Airworthiness directives › 2017-11-13
AD 2017-11-13 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 (S/Ns) 0001 through 0123 inclusive, except those that have embodied Airbus Modifications 21780 and 21781 in production.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
This paragraph restates the requirements of paragraph (a) of AD 98-13-14, with additional methods of approving repairs. For Model A320 series airplanes, as listed in Airbus Service Bulletins A320-53-1089 and A320-53-1090, both dated November 22, 1995: Prior to the accumulation of 20,000 total flight cycles, or within 500 flight cycles after July 30, 1998 (the effective date of AD 98-13-14), whichever occurs later, perform a rotating probe inspection for fatigue cracking of the fastener holes and/or the adjacent tooling hole, as applicable, of the right- and left-hand former junctions at FR 68, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1089, dated November 22, 1995. Accomplishing an inspection required by paragraph (h) of this AD terminates the actions required by this paragraph. (1) If no crack is detected, accomplish either paragraph (g)(1)(i) or (g)(1)(ii) of this AD. (i) Repeat the inspection thereafter at intervals not to exceed 20,000 flight cycles; or (ii) Prior to further flight following the accomplishment of the inspection required by paragraph (g) of this AD, cold work the fastener holes and/or the adjacent tooling hole of the right- and left-hand former junctions at FR 68, as applicable, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1090, dated November 22, 1995. Accomplishment of this cold working constitutes terminating action for the repetitive inspections required by paragraph (g)(1)(i) of this AD. (2) If any crack is detected, prior to further flight, repair in accordance with 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).
Unsafe condition
This AD was prompted by identification of four cracks in the fastener holes of the former junction at frame (FR) 68 between stringers 4 and 5, which occurred during a fatigue test, and a determination that certain compliance times specified in AD 98-13-14 must be reduced. We are issuing this AD to prevent fatigue cracks from occurring or propagating in certain structures, which could adversely affect the structural integrity of the airplane.
Affected ADs
This AD replaces AD 98-13-14, Amendment 39-10602 (63 FR 34556, June 25, 1998) (“AD 98-13-14”).
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