Airworthiness Directives; Airbus Airplanes, 3871-3876 [2015-01257]

Download as PDF Federal Register / Vol. 80, No. 16 / Monday, January 26, 2015 / Rules and Regulations agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. (h) Related Information Refer to MCAI Federal Office of Civil Aviation (FOCA) AD HB–2014–001, dated July 25, 2014; and AD HB–2014–001R1, dated November 5, 2014 for related information. The MCAI can be found in the AD docket on the Internet at: http:// www.regulations.gov/ #!docketBrowser;rpp=25;po=0;dct=PR%25 2BSR;D=FAA-2014-0770. tkelley on DSK3SPTVN1PROD with RULES (i) 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 the AD specifies otherwise. (i) Pilatus Aircraft Ltd. Pilatus PC–7 Service Bulletin No: 51–001, Revision No. 1, dated August 26, 2014. (ii) Reserved. (3) For Pilatus Aircraft Ltd. service information identified in this AD, contact Pilatus Aircraft Ltd., Customer Technical Support (MCC), P.O. Box 992, CH–6371 Stans, Switzerland; phone: +41 (0)41 619 67 74; fax: +41 (0)41 619 67 73; email: Techsupport@pilatus-aircraft.com; internet: http://www.pilatus-aircraft.com. (4) You may view this service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. (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/ibrlocations.html. Issued in Kansas City, Missouri, on December 31, 2014. Robert Busto, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–00010 Filed 1–23–15; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 17:58 Jan 23, 2015 Jkt 235001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0692; Directorate Identifier 2012–NM–024–AD; Amendment 39–18031; AD 2014–23–15] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) AD 2011– 14–06 for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2011–14–06 required revising the maintenance program. This new AD requires revising the maintenance program to incorporate new, more restrictive limitations. This AD was prompted by the determination that more restrictive limitations are necessary. We are issuing this AD to prevent fatigue cracking, accidental damage, or corrosion in principal structural elements, and possible failure of certain life limited parts, which could result in reduced structural integrity of the airplane. DATES: This AD becomes effective March 2, 2015. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of March 2, 2015. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of August 22, 2011 (76 FR 42024, July 18, 2011). The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of November 7, 2007 (72 FR 56262, October 3, 2007). ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2013-0692; 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.airworthSUMMARY: PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 3871 eas@airbus.com; Internet http:// 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. 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 supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 to supersede AD 2011–14–06, Amendment 39–16741 (76 FR 42024, July 18, 2011). AD 2011–14– 06 applied to Airbus Model A318, A319, A320, and A321 series airplanes. The SNPRM published in the Federal Register on May 28, 2014 (79 FR 30492). We preceded the SNPRM with a notice of proposed rulemaking (NPRM) that published in the Federal Register on August 13, 2013 (78 FR 49213). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2013–0147, dated July 16, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A318, A319, A320, and A321 series airplanes. The MCAI states: The airworthiness limitations for Airbus A320 family aeroplanes are currently included in Airbus A318/A319/A320/A321 Airworthiness Limitations Section (ALS) document. The airworthiness limitations applicable to the Damage Tolerant Airworthiness Limitation Items (DT ALI) are currently given in Airbus ALS Part 2, which is approved by EASA. Previously, EASA issued AD 2010–0071R1 [http://ad.easa.europa.eu/blob/easa_ad_ 2010_0071_R1.pdf/AD_2010–0071R1_1] [associated with FAA AD 2011–14–06, Amendment 39–16741 (76 FR 42024, July 18, 2011)], which required the implementation of the DT ALI maintenance instructions as specified in Airbus A318/A319/A320/A321 ALI Document ref. AI/SE–M4/95A.0252/96 issue 10 and Airbus A319 Corporate Jet ALI Document ref. AI/SE–M2/95A.1038/99. The new Airbus A318/A319/A320/A321 ALS Part 2 Revision 02, which includes also Airbus A319 Corporate Jet, introduces more restrictive DT ALI maintenance instructions. Failure to comply with these instructions could result in an unsafe condition. Application of new DT ALI tasks 531129– 02–2 and 531129–02–3 introduces initial and E:\FR\FM\26JAR1.SGM 26JAR1 3872 Federal Register / Vol. 80, No. 16 / Monday, January 26, 2015 / Rules and Regulations repetitive inspections of the windshield central lower node continuity fittings, replacing the one time inspection for that subject, previously required by EASA AD 2011–0231 [http://ad.easa.europa.eu/blob/ easa_ad_2011_0231.pdf] [associated with FAA AD 2013–13–03, Amendment 39–17491 (78 FR 41280, July 10, 2013)]. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2010–0071R1 * * *, which are superseded, and requires compliance with all maintenance tasks as described in Airbus A318/A319/A320/A321 ALS part 2 at Revision 02. The unsafe condition is fatigue cracking, accidental damage, or corrosion in principal structural elements, and possible failure of certain life limited parts, which could result in reduced structural integrity of the airplane. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2013-0002. tkelley on DSK3SPTVN1PROD with RULES Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the SNPRM (79 FR 30492, May 28, 2014) and the FAA’s response to each comment. Request To Extend Compliance Time United Airlines (UAL), Delta Airlines (DAL), and Virgin America asked that we extend the compliance time for incorporation of Airbus A318/A319/ A320/A321 ALS Part 2—DamageTolerant Airworthiness Limitation Items (DT ALI), Revision 02, dated May 28, 2013. UAL stated that it would like to manage the task incorporation on an individual basis. UAL proposed that we revise the compliance times specified in paragraph (n) of the SNPRM (79 FR 30492, May 28, 2014) as follows: ‘‘After the effective date of this AD, incorporate each task into the program within the specific threshold/interval provided.’’ DAL and Virgin America stated that, to provide time to revise the maintenance program and perform any related tasks that might exceed the compliance thresholds specified in the ALI, the grace period specified in paragraph (n) of the SNPRM should be changed from 4 to 12 months. DAL asked for more time to update the maintenance program to incorporate Airbus A318/A319/A320/A321 ALS Part 2—Damage-Tolerant Airworthiness Limitation Items (DT ALI), Revision 02, dated May 28, 2013. DAL and Virgin America requested 9 months, as opposed to 30 days, because 9 months was the allowed compliance time for incorporating airworthiness limitation items into the maintenance program VerDate Sep<11>2014 17:58 Jan 23, 2015 Jkt 235001 required by AD 2011–14–06, Amendment 39–16741 (76 FR 42024, July 18, 2011). We acknowledge the commenters’ concerns; however, we do not agree to extend the compliance times for incorporation of the tasks into the maintenance program. We based the compliance times in this AD primarily on our assessment of the safety risk. Since some safety issues are more timesensitive than others, we consider the overall risk to the fleet, including the severity of the failure and the likelihood of the occurrence of the failure. In this case, the primary reason for requiring incorporation of Airbus A318/A319/ A320/A321 ALS Part 2—DamageTolerant Airworthiness Limitation Items (DT ALI), Revision 02, dated May 28, 2013, is to cover extension of the design service goal and preliminary results from widespread fatigue damage. Therefore, we do not agree to extend the grace period or compliance times for incorporation of the tasks into the maintenance program. However, under the provisions of paragraph (p)(1) of this