Airworthiness directives › 2018-02-12
AD 2018-02-12 Airworthiness Directives; Airbus Airplanes
Models named: A320-211, -212, -231. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to Airbus Model A320-211, -212, and -231 airplanes, certificated in any category, manufacturer serial numbers up through 0104 inclusive.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
(1) At the latest of the times specified in paragraphs (g)(1)(i), (g)(1)(ii), and (g)(1)(iii) of this AD: Do a detailed inspection of the pressurized floor fittings at FR 36, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013. Repeat the inspection thereafter at intervals not to exceed 9,300 flight cycles or 18,600 flight hours, whichever occurs first. (i) Before exceeding 20,900 flight cycles or 41,800 flight hours, whichever occurs first since first flight of the airplane. (ii) Within 9,300 flight cycles or 18,600 flight cycles since the most recent inspection accomplished in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013. (iii) Within 1,250 flight cycles or 2,500 flight hours after March 3, 2016 (the effective date of AD 2016-02-01), without exceeding 12,000 flight cycles since the most recent inspection accomplished in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013. (2) If any crack is found during any inspection required by paragraph (g)(1) of this AD: Before further flight, repair using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.
Unsafe condition
This AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. We are issuing this AD to prevent fatigue cracking in the pressurized floor fittings at frame (FR) 36, which could result in the reduced structural integrity of the floor fittings and subsequent depressurization of the fuselage.
Affected ADs
This AD replaces AD 2016-02-01, Amendment 39-18380 (81 FR 4878, January 28, 2016) (“AD 2016-02-01”).
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