Airworthiness directives › 2017-17-05
AD 2017-17-05 Airworthiness Directives; Airbus Airplanes
Models named: A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, B4-203, A300 B4-601, B4-603, B4-620. 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)(5) of this AD, certificated in any category, except airplanes that have been repaired as specified in Airbus Service Bulletin A300-53-0370; or Airbus Service Bulletin A300-53-6144, as applicable. (1) Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes. (2) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes. (3) Model A300 B4-605R and B4-622R airplanes. (4) Model A300 F4-605R and F4-622R airplanes. (5) Model A300 C4-605R Variant F airplanes.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
Except as required by paragraph (h) of this AD: Before exceeding 10,000 flight cycles since first flight of the airplane or within 30 days after the effective date of this AD, whichever occurs later, do a special detailed inspection (SDI) for cracking of the FR 47 forward fitting upper radius on the left-hand and right-hand sides of the fuselage, in accordance with the Accomplishment Instructions of the applicable Airbus service information specified in paragraphs (g)(1) and (g)(2) of this AD. Repeat the inspection thereafter at intervals not to exceed 4,150 flight cycles, except as required by paragraph (j) of this AD. (1) Airbus Service Bulletin A300-53-0246, Revision 08, including Appendix 1, dated April 13, 2016. (2) Airbus Service Bulletin A300-53-6029, Revision 12, including Appendix 1, dated April 13, 2016.
Unsafe condition
This AD was prompted by reports of cracks initiating at the upper radius of frame (FR) 47 and a determination that the current inspection procedure is not reliable in detecting certain cracking of the forward fitting of FR 47. We are issuing this AD to detect and correct fatigue cracking of the FR 47 forward fitting upper radius on the left-hand and right-hand sides of the fuselage, which could propagate and result in reduced structural integrity of the airplane.
Affected ADs
This AD affects AD 2007-26-14, Amendment 39-15316 (73 FR 2803, January 16, 2008) (“AD 2007-26-14”).
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