Airworthiness Directives; Airbus Airplanes, 1486-1489 [2016-00014]

Download as PDF 1486 Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0678; Directorate Identifier 2013–NM–207–AD; Amendment 39–18367; AD 2016–01–08] 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) 2013–13– 04, for certain Airbus Model A318, A319, A320, and A321 series airplanes. AD 2013–13–04 required installing a power interruption protection circuit for the landing gear control interface unit (LGCIU). This new AD requires a new modification of any previously modified LGCIU. This new AD also requires revising the maintenance or inspection program to reduce a certain functional check interval. This new AD also adds airplanes to the applicability. This AD was prompted by a determination that additional work is necessary to adequately address the identified unsafe condition. We are issuing this AD to prevent untimely unlocking and/or retraction of the nose landing gear (NLG), which, while on the ground, could result in injury to ground personnel and damage to the airplane. DATES: This AD becomes effective February 17, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 17, 2016. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of August 14, 2013 (78 FR 41286, July 10, 2013) . ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov/ #!docketDetail;D=FAA-2015-0678; 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 final rule, contact Airbus, Airworthiness Office—EAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email asabaliauskas on DSK5VPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 15:56 Jan 12, 2016 Jkt 238001 account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 0678 FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2013–13–04, Amendment 39–17492 (78 FR 41286, July 10, 2013). AD 2013–13–04 applied to certain Airbus Model A318, A319, A320, and A321 series airplanes. The NPRM published in the Federal Register on March 31, 2015 (80 FR 17007). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2013–0202, dated September 5, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for Airbus Model A318–111, –112, –121, and –122 airplanes; Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–211, –212, –214, –231, –232, and –233 airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. The MCAI states: After a push back from the gate, an A320 aeroplane was preparing to initiate taxi, when an uncommanded nose landing gear (NLG) retraction occurred, causing the nose of the aeroplane to hit the ground. Investigations revealed that the retraction was caused by a combination of a power interruption to Landing Gear Control and Interface Units (LGCIU) and an internal hydraulic leak through the landing gear (LG) selector valve 40GA. Deeper investigations have revealed that LGCIU power interruption appears during engine start at each flight. Even though no incident has been reported in service, it has been determined that a non-compliance to the safety objective exists when combined with a dormant single failure of the selector valve seal leaking. This condition, if not corrected, could lead to further incidents of untimely unlocking PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 and/or retraction of the NLG which, while on the ground, could result in injury to ground personnel and damage to the aeroplane. To address the possible hydraulic leak of the LG selector valve, EASA issued AD 2007– 0065 [https://ad.easa.europa.eu/blob/easa_ ad_2007_0065.pdf/AD_2007-0065] currently at Revision 2. To address the risk of untimely unlocking and/or retraction of the NLG, EASA issued AD 2011–0202 [https://ad.easa.europa.eu/ blob/easa_ad_2011_0202.pdf/AD_2011-0202] to require installation of a power interruption protection circuit to the LGCIU and accomplishment of associated modifications. Since that [EASA] AD was issued, it has been discovered that additional work is necessary to adequately correct this unsafe condition and consequently, Airbus issued Service Bulletin (SB) A320–32–1346 to Revision 05. An update of the maintenance programme is required as well, following the required modification. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2011–0202, which is superseded, and requires certain additional actions, as defined in the revised Airbus SB, as applicable to aeroplane model, and an update of the approved maintenance programme. The additional actions include a new modification of any previously modified LGCIU, and reducing a certain functional check interval. This AD also adds airplanes on which Airbus modification 37866 has been embodied in production to the applicability. You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov/ #!documentDetail;D=FAA-2015-06780002. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (80 FR 17007, March 31, 2015) and the FAA’s response to the comment. Request To Include Revised Service Information United Airlines (UAL) stated that paragraphs (i) and (j) of the proposed AD (80 FR 17007, March 31, 2015) would be required to be done in accordance with the instructions of Airbus Service Bulletin A320–32–1346, Revision 05, dated January 13, 2012. UAL asked that we allow use of the latest revision available, Airbus Service Bulletin A320–32–1346, Revision 07, dated February 10, 2015, for accomplishing the modification. We agree with the commenter’s request. Airbus has issued Service Bulletin A320–32–1346, Revision 06, dated January 12, 2015, and Airbus Service Bulletin A320–32–1346, Revision 07, dated February 10, 2015. E:\FR\FM\13JAR1.SGM 13JAR1 Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations These revisions state that no additional work is necessary on airplanes changed in accordance with Airbus Service Bulletin A320–32–1346, Revision 05, dated January 13, 2012, which was specified as the appropriate source of service information in the NPRM (80 FR 17007, March 31, 2015). We have changed paragraphs (i) and (j) of this AD to specify accomplishing the modification in accordance with Airbus Service Bulletin A320–32–1346, Revision 07, dated February 10, 2015. We have also added a new paragraph (l)(2) to this AD (paragraph (l) of the proposed AD (80 FR 17007, March 31, 2015) has been changed to paragraph (l)(1) in this AD) to give credit for actions done before the effective date of this AD using Airbus Service Bulletin A320–32–1346, Revision 05, dated January 13, 2012; or Airbus Service Bulletin A320–32–1346, Revision 06, dated January 12, 2015. asabaliauskas on DSK5VPTVN1PROD with RULES Request To Include Terminating Action UAL stated that the NPRM (80 FR 17007, March 31, 2015) does not include a terminating action. UAL asked that we create a new paragraph detailing all actions that will be terminated by accomplishing the modification of the LGCIU, as specified in Airbus Service Bulletin A320–32–1346, Revision 07, dated February 10, 2015. We do not agree with the request. Paragraph (i) of this AD specifies that the modification terminates the actions required by paragraphs (g) and (h) of this AD. Therefore, no change to this AD is necessary in this regard. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (80 FR 17007, March 31, 2015) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (80 FR 17007, March 31, 2015). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320–32–1346, Revision 07, dated February 10, 2015, including Appendices 01 and 02, dated February 10, 2015; and Task 32.30.00.17, VerDate Sep<11>2014 15:56 Jan 12, 2016 Jkt 238001 ‘‘Functional Check of LGCIU Power Supply Relays,’’ of Section C–32 of Section C, Systems and Powerplant, of the Airbus A318/A319/A320/A321 Maintenance Review Board Report, Revision 18, dated March 2013. The service information describes procedures for installing a power interruption protection circuit for the LGCIU, and for a new modification of any previously modified LGCIU. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 851 airplanes of U.S. registry. The actions required by AD 2013–13– 04, Amendment 39–17492 (78 FR 41286, July 10, 2013), take about 48 work-hours per product, at an average labor rate of $85 per work-hour. Required parts will cost about $8,220 per product. Based on these figures, the estimated cost of the actions that are required by AD 2013–13–04 is $12,300 per product. We estimate that it takes about 46 work-hours per product to comply with the new modification in this AD. The average labor rate is $85 per work-hour. Required parts will cost about $9,650 per product. Based on these figures, we estimate the cost of the new modification on U.S. operators to be $11,539,560, or $13,560 per product. We estimate that it takes about 1 work-hour per product to revise the maintenance or inspection program in this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of revising the maintenance program 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 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 1487 that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov/ #!docketDetail;D=FAA-2015-0678; 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) 2013–13–04, Amendment 39–17492 (78 FR 41286, July 10, 2013), and adding the following new AD: ■ E:\FR\FM\13JAR1.SGM 13JAR1 1488 Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations 2016–01–08 Airbus: Amendment 39–18367. Docket No. FAA–2015–0678; Directorate Identifier 2013–NM–207–AD. (a) Effective Date This AD becomes effective February 17, 2016. (b) Affected ADs This AD replaces AD 2013–13–04, Amendment 39–17492 (78 FR 41286, July 10, 2013). (c) Applicability (1) This AD applies to Airbus Model A318– 111, –112, –121, and –122 airplanes; Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–211, –212, –214, –231, –232, and –233 airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes; certificated in any category; all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 32, Landing Gear. (e) Reason This AD was prompted by a determination that additional work is necessary to adequately address the identified unsafe condition. We are issuing this AD to prevent untimely unlocking and/or retraction of the nose landing gear (NLG), which, while on the ground, could result in injury to ground personnel and damage to the airplane. asabaliauskas on DSK5VPTVN1PROD with RULES (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Modification With No Changes This paragraph restates the requirements of paragraph (g) of AD 2013–13–04, Amendment 39–17492 (78 FR 41286, July 10, 2013) with no changes. For all