MIL-DTL-60201D
TABLE I. Torque requirements.
A
B
C
Components
Seating or bottoming
Breakaway, min
Run On, min (inch pounds)
(including A) (inch pounds)
(inch pounds)
Head and retainer guide
50
300 ± 20
200
Retainer guide and sleeve
--
300 ± 20
200
after insertion of cartridge
Head and body1/
50
600 ± 20
400
Cap screws
--
20 minimum
10
1/
At no time will torque be applied between the piston and body assembly.
3.4 Trunnion rotation. Upon completion of assembly, the trunnion shall be free to rotate 360 degrees.
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. Each thruster assembly shall be radiographically examined for defects
(see 4.3.3).
3.7 Functional.
3.7.1 Load. The thruster fired under load (see 6.3) shall perform as follows:
3.7.1.1 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 movement.
3.7.1.2 Operating time. The time from initial thrust rise to completion of the piston stroke shall be 30
milliseconds, minimum, and 90 milliseconds, maximum.
3.7.1.3 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 firing sheet.
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 +200F.
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 ± 5F.
3.7.5 Misfires. There shall be no misfires.
4
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