(1)
It must perform its intended function under any foreseeable operating condi-tion.

(2)
When systems and associated components are considered separately and in relation to other systems–

(i)
The occurrence of any failure conditionthat wouldpreventthe continued safe .ight andlanding of theairplanemustbeextremelyimprobable; and

(ii)
The occurrence of any other failure condition that would signi.cantly reduce the capability of the airplane or the ability of the crew to cope with adverse operating conditions must be improbable.

(3)
Warning information must be provided to alert the crew to unsafe system operating conditions and to enable them to take appropriate corrective action. Systems, controls, and associated monitoring and warning means must be designed to minimize crew errors that could create additional hazards.

(4)
Compliance with the requirements of paragraph (b)(2) of this section may be shown by analysis and, where necessary, by appropriate ground, .ight, or simulator test. The analysis must consider–

(i)
Possible modes of failure, including malfunctions and damage from exter-nal sources;

(ii)
The probability of multiple failures and the probability or undetected faults;

(iii) The resulting e.ects of the airplane and occupants, considering the stage of .ight and operating conditions; and
(iv) The crew warning cues, corrective action required, and the crew’s capa-bility of determining faults.
(c)
Each item of equipment, each system, and each installation whose functioning is required by this chapter and that requires a power supply is an ”essential load” on the power supply. The power sources and the system must be able to supply the following power loads in probable operating combinations and for probable durations :

(1)
Loads connected to thepowerdistribution system with the systemfunctioning normally.

(2)
Essential loads after failure of–

(i)
Any one engine on two-engine airplanes; or

(ii)
Any two engines on an airplane with three or more engines; or

(iii) Any power converter or energy storage device.

(3)
Essentialloadsfor whichan alternate source ofpoweris required, as applicable, by the operating rules of this chapter, after any failure or malfunction in any one power supply system, distribution system, or other utilization system.

(d)
Indeterminingcompliance withparagraph(c)(2) ofthis section,thepowerloads may be assumed to be reduced under a monitoring procedure consistent with safety in thekindsof operationsauthorized.Loadsnot requiredincontrolled .ightneed not be considered for the two-engine-inoperative condition on airplanes with three or more engines.

(e)
In showing compliance with this section with regard to the electrical power system and to equipment design and installation, critical environmental and atmospheric conditions,including radiofrequency energy and the e.ects(bothdirect andindi-rect) oflightning strikes, mustbe considered.For electricalgeneration,distribution, and utilization equipment required by or used in complying with this chapter, the ability to provide continuous, safe service under foreseeable environmental condi-tions maybe shownby environmentaltests,design analysis, or referencetoprevious comparable service experience on other airplanes.

(f)
As used in this section, ”systems” refers to all pneumatic systems, .uid systems, electrical systems, mechanical systems, and powerplant systems included in the airplane design, except for the following :

(1)
Powerplant systems provided as part of the certi.cated engine.

(2)
The .ightstructure(such aswing,empennage,control surfacesand theirsys-tems, the fuselage, engine mounting, and landing gear and their related pri-mary attachments) whose requirements are speci.c in subparts C and D of this part.
　
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本文鏈接地址：FAA規(guī)章 美國(guó)聯(lián)邦航空規(guī)章 Federal Aviation Regulations 2(82)