Airworthiness Directives; The Boeing Company Airplanes, 42411-42415 [2013-15526]

Download as PDF Federal Register / Vol. 78, No. 136 / Tuesday, July 16, 2013 / 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 helicopters 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 to the extent that it justifies making a regulatory distinction; 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. We prepared an economic evaluation of the estimated costs to comply with this AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ (P/N) 4639 310 065, installed in the tail rotor intermediate gear box (IGB), P/N 4639 002 007, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as failure of a bevel gear, failure of the tail rotor IGB, and subsequent loss of control of the helicopter. (c) Effective Date This AD becomes effective August 20, 2013. (d) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (e) Required Actions Within 30 days, do the following: (1) Determine if a bevel gear with a serial number (S/N) listed in Table 1 of Eurocopter Alert Service Bulletin MBB BK117 C–2–04A– 005, Revision 2, dated April 28, 2010 (ASB), is installed in the IGB. (i) If a bevel gear listed in Table 1 of the ASB is installed in the IGB, record the reduced life limit of the bevel gear onto the component history card or equivalent record of the IGB. (ii) If the bevel gear life limit has been reached or is exceeded, before further flight, replace the bevel gear with an airworthy bevel gear. (2) Revise the Airworthiness Limitations section of the maintenance manual by reducing the retirement life for each IGB bevel gear, P/N 4639 310 065, that has a S/ N listed in Table 1 of the ASB to the life limit corresponding to that S/N. (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Chinh Vuong, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email chinh.vuong@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC. ■ 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): 2013–12–05 Eurocopter Deutschland GmbH Helicopters: Amendment 39–17483; Docket No. FAA–2013–0018; Directorate Identifier 2010–SW–060–AD. (g) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2010–0096, dated May 25, 2010. You may view the EASA AD at https:// www.regulations.gov by searching for and locating it in Docket No. FAA–2013–0018. (h) Subject Joint Aircraft Service Component (JASC) Code: 6520, Tail Rotor Gearbox. Authority: 49 U.S.C. 106(g), 40113, 44701. mstockstill on DSK4VPTVN1PROD with RULES § 39.13 [Amended] (a) Applicability This AD applies to Model MBB–BK 117 C– 2 helicopters with a bevel gear, part number VerDate Mar<15>2010 18:29 Jul 15, 2013 Jkt 229001 (i) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 42411 (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Eurocopter Alert Service Bulletin MBB BK117 C–2–04A–005, Revision 2, dated April 28, 2010. (ii) Reserved. (3) For Eurocopter service information identified in this AD, contact American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at https://www.eurocopter.com/ techpub. (4) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. For information on the availability of this material at the FAA, call (817) 222–5110. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: https://www. archives.gov/federal-register/cfr/ibrlocations.html. Issued in Fort Worth, Texas, on June 13, 2013. Kim Smith, Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2013–14848 Filed 7–15–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0864; Directorate Identifier 2011–NM–023–AD; Amendment 39–17496; AD 2013–13–08] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 767 airplanes. That AD currently requires sealing certain fasteners and stiffeners in the fuel tank, changing certain wire bundle clamp configurations on the fuel tank walls, inspecting certain fasteners in the fuel tanks and determining the method of attachment of the vortex generators; and performing corrective actions if necessary. This new AD adds a general visual inspection for the presence of a polytetrafluoroethylene SUMMARY: E:\FR\FM\16JYR1.SGM 16JYR1 42412 Federal Register / Vol. 78, No. 136 / Tuesday, July 16, 2013 / Rules and Regulations mstockstill on DSK4VPTVN1PROD with RULES (TFE) sleeve at the clamp location on the rear spar, and installation of a TFE sleeve if necessary. This new AD also adds airplanes to the applicability. This AD was prompted by fuel system reviews conducted by the manufacturer, and the identification of another possible ignition source location. We are issuing this AD to prevent possible ignition sources in the auxiliary (center) fuel tank, main fuel tanks, and surge tanks caused by a wiring short or lightning strike, which could result in fuel tank explosions and consequent loss of the airplane. DATES: This AD is effective August 20, 2013. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of August 20, 2013. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of October 1, 2009 (76 FR 43621, August 27, 2009). ADDRESSES: 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. You may review copies of the 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. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document 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: Rebel Nichols, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6509; fax: 425–917–6590; email: rebel.nichols@faa.gov. SUPPLEMENTARY INFORMATION: VerDate Mar<15>2010 18:29 Jul 15, 2013 Jkt 229001 Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2009–18–02, Amendment 39–15998 (74 FR 43621, August 27, 2009). AD 2009–18–02 applied to the specified products. The NPRM published in the Federal Register on September 6, 2012 (77 FR 54850). The NPRM proposed to continue to require sealing certain fasteners and stiffeners in the fuel tank, changing certain wire bundle clamp configurations on the fuel tank walls, inspecting certain fasteners in the fuel tanks and determining the method of attachment of the vortex generators; and performing corrective action if necessary. The NPRM also proposed to require a general visual inspection for the presence of a polytetrafluoroethylene (TFE) sleeve at the clamp location on the rear spar, and installation of a TFE sleeve if necessary. The NPRM also proposed to add airplanes to the applicability. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal (77 FR 54850, September 6, 2012) and the FAA’s response to each comment. United Airlines stated that it has no comment for the NPRM (77 FR 54850, September 6, 2012). Request to Change Acronym Boeing requested that we change the NPRM (77 FR 54850, September 6, 2012) to correct an acronym from ‘‘TFE’’ to ‘‘PTFE.’’ Boeing stated that the proper acronym for polytetrafluoroethylene is ‘‘PTFE.’’ We disagree with changing the acronym in this AD. The service information required by this AD refers to polytetrafluoroethylene as ‘‘TFE’’ throughout; therefore, to reduce the potential for confusion, we have not changed the acronym ‘‘TFE’’ in this AD. Request for Credit Air New Zealand requested that we allow credit for prior incorporation of Boeing Service Bulletin 767–57A0102, Revision 3, dated December 2, 2010, for the requirements of paragraph (j) of the NPRM (77 FR 54850, September 6, 2012). We agree with the request, but provide the following clarification. Paragraph (j) of this AD specifies the compliance time for certain airplanes to accomplish the actions of paragraph (h) of this AD. We have changed the heading for paragraph (j) of this AD to PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 focus on the compliance time. Paragraph (h) of this AD specifies to do the actions in accordance with Boeing Service Bulletins 767–57A0102, Revision 01, dated November 27, 2007; or Revision 4, dated September 20, 2011. Since paragraph (l)(2) of this AD gives credit for Boeing Service Bulletin 767–57A0102, Revision 3, dated December 2, 2010, for accomplishing the actions in paragraph (h) of this AD, we have not changed the AD in this regard. STC Winglet Comment Aviation Partners Boeing and Air New Zealand stated that the installation of winglets per STC ST01920SE (https:// rgl.faa.gov/Regulatory_and_Guidance_ Library/rgstc.nsf/0/ 59027F43B9A7486E86257 B1D006591EE?OpenDocument &Highlight=st01920se) does not affect the accomplishment of the manufacturer’s service instructions. We have added paragraph (c)(2) to this AD to state that installation of STC ST01920SE does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01920SE is installed, a ‘‘change in product’’ alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. For all other AMOC requests, the operator must request approval for an AMOC in accordance with the procedures specified in paragraph (m) of this AD. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the change described previously and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (77 FR 54850, September 6, 2012) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (77 FR 54850, September 6, 2012). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Costs of Compliance We estimate that this AD affects 414 airplanes of U.S. registry. We estimate the following costs to comply with this AD: E:\FR\FM\16JYR1.SGM 16JYR1 42413 Federal Register / Vol. 78, No. 136 / Tuesday, July 16, 2013 / Rules and Regulations ESTIMATED COSTS Number of U.S.-registered airplanes Cost per product Labor cost Group 1—Seal ends of fasteners— Boeing Service Bulletin 767-57A0100 (retained actions from AD 2009–18–02, Amendment 39–15998 (74 FR 43621, August 27, 2009)). Group 2—Seal ends of fasteners— Boeing Service Bulletin 767-57A0100 (retained actions from AD 2009–18–02, Amendment 39–15998 (74 FR 43621, August 27, 2009)). Group 3—Inspection—Boeing Service Bulletin 767–57A0100 (retained actions from AD 2009–18– 02, Amendment 39–15998 (74 FR 43621, August 27, 2009)). Group 1—Change wire bundle clamp configurations, Boeing Service Bulletin 767-57A0102 (retained actions from AD 2009–18– 02, Amendment 39–15998 (74 FR 43621, August 27, 2009)). Group 2—Change wire bundle clamp configurations, Boeing Service Bulletin 767-57A0102 (retained actions from AD 2009–18– 02, Amendment 39–15998 (74 FR 43621, August 27, 2009)). Group 3—Change wire bundle clamp configuration and seal fasteners, Boeing Service Bulletin 767-57A0102 (retained actions from AD 2009–18–02, Amendment 39–15998 (74 FR 43621, August 27, 2009)). All airplanes—Inspection (new action). 6 work-hours × $85 per hour = $510 $0 $510 367 $187,170 114 work-hours × $85 per hour = $9,690. 0 9,690 37 358,530 1 work-hour × $85 per hour = $85 ... 0 85 9 765 250 work-hours × $85 per hour = $21,250. 1,632 22,882 376 8,603,632 874 work-hours × $85 per hour = $74,290. 1,304 75,594 37 2,796,978 26 work-hours × $85 per hour = $2,210. 338 2,548 1 2,548 1 work-hour × $85 per hour = $85 ... 0 85 414 35,190 We estimate the following costs to do any necessary repair that would be Parts cost Cost on U.S. operators Action required based on the results of the inspection. We have no way of determining the number of aircraft that might need this repair: ON-CONDITION COSTS Action Labor cost Seal ends of fasteners—Boeing Service Bulletin 767–57A0100 (retained actions from AD 2009–18–02, Amendment 39–15998 (74 FR 43621, August 27, 2009)). Installation of TFE sleeve—Boeing Service Bulletin 767-57A0102 ....... 