DOC AIRBUS | TSM A320FCSU Fault (51CV) or Fault in Wiring to SFCC 1 (2)
TASK 27-51-00-810-805-A
CSU Fault (51CV) or Fault in Wiring to SFCC 1 (2)
1. Possible Causes
2. Job Set-up Information
A. Referenced Information
3. Fault Confirmation
Subtask 27-51-00-710-054-A
Subtask 27-51-00-810-054-A
Subtask 27-51-00-942-079-A
[Rev.8 from Aug 2018]
2026.04.04 04:27:36 UTC
CSU Fault (51CV) or Fault in Wiring to SFCC 1 (2)
1. Possible Causes
2. Job Set-up Information
A. Referenced Information
| REFERENCE | DESIGNATION |
|---|---|
| ASM 275102 | |
| ASM 275103 | |
| AMM 27-51-17-000-001 | Removal of the Command Sensor Unit |
| AMM 27-51-17-400-001 | Installation of the Command Sensor Unit |
| AMM 27-51-34-000-001 | Removal of the SFCC |
| AMM 27-51-34-400-001 | Installation of the SFCC |
| AMM 27-54-00-710-002 | Operational Test of the Flap and Slat Systems |
| AMM 31-32-00-860-006 | Procedure to Get Access to the SYSTEM REPORT/TEST F/CTL Page |
Subtask 27-51-00-710-054-A
A. Test
(1) Do the operational test of the slats and flaps AMM 27-54-00-710-002. Do this not less than 5 times.
(2) Get access to the SYSTEM REPORT/TEST F/CTL page AMM 31-32-00-860-006.
(a) Set the related SFCC 1 or SFCC 2, which gave the initial failure message.
(b) Get access to the SYSTEM STATUS page:
1 If a CSU (51CV) failure message is shown, do the fault isolation procedure in Para. 4.A.
2 If a different failure message is shown, do the trouble shooting procedure related to the failure message.
3 If the fault does not occur again, do a check of the PFR:
a If the CSU (51CV) failure message is related to an ECAM warning, do the steps as given in Para 4.B.
b If the CSU (51CV) failure message is not related to an ECAM warning, no more action is necessary.
4. Fault Isolation(1) Do the operational test of the slats and flaps AMM 27-54-00-710-002. Do this not less than 5 times.
(2) Get access to the SYSTEM REPORT/TEST F/CTL page AMM 31-32-00-860-006.
(a) Set the related SFCC 1 or SFCC 2, which gave the initial failure message.
(b) Get access to the SYSTEM STATUS page:
1 If a CSU (51CV) failure message is shown, do the fault isolation procedure in Para. 4.A.
2 If a different failure message is shown, do the trouble shooting procedure related to the failure message.
3 If the fault does not occur again, do a check of the PFR:
a If the CSU (51CV) failure message is related to an ECAM warning, do the steps as given in Para 4.B.
b If the CSU (51CV) failure message is not related to an ECAM warning, no more action is necessary.
NOTE: It is necessary to RETURN to the F/CTL page and set the related SFCC again to update the SYSTEM STATUS page.
Subtask 27-51-00-810-054-A
A. Procedure
(1) Interchange SFCC 1 and SFCC 2,
AMM 27-51-34-000-001 and AMM 27-51-34-400-001.
(a) Do the test in Para. 3.A.
(b) If the fault moves with the SFCC 1(2):
1 Install the serviceable SFCC to its initial position.
2 Replace the defective SLAT/FLAP CONTR.COMP. [21CV] or SLAT/FLAP CONTR.COMP. [22CV] .
(c) If the fault does not move to the other SFCC:
(a) Do the test in Para. 3.A.
(b) If the fault moves to the other SFCC:
1 Replace the CSU [51CV] .
2 Make sure that the related electrical connectors are correctly installed.
(c) If the fault remains in the same circuit:
1 Install the electrical connectors in their initial positions.
2 Do a check and repair the aircraft wiring between the applicable SFCC ARINC tray interface and the applicable electrical connector 51CV-A or 51CV-B,
ASM 275102 or ASM 275103.
3 Do the test in Para. 3.A.
4 Make sure that there are no fault messages.
Subtask 27-51-00-810-111-A (1) Interchange SFCC 1 and SFCC 2,
AMM 27-51-34-000-001 and AMM 27-51-34-400-001.
(a) Do the test in Para. 3.A.
(b) If the fault moves with the SFCC 1(2):
1 Install the serviceable SFCC to its initial position.
2 Replace the defective SLAT/FLAP CONTR.COMP. [21CV] or SLAT/FLAP CONTR.COMP. [22CV] .
(c) If the fault does not move to the other SFCC:
- Install the SFCCs to their initial positions.
- Do step (2).
(a) Do the test in Para. 3.A.
(b) If the fault moves to the other SFCC:
1 Replace the CSU [51CV] .
2 Make sure that the related electrical connectors are correctly installed.
(c) If the fault remains in the same circuit:
1 Install the electrical connectors in their initial positions.
2 Do a check and repair the aircraft wiring between the applicable SFCC ARINC tray interface and the applicable electrical connector 51CV-A or 51CV-B,
ASM 275102 or ASM 275103.
3 Do the test in Para. 3.A.
4 Make sure that there are no fault messages.
B. Procedure
(1) Interchange SFCC 1 and SFCC 2, AMM 27-51-34-000-001 and AMM 27-51-34-400-001 and dispatch the aircraft.
(2) If the fault moves to the other SFCC during the subsequent flights, replace the defective SLAT/FLAP CONTR.COMP. [21CV] or SLAT/FLAP CONTR.COMP. [22CV] .
(3) Make sure that the serviceable SFCC is installed in its initial position.
(4) If the fault occurs again at the same SFCC, replace the CSU [51CV] ,
AMM 27-51-17-000-001 and AMM 27-51-17-400-001.
(5) During the subsequent flights, if the fault occurs again at the same SFCC:
5. Close-up(1) Interchange SFCC 1 and SFCC 2, AMM 27-51-34-000-001 and AMM 27-51-34-400-001 and dispatch the aircraft.
(2) If the fault moves to the other SFCC during the subsequent flights, replace the defective SLAT/FLAP CONTR.COMP. [21CV] or SLAT/FLAP CONTR.COMP. [22CV] .
(3) Make sure that the serviceable SFCC is installed in its initial position.
(4) If the fault occurs again at the same SFCC, replace the CSU [51CV] ,
AMM 27-51-17-000-001 and AMM 27-51-17-400-001.
(5) During the subsequent flights, if the fault occurs again at the same SFCC:
- Do a check and repair the aircraft wiring between the related SFCC ARINC tray interface and the related electrical connector 51CV-A or 51CV-B, ASM 275102 or ASM 275103.
Subtask 27-51-00-942-079-A
A. Remove the ground support and maintenance equipment, the special and standard tools and all other items.
Subtask 27-51-00-860-085-A B. Put the aircraft back to its initial configuration.