Airworthiness Directives; The Boeing Company Airplanes, 53908-53912 [2016-18952]

Download as PDF 53908 Federal Register / Vol. 81, No. 157 / Monday, August 15, 2016 / Rules and Regulations b. In paragraph (c), in note 2 to Table 7, by removing ‘‘Table 6’’ and adding in its place ‘‘Table 8’’; ■ c. By revising paragraph (c) introductory text, excluding Tables 7 and 8; ■ d. In paragraph (d)(1) by removing ‘‘Table 7 of’’; ■ e. In paragraph (d)(2) by removing ‘‘Table 8 of’’; and ■ f. In paragraph (d)(3) by removing ‘‘Table 9 of’’. The revisions read as follows: ■ § 431.97 Energy efficiency standards and their compliance dates. * * * (b) * * * * * TABLE 1 TO § 431.97—MINIMUM COOLING EFFICIENCY STANDARDS FOR AIR CONDITIONING AND HEATING EQUIPMENT [Not including single package vertical air conditioners and single package vertical heat pumps, packaged terminal air conditioners and packaged terminal heat pumps, computer room air conditioners, variable refrigerant flow multi-split air conditioners and heat pumps, and double-duct air-cooled commercial package air conditioning and heating equipment] * * * * * * * TABLE 2 TO § 431.97—MINIMUM HEATING EFFICIENCY STANDARDS FOR AIR CONDITIONING AND HEATING EQUIPMENT * * Equipment type * 3 And Cooling capacity * * * * Compliance date: Equipment manufactured starting on . . . Efficiency level * * * * * * * * * manufactured before October 9, 2015. See Table 4 of this section for updated heating efficiency standards. * * * * * * (c) Each non-standard size packaged terminal air conditioner (PTAC) and packaged terminal heat pump (PTHP) manufactured on or after October 7, 2010 must meet the applicable minimum energy efficiency standard level(s) set forth in Table 7 of this section. Each standard size PTAC manufactured on or after October 8, 2012, and before January 1, 2017 must meet the applicable minimum energy efficiency standard level(s) set forth in Table 7 of this section. Each standard size PTHP manufactured on or after October 8, 2012 must meet the applicable minimum energy efficiency standard level(s) set forth in Table 7 of this section. Each standard size PTAC manufactured on or after January 1, 2017 must meet the applicable minimum energy efficiency standard level(s) set forth in Table 8 of this section. * * * * * [FR Doc. 2016–19358 Filed 8–12–16; 8:45 am] BILLING CODE 6450–01–P sradovich on DSK3GMQ082PROD with RULES [Heat Pumps] * * VerDate Sep<11>2014 17:35 Aug 12, 2016 Jkt 238001 * * DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–8841; Directorate Identifier 2016–NM–115–AD; Amendment 39–18611; AD 2016–16–13] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are superseding Airworthiness Directive (AD) 2016–13– 10, for certain The Boeing Company Model 737–300, –400, and –500 series airplanes. AD 2016–13–10 required repetitive external detailed inspections and nondestructive inspections to detect cracks in the fuselage skin along the chem-mill steps at stringers S–1 and S– 2R, between station (STA) 400 and STA 460, and repair if necessary. AD 2016– 13–10 also required a preventive modification of the fuselage skin at crown stringers S–1 and S–2R. This AD requires the same actions as AD 2016– 13–10, and clarifies certain regulatory text. This AD was prompted by the determination that certain regulatory text in AD 2016–13–10 requires clarification. We are issuing this AD to detect and correct fatigue cracking of the fuselage skin panels at the chem-mill SUMMARY: PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 steps, which could result in sudden fracture and failure of the fuselage skin panels, and consequent rapid decompression of the airplane. DATES: This AD is effective August 15, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 9, 2016 (81 FR 43483, July 5, 2016). The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of July 23, 2012 (77 FR 36134, June 18, 2012). We must receive any comments on this AD by September 29, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this final rule, contact Boeing E:\FR\FM\15AUR1.SGM 15AUR1 Federal Register / Vol. 81, No. 157 / Monday, August 15, 2016 / Rules and Regulations Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; 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 https://www.regulations.gov by searching for and locating Docket No. FAA–2016–8841. sradovich on DSK3GMQ082PROD with RULES 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–2016–8841; 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 (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Jennifer Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5264; fax: 562–627– 5210; email: jennifer.tsakoumakis@faa.gov. SUPPLEMENTARY INFORMATION: Discussion On June 21, 2016, we issued AD 2016–13–10, Amendment 39–18574 (81 FR 43483, July 5, 2016) (‘‘AD 2016–13– 10’’), for certain The Boeing Company Model 737–300, –400, and –500 series airplanes. AD 2016–13–10 required repetitive external detailed inspections and nondestructive inspections to detect cracks in the fuselage skin along the chem-mill steps at stringers S–1 and S– 2R, between STA 400 and STA 460, and repair if necessary. AD 2016–13–10 also required a preventive modification of the fuselage skin at crown stringers S– 1 and S–2R. AD 2016–13–10 resulted from a determination that, for certain airplanes, the skin pockets adjacent to the Air Traffic Control (ATC) antenna VerDate Sep<11>2014 17:35 Aug 12, 2016 Jkt 238001 are susceptible to widespread fatigue damage. We issued AD 2016–13–10 to detect and correct fatigue cracking of the fuselage skin panels at the chem-mill steps, which could result in sudden fracture and failure of the fuselage skin panels, and consequent rapid decompression of the airplane. Actions Since AD 2016–13–10 Was Issued Since we issued AD 2016–13–10, we have determined that certain regulatory text in AD 2016–13–10 requires clarification: • We have revised paragraphs (h)(3) and (i) of this AD to refer to paragraph (l)(3) of this AD for the exception to the service information. • We have also removed the sentence from paragraph (h)(3) of AD 2016–13–10 that provided existing repair information and instead we have included existing repair information in the introductory text of paragraph (h) of this AD. • We have revised paragraph (j) of this AD to also refer to Boeing Alert Service Bulletin 737–53A1293, Revision 3, dated January 23, 2015, for locations for the modification of the chem-mill steps. • We have revised paragraphs (j) and (l)(3) of this AD to refer to paragraph (n) of this AD for the appropriate procedures to request approval of an alternative method of compliance. We are issuing this AD to correct the unsafe condition on certain The Boeing Company Model 737–300, –400, and –500 series airplanes. