DOC AIRBUS | TSM A320FP-Flange Monitoring Failure
TASK 77-32-00-810-825-A
P-Flange Monitoring Failure
1. Possible Causes
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Referenced Information
3. Fault Confirmation
Subtask 77-32-00-710-077-A ** ON A/C NOT FOR ALL
Subtask 77-32-00-860-051-A ** ON A/C NOT FOR ALL
[Rev.8 from Aug 2018]
2026.04.04 04:37:54 UTC
P-Flange Monitoring Failure
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 70-70-00-910-803 | SPOP 6 - Cleaning of the Contact Points and Wiring Harnesses |
| AMM 71-00-00-860-814 | Shutdown of the Engine |
| AMM 71-00-00-860-822 | Start the Engine (Normal Manual Start) |
| AMM 71-00-00-860-823 | Start the Engine (Normal Automatic Start) |
| AMM 73-21-63-000-802 | Removal of the Electronic Engine Control (EEC) Wiring Harness (W03) |
| AMM 73-21-63-400-802 | Installation of the Electronic Engine Control (EEC) Wiring Harness (W03) |
| AMM 77-31-01-000-801 | Removal of the Prognostics and Health Management Unit (PHMU) |
| AMM 77-31-01-400-801 | Installation of the Prognostics and Health Management Unit (PHMU) |
| AMM 77-32-22-000-801 | Removal of the Aft Vibration Sensor N1 |
| AMM 77-32-22-400-801 | Installation of the Aft Vibration Sensor N1 |
| AMM 78-36-00-010-802 | Opening of the Thrust Reverser Cowl-Doors |
| AMM 78-36-00-410-802 | Closing of the Thrust Reverser Cowl-Doors |
EEC and PHMU Wiring HarnessesSubtask 77-32-00-710-077-A ** ON A/C NOT FOR ALL
A. Do an engine run to idle to confirm repair of this fault AMM 71-00-00-860-822 or AMM 71-00-00-860-823.
(1) Shutdown the engine AMM 71-00-00-860-814.
(2) On Multipurpose Control and Display Unit (MCDU) screen, check if the fault is displayed on ground scanning report.
(a) If no problems are found, return the engine to service. Monitor the engine for reoccurring maintenance message.
(4) If the maintenance message comes back (hard fault), go to the Para. Fault Isolation.
4. Fault Isolation(1) Shutdown the engine AMM 71-00-00-860-814.
(2) On Multipurpose Control and Display Unit (MCDU) screen, check if the fault is displayed on ground scanning report.
NOTE: The Electronic Engine Control (EEC) channel A and channel B is reporting the circuit for the aft vibration sensor is open or shorted. The aft vibration sensor is monitored by the Prognostics and Health Management Unit (PHMU). The PHMU provides N1, N2, and Nf vibration information to both channel A and channel B of the EEC over two separate Controller Area Network (CAN) busses. The aft vibration sensor is attached to the engine core, located at the 3 o'clock position.
(3) 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.
(4) 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 77-32-00-810-076-A ** ON A/C NOT FOR ALL A. If there is confirmation of the fault:
(1) Open the thrust reverser cowl-doors AMM 78-36-00-010-802.
(2) Examine the W03 (4087KS) and connector P10 (4609KS-P10) - PHMU (4609KS) and connector P32 (4067KS-P32) - Aft vibration sensor (4067KS), for problems which are possible between the PHMU (4609KS) and the aft vibration sensor (4067KS).
(a) Inspect for harness damage.
(b) Inspect for loose or damaged connectors.
1 Replace W03 HARNESS(4087KS) AMM 73-21-63-000-802 and AMM 73-21-63-400-802.
2 Do the test given in Para. 3.
(3) If no problems are found with the harness or the fault continues, use a PLIERS - JAWED, SOFT to disconnect electrical connector P10 (4609KS-P10) from the PHMU (4609KS) and connector P32 (4067KS-P32) from the aft vibration sensor (4067KS).
(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) Clean the contacts with contact cleaner and clean cloth per SPOP 6. Blow dry with air (at less than 30 psi) across the connector face AMM 70-70-00-910-803.
(c) Reconnect electrical connector P10 (4609KS-P10) to the PHMU (4609KS) and connector P32 (4067KS-P32) to the aft vibration sensor (4067KS).
