B. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 27-54-00-710-001 Operational Test of the Flap System AMM 27-54-52-000-001 Removal of the Pressure-Off Brake of the Flap Power Control Unit AMM 27-54-52-400-001 Installation of the Pressure-Off Brake of the Flap Power Control Unit AMM 27-54-53-000-001 Removal of the Valve Blocks 23CV, 24CV of the Power
Control Unit (Flap) AMM 27-54-53-000-003 Removal of the Filters of the Valve Blocks AMM 27-54-53-400-001 Installation of the Valve Blocks 23CV, 24CV of the
Power Control Unit (Flap)
May 01/04R CES
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 27-54-53-400-003 Installation of the Filters of the Valve Blocks
ASM 27-51/02
ASM 27-51/03
3. Fault Confirmation
__________________
A. Table of the circuit breakers used in this procedure:
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------49VU FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1 6CV B07 121VU FLIGHT CONTROLS/FLP/CTL AND/MONG/SYS2 8CV Q21
B. SFCC Reset and Initialization.
(1) At the circuit breakers.
(a) Open the circuit breakers.
(b) Wait for 3 seconds and close the circuit breakers.
(c) Wait for 60 seconds
(d) Check the UPPER ECAM and the SD FLT/CTL page for the fault warnings.
(e) If the ECAM warning message clears, set the MCDU to MENU MODE and access the FLP ON GROUND FAULTS page and make sure that the ground log is clear.
(f) If the ECAM warning and the fault message stays displayed do the fault isolation.
4. Fault Isolation
_______________
A. Procedure.
(1) Do the operational test of the flaps system (Ref. AMM TASK 27-54-00-710-001)
NOTE : : For this operational test it is necessary that the Power
____
Tranafer Unit (PTU) be in operation.
(2) During the procedure test, if the fault gives a slow extension or slow retraction and there is no Hyd. fault.
「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 ∞∞27-51-00∞∞∞∞∞∞∞∞∞∞Page 259
May 01/04R CES
(3) Isolate the PCU fault, do a comparison between both motor speeds:
- de-activate SFCC 1 and move the flaps, time the extension.
- energize SFCC 1 and de-activate SFCC 2.
- move the flaps and time the extension.
(a) The time difference shows the slowest system.
(b) The slowest system is the PCU with possible internal friction.
(c) Go Para.4.A.(12).
(4) During the procedure at Para.4.A.(3).
(a) If one SFCC is energized and a flap extension is commanded and a system jam occurs.
(b) Do a ch e check of the POB solenoid circuit.
(5) Do a check of the POB electrical circuit
(a) Refer to: (Ref. AMM TASK 27-54-52-000-001) Figure 401/Task 27-54-52-991-001.
(b) Find the electrical connector for the VALVE BLOCK-FLAP 1 (23CV) or VALVE BLOCK-FLAP 2 (24CV) POB solenoids and release.
(c) Do a check of the aircraft wiring from the SFCC ARINC tray interface to the POB solenoid electrical connectors 23CV-A/24CV-A. (Ref. ASM 27-51/02) (Ref. ASM 27-51/03)
(d) If there is a wiring/interface fault do the repair.
(6) If the A/C wiring is satisfactory, do a check of the circuit resistance and circuit isolation of the fault related solenoid valve.
(a) On the valveblock use a Multimeter and do a check of the
resistance between
For SFCC1 -23CV = POB pins L and K
SM/275102S01
For SFCC2 -24CV = POB pins L and K SM/275103S01
(b) The reistance for the POB solenoid 667C0000-02 must be between 71 ohms and 84 ohms
(c) The reistance for the POB solenoid 903A0000-01 must be between 53 ohms and 60 ohms
「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 ∞∞27-51-00∞∞∞∞∞∞∞∞∞∞Page 260
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