DOC AIRBUS | TSM A320FEEC/ICV Wraparound Failure on Channel A
TASK 73-25-00-810-A38-A
EEC/ICV Wraparound Failure on Channel A
1. Possible Causes
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Referenced Information
3. Fault Confirmation
Subtask 73-25-00-710-475-A ** ON A/C NOT FOR ALL
Subtask 73-25-00-860-082-A ** ON A/C NOT FOR ALL
[Rev.8 from Aug 2018]
2026.04.04 04:36:28 UTC
EEC/ICV Wraparound Failure on Channel A
1. Possible Causes
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | 1 | MULTIMETER - STANDARD |
| No specific | 1 | PLIERS - JAWED, SOFT |
| REFERENCE | DESIGNATION |
|---|---|
| TSM TASK 71-00-00-810-834-A | General Troubleshooting Guidelines for Additional Troubleshooting Information |
| TSM TASK 71-00-00-810-835-A | Component and Harness Intermittent Troubleshooting Procedure for Guidance Troubleshooting Intermittent Faults |
| AMM 54-52-11-000-805 | Removal of the Access Skin Panels |
| AMM 71-13-00-010-802 | Opening of the Fan Cowl Doors |
| AMM 71-13-00-410-802 | Closing of the Fan Cowl Doors |
| AWM 715135 | |
| AMM 73-21-01-000-801 | Removal of the Electronic Engine Control (EEC) |
| AMM 73-21-01-400-801 | Installation of the Electronic Engine Control (EEC) |
| AMM 73-21-62-000-802 | Removal of the EEC Wiring Harness (WF02) |
| AMM 73-21-62-400-802 | Installation of the EEC Wiring Harness (WF02) |
| AMM 78-31-00-710-805 | Operational Test of Thrust Reverser with MCDU |
| AMM 78-31-01-000-801 | Removal of the TRAS Hydraulic Control Unit (HCU) |
| AMM 78-31-01-400-801 | Installation of the TRAS Hydraulic Control Unit (HCU) |
| AWM 783604 | |
| AWM 783605 |
Subtask 73-25-00-710-475-A ** ON A/C NOT FOR ALL
A. Do the operational test of thrust reverser to confirm this fault AMM 78-31-00-710-805.
(a) If no problems are found, return the engine to service. Monitor the engine for reoccurring maintenance message.
(2) If the maintenance message comes back (hard fault), go to the Para. Fault Isolation.
4. Fault IsolationNOTE: The Electronic Engine Control (EEC) has detected a EEC/ICV wraparound failure for channel A when ICV power supply is commanded.
(1) If the maintenance message does not come back, examine the harness and electrical connectors as described in the component and harness intermittent fault isolation procedure (Ref. TSM TASK 71-00-00-810-835). - Refer to the general troubleshooting guidelines for additional troubleshooting information (Ref. TSM TASK 71-00-00-810-834).
- Refer to the component and harness intermittent troubleshooting procedure for guidance troubleshooting intermittent faults (Ref. TSM TASK 71-00-00-810-835).
(a) If no problems are found, return the engine to service. Monitor the engine for reoccurring maintenance message.
(2) If the maintenance message comes back (hard fault), go to the Para. Fault Isolation.
WARNING:
BE CAREFUL WHEN YOU DO WORK ON THE ENGINE AFTER SHUTDOWN. THE ENGINE CAN STAY HOT FOR A LONG TIME. IF YOU DO NOT OBEY THIS WARNING, INJURY CAN OCCUR.
WARNING:
REFER TO THE MSDS FOR ALL MATERIAL USED AND THE MANUFACTURER'S SAFETY INSTRUCTIONS FOR ALL EQUIPMENT USED. IF YOU DO NOT OBEY THIS WARNING, INJURY CAN OCCUR.
CAUTION:
MAKE SURE YOU REMOVE ELECTRICAL POWER FROM THE EEC BEFORE YOU REMOVE THE ELECTRICAL CONNECTORS. IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE EEC CAN OCCUR.
