Airworthiness Directives; Airbus Airplanes, 12407-12410 [2017-03972]

Download as PDF Federal Register / Vol. 82, No. 41 / Friday, March 3, 2017 / Rules and Regulations telephone: (816) 329–4059; fax: (816) 329– 4090; email: doug.rudolph@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (h) Related Information Refer to MCAI EASA AD No.: 2016–0183, dated September 13, 2016, for related information. The MCAI can be found in the AD docket on the Internet at: https:// www.regulations.gov/document?D=FAA2016-9357-0002. (i) Material Incorporated by Reference mstockstill on DSK3G9T082PROD with RULES (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Pilatus PC–6 Service Bulletin (SB) No. 57–006, dated May 13, 2016. (ii) Reserved. (3) For Pilatus Aircraft Ltd. service information identified in this AD, contact Pilatus Aircraft Ltd., Customer Technical Support (MCC), P.O. Box 992, CH–6371 Stans, Switzerland; phone: +41 (0)41 619 3333; fax: +41 (0)41 619 7311; email: supportPC12@pilatus-aircraft.com; Internet: http://www.pilatus-aircraft.com. (4) You may review this referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. In addition, you can access this service information on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2016–9357. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives. gov/federal-register/cfr/ibr-locations.html. Issued in Kansas City, Missouri on February 8, 2016. Robert Busto, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–03719 Filed 3–2–17; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 16:07 Mar 02, 2017 Jkt 241001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–6893; Directorate Identifier 2015–NM–181–AD; Amendment 39–18812; AD 2017–05–02] 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 certain Airbus Model A318–112 airplanes; Model A319–111, –112, –115, –132, and –133 airplanes; Model A320–214, –232, and –233 airplanes; and Model A321– 211, –212, –213, –231, and –232 airplanes. This AD was prompted by a quality control review on the final assembly line, which determined that the wrong aluminum alloy was used to manufacture several structural parts. This AD requires a one-time eddy current conductivity measurement of certain cabin and cargo compartment structural parts to determine if an incorrect aluminum alloy was used, and replacement if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective April 7, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of April 7, 2017. ADDRESSES: For service information identified in this final rule, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet: http://www.airbus.com. 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 http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6893. SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 12407 6893; 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 Office (telephone 800–647– 5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus Model A318– 112 airplanes; Model A319–111, –112, –115, –132, and –133 airplanes; Model A320–214, –232, and –233 airplanes; and Model A321–211, –212, –213, –231, and –232 airplanes. The NPRM published in the Federal Register on May 26, 2016 (81 FR 33438). The NPRM was prompted by a quality control review on the final assembly line, which determined that the wrong aluminum alloy was used to manufacture several structural parts. The NPRM proposed to require a one-time eddy current conductivity measurement of certain cabin and cargo compartment structural parts to determine if an incorrect aluminum alloy was used, and replacement if necessary. We are issuing this AD to detect and replace structural parts made of incorrect aluminum alloy. This condition could result in reduced structural integrity of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015–0218, dated November 3, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A318–112 airplanes; Model A319–111, –112, –115, –132, and –133 airplanes; Model A320–214, –232, and –233 airplanes; and Model A321–211, –212, –213, –231, and –232 airplanes. The MCAI states: Following an Airbus quality control review on the final assembly line, it was discovered that wrong aluminum alloy were delivered E:\FR\FM\03MRR1.SGM 03MRR1 12408 Federal Register / Vol. 82, No. 41 / Friday, March 3, 2017 / Rules and Regulations by a supplier for several structural parts. The results of the investigations highlighted that 0.04% of the stock could be impacted by this wrong material. Structural investigations demonstrated the capability to sustain the static limits loads, and sufficient fatigue life up to a certain inspection threshold. This condition, if not detected and corrected, could reduce the structural integrity of the aeroplane. To address this potential unsafe condition, Airbus issued Service Bulletin (SB) A320– 53–1298 and SB A320–53–1299 to provide inspection instructions. For the reasons described above, this [EASA] AD requires a one-time Special Detailed Inspection (SDI) [eddy current conductivity measurements] of certain cabin and cargo compartment parts for material identification and, depending on findings, replacement with serviceable parts. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6893. 