AD 2004-03-24 Airworthiness Directives; Airbus Model A330-200, A330-300, A340-200, and A340-300 Series Airplanes

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

All Model A330-200, A330-300, A340-200, and A340-300 series airplanes; certificated in any category.

Required as indicated, unless accomplished previously. To ensure proper functioning of the elevator surfaces, and to detect and correct cracking of the attachment lugs of the mode selector valve position transducers on the elevator servocontrols, which could result in partial loss of elevator function and consequent reduced controllability of the airplane, accomplish the following: AFM Revision (a) Within 30 days after the effective date of this AD, revise the Limitations section of the airplane flight manual (AFM) to include a pre-flight elevator check, by including the following language. This may be done by inserting a copy of this AD into the applicable AFM. Thereafter perform the pre-flight check before every flight in accordance with the procedure. Prior or During Taxi:  “FLIGHT CONTROLS CHECK  1. AT A CONVENIENT STAGE, PRIOR TO OR DURING TAXI, AND BEFORE ARMING THE AUTOBRAKE, THE PF SILENTLY APPLIES FULL LONGITUDINAL AND LATERAL SIDESTICK DEFLECTION. ON THE F/CTL PAGE, THE PNF CHECKS FULL TRAVEL OF ALL ELEVATORS AND ALL AILERONS, AND THE CORRECT DEFLECTION AND RETRACTION OF ALL SPOILERS. THE PNF CALLS OUT “FULL UP,” “FULL DOWN,” “NEUTRAL,” “FULL LEFT,” “FULL RIGHT,” “NEUTRAL,” AS EACH FULL TRAVEL/NEUTRAL POSITION IS REACHED. THE PF SILENTLY CHECKS THAT THE PNF CALLS ARE IN ACCORDANCE WITH THE SIDESTICK ORDER.   NOTE: IN ORDER TO REACH FULL TRAVEL, FULL SIDESTICK MUST BE HELD FOR A SUFFICIENT PERIOD OF TIME.  2. THE PF PRESSES THE PEDAL DISC PUSHBUTTON ON THE NOSEWHEEL TILLER, AND SILENTLY APPLIES FULL LEFT RUDDER, FULL RIGHT RUDDER, AND NEUTRAL. THE PNF CALLS OUT “FULL LEFT,” “FULL RIGHT,” “NEUTRAL,” AS EACH FULL TRAVEL/NEUTRAL POSITION IS REACHED.  3. THE PNF APPLIES FULL LONGITUDINAL AND LATERAL SIDESTICK DEFLECTION, AND SILENTLY CHECKS FULL TRAVEL AND CORRECT SENSE OF ALL ELEVATORS AND ALL AILERONS, AND CORRECT DEFLECTION AND RETRACTION OF ALL SPOILERS, ON THE ECAM F/CTL PAGE.” Note 1: Full and complete elevator travel (position commanded) can be verified on the ECAM Flight Control Page. A determination of “correct sense” should include verification that there is complete and full motion of the sidesticks without binding. (b) If any pre-flight check required by paragraph (a) of this AD reveals improper function of the elevator: Before further flight, perform the inspections required by paragraph (c) of this AD. Inspections (c) At the applicable time specified in paragraph (c)(1) or (c)(2) of this AD, except as required by paragraph (b) of this AD: Perform a dye penetrant inspection of the attachment lugs of the mode selector valve position transducers on each elevator servocontrol installed at damping positions 3CS1 and 3CS2. Do the inspection in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-27A3115 or A340-27A4119, both Revision 02, both dated December 30, 2003, as applicable (hereafter “the service bulletin”). An inspection that is done before the effective date of this AD is acceptable for compliance with the initial inspection requirement of this paragraph, if the inspection is done in accordance with any of the following Airbus All Operators Telexes (AOTs): AOT A330-27A3115 or A340-27A4119, dated September 11, 2003, or Revision 01 of each AOT dated September 25, 2003; as applicable. Repeat the inspection thereafter at intervals not to exceed 350 flight cycles. (1) If the age of the servocontrol from the date of its first installation on the airplane can be positively determined: Do the inspection before the accumulation of 1,000 total flight cycles on the elevator servocontrol, or within 350 flight cycles on the servocontrol after the effective date of this AD, whichever occurs later. (2) If the age of the servocontrol from the date of its first installation on the airplane cannot be positively determined, do the inspection within 350 flight cycles on the servocontrol after the effective date of this AD. Note 2: The service bulletin refers to Goodrich Actuation Systems Inspection Service Bulletin SC4800-27-13 as an additional source of service information for the inspection. Corrective Actions (d) If any crack is found during any inspection required by paragraph (c) of this AD: Before further flight, replace either the transducer or servocontrol with a new part, in accordance with the service bulletin. Reporting Requirement (e) If any crack is found during any inspection required by paragraph (c) of this AD: Submit a report in accordance with the service bulletin at the applicable time(s) specified in paragraphs (e)(1) and (e)(2) of this AD: Submit reports to Airbus Customer Services, Engineering and Technical Support, Attention: J. Laurent, SEE53, fax +33/(0)5.61.93.44.25, Sita Code TLSBQ7X. Under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq. ), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120-0056. (1) For an initial inspection done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. (2) For an inspection done after the effective date of this AD: Submit the report within 30 days after the inspection. Parts Installation (f) As of the effective date of this AD, no person may install the following part on any airplane: a transducer, or a transducer fitted on an elevator servocontrol, in the operator's inventory before September 25, 2003, unless that transducer has been inspected in accordance with the service bulletin and is crack-free. 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 must be done in accordance with Airbus Service Bulletin A330-27A3115, Revision 02, including Appendix 01, dated December 30, 2003; or Airbus Service Bulletin A340-27A4119, Revision 02, including Appendix 01, dated December 30, 2003; as applicable. 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 Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Note 3: The subject of this AD is addressed in French airworthiness directive F-2003-460, dated December 24, 2003. Effective Date (i) This amendment becomes effective on February 26, 2004. Issued in Renton, Washington, on February 2, 2004. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-2683 Filed 2-10-04; 8:45 am] BILLING CODE 4910-13-P