MIL-DTL-9479E (USAF)
3.2.19 Survival subsystem. A survival kit in accordance with MIL-S-83427 shall be provided in
the seat bucket, except that oxygen equipment and provisions shall not be included within the kit.
The kit shall be restrained during negative g maneuvers. The system shall allow a seated crewman
to select manual or automatic deployment of the survival kit. The kit shall be attached to the
personal restraint subsystem and, when selected, shall be automatically deployed in conjunction
with the parachute recovery subsystem operation (see 4.5.1).
3.2.19.1 Personal locator devices. A method shall be incorporated for automatically actuating
personal locator devices upon seat ejection. Any personal locator device antenna shall be routed
to afford maximum signal capability. The automatic actuation feature shall include a rapid
dearming capability which will permit dearming of the locator device by the crew member while in
the seat (see 4.5.1).
3.3 Fit.
3.3.1 Dimensions. The seat system shall be compatible and integrate with the aircraft for which it
is manufactured (see 6.7). The dimensions of the seat system shall be as specified in figures 1 and
3 (see 4.5.2).
3.3.2 Weight. The weight of the seat system shall be kept to a minimum consistent with the
escape requirements and the performance of the aircraft (see 4.5.2).
3.3.3 Interchangeability. All parts having the same manufacturer's part number shall be directly
and completely interchangeable with each other with respect to installation and performance.
Changes in manufacturer's part numbers shall be documented by the contractor and provided to
the government when configuration control is transferred (see 4.5.2).
3.4 Function.
3.4.1 Windblast. Unless otherwise specified, the ejection seat shall be designed to prevent the
following windblast effects resulting from the maximum aircraft airspeed or 600 knots equivalent
airspeed (KEAS), whichever is less (see 4.5.6.11):
a. Disconnected personal leads.
b. Distorted personal leads.
c. Flailing of personal leads, equipment, or crewmember arms and legs.
d. Personnel restraint subsystem failure.
e. Separation or damage of seat components.
3.4.2 System operation time. The total time from ejection sequence initiation to full inflation of
the recovery parachute shall not exceed 3 seconds at any altitude below the pressure altitude
setting of the recovery parachute (see 4.5.8).
3.4.3 Acceleration limitations. The seat system shall protect the dummies utilized in all ejection
tests conducted without exceeding the acceleration limitations specified herein. The acceleration
limitations specified herein are given for acceleration measured or, during initial design
verification, computed as acting at the seat bucket. The limitations pertain to the condition where
the acceleration environment will not be amplified by the restraint system or seat cushion
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