Airworthiness Directives; Airbus Airplanes, 45857-45860 [2015-18564]

Download as PDF Federal Register / Vol. 80, No. 148 / Monday, August 3, 2015 / Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0652; Directorate Identifier 2014–NM–076–AD; Amendment 39–18223; AD 2015–15–13] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Discussion Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: 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. DATES: This AD becomes effective September 8, 2015. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of September 8, 2015. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0652 or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. 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.airwortheas@airbus.com; Internet https:// www.airbus.com. You may view this referenced 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. It is also available on the Internet at https://www.regulations.gov by mstockstill on DSK4VPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 16:06 Jul 31, 2015 Jkt 235001 searching for and locating Docket No. FAA–2014–0652. FOR FURTHER INFORMATION CONTACT: 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. SUPPLEMENTARY INFORMATION: We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus Model A319 series airplanes; Model A320–211, –212, –214, –231, –232, and –233 airplanes; and Model A321 series airplanes. The NPRM published in the Federal Register on October 1, 2014 (79 FR 59160). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2014–0081, dated March 31, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A319 series airplanes; Model A320–211, –212, –214, –231, –232, and –233 airplanes; and Model A321 series airplanes. The MCAI states: During the full scale fatigue test on A320– 200, it has been noticed that, due to fatigue, cracks could be initiated at the waste water service panel area and the potable water service panel area. This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. Prompted by these findings, ALS [airworthiness limitations section] Part 2 tasks have been introduced for the affected A320 family aeroplanes. Since those actions were taken, Airbus developed production mod 160055 and mod 160056 to embody reinforcements (cold working on certain rivet rows) of the potable water and waste water service panels, and published associated Airbus Service Bulletin (SB) A320–53–1272 (retrofit mod 153074) and SB A320–53–1267 (retrofit mod 153073) for in-service embodiment. Following complementary Design Office studies, it appears that the Sharklet installations on certain aeroplanes have a significant impact on the aeroplane structure (particularly, A319 and A320 post-mod 160001, and A321 post-mod 160021), leading to different compliance times, depending on aeroplane configuration. For the reasons described above, this [EASA] AD requires reinforcement of the potable water and waste water service panels. Accomplishment of these modifications cancels the need for the related ALS Part 2 Tasks. PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 45857 The modification includes doing applicable related investigative and corrective actions. Related investigative actions include measuring the diameter of a hole of a fastener and doing a rotating probe inspection. Corrective actions include repairs. You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov/ #!documentDetail;D=FAA-2014-06520003. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (79 FR 59160, October 1, 2014) and the FAA’s response to each comment. Request To Include Latest Service Information United Airlines (UAL) and Airbus requested that we revise the NPRM (79 FR 59160, October 1, 2014) to include the latest service information. UAL explained that Airbus Service Bulletin A320–53–1267, Revision 02, dated May 19, 2014, has similar modification requirements to those specified in Airbus Service Bulletin A320–53–1267, Revision 01, dated October 2, 2013, but also has updates including two new airplane configurations, which update compliance times corresponding to the times listed in paragraph (g)(2) of the NPRM. Airbus stated that Airbus Service Bulletin A320–53–1267, Revision 02, dated May 19, 2014, updates the effectivity and compliance times in the service information. We agree to include Airbus Service Bulletin A320–53–1267, Revision 02, dated May 19, 2014, in this AD. Airbus Service Bulletin A320–53–1267, Revision 02, dated May 19, 2014, was issued to provide updated compliance times and effectivity. Airbus Service Bulletin A320–53–1267, Revision 02, dated May 19, 2014, does not add additional requirements for AD compliance times. Also, we have added Airbus Service Bulletin A320–53–1267, Revision 01, dated October 2, 2013, to paragraph (j)(2) of this AD to offer credit for the corresponding actions performed before the effective date of this AD. Request To Omit Paragraph (h) of the NPRM (79 FR 59160, October 1, 2014) UAL requested that we revise the NPRM (79 FR 59160, October 1, 2014) to omit paragraph (h) of the proposed AD. UAL explained that Task 534126– 