(d) Do the test given in Para. 3.
(4) If the fault continues:
(a) Replace SENSOR-VIBRATION,AFT [4067KS] AMM 77-32-22-000-801 and AMM 77-32-22-400-801.
(b) Do the test given in Para. 3.
(5) If the fault continues:
(a) Disconnect electrical connector P10 (4609KS-P10) from the PHMU (4609KS) and connector P32 (4067KS-P32) from the aft vibration sensor (4067KS). Use a MULTIMETER - STANDARD to test the aft vibration sensor (4067KS) circuits in the harness. Refer to Table 1. Look for:
1 Wire-to-wire shorts
2 Shorts to ground
3 Continuity (less than 5 ohms resistance).
(b) If a problem is found with the harness or connectors:
1 Replace W03 HARNESS [4087KS] AMM 73-21-63-000-802 and AMM 73-21-63-400-802.
2 Do the test given in Para. 3.
(6) If no problems are found with the harness or the fault continues:
(a) Replace the PROGNOSTICS AND HEALTH MANAGEMENT UNIT [4609KS] AMM 77-31-01-000-801 and AMM 77-31-01-400-801.
(b) Do the test given in Para. 3.
5. Close-up(1) Open the thrust reverser cowl-doors AMM 78-36-00-010-802.
(2) Examine the W03 (4087KS) and connector P10 (4609KS-P10) - PHMU (4609KS) and connector P32 (4067KS-P32) - Aft vibration sensor (4067KS), for problems which are possible between the PHMU (4609KS) and the aft vibration sensor (4067KS).
(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 W03 HARNESS(4087KS) AMM 73-21-63-000-802 and AMM 73-21-63-400-802.
2 Do the test given in Para. 3.
(3) If no problems are found with the harness or the fault continues, use a PLIERS - JAWED, SOFT to disconnect electrical connector P10 (4609KS-P10) from the PHMU (4609KS) and connector P32 (4067KS-P32) from the aft vibration sensor (4067KS).
(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) Clean the contacts with contact cleaner and clean cloth per SPOP 6. Blow dry with air (at less than 30 psi) across the connector face AMM 70-70-00-910-803.
(c) Reconnect electrical connector P10 (4609KS-P10) to the PHMU (4609KS) and connector P32 (4067KS-P32) to the aft vibration sensor (4067KS).
(d) Do the test given in Para. 3.
(4) If the fault continues:
(a) Replace SENSOR-VIBRATION,AFT [4067KS] AMM 77-32-22-000-801 and AMM 77-32-22-400-801.
(b) Do the test given in Para. 3.
(5) If the fault continues:
(a) Disconnect electrical connector P10 (4609KS-P10) from the PHMU (4609KS) and connector P32 (4067KS-P32) from the aft vibration sensor (4067KS). Use a MULTIMETER - STANDARD to test the aft vibration sensor (4067KS) circuits in the harness. Refer to Table 1. Look for:
1 Wire-to-wire shorts
2 Shorts to ground
3 Continuity (less than 5 ohms resistance).
NOTE: A short to ground is found when the resistance is less than 100 000 (100K) ohms.
Table 1: Aft Vibration Sensor Connector Contacts | W03 (4087KS) Harness P10 (4609KS-P10) PHMU (4609KS) Connector Contacts | W03 (4087KS) Harness P32 (4067KS-P32) Aft Vibration Sensor(4067KS) Connector Contacts |
|---|---|
| R | 3 |
| g | 2 |
1 Replace W03 HARNESS [4087KS] AMM 73-21-63-000-802 and AMM 73-21-63-400-802.
2 Do the test given in Para. 3.
(6) If no problems are found with the harness or the fault continues:
(a) Replace the PROGNOSTICS AND HEALTH MANAGEMENT UNIT [4609KS] AMM 77-31-01-000-801 and AMM 77-31-01-400-801.
(b) Do the test given in Para. 3.
Subtask 77-32-00-860-051-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 thrust reverser cowl-doors AMM 78-36-00-410-802.
(1) Make sure that the work area is clean and clear of tools and other items.
(a) Close the thrust reverser cowl-doors AMM 78-36-00-410-802.