Airworthiness Directives; The Boeing Company Airplanes, 40672-40675 [2017-17591]

Download as PDF 40672 Federal Register / Vol. 82, No. 165 / Monday, August 28, 2017 / Rules and Regulations TABLE 1 TO PARAGRAPHS (g) AND (h) OF THIS AD—PARTS TO BE INSPECTED/INSTALLED Affected part No. F5347126620600 F5347126621000 F5377004320300 F5347170420400 F5347170420600 G5367131300000 G5367173700000 G5367173800000 ... ... ... ... ... ... ... ... Acceptable replacement part No. F5347126620000 F5347126620400 F5377004320351 F5347170420400 F5347170420600 G5367131300000 G5367173700000 G5367173800000 Area ... ... ... ... ... .. .. .. Cabin. Cabin. Cabin. 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 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 paragraphs (g)(1), (g)(2), and (g)(3) of this AD, except as provided by paragraph (i) of this AD: 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, replace the affected part 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 the applicable service information identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. asabaliauskas on DSKBBXCHB2PROD with RULES (i) Exception to Certain Service Information Where Figure A–GFAAA, Sheet 02, ‘‘Inspection Flowchart,’’ of the service information identified in paragraphs (g)(2) and (g)(3) of this AD specifies to ‘‘do the conductivity (s) measurement with 60kHz (refer to Appendix 01) s480 = lllMS/m,’’ the correct conductivity measurement is ‘‘s60 = lllMS/m.’’ (j) Additional Inspection for Certain Airplanes For Model A330 airplanes on which the inspection and replacement, as applicable, specified in paragraphs (g) and (h) of this AD were done before the effective date of this AD, in accordance with Airbus Service Bulletin A330–53–3261, dated June 23, 2015: 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 of structural parts having part number (P/N) G5367131300000, P/N G5367173700000, and P/N G5367173800000, located in fuselage section 15, in accordance with the ‘‘Additional Work’’ section of the Accomplishment Instructions of Airbus Service Bulletin A330–53–3261, Revision 01, including Appendixes 01, 02, and 03, dated November 10, 2016. (k) Replacement If during the inspection required by paragraph (j) of this AD, any affected part VerDate Sep<11>2014 17:58 Aug 25, 2017 Jkt 241001 having a part number specified in paragraph (j) of this AD is found to have a measured value greater than that specified in Figure A– GFAAA, Sheet 02, ‘‘Inspection Flowchart,’’ of Airbus Service Bulletin A330–53–3261, Revision 01, including Appendixes 01, 02, and 03, dated November 10, 2016: 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, replace the affected part 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 Bulletin A330–53–3261, Revision 01, including Appendixes 01, 02, and 03, dated November 10, 2016. (l) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the International Section, send it to the attention of the person identified in paragraph (m)(2) of this AD. Information may be emailed to 9-ANM-116AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (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 Section, Transport Standards Branch, 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 DOAauthorized signature. (3) Required for Compliance (RC): 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. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2017–0021, dated February 8, 2017, for related information. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2016–7264. (2) For more information about this AD, contact Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. (n) 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 A330–53–3261, Revision 01, including Appendixes 01, 02, and 03, dated November 10, 2016. (ii) Airbus Service Bulletin A330–53–3262, including Appendixes 01 and 02, dated June 23, 2015. (iii) Airbus Service Bulletin A340–53– 5072, including Appendixes 01 and 02, dated June 23, 2015. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. (4) You may view this service information at the FAA, Transport Standards Branch, 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 August 9, 2017. Dionne Palermo, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017–17536 Filed 8–25–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0337; Product Identifier 2017–NM–006–AD; Amendment 39–19006; AD 2017–17–16] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. AGENCY: E:\FR\FM\28AUR1.SGM 28AUR1 Federal Register / Vol. 82, No. 165 / Monday, August 28, 2017 / Rules and Regulations ACTION: Final rule. We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767 airplanes. This AD was prompted by a report of cracking of the vertical stiffener in the nose wheel well. This AD requires repetitive inspections of the nose wheel well bulkhead stiffener for any cracking, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective October 2, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of October 2, 2017. ADDRESSES: 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 service information at the FAA, Transport Standards Branch, 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–2017– 0337. 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–2017– 0337; 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 final rule, 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 40673 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 Section, FAA, Seattle ACO Branch, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6447; fax: 425–917–6590; email: wayne.lockett@faa.gov. SUPPLEMENTARY INFORMATION: 2017) as paragraph (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 AD. 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. Discussion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this final rule 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 final rule. We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain The Boeing Company Model 767 airplanes. The NPRM published in the Federal Register on May 16, 2017 (82 FR 22443). The NPRM was prompted by a report of cracking of the vertical stiffener in the nose wheel well. The NPRM proposed to require repetitive inspections of the nose wheel well bulkhead stiffener for any cracking, and corrective actions if necessary. We are issuing this AD to detect and correct such cracking, which could adversely affect the structural integrity of the airplane and possibly lead to cabin depressurization or a nose landing gear collapse. 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. United Airlines and The Boeing Company supported 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 actions specified in the NPRM. We concur with the commenter. We have redesignated paragraph (c) of the proposed AD (82 FR 22443, May 16, Conclusion Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 767–53A0275, dated January 5, 2017. The service information describes procedures for a detailed inspection and a medium frequency eddy current inspection of the nose wheel well bulkhead stiffener for any cracking, and corrective actions if necessary. 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 144 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Labor cost Inspection ...................... asabaliauskas on DSKBBXCHB2PROD with RULES Action 10 work-hour × $85 per hour = $850 per inspection cycle. We estimate the following costs to do certain repairs that would be required VerDate Sep<11>2014 17:58 Aug 25, 2017 Jkt 241001 Parts cost Cost per product $0 based on the results of the inspection. We have no way of determining the PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 $850 per inspection cycle. Cost on U.S. operators $122,400 per inspection cycle. number of aircraft that might need this repair: E:\FR\FM\28AUR1.SGM 28AUR1 40674 Federal Register / Vol. 82, No. 165 / Monday, August 28, 2017 / Rules and Regulations ON-CONDITION COSTS Action Labor cost Repair .............................................. 