Airworthiness Directives; Airbus Airplanes, 22364-22367 [2014-08597]

Download as PDF 22364 Federal Register / Vol. 79, No. 77 / Tuesday, April 22, 2014 / Rules and Regulations 821 4504060; fax: +49 821 419641; Internet: www.ballonbau.de. (4) You may view this service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Kansas City, Missouri, on April 4, 2014. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–08072 Filed 4–21–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–1072; Directorate Identifier 2012–NM–164–AD; Amendment 39–17828; AD 2014–08–04] 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) 2012–03– 04 for certain Airbus Model A310 series airplanes. AD 2012–03–04 required for certain airplanes, modifying the wire routing and installing additional protective sleeves. This new AD continues to require the actions in AD 2012–03–04, and requires additional work for certain airplanes. This AD was prompted by reports of new interferences of newly routed wire bundle 2S. We are issuing this AD to prevent short circuits leading to arcing, and possible fuel tank explosion. DATES: This AD becomes effective May 27, 2014. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 27, 2014. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of May 15, 2012 (77 FR 21397, April 10, 2012). ADDRESSES: You may examine the AD docket on the Internet at http:// ehiers on DSK2VPTVN1PROD with RULES SUMMARY: VerDate Mar<15>2010 15:06 Apr 21, 2014 Jkt 232001 www.regulations.gov/ #!docketDetail;D=FAA-2013-1072; or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2012–03–04, Amendment 39–16945 (77 FR 21397, April 10, 2012). AD 2012–03–04 applied to certain Airbus Model A310 series airplanes. The NPRM published in the Federal Register on January 14, 2014 (79 FR 2391). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2012–0188, dated September 19, 2012 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Within the scope of the Fuel System Safety Program (FSSP), analyses of the wire routing showed that the route 2S of the fuel electrical circuit in the Right Hand (RH) wing ensures insufficient segregation between fuel quantity indication wires and the 115 Volts Alternating Current (VAC) wires of route 2S which could, under certain conditions, lead to a short circuit and subsequent arcing, creating a potential ignition source in the fuel tank vapour space. This condition, if not detected, could result in a fuel tank explosion and consequent loss of the aeroplane. To address this potential unsafe condition, DGAC France issued [an] AD *** to require improvements of the design as specified in Airbus Service Bulletin (SB) A310–28–2148 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 original issue or Revision 01. EASA AD 2007–0230 [(http://ad.easa.europa.eu/blob/ easa_ad_2007_0230_Superseded.pdf/AD_ 2007-0230_1)], which superseded [a] DGAC France AD ***, [which] required those same actions, plus additional work 1, as defined in Airbus SB A310–28–2148 Revision 02. Since EASA AD 2007–0230 was issued, an operator reported the possibility of chafing between the new routing of the wire bundle 2S in the RH wing pylon area and the wire bundle of No.2 engine generator. The modification of this zone was introduced by Airbus SB A310–28–2148 Revision 02 as additional work 1. Investigation results showed that, to avoid the risk of chafing, the affected wiring harnesses must be installed at a higher position to provide sufficient clearance with the newly routed wire bundle 2S conduit. Airbus published Revision 03 of SB A310– 28–2148 to implement these changes as additional work 2. Subsequently, a new potential interference due to insufficient clearance was found, which prompted Airbus to issue SB A310–28–2148 Revision 04. Prompted by these findings and actions, EASA issued AD 2011–0005 [(http:// ad.easa.europa.eu/blob/easa_ad_2011_0005_ Superseded.pdf/AD_2011-0005_1)], retaining the requirements of EASA AD 2007–0230, which was superseded, and required the additional work 2 as specified in Revisions 03 and 04 of Airbus SB A310–28–2148. Since EASA AD 2011–0005 was issued, several operators of aeroplanes not having been modified in-service through Airbus SB A310–36–2015, or without having Airbus modification 07633 applied in production, reported to have embodied Airbus SB A310– 28–2148 at Revision 02 or Revision 03 on the aeroplane. However, the adequate instructions to avoid the new interferences were only introduced in Airbus SB A310–28– 2148 Revision 04. For the reasons described above, this new [EASA] AD retains the requirements of EASA AD 2011–0005, which is superseded, and requires, for certain aeroplanes, the additional work 3 [segregating wire route 2S in the RH pylon area or modifying the wire routings] as defined in Airbus SB A310–28– 2148 Revision 06. As SB A310–28–2148 Revision 07 was issued to clarify the additional work 1, 2 and 3 [segregating wire route 2S in the RH pylon area or modifying the wire routings] for aeroplanes that have previously embodied that SB at original issue, Revision 01 or Revision 02, this AD also clarifies the required additional work. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2013-10720002. