Airworthiness Directives; Airbus Airplanes, 38573-38576 [2016-13856]

Download as PDF Federal Register / Vol. 81, No. 114 / Tuesday, June 14, 2016 / Rules and Regulations Correction In FR Doc. 2016–11908 beginning on page 33098 in the Federal Register of May 24, 2016, make the following correction: Correction 1. On page 33098, in the first column, in the document heading, revise ‘‘[Docket No.: FAA–2014–0554; Amdt. Nos. 1–69, 11–59, 121–374, 125–65, and 135–133]’’ to read ‘‘[Docket No.: FAA– 2014–0554; Amdt. Nos. 1–69, 11–60, 121–374, 125–65, and 135–133]’’. Issued under authority provided by 49 U.S.C. 106(f) in Washington, DC, on June 1, 2016. Dale A. Bouffiou, Acting Director, Office of Rulemaking. [FR Doc. 2016–13955 Filed 6–13–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–6899; Directorate Identifier 2016–NM–066–AD; Amendment 39–18558; AD 2016–12–09] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: We are superseding Airworthiness Directive (AD) 2016–09– 11 for certain Airbus Model A330–200, –200 Freighter, and –300 series airplanes; and Model A340–200 and –300 series airplanes. AD 2016–09–11 required removing fasteners, doing a rototest inspection of fastener holes, installing new fasteners, oversizing the holes and doing rototest inspections for cracks if necessary, and repairing any cracking that is found. This new AD requires the same actions as AD 2016– 09–11, but includes Model A330–300 series airplanes in paragraph (g)(2) of this AD. This AD was prompted by the discovery of missing affected airplanes in paragraph (g)(2) of AD 2016–09–11 that resulted from converting a table in the proposed AD to text in AD 2016–09– 11. We are issuing this AD to detect and correct cracking on certain holes of certain frames of the center wing box (CWB), which could affect the structural integrity of the airplane. sradovich on DSK3TPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 This AD is effective June 29, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 13, 2016 (81 FR 27986, May 9, 2016). We must receive comments on this AD by July 29, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this final rule, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 45 80; email: airworthiness.A330-A340@airbus.com; Internet: https://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6899. DATES: 16:33 Jun 13, 2016 Jkt 238001 Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6899; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: 425–227–1138; fax: 425–227–1149. PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 38573 SUPPLEMENTARY INFORMATION: Discussion On April 21, 2016, we issued AD 2016–09–11, Amendment 39–18509 (81 FR 27986, May 9, 2016) (‘‘AD 2016–09– 11’’), for certain Airbus Model A330– 200, –200 Freighter, and –300 series airplanes; and Model A340–200 and –300 series airplanes. AD 2016–09–11 was prompted by reports that cracks were found on an adjacent hole of certain frames of the CWB. AD 2016– 09–11 required removing fasteners, doing a rototest inspection of fastener holes, installing new fasteners, oversizing the holes and doing rototest inspections for cracks if necessary, and repairing any cracking that was found. We issued AD 2016–09–11 to detect and correct cracking on certain holes of certain frames of the CWB that could affect the structural integrity of the airplane. Since we issued AD 2016–09–11, we discovered missing affected airplanes in paragraph (g)(2) of AD 2016–09–11 that resulted from converting a table to text in that AD. We stated in the preamble of AD 2016–09–11 that we revised the format of paragraph (g) of that AD, at the request of the Office of the Federal Register, by converting the table to text. We also stated this change to the format does not affect the requirements of that paragraph. However, in converting the table to text, we inadvertently omitted Model A330–300 series airplanes from paragraph (g)(2) of AD 2016–09–11. We have changed paragraph (g)(2) of this AD to include Model A330–300 series airplanes. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0149, dated June 13, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A330–200, –200 Freighter, and –300 series airplanes; and Model A340– 200 and –300 series airplanes. The MCAI states: During accomplishment of A330 Airworthiness Limitation Item (ALI) task 57– 11–04 on the rear fitting of the Frame (FR) 40 between stringers 38 and 39 on both [lefthand] LH/[right-hand] RH sides, cracks were found on an adjacent hole. After reaming at second oversize of the subject hole, the crack was still present. Other crack findings on this adjacent hole have been reported on A330 and A340–200/ –300 aeroplanes as a result of sampling inspections. E:\FR\FM\14JNR1.SGM 14JNR1 38574 Federal Register / Vol. 81, No. 114 / Tuesday, June 14, 2016 / Rules and Regulations This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. For