MIL-DTL-85769B(AS)
TABLE III. Conformance inspection.
Inspection or test
Requirement paragraph
Test paragraph
Nondestructive inspection
Visual
3.5
4.5.1
Radiographic
3.3.1
4.5.2
Circuit resistance
3.3.2
4.5.3
Destructive inspection
Ballistic test
3.4
4.5.5
@ -40°F
@ 140°F
4.5 Test methods
4.5.1 Visual. Motors and components shall be visually inspected to ensure the
requirements of 3.5 are met.
4.5.2 Radiographic inspection (M101). Each rocket motor assembly shall be subjected to
radiographic inspection in accordance with ASTM-E1742, radiographic quality 2-1T for
conformance to DL1638AS120 (see 3.3.1).
4.5.3 Circuit resistance (M102). The rocket motor igniters shall be tested for circuit
resistance by applying 0.010 amperes (maximum) to the initiator assembly circuit at 70+10°F.
4.5.4 Environmental and operational tests.
4.5.4.1 High temperature storage. Rocket motors shall be placed in a conditioning
chamber at 140° F for 45 days in accordance with MIL-STD-810, Method 501.4, Procedure I.
4.5.4.2 Temperature shock. The rocket motors shall withstand temperature shock in
accordance with MIL-STD-810, Method 503.4, Procedure I, Steady State. The motors shall be
equally divided into two groups with each group subjected to alternate conditioning chambers at
-40°F and 140°F. One group shall begin and end at -40°F, the other at 140°F. The motors shall
remain in each chamber for not greater than 8 hours, then transferred within 5 minutes to the
other chamber. Each motor shall undergo a total of 3 cycles (see 6.5.2). After temperature
cycling, the grain shall be returned to ambient temperature and radiographically inspected as
specified in 4.5.2.
4.5.4.3 Salt fog. The rocket motor shall be subjected to an aqueous salt atmosphere in
accordance with MIL-STD-810, Method 509.4, Procedure I, Aggravated Screening. Test
duration shall be 48 hours. After exposure, the motor shall be allowed to dry for 48 hours under
ambient conditions.
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