AD 2004-25-19 Airworthiness Directives; Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) Series Airplanes

This AD applies to the Bombardier airplanes, certificated in any category, that are listed in Table 1 of this AD. Table 1.—Applicability Bombardier model Having serial numbers Which have an angle of attack transducer (AOA) with the following part number CL-600-1A11 (CL-600) series airplanes 1004 through 1085 inclusive 600-59154-5 CL-600-2A12 (CL-601) series airplanes 3001 through 3066 inclusive 600-59154-5 CL-600-2B16 (CL-601-3A and CL-601-3R) series airplanes 5001 through 5194 inclusive 600-59154-5 CL-600-2B16 (CL-604) series airplanes 5301 and subsequent 600-59154-5

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Airplane Flight Manual (AFM) Revisions (f) Within 7 days after the effective date of this AD: Revise the Limitations, Performance, and Normal Procedures Sections of the applicable Canadair Challenger AFM by inserting the applicable Bombardier temporary revision (TR), as listed in Table 2 of this AD. Some TRs listed in Table 2 of this AD contain Product Support Publication (PSP) identifiers. Table 2.—Bombardier Temporary Revisions Model Temporary revision PSP Dated CL-600-1A11 (CL-600) series airplanes 600/20-2 600 (not stated in document) October 15, 2004.   600-1/15-2 600-1 (not stated in document) October 15, 2004. CL-600-2A12 (CL-601) series airplanes 601/12-2 601-1B-1 October 15, 2004.   601/13-2 601-1A-1 October 15, 2004.   601/17-2 601-1B October 15, 2004.   601/25-2 601-1A-18 (not stated in document) October 15, 2004. CL-600-2B16 (CL-601-3A and -3R) series airplanes 601/22-2 601A-1-1 October 15, 2004.   601/23-2 601A-1 October 15, 2004. CL-600-2B16 (CL-604) series airplanes 604/9-6 604-1 October 15, 2004. Repetitive Tests (g) Prior to the accumulation of 100 total flight hours on any AOA transducer, part number (P/N) 600-59154-5, since new, or within 50 flight hours after the effective date of this AD, whichever is later: Perform a linearity test of each AOA transducer by accomplishing all of the applicable actions specified in the Accomplishment Instructions of the applicable Bombardier alert service bulletin listed in Table 3 of this AD. Repeat the linearity test of each AOA transducer thereafter at intervals not to exceed 100 flight hours. Although the alert service bulletins specify to submit certain information to the manufacturer, this AD does not include such a requirement. Table 3.—Bombardier Alert Service Bulletins For model— Bombardier alert service bulletin Dated Excluding CL-600-1A11 (CL-600) series airplanes A600-0729 October 14, 2004 Appendix A CL-600-2A12 (CL-601) series airplanes and CL-600-2B16 (CL-601-3A and -3R) series airplanes A601-0571 October 14, 2004 Appendix A CL-600-2B16 (CL-604) series airplanes A604-27-026 October 14, 2004 Appendix A Corrective Action (h) For any AOA transducer, P/N 600-59154-5, that does not pass any linearity test as required by paragraph (g) of this AD: Before further flight, replace the affected AOA transducer with a serviceable transducer by accomplishing the applicable actions specified in the Accomplishment Instructions of the applicable Bombardier alert service bulletin listed in Table 3 of this AD. Alternative Methods of Compliance (AMOCs) (i) The Manager, New York Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Related Information (j) Canadian airworthiness directive CF-2004-22, dated October 22, 2004, also addresses the subject of this AD. Material Incorporated by Reference (k) You must use the Bombardier alert service bulletins and temporary revisions to the applicable Canadair Challenger airplane flight manuals specified in Table 4 of this AD, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approves the incorporation by reference of those documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. For copies of the service information, contact Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station Centre-ville, Montreal, Quebec H3C 3G9, Canada. You can review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Room PL-401, Nassif Building, Washington, DC; 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. Table 4.—Material Incorporated by Reference Bombardier document PSP Document date Alert Service Bulletin A600-0729, excluding Appendix A None October 14, 2004 Alert Service Bulletin A601-0571, excluding Appendix A None October 14, 2004 Alert Service Bulletin A604-27-026, excluding Appendix A None October 14, 2004 Temporary Revision 600/20-2 600 (not stated in document) October 15, 2004 Temporary Revision 600-1/15-2 600-1 (not stated in document) October 15, 2004 Temporary Revision 601/12-2 601-1B-1 October 15, 2004 Temporary Revision 601/13-2 601-1A-1 October 15, 2004 Temporary Revision 601/17-2 601-1B October 15, 2004 Temporary Revision 601/22-2 601A-1-1 October 15, 2004 Temporary Revision 601/23-2 601A-1 October 15, 2004 Temporary Revision 601/25-2 601-1A-18 (not stated in document) October 15, 2004 Temporary Revision 604/9-6 604-1 October 15, 2004 Issued in Renton, Washington, on December 6, 2004. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-27507 Filed 12-17-04; 8:45 am] BILLING CODE 4910-13-P

This AD was prompted by a report of premature wear of the potentiometers in AOA transducers having a certain part number. The FAA is issuing this AD to prevent a delay in the stall computer commands for stall warning, stick shaker, and stick pusher operation, due to premature wear of the potentiometers of the AOA transducers, which may cause the airplane to enter a stall condition, and result in loss of control of the airplane.