Airworthiness Directives; Airbus Airplanes, 78705-78710 [2013-30066]

Download as PDF Federal Register / Vol. 78, No. 249 / Friday, December 27, 2013 / Rules and Regulations Note 1 to paragraph (g) of this AD: Information on additional procedures for the modification can be found in Notes 4, 5, and 6, as applicable, of paragraph 1.D., ‘‘Compliance’’ of McDonnell Douglas DC–9 Alert Service Bulletin A53–144, Revision 2, dated February 23, 1984. (h) Exception to Service Information If any crack is found during any inspection required by this AD, and McDonnell Douglas DC–9 Alert Service Bulletin A53–144, Revision 2, dated February 23, 1984, specifies to contact the manufacturer for appropriate action: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (j) of this AD. (i) No Reporting Required Sheet 1 of Service Sketch 3109, and Sheet 7 of Service Sketch 3110B of McDonnell Douglas DC–9 Alert Service Bulletin A53– 144, Revision 2, dated February 23, 1984; specify reporting the details of any cracks found; however, this AD does not require reporting. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles Aircraft Certification Office (ACO), 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 manager of the Los Angeles ACO, send it to the attention of the person identified in paragraph (k) of this AD. (2) 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. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by Structures Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization who has been authorized by the Manager, Los Angeles ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and 14 CFR 25.571, Amendment 45, and the approval must specifically refer to this AD. tkelley on DSK3SPTVN1PROD with RULES (k) Related Information For more information about this AD, contact Eric Schrieber, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, CA 90712– 4137; phone: (562) 627–5348; fax: (562) 627– 5210; email: eric.schrieber@faa.gov. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. VerDate Mar<15>2010 18:49 Dec 26, 2013 Jkt 232001 (i) McDonnell Douglas DC–9 Alert Service Bulletin A53–144, Revision 2, dated February 23, 1984. (ii) Reserved. (3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, CA 90846–0001; telephone 206–544–5000, extension 2; fax 206–766–5683; Internet https:// www.myboeingfleet.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on December 10, 2013. John P. Piccola, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–30779 Filed 12–26–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0416; Directorate Identifier 2012–NM–144–AD; Amendment 39–17707; AD 2013–25–11] 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) 2010–24– 07 for all Airbus Model A318 series airplanes, Model A319 series airplanes, Model A320 series airplanes, and Model A321 series airplanes. AD 2010–24–07 required repetitive inspections of the 80VU rack lower lateral fittings for damage, repetitive inspections of the 80VU rack lower central support for cracking, and corrective action if necessary. AD 2010–24–07 also specified optional terminating action for the repetitive inspections. This new AD reduces the inspection compliance time, adds an inspection of the upper fittings and shelves of the 80VU rack, and adds airplanes to the applicability. This AD was prompted by reports of worn lower SUMMARY: PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 78705 lateral fittings of the 80VU rack. We are issuing this AD to detect and correct damage or cracking of the 80VU fittings and supports, which could lead to possible disconnection of the cable harnesses to one or more computers, and if occurring during a critical phase of flight, could result in reduced control of the airplane. DATES: This AD becomes effective January 31, 2014. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 31, 2014. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of January 11, 2011 (75 FR 75878, December 7, 2010). ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2013-0416; or in person at the U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone (425) 227–1405; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to the specified products. The NPRM was published in the Federal Register on May 14, 2013 (78 FR 28152), and proposed to supersede AD 2010– 24–07, Amendment 39–16526 (75 FR 75878, December 7, 2010). The NPRM proposed to correct an unsafe condition for the specified products. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2012–0134, dated July 18, 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: Damage to the lower lateral fittings of the 80VU rack, typically elongated holes, migrated bushes, and/or missing bolts have been reported on in-service aeroplanes. The 80VU rack contains computers for flight controls, communication and radionavigation. In addition, damage to the lower E:\FR\FM\27DER1.SGM 27DER1 78706 Federal Register / Vol. 78, No. 249 / Friday, December 27, 2013 / Rules and Regulations central support fitting (including cracking) has been reported. Failure of the 80VU fittings, in combination with a high load factor or strong vibration, could lead to failure of the rack structure and/or computers or rupture/ disconnection of the cable harnesses to one or more computers located in the 80VU rack. Even though the computer functions are duplicated across other racks, multiple system failures or (partial) disconnection of systems, if occurring during a critical phase of flight, could result in reduced control of the aeroplane. To address this potential unsafe condition, EASA issued AD 2007–0276 to require repetitive inspections of the lower lateral 80VU fittings and the lower central 80VU support and, depending on findings, the accomplishment of corrective actions. [EASA] AD 2007–0276 was revised to introduce a reinforced lower central support as an optional terminating action for the repetitive inspections. Since issuance of EASA AD 2007–0276R1 [http://ad.easa.europa.eu/blob/easa_ad_ 2007_0276_R1_superseded.pdf/AD_2007– 0276R1_1] [which corresponds to FAA AD 2010–24–07, Amendment 39–16526 (75 FR 75878, December 7, 2010)], and prompted by in-service experience, the previous inspection programme has been reassessed. New conditions of inspection for a new finding on the lower central fitting attachment (crack in the lower of the lateral flanges), and a new visual inspection of the upper fittings and shelves of the 80VU are introduced by this inspection programme. In addition, the replacement of a cracked lateral fitting or central support with a lateral fitting or central support having the same part number is no longer preferable as corrective action. Instead, the installation of the reinforced lower central support is now defined as optional terminating action for the repetitive inspections required by this [EASA] AD. For the reasons described above, this [EASA] AD supersedes EASA AD 2007– 0276R1 and requires implementation of an amended inspection programme with a reduced inspection threshold. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2013-04160002. tkelley on DSK3SPTVN1PROD with RULES Comments We gave the public the opportunity to participate in developing this AD. We have considered the comments received. Request to Change Compliance Time United Airlines (UAL) requested that we change the compliance time for the corrective actions specified in paragraphs (m), (o), and (p) of the NPRM (78 FR 28152, May 14, 2013) from ‘‘before further flight’’ to the following. • Within one deferral flight cycle, or the applicable time given in Paragraph E.(2), ‘‘Accomplish Timescale,’’ of Airbus Mandatory Service Bulletin VerDate Mar<15>2010 18:49 Dec 26, 2013 Jkt 232001 A320–25A1555, Revision 03, dated February 28, 2012, whichever is later. • Within 50 flight cycles or at the applicable time given in Paragraph E.(2), ‘‘Accomplish Timescale,’’ of Airbus Mandatory Service Bulletin A320– 25A1555, Revision 03, dated February 28, 2012, whichever is later. UAL stated that the first option would give operators a chance to fly a ferry flight to a more equipped resourced base maintenance station, and that the second option would give operators an option to create a short-term deferred item to plan for its accomplishment by creating a formal maintenance task with planned allocated resources. UAL stated that due to the inspection threshold and repeat interval of 500 flight cycles, it is concerned that the inspection will take place at mainly airplane line maintenance stations, with significant exposure to possible damage conditions that require correction before further flight. UAL commented that typical airplane line stations might not have the resources, materials, and equipment to perform this type of modification, repair, and access. UAL also stated that certain corrective actions require approximately 57 workhours, which would lead to lengthy outof-service time and costs to the airline. We do not agree with UAL’s request to extend the compliance time. The FAA AD provides a provision for operators to apply for a special flight permit in accordance with 14 CFR 21.197, which allows operators to fly airplanes to a base where repairs, alterations, or maintenance can be performed. These airplanes may not fully meet applicable airworthiness requirements, but are capable of safe flight for reasons stated in 14 CFR 21.197. In developing an appropriate compliance time for this final rule, we considered the urgency associated with the subject unsafe condition, the availability of required