Airworthiness Directives; Airbus Airplanes, 21236-21240 [2016-07373]

Download as PDF 21236 Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations (3) Will not affect intrastate aviation in Alaska to the extent that a regulatory; 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: (g) Alternative Methods of Compliance (AMOCs) 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) 2010–23–02, Amendment 39–16491 (75 FR 68169, November 5, 2010), and adding the following new AD: ■ 2016–07–26 Airbus Helicopters (previously Eurocopter France): Amendment 39– 18471; Docket No. FAA–2015–4112; Directorate Identifier 2014–SW–043–AD. (a) Applicability This AD applies to Model SA–365N, SA– 365N1, AS–365N2, and AS 365 N3 helicopters, with a horizontal stabilizer, part number 365A13–3030–1901, –1902, –1903, –1904, –1905, –1906, –1908, –1909; 365A13– 3036–00, –0001, –0002, –0003; or 365A13– 3038–00, installed, except those with modification 0755B28 installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as vibration during descent at high speed. This condition could result in failure of the horizontal stabilizer and subsequent loss of control of the helicopter. (c) Affected ADs This AD replaces AD 2010–23–02, Amendment 39–16491 (75 FR 68169, November 5, 2010). jstallworth on DSK7TPTVN1PROD with RULES (d) Effective Date This AD becomes effective May 16, 2016. (e) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (f) Required Actions Before further flight: (1) Revise the airspeed operating limitation in the Limitations section of the Rotorcraft VerDate Sep<11>2014 14:13 Apr 08, 2016 Jkt 238001 Flight Manual (RFM) by making pen and ink changes or by inserting a copy of this AD into the RFM stating: ‘‘The never-exceed speed (VNE) is limited to 150 knots indicated airspeed (KIAS)’’ and ‘‘The rate-of-descent (R/D) must not exceed 1,500 ft/min when the airspeed is beyond 140 KIAS.’’ (2) Install one or more self-adhesive placards, with 6 millimeter red letters on white background, on the cockpit instrument panel in full view of the pilot and co-pilot to read as follows: ‘‘VNE LIMITED TO 150 KIAS’’ and ‘‘R/D MUST NOT EXCEED 1,500 ft/min when airspeed is beyond 140 KIAS’’ (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Robert Grant, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Fort Worth, Texas 76177; telephone (817) 222–5110; email 9-asw-ftwamoc-requests@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC. (h) Additional Information (1) Eurocopter Emergency Alert Service Bulletin (EASB) No. 01.00.60, 01.00.16, and 01.28, Revision 1, dated December 2, 2008, and Airbus Helicopters Service Bulletin No. AS365–55.00.06, Revision 0, dated November 14, 2014, which are not incorporated by reference, contain additional information about the subject of this final rule. For service information identified in this final rule, contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at https:// www.airbushelicopters.com/techpub. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. (2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2008–0204R1, dated May 21, 2014. You may view the EASA AD on the Internet at https://www.regulations.gov in Docket No. FAA–2015–4112. (i) Subject Joint Aircraft Service Component (JASC) Code 5310: Horizontal Stabilizer Structure. Issued in Fort Worth, Texas, on March 31, 2016. James A. Grigg, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2016–07981 Filed 4–8–16; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2014-0775; Directorate Identifier 2014–NM–046–AD; Amendment 39–18467; AD 2016–07–22] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 B4–600, B4–600R, and F4–600R series airplanes, Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes), and Model A310 series airplanes. This AD was prompted by reports of insufficient clearance for the electrical wiring bundles in the leading and trailing edges of the right-hand (RH) and left-hand (LH) wings. This AD requires modifying the electrical routing installation at the RH and LH wings. We are issuing this AD to prevent insufficient clearance of electrical wiring bundles located in the leading and trailing edges of the RH and LH wings, which could lead to chafing damage and arcing, possibly resulting in an on-board fire. DATES: This AD becomes effective May 16, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of May 16, 2016. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0775; or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. For service information identified in this final rule, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet 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 SUMMARY: E:\FR\FM\11APR1.SGM 11APR1 Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations 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–2014– 0775. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: jstallworth on DSK7TPTVN1PROD with RULES Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Model A300 B4–600, B4–600R, and F4–600R series airplanes and Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes); and Model A310 series airplanes. The NPRM published in the Federal Register on November 21, 2014 (79 FR 69377) (‘‘the NPRM’’). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015–0176, dated August 25, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A300 B4–600, B4–600R, and F4– 600R series airplanes, and Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes); and Model A310 series airplanes. The MCAI states: Following publication of FAA SFAR 88 (Special Federal Aviation Regulation 88) [https://rgl.faa.gov/Regulatory_and_ Guidance_Library%5CrgFAR.nsf/0/EEFB3 F94451DC06286256C93004F5E07? OpenDocument), EASA issued AD 2006– 0076 (https://ad.easa.europa.eu/ad/2006– 0076] requiring inspection and corrective action to improve the explosion risk protection system for the left hand (LH) and right hand (RH) wings on A300, A300–600, A300–600ST and A310 aeroplanes. For A300–600, A300–600ST and A310 aeroplanes, the required detailed visual inspections of electrical bundles located in the leading and trailing edges of the RH and LH wings and a review of the wing electrical installation on the final assembly line have shown that the wing electrical installation does not comply with the minimum distance inspection criteria to the surrounding structure in a few wing locations. This condition, if not detected and corrected, could lead to damage on the electrical harnesses and on the surrounding structure. To address this unsafe condition, Airbus developed an improvement of the wing electrical installation to prevent possible VerDate Sep<11>2014 14:13 Apr 08, 2016 Jkt 238001 chafing and subsequent damage to the electrical harnesses and surrounding structure. Consequently EASA issued AD 2014–0034 [https://www.regulations.gov/ #!documentDetail;D=FAA–2014–0775–0002] to require installation of new bracket assemblies to ensure the clearance between the wiring and the structure, and installation of protective split sleeves as mechanical protection to the electrical harnesses. Since EASA AD 2014–0034 was issued, during embodiment of Airbus Service Bulletin (SB) A300–24–6103 Revision 02 on an aeroplane, an installation problem was identified, which prompted Airbus to revise SB A300–24–9014 Revision 01, and A300– 24–6103 Revision 02. Service Bulletin Information Transmission (SBIT) 14–0044 Revision 01 dated 06 February 2015 recommended to postpone embodiment of these two SB’s, and to wait for the availability of Airbus SB A300–24– 9014 Revision 02 and A300–24–6103 Revision 03. For the reasons described above, this [EASA]AD retains the requirement of the EASA AD 2014–0034, which is superseded, and requires in addition for the A300–600 and A300–600ST aeroplanes only, installation of new bracket assemblies in shroud box (LH and RH side) to ensure adequate clearance between wirings and flap track carriage (LH and RH side). Required actions include modifying the electrical routing installation at the RH and LH wings by installing new bracket assemblies to ensure adequate clearance between the wiring and the structure, and installing protective split sleeves as mechanical protection to the electrical harnesses. You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov/ #!documentDetail;D=FAA-2014-07750002. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA’s response to each comment. Requests To Use the Latest Service Information FedEx and United Parcel Service (UPS) requested that the NPRM reference the latest revision of Airbus Service Bulletin A300–24–6103, Revision 02, dated February 7, 2013. UPS stated that Airbus released an operators information transmission in October 2014, which stated that an operator reported that the installation of the clamps was not possible. UPS and FedEx stated that a revised version of the service information should be mandated. We agree with the commenters’ request. Since the NPRM was issued, we PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 21237 have reviewed Airbus Service Bulletin A300–24–6103, Revision 03, dated July 3, 2015, excluding Appendices 01, 02, 03, and 04, Revision 03, dated July 3, 2015; and Airbus Service Bulletin A310–24–2105, Revision 02, dated January 5, 2015, excluding Appendix 01, Revision 02, dated January 5, 2015. Airbus Service Bulletin A300–24–6103, Revision 03, dated July 3, 2015, excluding Appendices 01, 02, 03, and 04, Revision 03, dated July 3, 2015, adds an installation of new bracket assemblies in the shroud box (LH and RH sides) to the modification. Airbus Service Bulletin A310–24–2105, Revision 02, dated January 5, 2015, excluding Appendix 01, Revision 02, dated January 5, 2015, only includes minor changes to the modification. We have updated paragraphs (g) and (h) of this AD accordingly. Similar to the MCAI, credit is not given for Airbus Service Bulletin A300–24–6103, Revision 02, dated February 7, 2013. Request To Revise Costs of Compliance Section FedEx requested that we revise the Costs of Compliance section of the NPRM. FedEx stated that the 37 workhour estimate is consistent with what is specified in Airbus Service Bulletin A300–24–6103, Revision 02, dated February 7, 2013. However, FedEx stated that Airbus Service Bulletin A310–24–2105, Revision 01, dated December 11, 2013, shows an estimate of up to 55.5 work-hours, and does not include preparation and set up time. Airbus also stated that, from their experience, the work-hours tend to be understated compared to the actual time required to accomplish the actions. FedEx commented that it believes an estimate of 60 work-hours is more realistic. FedEx stated that it must be noted that 102 FedEx-registered airplanes are listed in the effectivity section of both service bulletins, and that the overall cost assessment omits the fact that over half of the total U.S. fleet cost will be borne by a single operator. We agree with the commenter’s request to revise the estimated costs of compliance; however, we have used the cost estimate identified in Airbus Service Bulletin A310–24–2105, Revision 02, dated January 5, 2015, excluding Appendix 01, Revision 02, dated January 5, 2015, which does include access and close-up work-hours. We have revised the Costs of Compliance section of this final rule to specify up to 56 work-hours per product to comply with the basic requirements of this AD. E:\FR\FM\11APR1.SGM 11APR1 21238 Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations jstallworth on DSK7TPTVN1PROD with RULES Request To Supersede and Revise the Affected ADs Paragraph of the Proposed AD FedEx requested that AD 2006–22–07, Amendment 39–14800 (71 FR 62890, October 27, 2006) (‘‘AD 2006–22–07’’), be listed as an affected AD in the proposed AD, and that the NPRM supersede AD 2006–22–07. FedEx stated that the manufacturer has linked the NPRM to AD 2006–22–07. FedEx commented that it has complied with the proposed requirements of the proposed AD, and all but two airplanes were found to be compliant with the clearance requirements specified in the applicable service information. FedEx stated that it has contacted the manufacturer for an approved method of compliance. FedEx stated that Airbus issued an