Airworthiness Directives; The Boeing Company Airplanes, 45697-45701 [2017-20689]

Download as PDF Federal Register / Vol. 82, No. 189 / Monday, October 2, 2017 / Rules and Regulations own disclosure so long as it is substantially similar. The creditor need not orally request the monitoring information if it is requested in writing. * * * * * Dated: September 8, 2017. Richard Cordray, Director, Bureau of Consumer Financial Protection. [FR Doc. 2017–20417 Filed 9–29–17; 8:45 am] BILLING CODE 4810–AM–P FEDERAL FINANCIAL INSTITUTIONS EXAMINATION COUNCIL 12 CFR Part 1101 [Docket No. FFIEC–2017–0003] Description of Office, Procedures, and Public Information Federal Financial Institutions Examination Council (FFIEC). ACTION: Final rule. AGENCY: The Federal Financial Institutions Examination Council (FFIEC or Council) is adopting as a final rule the interim final rule published July 3, 2017. The interim final rule announced revisions and additions to the Council’s information disclosure regulations under the Freedom of Information Act (FOIA Regulations). The interim final rule also replaced the interim final rule published on December 27, 2016. The revisions in the interim final rule implement recent statutory amendments to the FOIA that are mandated by the FOIA Improvement Act of 2016, as well as update the language of the Council’s regulations to more closely mirror the language of the FOIA and to reflect the Council’s current FOIA procedures. DATES: Effective October 2, 2017. FOR FURTHER INFORMATION CONTACT: Ms. Judith Dupre, Executive Secretary, Federal Financial Institutions Examination Council, via telephone: (703) 516–5590, or via email: JDupre@ FDIC.gov. SUPPLEMENTARY INFORMATION: The Council 1 is finalizing its interim rule (82 FR 30724 (July 3, 2017)), which revised its information disclosure regulations under the Freedom of Information Act 2 (FOIA Regulations). On June 30, 2016, the Freedom of Information Act (FOIA) was amended jstallworth on DSKBBY8HB2PROD with RULES SUMMARY: 1 The members of the Council are the Board of Governors of the Federal Reserve System, the Consumer Financial Protection Bureau, the Federal Deposit Insurance Corporation, the National Credit Union Administration, the Office of the Comptroller of the Currency, and the State Liaison Committee. 2 5 U.S.C. 552. VerDate Sep<11>2014 15:58 Sep 29, 2017 Jkt 244001 by the FOIA Improvement Act of 2016 3 (FOIA Improvement Act). Among other things, section 3 of the FOIA Improvement Act required each Federal agency to revise its disclosure regulations and procedures for processing FOIA requests in order to conform to the substantive amendments made by section 2 of the FOIA Improvement Act by December 27, 2016. Accordingly, the Council implemented the required substantive and procedural changes necessary to comply with the FOIA Improvement Act’s amendments through issuance of the interim final rule (81 FR 94937 (December 27, 2016)). In addition, the Council made certain changes to its FOIA Regulations to reflect revisions brought about by prior amendments to the FOIA that were incorporated into the Council’s procedures and to make the FOIA process easier for the public to navigate. In drafting these amendments to the FOIA Regulations, the Council consulted the ‘‘Guidance for Agency FOIA Regulations’’ issued by the U.S. Department of Justice’s Office for Information Policy. No comments were received in response to the interim final rule and it is being finalized without change. Authority and Issuance For the reasons set forth in the preamble, the Federal Financial Institutions Examination Council adopts as a final rule, without changes, the interim final rule amending 12 CFR 1101.4, which was published at 82 FR 30724 on July 3, 2017. Dated: September 27, 2017. Federal Financial Institutions Examinations Council. Judith E. Dupre, Executive Secretary. [FR Doc. 2017–21050 Filed 9–29–17; 8:45 am] BILLING CODE 7535–01–P; 6714–01–P; 6210–01–P; 4810–33–P; 4810–AM–P ACTION: 45697 Final rule. We are superseding Airworthiness Directive (AD) 2011–01– 15, which applied to certain The Boeing Company Model 757–200, –200CB, and –300 series airplanes. AD 2011–01–15 required repetitive inspections for cracking of the fuselage skin of the crown skin panel along the chem-milled step at certain stringers, and repair if necessary. This AD adds repetitive inspections for cracking in additional areas, and repair if necessary; removes airplanes from the applicability; adds an optional skin panel replacement, which terminates all inspections; adds an optional preventive modification, which terminates certain inspections; and reduces the compliance time for certain inspections. This AD was prompted by reports of the initiation of new fatigue cracking in the fuselage skin of the crown skin panel along locally thinned channels adjacent to the chem-milled steps. We are issuing this AD to address the unsafe condition on these products. SUMMARY: This AD is effective November 6, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 6, 2017. DATES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740; 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–2016– 3697. ADDRESSES: DEPARTMENT OF TRANSPORTATION Examining the AD Docket Federal Aviation Administration You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 3697; 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 14 CFR Part 39 [Docket No. FAA–2016–3697; Product