parts, and the practical aspect of accomplishing the required corrective actions. Some safety issues are more time-sensitive than others, so we consider the overall risk to the fleet, including the severity of the failure and the likelihood of the failure’s occurrence in establishing the compliance time in this final rule. The commenter has not provided sufficient substantiation for revising the corrective action compliance time for repairing certain damage conditions that will meet an acceptable level of safety to mitigate risk to the fleet. Under the provisions of paragraph (s) of this AD, we will consider requests for approval of an extension of the compliance time if sufficient data are submitted to substantiate that the new PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 compliance time would provide an acceptable level of safety. We have not changed this final rule in this regard. Additional Changes to This AD We have revised paragraph (o)(1) of this final rule to include the option of contacting the EASA (or its delegated agent) for repair instructions. Paragraph (p) of the NPRM (78 FR 28152, May 14, 2013) incorrectly referred to ‘‘paragraphs (m) and (o) of this AD’’ for certain special detailed inspections. Those special detailed inspections are specified in paragraphs (l) and (n) of this AD. We have revised paragraph (p) of this AD to refer to paragraphs (l) and (n) of this AD. Conclusion We reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these changes: • Are consistent with the intent that was proposed in the NPRM (78 FR 28152, May 14, 2013) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (78 FR 28152, May 14, 2013). Costs of Compliance We estimate that this AD affects about 755 products of U.S. registry. The actions that are required by AD 2010–24–07, Amendment 39–16526 (75 FR 75878, December 7, 2010), and retained in this AD, take about 82 workhours per product, at an average labor rate of $85 per work hour. Required parts cost about $2,592 per product. Based on these figures, the estimated cost of the currently required actions is $9,562 per product. We estimate that it takes about 5 work-hours per product to comply with the new basic requirements of this AD. The average labor rate is $85 per workhour. Where the service information lists parts costs that are covered under warranty, we have assumed that there will be no charge for these parts. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on these figures, we estimate the cost of this AD on U.S. operators to be $320,875, or $425 per product. In addition, we estimate that any necessary follow-on actions would take about 189 work-hours and require parts costing $7,047, for a cost of $23,112 per product. Where the service information lists required parts costs that are E:\FR\FM\27DER1.SGM 27DER1 Federal Register / Vol. 78, No. 249 / Friday, December 27, 2013 / Rules and Regulations covered under warranty, we have assumed that there will be no charge for these parts. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. We have no way of determining the number of products that may need these actions. through Friday, except Federal holidays. The AD docket contains this AD, the MCAI, 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. 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. List of Subjects in 14 CFR Part 39 tkelley on DSK3SPTVN1PROD with RULES Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 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. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2013-0416; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday VerDate Mar<15>2010 18:49 Dec 26, 2013 Jkt 232001 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) 2010–24–07, Amendment 39–16526 (75 FR 75878, December 7, 2010), and adding the following new AD: ■ 2013–25–11 Airbus: Amendment 39–17707. Docket No. FAA–2013–0416; Directorate Identifier 2012–NM–144–AD. (a) Effective Date This airworthiness directive (AD) becomes effective January 31, 2014. (b) Affected ADs This AD supersedes AD 2010–24–07, Amendment 39–16526 (75 FR 75878, December 7, 2010). (c) Applicability 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 A320–111, –211, –212, –214, –231, –232, and –233 airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes; certificated in any category; all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 25, Equipment/Furnishings; and Code 53, Fuselage. (e) Reason This AD was prompted by reports of worn lower lateral fittings of the 80VU rack. We are issuing this AD to detect and correct damage or cracking of the 80VU fittings and supports, which could lead to possible disconnection of the cable harnesses to one or more computers, and if occurring during a critical phase of flight, could result in reduced control of the airplane. PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 78707 (f) Compliance You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. (g) Retained Repetitive Inspections of the 80VU Rack Lower Lateral Fittings This paragraph restates the requirements of paragraph (g) of AD 2010–24–07, Amendment 39–16526 (75 FR 75878, December 7, 2010). Except for Model A318– 121 and –122 airplanes, and except for airplanes on which Airbus Modification 34804 has been embodied in production, or on which Airbus Service Bulletins A320–25– 1557 and A320–53–1215 have been done in service, prior to the accumulation of 24,000 total flight cycles, or within 500 flight cycles after January 11, 2011 (the effective date of AD 2010–24–07), whichever occurs later: Do a special detailed inspection of the 80VU rack lower lateral fittings for damage (e.g., broken fitting, missing bolts, migrated bushings, material burr, or rack in contact with the fitting) of the 80VU rack lower lateral fittings, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320–25A1555, Revision 02, dated November 5, 2008. Repeat the inspection thereafter at the interval specified in paragraph (g)(1) or (g)(2) of this AD, as applicable. Modifying the 80VU lower lateral fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–25–1557, Revision 02, dated November 5, 2008, terminates the inspection requirements of this paragraph. Doing the initial inspection specified in paragraph (l) of this AD terminates the requirements of this paragraph. (1) For airplanes on which the 80VU rack lower lateral fittings have not been replaced in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320–25A1555, Revision 02, dated November 5, 2008: Repeat the inspection thereafter at intervals not to exceed 4,500 flight cycles. (2) For airplanes on which the 80VU rack lower lateral fittings have been replaced in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320–25A1555, Revision 02, dated November 5, 2008: Do the next inspection within 24,000 flight cycles after doing the replacement and repeat the inspection thereafter at intervals not to exceed 4,500 flight cycles. (h) Retained Corrective Actions With Additional New Corrective Actions This paragraph restates the requirements of paragraph (h) of AD 2010–24–07, Amendment 39–16526 (75 FR 75878, December 7, 2010), with new corrective actions. If any damage is found during any inspection required by paragraph (g) of this AD, do all applicable corrective actions (inspection and/or repair), in accordance with the Accomplishment Instructions and timeframes in Airbus Mandatory Service Bulletin A320–25A1555, Revision 02, dated November 5, 2008; or in accordance with and at the time specified in paragraph (q) of this AD. As of the effective date of this AD, if any E:\FR\FM\27DER1.SGM 27DER1 78708 Federal Register / Vol. 78, No. 249 / Friday, December 27, 2013 / Rules and Regulations replacement terminates the inspection requirements of paragraph (i) of this AD. (i) Retained Repetitive Inspections of the 80VU Rack Lower Central Support This paragraph restates the requirements of paragraph (i) of AD 2010–24–07, Amendment 39–16526 (75 FR 75878, December 7, 2010). Except for airplanes on which Airbus Modification 34804 has been embodied in production or on which Airbus Service Bulletins A320–25–1557 and A320–53–1215 have been done in service, prior to the accumulation of 24,000 total flight cycles, or within 500 flight cycles after January 11, 2011 (the effective date of AD 2010–24–07), whichever occurs later: Do a special detailed inspection of the 80VU rack lower central support for cracking, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320–25A1555, Revision 02, dated November 5, 2008. Repeat the inspection thereafter at the interval specified in paragraph (i)(1) or (i)(2) of this AD, as applicable. Replacing the pyramid fitting on the 80VU rack with a new, reinforced fitting, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–53–1215, dated November 5, 2008, terminates the inspection requirements of this paragraph. Doing the initial inspection specified in paragraph (n) of this AD terminates the requirements of this paragraph. (1) For airplanes on which the 80VU rack lower central support has not been repaired or replaced using Airbus Mandatory Service Bulletin A320–25A1555 or Airbus Service Bulletin A320–25–1557: Repeat the inspection thereafter at the interval specified in paragraph (i)(1)(i) or (i)(1)(ii) of this AD, as applicable. (i) For airplanes on which the lower central support has accumulated 30,000 total flight cycles or more: At intervals not to exceed 500 flight cycles. (ii) For airplanes on which the lower central support has accumulated fewer than 30,000 total