AD 2004-20-12 Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes; Model A300 B4-600, A300 B4-600R, A300 F4-600R Series Airplanes, and A300 C4-605R Variant F Airplanes (Collectively Called A300-600); and Model A310 Series Airplanes

Models named: A300 B2, B4 series, A300 B4-600, A300 B4-600R, A300 F4-600R series, A310 series. Read the applicability below — it usually turns on serial or part numbers too.

All Model A300 B2 and B4 series airplanes; Model A300 B4-600, A300 B4-600R, A300 F4-600R series airplanes, and A300 C4-605R Variant F airplanes (collectively called A300-600); and Model A310 series airplanes; certificated in any category.

Required as indicated, unless accomplished previously. To detect and correct frayed or corroded control cables for the elevator and rudder, which could result in a ruptured control cable, and possible reduced controllability of the airplane, accomplish the following: Definitions (a) The term “service bulletin,” as used in this AD, means the Accomplishment Instructions of the following service bulletins, as applicable: (1) For Model A300 B2 and A300 B4 series airplanes: Airbus Service Bulletin A300-27A0197, Revision 01, including Appendix 01, dated February 26, 2003; (2) For Model A300 B4-600, A300 B4-600R, A300 F4-600R series airplanes; and A300 C4-605R Variant F airplanes (collectively called A300-600): Airbus Service Bulletin A300-27A6051, including Appendix 01, dated August 8, 2002; and (3) For Model A310 series airplanes: Airbus Service Bulletin A310-27A2098, including Appendix 01, dated August 8, 2002. (b) In this AD, the phrase “date of airworthiness certification” means the date of issuance of the original Airworthiness Certificate or the original Export Certificate of Airworthiness, whichever occurs first. (c) For Model A300 B2 and A300 B4 series airplanes: Actions accomplished before the effective date of this AD according to Airbus Service Bulletin A300-27A0197, including Appendix 01, dated August 8, 2002; are acceptable for compliance with the corresponding actions required by this AD. Inspection and Corrective Action (d) At the applicable time in paragraph (d)(1), (d)(2), (d)(3), or (d)(4) of this AD, do a detailed inspection for corrosion and damage ( e.g. , frayed or broken wires) of the pulleys and cables of the rudder, elevator, trimmable horizontal stabilizer, and rudder trim control located at the rear of the fuselage; including any applicable testing and lubrication following the inspection. If any corrosion or damage is found that is outside the limits specified in the service bulletin, prior to further flight, replace the affected cable with a new cable; including any applicable testing and lubrication following the replacement. Accomplish all the actions in accordance with the applicable service bulletin. (1) For airplanes that have accumulated, as of the effective date of this AD, less than 20,000 total flight hours and less than 10 years since the date of airworthiness certification: Inspect at the later of the times specified in paragraphs (d)(1)(i) and (d)(1)(ii) of this AD. (i) Prior to the accumulation of 20,000 total flight hours, or within 10 years since the date of airworthiness certification, whichever occurs earliest. (ii) Within 1,800 flight hours after the effective date of this AD. (2) For airplanes that have accumulated, as of the effective date of this AD, either 20,000 or more total flight hours or more than 10 years since the date of airworthiness certification, but less than 25,000 total flight hours and 13 years since the date of airworthiness certification: Inspect at the later of the times specified in paragraphs (d)(2)(i) and (d)(2)(ii) of this AD. (i) Prior to the accumulation of 25,000 total flight hours, or within 13 years since the date of airworthiness certification, whichever occurs earliest. (ii) Within 1,800 flight hours after the effective date of this AD. (3) For airplanes that have accumulated, as of the effective date of this AD, either 25,000 or more total flight hours or more than 13 years since the date of airworthiness certification, but less than 30,000 total flight hours and 16 years since the date of airworthiness certification: Inspect at the later of the times specified in paragraphs (d)(3)(i) and (d)(3)(ii) of this AD. (i) Prior to the accumulation of 30,000 total flight hours, or within 16 years since the date of airworthiness certification, whichever occurs earliest. (ii) Within 1,200 flight hours after the effective date of this AD. (4) For airplanes that have accumulated, as of the effective date of this AD, either 30,000 or more total flight hours or more than 16 years since the date of airworthiness certification: Inspect within 600 flight hours after the effective date of this AD. 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.” Reporting (e) Submit a report of the findings (both positive and negative) of the inspection required by paragraph (d) of this AD to Airbus, Customer Services Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; Attn: AI/SE-D32 Technical Data and Documentation Services, or fax: (+33) 5 61 93 28 06. Send the report at the applicable time specified in paragraph (e)(1) or (e)(2) of this AD. The Inspection Record Sheet in Appendix 01 of the applicable service bulletin may be used. Include the inspection results, a description of any discrepancy found, the airplane serial number, the number of landings and flight hours on the airplane, the service bulletin number, and the date of inspection. 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) If the inspection is done after the effective date of this AD: Submit the report within 60 days after the inspection. (2) If the inspection was done prior to the effective date of this AD: Submit the report within 60 days after the effective date of this AD. Alternative Methods of Compliance (f) 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 (g) Unless otherwise specified in this AD, the actions must be done in accordance with Airbus Service Bulletin A300-27A0197, Revision 01, including Appendix 01, dated February 26, 2003; Airbus Service Bulletin A300-27A6051, including Appendix 01, dated August 8, 2002; and Airbus Service Bulletin A310-27A2098, including Appendix 01, dated August 8, 2002; 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 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 directive 2002-608(B) R1, dated January 8, 2003. Effective Date (h) This amendment becomes effective on November 17, 2004. Issued in Renton, Washington, on September 29, 2004. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-22470 Filed 10-12-04; 8:45 am] BILLING CODE 4910-13-P