(b)
Thetorsionalandbending vibration stresses ofthe crankshaft andthepropeller shaft or other output shaft may not exceedthe endurancelimit stress ofthe materialfrom which the shaft is made. If the maximum stress in the shaft cannot be shown to be below the endurancelimit by measurement, the vibrationfrequency and amplitude must be measured. The peak amplitude must be shown to produce a stress below the endurancelimit; if not,the engine mustbe run atthe conditionproducing the peakamplitude until,for steel shafts,10 million stress reversalshavebeen sustained without fatigue failure and, for other shafts, until it is shown that fatigue will not occur within the endurance limit stress of the material.
(c)
Eachaccessorydrive and mounting attachment mustbeloaded, with theloadsimpo-sedby each accessory used only for an aircraft servicebeing the limit load speci.ed by the applicantforthedrive or attachmentpoint.
(d)
[Thevibrationsurveydescribedinparagraph(a) ofthissectionmustbe repeated with that cylinder not .ring which has the most adverse vibration e.ect, in order to establish the conditions under which the engine can be operated safely in that abnormal state. However, for this vibration survey, the engine speed range need only extend from idle to the maximum desired takeo. speed, and compliance with paragraph(b) of this section need notbe shown.]
Amdt. 33-10, E.. 3/26/84
FAR 33.45 : Calibration tests.
(a) [Each engine must be subjected to the calibration tests necessary to establish its power characteristics and the conditions for the endurance test speci.ed in Sec.
33.49. The results of the power characteristics calibration tests form the basis for establishingthe characteristics ofthe engine overits entire operating range of crank-shaft rotational speeds, manifoldpressures,fuel/air mixture settings, and altitudes. Power ratings are based upon standard atmospheric conditions with only those ac-cessories installed which are essential for engine functioning.
(b) A power check at sea level conditions must be accomplished on the endurance test engine after the endurance test. Any change in power characteristics which occurs during the endurance test must be determined. Measurements taken during the .nal portion of the endurance test may be used in showing compliance with the requirements of this paragraph.]
Amdt. 33-6, E.. 10/31/74
FAR 33.47 : Detonation test.
Each engine must be tested to establish that the engine can function without deto-nation throughout its range of intended conditions of operation.
FAR 33.49 : Endurance test.
(a)
General. Each engine mustbe subjected to an endurance test thatincludes a total of 150hours of operation(except asprovidedinparagraph(e)(1)(iii) ofthis section) and, depending upon the type and contemplated use of the engine, consists of one of the series of runs speci.edinparagraphs(b) through(e) of this section, as appli-cable.The runs mustbe madein the orderfound appropriateby theAdministrator fortheparticular enginebeing tested.During the endurancetestthe enginepower and the crankshaft rotational speed must be kept within ±3 percent of the rated values. During the runs at rated takeo. power and for at least 35 hours at rated maximum continuous power, one cylinder must be operated at not less than the limiting temperature, the other cylinders must be operated at a temperature not lower than 50 degrees F below the limiting temperature, and the oil inlet tempe-rature must be maintained within ±10 degrees F of the limiting temperature. An enginethatisequipped with apropellershaft mustbe .ttedfortheendurancetest with a propeller that thrust-loads the engine to the maximum thrust which the engine is designed to resist at each applicable operating condition speci.ed in this section. Each accessory drive and mounting attachment must be loaded. During operation at rated takeo. power and rated maximum continuous power, the load imposed by each accessory used only for an aircraft service must be the limit load speci.edby the applicantforthe enginedrive or attachmentpoint.
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本文鏈接地址：FAA規(guī)章 美國聯(lián)邦航空規(guī)章 Federal Aviation Regulations 5(130)