flight cycles: At intervals not to exceed 4,500 flight cycles, without exceeding 30,750 total flight cycles on the support for the first repetitive inspection. (2) For airplanes on which the 80VU rack lower central support has been repaired or replaced using Airbus Mandatory Service Bulletin A320–25A1555 or Airbus Service Bulletin A320–25–1557: Do the next inspection within 24,000 flight cycles after the repair or replacement and thereafter repeat the inspection at the interval specified in paragraph (i)(1)(i) or (i)(1)(ii) of this AD, as applicable. tkelley on DSK3SPTVN1PROD with RULES damage is found, do all applicable corrective actions in accordance with and at the times specified in paragraph (q) of this AD. This paragraph restates the requirements of paragraph (k) of AD 2010–24–07, Amendment 39–16526 (75 FR 75878, December 7, 2010). Doing the actions specified in paragraphs (k)(1) and (k)(2) of this AD terminates the repetitive inspections required by this AD. (1) Replacing the pyramid fitting on the 80VU rack with a new, reinforced fitting, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 53–1215, dated November 5, 2008. (2) Modifying the 80VU lower lateral fittings, in accordance with Airbus Service Bulletin A320–25–1557, Revision 02, dated November 5, 2008. (j) Retained Corrective Actions for Paragraph (i) of This AD This paragraph restates the requirements of paragraph (j) of AD 2010–24–07, Amendment 39–16526 (75 FR 75878, December 7, 2010). If any crack is found during any inspection required by paragraph (i) of this AD: Before further flight, replace the pyramid fitting on the 80VU rack with a new, reinforced fitting, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 53–1215, dated November 5, 2008. Doing this VerDate Mar<15>2010 18:49 Dec 26, 2013 Jkt 232001 (k) Retained Optional Terminating Action (l) New Requirement of This AD: Repetitive Inspection of Lower Lateral Support Fittings Except for airplanes on which Airbus Modification 34804 has been embodied in production, or on which the 80VU rack lower lateral support has been modified, as specified in the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320–25–1557, dated June 14, 2007; Revision 01, dated February 7, 2008; or Revision 02, dated November 5, 2008: At the latest of the applicable times specified in paragraphs (l)(1) through (l)(4) of this AD, do a special detailed (borescope) inspection of the 80VU rack lower lateral fittings for damage (e.g., broken fitting, missing bolts, migrated bushings, material burr, or rack in contact with the fitting), in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320–25A1555, Revision 03, dated February 28, 2012. Repeat the inspection thereafter at intervals not to exceed 500 flight cycles until the terminating action specified in paragraph (k) of this AD is done. Doing the initial inspection specified in this paragraph terminates the requirements of paragraph (g) of this AD. (1) Before the accumulation of 20,000 total flight cycles from the airplane first flight, or within 750 flight cycles after the effective date of this AD, whichever occurs later, without exceeding 24,000 total flight cycles. (2) Within 20,000 flight cycles after the most recent repair or replacement of the 80VU rack lower lateral fittings was done, as specified in the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320–25A1555, dated June 24, 2007; Revision 01, dated February 18, 2008; or Revision 02, dated November 5, 2008. (3) Within 500 flight cycles after the effective date of this AD, without exceeding 4,500 flight cycles after the most recent inspection of the 80VU rack lower lateral fittings was done, as specified in the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320–25A1555, dated June 14, 2007; Revision 01, dated February 18, 2008; or Revision 02, dated November 5, 2008. (4) Within 500 flight cycles after the effective date of this AD. PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 (m) New Requirement of This AD: Corrective Action for Damage of Lower Lateral Support Fittings If any damage is found during any inspection required by paragraph (l) of this AD: At the applicable time given in paragraph E.(2)., ‘‘Accomplishment Timescale,’’ in Airbus Mandatory Service Bulletin A320–25A1555, Revision 03, dated February 28, 2012, accomplish the applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320–25A1555, Revision 03, dated February 28, 2012; except where this service information specifies to contact Airbus for further instructions, before further flight, contact either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent) for instructions; and do those instructions. (n) New Requirement of This AD: Repetitive Inspection on Lower Central Support Except for airplanes on which Airbus Modification 34804 has been embodied in production, or on which the 80VU rack lower central support has been modified, as specified in the Accomplishment Instructions of Airbus Service Bulletin A320– 53–1215, dated November 5, 2008: At the latest of the applicable times specified in paragraphs (n)(1) through (n)(6) of this AD, do a special detailed (borescope) inspection of the 80VU rack lower central support for cracking, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320–25A1555, Revision 03, dated February 28, 2012. Repeat the inspection thereafter at intervals not to exceed 500 flight cycles until the terminating action specified in paragraph (k) of this AD is done. Doing the initial inspection specified in this paragraph terminates the requirements of paragraph (i) of this AD. (1) Before the accumulation of 20,000 total flight cycles from the airplane first flight, or within 750 flight cycles after the effective date of this AD, whichever occurs later, without exceeding 24,000 total flight cycles. (2) Within 20,000 flight cycles after the most recent repair or replacement of the 80VU rack lower central support was done, as specified in the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320–25A1555, dated June 14, 2007; Revision 01, dated February 18, 2008; or Revision 02, dated November 5, 2008. (3) Within 20,000 flight cycles after modification of the 80VU rack lower central support was done, as specified in the Accomplishment Instructions of Airbus Service Bulletin A320–25–1557, dated June 14, 2007; or Revision 01, dated February 07, 2008. (4) For airplanes on which, as of the effective date of this AD, the 80VU rack lower central support has accumulated fewer than 30,000 total flight cycles: Within 500 flight cycles after the effective date of this AD, without exceeding 4,500 flight cycles after the most recent inspection of the 80VU rack lower central support was done, as specified in the Accomplishment Instructions of Airbus Mandatory Service E:\FR\FM\27DER1.SGM 27DER1 Federal Register / Vol. 78, No. 249 / Friday, December 27, 2013 / Rules and Regulations Bulletin A320–25A1555, dated June 24, 2007; Revision 01, dated February 18, 2008; or Revision 02, dated November 5, 2008. (5) For airplanes on which, as of the effective date of this AD, the 80VU rack lower central support has accumulated 30,000 total flight cycles or more: Within 500 flight cycles after the most recent inspection of the 80VU rack lower central support was done, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320–25A1555, dated June 14, 2007; Revision 01, dated February 18, 2008; or Revision 02, dated November 5, 2008. (6) Within 500 flight cycles after the effective date of this AD. (o) New Requirement of This AD: Corrective Action for Damage to Lower Central Support If any cracking is found during any inspection required by paragraph (n) of this AD: Before further flight do the actions in paragraph (o)(1) or (o)(2) of this AD. (1) If kits 25A1555A01 thru A05 are available, contact the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent); for instructions and do the repair. (2) Do the actions specified in paragraph (k)(1) and (k)(2) of this AD. tkelley on DSK3SPTVN1PROD with RULES (p) New Requirement of This AD: Repetitive Inspection of Upper Fittings and Shelves Concurrently with each special detailed inspection required by paragraphs (l) and (n) of this AD: Do a general visual inspection for damage (cracking or deformation) of the upper fittings and shelves of the 80VU rack, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320–25A1555, Revision 03, dated February 28, 2012. If any damage is found: Before further flight, repair the damage using a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA (or its delegated agent). (q) New Requirement of This AD: Corrective Action for Previous Findings For airplanes that have been inspected before the effective date of this AD as specified in Airbus Service Bulletin A320– 25A1555, dated June 14, 2007; Airbus Mandatory Service Bulletin A320–25A1555, Revision 01, dated February 18, 2008; or Airbus Mandatory Service Bulletin A320– 25A1555, Revision 02, dated November 5, 2008; and on which damage of the fittings was found, except for airplanes specified in paragraph (q)(1) or (q)(2) of this AD: At the applicable time given in paragraph E.