DOC AIRBUS | TSM A320FFLP RH WTB BLU Solenoid 34CV or Open or Short Circuit to SFCC 1 FLP RH WTB GRN Solenoid 34CV or Open or Short Circuit to SFCC 2
TASK 27-51-00-810-837-A
FLP RH WTB BLU Solenoid 34CV or Open or Short Circuit to SFCC 1 FLP RH WTB GRN Solenoid 34CV 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 27-51-00-740-068-A
Subtask 27-51-00-810-087-A
Subtask 27-51-00-942-076-A
[Rev.8 from Aug 2018]
2026.04.04 04:27:39 UTC
FLP RH WTB BLU Solenoid 34CV or Open or Short Circuit to SFCC 1 FLP RH WTB GRN Solenoid 34CV or Open or Short Circuit to SFCC 2
1. Possible Causes
- WING TIP BRAKE [34CV]
A/C wiring between the SFCC 1 ARINC tray interface and the electrical connector - 34CVA
A/C wiring between the SFCC 2 ARINC tray interface and the electrical connector - 34CVB
- 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 27-51-00-740-002 | BITE Test of the Slat and Flap Control Computers (Flap System) |
| ASM 275106 | |
| ASM 275107 | |
| AMM 27-51-34-000-001 | Removal of the SFCC |
| AMM 27-51-34-400-001 | Installation of the SFCC |
| AMM 27-51-51-000-001 | Removal of the Flap Wing-Tip Brake |
| AMM 27-51-51-000-002 | Removal of the Solenoid Valves of the Flap Wing-Tip Brake (WTB) |
| AMM 27-51-51-400-001 | Installation of the Flap Wing-Tip Brake |
| AMM 27-51-51-400-002 | Installation of the Solenoid Valves of the Flap Wing-Tip Brake (WTB) |
Subtask 27-51-00-740-068-A
A. SFCC System Bite WTB Solenoid test
(1) Do a BITE test on the SFCC 1 (2) AMM 27-51-00-740-002. The fault data "RH WTB solenoid open circuit (disconnect)" is displayed, or the fault data "RH WTB solenoid short circuit" 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 "RH WTB solenoid open circuit (disconnect)" is displayed, or the fault data "RH WTB solenoid short circuit" is displayed.
(2) Do the fault isolation.
Subtask 27-51-00-810-087-A
A. Procedure
(2) Do a check of theA/C wiring between the SFCC 1 ARINC tray interface and the electrical connector ASM 275106 34CVA (BLUE solenoid).
(3) Do a check of theA/C wiring between the SFCC 2 ARINC tray interface and the electrical connector ASM 275107 34CVB (GREEN solenoid).
(4) If there is no continuity, repair the wiring/interface.
(5) If the A/C wiring is satisfactory, do a check of the circuit resistance and circuit isolation of the fault indicated solenoid valve.
(6) On the RH WTB, use a MULTIMETER - STANDARD to do a check of the resistance between:
(a) For SFCC1 - 34CVA - RH Blue Solenoid Pins A and B ASM 275106.
(b) For SFCC2 - 34CVB - RH Green Solenoid Pins A and B ASM 275107.
(c) The resistance values must be as follows:
(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.
(e) For the GREEN solenoid, do the steps given in Para (7) again.
(8) If the WING TIP BRAKE [34CV] does not give the correct results for one of the two tests (given at Paras 4.A.(6) and (7)):
(b) If the fault does not move to the other SFCC:
(e) Set the MCDU to MENU MODE and get access to the FLP ON GROUND FAULTS page. Make sure that the ground log is empty.
5. Close-upCAUTION:
DO NOT SWAP FLIGHT CONTROL COMPUTERS. IF THERE IS A SHORT CIRCUIT, YOU WILL CAUSE DAMAGE TO A SERVICEABLE COMPUTER WHEN YOU SWAP THEM.
(1) Disconnect the electrical connector for the WING TIP BRAKE [34CV] solenoids. (2) Do a check of the
(3) Do a check of the
(4) If there is no continuity, repair the wiring/interface.
(5) If the A/C wiring is satisfactory, do a check of the circuit resistance and circuit isolation of the fault indicated solenoid valve.
(6) On the RH WTB, use a MULTIMETER - STANDARD to do a check of the resistance between:
(a) For SFCC1 - 34CVA - RH Blue Solenoid Pins A and B ASM 275106.
(b) For SFCC2 - 34CVB - RH Green Solenoid Pins A and B ASM 275107.
(c) The resistance values must be as follows:
- The resistance for the solenoid valve 667C0000-02 must be between 71 ohms and 84 ohms.
- The resistance for the solenoid valves 903A0000-01, 1106A0000-01 and 1111A0000-01 must be between 53 ohms and 60 ohms.
- The resistance for the solenoid valve 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.
(e) For the GREEN solenoid, do the steps given in Para (7) again.
(8) If the WING TIP BRAKE [34CV] does not give the correct results for one of the two tests (given at Paras 4.A.(6) and (7)):
- Replace the WTB Solenoid Valve
AMM 27-51-51-000-002 and AMM 27-51-51-400-002.
- Replace the WING TIP BRAKE [34CV]
AMM 27-51-51-000-001 and AMM 27-51-51-400-001.
- Interchange SFCC 1 and SFCC 2 AMM 27-51-34-000-001 and AMM 27-51-34-400-001.
(b) If the fault does not move to the other SFCC:
- Install the SFCCs in their initial positions.
- Install the serviceable SFCC 1(2) in its initial position.
- Replace the unserviceable SLAT/FLAP CONTR.COMP. [21CV] or SLAT/FLAP CONTR.COMP. [22CV]
AMM 27-51-34-000-001 and AMM 27-51-34-400-001.
(e) Set the MCDU to MENU MODE and get access to the FLP ON GROUND FAULTS page. Make sure that the ground log is empty.
Subtask 27-51-00-942-076-A
A. Remove the ground support and maintenance equipment, the special and standard tools and all other items.
Subtask 27-51-00-860-080-A B. Put the aircraft back to its initial configuration.