Airworthiness directives › 2016-25-15
AD 2016-25-15 Airworthiness Directives; Airbus Airplanes
Models named: A300 B2-1C, A300 B2-203, A300 B2K-3C, A300-B4-103, A300 B4-203, A300 B4-2C. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to Airbus Model A300 B2-1C, A300 B2-203, A300 B2K-3C, A300-B4-103, A300 B4-203, and A300 B4-2C airplanes; certificated in any category; all manufacturer serial numbers, except those on which Airbus Modification 2611 has been embodied in production.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
This paragraph restates the requirements of paragraph (l) of AD 2011-17-05, with revised formatting. For airplanes on which any inspections of the fuselage bonded inner doublers of the longitudinal lap joints in sections 13 through 18 (except sections 16 and 17 at stringer 31 left-hand and right-hand) for disbonding and cracking have not been done as of November 16, 2011 (the effective date of AD 2011-17-05), as specified by Airbus Service Bulletin A300-53-229: Prior to the accumulation of 24,000 total flight cycles or within 15 years since new, whichever occurs first; or within 60 days after November 16, 2011; whichever occurs later; do a detailed inspection of the fuselage bonded inner doublers of the longitudinal lap joints in sections 13 through 18 (except sections 16 and 17 at stringer 31 left-hand and right-hand) for disbonding and cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. If no disbonding and no cracking are found, repeat the inspection thereafter at the applicable intervals specified in paragraph (h) of this AD. (1) If no cracking is found, and “minor” disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Repeat the inspection thereafter at intervals not to exceed 1 year for areas below stringer 22, and at intervals not to exceed 2 years for areas above and including stringer 22. (2) If no cracking is found, and “major” disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Within 1,000 flight cycles after doing the inspection, repair, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. (3) If any cracking is found, repair prior to further flight, in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997.
Unsafe condition
This AD was prompted by an evaluation done by the design approval holder indicating that certain sections of the longitudinal lap joints are subject to widespread fatigue damage. We are issuing this AD to detect and correct fatigue cracking of the longitudinal lap joints of the fuselage, which could result in reduced structural integrity of the airplane.
Affected ADs
This AD replaces AD 2011-17-05, Amendment 39-16769 (76 FR 63177, October 12, 2011) (“AD 2011-17-05”).
Read the original on the Federal Register →
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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