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|  MIL-S-85018A(AS)
3.3.14 Gyroscope Bearings -
3.3.14.1 Rotor Bearing Lubrication - The rotor bearing shall be lubricated
with Mobil RL-/43A oil conforming to MIL-B-81793.
3.3.14.2 Bearing Lubrication - The lubricating oil used in gimbal bearings
shall be Mobil-7 4 3 A conforming to MIL-B-81793.
3.3.14.3 Barrier Film Bearing Coating - All Rotorace motor bearings shall
The coating material shall be in
be processed in accordance with MIL-STD-1334.
accordance with MIL-B-81744. All Rotorace motor bearings, including chamfered
races or corners, and including interfacing parts where applicable, shall be
barrier coated.
3.3.14.4 Ball Bearings - Ball bearings shall be ABEC-5 grade or better.
Teflon separators shall be used on gimbal bearings where the bearing design
permits.
Spin rotor bearings shall have porous separators impregnated with
Mobil RL-743A per MIL-B-81793 and shall be ABEC-7 or better.
3.3.14.5 Ball Bearinq Pre-Loading - Means shall be provided for preloading
an alignment without causing eccentric loading unless otherwise authorized.
3.4 Performance - Unless otherwise specified in the approved test plans,
values set forth to establish the requirements of satisfactory performance apply
to performance under both standard and extreme service and input power condi-
tions. When reduced performance under the extreme conditions is acceptable,
tolerances or values setting forth acceptable variations from the performance
under the standard conditions will be specified.
3.4.1 Operation - The Second Order Attitude Reference System (a flight
safety reference system) shall be an all attitude source of roll, pitch and
heading angular displacement signals for other airborne installed equipments,
Including flight control and reference, navigation, weapons deliveries and
direct presentation or displays. Roll information shall be continuous through-
out 360 degrees and valid for all aircraft angles of pitch and heading. Pitch
information shall be continuous throughout plus or minus 90 degrees and valid
for all angles of roll or heading. Heading information shall be continuous
throughout 360 degrees and valid for all attitudes of pitch and roll. There are
no stops or controlled precession points in the attitude or heading axes of the
SOARS. The operativg ranges for SOARS shall be as follows:
Mission Condition
Parameter
Latitude Range (degrees)
S90 to N90
Aircraft Reference Velocity (knots)
0 to 1000
-180 to +180
Aircraft Roll Attitude (degrees)
-90 to +90
Aircraft Elevation (degrees)
Aircraft Heading (degrees)
0 to 360 (continuous)
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