Airworthiness directives › 2013-20-10
AD 2013-20-10 Airworthiness Directives; Airbus Airplanes
Models named: A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R. 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; certificated in any category; all manufacturer serial numbers, except airplanes on which Airbus Modification 10161 has been 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
At the applicable time specified in paragraph (g)(1) or (g)(2) of this AD: Perform an ultrasonic inspection to detect fatigue cracking of the bolt holes inboard and outboard of rib 9 on the bottom booms of the front and rear wing spars, in accordance with the Accomplishment Instruction of Airbus Mandatory Service Bulletin A300-57-6037, Revision 04, dated February 24, 2011, except as specified in paragraph (k) of this AD. Repeat the inspection thereafter at intervals not to exceed the applicable time specified in paragraph (h) of this AD. (1) For normal range airplanes, at the later of the times in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD. (i) Within 14,100 flight cycles or 30,400 flight hours since airplane first flight or within 14,100 flight cycles or 30,400 flight hours since airplane modification done as specified in the Accomplishment Instructions of Airbus Service Bulletin A300-57-6039 (which is not incorporated by reference in this AD), whichever occurs first. (ii) Within 1,600 flight cycles or 3,400 flight hours, whichever occurs first after the effective date of this AD. (2) For short range airplanes, at the later of the times in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD. (i) Within 15,200 flight cycles or 22,800 flight hours since airplane first flight, or since airplane modification done as specified in the Accomplishment Instructions of Airbus Service Bulletin A300-57-6039 (which is not incorporated by reference in this AD), whichever occurs first. (ii) Within 1,700 flight cycles or 2,500 flight hours, whichever occurs first after the effective date of this AD.
Unsafe condition
This AD was prompted by a fleet survey and an updated fatigue and damage tolerance analysis indicating a high risk for fatigue cracking on the front and rear spar bottom booms. We are issuing this AD to detect and correct fatigue cracks in the bolt holes of the wing spars, which could result in reduced structural integrity of a wing spar.
Affected ADs
This AD supersedes AD 2000-12-11, Amendment 39-11789 (65 FR 37853, June 19, 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