Airworthiness Directive · Amendment 39-18462 · Wings
Airbus Airplanes
This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, all manufacturer serial numbers except those on which Airbus Modification 10160 has been done in production.
(1) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
(2) Airbus Model A300 B4-605R and B4-622R airplanes.
(3) Airbus Model A300 F4-605R and F4-622R airplanes.
(4) Airbus Model A300 C4-605R Variant F airplanes.
We are superseding Airworthiness Directive (AD) 97-20-07 for certain Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). AD 97-20-07 required repetitive inspections to detect fatigue cracking in the left and right wings in the area where the top skin attaches to the center spar, and repair or modification of this area if necessary. This new AD reduces the inspection compliance time and repetitive inspection intervals. This AD was prompted by a determination that the inspection compliance time and repetitive inspection interval must be reduced to allow timely detection of fatigue cracking in the left and right wings in the area where the top skin attaches to the center spar. We are issuing this AD to detect and correct this fatigue cracking, which could reduce the residual strength of the top skin of the wings, and consequently affect the structural integrity of the airframe.
This paragraph restates the requirements of paragraph (a) of AD 97-20-07, with revised service information. For airplanes on which Airbus Modification 10089 has not been installed: Prior to the accumulation of 18,000 total landings, or within 1,500 landings after October 30, 1997 (the effective date of AD 97-20-07), whichever occurs later, conduct either a detailed visual inspection or a high frequency eddy current (HFEC) inspection to detect fatigue cracking in the left and right wings in the area where the top skin attaches to the center spar between ribs 1 and 7, in accordance with Airbus Service Bulletin A300-57-6044, Revision 2, dated September 6, 1995, including Appendix 1, Revision 1, dated November 25, 1994; or Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. As of the effective date of this AD, use only Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. Accomplishment of the inspection required by paragraph (i) of this AD terminates the inspection requirements of this paragraph.
(1) If no cracking is detected, conduct repetitive inspections thereafter at the following intervals:
(i) If the immediately preceding inspection was conducted using detailed visual inspection techniques, conduct the next inspection within 5,000 landings.
(ii) If the immediately preceding inspection was conducted using HFEC techniques, conduct the next inspection within 9,500 landings.
(2) If any cracking is detected or suspected during any detailed visual inspection required by the introductory text of paragraph (g), paragraph (g)(1), or paragraph (g)(3)(i) of this AD, prior to further flight, confirm this finding and the length of this cracking by conducting an HFEC inspection, in accordance with Airbus Service Bulletin A300-57-6044, Revision 2, dated September 6, 1995, including Appendix 1, Revision 1, dated November 25, 1994; or Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. As of the effective date of this AD, use only Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. If no cracking is confirmed during the HFEC inspection, accomplish the repetitive inspection required by paragraph (g)(1)(ii) of this AD at the time specified in that paragraph.
(3) If any cracking is detected or confirmed during any HFEC inspection required by the introductory text of paragraph (g), paragraph (g)(1), or paragraph (g)(2) of this AD:
(i) If the cracking is 75 millimeters (mm) or less per rib bay, prior to further flight, repair in accordance with Airbus Service Bulletin A300-57-6044, Revision 2, dated September 6, 1995, including Appendix 1, Revision 1, dated November 25, 1994; or Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. As of the effective date of this AD, use only Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. Thereafter, conduct repetitive detailed visual inspections of the repaired area at intervals not to exceed 50 landings, in accordance with Airbus Service Bulletin A300-57-6044, Revision 2, dated September 6, 1995, including Appendix 1, Revision 1, dated November 25, 1994; or Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. As of the effective date of this AD, use only Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011.
(ii) If the cracking exceeds 75 mm per rib bay, prior to further flight, install Airbus Modification 10089, in accordance with Airbus Service Bulletin A300-57-6044, Revision 2, dated September 6, 1995, including Appendix 1, Revision 1, dated November 25, 1994; or Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. As of the effective date of this AD, use only Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. Thereafter, conduct a low frequency eddy current (LFEC) inspection in accordance with the requirements of paragraph (h) of this AD.
Note 1 to paragraph (g) of this AD: Airbus Service Bulletin A300-57-6044, Revision 2, dated September 6, 1995, including Appendix 1, Revision 1, dated November 25, 1994, references Airbus Service Bulletin A300-57-6041, Revision 4, dated November 16, 1995, as an additional source of guidance for installing Airbus Modification 10089.
This paragraph restates the requirements of paragraph (b) of AD 97-20-07, with revised service information and repair instructions. For airplanes on which Airbus Modification 10089 has been installed: Prior to the accumulation of 22,000 total landings after this modification has been installed, or within 1,500 landings after October 30, 1997 (the effective date of AD 97-20-07), whichever occurs later, conduct a LFEC inspection to detect fatigue cracking in the inboard and rear edges of the top skin reinforcing plates, in accordance with Airbus Service Bulletin A300-57-6044, Revision 2, dated September 6, 1995, including Appendix 1, Revision 1, dated November 25, 1994; or Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. As of the effective date of this AD, use only Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. Accomplishment of the inspection required by paragraph (k) of this AD terminates the inspection requirements of this paragraph.
(1) If no cracking is detected, repeat this inspection thereafter at intervals not to exceed 11,000 landings.
