699
Federal Aviation Administration, DOT
§ 33.5
Subpart D—Block Tests; Reciprocating
Aircraft Engines
33.41
Applicability.
33.42
General.
33.43
Vibration test.
33.45
Calibration tests.
33.47
Detonation test.
33.49
Endurance test.
33.51
Operation test.
33.53
Engine system and component tests.
33.55
Teardown inspection.
33.57
General conduct of block tests.
Subpart E—Design and Construction;
Turbine Aircraft Engines
33.61
Applicability.
33.62
Stress analysis.
33.63
Vibration.
33.64
Pressurized engine static parts.
33.65
Surge and stall characteristics.
33.66
Bleed air system.
33.67
Fuel system.
33.68
Induction system icing.
33.69
Ignitions system.
33.70
Engine life-limited parts.
33.71
Lubrication system.
33.72
Hydraulic actuating systems.
33.73
Power or thrust response.
33.74
Continued rotation.
33.75
Safety analysis.
33.76
Bird ingestion.
33.77
Foreign object ingestion—ice.
33.78
Rain and hail ingestion.
33.79
Fuel burning thrust augmentor.
Subpart F—Block Tests; Turbine Aircraft
Engines
33.81
Applicability.
33.82
General.
33.83
Vibration test.
33.84
Engine overtorque test.
33.85
Calibration tests.
33.87
Endurance test.
33.88
Engine overtemperature test.
33.89
Operation test.
33.90
Initial maintenance inspection test.
33.91
Engine system and component tests.
33.92
Rotor locking tests.
33.93
Teardown inspection.
33.94
Blade containment and rotor unbal-
ance tests.
33.95
Engine-propeller systems tests.
33.96
Engine tests in auxiliary power unit
(APU) mode.
33.97
Thrust reversers.
33.99
General conduct of block tests.
Subpart G—Special Requirements: Turbine
Aircraft Engines
33.201
Design and test requirements for
Early ETOPS eligibility.
A
PPENDIX
A
TO
P
ART
33—I
NSTRUCTIONS FOR
C
ONTINUED
A
IRWORTHINESS
A
PPENDIX
B
TO
P
ART
33—C
ERTIFICATION
S
TANDARD
A
TMOSPHERIC
C
ONCENTRATIONS
OF
R
AIN AND
H
AIL
A
PPENDIX
C
TO
P
ART
33 [R
ESERVED
]
A
PPENDIX
D
TO
P
ART
33—M
IXED
P
HASE AND
I
CE
C
RYSTAL
I
CING
E
NVELOPE
(D
EEP
C
ON
-
VECTIVE
C
LOUDS
)
A
UTHORITY
: 49 U.S.C. 106(g), 40113, 44701,
44702, 44704.
S
OURCE
: Docket No. 3025, 29 FR 7453, June
10, 1964, unless otherwise noted.
N
OTE
: For miscellaneous amendments to
cross references in this Part 33, see Amdt. 33–
2, 31 FR 9211, July 6, 1966.
Subpart A—General
§ 33.1
Applicability.
(a) This part prescribes airworthiness
standards for the issue of type certifi-
cates and changes to those certificates,
for aircraft engines.
(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 and the
applicable requirements of part 34 of
this chapter.
[Amdt. 33–7, 41 FR 55474, Dec. 20, 1976, as
amended by Amdt. 33–14, 55 FR 32861, Aug. 10,
1990]
§ 33.3
General.
Each applicant must show that the
aircraft engine concerned meets the
applicable requirements of this part.
§ 33.4
Instructions for Continued Air-
worthiness.
The applicant must prepare Instruc-
tions for Continued Airworthiness in
accordance with appendix A to this
part that are acceptable to the Admin-
istrator. The instructions may be in-
complete at type certification if a pro-
gram exists to ensure their completion
prior to delivery of the first aircraft
with the engine installed, or upon
issuance of a standard certificate of
airworthiness for the aircraft with the
engine installed, whichever occurs
later.