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. Support for the NPRM One commenter, Jerry Curtis, expressed support for the NPRM. mstockstill on DSK3G9T082PROD with RULES Request To Refer to the Latest Service Information Airbus requested that we refer to the latest service information: Airbus Service Bulletins A320–53–1298 and A320–53–1299, both Revision 01, both dated June 9, 2016. We referred to Airbus Service Bulletins A320–53–1298 and A320–53–1299, both dated February 16, 2015, as the appropriate sources of service information for accomplishing the actions specified in the NPRM. We agree with the request to refer to the latest service information. Airbus Service Bulletins A320–53–1298 and A320–53–1299, both Revision 01, both dated June 9, 2016, include updated information and specify that no additional work is necessary for airplanes modified by the original issue. We have revised this AD to refer to Airbus Service Bulletins A320–53–1298 and A320–53–1299, both Revision 01, both dated June 9, 2016. We have also added credit for actions done before the effective date of this AD using Airbus Service Bulletins A320–53–1298 and A320–53–1299, both dated February 16, 2015. VerDate Sep<11>2014 16:07 Mar 02, 2017 Jkt 241001 Request To Correct a Certain Part Number (P/N) Allegiant Air asked if the part number, P/N D5358526421400, in the ninth row of table 1 to paragraphs (g) and (h) of the proposed AD under ‘‘Affected P/N’’ is correct. Allegiant Air stated that the affected part number is the same as the acceptable replacement part number. We acknowledge the commenter’s concern; however, we have confirmed that both part numbers in the ninth row of table 1 to paragraphs (g) and (h) of this AD are the same and are correct as written. Therefore, we have not changed this AD in this regard. Additional Change to NPRM We have added paragraph (i) to this AD to clarify that no reporting is required. 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 change 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 We reviewed Airbus Service Bulletins A320–53–1298 and A320–53–1299, both Revision 01, both including Appendixes 01 through 03, both dated June 9, 2016. The service information describes procedures for a one-time eddy current conductivity measurement of certain cabin and cargo compartment structural parts to determine if an incorrect aluminum alloy was used, and replacement of any affected part with a serviceable part. These documents are distinct since they apply to different parts of the airplane (cabin and cargo compartment). This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 167 airplanes of U.S. registry. PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 We also estimate that it takes about 1 work-hour per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $14,195, or $85 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD. According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all available costs in our cost estimate. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. E:\FR\FM\03MRR1.SGM 03MRR1 Federal Register / Vol. 82, No. 41 / Friday, March 3, 2017 / Rules and Regulations 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): ■ 2017–05–02 Airbus: Amendment 39–18812; Docket No. FAA–2016–6893; Directorate Identifier 2015–NM–181–AD. (a) Effective Date This AD is effective April 7, 2017. (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category; manufacturer serial numbers 3586, 3588, 3589, 3590, 3595, 3604, 3608, 3614, 3615, 3620, 3632, 3634, 3638, 3647, 3651, 3657, 3660, 3661, 3663, 3671, 3675, 3680, 3683 through 3687 inclusive, 3689, 3691, 3694, 3700, 3702, 3704, 3705, 3710, 3720, 3727, 3728, 3733, 3735, 3742, 3744, 3746, 3754, 3757, 3759, 3763, 3768, 3770, 3772, 3774, 3775, 3779, 3788, 3790, 3794, 3797, 3799, 3801, 3803, 3808, 3810, 3818, 3822, 3824, 3826 through 4329 inclusive, 4331 through 6051 inclusive, 6053 through 6061 inclusive, 6063 through 6072 inclusive, 6074 through 6100 inclusive, 6102 through 6115 inclusive, 6117 through 6126 inclusive, 6128 through 6136 inclusive, 6138 through 6143 inclusive, 6145 through 6150 inclusive, 6152 through 6159 inclusive, 6161 and 6162. (1) Airbus Model A318–112 airplanes. (2) Airbus Model A319–111, –112, –115, –132, and –133 airplanes. (3) Airbus Model A320–214, –232, and –233 airplanes. (4) Airbus Model A321–211, –212, –213, –231, and –232 airplanes. mstockstill on DSK3G9T082PROD with RULES (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by a quality control review of the final assembly line which determined that the wrong aluminum alloy was used to manufacture several structural parts. We are issuing this AD to detect and replace structural parts made of incorrect aluminum alloy. This condition could result 16:07 Mar 02, 2017 Jkt 241001 (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) One-Time Measurement Within 6 years after the effective date of this AD, but not exceeding 12 years since the date of issuance of the original certificate of airworthiness or the date of issuance of the original export certificate of airworthiness: Do a one-time eddy current conductivity measurement (with 60 kilohertz (kHz) and 480 kHz) of the cabin and cargo compartment structural parts identified in the ‘‘Affected P/ N’’ column of table 1 to paragraphs (g) and (h) of this AD to determine if an incorrect aluminum alloy was used, in accordance with the Accomplishment Instructions of Airbus Service Bulletins A320–53–1298, Revision 01, including Appendixes 01, 02, and 03, dated June 9, 2016 (for cabin parts); and A320–53–1299, Revision 01, including Appendixes 01, 02, and 03, dated June 9, 2016 (for cargo parts). TABLE 1 TO PARAGRAPHS (g) AND (h) OF THIS AD—PARTS TO BE INSPECTED/INSTALLED (b) Affected ADs None. VerDate Sep<11>2014 in reduced structural integrity of the airplane. Acceptable replacement P/N Affected P/N D5347120720000 D5347120720100 D5347120920000 D5347120920100 D5347118820400 D5347717620000 D5357020620000 D5358526421200 D5358526421400 D5358526421000 D5358513120001 Area D5347120720051 D5347120720151 D5347120920051 D5347120920151 D5347118820451 D5347717620051 D5357020620051 D5358526421251 D5358526421400 D5358526421051 D5358513120051 Cabin. Cabin. Cabin. Cabin. Cabin. Cargo. Cargo. Cargo. Cargo. Cargo. Cargo. (h) Replacement If during the inspection required by paragraph (g) of this AD, any affected part having a part number (P/N) specified in table 1 to paragraphs (g) and (h) of this AD is found