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 737–53A1293, Revision 3, dated January 23, 2015. The service information describes procedures for repetitive external detailed inspections and non-destructive inspections to detect cracks in the fuselage skin along the chem-mill steps at stringers S–1 and S–2R, between STA 400 and STA 460, and repair of any cracking. The service information also describes procedures for a modification of the chem-mill steps at the locations identified, including related investigative actions and corrective actions, and repetitive post-mod inspections. This service information is reasonably available because the interested parties have PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 53909 access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA’s Determination We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. AD Requirements This AD requires accomplishing the actions specified in the service information described previously. FAA’s Justification and Determination of the Effective Date We are superseding AD 2016–13–10 to clarify certain regulatory text. We have made no other changes to the requirements published in AD 2016–13– 10. Therefore, we find that notice and opportunity for prior public comment are unnecessary and that good cause exists for making this amendment effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments before it becomes effective. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include Docket No. FAA–2016– 8841; and Directorate Identifier 2016– NM–115–AD at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. Costs of Compliance We estimate that this AD affects 186 airplanes of U.S. registry. We estimate the following costs to comply with this AD: E:\FR\FM\15AUR1.SGM 15AUR1 53910 Federal Register / Vol. 81, No. 157 / Monday, August 15, 2016 / Rules and Regulations ESTIMATED COSTS Action Labor cost Retained inspections from AD 2016–13– 10. Retained modification from AD 2016–13– 10. Cost per product Cost on U.S. operators $0 Between $595 and $1,275 per inspection cycle. Between $110,670 and $237,150 per inspection cycle. (1) $20,060 ...................................... $3,731,160. Parts cost Between 7 and 15 work-hours × $85 per hour, depending on airplane configuration = between $595 and $1,275 per inspection cycle. 236 work-hours × $85 per hour = $20,060. 1 We currently have no specific cost estimates associated with the parts necessary for the modification. We cannot determine the cost of the materials because the modification parts must be sized at the time the modification is installed, taking into account any existing repairs in the area. under the criteria of the Regulatory Flexibility Act. We have received no definitive data that enables us to provide a cost estimate for the on-condition actions 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. sradovich on DSK3GMQ082PROD 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), (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 VerDate Sep<11>2014 17:35 Aug 12, 2016 Jkt 238001 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 part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2016–13–10, Amendment 39–18574 (81 FR 43483, July 5, 2016), and adding the following new AD: ■ 2016–16–13 The Boeing Company: Amendment 39–18611; Docket No. FAA–2016–8841; Directorate Identifier 2016–NM–115–AD. (a) Effective Date This AD is effective August 15, 2016. (b) Affected ADs This AD replaces AD 2016–13–10, Amendment 39–18574 (81 FR 43483, July 5, 2016) (‘‘AD 2016–13–10’’). (c) Applicability (1) This AD applies to The Boeing Company Model 737–300, -400, and -500 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 737–53A1293, Revision 3, dated January 23, 2015. (2) Installation of Supplemental Type Certificate (STC) ST01219SE (http://rgl.faa. gov/Regulatory_and_Guidance_Library/rgstc. nsf/0/BE866B732F6CF31086257B9700692 796?OpenDocument&Highlight=st01219se) does not affect the ability to accomplish the actions required by this AD. Therefore, for PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 airplanes on which STC ST01219SE 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 reports of cracks found on the fuselage skin at the chem-mill steps, and the determination that, for certain airplanes, the skin pockets adjacent to the Air Traffic Control antenna are susceptible to widespread fatigue damage. We are issuing this AD to detect and correct fatigue cracking of the fuselage skin panels at the chem-mill steps, which could result in sudden fracture and failure of the fuselage skin panels, and consequent rapid decompression of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspections With No Changes This paragraph restates the requirements of paragraph (g) of AD 2016–13–10, with no changes. At the applicable time specified in tables 1, 2, 3, and 5 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1293, Revision 3, dated January 23, 2015, except as required by paragraphs (l)(1) and (l)(2) of this AD: Do the actions specified in paragraphs (g)(1) and (g)(2) of this AD, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1293, Revision 3, dated January 23, 2015, except as required by paragraph (l)(3) of this AD. Repeat the applicable inspections thereafter at the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1293, Revision 3, dated January 23, 2015. (1) Do an external detailed inspection for cracking of the fuselage skin chem-mill steps. (2) Do an external non-destructive (medium frequency eddy current, magneto optical imaging, C-Scan, or ultrasonic phased array) inspection for cracking of the fuselage skin chem-mill steps. E:\FR\FM\15AUR1.SGM 15AUR1 Federal Register / Vol. 81, No. 157 / Monday, August 15, 2016 / Rules and Regulations sradovich on DSK3GMQ082PROD with RULES (h) Retained Repair With Clarification of Repair Information and Service Information Exception This paragraph restates the requirements of paragraph (h) of AD 2016–13–10, with clarification of repair information and service information exception. If any cracking is found during any inspection required by paragraph (g) of