(2)., ‘‘Accomplishment Timescale,’’ of Airbus Mandatory Service Bulletin A320–25A1555, Revision 03, dated February 28, 2012, accomplish the applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320–25A1555, Revision 03, dated February 28, 2012, except where this service information specifies to contact Airbus for further instructions, before further flight, contact either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA (or its delegated VerDate Mar<15>2010 18:49 Dec 26, 2013 Jkt 232001 agent); for instructions and follow those instructions. Accomplishing the actions required by this paragraph terminates the requirements of paragraph (h) of this AD. (1) Airplanes on which Airbus Modification 34804 has been embodied in production. (2) Airplanes on which the terminating action specified in paragraph (k) of this AD has been done. (r) Credit for Previous Actions This paragraph restates the credit given in paragraph (l) of AD 2010–24–07, Amendment 39–16526 (75 FR 75878, December 7, 2010). (1) This paragraph provides credit for actions required by paragraphs (g), (h), and (i) of this AD, if those actions were performed before January 11, 2011 (the effective date of AD 2010–24–07, Amendment 39–16526 (75 FR 75878, December 7, 2010)), using the service bulletins specified in paragraph (r)(1)(i) or (r)(1)(ii) of this AD. (i) Airbus Mandatory Service Bulletin A320–25A1555, Revision 01, dated February 18, 2008, which is not incorporated by reference in this AD. (ii) Airbus Service Bulletin A320– 25A1555, dated June 14, 2007, which is not incorporated by reference in this AD. (2) This paragraph provides credit for actions required by paragraphs (g) and (k)(2) of this AD, if those actions were performed before January 11, 2011 (the effective date of AD 2010–24–07, Amendment 39–16526 (75 FR 75878, December 7, 2010)), using the service bulletins specified in paragraph (r)(2)(i) or (r)(2)(ii) of this AD. (i) Airbus Service Bulletin A320–25–1557, dated June 14, 2007, which is not incorporated by reference in this AD. (ii) Airbus Service Bulletin A320–25–1557, Revision 01, dated February 7, 2008, which is not incorporated by reference in this AD. (s) 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: 9ANM-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. AMOCs approved previously for AD 2010–24–07, Amendment 39–16526 (75 FR 75878, December 7, 2010), are approved as AMOCs for the corresponding provisions of this AD. PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 78709 (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 the Design Approval Holder with a State of Design Authority’s design organization approval, as applicable). For a repair method to be approved, the repair approval must specifically refer to this AD. You are required to ensure the product is airworthy before it is returned to service. (t) Related Information (1) Refer to Mandatory Continuing Airworthiness Information European Aviation Safety Agency Airworthiness Directive 2012–0134, dated July 18, 2012, for related information. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/ #!documentDetail;D=FAA-2013-0416-0002. (2) Service information identified in this AD that is not incorporated by reference may be obtained at the addresses specified in paragraphs (u)(5) and (u)(6) of this AD. (u) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on January 31, 2014. (i) Airbus Mandatory Service Bulletin A320–25A1555, Revision 03, dated February 28, 2012. (ii) Reserved. (4) The following service information was approved for IBR on January 11, 2011 (75 FR 75878, December 7, 2010). (i) Airbus Mandatory Service Bulletin A320–25A1555, Revision 02, excluding Appendix 1, dated November 5, 2008. (ii) Airbus Service Bulletin A320–25–1557, Revision 02, dated November 5, 2008. (iii) Airbus Service Bulletin A320–53– 1215, dated November 5, 2008. (5) For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airwortheas@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. E:\FR\FM\27DER1.SGM 27DER1 78710 Federal Register / Vol. 78, No. 249 / Friday, December 27, 2013 / Rules and Regulations Issued in Renton, Washington, on December 4, 2013. John P. Piccola, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. Examining the AD Docket [FR Doc. 2013–30066 Filed 12–26–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0340; Directorate Identifier 2010–SW–081–AD; Amendment 39–17630; AD 2013–21–06] RIN 2120–AA64 Airworthiness Directives; Eurocopter Deutschland GmbH Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (Eurocopter) Model EC135 P1, EC135 P2, EC135 P2+, EC135 T1, EC135 T2, EC135 T2+, and MBB–BK 117 C–2 helicopters with a certain external mounted hoist system (hoist) with boom support assembly (boom) installed. This AD requires inspecting the boom for a crack and, if a crack exists, replacing the boom with an airworthy boom. Until the boom is inspected, this AD requires, before further flight, and thereafter before the first flight of each day, checking the hoist for a crack. This AD was prompted by cracks found on the boom during a pre-flight check of a hoist on an MBB–BK 117 C–2 helicopter. The actions of this AD are intended to detect a crack and prevent failure of the boom, loss of the boom and attached loads, and subsequent loss of helicopter control. DATES: This AD is effective January 31, 2014. The Director of the Federal Register approved the incorporation by reference of a certain document listed in this AD as of January 31, 2014. ADDRESSES: For service information identified in this AD, contact American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232– 0323; fax (972) 641–3775; or at http:// www.eurocopter.com/techpub, and contact UTC Aerospace Systems (formerly the Goodrich Corporation), 2727 East Imperial Highway, Brea, CA 92821; telephone (714) 984–1461; fax 714–984–1675, or at www.goodrich.com. You may review the referenced service tkelley on DSK3SPTVN1PROD with RULES SUMMARY: VerDate Mar<15>2010 18:49 Dec 26, 2013 Jkt 232001 You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the foreign authority’s ADs, any incorporated-byreference service information, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (phone: 800–647–5527) is U.S. Department of Transportation, Docket Operations Office, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Matt Wilbanks, Aviation Safety Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email matt.wilbanks@faa.gov. SUPPLEMENTARY INFORMATION: Discussion On April 15, 2013, at 78 FR 22209, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 by adding an AD that would apply to Eurocopter Model EC135 P1, EC135 P2, EC135 P2+, EC135 T1, EC135 T2 and EC135 T2+ helicopters with a Goodrich Corporation (Goodrich) hoist with a boom, Part Number (P/N) 44301–500, 44307–500, or 44307–500–1 installed, and Model MBB–BK 117 C–2 helicopters with a Goodrich hoist with boom P/N 44307–500 installed. The NPRM proposed to require dye penetrant inspecting the boom for a crack and, if a crack exists, replacing the boom with an airworthy boom. Until the inspection is completed, the NPRM proposed to require, before the first flight of each day, a visual check of the hoist for a crack. The NPRM proposed to allow an owner/operator (pilot) holding at least a private pilot certificate to conduct that check. The performance of the check would be required to be entered into the aircraft’s maintenance records showing compliance with this AD in accordance with applicable regulations. This authorization marks an exception to our standard maintenance regulations. The proposed requirements were intended to detect a crack and prevent failure of the boom, loss of the PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 boom and attached loads, and subsequent loss of helicopter control. The NPRM was prompted by AD No. 2010–0154, dated August 13, 2010, issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union. EASA issued AD No. 2010–0154 to correct an unsafe condition for Eurocopter Model MBB– BK 117 C–2, EC135, and EC635 series helicopters. EASA AD No. 2010–0154 supersedes EASA AD No. 2009–0093–E, dated April 17, 2009. EASA advises that cracks were detected on the boom, P/N 44307–500, during a pre-flight check of the hoist on a Model MBB–BK 117 C– 2 helicopter. EASA advises that this condition, if not detected and corrected, would impair the structural strength of the boom and could lead to failure of the boom. EASA advises that this could result in the loss of the boom and attached loads. According to EASA, boom P/Ns 44301–500 and 44307–500– 1 are of similar design to P/N 44307– 500, and therefore are also subject to this unsafe condition. As a result, EASA issued Emergency AD No. 2009–0093–E to require repetitive visual checks of the affected boom and removal or replacement of the boom when cracks are found. EASA advises that since AD No. 2009–0093–E was issued, further technical investigation determined that torque values that were too high have been applied. EASA advises that Goodrich Corporation, the manufacturer of the affected booms, had developed an inspection that would determine the need for further action. As a result, EASA superseded its AD to include a new inspection to detect damage, by issuing EASA AD No. 2010–0154. EASA AD states that if no damage is found during this new inspection, that constitutes terminating action. Comments We gave the public the opportunity to participate in developing this AD, but we received no comments on the NPRM (78 FR 22209, April 15, 2013). FAA’s Determination These helicopters have been approved by the aviation authority of Germany and are approved for operation in the United States. Pursuant to our bilateral agreement with Germany, EASA, its technical representative, has notified us of the unsafe condition described in the EASA AD. We are issuing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs and that air E:\FR\FM\27DER1.SGM 27DER1

