AD 2006-22-04 Airworthiness Directives; Airbus Model A318-100 and A319-100 Series Airplanes; Model A320-111 Airplanes; Model A320-200, A321-200, A330-200, A330-300, A340-200, and A340-300 Series Airplanes; Model A340-541 Airplanes; and Model A340-642 Airplanes; Equipped With Certain Sogerma-Services Powered Seats

This AD applies to the airplanes identified in Table 1 of this AD, certificated in any category; equipped with any Sogerma-Services pilot or co-pilot seat identified in Sogerma-Services Service Bulletin TAAI1-25-617, dated February 1, 2005, excluding any seat having part number (P/N) TAAI3-03PE00-01, TAAI3-03PE01-01, TAAI3-03CE00-01, and TAAI3-03CE01-01, with a serial number (S/N) higher than 791, on which the actuator has not been replaced after the date of issuance of the original standard airworthiness certificate or date of issuance of the original export certificate of airworthiness. Table 1.—Applicability Airbus model (1) A318-111 and -112 airplanes. (2) A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes. (3) A320-111 airplanes. (4) A320-211, -212, -214, -231, -232, and -233 airplanes. (5) A321-111, -112, -131, -211 and -231 airplanes. (6) A330-201, -202, -203, -223, and -243 airplanes. (7) A330-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes. (8) A340-211, -212, and -213 airplanes. (9) A340-311, -312, and -313 airplanes. (10) A340-541 airplanes. (11) A340-642 airplanes.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Inspection for the P/N of the Actuator (f) Within 56 months after the effective date of this AD, inspect to determine if an actuator identified in Table 2 of this AD is installed in the pilot's or co-pilot's seat, in accordance with Part 1, Paragraph D., “DESCRIPTION,” of Sogerma-Services Service Bulletin TAAI1-25-617, dated February 1, 2005. If any actuator identified in Table 2 of this AD is found installed, within 56 months after the effective date of this AD, do the applicable corrective actions in accordance with Paragraph D., “DESCRIPTION,” of the service bulletin. Table 2.—Affected Actuators Manufacturer Actuator P/N (1) Messier-Bugatti 4136290004, S/Ns 5079 and below. (2) Messier-Bugatti 4136290005, S/Ns 5079 and below. Note 1: Sogerma-Services Service Information Letter SIL-TAAI1-25-059, dated February 8, 2005, and Airbus Operator Information Telex SE 999.0040/05/FB, dated May 27, 2005, are additional sources of service information for inspecting the seats. Concurrent Replacements (g) For Messier-Bugatti actuators identified in Table 2 of this AD: Concurrently with the applicable corrective action required by paragraph (f) of this AD, replace the rotors on both vertical and horizontal movements with new rotors, and replace the clutch cap with a new cap, in accordance with Messier-Bugatti Service Bulletin 4136290004-25-05 or 4136290005-25-02, both dated April 2005, as applicable. No Report Required (h) Although Sogerma-Services Service Bulletin TAAI1-25-617, dated February 1, 2005, specifies sending certain information to the manufacturer, this AD does not require that action. Alternative Methods of Compliance (AMOCs) (i)(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 (j) French airworthiness directive F-2005-164, issued September 28, 2005, also addresses the subject of this AD. Material Incorporated by Reference (k) You must use Messier-Bugatti Service Bulletin 4136290004-25-05, dated April 2005, or Messier-Bugatti Service Bulletin 4136290005-25-02, dated April 2005; and Sogerma-Services Service Bulletin TAAI1-25-617, dated February 1, 2005; as applicable; 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 these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Sogerma-Services, Z.I. de l'Arsenal—BP 109—17303 Rochefort Cedex, France; and Messier-Bugatti, 45 Avenue Victor Hugo—Bat. 227—93538 Aubervilliers, France, 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 October 11, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-17662 Filed 10-27-06; 8:45 am] BILLING CODE 4910-13-P

This AD results from a report of heavy wear at the driving gear of the rotor shaft end of the electrical driven motor on certain actuators of the pilot's and co-pilot's seats. We are issuing this AD to prevent uncommanded movement of the pilot's or co-pilot's seat during takeoff or landing, which could result in interference with the operation of the airplane and consequent temporary loss of airplane control.