(v)
External surfaces of the engine, if speci.ed by the applicant.

(6)
Pressure of–

(i)
Fuel atthefuelinlet;

(ii)
Oil at a location speci.ed 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 .uid.

(7)
Accessory drive torque and overhang moment.

(8)
Component life.

(9)
Fuel .ltration.

(10)
Oil .ltration.

(11)
Bleed air.

(12)
The number ofstart-stop stress cycles approvedfor each rotordisc and spacer.

(13)
Inlet air distortion at the engine inlet.

(14)
Transient rotor shaft overspeed r.p.m., and number of overspeed occurrences.

(15)
Transientgasovertemperature,and number of overtemperatureoccurrences.

(16)
For engines to be used in supersonic aircraft, engine rotor windmilling rota-tional r.p.m.

Amdt. 33-18, E.. 8/19/96
FAR33.8 :[Selection of enginepower and thrust ratings.]
(a)
[Requestedengine 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, E.. 4/3/67
Chapitre 89
Subpart B : Design and
Construction; General

Sommaire
FAR33.11:Applicability. . . . . . . . . . . . . . . . . . . . . 1132 FAR33.13:[Reserved.] ..................... 1132 FAR33.14:Start-stop cyclicstress(low-cyclefatigue).. . . . 1132 FAR33.15:Materials.. . . . . . . . . . . . . . . . . . . . . . 1132 FAR33.17:Fireprevention. .................. 1132 FAR33.19:Durability. ..................... 1133 FAR33.21:Enginecooling.. . . . . . . . . . . . . . . . . . . 1133 FAR 33.23 : Engine mounting attachments and structure. . . 1133 FAR33.25:Accessory attachments. . . . . . . . . . . . . . . 1133 FAR33.27 :[Turbine,compressor,fan, and turbosupercharger
rotors.] ......................... 1133 FAR33.28:[Electrical and electroniccontrol systems.] . . . . 1134 FAR33.29:Instrumentconnection. . . . . . . . . . . . . . . 1135
1131
SubpartB :Design andConstruction;General
FAR 33.11 : Applicability.
This subpartprescribes thegeneraldesign and construction requirementsfor recipro-cating and turbine aircraft engines.
FAR33.13 :[Reserved.]
[Reserved.] Amdt. 33-6, E.. 10/31/74
FAR33.14:Start-stop cyclic stress(low-cyclefatigue).
[By a procedure approved by the FAA, operating limitations must be established which specify the maximum allowable number of start-stop stress cycles for each rotor structuralpart(such asdiscs, spacers,hubs, and shafts of the compressors and turbines), the failure of which could produce a hazard to the aircraft. A start-stop stress cycle consistsof a .ight cyclepro.leoranequivalent representationof engineusage.Itincludes starting the engine, accelerating to maximum rated power or thrust, decelerating, and stopping. For each cycle, the rotor structural parts must reach stabilized temperature during engine operation at maximum rated power or thrust and after engine shutdown, unless it is shown that the parts undergo the same stress range without temperature stabilization.] Amdt. 33-10, E.. 3/26/84
FAR 33.15 : Materials.
The suitability and durability of materials used in the engine must–
(a)
Be established onthebasis of experience ortests; and

(b)
[Conform to approvedspeci.cations(such asindustry or military speci.cations)that

ensuretheirhaving the strength and otherproperties assumedinthedesigndata.] Amdt. 33-10, E.. 3/26/84
FAR 33.17 : Fire prevention.
(a)
[The design and construction of the engine and the materials used must minimize the probability of the occurrence and spread of .re. In addition, the design and construction of turbine engines must minimizetheprobability of the occurrence of an internal .re that could result in structural failure, overheating, or other hazar-dous conditions.]
　
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