TSM 27-51-00-810-814-A — FLAP SYSTEM 1 (2) FAULT A320

TSM 27-51-00-810-814-A — FLAP SYSTEM 1 (2) FAULT A320

1. Possible Causes:

2. Job Set-up Information

3. Fault Confirmation

SUBTASK 27-51-00-740-054-A

A. Fault Analysis

(1) Do a check of the Post Flight Report (PFR):

— if the ECAM Warning message FLAP SYS 1 (2) FAULT is shown without a related CFDS message and the flaps operated correctly, do the next step.

(2) Do the EIS Start Procedure Ref. AMM 31-60-00-860-001.

(3) At an MCDU, get access to the SYSTEM REPORT/TEST F/CTL page Ref. AMM 31-32-00-860-006.

(a) Set F/CTL and get access to the SFCC 1 and SFCC 2 menus.

(b) For each SFCC, set LAST LEG REP FLP and do a check for one or more of the messages that follow:

— SYSTEM STOP DUE TO LOW PRESSURE

— DC POWER INTERRUPT

— DC POWER BELOW 16 V

— SINGLE MOTOR OPERATION

— LEVER OUT OF DETENT FOR MORE THAN 10 SEC.

— INHIBIT SIGNAL FROM CARGO DOOR YELLOW SYSTEM.

NOTE:   These messages are shown in the Last Leg Report (LLR) to help with trouble shooting when the ECAM Warning message FLAP SYS 1 (2) FAULT is shown because of a transient fault.

(c) From the check of the LLR:

— if one or more of the applicable messages are shown, do the related fault isolation procedure:

Para 4.A.’Procedure (If one or more of the applicable Messages are Shown)’.

— if none of the applicable messages are shown, do the related fault isolation procedure:

Para 4.B.’Procedure (If none of the applicable Messages is Shown)’.

— if the SFCC menu on the MCDU is not available (NO RESPONSE or SFCC menu cannot load), do the related fault isolation procedure:

Para 4.C.’Procedure (If SFCC Menu on the MCDU is not Available)’.

4. Fault Isolation

SUBTASK 27-51-00-810-063-B

A. Procedure (If one or more of the applicable Messages are Shown)

(1) For the applicable message from the SFCC 1 (2) Flap LLR, do the related procedure step:

— for SYSTEM STOP DUE TO LOW PRESSURE, do step (2).

— for DC POWER INTERRUPT, do step (3).

— for DC POWER BELOW 16V, do step (4).

— for SINGLE MOTOR OPERATION, do step (5).

— for INHIBIT SIGNAL FROM CARGO DOOR YELLOW SYSTEM, do step (6).

(2) SYSTEM STOP DUE TO LOW PRESSURE:

— If the ECAM Warning FLAP SYS 1 (2) FAULT was shown because of a hydraulic low pressure problem (green or yellow), no more maintenance work is necessary.

— If there is no apparent hydraulic system problem, do the next step.

(a) Do the operational test of the flap system Ref. AMM 27-54-00-710-001.

— If a permanent fault is found do the applicable fault isolation procedure.

— If there is no apparent fault with the flap operation, or the operation is intermittent, do the next step.

(b) Do the trouble shooting procedure for the applicable VALVE BLOCK-FLAP 1 (23CV) or VALVE BLOCK-FLAP 2 (24CV), Ref. TSM TASK 27-51-00-810-802.

NOTE:   When the hydraulic motor operates, the spool of the control valve is moved and flow occurs. This flow can push particles, in the hydraulic fluid, against the valve block filter and cause a blockage. If a blockage occurs, the flow decreases and the spool moves back. This movement of the spool is sensed by the related SFCC, which stops the applicable hydraulic motor. Flow then decreases and lets the particles become free from the filter. This removal of the blockage then increases the flow, which moves the spool. This movement of the spool is sensed by the related SFCC, which releases the applicable hydraulic motor. This causes the flow to increase to the condition where a blockage can occur again. This fault condition can cause the flaps to operate intermittently.

(3) DC POWER INTERRUPT:

— If the ECAM Warning FLAP SYS 1 (2) FAULT was shown because of a DC power interrupt, no more maintenance work is necessary.

