AD 2005-25-15 Airworthiness Directives; Dassault Model Falcon 2000 Airplanes Equipped With CFE Company CFE738-1-1B Turbofan Engines

Models named: Falcon 2000. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Dassault Model Falcon 2000 airplanes, certificated in any category; equipped with CFE Company CFE738-1-1B turbofan engines.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Determine Serial Number (S/N) and Inspect if Necessary (f) Within the applicable compliance time specified in paragraph (f)(1), (f)(2), or (f)(3) of this AD: Determine the serial number of the engines installed on the airplane, as identified in the table in paragraph 1.A., “Effectivity,” of Dassault Service Bulletin F2000-299, dated July 23, 2004; if any affected serial number is found on any engine, perform a borescope inspection to verify that a spherical bearing is installed on the attachment fitting of the front engine mount by doing all the applicable actions specified in the Accomplishment Instructions of the service bulletin. (1) For airplanes with any engine having 850 total landings or less as of the effective date of this AD: Before the accumulation of 880 total landings on the engine. (2) For airplanes with any engine having more than 850 total landings, but 1,000 total landings or less as of the effective date of this AD: Within 1 month after the effective date of this AD. (3) For airplanes with any engine having more than 1,000 total landings as of the effective date of this AD: Within 10 landings after the effective date of this AD. Corrective Action (g) If any spherical bearing is found missing during the inspection required by paragraph (f) of this AD: Before further flight, repair according to a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Direction Générale de l'Aviation Civile (or its delegated agent). No Reporting Requirement (h) This AD does not require submitting reporting information to the manufacturer. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, International Branch, ANM-116, 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 14 CFR 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 (j) French airworthiness directive F-2004-128, issued August 4, 2004, also addresses the subject of this AD. Material Incorporated by Reference (k) You must use Dassault Service Bulletin F2000-299, dated July 23, 2004, 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 Dassault Falcon Jet, P.O. Box 2000, South Hackensack, New Jersey 07606, 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 December 2, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-23829 Filed 12-12-05; 8:45 am] BILLING CODE 4910-13-P

This AD results from a report of a missing spherical bearing on the attachment fitting of the front engine mount on an in-service airplane, and subsequent damage and abnormal fatigue of the attachment fitting. We are issuing this AD to prevent reduced structural integrity of the engine mount, which could result in possible separation of an engine from the airplane.