Airworthiness Directives; Airbus Airplanes, 15152-15157 [2015-05731]

Download as PDF 15152 Federal Register / Vol. 80, No. 55 / Monday, March 23, 2015 / Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0489; Directorate Identifier 2015–NM–013–AD; Amendment 39–18112; AD 2015–05–02] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: We are superseding Airworthiness Directive (AD) 2014–23– 15 for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2014–23–15 required revising the maintenance or inspection program to incorporate new, more restrictive airworthiness limitations. This new AD retains the requirement to revise the maintenance or inspection program and removes a conflicting requirement. This AD was prompted by a determination that certain limitations required by AD 2014–23–15 conflict with limitations required by another AD. 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 23, 2015. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of March 2, 2015 (80 FR 3871, January 26, 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). We must receive comments on this AD by May 7, 2015. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, mstockstill on DSK4VPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 16:11 Mar 20, 2015 Jkt 235001 Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 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 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. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 0489; or in person at the Docket Operations office 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. Comments will be available in the AD docket shortly after receipt. 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 On December 23, 2014, we issued AD 2014–23–15, Amendment 39–18031 (80 FR 3871, January 26, 2015), to supersede AD 2011–14–06, Amendment 39–16741 (76 FR 42024, July 18, 2011). AD 2014– 23–15 applied to all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2014–23–15 was prompted by the determination that more restrictive airworthiness limitations were necessary. AD 2014– 23–15 required revising the maintenance program to incorporate new, more restrictive airworthiness limitations. We issued AD 2014–23–15 to prevent fatigue cracking, accidental damage, or corrosion in principal structural elements, and possible failure PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 of certain life limited parts, which could result in reduced structural integrity of the airplane. AD 2014–23–15, Amendment 39– 18031 (80 FR 3871, January 26, 2015), corresponds 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. You may examine the MCAI on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 0489. Since we issued AD 2014–23–15, Amendment 39–18031 (80 FR 3871, January 26, 2015), we have determined that certain limitations required by AD 2014–23–15 conflict with limitations required by AD 2014–26–10, Amendment 39–18061 (80 FR 2813, January 21, 2015). Paragraph (n) of AD 2014–23–15 requires revising the maintenance or inspection program, as applicable, to incorporate the airworthiness limitations specified in paragraphs (n)(1), (n)(2), and (n)(3) of AD 2014–23–15. Paragraph (n)(3) of AD 2014–23–15 references Airbus A318/ A319/A320/A321 ALS Part 4—Ageing Systems Maintenance, dated January 8, 2008. However, paragraph (g) of AD 2014–26–10 requires revising the maintenance or inspection program, as applicable, to incorporate Airbus A318/ A319/A320/A321 Airworthiness Limitations Section, ALS Part 4, Aging Systems Maintenance, Revision 01, dated June 15, 2012. Airbus A318/A319/A320/A321 Airworthiness Limitations Section, ALS Part 4, Aging Systems Maintenance, Revision 01, dated June 15, 2012, contains the most recent airworthiness limitations for ALS Part 4. Therefore, Airbus A318/A319/A320/A321 ALS Part 4—Ageing Systems Maintenance, dated January 8, 2008, should not be incorporated as required by AD 2014– 23–15, Amendment 39–18031 (80 FR 3871, January 26, 2015). We have removed paragraph (n)(3) of AD 2014– 23–15 from this AD. We have also revised the introductory text of paragraph (n) of this AD to refer only to paragraphs (n)(1) and (n)(2) of this AD. FAA’s Determination and Requirements of This AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are issuing this E:\FR\FM\23MRR1.SGM 23MRR1 Federal Register / Vol. 80, No. 55 / Monday, March 23, 2015 / Rules and Regulations AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of these same type designs. mstockstill on DSK4VPTVN1PROD with RULES FAA’s Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because operators must comply with the most recent airworthiness limitations, which are specified in Airbus A318/A319/A320/A321 ALS Part 4—Ageing Systems Maintenance, Revision 01, dated June 15, 2012, as required by AD 2014–26–10, Amendment 39–18061 (80 FR 2813, January 21, 2015). Since AD 2014–23– 15, Amendment 39–18031 (80 FR 3871, January 26, 2015), requires an earlier version of the airworthiness limitations, i.e., Airbus A318/A319/A320/A321 ALS Part 4—Ageing Systems Maintenance, dated January 8, 2008, we must remove that requirement in order to avoid a conflict with certain requirements of AD 2014–26–10. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2015–0489; Directorate Identifier 2015–NM–013– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. Costs of Compliance We estimate that this AD affects 851 airplanes of U.S. registry. The actions required by AD 2014–23– 15, Amendment 39–18031 (80 FR 3871, VerDate Sep<11>2014 16:11 Mar 20, 2015 Jkt 235001 January 26, 2015), and retained in this AD take about 2 work-hours per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that were required by AD 2014–23–15 is $170 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. 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: PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 15153 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) 2014–23–15, Amendment 39–18031 (80 FR 3871, January 26, 2015), and adding the following new AD: ■ 2015–05–02 Airbus: Amendment 39–18112. Docket No. FAA–2015–0489; Directorate Identifier 2015–NM–013–AD. (a) Effective Date This AD becomes effective March 23, 2015. (b) Affected ADs This AD replaces AD 2014–23–15, Amendment 39–18031 (80 FR 3871, January 26, 2015). (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; certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 05, Periodic Inspections. (e) Reason This AD was prompted by a determination that certain limitations required by AD 2014– 23–15, Amendment 39–18031 (80 FR 3871, January 26, 2015), conflict with limitations required by AD 2014–26–10, Amendment 39–18061 (80 FR 2813, January 21, 2015). 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), With No Changes This paragraph restates the requirements of paragraph (g) of AD 2014–23–15, Amendment 39–18031 (80 FR 3871, January 26, 2015), with no changes. 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 E:\FR\FM\23MRR1.SGM 23MRR1 15154 Federal Register / Vol. 80, No. 55 / Monday, March 23, 2015 / Rules and Regulations 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 of ALS for Certain Airplanes To Incorporate Damage Tolerant ALIs, With No Changes This paragraph restates certain provisions of paragraph (h) of AD 2014–23–15, Amendment 39–18031 (80 FR 3871, January 26, 2015), with no changes. 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 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, With No Changes This paragraph restates certain provisions of paragraph (i) of AD 2014–23–15, Amendment 39–18031 (80 FR 3871, January 26, 2015), with no changes. 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 No Changes This paragraph restates the requirements of paragraph (j) of AD 2014–23–15, Amendment 39–18031 (80 FR 3871, January 26, 2015), with no changes. Within 9 months after August 22, 2011 (the effective date of AD 2011–14–06, Amendment 39–16741 (76 FR 42024, July 18, 2011)): 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, With No Changes This paragraph restates the requirements of paragraph (k) of AD 2014–23–15, Amendment 39–18031 (80 FR 3871, January 26, 2015), with no changes. 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 (as specified in the applicability column of the task) Group 19–1A CFM, and planes with International gines. 545102–01–7 .......... mstockstill on DSK4VPTVN1PROD with RULES 545102–01–6 .......... Model A320–100 series airplanes ....... VerDate Sep<11>2014 16:11 Mar 20, 2015 CFM, Group 19–1B Model A320–200 airCFM Industrial (CFM)/ Aero Engine (IAE) en- Jkt 235001 PO 00000 Frm 00008 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. 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. Fmt 4700 23MRR1 Sfmt 4700 E:\FR\FM\23MRR1.SGM Federal Register / Vol. 80, No. 55 / Monday, March 23, 2015 / Rules and Regulations 15155 TABLE 1 TO PARAGRAPH (K) OF THIS AD—COMPLIANCE TIMES FOR TASKS—Continued Group 19–1A and Group 19–1B airplanes. 572050–01–4 or alternative task 572050–02–4. Model A320–200 series airplanes ....... 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 .......... mstockstill on DSK4VPTVN1PROD with RULES 572050–01–1 or alternative task 572050–02–1. 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. VerDate Sep<11>2014 16:11 Mar 20, 2015 Jkt 235001 PO 00000 Frm 00009 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. 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. Fmt 4700 Sfmt 4700 E:\FR\FM\23MRR1.SGM 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 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)). 23MRR1 15156 Federal Register / Vol. 80, No. 55 / Monday, March 23, 2015 / Rules and Regulations 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, With No Changes This paragraph restates the requirements of paragraph (l) of AD 2014–23–15, Amendment 39–18031 (80 FR 3871, January 26, 2015), with no changes. 