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|  M1L-S-85018A(As)
3.5.1.1.6.1 Roll Accuracy and Threshold - The roll output shall be O plus
or minus .20 degree when the assembly is mounted to a horizontal surface. The
angular movement of plus or minus .05 degree in the roll axis about the roll
level position shall be detectable in the roll outputs.
3.5.1.1.6.2 Roll Scale Error - The roll scale error shall not exceed O plus
or minus .2 degree at a O degree roll angle and shall not exceed plus or minus
.50 degree at roll angles in excess of plus or minus 5 degrees.
3.5.1.1.6.3 Roll Drift - The maximum drift in roll, exclusive of earth's
rate, shall not exceed 6.0 degrees per hour. The maximum apparent free drift in
roll shall not exceed 6.5 degrees per hour.
3.5.1.1.6.4 Roll Follow-Up Rate - The system shall be capable of con-
tinuously following a roll input rate of 600 degrees per second.
3.5. 1.1.7 Pitch Performance - The pitch outputs shall provide a measure of
angle between the aircraft longitudinal axis and the local horizontal plane.
The pitch output angle shall increase for an aircraft movement about the lateral
axis that causes the nose of the aircraft to rise above the horizontal plane.
The pitch output shall have a range of plus or minus 90 degrees.
3.5. 1.1.7.1 Pitch Accuracy and Threshold - The pitch outputs shall be O
plus or minus .20 degree when the gyroscope assembly is mounted to a horizontal
surface. The angular movement of O plus or minus .05 degree in the pitch axis
about the pitch level position shall be detectable in the pitch outputs.
3.5.1.1.7.2 Pitch Scale Error - The pitch scale error shall not exceed O
plus or minus .2 degree at a O degree pitch angle and shall not exceed plus or
minus .5 degree at pitch attitude beyond 5 degrees.
3.5.1.1.7.3 Fitch Drift - The maximum free drift in pitch, exclusive of
earth's rate, shall not exceed 6.0 degrees per hour. The maximum apparent free
drift in pitch shall not exceed 6.5 degrees per hour.
3.5.1.1.7.4 Pitch Follow-Up Rate - The system shall be capable of con-
tinuously following a pitch input rate of 50 degrees per second,
3.5.1. 1.8 Azimuth Performance - The heading outputs shall provide a measure
of angular displacement about the local vertical axis. The heading output angle
shall increase for a clockwise movement of the aircraft about the vertical axis.
Heading shall have a range of 360 degrees continuous.
3.5.1. 1.9 Initialization Cycle - Initialization of the directional gyro and
the heading outputs shall commence automatically following application of power.
Within the time specified in Paragraph 3.3.11, the system shall be operating in
the mode selected on the Controller, meeting the requirements of Paragraph
3.4.1.
3.5.1.2 DG Mode Performance -
3,5.1.2.1 Heading Accuracy and Threshold - The scale error of the heading
outputs shall be plus or minus .5 degree maximum. A movement of the
Displacement Gyroscope assembly about the vertical axis equal to or greater than
plus or minus .1 degree shall be detectable in the Heading outputs.
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