SLAT SYSTEM 1 (2) FAULT, No CFDS Message (normal mode)

TASK 27-81-00-810-811-A
SLAT SYSTEM 1 (2) FAULT, No CFDS Message (normal mode)

1. Possible Causes

transient fault
transient fault.
external fault
VALVE BLOCK SLAT 1 [25CV]
VALVE BLOCK SLAT 2 [26CV]
RELAY-SLAT 1 FAULT [90CV]
RELAY-SLAT 2 FAULT [92CV]
SLAT/FLAP CONTR.COMP. [21CV]
SLAT/FLAP CONTR.COMP. [22CV]
aircraft wiring
SDAC-1 [1WV1]
SDAC-2 [1WV2]

2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	AR	MULTIMETER - STANDARD

B. Referenced Information

REFERENCE	DESIGNATION
TSM TASK 27-51-00-810-805-A	CSU Fault (51CV) or Fault in Wiring to SFCC 1 (2)
TSM TASK 27-81-00-810-801-A	SFCC - Slat PCU Valveblock Fault
ESPM 2046500
AMM 27-51-34-000-001	Removal of the SFCC
AMM 27-51-34-400-001	Installation of the SFCC
ASM 278102
ASM 278103
AMM 27-84-00-710-001	Operational Test of the Slat System
AMM 31-32-00-860-006	Procedure to Get Access to the SYSTEM REPORT/TEST F/CTL Page
AMM 31-55-34-000-001	Removal of the SDAC
AMM 31-55-34-400-001	Installation of the SDAC
AMM 31-60-00-860-001	EIS Start Procedure
AMM 31-60-00-860-002	EIS Stop Procedure

3. Fault Confirmation
Subtask 27-81-00-740-054-A ** ON A/C NOT FOR ALL

A. Fault Analysis
(1) Do a check of the Post Flight Report (PFR):

if the ECAM Warning message SLAT SYS 1 (2) FAULT is shown without a related CFDS message and the slats operate correctly, do the next step.

(2) Do the EIS Start Procedure AMM 31-60-00-860-001.
(3) At an MCDU, get access to the SYSTEM REPORT/TEST page AMM 31-32-00-860-006.
(a) Set F/CTL and get access to the SFCC1 and SFCC 2 menus.
(b) For each SFFC, set SLT LAST LEG REP 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 16V
SINGLE MOTOR OPERATION
LEVER OUT OF DETENT FOR MORE THAN 10 SEC

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

if one or more of the applicable messages is shown, do the fault isolation in Para. 4.A..
if none of the applicable messages are shown, do the fault isolation procedure in Para. 4.B..
if the SFCC menu on the MCDU is not available (NO RESPONSE or SFCC menu cannot load), do the fault isolation procedure in Para. 4.C..

Subtask 27-81-00-740-054-B ** ON A/C NOT FOR ALL

A. Fault Analysis
(1) Do a check of the Post Flight Report (PFR):

if the ECAM Warning message SLAT SYS 1 (2) FAULT is shown without a related SLT 1 (2) CFDS message, do the next step.
if a SLT 1 (2) CFDS message is shown, do the trouble shooting procedure related to this fault message.
if the aircraft is operated with the SFCC channel related to the E/W under MMEL, do step (4).

SYSTEM STOP DUE TO LOW PRESSURE
DC POWER INTERRUPT
DC POWER BELOW 16V
SINGLE MOTOR OPERATION
LEVER OUT OF DETENT FOR MORE THAN 10 SEC

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

if one or more of the applicable messages is shown, do the fault isolation in Para. 4.A..
if none of the applicable messages are shown, do the fault isolation procedure in Para. 4.B..

NOTE: If the aircraft was under MMEL, do a check of the Previous Leg Reports. Use the fault message which was shown before MMEL opening to do the trouble shooting. Refer to step (4).

(4) Check the PLR and identify the CFDS message which was shown before MMEL. Do the trouble shooting related to this CFDS message.

4. Fault Isolation
Subtask 27-81-00-810-060-A ** ON A/C NOT FOR ALL

A. Procedure
(1) For the applicable message from the SFCC 1 (2) Slat 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 LEVER OUT OF DETENT FOR MORE THAN 10 SEC, do step (6)

(2) SYSTEM STOP DUE TO LOW PRESSURE:

if the ECAM Warning SLAT SYS 1 (2) FAULT is shown because of a hydraulic low pressure problem (green or blue), 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 slat system AMM 27-84-00-710-001.

if a permanent fault is found do the applicable fault isolation procedure
if there is no apparent fault with the slat operation, or the operation is intermittent, do the next step.

(b) Do the trouble shooting procedure for the applicable VALVE BLOCK SLAT 1 [25CV] or VALVE BLOCK SLAT 2 [26CV] , (Ref. TSM TASK 27-81-00-810-801).

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 conditon can cause the slats to operate intermittently.

(3) DC POWER INTERRUPT:

if the ECAM Warning SLAT SYS 1 (2) FAULT is 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 poweris less than 14VDC for more than 40 msec.

(4) DC POWER BELOW 16V:

if the ECAM Warning SLAT SYS 1 (2) FAULT is shown because the DC power is 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:

if the ECAM Warning SLAT SYS 1 (2) FAULT is shown because the slats operate momentarily on one motor only, no more maintenance work is necessary
if there is no apparent slat motor problem, do step (7)
if the message LEVER OUT OF DETENT FOR MORE THAN 10 SEC is also shown on the LLR, do the next step.

(6) LEVER OUT OF DETENT FOR MORE THAN 10 SEC:

if the ECAM Warning SLAT SYS 1 (2) FAULT is shown because the flap control lever is sensed out of detent by each system, do step (7)
if the ECAM Warning SLAT SYS 1 (2) FAULT is shown because the flap control lever is sensed out of detent by one system only, do the next step.