01–3, of the Airworthiness Limitation Section (ALS) Part 2, ‘‘Damage-Tolerant Airworthiness Limitation Items’’ of the E:\FR\FM\03AUR1.SGM 03AUR1 mstockstill on DSK4VPTVN1PROD with RULES 45858 Federal Register / Vol. 80, No. 148 / Monday, August 3, 2015 / Rules and Regulations Airbus A319/A320/A321 Airworthiness Limitation Items is addressed separately in other rulemaking, NPRM Docket No. FAA–2013–0692, Directorate Identifier 2012–NM–024–AD (78 FR 49213, August 13, 2013), and that NPRM contains the instructions for the corrective actions in paragraph (o)(2) of that NPRM. UAL concluded that paragraph (h) of the NPRM (79 FR 59160, October 1, 2014), which specifies corrective actions for Task 534126–01– 3, might cause confusion. UAL also suggested that, as an alternative to omitting paragraph (h) of NPRM (79 FR 59160, October 1, 2014), paragraph (h) of the NPRM could be revised so that the Task 534126–01–3 requirement refers to the other rulemaking, NPRM Docket No. FAA–2013–0692, Directorate Identifier 2012–NM–024–AD (78 FR 49213, August 13, 2013), which has since been issued as AD 2014–23–15, Amendment 39–18031 (80 FR 3871, January 26, 2015). (AD 2014–23–15 has since been superseded by AD 2015–05– 02, Amendment 39–18112 (80 FR 15152, March 23, 2015)). We disagree to omit or revise paragraph (h) of this AD. Paragraph (h) of this AD is not a duplicated action. Paragraph (h) of this AD specifies that for Airbus A320 airplanes having premodification 160001, that have exceeded 46,400 flight cycles or 92,800 flight hours, whichever occurred first since the airplane’s first flight, operators must repair cracks found during accomplishment of Task 534126–01–3, 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. This specific condition and corrective action is not included in paragraph (p)(2) of AD 2015–05–02, Amendment 39–18112 (80 FR 15152, March 23, 2015, which corresponds to paragraph (o)(2) of NPRM Docket No. FAA–2013–0692, Directorate Identifier 2012–NM–024–AD (78 FR 49213, August 13, 2013). AD 2015–05–02, does not mandate corrective actions associated with Task 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, but instead mandates incorporation of that task into operators’ maintenance or inspection programs. We have made no changes to this AD in this regard. Conclusion We reviewed the relevant data, considered the comments received, and VerDate Sep<11>2014 16:06 Jul 31, 2015 Jkt 235001 determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (79 FR 59160, October 1, 2014) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 59160, October 1, 2014). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 Airbus has issued Airbus Service Bulletin A320–53–1267, Revision 02, dated May 19, 2014; and Airbus Service Bulletin A320–53–1272, Revision 02, dated May 19, 2014. The service information describes procedures for a modification, which includes measuring the diameter of a hole of a fastener and doing a rotating probe inspection, and repairs if necessary. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this AD. Costs of Compliance We estimate that this AD affects 851 airplanes of U.S. registry. We also estimate that it will take about 25 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $420 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $2,165,795, or $2,545 per product. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0652; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ E:\FR\FM\03AUR1.SGM 03AUR1 Federal Register / Vol. 80, No. 148 / Monday, August 3, 2015 / Rules and Regulations 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. mstockstill on DSK4VPTVN1PROD with RULES (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 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 premodification 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 postmodification 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 premodification 160001: Within 54,200 flight VerDate Sep<11>2014 16:06 Jul 31, 2015 Jkt 235001 cycles or 108,400 flight hours, whichever occurs first since the airplane’s first flight. (iv) For Model A320 airplanes postmodification 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 premodification 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 postmodification 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 premodification 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 postmodification 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 premodification 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 postmodification 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 premodification 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 PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 45859 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, as applicable. (i) For Airbus A319 airplanes premodification 160001: Task No. 534125–01–2. (ii) For Airbus A319 airplanes postmodification 160001: Task No. 534125–01–5. (iii) For Airbus A320 airplanes premodification 160001: Task No. 534125–01–3. (iv) For Airbus A320 airplanes postmodification 160001: Task No. 