(1)
Ontheground(such asby a stickgauge); and

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

(e)
[Deleted.]

Amdt. 23-51, E.. 03/12/96
33.3 Electrical Systems and Equipment
FAR 23.1351 : General.
(a)
Electrical system capacity.Each electrical systemmustbe adequatefortheintended use. In addition–

(1)
Electric power sources, their transmission cables, and their associated control and protective devices, must be able to furnish the required power at the proper voltage to each load circuit essential for safe operation; and

(2)
Compliance withparagraph(a)(1) of this section mustbe shown asfollows–

(i)
Fornormal,utility, and acrobaticcategory airplanes,by an electricalload analysis orby electrical measurementsthat accountfor the electricalloads applied to the electrical systeminprobable combinations andforprobable durations; and

(ii)
For commuter category airplanes, by an electrical load analysis that ac-countsforthe electricalloads applied tothe electrical systeminprobable 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 airplane;

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

(iii) So designed that the risk of electrical shock to crew, passengers, and groundpersonnelis reduced to a minimum.

(2)
[Electricpower sources mustfunctionproperlywhen connectedin combination or independently.

(3)
No failure or malfunction of any electric power source may impair the ability of any remaining source to supply load circuits essential for safe operation.

(4)
In addition, for commuter category airplanes, the following apply :]

(i)
Each system must be designed so that essential load circuits can be sup-pliedinthe event of reasonablyprobablefaults oropen circuitsincluding faults in heavy current carrying cables;

(ii)
A means must be accessible in .ight to the .ight crewmembers for the individualand collectivedisconnection ofthe electricalpower sourcesfrom the system;

(iii) The system must be designed so that voltage and frequency, if appli-cable, at the terminals of all essential load equipment can be maintained within thelimitsfor which the equipmentisdesignedduring anyprobable operating conditions;
(iv)
If two independent sources of electrical power for particular equipment or systems are required, their electrical energy supply must be ensured by means such as duplicate electrical equipment, throwover switching, or multichannel orloop circuits separately routed; and

(v)
Forthepurpose of complying withparagraph(b)(5) of this section, the distribution system includes the distribution busses, their associated fee-ders, and each control and protective device.

′
Elodie Roux. Septembre 2003
Subpart F : Equipment
(c)
Generating system.There mustbe atleast onegenerator/alternatorif the electrical system supplies power to load circuits essential for safe operation. In addition–

(1)
Eachgenerator/alternatormustbe abletodeliverits continuous ratedpower, or such power as is limited by its regulation system.

(2)
Generator/alternator voltage control equipment must be able to dependably regulatethegenerator/alternatoroutput within ratedlimits;

(3)
[Automatic means mustbeprovidedtopreventdamageto anygenerator/alternator and adverse e.ects on the airplane electrical system due to reverse current. A means must alsobeprovided todisconnect eachgenerator/alternatorfrom the battery and other generators/alternators.]
　
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