MIL-DTL-48568D(OS)
4.4.6 Nondestructive tests. Each rocket catapult assembly shall be subjected to the following tests. When
specified in the contract (see 6.2), the contractor shall furnish test reports detailing the results of all
nondestructive tests for each lot of rocket catapults.
4.4.6.1 Radiographic inspection. Rocket catapults shall be radiographically inspected in accordance with
MIL-STD-453, radiographic quality level I. Any deficiency shall be cause for rejection of the unit.
Radiographs shall be capable of detecting defects and rocket catapult components 0.03 inch in length or
width. When specified in the contract (see 6.2), all radiographs taken of the rocket catapult assembly or
components thereof shall be forwarded to the activity designated by the contracting activity. Otherwise, all
radiographs shall be inspected on-site by a designated Government representative. Acceptance of the loaded
rocket catapult lot shall be subject to approval of the radiographs by the designated Government activity.
4.4.6.2 Breakaway torque. After ascertaining that each booster tube (Drawing 10551422) and head
(Drawing 10551412) assembly and the launcher tube (Drawing 10551423) and mount (Drawing 10551413)
assembly has been seated with 400 + 50, 0 inch-pounds of torque, a breakaway torque of 200 inch-pounds
shall be applied. Any evidence of loosening or deformation of any component of these assemblies shall result
in rejection of the part.
4.4.6.3 Residual magnetism. Each rocket catapult assembly shall be passed 6 inches in front of an
MS17983 compass along the entire length of the catapult in accordance with figure 1. If the compass
indicator deflects more than 5 degrees in either direction, the rocket catapult assembly shall be rejected. The
test shall be performed in an area free from local magnetic effects.
4.4.6.4 Nozzle O-ring integrity. The retainer-nozzle ball O-ring shall be tested for leakage by partially
assembling the catapult so that the retainer nozzle subassembly and the motor tube are assembled. The
assembly shall then be pressurized to 40 psig and the nozzle swiveled through its operational range. Any loss
of pressure within 15 seconds after the nozzle has been fully swiveled shall result in rejection of the catapult
assembly. Application of 40 psig internal pressure to the sealed assembly must cause the nozzle to rotate
from the axial position to the final canted position without application of any external force. Failure to rotate
completely shall result in rejection of the assembly.
4.4.6.5 Release O-ring integrity. The release O-rings shall be tested for leakage by pressurizing the launcher
tube-mount subassembly with nitrogen at 200 ± 5 psig. Any loss of pressure within 15 seconds of
pressurization shall result in rejection of the catapult assembly.
4.4.6.6 Nozzle/sleeve actuation force. The retainer/nozzle/sleeve subassembly shall be tested to permit
measurement of the axial force which is necessary to move the sleeve an adequate distance to cause full
rotation of the nozzle. The assembly shall include all internal O-rings when tested. The force measurement
shall be performed with a suitable force gage accurate to 1 pound. The measurement of an axial force
exceeding 25 pounds shall result in rejection of the assembly.
4.4.6.7 Hydrostatic pressure. Each component listed shall be subjected to the respective internal hydrostatic
pressure specified in table II for a minimum of 15 seconds without application of an external load. Any
leakage, permanent deformation outside drawing tolerances, or mechanical failure shall result in rejection of
that component. Each hydrostatically tested component shall then be subjected to the magnetic particle
inspection of 4.4.6.8.
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