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|  MIL-N-81497A(AS)
By virtue of the fact that the
Non-Operation -
3.4.1.3.2
aircraft provides the excitation for the following, these functions/
outputs shall not be required during the power interrupt period but
shall return to normal values and conditions after the reappearnce
of the aircraft power.
Synchro Transmitter Output (Energized by
(1)
Aircraft 26V, 400 Hz)
Roll CX No. 1
True Heading CX
Magnetic Heading CX
Roll CX No. 2
Pitch CX No. 1 Magnetic Variation CX
Pitch CX No. 2 Grid Heading CX
Clutched Heading CX
Control Panel Edge Lighting
(2)
Control Panel Advisory Lamps - All advisory
(3)
lamps need not be provided except the follow-
ing on the Control, Gyroscope Assembly.
System Fail
Battery in Use
Align
Test Submode
Magnetic, True Heading and Magnetic Variation
(4)
Servos - All heading servos need not be
operative during power interruptions but
shall automatically realign to their respective
references upon the reappearance of aircraft
power.
Accuracy.
3.4.2
3.4. 2.1
Present Latitude and Longitude - Present latitude and
longitude readings shall be used to calculate radial position error. In the pure
inertial mode the maximum radial error shall not exceed 5.4 nautical miles per
hour of flight (1. 5 nautical miles per hour CEP).
15
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