MIL-DTL-81963C
4.9.14.2 Screw-thread terminals. Each screw-thread terminal shall be tested by means of a 5-pound
spring scale or dead weight applying force inward toward the housing and outward from the housing.
Each terminal shall then be subjected to a torque of 4.5 lb-in by means of a device such as a torque
wrench or torque watch, which applies only torque and not force. The torque shall be applied clockwise
about the centerline of the terminal assembly. The specified load shall be increased gradually at a rate
not to exceed one pound per second. Screw-thread terminal strength shall be in accordance with
4.9.14.3 Solder-pin terminals. Each solder-pin terminal shall be tested using a two-pound pulling force
applied gradually in a direction parallel with the shaft axis and outward from the housing. The force shall
be applied once only in each direction specified and shall be maintained for a period of 5 to 10 seconds.
Solder-pin terminal strength shall be in accordance with 3.6.14.3.
4.10 Environmental.
4.10.1 Vibration. Servocomponents shall be tested in accordance with MIL-STD-202, method 204.
Servocomponents larger than size 23 shall be tested in accordance with requirements of Test Condition
A, and servocomponents size 23 and smaller shall be tested in accordance with the requirements of Test
Condition B. Throughout the test, the servocomponent shall be rigidly mounted on a test fixture, utilizing
standard mounting surfaces, shall be energized, and its shaft mechanically loaded and free to rotate as
specified in the applicable general specification. Servocomponents shall have an aluminum disc
conforming to figure 1A or 1B securely mounted on the shaft, utilizing standard hardware. After
completion of this test, the servocomponent shall meet the requirements of 3.7.1.
4.10.2 Shock.
4.10.2.1 Shock, specified pulse. Servocomponents shall be tested in accordance with MIL-STD-202,
Method 213, Test Condition A. The servocomponent shall be securely clamped to a rigid test fixture
utilizing normal mounting surfaces, which shall be rigidly mounted on the test device. During the test, the
servocomponent shall have the shaft loaded with the appropriate disc on figure 1A or 1B, or shall be
unloaded as called for by the applicable general specification. The servocomponent shall be energized
as designated in the general specification. The rotor shall be mechanically free to rotate or not, also as
indicated in the applicable general specification. After completion of this test, the servocomponent shall
meet the requirements specified in 3.7.2.1.
4.10.2.2 Shock, high impact. Servocomponents shall be tested in accordance with MIL-STD-202,
method 207 and shall be rigidly mounted to the equipment on the method 207 figure titled "Standard
mounting fixtures for electrical-indicating switchboard meters and other panel-mounted parts", therein,
utilizing normal mounting surfaces. The servocomponent shall have the shaft loaded with the appropriate
disc on figure 1A or 1B, or shall be unloaded as called for by the applicable general specification. The
servocomponent shall be energized as designated in the applicable general specification. After
completion of this test, the servocomponent shall meet the requirements specified in 3.7.2.2.
4.10.3 Altitude.
4.10.3.1 Altitude, low temperature. The unenergized servocomponent shall be placed in a test
chamber, the internal ambient temperature of which shall be reduced to and controlled at -55 ± 2 degrees
C and the servocomponent shall be allowed to attain the stabilized non-operating temperature condition
of 4.2.2.1. The servocomponent shall then be energized so as to attain the stabilized operating
temperature condition of 4.2.2.2. The pressure in the test chamber shall then be reduced to 8.27 Torr
(1,102.39 Pascals or approximately equivalent to an altitude of 100,000 feet). While still in this specified
environment, the servocomponent shall be subjected to and shall meet the requirements, as specified in
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