745
Federal Aviation Administration, DOT
Pt. 34
[Amdt. 33–34, 79 FR 65538, Nov. 4, 2014]
PART 34—FUEL VENTING AND EX-
HAUST EMISSION REQUIREMENTS
FOR TURBINE ENGINE POWERED
AIRPLANES
Subpart A—General Provisions
Sec.
34.1
Definitions.
34.2
Abbreviations.
34.3
General requirements.
34.4
[Reserved]
34.5
Special test procedures.
34.6
Aircraft safety.
34.7
Exemptions.
34.9
Exceptions.
Subpart B—Engine Fuel Venting Emissions
(New and In-Use Aircraft Gas Turbine
Engines)
34.10
Applicability.
34.11
Standard for fuel venting emissions.
Subpart C—Exhaust Emissions (New
Aircraft Gas Turbine Engines)
34.20
Applicability.
34.21
Standards for exhaust emissions.
34.23
Exhaust Emission Standards for En-
gines Manufactured on and after July 18,
2012.
Subpart D—Exhaust Emissions (In-Use
Aircraft Gas Turbine Engines)
34.30
Applicability.
34.31
Standards for exhaust emissions.
Subpart E—Certification Provisions
34.48
Derivative engines for emissions cer-
tification purposes.
Subpart F
[
Reserved
]
Subpart G—Test Procedures for Engine Ex-
haust Gaseous Emissions (Aircraft and
Aircraft Gas Turbine Engines)
34.60
Introduction.
34.61–34.71
[Reserved]
A
UTHORITY
: 42 U.S.C. 4321
et seq., 7572; 49
U.S.C. 106(g), 40113, 44701–44702, 44704, 44714.
S
OURCE
: Docket No. 25613, 55 FR 32861, Aug.
10, 1990, unless otherwise noted.
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14 CFR Ch. I (1–1–24 Edition)
§ 34.1
1
This incorporation by reference was ap-
proved by the Director of the Federal Reg-
ister in accordance with 5 U.S.C. 552(a) and 1
CFR part 51. This document can be obtained
from the ICAO, Document Sales Unit, 999
University Street, Montreal, Quebec H3C
5H7, Canada, phone + 1 514–954–8022, or
www.icao.int or sales14icao.int. Copies can be
reviewed at the FAA New England Regional
Office, 12 New England Executive Park, Bur-
lington, Massachusetts, 781–238–7101, or at
the National Archives and Records Adminis-
tration (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.html.
Subpart A—General Provisions
§ 34.1
Definitions.
As used in this part, all terms not de-
fined 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 Adminis-
trator of the Federal Aviation Admin-
istration 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 offi-
cer or employee of the Environmental
Protection Agency to whom the au-
thority 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 airworthi-
ness certificate or equivalent foreign
airworthiness certificate is issued.
Aircraft engine means a propulsion en-
gine which is installed in, or which is
manufactured for installation in, an
aircraft.
Aircraft gas turbine engine means a
turboprop, turbofan, or turbojet air-
craft engine.
Characteristic level has the meaning
given in Appendix 6 of ICAO Annex 16
as of July 2008. The characteristic level
is a calculated emission level for each
pollutant based on a statistical assess-
ment of measured emissions from mul-
tiple tests.
1
Class TP means all aircraft turboprop
engines.
Class TF means all turbofan or tur-
bojet aircraft engines or aircraft en-
gines 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 tur-
bine engines of the JT3D model family.
Class T8 means all aircraft gas tur-
bine engines of the JT8D model family.
Class TSS means all aircraft gas tur-
bine engines employed for propulsion
of aircraft designed to operate at su-
personic flight speeds.
Commercial aircraft engine means any
aircraft engine used or intended for use
by an ‘‘air carrier’’ (including those en-
gaged in ‘‘intrastate air transpor-
tation’’) or a ‘‘commercial operator’’
(including those engaged in ‘‘intrastate
air transportation’’) as these terms are
defined in Title 49 of the United States
Code and Title 14 of the Code of Federal
Regulations.
Commercial aircraft gas turbine engine
means a turboprop, turbofan, or tur-
bojet commercial aircraft engine.
Date of manufacture of an engine is
the date the inspection acceptance
records reflect that the engine is com-
plete and meets the FAA approved type
design.
Derivative engine for emissions certifi-
cation purposes means an engine that
has the same or similar emissions char-
acteristics as an engine covered by a
U.S. type certificate issued under 14
CFR part 33. These characteristics are
specified in § 34.48.
