DOC AIRBUS | TSM A320FLoss of the EIU2 Data to the EEC2
1. Possible Causes
· wiring
· EIU-2 ( 1KS2 )
· 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 73-22-34-000-010 Removal of the Electronic Engine Control (EEC)
Ref. AMM 73-22-34-400-010 Installation of the Electronic Engine Control (EEC)
Ref. ASM 73-25-05
Ref. ASM 73-25-06
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)
Engine Interface Unit SHEET 1
Figure 73(IAE)-25-00-991-00200-A / SHEET 1/1 - Engine Interface Unit not printed, as per printing
preferences
3. Fault Confirmation
Subtask 73-25-00-860-056-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/2 pushbutton switch.
Subtask 73-25-00-710-278-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).
4. Fault Isolation
(Ref. Fig. Engine Interface Unit SHEET 1)
Subtask 73-25-00-810-167-A
A. If the test does not give the maintenance message EIU/HC/EEC2, no further maintenance action is
necessary or if the test gives another maintenance message do the trouble shooting procedure related to
the maintenance message.
NOTE: Before you do the troubleshooting procedure of the EIU 2, make sure that, on the Post Flight Report
(PFR), no ATA 24 fault occurred at the same time as the EIU fault. This is because a power
supply interruption (ATA 24) can cause an EIU fault.
If the test gives the maintenance message EIU/HC/EEC2:
(1) Open the fan cowls 447AL and 448AL Ref. AMM 71-13-00-010-010
(2) Do a check of the wiring from the circuit breaker 4KS2 to the EIU2 (1KS2) pin AC/9 Ref. ASM
73-25-05
(a) Repair the wiring if necessary
(3) Do a check of the wiring from the circuit breaker 2KS2 to the EIU2(1KS2) pin AC/11 Ref. ASM
73-25-05
(a) Repair the wiring if necessary
(4) Do a check of the wiring from the EEC(4000KS) pins J1/P,N and J7/P,N to the EIU2(1KS2) pins
AB/5A,5C Ref. ASM 73-25-06
(a) If there is no continuity:
· Repair the above wiring
(b) If there is continuity:
1 Remove the EIU2(1KS2) Ref. AMM 73-25-34-000-041
2 Do a visual inspection of connectors at 85VU side
· Repair connector if necessary
3 If no damage found, replace the EIU-2 ( 1KS2 ) Ref. AMM 73-25-34-000-041 and Ref.
AMM 73-25-34-400-041
(5) If the faults continues:
(a) Replace the EEC ( 4000KS ) Ref. AMM 73-22-34-000-010 and Ref. AMM 73-22-34-400-010
Subtask 73-25-00-710-279-A
B. Do the test given in Para. 3.
5. Close-up
Subtask 73-25-00-860-057-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 .
(4) Make sure that the fan cowls 447AL and 448AR are closed Ref. AMM 71-13-00-410-010 . [Rev.6 from Feb 2017] 2026.04.04 04:36:24 UTC