JAR 25.903 Engines
(a) Engine type certification.
(1) Each engine must have a type
certificate. (See ACJ 25.903(a).)
(2) Any engine not certificated to JAR–E
must be shown to comply with JAR–E 790 and
JAR–E 800 or be shown to have a foreign
object ingestion service history in similar
installation locations which has not resulted in
any unsafe condition.
(b) Engine isolation. The powerplants must
be arranged and isolated from each other to allow
operation, in at least one configuration, so that the
failure or malfunction of any engine, or of any
system that can affect the engine, will not –
(1) Prevent the continued safe
operation of the remaining engines; or
(2) Require immediate action by any
crew member for continued safe operation.
1 [(c) Control of engine rotation. There must
be means for stopping the rotation of any engine
individually in flight, except that, for turbine
engine installations, the means for stopping the
rotation of any engine need be provided only
where continued rotation could jeopardise the
safety of the aeroplane. Each component of the
stopping system on the engine side of the firewall
that might be exposed to fire must be at least fire
resistant. If hydraulic propeller feathering systems
are used for this purpose, the feathering lines must
be at least fire-resistant under the operating
conditions that may be expected to exist during
feathering.
(d) Turbine engine installations. For
turbine engine installations –
(1) Design precautions must be taken to
minimise the hazards to the aeroplane in the
event of an engine rotor failure or of a fire
originating within the engine which burns
1 [through the engine case. (See ACJ
25.903(d)(1) and AMJ 20-128A.)
(2) The powerplant systems associated
with engine control devices, systems, and
instrumentation, must be designed to give
reasonable assurance that those engine
operating limitations that adversely affect
turbine rotor structural integrity will not be
exceeded in service.
(e) Restart capability.
(1) Means to restart any engine in flight
must be provided.
(2) An altitude and airspeed envelope
must be established for in-flight engine
restarting, and each engine must have a restart
capability within that envelope. (See ACJ
25.903(e)(2).)
(3) For turbine engine powered
aeroplanes, if the minimum windmilling speed
of the engines, following the in-flight shut
down of all engines, is insufficient to provide
the necessary electrical power for engine
ignition, a power source independent of the
engine-driven electrical power generating
system must be provided to permit in-flight
engine ignition for restarting.
(f) Not required for JAR–25. See Subpart J.
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