 |
|||
|
|
|||
| ||||||||||
|
|  MIL-C-38418E(AS)
4.6.16 Salt Fog - The control assembly components shall be subjected to a
salt fog test in accordance with method 509, procedure I of MIL-STD-810.
Upon completion of this test, the components shall meet the tests
specified in 4.6.2.1; 4.6.4.7; 4.6.4.14.1.1 (or 4.6.4.14.2.1) step d,
except the -30 and -180 shall not apply; and 4.6.5.3.5, as
applicable.
There shall be no evidence of corrosion that would shorten
the operational life of the components.
4.6.17 Dust The compass system controller and electronic control
amplifiers shall be subjected to a dust test in accordance with method
510, procedure I of MIL-STD-810.
Upon completion of this test, the
compass system controller and electronic control amplifiers shall meet
the tests specified in 4.6.4.7, and 4.6.4.14.1.1 (or 4.6.4.14.2.1), step
d, except the -30 and 180 shall not apply.
There shall be no
evidence of damage due to this test.
4.6.18 Temperature Shock The control assembly components shall be
subjected to a temperature shock test in accordance with MIL-STD-810,
method 503. Upon completion of this test, the components shall meet the
tests specified in 4.6.2.1, 4.6.4.7, 4.6.4.14.1.1 (or 4.6.4.14.2.1), step
d, except the -30 and 180 rates shall not apply; and 4.6.5.3.5.
4.6.18.1 Leak Rate - The displacement gyroscope seal shall not permit
the equivalent of more than 10 percent loss of the filling medium after
1,000 hours at a pressure differential equal to a 100,000 foot altitude.
4.6.19 Vibration Failure -
The components shall be subjected to a
vibration failure test in accordance with MIL-STD-810, method 514.1,
equipment category (a), curve M, figure 514.1-1. At the conclusion of
this Lest, the components shall meet the following tests:
a.
Compass System Controller - - - - - - - - 4.6.3
b.
Displacement Gyroscope - - - - - - - - - 4.6.2
Electronic Control Amplifier - - - - - - 4.6.4
c.
4.6.20 Acoustical Noise The control assembly shall be operated in the
SLAVED mode, synchronized to the simulated azimuth detector, and
subjected to an acoustical noise test in accordance with MIL-STD-810,
method 515, intensity category A, procedure I.
The control assembly
outputs of pitch, roll, and heading shall not vary by more than 3/4
from the initial position established with 10 percent of this noise
level, and shall return to the initial position when the noise level is
again reduced to 10 percent of the test noise level.
80
|
|
Privacy Statement - Press Release - Copyright Information. - Contact Us |
Click
here for thousands of PDF manuals