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|  MIL-S-85018A(AS)
indicator shall be of a meter type and shall have indicated on the panel a
"Cross" on the right hand side and a "Dot" on the left hand side.. The manual
heading set control knob shall have a "Cross" above and to the right and a "Dot"
above and to the left.
3.5.4.9.1 Synchronizing Indicator Sensitivity - When the Compass Trans-
mitter is rotated to a heading 10 degrees greater than the compass system
output, the sync indicator shall move full scale to the left. When the Compass
Transmitter is rotated to a heading 10 degrees less than the compass system
output, the synchronizing indicator shall move full scale to the right.
3.5.4.10 Malfunction Warning Lamp - A red malfunction lamp shall be
provided that will operate when a system malfunction is detected.
3.5.4.11 Vertical Gyro Fast Erection Control - A momentary pushbutton shall
be provided that when depressed will automatically result in the pitch and roll
erection system reverting to the fast erection rate for only the time necessary
to complete the erection cycle. The Amplifier Control Assembly monitor valid
signal shall indicate invalid for only the time the Control Assembly is in the
fast erection mode or when erection is inoperable.
3.5.4.12 BITE - The BITE function shall be continuous.
3.5.4.13 Magnetic Variation Input Control - A switch shall be provided to
permit the manual input of Magnetic Variation. The Magnetic Variation control
shall be a three-position switch labeled 15E, O, and 15W.
3.5.4.14 Markings - All markings shall be so durable as to withstand usage
encountered in service. Unless otherwise specified, the style and proportions
of numerals and letters shall conform to MS33558.
3.5.4.15 Color - The background of all dials, counters, and other external
surfaces not otherwise specified shall be lusterless black, Color No. 37038 of
FED-STD-595. Knobs shall be gray, Color No. 36231 of FED-STD-595 and all
markings shall be white, Color No. 37875 of FED-STD-595.
3.5.5 Electronic Compensator Unit - The Electronic Compensator Unit shall
be a modular unit which shall be mounted in the aircraft to permit easy removal.
The unit shall be of minimum size and weight and shall not exceed .5 pound. The
Electronic Compensator Unit must be completely interchangeable with the other
three component WRAs of this specification and shall not require any adjustment
or readjustment when one or more of the above mentioned system components are
removed and/or replaced. A compensator cutoff switch shall be provided as
required in 3.4.9.4.
3.5.5.1 Compass Compensator - The Compass Compensator shall meet the
following requirements:
3.5.5.1.1 Compensation - Heading compensation shall be provided to
compensate for index, one-cycle and two-cycle errors.
3.5.5.1.1.1 Index Error Adjustment and Range - A maximum of one adjustment
shall be required to compensate for the system index error. This index correc-
tion range shall be plus or minus 2.0 to plus or minus 4.0 degrees. When one-
and two-cycle adjustments are made, the index error adjustment shall not require
readjustment.
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