64-26-03: Elevator Push Rod Assembly

64-26-03 GRUMMAN: Amdt. 39-4 Part 39 (New) Federal Register November 25, 1964. Applies to Models TBM and TBF Series Aircraft. Compliance required as indicated. As a result of loose and sheared rivets found on the elevator push rod assembly, P/N 21399, accomplish the following: (a) Within 50 hours' time in service after the effective date of this AD, unless already accomplished within the last 50 hours' time in service, and thereafter within every 100 hours' time in service from the last inspection, inspect the four rivets on the elevator push-pull rod assembly which retain the clevis and bearing terminal fittings, P/N's G76-10 and 21356, to the tube, P/N 21399-1, and determine if any are loose or sheared. (The rod assembly, which connects the elevator horn to the sector, is located at the airplane centerline at approximately fuselage Station 326.) (b) If any rivets are determined to be loose or sheared, accomplish the following modification before further flight, except that one flight may be made in accordance with the provisions of CAR 1.76 for the purpose of obtaining these repairs: (1) Remove the four G10-D3-102 rivets. If the rivet holes in the tube or terminal fittings are elongated beyond the maximum diameter for the replacement rivet, replace that part with a new part of the same part number, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (2) Plug both hollow terminal fitting shanks with an aluminum alloy plug, or an FAA approved equivalent. The plug must be of such diameter so that it may be inserted into the terminal fitting shank creating an interference fit of 0.0005 inch, plus 0.000 inch, minus 0.0005 inch. The plug length must be long enough to fill the area occupied by the rivets. (3) Drill all four holes, including the plugs, to accommodate MS 20470AD8 rivets, or an FAA approved equivalent. (4) Install all four MS 20470AD8 replacement rivets, or an FAA approved equivalent. (c) The 100-hour repetitive inspections of (a) need not be made on aircraft which already incorporate aluminum alloy terminal plugs and four MS 20470AD8 rivets, or an FAA approved equivalent, and may be discontinued on aircraft that are modified in accordance with (b)(1) through (b)(4) inclusive, or an FAA approved equivalent. This directive effective December 25, 1964.