Amdt. 25-57, E.. 3/26/84
FAR 25.1165 : Engine ignition systems.
(a)
Eachbatteryignition system mustbe supplementedby agenerator thatis automati-cally available as an alternate source of electrical energy to allow continued engine operation if any battery becomes depleted.
(b)
The capacity of batteries and generators must be large enough to meet the simul-taneous demands of the engine ignition system and the greatest demands of any electrical system components that draw electrical energy from the same source.
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Elodie Roux. Septembre 2003
Subpart E : Powerplant
(c)
The design of the engine ignition system must account for–
(1)
The condition of an inoperative generator;
(2)
The condition of a completely depleted battery with the generator running at its normal operating speed; and
(3)
The condition of a completely depleted battery with the generator operating at idling speed, if there is only one battery.
(d)
Magnetoground wiring(forseparateignitioncircuits) thatliesonthe enginesideof the .re wall, must be installed, located, or protected, to minimize the probability of simultaneous failure of two or more wires as a result of mechanical damage, electrical faults, or other cause.
(e)
No ground wire for any engine may be routed through a .re zone of another engine unless each part of that wire within that zone is .reproof.
(f)
Each ignition system must be independent of any electrical circuit, not used for assisting, controlling, or analyzing the operation of that system.
(g)
Theremustbe meansto warnappropriate .ightcrewmembersif the malfunctioning of any part of the electrical system is causing the continuous discharge of any battery necessary for engine ignition.
(h)
[Eachengine ignition system of a turbine powered airplane must be considered an essential electrical load.]
Amdt. 25-72, E.. 8/20/90
FAR25.1167 :[Accessorygearboxes.]
[For airplanes equippedwith an accessory gearbox that is not certi.cated as part of an engine–
(a)
The engine withgearboxand connecting transmissionsand shafts attached mustbe subjected to the tests speci.ed in Secs.33.49 or33.87 of this chapter as applicable;
(b)
The accessorygearbox must meet the requirements ofSecs.33.25 and33.53 or33.91 of this chapter, as applicable; and
(c)
Possible misalignments andtorsionalloadings ofthegearbox,transmission, andshaft system, expected to result under normal operating conditions must be evaluated.]
Amdt. 25-38, E.. 2/1/77
48.9 Powerplant Fire Protection
FAR 25.1181 : Designated .re zones : regions included.
(a) Designated .re zones are–
(1)
The enginepower section;
(2)
The engine accessory section;
(3)
Except for reciprocating engines, any complete powerplant compartment in which noisolationisprovidedbetween the enginepower section andthe engine accessory section;
(4)
Any auxiliarypower unit compartment;
(5)
Any fuel-burning heater and other combustion equipment installation descri-bed in Sec. 25.859;
(6)
The compressor and accessory sections of turbine engines; and
(7)
Combustor, turbine, and tailpipe sections of turbine engine installations that contain lines or components carrying .ammable .uids or gases.
(b) [Each designated .re zone must meet the requirements of Secs. 25.867, and 25.1185 through 25.1203.]
Amdt. 25-72, E.. 8/20/90
FAR25.1182:[Nacelleareasbehind .rewalls,and enginepod attaching struc-tures containing .ammable .uid lines.]
(a)
[Each nacelle area immediately behind the .rewall, and each portion of any en-gine pod attaching structure containing .ammable .uid lines, must meet each re-quirement ofSecs. 25.1103(b),25.1165(d) and(e),25.1183,25.1185(c),25.1187, 25.1189, and 25.1195 through 25.1203, including those concerning designated .re zones.However,enginepod attaching structuresneed notcontain .redetectionor extinguishing means.
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本文链接地址：FAA规章 美国联邦航空规章 Federal Aviation Regulations 4(9)