the reasons described above, this [EASA] AD requires removal of the fasteners and repetitive rototest inspections of fastener holes at FR40 vertical web located above Center Wing Box (CWB) lower panel reference and/or below CWB lower panel reference on both sides and, depending on findings, accomplishment of the applicable corrective actions. Note: These holes affected by this [EASA] AD are different from the ones affected by EASA AD 2009–0001 [https:// ad.easa.europa.eu/blob/easa_ad_2009_ 0001.pdf/AD_2009–0001_1]. Required actions also include oversizing certain holes, installing new fasteners, and repairing any cracking that is found. The initial compliance times range from 13,500 to 30,900 flight cycles, or 57,000 to 162,000 flight hours, depending on airplane operation and utilization. The repetitive compliance times are 7,400 flight cycles/24,300 flight hours or 5,950 flight cycles/40,400 flight hours from ALI embodiment. You may examine the MCAI on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2016–6899. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. The service information describes procedures for removing the fasteners and doing a repetitive rototest inspection of fastener holes at FR40 vertical web on both sides, installing new fasteners in transition fit, and oversizing the holes. • Airbus Service Bulletin A330–57– 3114, dated March 12, 2013. • Airbus Service Bulletin A330–57– 3115, dated April 4, 2013. • Airbus Service Bulletin A330–57– 3116, dated March 12, 2013. • Airbus Service Bulletin A340–57– 4123, dated March 12, 2013. • Airbus Service Bulletin A340–57– 4124, Revision 01, dated August 22, 2013. • Airbus Service Bulletin A340–57– 4125, dated March 12, 2013. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA’s Determination and Requirements of This AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of these same type designs. FAA’s Justification and Determination of the Effective Date We are superseding AD 2016–09–11 to correct an error in the regulatory text that we made when we converted a table to text in paragraph (g)(2) of AD 2016–09–11. No other changes have been made to AD 2016–09–11. Therefore, we determined that notice and opportunity for prior public comment are unnecessary. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2016–6899; Directorate Identifier 2016–NM–066– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. Costs of Compliance We estimate that this AD affects 35 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Cost on U.S. operators Action Labor cost Parts cost Cost per product Inspection ......... 78 work-hours × $85 per hour = $6,630 per inspection cycle. $0 $6,630 per inspection cycle .......... We estimate the following costs to do any necessary repairs that will be required based on the results of the inspection. We have no way of $232,050 per inspection cycle. determining the number of airplanes that might need this repair: ON-CONDITION COSTS Labor cost Parts cost Cost per product Oversize, installation, and inspection ........................... sradovich on DSK3TPTVN1PROD with RULES Action 98 work-hours × $85 per hour = $8,330 ...................... $136,400 $144,730 We have received no definitive data that will enable us to provide cost estimates for the on-condition repair specified in this AD. VerDate Sep<11>2014 16:33 Jun 13, 2016 Jkt 238001 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 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 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 E:\FR\FM\14JNR1.SGM 14JNR1 Federal Register / Vol. 81, No. 114 / Tuesday, June 14, 2016 / Rules and Regulations 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. 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. [Amended] 2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2016–09–11, Amendment 39–18509 (81 FR 27986, May 9, 2016), and adding the following new AD: sradovich on DSK3TPTVN1PROD with RULES ■ 2016–12–09 Airbus: Amendment 39–18558. Docket No. FAA–2016–6899; Directorate Identifier 2016–NM–066–AD. (a) Effective Date This AD is effective June 29, 2016. VerDate Sep<11>2014 16:33 Jun 13, 2016 Jkt 238001 This AD replaces AD 2016–09–11, Amendment 39–18509 (81 FR 27986, May 9, 2016) (‘‘AD 2016–09–11’’). (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category, all manufacturer serial numbers, except those on which Airbus Modification (Mod) 55792 or Mod 55306 has been embodied in production, and except those on which Airbus Repair Instruction R57115092 has been embodied in service on both right-hand (RH) and left-hand (LH) sides. (1) Airbus Model A330–201, –202, –203, –223, –223F, –243 –243F, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes. (2) Airbus Model A340–211, –212, –213, –311, –312, and –313 airplanes. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by reports that cracks were found on an adjacent hole of certain frames of the center wing box (CWB). We are issuing this AD to detect and correct cracking on certain holes of the CWB, which could affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection List of Subjects in 14 CFR Part 39 § 39.13 (b) Affected ADs Do a rototest inspection of the fastener holes at the frame (FR) 40 vertical web, on both sides, as specified in paragraphs (g)(1) through (g)(6) of this AD, except as required by paragraph (k) of this AD. (1) For Model A330–300 series airplanes in pre-mod 44360 configuration: At the later of the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD, inspect below the CWB lower panel reference, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–57–3114, dated March 12, 2013. (i) At the applicable time specified in paragraph 1.E., ‘‘Compliance’’ of Airbus Service Bulletin A330–57–3114, dated March 12, 2013. (ii) Within 2,400 flight cycles or 24 months after the effective date of this AD, whichever occurs first. (2) For Model A330–200 and –300 series airplanes in post-mod 44360 and pre-mod 49202 configuration: At the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD, inspect below the CWB lower panel reference, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–57–3116, dated March 12, 2013. (i) At the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Airbus Service Bulletin A330–57–3116, dated March 12, 2013. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 38575 (ii) Within 2,400 flight cycles or 24 months after the effective date of this AD, whichever occurs first. (3) For Model A330–200 and –300 series airplanes in pre-mod 55306 and pre-mod 55792 configuration: At the later of the times specified in paragraphs (g)(3)(i) and (g)(3)(ii) of this AD, inspect above the CWB lower panel reference, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–57–3115, dated April 4, 2013. (i) At the applicable time specified in paragraph 1.E., ‘‘Compliance’’ of Airbus Service Bulletin A330–57–3115, dated April 4, 2013. (ii) Within 2,400 flight cycles or 24 months after the effective date of this AD, whichever occurs first. (4) For Model A340–200 and –300 series airplanes in pre-mod 44360 configuration: At the later of the times specified in paragraphs (g)(4)(i) and (g)(4)(ii) of this AD, inspect below the CWB lower panel reference, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340– 57–4123, dated March 12, 2013. (i) At the applicable time specified in paragraph 1.E., ‘‘Compliance’’ of Airbus Service Bulletin A330–57–4123, dated March 12, 2013. (ii) Within 1,300 flight cycles or 24 months after the effective date of this AD, whichever occurs first. (5) For Model A340–200 and –300 series airplanes in pre-mod 55306 and pre-mod 55792 configuration: At the later of the times specified in paragraphs (g)(5)(i) and (g)(5)(ii) of this AD, inspect above the CWB lower panel reference, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340–57–4124, Revision 01, dated August 22, 2013. (i) At the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Airbus Service Bulletin A340–57–4124, Revision 01, dated August 22, 2013. (ii) Within 1,300 flight cycles or 24 months after the effective date of this AD, whichever occurs first. (6) For Model A340–200 and –300 series airplanes in post-mod 44360 and pre-mod 49202 configuration: At the later of the times specified in paragraphs (g)(6)(i) and (g)(6)(ii) of this AD, inspect below the CWB lower panel reference, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340–57–4125, dated March 12, 2013. (i) At the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Airbus Service Bulletin A340–57–4125, dated March 12, 2013. (ii) Within 1,300 flight cycles or 24 months after the effective date of this AD, whichever occurs first. (h) Follow-On Actions: No Cracking If no crack is found during any inspection required by paragraph (g) of this AD, do the actions specified in paragraphs (h)(1) and (h)(2) of this AD. (1) Before further flight, install new fasteners in the transition fit, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g) of this AD. E:\FR\FM\14JNR1.SGM 14JNR1 38576 Federal Register / Vol. 81, No. 114 / Tuesday, June 14, 2016 / Rules and Regulations (2) Repeat the inspection required by paragraph (g) of this AD thereafter at the applicable time identified in paragraph 1.E., ‘‘Compliance,’’ of the applicable service information identified in paragraph (g) of this AD. (i) Follow-On Actions: Crack Findings If any crack is found during any inspection required by paragraph (g) of this AD: Before further flight, oversize the holes to the first oversize in comparison with the current hole diameter, and do a rototest inspection for cracks, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g) of this AD. (1) If no cracking is found during the rototest inspection required by paragraph (i) of this AD, do the actions specified