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (79 FR 2391, January 14, 2014) or on the determination of the cost to the public. E:\FR\FM\22APR1.SGM 22APR1 Federal Register / Vol. 79, No. 77 / Tuesday, April 22, 2014 / Rules and Regulations Conclusion We reviewed the available data and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (79 FR 2391, January 14, 2014) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already 22365 proposed in the NPRM (79 FR 2391, January 14, 2014). Costs of Compliance We estimate that this AD affects 41 airplanes of U.S. registry. ESTIMATED COSTS Parts cost Cost per product Cost on U.S. operators Action Labor cost Modification [retained actions from AD 2012– 03–04, Amendment 39–16945 (77 FR 21397, April 10, 2012)]. Modification (additional work) [new action] ..... 62 work-hours × $85 per hour = $5,270 ........ $2,210 $7,480 $306,680 32 work-hours × $85 per hour = $2,720 ........ 1,100 3,820 156,620 Authority for This Rulemaking Examining the AD Docket 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. You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2013-1072; 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. ehiers on DSK2VPTVN1PROD with RULES Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 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. VerDate Mar<15>2010 15:06 Apr 21, 2014 Jkt 232001 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) 2012–03–04, Amendment 39–16945 (77 FR 21397, April 10, 2012), and adding the following new AD: ■ 2014–08–04 Airbus: Amendment 39–17828. Docket No. FAA–2013–1072; Directorate Identifier 2012–NM–164–AD. (a) Effective Date This airworthiness directive (AD) becomes effective May 27, 2014. PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 (b) Affected ADs This AD supersedes AD 2012–03–04, Amendment 39–16945 (77 FR 21397, April 10, 2012). (c) Applicability This AD applies to Airbus Model A310– 203, –204, –221, –222, –304, –322, –324, and –325 airplanes, certificated in any category, all certified models, all serial numbers. (d) Subject Air Transport Association (ATA) of America Code 28, Fuel. (e) Reason This AD was prompted by reports of new interferences of newly routed wire bundle 2S. We are issuing this AD to prevent short circuits leading to arcing, and possible fuel tank explosion. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Modification of Routing Wires With Revised Service Information This paragraph restates the modification required by paragraph (g) of AD 2012–03–04, Amendment 39–16945 (77 FR 21397, April 10, 2012), with revised service information. For all airplanes except airplanes on which Airbus Service Bulletin A310–28–2148, Revision 02, dated March 9, 2007, has been done (Airbus Modifications 12427 and 12435): Within 4,000 flight hours after September 3, 2004 (the effective date of AD 2004–15–16, Amendment 39–13750 (69 FR 45578, July 30, 2004)), modify the routing of wires in the right-hand (RH) wing by installing cable sleeves. Do the modification as per the Accomplishment Instructions of the service information specified in paragraph (g)(1), (g)(2), (g)(3), (g)(4), or (g)(5) of this AD. As of February 20, 2008 (the effective date of AD 2008–01–05, Amendment 39–15330 (73 FR 2795, January 16, 2008)), only the service information specified in paragraphs (g)(2), (g)(3), (g)(4), and (g)(5) of this AD may be used. As of May 15, 2012 (the effective date of AD 2012–03– 04), only the service information specified in paragraphs (g)(3), (g)(4), and (g)(5) of this AD may be used. As of the effective date of this E:\FR\FM\22APR1.SGM 22APR1 22366 Federal Register / Vol. 79, No. 77 / Tuesday, April 22, 2014 / Rules and Regulations AD, only the service bulletin specified in paragraph (g)(5) of this AD may be used. (1) Airbus Service Bulletin A310–28–2148, Revision 01, dated October 29, 2002. (2) Airbus Service Bulletin A310–28–2148, Revision 02, dated March 9, 2007. (3) Airbus Mandatory Service Bulletin A310–28–2148, Revision 05, dated August 3, 2010. (4) Airbus Mandatory Service Bulletin A310–28–2148, Revision 06, dated August 31, 2011. (5) Airbus Mandatory Service Bulletin A310–28–2148, Revision 07, dated February 13, 2012. ehiers on DSK2VPTVN1PROD with RULES (h) Retained Modification of Protection Sleeves With Revised Service Information This paragraph restates the modification required by paragraph (i) of AD 2012–03–04, Amendment 39–16945 (77 FR 21397, April 10, 2012), with revised service information. For airplanes on which the actions specified in Airbus Service Bulletin A310–28–2148, dated January 23, 2002; or Airbus Service Bulletin A310–28–2148, Revision 01, dated October 29, 2002; have been done before February 20, 2008 (the effective date of AD 2008–01–05, Amendment 39–15330 (73 FR 2795, January 16, 2008)), except for airplanes on which Airbus Service Bulletin A310–28– 2148, Revision 02, dated March 9, 2007, has been done (Airbus Modifications 12427 and 12435): Within 6,000 flight hours or 30 months after February 20, 2008 (the effective date of AD 2008–01–05), whichever occurs first, perform further modification by installing additional protection sleeves in the outer wing area near the cadensicon sensor and segregating wire route 2S in the RH pylon area, in accordance with the Accomplishment Instructions of service information specified in paragraph (h)(1), (h)(2), (h)(3), or (h)(4) of this AD. As of May 15, 2012 (the effective date of AD 2012–03– 04), only the service information specified in paragraphs (h)(2), (h)(3), and (h)(4) of this AD may be used. As of the effective date of this AD, only the service bulletin specified in paragraph (h)(4) of this AD may be used. (1) Airbus Service Bulletin A310–28–2148, Revision 02, dated March 9, 