534125–01–6. (v) For Airbus A321 airplanes premodification 160021: Task No. 534125–01–4. (vi) For Airbus A321 airplanes postmodification 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 premodification 160001: Task No. 534126–01–2. (ii) For Airbus A319 airplanes postmodification 160001: Task No. 534126–01–5. (iii) For Airbus A320 airplanes premodification 160001: Task No. 534126–01–3. (iv) For Airbus A320 airplanes postmodification 160001: Task No. 534126–01–6. (v) For Airbus A321 airplanes premodification 160021: Task No. 534126–01–4. (vi) For Airbus A321 airplanes postmodification 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: E:\FR\FM\03AUR1.SGM 03AUR1 45860 Federal Register / Vol. 80, No. 148 / Monday, August 3, 2015 / Rules and Regulations (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-116AMOC-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. mstockstill on DSK4VPTVN1PROD with RULES (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 https://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 https://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 VerDate Sep<11>2014 17:58 Jul 31, 2015 Jkt 235001 the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. DEPARTMENT OF TRANSPORTATION 2. The FAA Air Traffic Organization Service Area in which the affected airport is located; 3. The office of Aeronautical Navigation Products, 6500 South MacArthur Blvd., Oklahoma City, OK 73169 or, 4. The National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/ federal_register/code_of_federal_ regulations/ibr_locations.html. Federal Aviation Administration Availability Issued in Renton, Washington, on July 22, 2015. Victor Wicklund, Acting Manager,Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–18564 Filed 7–31–15; 8:45 am] BILLING CODE 4910–13–P 14 CFR Part 97 [Docket No. 31028; Amdt. No. 3653] Standard Instrument Approach Procedures, and Takeoff Minimums and Obstacle Departure Procedures; Miscellaneous Amendments Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: This rule establishes, amends, suspends, or removes Standard Instrument Approach Procedures (SIAPs) and associated Takeoff Minimums and Obstacle Departure Procedures (ODPs) for operations at certain airports. These regulatory actions are needed because of the adoption of new or revised criteria, or because of changes occurring in the National Airspace System, such as the commissioning of new navigational facilities, adding new obstacles, or changing air traffic requirements. These changes are designed to provide safe and efficient use of the navigable airspace and to promote safe flight operations under instrument flight rules at the affected airports. DATES: This rule is effective August 3, 2015. The compliance date for each SIAP, associated Takeoff Minimums, and ODP is specified in the amendatory provisions. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of August 3, 2015. ADDRESSES: Availability of matters incorporated by reference in the amendment is as follows: SUMMARY: For Examination 1. U.S. Department of Transportation, Docket Ops-M30, 1200 New Jersey Avenue SE., West Bldg., Ground Floor, Washington, DC 20590–0001. PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 All SIAPs and Takeoff Minimums and ODPs are available online free of charge. Visit the National Flight Data Center at nfdc.faa.gov to register. Additionally, individual SIAP and Takeoff Minimums and ODP copies may be obtained from the FAA Air Traffic Organization Service Area in which the affected airport is located. FOR FURTHER INFORMATION CONTACT: Richard A. Dunham III, Flight Procedure Standards Branch (AFS–420), Flight Technologies and Programs Divisions, Flight Standards Service, Federal Aviation Administration, Mike Monroney Aeronautical Center, 6500 South MacArthur Blvd., Oklahoma City, OK 73169 (Mail Address: P.O. Box 25082, Oklahoma City, OK 73125) Telephone: (405) 954–4164. SUPPLEMENTARY INFORMATION: This rule amends Title 14 of the Code of Federal Regulations, Part 97 (14 CFR part 97), by establishing, amending, suspending, or removes SIAPS, Takeoff Minimums and/or ODPS. The complete regulatory description of each SIAP and its associated Takeoff Minimums or ODP for an identified airport is listed on FAA form documents which are incorporated by reference in this amendment under 5 U.S.C. 552(a), 1 CFR part 51, and 14 CFR part § 97.20. The applicable FAA forms are FAA Forms 8260–3, 8260–4, 8260–5, 8260–15A, and 8260–15B when required by an entry on 8260–15A. The large number of SIAPs, Takeoff Minimums and ODPs, their complex nature, and the need for a special format make publication in the Federal Register expensive and impractical. Further, airmen do not use the regulatory text of the SIAPs, Takeoff Minimums or ODPs, but instead refer to their graphic depiction on charts printed by publishers of aeronautical materials. Thus, the advantages of incorporation by reference are realized and publication of the complete description of each SIAP, Takeoff Minimums and ODP listed on FAA form documents is unnecessary. This E:\FR\FM\03AUR1.SGM 03AUR1

