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|  MIL-c-38418E(AS)
4.6.9 LOW Field Strength - The control assembly shall be connected to a
simulated azimuth detector and operated on a synchronized null.
Excitation of the simulated azimuth detector shall be reduced to 102 2.5
mV 800 Hz to represent a horizontal field strength of 0.080 0.002
oersted.
The simulated azimuth detector shall be oscillated through
5 either side of null at 6 cpm. The control assembly heading shall
be noted each minute after start of the oscillation until three
consecutive readings are within 0.10 of each other.
The difference
between the initial control assembly heading and the final heading shall
not exceed 0.5. The test shall be run on three headings not less than
60 apart.
4.6.10 Slaved Dynamic Acuracy - The control assembly shall be operated in
the SLAVED mode and synchronized to the simulated azimuth detector. The
simulated azimuth detector shall be oscillated through 5 either side
of null at 6 cpm, and readings of the heading output shall be made at 1
minute intervals.
Readings shall continue until three consecutive 1
minute readings are within 0.1 of each other, which shall occur within
45 q inutes from the start of the oscillation. The difference between the
initial and final headings shall not exceed 1.0.
4.6.11 Radio Noise Interference and Susceptibility - The radio noise and
susceptibility test shall be conducted in accordance with MIL-I-6181.
The control assembly shall be tested for radio noise interference over a
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frequency rangeof 150 kc to 400 mc and for susceptibility over a
frequency range of 150 kc to 1,000 mc. During this test, the control
assembly shall be properly connected with the displacement gyroscope
operating on a 15 scorsby q echanism and with the lighting circuit in
the compass system controller energized.
4.6.12 Temperature-altitude (Cycling) - The control assembly components
shall be subjected to a temperature-altitude test in accordance with
method 504, procedure I of MIL-STD-810 for Class 2 equipment. Maximum
test temperature with control assembly operating shall be 71C.
Maximum non-operating temperature for the compass system controller shall
be 85C.
Tests to determine satisfactory operation shall consist of
4.6.2.1; 4.6.4.14.1.1 (or 4.6.4.14.2.1), step d, except the -30 and
-180 per minute rates shall not apply; and 4.6.5.3.5 with tolerances
increased as noted. Tests to determine-performance characteristics shall
consist of 4.6.2.1; 4.6.2.4; 4.6.4.14.1.1 (or 4.6.4.14.2.1), step c;
4.6.4.14.1.2 (or 4.6.4.14.2.2), step d; 4.6.4.14.1.3 and 4.6.5.3.6, as
applicable, with the following tolerances increased.
At the conclusion
of this test, the control assembly components shall pass the individual
tests with no tolerance increases.
78
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