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|  MIL-S-85018A(AS)
3.5.1.3.3.2 Acceleration Cutoff - Heading slaving shall be cut off if
either the longitudinal or the lateral acceleration exceeds .07g plus or minus
.O2g.
3.5.1.3.3.3 Attitude Extremes - Heading slaving shall be cut off at any
time when either the roll or pitch attitude of the aircraft is not within plus
or minus 25 plus 3 minus 0 degrees of horizontal.
3.5.1.3.4 Coriolis Compensation - The magnetic heading signal shall be
compensated for errors due to Coriorlis acceleration using the reference
velocity. Should the velocity reference input be invalid or not available, a
fixed 300 knots velocity input shall be provided.
3.5.1.3.5 Fast Synchronization - Momentary depression of the Set Heading
control on the Cotroller while in the Slaved Mode shall Provide automatic
synchronization of the heading outputs to the magnetic heading at a slaving rate
of not less than plus or minus 60 degrees per second. Fast slaving shall be
automatically terminated when synchronization is complete to within plus or
minus .25 degree. Magnetic fast synchronization shall be inoperative in the DG
and Emergency modes or during slaving cutoff due to acceleration or attitude
extremes.
3.5.1.4 EMERGENCY Mode Performance - The system shall provide electroni-
cally damped magnetic data when the Displacement Gyroscope is inoperative. The
magnetic heading data shall be insensitive to normal magnetic field strength
variations as specified herein.
3.5.1.4.1 Accuracy - When operated in the EMERGENCY mode, the heading
outputs shall have an accuracy of 1.0 degree or less when referenced to the
output of the compass transmitter in the standard magnetic field, and shall be
damped electronically.
3.5.1.4.2 Backup Capability - In the EMERGENCY mode, the heading outputs
shall operate normally for 95 percent or greater of any failures in the gyro-
scope assembly (whether BITE detected or not), and shall always operate normally
if the cabling to the gyroscope assembly is disconnected.
3.5.1.5 Power Interruption
3.5.1.5.1 Erection Cycle - Means shall be provided to prevent the system
from recycling through the initial fast erection sequence when power has been
interrupted for a period of less than 60 seconds. For a power interruption of
more than 90 seconds, the system shall automatically recycle through the fast
erection sequence.
3.5.1.5.2 Attitude Information - After the initialization cycle is com-
plete, any time the power is removed for 25 seconds or less, and the gyroscope
displaced through angles of plus or minus 15 degrees in pitch and roll- and re-
turned to its original vertical position, the pitch and roll axes shall indicate
the original position to within plus or minus 1 degree within 10 seconds after
reapplication of power.
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