EASAapproved technical adaptation requiring that the affected wire bundles be wrapped and a repetitive inspection be performed until a permanent fix is available. FedEx stated that the permanent fix is ‘‘Airbus Service Bulletin A300–24–6103,’’ which was specified in the NPRM. FedEx commented that the manufacturer has linked the NPRM to AD 2006–22–07 because Airbus Service Bulletin A300–24–6103 will act as terminating action for the requirements of AD 2006–22–07 and the NPRM. FedEx also stated that it thinks that all airplanes that comply with AD 2006– 22–07 without requiring additional permanent modifications should be exempt from the NPRM. We agree that AD 2006–22–07 and this AD are related; however, we disagree with the commenter’s request to supersede AD 2006–22–07 and include that AD as an affected AD in paragraph (b) of this AD. We also disagree with the commenter’s request to exempt airplanes that comply with AD 2006–22–07 from this AD. Prior issues of Airbus Service Bulletin A300–24–6103 (issued before Revision 03, dated July 3, 2015) are not acceptable for compliance with this AD because this AD and AD 2006–22–07 address two different unsafe conditions and require different corrective actions. AD 2006–22–07 and prior issues of Airbus Service Bulletin A300–24–6103 (issued before Revision 03, dated July 3, 2015) do not address insufficient clearance of electrical wiring bundles located in the leading and trailing edges of the RH and LH wings, which is the unsafe condition identified in this final rule. Additional actions are required in Airbus Service Bulletin A300–24–6103, Revision 03, dated July 3, 2015, to address the unsafe conditions identified VerDate Sep<11>2014 14:13 Apr 08, 2016 Jkt 238001 by this final rule that were not addressed on airplanes modified using previous issues of Airbus Service Bulletin A300–24–6103. Therefore, this final rule will not supersede AD 2006–22–07. Regardless of the findings or corrective actions accomplished in accordance with AD 2006–22–07, the service information in this final rule must still be required. We have not change this final rule in this regard. Conclusion We reviewed the relevant data, considered the comments 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 minor changes: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A300–24–6103, Revision 03, dated July 3, 2015, excluding Appendices 01, 02, 03, and 04, Revision 03, dated July 3, 2015; and Service Bulletin A310–24– 2105, Revision 02, dated January 5, 2015, excluding Appendix 01, Revision 02, dated January 5, 2015. The service information describes procedures for modifying the electrical routing installation at the RH and LH wings. 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. Explanation of ‘‘RC’’ Procedures and Tests in Service Information The FAA worked in conjunction with industry, under the Airworthiness Directive Implementation Aviation Rulemaking Committee (ARC), to enhance the AD system. One enhancement was a new process for annotating which procedures and tests in the service information are required for compliance with an AD. Differentiating these procedures and tests from other tasks in the service information is expected to improve an owner’s/operator’s understanding of crucial AD requirements and help provide consistent judgment in AD compliance. The procedures and tests PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 identified as Required for Compliance (RC) in any service information have a direct effect on detecting, preventing, resolving, or eliminating an identified unsafe condition. As specified in a NOTE under the Accomplishment Instructions of the specified service information, procedures and tests that are identified as RC in any service information must be done to comply with the AD. However, procedures and tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC will require approval of an AMOC. Costs of Compliance We estimate that this AD affects 199 airplanes of U.S. registry. We also estimate that it will take about 56 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts would cost up to $18,000 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $4,529,240, or $22,760 per product. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on E:\FR\FM\11APR1.SGM 11APR1 Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0775; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): jstallworth on DSK7TPTVN1PROD with RULES ■ 2016–07–22 Airbus: Amendment 39–18467. Docket No. FAA–2014–0775; Directorate Identifier 2014–NM–046–AD. (a) Effective Date This AD becomes effective May 16, 2016. (b) Affected ADs None. VerDate Sep<11>2014 14:13 Apr 08, 2016 Jkt 238001 (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category. (1) All Airbus Model A300 B4–601, B4– 603, B4–620, and B4–622 airplanes; Model A300 B4–605R and B4–622R airplanes; Model A300 F4–605R and F4–622R airplanes; and Model A300 C4–605R Variant F airplanes. (2) All Airbus Model A310–203, –204, –221, –222, –304, –322, –324, and –325 airplanes. (d) Subject Air Transport Association (ATA) of America Code 24, Electrical Power. (e) Reason This AD was prompted by reports of insufficient clearance for the electrical wiring bundles in the leading and trailing edges of the right-hand (RH) and left-hand (LH) wings. We are issuing this AD to detect and correct insufficient clearance of electrical wiring bundles located in the leading and trailing edges of the RH and LH wings, which could lead to chafing damage and arcing, possibly resulting in an on-board fire. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Modification Within 30 months after the effective date of this AD: Modify the electrical routing installation at the RH and LH wings in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 24–6103, Revision 03, July 3, 2015, excluding Appendices 01, 02, 03, and 04, Revision 03, dated July 3, 2015; or Airbus Service Bulletin A310–24–2105, Revision 02, dated January 5, 2015, excluding Appendix 01, Revision 02, dated January 5, 2015; as applicable; except as required by paragraph (h) of this AD. (h) Exception to Service Information If, during any modification required by paragraph (g) of this AD: Any gap between the structure and the clamp has insufficient clearance, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–24–6103, Revision 03, July 3, 2015, excluding Appendices 01, 02, 03, and 04, Revision 03, dated July 3, 2015; or Airbus Service Bulletin A310–24–2105, Revision 02, dated January 5, 2015, excluding Appendix 01, Revision 02, dated January 5, 2015; as applicable; 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). (i) Credit for Previous Actions This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A310–24–2105, dated March 20, 2013; or Airbus Service Bulletin A310–24– 2105, Revision 01, dated December 11, 2013. PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 21239 (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone (425) 227–2125; fax (425) 227– 1149. Information may be emailed to: 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 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 EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as required by paragraph (h) of this AD: If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015–0176, dated August 25, 2015, for related information. This MCAI may be found in the AD docket on the Internet at https:// www.regulations.gov/ #!documentDetail;D=FAA-2014-0775-0002. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (l)(3) and (l)(4) of this AD. (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. E:\FR\FM\11APR1.SGM 11APR1 21240 Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Service Bulletin A300–24–6103, Revision 03, dated July 3, 2015, excluding Appendices 01, 02, 03, and 04, Revision 03, dated July 3, 2015. (ii) Airbus Service Bulletin A310–24–2105, Revision 02, dated January 5, 2015, excluding Appendix 01, Revision 02, dated January 5, 2015. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet https://www.airbus.com. (4) 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. (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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on March 24, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–07373 Filed 4–8–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration prevent unnecessary engine in-flight shutdown, which could result in reduced controllability of the airplane. DATES: This AD becomes effective May 16, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 16, 2016. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 4809; or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. For service information identified in this final rule, contact EADS–CASA, Military Transport Aircraft Division (MTAD), Integrated Customer Services (ICS), Technical Services, Avenida de ´ Aragon 404, 28022 Madrid, Spain; telephone +34 91 585 55 84; fax +34 91 585 55 05; email MTA.TechnicalService@casa.eads.net; Internet https://www.eads.net. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425 227–1221. It is also available on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 4809. FOR FURTHER INFORMATION CONTACT: Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM– 116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227– 1112; fax 425–227–1149. SUPPLEMENTARY INFORMATION: 14 CFR Part 39 [Docket No. FAA–2015–4809; Directorate Identifier 2015–NM–012–AD; Amendment 39–18463; AD 2016–07–18] RIN 2120–AA64 Airworthiness Directives; Airbus Defense and Space S.A. (Formerly Known as Construcciones Aeronauticas, S.A.) Airplanes Discussion Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Airbus Defense and Space S.A. Model CN–235–200 and CN–235–300 airplanes. This AD was prompted by reports of false engine fire warning events, which consequently led to engine in-flight shutdowns. This AD requires modification of the location and routing of the engine fire detection system. We are issuing this AD to jstallworth on DSK7TPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 14:13 Apr 08, 2016 Jkt 238001 We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus Defense and Space S.A. Model CN–235–200 and CN– 235–300 airplanes. The NPRM published in the Federal Register on November 12, 2015 (80 FR 69898) (‘‘the NPRM’’). The NPRM was prompted by reports of false engine fire warning events, which consequently led to engine in-flight shutdowns. The NPRM proposed to require modification of the location and routing of the engine fire detection system. We are issuing this AD to prevent unnecessary engine inflight shutdown, which could result in reduced controllability of the airplane. PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015–0011, dated January 20, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Defense and Space S.A. Model CN–235– 200 and CN–235–300 airplanes. The MCAI states: Several cases of false engine fire warning events were reported, which consequently led to engine in-flight shut down (IFSD) executed by the flightcrew using the appropriate emergency procedures. Subsequent investigation determined that these false engine fire warnings were the result of insufficient insulation capability of the engine fire detection system. This allowed penetration of moisture into the fire detector connectors, reducing the insulation resistance between the inner electrode and connector housing below the required values. This condition, if not corrected, could lead to further cases of unnecessary engine IFSD, possibly resulting in reduced control of the aeroplane. To address this potential unsafe condition, EADS–CASA issued Service Bulletin (SB) SB235–26–0006 providing modification instructions. For the reasons described above, this [EASA] AD requires modification of the location and routing of the engine fire detection system. You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 4809. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR part 51 EADS CASA has issued Service Bulletin SB–235–26–0006, dated July 8, 2014. The service information describes procedures for modifying the engine fire detection system. This service E:\FR\FM\11APR1.SGM 11APR1

