(5)
AMM 29-11-17/401, Air-Driven Pump
(6)
AMM 29-11-19/401, AC Motor-Driven Pump
(7)
AMM 54-62-00/201, Nacelle Strut Access Panels
(8)
AMM 71-00-02/401, Power Plant
(9)
AMM 71-11-04/401, Fan Cowl Panels
(10)
AMM 71-11-06/201, Core Cowl Panel
(11)
AMM 78-31-00/201, Thrust Reverser System
(12)
AMM 78-31-01/401, Thrust Reverser
(13)
CPM Part 3, 54-10-47
(14)
OHM 54-00-01
F. 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
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
54-51-02
ALL ú CONFIG 3 ú 10N Page 430 ú Feb 18/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
(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
G. Prepare for the Installation
S 214-008-003
(1) Do a check that all attach pins, bolts, caps, and washers at installation points are free from corrosion, including interior of fuse pins or hollow bolts and the inner diameter of fitting bushings.
(a) If corrosion exists, either replace part or remove corrosion and apply corrosion protection (CPM Part 3, 54-10-47). 1) Apply two coats of primer to all exposed surfaces,
including ID bore, but excluding chrome plate OD, if not already primed. 2) Apply a 0.05-inch (1.3 mm) thick coating of corrosion preventive compound to ID of attach pin/bolt.
S 214-009-003
(2) Make sure all the bushings at installation points are sealed from corrosion.
(a) If bushings are not sealed, apply sealant to bushings (AMM 51-31-01/201). 1) Apply fillet seal to flange end of all bushings. 2) Brush coat seal (maximum thickness 0.010 inch) to entire
periphery of all (except upper link wing fitting and diagonal brace wing fitting) unflanged bushing ends exposed to mating surface of parent part.
NOTE: No seal is required for bushing end not exposed to
____ mating surface of parent part. Corrosion prevention in this area is covered by application of grease during pin or bolt installation.
3) Apply fillet seal to entire periphery of unflanged bushing end at diagonal brace wing fitting.
S 214-010-003
(3) Do a check to make sure you have the correct part number fuse pin(s).
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
54-51-02
ALL ú CONFIG 3 ú 10N Page 431 ú Feb 18/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
H. Install the applicable attach pin/bolt.
S 424-011-003
(1) Install the midspar (inboard) or spring beam (outboard) fuse pin.
(a)
Apply a thin layer of grease to the fuse pin (55).
(b)
Apply antiseize compound (Never-Seez or equivalent) to threads of the self-locking nut (48).
(c)
If a slug is installed, push it out with the greased pin (55). Make sure the clevis and the lug stay aligned.
(d)
Install the washer (47) and nut (48) to the threaded end of the fuse pin (55). 1) Install the washer (47) and nut (48), and begin to turn the
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