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MIL-S-8551O(AS)
3.3.1 Seating surface. The seat bottom and back shall be designed for comfort
and durability. Seat bottoms made of fabric shall be provided with means of tighten-
ing to compensate for sagging in use. Sufficient clearance between fabric backs and
bottoms shall be provided to preclude body contact with structure when subjected to
the specified loads (see 3.6).  Fabric tensile strength characteristics shall be
sufficient to preclude tearing or complete structural failure when dynamically
loaded by the occupant inertial forces resulting from the dynamic test requirements
of figure 3.  To accommodate back and butt packs that troops may be wearing, the
backs of type II seats shall be convertible without tools to provide the recess
shown in figure 1.  Maximum time to convert either way shall not exceed 10 seconds,
and both back supports shall meet the strength requirements.
3.3.2 Crash resistance.  The seat shall prevent the 5th through 95th-percentile
occupants (see 6.4.1) from experiencing vertical decelerations in excess of human
tolerance (see figure 2) during crash pulses of the severity shown in figure 3 and
not experience structural failure.  Energy shall be absorbed in the vertical axis by
load-limiting devices.  The energy-absorption stroke shall be the maximum attainable
in the space between the seat bottom and the aircraft floor.  In any case, not less
than 14 inches of vertical stroking distance shall be provided when measured at the
occupants center of gravity.  The seat and restraint shall minimize occupant subma-
rining (see 6.4.5) and dynamic overshoot (see 6.4.6).
3.3.3 Seat attachment.  Acceptable means of attaching seats to the cabin interior
are listed below in order of desirability:
a.
Suspended from the ceiling with attenuators, and wall stabilized.
b.
Suspended from the ceiling with attenuators, and floor stabilized.
c.
Ceiling and floor mounted (vertical energy attenuators above and
below seat).
Wall mounted with attenuators.
d.
e.
Floor mounted with attenuators.
3.3.3.1 Attachment distortion.  Seat attachments shall be capable of accommo-
dating crash induced cabin distortion consisting of a four (4) inch vertical dis-
placement and a 10  misalignment of any attachment as shown in figure 15 for the
floor warpage condition.  Figure 16 defines the requirements for the bulkhead at-
tachment condition.
3.3.4 Seat folding and stowing. Seats shall be so designed that they may be
quickly removed or folded and secured. Tools shall not be required
.3.3.4.1 Seat disconnect time. The time for sidconnecting each size 1 seat (one-
man seat) by one man shall not exceed 20 seconds. The time for disconnecting multi-
unit seats by one man shall not exceed 20 seconds multiplied by the seat size
number.
5

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