Emission measurement system means
all of the equipment necessary to
transport the emission sample and
measure the level of emissions. This in-
cludes the sample system and the in-
strumentation system.
Engine model means all commercial
aircraft turbine engines which are of
the same general series, displacement,
and design characteristics and are ap-
proved under the same type certificate.
Excepted, as used in § 34.9, means an
engine that may be produced and sold
that does not meet otherwise applica-
ble standards. Excepted engines must
conform to regulatory conditions speci-
fied for an exception in § 34.9. Excepted
engines are subject to the standards of
this part even though they are not re-
quired to comply with the otherwise
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§ 34.1
applicable requirements. Engines ex-
cepted with respect to certain stand-
ards must comply with other standards
from which they are not specifically
excepted.
Exempt means an engine that does
not meet certain applicable standards
but may be produced and sold under
the terms allowed by a grant of exemp-
tion issued pursuant to § 34.7 of this
part and part 11 of this chapter. Ex-
empted engines must conform to regu-
latory conditions specified in the ex-
emption as well as other applicable
regulations. Exempted engines are sub-
ject to the standards of this part even
though they are not required to comply
with the otherwise applicable require-
ments. Engines exempted with respect
to certain standards must comply with
other standards as a condition of the
exemption.
Exhaust emissions means substances
emitted into the atmosphere from the
exhaust discharge nozzle of an aircraft
or aircraft engine.
Fuel venting emissions means raw fuel,
exclusive of hydrocarbons in the ex-
haust emissions, discharged from air-
craft 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.
Introduction date means the date of
manufacture of the first individual pro-
duction engine of a given engine model
or engine type certificate family to be
certificated. Neither test engines nor
engines not placed into service affect
this date.
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 or shaft power in
terms of kilowatts for turboprop en-
gines.
Rated output (rO) means the max-
imum power/thrust available for take-
off at standard day conditions as ap-
proved for the engine by the Federal
Aviation Administration, including re-
heat contribution where applicable, but
excluding any contribution due to
water injection, expressed in kilowatts
or kilonewtons (as applicable), rounded
to at least three significant figures.
Rated pressure ratio (rPR) means the
ratio between the combustor inlet pres-
sure and the engine inlet pressure
achieved by an engine operation at
rated output, rounded to at least three
significant figures.
Reference day conditions means the
reference ambient conditions to which
the gaseous emissions (HC and smoke)
are to be corrected. The reference day
conditions are as follows: Temperature
= 15
°
C, specific humidity = 0.00629 kg
H
2
O/kg of dry air, and pressure = 101325
Pa.
Sample system means the system
which provides for the transportation
of the gaseous emission sample from
the sample probe to the inlet of the in-
strumentation system.
Shaft power means only the measured
shaft power output of a turboprop en-
gine.
Smoke means the matter in exhaust
emissions which obscures the trans-
mission of light.
Smoke number (SN) means the
dimensionless term quantifying smoke
emissions.
Standard day conditions means the
following ambient conditions: tempera-
ture = 15
°
C, specific humidity = 0.00634
kg H
2
O/kg dry air, and pressure =
101.325 kPa.
Taxi/idle (in) means those aircraft op-
erations involving taxi and idle be-
tween the time of landing roll-out and
final shutdown of all propulsion en-
gines.
Taxi/idle (out) means those aircraft
operations involving taxi and idle be-
tween the time of initial starting of
the propulsion engine(s) used for the
taxi and the turn onto the duty run-
way.
Tier, as used in this part, is a des-
ignation related to the NO
X
emission
standard for the engine as specified in
§ 34.21 or § 34.23 of this part (e.g., Tier 0).
[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]
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14 CFR Ch. I (1–1–24 Edition)
§ 34.2
§ 34.2
Abbreviations.
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 Administra-
tion, United States Department of
Transportation
g Gram(s)
HC
Hydrocarbon(s)
HP
Horsepower
hr
Hour(s)
H
2
0
water
kg
Kilogram(s)
kJ
Kilojoule(s)
kN Kilonewton(s)
kW Kilowatt(s)
lb Pound(s)
LTO
Landing and takeoff
min
Minute(s)
NO
X
Oxides of nitrogen
Pa
Pascal(s)
rO
Rated output
rPR
Rated pressure ratio
sec
Second(s)
SP
Shaft power
SN
Smoke number
T
Temperature, degrees Kelvin
TIM
Time in mode
°
C
Degrees Celsius
%
Percent
[Doc. No. 25613, 55 FR 32861, Aug. 10, 1990, as
amended by Amdt. 34–3, 64 FR 5559, Feb. 3,
1999; Amdt. 34–5, 77 FR 76850, Dec. 31, 2012]
§ 34.3
General requirements.
