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|  MIL-S-25073A(USAF)
c. Safety belt mountings: A load of 2880 pounds ultimate, 1920
pounds proof, applied to the lap safety belt mounting (equally
distributed between the two) on the side of the seat in a direction
forward and inclined 40 degrees up from the floor plane, and a load
of 1800 pounds ultimate, 1200 pounds proof, applied to the
shoulder harness take-up reel in a forward direction parallel to
the floor plane, as indicated in 4.5.2. These loads shall be
applied simultaneously and under the following separate conditions:
directly forward, 20 degrees to the right of forward, and 20
degrees to the left of forward. If the structure is shown to be
symmetrical, the yaw load need only be applied to one side.
3.6 Environmental exposure. The seat shall be capable of conforming all
requirements specified herein after exposure to the following environmental
conditions:
Humidity of 100 percent.
a.
b. Fungus growth as may be encountered in tropical climates.
c.
Salt spray as may be encountered in salt-sea atmosphere.
d.
Sand and dust as may be encountered in tropical climates.
e.
Sunshine.
Vibration.
f.
3.7 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 MIL-D-1OOO.
3.8 Weight The complete seat, including all parts, inertia reel, adequate
finish coating and tracks which permit a 6 inch fore-and-aft adjustment
shall not exceed a total weight of 45 pounds for the Type II seat and 30
pounds for the Type I. seat. The seat bottom and seat back cushions are
not considered a part of the seat for the purpose of this specification.
3.9 Color. The color of the seat structure shall be medium gray conform-
ing to color No. 36231 of FED-STD-595, unless otherwise specified by the
procuring agency.
3.10 Finish. Aluminum alloy parts shall be anodically treated in accordance
with MIL-A-8625. Magnesium-alloy parts shall be treated in accordance with
MIL-M-3171. Noncorrosion-resisting steel parts shall be cadmium-plated in
accordance with QQ-P-416, or zinc-plated in accordance with QQ-Z-325. The
seat shall have a paint finish consisting of one think coat of zinc-chromate
primer conforming to MIL-P-8585, followed by two coats of aircraft lacquer
conforming to TT-L-20, except that anodized aluminum alloy parts need not be
painted if colored-anodized.
3.11 Identification of product.
3.11.1 Identification of product. Equipment, assemblies and parts shall be
marked for identification in accordance with MIL-STD-13O.
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