Agencies

[Federal Register Volume 80, Number 148 (Monday, August 3, 2015)]
[Rules and Regulations]
[Pages 45857-45860]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-18564]



[[Page 45857]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0652; Directorate Identifier 2014-NM-076-AD; 
Amendment 39-18223; AD 2015-15-13]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: 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.

DATES: This AD becomes effective September 8, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of September 8, 
2015.

ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0652 or in person at the 
Docket Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC.
    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 https://www.airbus.com. You may view this referenced 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. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0652.

FOR FURTHER INFORMATION CONTACT: 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.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain Airbus Model A319 
series airplanes; Model A320-211, -212, -214, -231, -232, and -233 
airplanes; and Model A321 series airplanes. The NPRM published in the 
Federal Register on October 1, 2014 (79 FR 59160).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2014-0081, dated March 31, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233 
airplanes; and Model A321 series airplanes. The MCAI states:

    During the full scale fatigue test on A320-200, it has been 
noticed that, due to fatigue, cracks could be initiated at the waste 
water service panel area and the potable water service panel area.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    Prompted by these findings, ALS [airworthiness limitations 
section] Part 2 tasks have been introduced for the affected A320 
family aeroplanes. Since those actions were taken, Airbus developed 
production mod 160055 and mod 160056 to embody reinforcements (cold 
working on certain rivet rows) of the potable water and waste water 
service panels, and published associated Airbus Service Bulletin 
(SB) A320-53-1272 (retrofit mod 153074) and SB A320-53-1267 
(retrofit mod 153073) for in-service embodiment.
    Following complementary Design Office studies, it appears that 
the Sharklet installations on certain aeroplanes have a significant 
impact on the aeroplane structure (particularly, A319 and A320 post-
mod 160001, and A321 post-mod 160021), leading to different 
compliance times, depending on aeroplane configuration.
    For the reasons described above, this [EASA] AD requires 
reinforcement of the potable water and waste water service panels. 
Accomplishment of these modifications cancels the need for the 
related ALS Part 2 Tasks.

    The modification includes doing applicable related investigative 
and corrective actions. Related investigative actions include measuring 
the diameter of a hole of a fastener and doing a rotating probe 
inspection. Corrective actions include repairs. You may examine the 
MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0652-0003.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (79 
FR 59160, October 1, 2014) and the FAA's response to each comment.

Request To Include Latest Service Information

    United Airlines (UAL) and Airbus requested that we revise the NPRM 
(79 FR 59160, October 1, 2014) to include the latest service 
information. UAL explained that Airbus Service Bulletin A320-53-1267, 
Revision 02, dated May 19, 2014, has similar modification requirements 
to those specified in Airbus Service Bulletin A320-53-1267, Revision 
01, dated October 2, 2013, but also has updates including two new 
airplane configurations, which update compliance times corresponding to 
the times listed in paragraph (g)(2) of the NPRM. Airbus stated that 
Airbus Service Bulletin A320-53-1267, Revision 02, dated May 19, 2014, 
updates the effectivity and compliance times in the service 
information.
    We agree to include Airbus Service Bulletin A320-53-1267, Revision 
02, dated May 19, 2014, in this AD. Airbus Service Bulletin A320-53-
1267, Revision 02, dated May 19, 2014, was issued to provide updated 
compliance times and effectivity. Airbus Service Bulletin A320-53-1267, 
Revision 02, dated May 19, 2014, does not add additional requirements 
for AD compliance times.
    Also, we have added Airbus Service Bulletin A320-53-1267, Revision 
01, dated October 2, 2013, to paragraph (j)(2) of this AD to offer 
credit for the corresponding actions performed before the effective 
date of this AD.

