Airworthiness Directive · Amendment 39-18639 · Fuselage
Airbus Airplanes
Superseded. A later AD replaced this one: AD 2020-18-07. Comply with the one in force.
This AD applies to the airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, all manufacturer serial numbers, except those on which Airbus Modification 37878 has been embodied in production, or Airbus Service Bulletin A320-53-1281 has been done in service.
(1) Airbus Model A318-111, -112, -121, and -122 airplanes.
(2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes.
(3) Airbus Model A320-211, -212, -214, -231, -232, and -233 airplanes.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A318, A319, and A320 series airplanes. This AD was prompted by reports of chafing damage on the fuselage skin at the bottom of certain frames, underneath the fairing structure. This AD requires repetitive detailed inspections for damage on the fuselage skin at certain frames, and applicable related investigative and corrective actions. We are issuing this AD to detect and correct damage to the fuselage skin, which could lead to crack initiation and propagation, possibly resulting in reduced structural integrity of the fuselage.
(1) Within the compliance times identified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD, whichever occurs later, do a detailed inspection for damage (including chafing marks) on the fuselage skin, including previously repaired areas, at frame (FR) 34 between stringer (STR) 43 on the left-hand and right-hand sides, in accordance with paragraph 3.C., “Procedure,” of Airbus Service Bulletin A320-53-1287, dated July 29, 2014. Repeat the inspection thereafter at intervals not to exceed 12,000 flight cycles or 24,000 flight hours, whichever occurs first.
(i) Before exceeding 12,000 flight cycles or 24,000 flight hours, whichever occurs first since the airplane's first flight.
(ii) Within 5,000 flight cycles or 10,000 flight hours, whichever occurs first after the effective date of this AD.
(2) If any damage is detected during any inspection required by paragraph (g)(1) of this AD, before further flight, do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1287, dated July 29, 2014, except as required by paragraph (g)(3) of this AD.
(3) If any cracking is found during any related investigative action required by paragraph (g)(2) of this AD, or if any damage detected during the inspection required by paragraph (g)(1) of this AD exceeds the limits defined in the Accomplishment Instructions of Airbus Service Bulletin A320-53-1287, dated July 29, 2014, before further flight, repair 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).
Accomplishment of a repair on an airplane as required by paragraphs (g)(2) and (g)(3) of this AD, does not constitute terminating action for the repetitive detailed inspections required by paragraph (g)(1) of this AD, unless the approved repair indicates otherwise.
Modification of the belly fairing on any airplane in accordance with paragraph 3.C., “Procedure,” of Airbus Service Bulletin A320-53-1281, Revision 02, including Appendix 01, dated October 9, 2015, constitutes terminating action for the repetitive detailed inspections required by paragraph (g)(1) of this AD for that airplane.
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.
