DOC AIRBUS | AMM A320FIGNITION - GENERAL - DESCRIPTION AND OPERATION
** ON A/C NOT FOR ALL
** ON A/C NOT FOR ALL
1. General
A. Ignition system
The ignition system supplies a high-energy spark to ignite the fuel/air mixture in the combustor. The ignition system is composed of the ignition exciter, two ignition cables and two igniter plugs. The Ignition Exciter is a dual channel exciter that supplies high voltage to the Ignition Cables and Igniter Plugs for the purpose of fuel ignition during engine start when commanded by the Engine Electronic Control (EEC).
The EEC alternates between Channel A and B after each start. In addition, if the engine fails to start using the Channel in control the EEC will automatically select dual ignition at the subsequent start and notify the crew of the single channel fault by and ECAM warning.
The Ignition Exciter receives 115 VAC electrical input power from the aircraft and delivers an output voltage to the Igniter Plugs at a spark rate of 1 to 3 sparks per second when commanded by the EEC. Both channels of the EEC can control either Ignition Cable 1 or Ignition Cable 2.
The system will provide adequate spark rates for burner ignition throughout the engine ignition envelope in continuous duty. Redundant ignition systems are incorporated into the design.
The ignition system supplies a high-energy spark to ignite the fuel/air mixture in the combustor. The ignition system is composed of the ignition exciter, two ignition cables and two igniter plugs. The Ignition Exciter is a dual channel exciter that supplies high voltage to the Ignition Cables and Igniter Plugs for the purpose of fuel ignition during engine start when commanded by the Engine Electronic Control (EEC).
The EEC alternates between Channel A and B after each start. In addition, if the engine fails to start using the Channel in control the EEC will automatically select dual ignition at the subsequent start and notify the crew of the single channel fault by and ECAM warning.
The Ignition Exciter receives 115 VAC electrical input power from the aircraft and delivers an output voltage to the Igniter Plugs at a spark rate of 1 to 3 sparks per second when commanded by the EEC. Both channels of the EEC can control either Ignition Cable 1 or Ignition Cable 2.
The system will provide adequate spark rates for burner ignition throughout the engine ignition envelope in continuous duty. Redundant ignition systems are incorporated into the design.
B. Electronic Engine Control
The EEC automatically controls the ignition systems. During engine start, one or both ignition systems are energized at the same time as the fuel flow is turned on. During an auto-start on the ground, the EEC selects one ignition system (System A or System B) for two starts in row (one on Channel A and one on Channel B), then for the next two starts in row, the other ignition system is selected.
The EEC automatically controls the ignition systems. During engine start, one or both ignition systems are energized at the same time as the fuel flow is turned on. During an auto-start on the ground, the EEC selects one ignition system (System A or System B) for two starts in row (one on Channel A and one on Channel B), then for the next two starts in row, the other ignition system is selected.
2. System Description
The ignition system is used at engine start, engine relight and each time ambient conditions require a continuous ignition to prevent the risk of flame-out.
Each engine has two electrically-independent ignition systems. Each system can be used at the same time or alternately to prevent dormant failure.
When the manual or continuous ignition selection is used, the EEC energizes both igniters based on the logic and aircraft inputs of the flap position, cowl anti-ice status and/or continuous ignition commands.
The EEC includes an automatic ignition system as an integral part of the EEC's ignition function.
The EEC includes an automatic relight system which energizes both igniters within two seconds of when an engine flame-out has been detected.
The ignition system consist of:
The ignition system is used at engine start, engine relight and each time ambient conditions require a continuous ignition to prevent the risk of flame-out.
Each engine has two electrically-independent ignition systems. Each system can be used at the same time or alternately to prevent dormant failure.
When the manual or continuous ignition selection is used, the EEC energizes both igniters based on the logic and aircraft inputs of the flap position, cowl anti-ice status and/or continuous ignition commands.
The EEC includes an automatic ignition system as an integral part of the EEC's ignition function.
The EEC includes an automatic relight system which energizes both igniters within two seconds of when an engine flame-out has been detected.
The ignition system consist of:
- Ignition Power Supply (Ref. AMM D/O 74-11-00-00)
- Low Tension Distribution System (Ref. AMM D/O 74-21-00-00)
- Ignition Starting and Continuous Relight (Ref. AMM D/O 74-31-00-00).