to have a measured value greater than that specified in Figure A–GFAAA, Sheet 02, ‘‘Inspection Flowchart,’’ of the applicable service information identified in paragraph (g) of this AD: Before further flight, replace with an acceptable replacement part having a part number specified in table 1 to paragraphs (g) and (h) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletins A320–53–1298, Revision 01, including Appendixes 01, 02, and 03, dated June 9, 2016 (for cabin parts); and A320–53–1299, Revision 01, including Appendixes 01, 02, and 03, dated June 9, 2016 (for cargo parts). (i) No Reporting Although reporting of inspection results is specified as a ‘‘Required for Compliance’’ (RC) action in Airbus Service Bulletins A320–53–1298, Revision 01, including Appendixes 01, 02, and 03, dated June 9, 2016; and A320–53–1299, Revision 01, PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 12409 including Appendixes 01, 02, and 03, dated June 9, 2016; this AD does not require any report. (j) Credit for Previous Actions This paragraph provides credit for the actions required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–53–1298, dated February 16, 2015; and Airbus Service Bulletin A320–53–1299, dated February 16, 2015; as applicable. (k) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: 425–227–1405; fax: 425–227– 1149. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. (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 European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as provided by paragraph (i) 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. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2015–0218, dated November 3, 2015, for related information. This MCAI may be found in the AD docket on the Internet at E:\FR\FM\03MRR1.SGM 03MRR1 12410 Federal Register / Vol. 82, No. 41 / Friday, March 3, 2017 / Rules and Regulations http://www.regulations.gov by searching for and locating Docket No. FAA–2016–6893. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (m)(3) and (m)(4) of this AD. (m) 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. (i) Airbus Service Bulletin A320–53–1298, Revision 01, including Appendixes 01 through 03, dated June 9, 2016. (ii) Airbus Service Bulletin A320–53–1299, Revision 01, including Appendixes 01 through 03, dated June 9, 2016. (3) For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet: http://www.airbus.com. (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: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on February 16, 2017. Thomas Groves, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–03972 Filed 3–2–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–7423; Directorate Identifier 2016–NM–034–AD; Amendment 39–18816; AD 2017–05–06] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. mstockstill on DSK3G9T082PROD with RULES AGENCY: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 767–200 and –300 series airplanes. This AD was prompted by an evaluation by the SUMMARY: VerDate Sep<11>2014 16:07 Mar 02, 2017 Jkt 241001 design approval holder (DAH) indicating that the frame-to-floor-beam joints and frames common to shear ties at certain locations of fuselage structure are subject to widespread fatigue damage (WFD). This AD requires inspections for cracking of certain frame inner chords and webs common to the floor beam joint and at frames common to the shear ties at certain sections, and corrective action if necessary. We are issuing this AD to address the unsafe condition on these products. This AD is effective April 7, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 7, 2017. DATES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone 562–797–1717; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 7423. ADDRESSES: Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 7423; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Wayne Lockett, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057 3356; phone: 425–917–6447; fax: 425–917–6590; email: wayne.lockett@ faa.gov. SUPPLEMENTARY INFORMATION: PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all The Boeing Company Model 767–200 and –300 series airplanes. The NPRM published in the Federal Register on July 7, 2016 (81 FR 44246). The NPRM was prompted by an evaluation by the DAH indicating that the frame-to-floor-beam joints and frames common to shear ties at certain locations of fuselage structure are subject to WFD. The NPRM proposed to require repetitive inspections for cracking of the frame inner chords and webs common to the floor beam joint and at frames common to the shear ties at certain sections on the left and right fuselage sides, and corrective action if necessary. We are issuing this AD to detect and correct cracking of the frame inner chords and webs common to the floor beam joint and at frames common to the shear ties at certain sections on the left and right fuselage sides, which could result in reduced structural integrity of the airplane. 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. Support for the NPRM Boeing and United Airlines expressed support for the NPRM. Effect of Winglets on Accomplishment of the Proposed Actions Aviation Partners Boeing stated that accomplishing the Supplemental Type Certificate (STC) ST01920SE does not affect the ability to accomplish the actions specified in the NPRM. We concur with the commenter. We have redesignated paragraph (c) of the proposed AD as (c)(1) and added paragraph (c)(2) to this AD to state that installation of STC ST01920SE does not affect the ability to accomplish the actions required by this final rule. Therefore, for airplanes on which STC ST01920SE is installed, a ‘‘change in product’’ alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. 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: E:\FR\FM\03MRR1.SGM 03MRR1