(a) This part provides for the ap-
proval or acceptance by the Adminis-
trator or the Administrator of the EPA
of testing and sampling methods, ana-
lytical techniques, and related equip-
ment not identical to those specified in
this part. Before either approves or ac-
cepts 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 Adminis-
trator 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 reg-
ulations to ensure compliance with 40
CFR part 87. This authority has been
delegated to the Administrator of the
FAA (49 CFR 1.47).
(c)
U.S. airplanes. This part applies to
civil airplanes that are powered by air-
craft gas turbine engines of the classes
specified herein and that have U.S.
standard airworthiness certificates.
(d)
Foreign airplanes. Pursuant to the
definition of ‘‘aircraft’’ in 40 CFR 87.1,
this regulation applies to civil air-
planes that are powered by aircraft gas
turbine engines of the classes specified
herein and that have foreign airworthi-
ness certificates that are equivalent to
U.S. standard airworthiness certifi-
cates. 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 op-
erations intended for the airplane. Pur-
suant to 40 CFR 87.3(c), this regulation
does not apply where it would be incon-
sistent 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 87 refers to title 40 of the
Code of Federal Regulations, chapter
I—Environmental Protection Agency,
part 87, Control of Air Pollution from
Aircraft and Aircraft Engines (40 CFR
part 87).
(f) This part contains regulations to
ensure compliance with certain stand-
ards contained in 40 CFR part 87. If
EPA takes any action, including the
issuance of an exemption or issuance of
a revised or alternate procedure, test
method, or other regulation, the effect
of which is to relax or delay the effec-
tive date of any provision of 40 CFR
part 87 that is made applicable to an
aircraft under this FAR, the Adminis-
trator of FAA will grant a general ad-
ministrative waiver of its more strin-
gent requirements until this FAR is
amended to reflect the more relaxed re-
quirements prescribed by EPA.
(g) Unless otherwise stated, all ter-
minology and abbreviations in this
FAR that are defined in 40 CFR part 87
have the meaning specified in that
part, and all terms in 40 CFR part 87
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§ 34.6
that are not defined in that part but
that are used in this FAR have the
meaning given them in the Clean Air
Act, as amended by Public Law 91–604.
(h) All interpretations of 40 CFR part
87 that are rendered by the EPA also
apply to this FAR.
(i) If the EPA, under 40 CFR 87.3(a),
approves or accepts any testing and
sampling procedures or methods, ana-
lytical techniques, or related equip-
ment not identical to those specified in
that part, this FAR requires an appli-
cant to show that such alternate,
equivalent, or otherwise nonidentical
procedures have been complied with,
and that such alternate equipment was
used to show compliance, unless the
applicant elects to comply with those
procedures, methods, techniques, and
equipment specified in 40 CFR part 87.
(j) If the EPA, under 40 CFR 87.5, pre-
scribes special test procedures for any
aircraft or aircraft engine that is not
susceptible to satisfactory testing by
the procedures in 40 CFR part 87, the
applicant must show the Administrator
that those special test procedures have
been complied with.
(k) Wherever 40 CFR part 87 requires
agreement, acceptance, or approval by
the Administrator of the EPA, this
FAR requires a showing that such
agreement or approval has been ob-
tained.
(l) Pursuant to 42 U.S.C. 7573, no
state or political subdivision thereof
may adopt or attempt to enforce any
standard respecting emissions of any
air pollutant from any aircraft or en-
gine thereof unless that standard is
identical to a standard made applicable
to the aircraft by the terms of this
FAR.
(m) If EPA, by regulation or exemp-
tion, relaxes a provision of 40 CFR part
87 that is implemented in this FAR, no
state or political subdivision thereof
may adopt or attempt to enforce the
terms of this FAR that are superseded
by the relaxed requirement.
(n) If any provision of this FAR is
rendered inapplicable to a foreign air-
craft as provided in 40 CFR 87.3(c)
(international agreements), and
§ 34.3(d) of this FAR, that provision
may not be adopted or enforced against
that foreign aircraft by a state or po-
litical subdivision thereof.
(o) For exhaust emissions require-
ments of this FAR that apply begin-
ning February 1, 1974, January 1, 1976,
January 1, 1978, January 1, 1984, and
August 9, 1985, continued compliance
with those requirements is shown for
engines for which the type design has
been shown to meet those require-
ments, if the engine is maintained in
accordance with applicable mainte-
nance requirements for 14 CFR chapter
I. All methods of demonstrating com-
pliance and all model designations pre-
viously found acceptable to the Admin-
istrator shall be deemed to continue to
be an acceptable demonstration of
compliance with the specific standards
for which they were approved.
