85-17-07: Wing Rear Spar

85-17-07 CESSNA: Amendment 39-5125. Applies to the following Cessna airplanes certificated in any category: MODEL SERIAL NUMBER U206F/TU206F S/N U20601071 thru U20603521 U206G/TU206G S/N U20603522 thru U20604649 207/T207 S/N 20700001 thru 20700315 207A/T207A S/N 20700363 thru 20700767 Compliance: Required within the next 100 hours time-in-service after the effective date of this AD unless already accomplished. To prevent a possible failure in the wing rear spar on airplanes that have had the full spar or inboard end of the spar replaced, accomplish the following: (a) Visually inspect the airplane in accordance with Cessna Single Engine Service Bulletin SEB85-9 dated May 3, 1985. If the P/N 1222111-1 doubler is missing, prior to further flight repair the spar in accordance with SEB85-9. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent method of compliance with this AD may be used if approved by Manager, Wichita Aircraft Certification Office, Federal Aviation Administration, 1801 Airport Road, Room 100, Wichita, Kansas 67209; Telephone (316) 946-4400. All persons affected by this directive may obtain copies of the document referred to herein upon request to Cessna Aircraft Company, Post Office Box 1521, Wichita, Kansas 67201 or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on September 30, 1985.