airplanes except airplanes on which Airbus modification 37866 has been embodied in production: At the applicable compliance time specified in paragraph (g)(1) or (g)(2) of this AD: Install a power interruption protection circuit for the landing gear control interface unit (LGCIU), in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–32–1346, Revision 04, including Appendices 01 and 02, dated April 22, 2011 (for Model A318, A319, A320, and A321 series airplanes other than the Model A319CJ (corporate jet) airplanes); or Airbus Service Bulletin A320–32–1349, Revision 03, including Appendix 1, dated October 5, 2011 (for Model A319CJ (corporate jet) airplanes). (1) For airplanes that have embodied Airbus Modification 38947 specified in Airbus Service Bulletin A320–32–1348 during production or in service: Within 72 months after August 14, 2013 (the effective date of AD 2013–13–04, Amendment 39– 17492 (78 FR 41286, July 10, 2013)). (2) For all airplanes other than those identified in paragraph (g)(1) of this AD: Within 60 months after August 14, 2013 (the effective date of AD 2013–13–04, Amendment 39–17492 (78 FR 41286, July 10, 2013)). VerDate Sep<11>2014 15:56 Jan 12, 2016 Jkt 238001 (h) Retained Re-Identification of Identification Plates With No Changes This paragraph restates the requirements of paragraph (h) of AD 2013–13–04, Amendment 39–17492 (78 FR 41286, July 10, 2013) with no changes. For airplanes on which the installation required by paragraph (g) of this AD has been done before August 14, 2013 (the effective date of AD 2013–13– 04) using Airbus Service Bulletin A320–32– 1346, dated December 4, 2008 (for Model A318, A319, A320, and A321 series airplanes other than Model A319CJ (corporate jet) airplanes): Within the applicable times specified in paragraphs (g)(1) and (g)(2) of this AD, re-identify the identification plates, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 32–1346, Revision 04, including Appendices 01 and 02, dated April 22, 2011 (for Model A318, A319, A320, and A321 series airplanes other than Model A319CJ (corporate jet) airplanes). (i) New Modification For airplanes identified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD except airplanes on which Airbus modification 37866 has been embodied in production: Modify the LGCIU at the applicable time specified in paragraph (i)(1), (i)(2), or (i)(3) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–32–1346, Revision 07, dated February 10, 2015, including Appendices 01 and 02, dated February 10, 2015; or Airbus Service Bulletin A320–32– 1349, Revision 03, including Appendix 1, dated October 5, 2011 (for Model A319CJ (corporate jet) airplanes), which was incorporated by reference on August 14, 2013 (78 FR 41286, July 10, 2013). Accomplishing the modification in this paragraph terminates the actions required by paragraphs (g) and (h) of this AD. (1) For airplanes on which any landing gear (LG) selector valve having part number (P/N) 114079019 is installed and that have embodied Airbus Modification 38947 specified in Airbus Service Bulletin A320– 32–1348 during production or in service: Modify the LGCIU within 72 months after the effective date of this AD. (2) For airplanes on which any LG selector valve 40GA having a part number listed in paragraphs (i)(2)(i) through (i)(2)(xii) of this AD, provided the valve has the marking ‘‘DI’’ or ‘‘DI–BE’’ recorded on its amendment plates: Modify the LGCIU within 72 months after the effective date of this AD. (i) P/N 114079001. (ii) P/N 114079005. (iii) P/N 114079009. (iv) P/N 114079013. (v) P/N 114079001A. (vi) P/N 114079005A. (vii) P/N 114079009A. (viii) P/N 114079015. (ix) P/N 114079001AB. (x) P/N 114079005AB. (xi) P/N 114079009AB. (xii) P/N 114079017. (3) For all airplanes other than those identified in paragraphs (i)(1) and (i)(2) of this AD: Modify the LGCIU within 60 months after the effective date of this AD. PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 (j) New Modification for Airplanes Previously Modified For airplanes that have been modified as of the effective date of this AD as specified in the applicable service information identified in paragraph (j)(1), (j)(2), (j)(3), or (j)(4) of this AD, except airplanes on which Airbus modification 37866 has been embodied in production: Within 72 months after the effective date of this AD, do the additional modification of the LGCIU, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–32–1346, Revision 07, dated February 10, 2015, including Appendices 01 and 02, dated February 10, 2015. (1) Airbus Service Bulletin A320–32–1346, Revision 01, dated October 27, 2009, which is not incorporated by reference in this AD. (2) Airbus Service Bulletin A320–32–1346, Revision 02, dated November 4, 2009, which is not incorporated by reference in this AD. (3) Airbus Service Bulletin A320–32–1346, Revision 03, dated January 7, 2010, which is not incorporated by reference in this AD. (4) Airbus Service Bulletin A320–32–1346, including Appendices 01 and 02, Revision 04, dated April 22, 2011, which is incorporated by reference in AD 2013–13–04, Amendment 39–17492 (78 FR 41286, July 10, 2013). (k) New Maintenance or Inspection Program Revision Before further flight after accomplishing the actions specified in paragraph (i) or (j) of this AD or within 7 days after the effective date of this AD, whichever occurs later: Revise the maintenance or inspection program, as applicable, to incorporate Task 32.30.00.17, ‘‘Functional Check of LGCIU Power Supply Relays,’’ of Section C–32 of Section C, Systems and Powerplant, of the Airbus A318/A319/A320/A321 Maintenance Review Board Report, Revision 18, dated March 2013. The initial compliance time is within 4,000 flight hours after accomplishing the additional modification of the LGCIU. (l) Credit for Previous Actions (1) This paragraph provides credit for A319 Corporate Jet airplanes for the modification required by paragraph (g) of this AD if that modification was performed before the effective date of this AD using the following applicable service information. This service information is not incorporated by reference in this AD. (i) Airbus Service Bulletin A320–32–1349, dated December 4, 2008; (ii) Airbus Service Bulletin A320–32–1349, Revision 01, dated August 31, 2009; (iii) Airbus Service Bulletin A320–32– 1349, Revision 02, dated June 16, 2010. (2) This paragraph provides credit for the modification required by paragraphs (i) and (j) of this AD, as applicable, if that modification was performed before the effective date of this AD using Airbus Service Bulletin A320–32–1346, Revision 05, dated January 13, 2012; or Airbus Service Bulletin A320–32–1346, Revision 06, dated January 12, 2015. This service information is not incorporated by reference in this AD. E:\FR\FM\13JAR1.SGM 13JAR1 Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations 1489 32 of Section C, Systems and Powerplant, of the Airbus A318/A319/A320/A321 Maintenance Review Board Report, Revision 18, dated March 2013. (4) The following service information was approved for IBR on August 14, 2013 (78 FR 41286, July 10, 2013). (i) Airbus Service Bulletin A320–32–1346, Revision 04, including Appendices 01 and 02, dated April 22, 2011. (ii) Airbus Service Bulletin A320–32–1349, Revision 03, including Appendix 1, dated October 5, 2011. (5) For service information identified in this AD, contact Airbus, Airworthiness Office—EAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. (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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. DEPARTMENT OF TRANSPORTATION Examining the AD Docket (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013–0202, dated September 5, 2013, for related information. This MCAI may be found in the AD docket on the Internet at https:// www.regulations.gov/ #!documentDetail;D=FAA-2015-0678-0002. (2) Service information identified in this AD that is not incorporated by reference in this AD is available at the addresses specified in paragraphs (o)(5) and (o)(6) of this AD. asabaliauskas on DSK5VPTVN1PROD with RULES (m) 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 2013–13–04, Amendment 39–17492 (78 FR 41286, July 10, 2013) are approved as AMOCs for the corresponding provisions of 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. Federal Aviation Administration You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 1984; 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 address for the Docket Office (phone: 800–647–5527) is 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 20590. FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6428; fax: 425–917–6590; email: nathan.p.weigand@faa.gov. SUPPLEMENTARY INFORMATION: (o) 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 February 17, 2016. (i) Airbus Service Bulletin A320–32–1346, Revision 07, dated February 10, 2015, including Appendices 01 and 02, dated February 10, 2015. (ii) Task 32.30.00.17, ‘‘Functional Check of LGCIU Power Supply Relays,’’ of Section C– VerDate Sep<11>2014 15:56 Jan 12, 2016 Jkt 238001 Issued in Renton, Washington, on December 31, 2015. Philip Forde, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–00014 Filed 1–12–16; 8:45 am] BILLING CODE 4910–13–P 14 CFR Part 39 [Docket No. FAA–2015–1984; Directorate Identifier 2015–NM–022–AD; Amendment 39–18363; AD 2016–01–04] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2005–01– 09, which applied to certain The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747–400, 747– 400D, 747–400F, and 747SR series airplanes. AD 2005–01–09 required a one-time detailed inspection for discrepancies of the frame web and inner chords on the forward edge frame of the number 5 main entry door cutout, and corrective action if necessary. This SUMMARY: PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 new AD adds repetitive high frequency eddy current (HFEC) inspections for cracking of the frame inner chords (forward and aft), and corrective action if necessary. This AD was prompted by additional cracking found in the same area after completion of the one-time detailed inspection. We are issuing this AD to detect and correct discrepancies of the frame web and inner chords, which could result in cracking, subsequent severing of the frame, and consequent rapid depressurization of the airplane. DATES: This AD is effective February 17, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 17, 2016. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 1984. E:\FR\FM\13JAR1.SGM 13JAR1

