MIL-S-58095A (AV)
3.7 Hardware. MS, AN or other military standard parts shall be used wherever
they are suitable for the purpose. Castings shall not be used in the primary
seat structure except in the inertia reel. The inertia reel and load carrying
castings in secondary structure shall be radiographically inspected per
MIL-C-6021. Primary structure is defined as any component whose failure under
crash loads would cause occupant displacement or loss of retention,
3.8 Environmental.
3.8.1 Temperature. The seat shall withstand nonoperating exposure from -65°
to +160°F (-54 to 71 °C ) without deterioration and deliver specified perfor-
mance in the range of -25° to +130°F (-32 to 54.°C) when subjected to the high
and low temperature tests of Methods 501 and 502, MIL-STD-810.
3.8.2 Solar Radiation. All materials used in the seat and exposed to sunshine
shall satisfy criteria in Method 505 of HIL-STD-810,
3.8.3 Humidity. The seat shall not deteriorate and shall operate
satisfactorily during and after being subjected to the humidity test specified
in Method 507 of MIL-STD-810.
3.8.4 Fungus. If any material utilized in the construction of the seat is
suspected to be a nutrient to fungi, the material shall no deterioration
when subjected to Method 508 of MIL-STD-810.
3.8.5 Salt fog. The seat shall be corrosion-resistant or processed to
withstand Method 509 of MIL-STD-810 without deterioration in the installed
condition.
3.8.6 Dust. The seat shall be capable of-satisfactory operation after
exposure to Method 510 or MIL-STD-810.
3.8.7 Vibration. The seat shall not deteriorate and shall be capable of
satisfactory operation after being subjected to the testing defined in 4.7.5.8.
3.9 Maintainability. Access to seat components shall conform to MIL-STD-1472.
The cushions and restraint shall be replaceable without removal of the seat
from the aircraft. Cushion replacement shall not require tools. Joints
requiring disassembly for installation and removal of the seat from the
aircraft, or disassembly of the component parts, shall be bolted. The design
shall require no scheduled maintenance.
3.10 Reliability. Endurance of component parts shall conform to specifications
of Section 4.
3.11 Physical Characteristics
3.11.1 Configuration. Basic seat design shall be consistent with the
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