S 864-004
(4)
Remove the pressure from hydraulic system No. 4 (Ref 29-11-00/201).
D.
Remove the Door Actuator.
S 024-005
(1)
Remove the actuator (Fig. 401):
(a)
Disconnect the hydraulic hoses from the actuator.
(b)
Install a plug on the hydraulic hoses.
(c)
Hold the actuator.
CAUTION:_______HOLD THE BOLT WHEN YOU LOOSEN IT. IF YOU PERMIT THE BOLT TO TURN, IT CAN CAUSE DAMAGE TO THE CLEVIS LOCKING DEVICE.
(d)
Remove the bolt (5) that attaches the rod end to the actuator beam.
(e)
Remove the bolt (21) that attaches the actuator release rod (17) to the actuator release cam (15).
(f)
Disconnect the actuator release rod (17) from the actuator release cam (15).
(g)
Remove the actuator release cam (15).
NOTE: Make a note of the positions of the shims and the
____
washers.
(h)
Hold the actuator.
CAUTION:_______HOLD THE BOLT WHEN YOU LOOSEN IT. IF YOU PERMIT THE BOLT TO TURN, IT CAN CAUSE DAMAGE TO THE CLEVIS LOCKING DEVICE.
(i)
Remove the head end bolt (14).
(j)
Remove the actuator (1).
(k)
Remove the actuator release lever (9) from the lock shaft that has splines on the actuator.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 747-400 MAINTENANCE MANUAL
SUPPORT RADIUS ROD
RADIUS ROD
SEE C
SEE A BEAM ACTUATOR DOOR
2. WASHER SELF-LOCKING NUT BUSHING4. 3. SEE B DOOR WING GEAR 1. DOOR ACTUATOR
A
5. BOLT
STRUCTURE NYLON WASHER (THICK) NYLON WASHER (THIN) NUT WASHER 7. 6. 8. 2.
7. (THICK) WASHER NYLON B 6. (THIN) WASHER NYLON BOLT WASHER COTTER PIN NUT ACTUATOR RELEASE ROD 16. 17. 20. 19. 18. 21. NUT 15. ACTUATOR RELEASE CAM HEAD END BOLT BUSHING C 14. 13. 12. 11. 10. THIN WASHER BOLT NUT ACTUATOR LEVER RELEASE (HEAD END) ACTUATOR 9.
Wing Landing Gear Door Actuator Installation Figure 401
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
RELEASE CAM
NO. INDEX PART NAME DIM. DESIGN LIMITS WEAR LIMITS WORN PART REPLACE PART WORN REPAIR INSTR. REPAIR
DIAMETER ALLOWEDDIM. WEAR MAX ANCE CLEAR-DIAM
MIN MAX
1 BEARING ID 1.2495 1.2500 1.2690 0.020 X
BOLT OD 1.2485 1.2490 1.2295 1 X 2
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
DIFFERENTIAL SAFETY VALVE ASSEMBLY
SEE C
DIFFERENTIAL OUTPUT ROD
SEE A
DOOR ACTUATOR
ACTUATOR
SEE B
BEAM FWD
NOTE: WHEN YOU MEASURE THE DIMENSIONS,
MAKE SURE THE HEAD END BOLT IS FWD
AT A RIGHT ANGLE TO THE STRUCTURAL
BRACKET TO |1 DEGREE.
A
ACTUATOR RELEASE LEVER
ACTUATOR ACTUATOR
CAM 0.07-0.09 INCH (1.78-2.29mm)
ACTUATOR RELEASE ROD
ACTUATOR RELEASE ROD
CAM
ROLLER
HEAD END
0.18-0.20 INCH
BOLT HEAD END
(4.57-5.08mm)
BOLT
ACTUATOR LOCK RELEASE ACTUATOR LOCK RELEASE
(RIGHT WING LANDING GEAR DOOR) (LEFT WING LANDING GEAR DOOR)
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本文鏈接地址：747-400 AMM 飛機維護手冊 起落架 LANDING GEAR 4(101)
