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  TB 1-1520-238-20-88
Hole
Hole Diameter
Location, RH
Distance From Top
Number
Side
of Frame
WL
BL
1
.63 (static)
144
17
1.5
2
.44 (pitot)
144
16.14
1.5
3
.312 (tooling)
142.75
16
2.75
4
Remaining 8 holes in upper RH, aft side of frame. Do not
remove grommets, anti-chafe material, or sealing compound.
e.
Using flashlight and 10X magnifier inspect the upper left corner area of the FS 176 frame. Pay particular at tention to
the area around all holes. If cracks are found refer to paragraph 9 and complete inspection.
f.
Using flashlight and 10X magnifier inspect the upper portion of the FS 176 frame cells between left BL 23.75 and right
BL 23.75 between WL 145.5 and 141.62. If cracks are found refer to paragraph 9 and complete inspection.
g.
Using flashlight and 10X magnifier inspect the area of the No. 2 right/left hand stringer connection at BL 23.75, WL
145.5. If cracks are found refer to paragraph 9 and complete inspection.
h.
Upon completion of the visual inspection contact AVIM support to schedule an eddy current inspection of the following
holes previously visually inspected on right hand aft side of the frame on or before the next phase:
Hole
Hole Diameter
Location, RH
Distance From Top
Number
Side
of Frame
WL
BL
1
.63 (static)
144
17
1.5
2
.44 (pitot)
144
16.14
1.5
3
.312 (tooling)
142.75
16
2.75
i.
The eddy current inspection will be performed as a recurring inspection at every phase.
j.
During next phase inspection visually inspect center opening in the FS 176 frame.
(1) Defuel aircraft.
(2) Remove ammo handling hardware.
(3) Remove panel P/N 7-311113510-11.
(4) Using flashlight and 10X magnifier visually inspect the inner flange of the FS 176 frame from WL 139.8, BL
0.0 around the cutout to WL 122.25, BL 17.55 for cracks resulting from previous fuel cell
removal/installation.
9. Correction Procedures.
a. If no cracks are found:
(1) Perform recurring visual inspection IAW paragraph 8 of this Technical Bulletin.
(2) Perform recurring eddy current inspection at every phase using qualified
3
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