AD, we will consider requests for approval of extending the compliance time based on the current status of the maintenance and inspection programs relative to the ALI tasks if sufficient data are submitted to substantiate that it would provide an acceptable level of safety. We have not changed this AD in this regard. ‘‘Contacting the Manufacturer’’ Paragraph in This AD Since late 2006, we have included a standard paragraph titled ‘‘Airworthy Product’’ in all MCAI ADs in which the FAA develops an AD based on a foreign authority’s AD. We have become aware that some operators have misunderstood or misinterpreted the Airworthy Product paragraph to allow the owner/operator to use messages provided by the manufacturer as approval of deviations during the accomplishment of an ADmandated action. The Airworthy Product paragraph does not approve messages or other information provided by the manufacturer for deviations to the requirements of the AD-mandated actions. The Airworthy Product paragraph only addresses the requirement to contact the manufacturer for corrective actions for the identified unsafe condition and does not cover deviations from other AD requirements. However, deviations to AD-required actions are addressed in 14 CFR 39.17, and anyone may request the approval for an alternative method of compliance to the AD-required actions using the procedures found in 14 CFR 39.19. PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 To address this misunderstanding and misinterpretation of the Airworthy Product paragraph, we have changed the paragraph and retitled it ‘‘Contacting the Manufacturer.’’ This paragraph now clarifies that for any requirement in this AD to obtain corrective actions from a manufacturer, the actions must be accomplished using a method approved by the FAA, the European Aviation Safety Agency (EASA), or Airbus’s EASA Design Organization Approval (DOA). The Contacting the Manufacturer paragraph also clarifies that, if approved by the DOA, the approval must include the DOA-authorized signature. The DOA signature indicates that the data and information contained in the document are EASA-approved, which is also FAAapproved. Messages and other information provided by the manufacturer that do not contain the DOA-authorized signature approval are not EASA-approved, unless EASA directly approves the manufacturer’s message or other information. This clarification does not remove flexibility previously afforded by the Airworthy Product paragraph. Consistent with long-standing FAA policy, such flexibility was never intended for required actions. This is also consistent with the recommendation of the Airworthiness Directive Implementation Aviation Rulemaking Committee to increase flexibility in complying with ADs by identifying those actions in manufacturers’ service instructions that are ‘‘Required for Compliance’’ with ADs. We continue to work with manufacturers to implement this recommendation. But once we determine that an action is required, any deviation from the requirement must be approved as an alternative method of compliance. We also have decided not to include a generic reference to either the ‘‘delegated agent’’ or ‘‘design approval holder (DAH) with State of Design Authority design organization approval,’’ but instead we have provided the specific delegation approval granted by the State of Design Authority for the DAH. 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 SNPRM (79 FR E:\FR\FM\26JAR1.SGM 26JAR1 Federal Register / Vol. 80, No. 16 / Monday, January 26, 2015 / Rules and Regulations 30492, May 28, 2014) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the SNPRM (79 FR 30492, May 28, 2014). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Costs of Compliance We estimate that this AD affects 851 airplanes of U.S. registry. The actions required by AD 2011–14– 06, Amendment 39–16741 (76 FR 42024, July 18, 2011), and retained in this AD take about 1 work-hour per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the required actions is $85 per product. We also estimate that it will take about 1 work-hour per product to comply with the new basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $72,335, or $85 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. tkelley on DSK3SPTVN1PROD with RULES 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: VerDate Sep<11>2014 17:58 Jan 23, 2015 Jkt 235001 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 http:// www.regulations.gov/ #!docketDetail;D=FAA-2013-0692; 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 removing Airworthiness Directive (AD) 2011–14–06, Amendment 39–16741 (76 FR 42024, July 18, 2011), and adding the following new AD: ■ 2014–23–15 Airbus: Amendment 39–18031. Docket No. FAA–2013–0692; Directorate Identifier 2012–NM–024–AD. (a) Effective Date This AD becomes effective March 2, 2015. (b) Affected ADs This AD replaces AD 2011–14–06, Amendment 39–16741 (76 FR 42024, July 18, 2011). (c) Applicability This AD applies to all Airbus Model A318– 111, –112, –121, and –122 airplanes; Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–111, PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 3873 –211, –212, –214, –231, –232, and –233 airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 05, Periodic Inspections. (e) Reason This AD was prompted by a determination that more restrictive limitations are necessary. We are issuing this AD to prevent fatigue cracking, accidental damage, or corrosion in principal structural elements, and possible failure of certain life limited parts, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Revision of Airworthiness Limitations Section (ALS) To Incorporate Safe Life Airworthiness Limitation Items (ALIs) This paragraph restates the requirements of paragraph (g) of AD 2011–14–06, Amendment 39–16741 (76 FR 42024, July 18, 2011). For Model A318–111 and –112 airplanes; Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–111, –211, –212, –214, –231, –232, and –233 airplanes; and Model A321– 111, –112, –131, –211, –212, –213, –231, and –232 airplanes: Within 3 months after November 7, 2007 (the effective date of AD 2007–20–05, Amendment 39–15215 (72 FR 56262, October 3, 2007)), revise the ALS of the Instructions for Continued Airworthiness to incorporate Sub-part 1–2, ‘‘Life Limits,’’ and Sub-part 1–3, ‘‘Demonstrated Fatigue Lives,’’ of Airbus A318/A319/A320/A321 ALS Part 1—Safe Life Airworthiness Limitation Items, Revision 00, dated February 28, 2006. Accomplish the actions in Sub-part 1–2, ‘‘Life Limits,’’ and Sub-part 1– 3, ‘‘Demonstrated Fatigue Lives,’’ of Airbus A318/A319/A320/A321 ALS Part 1—Safe Life Airworthiness Limitation Items, Revision 00, dated February 28, 2006, at the times specified in Sub-part 1–2, ‘‘Life Limits,’’ and Sub-part 1–3, ‘‘Demonstrated Fatigue Lives,’’ of Airbus A318/A319/A320/ A321 ALS Part 1—Safe Life Airworthiness Limitation Items, dated February 28, 2006, except as provided by paragraph (i) of this AD. Accomplishing the actions required by paragraph (j) of this AD terminates the requirements of this paragraph. (h) Retained Revision to ALS To Incorporate Damage Tolerant ALIs This paragraph restates certain provisions of paragraph (h) of AD 2011–14–06, Amendment 39–16741 (76 FR 42024, July 18, 2011). For Model A318–111 and –112 airplanes; Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–111, –211, –212, –214, –231, –232, and –233 airplanes; and Model A321– 111, –112, –131, –211, –212, –213, –231, and –232 airplanes; except Model A319 airplanes on which Airbus Modifications 28238, 28162, and 28342 have been incorporated in production: Within 14 days after November E:\FR\FM\26JAR1.SGM 26JAR1 3874 Federal Register / Vol. 80, No. 16 / Monday, January 26, 2015 / Rules and Regulations 7, 2007 (the effective date of AD 2007–20–05, Amendment 39–15215 (72 FR 56262, October 3, 2007)), revise the ALS of the Instructions for Continued Airworthiness to incorporate Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE–M4/95A.0252/96, Issue 7, dated December 2005 (approved by the European