Airworthiness Directive · Amendment 39-19681 · Nacelles/pylons
Airbus SAS Airplanes
This AD applies to Airbus SAS Model A318-111, -112; Model A319-111, -112, -113, -114, -115; Model A320-211, -212, -214, -216; and Model A321-111, -112, -211, -212, -213 airplanes, certificated in any category, as identified in European Aviation Safety Agency (EASA) AD 2018-0137R1, dated January 9, 2019 (“EASA AD 2018-0137R1”).
The FAA is superseding Airworthiness Directive (AD) 2016-07- 12, which applied to certain Airbus SAS Model A318, A319, A320, and A321 series airplanes. AD 2016-07-12 required repetitive inspections for damage and cracking of the aft fixed fairing (AFF) of the pylons, and repair if necessary. This AD retains the requirements of AD 2016- 07-12 and requires additional repetitive inspections at the upper spar at a certain rib area and corrective actions if necessary, as specified in an European Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by reports of cracking of the AFF of the pylons due to fatigue damage of the structure and reports of cracks on a certain rib of a modified AFF of the pylons. The FAA is issuing this AD to address the unsafe condition on these products.
Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2018-0137, dated June 28, 2018 (“EASA AD 2018-0137”); or EASA AD 2018-0137R1.
(1) For purposes of determining compliance with the requirements of this AD, use the following paragraphs.
(i) Where EASA ADs 2018-0137 and 2018-0137R1 refer to the effective date of EASA AD 2018-0137 (July 12, 2018), this AD requires using the effective date of this AD.
(ii) Where EASA AD 2018-0137 refers to a compliance time of after July 16, 2014, this AD requires using May 10, 2016 (the effective date of AD 2016-07-12).
(2) The “Remarks” section of EASA ADs 2018-0137 and 2018-0137R1 do not apply.
(3) Where paragraph (3) of EASA ADs 2018-0137 and 2018-0137R1 requires that airplanes that have embodied Airbus modification 156593 accomplish the initial inspection of the AFF of the pylons before exceeding 10,000 flight cycles or 15,000 flight hours, whichever occurs first since airplane first flight, this AD requires inspection of those airplanes before exceeding 10,000 flight cycles or 15,000 flight hours since embodiment of Airbus modification 156593, whichever occurs first.
(4) Where paragraph (6) of EASA AD 2018-0137 gives credit for “the initial requirements of paragraph (4)” of EASA AD 2018-0137, this AD gives credit for “the requirements of paragraph (4)” of EASA AD 2018-0137.
(5) Where EASA ADs 2018-0137 and 2018-0137R1 require any approval from EASA or Airbus SAS's Design Organization Approval (DOA), this AD requires approval by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
(6) Where any service information referenced in EASA ADs 2018-0137 and 2018-0137R1 specifies to use consumable material list (CML) material number 10ABC1, this AD allows the use of CML material number 10ABE1 as an additional method of compliance.
Although the service information referenced in EASA ADs 2018-0137 and 2018-0137R1 specifies to submit certain information to the manufacturer, this AD does not include that requirement.
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.
