AIRPLANE
OPERATIONS
MANUAL
POWERPLANT
REVISION 37
2-10-30
Page
1
Code
01
AOM-145/1114
IGNITION SYSTEM
The engine has a dual redundant ignition system composed of two
ignition exciters, two high-tension igniter leads and two igniters.
The ignition system is turned on by the FADEC during engine starting
cycle or when an engine flameout condition is detected (auto-relight).
Each ignition exciter is controlled by a separate FADEC and powered
by a separate electrical winding of the PMA.
Continuous ignition or ignition off can be manually selected through
the Ignition Selector Knob, located on the Powerplant Control Panel
and connected to the FADECs. Ignition control is performed according
to Ignition Selector Knob position, as follows:
Ignition Selector Knob set to ON:
Both FADECs command associated ignition channel during
start, as soon as the PMA provides sufficient power.
The ignition is not automatically deactivated when the start
cycle is completed.
If the engine is already running, both FADECs activate their
ignition channels.
Ignition Selector Knob set to AUTO:
During ground start, only the FADEC in control activates
the ignition system at the proper time. The engine start will
be performed with only one exciter. The exciters will be
alternately selected for each subsequent ground start.
The FADEC deactivates the ignition system when the
engine starting cycle is completed.
The auto-relight function activates the ignition system.
NOTE: Engines with FADEC B8 software version or later may not turn
off igniters during on-ground deceleration to IDLE.
Ignition Selector Knob set to OFF:
If the engine is not running, the FADEC neither activates
the ignition system nor actuates the engine fuel valve from
closed to open position.
If the engine is already running, at least in IDLE thrust, the
FADEC does not close the engine fuel valve.
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