MIL-DTL-9320E
3.4.2 Electrical circuits.
3.4.2.1 Power input. Terminal A of the connector shall be connected to 28 V DC positive.
The unit shall be energized by connection of terminal B through external circuitry to 28 V DC
negative.
3.4.2.2 System loading. The warning signal shall be compatible with the aircraft
communication system. The portion of the communication system into which the warning signal
shall operate is essentially an audio transformer terminated in a 9 ohms resistive headset. The
transformer should have the following characteristics: Line type, primary impedance 150 Ohms,
primary DC resistance of 7.5 ohms maximum, a secondary impedance of 9 ohms, a secondary
DC resistance of 4.5 ohms maximum, a frequency response of 200 Hz to 6,000 Hz, and an output
of 200 ±5 mW.
3.4.2.3 Electrical output characteristics. When not energized, the warning signal shall
present an open circuit to associated communications equipment. The resistance between any
output circuit and terminal A of the connector shall be not less than 10 megohms. When not
energized and 28 V DC is applied to pin B and pin C is grounded, the continuous current flow is
to be less than 1.0 milliampere (mA). When the signal warning is energized, it shall be
impossible for uninterrupted direct current to be conducted into the associated communication
equipment.
3.4.2.4 Power output requirement. When operating on 28 V DC, the warning signal
shall be capable of delivering 25 mA average direct current, minimum, into a 150-ohm load.
3.4.3 Dielectric strength. When tested as specified in 4.5.2, the warning signal shall
withstand a voltage of 600 V root mean square (RMS) for 60 seconds when applied
simultaneously between all connector terminals and the case.
3.4.4 Current consumption. When tested as specified in 4.5.3, the average current
consumed by the warning signal shall not exceed 0.20 amperes when operating on 29 V DC.
3.4.5 Operating voltage. When tested as specified in 4.5.4, the warning signal shall
operate as specified in 3.4.1 from 27 V DC to 29 V DC. The warning signal shall operate
without incurring damage between 14 V DC to 29 V DC.
3.4.6 Environmental conditions. The warning signal shall operate electrically under the
following conditions:
a. Vibration: When tested as specified in 4.5.9, the warning signal shall withstand
typical aircraft vibration. Vibration isolators shall not be used.
b. Shock: When tested as specified in 4.5.10, the warning signal shall withstand a shock
of 50 g.
c. High altitude - low temperature: When tested as specified in 4.5.11, the warning
signal shall withstand pressure equivalent to 80,000 feet altitude and temperature of -65 °C.
d. Temperature: When tested as specified in 4.5.13 and 4.5.14, the warning signal shall
operate without failure from -65 °C to 125 °C.
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