DOC AIRBUS | TSM A320FElectrical Power to the FLP 1 WTB Monitored to Below 14VDC Electrical Power to the FLP 2 WTB Monitored to Below 14VDC
TASK 27-51-00-810-835-A
Electrical Power to the FLP 1 WTB Monitored to Below 14VDC Electrical Power to the FLP 2 WTB Monitored to Below 14VDC
1. Possible Causes
A. Referenced Information
3. Fault Confirmation
Subtask 27-51-00-740-066-A
Subtask 27-51-00-865-074-A
Subtask 27-51-00-860-081-A
[Rev.8 from Aug 2018]
2026.04.04 04:27:39 UTC
Electrical Power to the FLP 1 WTB Monitored to Below 14VDC Electrical Power to the FLP 2 WTB Monitored to Below 14VDC
1. Possible Causes
- SLAT/FLAP CONTR.COMP. [21CV]
- SLAT/FLAP CONTR.COMP. [22CV]
A/C wiring/interface between SFCC 1 (2) and the WTB.
A. Referenced Information
| REFERENCE | DESIGNATION |
|---|---|
| ASM 246812 | |
| ASM 246813 | |
| AMM 27-51-00-740-002 | BITE Test of the Slat and Flap Control Computers (Flap System) |
| ASM 275101 | |
| ASM 275108 | |
| AMM 27-51-34-000-001 | Removal of the SFCC |
| AMM 27-51-34-400-001 | Installation of the SFCC |
Subtask 27-51-00-740-066-A
A. SFCC System Bite WTB Power Test.
(1) Do a BITE test on the SFCC 1 (2) AMM 27-51-00-740-002. The fault data" WTB electrical power off" is displayed.
(2) Do the fault isolation.
4. Fault Isolation(1) Do a BITE test on the SFCC 1 (2) AMM 27-51-00-740-002. The fault data" WTB electrical power off" is displayed.
(2) Do the fault isolation.
Subtask 27-51-00-865-074-A
A. Table of the circuit breakers used in this procedure:
Subtask 27-51-00-810-085-A | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C ALL | |||
| 121VU | FLIGHT CONTROLS/WTB/FLP/SYS2 | 12CV | P20 |
| 122VU | FLIGHT CONTROLS/WTB/FLP/SYS1 | 10CV | S07 |
B. Procedure
(1) At the circuit breakers.
(a) Examine the C/B for integrity.
(b) Do a check of the A/C HOT BUS 28VDC supply. ASM 246812 ASM 246813
(c) If the fault is found at steps 4.A.(1)(a) and/or (b), do the repair and do the test at step 3.A.(1).
(2) If the fault continues.
(a) Swap the SFCC 1 and SFCC 2. AMM 27-51-34-000-001 and AMM 27-51-34-400-001.
(b) If the fault moves with SFCC 1(2).
(c) Return the SFCC 1 (2) to their initial locations.
(d) Replace the unserviceable SLAT/FLAP CONTR.COMP. [21CV] or SLAT/FLAP CONTR.COMP. [22CV] .
(3) Do the BITE test of the SFCC 1 (2) Ref. Step 3.A.(1).
(4) If the fault continues, do a check of theA/C wiring/interface between SFCC 1 (2) and the WTB. ASM 275101 ASM 275108
(5) If there is a wiring/interface fault, do the repair.
(6) Do the BITE test.Ref 3.A.(1).
5. Close-up(1) At the circuit breakers.
(a) Examine the C/B for integrity.
(b) Do a check of the A/C HOT BUS 28VDC supply. ASM 246812 ASM 246813
(c) If the fault is found at steps 4.A.(1)(a) and/or (b), do the repair and do the test at step 3.A.(1).
(2) If the fault continues.
(a) Swap the SFCC 1 and SFCC 2. AMM 27-51-34-000-001 and AMM 27-51-34-400-001.
(b) If the fault moves with SFCC 1(2).
(c) Return the SFCC 1 (2) to their initial locations.
(d) Replace the unserviceable SLAT/FLAP CONTR.COMP. [21CV] or SLAT/FLAP CONTR.COMP. [22CV] .
(3) Do the BITE test of the SFCC 1 (2) Ref. Step 3.A.(1).
(4) If the fault continues, do a check of the
(5) If there is a wiring/interface fault, do the repair.
(6) Do the BITE test.Ref 3.A.(1).
Subtask 27-51-00-860-081-A
A. Put the aircraft back to its initial configuration.