AD 67-29-01

67-29-01 BEECHCRAFT: Amendment 39-574. Applies to Model 95-55 (Serial Numbers TC-1 through TC-190), 95-A55 (Serial Numbers TC-191 through TC-501 except TC- 350 and TC-371), 95-B55 (Serial Numbers TC-371, TC-502 through TC-1042), 95-C55 (Serial Numbers TC-350, TE-1 through TE-451), and 56TC (Serial Numbers TG-1 through TG-51) airplanes with 250 hours' or more time in service.

Compliance required as indicated.

To detect cracks in the rudder spar web, within the next 25 hours' time in service after the effective date of this AD, unless already accomplished, and thereafter at intervals of not to exceed 250 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 the center hinge attach points.

(b) If a crack is found during an inspection required by Paragraph (a), before further flight, accomplish one of the following -

(1) Modify the rudderspar web in accordance with the method contained in Beechcraft Service Bulletin 67-34, Rev. 1, or any other method approved as an equivalent by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Central Region; or

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

(c) When either the modification or replacement prescribed in Paragraph (b) of this AD have been accomplished, the inspections required by this airworthiness directive are no longer required.

Effective October 27, 1967.

Revised April 5, 1968.