Aviation Safety Agency (EASA) on February 7, 2006); Issue 08, dated March 2006 (approved by the EASA on January 4, 2007); or Issue 09, dated November 2006 (approved by the EASA on May 21, 2007). Accomplish the actions in Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE–M4/95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March 2006; or Issue 09, dated November 2006; at the times specified in Airbus A318/A319/A320/ A321 Airworthiness Limitation Items, Document AI/SE–M4/95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March 2006; or Issue 09, dated November 2006; as applicable; except as provided by paragraph (i) of this AD. Accomplishing the actions required by paragraph (j) or (n) of this AD, as applicable, terminates the requirements of this paragraph. (i) Retained Grace Period for New or More Restrictive Actions This paragraph restates certain provisions of paragraph (i) of AD 2011–14–06, Amendment 39–16741 (76 FR 42024, July 18, 2011). For Model A318–111 and –112 airplanes; Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–111, –211, –212, –214, –231, –232, and –233 airplanes; and Model A321– 111, –112, –131, –211, –212, –213, –231, and –232 airplanes: For any new or more restrictive life-limit introduced with Sub-part 1–2, ‘‘Life Limits,’’ and Sub-part 1–3, ‘‘Demonstrated Fatigue Lives,’’ of Airbus A318/A319/A320/A321 ALS Part 1—Safe Life Airworthiness Limitation Items, Revision 00, dated February 28, 2006, replace the part at the time specified in Sub-part 1– 2, ‘‘Life Limits,’’ and Sub-part 1–3, ‘‘Demonstrated Fatigue Lives,’’ of Airbus A318/A319/A320/A321 ALS Part 1—Safe Life Airworthiness Limitation Items, Revision 00, dated February 28, 2006, or within 6 months after November 7, 2007 (the effective date of AD 2007–20–05, Amendment 39–15215 (72 FR 56262, October 3, 2007)), whichever is later. Accomplishing the actions required by paragraph (n) of this AD terminates the requirements of this paragraph. (j) Retained Revision of ALS To Incorporate Damage-Tolerant ALIs With Revised Compliance Times This paragraph restates the requirements of paragraph (j) of AD 2011–14–06, Amendment 39–16741 (76 FR 42024, July 18, 2011), with revised compliance times. Within 9 months after August 22, 2011 (the effective date of AD 2011–14–06): Revise the maintenance program by incorporating all maintenance requirements and associated airworthiness limitations specified in the Airbus A318/ A319/A320/A321 Airworthiness Limitation Items, Document AI/SE–M4/95A.0252/96, Issue 10, dated October 2009; or Issue 11, dated September 2010. Comply with all applicable maintenance requirements and associated airworthiness limitations included in Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE–M4/95A.0252/96, Issue 10, dated October 2009; or Issue 11, dated September 2010; except as provided by paragraph (k) of this AD. Accomplishing the actions required by this paragraph terminates the requirements of paragraph (h) of this AD. Accomplishing the actions required by paragraph (n) of this AD terminates the requirements of this paragraph. (k) Retained Special Compliance Times for Certain Tasks This paragraph restates the requirements of paragraph (k) of AD 2011–14–06, Amendment 39–16741 (76 FR 42024, July 18, 2011), with changes to table 1 to paragraph (k) of this AD. For new and more restrictive tasks introduced with Airbus A318/A319/ A320/A321 Airworthiness Limitation Items, Document AI/SE–M4/95A.0252/96, Issue 10, dated October 2009; or Issue 11, dated September 2010; as specified in table 1 to paragraph (k) of this AD: The initial compliance time for doing the tasks is specified in table 1 to paragraph (k) of this AD. Accomplishing the actions required by paragraph (n) of this AD terminates the requirements of this paragraph. TABLE 1 TO PARAGRAPH (K) OF THIS AD—COMPLIANCE TIMES FOR TASKS Applicability (as specified in the applicability column of the task) 545102–01–6 .......... Group 19–1A CFM, Group 19–1B CFM, and Model A320-200 airplanes with CFM Industrial (CFM)/International Aero Engine (IAE) engines. 545102–01–7 .......... Model A320–100 series airplanes ....... 572050–01–1 or alternative task 572050-02–1. tkelley on DSK3SPTVN1PROD with RULES Task Group 19-1A and Group 19–1B airplanes. 572050–01–4 or alternative task 572050-02–4. Model A320–200 series airplanes ....... VerDate Sep<11>2014 17:58 Jan 23, 2015 Jkt 235001 PO 00000 Frm 00010 Compliance time, whichever occurs later The threshold as defined in Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/ SE-M4/95A.0252/96, Issue 10, dated October 2009; or Issue 11, dated September 2010. The threshold as defined in Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/ SE-M4/95A.0252/96, Issue 10, dated October 2009; or Issue 11, dated September 2010. At the time of the next due accomplishment of any one of the tasks 572004, 572020, or 572053 as currently described in the Airbus A318/ A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/ 95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March 2006; or Issue 09, dated November 2006. At the time of the next due accomplishment of any one of the tasks 572004, 572020, or 572053 as currently described in the Airbus A318/ A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/ 95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March 2006; or Issue 09, dated November 2006. Fmt 4700 Sfmt 4700 E:\FR\FM\26JAR1.SGM Within 2,000 flight cycles or 5,500 flight hours, after August 22, 2011 (the effective date of AD 2011–14– 06, Amendment 39–16741 (76 FR 42024, July 18, 2011)), whichever occurs first. Within 2,000 flight cycles or 2,000 flight hours, after August 22, 2011 (the effective date of AD 2011–14– 06, Amendment 39–16741 (76 FR 42024, July 18, 2011)), whichever occurs first. Within 6 months after August 22, 2011 (the effective date of AD 2011–14– 06, Amendment 39–16741 (76 FR 42024, July 18, 2011)). Within 6 months after August 22, 2011 (the effective date of AD 2011–14– 06, Amendment 39–16741 (76 FR 42024, July 18, 2011)). 26JAR1 Federal Register / Vol. 80, No. 16 / Monday, January 26, 2015 / Rules and Regulations 3875 TABLE 1 TO PARAGRAPH (K) OF THIS AD—COMPLIANCE TIMES FOR TASKS—Continued Task 572050–01–5 or alternative task 572050-02–5. Group 21-1A airplanes ......................... 572050–01–7 or alternative task 572050-02–7. Model A320–100 series airplanes ....... 534132–01–1 .......... Model A320 PRE 30748 airplanes ...... 531118–01–1 .......... Model A318 (except (A318–121 and -122), Group 19–1A, Group 19–1B, and Model A320 and A321 series airplanes. The threshold/interval as defined in Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 10, dated October 2009; or Issue 11, dated September 2010. 531118–01–1 .......... Model A318–121 and -122 airplanes ... The threshold/interval as defined in Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 10, dated October 2009; or Issue 11, dated September 2010. tkelley on DSK3SPTVN1PROD with RULES Note 1 to table 1 to paragraph (k) of this AD: ALI Task 572050 refers to the outer wing dry bay and is comprised of extracts from three ALI Tasks 572004, 572020, and 572053. The threshold of ALI Task 572050 for the whole dry bay area is that of the lowest threshold of the source ALI tasks, i.e., that of ALI Task 572053. (l) Retained Limitation: No Alternative Life Limits, Inspections, or Inspection Intervals After Accomplishment of the Actions Specified in Paragraphs (g) and (h) of This AD This paragraph restates the requirements of paragraph (l) of AD 2011–14–06, Amendment 39–16741 (76 FR 42024, July 18, 2011). After VerDate Sep<11>2014 17:58 Jan 23, 2015 Jkt 235001 At the time of the next due accomplishment of any one of the tasks 572004, 572020, or 572053 as currently described in the Airbus A318/ A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/ 95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March 2006; or Issue 09, dated November 2006. At the time of the next due accomplishment of any one of the tasks 572004, 572020, or 572053 as currently described in the Airbus A318/ A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/ 95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March 2006; or Issue 09, dated November 2006. The threshold/interval as defined in Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 10, dated October 2009; or Issue 11, dated September 2010. the actions specified in paragraphs (g) and (h) of this AD have been accomplished, no alternative life limits, inspections, or inspection intervals may be used, except as provided by paragraphs (i) and (m) of this AD, and except as required by paragraphs (j) and (n) of this AD. (m) Retained Limitation: No Alternative Life Limits, Inspections, or Inspection Intervals After Accomplishment of the Actions Specified in Paragraph (j) of This AD This paragraph restates the requirements of paragraph (m) of AD 2011–14–06, Amendment 39–16741 (76 FR 42024, July 18, 2011). After the actions specified in paragraph (j) of this AD have been PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 Within 6 months after August 22, 2011 (the effective date of AD 2011–14– 06, Amendment 39–16741 (76 FR 42024, July 18, 2011)). Within 6 months after August 22, 2011 (the effective date of AD 2011–14– 06, Amendment 39–16741 (76 FR 42024, July 18, 2011)). Within 100 days after August 22, 2011 (the effective date of AD 2011–14– 06, Amendment 39–16741 (76 FR 42024, July 18, 2011)), without exceeding the previous threshold/interval as defined in Airbus A318/A319/ A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/ 95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March 2006; or Issue 09, dated November 2006. Within 100 days after August 22, 2011 (the effective date of AD 2011–14– 06, Amendment 39–16741 (76 FR 42024, July 18, 2011)), without exceeding the previous threshold/interval as defined in Airbus A318/A319/ A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/ 95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March 2006; or Issue 09, dated November 2006. Within 100 days after August 22, 2011 (the effective date of AD 2011–14– 06, Amendment 39–16741 (76 FR 42024, July 18, 2011)). accomplished, no alternative life limits, inspections, or inspection intervals may be used, except as required by paragraph (n) of this AD. (n) New Maintenance or Inspection Program Revision Within 30 days after the effective date of this AD, revise the maintenance or inspection program, as applicable, to incorporate the ALIs specified in paragraphs (n)(1), (n)(2), and (n)(3) of this AD. The initial compliance time for accomplishing the actions is at the applicable time specified in the ALIs specified in paragraphs (n)(1), (n)(2), and (n)(3) of this AD; or within 4 months after the effective date of this AD; whichever occurs E:\FR\FM\26JAR1.SGM 26JAR1 3876 Federal Register / Vol. 80, No. 16 / Monday, January 26, 2015 / Rules and Regulations later. Accomplishing these actions terminates the requirements of paragraphs (g), (h), (i), (j), and (k) of this AD. (1) Airbus A318/A319/A320/A321 ALS Part 1—Safe Life Airworthiness Limitation Items, Revision 02, dated May 13, 2011. (2) Airbus A318/A319/A320/A321 ALS Part 2—Damage-Tolerant Airworthiness Limitation Items (DT ALI), Revision 02, dated May 28, 2013. (3) Airbus A318/A319/A320/A321 ALS Part 4—Ageing Systems Maintenance, dated January 8, 2008. tkelley on DSK3SPTVN1PROD with RULES (o) New Limitation: No Alternative Actions, Intervals, and/or Critical Design Configuration Control Limitations (CDCCLs) After accomplishing the revision required by paragraph (n) of this AD, no alternative actions (e.g., inspections), intervals, and/or CDCCLs may be used unless the actions, intervals, and/or CDCCLs are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (p)(1) of this AD. (p) Other FAA AD Provisions The following provisions also apply to this AD: (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. (i) 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. (ii) AMOCs approved previously for AD 2011–14–06, Amendment 39–16741 (76 FR 42024, July 18, 2011), are approved as AMOCs for the corresponding actions specified in this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, 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 European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (q) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency Airworthiness Directives 2012–0008, dated January 16, VerDate Sep<11>2014 17:58 Jan 23, 2015 Jkt 235001 2012; and 2013–0147, dated July 16, 2013; for related information. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!document Detail;D=FAA-2013-0692-0002. (r) 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 A318/A319/A320/A321 ALS Part 1—Safe Life Airworthiness Limitation Items, Revision 02, dated May 13, 2011. The revision level of this document is identified on only the title page and in the Record of Revisions. The revision date is not identified on the title page of this document. (ii) Airbus A318/A319/A320/A321 ALS Part 2—Damage-Tolerant Airworthiness Limitation Items (DT ALI), Revision 02, dated May 28, 2013. The revision date of this document is not identified on the title page of this document. (iii) Airbus A318/A319/A320/A321 ALS Part 4—Ageing Systems Maintenance, dated January 8, 2008. The revision date of this document is not identified on the title page of this document. (3) The following service information was approved for IBR on August 22, 2011 (76 FR 42024, July 18, 2011). (i) Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE–M4/95A.0252/96, Issue 10, dated October 2009. The revision level of this document is identified on only the title page and in the Record of Revisions. (ii) Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE–M4/95A.0252/96, Issue 11, dated September 2010. The revision level of this document is identified on only the title page and in the Record of Revisions. (4) The following service information was approved for IBR on November 7, 2007 (72 FR 56262, October 3, 2007). (i) Airbus A318/A319/A320/A321 ALS Part 1—Safe Life Airworthiness Limitation Items, Revision 00, dated February 28, 2006. (ii) Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE–M4/95A.0252/96, Issue 7, dated December 2005 (approved by the European Aviation Safety Agency (EASA) on February 7, 2006). Note 2 to paragraph (r)(4)(ii) of this AD: This document contains the following errors: The Summary of Changes is comprised of 11 pages, which are all identified as Page 2— LEP of Section LEP instead of Page 1—SOC [through] Page 11—SOC of Section SOC; the List of Effective Pages only refers to Page 1— SOC for the Summary of Changes. The List of Effective Pages is comprised of two pages, and both of those pages are identified as Page 2—LEP. The first page of Section 2 is identified as Page 6 of Section 1 and is not referred to in the List of Effective Pages. (iii) Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE–M4/95A.0252/96, Issue 08, dated PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 March 2006 (approved by the EASA on January 4, 2007). (iv) Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE–M4/95A.0252/96, Issue 09, dated November 2006 (approved by the EASA on May 21, 2007). (5) 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. (6) 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. (7) 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/ibrlocations.html. Issued in Renton, Washington, on December 23, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–01257 Filed 1–23–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 97 [Docket No. 30996; Amdt. No. 3624] Standard Instrument Approach Procedures, and Takeoff Minimums and Obstacle Departure Procedures; Miscellaneous Amendments Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: This rule amends, suspends, or removes Standard Instrument Approach Procedures (SIAPs) and associated Takeoff Minimums and Obstacle Departure Procedures 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 for the 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 January 26, 2015. The compliance date for each SUMMARY: E:\FR\FM\26JAR1.SGM 26JAR1