Agencies

[Federal Register Volume 81, Number 69 (Monday, April 11, 2016)]
[Rules and Regulations]
[Pages 21236-21240]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-07373]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0775; Directorate Identifier 2014-NM-046-AD; 
Amendment 39-18467; AD 2016-07-22]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, Model 
A300 C4-605R Variant F airplanes (collectively called Model A300-600 
series airplanes), and Model A310 series airplanes. This AD was 
prompted by reports of insufficient clearance for the electrical wiring 
bundles in the leading and trailing edges of the right-hand (RH) and 
left-hand (LH) wings. This AD requires modifying the electrical routing 
installation at the RH and LH wings. We are issuing this AD to prevent 
insufficient clearance of electrical wiring bundles located in the 
leading and trailing edges of the RH and LH wings, which could lead to 
chafing damage and arcing, possibly resulting in an on-board fire.

DATES: This AD becomes effective May 16, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of May 16, 2016.

ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0775; or in person at the 
Docket Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC.
    For service information identified in this final rule, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 44 51; email account.airworth-eas@airbus.com; Internet 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

[[Page 21237]]

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-2014-
0775.

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

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all Airbus Model A300 B4-
600, B4-600R, and F4-600R series airplanes and Model A300 C4-605R 
Variant F airplanes (collectively called Model A300-600 series 
airplanes); and Model A310 series airplanes. The NPRM published in the 
Federal Register on November 21, 2014 (79 FR 69377) (``the NPRM'').
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0176, dated August 25, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model A300 
B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R 
Variant F airplanes (collectively called Model A300-600 series 
airplanes); and Model A310 series airplanes. The MCAI states:

    Following publication of FAA SFAR 88 (Special Federal Aviation 
Regulation 88) [https://rgl.faa.gov/Regulatory_and_Guidance_Library%5CrgFAR.nsf/0/EEFB3F94451DC06286256C93004F5E07?OpenDocument), EASA issued AD 2006-
0076 (https://ad.easa.europa.eu/ad/2006-0076] requiring inspection 
and corrective action to improve the explosion risk protection 
system for the left hand (LH) and right hand (RH) wings on A300, 
A300-600, A300-600ST and A310 aeroplanes.
    For A300-600, A300-600ST and A310 aeroplanes, the required 
detailed visual inspections of electrical bundles located in the 
leading and trailing edges of the RH and LH wings and a review of 
the wing electrical installation on the final assembly line have 
shown that the wing electrical installation does not comply with the 
minimum distance inspection criteria to the surrounding structure in 
a few wing locations.
    This condition, if not detected and corrected, could lead to 
damage on the electrical harnesses and on the surrounding structure.
    To address this unsafe condition, Airbus developed an 
improvement of the wing electrical installation to prevent possible 
chafing and subsequent damage to the electrical harnesses and 
surrounding structure.
    Consequently EASA issued AD 2014-0034 [https://www.regulations.gov/#!documentDetail;D=FAA-2014-0775-0002] to 
require installation of new bracket assemblies to ensure the 
clearance between the wiring and the structure, and installation of 
protective split sleeves as mechanical protection to the electrical 
harnesses.
    Since EASA AD 2014-0034 was issued, during embodiment of Airbus 
Service Bulletin (SB) A300-24-6103 Revision 02 on an aeroplane, an 
installation problem was identified, which prompted Airbus to revise 
SB A300-24-9014 Revision 01, and A300-24-6103 Revision 02.
    Service Bulletin Information Transmission (SBIT) 14-0044 
Revision 01 dated 06 February 2015 recommended to postpone 
embodiment of these two SB's, and to wait for the availability of 
Airbus SB A300-24-9014 Revision 02 and A300-24-6103 Revision 03.
    For the reasons described above, this [EASA]AD retains the 
requirement of the EASA AD 2014-0034, which is superseded, and 
requires in addition for the A300-600 and A300-600ST aeroplanes 
only, installation of new bracket assemblies in shroud box (LH and 
RH side) to ensure adequate clearance between wirings and flap track 
carriage (LH and RH side).

    Required actions include modifying the electrical routing 
installation at the RH and LH wings by installing new bracket 
assemblies to ensure adequate clearance between the wiring and the 
structure, and installing protective split sleeves as mechanical 
protection to the electrical harnesses.
    You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0775-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment.

Requests To Use the Latest Service Information

    FedEx and United Parcel Service (UPS) requested that the NPRM 
reference the latest revision of Airbus Service Bulletin A300-24-6103, 
Revision 02, dated February 7, 2013. UPS stated that Airbus released an 
operators information transmission in October 2014, which stated that 
an operator reported that the installation of the clamps was not 
possible. UPS and FedEx stated that a revised version of the service 
information should be mandated.
    We agree with the commenters' request. Since the NPRM was issued, 
we have reviewed Airbus Service Bulletin A300-24-6103, Revision 03, 
dated July 3, 2015, excluding Appendices 01, 02, 03, and 04, Revision 
03, dated July 3, 2015; and Airbus Service Bulletin A310-24-2105, 
Revision 02, dated January 5, 2015, excluding Appendix 01, Revision 02, 
dated January 5, 2015. Airbus Service Bulletin A300-24-6103, Revision 
03, dated July 3, 2015, excluding Appendices 01, 02, 03, and 04, 
Revision 03, dated July 3, 2015, adds an installation of new bracket 
assemblies in the shroud box (LH and RH sides) to the modification. 
Airbus Service Bulletin A310-24-2105, Revision 02, dated January 5, 
2015, excluding Appendix 01, Revision 02, dated January 5, 2015, only 
includes minor changes to the modification. We have updated paragraphs 
(g) and (h) of this AD accordingly. Similar to the MCAI, credit is not 
given for Airbus Service Bulletin A300-24-6103, Revision 02, dated 
February 7, 2013.

Request To Revise Costs of Compliance Section

    FedEx requested that we revise the Costs of Compliance section of 
the NPRM. FedEx stated that the 37 work-hour estimate is consistent 
with what is specified in Airbus Service Bulletin A300-24-6103, 
Revision 02, dated February 7, 2013. However, FedEx stated that Airbus 
Service Bulletin A310-24-2105, Revision 01, dated December 11, 2013, 
shows an estimate of up to 55.5 work-hours, and does not include 
preparation and set up time. Airbus also stated that, from their 
experience, the work-hours tend to be understated compared to the 
actual time required to accomplish the actions. FedEx commented that it 
believes an estimate of 60 work-hours is more realistic. FedEx stated 
that it must be noted that 102 FedEx-registered airplanes are listed in 
the effectivity section of both service bulletins, and that the overall 
cost assessment omits the fact that over half of the total U.S. fleet 
cost will be borne by a single operator.
    We agree with the commenter's request to revise the estimated costs 
of compliance; however, we have used the cost estimate identified in 
Airbus Service Bulletin A310-24-2105, Revision 02, dated January 5, 
2015, excluding Appendix 01, Revision 02, dated January 5, 2015, which 
does include access and close-up work-hours. We have revised the Costs 
of Compliance section of this final rule to specify up to 56 work-hours 
per product to comply with the basic requirements of this AD.

