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 1. Possible Causes_______________
 - RELAY-A/C ON GND (94CV) - RELAY-A/C ON GND (96CV) - aircraft wiring
 2. Job Set-up Information______________________
 A. Referenced Information
 -------------------------------------------------------------------------------
REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM ASM ASM  27-81-00-740-002 27-81/0227-81/03 Bite Test of the Slat and Flap Control Computers (Slat System)
 3. Fault Confirmation__________________
 A. Test
 (1) If the Post Flight Report shows the ECAM message SLAT SYS 1(2) FAULT and the A-LOCK legend (cyan) flashed during slat retraction on the ground, do the next step.
R R R R R  (2) Do a BITE test of the applicable system SFCC slat channel (Ref. AMM TASK 27-81-00-740-002): - if the test completes, but gives a different maintenance message, do the trouble shooting procedure related to the maintenance message. - if you cannot access the test page, do the fault isolation procedure given in Para. 4.
 NOTE : When the aircraft is on the ground, the A-LOCK legend can only____ show if the SFCC1 or SFCC2 slat channel is incorrectly in the flight mode. The legend will go off when the serviceable channel has fully retracted the slats (at half speed). It is not possible to access the slat test page when the related slat channel is in the flight mode.

 4. Fault Isolation
_______________

 A. Procedure
 (1) Replace the applicable A/C ON GND relay:

 - for Slat 1 replace RELAY-A/C ON GND (94CV)

 - for Slat 2 replace RELAY-A/C ON GND (96CV).

 

 (2) Do the test given in Para. 3. A. (2):

 - if the fault continues, do the next step.

 (3) Do a check of the aircraft wiring (Ref. ASM 27-81/02) or (Ref. ASM 27-81/03) and repair as necessary.

 (4) Do the test given in Para. 3. A. (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 ∞∞27-81-00∞∞∞∞∞∞∞∞∞∞Page 283
 May 01/05R
 CES  Slats - WTB/POB Test Does Not Complete

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

 - SFCC-2 (22CV)

 - POWER CONTROL UNIT (6001CM)

 - aircraft wiring

 2. Job Set-up Information
______________________
 A. Referenced Information
 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
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 27-81-00-710-001 Operational Test of the Wing-Tip Brake and the

 Pressure-Off Brake AMM 27-84-51-000-001 Removal of the Power Control Unit 6001CM of the Slat System AMM 27-84-51-400-001 Installation of the Power Control Unit 6001CM of the Slat System
 3. Fault Confirmation
__________________
 A. Test
 (1) Do an operational test of the wing-tip brake and the pressure-off brake (Ref. AMM TASK 27-81-00-710-001):
 - if the test does not complete in less than 2 minutes do the fault isolation procedure in Para. 4.

 - if the test is OK, no more maintenance work is necessary.

 4. Fault Isolation
_______________
 A. Procedure
 (1) Abort the test as follows:

 (a) Reset the circuit breaker of the channel on test.

 (2) Interchange the SFCCs (Ref. AMM TASK 27-51-34-000-001) and (Ref. AMM TASK 27-51-34-400-001).

 (a) Do the test in Para. 3. A.
 - if the test is OK, do step (3)

 - if the test does not complete, do step (4).

 「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 ∞∞27-81-00∞∞∞∞∞∞∞∞∞∞Page 284
 May 01/05R CES

 (3) Replace the unserviceable SFCC-1 (21CV) or SFCC-2 (22CV) that was the source of the initial fault.

 (a) Do the test in Para. 3. A.
 - if the test does not complete, do the next step.

 (4) Replace the POWER CONTROL UNIT (6001CM) (Ref. AMM TASK 27-84-51-000-001) and (Ref. AMM TASK 27-84-51-400-001).

 (a) Do the test in Para. 3. A:
 - if the test does not complete, do the next step.

 (5) Do a check of the aircraft wiring between the applicable SFCC and the PCU:

 - do the repair.
 (a) Do the test in Para. 3. A.

 SLATS ELECTRICAL CONTROL AND MONITORING - TASK SUPPORTING DATA
　
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