188.8.131.52 Insulation resistance. The insulation resistance of the wiring
harness after installation in the launcher shall be not less than 20 megohms
(Mohms) at 500 +10 Volts direct current (Vdc) from conductor to conductor
and conductor to ground.
184.108.40.206 Continuity. The continuity resistance of the MK 40 firing circuit
after installation in the launcher shall be not greater than 0.3 ohm.
continuit;f resistance of the MK 66 firing circuit after installation in the
Continuity resistance of any
launcher shall be not greater than 0.1 ohm.
ground circuit shall be not greater than 0.1 ohm.
220.127.116.11 Rocket loading. The launcher shall require not greater than 20
pounds push or pull force exerted on the plug gage. The firing contact shall
make sufficient contact with the surface of the rocket igniter contact to
transmit a pulse which shall fire a rocket.
18.104.22.168 Detent pull. The detent shall not release before 400 +50, -0
pounds pull force is reached.
With 22.0 +1.0, -0.0 Vdc applied to pin A of J1
22.214.171.124 Static firing.
or J2 (pin E grounded), the launcher shall ignite all functional rockets,
remain intact on the suspension device, and sustain no damage other than
darkening of the exposed surfaces. Upon completion of the static firing
test, the launcher shall meet the requirements of 126.96.36.199, 188.8.131.52, 184.108.40.206,
220.127.116.11 Flight firing. During flight firing, the launcher shall ignite
all functional rockets, remain intact on the aircraft rack, and sustain no
damage other than darkening of the exposed surfaces. Upon completion of the
flight firing test, the launcher shall show no evidence of damage or defects,
and shall meet the requirements of 18.104.22.168, 3.3.~.2, 22.214.171.124, and 126.96.36.199.
3.4 Environmental conditions. The launcher shall not be damaged, nor
shall subsequent performance be degraded, by exposure to any natural combina-
tion of service-use environments. These shall include, but shall not be
limited to, the following environments.
3.4.1 Temperature shock. The launcher shall perform as specified in
188.8.131.52, 184.108.40.206, 220.127.116.11, and 18.104.22.168 after exposure to the temperature shock
test of 22.214.171.124.