2007. (2) Airbus Mandatory Service Bulletin A310–28–2148, Revision 05, dated August 3, 2010. (3) Airbus Mandatory Service Bulletin A310–28–2148, Revision 06, dated August 31, 2011. (4) Airbus Mandatory Service Bulletin A310–28–2148, Revision 07, dated February 13, 2012. (i) Retained New Modification/Installation of Wire Routings for Certain Airplanes With Revised Service Information This paragraph restates the new modification/installation required by paragraph (j) of AD 2012–03–04, Amendment 39–16945 (77 FR 21397, April 10, 2012), with revised service information. For airplanes on which the actions specified in Airbus Service Bulletin A310–28–2148, Revision 02, dated March 9, 2007, have been accomplished, and do not have production modification 07633; and on which Airbus Service Bulletin A310– 36–2015 has not been done: Within 6,000 VerDate Mar<15>2010 15:06 Apr 21, 2014 Jkt 232001 flight hours or 30 months after May 15, 2012 (the effective date of AD 2012–03–04), whichever occurs first, modify the wire routings, in accordance with the Accomplishment Instructions of the service information specified in paragraph (i)(1), (i)(2), or (i)(3) of this AD. As of the effective date of this AD, only the service bulletin specified in paragraph (i)(3) of this AD may be used. (1) Airbus Mandatory Service Bulletin A310–28–2148, Revision 05, dated August 3, 2010. (2) Airbus Mandatory Service Bulletin A310–28–2148, Revision 06, dated August 31, 2011. (3) Airbus Mandatory Service Bulletin A310–28–2148, Revision 07, dated February 13, 2012. (j) Retained New Modification/Installation of Bracket for Certain Other Airplanes With Revised Service Information This paragraph restates the new modification/installation required by paragraph (k) of AD 2012–03–04, Amendment 39–16945 (77 FR 21397, April 10, 2012), with revised service information. For airplanes on which the actions specified in Airbus Service Bulletin A310–28–2148, Revision 02, dated March 9, 2007, have been accomplished, and have production modification 07633; or on which Airbus Service Bulletin A310–36–2015 has been done: Within 1,000 flight hours after May 15, 2012 (the effective date of AD 2012–03–04), install a modified bracket, in accordance with paragraph 3.B.(7), ‘‘Additional Work 2,’’ of the Accomplishment Instructions of the service information specified in paragraph (j)(1), (j)(2), or (j)(3) of this AD. As of the effective date of this AD, only the service bulletin specified in paragraph (j)(3) of this AD may be used. (1) Airbus Mandatory Service Bulletin A310–28–2148, Revision 05, dated August 3, 2010. (2) Airbus Mandatory Service Bulletin A310–28–2148, Revision 06, dated August 31, 2011. (3) Airbus Mandatory Service Bulletin A310–28–2148, Revision 07, dated February 13, 2012. (k) Retained Modification/Installation Provision for Certain Airplanes This paragraph restates the modification/ installation provision specified in paragraph (l) of AD 2012–03–04, Amendment 39–16945 (77 FR 21397, April 10, 2012). For airplanes on which the actions specified in Airbus Service Bulletin A310–28–2148, Revision 03, dated June 2, 2009, have been accomplished; and have modification 07633 done in production; or on which the actions specified in Airbus Service Bulletin A310–36–2015 have been done; no further action is required by paragraphs (g) through (j) of this AD. (l) Retained Credit for Previous Actions (1) This paragraph restates the credit for previous actions required by paragraph (h) of AD 2012–03–04, Amendment 39–16945 (77 FR 21397, April 10, 2012). This paragraph provides credit for the modification of the routing of wires required by paragraph (g) of AD 2012–03–04, if the modification was PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 performed before September 3, 2004 (the effective date of AD 2004–15–16, Amendment 39–13750 (69 FR 45578, July 30, 2004)), using Airbus Service Bulletin A310– 28–2148, dated January 23, 2002. (2) This paragraph restates the credit for previous actions required by paragraph (m) of AD 2012–03–04, Amendment 39–16945 (77 FR 21397, April 10, 2012). This paragraph provides credit for modifications required by paragraphs (g), (i), (j), and (k) of AD 2012– 03–04, if the modifications were performed before May 15, 2012 (the effective date of AD 2012–03–04), using Airbus Mandatory Service Bulletin A310–28–2148, Revision 04, dated April 14, 2010. (m) New Requirement of This AD: Additional Work 2 and 3 For airplanes on which the actions specified in Airbus Service Bulletin A310– 28–2148, Revision 02, dated March 9, 2007, have been accomplished, and on which the actions specified in Airbus Service Bulletin A310–36–2015 have not been done; or have Airbus Modification 07633 done in production: Within 1,000 flight hours or 12 months after the effective date of this AD, whichever occurs first, do the modification, in accordance with paragraphs ‘‘Additional Work 2’’ and ‘‘Additional Work 3’’ of the Accomplishment Instructions of Airbus Service Bulletin A310–28–2148, Revision 07, dated February 13, 2012. (n) New Requirement of This AD: Additional Work 3 For airplanes on which the actions specified in Airbus Service Bulletin A310– 28–2148, Revision 03, dated June 2, 2009, have been accomplished, and do not have production modification 07633 or Airbus Service Bulletin A310–36–2015 has not been done: Within 1,000 flight hours or 12 months after the effective date of this AD, whichever occurs first, do the modification, in accordance with