Airworthiness Directive · Amendment 39-18741 · Fuselage
Airbus Airplanes
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.
We are superseding Airworthiness Directive (AD) 2011-17-05, for certain Airbus Model A300 B2-1C, A300 B2-203, A300 B2K-3C, A300-B4- 103, A300 B4-203, and A300 B4-2C airplanes. AD 2011-17-05 required repetitive inspections in sections 13 through 18 of the fuselage between rivets of the longitudinal lap joints between frames (FRs) 18 and 80 for cracking, and repair or modification if necessary. This new AD requires a revised repetitive inspection program of all longitudinal lap joints and repairs between FRs 18 and 80 to address widespread fatigue damage (WFD). 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 WFD; therefore, a revised inspection program is necessary. We are issuing this AD to address the unsafe condition on these products.
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.
This paragraph restates the repetitive intervals specified in table 1 of AD 2011-17-05, with no changes. At the applicable time specified in paragraph (h)(1) or (h)(2) of this AD, repeat the inspection required by paragraph (g) of this AD.
(1) For sections 13 and 14 as specified in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997: Repeat the inspection at intervals not to exceed 7 years or 12,000 flight cycles, whichever occurs first.
(2) For sections 15 through 18 as specified in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997: Repeat the inspection within 8.5 years or 12,000 flight cycles, whichever occurs first.
This paragraph restates the requirements of paragraph (m) of AD 2011-17-05, with no changes. 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 been done as of November 16, 2011 (the effective date of AD 2011-17-05), as specified in Airbus Service Bulletin A300-53-229; except for airplanes on which a repair of that area has been done as specified in Airbus Service Bulletin A300-53-229: Within 7 years or 12,000 flight cycles (for sections 13 and 14), or within 8.5 years or 12,000 flight cycles (for sections 15 and 18), after doing the inspection, 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 at the applicable time 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.
This paragraph restates the requirements of paragraph (n) of AD 2011-17-05, with no changes. For airplanes on which any inspections of the fuselage bonded inner doublers of the longitudinal lap joints in 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 in Airbus Service Bulletin A300-53-229: Prior to the accumulation of 24,000 total flight cycles or within 12 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 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 intervals not to exceed 7 years or 12,000 flight cycles, whichever occurs first.
(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. Doing a repair in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, terminates the repetitive inspections required by this paragraph for that area.
(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.
This paragraph restates the requirements of paragraph (o) of AD 2011-17-05, with no changes. For airplanes on which any inspections of the fuselage bonded inner doublers of the longitudinal lap joints in sections 16 and 17 at stringer 31 left-hand and right-hand for disbonding and cracking have been done as of November 16, 2011, as specified in Airbus Service Bulletin A300-53-229; except airplanes on which a repair of that area has been done as specified in Airbus Service Bulletin A300-53-229: Within 7 years or 12,000 flight cycles after doing the inspection, 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 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 corrosion are found, repeat the inspection thereafter at intervals not to exceed 7 years or 12,000 flight cycles, whichever occurs first.
(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. Doing a repair, in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, terminates the repetitive inspections required by this paragraph for that area.
(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.
Within 180 days after the effective date of this AD, do rototest and ultrasonic inspections, as applicable, for cracking of all longitudinal lap joints and repairs between frames 18 and 80; and repair any cracking before further flight; 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). Repeat the applicable inspection, including post-repair inspections, thereafter at intervals approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. Accomplishing the initial inspection and applicable repairs required by this paragraph terminates the actions required by paragraphs (g) through (k) of this AD.
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.
