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 B.  The aileron chord length at the outboard end is approximately 40% greater than at the inboard end.
 2.  Inboard Aileron Structure_________________________
 A.  The structural frame consists of front and rear spanwise spars, conventional chordwise ribs, hinge and actuator supports, and skins.
 B.  The spars consist of extruded T-section aluminum alloy chords and two-sheet, laminate webs of the same alloy.
 C.  The inspar ribs have aluminum alloy extruded T-chords with webs of the same alloy. The closure ribs, which are continuous from the front spar to the trailing edge, have aluminum webs and formed chords. Stiffeners are installed on the spars and ribs to provide additional web rigidity.
 D.  Lug-type hinge fittings, machined from aluminum plate, are attached to the lower, forward side of the front spar at four locations. Forged aluminum reinforcing support fittings are also installed at the locations of the primary hinge fittings, WBL 461.5 and 505.0. A double-lug forged aluminum fitting attached to the front spar between the inboard primary and fail-safe hinges provides attachments for the aileron power control package and reaction link (Ref 57-42-00 D&O).
 E.  The inspar and trailing edge skin panels are of plastic glass fabric reinforced honeycomb sandwich construction. Screws and nutplates attach the lower center inspar panel; the rest are fastened by rivets. The upper and lower trailing edge panels are bonded to each other at the aft end. Upper and lower nose skins are of clad aluminum sheet.
 F.  Three hoist attachment points on the upper chords of the spars facilitate lifting the surface during removal or installation. When hoist attachment points are not in use, the holes are plugged with a countersunk screw.
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 57-51-01
 ALL  ú ú 01 Page 1 ú Jun 10/88
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

FRONT SPAR
WBL
WBL

514.76

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 ALL  ú ú 01 Page 2 ú Jun 10/88
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 OUTBOARD AILERONS - DESCRIPTION AND OPERATION
_____________________________________________
 1.  General_______
 A.  The outboard ailerons are located in the wing trailing edge outboard of the outboard engine nacelle. In conjunction with the inboard ailerons, they serve as primary lateral control surfaces during low airspeed operation. They are supported by six hinge support fittings attached to the aileron front spar. These fittings are attached to wing trailing edge hinge support rib fittings by pin joints.
 B.  Static balance weights of a tungsten base high density metal are attached to ribs cantilevered forward of the aileron front spars.
 2.  Outboard Aileron Structure (Fig. 1)__________________________
 A.  The aileron structure consists of spanwise spars, chordwise ribs, skin panels, hinge supports, an actuator attachment fitting, and the trailing edge.
 B.  The front spar consists of extruded T-section aluminum alloy chords and a laminated web of two sheets of the same alloy. The rear spar is a channel section of glass fabric reinforced plastic laminate.
 C.  The inspar ribs are located in pairs, aft of the six aileron hinges. These ribs have extruded aluminum alloy chords and laminated webs of two sheets of the same alloy. Closure ribs of aluminum alloy chords and laminated webs are continuous from the nose ribs to the rear spar. Static balance weight support ribs are cantilevered forward from the front spar at hinges No. 1, 2, 3, 5, and 6 and are installed in groups of three at these hinge locations. Formed nose ribs and formers of aluminum alloy provide support for the upper and lower forward skins.
 D.  Upper and lower inspar skin panels are of plastic glass fabric reinforced honeycomb sandwich construction. Screws and nutplates attach the lower inspar skin to the ribs and spars; the upper inspar skin is riveted. The upper and lower skins forward of the front spar are contoured from aluminum sheet.
 E.  Six forged aluminum alloy hinge fittings are attached to the front spar to provide the aileron-to-wing structure attachment. All hinge fittings are single lug except hinge No. 4. The fitting located at hinge No. 4 has two double lugs for hinging and one double lug for the attachment of the hydraulic power control package (Ref 57-42-00, Description and Operation).
　
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