DOC AIRBUS | TSM A320FIgnition Mode Selection is A and B (instead of A or B)
1. Possible Causes
· RELAY BOX ( 4100KS )
· EEC ( 4000KS )
· EIU-2 ( 1KS2 )
· SEL SW-ENG/MODE/CRANK/AUTO IGN/IGN ( 6KS )
· LGCIU-2 ( 5GA2 )
· NOZZLE-FUEL ( 2005EM )
· PLUG-IGNITER, A ( 4001JH1 )
· PLUG-IGNITER, B ( 4001JH2 )
· LEAD-IGNITION, A ( 4002JH1 )
· LEAD-IGNITION, B ( 4002JH2 )
· EXCITER-IGNITION, A ( 4000JH1 )
· EXCITER-IGNITION, B ( 4000JH2 )
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 32-31-71-000-001 Removal of the LGCIU
Ref. AMM 32-31-71-400-001 Installation of the LGCIU
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 73-22-34-000-010 Removal of the Electronic Engine Control (EEC)
Ref. AMM 73-22-34-400-010 Installation of the Electronic Engine Control (EEC)
Ref. AMM 73-25-34-000-041 Removal of the Engine Interface Unit (EIU)
Ref. AMM 73-25-34-400-041 Installation of the Engine Interface Unit (EIU)
Ref. AMM 74-00-00-710-041 Operational Test of the Ignition System with the CFDS
Ref. AMM 74-11-38-000-010 Removal of the Ignition Exciter
REFERENCE DESIGNATION
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 74-00-00-710-094-A
A. Test
Not applicable
4. Fault Isolation
Subtask 74-00-00-810-073-A
A. If the fault symptom is identified by these two crew observations:
. ENG 2 Starting - Memo message "IGNITION" is shown
. ENG 2 - Ignition mode selection is A and B instead of A or B.
· do the operational test of the ignition systems with the CFDS (FADEC 2A and 2B) Ref.
AMM 74-00-00-710-041 .
NOTE: 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.
(1) If the tests are correct:
· replace the RELAY BOX ( 4100KS ) Ref. AMM 71-51-49-000-010 and Ref.
AMM 71-51-49-400-010 .
(a) If the fault continues:
· replace the EEC ( 4000KS ) Ref. AMM 73-22-34-000-010 and Ref. AMM 73-22-34-400-010 .
(b) If the fault continues:
· replace the EIU-2 ( 1KS2 ) Ref. AMM 73-25-34-000-041 and Ref. AMM 73-25-34-400-041 .
(c) If the fault continues:
· replace the SEL SW-ENG/MODE/CRANK/AUTO IGN/IGN ( 6KS )
(d) If the fault continues:
· Replace the LGCIU-2 ( 5GA2 ) Ref. AMM 32-31-71-000-001 and Ref.
AMM 32-31-71-400-001 .
(e) If the fault continues:
· replace the:
. NOZZLE-FUEL ( 2005EM ) adjacent to the igniter plug A (4001JH1)
. NOZZLE-FUEL ( 2005EM ) adjacent to the igniter plug B (4001JH2)
Ref. AMM 73-13-41-000-010 and Ref. AMM 73-13-41-400-010 .
(f) If the fault continues:
· replace the PLUG-IGNITER, A ( 4001JH1 ) and the PLUG-IGNITER, B ( 4001JH2 ) Ref.
AMM 74-21-41-000-010 and Ref. AMM 74-21-41-400-010 .
(g) If the fault continues:
· replace the LEAD-IGNITION, A ( 4002JH1 ) and the LEAD-IGNITION, B ( 4002JH2 ) Ref.
AMM 74-21-43-000-010 and Ref. AMM 74-21-43-400-010 .
(h) If the fault continues:
· replace the EXCITER-IGNITION, A ( 4000JH1 ) and the EXCITER-IGNITION, B ( 4000JH2 )
Ref. AMM 74-11-38-000-010 and Ref. AMM 74-11-38-400-010 .
(2) If the tests are not correct:
· replace the RELAY BOX ( 4100KS ) Ref. AMM 71-51-49-000-010 and Ref.
AMM 71-51-49-400-010 .
(a) If the fault continues:
· replace the EEC ( 4000KS ) Ref. AMM 73-22-34-000-010 and Ref. AMM 73-22-34-400-010 .
(b) If the fault continues:
· replace the EIU-2 ( 1KS2 ) Ref. AMM 73-25-34-000-041 and Ref. AMM 73-25-34-400-041 .
(c) If the fault continues:
· replace the SEL SW-ENG/MODE/CRANK/AUTO IGN/IGN ( 6KS )
(d) If the fault continues:
· replace the PLUG-IGNITER, A ( 4001JH1 ) and the PLUG-IGNITER, B ( 4001JH2 ) Ref.
AMM 74-21-41-000-010 and Ref. AMM 74-21-41-400-010 .
(e) If the fault continues:
· replace the LEAD-IGNITION, A ( 4002JH1 ) and the LEAD-IGNITION, B ( 4002JH2 ) Ref.
AMM 74-21-43-000-010 and Ref. AMM 74-21-43-400-010 .
(f) If the fault continues:
· replace the EXCITER-IGNITION, A ( 4000JH1 ) and the EXCITER-IGNITION, B ( 4000JH2 )
Ref. AMM 74-11-38-000-010 and Ref. AMM 74-11-38-400-010 .
Subtask 74-00-00-710-095-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.
(8) Fully decrease the brightness of the MCDU screen (display off).
5. Close-up
Subtask 74-00-00-860-074-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 PWR 2 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