Airworthiness directives › 2015-17-09
AD 2015-17-09 Airworthiness Directives; Airbus Airplanes
Models named: A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, A300 F4-605R, F4-622R, A300 C4-605R Variant F. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, and B4-622R airplanes, Model A300 F4-605R and F4-622R airplanes, and Model A300 C4-605R Variant F airplanes, certificated in any category, except those on which Airbus Modification 8608 is incorporated in production.
Compliance
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Required actions
For all airplanes, at the applicable time specified in paragraph (h) of this AD, accomplish the actions specified in paragraphs (g)(1) and (g)(2) of this AD concurrently. Repeat the inspection required by paragraph (g)(1) of this AD thereafter at intervals not to exceed the values as specified in the “Repeat Interval” column in Table 1 or Table 2 of Airbus Service Bulletin A300-57-6027, Revision 07, dated June 6, 2011, as applicable to the airplane configuration and utilization; except as required by paragraph (k) of this AD. (1) Do a high frequency eddy current (HFEC) inspection of the center spar sealing angles adjacent to the pylon rear attachment fitting for cracks, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6027, Revision 07, dated June 6, 2011. (2) Unless already done: Modify the airplane by cold expansion of the center spar sealing angles outboard of rib 8, adjacent to the pylon rear attachment fitting, including doing the eddy current inspections for cracks of the bolt holes, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6033, Revision 02, dated September 19, 2011.
Unsafe condition
This AD was prompted by reports of cracking in the vertical web of the center spar sealing angles of the wing, and subsequent analyses that showed that the inspection threshold and interval specified in AD 98-18-02, Amendment 39-10718 (63 FR 45689, August 27, 1998), must be reduced to allow timely detection of cracks on the sealing angles of the center spar, adjacent to rib 8. We are issuing this AD to prevent crack formation in the sealing angles; such cracks could rupture the sealing angle and lead to subsequent crack formation in the bottom skin of the wing, and resultant reduced structural integrity of the center spar section of the wing.
Affected ADs
This AD replaces AD 98-18-02, Amendment 39-10718 (63 FR 45689, August 27, 1998).
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