FILLET FAIRINGS CORROSION - MAITINENCE PRACTICES
1. General
A. This procedure contains 1 task:
(1) Corrosion Prevention of the Wing to Body Fairing Cavity.
TASK 53-51-37-600-801
2. Wing to Body Fairing Cavity - Corrosion Prevention
Figure 201
A. General
(1) The upper wing-to-body fairing is attached to the upper wing surface and fuselage skin along
the wing to fuselage joints. The lower lobe fairing houses the ambient air inlets to the ram air
system during pack cooling fan operation. The lower lobe fuselage skin under the fairing
extends to the bulkhead below the front spar of the center wing section. The cavity formed by
the lower lobe fairing and fuselage skin is the area of concern and is the subject of this figure.
Aft of this area the fairing covers the center wing section.
(2) Service experience has shown the revised finish system has been effective in controlling the
corrosion problem. Corrosion damage is due to the accumulation of moisture from the ambient
air as it enters the cavity during pack cooling fan operation.
(3) Corrosion was reported on the fuselage skin and the external doubler on the wing upper
surface under the wing to body fairing. The body surfaces under the fairing is treated with a
water displacing corrosion inhibiting compound in production.
(4) Refer to CORROSION PREVENTION, SECTION 51-00 of this manual for a discussion of the
Aging Airplane Corrosion Prevention and Control Program and related documentation.
Structural items within this section are subject to the unique requirements of the mandatory
Corrosion Prevention and Control Program.
B. References
Reference Title
51-00 CORROSION PREVENTION
51-00-51 INSPECTION AND DETECTION
51-00-59 STANDARD PREVENTIVE MAINTENANCE PROCEDURES
SRM 737-678 Structural Repair Manual
C. Consumable Materials
Reference Description Specification
G00009 Compound - Organic Corrosion Inhibiting BMS3-23
D. Location Zones
Zone Area
100 Lower Half of Fuselage
E. Corrosion Prevention
SUBTASK 53-51-37-610-001
(1) Make the periodic inspection described in INSPECTION AND DETECTION,
SUBJECT 51-00-51 to ensure that the protective finishes provided at manufacture remain
intact. Access for inspections can be made through service doors and access panels in the
fairing. A corrosion prevention program should be initiated to prevent the accumulation of
corrosive products in order to minimize the occurrence of corrosion.
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
53-51-37
Page 201
D633A101-ILF Oct 15/2014
ECCN 9E991 BOEING PROPRIETARY - Copyright © Unpublished Work - See title page for details
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