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3. Fault Confirmation
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A. SFCC system test.
(1) Do a BITE test on the SFCC 1 (2) (Ref. AMM TASK 27-51-00-740-002).
(2) If the fault data "APPU disconnected or faulty and WTB set" is displayed, page block 301 Table 7 gives the SFCC test menu selection details.
(3) Do the fault isolation.
4. Fault Isolation
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A. Procedure.
(1) Swop the SFCC 1 with the SFCC 2.
(a) Wait 60 seconds and examine the UPPER ECAM and the SD FLT/CTL page for the fault warnings and status data.
(b) Access the FLP ON GROUND FAULTS and do a check for faults.
(2) If the fault moves with the SFCC, replace the applicable SFCC-1 (21CV) SFCC-2 (22CV) (Ref. AMM TASK 27-51-34-000-001) (Ref. AMM TASK 27-51-34-400-001).
(3) If the fault does not move to the other SFCC.
(a) Replace the applicable APPU-L(R) FLAP 29CV (30CV) (Ref. AMM TASK 27-51-18-000-001) (Ref. AMM TASK 27-51-18-400-001).
(b) Access the FLP ON GROUND FAULTS and do a check for faults.
(4) If the fault stays.
(a) Use an ARINC Connector Breakout Box and do a check of the A/C Wiring between the SFCC 1 (2) and the APPU connectors 29CV-A (30CV-B) (Ref. ASM 27-51/06) (Ref. ASM 27-51/07).
(b) Do the repair.
(5) Do the SYSTEM TEST (BITE) (Ref. para 3.A.(1)).
(6) If the BITE test shows NO FAULTS.
(7) Do a check of the UPPER ECAM and the SD FLT/CLT page for the fault warning and status data.
(8) If the fault warning and status data fields are clear.
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(9) Do the operational test of the flap system (Ref. AMM TASK 27-54-00-710-001).
(10) Access the FLP ON GROUND FAULTS and make sure there are no faults shown.
5. Close-up
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A. Remove the ground support and maintenance equipment, the special and standard tools and all other items.
B. Put the aircraft back to its initial configuration.
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CES Flap System Jam.
WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU
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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
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CLEAR BEFORE YOU PRESSURIZE/DEPRESSURIZE A HYDRAULIC SYSTEM.
1. Possible Causes
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- POWER CONTROL UNIT (6201CM)
- BRAKE-L WING TIP (33CV)
- BRAKE-R WING TIP (34CV)
- Transmission Assembly
- Rotary Actuators
- PCU hydraulic motor
2. Job Set-up Information
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A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 27-50-00-866-010 Reset of the Torque Limiters of the Flap System on
the Ground
AMM 27-51-51-000-001 Removal of the Flap Wing-Tip Brake
AMM 27-51-51-400-001 Installation of the Flap Wing-Tip Brake
AMM 27-54-00-200-001 Detailed Visual Inspection of the Transmission
Assembly (Including Part of the Transmission in Zone
140) AMM 27-54-00-710-001 Operational Test of the Flap System AMM 27-54-49-000-001 Removal of the Flap Track 1 Actuator 6205CM(6255CM) AMM 27-54-49-400-001 Installation of the Flap Track 1 Actuator
6205CM(6255CM) AMM 27-54-51-000-001 Removal of the Power Control Unit 6201CM of the Flap System AMM 27-54-51-400-001 Installation of the Power Control Unit 6201CM of the Flap System
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 飛行操縱 1(90)