Request To Omit Paragraph (h) of the NPRM (79 FR 59160, October 1, 
2014)

    UAL requested that we revise the NPRM (79 FR 59160, October 1, 
2014) to omit paragraph (h) of the proposed AD. UAL explained that Task 
534126-01-3, of the Airworthiness Limitation Section (ALS) Part 2, 
``Damage-Tolerant Airworthiness Limitation Items'' of the

[[Page 45858]]

Airbus A319/A320/A321 Airworthiness Limitation Items is addressed 
separately in other rulemaking, NPRM Docket No. FAA-2013-0692, 
Directorate Identifier 2012-NM-024-AD (78 FR 49213, August 13, 2013), 
and that NPRM contains the instructions for the corrective actions in 
paragraph (o)(2) of that NPRM. UAL concluded that paragraph (h) of the 
NPRM (79 FR 59160, October 1, 2014), which specifies corrective actions 
for Task 534126-01-3, might cause confusion. UAL also suggested that, 
as an alternative to omitting paragraph (h) of NPRM (79 FR 59160, 
October 1, 2014), paragraph (h) of the NPRM could be revised so that 
the Task 534126-01-3 requirement refers to the other rulemaking, NPRM 
Docket No. FAA-2013-0692, Directorate Identifier 2012-NM-024-AD (78 FR 
49213, August 13, 2013), which has since been issued as AD 2014-23-15, 
Amendment 39-18031 (80 FR 3871, January 26, 2015). (AD 2014-23-15 has 
since been superseded by AD 2015-05-02, Amendment 39-18112 (80 FR 
15152, March 23, 2015)).
    We disagree to omit or revise paragraph (h) of this AD. Paragraph 
(h) of this AD is not a duplicated action. Paragraph (h) of this AD 
specifies that 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, operators 
must repair cracks found during accomplishment of Task 534126-01-3, 
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. This 
specific condition and corrective action is not included in paragraph 
(p)(2) of AD 2015-05-02, Amendment 39-18112 (80 FR 15152, March 23, 
2015, which corresponds to paragraph (o)(2) of NPRM Docket No. FAA-
2013-0692, Directorate Identifier 2012-NM-024-AD (78 FR 49213, August 
13, 2013). AD 2015-05-02, does not mandate corrective actions 
associated with Task 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, 
but instead mandates incorporation of that task into operators' 
maintenance or inspection programs. We have made no changes to this AD 
in this regard.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (79 FR 59160, October 1, 2014) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 59160, October 1, 2014).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Airbus Service Bulletin A320-53-1267, Revision 
02, dated May 19, 2014; and Airbus Service Bulletin A320-53-1272, 
Revision 02, dated May 19, 2014. The service information describes 
procedures for a modification, which includes measuring the diameter of 
a hole of a fastener and doing a rotating probe inspection, and repairs 
if necessary. This service information is reasonably available because 
the interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section of this 
AD.

Costs of Compliance

    We estimate that this AD affects 851 airplanes of U.S. registry.
    We also estimate that it will take about 25 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Required parts will cost about $420 per 
product. Based on these figures, we estimate the cost of this AD on 
U.S. operators to be $2,165,795, or $2,545 per product.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0652; or in person at the 
Docket Management Facility between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The AD docket contains this AD, the 
regulatory evaluation, any comments received, and other information. 
The street address for the Docket Operations office (telephone 800-647-
5527) is in the ADDRESSES section.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

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):


[[Page 45859]]


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 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.

(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, 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.

(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:

[[Page 45860]]

    (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 https://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 https://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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on July 22, 2015.
Victor Wicklund,
Acting Manager,Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-18564 Filed 7-31-15; 8:45 am]
 BILLING CODE 4910-13-P

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