paragraph ‘‘Additional Work 3’’ of the Accomplishment Instructions of Airbus Service Bulletin A310–28–2148, Revision 07, dated February 13, 2012. (o) New Requirement of This AD: Additional Work 1 and 2 For airplanes on which the actions specified in Airbus Service Bulletin A310– 36–2015 have not been accomplished and production modification 07633 has not been done, and that have done the actions specified in paragraphs (o)(1) and (o)(2) of this AD: Within 6,000 flight hours or 30 months after the effective date of this AD, whichever occurs first, do the modification, in accordance with paragraphs ‘‘Additional Work 1’’ and ‘‘Additional Work 2’’ of the Accomplishment Instructions of Airbus Service Bulletin A310–28–2148, Revision 07, dated February 13, 2012. (1) Modification in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310–28–2148, dated January 23, 2002; or Airbus Service Bulletin A310–28–2148, Revision 01, dated October 29, 2002. (2) Further modification by ‘‘Additional Work 3’’ of the Accomplishment Instructions of Airbus Service Bulletin A310–28–2148, Revision 06, dated August 31, 2011. E:\FR\FM\22APR1.SGM 22APR1 Federal Register / Vol. 79, No. 77 / Tuesday, April 22, 2014 / Rules and Regulations (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: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they were approved by the State of Design Authority (or its delegated agent, or by the Design Approval Holder with a State of Design Authority’s design organization approval, as applicable). You are required to ensure the product is airworthy before it is returned to service. (q) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency Airworthiness Directive 2012–0188, dated September 19, 2012, for related information. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/ #!documentDetail;D=FAA-2013-1072-0002. (2) Service information identified in this AD that is not incorporated by reference in this AD may be obtained at the addresses specified in paragraphs (r)(5) and (r)(6) of this AD. ehiers on DSK2VPTVN1PROD with RULES (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 May 27, 2014. (i) Airbus Service Bulletin A310–28–2148, Revision 07, dated February 13, 2012. (ii) Reserved. (4) The following service information was approved for IBR on May 15, 2012, (77 FR 21397, April 10, 2012). (i) Airbus Mandatory Service Bulletin A310–28–2148, Revision 05, dated August 3, 2010. VerDate Mar<15>2010 15:06 Apr 21, 2014 Jkt 232001 (ii) Airbus Mandatory Service Bulletin A310–28–2148, Revision 06, dated August 31, 2011. (5) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet http://www.airbus.com. (6) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. 22367 [Docket No. FAA–2014–0042; Directorate Identifier 2013–CE–050–AD; Amendment 39–17823; AD 2014–07–09] of a certain publication listed in the AD as of May 27, 2014. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0042; or in person at Document 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 service information identified in this AD, contact BAE Systems (Operations) Limited, Customer Information Department, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland, United Kingdom; telephone: +44 1292 675207; fax: +44 1292 675704; email: RApublications@ baesystems.com; Internet: http:// www.baesystems.com/Businesses/ RegionalAircraft/. You may review this referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329– 4148. FOR FURTHER INFORMATION CONTACT: Taylor Martin, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4138; fax: (816) 329–4090; email: taylor.martin@faa.gov. SUPPLEMENTARY INFORMATION: RIN 2120–AA64 Discussion Issued in Renton, Washington, on April 4, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–08597 Filed 4–21–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Airworthiness Directives; British Aerospace Regional Aircraft Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for British Aerospace Regional Aircraft Jetstream Series 3101 and Jetstream Model 3201 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as inadequate instructions for inspection for corrosion on the rudder upper hinge bracket and certain internal wing and drainage paths. We are issuing this AD to require actions to address the unsafe condition on these products. DATES: This AD is effective May 27, 2014. The Director of the Federal Register approved the incorporation by reference SUMMARY: PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to British Aerospace Regional Aircraft Jetstream Series 3101 and Jetstream Model 3201 airplanes. The NPRM was published in the Federal Register on January 31, 2014 (79 FR 5323). The NPRM proposed to correct an unsafe condition for the specified products and was based on mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country. The MCAI states: Compliance with the inspections in the Corrosion Prevention and Control Programme (CPCP) has been identified as a mandatory action for continued airworthiness and UK CAA AD 003–04–94 was issued to require operators to comply with those inspection instructions. Since the issuance of that AD, reports have been received of finding extensive corrosion on the rudder upper hinge bracket. Although there is an existing zonal inspection of the area in the CPCP, it has been concluded that this is inadequate to identify the corrosion on this bracket and consequently, a new specific inspection of the rudder upper hinge bracket, E:\FR\FM\22APR1.SGM 22APR1

