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Page Title:
Table XXII. Reliability Testing Tolerances |
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|  MIL-C-38418E(AS)
TABLE XXII.
Reliability Testing Tolerances
Percent Increase
Reliability Test Time Per
in Tolerance
Control Assembly or Component
0
0 to 500 hrs
25
500 to 1,000 hrs
50
1,000 to 1,500 hrs
100
1,500 hours and over
PACKAGING
5.
5.1
Preservation and Packaging - Sealed control assembly components
shall be preserved in accordance with MIL-P-116, method 1A and unsealed
control assembly components shall be preserved in accordance with method
II.
Packing - Packing shall be in accordance with MIL-STD-794, level A
5.2
for export shipment and level B for domestic shipment.
NOTES
6.
6.1
Intended Use - The attitude gyroscope control assemblies covered
by this specification are intended for use in either fixed-wing or
rotary-wing aircraft to provide pitch, roll, and heading displacement
signals of the aircraft for indication and tie-in to other equipment.
Provisions are made for various types of operation and error
compensation, depending upon the application and associated equipment.
6.2
Ordering Data
6.2.1 Procurement Requirements - Procurement documents shald specify
the following:
a.
Title, number, and date of this specification.
Type of Electronic Control Amplifier and type of Compass
b.
System Controller required (see 3.2) for the aircraft application.
c.
Disposition instructions for test samples (see 4.4.1)0
82
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