S 348-103
(4)
Apply adhesive to the back of the patches.
S 348-104
(5)
Put the patches over the center of the damaged area on the front and the back of the liner.
S 348-105
(6)
Apply pressure to the patches to make sure there is a good bond.
S 348-126
(7)
Do the steps that follow to permanently attach the patches:
(a)
Install bolts, NAS603-5P or equivalent, washers, AN960JD10L, and nuts, MS21042L3, at a maximum of 2 inches apart and 0.5 inch from the edges of the patches.
(b)
Make sure there is sufficient clearance between the bolts and the adjacent systems behind the liner.
(c)
If it is necessary, grind the ends of the bolts smooth with the nuts to get sufficient clearance.
S 438-127
(8)
Install the liner (AMM 25-52-01/401 or AMM 25-55-02/401).
S 968-128
(9)
If sufficient clearance is still not obtained, replace the damaged liner.
E. Procedure - Repair the Neoprene-coated Liners with Fiberglass Thread
S 038-129
(1) Remove the cargo liner from the support structure if it is necessary (AMM 25-52-01/401 or AMM 25-55-02/401).
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S 348-130
(2) Make a fiberglass patch.
NOTE: The patch should make a minimum of a 2-inch overlap on the
____ area that is not damaged. For example, the patch dimension that is necessary for a 1.5-inch diameter hole would be a 5.5-inch diameter.
S 118-131
(3)
Clean all of the surfaces using denatured alcohol to remove the loose particles.
S 348-132
(4)
Apply adhesive to the back of the patch.
S 348-133
(5)
Put the patch over the center of the damaged area on the front of the liner.
S 348-134
(6)
Apply pressure to the patch to make sure there is a good bond.
S 348-135
(7)
Use the fiberglass thread to stitch two lines around the edge of the patch.
NOTE: There should be seven, plus or minus one, stitches for each
____
inch.
S 438-136
(8) Install the liner (AMM 25-52-01/401 or AMM 25-55-02/401).
TASK 25-52-01-308-113
5. Repairs for Molded Panels, Shrouds, and Panels with Complex Curves
__________________________________________________________________
A. General
(1) The task that follows is a repair for molded panels, shrouds, and panels with complex curves.
B. Consumable Materials
(1)
A00904 Resin - Fiberglass, BMS 8-201, Type II
(2)
G01081 Abrasive paper (200 grit or finer)
(3)
G00316 Fiberglass Fabric - BMS 9-3, Type H
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(4) Solvent
NOTE: Use one of these:
____
(a) B00316 Naphtha, Aliphatic - TT-N-95, Type I or II
(b)
B00775 Isopropyl AlcoholReferences
(1)
AMM 25-52-01/401, Containerized Cargo Compartment Ceiling and Sidewall Linings
(2)
AMM 25-55-02/401, Bulk Cargo Compartment Ceiling and Sidewall Linings
(3)
SRM 51-70-06, Structural Repair ManualAccess
(1)
Location Zone 100 Lower Half of Fuselage
Procedure - Repair Molded Panels, Shrouds, and Panels with Complex Curves
S 038-114
(1)
Get access behind the panel or remove the panel from the airplane (AMM 25-52-01/401).
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