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 B.  The wing center section skin consists of three upper and five lower panels which extend spanwise between left and right WBL 128.4, The upper and lower panels are separately identified in numerical sequence from the rear spar forward. The upper panels have spanwise splices at the mid spar and stringers S27C; the lower panels are spliced at stringers S5C, S10C (mid spar), S15C, and S20C. Basic upper and lower skin thickness increases from the front spar to the rear spar.
 C.  The panels are preformed to match the rib contours and are machined sculptured to eliminate excess weight while maintaining the required strength. Upper and lower stringers are attached to the inner panel surfaces. The skins are sealed in the wing center section integral fuel tank. Chordwise splice fittings attach the skin panel ends to the wing to body ribs.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

FRONT SPAR
S20
S15
MID SPAR
S5
REAR SPAR
WING EXTENSION UPPER SKIN WBL
1241 WING INSPAR SKIN
Wing Plates and Skins Figure 1
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

 3.  Wing Secondary Skin (Fig. 2)
___________________
 A.  The wing leading edge skins consist of a series of fiberglass panels and aluminum skins, spliced both chordwise and spanwise. The forward portion is formed from aluminum alloy sheet to eliminate erosion by moisture particles and high velocity air impingement. Fiberglass honeycomb panels are attached to the nose sections and, except for cutouts for the leading edge flaps, form the major portion of the leading edge skin. The honeycomb panels are attached at the aft edge to the front spar chords. On the upper surface, laminated plastic glass panels or strips are used to effect the attachment. The Krueger flap skins are fabricated from 7075 clad aluminum sheet, except that the nose section skins are of 2024 clad aluminum sheet. The skins are attached to spanwise beams and chordwise ribs. To provide the flexibility required for the variable camber flaps, the skin is made of plastic glass honeycomb and fabric materials. The skins are attached to spanwise structural members and nose ribs. Maintenance access is accomplished through removable doors and fairings and through the flap wells.
 B.  The fixed trailing edge upper and lower skins inboard of wing station 1548.2 consist almost entirely of fiberglass honeycomb sandwich panels attached to spanwise and chordwise structural members. One exception is the lower surface aft of the outboard nacelle, which is of laminated fiberglass construction. The aft 10 inches on the under side of the inboard upper trailing edge fixed structure between the inboard spoiler and the fuselage is coated with an abrasion resistant teflon finish. This area is susceptible to chafing during operation of the inboard flaps (Ref 51-24-00). The inboard and outboard flap segment skins consist of fiberglass honeycomb panels forming the leading and trailing edge areas of each segment with aluminum honeycomb sandwich panels forming the upper and lower skins. With the exception of an upper forward aluminum sheet panel, the exterior of both ailerons consists of fiberglass honeycomb panels fastened to internal ribs and spars. The wing landing gear doors, located on the lower surface of the inboard wing, are aluminum bonded honeycomb material, and form a part of the trailing edge skin when closed. The flight and ground spoilers have aluminum honeycomb cores with bonded clad aluminum skins. Between wing sta. 1548.2 and WBL 1169, the inspar skin consists of upper and lower aluminum honeycomb panels supported by the wing spars and rib chords. Winglet fairings are made up of a leading edge fairing of formed aluminum, and three sandwich fairings attached to the wing and winglet skins. Access doors and flight control surface wells permit access to internal trailing edge structure and airplane systems components.
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