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1885 consists of chromic acid anodize surface treatment and a coat of BMS
10-11, type 1 primer on the detail parts. Many parts are fay sealed with BMS
5-95 sealant: parts that touch the skin below stringer 17, fin support fit-tings, longerons, skin splices, chords and web doubters of the fin rear spar
bulkhead. All non-aluminum fasteners are installed with wet sealant. A coat
of BMS 10-11 type 1 primer is applied to all of the assembled interior.
Below stringer 17, detail parts get a coat of BMS 10-11, type 2 enamel. BMS
3-23 corrosion inhibiting compound is applied to all interior surfaces after

assembly and painting.

C. The APU firewall is made of titanium alloy. Below stringer 17, the titanium
chords are sealed with BMS 5-63 sealant. The faying surfaces that touch the
aluminum body structure are sealed with EC 5128 sealant. All edges of the
firewall aft face are sealed with BMS 5-63 sealant.

D. Aft of station 1896, the aluminum skin is protected with phosphoric anodize
surface treatment. The aluminum frames get chromic acid anodize surface
treatment. Then both skin and frame surfaces get a coat of BMS 10-11, type 1
primer. The skin splices and frames, and the APU access door assembly, are
fay sealed with BMS 5-63 sealant. After assembly, the entire interior gets a
coat of BMS 10-11, type 1 primer and a coat of BMS 10-11, type 2 enamel.

2.  Corrosion Prevention

A. After you  clean the areas, do the inspection of Volume 1, 20-20-00 to make
sure that protective finishes stay serviceable.

B. For less important corrosion,  to decrease the downtime of the airplane,
clean off the corrosion products. Apply corrosion inhibiting compound on the
affected areas. Refer to Volume 1, 20-60-00 for how to apply corrosion
inhibiting compound. Repair the finish system when the maintenance schedule
permits.

C. Frequency of Application

(1)Regular inspection is required in areas which can get corrosion. Use the
schedules in the Maintenance Planning Document. Operators must know of
reported problems and areas.

(2)Regular  application of BMS 3-23 corrosion preventive compound is neces-sary in areas identified. Use the schedules in the Maintenance Planning
Document.

Volume 2-757

 

53 -80-01

Page 1
OCT 01/00

CORROSION PREVENTION MANUAL
FUSELAGE -SECTION 46

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Volume 2-757

53 -80-01

Page 2
OCT 01/00

CORROSION PREVENTION MANUAL
FUSELAGE SKIN LAP JOINTS

1. General

A. Skin lap joints are joined by rivets and are supplemented by BMS 5-95 corro-
sion inhibiting adhesive primer (CIAP). The CIAP serves as an adhesive as
well as a sealant to prevent contaminants from entering the splice. To fur-ther prevent the entrance of contaminants, lap splices on the airplane inte-rior are fillet sealed with BMS 5-32, Class B sealant. Airplanes may be
　
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