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|  MIL-N-81604C(AS)
Para 3.4.4.5b(3)
(cont)
self-test circuitry detects an over or under
voltage condition as specified in (1) above.
This may occur either in the event of a PSU
malfunction or if a lengthy aircraft power
interruption discharges the battery. This
output shall provide a ground when the malfunc-
tion flag is in the go state. The switch mini- *
mum current rating shall be 250 ma resistive
*
or 100 ma inductive at 28 volts d-c.
(4) PSU Fail - This discrete output from the PSU
to the CIU shall be connected to ground to
indicate that the PSU malfunction flag has been
*
set to the no-go state. This occurs whenever
the PSU self-test circuitry detects an over or
under voltage condition as specified in (1)
above. This may occur either in the event of
a PSU malfunction or if a lengthy aircraft power
interruption discharges the battery. The switch
contact minimum current rating shall be 250 ma
*
resistive or 100 ma inductive at 28 volts d-c.
This output shall be an open circuit in the go
*
state and a ground in the no-go state. This
*
signal shall-switch to the go state when the
mode switch OFF discrete is provided to the
PSU with input power supplied to the PSU. This
signal shall be routed through the ANCU to the
*
CIU to illuminate the PSU malfunction indica-
tor when in the no-go state.
*
(5) Flag Reset - The true (high) state of this input
to the PSU from the CAU shall reset the PSU mal-
function flag to the no-fault state. The
false (low, open, or CAU power off) state shall
cause restoration of the fault indicator cir-
cuit to its normal fault monitoring condition.
The PSU shall respond in this manner to true
or false states which occur for a minimum of
20 milliseconds. The line receiver in the PSU
shall be a Type C circuit.
(6) Mode Switch On - Refer to 3.4.4.4g.
(7) Mode Switch Off - Refer to 3.4.4.4h.
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