this AD, do the applicable actions specified in paragraph (h)(1), (h)(2),or (h)(3) of this AD. Installation of a repair prior to August 9, 2016 (the effective date of AD 2016–13–10) that meets the conditions specified in Part 9 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1293, Revision 3, dated January 23, 2015, terminates the inspections required by paragraph (g) of this AD for the area covered by that repair only. Installation of a repair prior to August 9, 2016, that meets the conditions specified in Part 9 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1293, Revision 3, dated January 23, 2015, covers all eight chem-mill step inspection areas between STA 410 and STA 450, and was done using a method approved in accordance with the procedures specified in paragraph (n) of this AD, terminates the inspections required by paragraph (g) of this AD for the area covered by that repair only, and terminates the preventive modification required by paragraph (i) of this AD. (1) Repair before further flight in accordance with Part 2 (for Group 1 airplanes) or Part 7 (for Group 2 airplanes) of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1293, Revision 3, dated January 23, 2015; except as required by paragraph (l)(3) of this AD. Installation of a repair that meets the conditions specified in Note (a) of table 1, 2, 3, or 5 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1293, Revision 3, dated January 23, 2015, terminates the repetitive inspections required by paragraph (g) of this AD for the area covered by that repair only. (2) For Group 1 airplanes: Accomplishing the modification specified in paragraph (i) of this AD is a method of compliance with paragraph (h)(1) of this AD. (3) If any cracking is found in any area not covered by the preventive modification doubler during any inspection required by paragraph (g) of this AD: Repair before further flight, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1293, Revision 3, dated January 23, 2015, except as provided by paragraph (l)(3) of this AD. Installation of this repair terminates the repetitive inspections required by paragraph (g) of this AD for the area covered by that repair only. (i) Retained Preventive Modification With Clarification of Service Information Exception and Method of Compliance Procedures This paragraph restates the requirements of paragraph (i) of AD 2016–13–10, with clarification of service information exception and method of compliance procedures. For Group 1 airplanes: At the applicable time specified in tables 1, 2, and 3 of paragraph VerDate Sep<11>2014 17:35 Aug 12, 2016 Jkt 238001 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1293, Revision 3, dated January 23, 2015, except as required by paragraphs (l)(1) and (l)(2) of this AD, do a preventive modification of the fuselage skin at crown stringers S–1 and S–2R, including all applicable related investigative actions, in accordance with Part 9 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1293, Revision 3, dated January 23, 2015, except as provided by paragraph (l)(3) of this AD. Do all applicable related investigative actions concurrently with the modification. Installation of a preventive modification terminates the repetitive inspections required by paragraph (g) of this AD for the modified area only. Thereafter, repeat the inspections specified in Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1293, Revision 3, dated January 23, 2015. (j) Retained Optional Modification With Clarification of Service Information This paragraph restates the requirements of paragraph (j) of AD 2016–13–10, with clarification of service information. Accomplishing a modification of the chemmill steps at any location identified in Boeing Service Bulletin 737–53A1293, Revision 2, dated August 10, 2011; or Boeing Alert Service Bulletin 737–53A1293, Revision 3, dated January 23, 2015; using a method approved in accordance with the procedures specified in paragraph (n) of this AD, terminates the repetitive inspections required by paragraph (g) of this AD for the modified area only. (k) Retained Post-Repair/Post-Modification Inspections With No Changes This paragraph restates the requirements of paragraph (k) of AD 2016–13–10, with no changes. Tables 4 and 6 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1293, Revision 3, dated January 23, 2015, specify post-repair/postmodification airworthiness limitation inspections in compliance with 14 CFR 25.571(a)(3) at the modified locations, which support compliance with 14 CFR 121.1109(c)(2) or 129.109(b)(2). As airworthiness limitations, these inspections are required by maintenance and operational rules. It is therefore unnecessary to mandate them in this AD. Deviations from these inspections require FAA approval, but do not require an alternative method of compliance. (l) Retained Exceptions to Service Bulletin Specifications With Clarification of Method of Compliance Procedures This paragraph restates the requirements of paragraph (l) of AD 2016–13–10, With clarification of method of compliance procedures. (1) Where Boeing Alert Service Bulletin 737–53A1293, Revision 3, dated January 23, 2015, specifies a compliance time ‘‘after the Revision 3 date of this service bulletin,’’ this AD requires compliance within the specified compliance time after August 9, 2016 (the effective date of AD 2016–13–10). (2) Where the Condition column of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1293, PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 53911 Revision 3, dated January 23, 2015, specifies a condition based on when an airplane has or has not been inspected, this AD bases the condition on whether an airplane has or has not been inspected on August 9, 2016 (the effective date of AD 2016–13–10). (3) Where Boeing Alert Service Bulletin 737–53A1293, Revision 3, dated January 23, 2015, specifies to contact Boeing for repair or preventive modification instructions: Before further flight, do the repair or preventive modification, as applicable, using a method approved in accordance with the procedures specified in paragraph (n) of this AD. (m) Retained Credit for Previous Actions With No Changes This paragraph restates the requirements of paragraph (m) of AD 2016–13–10, with no changes. (1) This paragraph provides credit for actions required by paragraphs (g) and (h) of this AD, if those actions were performed before July 23, 2012 (the effective date of AD 