(d)
For an engine type certi.cated for use in supersonic aircraft, the systems, safety devices, and external components that may fail because of operation at maximum and minimum operating temperatures must be identi.ed and tested at maximum and minimum operating temperatures and while temperature and other operating conditions are cycled between maximum and minimum operating values.]
Amdt. 33-6, E.. 10/31/74
FAR33.92 :[Rotorlocking tests.]
[Ifcontinued rotation is prevented by a means to lock the rotor(s), the engine must be subjected to a test that includes 25 operations of this means under the following conditions :
(a)
The engine must be shut down from rated maximum continuous thrust or power; and
(b)
The meansfor stopping andlocking the rotor(s) mustbe operated as speci.edin the engine operating instructions while being subjected to the maximum torque that could resultfromcontinued .ightinthiscondition; and
(c)
Following rotor locking, the rotor(s) must be held stationary under these conditions
for .ve minutes for each of the 25 operations.] Amdt. 33-17, E.. 7/5/96
FAR 33.93 : Teardown inspection.
(a) [After completingthe endurancetesting ofSec.33.87(b),(c),(d),(e), or(g) of this part, each engine must be completely disassembled, and
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Elodie Roux. Septembre 2003
SubpartF :BlockTests;TurbineAircraftEngines
(1)
Each component having an adjustment setting and a functioning characteris-tic that can be established independent of installation on the engine must retain each setting and functioning characteristic within the limits that were established and recorded at the beginning of the test; and
(2)
Each enginepart must conformtothetypedesign andbe eligibleforincorpo-rationinto an enginefor continued operation,in accordancewithinformation submitted in compliance with Sec. 33.4.
(b)
After completing the endurance testing of Sec. 33.87(f), each engine must be com-pletely disassembled, and
(1)
Each component having an adjustment setting and a functioning characteris-tic that can be established independent of installation on the engine must retain each setting and functioning characteristic within the limits that were established and recorded at the beginning of the test; and
(2)
Eachengine may exhibitdeteriorationin excess ofthatpermittedinparagraph (a)(2)of this sectionincluding some engineparts or componentsthat may be unsuitableforfurther use.The applicant must showby analysis and/ortest, as found necessary by the Administrator, that structural integrity of the engine including mounts, cases, bearing supports, shafts, and rotors, is maintained; or
(c)
Inlieu of compliance withparagraph(b) of this section, each enginefor which the 30-second OEI and 2-minute OEI ratings are desired, may be subjected to the endurance testing of Secs. 33.87(b),(c),(d), or(e) of thispart, and followedby the testing of Sec. 33.87(f), without intervening disassembly and inspection. However, the engine must comply withparagraph(a) ofthis section after completingthe endurance testing of Sec. 33.87(f).]
Amdt. 33-18, E.. 8/19/96
FAR33.94:[Bladecontainmentandrotor unbalancetests.]
(a)
[Except asprovidedinparagraph(b) ofthis section,it mustbedemonstratedby engine tests that the engine is capable of containing damage without catching .re and without failure of its mounting attachments when operated for at least 15 seconds, unless the resulting engine damage induces a self shutdown, after each of the following events :
(1)
Failure of the most critical compressor or fan blade while operating at maxi-mum permissible r.p.m. The blade failure must occur at the outermost re-tention groove or, for integrally-bladed rotor discs, at least 80 percent of the blade must fail.
(2)
Failureof themostcritical turbinebladewhile operating atmaximumpermis-sible r.p.m.Thebladefailure must occur at the outermost retentiongroove or, forintegrally-bladedrotordiscs, atleast80percent of theblade mustfail.The most critical turbine blade must be determined by considering turbine blade weight and the strength of the adjacent turbine case at case temperatures and pressures associated with operation at maximum permissible r.p.m.
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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(150)
