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|  MIL-S-18471G(AS)
3.2 Detail design requirements.
3.2.1 System design. The escape system includes: the ejection seat
assembly, aircraft canopy and escape path clearance subsystem, sequencing
subsystem, aircraft interface, and the aircrewember interface. The ejection
seat assembly shall include ejection seat mounted components and subsystems.
As part of the design effort, tradeoff analyses shall be conducted among the
possible design alternatives that are available within the range and limits
of the detail specification or contract (see 6.2.2). The contractor shall
ensure that all ejection seat assembly to aircraft interface connections
disconnect automatically upon ejection of the ejection seat from the aircraft
and do not cause injury to the aircrewmember or damage to personal equipment.
The desiqn of the assembly shall prevent leg abduction during the escape
sequence under the conditions specified in 3.3.2. All interface connections
shall be easily and securely connected upon ejection seat assembly installa-
tion and easily disconnected upon ejection seat assembly removal. The
escape system shall be electrically grounded to the aircraft structure in
accordance with MIL-B-5087, Class S.
3.2.1.1 Aircrewmember accommodation. The ejection seat assembly shall
accommodate the aircrewmember anthropometric population range specified in the
contract or aircraft detailed specification with the aircrewmember wearing
full personal flight gear (see appendix). The ejection seat assembly shall
provide comfortable and adequate support arid retention of the aircrewmember's
body under all conditions of flight throughout the aircraft performance
envelope, including takeoff and landing. All antropometric data for aircrew-
members shall be in accordance with SY-121R-81.
3.2.1.2 Cockpit compatibility. The aircrewmember station geometry shall
be in accordance with MIL-STD-1333. The ejection seat assembly shall be
compatible with the aircrewmember station in which the ejection seat assembly
is to be installed. Fully-equipped aircrewmembers within the specified
anthropometric population range shall be able to reach and fully actuate all
emergency aircraft controls throughout the full range of ejection seat assembly
adjustments while fully restrained in the full-back position by the restraint
subsystem. Each aircrewmember shall be able to reach and actuate all normal
aircraft and equipment controls assigned to or located in the crew station
with the ejection seat assembly adjusted to place the occupant's eye level at
the design eye position. Bivariate anthropometric data for verifying the
compatibility of the aircrewmember while seated in the ejection seat assembly
shall be in accordance with SY-121R-81. The location of the ejection seat
assembly, in relation to other aircraft equipment, shall permit the aircrewmember
to ingress to and egress front the ejection seat assembly in a safe, rapid, and
uncomplicated manner. This location shall not hinder emergency manual escape
from the aircraft by fully equipped aircrewmembers.
3.2.1.3 Escape system controls. Design and placement of escape system
controls shall be in accordance with MIL-STD-1472 and shall not jeopardize the
safety of the aircrewmember actuating those escape system controls. The design
or placement of escape system controls shall not hinder the fully-equipped
aircrewmember's emergency manual escape from the aircraft throughout the
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