6 work-hours × $85 per hour = $510. $0 Up to $510. 1 work-hour × $85 per hour = $85 $0 $85. mstockstill on DSK4VPTVN1PROD with RULES 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 VerDate Mar<15>2010 18:29 Jul 15, 2013 Jkt 229001 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. PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 Parts cost Cost per product 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: E:\FR\FM\16JYR1.SGM 16JYR1 42414 Federal Register / Vol. 78, No. 136 / Tuesday, July 16, 2013 / Rules and Regulations (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 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) 2009–18–02, Amendment 39–15998 (74 FR 43621, August 27, 2009), and adding the following new AD: ■ 2013–13–08 The Boeing Company: Amendment 39–17496; Docket No. FAA–2012–0864; Directorate Identifier 2011–NM–023–AD. (a) Effective Date This airworthiness directive (AD) is effective August 20, 2013. mstockstill on DSK4VPTVN1PROD with RULES (b) Affected ADs This AD supersedes AD 2009–18–02, Amendment 39–15998 (74 FR 43621, August 27, 2009). (c) Applicability (1) This AD applies to The Boeing Company Model 767–200, –300, –300F, and –400ER series airplanes; certificated in any category; as identified in Boeing Service Bulletin 767–57A0100, Revision 3, dated July 28, 2011; and Boeing Service Bulletin 767– 57A0102, Revision 4, dated September 20, 2011. (2) Installation of Supplemental Type Certificate (STC) ST01920SE (https:// rgl.faa.gov/Regulatory_and_Guidance_ Library/rgstc.nsf/0/59027F43B9A74 86E86257B1D006591EE?OpenDocument &Highlight=st01920se) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01920SE is installed, a ‘‘change in product’’ alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. VerDate Mar<15>2010 18:29 Jul 15, 2013 Jkt 229001 (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 57, Wings. (e) Unsafe Condition This AD was prompted by fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent possible ignition sources in the auxiliary (center) fuel tank, main fuel tanks, and surge tanks caused by a wiring short or lightning strike, which could result in fuel tank explosions and consequent loss of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Fastener Sealant Application This paragraph restates the requirements of paragraph (f) of AD 2009–18–02, Amendment 39–15998 (74 FR 43621, August 27, 2009), with revised service information. For airplanes identified in Boeing Service Bulletin 767–57A0100, Revision 01, dated June 19, 2008: Within 60 months after October 1, 2009 (the effective date of AD 2009–18–02), do the actions in paragraph (g)(1) or (g)(2) of this AD, as applicable, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767– 57A0100, Revision 01, dated June 19, 2008; or Boeing Service Bulletin 767–57A0100, Revision 3, dated July 28, 2011. As of the effective date of this AD, only Boeing Service Bulletin 767–57A0100, Revision 3, dated July 28, 2011, may be used to accomplish the requirements of this paragraph. (1) For Groups 1 and 2 airplanes: Seal the ends of the fasteners on the brackets that hold the vortex generators, and seal the ends of the fasteners on certain stiffeners on the rear spar, as applicable. (2) For Group 3 airplanes: Do a detailed inspection to determine the method of attachment of the vortex generators and, before further flight, do all applicable specified corrective actions. (h) Retained Wire Bundle Sleeve and Clamp Installation and Fastener Sealant Application This paragraph restates the requirements of paragraph (g) of AD 2009–18–02, Amendment 39–15998 (74 FR 43621, August 27, 2009), with revised service information. For airplanes identified in Boeing Service Bulletin 767–57A0102, Revision 01, dated November 27, 2007: Within 60 months after October 1, 2009 (the effective date of AD 2009–18–02), do the actions specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD, as applicable, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767–57A0102, Revision 01, dated November 27, 2007; or Boeing Service Bulletin 767–57A0102, Revision 4, dated September 20, 2011. As of the effective date of this AD, only Boeing Service Bulletin 767– 57A0102, Revision 4, dated September 20, 2011, may be used to accomplish the actions required by this paragraph. (1) Change the wire bundle clamp configurations at specified locations on the fuel tank walls. PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 (2) Seal the fasteners and certain stiffeners at specified locations in the fuel tank. (3) Do a detailed inspection of the sealant of the fasteners in the auxiliary tank center bay and rib 28 of the left and right main fuel tanks. Seal any unsealed fasteners before further flight. (i) Definition This paragraph restates the information specified in Note 1 of AD 2009–18–02, Amendment 39–15998 (74 FR 43621, August 27, 2009). For the purposes of this AD, a detailed inspection is: An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required. (j) Compliance Time for New Wire Bundle Sleeve and Clamp Installation and Fastener Sealant Application for Newly Added Airplanes For airplanes identified in Boeing Service Bulletin 767–57A0102, Revision 4, dated September 20, 2011, but not identified in paragraph (h) of this AD: Do the actions required by paragraph (h) of this AD within 60 months after the effective date of this AD. (k) New Inspection and Sleeve Installation For airplanes identified as Groups 1 and 2 in Boeing Service Bulletin 767–57A0102, Revision 4, dated September 20, 2011: Within 60 months after the effective date of this