Airworthiness Directive · Amendment 39-19224 · Fuselage
Airbus Airplanes
This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, except for airplanes on which Airbus Modification 151574 was embodied in production.
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes.
(3) Model A320-211, -212, -214, -231, -232, and -233 airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes.
We are superseding Airworthiness Directive (AD) 2004-03-07, which applied to certain Airbus Model A320-111, -211, -212, and -231 series airplanes. AD 2004-03-07 required repetitive inspections for fatigue cracking around the fasteners attaching the pressure panel to the flexible bracket at a certain frame (FR), adjacent to the longitudinal beams on the left and right sides of the airplane; and repair as necessary. This new AD retains certain requirements of AD 2004-03-07, expands the applicability, and requires an inspection of the fastener holes on the pressure panel and modification or repair as applicable. This AD was prompted by fatigue tests which revealed cracking around the fasteners attaching the pressure panel to the flexible bracket, and by the discovery of additional cracks under the longitudinal beams at locations that are not included in the inspection area required by AD 2004-03-07. We are issuing this AD to address the unsafe condition on these products.
This paragraph restates the requirements of paragraphs (a) and (b) of AD 2004-03-07, with no changes.
(1) For Model A320-211, -212, and -231 series airplanes having serial numbers 0002 through 0107 inclusive, except those airplanes on which Airbus Modification 21202/K1432 has been incorporated in production, or on which Airbus Service Bulletin A320-53-1029, Revision 01, including Appendix 01, dated April 29, 2002, has been incorporated in service: Prior to the accumulation of 30,000 total flight cycles, do a rotating probe inspection on airplanes with a center fuel tank, or a detailed inspection on airplanes without a center fuel tank, to detect cracking around the fasteners that attach the pressure panel to the flexible bracket at FR 36, adjacent to the longitudinal beams on the left and right sides of the airplane, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1030, Revision 01, excluding Appendix 01, dated May 21, 2002.
(2) If no crack is detected by the inspection required by paragraph (g)(1) of this AD, repeat the applicable inspection thereafter at intervals not to exceed 6,000 flight cycles for airplanes without a center fuel tank, and at intervals not to exceed 18,000 flight cycles for airplanes with a center fuel tank.
This paragraph restates the requirements of paragraphs (c) and (d) of AD 2004-03-07, with specific delegation approval language.
(1) If any crack is detected during any inspection required by paragraph (g)(1) of this AD, before further flight, repair the affected structure by accomplishing all applicable actions in accordance with paragraphs 3.B. through 3.E. of the Accomplishment Instructions of Airbus Service Bulletin A320-53-1030, Revision 01, excluding Appendix 01, dated May 21, 2002. Repeat the applicable inspection thereafter at intervals not to exceed 6,000 flight cycles for airplanes without a center fuel tank, and at intervals not to exceed 18,000 flight cycles for airplanes with a center fuel tank. For any area where cracking is repaired, the repair constitutes terminating action for the repetitive inspection of that area.
Note 1 to paragraph (h)(1) of this AD: Airbus Service Bulletin A320-53-1030 references Airbus Service Bulletin A320-53-1029, Revision 01, including Appendix 01, dated April 29, 2002, as an additional source of service information for certain repairs.
(2) If Airbus Service Bulletin A320-53-1030, Revision 01, excluding Appendix 01, dated May 21, 2002, specifies to contact the manufacturer for appropriate action: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (p)(2) of this AD.
This paragraph restates the requirements of paragraph (e) of AD 2004-03-07, with revised compliance language, to provide optional terminating action for paragraphs (g) and (h) of this AD. For Model A320-211, -212, and -231 series airplanes having serial numbers 0002 through 0107 inclusive, except those airplanes on which Airbus Modification 21202/K1432 has been incorporated in production, or Airbus Service Bulletin A320-53-1029, Revision 01, including Appendix 01, dated April 29, 2002, has been incorporated in service: Modification, before the effective date of this AD, of the structure around the fasteners that attach the pressure panel to the flexible bracket at FR 36, adjacent to the longitudinal beams on the left and right sides of the airplane, by accomplishing all applicable actions in accordance with paragraphs 3.A. through 3.E. of the Accomplishment Instructions of Airbus Service Bulletin A320-53-1029, Revision 01, including Appendix 01, dated April 29, 2002, constitutes terminating action for the actions required by paragraphs (g) and (h) of this AD.
