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|  MIL-I-85365(AS)
4.6.2 Circuit resistance. The igniter circuit shall be checked for circuit resistance in
accordance with the requirements of 3.3. Not more than 0.005 ampere shall be applied
to the igniter circuit during the test.
4.6.3 Impact test. Two igniters shall be subjected to a 40-foot drop test in accordance
with MIL-STD-331. Igniters shall not fire during the test and shall be safe to handle and
dispose after the test. Igniters do not have to be usable after the test.
4.6.4 Two-foot drop test. Three igniters shall be subjected to a 2-foot drop test along
the longitudinal axis. nose down, at ambient temperature. Acceptance shall be in accord-
ance with 4.6.10.
4.6.5 Temperature and humidity. Five igniters shall be subjected to the temperature
and humidity test. Igniters shall be subjected to alternate temperature conditions of 0 F
and +140" F; time at each temperature will be a minimum of 18 hours with a 5 minute
maximum transfer time. Three full cycles will be required. A full cycle is defined as 0
to + 140 to 0 F with relative humidity (RH) equal to 95 percent. After completing the
test, two of the igniters shall be test fired at 0 F and two at +1 40 F in accordance with
the testing schedule of Figure 1. Acceptance shall be m accordance with 4.6.10.
4.6.6 Vibration. Five igniters shall be vibrated along the longitudinal and transverse
axes. Igniters shall be mounted in a test vehicle which simulates the mounting of the igniter _
in the Rocket Motor Mark 23 Mods. Test Procedures and time schedules shall be in accor-
dance with MIL-STD-810 10. figure 514-6, curve AA, beginning at 5Hz. After the test, two
of the igniters shall be test fired at 0 F and two at + 140 F m accordance with the testing
schedule of Figure 1. Acceptance shall be in accordance with 4.6.10.
4.6.7 Acceleration. Five igniters shall be mounted simulating the actual mounting of
the Rocket Motor Mark 23 Mods and subjected to 15 2 g acceleration load. The test
shall be repeated 10 times. The g load shall be reached in 7 1 milliseconds and the accel-
eration shall exceed 8 g for a minimum of 11 milliseconds. The igniters shall be in such a
position that the load acts along the longitudinal axis of the igniters. After the load and
acceleration test, two of the igniters shall be test fired at 0 F and two at + 140 F in accord-
ance with the schedule of Figure 1. Acceptance shall be in accordance with 4.6.10.
4.6.8 High temperature test. Four igniters, in accordance with testing schedule of
Figure 1, shall be subjected to high temperature test. The igniter shall be enclosed in a
test chamber, the temperature of which shall be 350 20 F. After the igniter has been
subjected to this temperature for the specified minimum time of 2 hours, it shall be test
fired in accordance with the testing schedule of Figure 1.
4.6,9 Salt spray test. Four igniters shall be loaded into a simulated Rocket Motor
Mark 23 and subjected to the salt spray test in accordance with MIL-E-5272. 272. After com-
pleting the test, two of the igniters shall be test fired at 0 F, and two at + 140 F in accord-
ance with the testing schedule of Figure 1. Acceptance of igniters shall be in accordance
with 46 10.
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