Airworthiness directives › 2014-23-13
AD 2014-23-13 Airworthiness Directives; Airbus Airplanes
Models named: A300 B2-203, B2K-3C, B4-103, B4-203, B4-2C, A300 B4-620, B4-622R, B4-622, A310-221, -222. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category. (1) Airbus Model A300 B2-203, B2K-3C, B4-103, B4-203, and B4-2C airplanes on which Airbus Modification 2434 has been embodied in production. (2) Airbus Model A300 airplane having manufacturer serial number 125, on the left hand side pylon only. (3) Airbus Model A300 B4-620, B4-622R, and B4-622 airplanes, except for airplanes on which Airbus Modification 10149 has been embodied in production. (4) Airbus Model A310-221, -222, -322, -324, and -325 airplanes, except for airplanes on which Airbus Modification 10149 has been embodied 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 2000-12-12, Amendment 39-11790 (65 FR 39072, June 23, 2000), with additional sources for repair approvals. For Model A300 B4-2C, B2K-3C, B2-203, B4-103, and B4-203 series airplanes: Prior to the accumulation of 9,000 total landings, or within 500 landings after June 12, 1995 (the effective date of AD 95-10-03, Amendment 39-9220 (60 FR 25604, May 12, 1995)), whichever occurs later, perform an internal eddy current inspection to detect cracks in the lower spar axis of the pylon between ribs 9 and 10, in accordance with Airbus Service Bulletin A300-54-071, dated November 12, 1991; or Revision 1, dated October 15, 1993. Accomplishment of an inspection required by paragraph (k), (l), or (m) of this AD terminates the inspection requirements of this paragraph. (1) If no crack is found, repeat the inspection thereafter at intervals not to exceed 2,500 landings. (2) If any crack is found that is less than or equal to 30 millimeters (mm): Perform subsequent inspections and repair in accordance with the methods and times specified in Airbus Service Bulletin A300-54-071, dated November 12, 1991; or Revision 1, dated October 15, 1993. (3) If any crack is found that is greater than 30 mm, but less than 100 mm: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Direction Générale de l'Aviation Civile (DGAC) (or its delegated agent); or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). (4) If any crack is found that is greater than or equal to 100 mm: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the DGAC (or its delegated agent); or the EASA; or Airbus's EASA DOA. (5) Accomplishment of the modification specified in Airbus Service Bulletin A300-54-0079, dated October 15, 1993, constitutes terminating action for the inspections required by paragraph (g) of this AD.
Unsafe condition
This AD was prompted by reports of cracking of the lower pylon spar after accomplishing an existing modification. We are issuing this AD to detect and correct fatigue cracking, which could result in reduced structural integrity of the lower spar of the nacelle pylon.
Affected ADs
This AD replaces AD 2000-12-12, Amendment 39-11790 (65 FR 39072, June 23, 2000).
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