DOC AIRBUS | TSM A320FLeft Flap Interconnecting-Strut Attachment Failure-Detection Sensor Fault
TASK 27-51-00-810-817-A
Left Flap Interconnecting-Strut Attachment Failure-Detection Sensor Fault
A. Referenced Information
3. Fault Confirmation
Subtask 27-51-00-740-055-A
Subtask 27-51-00-810-065-A
[Rev.8 from Aug 2018]
2026.04.04 04:39:13 UTC
Left Flap Interconnecting-Strut Attachment Failure-Detection Sensor Fault
NOTE: If a fault occurs on the two proximity sensors 37CV and 39CV, a F/CTL FLAPS Fault E/W is shown on the top of the SFCS maintenance status when flaps are in conf 1, 2 or 3.
1. Possible Causes- SLAT/FLAP CONTR.COMP. [21CV]
- SLAT/FLAP CONTR.COMP. [22CV]
- SENSOR-L FLAP ATTACHMENT FAILURE DETECTION [37CV]
- SENSOR-L FLAP ATTACHMENT FAILURE DETECTION [39CV]
- aircraft wiring
A. Referenced Information
| REFERENCE | DESIGNATION |
|---|---|
| TSM TASK 32-31-00-810-828-A | Left Flap Disconnect Proximity Sensor |
| AMM 27-51-00-710-002 | Operational Test of the Flap Interconnecting Strut and the Flap-Attachment Failure-Detection Sensors |
| ASM 275106 | |
| ASM 275107 | |
| AMM 27-51-15-000-002 | Removal of the Proximity-Sensors of the Interconnecting Strut |
| AMM 27-51-15-400-002 | Installation of the Proximity-Sensors of the Interconnecting Strut |
| AMM 27-51-34-000-001 | Removal of the SFCC |
| AMM 27-51-34-400-001 | Installation of the SFCC |
| AMM 32-69-00-740-001 | BITE Check of Landing-Gear Control Interface-Unit (LGCIU) With Use of MCDU to Ensure that Continuous BITE is Operative |
Subtask 27-51-00-740-055-A
A. Test
(1) Do a BITE test with the LGCIU given in the CFDS message AMM 32-69-00-740-001.
(2) If the test gives a message that includes the DISC PROX SENSOR (37CV or 39CV), do the fault isolation procedure in (Ref. TSM TASK 32-31-00-810-828).
(3) If the test does not give a message that includes the DISC PROX SENSOR (37CV or 39CV), but the fault continues, do the fault isolation procedure in Para. 4.
4. Fault Isolation(1) Do a BITE test with the LGCIU given in the CFDS message AMM 32-69-00-740-001.
(2) If the test gives a message that includes the DISC PROX SENSOR (37CV or 39CV), do the fault isolation procedure in (Ref. TSM TASK 32-31-00-810-828).
(3) If the test does not give a message that includes the DISC PROX SENSOR (37CV or 39CV), but the fault continues, do the fault isolation procedure in Para. 4.
Subtask 27-51-00-810-065-A
A. Procedure
(1) Interchange the SFCCs AMM 27-51-34-000-001 and AMM 27-51-34-400-001.
(3) If the test is OK:
(a) Replace the SLAT/FLAP CONTR.COMP. [21CV] or SLAT/FLAP CONTR.COMP. [22CV] that was the source of the initial CFDS message.
(b) Install the serviceable SFFC in its initial position.
(4) If the test is not OK (gives the same CFDS message as the initial CFDS message):
(a) Install the SFCCs in their initial positions.
(b) Replace the applicable proximity sensor SENSOR-L FLAP ATTACHMENT FAILURE DETECTION [37CV] or SENSOR-L FLAP ATTACHMENT FAILURE DETECTION [39CV] , AMM 27-51-15-000-002 and AMM 27-51-15-400-002.
(5) If the fault continues, do a check and repair the aircraft wiring between:
(1) Interchange the SFCCs AMM 27-51-34-000-001 and AMM 27-51-34-400-001.
NOTE: This will cause each SFCC to get a new identification.
(2) Do an operational test of the flap interconnecting strut AMM 27-51-00-710-002. (3) If the test is OK:
(a) Replace the SLAT/FLAP CONTR.COMP. [21CV] or SLAT/FLAP CONTR.COMP. [22CV] that was the source of the initial CFDS message.
(b) Install the serviceable SFFC in its initial position.
(4) If the test is not OK (gives the same CFDS message as the initial CFDS message):
(a) Install the SFCCs in their initial positions.
(b) Replace the applicable proximity sensor SENSOR-L FLAP ATTACHMENT FAILURE DETECTION [37CV] or SENSOR-L FLAP ATTACHMENT FAILURE DETECTION [39CV] , AMM 27-51-15-000-002 and AMM 27-51-15-400-002.
(5) If the fault continues, do a check and repair the aircraft wiring between:
- the applicable proximity sensor and the related LGCIU, ASM 275106 or ASM 275107
- the applicable LGCIU and the related SFCC, ASM 275106 or ASM 275107.