MIL-DTL-85097/7D(OS)
pounds. Travel of sear to actuate the rocket motor shall be not less than 0.25 inch nor greater than 0.69 inch.
Travel to completely remove the sear shall be 0.75 inch maximum.
3.3.5 Center of gravity. The calculated or measured center of gravity shall be within 0.03 inch of the axis of
rotation.
4. VERIFICATION
4.1 Preproduction/production.
4.1.1 Conditioning temperatures. The conditioning temperatures and tolerance shall be as follows:
a. Cold: 40 ± 5 F
b. Hot: 160 ± 5 F
4.1.2 Conditioning periods. Time for conditioning prior to static firing or during temperature cycling shall
be as follows:
a. Static firing: 4 hours, minimum
b. Temperature cycling: 4 hours, minimum
4.1.3 Radiographic inspection. All components or assemblies shall be radiographed in two views 90
degrees apart.
4.1.4 Ballistic testing. Ballistic testing, for conformance to the requirements of 3.3.2, shall be performed as
specified in MIL-A-85097.
4.1.5 Sear pull test. Sear pull tests shall be conducted on all rocket motors. The sear force shall be statically
determined, before final assembly, by means of a pull test fixture. The sear pull velocity shall be 18 ± 2 ft/s.
Test results shall be made available to the procuring activity with DCASR acceptance (see 6.2).
5. PACKAGING
(This section is not applicable to this associated 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 Mk 84 Mod 1 and Mod 2 Rocket Motors are used as a means of stabilizing the
ejection seat during an emergency escape of personnel from the S-3A Aircraft.
6.2 Acquisition requirements. Acquisition documents should specify the following:
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