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B. The majority of the wing skin is a component of the wing boxes and the center wing box, of which it forms the upper and lower surfaces.
C. The remainder of the wing skin forms the surfaces of the leading and trailing edge fairings and of the wing tip, and is of secondary structural importance.
Primary Wing Skin
_________________
A. The left and right wing box structures are continuous and have no production joints. This feature allows the upper and lower wing skin panels to be continuous on each wing from tip to root. The wing inspar upper skin is in two sections, spliced in the spanwise direction. The entire upper inspar skin is made from 7178 aluminum alloy. The wing inspar lower skin is made in three sections spliced in the spanwise direction and pierced by the openings for fuel tank access holes and fuel pump access holes. Refer to Chapter 52 and 57 of the Structural Repair Manual for wear limits on tank doors and tank door openings respectively. All the lower inspar skin is made from 2024 aluminum alloy, the most suitable material for withstanding the heavy tensile loads on the lower surface, and is shotpeened to give additional fatigue life besides forming the curvature of the wing. The inside surface of both upper and lower wing skins is attached directly to the edges of the zee-section wing stringers. The upper and lower skin panels of the center wing box are also attached directly to similar internal stringers. At the outboard ends of the center wing box, the upper and lower skins are connected to the upper and lower skins of the left and right wings by heavy chordwise splice extrusions which follow the lines of the upper and lower edges of the wing root ribs.
Secondary Wing Skin
___________________
A. Many of the larger areas of fairing skin are laminated honeycomb panels. Several sections of the lower surface are removable for access purposes.
B. The lower wing leading edge skin associated with each slat incorporates one pressure relief door. The door is spring-loaded and will open when cavity pressure reaches 1.5 psi.
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57-30-00
ALL ú ú B01 Page 1 ú Oct 20/83
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
LEADING EDGE ACCESS PANELS - MAINTENANCE PRACTICES
_____________________________________________________
1. General
_______
A. Three tasks are in this procedure for maintenance practices on the leading edge access panels:
(1)
The removal of difficult fasteners.
(2)
The installation of difficult fasteners.
(3)
Guidelines for missing fasteners.
B. This procedure helps with the removal and installation of fasteners on the leading edge access panels. Also, there is information to help avoid panel loss.
C. The access panels are found on the lower surfaces of the wing leading edge.
TASK 57-30-01-022-019-B00
2. Removal of Difficult Fasteners
A. Equipment
(1) Access Panel Leverage Adapter, B20004-21
B. References
(1)
12-31-61/201 Wing Lower Surface Access Doors and Panels
(2)
20-50-11/201 Standard Torque Values
C. Access
(1)
Location Zones
300 Left Wing
400 Right Wing
(2)
Access Panels
6212L/6512R Slat Access Panel
6213L/6513R Slat Access Panel
6214L/6514R Slat Access Panel
6215L/6515R Slat Access Panel
6217L/6517R Slat Access Panel
6218L/6518R Slat Access Panel
6219L/6519R Slat Access Panel
6220L/6520R Slat Access Panel
6221L/6521R Slat Access Panel
6222L/6522R Slat Access Panel
6223L/6523R Slat Access Panel
6224L/6524R Slat Access Panel
6225L/6525R Slat Access Panel
6226L/6526R Slat Access Panel
6227L/6527R Slat Access Panel
6228L/6528R Slat Access Panel
6229L/6529R Slat Access Panel
6230L/6530R Slat Access Panel
6231L/6531R Slat Access Panel
6232L/6532R Slat Access Panel
6233L/6533R Slat Access Panel
6234L/6534R Slat Access Panel
6241L/6541R Slat Access Panel
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