CS-E 240 Ignition

(a)All spark-ignition Engines shall comply with the following:

(1)The Engine shall be equipped either with: -

(i)a dual ignition system that has entirely independent magnetic and electrical circuits, including spark plugs; or

(ii)an ignition system which will function with at least the equivalent reliability.

(2)If the design of the ignition system includes redundancy: -

(i)the maximum power reduction resulting from a loss of redundancy shall be declared in the appropriate manual(s); ii) provision shall be made to establish the serviceability of the ignition system; the associated procedures and required inspection intervals shall be specified in the appropriate manual(s).

(b)All self-ignition Piston Engines shall comply with the following:

(1)The Engine design and operating procedure must provide a continued ignition capability under the intended operating conditions established in compliance with CS-E 40(d). This must be substantiated, considering the fuel with the limiting ignition delay time or cetane number, by conducting appropriate tests or by providing other evidence. The ignition delay time or the cetane number of the fuel considered for the demonstration will be recorded in the Engine type certificate data sheet.

(2)The Engine constructor must recommend an envelope of conditions for relighting in flight, and must substantiate it by conducting appropriate tests or by providing other evidence. The recommendation must state all of the conditions that are applicable, e.g. the altitude, airspeed, windmilling rotational speed, whether starter assistance is required, and the recommended drill. The possible effects of a low ambient temperature on the relight capability must be included in the development of the recommendation.

[Amdt No: E/5]