Agencies

[Federal Register Volume 82, Number 41 (Friday, March 3, 2017)]
[Rules and Regulations]
[Pages 12407-12410]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-03972]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6893; Directorate Identifier 2015-NM-181-AD; 
Amendment 39-18812; AD 2017-05-02]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus Model A318-112 airplanes; Model A319-111, -112, -115, -132, and 
-133 airplanes; Model A320-214, -232, and -233 airplanes; and Model 
A321-211, -212, -213, -231, and -232 airplanes. This AD was prompted by 
a quality control review on the final assembly line, which determined 
that the wrong aluminum alloy was used to manufacture several 
structural parts. This AD requires a one-time eddy current conductivity 
measurement of certain cabin and cargo compartment structural parts to 
determine if an incorrect aluminum alloy was used, and replacement if 
necessary. We are issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective April 7, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of April 7, 
2017.

ADDRESSES: For service information identified in this final rule, 
contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet: 
http://www.airbus.com. 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 http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6893.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6893; 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 Office (telephone 
800-647-5527) is Docket Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

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

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain Airbus Model A318-
112 airplanes; Model A319-111, -112, -115, -132, and -133 airplanes; 
Model A320-214, -232, and -233 airplanes; and Model A321-211, -212, -
213, -231, and -232 airplanes. The NPRM published in the Federal 
Register on May 26, 2016 (81 FR 33438). The NPRM was prompted by a 
quality control review on the final assembly line, which determined 
that the wrong aluminum alloy was used to manufacture several 
structural parts. The NPRM proposed to require a one-time eddy current 
conductivity measurement of certain cabin and cargo compartment 
structural parts to determine if an incorrect aluminum alloy was used, 
and replacement if necessary. We are issuing this AD to detect and 
replace structural parts made of incorrect aluminum alloy. This 
condition could result in reduced structural integrity of the airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0218, dated November 3, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A318-112 airplanes; Model A319-111, -112, -115, -132, and -133 
airplanes; Model A320-214, -232, and -233 airplanes; and Model A321-
211, -212, -213, -231, and -232 airplanes. The MCAI states:

    Following an Airbus quality control review on the final assembly 
line, it was discovered that wrong aluminum alloy were delivered

[[Page 12408]]

by a supplier for several structural parts. The results of the 
investigations highlighted that 0.04% of the stock could be impacted 
by this wrong material.
    Structural investigations demonstrated the capability to sustain 
the static limits loads, and sufficient fatigue life up to a certain 
inspection threshold.
    This condition, if not detected and corrected, could reduce the 
structural integrity of the aeroplane.
    To address this potential unsafe condition, Airbus issued 
Service Bulletin (SB) A320-53-1298 and SB A320-53-1299 to provide 
inspection instructions.
    For the reasons described above, this [EASA] AD requires a one-
time Special Detailed Inspection (SDI) [eddy current conductivity 
measurements] of certain cabin and cargo compartment parts for 
material identification and, depending on findings, replacement with 
serviceable parts.

