2002-11-04: Attachment Holes on Left and Right Internal Angles of Wing Center Box

2002-11-04 Airbus Industrie: Amendment 39-12765. Docket 99-NM-322-AD. Supersedes AD 97-16-06, Amendment 39-10097. Applicability: All Model A300 B4-600 and A300 B4-600R series airplanes, and all Model A300 F4-605R airplanes; certificated in any category. Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (f)(1) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.Compliance: Required as indicated, unless accomplished previously. To prevent fatigue cracking of the forward fitting of fuselage frame FR47, which could result in reduced structural integrity of the frame, accomplish the following: Inspections (a) Perform a rotating probe inspection to detect cracking of the applicable attachment holes on the left and right internal angles of the wing center box, in accordance with Airbus Service Bulletin A300-57-6049, Revision 4, dated July 27, 2000. Do the inspection at the applicable time specified by paragraph 1.A.(2), Planning Information, of the service bulletin, except as required by paragraph (e) of this AD. Repeat the inspection thereafter at intervals not to exceed the applicable interval specified in the service bulletin, except that all touch-and-go landings must be counted in determining the total number of flight cycles between consecutive inspections. (1) If no cracking is found: Prior to further flight, installnew fasteners in accordance with the service bulletin. (2) If any cracking is found: Prior to further flight, perform applicable corrective actions (including reaming, drilling, drill-stopping holes, chamfering, performing follow-on inspections, and installing new or oversize fasteners) in accordance with the service bulletin, except as required by paragraph (d) of this AD. (b) Perform a rotating probe inspection to detect cracking of the applicable attachment holes in the horizontal flange of the internal corner angle fitting of frame FR47, in accordance with Airbus Service Bulletin A300-57-6086, dated June 6, 2000. Do the inspection at the applicable time specified by the service bulletin, except as required by paragraph (e) of this AD. Repeat the inspection thereafter at intervals not to exceed the applicable interval specified in the service bulletin, except that all touch-and-go landings must be counted in determining the total number of flight cycles between consecutive inspections. (1) If no cracking is detected: Prior to further flight, install new fasteners in accordance with the service bulletin. (2) If any cracking is detected: Prior to further flight, perform applicable corrective actions (including inspecting hole T, reaming the holes, and installing oversize fasteners) in accordance with the service bulletin, except as required by paragraph (d) of this AD. Modification (c) Modify the left and right internal angle fittings of the wing center box. The modification includes performing a rotating probe inspection to detect cracking, repairing cracks, cold expanding holes, and installing medium interference fitting bolts. Perform the modification in accordance with and at the applicable time specified by paragraph 1.B.(4), Accomplishment Timescale, of Airbus Service Bulletin A300-57-6050, Revision 02, dated February 10, 2000; except as required by paragraphs (d) and (e) of this AD. Note 2: Modification prior to the effective date of this AD in accordance with Airbus Service Bulletin A300-57-6050, dated September 9, 1994, or Revision 01, dated May 31, 1999, is acceptable for compliance with the requirements of paragraph (c) of this AD. Exceptions to Specifications in Service Bulletins (d) If any crack is detected during any inspection required by paragraph (b) or (c) of this AD, and the applicable service bulletin specifies to contact the manufacturer for disposition of certain corrective actions: Prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, or the Direction Generale de l'Aviation Civile (DGAC) (or its delegated agent). (e) Where the service bulletins specified in paragraphs (a), (b), and (c) of this AD specify a grace period relative to receipt of the service bulletin, this AD requires compliance within the applicable grace period following the effective date of this AD, if the threshold has been exceeded. Alternative Methods of Compliance (f)(1) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, International Branch, ANM-116. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116. (2) Alternative methods of compliance, approved previously in accordance with AD 97-16-06, amendment 39-10097, are approved as alternative methods of compliance with the applicable requirements of this AD. Note 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. Special Flight Permits (g) Special flight permits may be issued in accordance with [sect][sect] 21.197 and 21.199 of the Federal Aviation Regulations(14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. Incorporation by Reference (h) Except as required by paragraph (d) of this AD: The actions shall be done in accordance with Airbus Service Bulletin A300-57-6049, Revision 4, dated July 27, 2000; Airbus Service Bulletin A300-57-6086, dated June 6, 2000; and Airbus Service Bulletin A300-57-6050, Revision 02, dated February 10, 2000; as applicable. Revision 02 of Airbus Service Bulletin A300-57-6050 contains the following effective pages: Page number Revision level shown on page Date shown on page 1, 4, 8, 9, 17-32, 41, 42, 57, 58, 61-63, 75, 77 02 February 10, 2000. 2, 3, 5-7, 10-12, 33, 34, 37, 38, 47, 59, 60, 76 01 May 31, 1999. 13-16, 35, 36, 39, 40, 43-46, 48-56, 64-74 Original September 9, 1994. 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 Industrie, 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 4: The subject of this AD is addressed in French airworthiness directive 2000-533-328(B), dated December 27, 2000. Effective Date (i) This amendment becomes effective on July 8, 2002.