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|  MIL-S-18471G(AS)
a manual control mode. Any combination of methods, including but not limited
to ballistic jettisoning, camming, ballistic fragmenting, mechanical fracturing,
or other methods, shall be used to perform the clearing functions within the
three modes, provided that subsystem and mode requirements specified herein
are complied with. Designs which result in implosion during ejection shall not
be used. The aircraft canopy and escape path clearance subsystem capabilities
shall be demonstrated during the tests of 4.4.1, 4.4.2, and 4.6 and shall
be capable of meeting the following requirements:
Remain securely stowed in a dormant status during normal
a.
aircraft operating conditions.
Upon actuation of any ejection seat firing control,
b.
immediately actuate the redundant primary mode and the
automatic backup mode in a programmed sequence as required
to clear the escape path of all aircraft structure and
equipment such as the aircraft canopy, canopy glass, consoles,
controls, etc. Partial or toal failure of the redundant
primary mode shall not prevent completion of the escape path
clearing function by the backup mode.
Incorporate a manual control handle for initiating escape
c.
path clearance without initiating seat ejection.
Perform the escape path clearing function in a manner which
d.
delays the ejection seat's first motion to no more than
0.3 seconds following escape system initiation. Partial
or total failure of the redundant primary mode shall not
result in extending the time delay limit to more than 0.3
seconds.
Limit impulse noise levels resulting from subsystem operation
e.
in accordance with requirements of 3.2.1.5.
Function without degrading escape system performance throughout
f.
the escape envelope defined in 3.3.2.
3.2.2.12.1 Redundant primary mode. The aircraft canopy and escape path
clearance subsystem redundant primary mode shall be capable of meeting the
requirements specified in 3.2.2.12 and the following:
a. Upon actuation of any ejection seat firing control handle,
utilize redundant elements to automatically clear the
escape path of all aircraft structure and equipment.
b. Perform the escape path clearing function in a manner
which ensures that fixed obstructions (e.g., unbroken
aircraft canopy glass which is attached to the aircraft
canopy frame, consoles, and instrument panels) at each
point are removed prior to passage of the aircrewmember
through that point. Contact with fragmented or broken
materials shall be minimized.
c. During the redundant primary mode, limit the catapult
pressure dynamic loading contribution imposed upon the
ejection seat by the canopy or other structure to a
retarding pulse of peak amplitude not greater than 3.0g's
and base duration not greater than 20 milliseconds as
40
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