(2) If any cracking is detected, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, Transport Airplane Directorate, FAA. As of the effective date of this AD, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). Thereafter, repeat this inspection at intervals not to exceed 11,000 landings.
For airplanes on which Airbus Modification 10089 has not been installed: At the applicable time specified in paragraphs (i)(1) and (i)(2) of this AD, do either a detailed visual inspection or an HFEC inspection to detect fatigue cracking in the left and right wings in the area where the top skin attaches to the center spar between ribs 1 and 7, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. Accomplishment of the inspection required by this paragraph terminates the inspection requirements of paragraph (g) of this AD.
(1) For airplanes whose flight time average is equal to or more than 1.5 hours, at the later of the times specified in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD.
(i) Before the accumulation of 14,000 total flight cycles or 30,300 total flight hours, whichever occurs first.
(ii) Within 1,500 flight cycles or 3,200 flight hours after the effective date of this AD, whichever occurs first.
(2) For airplanes whose flight time average is less than 1.5 hours, at the later of the times specified in paragraphs (i)(2)(i) and (i)(2)(ii) of this AD.
(i) Before the accumulation of 15,100 total flight cycles or 22,700 total flight hours, whichever occurs first.
(ii) Within 1,600 flight cycles or 2,500 flight hours after the effective date of this AD, whichever occurs first.
Repeat the inspections specified in paragraph (i) of this AD thereafter at the applicable interval specified in paragraphs (j)(1) and (j)(2) of this AD.
(1) For airplanes whose flight time average is equal to or more than 1.5 hours, at the applicable interval specified in paragraphs (j)(1)(i) and (j)(1)(ii) of this AD.
(i) For a detailed visual inspection, at intervals not to exceed 3,900 flight cycles or 8,400 flight hours, whichever occurs first.
(ii) For an HFEC inspection, at intervals not to exceed 7,400 flight cycles or 16,000 flight hours, whichever occurs first.
(2) For airplanes whose flight time average is less than 1.5 hours, at the applicable interval specified in paragraphs (j)(2)(i) and (j)(2)(ii) of this AD.
(i) For a detailed visual inspection, at intervals not to exceed 4,200 flight cycles or 6,300 flight hours, whichever occurs first.
(ii) For an HFEC inspection, at intervals not to exceed 8,000 flight cycles or 11,900 flight hours, whichever occurs first.
For airplanes on which Airbus Modification 10089 has been installed: At the applicable time specified in paragraphs (k)(1) and (k)(2) of this AD, do an LFEC inspection to detect fatigue cracking in the inboard and rear edges of the top skin reinforcing plates, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. Accomplishment of the inspection required by this paragraph terminates the inspection requirements of paragraph (h) of this AD.
(1) For airplanes whose flight time average is equal to or more than 1.5 hours, at the later of the times specified in paragraphs (k)(1)(i) and (k)(1)(ii) of this AD.
(i) Before the accumulation of 17,000 total flight cycles or 37,100 total flight hours, whichever occurs first.
(ii) Within 1,500 flight cycles or 3,200 flight hours after the effective date of this AD, whichever occurs first.
(2) For airplanes whose flight time average is less than 1.5 hours, at the later of the times specified in paragraphs (k)(2)(i) and (k)(2)(ii) of this AD.
(i) Before the accumulation of 18,500 total flight cycles or 27,800 total flight hours, whichever occurs first.
(ii) Within 1,600 flight cycles or 2,500 flight hours after the effective date of this AD, whichever occurs first.
Repeat the inspection specified in paragraph (k) of this AD thereafter at the applicable interval specified in paragraphs (l)(1) and (l)(2) of this AD.
(1) For airplanes whose flight time average is equal to or more than 1.5 hours, at intervals not to exceed 8,500 flight cycles or 18,500 flight hours, whichever occurs first.
(2) For airplanes whose flight time average is less than 1.5 hours, at intervals not to exceed 9,200 flight cycles or 13,700 flight hours, whichever occurs first.
(1) If any cracking is detected or suspected during any detailed inspection required by paragraph (i) or (j) of this AD: Before further flight, confirm this finding and the length of this cracking by conducting an HFEC inspection, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011, except as specified in paragraph (o) of this AD. If no cracking is confirmed during the HFEC inspection, accomplish the applicable repetitive inspections required by paragraphs (j) and (l) of this AD at the applicable time specified in those paragraphs.
(2) If any cracking is found during any HFEC inspection required by paragraph (i), (j), or (m)(1) of this AD: Before further flight, do the applicable actions specified in paragraphs (m)(2)(i) and (m)(2)(ii) of this AD.
(i) If the cracking is 75 mm or less per each rib bay: Before further flight, repair the cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011, except as specified in paragraph (o) of this AD. Do repetitive detailed inspections of the repaired area thereafter at intervals not to exceed 50 flight cycles or 110 flight hours, whichever occurs first, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. Within 250 flight cycles or 550 flight hours, whichever occurs first after doing the temporary repair, do a permanent repair of the repaired area, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011.
(ii) If the cracking exceeds 75 mm per any rib bay: Before further flight, install Airbus Modification 10089, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. Do an LFEC inspection thereafter at the intervals specified in paragraph (l) of this AD.
(3) If any cracking is found during any inspection required by this AD at fastener hole 1A, 1, or 2: Before further flight, repair the cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011.
(4) If any cracking is found during any LFEC inspection required by paragraph (k) or (l) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