in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD. (i) Before further flight: Install new fasteners in the transition fit, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g) of this AD. (ii) Repeat the inspection required by paragraph (g) of this AD thereafter at the applicable time identified in paragraph 1.E., ‘‘Compliance,’’ of the applicable service information identified in paragraph (g) of this AD. (2) If cracking is found during the rototest inspection required by paragraph (i) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). sradovich on DSK3TPTVN1PROD with RULES (j) Terminating Action Specifications Accomplishment of the initial and repetitive inspections required by this AD terminates accomplishment of Airworthiness Limitation Items Tasks 57–11–04 and 57–11– 02 of the Airworthiness Limitation Section (ALS) Part 2, Damage Tolerant Airworthiness Limitation Items (DT ALI). (1) Installation of new fasteners, as specified in paragraph (h)(1) of this AD, does not terminate the repetitive inspections required by paragraph (g) of this AD. (2) Accomplishment of the corrective actions specified in the introductory text of paragraph (i) and paragraph (i)(1) of this AD does not terminate the repetitive inspections required by paragraph (g) of this AD. (3) Accomplishment of the repair specified in paragraph (i)(2) of this AD does not terminate repetitive inspections required by paragraph (g) of this AD, unless the approved repair method specifies otherwise. (k) Exceptions to Service Information (1) If the applicable service information identified in paragraph (g) of this AD specifies contacting Airbus for appropriate action: Before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the EASA; or Airbus’s EASA DOA. (2) Where paragraph 1.E., ‘‘Compliance,’’ of the applicable service information specified in paragraph (g) of this AD specifies a compliance time in terms of a ‘‘Threshold’’ VerDate Sep<11>2014 16:33 Jun 13, 2016 Jkt 238001 and ‘‘Grace Period,’’ this AD requires compliance at the later of the applicable threshold and grace period. (3) Where paragraph 1.E., ‘‘Compliance,’’ of the applicable service information specified in paragraph (g) of this AD specifies a threshold as ‘‘before next flight,’’ this AD requires compliance before the next flight after the applicable finding. actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (l) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (g) and (i) of this AD, if those actions were performed before the effective date of this AD using the applicable service information specified in paragraph (l)(1), (l)(2), (l)(3), (l)(4), (l)(5), (l)(6), (l)(7), (l)(8), or (l)(9) of this AD. This service information is not incorporated by reference in this AD. (1) Airbus Technical Disposition LR57D11023270, Issue B, dated July 12, 2011. (2) Airbus Technical Disposition LR57D11029171, Issue B, dated September 6, 2011. (3) Airbus Technical Disposition LR57D11029173, Issue B, dated September 6, 2011. (4) Airbus Technical Disposition LR57D11030741, Issue B, dated September 22, 2011. (5) Airbus Technical Disposition LR57D11029170, Issue C, dated September 6, 2011. (6) Airbus Technical Disposition LR57D11023714, Issue B, dated July 12, 2011. (7) Airbus Technical Disposition LR57D11029172, Issue B, dated September 6, 2011. (8) Airbus Technical Disposition LR57D11030740, Issue C, dated September 22, 2011. (9) Airbus Service Bulletin A340–57–4124, dated April 4, 2013. (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0149, dated June 13, 2014, for related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA– 2016–6899. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (o)(4) and (o)(5) of this AD. (m) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: 425–227–1138; 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. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective PO 00000 Frm 00008 Fmt 4700 Sfmt 9990 (n) Related Information (o) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on June 13, 2016, (81 FR 27986, May 9, 2016). (i) Airbus Service Bulletin A330–57–3114, dated March 12, 2013. (ii) Airbus Service Bulletin A330–57–3115, dated April 4, 2013. (iii) Airbus Service Bulletin A330–57– 3116, dated March 12, 2013. (iv) Airbus Service Bulletin A340–57– 4123, dated March 12, 2013. (v) Airbus Service Bulletin A340–57–4124, Revision 01, dated August 22, 2013. (vi) Airbus Service Bulletin A340–57– 4125, dated March 12, 2013. (4) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 45 80; email: airworthiness.A330-A340@airbus.com; Internet: https://www.airbus.com. (5) 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. (6) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives. gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on June 3, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–13856 Filed 6–13–16; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\14JNR1.SGM 14JNR1