18 work-hour × $85 per hour = $1,530 ..................................................... We have received no definitive data that would enable us to provide cost estimates for other repairs specified in this AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ‘‘General requirements.’’ Under that section, Congress charges the FAA with 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. asabaliauskas on DSKBBXCHB2PROD with RULES Regulatory Findings 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 DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), VerDate Sep<11>2014 17:58 Aug 25, 2017 Jkt 241001 (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 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): ■ 2017–17–16 The Boeing Company: Amendment 39–19006; Docket No. FAA–2017–0337; Product Identifier 2017–NM–006–AD. (a) Effective Date This AD is effective October 2, 2017. (b) Affected ADs None. (c) Applicability (1) This AD applies to The Boeing Company Model 767–200, –300, –300F, and –400ER series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 767–53A0275, dated January 5, 2017. (2) Installation of Supplemental Type Certificate (STC) ST01920SE does not affect the ability to accomplish the actions required by this AD. 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. (d) Subject Air Transport Association (ATA) of America Code 53; Fuselage. (e) Unsafe Condition This AD was prompted by a report of cracking in the vertical stiffener in the nose PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Cost per product Parts cost $0 $1,530 wheel well. We are issuing this AD to detect and correct such cracking, which could adversely affect the structural integrity of the airplane and possibly lead to cabin depressurization or a nose landing gear collapse. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections At the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 767–53A0275, dated January 5, 2017, except as specified in paragraph (h)(1) of this AD: Do a detailed inspection and a medium frequency eddy current inspection of the nose wheel well bulkhead stiffener for any cracking, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767–53A0275, dated January 5, 2017; except as specified in paragraph (h)(2) of this AD. Do all corrective actions before further flight. Repeat the inspections thereafter at the times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 767–53A0275, dated January 5, 2017. (h) Exceptions to the Service Information (1) Where Boeing Alert Service Bulletin 767–53A0275, dated January 5, 2017, specifies a compliance time ‘‘after the original issue date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. (2) If any cracking is found and Boeing Alert Service Bulletin 767–53A0275, dated January 5, 2017, specifies to contact Boeing for appropriate action and specifies that action as ‘‘RC’’ (Required for Compliance): Before further flight repair using a method approved in accordance with the procedures specified in paragraph (i) of this AD. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle ACO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (j) of this AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. E:\FR\FM\28AUR1.SGM 28AUR1 Federal Register / Vol. 82, No. 165 / Monday, August 28, 2017 / Rules and Regulations (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO Branch, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) Except as required by paragraph (h)(2) of this AD: For service information that contains steps that are labeled as RC, the provisions of paragraphs (i)(4)(i) and (i)(4)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or substep is labeled ‘‘RC Exempt,’’ then the RC requirement is removed from that step or substep. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled 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 RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. asabaliauskas on DSKBBXCHB2PROD with RULES (j) Related Information For more information about this AD, contact Wayne Lockett, Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 1601 Lind Avenue SW., Renton, WA 98057– 3356; phone: 425–917–6447; fax: 425–917– 6590; email: wayne.lockett@faa.gov. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Boeing Alert Service Bulletin 767– 53A0275, dated January 5, 2017. (ii) Reserved. (3) For Boeing service information identified in this AD, 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. (4) You may view this service information at the FAA, Transport Standards Branch, 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. VerDate Sep<11>2014 17:58 Aug 25, 2017 Jkt 241001 Issued in Renton, Washington, on August 11, 2017. Dionne Palermo, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017–17591 Filed 8–25–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9518; Product Identifier 2015–NM–091–AD; Amendment 39–18989; AD 2017–16–12] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2013–19– 09 and AD 2014–25–51, which applied to all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2013–19– 09 required replacing Angle of Attack (AOA) sensor conic plates with AOA sensor flat plates. AD 2014–25–51 required revising the airplane flight manual (AFM) to advise the flightcrew of emergency procedures for abnormal Alpha Protection (Alpha Prot). This new AD requires replacing certain AOA sensors; and doing a detailed inspection and a functional heating test for discrepancies on certain AOA sensors, and replacing the affected AOA sensors. This AD was prompted by a report indicating that a Model A321 airplane encountered a blockage of two AOA probes during climb, leading to activation of the Alpha Prot while the Mach number increased. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective October 2, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of October 2, 2017. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of November 6, 2013 (78 FR 60667, October 2, 2013). 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 SUMMARY: PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 40675 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 Standards Branch, 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– 9518. 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– 9518; 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 (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 Section, Transport Standards Branch, 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 to supersede AD 2013–19–09, Amendment 39–17591 (78 FR 60667, October 2, 2013) (‘‘AD 2013–19–09’’), and AD 2014–25–51, Amendment 39– 18067 (80 FR 3153, January 22, 2015) (‘‘AD 2014–25–51’’). AD 2013–19–09 and AD 2014–25–51 applied to all Airbus Model A318, A319, A320, and A321 series airplanes. The NPRM published in the Federal Register on December 28, 2016 (81 FR 95531). The NPRM was prompted by a report indicating that an Airbus Model A321 airplane encountered a blockage of two AOA probes during climb, leading to activation of the Alpha Prot while the Mach number increased. The NPRM proposed to continue to require replacing AOA sensor conic plates with AOA sensor flat plates and revising the AFM to advise the flight crew of emergency procedures for abnormal Alpha Prot. The NPRM also proposed to E:\FR\FM\28AUR1.SGM 28AUR1