(p) Each applicant must allow the
Administrator to make, or witness,
any test necessary to determine com-
pliance with the applicable provisions
of this FAR.
[Doc. No. 25613, 55 FR 32861, Aug. 10, 1990; 55
FR 37287, Sept. 10, 1990; Amdt. 34–5, 77 FR
76850, Dec. 31, 2012]
§ 34.4
[Reserved]
§ 34.5
Special test procedures.
The Administrator or the Adminis-
trator of the EPA may, upon written
application by a manufacturer or oper-
ator of aircraft or aircraft engines, ap-
prove test procedures for any aircraft
or aircraft engine that is not suscep-
tible to satisfactory testing by the pro-
cedures set forth herein. Prior to tak-
ing action on any such application, the
Administrator or the Administrator of
the EPA shall consult with the other.
§ 34.6
Aircraft safety.
(a) The provisions of this part will be
revised if at any time the Adminis-
trator determines that an emission
standard cannot be met within the
specified time without creating a safe-
ty hazard.
(b) Consistent with 40 CFR 87.6, if the
FAA Administrator determines that
any emission control regulation in this
part cannot be safely applied to an air-
craft, that provision may not be adopt-
ed or enforced against that aircraft by
any state or political subdivision
thereof.
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14 CFR Ch. I (1–1–24 Edition)
§ 34.7
§ 34.7
Exemptions.
Notwithstanding part 11 of the Fed-
eral Aviation Regulations (14 CFR part
11), all petitions for rulemaking involv-
ing 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 sub-
mitted to the EPA. Information copies
of such petitions are invited by the
FAA. Petitions for rulemaking or ex-
emption involving provisions of this
FAR that do not affect the substance
or the compliance date of an emission
standard or test procedure that is pre-
scribed 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 air-
craft operated in the United States for
short durations at infrequent intervals.
Such operations are limited to:
(1) Flights of an aircraft for the pur-
pose of export to a foreign country, in-
cluding any flights essential to dem-
onstrate 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 low production’’ is limited
to a maximum total production for
United States civil aviation applica-
tions of no more than 200 units covered
by the same type certificate after Jan-
uary 1, 1984. Engines manufactured
under this provision must be reported
to the FAA by serial number on or be-
fore the date of manufacture and ex-
emptions granted under this provision
are not transferable to any other en-
gine. This exemption is limited to the
requirements of § 34.21 only.
(c)
Exemptions for new engines in other
categories. The emissions standards of
this part do not apply to engines for
which the Administrator determines,
with the concurrence of the Adminis-
trator of the EPA, that application of
any standard under § 34.21 is not justi-
fied, 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;
and
(5) Other factors which the Adminis-
trator, after consultation with the Ad-
ministrator of the EPA, may deem rel-
evant to the case in question.
(d)
Applicants seeking exemption from
other emissions standards of this part and
40 CFR part 87. Applicants must request
exemption from both the FAA and the
EPA, even where the underlying regu-
latory requirements are the same. The
FAA and EPA will jointly consider
such exemption requests, and will as-
sure consistency in the respective
agency determinations.
(e) Applications for exemption from
this part shall be submitted in dupli-
cate to the Administrator in accord-
ance with the procedures established
by the Administrator in part 11.
(f) The Administrator shall publish in
the F
EDERAL
R
EGISTER
the name of the
organization to whom exemptions are
granted and the period of such exemp-
tions.
(g) No state or political subdivision
thereof may attempt to enforce a
standard respecting emissions from an
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§ 34.11
aircraft or engine if such aircraft or en-
gine has been exempted from such
standard under this part.
[Doc. No. 25613, 55 FR 32861, Aug. 10, 1990, as
amended by Amdt. 34–5, 77 FR 76850, Dec. 31,
2012]
§ 34.9
Exceptions.
(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 iden-
tical to a sub-model previously certifi-
cated to meet all applicable require-
ments.
(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 ex-
cepted under this paragraph (c) must
indicate that the engine was produced
as an excepted spare engine.
(6) Engines produced under this ex-
ception must be labeled ‘‘EXCEPTED
SPARE’’ in accordance with § 45.13 of
this chapter.
(b) On and after July 18, 2012, and be-
fore 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 ap-
proval is required to produce these en-
gines. Engines produced under this ex-
ception are to be labeled ‘‘COMPLY’’ in
accordance with § 45.13 of this chapter.
