(4)  
Mix 100 parts by weight of the Pro-Seal 501 with 30 parts by weight of the Pro-Seal 501-A accelerator. Mix for approximately 5 minutes with a spatula or an equivalent tool. If you mix the adhesive in the original can, cut off the rim of the can to make it easier.

 NOTE:____ Apply the adhesive as soon as it is possible.  The heat
 of the material in a container decreases the work life.  The
 Work life is 20 minutes at 77°F.

 Use 50 (|5) grams for each square foot of the surface that you cover.
Procedure - Repair the Mylar Water Barrier
 S 398-009-B00
 (1)  
Apply a layer of adhesive to the mating surface of the splice.

 S 398-010-B00

 (2)  
Bond the splice to the water barrier.

 S 148-011-B00

 (3)  
Remove the unwanted adhesive with a cloth moist with aliphatic naphtha.

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 S 358-013-B00
 (4)  Put a weight or tape on the edges that show signs of delamination until the adhesive dries.
 F. Put the Airplane Back to its Usual Condition
 S 868-012-B00
 (1)  Let the adhesive dry for a minimum of 2 hours.
 NOTE: A minimum of 12 hours is necessary for the adhesive to
____
 fully dry.

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 FIXED PARTITIONS - DESCRIPTION AND OPERATION
____________________________________________
 1.  General_______
 A.  The control cabin partition divides the control cabin from the forward end of the passenger cabin. A rearward-opening door is in the center of the partition. The right side of the partition is sheet metal, the left side is fiberglass.
 B.  The lavatory compartments are enclosed by fixed partitions, and each is equipped with a door opening inboard. The partitions are fiberglass with NOMEX core. The door has fiberglass skin with NOMEX honeycomb.
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 SKIN - DESCRIPTION AND OPERATION
________________________________
 1.  General_______
 A.  The fuselage skin varies in thickness according to the loads it must bear in any given area, and it is designed with fail-safe features to ensure alternate load paths in the event of a local failure. Refer to Chapter 53 of the Structural Repair Manual for skin identification.
 B.  The thickest skin panels are those over the area where the lower fuselage is cut away to accommodate the wing and the main leanding gear wheel well. In this area the skin panels are machined from thick sheets.
 C.  Many of the skin panels are attached to each other by bonded longitudinal lap joints, which provide pressure seals in addition to being structural joints. Circumferential skin splices exist aft of the control cabin, at the front spar bulkhead, at the bulkhead aft of the wheel well and at the aft pressure bulkhead.
 D.  The skin is reinforced by means of doublers bonded to the inside of the outer skin (Fig. 1). These doublers function as tear stoppers by forming a complete, integral fail-safe, circumferential and longitudinal "waffle" grid.

Typical Skin Reinforcements
Figure 1

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