MIL-S-58095A (AV)
requirements of MIL-STD-1472. Configuration and dimensions of the seat shall
conform to MIL-STD-1333. Other seat and restraint dimensions shall be based on
the anthropometric data of MIL-STD-1472 to fit a 5th to 95th percentile male
aviator with allowances for clothing and equipment. minimum inside seat width
shall be 19.0 inches (48cm). The overall seat and restraint system configuration
shall prevent occupant submarining under the 4.7.4 test conditions.
3.11.2 Adjustment. The seat shall have an adjustment range complying with
MIL-STD-1333 and provide and upward-downward and forward-aftward adjustment
pattern. The seat shall travel smoothly and be adjustable in increments of hot
more that 0.75 inch (19mm) in both axes. The adjustment mechanisms shall lock
the seat in position after each adjustment. Either a spring loaded or power
device may be used to raise the unlocked seat when the weight of the occupant is
removed. If a spring device is employed, the imbalance load shall be not more
than 125 pounds (556 newtons) when the seat is in the lowest position and not
less than 30 pounds (133 newtons) when the seat is in the highest position.
Suitable stops shall be provided at the ends of the adjustment range.
3.11.3 Controls. The seat adjustment controls shall be located on the forward
right hand side of the bucket for vertical adjustment and forward left hand
side for longitudinal adjustment. The inertia reel control shall be on the
forward left side of the bucket. Control levers shall be accessible to the
seat occupant clothed in all required personal flight and survival equipment
and reel locked. The position of the levers shall not change relative to the
occupant when the seat is adjusted. The locking mechanisms shall be released
by a forward movement of the controls and automatically lock, and indicate lock
by aft movement, when the controls are released. The location of the variable
load energy absorber control shall be visible and accessible for easy
adjustment. Movement and force requirements shall not exceed MIL-STD-1472
limits .
3.11.4 Cushions. The seat cushions shall be designed for comfort and
durability and not as a device to absorb crash energy. The thickness of the
compressed (1.0.G) cushion at the lowest point of the buttocks shall be between
0.5 inches (13mm) and 0.75 inches (19mm). The cushions shall be retained such
that aircraft maneuvers, crashes, or occupant motion shall not cause displace-
ment or separation.
3.11.5 Headrest. A headrest shall be provided that moves with the seat bucket
during seat adjustment and stroking. The headrest shall be positioned for the
5th through 95th percentile population. Headrest padding shall be 1 inch (25mm)
thick and consistent with Figure 1. Headrest width shall be a maximum consistent
with cockpit visibility requirements.
3.11.6 Drain holes. Unarmored buckets shall be provided with 0.25 inch (7mm)
diameter drains at the low point when the aircraft is in normal ground attitude.
Armored buckets shall be provided with provisions to drain moisture at the low
point when the aircraft is in normal ground attitude.
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