[[Page 21238]]

Request To Supersede and Revise the Affected ADs Paragraph of the 
Proposed AD

    FedEx requested that AD 2006-22-07, Amendment 39-14800 (71 FR 
62890, October 27, 2006) (``AD 2006-22-07''), be listed as an affected 
AD in the proposed AD, and that the NPRM supersede AD 2006-22-07. FedEx 
stated that the manufacturer has linked the NPRM to AD 2006-22-07.
    FedEx commented that it has complied with the proposed requirements 
of the proposed AD, and all but two airplanes were found to be 
compliant with the clearance requirements specified in the applicable 
service information. FedEx stated that it has contacted the 
manufacturer for an approved method of compliance. FedEx stated that 
Airbus issued an EASA-approved technical adaptation requiring that the 
affected wire bundles be wrapped and a repetitive inspection be 
performed until a permanent fix is available. FedEx stated that the 
permanent fix is ``Airbus Service Bulletin A300-24-6103,'' which was 
specified in the NPRM.
    FedEx commented that the manufacturer has linked the NPRM to AD 
2006-22-07 because Airbus Service Bulletin A300-24-6103 will act as 
terminating action for the requirements of AD 2006-22-07 and the NPRM. 
FedEx also stated that it thinks that all airplanes that comply with AD 
2006-22-07 without requiring additional permanent modifications should 
be exempt from the NPRM.
    We agree that AD 2006-22-07 and this AD are related; however, we 
disagree with the commenter's request to supersede AD 2006-22-07 and 
include that AD as an affected AD in paragraph (b) of this AD. We also 
disagree with the commenter's request to exempt airplanes that comply 
with AD 2006-22-07 from this AD.
    Prior issues of Airbus Service Bulletin A300-24-6103 (issued before 
Revision 03, dated July 3, 2015) are not acceptable for compliance with 
this AD because this AD and AD 2006-22-07 address two different unsafe 
conditions and require different corrective actions. AD 2006-22-07 and 
prior issues of Airbus Service Bulletin A300-24-6103 (issued before 
Revision 03, dated July 3, 2015) do not address insufficient clearance 
of electrical wiring bundles located in the leading and trailing edges 
of the RH and LH wings, which is the unsafe condition identified in 
this final rule. Additional actions are required in Airbus Service 
Bulletin A300-24-6103, Revision 03, dated July 3, 2015, to address the 
unsafe conditions identified by this final rule that were not addressed 
on airplanes modified using previous issues of Airbus Service Bulletin 
A300-24-6103.
    Therefore, this final rule will not supersede AD 2006-22-07. 
Regardless of the findings or corrective actions accomplished in 
accordance with AD 2006-22-07, the service information in this final 
rule must still be required. We have not change this final rule in this 
regard.

Conclusion

    We reviewed the relevant data, considered the comments 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 minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A300-24-6103, Revision 03, dated 
July 3, 2015, excluding Appendices 01, 02, 03, and 04, Revision 03, 
dated July 3, 2015; and Service Bulletin A310-24-2105, Revision 02, 
dated January 5, 2015, excluding Appendix 01, Revision 02, dated 
January 5, 2015. The service information describes procedures for 
modifying the electrical routing installation at the RH and LH wings. 
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.

Explanation of ``RC'' Procedures and Tests in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directive Implementation Aviation Rulemaking Committee 
(ARC), to enhance the AD system. One enhancement was a new process for 
annotating which procedures and tests in the service information are 
required for compliance with an AD. Differentiating these procedures 
and tests from other tasks in the service information is expected to 
improve an owner's/operator's understanding of crucial AD requirements 
and help provide consistent judgment in AD compliance. The procedures 
and tests identified as Required for Compliance (RC) in any service 
information have a direct effect on detecting, preventing, resolving, 
or eliminating an identified unsafe condition.
    As specified in a NOTE under the Accomplishment Instructions of the 
specified service information, procedures and tests that are identified 
as RC in any service information must be done to comply with the AD. 
However, procedures and tests that are not identified as RC are 
recommended. Those procedures and tests that are not identified as RC 
may be deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining approval 
of an AMOC, provided the procedures and tests identified as RC can be 
done and the airplane can be put back in an airworthy condition. Any 
substitutions or changes to procedures or tests identified as RC will 
require approval of an AMOC.

