AD 90-02-13

90-02-13 CESSNA: Amendment 39-6445.

Applicability: The following models and serial numbered airplanes certificated in any category:

MODEL SERIAL NUMBERS 310 310L0001 through 310R1690 320 320E0001 through 320F0045 340 340-0001 through 340A0801 401 401-0001 through 401B0221 402 402-0001 through 402C0125 411 411-0001 through 411A0300 414 414-0001 through 414A0340 421 421-0001 through 421C0715

Compliance: Required as indicated after the effective date of this AD, unless already accomplished.

To assure structural integrity of the main gear barrel inner bearing and prevent jamming of the inner and outer barrels of the main landing gears, accomplish the following:

(a) Upon the accumulation of 1,300 hours time-in-service (TIS), or within the next 300 hours TIS after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 1,000 hours TIS, inspect the left and right main gear strut barrel inner bearings, Part Numbers 5041108-1 and 5041108-2, in accordance with the following procedures:

(1) Using the appropriate Aircraft Service Manual or Maintenance Manual, refer to the Landing Gear section and use it as a guide to remove the lower barrel and axle assemblies from the upper barrel assemblies.

(2) Remove all oil and grease from the external lock rings, inner ring bearings, and extended stop spacers.

(3) Visually inspect the external lock rings, inner bearings, and extended stop spacers for cracks.

(4) If any cracks are found in the external lock rings or the extended stop spacers, prior to further flight replace the cracked part with a serviceable part.

(5) If any cracks are found in the inner bearings, prior to further flight replace the cracked part with a Part Number (P/N) 5141109-1 bearing.

(6) If no cracks are found, magnetic particle inspect the inner bearings using the procedures specified in Part B, "MAGNETIC PARTICLE NONDESTRUCTIVE INSPECTION PROCEDURES" of Cessna Service Bulletin MEB88-7, dated December 2, 1988. If any cracks are found, prior to further flight replace the cracked part with a P/N 5141109-1 bearing.

(b) The 1,000 hour repetitive inspections specified in paragraph (a) of this AD are no longer required when the P/N 5141109-1 bearing is installed in each gear.

(c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished.

(d) An alternate method of compliance or adjustment of the initial or repetitive compliance times which provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209.

NOTE: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and send it to the Manager, Wichita Aircraft Certification Office.

All persons affected by this directive may obtain copies of the document referred to herein upon request to the Cessna Aircraft Company, P.O. Box 7704, Wichita, Kansas 67277; or may examine this document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.

This amendment (39-6445, AD 90-02-13) becomes effective on February 5, 1990.