E. Access
(1)
Location Zone 451 Nacelle Strut 1 - Forward Fairing 452 Nacelle Strut 1 - Torque Box 454 Nacelle Strut 1 - Aft Fairing 521 Nacelle Strut 1 - Leading Edge to Front Spar 461 Nacelle Strut 2 - Forward Fairing 462 Nacelle Strut 2 - Torque Box 464 Nacelle Strut 2 - Aft Fairing 521 Nacelle Strut 2 - Leading Edge to Front Spar 471 Nacelle Strut 3 - Forward Fairing 472 Nacelle Strut 3 - Torque Box 474 Nacelle Strut 3 - Aft Fairing 621 Nacelle Strut 3 - Leading Edge to Front Spar 481 Nacelle Strut 4 - Forward Fairing 482 Nacelle Strut 4 - Torque Box 484 Nacelle Strut 4 - Aft Fairing 621 Nacelle Strut 4 - Leading Edge to Front Spar
(2)
Access Panel 454 Trailing Edge Fairing Door - Nacelle Strut 1 521FT Wing Leading Edge Cover - Nacelle Strut 1 464 Trailing Edge Fairing Door - Nacelle Strut 2 511CT Wing Leading Edge Cover - Nacelle Strut 2 474 Trailing Edge Fairing Door - Nacelle Strut 3 611CT Wing Leading Edge Cover - Nacelle Strut 3 484 Trailing Edge Fairing Door - Nacelle Strut 4 621FT Wing Leading Edge Cover - Nacelle Strut 4
F. Prepare for Installation
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747-400 MAINTENANCE MANUAL
S 864-135
WARNING:_______ 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. THIS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT.
(1)
Make sure that the wing leading edge flaps are retracted (AMM 27-81-00/201).
S 864-048
(2)
Make sure that the external electrical power is disconnected.
S 864-112
(3)
Make sure that the airplane is grounded.
S 864-049
(4)
Make sure that the toggle switches of the fuel control which are found on the engine start module are in the CUTOFF position.
S 864-050
(5)
Make sure that the applicable hydraulic system is released of the pressure (AMM 29-11-00/201).
S 864-051
(6)
Make sure that the applicable engine fuel and hydraulic fluid shutoff valves are closed.
S 864-113
(7)
Make sure that the electrical plugs are disconnected from the valves.
S 214-052
(8)
Make sure that all of the attach pins, bolts, retain caps and washers at the installation points of the nacelle strut are free from corrosion.
(a)
Also do this check on the inside of the hollow fuse pins, bolts and the inner diameter (ID) of the fitting bushings.
(b)
If there are corrosion, do one of these two steps: 1) Replace the part. 2) Remove the corrosion and apply the corrosion protection
(CPM Part 3, 54-10-47). 3) Apply two layers of primer to all open surfaces which includes the ID, but does not include the chrome plate OD. 4) Apply a 0.05 inch (1.3 mm) thick layer of corrosion preventive compound to the ID of each attach pin/bolt.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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747-400 MAINTENANCE MANUAL
S 624-053
(9) Make sure that all the attach fitting bushings at the installation points are sealed from corrosion.
(a) If the bushings are not sealed, apply the sealant (BMS 5-79) to the bushings (AMM 51-31-01/201). 1) Apply the seal to the flange end of all the bushings. 2) Apply a layer of the seal (maximum thickness 0.010 inch) to
the entire area of the unflanged bushing ends (except the upper link and wing fitting of the diagonal brace) which is opened to the mating surface of the parent part.
NOTE: No seal is necessary for the bushing end that is not
____ opened to the mating surface of the parent part. Corrosion in this area is done when you use grease during the installation of pins or bolt.
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