Agencies

[Federal Register Volume 81, Number 8 (Wednesday, January 13, 2016)]
[Rules and Regulations]
[Pages 1486-1489]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-00014]



[[Page 1486]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0678; Directorate Identifier 2013-NM-207-AD; 
Amendment 39-18367; AD 2016-01-08]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2013-13-04, 
for certain Airbus Model A318, A319, A320, and A321 series airplanes. 
AD 2013-13-04 required installing a power interruption protection 
circuit for the landing gear control interface unit (LGCIU). This new 
AD requires a new modification of any previously modified LGCIU. This 
new AD also requires revising the maintenance or inspection program to 
reduce a certain functional check interval. This new AD also adds 
airplanes to the applicability. This AD was prompted by a determination 
that additional work is necessary to adequately address the identified 
unsafe condition. We are issuing this AD to prevent untimely unlocking 
and/or retraction of the nose landing gear (NLG), which, while on the 
ground, could result in injury to ground personnel and damage to the 
airplane.

DATES: This AD becomes effective February 17, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of February 17, 
2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of August 
14, 2013 (78 FR 41286, July 10, 2013) .

ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2015-0678; 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 final rule, contact 
Airbus, Airworthiness Office--EAS, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 
51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0678

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2013-13-04, Amendment 39-17492 (78 FR 41286, 
July 10, 2013). AD 2013-13-04 applied to certain Airbus Model A318, 
A319, A320, and A321 series airplanes. The NPRM published in the 
Federal Register on March 31, 2015 (80 FR 17007).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2013-0202, dated September 5, 2013 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for Airbus Model A318-
111, -112, -121, and -122 airplanes; Model A319-111, -112, -113, -114, 
-115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -231, 
-232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -
213, -231, and -232 airplanes. The MCAI states:

    After a push back from the gate, an A320 aeroplane was preparing 
to initiate taxi, when an uncommanded nose landing gear (NLG) 
retraction occurred, causing the nose of the aeroplane to hit the 
ground. Investigations revealed that the retraction was caused by a 
combination of a power interruption to Landing Gear Control and 
Interface Units (LGCIU) and an internal hydraulic leak through the 
landing gear (LG) selector valve 40GA.
    Deeper investigations have revealed that LGCIU power 
interruption appears during engine start at each flight. Even though 
no incident has been reported in service, it has been determined 
that a non-compliance to the safety objective exists when combined 
with a dormant single failure of the selector valve seal leaking.
    This condition, if not corrected, could lead to further 
incidents of untimely unlocking and/or retraction of the NLG which, 
while on the ground, could result in injury to ground personnel and 
damage to the aeroplane.
    To address the possible hydraulic leak of the LG selector valve, 
EASA issued AD 2007-0065 [https://ad.easa.europa.eu/blob/easa_ad_2007_0065.pdf/AD_2007-0065] currently at Revision 2.
    To address the risk of untimely unlocking and/or retraction of 
the NLG, EASA issued AD 2011-0202 [https://ad.easa.europa.eu/blob/easa_ad_2011_0202.pdf/AD_2011-0202] to require installation of a 
power interruption protection circuit to the LGCIU and 
accomplishment of associated modifications.
    Since that [EASA] AD was issued, it has been discovered that 
additional work is necessary to adequately correct this unsafe 
condition and consequently, Airbus issued Service Bulletin (SB) 
A320-32-1346 to Revision 05. An update of the maintenance programme 
is required as well, following the required modification.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2011-0202, which is superseded, and requires 
certain additional actions, as defined in the revised Airbus SB, as 
applicable to aeroplane model, and an update of the approved 
maintenance programme.

    The additional actions include a new modification of any previously 
modified LGCIU, and reducing a certain functional check interval. This 
AD also adds airplanes on which Airbus modification 37866 has been 
embodied in production to the applicability. You may examine the MCAI 
in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2015-0678-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (80 
FR 17007, March 31, 2015) and the FAA's response to the comment.