(a) Do a check of the CSU and its wiring to the SFCC, which identified the out of detent condition (Ref. TSM TASK 27-51-00-810-805).

NOTE: When one system senses that the flap control lever is out of detent, but the other system senses a correct condition, then the fault is usually in the CSU.

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

Subtask 27-81-00-810-060-B ** ON A/C NOT FOR ALL

A. Procedure
(1) For the applicable message from the SFCC 1 (2) Slat 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)

(2) SYSTEM STOP DUE TO LOW PRESSURE:

if the ECAM Warning SLAT SYS 1 (2) FAULT is shown because of a hydraulic low pressure problem (green or blue), 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 slat system AMM 27-84-00-710-001.

if a permanent fault is found do the applicable fault isolation procedure
if there is no apparent fault with the slat operation, or the operation is intermittent, do the next step.

(b) Do the trouble shooting procedure for the applicable VALVE BLOCK SLAT 1 [25CV] or VALVE BLOCK SLAT 2 [26CV] , (Ref. TSM TASK 27-81-00-810-801).

(3) DC POWER INTERRUPT:

if the ECAM Warning SLAT SYS 1 (2) FAULT is shown because of a DC power interrupt, no more maintenance work is necessary
if there is no apparent DC power problem, do step (6).

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

(4) DC POWER BELOW 16V:

if the ECAM Warning SLAT SYS 1 (2) FAULT is shown because the DC power is less than 16.5 VDC, no more maintenance work is necessary
if there is no apparent DC power problem, do step (6).

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:

if the ECAM Warning SLAT SYS 1 (2) FAULT is shown because the slats operate momentarily on one motor only, no more maintenance work is necessary
if there is no apparent slat motor problem, do step (6).

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

Subtask 27-81-00-810-090-A

B. Procedure
(1) If the ECAM warning SLAT SYS 1 (2) FAULT is shown, but there is no related CFDS message on the PFR, or in the SFCC 1 (2) Slat LLR, do step (2).
(2) Remove the applicable slat fault relay 90CV or 92CV 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 (3)
if there is no ground signal on pin Z, do step (4)
if there is no 28VDC on pin X, do step (6)
ASM 278102 or ASM 278103.

(3) Replace the applicable slat fault relay:

for a SLAT SYS 1 FAULT message, replace RELAY-SLAT 1 FAULT [90CV]
for a SLAT SYS 2 FAULT message, replace RELAY-SLAT 2 FAULT [92CV]
ESPM 2046500.

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

if the message is shows, do step (4)
if the message does not show, no more maintenance work is necessary.

(4) Interchange SFCC1 with SFCC 2, AMM 27-51-34-000-001 and AMM 27-51-34-400-001.
(a) Do a check of the upper ECAM DU for the ECAM Warning SLAT SYS 1(2) FAULT:

if the fault moves to the opposite system, do step (5)
if the fault stays in the initial system, do step (6).

(5) Replace the SLAT/FLAP CONTR.COMP. [21CV] or SLAT/FLAP CONTR.COMP. [22CV] identified in the ECAM Warning message shown in step (4)(a), AMM 27-51-34-000-001 and AMM 27-51-34-400-001:
(a) Do a check of the upper ECAM DU for the ECAM Warning SLAT SYS 1 (2) FAULT:

if the message shows, do step (6)
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 slat system 1: Do the check between C/B 5CV and relay 90CV and between relay 90CV and SFCC1 connector AD pin 2J ASM 278102
For slat system 2: Do the check between C/B 7CV and relay 92CV and between relay 92CV and SFCC2 connector AD pin 2J ASM 278103

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

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

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

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

(c) Do the operational test of the slat system AMM 27-84-00-710-001 and make sure that the ECAM Warning SLAT SYS 1(2) FAULT does not show on the upper ECAM DU.
(7) Check of SDAC-1 and SDAC-2
(a) At SDAC-2: Remove connector AA pin 13A (connector AB pin 13G for slat system 2).
(b) Do a check of the upper ECAM DU for the ECAM warning SLAT SYS 1 (2) FAULT.
(c) If the fault continues:

For slat system 1: Do a wiring check between SFCC 1 connector AE pin 6D and SDAC-1 connector AA pin 13A.
For slat system 2: Do a wiring check between SFCC 2 connector AE pin 6D and SDAC-1 connector AB pin 13G.

1 If there is a fault, do the repair.
2 If the wiring is correct, replace SDAC-1 [1WV1] ,
AMM 31-55-34-000-001 and AMM 31-55-34-400-001.
(d) At SDAC-2: Connect connector AA pin 13A (connector AB pin 13G for slat system 2) again.
(e) Do a check of the upper ECAM DU for the ECAM Warning SLAT 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 slat system 1: Do a wiring check between SFCC 1 connector AE pin 6D and SDAC-2 connector AA pin 13A.
For slat system 2: Do a wiring check between SFCC 2 connector AE pin 6D and SDAC-2 connector AB pin 13G.

1 If there is a fault, do the repair.
2 If the wiring is correct, replace SDAC-2 [1WV2] ,
AMM 31-55-34-000-001 and AMM 31-55-34-400-001.
(g) Do the operational test of the slat system AMM 27-84-00-710-001 and make sure that the ECAM Warning SLAT SYS 1(2) FAULT does not show on the upper ECAM DU.

Subtask 27-81-00-810-093-A ** ON A/C NOT FOR ALL

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] ,
AMM 27-51-34-000-001 and 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 27-81-00-942-060-A

A. Put the aircraft back to its initial configuration.
(1) Do the EIS Stop Procedure, if not done before AMM 31-60-00-860-002.
(2) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

[Rev.8 from Aug 2018] 2026.04.04 04:27:47 UTC