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Inspection of rudder skins at points immediately adjacent to the upper and lower ends of the rudder tab hinge for cracks.
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The following repair procedure is recommended for those aircraft on which the hole in the elevator tab control horn has elongated.
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Information on the Marvel-Schebler Accelerator Pump Kit, part A666-581.
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Inspection to determine if fatigue cracks have developed in the fitting that attaches the horizontal stabilizer to the fin.
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As a precaution against possible cracking of the sliding window, at the knob, we recommend the following correction on airplanes in the above category.
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Reports of malfunctioning steerable tail wheels caused by the tail wheel arm striking the end of the tail wheel installation bolt.
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Correcting interference between the gas gauge tank unit float arm and the cast aluminum adapter in which the gas gauge tank unit is mounted.
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Corrective procedure for possible chafing of the wiring harness at the throttle bracket behind the instrument panel.
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Steps to restore the position locating feature in the fuel tank selector valve and assure positive operation of the valve at all times.
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In cooperation with the CAA program of increasing the safety factor of cabin interior in the event of crash, we have modified the attachment of the control wheel to its shaft.