Flaps - SFCC Flap Channel Failure

TASK 27-51-00-810-845-A
Flaps - SFCC Flap Channel Failure

1. Possible Causes

SLAT/FLAP CONTR.COMP. [21CV]
SLAT/FLAP CONTR.COMP. [22CV]

2. Job Set-up Information
A. Referenced Information

REFERENCE	DESIGNATION
TSM TASK 27-51-00-810-852-A	Flaps - SFCC 1 (2) Gives PCU Valveblock 23CV (24CV) Valve Sensor Message
AMM 27-51-00-710-001	Operational Test of the Wing Tip Brake and the Pressure Off Brake
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
AMM 27-51-34-400-001	Installation of the SFCC
AMM 27-54-00-710-001	Operational Test of the Flap System
AMM 31-32-00-860-006	Procedure to Get Access to the SYSTEM REPORT/TEST F/CTL Page
MCDU-Display ** ON A/C NOT FOR ALL
SFCC Test Result ** ON A/C NOT FOR ALL

3. Fault Confirmation
Subtask 27-51-00-740-071-A

A. Fault Monitor Action
(1) Possible causes of the SFCC 1 (2) reported fault are as follows:
(a) The non-validity of the synchro-excitation power generation.
(b) The SFCC primary/secondary internal power supply fault.
(c) Automatic integrity test detected fault conditions:

processor checks
ROM and RAM tests
processor I/O tests
consolidation logic tests.

(d) A cross lane monitoring fault.

Subtask 27-51-00-740-074-A ** ON A/C NOT FOR ALL

B. Fault Confirmation
(1) Set the MCDU to the MENU MODE and access the LAST LEG REPORT for a list of fault messages AMM 31-32-00-860-006.
(2) Do a BITE test with the applicable SFCC AMM 27-51-00-740-002.
(3) If the MCDU shows a failure message, do the Fault Isolation procedure.

Subtask 27-51-00-740-074-B ** ON A/C NOT FOR ALL

B. Fault Confirmation

MCDU-Display ** ON A/C NOT FOR ALL

SFCC Test Result ** ON A/C NOT FOR ALL

(1) Set the MCDU to the MAIN MENU of the related SFCC and get access to the TROUBLESHOOTING DATA page AMM 31-32-00-860-006.
(a) If the failure message SFCC-1 (SFCC-2) shows with the fault code 004 AND
the failure message SINGLE MOTOR OPERATION shows at the same time
(not more than one minute between the two messages):

No further action is necessary.
Leave the MCDU MENU MODE. This will automatically reset the SFCC (the fault messages will not show again).

(2) Do a BITE test with the applicable SFCC AMM 27-51-00-740-002.

NOTE: If the aircraft has a Diehl SFCC and if you find at the SFCC FAILURE TEST REPORT LANE B the fault code FE for row 4 and column 5 - refer to the attached figure, do not replace the SFCC at fault as a first action. Do Fault isolation 4.B.(1) to confirm that the opposite SFCC is defective.

(3) If the MCDU shows a failure message, do the Fault Isolation procedure.

4. Fault Isolation
Subtask 27-51-00-865-076-A

A. Table of the circuit breakers used in this procedure:

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C ALL
49VU	FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1	6CV	B07
121VU	FLIGHT CONTROLS/FLP/CTL AND/MONG/SYS2	8CV	Q21

Subtask 27-51-00-810-097-A

B. Procedure
(1) Set the MCDU to the MAIN MENU of the related SFCC and get access to the TROUBLESHOOTING DATA page AMM 31-32-00-860-006.
(a) If the failure message SFCC-1 (SFCC-2) shows with the fault code 005 (for a BAE SFCC) or fault code 005 or 020 (for a Diehl SFCC), do the TSM-Procedure (Ref. TSM TASK 27-51-00-810-852).
(b) If the fault continues, do the next step.
(2) Set the MCDU to the MAIN MENU of the related SFCC and get access to the TROUBLESHOOTING DATA page AMM 31-32-00-860-006.
(a) If the failure message SFCC-1 (SFCC-2) shows with the fault code related to the failed Automatic Integrity Test (AIT):

fault code 036 (for a BAE SFCC) or
fault code 001 (for a Diehl SFCC),

do the steps that follow:
1 Temporarily deactivate the SFCC that does not show this failure message:

Open, safety and tag the circuit breaker 6CV for SFCC-1 Flap channel OR 8CV for SFCC-2 Flap channel.

2 Do a BITE test with the SFCC that shows the fault AMM 27-51-00-740-002.
3 If the BITE test is o.k., replace the deactivated SFCC,
AMM 27-51-34-000-001 and AMM 27-51-34-400-001.
4 Remove the safety clip and the tag and close the related circuit breaker again.
5 Do a BITE test with the SFCC that shows the fault AMM 27-51-00-740-002.
(b) If the fault continues, do the next step.
(3) Interchange SFCC-1 with SFCC-2, AMM 27-51-34-000-001 and AMM 27-51-34-400-001.
(a) If the fault moves with the SFCC:
1 Put the serviceable SFCC back in its initial location.
2 Replace the defective SLAT/FLAP CONTR.COMP. [21CV] or SLAT/FLAP CONTR.COMP. [22CV] .
(b) If the fault does not move with the SFCC or there is no fault:

Install the SFCCs in their initial positions.
Do the next step.

(4) Do the Operational Test of the Flap System AMM 27-54-00-710-001.
(a) If there is a fault, interchange SFCC-1 with SFCC-2.
(b) Do the Operational Test of the Flap System again AMM 27-54-00-710-001.
(c) If the fault moves with the SFCC:
1 Put the serviceable SFCC back in its initial location.
2 Replace the defective SLAT/FLAP CONTR.COMP. [21CV] or SLAT/FLAP CONTR.COMP. [22CV] .
(d) If the fault does not move with the SFCC:
1 Install the SFCCs in their initial positions.
2 Do the related system trouble-shooting procedure.
(5) If there is no fault, do the Operational Test of the Wing-Tip Brake and the Pressure-Off Brake AMM 27-51-00-710-001.
(6) If there is a fault, interchange SFCC-1 with SFCC-2.
(a) Do the Operational Test of the Wing-Tip Brake and the Pressure-Off Brake again.
(b) If the fault moves with the SFCC:
1 Put the serviceable SFCC back in its initial location.
2 Replace the defective SLAT/FLAP CONTR.COMP. [21CV] or SLAT/FLAP CONTR.COMP. [22CV] .
(c) If the fault does not move with the SFCC:
1 Install the SFCCs in their initial positions.
2 Do the related system trouble-shooting procedure.

[Rev.8 from Aug 2018] 2026.04.04 04:27:40 UTC