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|  MIL-D-70484(AR)
3.4.3.1.12 Power requirements. The DU shall operate in
accordance with MIL-STD-704A, Category B, Abnormal Steady state
Level (ASSL) 1. Normal operating voltage shall be 28 volts DC
and average current shall not exceed 3 amperes. Reversal of
polarity of the primary power shall not damage the DU or other RMS
components, or cause false fuzing or firing signals. There shall
be no false outputs resulting from transients or from application
or removal of power.
3.4.3.1.12.1 Standby power. Standby power, which provides
the primary power for the RMS, shall be supplied through the
helicopter master arm switch.
3.4.3.1.12.2 Master arm power. Arming power shall be
controlled by the master arm switch, for the purpose of powering
rocket fire circuits. The DU shall control the power to the
operations units such that no arming power is provided unless a
zone arming function is executed.
3.4.3.1.12.3 DU Panel illumination control/power. The DU
shall interface with the helicopter lighting circuitry for
electrical control and power to illuminate the panel lights and
display.
3.4.3.1.13 Internal power supplies. For over-voltage
protection, the voltage trip point shall be less than the maximum
voltage rating of the devices supplied by the internal power
supplies.
3.4.3.1.13.1 Operations unit power. This secondary power
source, derived from standby power, shall be regulated with over-
voltage and short circuit protection. The voltage available at
the DU output terminals shall be 20 VDC minimum, 21.5 VDC maximum
with an output current capability of 2.0 amperes steady-state,
2.85 amperes peak for 3 seconds maximum.
3.4.3.1.14 Trigger input. The DU shall interface with the
wing stores firing switches on the cyclic controls. Closure of
the wing stores firing switches shall be the final step in the
rocket firing sequence.
3.4.3.1.15 Mechanical interface. The panel shall be in
accordance with MS25212. The DU shall not exceed 4.5 inches in
height and 7.0 inches in length. The outline of the DU shall
conform to 9324104, DU Interface Control Drawing.
3.4.3.1.16 Proof test. Display Unit assemblies shall operate
when assembled to an accepted AH-1S helicopter.
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