(b)
Each engine for which 30-second OEI and 2-minute OEI ratings are desired, that does not incorporate a means to limit temperature, must be run for a period of 5 minutes at the maximum power-on rpm with the gas temperature at least 75oF (42oC)higher than the 30-second OEI rating operating limit. Following this run, the turbine assembly may exhibitdistressbeyond thelimitsfor an overtemperature condition provided the engine is shown by analysis or test, as found necessary by the Administrator, to maintain the integrity of the turbine assembly.
(c)
Each engine for which 30-second OEI and 2-minute OEI ratings are desired, that incorporates a means tolimit temperature, mustbe runfor aperiod of4 minutes at the maximumpower-onrpmwith thegastemperatureatleast35oF(20oC)higher than the maximum operating limit. Following this run, the turbine assembly may exhibit distress beyond the limits for an overtemperature condition provided the engine is shown by analysis or test, as found necessary by the Administrator, to maintain the integrity of the turbine assembly.
(d)
A separate test vehicle may be used for each test condition.]
Amdt. 33-18, E.. 8/19/96
FAR 33.89 : Operation test.
(a)
The operation test must include testing found necessary by the Administrator to demonstrate–
(1)
Starting,idling, acceleration, overspeeding,ignition,functioning of thepropel-ler(ifthe engineisdesignated to operate with apropeller);
(2)
Compliance with the engine response requirements of Sec. 33.73; and
(3)
The minimum power or thrust response time to 95
(i)
No bleed air and power extraction for aircraft use.
(ii)
Maximum allowable bleed air and power extraction for aircraft use.
(iii) An intermediate value for bleed air and power extraction representative of that which might be used as a maximum for aircraft during approach to a landing.
(4)
If testing facilities are not available, the determination of power extraction requiredin subparagraphs(2) and(3) ofparagraph(c) of this section may be accomplished through appropriate analytical means.
(b)
[The operation test must include all testing found necessary by the Administrator to demonstrate that the engine has safe operating characteristics throughout its speci.ed operating envelope.]
Amdt. 33-10, E.. 3/26/84
FAR33.90 :[Initial maintenanceinspection.]
[Eachengine, except enginesbeingtype certi.catedthrough amendment of an existing type certi.cate or through supplemental type certi.cation procedures, must undergo an approvedtest run that simulatesthe conditionsin which the engineis expected to operate in service,includingstart-stop cycles,to establish whentheinitial maintenanceinspection is required.The testrun mustbe accomplished on an engine which substantially conforms to the .nal type design.] Amdt. 33-10, E.. 3/26/84
FAR 33.91 : Engine component tests.
(a)
For those systems that cannot be adequately substantiated by endurance testing in accordance with the provisions of Sec. 33.87, additional tests must be made to establish that components are able to function reliably in all normally anticipated .ight and atmospheric conditions.
(b)
Temperature limits must be established for those components that require tem-perature controlling provisions in the aircraft installation to assure satisfactory functioning, reliability, and durability.
(c)
[Each unpressurized hydraulic .uid tank may not fail or leak when subjected to maximum operating temperature and an internal pressure of 5 p.s.i., and each pressurized hydraulic .uid tank may not fail or leak when subjected to maximum operating temperature and aninternalpressure notless than5p.s.i.plus the maxi-mum operatingpressure ofthetank.
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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(149)