— If there is no apparent DC power problem, do step (7).

NOTE:   The message DC POWER INTERRUPT is shown in the LLR when the DC power is less than 14VDC for more than 40 msec.

(4) DC POWER BELOW 16V:

— If the ECAM Warning FLAP SYS 1 (2) FAULT was shown because the DC power was less than 16.5 VDC, no more maintenance work is necessary.

— If there is no apparent DC Power problem, do step (7).

NOTE:   The message DC POWER BELOW 16V is shown in the LLR when the DC power is less than 16.5VDC, but more than 14VDC, for more than 20 msec.

(5) SINGLE MOTOR OPERATION:

— Do the operational test of the flap system Ref. AMM 27-54-00-710-001.

If the ECAM Warning FLAP SYS 1(2) FAULT goes out of view: No more maintenance work is necessary.

If the ECAM Warning FLAP SYS 1(2) FAULT stays: Continue the trouble shooting procedure.

— If the ECAM Warning FLAP SYS 1 (2) FAULT was shown because the flaps operated momentarily on one motor only, no more maintenance work is necessary.

— If there is no apparent flap motor problem, do step (7).

(6) INHIBIT SIGNAL FROM CARGO DOOR YELLOW SYSTEM.

— If the ECAM Warning FLAP SYS 2 FAULT was shown because the flap operation was prevented by a Cargo Door fault, no more maintenance work is necessary.

— If there is no apparent Cargo Door fault, do the next step.

NOTE:   The cargo door inhibit signal is supplied by System 2 only.

(a) At the MCDU set RETURN to go back to the SFCC 2 menu page.

(b) Set CLASS 3 FAULTS FLP and do a check for the message WRONG INHIBIT SIGN FROM CARGO DOOR YELLOW SYSTEM:

— If the message is shown, do the related trouble shooting procedure Ref. TSM TASK 27-51-00-810-841

— If the message is not shown, do the next step.

(7) Make a record in the aircraft logbook to monitor the operation of the flap system during the next flight.

SUBTASK 27-51-00-810-108-A

B. Procedure (If none of the applicable Messages Show)

(1) If the ECAM warning FLAP SYS 1 (2) FAULT is shown, but there is no related CFDS message on the PFR, or on the SFCC 1 (2) Flap LLR, do the next step.

NOTE:   Do not apply this procedure if the aircraft was under MMEL during last leg. Refer to fault isolation to find the applicable trouble shooting procedure.

(2) Do the operational test of the flap system Ref. AMM 27-54-00-710-001 and make sure that the ECAM Warning FLAP SYS 1(2) FAULT does not show on the upper ECAM DU.

(a) If the ECAM Warning FLAP SYS 1(2) FAULT goes out of view: No more maintenance work is necessary.

(b) If the ECAM Warning FLAP SYS 1(2) FAULT stays: Continue with the next step.

(3) Remove the applicable flap fault relay 91CV or 93CV and use a MULTIMETER — STANDARD to do a check at the base of the holder for a ground signal on pin Z and 28VDC on pin X:

— if there is a ground signal on pin Z and 28VDC on pin X, do step (4).

— if there is no ground signal on pin Z, do step (5).

— if there is no 28VDC on pin X, do step (6). Ref. ASM 27-51-02 or Ref. ASM 27-51-03.

(4) Replace the applicable flap fault relay:

— for a FLAP SYS 1 FAULT message, replace RELAY-FLAP 1 FAULT (91CV).

— for a FLAP SYS 2 FAULT message, replace RELAY-FLAP 2 FAULT (93CV). Ref. ESPM 20-46-50.

(a) Do a check of the upper ECAM DU for the ECAM warning FLAP SYS 1 (2) FAULT:

— if the message shows, do the next step.

— if the message does not show, no more maintenance work is necessary.

(5) Interchange SFCC 1 with SFCC 2, Ref. AMM 27-51-34-000-001 and Ref. AMM 27-51-34-400-001.

(a) Do a check of the upper ECAM DU for the ECAM Warning FLAP SYS 1(2) FAULT.