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. mstockstill on DSK4VPTVN1PROD with RULES (m) Retained Limitation: No Alternative Life Limits, Inspections, or Inspection Intervals After Accomplishment of the Actions Specified in Paragraph (j) of This AD, With No Changes This paragraph restates the requirements of paragraph (m) of AD 2014–23–15, Amendment 39–18031 (80 FR 3871, January 26, 2015), with no changes. 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) Retained Maintenance or Inspection Program Revision, With Changes This paragraph restates the requirements of paragraph (n) of AD 2014–23–15, Amendment 39–18031 (80 FR 3871, January 26, 2015), except that paragraph (n)(3) of AD 2014–23–15 is not retained. Within 30 days after March 2, 2015 (the effective date of AD 2014–23–15), revise the maintenance or inspection program, as applicable, to incorporate the ALIs specified in paragraphs (n)(1) and (n)(2) of this AD. The initial compliance time for the accomplishing the actions is at the applicable time specified in the ALIs specified in paragraphs (n)(1) and (n)(2) of this AD; or within 4 months after March 2, 2015 (the effective date of AD 2014– 23–15); whichever occurs 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. (o) Retained Limitation: No Alternative Actions, Intervals, and/or Critical Design Configuration Control Limitations (CDCCLs), With No Changes This paragraph restates the requirements of paragraph (o) of AD 2014–23–15, Amendment 39–18031 VerDate Sep<11>2014 16:11 Mar 20, 2015 Jkt 235001 (80 FR 3871, January 26, 2015), with no changes. 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 of this AD. (2) Contacting the Manufacturer: As of March 2, 2015 (the effective date of AD 2014– 23–15, Amendment 39–18031 (80 FR 3871, January 26, 2015)), 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) EASA Airworthiness Directives 2012–0008, dated January 16, 2012; and 2013–0147, dated July 16, 2013; for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA– 2015–0489. (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. PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on March 2, 2015 (80 FR 3871, January 26, 2015). (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. (4) 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. (5) 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. Note 2 to paragraph (r)(5)(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. Note 3 to paragraph (r)(5)(iii) of this AD: This document contains the following errors: Pages 3—ROR and 2—SOC are not referred to in the List of Effective Pages. The List of Effective Pages is identified as Pages 1—SOC and 2—SOC, instead of 1—LEP and 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. (iv) Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE–M4/95A.0252/96, Issue 09, dated November 2006. (6) For service information identified in this AD, contact Airbus, Airworthiness E:\FR\FM\23MRR1.SGM 23MRR1 Federal Register / Vol. 80, No. 55 / Monday, March 23, 2015 / Rules and Regulations 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. (7) 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. (8) 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 February 25, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–05731 Filed 3–20–15; 8:45 am] BILLING CODE 4910–13–P FEDERAL TRADE COMMISSION 16 CFR Parts 2, 3, and 4 Revisions to Rules of Practice Federal Trade Commission. Final rules. AGENCY: ACTION: The Commission is revising certain of its rules of practice to promote fairness, flexibility and efficiency in its investigations, studies, and adjudicative proceedings. These rule revisions include a revision to the rule governing the status of cases in administrative adjudication following a district court’s denial of preliminary injunctive relief in an ancillary proceeding. Other changes include revisions to the list of Commission officials who have authority to modify the terms and timeframe for compliance with compulsory process, and a change to the deadline for the Commission to dispose of petitions to limit or quash compulsory process. In addition, the Commission is updating its procedures for accessing public records and list of exempt Privacy Act systems. DATES: These rule revisions are effective on March 23, 2015. FOR FURTHER INFORMATION CONTACT: Josephine Liu, Attorney, (202) 326– 2170, Office of the General Counsel, Federal Trade Commission, 600 Pennsylvania Avenue NW., Washington, DC 20580. For information about the revisions to 16 CFR part 4, contact G. Richard Gold, Attorney, (202) 326–3355, Office of the General Counsel, Federal Trade Commission, 600 Pennsylvania Avenue NW., Washington, DC 20580. mstockstill on DSK4VPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 16:11 Mar 20, 2015 Jkt 235001 The Federal Trade Commission is revising certain rules in