AD 2006-13-04 Airworthiness Directives; Airbus Model A300 B2 and A300 B4 Series Airplanes; and Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes)

Models named: A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, B4-203, B4-601, B4-603, B4-605R. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, B4-203, B4-601, B4-603, B4-605R, B4-620, B4-622, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes; certificated in any category; except those on which Airbus Modification 13031 or 19575 was accomplished 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. Inspections (f) Do a detailed inspection, using a borescope or endoscope, for cracking of the vertical stiffeners, and of the horizontal flanges between the stiffeners, of nose rib 7 of the inner flap of the left- and right-hand wings; and do an eddy current inspection to detect cracking in the horizontal flanges of the attachment lug root of nose rib 7 of the inner flap of the left- and right-hand wings; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-0240 or A300-57-6095, both Revision 01, both dated December 2, 2004, as applicable. Do the initial inspections at the applicable compliance time specified in paragraph (f)(1) or (f)(2) of this AD. Note 1: For the purposes of this AD, a detailed inspection is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.” (1) For airplanes on which nose rib 7 has not been replaced in accordance with Airbus Service Bulletin A300-57-0242 or A300-57-6097, both dated December 18, 2003: Do the initial inspections at the applicable time specified in paragraph (f)(1)(i) or (f)(1)(ii) of this AD. (i) For airplanes with 18,599 or fewer total flight cycles as of the effective date of this AD: Prior to the accumulation of 5,000 total flight cycles, or within 1,000 flight cycles after the effective date of this AD, whichever is later. (ii) For airplanes with 18,600 or more total flight cycles as of the effective date of this AD: Within 500 flight cycles after the effective date of this AD. (2) For airplanes on which nose rib 7 has been replaced in accordance with Airbus Service Bulletin A300-57-0242 or A300-57-6097, both dated December 18, 2003: Do the initial inspection within 5,000 flight cycles after accomplishing the replacement, or within 1,000 flight cycles after the effective date of this AD, whichever is later. No Crack Found: Repetitive Inspections (g) If no crack is found during the inspection required by paragraph (f) of this AD: Repeat the inspection at intervals not to exceed 1,000 flight cycles, until the terminating action in paragraph (i) of this AD is completed. Crack Found: Related Investigative/Corrective Actions (h) If any crack is found during any inspection required by paragraph (f) or (g) of this AD: Before further flight, replace nose rib 7 with a new, improved rib and do all related investigative actions and applicable corrective actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-0245, Revision 01; or A300-57-6100, Revision 01; both dated March 9, 2006; as applicable; except as provided by paragraph (j) of this AD. This terminates the repetitive inspections required by paragraph (g) of this AD for the modified flaps only. Terminating Action (i) Within 5,000 flight cycles or 36 months after the effective date of this AD, whichever is first: Replace nose rib 7 with a new, improved rib and do all related investigative actions and applicable corrective actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-0245, Revision 01; or A300-57-6100, Revision 01; both dated March 9, 2006; as applicable; except as provided by paragraph (j) of this AD. This terminates the repetitive inspections required by paragraph (g) of this AD. Repairing Per the FAA or Direction Générale de l'Aviation Civile (DGAC) (j) If any crack or damage is found for which the applicable service bulletin specifies to contact Airbus: Before further flight, repair per a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the DGAC (or its delegated agent). No Reporting Required (k) Airbus Service Bulletins A300-57-0240 and A300-57-6095, both Revision 01, both dated December 2, 2004, specify to submit certain information to the manufacturer, but this AD does not include that requirement. Actions Accomplished in Accordance With Initial Issue of Service Bulletins (l) Actions done before the effective date of this AD in accordance with Airbus Service Bulletin A300-57-0245 or A300-57-6100, both dated August 31, 2005, are acceptable for compliance with the requirements of paragraphs (h) and (i) of this AD. Alternative Methods of Compliance (AMOCs) (m)(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 14 CFR 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 (n) French airworthiness directive F-2005-198, dated December 7, 2005, also addresses the subject of this AD. Material Incorporated by Reference (o) You must use the applicable service information identified in Table 1 of this AD 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 Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 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. Table 1.—Material Incorporated by Reference Airbus Service Bulletin Revision level Date A300-57-0240 01 December 2, 2004. A300-57-0245 01 March 9, 2006. A300-57-6095 01 December 2, 2004. A300-57-6100 01 March 9, 2006. Issued in Renton, Washington, on June 14, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06-5530 Filed 6-20-06; 8:45 am] BILLING CODE 4910-13-P

This AD was prompted by reports of cracking in the web of nose rib 7 of the inner flap. We are issuing this AD to prevent cracking in the web of nose rib 7, which could result in rupture of the attachment fitting between the inner flap and flap track 2, and consequent reduced structural integrity of the flap.