DOC AIRBUS | TSM A320FFailure of the Ignition System B on Engine 2
1. Possible Causes
· PLUG-IGNITER, B ( 4001JH2 )
· LEAD-IGNITION, B ( 4002JH2 )
· EXCITER-IGNITION, B ( 4000JH2 )
· RELAY BOX ( 4100KS )
· NOZZLE-FUEL ( 2005EM )
2 Job Set-up Information
A. Referenced Information
REFERENCE DESIGNATION
Ref. AMM 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied from the External
Power
Ref. AMM 31-60-00-860-002 EIS Stop Procedure
Ref. AMM 71-00-00-710-018 Discontinued Start, Restart and Shutdown Procedures
Ref. AMM 71-00-00-710-043 Normal Engine Automatic Start Procedure
Ref. AMM 71-00-00-710-047 Normal Engine Manual Start Procedure
Ref. AMM 71-51-49-000-010 Removal of the Relay Box
Ref. AMM 71-51-49-400-010 Installation of the Relay Box
Ref. AMM 73-13-41-000-010 Removal of the Fuel Nozzle
Ref. AMM 73-13-41-400-010 Installation of the Fuel Nozzle
Ref. AMM 74-11-38-000-010 Removal of the Ignition Exciter
Ref. AMM 74-11-38-400-010 Installation of the Ignition Exciter
Ref. AMM 74-21-41-000-010 Removal of the Igniter Plug
Ref. AMM 74-21-41-400-010 Installation of the Igniter Plug
Ref. AMM 74-21-43-000-010 Removal of the Ignition Leads
Ref. AMM 74-21-43-400-010 Installation of the Ignition Leads
3. Fault Confirmation
Subtask 74-00-00-710-076-A
A. Test
(1) Not applicable, the engine does not start.
4. Fault Isolation
Subtask 74-00-00-810-063-A
A. If the fault symptom is identified by the maintenance message IGN2/115VAC/EEC2:
· remove the ignition lead from the igniter plug and examine the connector for arcing and burning.
(1) If you find arcing or burning, do the steps below:
(a) Replace the PLUG-IGNITER, B ( 4001JH2 ) Ref. AMM 74-21-41-000-010 and Ref.
AMM 74-21-41-400-010 .
(b) If the fault continues:
· replace the LEAD-IGNITION, B ( 4002JH2 ) Ref. AMM 74-21-43-000-010 and Ref.
AMM 74-21-43-400-010 .
(c) If the fault continues:
· replace the EXCITER-IGNITION, B ( 4000JH2 ) Ref. AMM 74-11-38-000-010 and Ref.
AMM 74-11-38-400-010 .
(d) If the fault continues:
· replace the RELAY BOX ( 4100KS ) Ref. AMM 71-51-49-000-010 and Ref.
AMM 71-51-49-400-010 .
(e) If the fault continues:
· replace the NOZZLE-FUEL ( 2005EM ) adjacent to the igniter plug (4001JH2) Ref.
AMM 73-13-41-000-010 and Ref. AMM 73-13-41-400-010 .
(2) If you find no arcing or burning, do the steps below:
(a) Replace the LEAD-IGNITION, B (4002JH2) Ref. AMM 74-21-43-000-010 and Ref.
AMM 74-21-43-400-010 .
(b) If the fault continues:
· replace the PLUG-IGNITER, B (4001JH2) Ref. AMM 74-21-41-000-010 and Ref.
AMM 74-21-41-400-010 .
(c) If the fault continues:
· replace the EXCITER-IGNITION, B ( 4000JH2 ) Ref. AMM 74-11-38-000-010 and Ref.
AMM 74-11-38-400-010 .
(d) If the fault continues:
· replace the RELAY BOX ( 4100KS ) Ref. AMM 71-51-49-000-010 and Ref.
AMM 71-51-49-400-010 .
(e) If the fault continues:
· replace the NOZZLE-FUEL ( 2005EM ) adjacent to the igniter plug (4001JH2) Ref.
AMM 73-13-41-000-010 and Ref. AMM 73-13-41-400-010 .
Subtask 74-00-00-710-077-A
B. Test
(1) On the panel 50VU, push the ENG FADEC GND PWR 2 pushbutton switch and release it again.
NOTE: This action resets the FADEC memory.
(2) Adjust the brightness of the MCDU screen.
(3) Push the INIT mode key. The INIT page comes into view.
(4) Enter a new flight number.
(5) Start the engine 2 by the normal engine automatic start procedure Ref. AMM 71-00-00-710-043 or
the normal engine manual start procedure Ref. AMM 71-00-00-710-047 and let it become stable for 5
minutes.
NOTE: Operation of the engine for at least 3 minutes erases the LAST LEG REPORT related to the
last flight and the new fault is recorded in the EEC LAST LEG REPORT.
(6) Do a shutdown of the engine 2 by the discontinued start, restart and shutdown procedure Ref.
AMM 71-00-00-710-018 .
(7) Read the LAST LEG REPORT of the FADEC (2A and 2B) menu on the MCDU (Ref. 70-00-00 Page
Block 301 Task Supporting Data).
(a) Make a record of the maintenance message.
(b) Make a record of the channel FADEC 2A or FADEC 2B which found the fault.
· Test
(8) Do again steps (3) to (7) to confirm fault cleared in both channels.
NOTE: The ignition system alternates between Channel A and Channel B at each start. A fault in one
channel would not show on the next start because the other channel would be used. Therefore,
two starts are required to make sure any faults are cleared from both channels.
(9) Fully decrease the brightness of the MCDU screen (display off).
5. Close-up
Subtask 74-00-00-860-062-A
A. Put the aircraft back to its initial configuration.
(1) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.
Ref. AMM 31-60-00-860-002 .
(2) On the panel 50VU, push the ENG/FADEC GND PWR2 pushbutton switch.
(3) De-energize the aircraft electrical circuits
Ref. AMM 24-41-00-862-002 . [Rev.6 from Feb 2017] 2026.04.04 04:36:59 UTC