(c) Return the SFCC 1 (2) to their initial locations.
(d) Replace the unserviceable SFCC-1 (21CV) or SFCC-2 (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 A/C wiring/interface between SFCC 1 (2) and the WTB. (Ref. ASM 27-51/01) (Ref. ASM 27-51/08)
(5) If there is a wiring/interface fault, do the repair.
(6) Do the BITE test.Ref 3.A.(1).
5. Close-up
________
A. Put the aircraft back to its initial configuration.
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1 EFF : ALL ∞∞27-51-00∞∞∞∞∞∞∞∞∞∞Page 277
May 01/05R CES
FLP LH WTB BLU Solenoid 33CV or Open or Short Circuit to SFCC 1 FLP LH WTB YEL Solenoid 33CV or Open or Short Circuit to SFCC 2
WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU
_______
START A TASK ON OR NEAR:
- THE FLIGHT CONTROLS
- THE FLIGHT CONTROL SURFACES
- THE LANDING GEAR AND THE RELATED DOORS
- COMPONENTS THAT MOVE.
WARNING : MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROL SURFACES ARE
_______
CLEAR BEFORE YOU PRESSURIZE/DEPRESSURIZE A HYDRAULIC SYSTEM.
WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING
_______
GEAR.
1. Possible Causes
_______________
- SFCC-1 (21CV)
- SFCC-2 (22CV)
- WTB Solenoid Valve
- aircraft wiring
2. Job Set-up Information
______________________
A. Fixtures, Tools, Test and Support Equipment
-------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
No specific multimeter
No specific 45 VDC Isolation Tester
B. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 27-51-00-740-002 Bite Test of the Slat and Flap Control Computers
(Flap System) AMM 27-51-34-000-001 Removal of the SFCC (21CV,22CV) AMM 27-51-34-400-001 Installation of the SFCC (21CV,22CV) AMM 27-51-51-000-002 Removal of the Solenoid Valves of the Flap Wing-Tip
Brake (WTB)
AMM 27-51-51-400-002 Installation of the Solenoid Valves of the Flap
Wing-Tip Brake (WTB)
ASM 27-51/06
ASM 27-51/07
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1 EFF : ALL ∞∞27-51-00∞∞∞∞∞∞∞∞∞∞Page 278
May 01/05R CES
3. Fault Confirmation
__________________
A. Test
(1) Do a BITE test on the SFCC 1 or SFCC 2, identified in the failure message (Ref. AMM TASK 27-51-00-740-002).
(2) If the failure message LH WTB SOLENOID OPEN CIRCUIT (DISCONNECT) or LH WTB SOLENOID SHORT CIRCUIT is shown, do the fault isolation procedure in Para. 4.A.
4. Fault Isolation
_______________
A. Procedure.
(1) Interchange the SFCC 1 and SFCC 2, (Ref. AMM TASK 27-51-34-000-001) and (Ref. AMM TASK 27-51-34-400-001).
(2) If the fault stays (in the initial SFCC position), go to step (4).
(3) If the fault goes (to the opposite SFCC position):
- replace the unserviceable SFCC-1 (21CV) or SFCC-2 (22CV).
(4) If the fault continues:
(a) Disconnect the applicable electrical connector attached to the Wing Tip Brake (33CV) solenoid valve, identified in the failure message:
- for the LH WTB blue hydraulic system solenoid, disconnect connector 33CV-A
- for the LH WTB yellow hydraulic system solenoid, diconnect connector 33CV-B.
(b) Use a multimeter to do a check of the resistance between pin A and pin B, (Ref. ASM 27-51/06) or (Ref. ASM 27-51/07):
- the resistance for the solenoid valve 667C0000-02 must be between 71 ohms and 84 ohms
- the resistance for the solenoid valves 903A0000-01; 1106A0000-1 and 1111A0000-01 must be between 53 ohms and 60 ohms.
(c) Connect the pins A and B together and use a 45 VDC Isolation Tester to do an isolation test between pins AB and pin C (ground):
- the resistance value must be greater than 100 Megohms.
(d) Connect the connector disconnected in step (a). 中國航空網 www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 飛行操縱 2(7)
