MIL-PRF-58111A(CR)
3.8.8 Explosive atmosphere. When operating in an explosive atmosphere environment
the unit shall not inflame a gaseous air mixture.
3.8.9 Rain. During periods of heavy precipitation with intermittent wind.
3.8.10 Acceleration. When exposed to steady-state acceleration levels of up to 6g for a
duration of 1 minute.
3.8.11 Vibration. When subjected to helicopter vibration characterized by dominant
sinusoidal superimposed on a broadband random background.
3.8.12 Shock. The equipment shall withstand shocks encountered during in-service use
and field servicing.
3.8.13 Crash safety. The equipment shall withstand forces induced by in-service crash
landings. A dummy mass with outside structure and mounting points identical to the flight
hardware and mass-loaded to be dynamically the same as the flight hardware may be used for the
crash safety test.
3.9 Voltage protection, low and reverse. The unit shall be subjected to input power
requirements of paragraph 3.10 and incur no damage after being subjected to 33 volts dc reverse
polarity and continuous operation at 17 to 33 volts dc.
3.10 Input power. The unit shall operate from normal 27.5 volt dc aircraft power and
shall maintain required performance over the input voltage range of 22 to 33 volts dc. It shall also
maintain required performance when subjected to input overvoltage. During emergency mode,
17.0 volts to 22.0 volts, and undervoltage conditions, the unit will operate with degraded
performance. When the input current is measured with 29.0 volt dc input, 1.25 volts audio output
at the headset pins (before transmit attenuation (see 3.29) and 0 dBm output on one transmitter
audio output line, the CSC input current shall not exceed 250 milliamps, 7.25 watts. The input
power requirements for front panel display lamps shall be no greater than:
a. 28 volts dc, 4.0 watts (red), 6.5 watts (green)
b. 5 volt ac/dc, 4.0 watts (red), 6.5 watts (green)
c. 115V ac, 400 Hz. 3 watts
3.11 Output interphone.
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