AD 2004-22-26 Airworthiness Directives; Airbus Model A330, A340-200, and A340-300 Series Airplanes

Models named: A330 series, A340-200, A340-300 series. Read the applicability below — it usually turns on serial or part numbers too.

Model A330 series airplanes; and Model A340-200 and A340-300 series airplanes; certificated in any category; except those airplanes on which Airbus Modification 48579 was incorporated in production.

Required as indicated, unless accomplished previously. To prevent loss of the sensor strut function, resulting in the inability to detect flap drive disconnection at flap track stations 4 and 5, which could lead to separation of the outboard flap from the airplane, and consequent reduced controllability of the airplane; accomplish the following: Inspection (a) At the latest of the times specified in paragraphs (a)(1), (a)(2), and (a)(3) of this AD: Do an inspection, by applying hand force to the piston of the sensor struts and moving the sensor struts longitudinally, for evidence of corrosion in the sensor struts at flap track 4, on the left and right sides of the airplane, by doing all the applicable actions specified in the Accomplishment Instructions of Airbus Service Bulletin A330-27-3091, Revision 03 (for Model A330 series airplanes); or Service Bulletin A340-27-4097, Revision 03 (for Model A340-200 and -300 series airplanes); both dated January 16, 2004; as applicable. If the longitudinal travel range is 60.0 millimeters (2.36 inches) or more: Repeat the inspection thereafter at intervals not to exceed 18 months, until the requirements of paragraph (d) of this AD are accomplished. (1) Within 18 months since the date of issuance of the original Airworthiness Certificate or the date of issuance of the original Export Certificate of Airworthiness, whichever occurs first. (2) Within 2,800 flight hours after the effective date of this AD. (3) Within 6 months after the effective date of this AD. Related Investigative and Corrective Actions (b) If the result of the inspection required by paragraph (a) of this AD is a longitudinal travel range of less than 60.0 mm (2.36 inches): Before further flight, remove all affected sensor struts, and measure the axial force of any affected sensor struts, by doing all of the applicable actions per the Accomplishment Instructions of Airbus Service Bulletin A330-27-3091, Revision 03 (for Model A330 series airplanes); or Service Bulletin A340-27-4097, Revision 03 (for Model A340-200 and -300 series airplanes); both dated January 16, 2004; as applicable. (1) If the axial force F is less than or equal to 50 daN (112.41 lbf.): Clean and re-install the sensor struts per the Accomplishment Instructions of the applicable service bulletin. Repeat the inspection required by paragraph (a) of this AD thereafter at intervals not to exceed 18 months, until the requirements of paragraph (d) of this AD are accomplished. (2) If the axial force F is more than 50 daN (112.41 lbf.): Before further flight, do a detailed inspection for cracking and/or deformation of the adjacent structure and attachment parts per the Accomplishment Instructions of the applicable service bulletin. (i) If no cracking and/or deformation is found: Re-install the sensor struts and within 25 flight cycles after the inspection required by paragraph (b) of this AD, replace the sensor struts and attachment bolts per the Accomplishment Instructions of the applicable service bulletin. Repeat the inspection required by paragraph (a) of this AD thereafter at intervals not to exceed 18 months, until the requirements of paragraph (d) of this AD are accomplished. (ii) If any cracking and/or deformation is found: Before further flight, repair any cracked or deformed structure and attachment parts per a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction Générale de l'Aviation Civile (or its delegated agent); and replace the sensor struts and attachment bolts per the Accomplishment Instructions of the applicable service bulletin. Repeat the inspection required by paragraph (a) of this AD thereafter at intervals not to exceed 18 months, until the requirements of paragraph (d) of this AD are accomplished. 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.” Concurrent Requirements (c) The actions required by paragraphs (a) and (b) of this AD must be done before or concurrently with the requirements of paragraph (d) of this AD. Replacement of any sensor strut with a sensor strut having part number (P/N) F5757492600000, during accomplishment of paragraph (b) of this AD, is acceptable for compliance with paragraph (d) of this AD, for that strut. Terminating Action (d) Within 30 months after the effective date of this AD: Replace all existing sensor struts with new, improved sensor struts having P/N F5757492600000 per the Accomplishment Instructions of Airbus Service Bulletin A330-27-3092 (for Model A330 series airplanes); or Service Bulletin A340-27-4098 (for Model A340-200 and -300 series airplanes); both dated February 14, 2003; as applicable. Accomplishment of this replacement constitutes terminating action for the repetitive inspections required by paragraphs (a) and (b) of this AD. Actions Done per Previous Issue of Service Bulletins (e) Accomplishment of the specified actions before the effective date of this AD per Airbus Service Bulletin A330-27-3091, dated February 6, 2002, Revision 01, dated May 17, 2002, or Revision 02, dated September 5, 2002; or A340-27-4097, dated February 6, 2002, Revision 01, dated May 17, 2002, or Revision 02, dated September 5, 2002; as applicable; is considered acceptable for compliance with the applicable requirements of paragraphs (a) and (b) of this AD. Submission of Information Not Required (f) Although the service bulletins specify to send inspection results to the manufacturer, that action is not required by this AD. Alternative Methods of Compliance (g) In accordance with 14 CFR 39.19, the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, is authorized to approve alternative methods of compliance for this AD. Incorporation by Reference (h) Unless otherwise specified in this AD, the actions shall be done in accordance with the applicable Airbus service bulletins listed in Table 1 of this AD. Table 1.—Service Bulletins Incorporated by Reference Airbus service bulletin Revision level Date A330-27-3091 03 Jan. 16, 2004. A330-27-3092 Original Feb. 14, 2003. A340-27-4097 03 Jan. 16, 2004. A340-27-4098 Original Feb. 14, 2003. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; 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 French airworthiness directives F-2003-425 and F-2003-426, both dated December 10, 2003. Effective Date (i) This amendment becomes effective on December 14, 2004. Issued in Renton, Washington, on October 26, 2004. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-24625 Filed 11-8-04; 8:45 am] BILLING CODE 4910-13-P