parts 2 and 3 of its rules of practice that govern investigations and adjudicative proceedings, and is revising other rules in part 4 of its rules of practice. The Commission is amending Rules 2.7 and 2.10 to provide the Office of Policy Planning (‘‘OPP’’) Director and Deputy Directors with the authority to modify the terms of compliance with compulsory process, alter the meet-andconfer prerequisite, and extend the deadline for filing a petition to limit or quash compulsory process. This change reflects OPP’s role in frequently conducting and leading studies under section 6(b) of the FTC Act. The Commission is also revising Rule 2.10(c) to impose a 40-day deadline for disposing of petitions to limit or quash compulsory process. In part 3 of its Rules, the Commission is amending Rule 3.26 to make clear that administrative litigation will be suspended if respondents file a qualifying motion for withdrawal or dismissal after a district court denies preliminary injunctive relief in an ancillary proceeding brought under section 13(b) of the FTC Act. As discussed below, the Commission will continue to follow the 1995 Policy Statement Regarding Administrative Merger Litigation Following the Denial of a Preliminary Injunction 1 and consider the specific circumstances of each case when deciding whether to pursue administrative litigation. In addition, the Commission is revising the Part 3 rules to correct typographical errors, ensure consistency between sections, clarify paragraph headings, and make other technical changes. In part 4 of its Rules, the Commission is revising the procedures and contact information for accessing public records in Rule 4.9, making a technical correction to Rule 4.11, and updating the names of exempt Privacy Act systems in Rule 4.13. Because these rule revisions relate solely to agency procedure and practice, publication for notice and comment is not required under the Administrative Procedure Act. 5 U.S.C. 553(b).2 These rule revisions are effective on March 23, 2015. SUPPLEMENTARY INFORMATION: 1 Administrative Litigation Following the Denial of a Preliminary Injunction: Policy Statement, 60 FR 39741 (Aug. 3, 1995). 2 For this reason, the requirements of the Regulatory Flexibility Act are also inapplicable. 5 U.S.C. 601(2), 604(a). Likewise, the amendments do not modify any FTC collections of information within the meaning of the Paperwork Reduction Act, 44 U.S.C. 3501 et seq. PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 15157 I. Revisions to Rules of Practice for Nonadjudicative Investigations (Part 2) In 2012, the Commission undertook an extensive revision of its rules governing the conduct of its investigations.3 The Commission is now revising certain of those rules to promote fairness, flexibility, and efficiency in FTC investigations, which includes studies conducted under section 6(b) of the FTC Act. Rules 2.7(l) and 2.10(a)(5): Officials With Authority To Modify Compulsory Process and Extend the Deadline for Petitions To Quash The Commission is revising Rules 2.7(l) and 2.10(a)(5) to reflect the fact that the FTC’s Office of Policy Planning frequently conducts and leads section 6(b) studies. The Commission is amending Rule 2.7(l) to include the Office of Policy Planning Director and Deputy Directors among the identified Commission officials authorized to modify the terms of compliance with orders to file special reports under section 6(b) of the FTC Act and other forms of compulsory process. Commission rules provide that the officials designated in Rule 2.7(l) also have the power to modify the manner and form of production of electronically stored information (in Rule 2.7(j)), and alter the meet-and-confer prerequisite for filing a petition to limit or quash compulsory process (in Rule 2.7(k)). Consistent with these amendments, the Commission is also revising Rule 2.10(a)(5) to state that the Office of Policy Planning Director and Deputy Directors are authorized to extend the deadline for filing a petition to limit or quash. The revised rules will better reflect Commission practice and provide further flexibility and efficiency for 6(b) studies and other investigations. Rule 2.10(c): Disposition of Petitions To Limit or Quash Compulsory Process The Commission revised Rule 2.10 in 2012 to eliminate the two-step procedure for rulings on petitions to limit or quash compulsory process by requiring the full Commission to rule on the petition in the first instance. The rule also imposed a 30-day deadline for disposition of the petition. The Commission received no comments regarding this provision, and adopted it as proposed, noting that if the Commission did not meet the deadline, the petition would not be automatically granted or denied.4 To enable sufficient time for full Commission review of the merits of the petition, the Commission 3 See 4 77 Rules of Practice, 77 FR 59294 (2012). FR 59300. E:\FR\FM\23MRR1.SGM 23MRR1