Request To Include Revised Service Information

    United Airlines (UAL) stated that paragraphs (i) and (j) of the 
proposed AD (80 FR 17007, March 31, 2015) would be required to be done 
in accordance with the instructions of Airbus Service Bulletin A320-32-
1346, Revision 05, dated January 13, 2012. UAL asked that we allow use 
of the latest revision available, Airbus Service Bulletin A320-32-1346, 
Revision 07, dated February 10, 2015, for accomplishing the 
modification.
    We agree with the commenter's request. Airbus has issued Service 
Bulletin A320-32-1346, Revision 06, dated January 12, 2015, and Airbus 
Service Bulletin A320-32-1346, Revision 07, dated February 10, 2015.

[[Page 1487]]

These revisions state that no additional work is necessary on airplanes 
changed in accordance with Airbus Service Bulletin A320-32-1346, 
Revision 05, dated January 13, 2012, which was specified as the 
appropriate source of service information in the NPRM (80 FR 17007, 
March 31, 2015).
    We have changed paragraphs (i) and (j) of this AD to specify 
accomplishing the modification in accordance with Airbus Service 
Bulletin A320-32-1346, Revision 07, dated February 10, 2015. We have 
also added a new paragraph (l)(2) to this AD (paragraph (l) of the 
proposed AD (80 FR 17007, March 31, 2015) has been changed to paragraph 
(l)(1) in this AD) to give credit for actions done before the effective 
date of this AD using Airbus Service Bulletin A320-32-1346, Revision 
05, dated January 13, 2012; or Airbus Service Bulletin A320-32-1346, 
Revision 06, dated January 12, 2015.

Request To Include Terminating Action

    UAL stated that the NPRM (80 FR 17007, March 31, 2015) does not 
include a terminating action. UAL asked that we create a new paragraph 
detailing all actions that will be terminated by accomplishing the 
modification of the LGCIU, as specified in Airbus Service Bulletin 
A320-32-1346, Revision 07, dated February 10, 2015.
    We do not agree with the request. Paragraph (i) of this AD 
specifies that the modification terminates the actions required by 
paragraphs (g) and (h) of this AD. Therefore, no change to this AD is 
necessary in this regard.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this AD with the changes described 
previously and minor editorial changes. We have determined that these 
minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (80 FR 17007, March 31, 2015) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 17007, March 31, 2015).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-32-1346, Revision 07, dated 
February 10, 2015, including Appendices 01 and 02, dated February 10, 
2015; and Task 32.30.00.17, ``Functional Check of LGCIU Power Supply 
Relays,'' of Section C-32 of Section C, Systems and Powerplant, of the 
Airbus A318/A319/A320/A321 Maintenance Review Board Report, Revision 
18, dated March 2013. The service information describes procedures for 
installing a power interruption protection circuit for the LGCIU, and 
for a new modification of any previously modified LGCIU. This service 
information is reasonably available because the interested parties have 
access to it through their normal course of business or by the means 
identified in the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 851 airplanes of U.S. registry.
    The actions required by AD 2013-13-04, Amendment 39-17492 (78 FR 
41286, July 10, 2013), take about 48 work-hours per product, at an 
average labor rate of $85 per work-hour. Required parts will cost about 
$8,220 per product. Based on these figures, the estimated cost of the 
actions that are required by AD 2013-13-04 is $12,300 per product.
    We estimate that it takes about 46 work-hours per product to comply 
with the new modification in this AD. The average labor rate is $85 per 
work-hour. Required parts will cost about $9,650 per product. Based on 
these figures, we estimate the cost of the new modification on U.S. 
operators to be $11,539,560, or $13,560 per product.
    We estimate that it takes about 1 work-hour per product to revise 
the maintenance or inspection program in this AD. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of revising the maintenance program 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 https://www.regulations.gov/#!docketDetail;D=FAA-2015-0678; 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) 
2013-13-04, Amendment 39-17492 (78 FR 41286, July 10, 2013), and adding 
the following new AD:


[[Page 1488]]


2016-01-08 Airbus: Amendment 39-18367. Docket No. FAA-2015-0678; 
Directorate Identifier 2013-NM-207-AD.

(a) Effective Date

    This AD becomes effective February 17, 2016.

(b) Affected ADs

    This AD replaces AD 2013-13-04, Amendment 39-17492 (78 FR 41286, 
July 10, 2013).

(c) Applicability

    (1) This AD applies to Airbus Model A318-111, -112, -121, and -
122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes; Model A320-211, -212, -214, -231, -232, and -233 
airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 airplanes; certificated in any category; all manufacturer 
serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing 
Gear.

