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|  MIL-S-18471G(AS)
f.
Automatically separate from the ejection seat and remain
secured to the aircrewmember during and after the separation
of the aircrewmember and the ejection seat. Separation shall
be in a repeatable, controlled positive manner through an
unobstructed path.
Be compatible with the positioning and restraint subsystem
g.
as specified in 3.2.2.3.
h.
Be easily detachable at the aircrewmember's option during
ground emergency egress.
i.
Provide an actuation handle(s) that is(are) useable by the
specified population of aircrewmembers using a single gloved
hand while suspended in the parachute harness.
Be of the lightest practical weight.
j.
3.2.2.7,1 Escape oxygen supply. The escape oxygen supply shall provide
not less than 7.0 cubic feet of free oxygen at 14.7 pounds-force per square
inch absolute (psia) and 60F (100 cubic inches at 1800 pounds-force per
square inch gage (psig)). Oxygen cylinders at 1800 psig, if used, shall be
in accordance with MIL-C-7905. The escape oxygen supply shall contain a
manual actuation provision that shall be designed and located to be accessible
to the aircrewmember for manual actuation while seated in the ejection seat
assembly in the aircrewmember station and in any position of ejection seat
adjustments The escape oxyqen supply shall be actuated automatically in
accordance with MIL-S-81018 during ejection for both rigid and non-rigid
survival equipment containers. The oxygen and communication services, for
either rigid or non-rigid containers, shall be as specified in MIL-S-81018
or the applicable detail specifications
3.2.2.8 Personal services connections. Personal services connections
shall be provided and be standard according to the service provided. All
connections shall be positive so that proper attachment is assured. All
disconnections shall be automatic during ejection. The disconnection of
the personal services leads shall not result in injury to the aircrewmember
or damage to flight garments or survival equipment. Upon emergency egress
with the survival kit, the personal services connections shall readily
disengage and shall not impede the escape of the aircrewmember.
3.2.2.9 Intraseat sequencing subsystems. The operating sequence of the
ejection seat assembly and its components and subsystems shall be controlled
by the intraseat sequencing subsystem approved by the procuring activity (see
6.2.2). The subsystem shall function following initiation by either the
initiation subsystem or the interseat sequencing/spatial separation subsystem
as applicable. Any method of signal transmission across the ejection seat
assembly-aircraft interfaces shall be automatically connected when the ejection
seat assembly is installed and automatically disconnected when the ejection
seat assembly is removed. Any method of signal transmission across the ejection
seat-aircraft interface shall be redundant and shall be protected against
damage, foreign objects, and dirt at all times. The intraseat sequencing
subsystem and its sensors shall be protected from, or shall be designed to
function properly after contamination by, metal chips and filings, moisture,
sand, dust, oil, grease, hydraulic fluids, and other debris potentially present
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