Agencies

[Federal Register Volume 78, Number 249 (Friday, December 27, 2013)]
[Rules and Regulations]
[Pages 78705-78710]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-30066]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0416; Directorate Identifier 2012-NM-144-AD; 
Amendment 39-17707; AD 2013-25-11]
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) 2010-24-07 for 
all Airbus Model A318 series airplanes, Model A319 series airplanes, 
Model A320 series airplanes, and Model A321 series airplanes. AD 2010-
24-07 required repetitive inspections of the 80VU rack lower lateral 
fittings for damage, repetitive inspections of the 80VU rack lower 
central support for cracking, and corrective action if necessary. AD 
2010-24-07 also specified optional terminating action for the 
repetitive inspections. This new AD reduces the inspection compliance 
time, adds an inspection of the upper fittings and shelves of the 80VU 
rack, and adds airplanes to the applicability. This AD was prompted by 
reports of worn lower lateral fittings of the 80VU rack. We are issuing 
this AD to detect and correct damage or cracking of the 80VU fittings 
and supports, which could lead to possible disconnection of the cable 
harnesses to one or more computers, and if occurring during a critical 
phase of flight, could result in reduced control of the airplane.

DATES: This AD becomes effective January 31, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 31, 
2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of January 
11, 2011 (75 FR 75878, December 7, 2010).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2013-0416; or in person at the 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC.

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

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to the specified products. The 
NPRM was published in the Federal Register on May 14, 2013 (78 FR 
28152), and proposed to supersede AD 2010-24-07, Amendment 39-16526 (75 
FR 75878, December 7, 2010). The NPRM proposed to correct an unsafe 
condition for the specified products. 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-
0134, dated July 18, 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:

    Damage to the lower lateral fittings of the 80VU rack, typically 
elongated holes, migrated bushes, and/or missing bolts have been 
reported on in-service aeroplanes. The 80VU rack contains computers 
for flight controls, communication and radio-navigation. In 
addition, damage to the lower

[[Page 78706]]

central support fitting (including cracking) has been reported.
    Failure of the 80VU fittings, in combination with a high load 
factor or strong vibration, could lead to failure of the rack 
structure and/or computers or rupture/disconnection of the cable 
harnesses to one or more computers located in the 80VU rack. Even 
though the computer functions are duplicated across other racks, 
multiple system failures or (partial) disconnection of systems, if 
occurring during a critical phase of flight, could result in reduced 
control of the aeroplane.
    To address this potential unsafe condition, EASA issued AD 2007-
0276 to require repetitive inspections of the lower lateral 80VU 
fittings and the lower central 80VU support and, depending on 
findings, the accomplishment of corrective actions. [EASA] AD 2007-
0276 was revised to introduce a reinforced lower central support as 
an optional terminating action for the repetitive inspections.
    Since issuance of EASA AD 2007-0276R1 [http://ad.easa.europa.eu/blob/easa_ad_2007_0276_R1_superseded.pdf/AD_2007-0276R1_1] 
[which corresponds to FAA AD 2010-24-07, Amendment 39-16526 (75 FR 
75878, December 7, 2010)], and prompted by in-service experience, 
the previous inspection programme has been reassessed. New 
conditions of inspection for a new finding on the lower central 
fitting attachment (crack in the lower of the lateral flanges), and 
a new visual inspection of the upper fittings and shelves of the 
80VU are introduced by this inspection programme. In addition, the 
replacement of a cracked lateral fitting or central support with a 
lateral fitting or central support having the same part number is no 
longer preferable as corrective action. Instead, the installation of 
the reinforced lower central support is now defined as optional 
terminating action for the repetitive inspections required by this 
[EASA] AD.
    For the reasons described above, this [EASA] AD supersedes EASA 
AD 2007-0276R1 and requires implementation of an amended inspection 
programme with a reduced inspection threshold.

