AD 2004-23-20 Airworthiness Directives; Airbus Model A300 B2, A300 B4, A300 B4-600, and A300 B4-600R Series Airplanes; and Model A300 C4-605R Variant F and A300 F4-605R Airplanes

Models named: A300 B2, A300 B4, A300 B4-600, A300 B4-600R series, A300 C4-605R Variant F, A300 F4-605R. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to all Airbus Model A300 B2, A300 B4, A300 B4-600, and A300 B4-600R series airplanes; and all Airbus Model A300 C4-605R Variant F and A300 F4-605R airplanes; certificated in any category; except those airplanes modified by Airbus Modification 12168.

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 2001-06-10 Inspections (f) For Model A300 B4-600 and A300 B4-600R series airplanes, and Model A300 C4-605R Variant F and A300 F4-605R airplanes: Perform a high-frequency eddy-current or rototest inspection to detect cracking in the area surrounding the frame feet attachment holes between fuselage frames (FR) 41 and FR46 from stringers 24 to 28, left- and right-hand sides, in accordance with Airbus Service Bulletin A300-53-6122, dated February 9, 2000, at the time specified in paragraph (f)(1) or (f)(2), as applicable. (1) For airplanes on which Task 53-15-54 in Maintenance Review Board Document (MRBD), Revision 3, dated April 1998, has not been accomplished as of May 7, 2001 (the effective date of AD 2001-06-10): Perform the inspection at the later of the times specified in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD. (i) Prior to the accumulation of the total flight-cycle or flight-hour threshold, whichever occurs first, specified in paragraph 1.E. (“Compliance”) of the service bulletin; or (ii) Within the applicable grace period specified in paragraph 1.E. (“Compliance”) of the service bulletin. (2) For airplanes on which Task 53-15-54 in the MRBD, Revision 3, dated April 1998, has been accomplished as of May 7, 2001: Perform the next repetitive inspection at the later of the times specified in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD. (i) Within the flight-cycle or flight-hour interval, whichever occurs first, specified in paragraph 1.E. (“Compliance”) of the service bulletin, following the latest inspection accomplished in accordance with the MRBD; or (ii) Within the grace period specified in paragraph 1.E. (“Compliance”) of the service bulletin. (g) For airplanes on which no cracking is detected during the inspection required by paragraph (f) of this AD, prior to further flight, install new fasteners as applicable, in accordance with Airbus Service Bulletin A300-53-6122, dated February 9, 2000; and repeat the inspection required by paragraph (f) of this AD thereafter at intervals not to exceed the applicable intervals specified in paragraph 1.E. (“Compliance”) of the service bulletin, until the actions required by paragraph (i) of this AD have been done. Corrective Actions (h) For airplanes on which cracking is detected during any inspection required by paragraph (f) of this AD: Prior to further flight, except as required by paragraph (j) of this AD, accomplish corrective actions ( e.g. , performing rotating probe inspections, reaming out cracks, cold working fastener holes, and installing oversized fasteners) in accordance with Airbus Service Bulletin A300-53-6122, dated February 9, 2000. Repeat the inspection required by paragraph (f) of this AD thereafter at intervals not to exceed the applicable intervals specified in paragraph 1.E. (“Compliance”) of the service bulletin, until the actions required by paragraph (i) of this AD have been done. New Requirements of This AD Modification: All Airplanes (i) For all airplanes: Within the compliance times specified in paragraph 1.E. of the applicable service bulletin listed in Table 1 of this AD, modify the fuselage frames in accordance with the Accomplishment Instructions of the applicable service bulletin. For airplanes that have exceeded their design service goal, as specified in NOTE (01) of paragraph 1.E. of the service bulletin, this AD requires compliance within the earlier of the flight-cycle and flight-hour grace periods specified in the service bulletin. Table 1.—Service Information Airplane model Airbus service bulletin Required revision level Revision level(s) also acceptable for compliance if done before the effective date of this AD A300 B2 and A300 B4 series airplanes A300-53-0271 Revision 03, dated June 13, 2003 Original, dated September 10, 1991. Revision 01, dated February 16, 1993. Revision 02, dated July 13, 2000. A300 B4-600 and A300 B4-600R series airplanes, and A300 C4-605 Variant F and A300 F4-605R airplanes A300-53-6125 Revision 01, dated June 13, 2003 Original, dated November 8, 2000. (1) For the affected Model A300 B4-600 series airplanes: Accomplishment of the modification terminates the requirements of this AD. (2) For Model A300 B2 and A300 B4 series airplanes: Accomplishment of the modification terminates certain repetitive inspections required by AD 96-13-11, i.e., inspections of the frame feet holes for frames 41 to 46 (as specified in Airbus Service Bulletin A300-53-0345) and frames 48 to 54 (as specified in Airbus Service Bulletin A300-53-238). However, the repetitive inspections of the frame foot angle radius (as specified in Service Bulletin A300-53-238), which are required by AD 96-13-11, must continue. Exceptions to Service Bulletin Procedures (j) During any inspection required by this AD, if the applicable service bulletin specifies to contact the manufacturer for appropriate instructions: Before further flight, perform applicable corrective action in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Direction Generale de l'Aviation Civile (DGAC) (or its delegated agent). Alternative Methods of

This AD was prompted by the development of a modification intended to prevent cracking of the center section of the fuselage, which could result in a ruptured frame foot and reduced structural integrity of the airplane.