DOC AIRBUS | TSM A320FAPU Boost Output Fault on EIU-1
TASK 73-25-00-810-A83-A
APU Boost Output Fault on EIU-1
1. Possible Causes
2. Job Set-up Information
A. Referenced Information
3. Fault Confirmation
Subtask 73-25-00-710-522-A ** ON A/C NOT FOR ALL
Subtask 73-25-00-810-384-A ** ON A/C NOT FOR ALL
Subtask 73-25-00-860-144-A ** ON A/C NOT FOR ALL
[Rev.8 from Aug 2018]
2026.04.04 04:36:46 UTC
APU Boost Output Fault on EIU-1
1. Possible Causes
2. Job Set-up Information
A. Referenced Information
| REFERENCE | DESIGNATION |
|---|---|
| AWM 496103 | |
| AMM 49-61-34-000-001 | Removal of the Electronic Control Box (ECB) (GTCP 36-300) |
| AMM 49-61-34-000-002 | Removal of the Electronic Control Box (ECB) (APS 3200) |
| AMM 49-61-34-000-003 | Removal of the Electronic Control Box (ECB) (131-9(A)) |
| AMM 49-61-34-400-001 | Installation of the Electronic Control Box (ECB) (GTCP 36-300) |
| AMM 49-61-34-400-002 | Installation of the Electronic Control Box (ECB) (APS 3200) |
| AMM 49-61-34-400-003 | Installation of the Electronic Control Box (ECB) (131-9(A)) |
| AWM 732505 | |
| AMM 73-25-34-000-802 | Removal of the Engine Interface Unit (EIU) |
| AMM 73-25-34-400-802 | Installation of the Engine Interface Unit (EIU) |
| AMM 73-25-34-710-802 | Operational Test of the Engine Interface Unit (EIU) with the Centralized Fault Display System (CFDS) |
| AMM 73-25-34-860-803 | Engine Interface Unit (EIU) DISCRETE OUTPUTS Simulation |
Subtask 73-25-00-710-522-A ** ON A/C NOT FOR ALL
A. Do the operational test of the Engine Interface Unit (EIU) with the Centralized Fault Display System (CFDS) to confirm this fault AMM 73-25-34-710-802.
4. Fault IsolationSubtask 73-25-00-810-384-A ** ON A/C NOT FOR ALL
A. If there is confirmation of the fault:
(1) Remove the Electronic Control Box (ECB) (59KD) (Refer to AMM task indicated in step (5)).
(2) On the MCDU, simulate the Discrete Output (DSO) 2:
(a) Push the adjacent button to DSO 2 to have the status equal to 1 AMM 73-25-34-860-803.
(b) At ECB tray connector (AB), do a check for 28 VDC at contact 5E AWM 496103.
1 Stop the simulation of DSO 2 AMM 73-25-34-860-803.
(3) If there is no 28VDC, do a check of wiring between contact 5E and contact 1C at EIU-1 (1KS1) AWM 496103 and AWM 732505 for:
(a) Continuity (less than 5 ohms resistance)
(b) Short to ground.
1 If you find damage, repair or replace aircraft wiring AWM 496103 and AWM 732505.
2 If you find no damage, go to step (4)(e).
(4) On the MCDU, simulate the DSO 3:
(a) Push the adjacent button to DSO 3 to have the status equal to 1 AMM 73-25-34-860-803.
(b) At ECB tray connector (AB), do a check for 28 VDC at pin 12K of connector AB AWM 496103.
1 Stop the simulation of DSO 3 AMM 73-25-34-860-803.
(c) If there is no 28VDC, do a check of wiring between contact 12K and contact 2C at EIU-1 (1KS1) AWM 496103 and AWM 732505 for:
1 Continuity
2 Short to ground.
(d) If you find damage, repair or replace aircraft wiring AWM 496103 and AWM 732505.
(e) If you find no damage:
1 Replace EIU-1 [1KS1] AMM 73-25-34-000-802 and AMM 73-25-34-400-802.
(f) Install the ECB (59KD). Refer to AMM task indicated in step (5).
(g) Do the test given in Para. 3.
(5) If there is 28 VDC at contacts 5E and 12K or if the fault continues:
(a) Replace
1 If ECB (GTCP 36-300) is installed AMM 49-61-34-000-001 and AMM 49-61-34-400-001.
2 If ECB (APS 3200) is installed AMM 49-61-34-000-002 and AMM 49-61-34-400-002.
3 If ECB (131-9(A)) is installed AMM 49-61-34-000-003 and AMM 49-61-34-400-003.
(b) Do the test given in Para. 3.
(6) If the fault continues:
(a) Replace EIU-1 [1KS1] AMM 73-25-34-000-802 and AMM 73-25-34-400-802.
(b) Do the test given in Para. 3.
5. Close-up(1) Remove the Electronic Control Box (ECB) (59KD) (Refer to AMM task indicated in step (5)).
(2) On the MCDU, simulate the Discrete Output (DSO) 2:
(a) Push the adjacent button to DSO 2 to have the status equal to 1 AMM 73-25-34-860-803.
(b) At ECB tray connector (AB), do a check for 28 VDC at contact 5E AWM 496103.
1 Stop the simulation of DSO 2 AMM 73-25-34-860-803.
(3) If there is no 28VDC, do a check of wiring between contact 5E and contact 1C at EIU-1 (1KS1) AWM 496103 and AWM 732505 for:
(a) Continuity (less than 5 ohms resistance)
(b) Short to ground.
1 If you find damage, repair or replace aircraft wiring AWM 496103 and AWM 732505.
2 If you find no damage, go to step (4)(e).
(4) On the MCDU, simulate the DSO 3:
(a) Push the adjacent button to DSO 3 to have the status equal to 1 AMM 73-25-34-860-803.
(b) At ECB tray connector (AB), do a check for 28 VDC at pin 12K of connector AB AWM 496103.
1 Stop the simulation of DSO 3 AMM 73-25-34-860-803.
(c) If there is no 28VDC, do a check of wiring between contact 12K and contact 2C at EIU-1 (1KS1) AWM 496103 and AWM 732505 for:
1 Continuity
2 Short to ground.
(d) If you find damage, repair or replace aircraft wiring AWM 496103 and AWM 732505.
(e) If you find no damage:
1 Replace EIU-1 [1KS1] AMM 73-25-34-000-802 and AMM 73-25-34-400-802.
(f) Install the ECB (59KD). Refer to AMM task indicated in step (5).
(g) Do the test given in Para. 3.
(5) If there is 28 VDC at contacts 5E and 12K or if the fault continues:
(a) Replace
1 If ECB (GTCP 36-300) is installed AMM 49-61-34-000-001 and AMM 49-61-34-400-001.
2 If ECB (APS 3200) is installed AMM 49-61-34-000-002 and AMM 49-61-34-400-002.
3 If ECB (131-9(A)) is installed AMM 49-61-34-000-003 and AMM 49-61-34-400-003.
(b) Do the test given in Para. 3.
(6) If the fault continues:
(a) Replace EIU-1 [1KS1] AMM 73-25-34-000-802 and AMM 73-25-34-400-802.
(b) Do the test given in Para. 3.
Subtask 73-25-00-860-144-A ** ON A/C NOT FOR ALL
A. Put the aircraft back to its initial configuration.
(1) Make sure that the work area is clean and clear of tools and other items.
(1) Make sure that the work area is clean and clear of tools and other items.