Airworthiness Directive · Amendment 39-18040 · Fuselage
Airbus Airplanes
Superseded. A later AD replaced this one: AD 2020-02-20. 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 A320-111, -211, -212, -214, -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 on which Airbus Modification 21202 has been embodied in production, except those on which Modification 152569 has been embodied in production.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a report of a crack found in the fuselage during a fatigue test campaign. This AD requires repetitive rototest inspections for cracking; corrective actions if necessary; and modification of the torsion box, which would terminate the repetitive inspections. We are issuing this AD to prevent cracking in the side box beam flange of the fuselage, which could affect the structural integrity of the airplane.
At the time specified in paragraph (g)(1) or (g)(2) of this AD, whichever occurs later: Do a rototest inspection for cracking of the beam flange of the stiffener 15 side box on the left- and right-hand sides in the FR43 area, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1258, dated October 18, 2012. Repeat the inspection thereafter at intervals not to exceed 7,500 flight cycles or 15,000 flight hours, whichever occurs first.
(1) Before exceeding 24,000 flight cycles or 48,000 flight hours, whichever occurs first since the airplane's first flight.
(2) Within 3,000 flight cycles or 6,000 flight hours, whichever occurs first after the effective date of this AD.
If any crack is found during any inspection required by paragraph (g) of this AD: 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).
Before exceeding 48,000 flight cycles or 96,000 flight hours, whichever occurs first since the airplane's first flight: Modify the fittings on the left- and right-hand sides of the torsion box, including doing all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1251, Revision 01, dated October 18, 2013; except where Airbus Service Bulletin A320-53-1251, Revision 01, dated October 18, 2013, specifies to contact Airbus for repair, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
Modification of the airplane as required by paragraph (i) of this AD constitutes terminating action for the repetitive inspections required by paragraph (g) 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.
Aircraft