Agencies

[Federal Register Volume 81, Number 114 (Tuesday, June 14, 2016)]
[Rules and Regulations]
[Pages 38573-38576]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-13856]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6899; Directorate Identifier 2016-NM-066-AD; 
Amendment 39-18558; AD 2016-12-09]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule; request for comments.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2016-09-11 for 
certain Airbus Model A330-200, -200 Freighter, and -300 series 
airplanes; and Model A340-200 and -300 series airplanes. AD 2016-09-11 
required removing fasteners, doing a rototest inspection of fastener 
holes, installing new fasteners, oversizing the holes and doing 
rototest inspections for cracks if necessary, and repairing any 
cracking that is found. This new AD requires the same actions as AD 
2016-09-11, but includes Model A330-300 series airplanes in paragraph 
(g)(2) of this AD. This AD was prompted by the discovery of missing 
affected airplanes in paragraph (g)(2) of AD 2016-09-11 that resulted 
from converting a table in the proposed AD to text in AD 2016-09-11. We 
are issuing this AD to detect and correct cracking on certain holes of 
certain frames of the center wing box (CWB), which could affect the 
structural integrity of the airplane.

DATES: This AD is effective June 29, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of June 13, 2016 
(81 FR 27986, May 9, 2016).
    We must receive comments on this AD by July 29, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this final rule, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 
61 93 45 80; email: airworthiness.A330-A340@airbus.com; Internet: 
https://www.airbus.com. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at the 
FAA, call 425-227-1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6899.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6899; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., proposed AD, the regulatory evaluation, any comments received, 
and other information. The street address for the Docket Operations 
office (telephone: 800-647-5527) is in the ADDRESSES section. Comments 
will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1138; 
fax: 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    On April 21, 2016, we issued AD 2016-09-11, Amendment 39-18509 (81 
FR 27986, May 9, 2016) (``AD 2016-09-11''), for certain Airbus Model 
A330-200, -200 Freighter, and -300 series airplanes; and Model A340-200 
and -300 series airplanes. AD 2016-09-11 was prompted by reports that 
cracks were found on an adjacent hole of certain frames of the CWB. AD 
2016-09-11 required removing fasteners, doing a rototest inspection of 
fastener holes, installing new fasteners, oversizing the holes and 
doing rototest inspections for cracks if necessary, and repairing any 
cracking that was found. We issued AD 2016-09-11 to detect and correct 
cracking on certain holes of certain frames of the CWB that could 
affect the structural integrity of the airplane.
    Since we issued AD 2016-09-11, we discovered missing affected 
airplanes in paragraph (g)(2) of AD 2016-09-11 that resulted from 
converting a table to text in that AD. We stated in the preamble of AD 
2016-09-11 that we revised the format of paragraph (g) of that AD, at 
the request of the Office of the Federal Register, by converting the 
table to text. We also stated this change to the format does not affect 
the requirements of that paragraph.
    However, in converting the table to text, we inadvertently omitted 
Model A330-300 series airplanes from paragraph (g)(2) of AD 2016-09-11. 
We have changed paragraph (g)(2) of this AD to include Model A330-300 
series airplanes.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0149, dated June 13, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A330-200, -200 Freighter, and -300 series airplanes; and Model A340-200 
and -300 series airplanes. The MCAI states:

    During accomplishment of A330 Airworthiness Limitation Item 
(ALI) task 57-11-04 on the rear fitting of the Frame (FR) 40 between 
stringers 38 and 39 on both [left-hand] LH/[right-hand] RH sides, 
cracks were found on an adjacent hole. After reaming at second 
oversize of the subject hole, the crack was still present.
    Other crack findings on this adjacent hole have been reported on 
A330 and A340-200/-300 aeroplanes as a result of sampling 
inspections.

[[Page 38574]]

    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    For the reasons described above, this [EASA] AD requires removal 
of the fasteners and repetitive rototest inspections of fastener 
holes at FR40 vertical web located above Center Wing Box (CWB) lower 
panel reference and/or below CWB lower panel reference on both sides 
and, depending on findings, accomplishment of the applicable 
corrective actions.

