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| MIL-S-8551O(AS)
3.10 Environmental resistance. The seat with restraint system shall be capable
of operating and of meeting the structural requirements of 4.6.2 after exposure to
the following conditions:
3.10.1 Temperature. The seat shall deliver the specified operational and
crashworthiness performance when subjected to the 4.6.4.1 and 4.6.4.2 temperature
tests.
3.10.2 Sunshine. All nonfabric materials shall show no evidence of any degrading
effect when subjected to the 4.6.4.3 sunshine test.
The seat shall withstand the humidity test specified in
3.10.3 Humidity.
4.6.4.4.
3.10.4 Fungus. If any material utilized in the construction of the seat is
suspected to be a nutrient to fungi, the material shall show no deterioration when
subjected to fungus tests in accordance with 4.6.4.5.
3.10.5 Salt fog. All materials used in the construction of the seat shall
withstand the salt fog test of 4.6.4.6.
3.10.6 Dust. The seat shall be capable of satisfactory operation after exposure
to the dust test-specified in 4.6.4.7.
3.10.7 Vibration. The seat shall be capable of satisfactory operation after
being subjected to the vibration tests of 4.6.4.8. The occupied and unoccupied seat
shall be free of resonance within the frequency range of the aircraft in which it
will be used and no amplification shall occur.
The seat shall be capable of satisfactory operation after the
3.10.8 Mud.
4.6.4,9 test.
3.11 Dimensions. Seats shall comply with the dimensions shown in figure 1.
Unless otherwise specified, a tolerance of 1/16 inch will be allowed for seat
overall dimensions. Restraint system webbing dimensions shall comply with table 11,
figures 5 and 6. The seat package, when it is in the stowed position, shall be held
to a minimum size, not to exceed a thickness of 6 inches.
3.12 Finish.
3.12.1 Surface roughness. All exterior surfaces of the seat and restraint shall
be free from any sharp edges or corners; and any other projection sthat could scratch
the hands or damage the clothing of the occupant.
3.12.2 Finishes. Aluminum alloy parts shall be anodized in accordance with MIL-
A-8625, type 11. Magnesium alloy parts shall be treated in accordance with MIL-M-
3171. Corrosive steel parts shall be either cadmium-plated in accordance with QQ-P-
416; zinc-plated in accordance with QQ-Z-325; or chrome plated in accordance with
QQ-C-320.
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