TM 1-1520-238-23
2-42
Change 6
2.12.
CLASSIFICATION OF FUSELAGE DAMAGE AND TYPES OF REPAIR – continued
Category
Limits
Action
f. Transparent Panels Cracks
A
Cracks in nylon retainer which do not
propagate into acrylic panel.
Seal with sealing compound (item 174,
App F).
B
Less than 1.00 INCH long within 2.00
INCHES of panel edge and/or
propagating from attachment bolt holes.
Repair by stop drilling crack
(TM 1-1500-204-23).
C
Exceeds B or propagates beyond stop
drilled hole.
Replace.
g. Glass Windshield
C
Cracks and pitted or scratched areas that
hinder or restrict flight crew vision.
Replace.
h. Cover and Door Cracks, Tears, and Punctures
B
Less than 25 PERCENT length of shortest
dimension.
Repair (TM 1-1500-204-23).
C
Exceeds B.
Replace.
i. Main Landing Gear Shock Strut Support Flaws (Pits, Grooves, and Scratches)
A
Flaws no deeper than 0.010 INCH are
allowed on shaft in area extending from
base of strut support outward along shaft
0.25 INCH.
-------
Flaws no deeper than 0.020 INCH are
allowed on shaft in area extending from
base of strut support outward along shaft
0.25 INCH.
-------
B
Exceeds A.
Must be blended out at 20:1 ratio.
C
Cracks or a continuous groove extending
around entire shaft surface are not
allowed.
Perform magnetic particle inspection on
strut support (TM 55-1500-335-23).
Replace.
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