Identifier 2015–NM–143–AD; Amendment 39–19062; AD 2017–20–05] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. AGENCY: 3 Public Law 114–185, 130 Stat. 538 (June 30, 2016). PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 E:\FR\FM\02OCR1.SGM 02OCR1 45698 Federal Register / Vol. 82, No. 189 / Monday, October 2, 2017 / Rules and Regulations New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Eric Schrieber, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5348; fax: 562–627– 5210; email: eric.schrieber@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2011–01–15, Amendment 39–16572 (76 FR 1351, January 10, 2011) (‘‘AD 2011–01–15’’). AD 2011–01–15 applied to certain The Boeing Company Model 757–200, –200CB, and –300 series airplanes. AD 2011–01–15 required repetitive inspections for cracking of the fuselage skin of the crown skin panel along the chem-milled step at stringers S–4L and S–4R, from station (STA) 297 through STA 439, and repair if necessary. AD 2011–01–15 also included terminating action for the repetitive inspections of the repaired areas only. AD 2011–01–15 resulted from reports of cracking in the fuselage skin of the crown skin panel. The NPRM published in the Federal Register on February 18, 2016 (81 FR 8157) (‘‘The NPRM’’). The NPRM was prompted by reports of the initiation of new fatigue cracking in the fuselage skin of the crown skin panel along locally thinned channels adjacent to the chemmilled steps. The NPRM proposed to add repetitive inspections for cracking in additional areas, and repair if necessary. The NPRM also proposed to remove airplanes from the applicability in AD 2011–01–15. The NPRM also proposed to add an optional skin panel replacement, which would terminate all inspections, and an optional preventive modification, which would terminate certain inspections. We issued a supplemental NPRM (SNPRM) that published in the Federal Register on May 5, 2017 (82 FR 21146). The SNPRM proposed to reduce the compliance time for certain inspections. We are issuing this AD to correct the unsafe condition on these products. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the SNPRM and the FAA’s response to each comment. Supportive Comment United Airlines and Boeing concurred with the SNPRM. Request for Alternative Method of Compliance (AMOC) VT Mobile Aerospace Engineering (MAE) Inc. stated that the proposed AD (in the SNPRM) affects Model 757–200 airplanes that were modified using certain VT MAE supplemental type certificates (STCs). VT MAE noted that its design at certain inspection locations is not identical to that of the Boeing STC design at those locations. Therefore, VT MAE plans to issue new service information to address the unsafe condition, and plans to request approval of an AMOC from the FAA for use of the new service information. FedEx stated that its airplanes have been modified in accordance with the VT MAE STC, and once this AMOC is approved to address this issue, FedEx will use it to comply with the requirements in the proposed AD (in the SNPRM). We acknowledge the commenters’ remarks. Under the provisions of paragraph (n) of this AD, we will consider requests for approval of an AMOC that addresses the VT MAE STCs, if appropriate data are submitted to substantiate that the method would provide an acceptable level of safety. We have made no change to this AD in this regard. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD as proposed, except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the SNPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the SNPRM. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Special Attention Service Bulletin 757–53– 0097, Revision 3, dated December 2, 2016. This service information describes procedures for repetitive external sliding probe eddy current (EC) and external spot-probe-medium-frequency EC inspections for cracking of the crown skin panel, repair, a preventive modification, and replacement of the crown skin panel. 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 652 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Inspections (Zone 1) [Retained actions from AD 2011-01-15]. Inspections (Zones 2 and 3) [new action]. jstallworth on DSKBBY8HB2PROD with RULES Optional modification ............ Labor cost Parts cost Cost per product 2 work-hours × $85 per hour = $170 per inspection cycle. Up to 4 work-hours × $85 per hour = Up to $340 per inspection cycle. Up to 615 work-hours × $85 per hour = Up to $52,275. $0 ......................... $170 per inspection cycle .... $110,840 per inspection cycle. $0 ......................... Up to $340 per inspection cycle. Up to $221,680 per inspection cycle. Up to $26,496 ...... Up to $78,771 ...................... Up to $51,358,692. We have received no definitive data that enables us to provide a cost estimate for the on-condition actions or the optional replacement specified in this AD. VerDate Sep<11>2014 15:21 Sep 29, 2017 Jkt 244001 Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 Cost on U.S. operators detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with E:\FR\FM\02OCR1.SGM 02OCR1 Federal Register / Vol. 82, No. 189 / Monday, October 2, 2017 / Rules and Regulations promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. 