    Note: These holes affected by this [EASA] AD are different from 
the ones affected by EASA AD 2009-0001 [https://ad.easa.europa.eu/blob/easa_ad_2009_0001.pdf/AD_2009-0001_1].
    Required actions also include oversizing certain holes, installing 
new fasteners, and repairing any cracking that is found. The initial 
compliance times range from 13,500 to 30,900 flight cycles, or 57,000 
to 162,000 flight hours, depending on airplane operation and 
utilization. The repetitive compliance times are 7,400 flight cycles/
24,300 flight hours or 5,950 flight cycles/40,400 flight hours from ALI 
embodiment. You may examine the MCAI on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6899.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information. The service 
information describes procedures for removing the fasteners and doing a 
repetitive rototest inspection of fastener holes at FR40 vertical web 
on both sides, installing new fasteners in transition fit, and 
oversizing the holes.
     Airbus Service Bulletin A330-57-3114, dated March 12, 
2013.
     Airbus Service Bulletin A330-57-3115, dated April 4, 2013.
     Airbus Service Bulletin A330-57-3116, dated March 12, 
2013.
     Airbus Service Bulletin A340-57-4123, dated March 12, 
2013.
     Airbus Service Bulletin A340-57-4124, Revision 01, dated 
August 22, 2013.
     Airbus Service Bulletin A340-57-4125, dated March 12, 
2013.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

FAA's Determination and Requirements of This AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are issuing this AD because we 
evaluated all pertinent information and determined the unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

FAA's Justification and Determination of the Effective Date

    We are superseding AD 2016-09-11 to correct an error in the 
regulatory text that we made when we converted a table to text in 
paragraph (g)(2) of AD 2016-09-11. No other changes have been made to 
AD 2016-09-11. Therefore, we determined that notice and opportunity for 
prior public comment are unnecessary.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2016-6899; Directorate 
Identifier 2016-NM-066-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD because of 
those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    We estimate that this AD affects 35 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
          Action                  Labor cost          Parts cost       Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Inspection................  78 work-hours x $85                $0   $6,630 per inspection  $232,050 per
                             per hour = $6,630                       cycle.                 inspection cycle.
                             per inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs that 
will be required based on the results of the inspection. We have no way 
of determining the number of airplanes that might need this repair:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Oversize, installation, and inspection.......  98 work-hours x $85 per hour =         $136,400         $144,730
                                                $8,330.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that will enable us to provide 
cost estimates for the on-condition repair specified in this AD.

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

[[Page 38575]]

promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing airworthiness directive (AD) 
2016-09-11, Amendment 39-18509 (81 FR 27986, May 9, 2016), and adding 
the following new AD:

2016-12-09 Airbus: Amendment 39-18558. Docket No. FAA-2016-6899; 
Directorate Identifier 2016-NM-066-AD.

(a) Effective Date

    This AD is effective June 29, 2016.

(b) Affected ADs

    This AD replaces AD 2016-09-11, Amendment 39-18509 (81 FR 27986, 
May 9, 2016) (``AD 2016-09-11'').

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
and (c)(2) of this AD, certificated in any category, all 
manufacturer serial numbers, except those on which Airbus 
Modification (Mod) 55792 or Mod 55306 has been embodied in 
production, and except those on which Airbus Repair Instruction 
R57115092 has been embodied in service on both right-hand (RH) and 
left-hand (LH) sides.
    (1) Airbus Model A330-201, -202, -203, -223, -223F, -243 -243F, 
-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes.
    (2) Airbus Model A340-211, -212, -213, -311, -312, and -313 
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by reports that cracks were found on an 
adjacent hole of certain frames of the center wing box (CWB). We are 
issuing this AD to detect and correct cracking on certain holes of 
the CWB, which could affect the structural integrity of the 
airplane.

