(2)
For engines used in helicopters the applicant must conduct the runs speci.ed inparagraph(d) of this section, except–

(i)
The entire run speci.edinparagraph(d)(1) of this section mustbe made at critical altitude pressure;

(ii)
The portions of the runs speci.ed in paragraph (d)(2) and (3) of this section at rated maximum continuous power must be made at critical altitude pressure and the portions of the runs at other power must be made at 8,000 feet altitude pressure;

(iii) The entire run speci.edinparagraph(d)(4)of this section mustbe made at 8,000 feet altitude pressure;
(iv)
Theportion of the runs speci.edinparagraph(d)(5) of this section at 80 percent of rated maximum continuous power must be made at 8,000 feet altitude pressure and the portions of the runs at other power must be made at critical altitude pressure;

(v)
The entirerunspeci.edinparagraph(d)(6) of thissectionmustbemade at critical altitude pressure; and

(vi)
The turbosupercharger used during the endurance test must be run on thebenchfor50hours at thelimiting turbine wheelinletgas temperature and rotational speedfor rated maximum continuouspower operation un-less the limiting temperature and speed are maintained during 50 hours of the rated maximum continuouspower operation.

Amdt. 33-10, E.. 3/26/84
FAR 33.51 : Operation test.
The operation test must include the testing found necessary by the Administrator todemonstrateback.recharacteristics,starting,idling, acceleration,overspeeding,func-tioning ofpropeller andignition, and any other operational characteristic ofthe engine. If the engine incorporates a multispeed supercharger drive, the design and construction must allow the supercharger to be shifted from operation at the lower speed ratio to the
higher and thepowerappropriatetothe manifoldpressureand speed settingsfor[rated]
maximum continuous power at the higher supercharger speed ratio must be obtainable
within .ve seconds.
Amdt. 33-3, E.. 4/3/67

FAR 33.53 : Engine component tests.
(a)
For each engine that cannot be adequately substantiated by endurance testing in accordance withSec.33.49, the applicant must conduct additionaltests to establish that components are able to function reliably in all normally anticipated .ight and atmospheric conditions.

(b)
Temperature limits must be established for each component that requires tempera-ture controllingprovisionsin the aircraftinstallation to assure satisfactoryfunctio-ning, reliability, and durability.

FAR 33.55 : Teardown inspection.
After completing the endurance test–
(a)
Each engine must be completely disassembled;

(b)
Each component having an adjustment setting and a functioning characteristic that canbe establishedindependent ofinstallation onthe engine must retain each setting and functioning characteristic within the limits that were established and recorded atthebeginning of thetest; and

(c)
Each engine component must conform to the type design and be eligible for incor-poration into an engine for continued operation, in accordance with information submittedin compliance with[Sec.33.4].

Amdt. 33-9, E.. 10/14/80
FAR 33.57 : General conduct of block tests.
(a)
The applicant may, in conducting the block tests, use separate engines of identical design and construction in the vibration, calibration, detonation, endurance, and operation tests, except that, if a separate engine is used for the endurance test it must be subjected to a calibration check before starting the endurance test.

(b)
The applicant may service and make minor repairs to the engine during the block tests in accordance with the service and maintenance instructions submitted in compliance with[Sec. 33.4].If the frequency of the serviceis excessive, or the num-ber ofstopsdueto engine malfunctionis excessive, or a major repair, or replacement of apartisfound necessaryduring theblock testsorastheresultof .ndingsfrom the teardowninspection, the engine oritsparts maybe subjected to any additional test the Administrator .nds necessary.
　
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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(133)