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 We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under 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: jstallworth on DSKBBY8HB2PROD with RULES 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) ■ VerDate Sep<11>2014 15:21 Sep 29, 2017 Jkt 244001 2011–01–15, Amendment 39–16572 (76 FR 1351, January 10, 2011), and adding the following new AD: 2017–20–05 The Boeing Company: Amendment 39–19062; Docket No. FAA–2016–3697; Product Identifier 2015–NM–143–AD. (a) Effective Date This AD is effective November 6, 2017. (b) Affected ADs This AD replaces AD 2011–01–15, Amendment 39–16572 (76 FR 1351, January 10, 2011) (‘‘AD 2011–01–15’’). (c) Applicability (1) This AD applies to The Boeing Company Model 757–200 and –300 series airplanes, certificated in any category, as identified in Boeing Special Attention Service Bulletin 757–53–0097, Revision 3, dated December 2, 2016. (2) Installation of Supplemental Type Certificate (STC) ST01518SE (http:// rgl.faa.gov/Regulatory_and_Guidance_ Library/rgSTC.nsf/0/38B606833BB D98B386257FAA 00602538?OpenDocument&Highlight= st01518se) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01518SE 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 the initiation of fatigue cracking in the fuselage skin of the crown skin panel along locally thinned channels adjacent to the chemmilled steps. We are issuing this AD to detect and correct fatigue cracking of the fuselage skin of the crown skin panel, which could result in pressure venting and consequent rapid decompression of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections Do the applicable inspections required by paragraphs (g)(1), (g)(2), and (g)(3) of this AD. (1) For all airplanes: Within the compliance time specified in paragraph (h) of this AD, do the Zone 1 inspection specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD. Repeat the applicable Part 1 or Part 2 inspection thereafter at the applicable times specified in table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 757–53–0097, Revision 3, dated December 2, 2016. Accomplishing the preventive modification specified in paragraph (k)(1) of this AD or the replacement specified in paragraph (k)(2) of this AD terminates the inspections required by this paragraph. PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 45699 (i) Do an external sliding probe eddy current (EC) inspection for cracking of the crown skin panel in the applicable Zone 1 areas specified in, and in accordance with, Part 1 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757–53–0097, Revision 3, dated December 2, 2016. (ii) Do an external spot-probe-mediumfrequency EC inspection for cracking of the crown skin panel in the applicable Zone 1 areas specified in, and in accordance with, Part 2 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757–53–0097, Revision 3, dated December 2, 2016. (2) For airplanes on which any crack is found during any inspection required by paragraph (g)(1) of this AD; or any repair is installed that covers any portion of the Zone 1 inspection area specified in Boeing Special Attention Service Bulletin 757–53–0097, Revision 3, dated December 2, 2016; or the optional Zone 1 preventive modification specified in paragraph (k)(1) of this AD is installed: At the applicable time specified in table 2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 757–53–0097, Revision 3, dated December 2, 2016, except as required by paragraph (l)(1) of this AD: Do the Zone 2 inspection specified in paragraph (g)(2)(i) or (g)(2)(ii) of this AD. Repeat the applicable Part 4 or Part 5 inspection thereafter at the applicable times specified in table 2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 757–53–0097, Revision 3, dated December 2, 2016. Accomplishing the replacement specified in paragraph (k)(2) of this AD terminates the inspections required by this paragraph. (i) Do an external sliding probe EC inspection for cracking of the crown skin panel in the applicable Zone 2 areas specified in, and in accordance with, Part 4 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757–53–0097, Revision 3, dated December 2, 2016. (ii) Do an external spot-probe-mediumfrequency EC inspection for cracking of the crown skin panel in the applicable Zone 2 areas specified in, and in accordance with, Part 5 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757–53–0097, Revision 3, dated December 2, 2016. (3) For airplanes on which any crack is found during any inspection required by paragraph (g)(1) of this AD; or any repair is installed that covers any portion of the Zone 1 inspection area specified in Boeing Special Attention Service Bulletin 757–53–0097, Revision 3, dated December 2, 2016; or the optional Zone 1 preventive modification specified in paragraph (k)(1) of this AD is installed: At the applicable time specified in table 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 757–53–0097, Revision 3, dated December 2, 2016, except as required by paragraph (l)(1) of this AD, do the Zone 3 inspection specified in paragraph (g)(3)(i) or (g)(3)(ii) of this AD. Repeat the applicable Part 6 or Part 7 inspection thereafter at the applicable times specified in table 3 of paragraph 1.E., E:\FR\FM\02OCR1.SGM 02OCR1 45700 Federal Register / Vol. 82, No. 189 / Monday, October 2, 2017 / Rules and Regulations ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 757–53–0097, Revision 3, dated December 2, 2016. Accomplishing the replacement specified in paragraph (k)(2) of this AD terminates the inspections required