Airworthiness Directives; The Boeing Company Airplanes, 47084-47087 [2016-16906]

Download as PDF 47084 Federal Register / Vol. 81, No. 139 / Wednesday, July 20, 2016 / Proposed Rules variable CCT or CRI), the manufacturer may select any of these modes for testing; however, all measurements must be taken at the same selected mode. The manufacturer must indicate in the test report which mode was selected for testing and include detail such that another laboratory could operate the lamp in the same mode. 3.6. To measure initial lumen output, input power, input voltage, and input current use the test procedures in the table in this section. TABLE 3.1—REFERENCES TO INDUSTRY STANDARD TEST PROCEDURES Lamp type Referenced test procedure General service incandescent lamps ....................................................... Compact fluorescent lamps ...................................................................... Integrated LED lamps ............................................................................... Other incandescent lamps that are not reflector lamps ........................... Other incandescent lamps that are reflector lamps ................................. Other fluorescent lamps ........................................................................... OLED lamps ............................................................................................. Appendix R to Subpart B of 10 CFR part 430. Appendix W to Subpart B of 10 CFR part 430. Appendix BB to Subpart B of 10 CFR part 430. IES LM–45–15, sections 4–6, and section 7.1. IES LM–20–13, sections 4–6, and section 8. IES LM–9–09–DD, sections 4–6, and section 7.5. IES LM–79–08–DD, sections 1.3 (except 1.3[f]), 2.0, 3.0, 5.0, 7.0, 8.0, 9.1 and 9.2. IES LM–79–08–DD, sections 1.3 (except 1.3[f]), 2.0, 3.0, 5.0, 7.0, 8.0, 9.1 and 9.2. Non-integrated LED lamps ....................................................................... * (incorporated by reference, see § 430.3) 3.7. Determine initial lamp efficacy by dividing the measured initial lumen output (lumens) by the measured initial input power (watts). 3.8. Determine power factor by dividing the measured initial input power (watts) by the product of the measured input voltage (volts) and measured input current (amps). 4. Standby Mode Test Procedure 4.1. Measure standby mode power only for lamps that are capable of standby mode operation. 4.2. Connect the lamp to the manufacturerspecified wireless control network (if applicable) and configure the lamp in standby mode by sending a signal to the lamp instructing it to have zero light output. Lamp must remain connected to the network throughout testing. 4.3. Operate the lamp at the rated voltage throughout testing. For lamps with multiple rated voltages including 120 volts, operate the lamp at 120 volts. If a lamp is not rated for 120 volts, operate the lamp at the highest rated input voltage. 4.4. Stabilize the lamp prior to measurement as specified in section 5 of IEC 62301–DD (incorporated by reference; see § 430.3). 4.5. Measure the standby mode power in watts as specified in section 5 of IEC 62301– DD (incorporated by reference; see § 430.3). [FR Doc. 2016–17135 Filed 7–19–16; 8:45 am] BILLING CODE 6450–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration mstockstill on DSK3G9T082PROD with PROPOSALS 14 CFR Part 39 [Docket No. FAA–2016–8179; Directorate Identifier 2015–NM–201–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. AGENCY: VerDate Sep<11>2014 17:58 Jul 19, 2016 Jkt 238001 Notice of proposed rulemaking (NPRM). ACTION: We propose to supersede Airworthiness Directive (AD) 2011–26– 03, which applies to certain The Boeing Company Model 777–200, –200LR, –300, and –300ER series airplanes. AD 2011–26–03 currently requires installing Teflon sleeving under the clamps of certain wire bundles routed along the fuel tank boundary structure, and cap sealing certain penetrating fasteners of the main and center fuel tanks. AD 2011–26–03 resulted from fuel system reviews conducted by the manufacturer. Since we issued AD 2011–26–03, we have received a report indicating that additional airplanes are affected by the identified unsafe condition. This proposed AD would add airplanes to the applicability. This AD would also add, for certain airplanes, detailed inspections of certain wire bundle clamps, certain Teflon sleeves, and certain fasteners; corrective actions if necessary; and installation of Teflon sleeves under certain wire bundle clamps. We are proposing this AD to prevent electrical arcing on the fuel tank boundary structure or inside the fuel tanks, which could result in a fire or explosion. DATES: We must receive comments on this proposed AD by September 6, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. SUMMARY: PO 00000 Frm 00036 Fmt 4702 Sfmt 4702 • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, 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 view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 8179. 