2012–12–04, Amendment 39–17093 (77 FR 36134, June 18, 2012) (‘‘AD 2012–12–04’’)), using Boeing Alert Service Bulletin 737– 53A1293, Revision 1, dated July 7, 2010, which is not incorporated by reference in this AD. (2) This paragraph provides credit for actions required by paragraphs (g) and (h) of this AD, if those actions were performed before August 9, 2016 (the effective date of AD 2016–13–10), using Boeing Service Bulletin 737–53A1293, Revision 2, dated August 10, 2011, which was incorporated by reference in AD 2012–12–04. (n) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (o)(1) of this AD. Information may be emailed to: 9-ANM-LAACO-AMOCRequests@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. (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, Los Angeles ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation method must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) AMOCs approved for AD 2012–12–04 are approved as AMOCs for the corresponding provisions of this AD. E:\FR\FM\15AUR1.SGM 15AUR1 53912 Federal Register / Vol. 81, No. 157 / Monday, August 15, 2016 / Rules and Regulations (o) Related Information DEPARTMENT OF TRANSPORTATION (1) For more information about this AD, contact Jennifer Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5264; fax: 562–627–5210; email: jennifer.tsakoumakis@faa.gov. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (p)(5) and (p)(6) of this AD. Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2016–3937; Airspace Docket No. 16–AWA–1] RIN 2120–AA66 Amendment of Class C Airspace; Syracuse Hancock International Airport, NY (p) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on August 9, 2016 (81 FR 43483, July 5, 2016). (i) Boeing Alert Service Bulletin 737– 53A1293, Revision 3, dated January 23, 2015. (ii) Reserved. (4) The following service information was approved for IBR on July 23, 2012 (77 FR 36134, June 18, 2012). (i) Boeing Service Bulletin 737–53A1293, Revision 2, dated August 10, 2011. (ii) Reserved. (5) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206– 544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.com. (6) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on August 4, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–18952 Filed 8–12–16; 8:45 am] sradovich on DSK3GMQ082PROD with RULES BILLING CODE 4910–13–P Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: History This action amends the Syracuse Hancock International Airport, NY, Class C airspace by removing a cutout from the surface area that was incorporated to accommodate operations at an airport that has permanently closed. DATES: Effective date 0901 UTC, November 10, 2016. The Director of the Federal Register approves this incorporation by reference action under title 1, Code of Federal Regulations, part 51, subject to the annual revision of FAA Order 7400.9 and publication of conforming amendments. ADDRESSES: FAA Order 7400.9Z, Airspace Designations and Reporting Points and subsequent amendments can be viewed online at http://www.faa.gov/ airtraffic/publications/. For further information, you can contact the Airspace Policy Group, Federal Aviation Administration, 800 Independence Avenue SW., Washington, DC 20591; telephone: (202) 267–8783. The order is also available for inspection at the National Archives and Records Administration (NARA). For information on the availability of FAA Order 7400.9Z at NARA, call (202) 741– 6030, or go to http://www.archives.gov/ federal_register/code_of_federalregulations/ibr_locations.html. FAA Order 7400.9, Airspace Designations and Reporting Points, is published yearly and effective on September 15. FOR FURTHER INFORMATION CONTACT: Paul Gallant, Airspace Policy Group, Office of Airspace Services, Federal Aviation Administration, 800 Independence Avenue SW., Washington, DC 20591; telephone: (202) 267–8783. SUPPLEMENTARY INFORMATION: SUMMARY: Authority for This Rulemaking The FAA’s authority to issue rules regarding aviation safety is found in Title 49 of the United States Code. Subtitle I, Section 106 describes the authority of the FAA Administrator. VerDate Sep<11>2014 17:35 Aug 12, 2016 Jkt 238001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Subtitle VII, Aviation Programs, describes in more detail the scope of the agency’s authority. This rulemaking is promulgated under the authority described in Subtitle VII, Part A, Subpart I, Section 40103. Under that section, the FAA is charged with prescribing regulations to assign the use of airspace necessary to ensure the safety of aircraft and the efficient use of airspace. This regulation is within the scope of that authority as it updates the description of the Class C airspace area at Syracuse Hancock International Airport, NY. On March 28, 2016, the FAA published in the Federal Register a notice proposing to remove a cutout from the description of the Syracuse Hancock International Airport, NY, Class C surface area (81 FR 17113), FR Doc. 2016–06833. Interested parties were invited to participate in this rulemaking effort by submitting written comments on the proposal. No comments were received. Availability and Summary of Documents for Incorporation by Reference This document amends FAA Order 7400.9Z, Airspace Designations and Reporting Points, dated August 6, 2015, and effective September 15, 2015. FAA Order 7400.9Z is publicly available as listed in the ADDRESSES section of this final rule. FAA Order 7400.9Z lists Class A, B, C, D, and E airspace areas, air traffic service routes, and reporting points. The Rule This amendment to Title 14, Code of Federal Regulations (14 CFR) part 71 modifies the Syracuse Hancock International Airport Class C airspace area by removing a cutout from the Class C surface area. The cutout excluded the airspace within a 0.75nautical mile radius of the former Michael Field/Onondaga Flight School Airport. The sole purpose of the exclusion was to allow aircraft to operate freely to and from the airport without the need to contact air traffic control. Since the former airport is now permanently closed, the purpose for the exclusion no longer exists; therefore, the FAA is removing the words ‘‘. . . excluding that airspace within a 0.75mile radius of Michael Field/Onondaga Flight School Airport . . .;’’ as well as the words ‘‘Michael Field/Onondaga Flight School Airport, NY (lat. 43°10′45″ N., long. 76°07′29″ W.),’’ from the Class C airspace description. E:\FR\FM\15AUR1.SGM 15AUR1

