82-26-05: Rudder Balance Weight Rib

82-26-05 CESSNA: Amendment 39-4519. Applies to Models 335 (S/N 335-0001 through 335- 0065), 340 (S/N 340-0001 through 340-0555), and 340A (S/N 340A0001 through 340A1521) airplanes certificated in any category. COMPLIANCE: Required as indicated, unless already accomplished. To ensure structural integrity of the rudder balance weight rib, accomplish the following: a) Within the next 100 hours time-in-service after the effective date of this AD and each 100 hours time-in-service thereafter, remove the fiberglass rudder tip cap and visually inspect the original rudder balance weight rib, Cessna P/N 0831311-1, for cracks. If cracks are found, before further flight, install a new rudder balance weight rib Cessna P/N 5331004-2. b) After Cessna P/N 5331004-2 rudder balance weight rib has been installed, the inspections required by paragraph a) of this AD may be discontinued. c) Aircraft may be flown, in accordance with Federal Aviation Regulation 21.197, to a location where the provisions of this AD can be accomplished. d) Any equivalent method of compliance with this AD must be approved by the Manager, Aircraft Certification Office, Federal Aviation Administration, Room 238, Terminal Building 2299, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 269-7000. Cessna Service Information Letter, ME 82-8 dated April 2, 1982, pertains to this subject. This amendment becomes effective December 27, 1982.