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– 8179; 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Suzanne Lucier, Aerospace Engineer, Propulsion Branch, ANM 140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6438; fax: 425–917–6590; email: suzanne.lucier@faa.gov. E:\FR\FM\20JYP1.SGM 20JYP1 Federal Register / Vol. 81, No. 139 / Wednesday, July 20, 2016 / Proposed Rules SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2016–8179; Directorate Identifier 2015–NM–201–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. mstockstill on DSK3G9T082PROD with PROPOSALS Discussion The FAA has examined the underlying safety issues involved in fuel tank explosions on several large transport airplanes, including the adequacy of existing regulations, the service history of airplanes subject to those regulations, and existing maintenance practices for fuel tank systems. As a result of those findings, we issued a regulation titled ‘‘Transport Airplane Fuel Tank System Design Review, Flammability Reduction and Maintenance and Inspection Requirements’’ (66 FR 23086, May 7, 2001). In addition to new airworthiness standards for transport airplanes and new maintenance requirements, this rule included Special Federal Aviation Regulation No. 88 (‘‘SFAR 88’’), Amendment 21–78. Subsequently, SFAR 88 was amended by: Amendment 21–82 (67 FR 57490, September 10, 2002; corrected at 67 FR 70809, November 26, 2002) and Amendment 21–83 (67 FR 72830, December 9, 2002; corrected at 68 FR 37735, June 25, 2003, to change ‘‘21–82’’ to ‘‘21–83’’). Among other actions, SFAR 88 requires certain type design (i.e., type certificate (TC) and supplemental type certificate (STC)) holders to substantiate that their fuel tank systems can prevent ignition sources in the fuel tanks. This requirement applies to type design holders for large turbine-powered transport airplanes and for subsequent modifications to those airplanes. It requires them to perform design reviews and to develop design changes and maintenance procedures if their designs VerDate Sep<11>2014 17:58 Jul 19, 2016 Jkt 238001 do not meet the new fuel tank safety standards. As explained in the preamble to the rule, we intended to adopt airworthiness directives to mandate any changes found necessary to address unsafe conditions identified as a result of these reviews. In evaluating these design reviews, we have established four criteria intended to define the unsafe conditions associated with fuel tank systems that require corrective actions. The percentage of operating time during which fuel tanks are exposed to flammable conditions is one of these criteria. The other three criteria address the failure types under evaluation: Single failures, combination of failures, and unacceptable (failure) experience. For all three failure criteria, the evaluations included consideration of previous actions taken that may mitigate the need for further action. We have determined that the actions identified in this proposed AD are necessary to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. On December 5, 2011, we issued AD 2011–26–03, Amendment 39–16893 (76 FR 78138, December 16, 2011) (‘‘AD 2011–26–03’’), for certain The Boeing Company Model 777–200, –200LR, –300, and –300ER series airplanes. AD 2011–26–03 requires installing Teflon sleeving under the clamps of certain wire bundles routed along the fuel tank boundary structure, and cap sealing certain penetrating fasteners of the main and center fuel tanks. AD 2011–26–03 resulted from fuel system reviews conducted by the manufacturer. We issued AD 2011–26–03 to prevent electrical arcing on the fuel tank boundary structure or inside the fuel tanks, which could result in a fire or explosion. Actions Since AD 2011–26–03 Was Issued Since we issued AD 2011–26–03, we have received a report indicating that additional airplanes are affected by the identified unsafe condition. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Service Bulletin 777–57A0050, Revision 4, dated September 28, 2015. The service information describes procedures for installing Teflon sleeving under the clamps of certain wire bundles routed along the fuel tank boundary structure, PO 00000 Frm 00037 Fmt 4702 Sfmt 4702 47085 and cap sealing certain penetrating fasteners of the main and center fuel tanks; as well as detailed inspections of certain wire bundle clamps, certain Teflon sleeves, and certain fasteners; corrective actions if necessary; and installation of Teflon sleeves under certain wire bundle clamps. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would retain all of the requirements of AD 2011–26–03. This proposed AD would also revise the applicability by adding Boeing Model 777–200LR and 777F series airplanes. This proposed AD would also require accomplishing the actions specified in the service information described previously, except as described in ‘‘Differences Between this Proposed AD and the Service Information’’. For information on the procedures and compliance times, see this service information at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 8179. The phrase ‘‘corrective actions’’ is used in this proposed AD. ‘‘Corrective actions’’ correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Differences Between This Proposed AD and the Service Information Boeing has issued Alternative Method of Compliance (AMOC) Notice 777– 57A0050 AMOC 02, dated February 15, 2016, to provide the correct group applicability for ‘‘WORK PACKAGE 21: More Work: Rear Spar Wire Bundle Teflon sleeve Installation,’’ Figure 3, and Figure 100 of Boeing Service Bulletin 777–57A0050, Revision 4, dated September 28, 2015. We have included these changes in paragraphs (k)(1), (k)(2), and (k)(3) of this AD. Costs of Compliance We estimate that this proposed AD affects 182 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: E:\FR\FM\20JYP1.SGM 20JYP1 47086 Federal Register / Vol. 81, No. 139 / Wednesday, July 20, 2016 / Proposed Rules ESTIMATED COSTS Action Labor cost Parts cost Install Teflon sleeving and cap sealing Up to 358 work-hours × $85 per hour = (retained actions from AD 2011–26–03). $30,430. Detailed inspections and installation of Up to 53 work-hours × $85 per hour = Teflon sleeves (new proposed actions). $4,505. Cost per product Cost on U.S. operators $2,241 Up to $32,671 .. Up to $5,946,122. 10 Up to $4,505 ..... Up to $819,910. 1 We have received no definitive data that would enable us to provide parts cost estimates for the installation of Teflon sleeves (new proposed action) specified in this proposed AD. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. Authority for This Rulemaking mstockstill on DSK3G9T082PROD with PROPOSALS Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 the proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. 17:58 Jul 19, 2016 Jkt 238001 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment 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. VerDate Sep<11>2014 List of Subjects in 14 CFR Part 39 Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2011–26–03, Amendment 39–16893 (76 FR 78138, December 16, 2011), and adding the following new AD: ■ The Boeing Company: Docket No. FAA– 2016–8179; Directorate Identifier 2015– NM–201–AD. (a) Comments Due Date The FAA must receive comments on this AD action by September 6, 2016. (b) Affected ADs This AD replaces AD 2011–26–03, Amendment 39–16893 (76 FR 78138, December 16, 2011) (‘‘AD 2011–26–03’’). (c) Applicability This AD applies to The Boeing Company airplanes, certificated in any category, as identified in the applicable service information specified in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD. (1) For The Boeing Company Model 777– 200, –200LR, –300, –300ER, and 777F airplanes: Boeing Service Bulletin 777– 57A0050, Revision 4, dated September 28, 2015. (2) For The Boeing Company Model 777– 200 and –300 airplanes: Boeing Alert Service Bulletin 777–57A0051, dated May 15, 2006. (3) For The Boeing Company Model 777– 200, –300, and –300ER airplanes: Boeing Alert Service Bulletin 777–57A0057, Revision 1, dated August 2, 2007. (4) For The Boeing Company Model 777– 200, –200LR, –300, and –300ER airplanes: Boeing Alert Service Bulletin 777–57A0059, dated October 30, 2008. PO 00000 Frm 00038 Fmt 4702 Sfmt 4702 (e) Unsafe Condition This AD was prompted by fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent electrical arcing on the fuel tank boundary structure or inside the main and center fuel tanks, which could result in a fire or explosion. (f) Compliance Comply with this AD within the compliance times specified, unless already done. PART 39—AIRWORTHINESS DIRECTIVES § 39.13 (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (g) Retained Corrective Actions (Installing Teflon Sleeving, Cap Sealing, One-Time Inspection), With Revised Service Information This paragraph restates the requirements of paragraph (g) of AD 2011–26–03, with revised service information. Within 60 months after January 20, 2011 (the effective date of AD 2010–24–12, Amendment 39– 16531 (75 FR 78588, December 16, 2010) (‘‘AD 2010–24–12’’)), do the applicable actions specified in paragraph (g)(1), (g)(2), (g)(3), or (g)(4) of this AD, except as required by paragraph (k)(2) of this AD. (1) For airplanes identified in Boeing Service Bulletin 777–57A0050, Revision 2, dated May 14, 2009: Install Teflon sleeving under the clamps of certain wire bundles routed along the fuel tank boundary structure, and cap seal certain penetrating fasteners of the fuel tanks, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777–57A0050, Revision 2, dated May 14, 2009; or Revision 4, dated September 28, 2015. As of the effective date of this AD, only use Boeing Service Bulletin 777–57A0050, Revision 4, dated September 28, 2015, for accomplishing the actions required by this paragraph. (2) For airplanes identified in Boeing Alert Service Bulletin 777–57A0051, dated May 