AD, do a general visual inspection of the clamp location on the rear spar to determine whether a polytetrafluoroethylene (TFE) sleeve is installed between the clamp and the plastic convoluted tube, in accordance with Work Package 13 of the Accomplishment Instructions of Boeing Service Bulletin 767– 57A0102, Revision 4, dated September 20, 2011. (1) If a TFE sleeve is not installed between the clamp and the plastic convoluted tubing, before further flight, install a TFE sleeve, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767– 57A0102, Revision 4, dated September 20, 2011. (2) If a TFE sleeve is installed between the clamp and the plastic convoluted tubing, no more work is required by this paragraph. (l) Credit for Previous Actions (1) This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Boeing Service Bulletin 767–57A0100, dated August 21, 2006, which is not incorporated by reference in this AD; Revision 1, dated June 19, 2008; or Revision 2, dated May 20, 2010, which is not incorporated by reference in this AD. (2) This paragraph provides credit for the actions required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using Boeing Service Bulletin 767–57A0102, Revision 1, dated November 27, 2007; Revision 2, dated January 7, 2010, which is not incorporated by E:\FR\FM\16JYR1.SGM 16JYR1 Federal Register / Vol. 78, No. 136 / Tuesday, July 16, 2013 / Rules and Regulations reference in this AD; or Revision 3, dated December 2, 2010, which is not incorporated by reference in this AD. (m) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle 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 the Related Information section of this AD. Information may be emailed to: 9-ANMSeattle-ACO–AMOC-Requests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) AMOCs approved previously in accordance with AD 2009–18–02, Amendment 39–15998 (74 FR 43621, August 27, 2009), are approved as AMOCs for the corresponding provisions of this AD. mstockstill on DSK4VPTVN1PROD with RULES (n) Related Information (1) For more information about this AD, contact Rebel Nichols, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6509; fax: 425–917–6590; email: rebel.nichols@faa.gov. (2) Service information identified in this AD that is not incorporated by reference may be obtained at the address specified in paragraph (o)(5) of this AD. 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. You may review copies of the 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. (o) 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 20, 2013. (i) Boeing Service Bulletin 767–57A0100, Revision 3, dated July 28, 2011. (ii) Boeing Service Bulletin 767–57A0102, Revision 4, dated September 20, 2011. (4) The following service information was approved for IBR on October 1, 2009, (74 FR 43621, August 27, 2009). (i) Boeing Service Bulletin 767–57A0100, Revision 01, dated June 19, 2008. (ii) Boeing Service Bulletin 767–57A0102, Revision 01, dated November 27, 2007. VerDate Mar<15>2010 18:29 Jul 15, 2013 Jkt 229001 (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 FAA, 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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on June 13, 2013. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–15526 Filed 7–15–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0302; Directorate Identifier 2013–NM–019–AD; Amendment 39–17503; AD 2013–13–15] RIN 2120–AA64 Airworthiness Directives; the Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding airworthiness directive (AD) 87–02–07, which applied to all The Boeing Company Model 737–100 and –200 series airplanes. AD 87–02–07 required replacement of certain underwing fuel tank access covers with stronger, fireresistant covers. This new AD also requires inspecting fuel tank access doors to determine that impact-resistant access doors are installed in the correct locations, inspecting application of stencils and index markers of impactresistant access doors, doing corrective actions if necessary, revising the maintenance program, and adding airplanes to the applicability. This AD was prompted by reports of standard access doors installed where impactresistant access doors are required, and reports of impact-resistant doors without stencils. We are issuing this AD to prevent foreign object penetration of the wing tank, which could lead to a fuel leak near ignition sources (engine, SUMMARY: PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 42415 hot brakes), consequently leading to a fuel-fed fire. DATES: This AD is effective August 20, 2013. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of August 20, 2013. ADDRESSES: 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. You may review copies of the referenced service information at the FAA, Transport Airplane Directate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document 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: Suzanne Lucier, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425– 917–6438; fax: 425–917–6590; email: suzanne.lucier@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 87–02–07, Amendment 39–5506 (Docket No. 86– NM–175–AD; 52 FR 518, January 7, 1987), (‘‘AD 87–02–07’’). AD 87–02–07 applied to the specified products. The NPRM published in the Federal Register on April 10, 2013 (78 FR 21279). The NPRM proposed to continue to require replacement of certain underwing fuel tank access covers with stronger, fire-resistant covers. The NPRM also proposed to require inspecting fuel tank access doors to determine that impact-resistant access doors are installed in the correct E:\FR\FM\16JYR1.SGM 16JYR1

