W DOC AIRBUS | TSM A320F

Failure of the Engine Dedicated Alternator (EDA) Stator on Engine 1


1. Possible Causes
· PMA-EEC ( 4005EV )
· wiring from the EEC (4000KS) to the engine dedicated alternator stator (4005EV)
· EEC ( 4000KS )
· Engine Dedicated Alternator (EDA) Drive Gear Assembly Retention Nut
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 70-23-15-912-010 Connection of Electrical Connectors
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 71-13-00-410-010 Closing of the Fan Cowls 437AL(447AL),438AR(448AR)
Ref. AMM 71-50-00-210-010 Wire Harness Visual Inspection - All Power Plant Electrical Cables
Ref. AMM 72-60-33-200-011 Inspection of the Dedicated Alternator Drive Gear Assembly Retention
Nut
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 73-22-38-000-010 Removal of the Engine Dedicated Alternator (EDA) Stator and/or Cooling
Shroud
Ref. AMM 73-22-38-400-010 Installation of the Engine Dedicated Alternator (EDA) Stator and/or
Cooling Shroud
Ref. ASM 73-25-14
Engine Dedicated Alternator Stator SHEET 1
Figure 73(IAE)-22-00-991-00300-A / SHEET 1/1 - Engine Dedicated Alternator Stator not printed, as
per printing preferences
3. Fault Confirmation
Subtask 73-22-00-860-076-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 73-22-00-710-102-A
B. 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
(Ref. Fig. Engine Dedicated Alternator Stator SHEET 1)
Subtask 73-22-00-810-078-B
A. If the test gives the maintenance message ENG DED ALTERN/HC/EEC 1:
· examine the harness Ref. AMM 71-50-00-210-010 from the EEC (4000KS) to the engine dedicated
alternator stator (4005EV) Ref. ASM 73-25-14.
(1) If the fault continues:
· disconnect the connectors from the engine dedicated alternator stator
· examine the connectors and receptacles Ref. AMM 71-50-00-210-010
· connect the connectors to the engine dedicated alternator stator Ref. AMM 70-23-15-912-010 .
(2) If the fault continues:
· replace the PMA-EEC ( 4005EV ) Ref. AMM 73-22-38-000-010 and Ref.
AMM 73-22-38-400-010 .
(3) If the fault continues:
· read the fault code shown on the FLIGHT DATA and GROUND DATA of the FADEC (1A and 1B)
menu on the MCDU (Ref. 70-00-00 Page Block 301 Task Supporting Data)
· make a record of the fault code.
(a) If the FADEC 1A menu gives the fault code ALTCRF:
· do a check and repair the wiring from the EEC (4000KS) to the engine dedicated alternator
stator (4005EV)
. pins J5/W, j, A, X, B, Y to pins A/4, 5, 6, 7, 8, 9
. pins J2/M, e to pins A/10, 11 Ref. ASM 73-25-14.
(b) If the FADEC 1B menu gives the fault code ALTCRF:
· do a check and repair the:
. wiring from the EEC (4000KS) to the engine dedicated alternator stator
(4005EV) pins J11/W, j, A, X, B, Y to pins B/5, 4, 6, 7, 8, 9
. wiring at the EEC connector (4000KS-J11) between pins V and U Ref.
ASM 73-25-14.
(c) If the FADEC 1A and FADEC 1B menus give no fault code and the fault continues:
· replace the EEC ( 4000KS ) Ref. AMM 73-22-34-000-010 and Ref. AMM 73-22-34-400-010 .
(4) If the fault continues:
· inspect the Engine Dedicated Alternator (EDA) Drive Gear Assembly Retention Nut Ref.
AMM 72-60-33-200-011 .
Subtask 73-22-00-710-103-A
B. Do the test given in Para. 3.
5. Close-up
Subtask 73-22-00-860-077-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 04:36:17 UTC
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