You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0416-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We have considered the comments received.

Request to Change Compliance Time

    United Airlines (UAL) requested that we change the compliance time 
for the corrective actions specified in paragraphs (m), (o), and (p) of 
the NPRM (78 FR 28152, May 14, 2013) from ``before further flight'' to 
the following.
     Within one deferral flight cycle, or the applicable time 
given in Paragraph E.(2), ``Accomplish Timescale,'' of Airbus Mandatory 
Service Bulletin A320-25A1555, Revision 03, dated February 28, 2012, 
whichever is later.
     Within 50 flight cycles or at the applicable time given in 
Paragraph E.(2), ``Accomplish Timescale,'' of Airbus Mandatory Service 
Bulletin A320-25A1555, Revision 03, dated February 28, 2012, whichever 
is later.
    UAL stated that the first option would give operators a chance to 
fly a ferry flight to a more equipped resourced base maintenance 
station, and that the second option would give operators an option to 
create a short-term deferred item to plan for its accomplishment by 
creating a formal maintenance task with planned allocated resources.
    UAL stated that due to the inspection threshold and repeat interval 
of 500 flight cycles, it is concerned that the inspection will take 
place at mainly airplane line maintenance stations, with significant 
exposure to possible damage conditions that require correction before 
further flight. UAL commented that typical airplane line stations might 
not have the resources, materials, and equipment to perform this type 
of modification, repair, and access. UAL also stated that certain 
corrective actions require approximately 57 work-hours, which would 
lead to lengthy out-of-service time and costs to the airline.
    We do not agree with UAL's request to extend the compliance time. 
The FAA AD provides a provision for operators to apply for a special 
flight permit in accordance with 14 CFR 21.197, which allows operators 
to fly airplanes to a base where repairs, alterations, or maintenance 
can be performed. These airplanes may not fully meet applicable 
airworthiness requirements, but are capable of safe flight for reasons 
stated in 14 CFR 21.197. In developing an appropriate compliance time 
for this final rule, we considered the urgency associated with the 
subject unsafe condition, the availability of required parts, and the 
practical aspect of accomplishing the required corrective actions. Some 
safety issues are more time-sensitive than others, so we consider the 
overall risk to the fleet, including the severity of the failure and 
the likelihood of the failure's occurrence in establishing the 
compliance time in this final rule. The commenter has not provided 
sufficient substantiation for revising the corrective action compliance 
time for repairing certain damage conditions that will meet an 
acceptable level of safety to mitigate risk to the fleet.
    Under the provisions of paragraph (s) of this AD, we will consider 
requests for approval of an extension of the compliance time if 
sufficient data are submitted to substantiate that the new compliance 
time would provide an acceptable level of safety. We have not changed 
this final rule in this regard.

Additional Changes to This AD

    We have revised paragraph (o)(1) of this final rule to include the 
option of contacting the EASA (or its delegated agent) for repair 
instructions.
    Paragraph (p) of the NPRM (78 FR 28152, May 14, 2013) incorrectly 
referred to ``paragraphs (m) and (o) of this AD'' for certain special 
detailed inspections. Those special detailed inspections are specified 
in paragraphs (l) and (n) of this AD. We have revised paragraph (p) of 
this AD to refer to paragraphs (l) and (n) of this AD.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these changes:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 28152, May 14, 2013) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 28152, May 14, 2013).

Costs of Compliance

    We estimate that this AD affects about 755 products of U.S. 
registry.
    The actions that are required by AD 2010-24-07, Amendment 39-16526 
(75 FR 75878, December 7, 2010), and retained in this AD, take about 82 
work-hours per product, at an average labor rate of $85 per work hour. 
Required parts cost about $2,592 per product. Based on these figures, 
the estimated cost of the currently required actions is $9,562 per 
product.
    We estimate that it takes about 5 work-hours per product to comply 
with the new basic requirements of this AD. The average labor rate is 
$85 per work-hour. Where the service information lists parts costs that 
are covered under warranty, we have assumed that there will be no 
charge for these parts. As we do not control warranty coverage for 
affected parties, some parties may incur costs higher than estimated 
here. Based on these figures, we estimate the cost of this AD on U.S. 
operators to be $320,875, or $425 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 189 work-hours and require parts costing $7,047, for a cost 
of $23,112 per product. Where the service information lists required 
parts costs that are

[[Page 78707]]

covered under warranty, we have assumed that there will be no charge 
for these parts. As we do not control warranty coverage for affected 
parties, some parties may incur costs higher than estimated here. We 
have no way of determining the number of products that may need these 
actions.

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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2013-0416; or in person at the 
Docket Operations office between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The AD docket contains this AD, the 
MCAI, 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) 
2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010), and 
adding the following new AD:

2013-25-11 Airbus: Amendment 39-17707. Docket No. FAA-2013-0416; 
Directorate Identifier 2012-NM-144-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective January 31, 
2014.

(b) Affected ADs

    This AD supersedes AD 2010-24-07, Amendment 39-16526 (75 FR 
75878, December 7, 2010).

(c) Applicability

    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 A320-111, -211, -212, -214, -231, -232, and -
233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -
231, and -232 airplanes; certificated in any category; all 
manufacturer serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 25, Equipment/
Furnishings; and Code 53, Fuselage.

(e) Reason

    This AD was prompted by reports of worn lower lateral fittings 
of the 80VU rack. We are issuing this AD to detect and correct 
damage or cracking of the 80VU fittings and supports, which could 
lead to possible disconnection of the cable harnesses to one or more 
computers, and if occurring during a critical phase of flight, could 
result in reduced control of the airplane.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Retained Repetitive Inspections of the 80VU Rack Lower Lateral 
Fittings

    This paragraph restates the requirements of paragraph (g) of AD 
2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010). 
Except for Model A318-121 and -122 airplanes, and except for 
airplanes on which Airbus Modification 34804 has been embodied in 
production, or on which Airbus Service Bulletins A320-25-1557 and 
A320-53-1215 have been done in service, prior to the accumulation of 
24,000 total flight cycles, or within 500 flight cycles after 
January 11, 2011 (the effective date of AD 2010-24-07), whichever 
occurs later: Do a special detailed inspection of the 80VU rack 
lower lateral fittings for damage (e.g., broken fitting, missing 
bolts, migrated bushings, material burr, or rack in contact with the 
fitting) of the 80VU rack lower lateral fittings, in accordance with 
the Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A320-25A1555, Revision 02, dated November 5, 2008. Repeat the 
inspection thereafter at the interval specified in paragraph (g)(1) 
or (g)(2) of this AD, as applicable. Modifying the 80VU lower 
lateral fittings, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A320-25-1557, Revision 02, dated November 
5, 2008, terminates the inspection requirements of this paragraph. 
Doing the initial inspection specified in paragraph (l) of this AD 
terminates the requirements of this paragraph.
    (1) For airplanes on which the 80VU rack lower lateral fittings 
have not been replaced in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A320-25A1555, 
Revision 02, dated November 5, 2008: Repeat the inspection 
thereafter at intervals not to exceed 4,500 flight cycles.
    (2) For airplanes on which the 80VU rack lower lateral fittings 
have been replaced in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A320-25A1555, 
Revision 02, dated November 5, 2008: Do the next inspection within 
24,000 flight cycles after doing the replacement and repeat the 
inspection thereafter at intervals not to exceed 4,500 flight 
cycles.

