Airworthiness directives › 2013-15-12
AD 2013-15-12 Airworthiness Directives; Airbus Airplanes
Models named: A310-203, -204, -221, -222, -304, -322, -324, -325. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes, certificated in any category, all serial numbers; except for airplanes identified in paragraphs (c)(1) and (c)(2) of this AD. (1) Airplanes that have been modified in service according to Airbus Service Bulletin A310-57-2081 or during production by Airbus modification 12525. (2) Airplanes that have been repaired according to Airbus Repair Inspection R573-49243 or R573-49237.
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
This paragraph restates the requirements of paragraph (a) of AD 2004-15-07, Amendment 39-13741 (69 FR 44592, July 27, 2004). For airplanes on which Airbus Modification 5106 (Airbus Service Bulletin A310-57-2004, Revision 2, dated March 5, 1990, which is not incorporated by reference in this AD) has not been done as of August 31, 2004 (the effective date of AD 2004-15-07): Within 2,000 flight cycles after August 31, 2004 (the effective date of AD 2004-15-07), or within 3,000 flight cycles after the last inspection done per paragraph (k) of AD 98-26-01, Amendment 39-10942 (63 FR 69179, December 16, 1998), whichever is first; do a high frequency eddy current (HFEC) inspection for cracking of the area around the fasteners of the landing plate of the wing bottom skin panel No. 2 of the left and right wings. Do the inspection per the Accomplishment Instructions of Airbus Service Bulletin A310-57-2082, dated June 11, 2002. If no cracking is found, repeat the inspection thereafter at intervals not to exceed 1,900 flight cycles, until accomplishment of the terminating action specified in paragraph (j) of this AD. Accomplishment of the inspection required by paragraph (k) of this AD terminates the requirements of paragraph (g) of this AD.
Unsafe condition
This AD was prompted by a reassessment of the previous fatigue threshold and inspection interval specified in AD 2004-15-07, Amendment 39-13741 (69 FR 44592, July 27, 2004), which resulted in a determination that reduced inspection thresholds and intervals for accomplishment of the tasks are necessary. We are issuing this AD to detect and correct fatigue cracking of the area around the fasteners of the landing plate of the aileron access doors and the bottom skin panel of the wings, which could result in reduced structural integrity of the wings.
Affected ADs
This AD supersedes AD 2004-15-07, Amendment 39-13741 (69 FR 44592, July 27, 2004).
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