Agencies

[Federal Register Volume 78, Number 136 (Tuesday, July 16, 2013)]
[Rules and Regulations]
[Pages 42411-42415]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-15526]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0864; Directorate Identifier 2011-NM-023-AD; 
Amendment 39-17496; AD 2013-13-08]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are superseding an existing airworthiness directive (AD) 
for certain The Boeing Company Model 767 airplanes. That AD currently 
requires sealing certain fasteners and stiffeners in the fuel tank, 
changing certain wire bundle clamp configurations on the fuel tank 
walls, inspecting certain fasteners in the fuel tanks and determining 
the method of attachment of the vortex generators; and performing 
corrective actions if necessary. This new AD adds a general visual 
inspection for the presence of a polytetrafluoroethylene

[[Page 42412]]

(TFE) sleeve at the clamp location on the rear spar, and installation 
of a TFE sleeve if necessary. This new AD also adds airplanes to the 
applicability. This AD was prompted by fuel system reviews conducted by 
the manufacturer, and the identification of another possible ignition 
source location. We are issuing this AD to prevent possible ignition 
sources in the auxiliary (center) fuel tank, main fuel tanks, and surge 
tanks caused by a wiring short or lightning strike, which could result 
in fuel tank explosions and consequent loss of the airplane.

DATES: This AD is effective August 20, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of August 20, 
2013.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of October 
1, 2009 (76 FR 43621, August 27, 2009).

ADDRESSES: 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. 
You may review copies of the 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (phone: 800-647-5527) is Document 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: Rebel Nichols, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification 
Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6509; fax: 425-917-6590; email: rebel.nichols@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2009-18-02, Amendment 39-15998 (74 FR 43621, 
August 27, 2009). AD 2009-18-02 applied to the specified products. The 
NPRM published in the Federal Register on September 6, 2012 (77 FR 
54850). The NPRM proposed to continue to require sealing certain 
fasteners and stiffeners in the fuel tank, changing certain wire bundle 
clamp configurations on the fuel tank walls, inspecting certain 
fasteners in the fuel tanks and determining the method of attachment of 
the vortex generators; and performing corrective action if necessary. 
The NPRM also proposed to require a general visual inspection for the 
presence of a polytetrafluoroethylene (TFE) sleeve at the clamp 
location on the rear spar, and installation of a TFE sleeve if 
necessary. The NPRM also proposed to add airplanes to the 
applicability.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
(77 FR 54850, September 6, 2012) and the FAA's response to each 
comment.
    United Airlines stated that it has no comment for the NPRM (77 FR 
54850, September 6, 2012).

