(2)
No failure or malfunction of any power source can create a hazard or impair the ability of remaining sources to supply essential loads;

(3)
The system voltage andfrequency(as applicable) attheterminals of essential load equipment can be maintained within the limits for which the equipment isdesigned,during anyprobable operating condition;

(4)
System transientsdue to switching,fault clearing, or other causesdo not make essential loads inoperative, and do not cause a smoke or .re hazard;

(5)
There are means accessible in .ight to appropriate crewmembers for the in-dividual and collective disconnection of the electrical power sources from the mainbus; and

(6)
There are means to indicate to appropriate crewmembers the generating sys-temquantities essentialforthe safe operation ofthe system, such asthe voltage and current supplied by each generator.

(c)
External power. If provisions are made for connecting external power to the rotor-craft, and that external power can be electrically connected to equipment other than that used for engine starting, means must be provided to ensure that no ex-ternal power supply having a reverse polarity, or a reverse phase sequence, can supply power to the rotorcraft’s electrical system.

(d)
[Operation with the normal electrical power generating system inoperative.

(1)
It must be shown by analysis, tests, or both, that the rotorcraft can be ope-rated safely in VFR conditions for a period of not less than 5 minutes, with the normal electrical power generating system (electrical power sources ex-cluding thebattery) inoperative, with criticaltypefuel(fromthe standpoint of .ameout and restart capability), and with the rotorcraft initially at the maximum certi.cated altitude. Parts of the electrical system may remain on if–

(i)
Asinglemalfunction,including awirebundleorjunctionbox .re,cannot result in loss of the part turned o. and the part turned on;

(ii)
The parts turned on are electrically and mechanically isolated from the partsturned o.; and]

(2)
Additional requirements for Category A Rotorcraft.

(i)
Unless it can be shown that the loss of normal electrical power genera-ting system is extremely improbable, an emergency electrical power sys-tem,independent of the normal electricalpowergenerating system, must be provided, with su.cient capacity to power all systems necessary for continued safe .ight and landing.

(ii)
Failures,includingjunctionbox,controlpanel,orwirebundle .res,which would result in the loss of the normal and emergency systems, must be shown to be extremely improbable.

(iii) Systems necessary for immediate safety must continue to operate follo-wing the loss of the normal electrical power generating system, without the need for .ight crew action.
Amdt. 29-42, E.. 9/8/98
′
Elodie Roux. Septembre 2003
Subpart F : Equipment
FAR 29.1353 : Electrical equipment and installations.
(a)
Electrical equipment, controls, and wiring mustbe installed so that operation of any one unit or system of units will not adversely a.ect the simultaneous operation of any other electrical unit or system essential to safe operation.

(b)
Cables mustbegrouped, routed, and spaced so thatdamage to essential circuits will be minimized if there are faults in heavy current-carrying cables.

(c)
Storage batteries must be designed and installed as follows :

(1)
Safe cell temperatures andpressuresmustbe maintainedduring anyprobable charging and discharging condition. No uncontrolled increase in cell tempe-rature may result when the battery is recharged (after previous complete discharge)–

(i)
At maximum regulated voltage orpower;

(ii)
During the .ight of maximum duration; and

(iii) Under the most adverse cooling condition likely in service.
　
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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(93)