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MIL-S-85018A(AS)
3.5.0.2 The Displacement Gyroscope shall provide angular output in pitch,
roll, and azimuth.  The gyroscopic reference shall consist of either single-
degree-of-freedom or two-degree-of-freedom gyros and accelerometers mounted
within the selected gimbal arrangement.  The arrangement shall permit all-
altitude operation at all times without any restrictions.  No error exceeding
1.0 degree and lasting more than 5 seconds shall be developed as a result of
flying in the vertical climb and/or dive positions.  The accelerometers shall be
linear over the total range of plus or minus 2gs. The hermetically sealed
gyroscopes and electronics shall be so constructed that they shall be removable
from the assembly and replaceable without use of special tools or skill.
3.5.0.3 The Electronic Control Amplifier shall supply the following
functions:
(1) First and Second Order vertical erection control and
functionally associated reference computations.
heading system outputs
(2) Roll, pitch, rate of turn, and magnetic
and circuitry.
(3) Required circuits for processing all  incoming and outgoing
signals required for operation and application of the system.
(4) AC/DC power supply, all vertical and directional gyro erection
and control circuitry, all system interface circuits, mode control, tests, and
digital logic.
(5) Self-cooling features.
(6) System functions not assigned to other components.
The amplifier cards shall be modular plug-in type. The amplifier circuit cards
shall be designed to assure maximum efficiency in the use of plug-in subassem-
blies, with maximum reliability and  minimum maintenance time.
3.5.0.4 The SOARS Controller shall  provide as a minimum the following sys-
tern control functions and indications with all respective reference functions
grouped in the related areas:
(1) Mode Selector
(2) Fast Synchronization Command
(3) Set Heading Control
(4) Synchronization Indicator
(5) Latitude Readout and Manual Control
(6) Malfunction Naming Lamp
(7) Fast Erection Command
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