[Doc. No. FAA–2012–1333, 77 FR 76850, Dec. 31,
2012]
Subpart B—Engine Fuel Venting
Emissions (New and In-Use
Aircraft Gas Turbine Engines)
§ 34.10
Applicability.
(a) The provisions of this subpart are
applicable to all new aircraft gas tur-
bine 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 man-
ufactured 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 tur-
bine engines of class TF less than 36 kN
(8,090 lb) rated output and class TP
manufactured after January 1, 1975.
[Doc. No. FAA–2012–1333, 77 FR 76850, Dec. 31,
2012]
§ 34.11
Standard for fuel venting emis-
sions.
(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 elimi-
nation 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 fuel
venting and emissions requirements of
this section that were effective begin-
ning 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 com-
pliance 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 pressur-
ization and drain valve.
(3) Manually draining the fuel from a
holding tank into a container.
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14 CFR Ch. I (1–1–24 Edition)
§ 34.20
Subpart C—Exhaust Emissions
(New Aircraft Gas Turbine En-
gines)
§ 34.20
Applicability.
The provisions of this subpart are ap-
plicable to all aircraft gas turbine en-
gines of the classes specified beginning
on the dates specified in § 34.21.
§ 34.21
Standards for exhaust emis-
sions.
(a) Exhaust emissions of smoke from
each new aircraft gas turbine engine of
class T8 manufactured on or after Feb-
ruary 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, manufac-
tured 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 Jan-
uary 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 De-
cember 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 indi-
vidual 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 De-
cember 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 out-
put greater than 89 kN:
Oxides of Nitrogen: (19 + 1.6(rPR)) g/kN
rO.
(B) That have a rated pressure ratio
of 30 or less and a maximum rated out-
put greater than 26.7 kN but not great-
er than 89 kN:
Oxides of Nitrogen: (37.572 + 1.6(rPR)
¥
0.2087(rO)) g/kN rO.
(C) That have a rated pressure ratio
greater than 30 but less than 62.5, and
a maximum rated output greater than
89 kN:
Oxides of Nitrogen: (7 + 2(rPR)) g/kN
rO.
(D) That have a rated pressure ratio
greater than 30 but less than 62.5, and
a maximum rated output greater than
26.7 kN but not greater than 89 kN:
Oxides of Nitrogen: (42.71 + 1.4286(rPR)
¥
0.4013(rO) + 0.00642(rPR
×
rO)) g/
kN rO.
(E) That have a rated pressure ratio
of 62.5 or more:
Oxides of Nitrogen: (32 + 1.6(rPR)) g/kN
rO.
(2) For Class TSS Engines manufac-
tured on or after January 1, 1984:
Hydrocarbons: 140 (0.92)
rPR
g/kN rO.
(e) Smoke exhaust emissions from
each gas turbine engine of the classes
specified below shall not exceed:
(1) For Class TF of rated output less
than 26.7 kN (6,000 lb) manufactured on
or after August 9, 1985:
SN = 83.6(rO)
¥
0.274
(rO is in kN) not to
exceed a maximum of SN = 50.
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Federal Aviation Administration, DOT
§ 34.23
(2) For Classes T3, T8, TSS, and TF of
rated output equal to or greater than
26.7 kN (6,000 lb) manufactured on or
after January 1, 1984:
SN = 83.6(rO)
¥
0.274
(rO is in kN) not to
exceed a maximum of SN = 50.
(3) For Class TP of rated output
equal to or greater than 1,000 kW man-
ufactured on or after January 1, 1984:
SN = 187(rO)
¥
0.168
(rO is in kW).
(f) The standards set forth in para-
graphs (a), (b), (c), (d), and (e) of this
section refer to a composite gaseous
emission sample representing the oper-
ation cycles and exhaust smoke emis-
sion 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 sub-
part G.
(g) Where a gaseous emission stand-
ard is specified by a formula, calculate
and round the standard to three signifi-
cant 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 en-
gine type certificate family’s char-
acteristic level does not exceed the nu-
merical level of that standard, as de-
scribed in § 34.60.
[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]
§ 34.23
Exhaust Emission Standards
for Engines Manufactured on and
after July 18, 2012.
