E. Corrosion Prevention
SUBTASK 53-11-37-610-032
(1) Make the periodic inspection described in INSPECTION AND DETECTION,
SUBJECT 51-00-51 to preclude or detect the early stages of corrosion. Missing fasteners,
white powdery or any discolored deposits are evidences of the existence of corrosion which
should alert operators that some corrective action is required. A corrosion prevention program
should be initiated to prevent the accumulation of corrosive products in order to minimize the
occurrence of corrosion.
SUBTASK 53-11-37-610-033
(2) Corrosion Inspection/Removal
(a) Following cleaning of suspected areas, a visual inspection utilizing bright lighting and
mirror is effective for identifying the existence of corrosion. In specific localized areas
where inspection by visual means is impossible or where extent of corrosion has to be
determined after visual detection, INSPECTION AND DETECTION, SUBJECT 51-00-51
for applicable method.
(b) Where corrosion exists (noticeable bulges of the skin or white deposits of corrosion
products at fastener heads or joint edges), refer to Structural Repair Manual for details of
corrosion removal.
(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 (STANDARD PREVENTIVE
MAINTENANCE PROCEDURES, SUBJECT 51-00-59). The finish system should be
restored at the next maintenance opportunity.
SUBTASK 53-11-37-610-034
(3) Application of Corrosion Inhibitors
(a) For details of application of water displacing corrosion inhibiting compound, refer to
STANDARD PREVENTIVE MAINTENANCE PROCEDURES, SUBJECT 51-00-59.
SUBTASK 53-11-37-610-035
(4) Prevention Treatment
(a) At the next maintenance opportunity, corrosion prevention treatment should be
accomplished in the wheel well.
(b) Treatment of the wheel well at the same time as the nose gear is recommended.
(c) Remove runway debris and generally clean the entire wheel well. Make sure that all drain
paths are clear in structural areas at the nose gear wheel well.
(d) Replace damaged or broken finishes if at all possible. Refer to STANDARD
PREVENTIVE MAINTENANCE PROCEDURES, SUBJECT 51-00-59 for protective finish
systems.
(e) Apply water displacing corrosion inhibiting compound to all exposed wheel well structure.
Special effort should be made to apply the corrosion inhibitor along doubler edges, along
faying surfaces and on fastener heads. The use of spray equipment with nozzle directed
into faying surfaces is recommended.
NOTE: The manual extension release mechanism on the nose landing gear must be
protected from corrosion inhibiting compound contamination.
(f) Apply water displacing corrosion inhibiting compound to nose gear actuator attachment
fitting, nose gear trunnion support fittings and miscellaneous other fittings. Ensure that all
lugs and lug faces are treated.
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
53-11-37
Page 229
D633A101-ILF Oct 15/2018
ECCN 9E991 BOEING PROPRIETARY - Copyright © Unpublished Work - See title page for details
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