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_______ THE APPLICATION OF 125 POUND-INCHES MAXIMUM TORQUE. DO NOT LIFT THE STRUT OR PULL DOWN ON THE STRUT WITH MORE THAN 3,000 POUNDS OF FORCE ON THE INBOARD STRUTS OR 1,800 POUNDS OF FORCE ON THE OUTBOARD STRUTS. IF YOU APPLY A FORCE THAT IS MORE THAN NECESSARY, DAMAGE TO THE STRUCTURE CAN OCCUR.
 (19) Unload the attach pin/bolt of the diagonal brace, upper link, or side brace.
 NOTE: If the midspar fuse pin is to be replaced it is first
____ necessary to disconnect one end of the diagonal brace to remove the preload.
 (a)  Gently apply a load sufficient to remove the strut preload. The intent is to unload the pin/bolt to be removed. 1) Make sure the pin/bolt to be removed can be rotated by
 applying no more than 125 pound-inches (14.3 N.m) torque.
 NOTE: Castellated nuts may have to be tightened up to
____ 200 pound-inches (22.6 N.m) to allow the fuse pin assembly to rotate as a unit with 125 pound-inches (14 N.m) applied torque.
 S 864-053-003
 (20) Unload the midspar (inboard) or spring beam (outboard) fuse pins.
 (a) Unload and remove one of the diagonal brace attach pins.
 NOTE: You can use a rope to temporarily support the loose
____
 end of the diagonal brace.

 1)  Slowly release the load on the diagonal brace unload sling and remove the sling.
 (b)  Use the tool placard to install the strut overhead sling. 1) Remove the No. 3 forward fairing. 2) Attach the sling to the front of the strut with the forward
 hoisting attach fitting. 3) Attach the sling to the lower aft attach points of the strut with the aft hoisting attach fittings. 4) Use the lift point as marked on the sling for the engine and strut location.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 5)  Use the hole in the lift point as follows: a) Engines 1 & 2 - left hole b) Engines 3 & 4 - right hole.
 (c)  Unload the midspar (inboard) or spring beam (outboard) fuse pins. 1) Gently apply a load to unload the midspar fuse pin to be
 removed. 2) Make sure the pin to be removed can be rotated by applying no more than 125 pound-inches (14.3 N.m) torque. 3) The fuse pin, caps, and bolt must rotate as an assembly. The intent is to have no load on the pin to be removed.
 G.  Prepare for removal (engine supported).
 S 864-054-003
 (1)  Ground airplane to an approved grounding lug.
 S 494-055-003
 WARNING:_______LEADING EDGE FLAPS ARE FAST ACTING. LOCKS MUST BE INSTALLED TO PREVENT POSSIBLE INJURY DUE TO INADVERTENT OPERATION OF FLAPS.
 (2)  
Make sure leading edge flaps are retracted and leading edge flap drive unit lock is installed (AMM 27-81-00/201).

 S 014-056-003

 (3)  
Open trailing edge fairing doors (AMM 54-62-00/201), if necessary for access to diagonal brace attach pins/bolts. Prop doors open with suitable rod. Remove door support rods from nacelle strut torque bulkhead.

 S 014-060-003

 (4)  
Remove the air driven pump (AMM 29-11-17/401) aft of the torque bulkhead, if it is necessary for access to mid-spar or spring beam pins.

 S 014-061-003

 (5)  
ON OUTBOARD STRUTS; Remove the air-driven pump turbine drive (AMM 29-11-08/401) aft of the torque bulkhead, if it is necessary for access to spring beam pins.

 S 014-062-003

 (6)  
ON INBOARD STRUTS; Remove the AC motor-driven pump (AMM 29-11-19/401) aft of the torque bulkhead, if it is necessary for access to midspar pins.

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

 S 014-059-003
 (7)  Open the wing leading edge cover, if it is necessary for access to the upper link attach pins/bolts.
 S 014-057-003
 (8)  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.
　
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