Airworthiness Directive · Amendment 39-18223 · Fuselage
Airbus Airplanes
Superseded. A later AD replaced this one: AD 2018-09-16. Comply with the one in force.
This AD applies to the airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, all manufacturer serial numbers, except those on which Airbus Modification 160055 or Airbus Modification 160056 has been embodied in production.
(1) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes.
(2) Airbus Model A320-211, -212, -214, -231, -232, and -233 airplanes.
(3) 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 A319 series airplanes; Model A320-211, -212, -214, -231, - 232, and -233 airplanes; and Model A321 series airplanes. This AD was prompted by reports of cracks that could be initiated at the waste water service panel area and the potable water service panel area. This AD requires modification of the potable water service panel and waste water service panel, including doing applicable related investigative and corrective actions. We are issuing this AD to prevent any cracking at the waste water service panel area and the potable water service panel area, which could affect the structural integrity of the airplane.
(1) Within the compliance time specified in paragraphs (g)(1)(i), (g)(1)(ii), (g)(1)(iii), (g)(1)(iv), and (g)(1)(v) of this AD, as applicable, modify the potable water service panel, including doing all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1272, Revision 02, dated May 19, 2014, except where Airbus Service Bulletin A320-53-1272, Revision 02, dated May 19, 2014, specifies to contact Airbus, repair before further flight 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). Do all applicable related investigative and corrective actions within the compliance time specified in paragraphs (g)(1)(i), (g)(1)(ii), (g)(1)(iii), (g)(1)(iv), and (g)(1)(v) of this AD.
(i) For Model A319 airplanes pre-modification 160001: Within 48,500 flight cycles or 97,000 flight hours, whichever occurs first since the airplane's first flight.
(ii) For Model A319 airplanes post-modification 160001: Within 46,000 flight cycles or 92,000 flight hours, whichever occurs first since the airplane's first flight.
(iii) For Model A320 airplanes pre-modification 160001: Within 54,200 flight cycles or 108,400 flight hours, whichever occurs first since the airplane's first flight.
(iv) For Model A320 airplanes post-modification 160001: Within 36,000 flight cycles or 72,000 flight hours, whichever occurs first since the airplane's first flight.
(v) For Model A321 airplanes: Within 60,000 flight cycles or 120,000 flight hours, whichever occurs first since the airplane's first flight.
(2) Within the compliance time specified in paragraphs (g)(2)(i), (g)(2)(ii), (g)(2)(iii), (g)(2)(iv), (g)(2)(v), and (g)(2)(vi) of this AD, as applicable, modify the waste water service panel, including doing all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1267, Revision 02, dated May 19, 2014, except where Airbus Service Bulletin A320-53-1267, Revision 02, dated May 19, 2014, specifies to contact Airbus, repair before further flight using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. Do all applicable related investigative and corrective actions within the compliance time specified in paragraphs (g)(2)(i), (g)(2)(ii), (g)(2)(iii), (g)(2)(iv), and (g)(2)(v) of this AD.
(i) For Airbus A319 airplanes pre-modification 160001: Within 44,400 flight cycles or 88,800 flight hours, whichever occurs first since the airplane's first flight.
(ii) For Airbus A319 airplanes post-modification 160001: Within 43,600 flight cycles or 87,200 flight hours, whichever occurs first since the airplane's first flight.
(iii) For Airbus A320 airplanes pre-modification 160001, within the compliance times specified in paragraph (g)(2)(iii)(A) or (g)(2)(iii)(B) of this AD, whichever occurs later:
(A) Within 46,400 flight cycles or 92,800 flight hours, whichever occurs first since the airplane's first flight.
(B) Within 2,300 flight cycles or 4,600 flight hours, whichever occurs first since last accomplishment of Task No. 534126-01-3, of the Airworthiness Limitation Section (ALS) Part 2, “Damage-Tolerant Airworthiness Limitation Items” of the Airbus A319/A320/A321 Airworthiness Limitation Items, without exceeding 48,000 flight cycles or 96,000 flight hours, whichever occurs first since the airplane's first flight.
(iv) For Airbus A320 airplanes post-modification 160001: Within 39,200 flight cycles or 78,400 flight hours, whichever occurs first since the airplane's first flight.
(v) For Airbus A321 airplanes pre-modification 160021: Within 51,600 flight cycles or 103,200 flight hours, whichever occurs first since the airplane's first flight.
(vi) For Airbus A321 airplanes post-modification 160021: Within 51,200 flight cycles or 102,400 flight hours, whichever occurs first since the airplane's first flight.
For Airbus A320 airplanes having pre-modification 160001, that have exceeded 46,400 flight cycles or 92,800 flight hours, whichever occurred first since the airplane's first flight: If any crack is found during accomplishment of Task No. 534126-01-3, of the ALS Part 2, “Damage-Tolerant Airworthiness Limitation Items” of the Airbus A319/A320/A321 Airworthiness Limitation Items, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA.
(1) Modification of an airplane as required by paragraph (g)(1) of this AD, terminates the requirement for the task in the ALS Part 2, “Damage-Tolerant Airworthiness Limitation Items” of the Airbus A318/A319/A320/A321 Airworthiness Limitation Items for that airplane, as identified in paragraphs (i)(1)(i), (i)(1)(ii), (i)(1)(iii), (i)(1)(iv), (i)(1)(v), and (i)(1)(vi) of this AD, as applicable.
(i) For Airbus A319 airplanes pre-modification 160001: Task No. 534125-01-2.
(ii) For Airbus A319 airplanes post-modification 160001: Task No. 534125-01-5.
(iii) For Airbus A320 airplanes pre-modification 160001: Task No. 534125-01-3.
(iv) For Airbus A320 airplanes post-modification 160001: Task No. 534125-01-6.
(v) For Airbus A321 airplanes pre-modification 160021: Task No. 534125-01-4.
(vi) For Airbus A321 airplanes post-modification 160021: Task No. 534125-01-7.
(2) Modification of an airplane as required by paragraphs (g)(2) and (g)(3) of this AD, terminates the requirement for the task in the ALS Part 2, “Damage-Tolerant Airworthiness Limitation Items” of the Airbus A318/A319/A320/A321 Airworthiness Limitation Items for that airplane, as identified in paragraphs (i)(2)(i), (i)(2)(ii), (i)(2)(iii), (i)(2)(iv), (i)(2)(v), and (i)(2)(vi) of this AD, as applicable.
(i) For Airbus A319 airplanes pre-modification 160001: Task No. 534126-01-2.
(ii) For Airbus A319 airplanes post-modification 160001: Task No. 534126-01-5.
(iii) For Airbus A320 airplanes pre-modification 160001: Task No. 534126-01-3.
(iv) For Airbus A320 airplanes post-modification 160001: Task No. 534126-01-6.
(v) For Airbus A321 airplanes pre-modification 160021: Task No. 534126-01-4.
(vi) For Airbus A321 airplanes post-modification 160021: Task No. 534126-01-7.
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.