Request to Change Acronym

    Boeing requested that we change the NPRM (77 FR 54850, September 6, 
2012) to correct an acronym from ``TFE'' to ``PTFE.'' Boeing stated 
that the proper acronym for polytetrafluoroethylene is ``PTFE.''
    We disagree with changing the acronym in this AD. The service 
information required by this AD refers to polytetrafluoroethylene as 
``TFE'' throughout; therefore, to reduce the potential for confusion, 
we have not changed the acronym ``TFE'' in this AD.

Request for Credit

    Air New Zealand requested that we allow credit for prior 
incorporation of Boeing Service Bulletin 767-57A0102, Revision 3, dated 
December 2, 2010, for the requirements of paragraph (j) of the NPRM (77 
FR 54850, September 6, 2012).
    We agree with the request, but provide the following clarification. 
Paragraph (j) of this AD specifies the compliance time for certain 
airplanes to accomplish the actions of paragraph (h) of this AD. We 
have changed the heading for paragraph (j) of this AD to focus on the 
compliance time. Paragraph (h) of this AD specifies to do the actions 
in accordance with Boeing Service Bulletins 767-57A0102, Revision 01, 
dated November 27, 2007; or Revision 4, dated September 20, 2011. Since 
paragraph (l)(2) of this AD gives credit for Boeing Service Bulletin 
767-57A0102, Revision 3, dated December 2, 2010, for accomplishing the 
actions in paragraph (h) of this AD, we have not changed the AD in this 
regard.

STC Winglet Comment

    Aviation Partners Boeing and Air New Zealand stated that the 
installation of winglets per STC ST01920SE (https://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/59027F43B9A7486E86257B1D006591EE?OpenDocument&Highlight=st01920se) does 
not affect the accomplishment of the manufacturer's service 
instructions.
    We have added paragraph (c)(2) to this AD to state that 
installation of STC ST01920SE does not affect the ability to accomplish 
the actions required by this AD. Therefore, for airplanes on which STC 
ST01920SE is installed, a ``change in product'' alternative method of 
compliance (AMOC) approval request is not necessary to comply with the 
requirements of 14 CFR 39.17. For all other AMOC requests, the operator 
must request approval for an AMOC in accordance with the procedures 
specified in paragraph (m) of this AD.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the change described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (77 FR 54850, September 6, 2012) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (77 FR 54850, September 6, 2012).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 414 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

[[Page 42413]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                  Number of U.S.-
            Action                 Labor cost       Parts cost       Cost per       registered     Cost on U.S.
                                                                      product        airplanes       operators
----------------------------------------------------------------------------------------------------------------
Group 1--Seal ends of           6 work-hours x                $0            $510             367        $187,170
 fasteners--Boeing Service       $85 per hour =
 Bulletin 767[dash]57A0100       $510.
 (retained actions from AD
 2009-18-02, Amendment 39-
 15998 (74 FR 43621, August
 27, 2009)).
Group 2--Seal ends of           114 work-hours x               0           9,690              37         358,530
 fasteners--Boeing Service       $85 per hour =
 Bulletin 767[dash]57A0100       $9,690.
 (retained actions from AD
 2009-18-02, Amendment 39-
 15998 (74 FR 43621, August
 27, 2009)).
Group 3--Inspection--Boeing     1 work-hour x                  0              85               9             765
 Service Bulletin 767-57A0100    $85 per hour =
 (retained actions from AD       $85.
 2009-18-02, Amendment 39-
 15998 (74 FR 43621, August
 27, 2009)).
Group 1--Change wire bundle     250 work-hours x           1,632          22,882             376       8,603,632
 clamp configurations, Boeing    $85 per hour =
 Service Bulletin                $21,250.
 767[dash]57A0102 (retained
 actions from AD 2009-18-02,
 Amendment 39-15998 (74 FR
 43621, August 27, 2009)).
Group 2--Change wire bundle     874 work-hours x           1,304          75,594              37       2,796,978
 clamp configurations, Boeing    $85 per hour =
 Service Bulletin                $74,290.
 767[dash]57A0102 (retained
 actions from AD 2009-18-02,
 Amendment 39-15998 (74 FR
 43621, August 27, 2009)).
Group 3--Change wire bundle     26 work-hours x              338           2,548               1           2,548
 clamp configuration and seal    $85 per hour =
 fasteners, Boeing Service       $2,210.
 Bulletin 767[dash]57A0102
 (retained actions from AD
 2009-18-02, Amendment 39-
 15998 (74 FR 43621, August
 27, 2009)).
All airplanes--Inspection (new  1 work-hour x                  0              85             414          35,190
 action).                        $85 per hour =
                                 $85.
----------------------------------------------------------------------------------------------------------------

