3. Fault Confirmation
__________________
 A. Job Set-up
 (1) Aircraft Maintenance Configuration
 (a) Pressurize the aircraft hydraulic systems (Ref. AMM TASK 29-10-00-863-003) (Ref. AMM TASK 29-23-00-863-001) (Ref. AMM TASK 29-24-00-863-001).
 B. Test
 (1) Do the Ground Scanning of the AFS (Ref. AMM TASK 22-91-00-710-001).
 「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 ∞∞22-63-00∞∞∞∞∞∞∞∞∞∞Page 225
 Feb 01/03 CES

 4. Fault Isolation
_______________

 A. If the test gives the maintenance message AFS : HYD Y 3151GN:
 - on the MCDU, get the AFS/TEST REPORT TROUBLE SHOOTING DATA page.

 - make sure that the fourth number of the word W3 is equal to one of these values: . 8, 9, A, B, C, D, E or F.
 (1) If the fourth number is not equal to one of the above values:
 - replace the FAC-2 (1CC2) (Ref. AMM TASK 22-66-34-000-002) and (Ref. AMM TASK 22-66-34-400-002).
 (a) If the fault continues:
 - do a check and repair the wiring of the HYD CIRC PRESS SW discrete (from the FAC 2 (1CC2) to the first terminal block) (Ref. ASM 22-68/04).
 B. Do the test given in Para. 3.
 5. Close-up
________
 A. Put the aircraft back to its initial configuration.
 (1) Depressurize the aircraft hydraulic systems (Ref. AMM TASK 29-10-00-864-003) (Ref. AMM TASK 29-23-00-864-001) and (Ref. AMM TASK 29-24-00-864-001).

R TASK 22-63-00-810-815

R  Loss of the Yaw Damper Function 
R  1. Possible Causes_______________ 
R  2. Job Set-up Information______________________ 
R  A. Referenced Information 
R  -------------------------------------------------------------------------------
R  REFERENCE  DESIGNATION 
R  -------------------------------------------------------------------------------
R  22-63-00-810-801  Loss of the Yaw Damper Function on the FAC 1 
R  22-63-00-810-802  Loss of the Yaw Damper Function on the FAC 2 
R  3. Fault Confirmation__________________ 
R  A. Not applicable. 
R  B. Make sure that this(these) circuit breaker(s) is(are) closed: 
R  -------------------------------------------------------------------------------
R  PANEL  DESIGNATION  IDENT. LOCATION 
R  -------------------------------------------------------------------------------
R  49VU AUTO FLT/FAC1/28VDC  5CC1  B04 
R  121VU AUTO FLT/FAC2/28VDC  5CC2  M19 
R  4. Fault Isolation_______________ 
R  A. In case of appearance of the ECAM warnings AUTO FLT YAW DAMPER 1, AUTO 
R  FLT YAW DAMPER 2 or AUTO FLT YAW DAMPER SYS, at or after engine start: 
R  - perform a reset of FAC 1 and FAC 2 pushbuttons on the overhead panel 
R  - if unsuccessful, shut down the engines and perform a reset of both FAC 
R  1 and 2 circuits breakers: 5CC1 and 5CC2 (for more than 5 seconds). 
R  - if fault persists, do the following procedures (Ref. TASK 22-63-00-810-
R  801) and/or (Ref. TASK 22-63-00-810-802).

 FLIGHT AUGMENTATION COMPUTER (FAC) - FAULT ISOLATION PROCEDURES
_______________________________________________________________
 TASK 22-66-00-810-801
 Failure of the FAC 1
 1. Possible Causes
_______________
 - FAC-1 (1CC1)

 - LIMITATION UNIT-RUDDER TRAVEL (4CC)

 - ACTUATOR-RUDDER TRIM (10CC)

 - wiring of the 28VDC signal from the circuit breaker (5CC1) to the FAC 1 (1CC1)

 - wiring of the ground signal at the FAC 1 (1CC1)

 - C/B-AUTO FLT/FAC 1/28VDC (5CC1)

 - short to ground between the circuit breaker 5CC1 and the three units

 - C/B-AUTO FLT /FAC 1/28VDC (5CC1)

 2. Job Set-up Information
______________________
 A. Referenced Information
 -------------------------------------------------------------------------------REFERENCE DESIGNATION
 -------------------------------------------------------------------------------
AMM 22-66-34-000-002 Removal of the FAC (1CC1,1CC2)
 AMM 22-66-34-400-002 Installation of the FAC (1CC1,1CC2)
 AMM 22-96-00-710-001 Operational Test of the AFS
 AMM 27-22-51-000-001 Removal of the Rudder Trim Actuator (10CC)
 AMM 27-22-51-400-001 Installation of the Rudder Trim Actuator (10CC)
　
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