(e) Reason

    This AD was prompted by a determination that additional work is 
necessary to adequately address the identified unsafe condition. We 
are issuing this AD to prevent untimely unlocking and/or retraction 
of the nose landing gear (NLG), which, while on the ground, could 
result in injury to ground personnel and damage to the airplane.

(f) Compliance

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

(g) Retained Modification With No Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2013-13-04, Amendment 39-17492 (78 FR 41286, July 10, 2013) with no 
changes. For all airplanes except airplanes on which Airbus 
modification 37866 has been embodied in production: At the 
applicable compliance time specified in paragraph (g)(1) or (g)(2) 
of this AD: Install a power interruption protection circuit for the 
landing gear control interface unit (LGCIU), in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-32-1346, 
Revision 04, including Appendices 01 and 02, dated April 22, 2011 
(for Model A318, A319, A320, and A321 series airplanes other than 
the Model A319CJ (corporate jet) airplanes); or Airbus Service 
Bulletin A320-32-1349, Revision 03, including Appendix 1, dated 
October 5, 2011 (for Model A319CJ (corporate jet) airplanes).
    (1) For airplanes that have embodied Airbus Modification 38947 
specified in Airbus Service Bulletin A320-32-1348 during production 
or in service: Within 72 months after August 14, 2013 (the effective 
date of AD 2013-13-04, Amendment 39-17492 (78 FR 41286, July 10, 
2013)).
    (2) For all airplanes other than those identified in paragraph 
(g)(1) of this AD: Within 60 months after August 14, 2013 (the 
effective date of AD 2013-13-04, Amendment 39-17492 (78 FR 41286, 
July 10, 2013)).

(h) Retained Re-Identification of Identification Plates With No Changes

    This paragraph restates the requirements of paragraph (h) of AD 
2013-13-04, Amendment 39-17492 (78 FR 41286, July 10, 2013) with no 
changes. For airplanes on which the installation required by 
paragraph (g) of this AD has been done before August 14, 2013 (the 
effective date of AD 2013-13-04) using Airbus Service Bulletin A320-
32-1346, dated December 4, 2008 (for Model A318, A319, A320, and 
A321 series airplanes other than Model A319CJ (corporate jet) 
airplanes): Within the applicable times specified in paragraphs 
(g)(1) and (g)(2) of this AD, re-identify the identification plates, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-32-1346, Revision 04, including Appendices 01 and 02, 
dated April 22, 2011 (for Model A318, A319, A320, and A321 series 
airplanes other than Model A319CJ (corporate jet) airplanes).

(i) New Modification

    For airplanes identified in paragraphs (i)(1), (i)(2), and 
(i)(3) of this AD except airplanes on which Airbus modification 
37866 has been embodied in production: Modify the LGCIU at the 
applicable time specified in paragraph (i)(1), (i)(2), or (i)(3) of 
this AD, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-32-1346, Revision 07, dated February 
10, 2015, including Appendices 01 and 02, dated February 10, 2015; 
or Airbus Service Bulletin A320-32-1349, Revision 03, including 
Appendix 1, dated October 5, 2011 (for Model A319CJ (corporate jet) 
airplanes), which was incorporated by reference on August 14, 2013 
(78 FR 41286, July 10, 2013). Accomplishing the modification in this 
paragraph terminates the actions required by paragraphs (g) and (h) 
of this AD.
    (1) For airplanes on which any landing gear (LG) selector valve 
having part number (P/N) 114079019 is installed and that have 
embodied Airbus Modification 38947 specified in Airbus Service 
Bulletin A320-32-1348 during production or in service: Modify the 
LGCIU within 72 months after the effective date of this AD.
    (2) For airplanes on which any LG selector valve 40GA having a 
part number listed in paragraphs (i)(2)(i) through (i)(2)(xii) of 
this AD, provided the valve has the marking ``DI'' or ``DI-BE'' 
recorded on its amendment plates: Modify the LGCIU within 72 months 
after the effective date of this AD.
    (i) P/N 114079001.
    (ii) P/N 114079005.
    (iii) P/N 114079009.
    (iv) P/N 114079013.
    (v) P/N 114079001A.
    (vi) P/N 114079005A.
    (vii) P/N 114079009A.
    (viii) P/N 114079015.
    (ix) P/N 114079001AB.
    (x) P/N 114079005AB.
    (xi) P/N 114079009AB.
    (xii) P/N 114079017.
    (3) For all airplanes other than those identified in paragraphs 
(i)(1) and (i)(2) of this AD: Modify the LGCIU within 60 months 
after the effective date of this AD.