Agencies

[Federal Register Volume 82, Number 165 (Monday, August 28, 2017)]
[Rules and Regulations]
[Pages 40672-40675]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-17591]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0337; Product Identifier 2017-NM-006-AD; Amendment 
39-19006; AD 2017-17-16]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

[[Page 40673]]


ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model 767 airplanes. This AD was prompted by a 
report of cracking of the vertical stiffener in the nose wheel well. 
This AD requires repetitive inspections of the nose wheel well bulkhead 
stiffener for any cracking, and corrective actions if necessary. We are 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective October 2, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of October 2, 
2017.

ADDRESSES: 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 service information at the 
FAA, Transport Standards Branch, 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-2017-
0337.

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-2017-
0337; 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 final rule, 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 Section, FAA, Seattle ACO Branch, 1601 Lind Avenue SW., 
Renton, WA 98057-3356; phone: 425-917-6447; fax: 425-917-6590; email: 
wayne.lockett@faa.gov.

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 The Boeing Company 
Model 767 airplanes. The NPRM published in the Federal Register on May 
16, 2017 (82 FR 22443). The NPRM was prompted by a report of cracking 
of the vertical stiffener in the nose wheel well. The NPRM proposed to 
require repetitive inspections of the nose wheel well bulkhead 
stiffener for any cracking, and corrective actions if necessary. We are 
issuing this AD to detect and correct such cracking, which could 
adversely affect the structural integrity of the airplane and possibly 
lead to cabin depressurization or a nose landing gear collapse.

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. United Airlines and The Boeing 
Company supported 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 actions specified 
in the NPRM.
    We concur with the commenter. We have redesignated paragraph (c) of 
the proposed AD (82 FR 22443, May 16, 2017) as paragraph (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 AD. 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 comment received, and 
determined that air safety and the public interest require adopting 
this final rule 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 final 
rule.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 767-53A0275, dated 
January 5, 2017. The service information describes procedures for a 
detailed inspection and a medium frequency eddy current inspection of 
the nose wheel well bulkhead stiffener for any cracking, and corrective 
actions if necessary. 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 144 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                     Labor cost          Parts cost     Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection.....................  10 work-hour x $85 per               $0  $850 per            $122,400 per
                                  hour = $850 per                          inspection cycle.   inspection cycle.
                                  inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do certain repairs that would be 
required based on the results of the inspection. We have no way of 
determining the number of aircraft that might need this repair:

[[Page 40674]]



                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Repair.....................................  18 work-hour x $85 per hour =                    $0          $1,530
                                              $1,530.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for other repairs specified in this AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes to 
the Director of the System Oversight Division.

