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 PREVENT POSSIBLE INJURY DUE TO INADVERTENT OPERATION OF FLAPS.
 MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE LE AND TE
 FLAPS AND FLAP DRIVE MECHANISMS BEFORE YOU MOVE THE FLAP
 CONTROL LEVER.  WITH HYDRAULIC POWER REMOVED, THE FLAPS WILL
 MOVE AUTOMATICALLY BY ELECTRICAL POWER WHEN YOU MOVE THE FLAP

 CONTROL LEVER.
 (1)  
Make sure the leading edge flaps are retracted and leading edge flap drive unit lock is installed (AMM 27-81-00/201).

 S 014-075-003

 (2)  
Remove the thrust reverser (AMM 78-31-01/401).

 S 024-076-003

 (3)  
Remove the engine (AMM 71-00-02/401).

 S 864-095-003
 WARNING: KEEP ELECTRICAL POWER OFF DURING DISCONNECTION OR CONNECTION
_______ OF FUEL, HYDRAULIC, AND ELECTRICAL LINES TO PREVENT INJURY TO PERSONNEL THAT COULD RESULT FROM ACCIDENTAL APPLICATION OF PRESSURIZED FLUIDS, ENERGIZING OF ELECTRICAL CIRCUITS, OR FIRE.
 (4)  
Make sure the external electrical power is disconnected and that the airplane is grounded.

 S 864-078-003

 (5)  
Make sure the FUEL CONTROL toggle switches, located on engine start module, are in the CUTOFF position.

 S 864-079-003

 (6)  
Make sure the engine fuel and hydraulic supply shutoff valves are closed, and that the electrical plugs are disconnected from valves.

 S 864-080-003

 (7)  
Make sure the hydraulic system is depressurized (AMM 29-11-00/201).

 S 684-049-003

 (8)  
Make sure the fuel supply line and hydraulic fluid lines to engine are drained.

 S 014-081-003

 (9)  
Open trailing edge fairing doors (AMM 54-62-00/201), if it is necessary for access to diagonal brace attach pins/bolts.

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 54-51-02
 ALL  ú CONFIG 3 ú 10N Page 407 ú Feb 18/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

 S 864-082-003
 (10)
 Prop the doors open with a suitable rod, and remove the door support rods from the nacelle strut torque bulkhead.

 S 014-050-003

 (11)
 ON INBOARD STRUTS; Remove the right and left forward wedge assemblies of the fixed aft fairing, for access to the aft diagonal brace attach point.

 (a)  
On each side, remove the two fasteners that attach the secondary retainer to the fairing.

 (b)  
On each side, remove twenty six fasteners that attach the fairing assembly to the forward web assembly.

 (c)  
On each side, remove the thrity four fasteners that attach the fairing assembly to the skate angle.

 

 S 014-051-003
 (12)
 Open all the strut access doors (AMM 54-62-00/201).

 S 014-083-003

 (13)
 ON OUTBOARD STRUTS; Remove forward fairing no. 4.

 S 014-084-003

 (14)
 Open the wing leading edge cover, if it is necessary for access to the upper link attach pins/bolts.

 S 024-085-003

 (15)
 ON OUTBOARD STRUTS; Remove the air-driven pump (AMM 29-11-17/401) aft of the torque bulkhead, if it is necessary for access to spring beam pins.

 S 024-086-003

 (16)
 ON OUTBOARD STRUTS; Remove the air-driven pump turbine drive (AMM 29-11-08/401) aft of torque bulkhead, if it is necessary for access to spring beam pins.

 S 024-087-003

 (17)
 ON INBOARD STRUTS; Remove the AC motor-driven pump (AMM 29-11-19/401) aft of torque bulkhead, if it is necessary for access to midspar pins.

 S 494-088-003

 (18)
 Use the tool placard to install the diagonal brace unload sling G54007.

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 54-51-02
 ALL  ú CONFIG 3 ú 10N Page 408 ú Feb 18/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

 S 864-052-003
 CAUTION: DO NOT EXCEED UPLOAD NECESSARY TO PERMIT PIN/BOLT ROTATION WITH
　
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