by this paragraph. (i) Do an external sliding probe EC inspection for cracking of the crown skin panel in the applicable Zone 3 areas specified in, and in accordance with, Part 6 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757–53–0097, Revision 3, dated December 2, 2016. (ii) Do an external spot-probe-mediumfrequency EC inspection for cracking of the crown skin panel in the applicable Zone 3 areas specified in, and in accordance with, Part 7 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757–53–0097, Revision 3, dated December 2, 2016. jstallworth on DSKBBY8HB2PROD with RULES (h) Initial Compliance Time for Inspection Required by Paragraph (g)(1) of This AD Within the applicable compliance times specified in paragraphs (h)(1), (h)(2), (h)(3), and (h)(4) of this AD, whichever occurs latest: Do the initial inspection required by paragraph (g)(1) of this AD. (1) For all airplanes: Before the accumulation of 15,000 total flight cycles. (2) For airplanes on which an external sliding probe EC inspection for Zone 1, as specified in Boeing Special Attention Service Bulletin 757–53–0097, has been done as of the effective date of this AD: Within 620 flight cycles after accomplishing the most recent external sliding probe EC inspection for Zone 1. (3) For airplanes on which an external spot-probe-medium-frequency EC inspection for Zone 1, as specified in Boeing Special Attention Service Bulletin 757–53–0097, has been done as of the effective date of this AD: Within 200 flight cycles after accomplishing the most recent external spot-probe-mediumfrequency EC inspection for Zone 1. (4) For all airplanes: Within 200 flight cycles or 90 days after the effective date of this AD, whichever occurs first. (i) Post-Preventive Modification Supplemental Inspections For airplanes on which a preventive modification has been installed as specified in Part 3 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757–53–0097, Revision 3, dated December 2, 2016: At the applicable time specified in table 4 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 757–53–0097, Revision 3, dated December 2, 2016; do eddy current and detailed inspections for cracking of the applicable areas of the fuselage skin of the doublers, triplers, and fillers of the preventive modification, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757–53– 0097, Revision 3, dated December 2, 2016. Repeat the inspection thereafter at the applicable times specified in table 4 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 757–53– 0097, Revision 3, dated December 2, 2016. VerDate Sep<11>2014 15:21 Sep 29, 2017 Jkt 244001 (j) Repair If any cracking is found during any inspection required by paragraph (g)(1), (g)(2), (g)(3), or (i) of this AD, repair before further flight using a method approved in accordance with the procedures specified in paragraph (n) of this AD. Doing the repair ends the repetitive inspections for the repaired area only. (k) Optional Terminating Actions (1) Accomplishing the preventive modification, including doing high frequency EC open-hole inspections for cracking in the existing fastener holes, in accordance with Part 3 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757–53–0097, Revision 3, dated December 2, 2016, except as required by paragraph (l)(2) of this AD, terminates the inspections required by paragraph (g)(1) of this AD, provided the preventive modification is done before further flight after accomplishing an inspection required by paragraph (g)(1) of this AD. If any cracking is found during any high frequency EC open-hole inspection, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (n) of this AD. (2) Replacing the crown skin panel between station (STA) 297 and STA 439, and stringers S–4L and S–4R, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757–53– 0097, Revision 3, dated December 2, 2016, or using a method approved in accordance with the procedures specified in paragraph (n) of this AD, terminates the inspections required by paragraphs (g)(1), (g)(2), and (g)(3) of this AD. (l) Exceptions to Service Information Specifications and Preventive Modification (1) Where Boeing Special Attention Service Bulletin 757–53–0097, Revision 3, dated December 2, 2016, specifies a compliance time ‘‘after the Revision 2 date of this service bulletin,’’ or ‘‘after the Revision 3 date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Where Boeing Special Attention Service Bulletin 757–53–0097, Revision 3, dated December 2, 2016, specifies to contact Boeing for repair instructions: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (n) of this AD. (m) Credit for Previous Actions This paragraph provides credit for Zone 1 inspections required by paragraph (g)(1) of this AD, if those actions were performed before the effective date of this AD using Boeing Special Attention Service Bulletin 757–53–0097, dated November 22, 2010 (which was incorporated by reference in AD 2011–01–15); Boeing Special Attention Service Bulletin 757–53–0097, Revision 1, dated January 6, 2011; or Boeing Special Attention Service Bulletin 757–53–0097, Revision 2, dated July 28, 2015. (n) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles ACO Branch, FAA, has the authority to approve AMOCs PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 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 (o)(1) of this AD. Information may be emailed to: 9ANM-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 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) AMOCs approved for AD 2011–01–15 are approved as AMOCs for the corresponding provisions of paragraph (g) of this AD; except, as of the effective date of this AD, AMOCs that extend the initial compliance times specified in AD 2011–01– 15 are no longer approved for the compliance time extension, and the compliance times required by this AD must be complied with. (5) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (n)(5)(i) and (n)(5)(ii) 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. 