Agencies

[Federal Register Volume 79, Number 77 (Tuesday, April 22, 2014)]
[Rules and Regulations]
[Pages 22364-22367]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-08597]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-1072; Directorate Identifier 2012-NM-164-AD; 
Amendment 39-17828; AD 2014-08-04]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2012-03-04 for 
certain Airbus Model A310 series airplanes. AD 2012-03-04 required for 
certain airplanes, modifying the wire routing and installing additional 
protective sleeves. This new AD continues to require the actions in AD 
2012-03-04, and requires additional work for certain airplanes. This AD 
was prompted by reports of new interferences of newly routed wire 
bundle 2S. We are issuing this AD to prevent short circuits leading to 
arcing, and possible fuel tank explosion.

DATES: This AD becomes effective May 27, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 27, 
2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of May 15, 
2012 (77 FR 21397, April 10, 2012).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2013-1072; or in person at the 
Docket Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC.
    For service information identified in this AD, contact Airbus SAS, 
Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; 
email account.airworth-eas@airbus.com; Internet http://www.airbus.com. 
You may view this referenced service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2012-03-04, Amendment 39-16945 (77 FR 21397, 
April 10, 2012). AD 2012-03-04 applied to certain Airbus Model A310 
series airplanes. The NPRM published in the Federal Register on January 
14, 2014 (79 FR 2391).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2012-0188, dated September 19, 2012 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    Within the scope of the Fuel System Safety Program (FSSP), 
analyses of the wire routing showed that the route 2S of the fuel 
electrical circuit in the Right Hand (RH) wing ensures insufficient 
segregation between fuel quantity indication wires and the 115 Volts 
Alternating Current (VAC) wires of route 2S which could, under 
certain conditions, lead to a short circuit and subsequent arcing, 
creating a potential ignition source in the fuel tank vapour space.
    This condition, if not detected, could result in a fuel tank 
explosion and consequent loss of the aeroplane.
    To address this potential unsafe condition, DGAC France issued 
[an] AD *** to require improvements of the design as specified in 
Airbus Service Bulletin (SB) A310-28-2148 original issue or Revision 
01. EASA AD 2007-0230 [(http://ad.easa.europa.eu/blob/easa_ad_2007_0230_Superseded.pdf/AD_2007-0230_1)], which superseded [a] 
DGAC France AD ***, [which] required those same actions, plus 
additional work 1, as defined in Airbus SB A310-28-2148 Revision 02.
    Since EASA AD 2007-0230 was issued, an operator reported the 
possibility of chafing between the new routing of the wire bundle 2S 
in the RH wing pylon area and the wire bundle of No.2 engine 
generator. The modification of this zone was introduced by Airbus SB 
A310-28-2148 Revision 02 as additional work 1. Investigation results 
showed that, to avoid the risk of chafing, the affected wiring 
harnesses must be installed at a higher position to provide 
sufficient clearance with the newly routed wire bundle 2S conduit.
    Airbus published Revision 03 of SB A310-28-2148 to implement 
these changes as additional work 2. Subsequently, a new potential 
interference due to insufficient clearance was found, which prompted 
Airbus to issue SB A310-28-2148 Revision 04.
    Prompted by these findings and actions, EASA issued AD 2011-0005 
[(http://ad.easa.europa.eu/blob/easa_ad_2011_0005_Superseded.pdf/AD_2011-0005_1)], retaining the requirements of 
EASA AD 2007-0230, which was superseded, and required the additional 
work 2 as specified in Revisions 03 and 04 of Airbus SB A310-28-
2148.
    Since EASA AD 2011-0005 was issued, several operators of 
aeroplanes not having been modified in-service through Airbus SB 
A310-36-2015, or without having Airbus modification 07633 applied in 
production, reported to have embodied Airbus SB A310-28-2148 at 
Revision 02 or Revision 03 on the aeroplane. However, the adequate 
instructions to avoid the new interferences were only introduced in 
Airbus SB A310-28-2148 Revision 04.
    For the reasons described above, this new [EASA] AD retains the 
requirements of EASA AD 2011-0005, which is superseded, and 
requires, for certain aeroplanes, the additional work 3 [segregating 
wire route 2S in the RH pylon area or modifying the wire routings] 
as defined in Airbus SB A310-28-2148 Revision 06. As SB A310-28-2148 
Revision 07 was issued to clarify the additional work 1, 2 and 3 
[segregating wire route 2S in the RH pylon area or modifying the 
wire routings] for aeroplanes that have previously embodied that SB 
at original issue, Revision 01 or Revision 02, this AD also 
clarifies the required additional work.

