MIL-DTL-60201D
4.3.3 Radiographic examination. All assembled thrusters shall be radiographically examined in
accordance with ASTM E 1742, with the exception that an thruster assembly will be used for the
penetrameter. Any observable imperfections in components or assembly shall be cause for rejection. The
thrusters shall be positioned for the most revealing exposure, with the long axis of each assembly
perpendicular to the rays of the X-ray machine. All thrusters shall be identified with serial numbers prior to
X-ray examination. The serial numbers shall be in consecutive order beginning with the number 001 in each
production lot. Any missing numbers are to be identified on the X-rays. The thrusters shall be arranged on
trays or boards in consecutive numerical order, and each radiograph shall carry a permanent identification of
the units displayed thereon. The radiographic plate identification shall include item nomenclature, the
complete lot number, the span of serial numbers displayed, and the contract number. The radiographs of the
entire production lot shall accompany the ballistic sample to the activity conducting the production lot
acceptance test. Defective thrusters found during X-ray review are to be marked on the X-ray prior to
shipment and those defective items shall be removed from the production lot. Film interpretation of the
radiographs shall verify the presence and correct positioning of the following parts:
a.
Cartridge, Impulse, P/N 10520589
b.
Firing Pin, P/N 8593864
c.
Head, P/N 10521455
d.
Shear Pin, P/N 10521618
e.
Trunnion, P/N 8594482
f.
Guide, Retainer, P/N 10521616
g.
Sleeve, P/N 10521617
h.
Body, P/N 10534179
i.
Keys (3), P/N 10534180
j.
Piston, P/N 10534181
k.
Piston, unlocking, P/N 10534182
l.
Ring, P/N 10534183
m.
Spring, P/N 10534184
n.
O-ring, P/N MS29513-12
o.
O-ring, P/N MS29513-113
p.
O-ring (2), P/N MS29513-212
q.
O-ring, P/N MS29513-214
r.
Cap Screw (2), P/N MS16998-9
4.3.4 Functional.
4.3.4.1 Ballistics. The test sample shall be rigidly supported so that the entire thrust is borne by the
thruster mounting points. The samples shall be tested within 10 minutes after removal from the temperature
conditioning chamber. When this time limit is exceeded, the sample units shall be reconditioned at the
original temperatures.
4.3.4.2 Temperature conditioning. Each assembled thruster shall be conditioned for not less than 4
hours nor greater than 24 hours. When reconditioning thrusters at -65F, all condensation shall be removed
from the exterior surfaces before returning the thruster to the conditioning chamber.
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