Agencies

[Federal Register Volume 81, Number 157 (Monday, August 15, 2016)]
[Rules and Regulations]
[Pages 53908-53912]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-18952]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-8841; Directorate Identifier 2016-NM-115-AD; 
Amendment 39-18611; AD 2016-16-13]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2016-13-10, 
for certain The Boeing Company Model 737-300, -400, and -500 series 
airplanes. AD 2016-13-10 required repetitive external detailed 
inspections and nondestructive inspections to detect cracks in the 
fuselage skin along the chem-mill steps at stringers S-1 and S-2R, 
between station (STA) 400 and STA 460, and repair if necessary. AD 
2016-13-10 also required a preventive modification of the fuselage skin 
at crown stringers S-1 and S-2R. This AD requires the same actions as 
AD 2016-13-10, and clarifies certain regulatory text. This AD was 
prompted by the determination that certain regulatory text in AD 2016-
13-10 requires clarification. We are issuing this AD to detect and 
correct fatigue cracking of the fuselage skin panels at the chem-mill 
steps, which could result in sudden fracture and failure of the 
fuselage skin panels, and consequent rapid decompression of the 
airplane.

DATES: This AD is effective August 15, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 9, 
2016 (81 FR 43483, July 5, 2016).
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of July 
23, 2012 (77 FR 36134, June 18, 2012).
    We must receive any comments on this AD by September 29, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this final rule, contact 
Boeing

[[Page 53909]]

Commercial Airplanes, Attention: Data & Services Management, P.O. Box 
3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000, 
extension 1; fax 206-766-5680; 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 https://www.regulations.gov by 
searching for and locating Docket No. FAA-2016-8841.

