administrator, that any applicable standard under Sec. 87.11(a),
Sec. 87.31(a), or Sec. 87.31(c), should not be applied based upon
consideration of the following:
(1) Documentation demonstrating that all good faith efforts to
achieve compliance with such standard have been made.
(2) Documentation demonstrating that the inability to comply with
such
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standard is due to circumstances beyond the control of the owner or
operator of the aircraft.
(3) A plan in which the owner or operator of the aircraft shows that
he will achieve compliance in the shortest time which is feasible.
(4) Applications for a determination that any requirements of
Sec. 87.11(a), Sec. 87.31(a) or Sec. 87.31(c) do not apply shall be
submitted in duplicate to the Secretary in accordance with procedures
established by the Secretary.
(e) The Secretary shall publish in the Federal Register the name of
the organization to whom exemptions are granted and the period of such
exemptions.
(f) No state or political subdivision thereof may attempt to enforce
a standard respecting emissions from an aircraft or engine if such
aircraft or engine has been exempted from such standard under this part.
[47 FR 58470, Dec. 30, 1982, as amended at 49 FR 31875, Aug. 9, 1984; 49
FR 41002, Oct. 18, 1984]
Subpart B--Engine Fuel Venting Emissions (New and In-Use Aircraft Gas
Turbine Engines)
Sec. 87.10 Applicability.
(a) The provisions of this subpart are applicable to all new
aircraft gas turbines of classes T3, T8, TSS and TF equal to or greater
than 36 kilonewton 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 kilonewton rated output
manufactured after February 1, 1974.
(b) The provisions of this subpart are also applicable to all new
aircraft gas turbines of class TF less than 36 kilonewton rated output
and class TP manufactured on or after January 1, 1975 and to all in-use
aircraft gas turbines of class TF less than 36 kilonewton rated output
and class TP manufactured after January 1, 1975.
[49 FR 41002, Oct. 18, 1984]
Sec. 87.11 Standard for fuel venting emissions.
(a) No 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.
Subpart C--Exhaust Emissions (New Aircraft Gas Turbine Engines)
Sec. 87.20 Applicability.
The provisions of this subpart are applicable to all aircraft gas
turbine engines of the classes specified beginning on the dates
specified.
Sec. 87.21 Standards for exhaust emissions.
(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: Smoke number of 30.
(b) Exhaust emissions of smoke from each new aircraft gas turbine
engine of class TF and of rated output of 129 kilonewtons thrust or
greater, manufactured on or after January 1, 1976, shall not exceed:
SN=83.6(r0)-0.274 (r0 is in kilonewtons).
(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: Smoke number of 25.
(d) Gaseous exhaust emissions from each new commercial aircraft gas
turbine engine that is manufactured on or after January 1, 1984, shall
not exceed:
(1) Classes TF, T3, T8 engines equal to or greater than 26.7
kilonewtons rated output:
Hydrocarbons: 19.6 grams/kilonewton r0.
(2) Class TSS:
Hydrocarbons=140(0.92)rPR grams/kilonewton r0.
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(e) Smoke exhaust emissions from each gas turbine engine of the
classes specified below shall not exceed:
(1) Class TF of rated output less than 26.7 kilonewtons manufactured
on or after (one year from date of publication):
SN=83.6(ro)-0.274 (ro is in kilonewtons) not to exceed a maximum of
SN=50.
(2) Classes T3, T8, TSS and TF of rated output equal to or greater
than 26.7 kilonewtons manufactured on or after January 1, 1984:
SN=83.6(ro)-0.274 (ro is in kilonewtons) not to exceed a maximum of
SN=50.
(3) Class TP of rated output equal to or greater than 1,000
kilowatts manufactured on or after January 1, 1984:
SN=187(ro)-168 (ro is in kilowatts)
(f) The standards set forth in paragraphs (a), (b), (c), (d), and
(e) of this section refer to a composite gaseous emission sample
representing the operating cycles set forth in the applicable sections
of subpart G of this part, and exhaust smoke emissions emitted during
operations of the engine as specified in the applicable sections of
subpart H of this part, measured and calculated in accordance with the
procedures set forth in those subparts.