You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-1072-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (79 FR 2391, January 14, 
2014) or on the determination of the cost to the public.

[[Page 22365]]

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting this AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (79 FR 2391, January 14, 2014) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 2391, January 14, 2014).

Costs of Compliance

    We estimate that this AD affects 41 airplanes of U.S. registry.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Modification [retained actions from AD  62 work-hours x $85 per           $2,210          $7,480        $306,680
 2012-03-04, Amendment 39-16945 (77 FR   hour = $5,270.
 21397, April 10, 2012)].
Modification (additional work) [new     32 work-hours x $85 per            1,100           3,820         156,620
 action].                                hour = $2,720.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

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

Regulatory Findings

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

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2013-1072; 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) 
2012-03-04, Amendment 39-16945 (77 FR 21397, April 10, 2012), and 
adding the following new AD:

2014-08-04 Airbus: Amendment 39-17828. Docket No. FAA-2013-1072; 
Directorate Identifier 2012-NM-164-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective May 27, 
2014.

(b) Affected ADs

    This AD supersedes AD 2012-03-04, Amendment 39-16945 (77 FR 
21397, April 10, 2012).

(c) Applicability

    This AD applies to Airbus Model A310-203, -204, -221, -222, -
304, -322, -324, and -325 airplanes, certificated in any category, 
all certified models, all serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 28, Fuel.

(e) Reason

    This AD was prompted by reports of new interferences of newly 
routed wire bundle 2S. We are issuing this AD to prevent short 
circuits leading to arcing, and possible fuel tank explosion.

(f) Compliance

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

(g) Retained Modification of Routing Wires With Revised Service 
Information

    This paragraph restates the modification required by paragraph 
(g) of AD 2012-03-04, Amendment 39-16945 (77 FR 21397, April 10, 
2012), with revised service information. For all airplanes except 
airplanes on which Airbus Service Bulletin A310-28-2148, Revision 
02, dated March 9, 2007, has been done (Airbus Modifications 12427 
and 12435): Within 4,000 flight hours after September 3, 2004 (the 
effective date of AD 2004-15-16, Amendment 39-13750 (69 FR 45578, 
July 30, 2004)), modify the routing of wires in the right-hand (RH) 
wing by installing cable sleeves. Do the modification as per the 
Accomplishment Instructions of the service information specified in 
paragraph (g)(1), (g)(2), (g)(3), (g)(4), or (g)(5) of this AD. As 
of February 20, 2008 (the effective date of AD 2008-01-05, Amendment 
39-15330 (73 FR 2795, January 16, 2008)), only the service 
information specified in paragraphs (g)(2), (g)(3), (g)(4), and 
(g)(5) of this AD may be used. As of May 15, 2012 (the effective 
date of AD 2012-03-04), only the service information specified in 
paragraphs (g)(3), (g)(4), and (g)(5) of this AD may be used. As of 
the effective date of this

[[Page 22366]]

AD, only the service bulletin specified in paragraph (g)(5) of this 
AD may be used.
    (1) Airbus Service Bulletin A310-28-2148, Revision 01, dated 
October 29, 2002.
    (2) Airbus Service Bulletin A310-28-2148, Revision 02, dated 
March 9, 2007.
    (3) Airbus Mandatory Service Bulletin A310-28-2148, Revision 05, 
dated August 3, 2010.
    (4) Airbus Mandatory Service Bulletin A310-28-2148, Revision 06, 
dated August 31, 2011.
    (5) Airbus Mandatory Service Bulletin A310-28-2148, Revision 07, 
dated February 13, 2012.

