Airworthiness Directive · Amendment 39-21302 · Fuselage
Airbus SAS Airplanes
This AD applies to Airbus SAS Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; and Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes, certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2020-0040R1, dated June 16, 2020 (“EASA AD 2020-0040R1”).
The FAA is superseding Airworthiness Directive (AD) 99-01-19 and AD 2004-25-02, which applied to certain Airbus SAS Model A320 series airplanes. AD 99-01-19 and AD 2004-25-02 required repetitive inspections to detect fatigue cracking in certain areas of the fuselage, and corrective action if necessary. AD 2004-25-02 also provided an optional terminating action for the repetitive inspections. This AD continues to require, for certain airplanes, repetitive inspections of the fastener holes for any cracking, and repair if necessary, and provides an optional terminating action for the fastener hole inspections. This AD also revises the applicability to include additional airplanes and requires, for all airplanes, inspections of the emergency exit door structure for any cracking and repair if necessary; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a report that during full scale tests to support the Model A320 structure extended service goal (ESG) exercise, several cracks were found on both sides of the overwing emergency exit door cut-outs at fuselage section 15. The FAA is issuing this AD to address the unsafe condition on these products.
For Airbus SAS Model A320-111, -211, -212, and -231 series airplanes on which Airbus Modification 21346 has not been done: This paragraph restates the requirements of paragraph (f) of AD 2004-25-02, with no changes. At the applicable time specified in paragraph (g)(1) or (2) of this AD: Do a detailed inspection to find cracking on the outboard flanges around the fastener holes of frames 38 through 41, between stringers 12 and 21, using Airbus Service Bulletin A320-53-1032, Revision 02, dated December 5, 2001.
(1) For airplanes on which the inspection specified in Airbus Service Bulletin A320-53-1032, Revision 01, dated January 15, 1998; or Airbus Service Bulletin A320-53-1032, Revision 02, dated December 5, 2001; has been done as of February 10, 2005 (the effective date of AD 2004-25-02): Do the next inspection within 4,900 flight cycles after accomplishment of the last inspection, or within 1,100 flight cycles after February 10, 2005, whichever is later.
(2) For airplanes on which no inspection specified in Airbus Service Bulletin A320-53-1032, Revision 01, dated January 15, 1998; or Airbus Service Bulletin A320-53-1032, Revision 02, dated December 5, 2001; has been done as of February 10, 2005 (the effective date of AD 2004-25-02): Do the inspection at the earlier of the times specified in paragraphs (g)(2)(i) and (ii) of this AD.
(i) Before the accumulation of 30,000 total flight cycles.
(ii) Before the accumulation of 24,800 total flight cycles, or within 3,500 flight cycles after February 10, 2005 (the effective date of AD 2004-25-02), whichever is later.
This paragraph restates the requirements of paragraph (g) of AD 2004-25-02, with no changes. If no crack is found during the inspection required by paragraph (g)(1) or (2) of this AD: Repeat the inspection thereafter at intervals not to exceed 4,900 flight cycles.
This paragraph restates the requirements of paragraph (h) of AD 2004-25-02, with new repetitive inspections and compliance language. If any crack is found during any inspection required by paragraph (g) of this AD, before further flight, repair using Airbus Service Bulletin A320-53-1032, Revision 01, dated January 15, 1998; or Airbus Service Bulletin A320-53-1032, Revision 02, dated December 5, 2001. Accomplishment of a repair using the service bulletin before the effective date of this AD ends the repetitive inspection requirements for the area repaired. As of the effective date of this AD, the repair does not constitute terminating action for the repetitive inspection. Thereafter, repeat the inspection at intervals not to exceed 4,900 flight cycles. If any crack is found during any inspection required by this AD, and the service bulletin specifies to contact Airbus for appropriate action: Before further flight, repair using a method approved by the Manager, Large Aircraft Section, International Validation Branch, FAA; or EASA; or Airbus SAS's EASA Design Organization Approval (DOA).
This paragraph restates the optional terminating action specified in paragraphs (i) and (j) of AD 2004-25-02, with changes to the service information compliance language. Accomplishment of Airbus Modification 21346 using Airbus Service Bulletin A320-53-1031, Revision 02, dated December 5, 2001, constitutes terminating action for the repetitive inspection requirements of paragraphs (h) and (i) this AD.
Except as specified in paragraph (l) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2020-0040R1.
(1) Where EASA AD 2020-0040R1 refers to its effective date, this AD requires using the effective date of this AD.
(2) Where EASA AD 2020-0040R1 refers to “13 March 2020 [the effective date of the original issue of this AD],” this AD requires using the effective date of this AD.
(3) Where EASA AD 2020-0040R1 requires the accomplishment of repetitive inspections and corrective actions as specified in paragraphs (1) and (2) of the EASA AD, those actions are not required by this AD as specified in the EASA AD. Those actions are required by paragraphs (g), (h), and (i) of this AD.
(4) The “Remarks” section of EASA AD 2020-0040R1 does not apply to 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.
