(2)
Anyautomatic engine controlthatispart ofthe engine must controlthe engine during the endurance test except for operations where automatic control is normally overridden by manual control or where manual control is otherwise speci.ed for a particular test run.
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Elodie Roux. Septembre 2003
SubpartF :BlockTests;TurbineAircraftEngines
(3)
Except asprovidedinparagraph(a)(5) ofthis section,powerorthrust,gas temperature, rotor shaft rotational speed, and,iflimited,temperature of exter-nal surfacesof the engine mustbe atleast100percent of the value associated with theparticularengine operationbeing tested.Morethan onetest may be run if all parameters cannot be held at the 100 percent level simultaneously.
(4)
Therunsmustbemadeusingfuel,lubricantsandhydraulic .uidwhich conform to the speci.cations speci.ed in complying with Sec. 33.7(c).
(5)
Maximum airbleedfor engine andaircraft services mustbe usedduring atleast one-.fth of the runs.However,fortheseruns,thepowerorthrustorthe rotor shaft rotational speed may be less than 100 percent of the value associated with the particular operation being tested if the Administrator .nds that the validity of the endurance test is not compromised.
(6)
Each accessory drive and mounting attachment must be loaded. The load im-posed by each accessory used only for aircraft service must be the limit load speci.ed by the applicant for the engine drive and attachment point during rated maximum continuous power or thrust and higher output. The endu-rance test of any accessory drive and mounting attachment under load may be accomplished on a separate rig if the validity of the test is con.rmed by an approved analysis.
(7)
During the runs at any rated power or thrust the gas temperature and the oil inlet temperature must be maintained at the limiting temperature except where the test periods are not longer than 5 minutes and do not allow sta-bilization. At least one run must be made with fuel, oil, and hydraulic .uid at the minimum pressure limit and at least one run must be made with fuel, oil,andhydraulic .uid atthemaximumpressurelimitwith .uid temperature reduced as necessary to allow maximum pressure to be attained.
(8)
[Ifthe number of occurrences of either transient rotor shaft overspeed or tran-sientgas overtemperatureislimited, that number ofthe accelerations required byparagraph(b) through(g) ofthis section mustbe made atthelimiting overspeed or overtemperature. If the number of occurrences is not limited, half the required accelerations must be made at the limiting overspeed or overtemperature.]
(9)
For each engine type certi.cated for use on supersonic aircraft the following additional test requirements apply :
(i)
To changethethrust setting,thepowercontrollevermustbemovedfrom the initial position to the .nal position in not more than one second ex-cept for movementsinto the fuel burning thrust augmentor augmentation position if additional time to con.rm ignition is necessary.
(ii)
During the runs at any rated augmented thrust the hydraulic .uid tem-perature must be maintained at the limiting temperature except where the test periods are not long enough to allow stabilization.
(iii) Duringthe simulatedsupersonic runs thefuel temperature andinduction air temperature may not be less than the limiting temperature.
(iv)
The endurance test must be conducted with the fuel burning thrust aug-mentor installed, with the primary and secondary exhaust nozzles instal-led, and with the variable area exhaust nozzles operated during each run according to the methods speci.ed in complying with Sec. 33.5(b).
(v) During the runs at thrust settings for maximum continuous thrust and percentages thereof, the engine must be operated with the inlet air dis-tortion at the limit for those thrust settings. 中國航空網 www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 5(144)
