MIL-DTL-9479E (USAF)
4,300 pounds plus 25 times the seat system weight downward, through the occupant and seat
system combination cg.
h. Ejection airload - The ejection airload (simulating the dynamic pressure loads imposed
upon the seat and its occupant by windblast during ejection from the aircraft) as applied
normal to the centerline of the rollers (or slide blocks) and through the combined center of
pressure of the exposed portion of the seat and its occupant, distributed over that portion of
the seat back exposed to the airstream. For the application of this load, the seat shall be
positioned on the rails (or slide blocks) in the most structurally critical position. The ejection
airload shall be applied simultaneously with the applicable rocket-catapult load. The ejection
airload shall be computed in accordance with conventional methods of aerodynamic
computation and shall be subject to approval by the procuring activity. The critical condition
for computation of the ejection airload shall be assumed to be the maximum free-stream
dynamic pressure associated with the ejection seat system performance. Unless otherwise
specified, the computed load shall be considered an ultimate load at maximum aircraft speed
or 600 KEAS, whichever is less.
3.4.5.5 Environmental conditions. The seat system shall be capable of satisfactory operation
under the following conditions and shall withstand the applicable tests specified in section 4
without degradation in performance (see 4.5.6):
a. Operation at temperature from -65° to 160°F (see 4.5.6.1, 4.5.6.2).
b. Vibration which may be experienced within the aircraft structural limits (see 4.5.6.3).
c. Exposure to salt-laden atmosphere (see 4.5.6.4).
d. Exposure to a warm, highly humid atmosphere as encountered in tropical climates (see
4.5.6.5).
e. Exposure to rainfall as encountered in any locale (see 4.5.6.6).
f. Shock which may be experienced within the mechanical shock environment expected in
service use. The seat shall not become detached from the attachment points during crash
safety shock conditions as specified (see 4.5.6.9).
g. Exposure to dust (see 4.5.6.8).
h. Explosive decompression conditions which may be encountered in service use (see
4.5.6.10).
3.4.6 Materials, construction, corrosion protection treatments, and finishes.
3.4.6.1 Lubrication. Lubrication shall function satisfactorily within the temperature range of -65°
to +200°F (see 4.5, 4.5.2).
3.4.6.2 Metals. Metals shall be of the corrosion-resistant type or treated to resist corrosion due
to fuels, salt spray, or atmospheric conditions which may be encountered during normal service
(see 4.5).
3.4.6.2.1 Heat treatment. The heat treatment of aluminum and steel parts, if accomplished, shall
be in accordance with ASTM B597 and SAE AMS 2759, respectively (see 4.5.2).
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