Airworthiness directives › 2016-01-10
AD 2016-01-10 Airworthiness Directives; Airbus Airplanes
Models named: A300 B4-2C, B4-103, B4-203, A300 B4-601, B4-603, B4-620, B4-622, A300 B4-605R, B4-622R, A300 F4-605R. 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)(5) of this AD, certificated in any category, all manufacturer serial numbers. (1) Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes. (2) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes. (3) Airbus Model A300 B4-605R and B4-622R airplanes. (4) Airbus Model A300 F4-605R and F4-622R airplanes. (5) 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 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004), with new service information. For airplanes defined in Airbus Service Bulletin A300-53-0350, Revision 02, dated November 12, 2002: Do a high frequency eddy current (HFEC) inspection to detect cracking of the splice fitting at fuselage FR 47 between stringers 24 and 26 (left- and right-hand sides), at the applicable times specified in paragraph (g)(1) or (g)(2) of this AD. Repeat the inspection thereafter at the earlier of the flight-cycle/flight-hour intervals specified in the applicable column in Table 2 of Figure 1 and Sheet 1 of the Accomplishment Instructions of Airbus Service Bulletin A300-53-0350, Revision 02, excluding Appendix 01, dated November 12, 2002. Do the inspections in accordance with Airbus Service Bulletin A300-53-0350, Revision 02, excluding Appendix 01, dated November 12, 2002; or Revision 03, excluding Appendix 01, dated July 26, 2007. As of the effective date of this AD, use only Airbus Service Bulletin A300-53-0350, Revision 03, excluding Appendix 01, dated July 26, 2007. (1) For airplanes that have accumulated 20,000 or more total flight cycles as of November 17, 2004 (the effective date of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)): Do the initial inspection at the later of the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD. (i) At the earlier of the flight-cycle/flight-hour intervals after November 17, 2004 (the effective date of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)), as specified in the applicable column in Table 1 of Figure 1 and Sheet 1 of the Accomplishment Instructions of Airbus Service Bulletin A300-53-0350, Revision 02, excluding Appendix 01, dated November 12, 2002. (ii) Within 750 flight cycles or 1,500 flight hours after November 17, 2004 (the effective date of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)), whichever is first. (2) For airplanes that have accumulated fewer than 20,000 total flight cycles as of November 17, 2004 (the effective date of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)): Do the initial inspection at the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD. (i) At the earlier of the flight-cycle/flight-hour intervals after November 17, 2004 (the effective date of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)), as specified in the applicable column in Table 1 of Figure 1 and Sheet 1 of the Accomplishment Instructions of Airbus Service Bulletin A300-53-0350, Revision 02, excluding Appendix 01, dated November 12, 2002. (ii) Within 1,800 flight cycles or 3,000 flight hours after November 17, 2004 (the effective date of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)), whichever is first.
Unsafe condition
This AD was prompted by a determination that the inspection compliance time and repetitive inspection interval specified in AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004), must be reduced to allow timely detection of cracks in the splice fitting at fuselage frame (FR) 47. We are issuing this AD to detect and correct cracking of the splice fitting at fuselage FR 47; such cracking could result in reduced structural integrity of the airplane.
Affected ADs
This AD replaces AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004).
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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