Adoption of the Amendment
Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0 1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD):
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2015-15-13 Airbus: Amendment 39-18223. Docket No. FAA-2014-0652; Directorate Identifier 2014-NM-076-AD.
(a) Effective Date
This AD becomes effective September 8, 2015.
(b) Affected ADs
None.
(c) Applicability
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.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
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. 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.
(f) Compliance
Comply with this AD within the compliance times specified, unless already done.
(g) Modification
(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 doingall 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.
(h) Corrective Action
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.
(i) Terminating Action for ALS Task
(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, asapplicable.
(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.
(j) Credit for Previous Actions
(1) This paragraph provides credit for the actions required by paragraph (g)(1) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-53- 1272, dated January 10, 2013; or Airbus Service Bulletin A320-53- 1272, Revision 01, dated August 6, 2013; which are not incorporated by reference in this AD.
(2) This paragraph provides credit for the actions required by paragraph (g)(2) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-53- 1267, dated June 24, 2013; or Airbus Service Bulletin A320-53-1267, Revision 01, dated October 2, 2013; which are not incorporated by reference in this AD.
(k) Other FAA AD Provisions
The following provisions also apply to this AD:
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(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone 425-227-1405; fax 425-227-1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD.
(2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
(l) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0081, dated March 31, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA- 2014-0652-0003.
(2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (m)(3) and (m)(4) of this AD.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A320-53-1267, Revision 02, dated May 19, 2014.
(ii) Airbus Service Bulletin A320-53-1272, Revision 02, dated May 19, 2014.
(3) For service information identified in this AD, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com.
(4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221.
(5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.