(c)
Category A : Control of engine rotation. For each category A rotorcraft, there must be a means for stopping the rotation of any engine individually in .ight, except that, for turbine engine installations, the means for stopping the engine need be provided only where necessary for safety. In addition–
(1)
Each component of the engine stopping system that is located on the engine side of the .rewall, and that might be exposed to .re, must be at least .re resistant; or
(2)
Duplicate means must be available for stopping the engine and the controls must be where all are not likely to be damaged at the same time in case of .re.
(d)
[Turbine engine installation. For turbine engine installations–
(1)
Designprecautions must be taken to minimize the hazards to the rotorcraftin the event of an engine rotor failure; and
(2)
The powerplant systems associated with engine control devices, systems, and instrumentation must be designed to give reasonable assurance that those engine operatinglimitationsthatadversely a.ectengine rotorstructuralinte-grity will not be exceeded in service.]
(e)
Restart capability :
(1)
A means to restart any engine in .ight must be provided.
(2)
Except for the in-.ight shutdown of all engines, engine restart capability must be demonstrated throughout a .ight envelope for the rotorcraft.
(3)
Following the in-.ight shutdown of all engines, in-.ight engine restart capabi-lity must be provided.
Amdt. 29-36, E.. 1/31/96
FAR 29.907 : Engine vibration.
(a)
Each engine must beinstalled topreventharmful vibration of anypart of the engine or rotorcraft.
(b)
The addition of the rotor and the rotor drive system to the engine may not subject theprincipal rotatingpartsof the engineto excessivevibrationstresses.This must be shown by a vibration investigation.
FAR 29.908 : Cooling fans.
[For coolingfans that are a part of a powerplant installation the following apply :
(a)
Category A. For cooling fans installed in Category A rotorcraft, it must be shown that a fan blade failure will not prevent continued safe .ight either because of damage caused by the failed blade or loss of cooling air.]
(b)
Category B. For coolingfans installedin categoryB rotorcraft, there must be means to protect the rotorcraft and allow a safe landing if a fan blade fails. It must be shown that–
(1) Thefanblade wouldbe containedinthe case of afailure;
′
Elodie Roux. Septembre 2003
Subpart E : Powerplant
(2)
Eachfanislocated sothat afanbladefailure will notjeopardize safety; or
(3)
Each fan blade can withstand an ultimate load of 1.5 times the centrifugal force expected in service, limited by either–
(i)
The highest rotational speeds achievable under uncontrolled conditions; or
(ii)
An overspeed limiting device.
(c) [Fatigue evaluation. Unless a fatigue evaluation under Sec. 29.571 is conducted, it must be shown that cooling fan blades are not operating at resonant conditions within the operating limits of the
rotorcraft.] Amdt. 29-26, E.. 10/3/88
75.2 Rotor Drive System
FAR 29.917 : Design.
(a)
General.The rotordrivesystemincludesanypartnecessary totransmitpowerfrom the enginesto the rotorhubs.Thisincludesgearboxes, shafting, universaljoints, couplings, rotor brake assemblies, clutches, supporting bearings for shafting, any attendant accessorypads ordrives, and any coolingfans that are apart of, attached to, or mounted on the rotor drive system.
(b)
[Design assessment.Adesign assessment mustbeperformed to ensure that the rotor drive systemfunctions safelyover thefull range of conditionsfor which certi.cation is sought.Thedesign assessment mustinclude a detailedfailure analysis toidentify allfailuresthatwillpreventcontinued safe .ightorsafelanding and mustidentify the means to minimize the likelihood of their occurrence.
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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(59)