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. (o) Related Information (1) For more information about this AD, contact Eric Schrieber, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627– 5348; fax: 562–627–5210; email: Eric.Schrieber@faa.gov. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (p)(3) and (p)(4) 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. E:\FR\FM\02OCR1.SGM 02OCR1 Federal Register / Vol. 82, No. 189 / Monday, October 2, 2017 / Rules and Regulations (i) Boeing Special Attention Service Bulletin 757–53–0097, Revision 3, dated December 2, 2016. (ii) Reserved. (3) For 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; 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. Issued in Renton, Washington, on September 14, 2017. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017–20689 Filed 9–29–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0532; Product Identifier 2016–NM–203–AD; Amendment 39–19060; AD 2017–20–03] RIN 2120–AA64 Airworthiness Directives; Dassault Aviation Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: jstallworth on DSKBBY8HB2PROD with RULES VerDate Sep<11>2014 15:21 Sep 29, 2017 Jkt 244001 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– 0532; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647– 5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1137; fax 425–227– 1149. SUPPLEMENTARY INFORMATION: Discussion We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a review showing that inadequate clearance may exist between certain electrical wiring and nearby structures. This AD requires an inspection of certain electrical wiring bundles and feeders, modifications, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective November 6, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 6, 2017. SUMMARY: For service information identified in this final rule, contact Dassault Falcon Jet Corporation, Teterboro Airport, P.O. Box 2000, South Hackensack, NJ 07606; telephone 201– 440–6700; Internet http:// www.dassaultfalcon.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–2017–0532. ADDRESSES: We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Dassault Aviation Model FALCON 7X airplanes. The NPRM published in the Federal Register on June 12, 2017 (82 FR 26867) (‘‘the NPRM’’). The NPRM was prompted by a review showing that inadequate clearance may exist between certain electrical wiring and nearby structures. The NPRM proposed to require an inspection of certain electrical wiring bundles and feeders, modifications, and corrective actions if necessary. We are issuing this AD to detect and correct inadequate clearances between electrical wiring and nearby structures, which could lead to interference or contact with a structure and cause an electrical short circuit or fluid leakage. This could result in the PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 45701 loss of several functions essential for safe flight. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2016–0230, dated November 21, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Dassault Aviation Model FALCON 7X airplanes. The MCAI states: A review of the wiring and tubing lay-out showed that there may be low clearance between electrical wiring and nearby structure. Although no in-service incident has been reported, the minimum clearances could deteriorate over time. This condition, if not detected and corrected, could lead to interference or contact with structure, provoking an electrical short circuit or fluid leakage, possibly resulting in loss of several functions essential for safe flight. To initially address this potential unsafe condition, [Dassault Aviation] DA developed some interim modifications (mod) addressing the risk of short circuit and fluid leakage, and EASA issued AD 2010–0029 (later revised) [which corresponds to FAA AD 2011–14–04, Amendment 39–16739 (76 FR 39256, July 6, 2011) (‘‘AD 2011–14–04’’)] to require embodiment of those modifications inservice. Since EASA AD 2010–0029R1 was issued, DA developed another set of modifications, available for in-service application through Service Bulletin (SB) F7X–056, which are considered the final solutions for this unsafe condition. For the reasons described above, this [EASA] AD requires a one-time [general visual] inspection [for worn or damaged wiring or connectors due to inadequate clearance between wiring and nearby structures] of the affected electrical wiring and, depending on findings, corrective action(s) and modification of the aeroplane. Corrective actions include modifying the clamping and routing; adding new brackets, clamps, and cable protections; replacing damaged parts; and improving connections using lock wires. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0532. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial E:\FR\FM\02OCR1.SGM 02OCR1

