Airworthiness directives › 2015-09-03
AD 2015-09-03 Airworthiness Directives; Airbus Airplanes
Models named: A318-111, -112, A319-111, -113, -114, -115, -131, -132, -133, A320-211. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, except for airplanes on which Airbus Modification 33844 or Modification 33847, as applicable, has been embodied in production. (1) Airbus Model A318-111 and -112 airplanes. (2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes. (3) Airbus Model A320-211, -212, -214, -231, -232, and -233 airplanes. (4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
At the latest of the times specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD: Do a detailed inspection for cracking of forward corner fittings having part number (P/N) D54530014201 (right-hand (RH)) and P/N D54530014200 (left-hand (LH)) of the pylon aft secondary structures, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-54-1022, Revision 03, dated April 15, 2014, except as provided by paragraph (j) of this AD. Repeat the inspection thereafter at intervals not to exceed 15,000 flight cycles or 22,500 flight hours, whichever occurs first. Accomplishment of the actions specified in paragraph (i) of this AD terminates the actions required by this paragraph. (1) Within 15,000 flight cycles or 22,500 flight hours, whichever occurs first since first flight of the airplane. (2) Within 5,000 flight cycles or 7,500 flight hours after the effective date of this AD, without exceeding 40,750 flight cycles or 60,750 flight hours, whichever occurs first since first flight of the airplane. (3) Within 750 flight cycles or 750 flight hours, whichever occurs first after the effective date of this AD.
Unsafe condition
This AD was prompted by reports of cracks on the forward corner fittings of engine pylon aft secondary structures. We are issuing this AD to detect and correct detachment of the lower fairing attachment and/or loss of the aft fixed fairing with the movable fairing from the airplane in flight, which could result in damage to the airplane.
Affected ADs
None.
Read the original on the Federal Register →
You just looked this one up by hand
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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