DOC AIRBUS | AMM A320FIGNITION STARTING AND CONTINUOUS RELIGHT - DESCRIPTION AND OPERATION
** ON A/C NOT FOR ALL
1. Description
The ignition circuit is supplied with 115VAC - 400Hz. The electrical power is supplied via the EEC and EIU which control the ignition of the igniter plugs. A dormant failure of an ignition exciter is not possible for more than one flight because:
** ON A/C NOT FOR ALL The ignition circuit is supplied with 115VAC - 400Hz. The electrical power is supplied via the EEC and EIU which control the ignition of the igniter plugs. A dormant failure of an ignition exciter is not possible for more than one flight because:
- the two ignition systems are independent
- the EEC selects alternately ignition system A or B.
Ignition system A comprises the upper ignition exiter and its associated cable and igniter, ignition system B comprises the lower ignition exiter and its associated cable and igniter.
2. Operation
Ignition and Starting System - Engine 1A. Automatic Start Sequence
When an automatic start sequence has been activated by the EEC (ENG/MODE selector switch in IGN/START position and MASTER control switch to ON), an automatic dry crank sequence of 30 seconds is performed; then, the EEC energizes automatically the appropriate ignition exciter and keeps it energized until N2 reaches 43%.
For inflight restart the EEC selects simultaneously both ignition exciters.
On the ground, after engine start, the selector must be placed in NORM position, then back to IGN/START to select continuous ignition.
In flight after engine restart, if the selector is maintained in IGN/START position, the EEC selects the continuous ignition on the corresponding engine.
In case of incident during an automatic starting on the ground, the EEC aborts automatically the sequence by closing the starter shut-off valve and the HP fuel shut-off valve and deenergizing the ignitors.
When an automatic start sequence has been activated by the EEC (ENG/MODE selector switch in IGN/START position and MASTER control switch to ON), an automatic dry crank sequence of 30 seconds is performed; then, the EEC energizes automatically the appropriate ignition exciter and keeps it energized until N2 reaches 43%.
For inflight restart the EEC selects simultaneously both ignition exciters.
On the ground, after engine start, the selector must be placed in NORM position, then back to IGN/START to select continuous ignition.
In flight after engine restart, if the selector is maintained in IGN/START position, the EEC selects the continuous ignition on the corresponding engine.
In case of incident during an automatic starting on the ground, the EEC aborts automatically the sequence by closing the starter shut-off valve and the HP fuel shut-off valve and deenergizing the ignitors.
B. Alternate Start Sequence
When a manual start sequence has been activated by the EEC (ENG/MODE selector switch in IGN/START position and the ENG/MAN START pushbutton switch selected to ON) the EEC opens the starter valve and a dry crank sequence of 30s is performed. Then the MASTER control switch is placed in ON position (the EEC opens the HP fuel shut off valve and energizes the ignition exciters).
The deenergization of the ignition exciters is automatically commanded by the EEC.
Positioning of the MASTER control switch to OFF , during that starting sequence, results in ignition exciter deenergization.
When a manual start sequence has been activated by the EEC (ENG/MODE selector switch in IGN/START position and the ENG/MAN START pushbutton switch selected to ON) the EEC opens the starter valve and a dry crank sequence of 30s is performed. Then the MASTER control switch is placed in ON position (the EEC opens the HP fuel shut off valve and energizes the ignition exciters).
The deenergization of the ignition exciters is automatically commanded by the EEC.
Positioning of the MASTER control switch to OFF , during that starting sequence, results in ignition exciter deenergization.
C. Continuous Ignition
(1) Manual Selection
When the engines are running on the ground or in flight the continuous ignition is obtained by positioning the ENG/MODE selector switch in IGN/START position.
When the engines are running on the ground or in flight the continuous ignition is obtained by positioning the ENG/MODE selector switch in IGN/START position.
(2) Automatic selection
The EEC automatically selects continuous ignition when:
The EEC automatically selects continuous ignition when:
- the ENG/MODE selector switch is turned to IGN/START while the engines are at or above idle,
- flameout is detected,
- takeoff (determined by TRA) or flex takeoff is performed,
- engine anti-ice is selected,
- EIU fails (except during cranking),
- approach idle is selected,
- Master Lever is inadvertently cycled from ON to OFF then back to ON position.
D. Igniter Plug Test
The operation of the igniter plugs can be checked on the ground, engine not running, through the maintenance MENU mode of the FADEC.
The test will be performed by selecting the corresponding IGNITOR TEST page in the MENU and positioning the MASTER control switch to ON to have the 115VAC power supply on the relevant engine.
The operation of the igniter plugs can be checked on the ground, engine not running, through the maintenance MENU mode of the FADEC.
The test will be performed by selecting the corresponding IGNITOR TEST page in the MENU and positioning the MASTER control switch to ON to have the 115VAC power supply on the relevant engine.