You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6893.

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.

Support for the NPRM

    One commenter, Jerry Curtis, expressed support for the NPRM.

Request To Refer to the Latest Service Information

    Airbus requested that we refer to the latest service information: 
Airbus Service Bulletins A320-53-1298 and A320-53-1299, both Revision 
01, both dated June 9, 2016. We referred to Airbus Service Bulletins 
A320-53-1298 and A320-53-1299, both dated February 16, 2015, as the 
appropriate sources of service information for accomplishing the 
actions specified in the NPRM.
    We agree with the request to refer to the latest service 
information. Airbus Service Bulletins A320-53-1298 and A320-53-1299, 
both Revision 01, both dated June 9, 2016, include updated information 
and specify that no additional work is necessary for airplanes modified 
by the original issue. We have revised this AD to refer to Airbus 
Service Bulletins A320-53-1298 and A320-53-1299, both Revision 01, both 
dated June 9, 2016. We have also added credit for actions done before 
the effective date of this AD using Airbus Service Bulletins A320-53-
1298 and A320-53-1299, both dated February 16, 2015.

Request To Correct a Certain Part Number (P/N)

    Allegiant Air asked if the part number, P/N D5358526421400, in the 
ninth row of table 1 to paragraphs (g) and (h) of the proposed AD under 
``Affected P/N'' is correct. Allegiant Air stated that the affected 
part number is the same as the acceptable replacement part number.
    We acknowledge the commenter's concern; however, we have confirmed 
that both part numbers in the ninth row of table 1 to paragraphs (g) 
and (h) of this AD are the same and are correct as written. Therefore, 
we have not changed this AD in this regard.

Additional Change to NPRM

    We have added paragraph (i) to this AD to clarify that no reporting 
is required.

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 change 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

    We reviewed Airbus Service Bulletins A320-53-1298 and A320-53-1299, 
both Revision 01, both including Appendixes 01 through 03, both dated 
June 9, 2016. The service information describes procedures for a one-
time eddy current conductivity measurement of certain cabin and cargo 
compartment structural parts to determine if an incorrect aluminum 
alloy was used, and replacement of any affected part with a serviceable 
part. These documents are distinct since they apply to different parts 
of the airplane (cabin and cargo compartment). This service information 
is reasonably available because the interested parties have access to 
it through their normal course of business or by the means identified 
in the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 167 airplanes of U.S. registry.
    We also estimate that it takes about 1 work-hour per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Based on these figures, we estimate the cost of 
this AD on U.S. operators to be $14,195, or $85 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this AD.
    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all available costs in our 
cost estimate.

Authority for This Rulemaking

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

Regulatory Findings

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

[[Page 12409]]

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):

2017-05-02 Airbus: Amendment 39-18812; Docket No. FAA-2016-6893; 
Directorate Identifier 2015-NM-181-AD.

(a) Effective Date

    This AD is effective April 7, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(4) of this AD, certificated in any category; 
manufacturer serial numbers 3586, 3588, 3589, 3590, 3595, 3604, 
3608, 3614, 3615, 3620, 3632, 3634, 3638, 3647, 3651, 3657, 3660, 
3661, 3663, 3671, 3675, 3680, 3683 through 3687 inclusive, 3689, 
3691, 3694, 3700, 3702, 3704, 3705, 3710, 3720, 3727, 3728, 3733, 
3735, 3742, 3744, 3746, 3754, 3757, 3759, 3763, 3768, 3770, 3772, 
3774, 3775, 3779, 3788, 3790, 3794, 3797, 3799, 3801, 3803, 3808, 
3810, 3818, 3822, 3824, 3826 through 4329 inclusive, 4331 through 
6051 inclusive, 6053 through 6061 inclusive, 6063 through 6072 
inclusive, 6074 through 6100 inclusive, 6102 through 6115 inclusive, 
6117 through 6126 inclusive, 6128 through 6136 inclusive, 6138 
through 6143 inclusive, 6145 through 6150 inclusive, 6152 through 
6159 inclusive, 6161 and 6162.
    (1) Airbus Model A318-112 airplanes.
    (2) Airbus Model A319-111, -112, -115, -132, and -133 airplanes.
    (3) Airbus Model A320-214, -232, and -233 airplanes.
    (4) Airbus Model A321-211, -212, -213, -231, and -232 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by a quality control review of the final 
assembly line which determined that the wrong aluminum alloy was 
used to manufacture several structural parts. We are issuing this AD 
to detect and replace structural parts made of incorrect aluminum 
alloy. This condition could result in reduced structural integrity 
of the airplane.

