H.
On airplane, line number 689, RR 92007-36 applies corrosion inhibiting com-pound BMS 3-29 on:
(1) Fastener heads on floor panels under galleys, galley work areas, door-ways and lavatories.
(2)
Underside surface of lower lobe cargo bay sidewalks and flanges common
to sidewalk and deck liners.
I.
Airplane, line number 707 and on; SRP 53-0052 applies BMS 3-29 Corrosion
Inhibiting Compound on top of floor beams and moisture barrier tape on top
of floor panels in all wet areas (galleys, lavatories, and doors).
2. Corrosion Prevention
A. Following cleaning of suspected areas, a thorough inspection as described in
Volume 1, 20-20-00 is effective to ensure that protective finishes provided
during manufacture remain intact. Refer to Volume 1, 20-60-00 for details on
the application of corrosion inhibiting compound.
B. Where corrosion exists (noticeable bulges of the skin or white deposits of
corrosion products at fastener heads of joint edges), refer to the index
column in 53-00-01 for reference rework chapter.
C. For minor corrosion, to minimize the downtime of the airplane, the corrosion
products should be cleaned off, followed by the application of a corrosion
inhibiting compound into the affected area to retard the corrosion process
(Ref Volume I, 20-60-00). The finish system should be restored at the first
opportunity consistent with the maintenance schedule.
Volume 2-757
53-10-01
Page 2
OCT 01/00
CORROSION PREVENTION MANUAL
FUSELAGE -SECTION 41
D. Prevention Treatment
(1)At first opportunity consistent with scheduled maintenance activity,
corrosion prevention treatment should be accomplished in the external
drains, wheel well opening, and door opening.
(2)External Drains:
(a)
Clean out drains and drain paths.
(b)
Check that drain valve is free to open and close.
CAUTION: OBSERVE DRAIN VALVE TORQUE LIMITS. EXCESSIVE TIGHTENING OF
PLUNGER TYPE DRAIN VALVE WILL CAUSE VALVE FLANGE TO CRACK OR
BREAK.
(c) If required, remove plunger type drain valve from outside the fuse-lage, clean out obstructions and reinstall valve until flange con-tacts skin. Tighten to 15 lb-in. maximum.
(3)Nose Wheel Well Opening:
(a)
Treatment of the wheel well at the same time as the nose gear is rec-ommended.
(b)
Remove runway debris and generally clean the entire wheel well.
(c)
Replace damaged or broken protective finishes if at all possible.
Refer to Volume 1, 20-60-00 for protective finish systems.
(d)
Apply BMS 3-23 to all exposed wheel well structure. Special effort
should be made to apply the corrosion inhibitor along doubter edges,
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