CS 25.1165 Engine ignition systems
ED Decision 2003/2/RM
(a) Each battery ignition system must be supplemented by a generator that is automatically 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 simultaneous demands of the engine ignition system and the greatest demands of any electrical system components that draw electrical energy from the same source.
(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) Reserved.
(e) No ground wire for any engine may be routed through a fire zone of another engine unless each part of that wire within that zone is fireproof.
(f) Each ignition system must be independent of any electrical circuit not used for assisting, controlling, or analysing the operation of that system.
(g) There must be means to warn appropriate flight-crew members if the malfunctioning of any part of the electrical system is causing the continuous discharge of any battery necessary for engine ignition.
(h) Each engine ignition system of a turbine powered aeroplane must be considered an essential electrical load.
For large aeroplanes, engine ignition systems must have backup generators ensuring continuous operation if batteries fail. Batteries and generators must handle ignition and electrical demands. Ignition design must consider generator failure and depleted battery scenarios. Engine ignition wiring must be fireproof and independent. Flight crew must be warned of battery discharge. Turbine engine ignition is an essential electrical load.
* Summary by Aviation.Bot - Always consult the original document for the most accurate information.
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