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                Action                         Labor cost           Parts cost           Cost per product
----------------------------------------------------------------------------------------------------------------
Seal ends of fasteners--Boeing Service  6 work-hours x $85 per                $0  Up to $510.
 Bulletin 767-57A0100 (retained          hour = $510.
 actions from AD 2009-18-02, Amendment
 39-15998 (74 FR 43621, August 27,
 2009)).
Installation of TFE sleeve--Boeing      1 work-hour x $85 per                 $0  $85.
 Service Bulletin 767[dash]57A0102.      hour = $85.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

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

Regulatory Findings

    We 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:

[[Page 42414]]

    (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) 
2009-18-02, Amendment 39-15998 (74 FR 43621, August 27, 2009), and 
adding the following new AD:

2013-13-08 The Boeing Company: Amendment 39-17496; Docket No. FAA-
2012-0864; Directorate Identifier 2011-NM-023-AD.

(a) Effective Date

    This airworthiness directive (AD) is effective August 20, 2013.

(b) Affected ADs

    This AD supersedes AD 2009-18-02, Amendment 39-15998 (74 FR 
43621, August 27, 2009).

(c) Applicability

    (1) This AD applies to The Boeing Company Model 767-200, -300, -
300F, and -400ER series airplanes; certificated in any category; as 
identified in Boeing Service Bulletin 767-57A0100, Revision 3, dated 
July 28, 2011; and Boeing Service Bulletin 767-57A0102, Revision 4, 
dated September 20, 2011.
    (2) Installation of Supplemental Type Certificate (STC) 
ST01920SE (https://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/59027F43B9A7486E86257B1D006591EE?OpenDocument&Highlight=st01920se) 
does not affect the ability to accomplish the actions required by 
this AD. Therefore, for airplanes on which STC ST01920SE is 
installed, a ``change in product'' alternative method of compliance 
(AMOC) approval request is not necessary to comply with the 
requirements of 14 CFR 39.17.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD was prompted by fuel system reviews conducted by the 
manufacturer. We are issuing this AD to prevent possible ignition 
sources in the auxiliary (center) fuel tank, main fuel tanks, and 
surge tanks caused by a wiring short or lightning strike, which 
could result in fuel tank explosions and consequent loss of the 
airplane.

(f) Compliance

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

(g) Retained Fastener Sealant Application

    This paragraph restates the requirements of paragraph (f) of AD 
2009-18-02, Amendment 39-15998 (74 FR 43621, August 27, 2009), with 
revised service information. For airplanes identified in Boeing 
Service Bulletin 767-57A0100, Revision 01, dated June 19, 2008: 
Within 60 months after October 1, 2009 (the effective date of AD 
2009-18-02), do the actions in paragraph (g)(1) or (g)(2) of this 
AD, as applicable, in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin 767-57A0100, Revision 01, 
dated June 19, 2008; or Boeing Service Bulletin 767-57A0100, 
Revision 3, dated July 28, 2011. As of the effective date of this 
AD, only Boeing Service Bulletin 767-57A0100, Revision 3, dated July 
28, 2011, may be used to accomplish the requirements of this 
paragraph.
    (1) For Groups 1 and 2 airplanes: Seal the ends of the fasteners 
on the brackets that hold the vortex generators, and seal the ends 
of the fasteners on certain stiffeners on the rear spar, as 
applicable.
    (2) For Group 3 airplanes: Do a detailed inspection to determine 
the method of attachment of the vortex generators and, before 
further flight, do all applicable specified corrective actions.

(h) Retained Wire Bundle Sleeve and Clamp Installation and Fastener 
Sealant Application

    This paragraph restates the requirements of paragraph (g) of AD 
2009-18-02, Amendment 39-15998 (74 FR 43621, August 27, 2009), with 
revised service information. For airplanes identified in Boeing 
Service Bulletin 767-57A0102, Revision 01, dated November 27, 2007: 
Within 60 months after October 1, 2009 (the effective date of AD 
2009-18-02), do the actions specified in paragraphs (h)(1), (h)(2), 
and (h)(3) of this AD, as applicable, in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 767-57A0102, 
Revision 01, dated November 27, 2007; or Boeing Service Bulletin 
767-57A0102, Revision 4, dated September 20, 2011. As of the 
effective date of this AD, only Boeing Service Bulletin 767-57A0102, 
Revision 4, dated September 20, 2011, may be used to accomplish the 
actions required by this paragraph.
    (1) Change the wire bundle clamp configurations at specified 
locations on the fuel tank walls.
    (2) Seal the fasteners and certain stiffeners at specified 
locations in the fuel tank.
    (3) Do a detailed inspection of the sealant of the fasteners in 
the auxiliary tank center bay and rib 28 of the left and right main 
fuel tanks. Seal any unsealed fasteners before further flight.