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 for-
mula, 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 stand-
ard is specified by a formula, calculate
and round the standard to the nearest
0.1 SN. Engines comply with an appli-
cable 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) For Classes TF, T3 and T8 of rated
output less than 26.7 kN (6,000 lb) man-
ufactured on and after July 18, 2012:
SN = 83.6(rO)
¥
0.274
or 50.0, whichever is
smaller
(2) Except as provided in §§ 34.9(b) and
34.21(c), for Classes TF, T3 and T8 en-
gines manufactured on and after July
18, 2012, and for which the first indi-
vidual production model was manufac-
tured on or before December 31, 2013
(Tier 6):
T
IER
6 O
XIDES OF
N
ITROGEN
E
MISSION
S
TANDARDS FOR
S
UBSONIC
E
NGINES
Class
Rated pressure ratio—
rPR
Rated output rO
(kN)
NO
X
(g/kN)
TF, T3, T8 .....................
rPR
≤
30 .......................
26.7 < rO
≤
89.0 ...........
38.5486 + 1.6823 (rPR)
¥
0.2453 (rO)
¥
(0.00308 (rPR) (rO)).
rO > 89.0 ......................
16.72 + 1.4080 (rPR).
30 < rPR < 82.6 ...........
26.7 < rO
≤
89.0 ...........
46.1600 + 1.4286 (rPR)
¥
0.5303 (rO) +
(0.00642 (rPR) (rO)).
rO > 89.0 ......................
¥
1.04 + 2.0 (rPR).
rPR
≥
82.6 ....................
rO
≥
26.7 ......................
32 + 1.6 (rPR).
(3) Engines exempted from paragraph
(a)(2) of this section produced on or be-
fore December 31, 2016 must be labeled
‘‘EXEMPT NEW’’ in accordance with
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14 CFR Ch. I (1–1–24 Edition)
§ 34.30
§ 45.13 of this chapter. No exemptions to
the requirements of paragraph (a)(2) of
this section will be granted after De-
cember 31, 2016.
(4) For Class TSS Engines manufac-
tured on and after July 18, 2012:
G
ASEOUS
E
MISSION
S
TANDARDS FOR
S
UPERSONIC
E
NGINES
Class
Rated output
rO
1
(kN)
NO
X
(g/kN)
CO
(g/kN)
TSS ..........................................
All ............................................
36 + 2.42 (rPR) .....................
4,550 (rPR)
¥
1.03
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 in-
dividual production model was manu-
factured after December 31, 2013 (Tier
8):
T
IER
8 O
XIDES OF
N
ITROGEN
E
MISSION
S
TANDARDS FOR
S
UBSONIC
E
NGINES
Class
Rated pressure ratio—
rPR
Rated output rO
(kN)
NO
X
(g/kN)
TF, T3, T8 .....................
rPR
≤
30 .......................
26.7 < rO
≤
89.0 ...........
40.052 + 1.5681 (rPR)
¥
0.3615 (rO)
¥
(0.0018 (rPR) (rO)).
rO > 89.0 ......................
7.88 + 1.4080 (rPR).
30 < rPR < 104.7 .........
26.7 < rO
≤
89.0 ...........
41.9435 + 1.505 (rPR)
¥
0.5823 (rO) +
(0.005562 (rPR) (rO)).
rO > 89.0 ......................
¥
9.88 + 2.0 (rPR).
rPR
≥
104.7 ..................
rO
≥
26.7 ......................
32 + 1.6 (rPR).
(c) Engines (including engines that
are determined to be derivative engines
for the purposes of emission certifi-
cation) type certificated with char-
acteristic levels at or below the NO
X
standards of § 34.21(d)(1)(vi) of this part
(as applicable based on rated output
and rated pressure ratio) and intro-
duced before July 18, 2012, may be pro-
duced through December 31, 2012, with-
out meeting the NO
X
standard of para-
graph (a)(2) of this section.
[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]
Subpart D—Exhaust Emissions (In-
use Aircraft Gas Turbine Engines)
§ 34.30
Applicability.
The provisions of this subpart are ap-
plicable to all in-use aircraft gas tur-
bine engines certificated for operation
within the United States of the classes
specified, beginning on the dates speci-
fied in § 34.31.
§ 34.31
Standards for exhaust emis-
sions.
(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, begin-
ning January l, 1976, shall not exceed
SN = 83.6(rO)
¥
0.274
(rO is in kN).
(c) The standards set forth in para-
graphs (a) and (b) of this section refer
to exhaust smoke emission emitted
during operation of the engine as speci-
fied in the applicable sections of sub-
part G of this part, and measured and
calculated in accordance with the pro-
cedures set forth in subpart G.
