 |
|||
|
|
|||
| ||||||||||
|
|  MIL-T-60201C
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 65 F, all condensation
shall be removed from the exterior surfaces before returning the thruster to the conditioning
chamber.
4.4 Inspection of packaging. The sampling and inspection of the packaging, packing, and
container marking shall be in accordance with section 5.
5. PACKAGING
5.1 Packing and marking. Packing and marking shall be Level A or B, as specified by the
contracting activity (see 6.2). Level A shall be in accordance with Drawings 8797741 and 8797742.
Level B shall be in accordance with Drawings 8797741 and 9217579.
5.1.1 Lot numbers. Lot numbers shall be in accordance with MIL-STD-1168.
5.2 Air Force packaging. Air Force packaging shall be in accordance with TPO 00-554-3103.
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 thruster assembly is used in conjunction with other propellant actuated
devices in Aircrew Emergency Escape Systems.
6.2 Acquisition requirements. Acquisition documents must specify the following:
a. Title, number, and revision letter of this specification
b. Issue of DODISS to be cited in the solicitation and, if required, the specific issue of
individual documents referenced (see 2.1.1 and 2.1.2)
11
|
|
Privacy Statement - Press Release - Copyright Information. - Contact Us |
Click
here for thousands of PDF manuals