3. Fault Confirmation
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A. Job Set-up
Aircraft Maintenance Configuration
(1) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
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(2) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001).
(3) Pressurize the aircraft hydraulic systems (Ref. AMM TASK 29-24-00-863-001) (Ref. AMM TASK 29-23-00-863-001).
(4) On the overhead panel 23VU:
- make sure that the FLT CTL/ELAC1 and FLT CTL/SEC1 pushbutton switches are pushed (the OFF legends of these pushbutton switches are off).
(5) On the overhead panel 24VU:
- make sure that the FLT CTL/ELAC2 and FLT CTL/SEC2 pushbutton switches are pushed (the OFF legends of these pushbutton switches are off).
B. Test
-------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------
1. On the center pedestal: On the SD:
- move the pitch-trim control - the PITCH TRIM Indicator shows: wheels in the nose-up direction 13.5 +0.4 -0.6 deg. to the mechanical stop.
2. On the center pedestal: On the SD:
- move the pitch-trim control - the PITCH TRIM Indicator shows: wheels in the nose-down 4 +0.3 -0.5 deg.. direction to the mechanical stops.
4. Fault Isolation
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A. On the SD, the THS position is in the tolerances:
(1) Install the TOOL - ZERO POSITIONING, THS ACTUATOR (0U190834) on the screw jack of the THS actuator.
(2) Install the PIN - RIGGING (0U190360) on the input lever of the THS actuator.
(3) Do the adjustment of the THS control cables (Ref. AMM TASK 27-41-00-820-002).
(4) If the fault continues:
- remove and install in the correct position the pitch-trim control mechanism (Ref. AMM TASK 27-41-41-000-001) and (Ref. AMM TASK 27-41-41-400-001).
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(5) Remove the TOOL - ZERO POSITIONING, THS ACTUATOR (0U190834) and the PIN - RIGGING (0U190360).
B. On the SD, the THS position is out of the tolerances:
(1) Install the TOOL - ZERO POSITIONING, THS ACTUATOR (0U190834) on the screw jack of the THS actuator.
(2) Install the PIN - RIGGING (0U190360) on the input lever of the THS actuator.
(3) Do the adjustment of the THS zero position (Ref. AMM TASK 27-41-00-820-001).
(4) Do the adjustment of the THS control cables (Ref. AMM TASK 27-41-00-820-002).
(5) Remove and install in the correct position the pitch-trim control mechanism (Ref. AMM TASK 27-41-41-000-001) and (Ref. AMM TASK 27-41-41-400-001).
(6) If the fault continues:
- replace the ACTUATOR-THS (9CE) (Ref. AMM TASK 27-44-51-000-001) and (Ref. AMM TASK 27-44-51-400-001)
(7) Remove the TOOL - ZERO POSITIONING, THS ACTUATOR (0U190834) and PIN -RIGGING (0U190360)
C. Test Do the test given in Para. 3.
Mechanical Latched Indicator R Figure 202/TASK 27-40-00-991-002
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FLAPS ELECTRICAL CONTROL AND MONITORING - FAULT ISOLATION PROCEDURES
____________________________________________________________________
TASK 27-51-00-810-802
R R SFCC - FLAP 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.
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 飛行操縱 1(82)
