AD 76-13-07

76-13-07 CESSNA: Amendment 39-2656. Applies to Models 401, 402, 411, 414 and 421 Series Airplanes.

Compliance: Required as indicated, unless already accomplished.

To prevent failure of the fork bolt located at the aft end of the main landing gear retraction system torque tube connecting the torque tube to the outboard push/pull tube, accomplish the following:

A) Within 200 hours' time in service on those airplanes having 1,800 or more hours' time in service or prior to 2,000 hours' time in service on those airplanes having less than 1,800 hours' time in service, and at each subsequent 2,000 hours' time in service thereafter, replace right and left 1/2-inch diameter P/Ns 0843518-1, 0843518-2, 0843500-35, 0843500-54, 5243518-1 and 5243518-3 fork bolts with new P/N 5243518-3 or FAA-approved superseding part number fork bolts on the airplanes specified below except airplanes on which P/N 5141052-1 fork bolts have been installed as field replacements:

401 - 401-0001 thru 401B0053

402 - 402-0001 thru 4-2B0035

411 - All Serials

414 - 414-0001 thru 414-0098

421 - 421-0001 thru 421A0158

B) Within 200 hours' time in service on those airplanes having 4,800 or more hours' time in service or prior to 5,000 hours' time in service on those airplanes having less than 4,800 hours' time in service, and at each subsequent 5,000 hours' time in service thereafter, replace right and left 5/8-inch diameter P/N 5141052-1 fork bolts with new P/N 5141052-1 or FAA-approved superseding part number fork bolts on the airplanes specified below or any lower airplane serial numbers on which these fork bolts have been installed as field replacements.

401 - 401B0054 and on

401 - 402B0036 and on

414 - 414-0099 and on

421 - 421B0001 and on

C) Fork bolt life limits set by this AD may be extended 25 hours, up to 2,025 hours for 1/2-inch diameter fork bolts and 5,025 hours for 5/8-inch diameter fork bolts, to allow replacement at regular scheduled maintenance or inspections.

D) Aircraft may be flown in accordance with FAR 21.197 to a base where this AD may be accomplished.

E) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region.

Cessna Service Letter ME75-23 or later approved revisions refers to this subject.

This amendment becomes effective July 7, 1976.