(d)
Eachareawhere .ammable .uidsorvaporsmight escapebyleakageof a .uid system must be identi.ed and de.ned.]

Amdt. 27-16, E.. 12/1/78
64.8 External Loads
FAR 27.865 : 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. 27.337 through 27.341, 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. 27.337 through 27.341, 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 cannot 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–
(i)
Be reliable, durable, and function properly with all external loads up to and including the maximum external limit load for which authorization is requested.

(ii)
Be protected against electromagnetic interference (EMI) from external and internal sources and against lightning to prevent inadvertent load release.

(A)
The minimumlevel ofprotection requiredforjettisonable rotorcraft-load combinations used for nonhuman external cargo is a radio fre-quency .eld strength of 20 volts per meter.

(B)
The minimum level ofprotection requiredforjettisonable rotorcraft-load combinations used for human external cargois a radio frequency .eld strength of200 voltsper meter.

(iii) Beprotected against anyfailure that could be induced by afailure mode of any other electrical or mechanical rotorcraft system.
(c)
For rotorcraft-load combinations to be used for human external cargo applications, the rotorcraft must–

(1)
For jettisonable external loads, have a quick-release system that meets the requirements ofparagraph(b) of this section and that–

(i)
Providesadual actuationdevicefortheprimaryquick releasesubsystem, and

(ii)
Provides a separate dual actuation device for the backup quick release subsystem;
　
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 4(100)