(Continued)
Reference Description Specification
C00259 Coating - Chemical And Solvent Resistant
Finish, Corrosion Inhibiting Primer
BMS10-11 Type I
C00260 Coating - Chemical And Solvent Resistant
Finish, Epoxy Resin Enamel
BMS10-11 Type II
D00633 Grease - Aircraft General Purpose BMS3-33
G00009 Compound - Organic Corrosion Inhibiting BMS3-23
D. Location Zones
Zone Area
100 Lower Half of Fuselage
E. Corrosion Prevention
SUBTASK 53-11-37-610-013
(1) Make the regular inspections of INSPECTION AND DETECTION, SUBJECT 51-00-51 to stop
of find the start of corrosion. Inspect the areas beneath the forward and aft cargo floors. Skin
bulges, missing fasteners, or white powdery deposits are signs of corrosion.
SUBTASK 53-11-37-610-014
WARNING
DO NOT APPLY THE CORROSION-INHIBITING COMPOUNDS IN THE AREAS
THAT HAVE OXYGEN SYSTEM COMPONENTS. THE MIXTURE OF
CORROSION-INHIBITING COMPOUNDS, AND OXYGEN CAN CAUSE AN
EXPLOSION. AN EXPLOSION CAN CAUSE INJURIES TO PERSONS, AND
DAMAGE TO EQUIPMENT.
CAUTION
DO NOT INSTALL THE INSULATION BLANKETS THAT ARE SOAKED WITH
CORROSION INHIBITING COMPOUNDS. INSULATION BLANKETS
INADVERTENTLY SPATTERED WITH THE CORROSION INHIBITING
COMPOUNDS SHOULD BE ALLOWED TO DRY BEFORE INSTALLATION.
SOAKED INSULATION BLANKETS ARE POTENTIAL FIRE HAZARDS. THEY
CAN CAUSE DAMAGE TO THE AIRPLANE.
(2) If you find corrosion (skin bulges, missing fasteners or large amounts of white deposits at the
fastener heads or faying surfaces), refer to SRM 737-678 for details of corrosion removal.
SUBTASK 53-11-37-610-015
(3) For details of application of water displacing corrosion inhibiting compound, refer to
STANDARD PREVENTIVE MAINTENANCE PROCEDURES, SUBJECT 51-00-59.
SUBTASK 53-11-37-610-016
(4) For minor corrosion, to minimize the downtime of the airplane, the corrosion products should
be cleaned off, followed by an application of a corrosion inhibiting compound into the affected
area to retard the corrosion process. The finish system should be restored at the next
maintenance opportunity.
NOTE: The treatment of internal structure described above should be made at first opportunity
the area is exposed. Location of the area should be noted and monitored from the
outside every 3 months for visual indication of corrosion progression. Any noticeable
skin bulges would require scheduling corrosion removal outlined in SRM 737-678.
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
53-11-37
Page 207
D633A101-ILF Oct 15/2018
ECCN 9E991 BOEING PROPRIETARY - Copyright © Unpublished Work - See title page for details
EFFECTIVITY
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