Airworthiness directives › 2013-15-21
AD 2013-15-21 Airworthiness Directives; Airbus Airplanes
Models named: A319-111, -112, -113, -114, -115, -131, -132, -133, A320-111, -211. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
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.
Compliance
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Required actions
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.
Unsafe condition
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.
Affected ADs
This AD supersedes AD 2004-13-06, Amendment 39-13688 (69 FR 38818, June 29, 2004).
Read the original on the Federal Register →
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1