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Inspect the fittings at each end of the elevator connector tube to determine if the end fittings are riveted to the tube with two rivets 90 degrees apart.
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Inspect the two aileron stop pins (Taylorcraft P/N A-235) of the aileron control assembly.
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Steps to preclude weld separations on the end of the landing gear shock strut assembly.
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Provisions for locking the sliding windows with or without the green sunshade.
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Installation of a reinforcing patch around the fuel outlet fitting of the fuel tank.
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Installation of this boot will reduce the possibility of moisture accumulating between the oleo assembly and the oleo housing.
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Excerpts of FAR 8110.42 Parts Manufacturer Approval Procedures.
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Reports have been received indicating overheating of cylinder heads. To provide continuous indication of engine operating temperatures accomplish the following.
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This memorandum is a supplement to Memorandum #49, covering the inspection of control column cables.
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Checking the attachment of the rudder control arm on the torque tubes.