(b)
The intake passages of the engine through which air or fuel in combination with airpassesfor combustionpurposes mustbedesigned and constructed to minimize the danger of ice accretion in those passages. The engine must be designed and constructed to permit the use of a means for ice prevention.
(c)
Thetypeanddegreeoffuel.lteringnecessaryforprotectionoftheenginefuel system againstforeignparticlesin thefuel mustbe speci.ed.The applicant must show that foreign particles passing through the prescribed .ltering means will not critically impair engine fuel system functioning.
(d)
Each passage in the induction system that conducts a mixture of fuel and air must be self-draining, to prevent a liquid lock in the cylinders, in all attitudes that the applicant establishes as those the engine can have when the aircraft in which it is installed is in the static ground attitude.
(e)
[If providedas part of the engine, the applicant must show for each .uid injection (other than fuel) system and its controls that the .ow of the injected .uid is adequately controlled.]
Amdt. 33-10, E.. 3/26/84
FAR 33.37 : Ignition system.
Each spark ignition engine must have a dual ignition system with at least two spark plugsfor eachcylinder andtwo separate electric circuits with separate sources of electrical energy, or have an ignition system of equivalent in-.ight reliability.
FAR 33.39 : Lubrication system.
(a)
The lubrication system of the engine must be designed and constructed so that it will function properly in all .ight attitudes and atmospheric conditions in which the airplaneisexpected tooperate.In wetsump engines,this requirement mustbe met when only one-half of the maximum lubricant supply is in the engine.
(b)
The lubrication system of the engine must be designed and constructed to allow installing a means of cooling the lubricant.
(c)
The crankcase must be vented to the atmosphere to preclude leakage of oil from excessivepressureinthe crankcase.
Chapitre 91
SubpartD :BlockTests; Reciprocating Aircraft Engines
Sommaire
FAR33.41:Applicability. . . . . . . . . . . . . . . . . . . . . 1140 FAR33.42:[General.] ...................... 1140 FAR33.43:Vibrationtest. ................... 1140 FAR33.45:Calibrationtests.. . . . . . . . . . . . . . . . . . 1140 FAR33.47:Detonationtest. .................. 1141 FAR33.49:Endurancetest. .................. 1141 FAR33.51:Operationtest. . . . . . . . . . . . . . . . . . . . 1144 FAR33.53:Enginecomponenttests.. . . . . . . . . . . . . . 1145 FAR33.55:Teardowninspection. . . . . . . . . . . . . . . . 1145 FAR 33.57 : General conduct of block tests. . . . . . . . . . . 1145
1139
Subpart D : Block Tests; Reciprocating Aircraft Engines
FAR 33.41 : Applicability.
This subpart prescribes the block tests and inspections for reciprocating aircraft en-gines.
FAR33.42 :[General.]
[Before eachendurance test requiredbythis subpart, the adjustment setting andfunc-tioning characteristic of each component having an adjustment setting and a functioning characteristic that can be established independent of installation on the engine must be established and recorded.] Amdt. 33-6, E.. 10/31/74
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本文链接地址：FAA规章 美国联邦航空规章 Federal Aviation Regulations 5(129)
