Airworthiness Directive · Amendment 39-19273 · Fuselage
Airbus Airplanes
This AD applies to the airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, except for those airplanes on which Airbus modification 160055 or modification 160056 has been embodied in production, and except for Model A319 series airplanes on which modification 28162, 28238, and 28342 have been embodied (“Corporate Jet”).
(1) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes.
(2) Airbus Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes.
(3) Airbus Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes.
We are superseding Airworthiness Directive (AD) 2015-15-13, which applied to certain Airbus Model A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321- 111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2015- 15-13 required a modification of the potable water service panel and waste water service panel, including doing applicable related investigative and corrective actions. This AD requires a modification of the waste water and potable water service panels with new compliance times. This AD also removes certain airplanes from the applicability and adds Model A320-216 airplanes to the applicability. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the potable water and waste water service panel areas are subject to widespread fatigue damage (WFD). We are issuing this AD to address the unsafe condition on these products.
(1) Within the compliance times specified in table 1 to paragraphs (g)(1) and (i) of this AD, as applicable, modify the potable water service panel, including doing a check of the diameter of the holes of removed fasteners, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1272, Revision 04, dated November 29, 2016, except as required by paragraph (g)(2) of this AD. Do all applicable related investigative and corrective actions before further flight.
(2) Where Airbus Service Bulletin A320-53-1272, Revision 04, dated November 29, 2016, specifies to contact Airbus for appropriate action, and specifies that action as “RC” (Required for Compliance): Before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (m)(2) of this AD.
(1) Within the compliance times specified in table 2 to paragraphs (h)(1) and (i) of this AD, as applicable, modify the waste water service panel, including doing a check of the diameter of the holes of removed fasteners, and do all applicable related investigative and corrective actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1267, Revision 05, dated November 29, 2016, except as required by paragraph (h)(2) of this AD. Do all applicable related investigative and corrective actions before further flight.
(2) Where Airbus Service Bulletin A320-53-1267, Revision 05, dated November 29, 2016, specifies to contact Airbus for appropriate action, and specifies that action as “RC” (Required for Compliance): Before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (m)(2) of this AD.
For airplanes on which the modification, as required by paragraph (g) or (h) of this AD, as applicable, was accomplished before reaching the applicable minimum compliance time as defined in table 1 to paragraphs (g)(1) and (i) of this AD or table 2 to paragraphs (h)(1) and (i) of this AD: Before exceeding 60,000 flight cycles since the airplane's first flight, contact the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA) for approved corrective action instructions and accomplish those instructions accordingly. If approved by the DOA, the approval must include the DOA-authorized signature.
Modification of an airplane as required by paragraph (g) of this AD terminates the requirement for accomplishing the ALS Part 2 task for that airplane as specified in table 3 to paragraph (j) of this AD, as applicable.
Modification of an airplane as required by paragraph (h) of this AD terminates the requirement for accomplishing the ALS Part 2 task for that airplane as specified in table 4 to paragraph (k) of this AD, 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.
