27-81-03
ALL ú ú 02 Page 233 ú Jun 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
(5)
AIPC 27-81-03, Fig. 1
(6)
SSM 27-81-01, SSM 27-81-02, SSM 27-81-03, SSM 27-81-04,
SSM 27-81-05, SSM 27-81-06
(7)
WDM 27-51-21, WDM 27-51-22, WDM 27-81-11, WDM 27-81-12,
WDM 27-81-21, WDM 27-81-22, WDM 27-81-31, WDM 27-81-32,
WDM 27-81-41, WDM 27-81-42, WDM 27-81-81, WDM 27-81-82
C.
Access
(1)
Location Zone
512 Krueger Flap Inboard, LH
523 Variable Camber Flap, LH
525 Variable Camber Flap, LH
535 Variable Camber Flap, LH
612 Krueger Flap Inboard, RH
623 Variable Camber Flap, RH
625 Variable Camber Flap, RH
635 Variable Camber Flap, RH
D.
Prepare for Removal
S 492-087
WARNING: YOU MUST CAREFULLY DO THE STEPS IN THE TASK BELOW TO INSTALL
_______ THE LE FLAP SAFETY LOCKS. THE LE FLAPS CAN MOVE QUICKLY IF YOU DO NOT INSTALL THE SAFETY LOCKS CORRECTLY. THIS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
(1)
Do this task: "Extended Leading Edge Flap Deactivation and Safety Lock Installation" (AMM 27-81-00/201).
S 862-088
(2)
Do this task: "Electrical Power Removal" (AMM 24-22-00/201).
S 862-089
(3)
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
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27-81-03
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
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
(d)
P415 Power Distribution Center - Right 1) 415M35 LE FLAP ELEC DRIVE 2 2) 415B32 LE FLAP ELEC DRIVE 3
S 862-090
(4)
Do this task: "Pneumatic Power Removal" (AMM 36-00-00/201).
S 862-091
(5)
Do this task to depressurize hydraulic systems No. 1 and 4: "Hydraulic System Depressurization" (AMM 29-11-00/201).
E.
Remove the Rectifier and Primary Solenoid Valve Assembly
S 032-092
(1)
Disconnect the electrical connector P102 (53) from the rectifier (49).
S 022-093
(2)
Remove the rectifier and primary solenoid valve assembly (38) (Fig. 201):
CAUTION: DO NOT USE THE CABLE TO LIFT THE RECTIFIER AND PRIMARY
_______ SOLENOID VALVE ASSEMBLY. IF YOU USE THE CABLE TO LIFT THE ASSEMBLY, IT WILL CAUSE DAMAGE TO THE CABLE.
(a)
Remove two mounting screws (50) from the rectifier.
(b)
Remove four screws (48) from the primary solenoid valve (54).
(c)
Remove the rectifier (49) and the primary solenoid valve assembly (54) from the airplane.
(d)
Put a cover on the opening in the PDU.
TASK 27-81-03-402-094
9. Rectifier and Primary Solenoid Valve Assembly Installation__________________________________________________________
A. Special Tools and Equipment
(1) 17MIT65B04017 Leading Edge Flap Drive Unit Lock
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本文链接地址：747-400 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 7(112)
