(b)
Compliance withparagraph(a) ofthis section mustbe shownby analysis ortests, and the following factors must be considered :
(1)
Possible sources and paths of .uid leakage, and means of detecting leakage.
(2)
Flammability characteristics of .uids, including e.ects of any combustible or absorbing materials.
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Elodie Roux. Septembre 2003
Subpart D : Design and Construction
(3)
Possible ignition sources, including electrical faults, overheating of equipment, and malfunctioning of protective devices.
(4)
Meansavailableforcontrolling orextinguishing a .re,such asstopping .owof .uids,shuttingdownequipment, .reproof containment,oruseof extinguishing agents.
(5)
Abilityof rotorcraft componentsthat arecriticaltosafety of.ighttowithstand .re and heat.
(c)
If action by the .ight crew is required to prevent or counteract a .uid .re (e.g. equipment shutdown or actuation of a .re extinguisher),quick acting means must be provided to alert the crew.
(d)
Eachareawhere .ammable .uidsorvaporsmight escapebyleakageof a .uid system must be identi.ed and de.ned.]
Amdt. 29-17, E.. 12/1/78
FAR 29.865 : External loads.
(a)
[ It must be shown by analysis, test, or both, that the rotorcraft external load at-taching means for rotorcraft-load combinations to be used for nonhuman external cargo applications can withstand alimit staticload equal to2.5, or somelowerload factor approved under Secs. 29.337 through 29.341, multiplied by the maximum external load for which authorization is requested. It must be shown by analysis, test, or both that the rotorcraft external load attaching means and corresponding personnel carrying device system for rotorcraft-load combinations to be used for human external cargo applications can withstand a limit static load equal to 3.5 or some lower load factor, not less than 2.5, approved under Secs. 29.337 through 29.341, multiplied by the maximum external load for which authorization is re-quested. The load for any rotorcraft-load combination class, for any external cargo type, mustbe appliedinthe verticaldirection.Forjettisonable externalloadsof any applicable external cargo type, the load must also be applied in any direction making the maximum angle with the vertical that can be achieved in service but not less than 30 deg.. However, the 30 deg. angle may be reduced to a lesser angle if–]
(1)
An operatinglimitationis establishedlimiting externalload operations to such angles for which compliance with this paragraph has been shown; or
(2)
It is shown that the lesser angle can not be exceeded in service.
(b)
[The externalloadattaching means,forjettisonable rotorcraft-load combinations, mustinclude aquick-releasesystemto enablethepilotto releasethe externalload quickly during .ight. The quick-release system must consist of a primary quick releasesubsystemand abackupquick releasesubsystemthat areisolatedfrom one another. The quick release system, and the means by which it is controlled, must comply with the following :
(1)
A controlfortheprimaryquick release subsystem mustbeinstalled either on one of the pilot’s primary controls or in an equivalently accessible location and must be designed and located so that it may be operated by either the pilot ora crewmember withouthazardouslylimiting the ability to control the rotorcraft during an emergency situation.
(2)
A control for the backup quick release subsystem, readily accessible to either the pilot or another crewmember, must be provided.
(3) Both the primary and backup quick release subsystems must–
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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(55)
