AD 69-06-06

69-06-06 BEECHCRAFT: Amendment 39-740 as amended by Amendment 39-757 is further amended by Amendment 39-1222. Applies to Models 65-80, 65-A80, 65-A80-8800 and 65-B80 (Serial Numbers LD-1 through LD-398); 65-88 (Serial Numbers LP-1 through LP-47); 65-90, 65-A90 and B90 (Serial Numbers LJ-1 through LJ-428); and all 99 series airplanes (Serial Numbers U-1 through U-62) with 250 hours' or more time-in- service.

Compliance required as indicated.

To detect cracks in the rudder spar, within the next 50 hours' time-in-service after the effective date of this airworthiness directive, unless already accomplished, and thereafter at intervals of not to exceed 300 hours' time- in-service from the date of the last inspection, accomplish the following:

(A) Inspect visually the rudder spar web, in the area under and adjacent to the upper and center hinge attach points.

(B) If a crack is found during an inspection required by Paragraph (A), before further flight, accomplish thefollowing:

(1) Modify the rudder spar web in accordance with the method contained in Beechcraft Instructions No. 0101-135, or any other method approved as an equivalent by the Chief, Engineering and Manufacturing Branch, FAA, Central Region; or

(2) Replace the rudder spar with one that has been modified in accordance with Paragraph (B)(1) of this airworthiness directive.

(C) When either the modification or replacement described in Paragraph (B) of this airworthiness directive has been accomplished, the inspections required by this airworthiness directive are no longer required.

Amendment 39-740 became effective March 26, 1969.

Amendment 39-757 became effective April 29, 1969.

This Amendment 39-1222 becomes effective June 3, 1971.