Subtask 73-25-00-810-315-A ** ON A/C NOT FOR ALL A. If there is confirmation of the fault:
(1) Open the fan cowl doors AMM 71-13-00-010-802.
(2) Examine the WF02 (4218KS) harness, connector P1 (4000KS-P1) - EEC (4000KS) and connector P402 (402VC-A) - pylon junction box, for problems which are possible between the EEC (4000KS) and the pylon junction box.
(a) Inspect for harness damage.
(b) Inspect for loose or damaged connectors.
1 Replace HARNESS-FAN, WF02 [4218KS] AMM 73-21-62-000-802 and AMM 73-21-62-400-802.
(3) If no problems are found with the harness, use a PLIERS - JAWED, SOFT to disconnect the electrical connector P1 (4000KS-P1) from the EEC (4000KS) and connector P402 (402VC-A) from the pylon junction box.
(a) Examine the pins and sockets (contacts) for alignment and damage. Look for contacts pushed rearward into the connector face. Replace parts as necessary.
(b) Reconnect the electrical connector P1 (4000KS-P1) to the EEC (4000KS) and connector P402 (402VC-A) to the pylon junction box.
(4) Remove the access panel on the pylon to get access to the HCU (4310EG) AMM 54-52-11-000-805.
(5) Check for correct engagement of connector (4310EG-A) AMM 78-31-01-400-801.
(a) Correct as necessary.
(b) If any damage corrected, connect all connectors disconnected.
(c) Do the test given in Para. 3.
(6) If no damage found or the fault continue, disconnect connector (4310EG-A).
(a) Inspect for loose or damaged connector.
(b) Examine the pins and sockets (contacts) for alignment and damage. Look for contacts pushed rearward into the connector face. Replace parts as necessary.
(c) If any damage corrected, connect all connectors disconnected.
(d) Do the test given in Para. 3.
(7) If no damage found or if fault continues, check resistance between pins 2 and 3 of HCU (4310EG).
(a) If resistance is not between 76 to 87 ohms at room temperature or higher than 102 ohms at hot day:
1 Replace HCU-T/R, ENG1 [4310EG1] or HCU-T/R, ENG2 [4310EG2] AMM 78-31-01-000-801 and AMM 78-31-01-400-801.
2 Do the test given in Para. 3.
(b) If the resistance is correct, continues to troubleshoot.
(8) If the fault continues:
(a) Disconnect the electrical connector P1 (4000KS-P1) from the EEC (4000KS) and connector P402 (402VC-A) from the pylon junction box. Use a MULTIMETER - STANDARD to test the aircraft 28 VDC circuit in the harness. Refer to Table 1 and AWM 715135 P0001. Look for:
1 Continuity (less than 5 ohms resistance)
2 Wire-to-wire short
3 Short to ground.
Table 1: Aircraft 28 VDC Channel A Connector Contacts
(b) If a problem is found with the harness or connectors:
1 Replace HARNESS-FAN, WF02 [4218KS] AMM 73-21-62-000-802 and AMM 73-21-62-400-802.
2 Do the test given in Para. 3.
(9) If no problems with the harness are found or the fault continues:
(a) Check the aircraft wiring for AWM 715135 P0001 and AWM 783605 for ENG 1 fault and AWM 783604 for ENG 2 fault. Look for:
1 Continuity (less than 5 ohms resistance)
2 Wire-to-wire short
3 Short to ground.
(b) Repair or replace the aircraft wiring if necessary.
1 Connect all connectors disconnected.
2 Do the test given in Para. 3.
(10) If the fault continues:
(a) Replace
(b) Do the test given in Para. 3.
5. Close-up(1) Open the fan cowl doors AMM 71-13-00-010-802.
(2) Examine the WF02 (4218KS) harness, connector P1 (4000KS-P1) - EEC (4000KS) and connector P402 (402VC-A) - pylon junction box, for problems which are possible between the EEC (4000KS) and the pylon junction box.
(a) Inspect for harness damage.
(b) Inspect for loose or damaged connectors.
