95-22-04: Main Landing Gear Axle

95-22-04 CANADAIR: Amendment 39-9411. Docket 95-NM-173-AD. Applicability: Model CL-215-1A10 (piston) and CL-215-6B11 (turboprop) series airplanes, having serial numbers 1001 through 1125 inclusive, certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (f) of this AD to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent cracking in the inner bearing surface of the main landing gear (MLG) axle, which can result in failure of the axle, separation of the wheel from the aircraft, and consequent reduced controllability of the airplane during takeoff or landing, accomplish the following: (a) Within 60 days after the effective date of this AD, perform either an eddy current inspection or a chemical inspection of the inner bearing surface area of the left and right MLG axles to determine if they have been reworked using chromium plating, in accordance with Canadair Alert Service Bulletin 215-A462, dated June 2, 1993. (b) If the inner bearing surface of the MLG axle has not been reworked using chromium plating, no further action is required by this AD for that axle. (c) If the inner bearing surface of the MLG axle has been reworked using chromium plating, prior to further flight, perform an ultrasonic inspection to detect cracking in the axle, in accordance with Canadair Alert Service Bulletin 215-A462, dated June 2, 1993. (1) If no crack is detected during this inspection, repeat the ultrasonic inspection at intervals not to exceed 150 landings. (2) If any crack is detected during this inspection, prior to further flight, remove the cracked axle and replace it with a serviceable axle that does not have an inner bearing surface that has been reworked using chromium plating, in accordance with the service bulletin. (d) Within 5 days after completing each ultrasonic inspection required by paragraph (c) of this AD, submit a report of inspection findings, both positive and negative, to Canadair, Amphibious Aircraft Division, Customer Support, Dept. 645, Attention: Manager of Technical Support, P.O. Box 6087, Station A,Montreal, Quebec H3C 3G9, Canada; fax (514) 856-0152. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. (e) Installation of an MLG axle that does not have an inner bearing surface that has been reworked using chromium plating, in accordance with Canadair Alert Service Bulletin 215- A462, dated June 2, 1993, constitutes terminating action for the inspections required by this AD for that axle. (f) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, New York Aircraft Certification Office (ACO), FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. (g) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (h) The inspections and replacement shall be done in accordance with Canadair Alert Service Bulletin 215-A462, dated June 2, 1993. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Bombardier, Inc., Canadair Aerospace Group, P.O. Box 6087, Station Centre-ville, Quebec H3C 3G9, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, New York Aircraft Certification Office, Engine and Propeller Directorate, 10 Fifth Street, Third Floor, Valley Stream, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (i) This amendment becomes effective on November 8, 1995.