Costs of Compliance

    We estimate that this AD affects 199 airplanes of U.S. registry.
    We also estimate that it will take about 56 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Required parts would cost up to $18,000 per 
product. Based on these figures, we estimate the cost of this AD on 
U.S. operators to be $4,529,240, or $22,760 per product.

Authority for This Rulemaking

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

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on

[[Page 21239]]

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

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0775; or in person at the 
Docket Management Facility between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The AD docket contains this AD, the 
regulatory evaluation, any comments received, and other information. 
The street address for the Docket Operations office (telephone 800-647-
5527) is in the ADDRESSES section.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2016-07-22 Airbus: Amendment 39-18467. Docket No. FAA-2014-0775; 
Directorate Identifier 2014-NM-046-AD.

(a) Effective Date

    This AD becomes effective May 16, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
and (c)(2) of this AD, certificated in any category.
    (1) All Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4-
605R and F4-622R airplanes; and Model A300 C4-605R Variant F 
airplanes.
    (2) All Airbus Model A310-203, -204, -221, -222, -304, -322, -
324, and -325 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 24, Electrical 
Power.

(e) Reason

    This AD was prompted by reports of insufficient clearance for 
the electrical wiring bundles in the leading and trailing edges of 
the right-hand (RH) and left-hand (LH) wings. We are issuing this AD 
to detect and correct insufficient clearance of electrical wiring 
bundles located in the leading and trailing edges of the RH and LH 
wings, which could lead to chafing damage and arcing, possibly 
resulting in an on-board fire.

(f) Compliance

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

(g) Modification

    Within 30 months after the effective date of this AD: Modify the 
electrical routing installation at the RH and LH wings in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A300-24-6103, Revision 03, July 3, 2015, excluding Appendices 01, 
02, 03, and 04, Revision 03, dated July 3, 2015; or Airbus Service 
Bulletin A310-24-2105, Revision 02, dated January 5, 2015, excluding 
Appendix 01, Revision 02, dated January 5, 2015; as applicable; 
except as required by paragraph (h) of this AD.

(h) Exception to Service Information

    If, during any modification required by paragraph (g) of this 
AD: Any gap between the structure and the clamp has insufficient 
clearance, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A300-24-6103, Revision 03, July 3, 2015, 
excluding Appendices 01, 02, 03, and 04, Revision 03, dated July 3, 
2015; or Airbus Service Bulletin A310-24-2105, Revision 02, dated 
January 5, 2015, excluding Appendix 01, Revision 02, dated January 
5, 2015; as applicable; 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).

(i) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A310-24-
2105, dated March 20, 2013; or Airbus Service Bulletin A310-24-2105, 
Revision 01, dated December 11, 2013.

(j) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone (425) 227-2125; fax (425) 227-1149. Information may 
be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (2) 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 EASA; or 
Airbus's EASA DOA. If approved by the DOA, the approval must include 
the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraph (h) of this AD: If any service information contains 
procedures or tests that are identified as RC, those procedures and 
tests must be done to comply with this AD; any procedures or tests 
that are not identified as RC are recommended. Those procedures and 
tests that are not identified as RC may be deviated from using 
accepted methods in accordance with the operator's maintenance or 
inspection program without obtaining approval of an AMOC, provided 
the procedures and tests identified as RC can be done and the 
airplane can be put back in an airworthy condition. Any 
substitutions or changes to procedures or tests identified as RC 
require approval of an AMOC.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2015-0176, dated August 25, 
2015, for related information. This MCAI may be found in the AD 
docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0775-0002.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (l)(3) and (l)(4) of this AD.

(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.

[[Page 21240]]

    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Service Bulletin A300-24-6103, Revision 03, dated 
July 3, 2015, excluding Appendices 01, 02, 03, and 04, Revision 03, 
dated July 3, 2015.
    (ii) Airbus Service Bulletin A310-24-2105, Revision 02, dated 
January 5, 2015, excluding Appendix 01, Revision 02, dated January 
5, 2015.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; 
Internet https://www.airbus.com.
    (4) 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.
    (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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on March 24, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-07373 Filed 4-8-16; 8:45 am]
 BILLING CODE 4910-13-P
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