(i) Definition

    This paragraph restates the information specified in Note 1 of 
AD 2009-18-02, Amendment 39-15998 (74 FR 43621, August 27, 2009). 
For the purposes of this AD, a detailed inspection is: An intensive 
examination of a specific item, installation, or assembly to detect 
damage, failure, or irregularity. Available lighting is normally 
supplemented with a direct source of good lighting at an intensity 
deemed appropriate. Inspection aids such as mirror, magnifying 
lenses, etc., may be necessary. Surface cleaning and elaborate 
procedures may be required.

(j) Compliance Time for New Wire Bundle Sleeve and Clamp Installation 
and Fastener Sealant Application for Newly Added Airplanes

    For airplanes identified in Boeing Service Bulletin 767-57A0102, 
Revision 4, dated September 20, 2011, but not identified in 
paragraph (h) of this AD: Do the actions required by paragraph (h) 
of this AD within 60 months after the effective date of this AD.

(k) New Inspection and Sleeve Installation

    For airplanes identified as Groups 1 and 2 in Boeing Service 
Bulletin 767-57A0102, Revision 4, dated September 20, 2011: Within 
60 months after the effective date of this AD, do a general visual 
inspection of the clamp location on the rear spar to determine 
whether a polytetrafluoroethylene (TFE) sleeve is installed between 
the clamp and the plastic convoluted tube, in accordance with Work 
Package 13 of the Accomplishment Instructions of Boeing Service 
Bulletin 767-57A0102, Revision 4, dated September 20, 2011.
    (1) If a TFE sleeve is not installed between the clamp and the 
plastic convoluted tubing, before further flight, install a TFE 
sleeve, in accordance with the Accomplishment Instructions of Boeing 
Service Bulletin 767-57A0102, Revision 4, dated September 20, 2011.
    (2) If a TFE sleeve is installed between the clamp and the 
plastic convoluted tubing, no more work is required by this 
paragraph.

(l) Credit for Previous Actions

    (1) This paragraph provides credit for the actions required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using Boeing Service Bulletin 767-57A0100, 
dated August 21, 2006, which is not incorporated by reference in 
this AD; Revision 1, dated June 19, 2008; or Revision 2, dated May 
20, 2010, which is not incorporated by reference in this AD.
    (2) This paragraph provides credit for the actions required by 
paragraph (h) of this AD, if those actions were performed before the 
effective date of this AD using Boeing Service Bulletin 767-57A0102, 
Revision 1, dated November 27, 2007; Revision 2, dated January 7, 
2010, which is not incorporated by

[[Page 42415]]

reference in this AD; or Revision 3, dated December 2, 2010, which 
is not incorporated by reference in this AD.

(m) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle 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 the Related Information 
section of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) AMOCs approved previously in accordance with AD 2009-18-02, 
Amendment 39-15998 (74 FR 43621, August 27, 2009), are approved as 
AMOCs for the corresponding provisions of this AD.

(n) Related Information

    (1) For more information about this AD, contact Rebel Nichols, 
Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle 
Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 
98057-3356; phone: 425-917-6509; fax: 425-917-6590; email: 
rebel.nichols@faa.gov.
    (2) Service information identified in this AD that is not 
incorporated by reference may be obtained at the address specified 
in paragraph (o)(5) of this AD. 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. You may review copies of the 
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.

(o) 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 20, 2013.
    (i) Boeing Service Bulletin 767-57A0100, Revision 3, dated July 
28, 2011.
    (ii) Boeing Service Bulletin 767-57A0102, Revision 4, dated 
September 20, 2011.
    (4) The following service information was approved for IBR on 
October 1, 2009, (74 FR 43621, August 27, 2009).
    (i) Boeing Service Bulletin 767-57A0100, Revision 01, dated June 
19, 2008.
    (ii) Boeing Service Bulletin 767-57A0102, Revision 01, dated 
November 27, 2007.
    (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 FAA, 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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on June 13, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-15526 Filed 7-15-13; 8:45 am]
BILLING CODE 4910-13-P