DOC AIRBUS | TSM A320FFailure of the Group 1 Solenoids on Engine 1
1. Possible Causes
· wiring
· EEC ( 4000KS )
2 Job Set-up Information
A. Referenced Information
REFERENCE DESIGNATION
Ref. AMM 24-41-00-861-002 Energize the Aircraft Electrical Circuits from the External Power
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 71-13-00-010-010 Opening of the Fan Cowls 437AL(447AL),438AR(448AR)
Ref. AMM 71-13-00-410-010 Closing of the Fan Cowls 437AL(447AL),438AR(448AR)
Ref. AMM 73-22-00-710-040 Operational Test of the FADEC SYSTEM on the Ground
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. ASM 73-25-18
3. Fault Confirmation
Subtask 73-00-00-860-110-A
A. Job Set-up
(1) Energize the aircraft electrical circuits
Ref. AMM 24-41-00-861-002 .
(2) On the panel 50VU, release the ENG/FADEC GND PWR/1 pushbutton switch.
Subtask 73-00-00-710-322-A
B. FADEC Ground Test
(1) Do the CFDS Message Decoding and read the Scheduled Maintenance Report (Ref. 70-00-00 Page
Block 301 Task Supporting Data).
(2) If the readout gives one of the following fault codes in FADEC 1A or FADEC 1B (Fault Acronym:
EG1LF):
· do the FADEC Ground Test Ref. AMM 73-22-00-710-040 for fault confirmation.
· continue with Fault Isolation Para 4.
(3) If the fault code readout in (1) does not give one of the above listed fault codes:
· continue with fault confirmation by Engine Ground Run Section 4.B below.
Subtask 73-00-00-710-120-A
C. Test
(1) On the panel 50VU, push the ENG FADEC GND PWR 1 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 1 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 .
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 1 by the discontinued start, restart and shutdown procedure Ref.
AMM 71-00-00-710-018 .
(7) Read the LAST LEG REPORT of the FADEC (1A and 1B) 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 1A or FADEC 1B which found the fault.
(8) Fully decrease the brightness of the MCDU screen (display off).
4. Fault Isolation
Subtask 73-00-00-810-086-A
A. If the test gives the maintenance message ENG GROUP1 SOL/EEC1:
· open the fan cowls 437AL and 438AR Ref. AMM 71-13-00-010-010
· do a check of the engine group 1 solenoids for shorts across their windings, shorts to ground and for
open circuits caused by short circuits.
(1) If the channel which found the fault (during the test) was FADEC 1A and the fault continues:
· do a check and repair the wiring :
. at the HPC stage 7 solenoid-valve connector (4020KS3-A) between pins 3 and 4
. at the HPC stage 7 solenoid-valve connector (4020KS1-A) between pins 3 and 4
Ref. ASM 73-25-18.
(2) If the channel which found the fault (during the test) was FADEC 1B and the fault continues:
· do a check and repair the wiring :
. at the HPC stage 7 solenoid-valve connector (4020KS3-A) between pins 6 and 7
. at the HPC stage 7 solenoid-valve connector (4020KS1-A) between pins 6 and 7
Ref. ASM 73-25-18.
(3) If the fault continues:
· replace the EEC ( 4000KS ) Ref. AMM 73-22-34-000-010 and Ref. AMM 73-22-34-400-010 .
Subtask 73-00-00-710-121-A
B. Repeat the fault confirmation as given in Para. 3 using the same method (FADEC Ground Test or Engine
Ground Run) as before and confirm fault elimination.
5. Close-up
Subtask 73-00-00-860-111-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/1 pushbutton switch.
(3) De-energize the aircraft electrical circuits
Ref. AMM 24-41-00-862-002 .
(4) Make sure that the fan cowls 437AL and 438AR are closed Ref. AMM 71-13-00-410-010 . [Rev.6 from Feb 2017] 2026.04.04 04:36:06 UTC