Airworthiness directives › 2016-13-08
AD 2016-13-08 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 all Airbus airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category. (1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes. (2) Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
Within 1,000 flight hours after the effective date of this AD: Do an HFEC inspection for cracking of fasteners 1 through 3 at the left-hand and right-hand sides of the FR40 lower junction, and of the fitting around the fastener holes, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-0257, excluding Appendix 01 and including Appendix 02, dated April 4, 2014 (for Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes); or Airbus Service Bulletin A300-57-6115, dated April 4, 2014 (for Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes). If no cracking is found, repeat the HFEC inspection at intervals not to exceed 1,000 flight hours until a rototest inspection required by paragraph (h)(2) of this AD has been done. Where Airbus Service Bulletin A300-57-6115, dated April 4, 2014, refers to Structural Repair Manual (SRM) 51-40-13 for applying special protection, the correct reference is SRM 51-23-20; and to SRM 51-40-12 for applying paint coatings, the correct reference is SRM 51-23-10.
Unsafe condition
This AD was prompted by a report of cracking of the lower tension bolt area at rib one junction (both sides) of the lower wing. We are issuing this AD to detect and correct crack initiation of the fittings of the frame (FR) 40 lower wing locations, which could result in reduced structural integrity of the airplane.
Affected ADs
None.
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