AD 2001-22-09

Applicability: Model CL-600-2B19 series airplanes, certificated in any category, having serial numbers 7003 and subsequent, and equipped with a main landing gear (MLG) main fitting having part number (P/N) 17064-101, 17064-102, 17064-103, or 17064-104.

Note 1:

This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been 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 request approval for an alternative method of compliance in accordance with paragraph (g) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Compliance: Required as indicated, unless accomplished previously.

To prevent failure of MLG main fitting, which could result in collapse of the MLG upon landing, accomplish the following:

(a) Prior to the accumulation of 1,500 total flight cycles, or within 150 flight cycles after December 4, 2001, the effective date of this AD, whichever occurs later: Perform an eddy current inspection to detect cracking of the MLG main fittings, in accordance with Part B of the Accomplishment Instructions of Bombardier Alert Service Bulletin A601R-32-079, Revision D, dated December 1, 2000. If any cracking is found, prior to further flight, replace the cracked fitting with a new or serviceable fitting in accordance with the alert service bulletin. Repeat the inspection thereafter at intervals not to exceed 500 flight cycles.

(b) Prior to the accumulation of 1,500 total flight cycles since the date of manufacture, or within 500 flight cycles after the effective date of this AD, whichever occurs later: Perform a servicing (Oil and Nitrogen) of the MLG shock struts (left and right main landing shock struts), in accordance with Part C (for airplanes on the ground) or Part D (for airplanes on jacks) of the Accomplishment Instructions of Bombardier Alert Service Bulletin A601R-32-079, Revision D, dated December 1, 2000.

(c) Within 500 flight cycles after completing the actions required by paragraph (b) of this AD: Perform an inspection of the MLG left and right shock struts for nitrogen pressure, visible chrome dimension, and oil leakage, in accordance with Part E of the Accomplishment Instructions of Bombardier Alert Service Bulletin A601R-32-079, Revision D, dated December 1, 2000. Thereafter, repeat the inspection at intervals not to exceed 500 flight cycles.

(d) If the chrome extension dimension of the shock strut pressure reading is outside the limits specified in the Airplane Maintenance Manual, Task 32-11-05-220-801, or any oil leakage is found: Prior to further flight, service the MLG shock strut in accordance with Part C (for airplanes on the ground) or Part D (for airplanes on jacks) of the Accomplishment Instructions of Bombardier Alert Service Bulletin A601R-32-079, Revision D, dated December 1, 2000.

(e) After the effective date of this AD: After a total of five consecutive inspections of the MLG shock struts that verify that the shock struts are serviced properly, and a total of five consecutive eddy current inspections of the MLG main fitting has been accomplished that verify there is no cracking of the main fitting, in accordance with Bombardier Alert Service Bulletin A601R-32-079, Revision D, dated December 1, 2000, the repetitive interval for the eddy current inspections required by paragraph (a) of this AD may be extended from every 500 flight cycles to every 1,000 flight cycles.

(f) Within 30 days after each inspection and servicing required by paragraphs (a), (b), and (c) of this AD, report all findings, positive or negative, to: Bombardier Aerospace, Regional Aircraft, CRJ Action Desk, fax number 514-855-8501. Information collection requirements contained in this AD 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.

(g) 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. 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.

(h) 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.

(i) The actions shall be done in accordance with Bombardier Alert Service Bulletin A601R-32-079, Revision D, dated December 1, 2000. This incorporation by reference was approved previously by the Director of the Federal Register as of December 4, 2001 (66 FR 54658, October 30, 2001). 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, 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.

Note 3:

The subject of this AD is addressed in Canadian airworthiness directive CF-1999-32R1, dated January 22, 2001.

(j) The effective date of this amendment remains December 4, 2001.