(f) Compliance

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

(g) Inspection

    Do a rototest inspection of the fastener holes at the frame (FR) 
40 vertical web, on both sides, as specified in paragraphs (g)(1) 
through (g)(6) of this AD, except as required by paragraph (k) of 
this AD.
    (1) For Model A330-300 series airplanes in pre-mod 44360 
configuration: At the later of the times specified in paragraphs 
(g)(1)(i) and (g)(1)(ii) of this AD, inspect below the CWB lower 
panel reference, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A330-57-3114, dated March 12, 2013.
    (i) At the applicable time specified in paragraph 1.E., 
``Compliance'' of Airbus Service Bulletin A330-57-3114, dated March 
12, 2013.
    (ii) Within 2,400 flight cycles or 24 months after the effective 
date of this AD, whichever occurs first.
    (2) For Model A330-200 and -300 series airplanes in post-mod 
44360 and pre-mod 49202 configuration: At the later of the times 
specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD, inspect 
below the CWB lower panel reference, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-57-3116, 
dated March 12, 2013.
    (i) At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Airbus Service Bulletin A330-57-3116, dated March 
12, 2013.
    (ii) Within 2,400 flight cycles or 24 months after the effective 
date of this AD, whichever occurs first.
    (3) For Model A330-200 and -300 series airplanes in pre-mod 
55306 and pre-mod 55792 configuration: At the later of the times 
specified in paragraphs (g)(3)(i) and (g)(3)(ii) of this AD, inspect 
above the CWB lower panel reference, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-57-3115, 
dated April 4, 2013.
    (i) At the applicable time specified in paragraph 1.E., 
``Compliance'' of Airbus Service Bulletin A330-57-3115, dated April 
4, 2013.
    (ii) Within 2,400 flight cycles or 24 months after the effective 
date of this AD, whichever occurs first.
    (4) For Model A340-200 and -300 series airplanes in pre-mod 
44360 configuration: At the later of the times specified in 
paragraphs (g)(4)(i) and (g)(4)(ii) of this AD, inspect below the 
CWB lower panel reference, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A340-57-4123, dated March 
12, 2013.
    (i) At the applicable time specified in paragraph 1.E., 
``Compliance'' of Airbus Service Bulletin A330-57-4123, dated March 
12, 2013.
    (ii) Within 1,300 flight cycles or 24 months after the effective 
date of this AD, whichever occurs first.
    (5) For Model A340-200 and -300 series airplanes in pre-mod 
55306 and pre-mod 55792 configuration: At the later of the times 
specified in paragraphs (g)(5)(i) and (g)(5)(ii) of this AD, inspect 
above the CWB lower panel reference, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A340-57-4124, 
Revision 01, dated August 22, 2013.
    (i) At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Airbus Service Bulletin A340-57-4124, Revision 
01, dated August 22, 2013.
    (ii) Within 1,300 flight cycles or 24 months after the effective 
date of this AD, whichever occurs first.
    (6) For Model A340-200 and -300 series airplanes in post-mod 
44360 and pre-mod 49202 configuration: At the later of the times 
specified in paragraphs (g)(6)(i) and (g)(6)(ii) of this AD, inspect 
below the CWB lower panel reference, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A340-57-4125, 
dated March 12, 2013.
    (i) At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Airbus Service Bulletin A340-57-4125, dated March 
12, 2013.
    (ii) Within 1,300 flight cycles or 24 months after the effective 
date of this AD, whichever occurs first.

(h) Follow-On Actions: No Cracking

    If no crack is found during any inspection required by paragraph 
(g) of this AD, do the actions specified in paragraphs (h)(1) and 
(h)(2) of this AD.
    (1) Before further flight, install new fasteners in the 
transition fit, in accordance with the Accomplishment Instructions 
of the applicable service information identified in paragraph (g) of 
this AD.

[[Page 38576]]

    (2) Repeat the inspection required by paragraph (g) of this AD 
thereafter at the applicable time identified in paragraph 1.E., 
``Compliance,'' of the applicable service information identified in 
paragraph (g) of this AD.

(i) Follow-On Actions: Crack Findings

    If any crack is found during any inspection required by 
paragraph (g) of this AD: Before further flight, oversize the holes 
to the first oversize in comparison with the current hole diameter, 
and do a rototest inspection for cracks, in accordance with the 
Accomplishment Instructions of the applicable service information 
identified in paragraph (g) of this AD.
    (1) If no cracking is found during the rototest inspection 
required by paragraph (i) of this AD, do the actions specified in 
paragraphs (i)(1)(i) and (i)(1)(ii) of this AD.
    (i) Before further flight: Install new fasteners in the 
transition fit, in accordance with the Accomplishment Instructions 
of the applicable service information identified in paragraph (g) of 
this AD.
    (ii) Repeat the inspection required by paragraph (g) of this AD 
thereafter at the applicable time identified in paragraph 1.E., 
``Compliance,'' of the applicable service information identified in 
paragraph (g) of this AD.
    (2) If cracking is found during the rototest inspection required 
by paragraph (i) of this AD: Before further flight, repair using a 
method approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or the European Aviation Safety 
Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).