(b) If the fault stays in the initial system:

1 Install the SFCCs in their initial positions.

2 Do step (6).

(c) If the fault moves to the opposite system:

1 Install the serviceable SFCC in its initial position.

2 Replace SLAT/FLAP CONTR.COMP. (21CV) or SLAT/FLAP CONTR.COMP. (22CV) that shows the fault.

3 Do a check of the upper ECAM DU for the ECAM warning FLAP SYS 1 (2) FAULT:

— If the message shows, do the next step.

— If the message does not show, no more maintenance is necessary.

(6) Do a check and repair as necessary the aircraft wiring between the applicable C/B and the applicable fault relay and then between this relay and the applicable SFCC:

— For flap system 1: Do the check between C/B 6CV and relay 91CV and between relay 91CV and SFCC 1 connector AA pin 2J Ref. ASM 27-51-02

— For flap system 2: Do the check between C/B 8CV and relay 93CV and between relay 93CV to SFCC 2 connector AA pin 2J Ref. ASM 27-51-03.

(a) If the aircraft wiring is correct and the fault continues:

— Make sure that there is a ground signal on SFCC 1 (2) connector AA pin 3J.

(b) If there is no ground signal and the fault continues:

— Do the check and repair as necessary the aircraft wiring between SFCC 1 (2) connector AA pin 3J and the DC ground point.

(c) If the aircraft wiring is correct and the fault continues:

— Replace SFCC 1 (2) (because the internal connection between pins 2J and 3J is defective) Ref. AMM 27-51-34-000-001 and Ref. AMM 27-51-34-400-001.

(d) Do the operational test of the flap system Ref. AMM 27-54-00-710-001.

(7) Check of SDAC-1 and SDAC-2

(a) At SDAC-2: Remove connector AA pin 14A (connector AD pin 14G for flap system 2).

(b) Do a check of the upper ECAM DU for the ECAM warning FLAP SYS 1 (2) FAULT.

(c) If the fault continues:

— For flap system 1: Do a wiring check between SFCC 1 connector AB pin 6D and SDAC-1 connector AA pin 14A.

— For flap system 2: Do a wiring check between SFCC 2 connector AB pin 6D and SDAC-1 connector AD pin 14G.

1 If there is a fault, do the repair.

2 If the wiring is correct, replace SDAC-1 (1WV1), Ref. AMM 31-55-34-000-001 and Ref. AMM 31-55-34-400-001.

(d) At SDAC-2: Connect connector AA pin 14A (connector AD pin 14G for flap system 2) again.

(e) Do a check of the upper ECAM DU for the ECAM warning FLAP SYS 1 (2) FAULT:

— if the message does not show, no more maintenance is necessary.

— if the message shows, do step (7)(f).

(f) If the fault continues:

— For flap system 1: Do a wiring check between SFCC 1 connector AB pin 6D and SDAC-2 connector AA pin 14A.

— For flap system 2: Do a wiring check between SFCC 2 connector AB pin 6D and SDAC-2 connector AD pin 14G.

1 If there is a fault, do the repair.

2 If the wiring is correct, replace SDAC-2 (1WV2), Ref. AMM 31-55-34-000-001 and Ref. AMM 31-55-34-400-001.

(g) Do the operational test of the flap system Ref. AMM 27-54-00-710-001 and make sure that the ECAM Warning FLAP SYS 1(2) FAULT does not show on the upper ECAM DU.

SUBTASK 27-51-00-810-112-A

C. Procedure (If SFCC Menu on the MCDU is not Available)

(1) Replace the related SFCC SLAT/FLAP CONTR.COMP. (21CV) or SLAT/FLAP CONTR.COMP. (22CV),

Ref. AMM 27-51-34-000-001 and Ref. AMM 27-51-34-400-001.

(a) Write the applicable information on the repair tag: NO RESPONSE via MCDU or SFCC MENU CANNOT LOAD.

NOTE:   This information is important for the repair shop to do the repair (as given in BAE System vSIL 067).

5. Close-up

SUBTASK 27-51-00-942-063-A

A. Put the aircraft back to its initial configuration.

(1)          Do the EIS Stop Procedure, if not done before Ref. AMM 31-60-00-860-002.

(2)          Remove the ground support and maintenance equipment, the special and standard tools and all other items.