D.
Prepare for Removal
S 864-002
(1) Do this task: "Supply Electrical Power" (AMM 24-22-00/201).
S 864-003
CAUTION: DO NOT ELECTRICALLY EXTEND OR RETRACT THE FLAPS MORE THAN ONE
_______ TIME IN 5 MINUTES. DAMAGE TO THE MOTOR CAN OCCUR IF THE MOTOR BECOMES TOO HOT.
(2)
Electrically extend the flaps approximately 1/3:
(a)
Push the ALTN FLAPS ARM switch on the pilot's center panel to put the flap system in alternate control.
(b)
Set the ALTN FLAPS EXT/RET switch on the pilot's center panel in the EXT position.
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S 494-004 WARNING: YOU MUST CAREFULLY DO THE STEPS IN THE TASK BELOW TO INSTALL
_______
THE LE FLAP SAFETY LOCKS. THE LE FLAPS CAN DO NOT INSTALL THE SAFETY LOCKS CORRECTLY. INJURY TO PERSONS OR DAMAGE TO EQUIPMENT. MOVE QUICKLY IF YOUTHIS CAN CAUSE
(3) Do this task: "Extended Leading Edge Flap Deact Lock Installation" (AMM 27-81-00/201). iva tion and Safety
S 864-005 (4) Do this task if electrical power is not necessar Power Removal" (AMM 24-22-00/201). y: "Electrical
S 864-006
(5)
For applicable system, open these circuit breakers and attach DO-NOT-CLOSE tags:
(a)
P6 Main Power Distribution Panel 1) 6L21 LE FLAP ELEC CONT GRP B DRIVE 1 2) 6L22 LE FLAP ELEC CONT GRP A DRIVE 2 3) 6L23 LE FLAP ELEC CONT GRP A DRIVE 3 4) 6L24 LE FLAP ELEC CONT GRP A DRIVE 4 5) 6E3 PRIM LE FLAP CONT GRP A AC 6) 6E4 PRIM LE FLAP CONT GRP A DC 7) 6E5 PRIM LE FLAP CONT GRP B AC 8) 6E6 PRIM LE FLAP CONT GRP B DC
(b)
P7 Overhead Circuit Breaker Panel 1) 7C10 FLT CONT ELEC 2L-AC 2) 7C11 FLT CONT ELEC 2L-DC 3) 7C12 FLT CONT ELEC 1L-AC 4) 7C13 FLT CONT ELEC 1L-DC 5) 7C14 FLT CONT ELEC 1R-AC 6) 7C15 FLT CONT ELEC 1R-DC 7) 7C16 FLT CONT ELEC 2R-AC 8) 7C17 FLT CONT ELEC 2R-DC
(c)
P414 Power Distribution Center - Left 1) 414A5 LE FLAP ELEC DRIVE 1 2) 414A2 LE FLAP ELEC DRIVE 4
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747-400 MAINTENANCE MANUAL
(d)
P415 Power Distribution Center - Right 1) 415M35 LE FLAP ELEC DRIVE 2 2) 415B32 LE FLAP ELEC DRIVE 3
E.
Procedure
S 024-007
(1)
Remove the rotary actuator (Fig. 401):
(a)
Remove the screws (13) that attach the drive shaft coupling (14) to the actuator input shaft.
(b)
Disengage the drive shaft (7).
(c)
Remove the bolts (3 and 10) that attach the rotary actuator to the structure.
(d)
Move the rotary actuator (1) axially to disengage the actuator splines (2 and 9) from the flap linkage and the drive shaft (7).
(e)
Remove the rotary actuator (1) from the airplane.
(f)
Remove the bearing retainer (8) from the airplane.
TASK 27-81-07-404-008
3. Variable Camber Flaps Rotary Actuator Installation__________________________________________________
A. Special Tools and Equipment
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本文鏈接地址：747-400 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 7(136)
