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Arresting gear assembly
Catapult system hydraulic schematic

Aviation Structural Mechanic (H&S) 3&2 - How airplanes are built and how to maintain them
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Figure 12-59.—Centering spring. 2. Adjust the rod ends of both centering springs to reach the attaching pivot holes. Threads must be visible through the rod end inspection hole. See figure 12-59. 3. Tighten the nuts on the attaching bolts finger tight. Safety with cotter pins. 4. Torque the rod end jam nuts to 270-300 inch- pounds and safety with Iockwire, as shown in figure 12-59. 5. Check lateral movement of the hook in accordance with the procedures prescribed in the MIM. Intermediate-level maintenance of the centering springs consists of checking the disassembled parts for scoring, corrosion, nicks, structural deformation, or failure. Nonferrous parts are subjected to fluorescent penetrant inspection and ferrous parts to magnetic particle inspection. The diameter of all parts and the free length dimensions of the two springs, shown in figure 12-59, are checked against the values given in the parts tolerance tables provided in the MIM. WARNING Disassembly and assembly require extreme caution. The spring force is in excess of 500 pounds. Failure to observe the proper safety precautions could result in personnel injury. Post repair testing includes checking the breakout force required to extend and compress the springs. Force required is 560 60 pounds. The spring should extend 1.60 inches 0.03 inch and compress 1.40 inches 0.03 inch from neutral. CATAPULT LAUNCH SYSTEM The purpose of the nose landing gear catapult launch system is to provide a means of directing the aircraft into position for catapult launching, as well as being connected automatically to the ship’s catapult equipment. Such a device eliminates the necessity for flight deck personnel to manually connect catapult 12-68







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