[47 FR 58470, Dec. 30, 1982, as amended at 49 FR 31875, Aug. 9, 1984]
Subpart D--Exhaust Emissions (In-use Aircraft Gas Turbine Engines)
Sec. 87.30 Applicability.
The provisions of this subpart are applicable to all in-use aircraft
gas turbine engines certified for operation within the United States of
the classes specified beginning on the dates specified.
Sec. 87.31 Standards for exhaust emissions.
(a) Exhaust emissions of smoke from each in-use aircraft gas turbine
engine of Class T8, beginning February 1, 1974, shall not exceed: Smoke
number of 30.
(b) Exhaust emissions of smoke from each in-use aircraft gas turbine
engine of class TF and of rated output of 129 kilonewtons thrust or
greater, beginning January 1, 1976, shall not exceed:
SN=83.6(r0)-0.274 (r0 is in kilonewtons).
(c) The standards set forth in paragraphs (a) and (b) of this
section refer to exhaust smoke emissions emitted during operations of
the engine as specified in the applicable section of subpart H of this
part, and measured and calculated in accordance with the procedures set
forth in this subpart.
[47 FR 58470, Dec. 30, 1982, as amended at 48 FR 2718, Jan. 20, 1983]
Subparts E-F--[Reserved]
Subpart G--Test Procedures for Engine Exhaust Gaseous Emissions
(Aircraft and Aircraft Gas Turbine Engines)
Sec. 87.60 Introduction.
(a) Except as provided under Sec. 87.5, the procedures described in
this subpart shall be the test program 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 are sampled
continuously for specific component analysis through the analytical
train.
(c) The exhaust emission test is designed to measure hydrocarbons,
carbon monoxide and carbon dioxide concentrations, 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 a 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
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engine shall be used with all accessories which might reasonably be
expected to influence emissions to the atmosphere installed and
functioning, if not otherwise prohibited by Sec. 87.62(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 Secretary.
[47 FR 58470, Dec. 30, 1982, as amended at 49 FR 31875, Aug. 9, 1984]
Sec. 87.61 Turbine fuel specifications.
For exhaust emission testing, fuel meeting the specifications listed
below shall be used. Additives used for the purpose of smoke suppression
(such as organometallic compounds) shall not be present.
Property and Allowable Range of Values
Specific gravity at 15 deg.C: 0.78-0.82.
Distillation temperature, deg.C: 10% boiling point, 160-201; final
boiling point, 240-285.
Net heat of combustion, kJ/kg: 42,860-43,500.
Aromatics, volume %: 15-20.
Naphthalenes, volume %: 1.0-3.0.
Smoke point, mm: 20-28.
Hydrogen, mass %: 13.4-14.0.
Sulfur, mass %: less than 0.3%.
Kinematic viscosity at -20 deg.C, mm/s: 4.0-6.5.
[49 FR 41002, Oct. 18, 1984]
Sec. 87.62 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 Secretary:
------------------------------------------------------------------------
Class
--------------------------
Mode TF, T3,
TP T8 TSS
------------------------------------------------------------------------
Taxi/idle.................................... (\1\) (\1\) (\1\)
Takeoff...................................... 100 100 100
Climbout..................................... 90 85 65
Descent...................................... NA NA 15
Approach..................................... 30 30 34
------------------------------------------------------------------------
\1\ See paragraph (a)(2) of this section.
(2) The taxi/idle operating modes shall be carried out at a power
setting of 7% rated thrust unless the Secretary determines that the
unique characteristics of an engine model undergoing certification
testing at 7% would result in substantially different HC emissions than
if the engine model were tested at the manufacturers recommended idle
power setting. In such cases the Secretary shall specify an alternative
test condition.
