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Escape system component and subsystem specifications |
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|  MIL-S-18471G(AS)
3.2.2.17 Escape system component and subsystem specifications. The
contractor shall prepare for procuring activity approval, specifications
for components and subsystems covering the design, test, manufacture, or
quality assurance procedures not adequately defined by military or federal
specifications or standards or acceptable non-government organization speci-
fications or standards (see 6.2.2). Specifications shall be prepared in
accordance with MIL-STD-961.
3.3 System performance. The escape system shall provide immediate
initiation and the subsequent complete automatic functioning of all components
and subsystems in proper sequence, after a single non-interrupted actuation of
any appropriate escape system firing control handle.
3.3.1 Aircrewmember maximum loads. Loading during the ejection sequence
shall be controlled to minimize adverse physiological consequences on the
aircrewmember while meeting the performance criteria of 3.3.2. Maximum
loads imparted to the aircrewmember during the ejection sequence shall:
a.
Be not greater than 25g's in the Z-axis at a 70F temperature
condition during the initial boost or catapult phase as measured
by seat-mounted instrumentation and calculated in accordance
with 30.3.8c (see 4.4.2 and 4.6.1).
b. Be in accordance with the requirements of 3.2.2.12.1.c and
3.2.2.12.2.b for aircraft canopy and escape path clearance
(see 4.4.1).
c. Be in compliance with table I for all other phases leading up
to and including parachute opening (see 4.4.2 and 4.6.1).
d. Not be evaluated after recovery parachute opening.
3.3.2 Escape envelope. Upon actuation of the escape system, the aircrew-
member shall be provided with the escape capabilities throughout the performance
envelope represented in table II for all conditions of ejection seat-aircrew-
member center of gravity locations as specified in 3.2.2.4.1, regardless of
the position of the ejection seat height adjustment or position of the
ejection seat assembly within the aircraft (see 4.4.2, 4.4.3, and 4.6.1).
3.3.3 Emergency egress. The aircrewmember shall be provided with the
capability of egressing from the aircraft in an emergency without ejecting
(see 4.6.2.1.1). During emergency egress, the aircrewmember shall have the
option to either retain or detach the survival equipment container. The
aircrewmember shall have the capability of clearing the escape path for
rapid egress either on land or in the water to a depth of thirty feet,
measured from the surface of the water to the top of the aircraft canopy.
The time required for emergency egress, exclusive of aircraft canopy clearance
but including all aircrewmember actuations, shall be not greater than 10 seconds.
3.4 System effectiveness.
3.4.1 Reliability. The contractor shall establish, implement, and document
a system reliability program in accordance with and embodying the program
elements defined in MIL-STD-2067 (see 6.2.2).
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