(j) New Modification for Airplanes Previously Modified

    For airplanes that have been modified as of the effective date 
of this AD as specified in the applicable service information 
identified in paragraph (j)(1), (j)(2), (j)(3), or (j)(4) of this 
AD, except airplanes on which Airbus modification 37866 has been 
embodied in production: Within 72 months after the effective date of 
this AD, do the additional modification of the LGCIU, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A320-32-1346, Revision 07, dated February 10, 2015, including 
Appendices 01 and 02, dated February 10, 2015.
    (1) Airbus Service Bulletin A320-32-1346, Revision 01, dated 
October 27, 2009, which is not incorporated by reference in this AD.
    (2) Airbus Service Bulletin A320-32-1346, Revision 02, dated 
November 4, 2009, which is not incorporated by reference in this AD.
    (3) Airbus Service Bulletin A320-32-1346, Revision 03, dated 
January 7, 2010, which is not incorporated by reference in this AD.
    (4) Airbus Service Bulletin A320-32-1346, including Appendices 
01 and 02, Revision 04, dated April 22, 2011, which is incorporated 
by reference in AD 2013-13-04, Amendment 39-17492 (78 FR 41286, July 
10, 2013).

(k) New Maintenance or Inspection Program Revision

    Before further flight after accomplishing the actions specified 
in paragraph (i) or (j) of this AD or within 7 days after the 
effective date of this AD, whichever occurs later: Revise the 
maintenance or inspection program, as applicable, to incorporate 
Task 32.30.00.17, ``Functional Check of LGCIU Power Supply Relays,'' 
of Section C-32 of Section C, Systems and Powerplant, of the Airbus 
A318/A319/A320/A321 Maintenance Review Board Report, Revision 18, 
dated March 2013. The initial compliance time is within 4,000 flight 
hours after accomplishing the additional modification of the LGCIU.

(l) Credit for Previous Actions

    (1) This paragraph provides credit for A319 Corporate Jet 
airplanes for the modification required by paragraph (g) of this AD 
if that modification was performed before the effective date of this 
AD using the following applicable service information. This service 
information is not incorporated by reference in this AD.
    (i) Airbus Service Bulletin A320-32-1349, dated December 4, 
2008;
    (ii) Airbus Service Bulletin A320-32-1349, Revision 01, dated 
August 31, 2009;
    (iii) Airbus Service Bulletin A320-32-1349, Revision 02, dated 
June 16, 2010.
    (2) This paragraph provides credit for the modification required 
by paragraphs (i) and (j) of this AD, as applicable, if that 
modification was performed before the effective date of this AD 
using Airbus Service Bulletin A320-32-1346, Revision 05, dated 
January 13, 2012; or Airbus Service Bulletin A320-32-1346, Revision 
06, dated January 12, 2015. This service information is not 
incorporated by reference in this AD.

[[Page 1489]]

(m) 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 2013-13-04, Amendment 39-
17492 (78 FR 41286, July 10, 2013) are approved as AMOCs for the 
corresponding provisions of 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.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2013-0202, dated September 5, 
2013, for related information. This MCAI may be found in the AD 
docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2015-0678-0002.
    (2) Service information identified in this AD that is not 
incorporated by reference in this AD is available at the addresses 
specified in paragraphs (o)(5) and (o)(6) of this AD.

(o) 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 
February 17, 2016.
    (i) Airbus Service Bulletin A320-32-1346, Revision 07, dated 
February 10, 2015, including Appendices 01 and 02, dated February 
10, 2015.
    (ii) Task 32.30.00.17, ``Functional Check of LGCIU Power Supply 
Relays,'' of Section C-32 of Section C, Systems and Powerplant, of 
the Airbus A318/A319/A320/A321 Maintenance Review Board Report, 
Revision 18, dated March 2013.
    (4) The following service information was approved for IBR on 
August 14, 2013 (78 FR 41286, July 10, 2013).
    (i) Airbus Service Bulletin A320-32-1346, Revision 04, including 
Appendices 01 and 02, dated April 22, 2011.
    (ii) Airbus Service Bulletin A320-32-1349, Revision 03, 
including Appendix 1, dated October 5, 2011.
    (5) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com.
    (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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on December 31, 2015.
Philip Forde,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-00014 Filed 1-12-16; 8:45 am]
 BILLING CODE 4910-13-P

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