[Amdt. 33–9, 45 FR 60181, Sept. 11, 1980]
§ 33.5
Instruction manual for installing
and operating the engine.
Each applicant must prepare and
make available to the Administrator
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14 CFR Ch. I (1–1–24 Edition)
§ 33.7
prior to the issuance of the type cer-
tificate, and to the owner at the time
of delivery of the engine, approved in-
structions for installing and operating
the engine. The instructions must in-
clude at least the following:
(a)
Installation instructions. (1) The lo-
cation of engine mounting attach-
ments, the method of attaching the en-
gine to the aircraft, and the maximum
allowable load for the mounting at-
tachments and related structure.
(2) The location and description of
engine connections to be attached to
accessories, pipes, wires, cables, ducts,
and cowling.
(3) An outline drawing of the engine
including overall dimensions.
(4) A definition of the physical and
functional interfaces with the aircraft
and aircraft equipment, including the
propeller when applicable.
(5) Where an engine system relies on
components that are not part of the en-
gine type design, the interface condi-
tions and reliability requirements for
those components upon which engine
type certification is based must be
specified in the engine installation in-
structions directly or by reference to
appropriate documentation.
(6) A list of the instruments nec-
essary for control of the engine, includ-
ing the overall limits of accuracy and
transient response required of such in-
struments for control of the operation
of the engine, must also be stated so
that the suitability of the instruments
as installed may be assessed.
(b)
Operation instructions. (1) The op-
erating limitations established by the
Administrator.
(2) The power or thrust ratings and
procedures for correcting for non-
standard atmosphere.
(3) The recommended procedures,
under normal and extreme ambient
conditions for—
(i) Starting;
(ii) Operating on the ground; and
(iii) Operating during flight.
(4) For rotorcraft engines having one
or more OEI ratings, applicants must
provide data on engine performance
characteristics and variability to en-
able the aircraft manufacturer to es-
tablish aircraft power assurance proce-
dures.
(5) A description of the primary and
all alternate modes, and any back-up
system, together with any associated
limitations, of the engine control sys-
tem and its interface with the aircraft
systems, including the propeller when
applicable.
(c)
Safety analysis assumptions. The
assumptions of the safety analysis as
described in § 33.75(d) with respect to
the reliability of safety devices, instru-
mentation, early warning devices,
maintenance checks, and similar
equipment or procedures that are out-
side the control of the engine manufac-
turer.
[Amdt. 33–6, 39 FR 35463, Oct. 1, 1974, as
amended by Amdt. 33–9, 45 FR 60181, Sept. 11,
1980; Amdt. 33–24, 47 FR 50867, Sept. 4, 2007;
Amdt. 33–25, 73 FR 48123, Aug. 18, 2008; Amdt.
33–26, 73 FR 48284, Aug. 19, 2008]
§ 33.7
Engine ratings and operating
limitations.
(a) Engine ratings and operating lim-
itations are established by the Admin-
istrator and included in the engine cer-
tificate data sheet specified in § 21.41 of
this chapter, including ratings and lim-
itations based on the operating condi-
tions and information specified in this
section, as applicable, and any other
information found necessary for safe
operation of the engine.
(b) For reciprocating engines, ratings
and operating limitations are estab-
lished relating to the following:
(1) Horsepower or torque, r.p.m.,
manifold pressure, and time at critical
pressure altitude and sea level pressure
altitude for—
(i) Rated maximum continuous power
(relating to unsupercharged operation
or to operation in each supercharger
mode as applicable); and
(ii) Rated takeoff power (relating to
unsupercharged operation or to oper-
ation in each supercharger mode as ap-
plicable).
(2) Fuel grade or specification.
(3) Oil grade or specification.
(4) Temperature of the—
(i) Cylinder;
(ii) Oil at the oil inlet; and
(iii) Turbosupercharger turbine wheel
inlet gas.
(5) Pressure of—
(i) Fuel at the fuel inlet; and
(ii) Oil at the main oil gallery.
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