DOC AIRBUS | TSM A320FSLT RH WTB BLU Solenoid 36CV or Open or Short Circuit to SFCC 1 SLT RH WTB GRN Solenoid 36CV or Open or Short Circuit to SFCC 2
TASK 27-81-00-810-823-A
SLT RH WTB BLU Solenoid 36CV or Open or Short Circuit to SFCC 1 SLT RH WTB GRN Solenoid 36CV or Open or Short Circuit to SFCC 2
1. Possible Causes
A. Fixtures, Tools, Test and Support Equipment
B. Referenced Information
3. Fault Confirmation
Subtask 27-81-00-740-062-A
Subtask 27-81-00-810-072-A
Subtask 27-81-00-942-072-A
[Rev.8 from Aug 2018]
2026.04.04 04:27:48 UTC
SLT RH WTB BLU Solenoid 36CV or Open or Short Circuit to SFCC 1 SLT RH WTB GRN Solenoid 36CV or Open or Short Circuit to SFCC 2
1. Possible Causes
- WING TIP BRAKE [36CV]
A/C wiring between the SFCC 1 ARINC tray interface and the electrical connector A/C Wiring between the SFCC 2 ARINC tray interface and the electrical connector - WTB Solenoid Valve
- SLAT/FLAP CONTR.COMP. [21CV]
- SLAT/FLAP CONTR.COMP. [22CV]
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | 1 | MEGOHMMETER 100 MOHMS - MEASURING VOLTAGE 45 VDC |
| No specific | 1 | MULTIMETER - STANDARD |
| REFERENCE | DESIGNATION |
|---|---|
| AMM 27-51-34-000-001 | Removal of the SFCC |
| AMM 27-51-34-400-001 | Installation of the SFCC |
| AMM 27-81-00-740-002 | BITE Test of the Slat and Flap Control Computers (Slat System) |
| ASM 278106 | |
| ASM 278107 | |
| AMM 27-81-51-000-001 | Removal of the Slat Wing-Tip Brake |
| AMM 27-81-51-000-004 | Removal of the Solenoid Valve from the Slat Wing-Tip Brake (WTB) |
| AMM 27-81-51-400-001 | Installation of the Slat Wing-Tip Brake |
| AMM 27-81-51-400-002 | Installation of the Solenoid Valve to the Slat Wing-Tip Brake (WTB) |
Subtask 27-81-00-740-062-A
A. SFCC System BITE WTB Solenoid Test
(1) Do a BITE test on the SFCC 1 (2) AMM 27-81-00-740-002.
(2) If the fault data "RH WTB solenoid open circuit (disconnect)" or "RH WTB solenoid short circuit" comes into view:
4. Fault Isolation(1) Do a BITE test on the SFCC 1 (2) AMM 27-81-00-740-002.
(2) If the fault data "RH WTB solenoid open circuit (disconnect)" or "RH WTB solenoid short circuit" comes into view:
- Do the fault isolation.
Subtask 27-81-00-810-072-A
A. Procedure
(1) Do not swap the SFCC's at this time.
(3) Do a check of theA/C wiring between the SFCC 1 ARINC tray interface and the electrical connector ASM 278106 36CVA (Blue Solenoid).
(4) Do a check of theA/C Wiring between the SFCC 2 ARINC tray interface and the electrical connector ASM 278107 36CVB (Green Solenoid).
(5) If there is no continuity, repair the wiring/interface.
(6) If the A/C wiring is satisfactory, do a check of the circuit resistance and circuit isolation of the fault indicated solenoid valve.
(7) On the RH WTB, use a MULTIMETER - STANDARD to do a check of the resistance between:
(a) For the BLUE Solenoid, connect the pins A and B together.
(b) Connect one test lead of the MEGOHMMETER 100 MOHMS - MEASURING VOLTAGE 45 VDC or a 50VDC +5VDC/-5VDC Isolation Tester to the pins AB for the BLUE Solenoid. Connect the other test lead to pin C.
(c) Supply a test signal for 5 seconds and read the shown resistance value.
(d) The resistance value must be more than 100 Megohms.
(9) For the GREEN Solenoid, do the steps (8)(a) thru (8)(d) again.
(10) If the WING TIP BRAKE [36CV] does not give the correct results for one of the two tests (Refer to steps (7) and (8) or (9)):
AMM 27-51-34-000-001 and AMM 27-51-34-400-001.
(a) Get access to the SLT ON GROUND FAULTS and do a check of the ground log.
(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:
1 Install the SFCCs to their initial positions.
2 Do the next step.
(13) Do the System BITE test as given in Para 3.A.(1).
(14) Set the MCDU to MENU MODE and access the SLT ON GROUND FAULTS page. Make sure that the ground log is empty.
5. Close-up(1) Do not swap the SFCC's at this time.
CAUTION:
DO NOT SWAP FLIGHT CONTROL COMPUTERS. IF THERE IS A SHORT CIRCUIT, YOU WILL CAUSE DAMAGE TO A SERVICEABLE COMPUTER WHEN YOU SWAP THEM.
(2) Disconnect the electrical connector for the RH WING TIP BRAKE [36CV] solenoids. (3) Do a check of the
(4) Do a check of the
(5) If there is no continuity, repair the wiring/interface.
(6) If the A/C wiring is satisfactory, do a check of the circuit resistance and circuit isolation of the fault indicated solenoid valve.
(7) On the RH WTB, use a MULTIMETER - STANDARD to do a check of the resistance between:
- SFCC1 - 36CVA - RH Blue Solenoid Pins A and B ASM 278106
- SFCC2 - 36CVB - RH Green Solenoid Pins A and B ASM 278107.
- P/N 667C0000-02 must be between 71 Ohms and 84 Ohms.
- P/Ns 903A0000-01, 1106A0000-01 and 1111A0000-01 must be between 53 Ohms and 60 Ohms.
- P/N 5751A0000-01 must be between 53 Ohms and 60 Ohms.
(a) For the BLUE Solenoid, connect the pins A and B together.
(b) Connect one test lead of the MEGOHMMETER 100 MOHMS - MEASURING VOLTAGE 45 VDC or a 50VDC +5VDC/-5VDC Isolation Tester to the pins AB for the BLUE Solenoid. Connect the other test lead to pin C.
(c) Supply a test signal for 5 seconds and read the shown resistance value.
(d) The resistance value must be more than 100 Megohms.
(9) For the GREEN Solenoid, do the steps (8)(a) thru (8)(d) again.
(10) If the WING TIP BRAKE [36CV] does not give the correct results for one of the two tests (Refer to steps (7) and (8) or (9)):
- Replace the WTB Solenoid Valve
AMM 27-81-51-000-004 AMM 27-81-51-400-002.
- Replace the WING TIP BRAKE [36CV]
AMM 27-81-51-000-001 and AMM 27-81-51-400-001.
AMM 27-51-34-000-001 and AMM 27-51-34-400-001.
(a) Get access to the SLT ON GROUND FAULTS and do a check of the ground log.
(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:
1 Install the SFCCs to their initial positions.
2 Do the next step.
(13) Do the System BITE test as given in Para 3.A.(1).
(14) Set the MCDU to MENU MODE and access the SLT ON GROUND FAULTS page. Make sure that the ground log is empty.
Subtask 27-81-00-942-072-A
A. Remove the ground support and maintenance equipment, the special and standard tools and all other items.
Subtask 27-81-00-860-073-A B. Put the aircraft back to its initial configuration.