Agencies

[Federal Register Volume 82, Number 189 (Monday, October 2, 2017)]
[Rules and Regulations]
[Pages 45697-45701]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-20689]


=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-3697; Product Identifier 2015-NM-143-AD; Amendment 
39-19062; AD 2017-20-05]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2011-01-15, 
which applied to certain The Boeing Company Model 757-200, -200CB, and 
-300 series airplanes. AD 2011-01-15 required repetitive inspections 
for cracking of the fuselage skin of the crown skin panel along the 
chem-milled step at certain stringers, and repair if necessary. This AD 
adds repetitive inspections for cracking in additional areas, and 
repair if necessary; removes airplanes from the applicability; adds an 
optional skin panel replacement, which terminates all inspections; adds 
an optional preventive modification, which terminates certain 
inspections; and reduces the compliance time for certain inspections. 
This AD was prompted by reports of the initiation of new fatigue 
cracking in the fuselage skin of the crown skin panel along locally 
thinned channels adjacent to the chem-milled steps. We are issuing this 
AD to address the unsafe condition on these products.

DATES: This AD is effective November 6, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of November 6, 
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; 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-2016-3697.

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-
3697; 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

[[Page 45698]]

New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Eric Schrieber, Aerospace Engineer, 
Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount 
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5348; fax: 562-627-
5210; email: eric.schrieber@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2011-01-15, Amendment 39-16572 (76 FR 1351, 
January 10, 2011) (``AD 2011-01-15''). AD 2011-01-15 applied to certain 
The Boeing Company Model 757-200, -200CB, and -300 series airplanes. AD 
2011-01-15 required repetitive inspections for cracking of the fuselage 
skin of the crown skin panel along the chem-milled step at stringers S-
4L and S-4R, from station (STA) 297 through STA 439, and repair if 
necessary. AD 2011-01-15 also included terminating action for the 
repetitive inspections of the repaired areas only. AD 2011-01-15 
resulted from reports of cracking in the fuselage skin of the crown 
skin panel. The NPRM published in the Federal Register on February 18, 
2016 (81 FR 8157) (``The NPRM''). The NPRM was prompted by reports of 
the initiation of new fatigue cracking in the fuselage skin of the 
crown skin panel along locally thinned channels adjacent to the chem-
milled steps. The NPRM proposed to add repetitive inspections for 
cracking in additional areas, and repair if necessary. The NPRM also 
proposed to remove airplanes from the applicability in AD 2011-01-15. 
The NPRM also proposed to add an optional skin panel replacement, which 
would terminate all inspections, and an optional preventive 
modification, which would terminate certain inspections.
    We issued a supplemental NPRM (SNPRM) that published in the Federal 
Register on May 5, 2017 (82 FR 21146). The SNPRM proposed to reduce the 
compliance time for certain inspections.
    We are issuing this AD to correct the unsafe condition on these 
products.

Comments

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

Supportive Comment

    United Airlines and Boeing concurred with the SNPRM.

Request for Alternative Method of Compliance (AMOC)

    VT Mobile Aerospace Engineering (MAE) Inc. stated that the proposed 
AD (in the SNPRM) affects Model 757-200 airplanes that were modified 
using certain VT MAE supplemental type certificates (STCs). VT MAE 
noted that its design at certain inspection locations is not identical 
to that of the Boeing STC design at those locations. Therefore, VT MAE 
plans to issue new service information to address the unsafe condition, 
and plans to request approval of an AMOC from the FAA for use of the 
new service information.
    FedEx stated that its airplanes have been modified in accordance 
with the VT MAE STC, and once this AMOC is approved to address this 
issue, FedEx will use it to comply with the requirements in the 
proposed AD (in the SNPRM).
    We acknowledge the commenters' remarks. Under the provisions of 
paragraph (n) of this AD, we will consider requests for approval of an 
AMOC that addresses the VT MAE STCs, if appropriate data are submitted 
to substantiate that the method would provide an acceptable level of 
safety. We have made no change to this AD in this regard.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD as proposed, except for minor editorial changes. We have 
determined that these minor changes:
     Are consistent with the intent that was proposed in the 
SNPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the SNPRM.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Special Attention Service Bulletin 757-53-0097, 
Revision 3, dated December 2, 2016. This service information describes 
procedures for repetitive external sliding probe eddy current (EC) and 
external spot-probe-medium-frequency EC inspections for cracking of the 
crown skin panel, repair, a preventive modification, and replacement of 
the crown skin panel. 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 652 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
----------------------------------------------------------------------------------------------------------------
Inspections (Zone 1) [Retained  2 work-hours x     $0......................  $170 per           $110,840 per
 actions from AD                 $85 per hour =                               inspection cycle.  inspection
 2011[dash]01[dash]15].          $170 per                                                        cycle.
                                 inspection cycle.
Inspections (Zones 2 and 3)     Up to 4 work-      $0......................  Up to $340 per     Up to $221,680
 [new action].                   hours x $85 per                              inspection cycle.  per inspection
                                 hour = Up to                                                    cycle.
                                 $340 per
                                 inspection cycle.
Optional modification.........  Up to 615 work-    Up to $26,496...........  Up to $78,771....  Up to
                                 hours x $85 per                                                 $51,358,692.
                                 hour = Up to
                                 $52,275.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that enables us to provide a 
cost estimate for the on-condition actions or the optional replacement 
specified in this AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with

[[Page 45699]]

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

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

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2011-01-15, Amendment 39-16572 (76 FR 1351, January 10, 2011), and 
adding the following new AD:

2017-20-05 The Boeing Company: Amendment 39-19062; Docket No. FAA-
2016-3697; Product Identifier 2015-NM-143-AD.

(a) Effective Date

    This AD is effective November 6, 2017.

(b) Affected ADs

    This AD replaces AD 2011-01-15, Amendment 39-16572 (76 FR 1351, 
January 10, 2011) (``AD 2011-01-15'').

(c) Applicability

    (1) This AD applies to The Boeing Company Model 757-200 and -300 
series airplanes, certificated in any category, as identified in 
Boeing Special Attention Service Bulletin 757-53-0097, Revision 3, 
dated December 2, 2016.
    (2) Installation of Supplemental Type Certificate (STC) 
ST01518SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgSTC.nsf/0/38B606833BBD98B386257FAA00602538?OpenDocument&Highlight=st01518se) 
does not affect the ability to accomplish the actions required by 
this AD. Therefore, for airplanes on which STC ST01518SE 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 the initiation of fatigue 
cracking in the fuselage skin of the crown skin panel along locally 
thinned channels adjacent to the chem-milled steps. We are issuing 
this AD to detect and correct fatigue cracking of the fuselage skin 
of the crown skin panel, which could result in pressure venting and 
consequent rapid decompression of the airplane.

