AD 2004-10-04 Airworthiness Directives; Bombardier Model CL-215-6B11 (CL215T Variant), and CL-215-6B11 (CL415 Variant) Series Airplanes

Model CL-215-6B11 (CL215T Variant) series airplanes, serial numbers 1056, 1057, 1061, 1080, 1109, 1113 through 1122 inclusive, 1124, and 1125; and Model CL-215-6B11 (CL415 Variant) series airplanes, serial numbers 2001 through 2067 inclusive; certificated in any category.

Required as indicated, unless accomplished previously. To prevent failure of the rear engine mount struts, which could subsequently result in reduced structural integrity of the nacelle and engine support structure, accomplish the following: Restatement of Requirements of AD 94-04-02 Inspection and Corrective Action (a) For Model CL-215-6B11 series airplanes, serial numbers 1057, 1061, 1080, 1113 through 1115 inclusive, 1121, 1122, 1124, and 1125; turboprop versions only: Within 50 hours time-in-service after April 4, 1994 (the effective date of AD 94-04-02, amendment 39-8820), perform a visual inspection to detect cracking in the rear engine mount struts, part number (P/N) 87110016-003, in accordance with Canadair Alert Service Bulletin 215-A3040, dated September 2, 1992. (1) If no cracking is detected, repeat the visual inspection thereafter at intervals not to exceed 50 hours time-in-service, until the requirements of paragraph (b) of this AD are accomplished. (2) If any cracking is detected, prior to further flight, replace the engine rear mount strut with a new strut, P/N 87110016-009 or -011, in accordance with the service bulletin. (b) For Model CL-215-6B11 series airplanes, serial numbers 1057, 1061, 1080, 1113 through 1115 inclusive, 1121, 1122, 1124, and 1125; turboprop versions only: Within 2 years after April 4, 1994, replace all engine rear mount struts with new struts, P/N 87110016-009 or -011, in accordance with Canadair Alert Service Bulletin 215-A3040, dated September 2, 1992. Such replacement constitutes terminating action for the inspections required by paragraph (a) of this AD. (c) For Model CL-215-6B11 series airplanes, serial numbers 1057, 1061, 1080, 1113 through 1115 inclusive, 1121, 1122, 1124, and 1125; turboprop versions only: As of April 4, 1994, no person shall install a rear engine mount strut, P/N 87110016-003, on any airplane. New Requirements of This AD Inspection and Corrective Action (d) For all airplanes: Within 50 flight hours after the effective date of this AD, perform a detailed inspection to detect cracking in the rear mount strut assemblies of the engines in accordance with Bombardier Alert Service Bulletin 215-A3111, Revision 2, dated January 23, 2003 (Model CL-215-6B11 (CL215T Variant) series airplanes); or Bombardier Alert Service Bulletin 215-A4287, Revision 2, dated January 23, 2003 (Model CL-215-6B11 (CL415 Variant) series airplanes); as applicable. Accomplishment of this detailed inspection constitutes terminating action for the requirements of paragraph (a) of this AD. Note 1: For the purposes of this AD, a detailed inspection is defined as: “An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.” (1) If no cracking is detected, repeat the detailed inspection thereafter at intervals not to exceed 250 flight hours until the requirements of paragraph (e) of this AD are accomplished. (2) If any crack is detected, before further flight, do the replacement in either paragraph (d)(2)(i) or (d)(2)(ii) of this AD in accordance with the applicable service bulletin. (i) Replace the rear engine mount strut with a new, welded strut, P/N 87110016-009 or -011. Repeat the detailed inspection thereafter at intervals not to exceed 250 flight hours until the requirements of paragraph (e) of this AD are accomplished. (ii) Replace the rear engine mount strut with a new, machined strut, P/N 87110047-001. Repeat the detailed inspection thereafter at intervals not to exceed 500 flight hours for the new, machined strut until the requirements of paragraph (e) of this AD are accomplished. Optional Terminating Replacement (e) Replace both rear engine mount struts with new, machined struts, P/N 87110047-001, in accordance with Bombardier Alert Service Bulletin 215-A3111, Revision 2, dated January 23, 2003 (Model CL-215-6B11 (CL215T Variant) series airplanes); or Bombardier Alert Service Bulletin 215-A4287, Revision 2, dated January 23, 2003 (Model CL-215-6B11 (CL415 Variant) series airplanes); as applicable. Replacement constitutes terminating action for the repetitive inspections required by this AD. Parts Installation (f) As of the effective date of this AD, no person shall install a rear engine mount strut, P/N 87110016-003, on any airplane. Reporting Paragraph in Service Bulletins (g) Although the service bulletins referenced in this AD specify to submit certain information to the manufacturer, this AD does not include such a requirement. Alternative Methods of Compliance (h) In accordance with 14 CFR 39.19, the Manager, New York Aircraft Certification Office (ACO), FAA, is authorized to approve alternative methods of compliance (AMOCs) for this AD. Incorporation by Reference (i) The actions shall be done in accordance with Canadair Alert Service Bulletin 215-A3040, dated September 2, 1992; Bombardier Alert Service Bulletin 215-A3111, Revision 2, dated January 23, 2003; and Bombardier Alert Service Bulletin 215-A4287, Revision 2, dated January 23, 2003; as applicable. (1) The incorporation by reference of Bombardier Alert Service Bulletin 215-A3111, Revision 2, dated January 23, 2003; and Bombardier Alert Service Bulletin 215-A4287, Revision 2, dated January 23, 2003; 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-A3040, dated September 2, 1992, was approved previously by the Director of the Federal Register as of April 4, 1994 (59 FR 10272). (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; at the FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, suite 410, Westbury, New York; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Note 2: The subject of this AD is addressed in Canadian airworthiness directive CF-2003-02, dated February 28, 2003. Effective Date (j) This amendment becomes effective on June 21, 2004. Issued in Renton, Washington, on May 5, 2004. Ali Bahrami, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-10739 Filed 5-14-04; 8:45 am] BILLING CODE 4910-13-P