(h) Retained Modification of Protection Sleeves With Revised Service 
Information

    This paragraph restates the modification required by paragraph 
(i) of AD 2012-03-04, Amendment 39-16945 (77 FR 21397, April 10, 
2012), with revised service information. For airplanes on which the 
actions specified in Airbus Service Bulletin A310-28-2148, dated 
January 23, 2002; or Airbus Service Bulletin A310-28-2148, Revision 
01, dated October 29, 2002; have been done before February 20, 2008 
(the effective date of AD 2008-01-05, Amendment 39-15330 (73 FR 
2795, January 16, 2008)), except for airplanes on which Airbus 
Service Bulletin A310-28-2148, Revision 02, dated March 9, 2007, has 
been done (Airbus Modifications 12427 and 12435): Within 6,000 
flight hours or 30 months after February 20, 2008 (the effective 
date of AD 2008-01-05), whichever occurs first, perform further 
modification by installing additional protection sleeves in the 
outer wing area near the cadensicon sensor and segregating wire 
route 2S in the RH pylon area, in accordance with the Accomplishment 
Instructions of service information specified in paragraph (h)(1), 
(h)(2), (h)(3), or (h)(4) of this AD. As of May 15, 2012 (the 
effective date of AD 2012-03-04), only the service information 
specified in paragraphs (h)(2), (h)(3), and (h)(4) of this AD may be 
used. As of the effective date of this AD, only the service bulletin 
specified in paragraph (h)(4) of this AD may be used.
    (1) Airbus Service Bulletin A310-28-2148, Revision 02, dated 
March 9, 2007.
    (2) Airbus Mandatory Service Bulletin A310-28-2148, Revision 05, 
dated August 3, 2010.
    (3) Airbus Mandatory Service Bulletin A310-28-2148, Revision 06, 
dated August 31, 2011.
    (4) Airbus Mandatory Service Bulletin A310-28-2148, Revision 07, 
dated February 13, 2012.

(i) Retained New Modification/Installation of Wire Routings for Certain 
Airplanes With Revised Service Information

    This paragraph restates the new modification/installation 
required by paragraph (j) of AD 2012-03-04, Amendment 39-16945 (77 
FR 21397, April 10, 2012), with revised service information. For 
airplanes on which the actions specified in Airbus Service Bulletin 
A310-28-2148, Revision 02, dated March 9, 2007, have been 
accomplished, and do not have production modification 07633; and on 
which Airbus Service Bulletin A310-36-2015 has not been done: Within 
6,000 flight hours or 30 months after May 15, 2012 (the effective 
date of AD 2012-03-04), whichever occurs first, modify the wire 
routings, in accordance with the Accomplishment Instructions of the 
service information specified in paragraph (i)(1), (i)(2), or (i)(3) 
of this AD. As of the effective date of this AD, only the service 
bulletin specified in paragraph (i)(3) of this AD may be used.
    (1) Airbus Mandatory Service Bulletin A310-28-2148, Revision 05, 
dated August 3, 2010.
    (2) Airbus Mandatory Service Bulletin A310-28-2148, Revision 06, 
dated August 31, 2011.
    (3) Airbus Mandatory Service Bulletin A310-28-2148, Revision 07, 
dated February 13, 2012.

(j) Retained New Modification/Installation of Bracket for Certain Other 
Airplanes With Revised Service Information

    This paragraph restates the new modification/installation 
required by paragraph (k) of AD 2012-03-04, Amendment 39-16945 (77 
FR 21397, April 10, 2012), with revised service information. For 
airplanes on which the actions specified in Airbus Service Bulletin 
A310-28-2148, Revision 02, dated March 9, 2007, have been 
accomplished, and have production modification 07633; or on which 
Airbus Service Bulletin A310-36-2015 has been done: Within 1,000 
flight hours after May 15, 2012 (the effective date of AD 2012-03-
04), install a modified bracket, in accordance with paragraph 
3.B.(7), ``Additional Work 2,'' of the Accomplishment Instructions 
of the service information specified in paragraph (j)(1), (j)(2), or 
(j)(3) of this AD. As of the effective date of this AD, only the 
service bulletin specified in paragraph (j)(3) of this AD may be 
used.
    (1) Airbus Mandatory Service Bulletin A310-28-2148, Revision 05, 
dated August 3, 2010.
    (2) Airbus Mandatory Service Bulletin A310-28-2148, Revision 06, 
dated August 31, 2011.
    (3) Airbus Mandatory Service Bulletin A310-28-2148, Revision 07, 
dated February 13, 2012.

(k) Retained Modification/Installation Provision for Certain Airplanes

    This paragraph restates the modification/installation provision 
specified in paragraph (l) of AD 2012-03-04, Amendment 39-16945 (77 
FR 21397, April 10, 2012). For airplanes on which the actions 
specified in Airbus Service Bulletin A310-28-2148, Revision 03, 
dated June 2, 2009, have been accomplished; and have modification 
07633 done in production; or on which the actions specified in 
Airbus Service Bulletin A310-36-2015 have been done; no further 
action is required by paragraphs (g) through (j) of this AD.

