Airworthiness Directive · Amendment 39-18148 · Nacelles/pylons
Airbus Airplanes
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.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A318-111 and -112 airplanes and Model A319, A320, and A321 series airplanes. This AD was prompted by reports of cracks on the forward corner fittings of engine pylon aft secondary structures. This AD requires repetitive inspections of certain forward corner fittings of the pylon aft secondary structures, and corrective actions if necessary. This AD also provides optional terminating action for the repetitive inspections. 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.
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.
If any crack is found on the corner fittings of a pylon during any inspection required by paragraph (g) of this AD: Before further flight, do a detailed inspection for cracking of the lower and medium spars, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-54-1022, Revision 03, dated April 15, 2014.
(1) If any damage is found: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).
(2) If no damage is found: Within 5,000 flight cycles or 7,500 flight hours, whichever occurs first after the detailed inspection specified in the introductory text to paragraph (h) of this AD, modify the airplane, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-54-1019, Revision 02, dated April 15, 2014.
Modification of an airplane by installation of corner fittings having P/N D0041092120000 (RH) and P/N D0041092120100 (LH) on both pylons, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-54-1019, Revision 02, dated April 15, 2014, constitutes terminating action for the repetitive inspections required by paragraph (g) of this AD.
Airplanes on which Airbus Modification 38067 (installation of new corner fittings) has been embodied in production, and airplanes already modified in service as described in Airbus Service Bulletin A320-54-1019, are not affected by the requirements of paragraph (g) of this AD, provided that no corner fittings having P/N D54530014201 (RH) or P/N D54530014200 (LH) have been installed since first flight of the airplane, or since modification, as applicable.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
