Airworthiness directives › 2016-07-17
AD 2016-07-17 Airworthiness Directives; Airbus Airplanes
Models named: A300 B4-601, B4-603, B4-620, B4-622, A300 B4-605R, B4-622R, A300 F4-605R, F4-622R, A300 C4-605R Variant F. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
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.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
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.
Unsafe condition
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.
Affected ADs
This AD replaces AD 97-20-07, Amendment 39-10145 (62 FR 50251, September 25, 1997) (“AD 97-20-07”).
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1