AD 71-01-03

71-01-03 CESSNA: Amdt. 39-1138. Applies to Model 177 series (Serial Numbers 17700001 through 17701164) and Model 177A series (Serial Numbers 17701165 through 17701370) Airplanes.

Compliance: Required as indicated, unless already accomplished.

To prevent cracks in the stabilator attachment angles P/N 1712108, accomplish the following:

A) Within 25 hours' time in service after the effective date of this AD, remove the fuselage tail stinger and inspect the stabilator attachment angles, P/N 1712108, for evidence of cracks using the dye penetrant method in conjunction with the procedure set forth in Cessna Service Kit, No. SK 177-11, dated December 8, 1970, or any other method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. If no cracks are found during this inspection, install stiffener brackets, P/N 1709019-3 and -4, in accordance with the instructions contained in said Service Kit.

B) If cracks are detected during the inspectionrequired by Paragraph A, prior to further flight, rework or replace the stabilator attachment angles, P/N 1712108, and then install stiffener brackets P/N 1709019-3 and -4 in accordance with the instructions contained in Cessna Service Kit SK 177-11, dated December 8, 1970, or any other method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region.

Cessna Service Letter SE70-32, dated December 18, 1970, or later FAA-approved revisions pertain to this subject.

This amendment becomes effective January 5, 1971.