Agencies

[Federal Register Volume 80, Number 16 (Monday, January 26, 2015)]
[Rules and Regulations]
[Pages 3871-3876]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-01257]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0692; Directorate Identifier 2012-NM-024-AD; 
Amendment 39-18031; AD 2014-23-15]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are superseding Airworthiness Directive (AD) AD 2011-14-06 
for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 
2011-14-06 required revising the maintenance program. This new AD 
requires revising the maintenance program to incorporate new, more 
restrictive limitations. This AD was prompted by the determination that 
more restrictive limitations are necessary. We are issuing this AD to 
prevent fatigue cracking, accidental damage, or corrosion in principal 
structural elements, and possible failure of certain life limited 
parts, which could result in reduced structural integrity of the 
airplane.

DATES: This AD becomes effective March 2, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of March 2, 
2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of August 
22, 2011 (76 FR 42024, July 18, 2011).
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of 
November 7, 2007 (72 FR 56262, October 3, 2007).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2013-0692; 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 http://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.

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 supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 to supersede AD 2011-14-06, Amendment 39-16741 (76 
FR 42024, July 18, 2011). AD 2011-14-06 applied to Airbus Model A318, 
A319, A320, and A321 series airplanes. The SNPRM published in the 
Federal Register on May 28, 2014 (79 FR 30492). We preceded the SNPRM 
with a notice of proposed rulemaking (NPRM) that published in the 
Federal Register on August 13, 2013 (78 FR 49213).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2013-0147, dated July 16, 2013 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A318, A319, A320, and A321 series airplanes. The MCAI states:

    The airworthiness limitations for Airbus A320 family aeroplanes 
are currently included in Airbus A318/A319/A320/A321 Airworthiness 
Limitations Section (ALS) document. The airworthiness limitations 
applicable to the Damage Tolerant Airworthiness Limitation Items (DT 
ALI) are currently given in Airbus ALS Part 2, which is approved by 
EASA.
    Previously, EASA issued AD 2010-0071R1 [http://ad.easa.europa.eu/blob/easa_ad_2010_0071_R1.pdf/AD_2010-0071R1_1] 
[associated with FAA AD 2011-14-06, Amendment 39-16741 (76 FR 42024, 
July 18, 2011)], which required the implementation of the DT ALI 
maintenance instructions as specified in Airbus A318/A319/A320/A321 
ALI Document ref. AI/SE-M4/95A.0252/96 issue 10 and Airbus A319 
Corporate Jet ALI Document ref. AI/SE-M2/95A.1038/99.
    The new Airbus A318/A319/A320/A321 ALS Part 2 Revision 02, which 
includes also Airbus A319 Corporate Jet, introduces more restrictive 
DT ALI maintenance instructions. Failure to comply with these 
instructions could result in an unsafe condition.
    Application of new DT ALI tasks 531129-02-2 and 531129-02-3 
introduces initial and

[[Page 3872]]

repetitive inspections of the windshield central lower node 
continuity fittings, replacing the one time inspection for that 
subject, previously required by EASA AD 2011-0231 [http://ad.easa.europa.eu/blob/easa_ad_2011_0231.pdf] [associated with FAA 
AD 2013-13-03, Amendment 39-17491 (78 FR 41280, July 10, 2013)].
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2010-0071R1 * * *, which are superseded, and 
requires compliance with all maintenance tasks as described in 
Airbus A318/A319/A320/A321 ALS part 2 at Revision 02.

The unsafe condition is fatigue cracking, accidental damage, or 
corrosion in principal structural elements, and possible failure of 
certain life limited parts, which could result in reduced structural 
integrity of the airplane. You may examine the MCAI in the AD docket on 
the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-
0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the SNPRM (79 
FR 30492, May 28, 2014) and the FAA's response to each comment.

Request To Extend Compliance Time

    United Airlines (UAL), Delta Airlines (DAL), and Virgin America 
asked that we extend the compliance time for incorporation of Airbus 
A318/A319/A320/A321 ALS Part 2--Damage-Tolerant Airworthiness 
Limitation Items (DT ALI), Revision 02, dated May 28, 2013. UAL stated 
that it would like to manage the task incorporation on an individual 
basis. UAL proposed that we revise the compliance times specified in 
paragraph (n) of the SNPRM (79 FR 30492, May 28, 2014) as follows: 
``After the effective date of this AD, incorporate each task into the 
program within the specific threshold/interval provided.'' DAL and 
Virgin America stated that, to provide time to revise the maintenance 
program and perform any related tasks that might exceed the compliance 
thresholds specified in the ALI, the grace period specified in 
paragraph (n) of the SNPRM should be changed from 4 to 12 months.
    DAL asked for more time to update the maintenance program to 
incorporate Airbus A318/A319/A320/A321 ALS Part 2--Damage-Tolerant 
Airworthiness Limitation Items (DT ALI), Revision 02, dated May 28, 
2013. DAL and Virgin America requested 9 months, as opposed to 30 days, 
because 9 months was the allowed compliance time for incorporating 
airworthiness limitation items into the maintenance program required by 
AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011).
    We acknowledge the commenters' concerns; however, we do not agree 
to extend the compliance times for incorporation of the tasks into the 
maintenance program. We based the compliance times in this AD primarily 
on our assessment of the safety risk. Since some safety issues are more 
time-sensitive than others, we consider the overall risk to the fleet, 
including the severity of the failure and the likelihood of the 
occurrence of the failure. In this case, the primary reason for 
requiring incorporation of Airbus A318/A319/A320/A321 ALS Part 2--
Damage-Tolerant Airworthiness Limitation Items (DT ALI), Revision 02, 
dated May 28, 2013, is to cover extension of the design service goal 
and preliminary results from widespread fatigue damage.
    Therefore, we do not agree to extend the grace period or compliance 
times for incorporation of the tasks into the maintenance program. 
However, under the provisions of paragraph (p)(1) of this AD, we will 
consider requests for approval of extending the compliance time based 
on the current status of the maintenance and inspection programs 
relative to the ALI tasks if sufficient data are submitted to 
substantiate that it would provide an acceptable level of safety. We 
have not changed this AD in this regard.

``Contacting the Manufacturer'' Paragraph in This AD

    Since late 2006, we have included a standard paragraph titled 
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD 
based on a foreign authority's AD.
    We have become aware that some operators have misunderstood or 
misinterpreted the Airworthy Product paragraph to allow the owner/
operator to use messages provided by the manufacturer as approval of 
deviations during the accomplishment of an AD-mandated action. The 
Airworthy Product paragraph does not approve messages or other 
information provided by the manufacturer for deviations to the 
requirements of the AD-mandated actions. The Airworthy Product 
paragraph only addresses the requirement to contact the manufacturer 
for corrective actions for the identified unsafe condition and does not 
cover deviations from other AD requirements. However, deviations to AD-
required actions are addressed in 14 CFR 39.17, and anyone may request 
the approval for an alternative method of compliance to the AD-required 
actions using the procedures found in 14 CFR 39.19.
    To address this misunderstanding and misinterpretation of the 
Airworthy Product paragraph, we have changed the paragraph and retitled 
it ``Contacting the Manufacturer.'' This paragraph now clarifies that 
for any requirement in this AD to obtain corrective actions from a 
manufacturer, the actions must be accomplished using a method approved 
by the FAA, the European Aviation Safety Agency (EASA), or Airbus's 
EASA Design Organization Approval (DOA).
    The Contacting the Manufacturer paragraph also clarifies that, if 
approved by the DOA, the approval must include the DOA-authorized 
signature. The DOA signature indicates that the data and information 
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer 
that do not contain the DOA-authorized signature approval are not EASA-
approved, unless EASA directly approves the manufacturer's message or 
other information.
    This clarification does not remove flexibility previously afforded 
by the Airworthy Product paragraph. Consistent with long-standing FAA 
policy, such flexibility was never intended for required actions. This 
is also consistent with the recommendation of the Airworthiness 
Directive Implementation Aviation Rulemaking Committee to increase 
flexibility in complying with ADs by identifying those actions in 
manufacturers' service instructions that are ``Required for 
Compliance'' with ADs. We continue to work with manufacturers to 
implement this recommendation. But once we determine that an action is 
required, any deviation from the requirement must be approved as an 
alternative method of compliance.
    We also have decided not to include a generic reference to either 
the ``delegated agent'' or ``design approval holder (DAH) with State of 
Design Authority design organization approval,'' but instead we have 
provided the specific delegation approval granted by the State of 
Design Authority for the DAH.

