(ii)
The amount of trapped oil must be enough to accomplish the feathering operation and mustbe available only tothefeatheringpump; and

(iii) Provision must be made to prevent sludge or other foreign matter from a.ecting the safe operation of the propeller feathering system.

(d)
Oil drains.Adrain(ordrains) mustbeprovidedto allowsafedrainageofthe oil system. Each drain must–

(1)
Be accessible; and

(2)
Have manual or automatic means for positive locking in the closed position.

(e)
Oil radiators. Each oil radiator must withstand, without failure, any vibration, iner-tia, and oil pressure load to which it is subjected during the block tests.]

Amdt. 33-10, E.. 3/26/84
′
Elodie Roux. Septembre 2003
SubpartE :Design andConstruction;TurbineAircraftEngines
FAR33.72 :[Hydraulic actuating systems.]
[Eachhydraulic actuatingsystem mustfunctionproperly under all conditionsin which the engine is expected to operate. Each .lter or screen must be accessible for servicing and each tank must meet the design criteria of Sec. 33.71.] Amdt. 33-6, E.. 10/31/74
FAR 33.73 : Power or thrust response.
[The design andconstruction of the engine must enable an increase–
(a)
From minimum to rated takeo. power or thrust with the maximum bleed air and power extraction to be permitted in an aircraft, without overtemperature, surge, stall, or other detrimental factors occurring to the engine whenever the power control lever is moved from the minimum to the maximum position in not more than1 second, except that theAdministrator may allow additional timeincrements for di.erent regimes of control operation requiring control scheduling; and

(b)
From the .xed minimum .ight idle power lever position when provided, or if not provided, from not more than 15 percent of the rated takeo. power or thrust availableto95percent rated takeo.power orthrustin not over5 seconds.The5-secondpower or thrust response must occurfrom a stabilized static condition using only the bleed air and accessories loads necessary to run the engine. This takeo. rating is speci.ed by the applicant and need not include thrust augmentation.]

Amdt. 33-4, E.. 4/23/71
FAR33.74 :[Continued rotation.]
[If any of the engine main rotating systems will continue to rotate after the engine is shutdown for any reason while in .ight, and where means to prevent that continued rotation are not provided; then any continued rotation during the maximum period of .ight, and in the .ight conditions expected to occur with that engine inoperative, must not resultin any conditiondescribedinSec.33.75(a) through(c).] [Amdt. 33-17, E.. 7/5/96]
FAR 33.75 : Safety analysis.
It must be shown by analysis that any probable malfunction or any probable single or multiple failure, or any probable improper operation of the engine will not cause the engine to–
(a)
Catch .re;

(b)
[Burst(releasehazardousfragmentsthroughthe engine case);

(c)
Generate loads greater than those ultimate loads speci.ed in Sec. 33.23(a); or]

(d)
Lose the capability of being shut down. Amdt. 33-10, E.. 3/26/84

FAR33.76 :[Birdingestion.]

(a)
[General.Compliance withparagraphs(b)and(c) ofthis section shallbein accor-dance with the following :

(1)
Allingestion tests shallbe conducted with the engine stabilized at noless than 100-percent takeo. power or thrust, for test day ambient conditions prior to the ingestion. In addition, the demonstration of compliance must account for engine operation at sea level takeo. conditions on the hottest day that a minimum engine can achieve maximum rated takeo. thrust or power.

(2)
The engine inlet throat area as used in this section to determine the bird quantity and weights will be established by the applicant and identi.ed as a limitation in the installation instructions required under r33.5.
　
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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(137)