(j) Terminating Action Specifications

    Accomplishment of the initial and repetitive inspections 
required by this AD terminates accomplishment of Airworthiness 
Limitation Items Tasks 57-11-04 and 57-11-02 of the Airworthiness 
Limitation Section (ALS) Part 2, Damage Tolerant Airworthiness 
Limitation Items (DT ALI).
    (1) Installation of new fasteners, as specified in paragraph 
(h)(1) of this AD, does not terminate the repetitive inspections 
required by paragraph (g) of this AD.
    (2) Accomplishment of the corrective actions specified in the 
introductory text of paragraph (i) and paragraph (i)(1) of this AD 
does not terminate the repetitive inspections required by paragraph 
(g) of this AD.
    (3) Accomplishment of the repair specified in paragraph (i)(2) 
of this AD does not terminate repetitive inspections required by 
paragraph (g) of this AD, unless the approved repair method 
specifies otherwise.

(k) Exceptions to Service Information

    (1) If the applicable service information identified in 
paragraph (g) of this AD specifies contacting Airbus for appropriate 
action: Before further flight, repair using a method approved by the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or the EASA; or Airbus's EASA DOA.
    (2) Where paragraph 1.E., ``Compliance,'' of the applicable 
service information specified in paragraph (g) of this AD specifies 
a compliance time in terms of a ``Threshold'' and ``Grace Period,'' 
this AD requires compliance at the later of the applicable threshold 
and grace period.
    (3) Where paragraph 1.E., ``Compliance,'' of the applicable 
service information specified in paragraph (g) of this AD specifies 
a threshold as ``before next flight,'' this AD requires compliance 
before the next flight after the applicable finding.

(l) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g) and (i) of this AD, if those actions were performed 
before the effective date of this AD using the applicable service 
information specified in paragraph (l)(1), (l)(2), (l)(3), (l)(4), 
(l)(5), (l)(6), (l)(7), (l)(8), or (l)(9) of this AD. This service 
information is not incorporated by reference in this AD.
    (1) Airbus Technical Disposition LR57D11023270, Issue B, dated 
July 12, 2011.
    (2) Airbus Technical Disposition LR57D11029171, Issue B, dated 
September 6, 2011.
    (3) Airbus Technical Disposition LR57D11029173, Issue B, dated 
September 6, 2011.
    (4) Airbus Technical Disposition LR57D11030741, Issue B, dated 
September 22, 2011.
    (5) Airbus Technical Disposition LR57D11029170, Issue C, dated 
September 6, 2011.
    (6) Airbus Technical Disposition LR57D11023714, Issue B, dated 
July 12, 2011.
    (7) Airbus Technical Disposition LR57D11029172, Issue B, dated 
September 6, 2011.
    (8) Airbus Technical Disposition LR57D11030740, Issue C, dated 
September 22, 2011.
    (9) Airbus Service Bulletin A340-57-4124, dated April 4, 2013.

(m) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone: 425-227-1138; 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) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; 
or Airbus's EASA DOA. If approved by the DOA, the approval must 
include the DOA-authorized signature.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0149, dated June 13, 2014, 
for related information. This MCAI may be found in the AD docket on 
the Internet at https://www.regulations.gov by searching for and 
locating Docket No. FAA-2016-6899.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (o)(4) and (o)(5) of this AD.

(o) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
June 13, 2016, (81 FR 27986, May 9, 2016).
    (i) Airbus Service Bulletin A330-57-3114, dated March 12, 2013.
    (ii) Airbus Service Bulletin A330-57-3115, dated April 4, 2013.
    (iii) Airbus Service Bulletin A330-57-3116, dated March 12, 
2013.
    (iv) Airbus Service Bulletin A340-57-4123, dated March 12, 2013.
    (v) Airbus Service Bulletin A340-57-4124, Revision 01, dated 
August 22, 2013.
    (vi) Airbus Service Bulletin A340-57-4125, dated March 12, 2013.
    (4) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; 
fax: +33 5 61 93 45 80; email: airworthiness.A330-A340@airbus.com; 
Internet: https://www.airbus.com.
    (5) 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.
    (6) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on June 3, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-13856 Filed 6-13-16; 8:45 am]
 BILLING CODE 4910-13-P

This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.