(f) Compliance

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

(g) One-Time Measurement

    Within 6 years after the effective date of this AD, but not 
exceeding 12 years since the date of issuance of the original 
certificate of airworthiness or the date of issuance of the original 
export certificate of airworthiness: Do a one-time eddy current 
conductivity measurement (with 60 kilohertz (kHz) and 480 kHz) of 
the cabin and cargo compartment structural parts identified in the 
``Affected P/N'' column of table 1 to paragraphs (g) and (h) of this 
AD to determine if an incorrect aluminum alloy was used, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletins A320-53-1298, Revision 01, including Appendixes 01, 02, 
and 03, dated June 9, 2016 (for cabin parts); and A320-53-1299, 
Revision 01, including Appendixes 01, 02, and 03, dated June 9, 2016 
(for cargo parts).

  Table 1 to Paragraphs (g) and (h) of This AD--Parts To Be Inspected/
                                Installed
------------------------------------------------------------------------
        Affected P/N          Acceptable replacement P/N       Area
------------------------------------------------------------------------
D5347120720000               D5347120720051               Cabin.
D5347120720100               D5347120720151               Cabin.
D5347120920000               D5347120920051               Cabin.
D5347120920100               D5347120920151               Cabin.
D5347118820400               D5347118820451               Cabin.
D5347717620000               D5347717620051               Cargo.
D5357020620000               D5357020620051               Cargo.
D5358526421200               D5358526421251               Cargo.
D5358526421400               D5358526421400               Cargo.
D5358526421000               D5358526421051               Cargo.
D5358513120001               D5358513120051               Cargo.
------------------------------------------------------------------------

(h) Replacement

    If during the inspection required by paragraph (g) of this AD, 
any affected part having a part number (P/N) specified in table 1 to 
paragraphs (g) and (h) of this AD is found to have a measured value 
greater than that specified in Figure A-GFAAA, Sheet 02, 
``Inspection Flowchart,'' of the applicable service information 
identified in paragraph (g) of this AD: Before further flight, 
replace with an acceptable replacement part having a part number 
specified in table 1 to paragraphs (g) and (h) of this AD, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletins A320-53-1298, Revision 01, including Appendixes 01, 02, 
and 03, dated June 9, 2016 (for cabin parts); and A320-53-1299, 
Revision 01, including Appendixes 01, 02, and 03, dated June 9, 2016 
(for cargo parts).

(i) No Reporting

    Although reporting of inspection results is specified as a 
``Required for Compliance'' (RC) action in Airbus Service Bulletins 
A320-53-1298, Revision 01, including Appendixes 01, 02, and 03, 
dated June 9, 2016; and A320-53-1299, Revision 01, including 
Appendixes 01, 02, and 03, dated June 9, 2016; this AD does not 
require any report.

(j) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraphs (g) and (h) of this AD, if those actions were performed 
before the effective date of this AD using Airbus Service Bulletin 
A320-53-1298, dated February 16, 2015; and Airbus Service Bulletin 
A320-53-1299, dated February 16, 2015; as applicable.

(k) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Sanjay 
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone: 425-227-1405; fax: 425-227-1149. Information may be 
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (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 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as provided by 
paragraph (i) 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.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2015-0218, dated November 3, 2015, for related 
information. This MCAI may be found in the AD docket on the Internet 
at

[[Page 12410]]

http://www.regulations.gov by searching for and locating Docket No. 
FAA-2016-6893.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (m)(3) and (m)(4) of this AD.

(m) 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.
    (i) Airbus Service Bulletin A320-53-1298, Revision 01, including 
Appendixes 01 through 03, dated June 9, 2016.
    (ii) Airbus Service Bulletin A320-53-1299, Revision 01, 
including Appendixes 01 through 03, dated June 9, 2016.
    (3) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email account.airworth-eas@airbus.com; Internet: http://www.airbus.com.
    (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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on February 16, 2017.
Thomas Groves,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-03972 Filed 3-2-17; 8:45 am]
BILLING CODE 4910-13-P