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|  MIL-C-38418E(AS)
R1. Positive rotation of the input transmitter (to simulate a right
turn) shall cause the stator voltage of each output transmitter to become
maximum in the sequence S2-1, S1-3, S3-2.
3.7.5.1.2 Pitch and Roll Transmitters - Stator leads of the pitch and
roll output transmitters of the displacement gyroscope shall be routed
through the electronic control amplifier, and shall be available at
connector 2J4. The connections are identified in table VI in accordance
with the lead coding standards of MIL-S-20708.
3.7.6 Malfunctioning Monitoring - Provisions shall be made for detecting
the following faults:
a.
Supply voltage high (indication initiated at between +10 and
+20 percent).
Supply voltage low (indication initiated at between -10 and
b.
-20 percent).
Loss of synchro excitation caused by an open in the power
c.
source or in the rotor of the gyroscope heading synchro transmitter.
Loss of synchro signal transmission caused by an open in any
d.
two stator connections from the gyroscope heading synchro transmitter
including opens in the aircraft interconnecting wiring between the
gyroscope and the electronic control amplifier.
Heading servo folloow-up displaced from null.
e.
(Indication
initiated at between 2 and 3 error signal).
3.7.6.1 Malfunction Indication
a. A negative 28Vdc signal shall be removed from connector 2J3-22
and 2J1-22 when any fault in the heading channel is detected as specified
in 3.7.6.
A set of normally open contacts shall be provided between
b.
connector 2J1-27 and 2J1-30.
These shall close when any fault is
detected as specified in 3.7.6.
3.7.6.2 Auxiliary Malfunction indication - A 26V A signal shall be
provided at connector 2J3-11 when any fault detected as specified in
3.7.6.
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