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-
8841; 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 (phone: 
800-647-5527) is in the ADDRESSES section. Comments will be available 
in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Jennifer Tsakoumakis, Aerospace 
Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft 
Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 
90712-4137; phone: 562-627-5264; fax: 562-627-5210; email: 
jennifer.tsakoumakis@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    On June 21, 2016, we issued AD 2016-13-10, Amendment 39-18574 (81 
FR 43483, July 5, 2016) (``AD 2016-13-10''), for certain The Boeing 
Company Model 737-300, -400, and -500 series airplanes. AD 2016-13-10 
required repetitive external detailed inspections and nondestructive 
inspections to detect cracks in the fuselage skin along the chem-mill 
steps at stringers S-1 and S-2R, between STA 400 and STA 460, and 
repair if necessary. AD 2016-13-10 also required a preventive 
modification of the fuselage skin at crown stringers S-1 and S-2R. AD 
2016-13-10 resulted from a determination that, for certain airplanes, 
the skin pockets adjacent to the Air Traffic Control (ATC) antenna are 
susceptible to widespread fatigue damage. We issued AD 2016-13-10 to 
detect and correct fatigue cracking of the fuselage skin panels at the 
chem-mill steps, which could result in sudden fracture and failure of 
the fuselage skin panels, and consequent rapid decompression of the 
airplane.

Actions Since AD 2016-13-10 Was Issued

    Since we issued AD 2016-13-10, we have determined that certain 
regulatory text in AD 2016-13-10 requires clarification:
     We have revised paragraphs (h)(3) and (i) of this AD to 
refer to paragraph (l)(3) of this AD for the exception to the service 
information.
     We have also removed the sentence from paragraph (h)(3) of 
AD 2016-13-10 that provided existing repair information and instead we 
have included existing repair information in the introductory text of 
paragraph (h) of this AD.
     We have revised paragraph (j) of this AD to also refer to 
Boeing Alert Service Bulletin 737-53A1293, Revision 3, dated January 
23, 2015, for locations for the modification of the chem-mill steps.
     We have revised paragraphs (j) and (l)(3) of this AD to 
refer to paragraph (n) of this AD for the appropriate procedures to 
request approval of an alternative method of compliance.
    We are issuing this AD to correct the unsafe condition on certain 
The Boeing Company Model 737-300, -400, and -500 series airplanes.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 737-53A1293, Revision 3, 
dated January 23, 2015. The service information describes procedures 
for repetitive external detailed inspections and non-destructive 
inspections to detect cracks in the fuselage skin along the chem-mill 
steps at stringers S-1 and S-2R, between STA 400 and STA 460, and 
repair of any cracking. The service information also describes 
procedures for a modification of the chem-mill steps at the locations 
identified, including related investigative actions and corrective 
actions, and repetitive post-mod inspections. This service information 
is reasonably available because the interested parties have access to 
it through their normal course of business or by the means identified 
in the ADDRESSES section.

FAA's Determination

    We are issuing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

AD Requirements

    This AD requires accomplishing the actions specified in the service 
information described previously.

FAA's Justification and Determination of the Effective Date

    We are superseding AD 2016-13-10 to clarify certain regulatory 
text. We have made no other changes to the requirements published in AD 
2016-13-10. Therefore, we find that notice and opportunity for prior 
public comment are unnecessary and that good cause exists for making 
this amendment effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments before it becomes effective. However, we invite 
you to send any written data, views, or arguments about this AD. Send 
your comments to an address listed under the ADDRESSES section. Include 
Docket No. FAA-2016-8841; and Directorate Identifier 2016-NM-115-AD at 
the beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of this 
AD. We will consider all comments received by the closing date and may 
amend this AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    We estimate that this AD affects 186 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

[[Page 53910]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                   Labor cost         Parts cost      Cost per product         operators
----------------------------------------------------------------------------------------------------------------
Retained inspections from AD     Between 7 and 15                  $0  Between $595 and      Between $110,670
 2016-13-10.                      work-hours x $85                      $1,275 per            and $237,150 per
                                  per hour, depending                   inspection cycle.     inspection cycle.
                                  on airplane
                                  configuration =
                                  between $595 and
                                  $1,275 per
                                  inspection cycle.
Retained modification from AD    236 work-hours x $85           (\1\)  $20,060.............  $3,731,160.
 2016-13-10.                      per hour = $20,060.
----------------------------------------------------------------------------------------------------------------
\1\ We currently have no specific cost estimates associated with the parts necessary for the modification. We
  cannot determine the cost of the materials because the modification parts must be sized at the time the
  modification is installed, taking into account any existing repairs in the area.

    We have received no definitive data that enables us to provide a 
cost estimate for the on-condition actions 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.

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 part 39 of the Federal Aviation 
Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2016-13-10, Amendment 39-18574 (81 FR 43483, July 5, 2016), and adding 
the following new AD:

2016-16-13 The Boeing Company: Amendment 39-18611; Docket No. FAA-
2016-8841; Directorate Identifier 2016-NM-115-AD.

(a) Effective Date

    This AD is effective August 15, 2016.

(b) Affected ADs

    This AD replaces AD 2016-13-10, Amendment 39-18574 (81 FR 43483, 
July 5, 2016) (``AD 2016-13-10'').

