AD 2006-07-22 Airworthiness Directives; BAE Systems (Operations) Limited Model BAe 146 and Model Avro 146-RJ Airplanes

Models named: BAe 146-100A, -200A, -300A series, Avro 146-RJ70A, 146-RJ85A, 146-RJ100A. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to BAE Systems (Operations) Limited Model BAe 146-100A, -200A, and -300A series airplanes, and Model Avro 146-RJ70A, 146-RJ85A, and 146-RJ100A airplanes; certificated in any category; as identified in BAE Systems (Operations) Limited Modification Service Bulletin SB.25-459-36241A, Revision 1, dated March 30, 2005.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Modification (f) Within 9 months after the effective date of this AD: Do the actions specified in either paragraph (f)(1) or (f)(2) of this AD by doing all the applicable actions specified in the Accomplishment Instructions of BAE Systems (Operations) Limited Modification Service Bulletin SB.25-459-36241A, Revision 1, dated March 30, 2005. (1) For airplanes on which BAE Modification HCM50303C has been installed, but on which BAE Modification HCM30033E, HCM30033F, HCM30033G, or HCM30033N has not been installed: Modify the control cable duct on the left bulkhead structure at frame 12 in accordance with Part 1 of the Accomplishment Instructions of the service bulletin. (2) For airplanes on which BAE Modification HCM50303C has been installed, and on which BAE Modification HCM30033E, HCM30033F, HCM30033G, or HCM30033N has also been installed: Modify the control cable duct on the left bulkhead structure at frame 12 and the forward toilet bulkhead structure in accordance with Parts 1 and 2 of the Accomplishment Instructions of the service bulletin. Modifications Accomplished According to Previous Issue of Service Bulletin (g) Modifications accomplished before the effective date of this AD in accordance with BAE Systems (Operations) Limited Modification Service Bulletin SB.25-459-36241A, dated July 22, 2004, are considered acceptable for compliance with the corresponding action specified in this AD. Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (i) British airworthiness directive G-2005-0026, dated September 21, 2005, also addresses the subject of this AD. Material Incorporated by Reference (j) You must use BAE Systems (Operations) Limited Modification Service Bulletin SB.25-459-36241A, Revision 1, dated March 30, 2005, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact British Aerospace Regional Aircraft American Support, 13850 Mclearen Road, Herndon, Virginia 20171, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Room PL-401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Issued in Renton, Washington, on March 30, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06-3379 Filed 4-10-06; 8:45 am] BILLING CODE 4910-13-P

This AD results from a structural analysis by the manufacturer which revealed that rapid decompression of the flight compartment with the door closed could cause structural deformation of the left bulkhead structure at frame 12, and of the attached cable duct structure. The duct structure protects the cables for the primary flight controls. We are issuing this AD to prevent deformation of the cable duct structure in the event of a rapid decompression, which could result in restriction of the primary flight controls and consequent reduced controllability of the airplane.