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|  MIL-N-85005A(AS)
IMS Sequencing and Interlocks - IMS sequence and
3.5.10.4.5
interlock controls shall be provided as follows:
(1)
During the first ten seconds of ALIGN Mode,
supply discretes D1, D2, D3 and D5 to IMS.
Prevent turn ON of the gyro unless logic ones
(2)
for D1, D2, D3 and D5 are available from the
NC.
Upon receipt of a logic discrete Operate Mode
(3)
Interlock from the computer, switch discrete
output lines D1, D2, D3, D5, D9, and D10 to the
logic zero state and maintain this state until
the system is switched to OFF.
(4)
During SLAVE and during ATTD switch discrete
output line D6 (back up level) to the logic one
state and as long as no erection cutout signal
is present maintain this state until the system
is switched to OFF.
Upon receipt of an Erection Cutout Signal
(5)
during SLAVE or ATTD, switch discrete output
line D6 to the logic zero state and maintain
this state as long as the cutout signal is
present.
Route discrete D11 from the NC to the GA.
(6)
Upon receipt of input discrete D6 from the NC,
(7)
send output discrete D6 (or'd also with ATTD
and SLAVE Mode Selector Switch positions) to
the GA.
Upon receipt of a NC Fail signal (Fault is
(8)
high), the Battery Unit shall close isolated
switch contacts to indicate attitude mode to
the Mode Controller.
Input Power
3.5.10.5
*3.5.10.5.1
Aircraft Power - The equipment shall utilize Aircraft
Power in accordance with Paragraph 3.3.12 as follows:
115 VAC, 400 Hz, 3 0, Category B, 90 VA
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