Agencies

[Federal Register Volume 80, Number 55 (Monday, March 23, 2015)]
[Rules and Regulations]
[Pages 15152-15157]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-05731]



[[Page 15152]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0489; Directorate Identifier 2015-NM-013-AD; 
Amendment 39-18112; AD 2015-05-02]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule; request for comments.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2014-23-15 for 
all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2014-
23-15 required revising the maintenance or inspection program to 
incorporate new, more restrictive airworthiness limitations. This new 
AD retains the requirement to revise the maintenance or inspection 
program and removes a conflicting requirement. This AD was prompted by 
a determination that certain limitations required by AD 2014-23-15 
conflict with limitations required by another AD. 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 23, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of March 2, 2015 
(80 FR 3871, January 26, 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).
    We must receive comments on this AD by May 7, 2015.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0489; or in person at the Docket Operations office 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. Comments will be 
available in the AD docket shortly after receipt.

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

    On December 23, 2014, we issued AD 2014-23-15, Amendment 39-18031 
(80 FR 3871, January 26, 2015), to supersede AD 2011-14-06, Amendment 
39-16741 (76 FR 42024, July 18, 2011). AD 2014-23-15 applied to all 
Airbus Model A318, A319, A320, and A321 series airplanes. AD 2014-23-15 
was prompted by the determination that more restrictive airworthiness 
limitations were necessary. AD 2014-23-15 required revising the 
maintenance program to incorporate new, more restrictive airworthiness 
limitations. We issued AD 2014-23-15 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.
    AD 2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015), 
corresponds 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. You may 
examine the MCAI on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2015-0489.
    Since we issued AD 2014-23-15, Amendment 39-18031 (80 FR 3871, 
January 26, 2015), we have determined that certain limitations required 
by AD 2014-23-15 conflict with limitations required by AD 2014-26-10, 
Amendment 39-18061 (80 FR 2813, January 21, 2015). Paragraph (n) of AD 
2014-23-15 requires revising the maintenance or inspection program, as 
applicable, to incorporate the airworthiness limitations specified in 
paragraphs (n)(1), (n)(2), and (n)(3) of AD 2014-23-15. Paragraph 
(n)(3) of AD 2014-23-15 references Airbus A318/A319/A320/A321 ALS Part 
4--Ageing Systems Maintenance, dated January 8, 2008. However, 
paragraph (g) of AD 2014-26-10 requires revising the maintenance or 
inspection program, as applicable, to incorporate Airbus A318/A319/
A320/A321 Airworthiness Limitations Section, ALS Part 4, Aging Systems 
Maintenance, Revision 01, dated June 15, 2012.
    Airbus A318/A319/A320/A321 Airworthiness Limitations Section, ALS 
Part 4, Aging Systems Maintenance, Revision 01, dated June 15, 2012, 
contains the most recent airworthiness limitations for ALS Part 4. 
Therefore, Airbus A318/A319/A320/A321 ALS Part 4--Ageing Systems 
Maintenance, dated January 8, 2008, should not be incorporated as 
required by AD 2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 
2015). We have removed paragraph (n)(3) of AD 2014-23-15 from this AD. 
We have also revised the introductory text of paragraph (n) of this AD 
to refer only to paragraphs (n)(1) and (n)(2) of this AD.

