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|  MIL-N-85005A(AS)
3.5.8.4.11
ITADS interface - The SDC shall provide the computer
subsystem interface with the ITADS as defined by Paragraphs 3.5.5 and
3.5.6.
3.5.8.4.12
Altimeter Interface - The SDC shall interface with
an AAU-21A or AAU-32A Digital Encoder Altimeter in accordance with
MIL-A-81403 or MIL-A-81852.
3.5.8.4.13
BITE - The SDC shall include a latching GO/NO-GO
indicator for continuous monitoring of SDC status. Manual reset of the
indicator shall be provided adjacent to the indicator. Hardware shall
be incorporated to monitor the status of the SDC power supply. As a
minimum, provision shall be made for software testing of critical SDC
hardware functions. Provisions shall also be made for reporting these
status indications to the NC for display on the Digital Display Indi-
cator.
Power
3.5.8.5.
3.5.3.8.5.1
Aircraft Power - The equipment shall utilize aircraft
power in accordance with paragraph 3.3.12 as follows:
(1) 115 VAC, 400 Hz, 3 0, Category B, 320 VA
(2) 0-26 VAC, 400 HZ, 1 0, 1.0 Amp.
(3) 28 VDC, 1.4 watts
(4) 26 VAC, 400 Hz, 1 0, 6 VA
3.5.9.5.2
System Power - The equipment shall utilize power
from PP-4964/ASN-84 Power Supply as follows:
(1)
+5 VDC, 4 watts
(2)
+15 VDC, 0.5 watts
(3)
-15 VDC, 0.3 watts
(4)
+26 VDC, 1 watt
-26 VDC, 1 watt
(5)
*3.5.8.5.3
Power Outputs - The SDC shall be capable of supplying
the following power to equipment external to the SDC:
(1)
115 V, 400 Hz, 3 0, 56 watts
(2)
0-26 VAC, 400 Hz, 1 0, 0.8 Amp
(3)
+13.5 VDC 5% at 1 Amp
(4)
-13.5 VDC 5% at 1 Amp
(5)
+5 VDC 5% at 8 amp., with respect to chassis
ground, less than 100 mV RMS ripple content,
short circuit protected.
(6) Analog ground shall be isolated from chassis
ground.
3.5.8.6
Mounting - The SDC shall be mounted on shockmount. The
shockmount shall not be supplied as part of the equipment.
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