(b)
Analysis based on rig testing, component testing, or service experience may be sub-stitutedfor oneofthe enginetestsprescribedinparagraphs(a)(1) and(a)(2) of this section if–
(1) That test, of the two prescribed, produces the least rotor unbalance; and
(2) The analysis is shown to be equivalent to the test.] Amdt. 33-10, E.. 3/26/84
FAR 33.95 : Engine-propeller systems tests.
If the engineisdesigned to operate with apropeller, thefollowing tests mustbe made with a representative propeller installed by either including the tests in the endurance run or otherwise performing them in a manner acceptable to the Administrator :
(a)
Feathering operation : 25 cycles.
(b)
Negative torque and thrust system operation : 25 cycles from [rated] maximum continuouspower.
(c)
Automaticdecoupler operation:25 cyclesfrom[rated] maximum continuouspower (if repeated decoupling and recoupling in service is the intended function of the device).
(d)
Reversethrustoperation:175 cyclesfromthe .ight-idlepositiontofull reverseand 25 cycles at [rated] maximum continuous power from full forward to full reverse thrust.Atthe end of each cyclethepropellermustbe operatedin reversepitchfor a period of 30 seconds at the maximum rotational speed and power speci.ed by the applicantfor reversepitch operation.
Amdt. 33-3, E.. 4/3/67
FAR33.96:[Enginetestsinauxiliarypowerunit(APU) mode.]
[If the engine is designedwith a propeller brake which will allow the propeller to be brought to a stop while the gas generator portion of the engine remains in operation, and remain stoppedduring operationofthe engineas anauxiliarypowerunit(”APU mode”), in addition to the requirements of Sec. 33.87, the applicant must conduct the following tests :
(a)
Ground locking : A total of 45 hours with the propeller brake engaged in a manner which clearly demonstrates its ability to function without adverse e.ects on the complete engine whilethe engineis operatingintheAPU mode underthe maximum conditionsof enginespeed,torque,temperature,airbleed, andpowerextractionas speci.ed by the applicant.
(b)
Dynamic braking : A total of 400 application-release cycles of brake engagements mustbe madein a manner which clearlydemonstratesits abilitytofunction without adverse e.ects on the complete engine under the maximum conditions of engine acceleration/deceleration rate, speed, torque, and temperature as speci.ed by the applicant. The propeller must be stopped prior to brake release.
(c)
One hundred engine starts and stops with the propeller brake engaged.
(d)
Thetests requiredbyparagraphs(a),(b), and(c) of this sectionmustbeperformed on the same engine, but this engine need not be the same engine used for the tests required by Sec. 33.87.
(e)
The tests required by paragraphs (a), (b), and (c) of this section must be follo-wed by engine disassembly to the extent necessary to show compliance with the requirements of Sec. 33.93(a) and Sec. 33.93(b).]
Amdt. 33-11, E.. 4/24/86
′
Elodie Roux. Septembre 2003
SubpartF :BlockTests;TurbineAircraftEngines
FAR 33.97 : Thrust reversers.
(a)
If the engine incorporates a reverser, the endurance, calibration, operation, and vibration tests prescribed in this subpart must be run with the reverser installed. In complying with this section, the power control lever must be moved from one extreme position to the other in not more than one second except, if regimes of control operations are incorporated necessitating scheduling of the power-control lever motioningoingfrom one extremepositionto the other, alongerperiodoftime is acceptable but not more than three seconds. In addition, the test prescribed in paragraph(b) mustbe made.Thistest may be scheduled aspart of the endurance run.
(b)
175 reversals must be made from .ight-idle forward thrust to maximum reverse thrust and 25 reversals must be made from [rated takeo. thrust] to maximum reverse thrust. After each reversal, the reverser must be operated at full reverse thrust for a period of one minute, except that, in the case of a reverser intended for use only as abraking means ontheground,the reverserneed only be operated at full reverse thrust for 30 seconds.
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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(151)