[Doc. No. FAA–2012–1333, 77 FR 76852, Dec. 31,
2012]
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§ 34.60
Subpart E—Certification Provisions
§ 34.48
Derivative engines for emis-
sions certification purposes.
(a)
General. A derivative engine for
emissions certification purposes is an
engine configuration that is deter-
mined to be similar in design to a pre-
viously certificated (original) engine
for purposes of compliance with ex-
haust emissions standards (gaseous and
smoke). A type certificate holder may
request from the FAA a determination
that an engine configuration is consid-
ered a derivative engine for emissions
certification purposes. To be consid-
ered a derivative engine for emission
purposes under this part, the configu-
ration 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 en-
gine modification.
(2) Emissions from the derivative en-
gines are determined to be similar. In
general, this means the emissions must
meet the criteria specified in para-
graph (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)
Emissions 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 only within the
following ranges:
(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.
(2) If the characteristic level of the
original certificated engine model (or
any other sub-models within the emis-
sion type certificate family tested for
certification) before modification is at
or above 95% of the applicable standard
for any pollutant, an applicant must
measure the proposed derivative engine
model’s emissions for all pollutants to
demonstrate that the derivative en-
gine’s resulting characteristic levels
will not exceed the applicable emission
standards. If the characteristic levels
of the originally certificated engine
model (and all other sub-models within
the emission type certificate family
tested for certification) are below 95%
of the applicable standard for each pol-
lutant, the applicant may use engineer-
ing analysis consistent with good engi-
neering judgment to demonstrate that
the derivative engine will not exceed
the applicable emission standards. The
engineering analysis must address all
modifications from the original engine,
including those approved for previous
derivative engines.
(c)
Continued production allowance.
Derivative engines for emissions cer-
tification purposes may continue to be
produced after the applicability date
for new emissions standards when the
engines conform to the specifications
of this section.
(d)
Non-derivative engines. If the FAA
determines that an engine model does
not meet the requirements for a deriva-
tive engine for emissions certification
purposes, the type certificate holder is
required to demonstrate that the en-
gine complies with the emissions
standards applicable to a new engine
type.
[Doc. No. 34–5, 77 FR 76852, Dec. 31, 2012]
Subpart F
[
Reserved
]
Subpart G—Test Procedures for
Engine Exhaust Gaseous Emis-
sions (Aircraft and Aircraft
Gas Turbine Engines)
§ 34.60
Introduction.
(a) Use the equipment and procedures
specified in Appendix 3, Appendix 5,
and Appendix 6 of ICAO Annex 16, as
applicable, to demonstrate whether en-
gines 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
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14 CFR Ch. I (1–1–24 Edition)
§ 34.60
calculating a ‘‘characteristic level’’ by
applying a set of statistical factors
that take into account the number of
engines tested. Round each char-
acteristic level to the same number of
decimal places as the corresponding
emission standard. For turboprop en-
gines, 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 pro-
duction 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 proce-
dures for measuring emissions, includ-
ing testing and sampling methods, ana-
lytical techniques, and equipment
specifications that differ from those
specified in this part. Manufacturers
and operators may request approval of
alternative procedures by written re-
quest with supporting justification to
the FAA and to the Designated EPA
Program Officer. To be approved, one
of the following conditions must be
met:
(1) The engine cannot be tested using
the specified procedures; or
(2) The alternative procedure is
shown to be equivalent to, or more ac-
curate or precise than, the specified
procedure.
(f) The following landing and takeoff
(LTO) cycles apply for emissions test-
ing and for calculating weighted LTO
values:
LTO T
EST
C
YCLES AND
T
IME IN
M
ODE
Mode
Class
TP
TF, T3, T8
TSS
TIM (min)
% of rO
TIM (min)
% of rO
TIM (min)
% of rO
Taxi/idle .................................................
26.0 7
26.0 7
26.0
5.8
Takeoff ..................................................
0.5 100 0.7 100 1.2 100
Climbout ................................................
2.5 90 2.2 85 2.0 65
Descent .................................................
NA NA NA NA 1.2 15
Approach ...............................................
4.5 30 4.0 30 2.3 34
(g) Engines comply with an applica-
ble standard if the testing results show
that the engine type certificate fam-
ily’s characteristic level does not ex-
ceed the numerical level of that stand-
ard, as described in the applicable ap-
pendix of Annex 16.
(h) The system and procedure for
sampling and measurement of gaseous
emissions shall be as specified by in
Appendices 2, 3, 4, 5 and 6 to the Inter-
national Civil Aviation Organization
(ICAO) Annex 16, Environmental Pro-
tection, Volume II, Aircraft Engine
Emissions, Third Edition, July 2008.
