MIL-DTL-62737A(AT)
4.2.6.1 Temperature. To determine conformance to 3.6.1, the PWA shall be tested as
follows.
4.2.6.1.1 High temperature (operating). To determine conformance to 3.6.1.1, the PWA
shall be subjected to high temperature test in accordance with method 501.3, procedure II (hot
category), of MIL-STD-810, or equivalent (see 4.2.1), and tested to 3.3.
4.2.6.1.2 Low temperature (operating). To determine conformance to 3.6.1.2, the PWA
shall be subjected to low temperature test in accordance with method 502.3, procedure II, of
MIL-STD-810, or equivalent (see 4.2.1), and tested to 3.3.
4.2.6.1.3 High temperature (nonoperating). To determine conformance to 3.6.1.3, the
PWA shall be subjected to high temperature test in accordance with method 501.3, procedure I,
of MIL-STD-810, or equivalent (see 4.2.1).
4.2.6.1.4 Low temperature (nonoperating). To determine conformance to 3.6.1.4, the
PWA shall be subjected to low temperature test in accordance with method 502.3, procedure I, of
MIL-STD-810, or equivalent (see 4.2.1).
4.2.6.2 Fungus. To determine conformance to 3.6.2, the PWA shall be subjected to the
applicable fungus test in accordance with method 508.4 of MIL-STD-810 (28 day test), or
equivalent (see 4.2.1).
4.2.6.3 Shock. To determine conformance to 3.6.3, the PWA shall be subjected to the
shock test in accordance with method 516.4, Procedure I, 40g peak of MIL-STD-810, or
equivalent (see 4.2.1), and tested to 3.3 after shock test.
4.2.6.4 Vibration. To determine conformance to 3.6.4, the PWA shall be subjected to a
vibration test using a composite of figure 11 through 13. These figures represent the cargo
environment at the cargo bed of a composite of tactical wheeled vehicles, the 5-ton M813 truck
and the 12-ton M127 semitrailer. The data include differing vehicle loading conditions traversing
over specially designed courses ranging from paved highway to off road conditions at various
vehicle speeds. The spectrum is broad band random with peaks and notches at various discrete
frequency bands. Break points are provided for establishing the spectrum shape. The test
duration is 500 miles. The PWA shall be tested to 3.3 after the vibration test.
4.2.6.5 Burn-in. When required (see 6.2), the burn-in shall consist of three temperature
cycles and a six gravity unit (g) root mean square (rms) random vibration as follows:
a. Temperature cycle. Each temperature cycle shall consist of 30 minutes at minus
(-) 60 degrees Fahrenheit (°F) (-51 degrees Celsius (°C)) and 30 minutes at plus
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