Airworthiness directives › 2018-06-03
AD 2018-06-03 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.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
Except for airplanes modified before the effective date of this AD using the Accomplishment Instructions of Airbus Service Bulletin A310-53-2124: At the times specified in paragraph (g)(1) of this AD but no later than the times specified in paragraph (g)(2) of this AD, do a high frequency eddy current (HFEC) rotating probe inspection for cracking of fastener holes H1 through H29 on frames 43 through 46, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-53-2124, Revision 03, dated December 22, 2014, except as required by paragraph (h) of this AD. If no cracking is found and the edge distance of the fastener hole is equal to or greater than the distance specified in the Accomplishment Instructions of Airbus Service Bulletin A310-53-2124, Revision 03, dated December 22, 2014, before further flight, do the modification (cold expansion) of the affected fastener holes, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-53-2124, Revision 03, dated December 22, 2014. Do all applicable related investigative and corrective actions before further flight. (1) Inspect at the applicable time specified in table 1 to paragraph (g)(1) of this AD, or within 24 months after the effective date of this AD, whichever occurs later. To establish the average flight time (AFT), take the accumulated flight time (counted from the take-off up to the landing) and divide by the number of accumulated flight cycles. This gives the AFT per flight cycle. Although the thresholds for Model A310-304, -322, -324, and -325 airplanes are optimized to airplane utilization, an operator can choose to use the thresholds for the other AFT. ER15MR18.002 (2) Inspect at the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD. (i) At the applicable time indicated in table 2 to paragraph (g)(2)(i) of this AD. Airbus Model A310-304, -322, -324, and -325 airplanes with an AFT equal to or less than 3.16 flight hours are short range airplanes. Airbus Model A310-304, -322, -324, and -325 airplanes with an AFT exceeding 3.16 flight hours are long range airplanes. For this paragraph, to establish the average flight time, take the accumulated flight time (counted from the take-off up to the landing) and divide by the number of accumulated flight cycles. This gives the AFT per flight cycle. ER15MR18.003 (ii) Within 500 flight cycles or 800 flight hours after October 14, 2009 (the effective date of AD 2009-18-16), whichever occurs first.
Unsafe condition
This AD was prompted by an evaluation by the design approval holder indicating that the junctions of center box upper frame bases to the upper fuselage arches are subject to widespread fatigue damage and that the compliance threshold for the modification in AD 2009-18-16 should be reduced. We are issuing this AD to prevent fatigue cracking of the frame foot run-outs, which could lead to rupture of the frame foot and cracking in adjacent frames and skin, and which could result in reduced structural integrity of the airplane.
Affected ADs
This AD replaces AD 2009-18-16, Amendment 39-16012 (74 FR 46342, September 9, 2009) (“AD 2009-18-16”).
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