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 
SNPRM (79 FR

[[Page 3873]]

30492, May 28, 2014) for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the SNPRM (79 FR 30492, May 28, 2014).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 851 airplanes of U.S. registry.
    The actions required by AD 2011-14-06, Amendment 39-16741 (76 FR 
42024, July 18, 2011), and retained in this AD take about 1 work-hour 
per product, at an average labor rate of $85 per work-hour. Based on 
these figures, the estimated cost of the required actions is $85 per 
product.
    We also estimate that it will take about 1 work-hour per product to 
comply with the new basic requirements of this AD. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of this AD on U.S. operators to be $72,335, or $85 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 http://www.regulations.gov/#!docketDetail;D=FAA-2013-0692; 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 removing Airworthiness Directive (AD) 
2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011), and adding 
the following new AD:

2014-23-15 Airbus: Amendment 39-18031. Docket No. FAA-2013-0692; 
Directorate Identifier 2012-NM-024-AD.

(a) Effective Date

    This AD becomes effective March 2, 2015.

(b) Affected ADs

    This AD replaces AD 2011-14-06, Amendment 39-16741 (76 FR 42024, 
July 18, 2011).

(c) Applicability

    This AD applies to all Airbus Model A318-111, -112, -121, and -
122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes; Model A320-111, -211, -212, -214, -231, -232, 
and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -
213, -231, and -232 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 05, Periodic 
Inspections.

(e) Reason

    This AD was prompted by a determination that more restrictive 
limitations are necessary. We are issuing this AD to prevent fatigue 
cracking, accidental damage, or corrosion in principal structural 
elements, and possible failure of certain life limited parts, which 
could result in reduced structural integrity of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Retained Revision of Airworthiness Limitations Section (ALS) To 
Incorporate Safe Life Airworthiness Limitation Items (ALIs)

    This paragraph restates the requirements of paragraph (g) of AD 
2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011). For 
Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -114, 
-115, -131, -132, and -133 airplanes; Model A320-111, -211, -212, -
214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, 
-211, -212, -213, -231, and -232 airplanes: Within 3 months after 
November 7, 2007 (the effective date of AD 2007-20-05, Amendment 39-
15215 (72 FR 56262, October 3, 2007)), revise the ALS of the 
Instructions for Continued Airworthiness to incorporate Sub-part 1-
2, ``Life Limits,'' and Sub-part 1-3, ``Demonstrated Fatigue 
Lives,'' of Airbus A318/A319/A320/A321 ALS Part 1--Safe Life 
Airworthiness Limitation Items, Revision 00, dated February 28, 
2006. Accomplish the actions in Sub-part 1-2, ``Life Limits,'' and 
Sub-part 1-3, ``Demonstrated Fatigue Lives,'' of Airbus A318/A319/
A320/A321 ALS Part 1--Safe Life Airworthiness Limitation Items, 
Revision 00, dated February 28, 2006, at the times specified in Sub-
part 1-2, ``Life Limits,'' and Sub-part 1-3, ``Demonstrated Fatigue 
Lives,'' of Airbus A318/A319/A320/A321 ALS Part 1--Safe Life 
Airworthiness Limitation Items, dated February 28, 2006, except as 
provided by paragraph (i) of this AD. Accomplishing the actions 
required by paragraph (j) of this AD terminates the requirements of 
this paragraph.

(h) Retained Revision to ALS To Incorporate Damage Tolerant ALIs

    This paragraph restates certain provisions of paragraph (h) of 
AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011). For 
Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -114, 
-115, -131, -132, and -133 airplanes; Model A320-111, -211, -212, -
214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, 
-211, -212, -213, -231, and -232 airplanes; except Model A319 
airplanes on which Airbus Modifications 28238, 28162, and 28342 have 
been incorporated in production: Within 14 days after November

[[Page 3874]]

7, 2007 (the effective date of AD 2007-20-05, Amendment 39-15215 (72 
FR 56262, October 3, 2007)), revise the ALS of the Instructions for 
Continued Airworthiness to incorporate Airbus A318/A319/A320/A321 
Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 
7, dated December 2005 (approved by the European Aviation Safety 
Agency (EASA) on February 7, 2006); Issue 08, dated March 2006 
(approved by the EASA on January 4, 2007); or Issue 09, dated 
November 2006 (approved by the EASA on May 21, 2007). Accomplish the 
actions in Airbus A318/A319/A320/A321 Airworthiness Limitation 
Items, Document AI/SE-M4/95A.0252/96, Issue 7, dated December 2005; 
Issue 08, dated March 2006; or Issue 09, dated November 2006; at the 
times specified in Airbus A318/A319/A320/A321 Airworthiness 
Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 7, dated 
December 2005; Issue 08, dated March 2006; or Issue 09, dated 
November 2006; as applicable; except as provided by paragraph (i) of 
this AD. Accomplishing the actions required by paragraph (j) or (n) 
of this AD, as applicable, terminates the requirements of this 
paragraph.

(i) Retained Grace Period for New or More Restrictive Actions

    This paragraph restates certain provisions of paragraph (i) of 
AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011). For 
Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -114, 
-115, -131, -132, and -133 airplanes; Model A320-111, -211, -212, -
214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, 
-211, -212, -213, -231, and -232 airplanes: For any new or more 
restrictive life-limit introduced with Sub-part 1-2, ``Life 
Limits,'' and Sub-part 1-3, ``Demonstrated Fatigue Lives,'' of 
Airbus A318/A319/A320/A321 ALS Part 1--Safe Life Airworthiness 
Limitation Items, Revision 00, dated February 28, 2006, replace the 
part at the time specified in Sub-part 1-2, ``Life Limits,'' and 
Sub-part 1-3, ``Demonstrated Fatigue Lives,'' of Airbus A318/A319/
A320/A321 ALS Part 1--Safe Life Airworthiness Limitation Items, 
Revision 00, dated February 28, 2006, or within 6 months after 
November 7, 2007 (the effective date of AD 2007-20-05, Amendment 39-
15215 (72 FR 56262, October 3, 2007)), whichever is later. 
Accomplishing the actions required by paragraph (n) of this AD 
terminates the requirements of this paragraph.

(j) Retained Revision of ALS To Incorporate Damage-Tolerant ALIs With 
Revised Compliance Times

    This paragraph restates the requirements of paragraph (j) of AD 
2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011), with 
revised compliance times. Within 9 months after August 22, 2011 (the 
effective date of AD 2011-14-06): Revise the maintenance program by 
incorporating all maintenance requirements and associated 
airworthiness limitations specified in the Airbus A318/A319/A320/
A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, 
Issue 10, dated October 2009; or Issue 11, dated September 2010. 
Comply with all applicable maintenance requirements and associated 
airworthiness limitations included in Airbus A318/A319/A320/A321 
Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 
10, dated October 2009; or Issue 11, dated September 2010; except as 
provided by paragraph (k) of this AD. Accomplishing the actions 
required by this paragraph terminates the requirements of paragraph 
(h) of this AD. Accomplishing the actions required by paragraph (n) 
of this AD terminates the requirements of this paragraph.