Regulatory Findings

    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 DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

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

2017-17-16 The Boeing Company: Amendment 39-19006; Docket No. FAA-
2017-0337; Product Identifier 2017-NM-006-AD.

(a) Effective Date

    This AD is effective October 2, 2017.

(b) Affected ADs

    None.

(c) Applicability

    (1) This AD applies to The Boeing Company Model 767-200, -300, -
300F, and -400ER series airplanes, certificated in any category, as 
identified in Boeing Alert Service Bulletin 767-53A0275, dated 
January 5, 2017.
    (2) Installation of Supplemental Type Certificate (STC) 
ST01920SE does not affect the ability to accomplish the actions 
required by this AD. 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.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a report of cracking in the vertical 
stiffener in the nose wheel well. We are issuing this AD to detect 
and correct such cracking, which could adversely affect the 
structural integrity of the airplane and possibly lead to cabin 
depressurization or a nose landing gear collapse.

(f) Compliance

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

(g) Inspections

    At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 767-53A0275, dated 
January 5, 2017, except as specified in paragraph (h)(1) of this AD: 
Do a detailed inspection and a medium frequency eddy current 
inspection of the nose wheel well bulkhead stiffener for any 
cracking, and do all applicable corrective actions, in accordance 
with the Accomplishment Instructions of Boeing Alert Service 
Bulletin 767-53A0275, dated January 5, 2017; except as specified in 
paragraph (h)(2) of this AD. Do all corrective actions before 
further flight. Repeat the inspections thereafter at the times 
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 767-53A0275, dated January 5, 2017.

(h) Exceptions to the Service Information

    (1) Where Boeing Alert Service Bulletin 767-53A0275, dated 
January 5, 2017, specifies a compliance time ``after the original 
issue date of this service bulletin,'' this AD requires compliance 
within the specified compliance time after the effective date of 
this AD.
    (2) If any cracking is found and Boeing Alert Service Bulletin 
767-53A0275, dated January 5, 2017, specifies to contact Boeing for 
appropriate action and specifies that action as ``RC'' (Required for 
Compliance): Before further flight repair using a method approved in 
accordance with the procedures specified in paragraph (i) of this 
AD.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle ACO Branch, FAA, has the authority to 
approve AMOCs for this AD, if requested using the procedures found 
in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request 
to your principal inspector or local Flight Standards District 
Office, as appropriate. If sending information directly to the 
manager of the certification office, send it to the attention of the 
person identified in paragraph (j) of this AD. Information may be 
emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

[[Page 40675]]

    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair, modification, or alteration required by this AD 
if it is approved by the Boeing Commercial Airplanes Organization 
Designation Authorization (ODA) that has been authorized by the 
Manager, Seattle ACO Branch, to make those findings. To be approved, 
the repair method, modification deviation, or alteration deviation 
must meet the certification basis of the airplane, and the approval 
must specifically refer to this AD.
    (4) Except as required by paragraph (h)(2) of this AD: For 
service information that contains steps that are labeled as RC, the 
provisions of paragraphs (i)(4)(i) and (i)(4)(ii) of this AD apply.
    (i) The steps labeled as RC, including substeps under an RC step 
and any figures identified in an RC step, must be done to comply 
with the AD. If a step or substep is labeled ``RC Exempt,'' then the 
RC requirement is removed from that step or substep. An AMOC is 
required for any deviations to RC steps, including substeps and 
identified figures.
    (ii) Steps not labeled 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 RC 
steps, including substeps and identified figures, can still be done 
as specified, and the airplane can be put back in an airworthy 
condition.

(j) Related Information

    For more information about this AD, contact Wayne Lockett, 
Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 1601 
Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6447; fax: 
425-917-6590; email: wayne.lockett@faa.gov.

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Boeing Alert Service Bulletin 767-53A0275, dated January 5, 
2017.
    (ii) Reserved.
    (3) For Boeing service information identified in this AD, 
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.
    (4) You may view this service information at the FAA, Transport 
Standards Branch, 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 August 11, 2017.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2017-17591 Filed 8-25-17; 8:45 am]
BILLING CODE 4910-13-P