- replace the Spoiler Servo Control in relation to the wrong indication. SERVO CTL-SPLR1, L G (31CE1), SERVO CTL-SPLR1, R G (31CE2), for spoiler 1 SERVO CTL-SPLR2, L Y (31CE3), SERVO CTL-SPLR2, R Y (31CE4), for spoiler 2 SERVO CTL-SPLR3, L B (31CE5), SERVO CTL-SPLR3, R B (31CE6), for spoiler 3 SERVO CTL-SPLR4, L Y (31CE7), SERVO CTL-SPLR4, R Y (31CE8) for spoiler 4 SERVO CTL-SPLR5, L G (31CE9), SERVO CTL-SPLR5, R G (31CE10) for spoiler 5 (Ref. AMM TASK 27-64-51-000-004) and (Ref. AMM TASK 27-64-51-400-004).
(2) If the fault continues:
- do a check and repair the wiring of the LVDT POS Signal from the spoiler servocontrol to the SEC COM and MON parts (Ref. ASM 27-94/02), (Ref. ASM 27-94/04).
5. Close-up
________
A. Do the test given in Para 3.
SLATS ELECTRICAL CONTROL AND MONITORING - FAULT ISOLATION PROCEDURES
____________________________________________________________________
TASK 27-81-00-810-801
SFCC - Slat PCU Valveblock Fault
WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU
_______ START A TASK ON OR NEAR:
- THE FLIGHT CONTROLS
- THE FLIGHT CONTROL SURFACES
- THE LANDING GEAR AND THE RELATED DOORS
- COMPONENTS THAT MOVE.
WARNING : MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROL SURFACES ARE
_______ CLEAR BEFORE YOU PRESSURIZE/DEPRESSURIZE A HYDRAULIC SYSTEM.
WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING
_______ GEAR.
1. Possible Causes
_______________
- SFCC-1 (21CV)
- SFCC-2 (22CV)
- VALVE BLOCK SLAT 1 (25CV)
- VALVE BLOCK SLAT 2 (26CV)
- solenoid valve
- valve block filters
- aircraft wiring
2. Job Set-up Information
______________________
A. Fixtures, Tools, Test and Support Equipment
-------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
No specific 45VDC Isolation Tester No specific 1 MEGOHMMETER 100 MOHMS - MEASURING VOLTAGE 45VDC No specific 1 MULTIMETER - STANDARD
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CES
B. 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 27-80-00-866-004 Extending the Slats on the Ground AMM 27-80-00-866-005 Retracting the Slats on the Ground AMM 27-84-53-000-001 Removal of the Valve Blocks 25CV, 26CV of the Power
Control Unit (Slat) AMM 27-84-53-000-002 Removal of the Solenoid Valves of the Power Control
Unit (Slat) AMM 27-84-53-000-003 Removal of the Filters of the Valve Blocks AMM 27-84-53-400-001 Installation of the Valve Blocks 25CV, 26CV of the
Power Control Unit (Slat) AMM 27-84-53-400-002 Installation of the Solenoid Valves of the Power Control Unit (Slat)
AMM 27-84-53-400-003 Installation of the Filters of the Valve Blocks R AMM 31-32-00-860-006 Procedure to Get Access to the SYSTEM REPORT/TEST R F/CTL Page
ASM 27-81/02
ASM 27-81/03
3. Fault Confirmation
__________________
A. Test
(1) Make sure that the Post Flight Report does not show any hydraulic system faults.
(2) Move the slats (Ref. AMM TASK 27-80-00-866-004) and (Ref. AMM TASK 27-80-00-866-005).
R (a) Examine the SFCC, SLT ON GROUND FAULTS page for a PCU valve block R message.
R (3) If a valve block message is shown, or the A/C has had this fault R before, do the fault isolation procedure.
4. Fault Isolation
_______________
A. Procedure. R CAUTION: DO NOT SHORT CIRCUIT THE WIRING TO THE SOLENOID VALVES. R DAMAGE TO THE SFCC CAN OCCUR
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(1) Do a check of the circuit resistance and the circuit isolation of the extend and retract solenoids on each slat system PCU valve block (25CV; 26CV) as follows:
(a) Get access to the electrical connector on each valve block (Ref. AMM TASK 27-84-53-000-001).
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