MIL-S-6551A(USAF)
3.3.3.8.2 Sides. The load requirements shall be identical to those specified in paragraph 3.3.3.8.1 with the exception that the direction of application of the loads shall be 20 degrees to either side of the forward direction.
3.3.3.8.3 Downward. A load of 4,000 pounds ultimate, 2,665 pounds proof, shall be applied downward perpendicular to the seat bottom {pan) and through the center of gravity of the crew member. The load shall be distributed
over the seat bottom. The seat shall be adjusted to the up position during
the test.
3.3.3.8.4 Back. A load of 3,000 pounds ultimate, 2,000 pounds proof, shall be uniformly distributed over an area on the inside face of the seat back equal to that occupied by the parachute and applied perpendicular to the surface of the seat back. The maximum deflection of the seat back shall not exceed 5/8-inch while the seat supports the ultimate loa4. The seat shall
be adjusted to the up position during this test.
3.4 Interchangeability. All parts having the same manufacturer's part number shall be directly and completely interchangeable with each other with respect to installation and performance. Changes in manufacturer's part numbers shall be governed by the drawing number requirements of Specification DOD-D-1000.
3.5 Dimensions. The outline dimensions of the seat shall be generally within the limiting dimensions specified in Figures 1, 2, 3, 4, 5, and 6� Unless otherwise specified, a tolerance of plus or minus 1/8-inch will be allowed on the dimensions.
3.6 Weight. The weight of the part of the crew ejection seat that is ejected shall not exceed the following:
TypeH-1: Type H-2:
75 pounds
60 pounds
3.7 Color. The seat color shall be lacquer in accordance with Specification
No TT-L-20.
3.8 Finish. Aluminum alloy parts shall be anodically treated in accordance with MIL-A-8625, Type I and II as applicable and non-corrosion-resisting
steel parts shall be cadmium plated in accordance with Specification QQ-P-416. Aluminum alloy 7079 shall not be used. The metal seat assembly shall be finished with one coat of primer conforming to Specification MIL-P-23377 and top-coated with two coats of lacquer conforming to Specification TT-L-20
(color 36231) except magnesium parts which shall receive two coats of primer
and two coats of aluminumized lacquer. Magnesium. alloy parts shall be
treated in accordance with Specification MIL-M-3171 prior to coating with
primer and lacq�er.
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