For all airplanes, except for airplanes identified in paragraph (l) of this AD: At the applicable time specified in table 1 to paragraph (j) of this AD, do a special detailed inspection for cracking of the fastener holes on the pressure panel between FR 35 and FR 36 under the longitudinal beam, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1264, Revision 01, excluding Appendix 01, dated July 4, 2016.
(1) If, during any inspection required by paragraph (j) of this AD, no cracking is found, or cracking is found that is within the limits specified in Airbus Service Bulletin A320-53-1264, Revision 01, excluding Appendix 01, dated July 4, 2016: Before further flight, modify the pressure panel above the left and right longitudinal beams, including doing all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1240, Revision 02, dated March 14, 2017; or Service Bulletin A320-53-1263, Revision 02, excluding Appendix 01 and including Appendix 02, dated December 6, 2017, as applicable. Do all related investigative and corrective actions before further flight. Where Airbus Service Bulletin A320-53-1240, Revision 02, dated March 14, 2017; or Service Bulletin A320-53-1263, Revision 02, excluding Appendix 01 and including Appendix 02, dated December 6, 2017; specify to contact Airbus for appropriate action: Before further flight, accomplish the repair using a method approved in accordance with the procedures specified in paragraph (p)(2) of this AD.
(2) If, during any inspection required by paragraph (j) of this AD, any cracking is found that exceeds the limits specified in Airbus Service Bulletin A320-53-1264, Revision 01, excluding Appendix 01, dated July 4, 2016: Before further flight, repair any cracking in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1264, Revision 01, excluding Appendix 01, dated July 4, 2016. Where Airbus Service Bulletin A320-53-1264, Revision 01, excluding Appendix 01, dated July 4, 2016, specifies to contact Airbus for appropriate action, and specifies that action as “RC” (Required for Compliance), before further flight, request approval of repair instructions using a method approved in accordance with the procedures specified in paragraph (p)(2) of this AD, and accomplish the repair accordingly within the compliance time specified in those instructions. If no compliance time is defined in the repair instructions, accomplish the repair before further flight.
For Model A319 and Model A320 series airplanes on which the actions specified in Airbus Service Bulletin A320-57-1193 have been embodied and the airplane has accumulated 33,000 flight cycles or 66,000 flight hours or more since the airplane's first flight on the effective date of this AD: Within 30 days after the effective date of this AD, contact the Manager, International Section, Transport Standards Branch FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA) for approved repair instructions and within the compliance time specified in those instructions, accomplish the repair accordingly. If approved by the DOA, the approval must include the DOA-authorized signature. If no compliance time is defined in the repair instructions, accomplish the repair before the next flight.
(1) Modification of an airplane as specified in paragraph (m)(1)(i), (m)(1)(ii), or (m)(1)(iii) of this AD constitutes terminating action for the repetitive inspection required by paragraph (g)(2) of this AD for that airplane only.
(i) Modification of an airplane as required by paragraph (k)(1) of this AD.
(ii) Modification of an airplane prior to the effective date of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1240, Revision 01, dated April 4, 2016; or Airbus Service Bulletin A320-53-1263, Revision 01, dated February 29, 2016; as applicable.
(iii) Modification of an airplane using instructions obtained in accordance with the procedures specified in paragraph (p)(2) of this AD.
(2) Repair of an airplane as required by paragraph (k)(2) of this AD constitutes terminating action for the repetitive inspections required by paragraph (g)(2) of this AD for that airplane, unless specified otherwise in the repair instructions approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
Although Airbus Service Bulletin A320-53-1264, Revision 01, excluding Appendix 01, dated July 4, 2016, specifies to submit certain information to the manufacturer, and specifies that action as “RC” (Required for Compliance), this AD does not include that requirement.
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.
