2004-03-13: Main landing gear (MLG) axles

2004-03-13 Bombardier, Inc. (Formerly Canadair): Amendment 39-13457. Docket 2003-NM-139-AD. Supersedes AD 95-22-04, Amendment 39-9411. Applicability: Model CL-215-1A10 (piston) and CL-215-6B11 (turboprop) series airplanes, having serial numbers 1001 through 1125 inclusive, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent cracking in the inner bearing surface of the main landing gear (MLG) axles, which could result in failure of an axle, subsequent separation of the wheel from the airplane, and consequent reduced controllability of the airplane during takeoff or landing, accomplish the following: Restatement of Certain Requirements of AD 95-22-04 Repetitive Inspections/Corrective Action (a) Within 60 days after November 8, 1995 (the effective date of AD 95-22-04, amendment 39-9411), 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; or Bombardier Alert Service Bulletin 215-A462, Revision 3, dated January 17, 2000. If the inner bearing surface of the MLG axle has not been reworked using chromium plating, no further action is required by this paragraph for that axle only. (b) 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; or Bombardier Alert Service Bulletin 215-A462, Revision 3, dated January 17, 2000. (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. New Requirements of This AD Dimensional Check/Follow-on Corrective Actions (c) Within 150 landings after the effective date of this AD: Do a dimensional check by measuring the diameter of the left and right MLG axles to determine if they have been reworked outside the dimensions specified in Canadair CL-215 Overhaul Manual PSP 298, or if the axle has unknown rework dimensions or the service life of that axle cannot be determined, in accordance with Bombardier Alert Service Bulletin 215-A462, Revision 3, dated January 17, 2000. (1) If any axle has been reworked outside the specified dimensions, or has unknown rework dimensions, or if the service life of that axle cannot be determined: Prior to further flight, do an ultrasonic inspection to detect cracking of the axle, in accordance with the alert service bulletin, and replace the axle with a serviceable axle before the accumulation of 1,050 total landings, in accordance with the alert service bulletin. Such replacement ends the repetitive inspections for that axle only. (i) If no cracking is detected during the inspection required by paragraph (c)(1) of this AD, repeat the inspection at intervals not to exceed 150 landings, and replace with a serviceable axle before the accumulation of 1,050 total landings, in accordance with the alert service bulletin. (ii) If any cracking is detected during the inspection required by paragraph (c)(1) of this AD, prior to further flight, replace the axle with a serviceable axle in accordance with the alert service bulletin. (2) If the service life of the axle is known, and the axle has not been reworked outside the specified dimensions, no further action is required by this AD for that axle only. Actions Done per Previous Issues of Service Bulletin (d) Inspections and replacements done before the effective date of this AD in accordance with Canadair Alert Service Bulletin 215- A462, dated June 2, 1993; or Bombardier Alert Service Bulletin 215- A462, Revision 1, dated August 26, 1996; or Revision 2, dated March 3, 1999; are considered acceptable for compliance with the applicable actions specified in this AD. Alternative Methods of Compliance (e) In accordance with 14 CFR 39.19, the Manager, New York Aircraft Certification Office, FAA, is authorized to approve alternative methods of compliance for this AD. Incorporation by Reference (f) The actions shall be done in accordance with Canadair Alert Service Bulletin 215-A462, dated June 2, 1993; and Bombardier Alert Service Bulletin 215-A462, Revision 3, dated January 17, 2000; as applicable. (1) The incorporation by reference of Bombardier Alert Service Bulletin 215-A462, Revision 3, dated January 17, 2000; is approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) The incorporation by reference of Canadair Alert Service Bulletin 215-A462, dated June 2, 1993; was approved previously by the Director of the Federal Register as of November 8, 1995 (60 FR 54421, October 24, 1995). (3) Copies may be obtained from Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station Centre-ville, Montreal, 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, 1600 Stewart Avenue, Westbury, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Note 1: The subject of this AD is addressed in Canadian airworthiness directive CF-1993-08R3, dated March 30, 2000. Effective Date (g) This amendment becomes effective on March 17, 2004.