(f) Compliance

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

(g) Repetitive Inspections

    Do the applicable inspections required by paragraphs (g)(1), 
(g)(2), and (g)(3) of this AD.
    (1) For all airplanes: Within the compliance time specified in 
paragraph (h) of this AD, do the Zone 1 inspection specified in 
paragraph (g)(1)(i) or (g)(1)(ii) of this AD. Repeat the applicable 
Part 1 or Part 2 inspection thereafter at the applicable times 
specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing 
Special Attention Service Bulletin 757-53-0097, Revision 3, dated 
December 2, 2016. Accomplishing the preventive modification 
specified in paragraph (k)(1) of this AD or the replacement 
specified in paragraph (k)(2) of this AD terminates the inspections 
required by this paragraph.
    (i) Do an external sliding probe eddy current (EC) inspection 
for cracking of the crown skin panel in the applicable Zone 1 areas 
specified in, and in accordance with, Part 1 of the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 757-53-
0097, Revision 3, dated December 2, 2016.
    (ii) Do an external spot-probe-medium-frequency EC inspection 
for cracking of the crown skin panel in the applicable Zone 1 areas 
specified in, and in accordance with, Part 2 of the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 757-53-
0097, Revision 3, dated December 2, 2016.
    (2) For airplanes on which any crack is found during any 
inspection required by paragraph (g)(1) of this AD; or any repair is 
installed that covers any portion of the Zone 1 inspection area 
specified in Boeing Special Attention Service Bulletin 757-53-0097, 
Revision 3, dated December 2, 2016; or the optional Zone 1 
preventive modification specified in paragraph (k)(1) of this AD is 
installed: At the applicable time specified in table 2 of paragraph 
1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 
757-53-0097, Revision 3, dated December 2, 2016, except as required 
by paragraph (l)(1) of this AD: Do the Zone 2 inspection specified 
in paragraph (g)(2)(i) or (g)(2)(ii) of this AD. Repeat the 
applicable Part 4 or Part 5 inspection thereafter at the applicable 
times specified in table 2 of paragraph 1.E., ``Compliance,'' of 
Boeing Special Attention Service Bulletin 757-53-0097, Revision 3, 
dated December 2, 2016. Accomplishing the replacement specified in 
paragraph (k)(2) of this AD terminates the inspections required by 
this paragraph.
    (i) Do an external sliding probe EC inspection for cracking of 
the crown skin panel in the applicable Zone 2 areas specified in, 
and in accordance with, Part 4 of the Accomplishment Instructions of 
Boeing Special Attention Service Bulletin 757-53-0097, Revision 3, 
dated December 2, 2016.
    (ii) Do an external spot-probe-medium-frequency EC inspection 
for cracking of the crown skin panel in the applicable Zone 2 areas 
specified in, and in accordance with, Part 5 of the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 757-53-
0097, Revision 3, dated December 2, 2016.
    (3) For airplanes on which any crack is found during any 
inspection required by paragraph (g)(1) of this AD; or any repair is 
installed that covers any portion of the Zone 1 inspection area 
specified in Boeing Special Attention Service Bulletin 757-53-0097, 
Revision 3, dated December 2, 2016; or the optional Zone 1 
preventive modification specified in paragraph (k)(1) of this AD is 
installed: At the applicable time specified in table 3 of paragraph 
1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 
757-53-0097, Revision 3, dated December 2, 2016, except as required 
by paragraph (l)(1) of this AD, do the Zone 3 inspection specified 
in paragraph (g)(3)(i) or (g)(3)(ii) of this AD. Repeat the 
applicable Part 6 or Part 7 inspection thereafter at the applicable 
times specified in table 3 of paragraph 1.E.,

[[Page 45700]]

``Compliance,'' of Boeing Special Attention Service Bulletin 757-53-
0097, Revision 3, dated December 2, 2016. Accomplishing the 
replacement specified in paragraph (k)(2) of this AD terminates the 
inspections required by this paragraph.
    (i) Do an external sliding probe EC inspection for cracking of 
the crown skin panel in the applicable Zone 3 areas specified in, 
and in accordance with, Part 6 of the Accomplishment Instructions of 
Boeing Special Attention Service Bulletin 757-53-0097, Revision 3, 
dated December 2, 2016.
    (ii) Do an external spot-probe-medium-frequency EC inspection 
for cracking of the crown skin panel in the applicable Zone 3 areas 
specified in, and in accordance with, Part 7 of the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 757-53-
0097, Revision 3, dated December 2, 2016.

(h) Initial Compliance Time for Inspection Required by Paragraph (g)(1) 
of This AD

    Within the applicable compliance times specified in paragraphs 
(h)(1), (h)(2), (h)(3), and (h)(4) of this AD, whichever occurs 
latest: Do the initial inspection required by paragraph (g)(1) of 
this AD.
    (1) For all airplanes: Before the accumulation of 15,000 total 
flight cycles.
    (2) For airplanes on which an external sliding probe EC 
inspection for Zone 1, as specified in Boeing Special Attention 
Service Bulletin 757-53-0097, has been done as of the effective date 
of this AD: Within 620 flight cycles after accomplishing the most 
recent external sliding probe EC inspection for Zone 1.
    (3) For airplanes on which an external spot-probe-medium-
frequency EC inspection for Zone 1, as specified in Boeing Special 
Attention Service Bulletin 757-53-0097, has been done as of the 
effective date of this AD: Within 200 flight cycles after 
accomplishing the most recent external spot-probe-medium-frequency 
EC inspection for Zone 1.
    (4) For all airplanes: Within 200 flight cycles or 90 days after 
the effective date of this AD, whichever occurs first.

