Airworthiness directives › 2018-14-09
AD 2018-14-09 Airworthiness Directives; Airbus Airplanes
Models named: A318-111, -112, -121, -122, A319-111, -113, -114, -115, -131, -132. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to Airbus Model A318-111, -112, -121, and -122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes, certificated in any category, all manufacturer serial numbers, except the airplanes specified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD. (1) Airplanes on which Airbus modification 161255 has been embodied in production. (2) Model A319 series airplanes on which Airbus modifications 28238, 28162, and 28342 have been concurrently embodied in production. (3) Model A318 series airplanes on which Airbus modification 39195 has been embodied in production.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
Before exceeding the threshold specified in table 1 to paragraphs (g) and (n) of this AD, or table 2 to paragraphs (g) and (n) of this AD, as applicable to airplane configuration (pre- or post-modification 20416 or pre- or post-modification 21999): Do a special detailed (rototest) inspection of the two upper rows of fasteners of the crossbeam splicing at FR16 and FR20 on both LH and RH sides, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1286, Revision 01, dated December 22, 2015. Thereafter, repeat the inspection at the intervals specified in table 1 to paragraphs (g) and (n) of this AD, or table 2 to paragraphs (g) and (n) of this AD, as applicable to airplane configuration (pre- or post-modification 20416 or pre- or post-modification 21999). BILLING CODE 4910-13-P ER19JY18.002 ER19JY18.003 BILLING CODE 4910-13-C
Unsafe condition
This AD was prompted by reports of early cracking on the four holes of the crossbeam splicing at certain fuselage frames (FR). We are issuing this AD to detect and correct cracking at two upper rows of fasteners of the crossbeam splicing at FR16 and FR20, on both the left-hand (LH) and right-hand (RH) sides, which can result in reduced structural integrity of the airplane due to the failure of structural components.
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