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|  MIL-S-85018A(AS)
aircraft pitch attitudes. The erection system shall provide both initial,
normal, fast and final erection circuitry.
3.5.2.4.4 Acceleration Sensors - Acceleration sensors shall provide a
measure of lateral and longitudinal acceleration as specified in Figure 1.
3.5.2.4.5 Erection Torquers - Torque motors shall be affixed to the
vertical gimbal set to provide erection precession control for the vertical
gyro. These torque motors shall be capable of erection at normal or fast rates
aS specified herein.
3.5.2.4.6 Output Devices - Standard output devices shall be affixed to the
gimbals to provide roll, pitch, and heading displacement outputs from the gyro-
scope assembly.
3.5.2.4.6.1 Roll Devices - The roll devices shall provide sine and cosine
outputs of the measured roll angle. The roll devices shall be affixed to the
first vertical gyro axis of freedom.
3.5.2.4.6.2 Pitch Devices - the pitch devices shall provide sine and cosine
outputs of the measured pitch angle. The pitch devices shall be affixed to the
second vertical gyro axis of freedom.
The heading output devices shall
provide the sine and cosine output of the resolved heading. The devices shall
be affixed to the pivot axis of the directional gyro gimbal so that the device
Input to the heading
shaft will provide a measure of angular displacement.
devices shall be provided by the Electronic Control Amplifier.
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3.5.2.4.7 Time Totalizing Meter - The Displacement Gyroscope assembly shall
contain a time totalizing meter conforming to MS27651. The time totalizing
meter shall be located on and shall be visible without disassembly of the
gyroscope assembly case.
3.5.2.4.8 BIT Indicator - A BIT failure indicator shall be located on the
Gyroscope Assembly case and shall be visible without disassembly of the case.
Upon indication of a Gyroscope Assembly failure from the Electronic Control
Amplifier, the indicator shall be tripped to a latched position. Less of
electrical power to the Displacement Gyroscope and the slewing of directional
heading and other system operational functions shall not be indicated as a
failure.
3.5.2.4.9 DG Drift Bias Adjustment - A DG drift bias adjustment if required
shall be provided on the Displacement Gyroscope to compensate for DG drift. The
DG drift bias element shall be accessible from the outside of the sealed case.
The element shall incorporate a removable cover to prevent inadvertent change in
adjustment. The DG bias adjustment, as necessary shall provide a range of plus
or minus 4.5 degrees per hour when interfaced with the Electronic Control
Amplifier.
3.5.2.5 Case - The Displacement Gyroscope assembly case shall form an
integral unit for mounting directly to the aircraft. The gyroscope assembly
shall be provided with quick disconnect mounts that require no special tools for
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