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Safety belt and shoulder harness |
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|  MIL-S-25073A(USAF)
the roller and guide shall be as shown on Figures 2 and 3. The roller
shall have a minimum diameter of 1 inch.
3.4.7 Safety belt and shoulder harness. Provisions shall be made for the
use of either Type MD-1 or MD-2 safety belt conforming to drawing 54H19650 and
54H19651, respectively, the belt to be attached with l/4-inch diameter aircraft
bolts. The attachment fitting shall be of the fork type which will place the
attachment bolt in double shear. The point of attachment of the belt to the
seat shall be as indicated in Figure 3. Provisions shall also be made for the
use of the Type MB-2A shoulder harness (depicted on drawing 5D677).
3.4.8 Parachute support bulkhead. The seat shall be provided with a
metal bulkhead permanently fastened within the seat. The size and location
of this bulkhead shall be as shown in Figure 3.
3.4.9 Drain holes. Drain holes shall be provided to drain the seat with
the bottom in any position into which it might be placed by any normal
ground position of the airplane.
3.4.10 Tracks. The tracks which permit fore-and-aft adjustment of the seat
shall be provided with holes for attachment to the floor. These holes shall
be drilled 17/64 inch in diameter for l/k-inch bolts. The holes shall be
arranged in two rows on each track. The two rows shall be symmetrical about
the centerline of the tract (not in staggered rows) and shall be 2-1/2
inches apart. The longitudinal spacing of the holes in both rows shall be
5-1/2 inches between center starting with a set of holes directly below the
seat reference point when the seat is adjusted to a position midway of the
fore-and-aft travel The tolerance on the distance between the centerlines
of any two holes (on one track) shall be plus or minus 1/64 inch.
3.5 Construction.
3.5.1 Methods. Riveting or welding may be used for assembly of component
parts fabricated of metals which are suitable for this type of construction.
Fittings and joints which will require disassembly for installation or
removal of the seat from the airplane or for disassembly of the component
parts of the seat shall be bolted.
3.5.2 Projections The inside surfaces of the seat shall be free from
projections which could catch or damage by abrasion the parachute pack or the
clothing of the occupant. The exterior surfaces of the seat shall be free
from sharp edges or any projections which might scratch the hands or cloth-
ing of the occupant as he moves his arms about the sides of the seat to
handle equipment within his reach to the rear and to the sides.
3.5.3 Strength requirements. The seat shall have sufficient strength to
carry the following loads:
Types I and II:
a. Headrest: An aft load of 200 pounds ultimate, 135 pounds
proof, uniformly distributed over the headrest. The seat back
shall be inclined to the 13-1/2-degree position during this test.
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