(l) Retained Credit for Previous Actions

    (1) This paragraph restates the credit for previous actions 
required by paragraph (h) of AD 2012-03-04, Amendment 39-16945 (77 
FR 21397, April 10, 2012). This paragraph provides credit for the 
modification of the routing of wires required by paragraph (g) of AD 
2012-03-04, if the modification was performed before September 3, 
2004 (the effective date of AD 2004-15-16, Amendment 39-13750 (69 FR 
45578, July 30, 2004)), using Airbus Service Bulletin A310-28-2148, 
dated January 23, 2002.
    (2) This paragraph restates the credit for previous actions 
required by paragraph (m) of AD 2012-03-04, Amendment 39-16945 (77 
FR 21397, April 10, 2012). This paragraph provides credit for 
modifications required by paragraphs (g), (i), (j), and (k) of AD 
2012-03-04, if the modifications were performed before May 15, 2012 
(the effective date of AD 2012-03-04), using Airbus Mandatory 
Service Bulletin A310-28-2148, Revision 04, dated April 14, 2010.

(m) New Requirement of This AD: Additional Work 2 and 3

    For airplanes on which the actions specified in Airbus Service 
Bulletin A310-28-2148, Revision 02, dated March 9, 2007, have been 
accomplished, and on which the actions specified in Airbus Service 
Bulletin A310-36-2015 have not been done; or have Airbus 
Modification 07633 done in production: Within 1,000 flight hours or 
12 months after the effective date of this AD, whichever occurs 
first, do the modification, in accordance with paragraphs 
``Additional Work 2'' and ``Additional Work 3'' of the 
Accomplishment Instructions of Airbus Service Bulletin A310-28-2148, 
Revision 07, dated February 13, 2012.

(n) New Requirement of This AD: Additional Work 3

    For airplanes on which the actions specified in Airbus Service 
Bulletin A310-28-2148, Revision 03, dated June 2, 2009, have been 
accomplished, and do not have production modification 07633 or 
Airbus Service Bulletin A310-36-2015 has not been done: Within 1,000 
flight hours or 12 months after the effective date of this AD, 
whichever occurs first, do the modification, in accordance with 
paragraph ``Additional Work 3'' of the Accomplishment Instructions 
of Airbus Service Bulletin A310-28-2148, Revision 07, dated February 
13, 2012.

(o) New Requirement of This AD: Additional Work 1 and 2

    For airplanes on which the actions specified in Airbus Service 
Bulletin A310-36-2015 have not been accomplished and production 
modification 07633 has not been done, and that have done the actions 
specified in paragraphs (o)(1) and (o)(2) of this AD: Within 6,000 
flight hours or 30 months after the effective date of this AD, 
whichever occurs first, do the modification, in accordance with 
paragraphs ``Additional Work 1'' and ``Additional Work 2'' of the 
Accomplishment Instructions of Airbus Service Bulletin A310-28-2148, 
Revision 07, dated February 13, 2012.
    (1) Modification in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A310-28-2148, dated January 
23, 2002; or Airbus Service Bulletin A310-28-2148, Revision 01, 
dated October 29, 2002.
    (2) Further modification by ``Additional Work 3'' of the 
Accomplishment Instructions of Airbus Service Bulletin A310-28-2148, 
Revision 06, dated August 31, 2011.

[[Page 22367]]

(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: Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-2125; fax 425-227-1149. Information may be 
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer, use these actions if they 
are FAA-approved. Corrective actions are considered FAA-approved if 
they were approved by the State of Design Authority (or its 
delegated agent, or by the Design Approval Holder with a State of 
Design Authority's design organization approval, as applicable). You 
are required to ensure the product is airworthy before it is 
returned to service.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency Airworthiness Directive 2012-
0188, dated September 19, 2012, for related information. You may 
examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-1072-0002.
    (2) Service information identified in this AD that is not 
incorporated by reference in this AD may be obtained at the 
addresses specified in paragraphs (r)(5) and (r)(6) of this AD.

(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 
May 27, 2014.
    (i) Airbus Service Bulletin A310-28-2148, Revision 07, dated 
February 13, 2012.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
May 15, 2012, (77 FR 21397, April 10, 2012).
    (i) Airbus Mandatory Service Bulletin A310-28-2148, Revision 05, 
dated August 3, 2010.
    (ii) Airbus Mandatory Service Bulletin A310-28-2148, Revision 
06, dated August 31, 2011.
    (5) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; 
Internet http://www.airbus.com.
    (6) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on April 4, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-08597 Filed 4-21-14; 8:45 am]
BILLING CODE 4910-13-P