(c)
Fuel .owmeter system. If a fuel .owmeter system is installed, each metering com-ponent must have a means for bypassing the fuel supply if malfunction of that component severely restricts fuel .ow.

(d)
Oil quantity indicator. There must be means to indicate the quantity of oil in each tank–

(1)
Ontheground(including during the .lling of each tank); and

(2)
In .ight, if there is an oil transfer system or reserve oil supply system.

(e)
[Rotor drive system transmissions and gearboxes utilizing ferromagnetic materials must be equipped with chip detectors designed to indicate the presence of ferro-magnetic particles resulting from damage or excessive wear. Chip detectors must–

(1) Bedesignedtoprovide a signalto thedevice requiredbySec.27.1305(v)andbe provided with a means to allow crewmembers to check, in .ight, the function of each detector electrical circuit and signal.]

(2)
[Reserved.] Amdt. 27-37, E.. 10/18/99

66.3 Electrical Systems and Equipment
FAR 27.1351 : General
(a)
Electrical system capacity. Electrical equipment must be adequate for its intended use. In addition–

(1)
Electric power sources, their transmission cables, and their associated control andprotectivedevices mustbe abletofurnishthe requiredpower at theproper voltage to each load circuit essential for safe operation; and

(2)
Compliance with subparagraph (1) of this paragraph must be shown by an electrical load analysis, or by electrical measurements that take into account the electrical loads applied to the electrical system, in probable combinations and for probable durations.

(b)
Function. For each electrical system, the following apply :

(1) Each system, when installed, must be–
(i)
Free from hazards in itself, in its method of operation, and in its e.ects on other parts of the rotorcraft; and

(ii)
Protectedfrom fuel, oil, water, otherdetrimental substances, and mecha-nical damage.

(2)
Electricpowersourcesmustfunctionproperly when connectedin combination or independently.

(3)
Nofailure or malfunction ofany source mayimpair the ability of any remaining source to supply load circuits essential for safe operation.

(4)
Each electric power source control must allow the independent operation of each source.

(c)
Generating system.There mustbe atleast onegeneratorif the system suppliespower to load circuits essential for safe operation. In addition–

(1)
Each generator must be able to deliver its continuous rated power;

(2)
Generator voltage controlequipment mustbe able todependably regulate each generator output within ratedlimits;

(3)
Eachgenerator musthave a reverse current cutoutdesigned todisconnectthe generatorfrom thebatteryandfrom the othergenerators when enough reverse current exists to damage that generator; and

(4)
Each generator must have an overvoltage control designed and installed to preventdamage to the electricalsystem, or to equipment suppliedby the elec-trical system, that could resultif thatgenerator weretodevelop an overvoltage condition.

(d)
Instruments.There mustbe means toindicate to appropriate crewmembers the elec-tricpower systemquantities essentialfor safe operation of the system. In addition–

(1)
For direct current systems, an ammeter that can be switched into each gene-rator feeder may be used; and

(2)
If there is only one generator, the ammeter may be in the battery feeder.

(e)
[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.]
　
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本文鏈接地址：FAA規(guī)章 美國聯(lián)邦航空規(guī)章 Federal Aviation Regulations 4(124)