(3) The times in mode (TIM) shall be as specified below:
------------------------------------------------------------------------
Class
--------------------------
Mode TF, T3
TP or T8 TSS
------------------------------------------------------------------------
Taxi/idle (minutes).......................... 26.0 26.0 26.0
Takeoff...................................... 0.5 0.7 1.2
Climbout..................................... 2.5 2.2 2.0
Descent...................................... N/A N/A 1.2
Approach..................................... 4.5 4.0 2.3
------------------------------------------------------------------------
(b) Emissions testing shall be conducted on warmed-up engines which
have achieved a steady operating temperature.
Sec. 87.63 [Reserved]
Sec. 87.64 Sampling and analytical procedures for measuring gaseous exhaust emissions.
The system and procedures for sampling and measurement of gaseous
emissions shall be as specified by appendices 3 and 5 to ICAO Annex 16,
Volume II, Aircraft Engine Emissions, First Edition, June 1981, which
are incorporated herein by reference. This document can be obtained from
the International Civil Aviation Organization, P.O. Box 400, Succursale:
Place de L'Aviation Internationale, 1000 Sherbrooke Street West,
Montreal, Quebec, Canada H3A 2R2 at $3.00 per copy. It is also available
for inspection
[[Page 11]]
at the Office of the Federal Register Information Center, 800 North
Capitol Street, NW., suite 700, Washington, DC. This incorporation by
reference was approved by the Director of the Federal Register on
September 3, 1982. These materials are incorporated as they exist on the
date of the approval and a notice of any change in these materials will
be published in the Federal Register. Frequent changes are not
anticipated.
Secs. 87.65--87.70 [Reserved]
Sec. 87.71 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
Sec. 87.64 with the applicable emission standard under this part.
Subpart H--Test Procedures for Engine Smoke Emissions (Aircraft Gas
Turbine Engines)
Sec. 87.80 Introduction.
Except as provided under Sec. 87.5, the procedures described in this
subpart shall be the test program to determine the conformity of new and
in-use gas turbine engines with the applicable standards set forth in
this part. The test is essentially the same as that described in
Secs. 87.60 through 87.62, except that the test is designed to determine
the smoke emission level at various operating points representative of
engine usage in aircraft. Other smoke measurement systems may be used if
shown to yield equivalent results and if approved in advance by the
Administrator or the Secretary.
Sec. 87.81 Fuel specifications.
Fuel having specifications as provided in Sec. 87.61 shall be used
in smoke emission testing.
Sec. 87.82 Sampling and analytical procedures for measuring smoke exhaust emissions.
The system and procedures for sampling and measurement of smoke
emissions shall be as specified by Appendix 2, Volume II, Aircraft
Engine Emissions to ICAO Annex 16, Aircraft Engine Emissions, First
Edition, June, 1981. This document can be obtained from the
International Civil Aviation Organization, P.O. Box 400, Succursale:
Place de L'Aviation Internationale, 1000 Sherbrooke Street West,
Montreal, Quebec, Canada H3A 2R2 at $3.00 per copy. It is also available
for inspection at the Office of the Federal Register Information Center,
800 North Capitol Street, NW., suite 700, Washington, DC. This
incorporation by reference was approved by the Director of the Federal
Register on September 3, 1982. These materials are incorporated as they
exist on the date of the approval and a notice of any change in these
materials will be published in the Federal Register. Frequent changes
are not anticipated.
Secs. 87.83--87.88 [Reserved]
Sec. 87.89 Compliance with smoke emission standards.
Compliance with each smoke emission standard shall be determined by
comparing the plot of SN as a function of power setting with the
applicable emission standard under this part. The SN at every power
setting must be such that there is a high degree of confidence that the
standard will not be exceeded by any engine of the model being tested.
The level of confidence required, a practical interpretation of the
requirement for total compliance, and a testing program to assure
compliance will be established by the Secretary prior to January 1,
1984, and shall be approved by the Administrator.