(i) Post-Preventive Modification Supplemental Inspections

    For airplanes on which a preventive modification has been 
installed as specified in Part 3 of the Accomplishment Instructions 
of Boeing Special Attention Service Bulletin 757-53-0097, Revision 
3, dated December 2, 2016: At the applicable time specified in table 
4 of paragraph 1.E., ``Compliance,'' of Boeing Special Attention 
Service Bulletin 757-53-0097, Revision 3, dated December 2, 2016; do 
eddy current and detailed inspections for cracking of the applicable 
areas of the fuselage skin of the doublers, triplers, and fillers of 
the preventive modification, in accordance with the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 757-53-
0097, Revision 3, dated December 2, 2016. Repeat the inspection 
thereafter at the applicable times specified in table 4 of paragraph 
1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 
757-53-0097, Revision 3, dated December 2, 2016.

(j) Repair

    If any cracking is found during any inspection required by 
paragraph (g)(1), (g)(2), (g)(3), or (i) of this AD, repair before 
further flight using a method approved in accordance with the 
procedures specified in paragraph (n) of this AD. Doing the repair 
ends the repetitive inspections for the repaired area only.

(k) Optional Terminating Actions

    (1) Accomplishing the preventive modification, including doing 
high frequency EC open-hole inspections for cracking in the existing 
fastener holes, in accordance with Part 3 of the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 757-53-
0097, Revision 3, dated December 2, 2016, except as required by 
paragraph (l)(2) of this AD, terminates the inspections required by 
paragraph (g)(1) of this AD, provided the preventive modification is 
done before further flight after accomplishing an inspection 
required by paragraph (g)(1) of this AD. If any cracking is found 
during any high frequency EC open-hole inspection, before further 
flight, repair using a method approved in accordance with the 
procedures specified in paragraph (n) of this AD.
    (2) Replacing the crown skin panel between station (STA) 297 and 
STA 439, and stringers S-4L and S-4R, in accordance with the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 757-53-0097, Revision 3, dated December 2, 2016, or using a 
method approved in accordance with the procedures specified in 
paragraph (n) of this AD, terminates the inspections required by 
paragraphs (g)(1), (g)(2), and (g)(3) of this AD.

(l) Exceptions to Service Information Specifications and Preventive 
Modification

    (1) Where Boeing Special Attention Service Bulletin 757-53-0097, 
Revision 3, dated December 2, 2016, specifies a compliance time 
``after the Revision 2 date of this service bulletin,'' or ``after 
the Revision 3 date of this service bulletin,'' this AD requires 
compliance within the specified compliance time after the effective 
date of this AD.
    (2) Where Boeing Special Attention Service Bulletin 757-53-0097, 
Revision 3, dated December 2, 2016, specifies to contact Boeing for 
repair instructions: Before further flight, repair using a method 
approved in accordance with the procedures specified in paragraph 
(n) of this AD.

(m) Credit for Previous Actions

    This paragraph provides credit for Zone 1 inspections required 
by paragraph (g)(1) of this AD, if those actions were performed 
before the effective date of this AD using Boeing Special Attention 
Service Bulletin 757-53-0097, dated November 22, 2010 (which was 
incorporated by reference in AD 2011-01-15); Boeing Special 
Attention Service Bulletin 757-53-0097, Revision 1, dated January 6, 
2011; or Boeing Special Attention Service Bulletin 757-53-0097, 
Revision 2, dated July 28, 2015.

(n) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles 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 (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 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) AMOCs approved for AD 2011-01-15 are approved as AMOCs for 
the corresponding provisions of paragraph (g) of this AD; except, as 
of the effective date of this AD, AMOCs that extend the initial 
compliance times specified in AD 2011-01-15 are no longer approved 
for the compliance time extension, and the compliance times required 
by this AD must be complied with.
    (5) For service information that contains steps that are labeled 
as Required for Compliance (RC), the provisions of paragraphs 
(n)(5)(i) and (n)(5)(ii) 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. 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.

(o) Related Information

    (1) For more information about this AD, contact Eric Schrieber, 
Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5348; fax: 562-627-5210; email: Eric.Schrieber@faa.gov.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (p)(3) and (p)(4) 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.

[[Page 45701]]

    (i) Boeing Special Attention Service Bulletin 757-53-0097, 
Revision 3, dated December 2, 2016.
    (ii) Reserved.
    (3) For 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; 
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 September 14, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-20689 Filed 9-29-17; 8:45 am]
 BILLING CODE 4910-13-P