(b) Wait for 3 seconds and close the circuit breakers.

 (c) Wait for 60 seconds

 (d) Check the UPPER ECAM and the SD FLT/CTL page for the fault warnings.

 (e) If the ECAM warning message clears, set the MCDU to MENU MODE and access the FLP ON GROUND FAULTS page and make sure that the ground log is clear.

 (f) If the ECAM warning and the fault message stays displayed do the procedure at Para.4.C.

 C. Procedure
 (1) Swap the SFCC 1 (2) with SFCC 2 (1) (Ref. AMM TASK 27-51-34-000-001) (Ref. AMM TASK 27-51-34-400-001).
 (a) If the fault moves with the SFCC 1 (2) to the SFCC 2 (1) position, the fault is in the SFCC 1 (2).
 「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 274
 May 01/05R CES

 (2) Return the SFCC 1 (2) and 2 (1) in their initial locations and replace the unserviceable SFCC-1 (21CV) (SFCC-2 (22CV)) Refer to Para. 4.A.(1).

 (a) If the fault remains in the SFCC 1 (2) the fault is in the SFCC 1
 (2) interface/circuit or CFDIU

 (3) Do a check of the aircraft wiring between the CFDIU ARINC connector and the SFCC 1 (2) ARINC electrical connecter. (Ref. AWM 27-51-21) (Ref. AWM 27-51-22).

 (4) If there is no continuity repair the wiring/interface.

 (5) Do the Reset as in Para. 3.A.(2)(c).

 (a) Set the MCDU to MENU MODE and access the FLAP ON GROUND FAULTS page and make sure that the ground log is clear.

 (6) If the fault remains,the fault is with the circuit inteface to the CFDIU, refer to TSM page block 101 34- 12- 00.

 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 275
 May 01/05R
 CES  Electrical Power to the FLP 1 WTB Monitored to Below 14Vdc Electrical Power to the FLP 2 WTB Monitored to Below 14Vdc

 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.

 1. Possible Causes
_______________
 - SFCC-1 (21CV)

 - SFCC-2 (22CV)

 - A/C wiring/interface between SFCC 1 (2) and the WTB.

 2. Job Set-up Information
______________________
 A. 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) ASM 24-68/12 ASM 24-68/13 ASM 27-51/01 ASM 27-51/08
 3. Fault Confirmation
__________________
 A. SFCC System Bite WTB Power Test.
 (1) Do a BITE test on the SFCC 1 (2) (Ref. AMM TASK 27-51-00-740-002). The fault data" WTB electrical power off" is displayed.

 (2) Do the fault isolation.

 「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 276
 May 01/05R
 CES

 4. Fault Isolation
_______________

 A. Table of the circuit breakers used in this procedure:
 -------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------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. (Ref. ASM 24-68/12) (Ref. ASM 24-68/13)

 (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. (Ref. AMM TASK 27-51-34-000-001) and (Ref. AMM TASK 27-51-34-400-001).

 (b) If the fault moves with SFCC 1(2).