This incorporation by reference was ap-
proved by the Director of the Federal
Register in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. This docu-
ment can be obtained from the ICAO,
Document Sales Unit, 999 University
Street, Montreal, Quebec H3C 5H7, Can-
ada, phone + 1 514–954–8022, or
www.icao.int or sales25icao.int. Copies
can be reviewed at the FAA New Eng-
land Regional Office, 12 New England
Executive Park, Burlington, Massachu-
setts, 781–238–7101, or at the National
Archives and Records Administration
(NARA). For information on the avail-
ability of this material at NARA, call
202–741–6030, or go to:
http://
www.archives.gov/federal
_
register/
code
_
of
_
federal
_
regulations/
ibr
_
locations.html.
[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]
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§ 35.3
§§ 34.61–34.71
[Reserved]
PART 35—AIRWORTHINESS
STANDARDS: PROPELLERS
Subpart A—General
Sec.
35.1
Applicability.
35.2
Propeller configuration.
35.3
Instructions for propeller installation
and operation.
35.4
Instructions for Continued Airworthi-
ness.
35.5
Propeller ratings and operating limita-
tions.
35.7
Features and characteristics.
Subpart B—Design and Construction
35.11
[Reserved]
35.13
[Reserved]
35.15
Safety analysis.
35.16
Propeller critical parts.
35.17
Materials and manufacturing methods.
35.19
Durability.
35.21
Variable and reversible pitch propel-
lers.
35.22
Feathering propellers.
35.23
Propeller control system.
35.24
Strength.
Subpart C—Tests and Inspections
35.31
[Reserved]
35.33
General.
35.34
Inspections, adjustments and repairs.
35.35
Centrifugal load tests.
35.36
Bird impact.
35.37
Fatigue limits and evaluation.
35.38
Lightning strike.
35.39
Endurance test.
35.40
Functional test.
35.41
Overspeed and overtorque.
35.42
Components of the propeller control
system.
35.43
Propeller hydraulic components.
35.45–35.47
[Reserved]
A
PPENDIX
A
TO
P
ART
35—I
NSTRUCTIONS FOR
C
ONTINUED
A
IRWORTHINESS
A
UTHORITY
: 49 U.S.C. 106(f), 106(g), 40113,
44701–44702, 44704.
S
OURCE
: Docket No. 2095, 29 FR 7458, June
10, 1964, unless otherwise noted.
Subpart A—General
§ 35.1
Applicability.
(a) This part prescribes airworthiness
standards for the issue of type certifi-
cates and changes to those certificates,
for propellers.
(b) Each person who applies under
part 21 for such a certificate or change
must show compliance with the appli-
cable requirements of this part.
(c) An applicant is eligible for a pro-
peller type certificate and changes to
those certificates after demonstrating
compliance with subparts A, B, and C
of this part. However, the propeller
may not be installed on an airplane un-
less the applicant has shown compli-
ance with either § 23.2400(c) or § 25.907 of
this chapter, as applicable, or compli-
ance is not required for installation on
that airplane.
(d) For the purposes of this part, the
propeller consists of those components
listed in the propeller type design, and
the propeller system consists of the
propeller and all the components nec-
essary for its functioning, but not nec-
essarily included in the propeller type
design.
[Amdt. 35–3, 41 FR 55475, Dec. 20, 1976, as
amended by Amdt. 35–8, 73 FR 63346, Oct. 24,
2008; Doc. FAA–2015–1621, Amdt. 35–10, 81 FR
96700, Dec. 30, 2016]
§ 35.2
Propeller configuration.
The applicant must provide a list of
all the components, including ref-
erences to the relevant drawings and
software design data, that define the
type design of the propeller to be ap-
proved under § 21.31 of this chapter.
[Amdt. 35–8, 73 FR 63346, Oct. 24, 2008]
§ 35.3
Instructions for propeller instal-
lation and operation.
The applicant must provide instruc-
tions that are approved by the Admin-
istrator. Those approved instructions
must contain:
(a) Instructions for installing the
propeller, which:
(1) Include a description of the oper-
ational modes of the propeller control
system and functional interface of the
control system with the airplane and
engine systems;
(2) Specify the physical and func-
tional interfaces with the airplane, air-
plane equipment and engine;
(3) Define the limiting conditions on
the interfaces from paragraph (a)(2) of
this section;
(4) List the limitations established
under § 35.5;
(5) Define the hydraulic fluids ap-
proved for use with the propeller, in-
cluding grade and specification, related
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