FAA's Determination and Requirements of This AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are issuing this

[[Page 15153]]

AD because we evaluated all pertinent information and determined the 
unsafe condition exists and is likely to exist or develop on other 
products of these same type designs.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because 
operators must comply with the most recent airworthiness limitations, 
which are specified in Airbus A318/A319/A320/A321 ALS Part 4--Ageing 
Systems Maintenance, Revision 01, dated June 15, 2012, as required by 
AD 2014-26-10, Amendment 39-18061 (80 FR 2813, January 21, 2015). Since 
AD 2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015), 
requires an earlier version of the airworthiness limitations, i.e., 
Airbus A318/A319/A320/A321 ALS Part 4--Ageing Systems Maintenance, 
dated January 8, 2008, we must remove that requirement in order to 
avoid a conflict with certain requirements of AD 2014-26-10. Therefore, 
we determined that notice and opportunity for public comment before 
issuing this AD are impracticable and that good cause exists for making 
this amendment effective in fewer than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2015-0489; Directorate 
Identifier 2015-NM-013-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD because of 
those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    We estimate that this AD affects 851 airplanes of U.S. registry.
    The actions required by AD 2014-23-15, Amendment 39-18031 (80 FR 
3871, January 26, 2015), and retained in this AD take about 2 work-
hours per product, at an average labor rate of $85 per work-hour. Based 
on these figures, the estimated cost of the actions that were required 
by AD 2014-23-15 is $170 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.

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) 
2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015), and 
adding the following new AD:

2015-05-02 Airbus: Amendment 39-18112. Docket No. FAA-2015-0489; 
Directorate Identifier 2015-NM-013-AD.

(a) Effective Date

    This AD becomes effective March 23, 2015.

(b) Affected ADs

    This AD replaces AD 2014-23-15, Amendment 39-18031 (80 FR 3871, 
January 26, 2015).

(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; certificated in any category.

(d) Subject

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

(e) Reason

    This AD was prompted by a determination that certain limitations 
required by AD 2014-23-15, Amendment 39-18031 (80 FR 3871, January 
26, 2015), conflict with limitations required by AD 2014-26-10, 
Amendment 39-18061 (80 FR 2813, January 21, 2015). 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), With No 
Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015), with 
no changes. 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

[[Page 15154]]

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 of ALS for Certain Airplanes To Incorporate 
Damage Tolerant ALIs, With No Changes

    This paragraph restates certain provisions of paragraph (h) of 
AD 2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015), 
with no changes. 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 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, With No 
Changes

    This paragraph restates certain provisions of paragraph (i) of 
AD 2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015), 
with no changes. 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 
No Changes

    This paragraph restates the requirements of paragraph (j) of AD 
2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015), with 
no changes. Within 9 months after August 22, 2011 (the effective 
date of AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 
2011)): 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, With No 
Changes

    This paragraph restates the requirements of paragraph (k) of AD 
2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015), with 
no changes. 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 (as            Compliance time, whichever occurs later
                                        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 A320-    in Airbus A318/A319/      cycles or 5,500 flight
                                    200 airplanes with CFM     A320/A321 Airworthiness   hours, after August 22,
                                    Industrial (CFM)/          Limitation Items,         2011 (the effective
                                    International Aero         Document AI/SE-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-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.

