3.4 Trunnion rotation. Upon completion of assembly, the trunnion shall be free to rotate 360
3.5 Residual magnetism. The thruster shall not deflect the indicator of the compass more than
five degrees in either direction (see 4.3.2).
3.6 Radiographic examination. Eachthruster assembly shall be radiographically examined for
defects (see 4.3.3).
3.7.1 Load. The thruster fired under load (see 6.3) shall perform as follows:
220.127.116.11 Thrust. With the piston connected to a 50 pound weight, the thruster shall deliver
sufficient thrust to overcome a 3,000 pound resistive load, horizontally, throughout its total
stroke of 5 inches minimum. The resistive load shall not be applied on the piston before initial
18.104.22.168 Operating time. The time from initial thrust rise to completion of the piston stroke
shall be 30 milliseconds, minimum, and 90 milliseconds, maximum.
22.214.171.124 Maximum thrust. A thrust-time record shall be made for each ballistic firing. The
maximum thrust will be computed from that trace and recorded for information purposes on the
3.7.2 Ignition delay. The ignition delay time shall not exceed 65 milliseconds (see 6.5.1).
3.7.3 Temperature. The thruster shall comply with all the ballistic requirements throughout
the temperature range of 65 to +200 F.
3.7.4 Initiation. The thruster shall be fired by a source delivering an output pressure of
700 + 25, 0 pounds per square inch gage (psig) at the end of 15 feet of aircraft hose, MS28741-4
at 70 ± 5 F.
3.7.5 Misfires. There shall be no misfires.
3.7.6 Mechanical failures. The thruster shall function without mechanical failure (see
3.8 Workmanship. Thrusters shall be free of cracks, splits, or other defects which might
prevent proper mating with connecting parts or proper functioning of the device.
3.8.1 Metal defects. All components shall be free from cracks, splits, cold shuts,
inclusions, porosity, or any similar defect.