Airworthiness Directive · Amendment 39-19320 · Wings
Airbus Airplanes
Superseded. A later AD replaced this one: AD 2022-14-10. Comply with the one in force.
This AD applies to Airbus Model A318-111, -112, -121, and -122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes; certificated in any category; all manufacturer serial numbers, except airplanes specified in paragraphs (c)(1) and (c)(2) of this AD.
(1) Model A319 and A320 series airplanes on which Airbus Modification 160000 (structural reinforcement for sharklet installation) has been embodied in production.
(2) Model A321 series airplanes on which Airbus Modification 160021 (structural reinforcement for sharklet installation) has been embodied in production.
We are superseding Airworthiness Directive (AD) 2016-01-11, which applied to certain Airbus Model A320-211, -212, and -231 airplanes. AD 2016-01-11 required repetitive inspections for cracking of the radius of the front spar vertical stringers and the horizontal floor beam on frame (FR) 36, repetitive inspections for cracking of the fastener holes of the front spar vertical stringers on FR 36, and repair if necessary. This AD adds new thresholds and intervals for the repetitive inspections; requires, for certain airplanes, a potential terminating action modification of the center wing box area; and expands the applicability. This AD was prompted by a report that, during a center fuselage certification full-scale fatigue test, cracks were found on the front spar vertical stringer at a certain frame. This AD was also prompted by a determination that, during further investigations of the frame as part of the widespread fatigue damage (WFD) campaign, certain inspection compliance times have to be revised and new inspections and a new potential terminating action modification have to be introduced. We are issuing this AD to address the unsafe condition on these products.
For the purposes of this AD, airplane configurations are defined in figure 1 to paragraphs (g), (h), (i)(1), and (j) of this AD and figure 2 to paragraphs (g) and (i)(1) of this AD.
For Configuration 001, 002, or 003 airplanes, as identified in figure 1 to paragraphs (g), (h), (i)(1), and (j) of this AD, on which the inspections specified in Airbus Service Bulletin A320-57-1178, dated October 29, 2013, have been accomplished before the effective date of this AD; but the additional work specified in Airbus Service Bulletin A320-57-1178, Revision 01, dated May 28, 2014, including Appendix 01, dated May 28, 2014, has not been accomplished before the effective date of this AD: Before accomplishing the initial inspection required by paragraph (i)(1) 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 further instructions and accomplish those instructions accordingly.
(1) Within the compliance time defined in figure 3 to paragraph (i)(1) of this AD, as applicable to airplane configuration as identified in figure 1 to paragraphs (g), (h), (i)(1), and (j) of this AD and figure 2 to paragraphs (g) and (i)(1) of this AD, accomplish a special detailed inspection (SDI) for cracking of the radius of the front spar vertical stringers and the horizontal floor beam and the fastener holes on FR 36, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1178, Revision 03, including only Appendix 03, both dated November 29, 2016.
(2) If no cracking is found during any inspection required by paragraph (i)(1) of this AD, repeat the inspection required by paragraph (i)(1) of this AD thereafter at intervals not to exceed the inspection interval values defined in figure 4 to paragraphs (i)(2) and (l) of this AD, except as provided by paragraph (l) of this AD.
For A320 series airplanes, Configuration 001, 002, or 003 as identified in figure 1 to paragraphs (g), (h), (i)(1), and (j) of this AD: Within the compliance time defined in figure 5 to paragraph (j) of this AD, as applicable, modify the center wing box area, including doing all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1200, dated November 20, 2015, except as required by paragraph (k) of this AD. Do all applicable related investigative and corrective actions before further flight.
If any crack is found during any inspection required by this AD: Before further flight, repair using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. Where Airbus Service Bulletin A320-57-1178, Revision 03, including only Appendix 03, both dated November 29, 2016; and Airbus Service Bulletin A320-57-1200, dated November 20, 2015; specify to contact Airbus for appropriate action, and specify that action as “RC” (Required for Compliance), accomplish corrective actions in accordance with this paragraph.
For airplanes that have been repaired in the inspection area specified in paragraph (i)(1) of this AD before the effective date of this AD using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the EASA; or Airbus's EASA DOA: Accomplish repetitive SDIs within the compliance time defined in those repair instructions for repetitive SDIs. If no compliance time is identified in the repair instructions for repetitive SDIs, accomplish the repetitive SDIs required by paragraph (i)(2) of this AD at the compliance times defined in figure 4 to paragraphs (i)(2) and (l) of this AD.
Modification or repair of an airplane, as specified in paragraph (j) or (k) of this AD, does not constitute terminating action for the repetitive inspections required by this AD, unless it is specified otherwise in a repair method approved by the Manager, International Section, Transport Standards Branch, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
Submit a report of the positive findings of the inspections required by paragraphs (i) and (j) of this AD to “Airbus Service Bulletin Reporting Online Application” on Airbus World (https://w3.airbus.com/), at the applicable time specified in paragraph (n)(1) or (n)(2) of this AD.
(1) If the inspection was done on or after the effective date of this AD: Report within 30 days after that inspection.
(2) If the inspection was done before the effective date of this AD: Report within 30 days after the effective date 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.