(k) Retained Special Compliance Times for Certain Tasks

    This paragraph restates the requirements of paragraph (k) of AD 
2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011), with 
changes to table 1 to paragraph (k) of this AD. For new and more 
restrictive tasks introduced with Airbus A318/A319/A320/A321 
Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 
10, dated October 2009; or Issue 11, dated September 2010; as 
specified in table 1 to paragraph (k) of this AD: The initial 
compliance time for doing the tasks is specified in table 1 to 
paragraph (k) of this AD. Accomplishing the actions required by 
paragraph (n) of this AD terminates the requirements of this 
paragraph.

                         Table 1 to Paragraph (k) of This AD--Compliance Times for Tasks
----------------------------------------------------------------------------------------------------------------
 
----------------------------------------------------------------------------------------------------------------
Task                               Applicability............        Compliance time, whichever occurs later
                                   (as specified in the
                                    applicability column of
                                    the task).
----------------------------------------------------------------------------------------------------------------
545102-01-6......................  Group 19-1A CFM, Group 19- The threshold as defined  Within 2,000 flight
                                    1B CFM, and Model          in Airbus A318/A319/      cycles or 5,500 flight
                                    A320[dash]200 airplanes    A320/A321 Airworthiness   hours, after August 22,
                                    with CFM Industrial        Limitation Items,         2011 (the effective
                                    (CFM)/International Aero   Document AI/SE[dash]M4/   date of AD 2011-14-06,
                                    Engine (IAE) engines.      95A.0252/96, Issue 10,    Amendment 39-16741 (76
                                                               dated October 2009; or    FR 42024, July 18,
                                                               Issue 11, dated           2011)), whichever
                                                               September 2010.           occurs first.
545102-01-7......................  Model A320-100 series      The threshold as defined  Within 2,000 flight
                                    airplanes.                 in Airbus A318/A319/      cycles or 2,000 flight
                                                               A320/A321 Airworthiness   hours, after August 22,
                                                               Limitation Items,         2011 (the effective
                                                               Document AI/SE[dash]M4/   date of AD 2011-14-06,
                                                               95A.0252/96, Issue 10,    Amendment 39-16741 (76
                                                               dated October 2009; or    FR 42024, July 18,
                                                               Issue 11, dated           2011)), whichever
                                                               September 2010.           occurs first.
572050-01-1 or alternative task    Group 19[dash]1A and       At the time of the next   Within 6 months after
 572050[dash]02-1.                  Group 19-1B airplanes.     due accomplishment of     August 22, 2011 (the
                                                               any one of the tasks      effective date of AD
                                                               572004, 572020, or        2011-14-06, Amendment
                                                               572053 as currently       39-16741 (76 FR 42024,
                                                               described in the Airbus   July 18, 2011)).
                                                               A318/A319/A320/A321
                                                               Airworthiness
                                                               Limitation Items,
                                                               Document AI/SE[dash]M4/
                                                               95A.0252/96, Issue 7,
                                                               dated December 2005;
                                                               Issue 08, dated March
                                                               2006; or Issue 09,
                                                               dated November 2006.
572050-01-4 or alternative task    Model A320-200 series      At the time of the next   Within 6 months after
 572050[dash]02-4.                  airplanes.                 due accomplishment of     August 22, 2011 (the
                                                               any one of the tasks      effective date of AD
                                                               572004, 572020, or        2011-14-06, Amendment
                                                               572053 as currently       39-16741 (76 FR 42024,
                                                               described in the Airbus   July 18, 2011)).
                                                               A318/A319/A320/A321
                                                               Airworthiness
                                                               Limitation Items,
                                                               Document AI/SE[dash]M4/
                                                               95A.0252/96, Issue 7,
                                                               dated December 2005;
                                                               Issue 08, dated March
                                                               2006; or Issue 09,
                                                               dated November 2006.

[[Page 3875]]

 
572050-01-5 or alternative task    Group 21[dash]1A           At the time of the next   Within 6 months after
 572050[dash]02-5.                  airplanes.                 due accomplishment of     August 22, 2011 (the
                                                               any one of the tasks      effective date of AD
                                                               572004, 572020, or        2011-14-06, Amendment
                                                               572053 as currently       39-16741 (76 FR 42024,
                                                               described in the Airbus   July 18, 2011)).
                                                               A318/A319/A320/A321
                                                               Airworthiness
                                                               Limitation Items,
                                                               Document AI/SE[dash]M4/
                                                               95A.0252/96, Issue 7,
                                                               dated December 2005;
                                                               Issue 08, dated March
                                                               2006; or Issue 09,
                                                               dated November 2006.
572050-01-7 or alternative task    Model A320-100 series      At the time of the next   Within 6 months after
 572050[dash]02-7.                  airplanes.                 due accomplishment of     August 22, 2011 (the
                                                               any one of the tasks      effective date of AD
                                                               572004, 572020, or        2011-14-06, Amendment
                                                               572053 as currently       39-16741 (76 FR 42024,
                                                               described in the Airbus   July 18, 2011)).
                                                               A318/A319/A320/A321
                                                               Airworthiness
                                                               Limitation Items,
                                                               Document AI/SE[dash]M4/
                                                               95A.0252/96, Issue 7,
                                                               dated December 2005;
                                                               Issue 08, dated March
                                                               2006; or Issue 09,
                                                               dated November 2006.
534132-01-1......................  Model A320 PRE 30748       The threshold/interval    Within 100 days after
                                    airplanes.                 as defined in Airbus      August 22, 2011 (the
                                                               A318/A319/A320/A321       effective date of AD
                                                               Airworthiness             2011-14-06, Amendment
                                                               Limitation Items,         39-16741 (76 FR 42024,
                                                               Document AI/SE[dash]M4/   July 18, 2011)),
                                                               95A.0252/96, Issue 10,    without exceeding the
                                                               dated October 2009; or    previous threshold/
                                                               Issue 11, dated           interval as defined in
                                                               September 2010.           Airbus A318/A319/A320/
                                                                                         A321 Airworthiness
                                                                                         Limitation Items,
                                                                                         Document AI/SE[dash]M4/
                                                                                         95A.0252/96, Issue 7,
                                                                                         dated December 2005;
                                                                                         Issue 08, dated March
                                                                                         2006; or Issue 09,
                                                                                         dated November 2006.
531118-01-1......................  Model A318 (except (A318-  The threshold/interval    Within 100 days after
                                    121 and [dash]122),        as defined in Airbus      August 22, 2011 (the
                                    Group 19-1A, Group 19-     A318/A319/A320/A321       effective date of AD
                                    1B, and Model A320 and     Airworthiness             2011-14-06, Amendment
                                    A321 series airplanes.     Limitation Items,         39-16741 (76 FR 42024,
                                                               Document AI/SE[dash]M4/   July 18, 2011)),
                                                               95A.0252/96, Issue 10,    without exceeding the
                                                               dated October 2009; or    previous threshold/
                                                               Issue 11, dated           interval as defined in
                                                               September 2010.           Airbus A318/A319/A320/
                                                                                         A321 Airworthiness
                                                                                         Limitation Items,
                                                                                         Document AI/SE[dash]M4/
                                                                                         95A.0252/96, Issue 7,
                                                                                         dated December 2005;
                                                                                         Issue 08, dated March
                                                                                         2006; or Issue 09,
                                                                                         dated November 2006.
531118-01-1......................  Model A318-121 and         The threshold/interval    Within 100 days after
                                    [dash]122 airplanes.       as defined in Airbus      August 22, 2011 (the
                                                               A318/A319/A320/A321       effective date of AD
                                                               Airworthiness             2011-14-06, Amendment
                                                               Limitation Items,         39-16741 (76 FR 42024,
                                                               Document AI/SE[dash]M4/   July 18, 2011)).
                                                               95A.0252/96, Issue 10,
                                                               dated October 2009; or
                                                               Issue 11, dated
                                                               September 2010.
----------------------------------------------------------------------------------------------------------------


