(c)
Eachapplicant mustfurnish all testingfacilities,including equipment and competent personnel, to conduct the block tests.

Amdt. 33-9, E.. 10/14/80
′
Elodie Roux. Septembre 2003
Subpart D : Block Tests; Reciprocating Aircraft Engines
Chapitre 92
Subpart E : Design and Construction; Turbine Aircraft Engines
Sommaire
FAR33.61:Applicability. . . . . . . . . . . . . . . . . . . . . 1148 FAR33.62:[Stressanalysis.] . . . . . . . . . . . . . . . . . . 1148 FAR33.63:Vibration.. . . . . . . . . . . . . . . . . . . . . . 1148 FAR33.65:[Surgeand stall characteristics.] . . . . . . . . . 1148 FAR33.66:Bleed airsystem.. . . . . . . . . . . . . . . . . . 1148 FAR33.67:Fuel system. .................... 1148 FAR33.68:Inductionsystemicing. . . . . . . . . . . . . . . 1149 FAR33.69:[Ignitionssystem.] . . . . . . . . . . . . . . . . . 1150 FAR33.71:Lubricationsystem. . . . . . . . . . . . . . . . . 1150 FAR33.72:[Hydraulicactuating systems.] . . . . . . . . . . 1152 FAR33.73:Powerorthrustresponse. . . . . . . . . . . . . . 1152 FAR33.74:[Continued rotation.] . . . . . . . . . . . . . . . . 1152 FAR33.75:Safety analysis.. . . . . . . . . . . . . . . . . . . 1152 FAR33.76:[Birdingestion.] . . . . . . . . . . . . . . . . . . 1152 FAR33.77:[Foreignobjectingestion–ice.] . . . . . . . . . . . 1155 FAR33.78:[Rainandhailingestion.] . . . . . . . . . . . . . 1157 FAR 33.79 : Fuel burning thrust augmentor. . . . . . . . . . . 1158
1147
SubpartE :Design andConstruction;TurbineAircraftEngines
FAR 33.61 : Applicability.
This subpart prescribes additional design and construction requirements for turbine aircraft engines.
FAR33.62 :[Stress analysis.]
[Astress analysis mustbeperformed on each turbine engine showingthedesign safety margin of each turbine engine rotor, spacer, and rotor shaft.] Amdt. 33-6, E.. 10/31/74
FAR 33.63 : Vibration.
[Eachengine must be designed and constructed to function throughout its declared .ight envelope and operating range of rotational speeds and power/thrust, without in-ducing excessive stress in any engine part because of vibration and without imparting excessive vibration forces to the aircraft structure.] Amdt. 33-17, E.. 7/5/96
FAR33.65 :[Surge and stall characteristics.]
[When the engine is operated in accordance withoperating instructions required by Sec.33.5(b), starting, a change ofpower orthrust,power orthrustaugmentation,limiting inletairdistortion, orinlet airtemperature may not cause surge or stallto the extent that .ameout, structuralfailure, overtemperature, or failure of the engine to recoverpower or thrust will occur at any point in the operating envelope.] Amdt. 33-6, E.. 10/31/74
FAR 33.66 : Bleed air system.
[The engine must supply bleed air without adverse e.ect on the engine, excluding reduced thrustorpoweroutput,atall conditionssetup tothedischarge .owconditions established as a limitation under Sec. 33.7(c)(11). If bleed air used for engine anti-icing canbe controlled,provisionmustbe madefor a meanstoindicatethefunctioning of the engine ice protection system.] Amdt. 33-10, E.. 3/26/84
FAR 33.67 : Fuel system.
(a)
Withfuel supplied totheengineatthe .owandpressurespeci.edby theapplicant, the engine must function properly under each operating condition required by this part.Eachfuelcontrol adjusting means that may notbe manipulated while thefuel control device is mounted on the engine must be secured by a locking device and sealed, or otherwise be inaccessible. All other fuel control adjusting means must be accessible and marked to indicate the function of the adjustment unless the function is obvious.

(b)
There must be a fuel strainer or .lter between the engine fuel inlet opening and the inlet of either the fuel metering device or the engine-driven positive displacement pumpwhicheveris nearer the enginefuelinlet. In addition, thefollowingprovisions apply to each strainer or .lter required by this paragraph :
　
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 5(134)