(c) Applicability

    (1) This AD applies to The Boeing Company Model 737-300, -400, 
and -500 series airplanes, certificated in any category, as 
identified in Boeing Alert Service Bulletin 737-53A1293, Revision 3, 
dated January 23, 2015.
    (2) Installation of Supplemental Type Certificate (STC) 
ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/BE866B732F6CF31086257B9700692796?OpenDocument&Highlight=st01219se) 
does not affect the ability to accomplish the actions required by 
this AD. Therefore, for airplanes on which STC ST01219SE 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 reports of cracks found on the fuselage 
skin at the chem-mill steps, and the determination that, for certain 
airplanes, the skin pockets adjacent to the Air Traffic Control 
antenna are susceptible to widespread fatigue damage. We are issuing 
this AD to detect and correct fatigue cracking of the fuselage skin 
panels at the chem-mill steps, which could result in sudden fracture 
and failure of the fuselage skin panels, and consequent rapid 
decompression of the airplane.

(f) Compliance

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

(g) Retained Inspections With No Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2016-13-10, with no changes. At the applicable time specified in 
tables 1, 2, 3, and 5 of paragraph 1.E., ``Compliance,'' of Boeing 
Alert Service Bulletin 737-53A1293, Revision 3, dated January 23, 
2015, except as required by paragraphs (l)(1) and (l)(2) of this AD: 
Do the actions specified in paragraphs (g)(1) and (g)(2) of this AD, 
in accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-53A1293, Revision 3, dated January 23, 2015, 
except as required by paragraph (l)(3) of this AD. Repeat the 
applicable inspections thereafter at the applicable times specified 
in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
737-53A1293, Revision 3, dated January 23, 2015.
    (1) Do an external detailed inspection for cracking of the 
fuselage skin chem-mill steps.
    (2) Do an external non-destructive (medium frequency eddy 
current, magneto optical imaging, C-Scan, or ultrasonic phased 
array) inspection for cracking of the fuselage skin chem-mill steps.

[[Page 53911]]

(h) Retained Repair With Clarification of Repair Information and 
Service Information Exception

    This paragraph restates the requirements of paragraph (h) of AD 
2016-13-10, with clarification of repair information and service 
information exception. If any cracking is found during any 
inspection required by paragraph (g) of this AD, do the applicable 
actions specified in paragraph (h)(1), (h)(2),or (h)(3) of this AD. 
Installation of a repair prior to August 9, 2016 (the effective date 
of AD 2016-13-10) that meets the conditions specified in Part 9 of 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
737-53A1293, Revision 3, dated January 23, 2015, terminates the 
inspections required by paragraph (g) of this AD for the area 
covered by that repair only. Installation of a repair prior to 
August 9, 2016, that meets the conditions specified in Part 9 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1293, Revision 3, dated January 23, 2015, covers all eight chem-
mill step inspection areas between STA 410 and STA 450, and was done 
using a method approved in accordance with the procedures specified 
in paragraph (n) of this AD, terminates the inspections required by 
paragraph (g) of this AD for the area covered by that repair only, 
and terminates the preventive modification required by paragraph (i) 
of this AD.
    (1) Repair before further flight in accordance with Part 2 (for 
Group 1 airplanes) or Part 7 (for Group 2 airplanes) of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1293, Revision 3, dated January 23, 2015; except as required by 
paragraph (l)(3) of this AD. Installation of a repair that meets the 
conditions specified in Note (a) of table 1, 2, 3, or 5 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1293, 
Revision 3, dated January 23, 2015, terminates the repetitive 
inspections required by paragraph (g) of this AD for the area 
covered by that repair only.
    (2) For Group 1 airplanes: Accomplishing the modification 
specified in paragraph (i) of this AD is a method of compliance with 
paragraph (h)(1) of this AD.
    (3) If any cracking is found in any area not covered by the 
preventive modification doubler during any inspection required by 
paragraph (g) of this AD: Repair before further flight, in 
accordance with Part 3 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 737-53A1293, Revision 3, dated January 23, 
2015, except as provided by paragraph (l)(3) of this AD. 
Installation of this repair terminates the repetitive inspections 
required by paragraph (g) of this AD for the area covered by that 
repair only.

(i) Retained Preventive Modification With Clarification of Service 
Information Exception and Method of Compliance Procedures

    This paragraph restates the requirements of paragraph (i) of AD 
2016-13-10, with clarification of service information exception and 
method of compliance procedures. For Group 1 airplanes: At the 
applicable time specified in tables 1, 2, and 3 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1293, 
Revision 3, dated January 23, 2015, except as required by paragraphs 
(l)(1) and (l)(2) of this AD, do a preventive modification of the 
fuselage skin at crown stringers S-1 and S-2R, including all 
applicable related investigative actions, in accordance with Part 9 
of the Accomplishment Instructions of Boeing Alert Service Bulletin 
737-53A1293, Revision 3, dated January 23, 2015, except as provided 
by paragraph (l)(3) of this AD. Do all applicable related 
investigative actions concurrently with the modification. 
Installation of a preventive modification terminates the repetitive 
inspections required by paragraph (g) of this AD for the modified 
area only. Thereafter, repeat the inspections specified in Part 3 of 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
737-53A1293, Revision 3, dated January 23, 2015.