NOTE: Loose connectors must be disconnected and examined for further wear or damage.
(c) If a problem is found with the harness or connectors: 1 Replace HARNESS-FAN, WF02 [4218KS] AMM 73-21-62-000-802 and AMM 73-21-62-400-802.
(3) If no problems are found with the harness, use a PLIERS - JAWED, SOFT to disconnect the electrical connector P1 (4000KS-P1) from the EEC (4000KS) and connector P402 (402VC-A) from the pylon junction box.
(a) Examine the pins and sockets (contacts) for alignment and damage. Look for contacts pushed rearward into the connector face. Replace parts as necessary.
(b) Reconnect the electrical connector P1 (4000KS-P1) to the EEC (4000KS) and connector P402 (402VC-A) to the pylon junction box.
(4) Remove the access panel on the pylon to get access to the HCU (4310EG) AMM 54-52-11-000-805.
(5) Check for correct engagement of connector (4310EG-A) AMM 78-31-01-400-801.
(a) Correct as necessary.
(b) If any damage corrected, connect all connectors disconnected.
(c) Do the test given in Para. 3.
(6) If no damage found or the fault continue, disconnect connector (4310EG-A).
(a) Inspect for loose or damaged connector.
(b) Examine the pins and sockets (contacts) for alignment and damage. Look for contacts pushed rearward into the connector face. Replace parts as necessary.
(c) If any damage corrected, connect all connectors disconnected.
(d) Do the test given in Para. 3.
(7) If no damage found or if fault continues, check resistance between pins 2 and 3 of HCU (4310EG).
(a) If resistance is not between 76 to 87 ohms at room temperature or higher than 102 ohms at hot day:
1 Replace HCU-T/R, ENG1 [4310EG1] or HCU-T/R, ENG2 [4310EG2] AMM 78-31-01-000-801 and AMM 78-31-01-400-801.
2 Do the test given in Para. 3.
(b) If the resistance is correct, continues to troubleshoot.
(8) If the fault continues:
(a) Disconnect the electrical connector P1 (4000KS-P1) from the EEC (4000KS) and connector P402 (402VC-A) from the pylon junction box. Use a MULTIMETER - STANDARD to test the aircraft 28 VDC circuit in the harness. Refer to Table 1 and AWM 715135 P0001. Look for:
1 Continuity (less than 5 ohms resistance)
2 Wire-to-wire short
3 Short to ground.
NOTE: A short to ground is found when the resistance is less than 100 000 (100K) ohms.
Table 1: Aircraft 28 VDC Channel A Connector Contacts
| WF02 (4218KS) Harness P1(4000KS-P1) EEC (4000KS) Connector Contacts | WF02 (4218KS) Harness P402(402VC-A) Connector Contacts |
|---|---|
| D | 15 |
| e | 29 |
1 Replace HARNESS-FAN, WF02 [4218KS] AMM 73-21-62-000-802 and AMM 73-21-62-400-802.
2 Do the test given in Para. 3.
(9) If no problems with the harness are found or the fault continues:
(a) Check the aircraft wiring for AWM 715135 P0001 and AWM 783605 for ENG 1 fault and AWM 783604 for ENG 2 fault. Look for:
1 Continuity (less than 5 ohms resistance)
2 Wire-to-wire short
3 Short to ground.
NOTE: A short to ground is found when the resistance is less than 100 000 (100K) ohms.
| HCU (4310EG-A) Connector Contacts | (402VC) Connector Contacts |
|---|---|
| 3 | 15 |
| 29 at ground |
(b) Repair or replace the aircraft wiring if necessary.
1 Connect all connectors disconnected.
2 Do the test given in Para. 3.
(10) If the fault continues:
(a) Replace
(b) Do the test given in Para. 3.
Subtask 73-25-00-860-082-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.
(a) Close the fan cowl doors AMM 71-13-00-410-802.
(1) Make sure that the work area is clean and clear of tools and other items.
(a) Close the fan cowl doors AMM 71-13-00-410-802.