MIL-DTL-85097/13C(OS)
4.1.2 Conditioning temperature. The conditioning temperatures and tolerances shall be as follows:
a. Cold: !65 ± 5EF
b. Hot: 165 ± 5EF
4.1.3 Conditioning period. Time for temperature conditioning prior to static firing or during
temperature cycling shall be as follows:
a. Static firing: 4 hours, minimum
b. Temperature cycling: 5 hours, minimum
4.1.4 Radiographic inspection. All components or assemblies shall be radiographed in two views 90E
apart.
4.1.5 Hydrostatic proof test. Each motor tube shall be subjected to the hydrostatic tests of drawing
1507AS132.
4.1.6 Leakage test. Each rocket motor assembly shall be subjected to a dry leak test to verify
compliance with a leakage rate of less than 1 x 10 4 cc/sec air.
4.1.7 Threaded joint torque test. The 1.890-24NS-3 threaded joints (2) of each rocket motor assembly
shall be subjected to the torque test of MIL-P-83126.
4.1.8 Electrical bonding resistance test. The electrical bonding resistance between the shielded mild
detonating cord (SMDC) housing and the mounting lugs of each rocket motor assembly, selected as a
sampling test specimen, shall be tested in accordance with MIL-STD-464.
5. PACKAGING
(This section is not applicable to this specification.)
6. NOTES
(This section contains information of a general or explanatory nature that may be helpful, but is not
mandatory.)
6.1 Intended use. The rocket motors described herein are intended to be used to eject the canopy during
an emergency crew ejection from the F/A/TF-18 Aircraft.
6.2 Acquisition requirements. Acquisition documents must specify the following:
a. Title, number, and date of this specification.
b. Issue of DoDISS to be cited in the solicitation, and if required, the specific issue of
individual documents referenced (see 2.2.1 and 2.2.2).
c. Mark and Mod designation of rocket motor.
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