17. Push the line key SYSTEM STATUS FLP >. - the MCDU shows SFCC 1 SYSTEM STATUSFLAP CHECK LH DRIVE INTEGRITY.
18. Push the line key < RETURN frequently until the SYSTEM REPORT/TEST - F/CTL menu is shown.
19. At the LH flaps: - move the actuating rod into the normal position.
20. Open the circuit breakers 6CV and 8CV. The SFCC 1 and SFCC 2 are de-energized.
21. Close the circuit breakers 6CV and 8CV. The failure conditions are reset.
R R R On the upper ECAM DU: - the F/CTL FLAPS LOCKED message goes out - the ALIGNMENT FAULT message goes out.
22. Push the line key F/CTL >. - the SYSTEM REPORT/TEST - F/CTL menu shows.
23. Push the line key < SFCC 1. - the SFCC 1 menu shows.
NOTE : Alternatively you can use the SFCC 2 menu but do not change SFCC
____
menu's during the test procedure.
24. Push the line key SYSTEM STATUS - the MCDU shows SFCC 1 SYSTEM STATUS FLP >. FLAP NO FAULTS.
-------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------25. Push the line key < RETURN frequently until the SYSTEM REPORT/TEST - F/CTL menu is shown.
26. Do the steps 1 thru 25 again for the RH flap interconnecting strut.
27. Push the line key < RETURN frequently until the CFDS menu page is shown.
5. Close-up________
Subtask 27-51-00-865-059
A. Open, safety and tag this(these) circuit breaker(s):
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------49VU FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1 6CV B07 121VU FLIGHT CONTROLS/FLP/CTL AND/MONG/SYS2 8CV Q21
R Subtask 27-51-00-420-053-A
R B. Connect the Interconnecting Strut
R R R (1) Hold the rod eye-ends of the interconnecting struts in position to the outer flaps. Adjust the interconnecting struts if necessary (Ref. TASK 27-51-44-400-001).
R (2) Install the bolts (5), the washer (4) and the nuts (3).
R R (3) TORQUE the nuts (3) to between 1.1 and 1.7 m.daN (97.34 and 150.44 lbf.in).
R (4) Install the new cotter pins (2).
R R R R R (5) Apply a layer of STORAGE PRESERVATION (Material No. 15-007) to: - the head of the bolt (5) - the nut (3) - the washer (4) - the cotter pin (2).
Subtask 27-51-00-410-051
C. Close Access
(1)
Make sure that the work area is clean and clear of tool(s) and other items.
(2)
Install the lower kink seals of the two wings (Ref. TASK 27-54-61-400-006).
Subtask 27-51-00-865-060
D. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 6CV, 8CV.
Subtask 27-51-00-860-055
E. Aircraft Configuration
WARNING : OBEY THE HYDRAULIC SAFETY PROCEDURES.
_______
(1)
Pressurize the Green and the Yellow hydraulic systems (Ref. TASK 29-10-00-863-001) and (Ref. TASK 29-10-00-863-002).
(2)
Retract the flaps fully (Ref. TASK 27-50-00-866-009).
(3)
Do the EIS stop procedure
(Ref. TASK 31-60-00-860-002).
(4)
De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).
Subtask 27-51-00-942-067
F. Removal of Equipment
(1)
Remove the safety barriers.
(2)
Remove the warning notice(s).
(3)
Remove the ground support and maintenance equipment, the special and standard tools and all other items.
1EFF : ALL 1 27-51-00Page 546 1 1 May 01/04R 1 1 1CES 1
TASK 27-51-00-750-001
Automatic Integrity Test of the Slat and Flap Control Computers
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 GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING
_______ GEAR.
1. Reason for the Job
__________________
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本文鏈接地址：A320飛機維護手冊 AMM FLIGHT CONTROLS 飛行操縱4(51)