    Note 1 to table 1 to paragraph (k) of this AD: ALI Task 572050 
refers to the outer wing dry bay and is comprised of extracts from 
three ALI Tasks 572004, 572020, and 572053. The threshold of ALI 
Task 572050 for the whole dry bay area is that of the lowest 
threshold of the source ALI tasks, i.e., that of ALI Task 572053.

(l) Retained Limitation: No Alternative Life Limits, Inspections, or 
Inspection Intervals After Accomplishment of the Actions Specified in 
Paragraphs (g) and (h) of This AD

    This paragraph restates the requirements of paragraph (l) of AD 
2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011). After 
the actions specified in paragraphs (g) and (h) of this AD have been 
accomplished, no alternative life limits, inspections, or inspection 
intervals may be used, except as provided by paragraphs (i) and (m) 
of this AD, and except as required by paragraphs (j) and (n) of this 
AD.

(m) Retained Limitation: No Alternative Life Limits, Inspections, or 
Inspection Intervals After Accomplishment of the Actions Specified in 
Paragraph (j) of This AD

    This paragraph restates the requirements of paragraph (m) of AD 
2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011). After 
the actions specified in paragraph (j) of this AD have been 
accomplished, no alternative life limits, inspections, or inspection 
intervals may be used, except as required by paragraph (n) of this 
AD.

(n) New Maintenance or Inspection Program Revision

    Within 30 days after the effective date of this AD, revise the 
maintenance or inspection program, as applicable, to incorporate the 
ALIs specified in paragraphs (n)(1), (n)(2), and (n)(3) of this AD. 
The initial compliance time for accomplishing the actions is at the 
applicable time specified in the ALIs specified in paragraphs 
(n)(1), (n)(2), and (n)(3) of this AD; or within 4 months after the 
effective date of this AD; whichever occurs

[[Page 3876]]

later. Accomplishing these actions terminates the requirements of 
paragraphs (g), (h), (i), (j), and (k) of this AD.
    (1) Airbus A318/A319/A320/A321 ALS Part 1--Safe Life 
Airworthiness Limitation Items, Revision 02, dated May 13, 2011.
    (2) Airbus A318/A319/A320/A321 ALS Part 2--Damage-Tolerant 
Airworthiness Limitation Items (DT ALI), Revision 02, dated May 28, 
2013.
    (3) Airbus A318/A319/A320/A321 ALS Part 4--Ageing Systems 
Maintenance, dated January 8, 2008.

(o) New Limitation: No Alternative Actions, Intervals, and/or Critical 
Design Configuration Control Limitations (CDCCLs)

    After accomplishing the revision required by paragraph (n) of 
this AD, no alternative actions (e.g., inspections), intervals, and/
or CDCCLs may be used unless the actions, intervals, and/or CDCCLs 
are approved as an alternative method of compliance (AMOC) in 
accordance with the procedures specified in paragraph (p)(1) of this 
AD.

(p) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (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.
    (i) 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.
    (ii) AMOCs approved previously for AD 2011-14-06, Amendment 39-
16741 (76 FR 42024, July 18, 2011), are approved as AMOCs for the 
corresponding actions specified in this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, 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 European Aviation Safety Agency 
(EASA); or Airbus's EASA Design Organization Approval (DOA). If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

(q) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
European Aviation Safety Agency Airworthiness Directives 2012-0008, 
dated January 16, 2012; and 2013-0147, dated July 16, 2013; for 
related information. You may examine the MCAI in the AD docket on 
the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-
2013-0692-0002.

(r) 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 A318/A319/A320/A321 ALS Part 1--Safe Life 
Airworthiness Limitation Items, Revision 02, dated May 13, 2011. The 
revision level of this document is identified on only the title page 
and in the Record of Revisions. The revision date is not identified 
on the title page of this document.
    (ii) Airbus A318/A319/A320/A321 ALS Part 2--Damage-Tolerant 
Airworthiness Limitation Items (DT ALI), Revision 02, dated May 28, 
2013. The revision date of this document is not identified on the 
title page of this document.
    (iii) Airbus A318/A319/A320/A321 ALS Part 4--Ageing Systems 
Maintenance, dated January 8, 2008. The revision date of this 
document is not identified on the title page of this document.
    (3) The following service information was approved for IBR on 
August 22, 2011 (76 FR 42024, July 18, 2011).
    (i) Airbus A318/A319/A320/A321 Airworthiness Limitation Items, 
Document AI/SE-M4/95A.0252/96, Issue 10, dated October 2009. The 
revision level of this document is identified on only the title page 
and in the Record of Revisions.
    (ii) Airbus A318/A319/A320/A321 Airworthiness Limitation Items, 
Document AI/SE-M4/95A.0252/96, Issue 11, dated September 2010. The 
revision level of this document is identified on only the title page 
and in the Record of Revisions.
    (4) The following service information was approved for IBR on 
November 7, 2007 (72 FR 56262, October 3, 2007).
    (i) Airbus A318/A319/A320/A321 ALS Part 1--Safe Life 
Airworthiness Limitation Items, Revision 00, dated February 28, 
2006.
    (ii) Airbus A318/A319/A320/A321 Airworthiness Limitation Items, 
Document AI/SE-M4/95A.0252/96, Issue 7, dated December 2005 
(approved by the European Aviation Safety Agency (EASA) on February 
7, 2006).

    Note 2 to paragraph (r)(4)(ii) of this AD: This document 
contains the following errors: The Summary of Changes is comprised 
of 11 pages, which are all identified as Page 2--LEP of Section LEP 
instead of Page 1--SOC [through] Page 11--SOC of Section SOC; the 
List of Effective Pages only refers to Page 1--SOC for the Summary 
of Changes. The List of Effective Pages is comprised of two pages, 
and both of those pages are identified as Page 2--LEP. The first 
page of Section 2 is identified as Page 6 of Section 1 and is not 
referred to in the List of Effective Pages.

    (iii) Airbus A318/A319/A320/A321 Airworthiness Limitation Items, 
Document AI/SE-M4/95A.0252/96, Issue 08, dated March 2006 (approved 
by the EASA on January 4, 2007).
    (iv) Airbus A318/A319/A320/A321 Airworthiness Limitation Items, 
Document AI/SE-M4/95A.0252/96, Issue 09, dated November 2006 
(approved by the EASA on May 21, 2007).
    (5) 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.
    (6) 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.
    (7) 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.

    Issued in Renton, Washington, on December 23, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-01257 Filed 1-23-15; 8:45 am]
BILLING CODE 4910-13-P