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 ignition circuit is energized via the ECU and EIU which control the ignition of the spark igniters. 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 ignition circuit is energized via the ECU and EIU which control the ignition of the spark igniters. A dormant failure of an ignition exciter is not possible for more than one flight because:
- the two ignition systems are independent,
- the FADEC selects alternately ignition system A or B.
Ignition and Starting SystemA. Automatic Start
The ENG start panel (115VU) initial configuration is:
The ENG start panel (115VU) initial configuration is:
- ENG/MODE/CRANK/NORM/IGN START selector switch in NORM position,
- both ENG/MASTER control switches in OFF position.
B. On ENG start panel (115VU)
(1) Place the selector switch in the IGN/START position: the engine page appears
(2) Place the MASTER 1(2) control switch in the ON position:
- the starter pneumatic valve opens,
- at N2 > 16 percent the ignition system is excited,
- at N2 > 20 percent the HP fuel SOV opens,
- at N2 > 50 percent the starter valve closes and the ignition stops.
(3) Place the selector switch in NORM position. The engine page disappears.
(4) If you place the selector switch in: NORM position after engine 1 starting then in IGN/START position prior to starting : continuous ignition is selected for engine 1.
For ground start, in case of failure of the automatic starter valve actuation device: the ECU logic is compatible with a manual actuation of the start valve without any additional signal.
In case of an ignition delay: the ECU operates automatically both ignition exciters after an automatic dry motoring sequence and provides information to the cockpit.
During automatic starting, the ECU provides engine limit protection (N1, N2, EGT).
For ground start, in case of failure of the automatic starter valve actuation device: the ECU logic is compatible with a manual actuation of the start valve without any additional signal.
In case of an ignition delay: the ECU operates automatically both ignition exciters after an automatic dry motoring sequence and provides information to the cockpit.
During automatic starting, the ECU provides engine limit protection (N1, N2, EGT).
(5) Start Interruption
The interruption of automatic starting can be achieved if:
The interruption of automatic starting can be achieved if:
(a) You place the MASTER control switch back to OFF. This causes:
- the direct closure of the HP fuel SOV,
- the starter valve closure via the ECU,
- the ignition exciters deenergization.
(b) The ECU aborts the starting sequence in case of detected incident:
- valve failure,
- HP fuel SOV failure,
- hot start,
- stall,
- overspeed,
- Engine fails to lightoff after continuous ignition is selected.
(6) The monitoring of an engine start is described in 73-20-00.
C. Alternative Start (Manual Start)
(1) On the ENG start panel (115VU):
- the selector switch is in NORM position,
- both MASTER control switches are in OFF position.
(2) ENG/MAN START pushbutton switch on the overhead panel is in OFF position.
(a) On the overhead panel: select ENG/MAN START pushbutton switch to ON.
(b) On the ENG start panel (115VU).
1 Place the selector switch in IGN/START position:
- the starter valve opens,
- the ENG page appears.
2 Place the MASTER control switch in ON position at 20 percent N2:
- ignition system 1(2) is excited and the HP fuel SOV opens,
- at N2 > 50 percent the starter valve closes and ignition system 1(2) is no more excited.
3 Place the selector switch in NORM position:
- the ENG page disappears.
4 Place ENG/MAN START pushbutton switch in OFF position
NOTE: If you place the ENG/MODE/CRANK/NORM/IGN START selector switch in: NORM position after engine 1 starting, then in IGN/START position prior to engine 2 starting: continuous ignition is automatically selected for engine 1.
With the MASTER control switch in ON position or ENG/MAN START pushbutton switch set to ON and the selector switch in NORM position : there is not effect on the corresponding engine (if it is not running).
With the MASTER control switch in ON position or ENG/MAN START pushbutton switch set to ON and the selector switch in NORM position : there is not effect on the corresponding engine (if it is not running).
(3) Alternative start interruption
You interrupt the alternative start if:
You interrupt the alternative start if:
- you release the ENG/MAN START pushbutton switch with the MASTER control switch in OFF position,
- you place the MASTER control switch back in OFF position if it was to ON.
D. Continuous Ignition
(1) Manual selection
When engines are running on ground or in flight: place the ENG/MODE/CRANK/NORM/IGN START selector switch in IGN START position.
When engines are running on ground or in flight: place the ENG/MODE/CRANK/NORM/IGN START selector switch in IGN START position.
(2) Automatic selection
For an in-flight restarting when:
For an in-flight restarting when:
- you select engine anti-ice (ECS data),
- the EIU fails (except during cranking),
- flameout is detected,
- ignition delay during start.
During an automatic start, as soon as N2 is higher than 16 percent, the start must occur in the 15 to 20 seconds that follow (depending on the ambient temperature). If this time is greater and the ECU does not detect a difference of the EGT of at least 42 DEG.C, the ECU controls a dry motoring cycle followed by a selection of the continuous ignition.