701 

Federal Aviation Administration, DOT 

§ 33.15 

(6) Accessory drive torque and over-

hang 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 2

1

⁄

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 over- 
temperature 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 over-
pressure and time allowed; and 

(iv) Hydraulic fluid. 
(7) Accessory drive torque and over-

hang 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 occur-
rences. 

(15) Transient gas overtemperature, 

and number of overtemperature occur-
rences. 

(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 super-

sonic aircraft, engine rotor 
windmilling rotational r.p.m. 

(d) In determining the engine per-

formance and operating limitations, 
the overall limits of accuracy of the 
engine control system and of the nec-
essary instrumentation as defined in 
§ 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] 

§ 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 en-
gines 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 

§ 33.11

Applicability. 

This subpart prescribes the general 

design and construction requirements 
for reciprocating and turbine aircraft 
engines. 

§ 33.13

[Reserved] 

§ 33.15

Materials. 

The suitability and durability of ma-

terials used in the engine must— 

(a) Be established on the basis of ex-

perience or tests; and 

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