AD 2007-07-15 Airworthiness Directives; Airbus Model A300 B4-601, A300 B4-603, A300 B4-605R, A300 C4-605R Variant F, A310-204, and A310-304 Airplanes Equipped With General Electric CF6-80C2 Engines

Models named: A300 B4-601, A300 B4-603, A300 B4-605R, A300 C4-605R Variant F, A310-204, A310-304. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Airbus Model A300 B4-601, A300 B4-603, A300 B4-605R, A300 C4-605R Variant F, A310-204, and A310-304 airplanes; certificated in any category; equipped with General Electric CF6-80C2 engines without full-authority digital electronic control (FADEC); excluding airplanes on which Airbus Modification 13184 was done in production.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Restatement of Certain Requirements of AD 2004-09-01 All Operators Telex Reference (f) The term “All Operators Telex,” or “AOT,” as used in paragraphs (g), (h), and (j) of this AD, means the following AOTs, as applicable: (1) For Model A300 B4-601, A300 B4-603, A300 B4-605R, and A300 C4-605R Variant F airplanes: Airbus AOT A300-54A6037, dated February 19, 2004; and (2) For Model A310-204, and A310-304 airplanes: Airbus AOT A310-54A2038, dated February 19, 2004. Inspection (g) At the applicable time in paragraph (g)(1) or (g)(2) of this AD, do a one-time detailed inspection for discrepancies of the IDG harness, harness bracket, retaining fasteners, and pyramid arm, in accordance with the applicable AOT. (1) For airplanes on which Airbus Modification 07591 has not been incorporated as of May 13, 2004 (the effective date of AD 2004-09-01): Within 10 days after May 13, 2004. (2) For airplanes on which Airbus Modification 07591 has been incorporated as of May 13, 2004: Within 600 flight hours after May 13, 2004. 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.” Related Investigative and Corrective Actions for Damaged Electrical Harness (h) If any discrepancy in the IDG electrical harness, fretting at the convoluted conduits, or contact between the IDG electrical harness and the pyramid arms is found during the inspection required by paragraph (g) of this AD: Before further flight, do the applicable related investigative actions and corrective actions in accordance with the applicable AOT. Corrective Action for Damaged Electrical Harness Bracket, Retaining Fasteners, or Pyramid Arm (i) If any discrepancy in the electrical harness bracket, retaining fasteners, or pyramid arm is found during the inspection required by paragraph (g) of this AD: Before further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; the Direction Générale de l'Aviation Civile (DGAC) (or its delegated agent); or the European Aviation Safety Agency (EASA) (or its delegated agent). After the effective date of this AD, repair in accordance with a method approved by the FAA or the EASA. No Reporting Requirement for Paragraph (g) of this AD (j) Although the referenced AOTs describe procedures for submitting certain information to the manufacturer, no report is required for the inspection required by paragraph (g) of this AD. New Requirements of this AD Repetitive Inspections (k) Within 6 months after the effective date of this AD, and thereafter at intervals not to exceed 12 months: Do a detailed inspection for damage of the IDG harness and the pylon pyramid arms, and protect the harness. Do the actions in accordance with Airbus Service Bulletin A300-24-6097, dated March 3, 2006 (for Model A300 B4-601, A300 B4-603, A300 B4-605R, and A300 C4-605R Variant F airplanes); or A310-24-2100, dated March 3, 2006 (for Model A310-204, and A310-304 airplanes). The initial inspection terminates the requirements of paragraph (g) of this AD. If any discrepancy is found: Before further flight, repair in accordance with the applicable service bulletin; except, where the service bulletin specifies to contact the manufacturer for repair instructions, this AD requires repair using a method approved by either the Manager, International Branch, ANM-116; or the EASA (or its delegated agent). Report (l) At the applicable times specified in paragraphs (l)(1) and (l)(2) of this AD, submit a report of the findings (both positive and negative) of each inspection required by paragraph (k) of this AD. Send the report to Airbus Customer Services Directorate, Department AI/SE-E43, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. The report must include the information specified in Appendix 01 of Airbus Service Bulletin A300-24-6097 or A310-24-2100, both dated March 3, 2006, as applicable. Under the provisions of the Paperwork Reduction Act (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 each inspection done after the effective date of this AD: Send the report within 30 days after the inspection. (2) If an inspection was done before the effective date of this AD: Send the report within 30 days after the effective date of this AD. Optional Terminating Action (m) Replacement of the bracket feeder on the pylons terminates the requirements of this AD if the bracket feeder is replaced in accordance with Airbus Service Bulletin A300-54-6038, dated May 12, 2006 (for Model A300 B4-601, A300 B4-603, A300 B4-605R, and A300 C4-605R Variant F airplanes); or A310-54-2039, dated May 12, 2006 (for Model A310-204, and A310-304 airplanes); as applicable. Alternative Methods of Compliance (AMOCs) (n)(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 § 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 (o) EASA airworthiness directive 2006-0155, dated June 1, 2006, also addresses the subject of this AD. Material Incorporated by Reference (p) You must use the service information identified in Table 1 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. Table 1.—Required Material Incorporated by Reference Airbus Service information Date All Operators Telex A300-54A6037 February 19, 2004. All Operators Telex A310-54A2038 February 19, 2004. Service Bulletin A300-24-6097, including Appendix 01 March 3, 2006. Service Bulletin A310-24-2100, including Appendix 01 March 3, 2006. You must use the service information identified in Table 2 of this AD to perform the optional terminating action, if accomplished, unless the AD specifies otherwise. Table 2.—Optional Material Incorporated by Reference Airbus Service information Date Service Bulletin A300-54-6038 May 12, 2006. Service Bulletin A310-54-2039 May 12, 2006. (1) The Director of the Federal Register approved the incorporation by reference of the service information identified in Table 3 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Table 3.—New Material Incorporated by Reference Airbus Service Bulletin Date A300-24-6097, including Appendix 01 March 3, 2006. A300-54-6038 May 12, 2006. A310-24-2100, including Appendix 01 March 3, 2006. A310-54-2039 May 12, 2006. (2) On May 13, 2004 (69 FR 23090, April 28, 2004), the Director of the Federal Register approved the incorporation by reference of Airbus All Operators Telex A310-54A2038, dated February 19, 2004; and Airbus All Operators Telex A300-54A6037, dated February 19, 2004. (3) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may review copies 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/cfr/ibr-locations.html. Issued in Renton, Washington, on March 28, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-6450 Filed 4-6-07; 8:45 am] BILLING CODE 4910-13-P

This AD results from a report of structural damage on the forward pyramid arm of an engine pylon due to chafing of the integrated drive generator (IDG) electrical harness against the structure of the pyramid arm. We are issuing this AD to prevent electrical arcing in the engine pylon, which could result in loss of the relevant alternating current (AC) bus bar, reduced structural integrity of the engine pylon, and possible loss of control of the airplane.