spaschal on DSK3GDR082PROD with CFR

Federal Aviation Administration, DOT

Section 33.15

(6) Accessory drive torque and overhang moment.
(7) Component life.
(8) Turbosupercharger turbine wheel
r.p.m.
(c) For turbine engines, ratings and
operating limitations are established
relating to the following:
(1) Horsepower, torque, or thrust,
r.p.m., gas temperature, and time for - 
(i) Rated maximum continuous power
or thrust (augmented);
(ii) Rated maximum continuous
power or thrust (unaugmented);
(iii) Rated takeoff power or thrust
(augmented);
(iv) Rated takeoff power or thrust
(unaugmented);
(v) Rated 30-minute OEI power;
(vi) Rated 21-2-minute OEI power;
(vii) Rated continuous OEI power;
and
(viii) Rated 2-minute OEI Power;
(ix) Rated 30-second OEI power; and
(x) Auxiliary power unit (APU) mode
of operation.
(2) Fuel designation or specification.
(3) Oil grade or specification.
(4) Hydraulic fluid specification.
(5) Temperature of - 
(i) Oil at a location specified by the
applicant;
(ii) Induction air at the inlet face of
a supersonic engine, including steady
state operation and transient overtemperature and time allowed;
(iii) Hydraulic fluid of a supersonic
engine;
(iv) Fuel at a location specified by
the applicant; and
(v) External surfaces of the engine, if
specified by the applicant.
(6) Pressure of - 
(i) Fuel at the fuel inlet;
(ii) Oil at a location specified by the
applicant;
(iii) Induction air at the inlet face of
a supersonic engine, including steady
state operation and transient overpressure and time allowed; and
(iv) Hydraulic fluid.
(7) Accessory drive torque and overhang moment.
(8) Component life.
(9) Fuel filtration.
(10) Oil filtration.
(11) Bleed air.
(12) The number of start-stop stress
cycles approved for each rotor disc and
spacer.

(13) Inlet air distortion at the engine
inlet.
(14) Transient rotor shaft overspeed
r.p.m., and number of overspeed occurrences.
(15) Transient gas overtemperature,
and number of overtemperature occurrences.
(16) Transient engine overtorque, and
number of overtorque occurrences.
(17) Maximum engine overtorque for
turbopropeller and turboshaft engines
incorporating free power turbines.
(18) For engines to be used in supersonic
aircraft,
engine
rotor
windmilling rotational r.p.m.
(d) In determining the engine performance and operating limitations,
the overall limits of accuracy of the
engine control system and of the necessary instrumentation as defined in
Section 33.5(a)(6) must be taken into account.
[Amdt. 33-6, 39 FR 35463, Oct. 1, 1974, as
amended by Amdt. 33-10, 49 FR 6850, Feb. 23,
1984; Amdt. 33-11, 51 FR 10346, Mar. 25, 1986;
Amdt. 33-12, 53 FR 34220, Sept. 2, 1988; Amdt.
33-18, 61 FR 31328, June 19, 1996; Amdt. 33-26,
73 FR 48284, Aug. 19, 2008; Amdt. 33-30, 74 FR
45310, Sept. 2, 2009]

Section 33.8 Selection of engine power and
thrust ratings.
(a) Requested engine power and
thrust ratings must be selected by the
applicant.
(b) Each selected rating must be for
the lowest power or thrust that all engines of the same type may be expected
to produce under the conditions used to
determine that rating.
[Amdt. 33-3, 32 FR 3736, Mar. 4, 1967]

Subpart B - Design and
Construction; General
Section 33.11

Applicability.

This subpart prescribes the general
design and construction requirements
for reciprocating and turbine aircraft
engines.
Section 33.13

[Reserved]

Section 33.15

Materials.

The suitability and durability of materials used in the engine must - 
(a) Be established on the basis of experience or tests; and

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