[[Page 15155]]

 
572050-01-1 or alternative task    Group 19-1A and Group 19-  At the time of the next   Within 6 months after
 572050-02-1.                       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-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
 572050-02-4.                       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-M4/
                                                               95A.0252/96, Issue 7,
                                                               dated December 2005;
                                                               Issue 08, dated March
                                                               2006; or Issue 09,
                                                               dated November 2006.
572050-01-5 or alternative task    Group 21-1A airplanes....  At the time of the next   Within 6 months after
 572050-02-5.                                                  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-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
 572050-02-7.                       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-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-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-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 -122), Group 19-   as defined in Airbus      August 22, 2011 (the
                                    1A, Group 19-1B, and       A318/A319/A320/A321       effective date of AD
                                    Model A320 and A321        Airworthiness             2011-14-06, Amendment
                                    series airplanes.          Limitation Items,         39-16741 (76 FR 42024,
                                                               Document AI/SE-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-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 -122    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-M4/        July 18, 2011)).
                                                               95A.0252/96, Issue 10,
                                                               dated October 2009; or
                                                               Issue 11, dated
                                                               September 2010.
----------------------------------------------------------------------------------------------------------------



[[Page 15156]]

    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, With No Changes

    This paragraph restates the requirements of paragraph (l) of AD 
2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015), with 
no changes. 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, With No Changes

    This paragraph restates the requirements of paragraph (m) of AD 
2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015), with 
no changes. 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) Retained Maintenance or Inspection Program Revision, With Changes

    This paragraph restates the requirements of paragraph (n) of AD 
2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015), 
except that paragraph (n)(3) of AD 2014-23-15 is not retained. 
Within 30 days after March 2, 2015 (the effective date of AD 2014-
23-15), revise the maintenance or inspection program, as applicable, 
to incorporate the ALIs specified in paragraphs (n)(1) and (n)(2) of 
this AD. The initial compliance time for the accomplishing the 
actions is at the applicable time specified in the ALIs specified in 
paragraphs (n)(1) and (n)(2) of this AD; or within 4 months after 
March 2, 2015 (the effective date of AD 2014-23-15); whichever 
occurs 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.

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

    This paragraph restates the requirements of paragraph (o) of AD 
2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015), with 
no changes. 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 of this AD.
    (2) Contacting the Manufacturer: As of March 2, 2015 (the 
effective date of AD 2014-23-15, Amendment 39-18031 (80 FR 3871, 
January 26, 2015)), 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) 
EASA Airworthiness Directives 2012-0008, dated January 16, 2012; and 
2013-0147, dated July 16, 2013; for related information. This MCAI 
may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-
2015-0489.

(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.
    (3) The following service information was approved for IBR on 
March 2, 2015 (80 FR 3871, January 26, 2015).
    (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.
    (4) 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.
    (5) 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.

    Note 2 to paragraph (r)(5)(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.

    Note 3 to paragraph (r)(5)(iii) of this AD: This document 
contains the following errors: Pages 3--ROR and 2--SOC are not 
referred to in the List of Effective Pages. The List of Effective 
Pages is identified as Pages 1--SOC and 2--SOC, instead of 1--LEP 
and 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.

    (iv) Airbus A318/A319/A320/A321 Airworthiness Limitation Items, 
Document AI/SE-M4/95A.0252/96, Issue 09, dated November 2006.
    (6) For service information identified in this AD, contact 
Airbus, Airworthiness

[[Page 15157]]

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.
    (7) 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.
    (8) 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 February 25, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-05731 Filed 3-20-15; 8:45 am]
 BILLING CODE 4910-13-P