FRONT SPAR TO REAR SPAR UNDERWING PANEL - INSPECTION/REPAIR
1. General
A. This procedure contains two tasks. The first task is to examine the countersunk of the fastener holes
of the front spar to rear spar underwing panel. The second task is the repair the holes if cracks are
found.
TASK 53-51-00-200-801
2. Front Spar to Rear Spar Underwing Panel Inspection
Figure 201
A. Location Zones
Zone Area
100 Lower Half of Fuselage
B. Procedure
SUBTASK 53-51-00-010-001
(1) Remove the sixteen 0.25 in. (6.35 mm) attach fasteners from the outboard edge of the aft and
forward panels on the left and right sides (Figure 201).
SUBTASK 53-51-00-210-001
(2) Do a visual inspection with a 10X magnifying glass of the countersunk and adjacent area of the
hole.
SUBTASK 53-51-00-300-001
(3) If you find cracks in or adjacent to the countersunk area, do this task: Front Spar to Rear Spar
Underwing Panel Repair, TASK 53-51-00-300-801.
SUBTASK 53-51-00-420-002
(4) If you do not find cracks, or you have made repairs to cracks, install the bolts and washers:
(a) Measure and record the nutplate for the self-locking torque. The torque should be
3.5 in-lb (0.4 N·m) to 30 in-lb (3 N·m).
(b) Add the self-locking torque (5 in-lb (1 N·m) to 10 in-lb (1 N·m)) to calculate the installation
torque.
(c) Tighten the bolts to the midrange of this torque range.
END OF TASK
TASK 53-51-00-300-801
3. Front Spar to Rear Spar Underwing Panel Repair
A. References
Reference Title
SRM 51-70-04 Repair of Damage to the Edgeband of a Honeycomb Panel
SRM 51-70-05 Structural Repair Manual
B. Consumable Materials
Reference Description Specification
G50400 Resin - Fiberglass Layup, Short Worklife,
Non-Brominated
BMS8-201 Type IV
(Supersedes BMS8-201
Type II)
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
53-51-00
Page 201
D633A101-ILF Oct 15/2015
ECCN 9E991 BOEING PROPRIETARY - Copyright © Unpublished Work - See title page for details
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