Airworthiness Directive · Amendment 39-17537 · Fuselage
Airbus Airplanes
This AD applies to Airbus Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; and Model A320-111, -211, -212, -214, -231, -232, and -233 airplanes; certificated in any category; all manufacturer serial numbers, except those having embodied Airbus modification 30355 in production.
We are superseding airworthiness directive (AD) 2004-13-06 for certain Airbus Model A319 and A320 series airplanes. AD 2004-13-06 required repetitive detailed inspections to detect cracks in the keel beam side panels, and repair if necessary. This new AD requires repetitive eddy current inspections for cracking in the keel beam side panels, and corrective actions if necessary. This AD was prompted by reports of cracks on the side panels of the keel beams. We are issuing this AD to detect and correct fatigue cracks on the side panels of the keel beams, which could result in reduced structural integrity of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
At the applicable compliance time in paragraph (g)(1) or (g)(2) of this AD: Do an eddy current non-destructive test (NDT) inspection to detect cracks in the keel beam side panels at Area A and Area B, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-53-1060, Revision 04, dated September 13, 2012. Repeat the inspection thereafter at intervals not to exceed 12,000 flight cycles or 26,700 flight hours, whichever occurs first. Area A is part of the area of the upper elliptical cut-out stringer (STGR) 42 on the left-hand (LH) and right-hand (RH) side forward of frame (FR) 41; Area B is the area around the fasteners on both sides of the keel beam side panel below the center wing box at STGR 42 on the LH and RH side between FR 40 and FR 42.
(1) For airplanes that have been inspected as specified in Airworthiness Limitations Item (ALI) Task 533142-01-1, which was specified in the Airbus A319/A320/A321 ALI document up to Revision 05 inclusive; or as specified in Airbus A319/A320/A321 Maintenance Review Board (MRB) Report up to Revision 08 inclusive; or as specified in the instructions of Airbus Service Bulletin A320-53-1060, dated June 19, 2002, or Revision 01, dated April 2, 2004: At the later of the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD.
(i) Within 4,300 flight cycles or 9,600 flight hours after the last inspection, whichever occurs first.
(ii) Within 30 days after the effective date of this AD.
(2) For airplanes other than those identified in paragraph (g)(1) of this AD: At the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD.
(i) Prior to the accumulation of 24,200 total flight cycles, or 48,400 total flight hours, whichever occurs first.
(ii) Within 30 days after the effective date of this AD.
(1) If any crack is found in Area A during any inspection required by paragraph (g) of this AD: Before further flight, repair the affected area, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-53-1060, Revision 04, dated September 13, 2012. Accomplishing a repair terminates the repetitive inspections of Area A required by paragraph (g) of this AD for that side of the keel beam.
(2) If any crack is found in Area B during any inspection required by this AD: Before further flight, repair the affected area in accordance with a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent).
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
