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|  MIL-N-81604C(AS)
Para 3.5.5.8
(cont)
g. DOP - The DOP lamp ON without the INS lamp
ON shall indicate the doppler navigation
mode.
h .AD - The AD lamp ON shall indicate the air
data mode.
Malfunction Lamps - The following malfunction
i.
lamps shall be controlled by the malfunction
flags in the specified units: ANCU, IMU
CAU, and PSU. Except for the PSU, these
flags may be set under program control. The
malfunction lamps shall indicate the detec-
tion of a failure in the unit.
3.5.5.9 DIM/TEST Control - The DIM/TEST control shall serve a
dual function. When rotated, it shall control the intensity - of
*
the annunciator lamps, the display lamps, and the three Push
buttons (POS FIX, Enter and CLEAR). When depressed, it shall
initiate panel lamp test.
305.5.10 HDG SLEW - This shall be a five position rotary switch,
spring-loaded to cause it to return to the center (no slew) posi-
tion. It shall be used in the free attitude reference mode to
slew the grid heading outputs from the CAU in an increasing or
*
decreasing direction. Refer to appendix I.
3.5.5.11 Power Requirement - The CIU shall require maximum of
*
4 amperes (maximum steady-state) or 6 amperes (100-msec peak
*
transient) of +5 volts d-c 2 percent (measured at the CIU ex-
ternal connector) from the ANCU. The ANCU shall supply 5.1 volts
*
d-c (measured at the ANCU external connector) to the CIU to com-
pensate for cable losses. The CIU shall require a maximum of 2
*
watts of aircraft 115 volts rms for the ETI, and a maximum of 10
*
In addi-
watts of aircraft 5 volts rms or d-c for edgelighting.
tion, the CIU shall not require more than the transient current
*
levels specified in 3.5.4.7.
3.5.5.12 Mechanical Design -
a.
Weight - The CIU weight shall be no greater
than 5.8 pounds.
b.
Size - The CIU shall conform to the outline
and mounting drawing shown in figure 31.
126
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