(h) Retained Corrective Actions With Additional New Corrective Actions

    This paragraph restates the requirements of paragraph (h) of AD 
2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010), with 
new corrective actions. If any damage is found during any inspection 
required by paragraph (g) of this AD, do all applicable corrective 
actions (inspection and/or repair), in accordance with the 
Accomplishment Instructions and timeframes in Airbus Mandatory 
Service Bulletin A320-25A1555, Revision 02, dated November 5, 2008; 
or in accordance with and at the time specified in paragraph (q) of 
this AD. As of the effective date of this AD, if any

[[Page 78708]]

damage is found, do all applicable corrective actions in accordance 
with and at the times specified in paragraph (q) of this AD.

(i) Retained Repetitive Inspections of the 80VU Rack Lower Central 
Support

    This paragraph restates the requirements of paragraph (i) of AD 
2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010). 
Except for airplanes on which Airbus Modification 34804 has been 
embodied in production or on which Airbus Service Bulletins A320-25-
1557 and A320-53-1215 have been done in service, prior to the 
accumulation of 24,000 total flight cycles, or within 500 flight 
cycles after January 11, 2011 (the effective date of AD 2010-24-07), 
whichever occurs later: Do a special detailed inspection of the 80VU 
rack lower central support for cracking, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A320-25A1555, Revision 02, dated November 5, 2008. Repeat the 
inspection thereafter at the interval specified in paragraph (i)(1) 
or (i)(2) of this AD, as applicable. Replacing the pyramid fitting 
on the 80VU rack with a new, reinforced fitting, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A320-53-
1215, dated November 5, 2008, terminates the inspection requirements 
of this paragraph. Doing the initial inspection specified in 
paragraph (n) of this AD terminates the requirements of this 
paragraph.
    (1) For airplanes on which the 80VU rack lower central support 
has not been repaired or replaced using Airbus Mandatory Service 
Bulletin A320-25A1555 or Airbus Service Bulletin A320-25-1557: 
Repeat the inspection thereafter at the interval specified in 
paragraph (i)(1)(i) or (i)(1)(ii) of this AD, as applicable.
    (i) For airplanes on which the lower central support has 
accumulated 30,000 total flight cycles or more: At intervals not to 
exceed 500 flight cycles.
    (ii) For airplanes on which the lower central support has 
accumulated fewer than 30,000 total flight cycles: At intervals not 
to exceed 4,500 flight cycles, without exceeding 30,750 total flight 
cycles on the support for the first repetitive inspection.
    (2) For airplanes on which the 80VU rack lower central support 
has been repaired or replaced using Airbus Mandatory Service 
Bulletin A320-25A1555 or Airbus Service Bulletin A320-25-1557: Do 
the next inspection within 24,000 flight cycles after the repair or 
replacement and thereafter repeat the inspection at the interval 
specified in paragraph (i)(1)(i) or (i)(1)(ii) of this AD, as 
applicable.

(j) Retained Corrective Actions for Paragraph (i) of This AD

    This paragraph restates the requirements of paragraph (j) of AD 
2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010). If 
any crack is found during any inspection required by paragraph (i) 
of this AD: Before further flight, replace the pyramid fitting on 
the 80VU rack with a new, reinforced fitting, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-53-1215, 
dated November 5, 2008. Doing this replacement terminates the 
inspection requirements of paragraph (i) of this AD.

(k) Retained Optional Terminating Action

    This paragraph restates the requirements of paragraph (k) of AD 
2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010). 
Doing the actions specified in paragraphs (k)(1) and (k)(2) of this 
AD terminates the repetitive inspections required by this AD.
    (1) Replacing the pyramid fitting on the 80VU rack with a new, 
reinforced fitting, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-53-1215, dated November 
5, 2008.
    (2) Modifying the 80VU lower lateral fittings, in accordance 
with Airbus Service Bulletin A320-25-1557, Revision 02, dated 
November 5, 2008.

(l) New Requirement of This AD: Repetitive Inspection of Lower Lateral 
Support Fittings

    Except for airplanes on which Airbus Modification 34804 has been 
embodied in production, or on which the 80VU rack lower lateral 
support has been modified, as specified in the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A320-25-1557, 
dated June 14, 2007; Revision 01, dated February 7, 2008; or 
Revision 02, dated November 5, 2008: At the latest of the applicable 
times specified in paragraphs (l)(1) through (l)(4) of this AD, do a 
special detailed (borescope) inspection of the 80VU rack lower 
lateral fittings for damage (e.g., broken fitting, missing bolts, 
migrated bushings, material burr, or rack in contact with the 
fitting), in accordance with the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A320-25A1555, Revision 03, dated 
February 28, 2012. Repeat the inspection thereafter at intervals not 
to exceed 500 flight cycles until the terminating action specified 
in paragraph (k) of this AD is done. Doing the initial inspection 
specified in this paragraph terminates the requirements of paragraph 
(g) of this AD.
    (1) Before the accumulation of 20,000 total flight cycles from 
the airplane first flight, or within 750 flight cycles after the 
effective date of this AD, whichever occurs later, without exceeding 
24,000 total flight cycles.
    (2) Within 20,000 flight cycles after the most recent repair or 
replacement of the 80VU rack lower lateral fittings was done, as 
specified in the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A320-25A1555, dated June 24, 2007; Revision 01, 
dated February 18, 2008; or Revision 02, dated November 5, 2008.
    (3) Within 500 flight cycles after the effective date of this 
AD, without exceeding 4,500 flight cycles after the most recent 
inspection of the 80VU rack lower lateral fittings was done, as 
specified in the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A320-25A1555, dated June 14, 2007; Revision 01, 
dated February 18, 2008; or Revision 02, dated November 5, 2008.
    (4) Within 500 flight cycles after the effective date of this 
AD.

(m) New Requirement of This AD: Corrective Action for Damage of Lower 
Lateral Support Fittings

    If any damage is found during any inspection required by 
paragraph (l) of this AD: At the applicable time given in paragraph 
E.(2)., ``Accomplishment Timescale,'' in Airbus Mandatory Service 
Bulletin A320-25A1555, Revision 03, dated February 28, 2012, 
accomplish the applicable corrective actions, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A320-25A1555, Revision 03, dated February 28, 2012; except where 
this service information specifies to contact Airbus for further 
instructions, before further flight, contact either the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the European Aviation Safety Agency (EASA) (or its delegated 
agent) for instructions; and do those instructions.