(j) Retained Optional Modification With Clarification of Service 
Information

    This paragraph restates the requirements of paragraph (j) of AD 
2016-13-10, with clarification of service information. Accomplishing 
a modification of the chem-mill steps at any location identified in 
Boeing Service Bulletin 737-53A1293, Revision 2, dated August 10, 
2011; or Boeing Alert Service Bulletin 737-53A1293, Revision 3, 
dated January 23, 2015; using a method approved in accordance with 
the procedures specified in paragraph (n) of this AD, terminates the 
repetitive inspections required by paragraph (g) of this AD for the 
modified area only.

(k) Retained Post-Repair/Post-Modification Inspections With No Changes

    This paragraph restates the requirements of paragraph (k) of AD 
2016-13-10, with no changes. Tables 4 and 6 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1293, 
Revision 3, dated January 23, 2015, specify post-repair/post-
modification airworthiness limitation inspections in compliance with 
14 CFR 25.571(a)(3) at the modified locations, which support 
compliance with 14 CFR 121.1109(c)(2) or 129.109(b)(2). As 
airworthiness limitations, these inspections are required by 
maintenance and operational rules. It is therefore unnecessary to 
mandate them in this AD. Deviations from these inspections require 
FAA approval, but do not require an alternative method of 
compliance.

(l) Retained Exceptions to Service Bulletin Specifications With 
Clarification of Method of Compliance Procedures

    This paragraph restates the requirements of paragraph (l) of AD 
2016-13-10, With clarification of method of compliance procedures.
    (1) Where Boeing Alert Service Bulletin 737-53A1293, Revision 3, 
dated January 23, 2015, specifies a compliance time ``after the 
Revision 3 date of this service bulletin,'' this AD requires 
compliance within the specified compliance time after August 9, 2016 
(the effective date of AD 2016-13-10).
    (2) Where the Condition column of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1293, 
Revision 3, dated January 23, 2015, specifies a condition based on 
when an airplane has or has not been inspected, this AD bases the 
condition on whether an airplane has or has not been inspected on 
August 9, 2016 (the effective date of AD 2016-13-10).
    (3) Where Boeing Alert Service Bulletin 737-53A1293, Revision 3, 
dated January 23, 2015, specifies to contact Boeing for repair or 
preventive modification instructions: Before further flight, do the 
repair or preventive modification, as applicable, using a method 
approved in accordance with the procedures specified in paragraph 
(n) of this AD.

(m) Retained Credit for Previous Actions With No Changes

    This paragraph restates the requirements of paragraph (m) of AD 
2016-13-10, with no changes.
    (1) This paragraph provides credit for actions required by 
paragraphs (g) and (h) of this AD, if those actions were performed 
before July 23, 2012 (the effective date of AD 2012-12-04, Amendment 
39-17093 (77 FR 36134, June 18, 2012) (``AD 2012-12-04'')), using 
Boeing Alert Service Bulletin 737-53A1293, Revision 1, dated July 7, 
2010, which is not incorporated by reference in this AD.
    (2) This paragraph provides credit for actions required by 
paragraphs (g) and (h) of this AD, if those actions were performed 
before August 9, 2016 (the effective date of AD 2016-13-10), using 
Boeing Service Bulletin 737-53A1293, Revision 2, dated August 10, 
2011, which was incorporated by reference in AD 2012-12-04.

(n) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles Aircraft Certification Office 
(ACO), FAA, has the authority to approve AMOCs for this AD, if 
requested using the procedures found in 14 CFR 39.19. In accordance 
with 14 CFR 39.19, send your request to your principal inspector or 
local Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in paragraph (o)(1) of this AD. 
Information may be emailed to: 9-ANM-LAACO-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.
    (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, Los Angeles ACO, to make those findings. To be approved, 
the repair method, modification deviation, or alteration deviation 
method must meet the certification basis of the airplane, and the 
approval must specifically refer to this AD.
    (4) AMOCs approved for AD 2012-12-04 are approved as AMOCs for 
the corresponding provisions of this AD.

[[Page 53912]]

(o) Related Information

    (1) For more information about this AD, contact Jennifer 
Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los 
Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; 
phone: 562-627-5264; fax: 562-627-5210; email: 
jennifer.tsakoumakis@faa.gov.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (p)(5) and (p)(6) of this AD.

(p) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
August 9, 2016 (81 FR 43483, July 5, 2016).
    (i) Boeing Alert Service Bulletin 737-53A1293, Revision 3, dated 
January 23, 2015.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
July 23, 2012 (77 FR 36134, June 18, 2012).
    (i) Boeing Service Bulletin 737-53A1293, Revision 2, dated 
August 10, 2011.
    (ii) Reserved.
    (5) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
    (6) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on August 4, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-18952 Filed 8-12-16; 8:45 am]
 BILLING CODE 4910-13-P