(n) New Requirement of This AD: Repetitive Inspection on Lower Central 
Support

    Except for airplanes on which Airbus Modification 34804 has been 
embodied in production, or on which the 80VU rack lower central 
support has been modified, as specified in the Accomplishment 
Instructions of Airbus Service Bulletin A320-53-1215, dated November 
5, 2008: At the latest of the applicable times specified in 
paragraphs (n)(1) through (n)(6) of this AD, do a special detailed 
(borescope) inspection of the 80VU rack lower central support for 
cracking, in accordance with the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A320-25A1555, Revision 03, dated 
February 28, 2012. Repeat the inspection thereafter at intervals not 
to exceed 500 flight cycles until the terminating action specified 
in paragraph (k) of this AD is done. Doing the initial inspection 
specified in this paragraph terminates the requirements of paragraph 
(i) of this AD.
    (1) Before the accumulation of 20,000 total flight cycles from 
the airplane first flight, or within 750 flight cycles after the 
effective date of this AD, whichever occurs later, without exceeding 
24,000 total flight cycles.
    (2) Within 20,000 flight cycles after the most recent repair or 
replacement of the 80VU rack lower central support was done, as 
specified in the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A320-25A1555, dated June 14, 2007; Revision 01, 
dated February 18, 2008; or Revision 02, dated November 5, 2008.
    (3) Within 20,000 flight cycles after modification of the 80VU 
rack lower central support was done, as specified in the 
Accomplishment Instructions of Airbus Service Bulletin A320-25-1557, 
dated June 14, 2007; or Revision 01, dated February 07, 2008.
    (4) For airplanes on which, as of the effective date of this AD, 
the 80VU rack lower central support has accumulated fewer than 
30,000 total flight cycles: Within 500 flight cycles after the 
effective date of this AD, without exceeding 4,500 flight cycles 
after the most recent inspection of the 80VU rack lower central 
support was done, as specified in the Accomplishment Instructions of 
Airbus Mandatory Service

[[Page 78709]]

Bulletin A320-25A1555, dated June 24, 2007; Revision 01, dated 
February 18, 2008; or Revision 02, dated November 5, 2008.
    (5) For airplanes on which, as of the effective date of this AD, 
the 80VU rack lower central support has accumulated 30,000 total 
flight cycles or more: Within 500 flight cycles after the most 
recent inspection of the 80VU rack lower central support was done, 
in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A320-25A1555, dated June 14, 2007; 
Revision 01, dated February 18, 2008; or Revision 02, dated November 
5, 2008.
    (6) Within 500 flight cycles after the effective date of this 
AD.

(o) New Requirement of This AD: Corrective Action for Damage to Lower 
Central Support

    If any cracking is found during any inspection required by 
paragraph (n) of this AD: Before further flight do the actions in 
paragraph (o)(1) or (o)(2) of this AD.
    (1) If kits 25A1555A01 thru A05 are available, contact the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or the European Aviation Safety Agency (EASA) (or 
its delegated agent); for instructions and do the repair.
    (2) Do the actions specified in paragraph (k)(1) and (k)(2) of 
this AD.

(p) New Requirement of This AD: Repetitive Inspection of Upper Fittings 
and Shelves

    Concurrently with each special detailed inspection required by 
paragraphs (l) and (n) of this AD: Do a general visual inspection 
for damage (cracking or deformation) of the upper fittings and 
shelves of the 80VU rack, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A320-25A1555, 
Revision 03, dated February 28, 2012. If any damage is found: Before 
further flight, repair the damage using a method approved by either 
the Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or EASA (or its delegated agent).

(q) New Requirement of This AD: Corrective Action for Previous Findings

    For airplanes that have been inspected before the effective date 
of this AD as specified in Airbus Service Bulletin A320-25A1555, 
dated June 14, 2007; Airbus Mandatory Service Bulletin A320-25A1555, 
Revision 01, dated February 18, 2008; or Airbus Mandatory Service 
Bulletin A320-25A1555, Revision 02, dated November 5, 2008; and on 
which damage of the fittings was found, except for airplanes 
specified in paragraph (q)(1) or (q)(2) of this AD: At the 
applicable time given in paragraph E.(2)., ``Accomplishment 
Timescale,'' of Airbus Mandatory Service Bulletin A320-25A1555, 
Revision 03, dated February 28, 2012, accomplish the applicable 
corrective actions, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A320-25A1555, 
Revision 03, dated February 28, 2012, except where this service 
information specifies to contact Airbus for further instructions, 
before further flight, contact either the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA (or 
its delegated agent); for instructions and follow those 
instructions. Accomplishing the actions required by this paragraph 
terminates the requirements of paragraph (h) of this AD.
    (1) Airplanes on which Airbus Modification 34804 has been 
embodied in production.
    (2) Airplanes on which the terminating action specified in 
paragraph (k) of this AD has been done.

(r) Credit for Previous Actions

    This paragraph restates the credit given in paragraph (l) of AD 
2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010).
    (1) This paragraph provides credit for actions required by 
paragraphs (g), (h), and (i) of this AD, if those actions were 
performed before January 11, 2011 (the effective date of AD 2010-24-
07, Amendment 39-16526 (75 FR 75878, December 7, 2010)), using the 
service bulletins specified in paragraph (r)(1)(i) or (r)(1)(ii) of 
this AD.
    (i) Airbus Mandatory Service Bulletin A320-25A1555, Revision 01, 
dated February 18, 2008, which is not incorporated by reference in 
this AD.
    (ii) Airbus Service Bulletin A320-25A1555, dated June 14, 2007, 
which is not incorporated by reference in this AD.
    (2) This paragraph provides credit for actions required by 
paragraphs (g) and (k)(2) of this AD, if those actions were 
performed before January 11, 2011 (the effective date of AD 2010-24-
07, Amendment 39-16526 (75 FR 75878, December 7, 2010)), using the 
service bulletins specified in paragraph (r)(2)(i) or (r)(2)(ii) of 
this AD.
    (i) Airbus Service Bulletin A320-25-1557, dated June 14, 2007, 
which is not incorporated by reference in this AD.
    (ii) Airbus Service Bulletin A320-25-1557, Revision 01, dated 
February 7, 2008, which is not incorporated by reference in this AD.

(s) 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. 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. AMOCs 
approved previously for AD 2010-24-07, Amendment 39-16526 (75 FR 
75878, December 7, 2010), are approved as AMOCs for the 
corresponding provisions of 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 the Design Approval Holder with a State of 
Design Authority's design organization approval, as applicable). For 
a repair method to be approved, the repair approval must 
specifically refer to this AD. You are required to ensure the 
product is airworthy before it is returned to service.

(t) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
European Aviation Safety Agency Airworthiness Directive 2012-0134, 
dated July 18, 2012, for related information. You may examine the 
MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0416-0002.
    (2) Service information identified in this AD that is not 
incorporated by reference may be obtained at the addresses specified 
in paragraphs (u)(5) and (u)(6) of this AD.

 (u) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
January 31, 2014.
    (i) Airbus Mandatory Service Bulletin A320-25A1555, Revision 03, 
dated February 28, 2012.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
January 11, 2011 (75 FR 75878, December 7, 2010).
    (i) Airbus Mandatory Service Bulletin A320-25A1555, Revision 02, 
excluding Appendix 1, dated November 5, 2008.
    (ii) Airbus Service Bulletin A320-25-1557, Revision 02, dated 
November 5, 2008.
    (iii) Airbus Service Bulletin A320-53-1215, dated November 5, 
2008.
    (5) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com.
    (6) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.



[[Page 78710]]


    Issued in Renton, Washington, on December 4, 2013.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-30066 Filed 12-26-13; 8:45 am]
BILLING CODE 4910-13-P