15, 2006: Cap seal certain penetrating fasteners of the fuel tanks, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777–57A0051, dated May 15, 2006. (3) For airplanes identified in Boeing Alert Service Bulletin 777–57A0057, Revision 1, dated August 2, 2007: Do a general visual inspection to determine if certain fasteners are cap sealed, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777–57A0057, Revision 1, dated August 2, 2007. Do all applicable corrective actions before further flight. E:\FR\FM\20JYP1.SGM 20JYP1 Federal Register / Vol. 81, No. 139 / Wednesday, July 20, 2016 / Proposed Rules (4) For Model 777–200, –300, and –300ER airplanes identified in Boeing Alert Service Bulletin 777–57A0059, dated October 30, 2008: Cap seal the fasteners in the center fuel tanks that were not sealed during production, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777–57A0059, dated October 30, 2008. mstockstill on DSK3G9T082PROD with PROPOSALS (h) Retained Cap Sealing the Fasteners, With No Changes This paragraph restates the requirements of paragraph (i) of AD 2011–26–03, with no changes. For Model 777–200LR airplanes identified in Boeing Alert Service Bulletin 777–57A0059, dated October 30, 2008: Within 60 months after January 3, 2012 (the effective date of AD 2011–26–03), cap seal the fasteners in the center fuel tanks that were not sealed during production, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777–57A0059, dated October 30, 2008. (i) New Detailed Inspection and Corrective Actions For Group 1, Configurations 2 through 4 airplanes; Groups 2 through 4, Configurations 3 through 5 airplanes; Groups 5 through 43, Configuration 1 airplanes; and Groups 44 and 45 airplanes; as identified in Boeing Service Bulletin 777–57A0050, Revision 4, dated September 28, 2015: Within 60 months after the effective date of this AD, do the applicable actions specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD, except as required by paragraph (k)(2) of this AD. (1) For Group 1, Configurations 2 through 4 airplanes; Groups 2 through 4, Configurations 3 through 5 airplanes; Groups 5 through 43, Configuration 1 airplanes; and Groups 44 and 45 airplanes; as identified in Boeing Service Bulletin 777–57A0050, Revision 4, dated September 28, 2015: Do a detailed inspection for installation of Teflon sleeves on certain wire bundle clamps, as applicable; a detailed inspection to determine the type of wire bundle clamp; and do all applicable corrective actions; in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777– 57A0050, Revision 4, dated September 28, 2015. Do all applicable corrective actions before further flight. (2) For Group 1, Configurations 2 through 4 airplanes; and Groups 2 through 4, Configurations 3 through 5 airplanes; as identified in Boeing Service Bulletin 777– 57A0050, Revision 4, dated September 28, 2015: Do a detailed inspection for correct installation of certain Teflon sleeves, as applicable; and do all applicable corrective actions; in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777–57A0050, Revision 4, dated September 28, 2015. Do all applicable corrective actions before further flight. (3) For Group 1, Configurations 2 through 4 airplanes; and Groups 2 through 4, Configurations 3 through 5 airplanes; as identified in Boeing Service Bulletin 777– 57A0050, Revision 4, dated September 28, 2015: Do a detailed inspection for cap sealing of certain fasteners, as applicable; and do all applicable corrective actions; in accordance with the Accomplishment Instructions of VerDate Sep<11>2014 18:35 Jul 19, 2016 Jkt 238001 Boeing Service Bulletin 777–57A0050, Revision 4, dated September 28, 2015. Do all applicable corrective actions before further flight. (j) New Installation of Teflon Sleeves For Group 1, Configurations 2 through 5 airplanes; Groups 2 through 4, Configurations 3 through 6 airplanes; and Groups 5 through 43, Configuration 2 airplanes; as identified in Boeing Service Bulletin 777–57A0050, Revision 4, dated September 28, 2015: Within 60 months after the effective date of this AD, install Teflon sleeves under certain wire bundle clamps, as applicable, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777– 57A0050, Revision 4, dated September 28, 2015, except as required by paragraphs (k)(1), (k)(2), and (k)(3) of this AD. (k) Exception to the Service Information (1) Where ‘‘WORK PACKAGE 21: More Work: Rear Spar Wire Bundle Teflon sleeve Installation’’ of Boeing Service Bulletin 777– 57A0050, Revision 4, dated September 28, 2015, specifies ‘‘Groups 5 through 43, Configuration 2,’’ for this AD, ‘‘WORK PACKAGE 21: More Work: Rear Spar Wire Bundle Teflon sleeve Installation’’ of Boeing Service Bulletin 777–57A0050, Revision 4, dated September 28, 2015, applies to Groups 5 through 43. (2) Where Figure 3 of Boeing Service Bulletin 777–57A0050, Revision 4, dated September 28, 2015, specifies ‘‘Groups 1 through 7, and 9 through 43,’’ for this AD, Figure 3 of Boeing Service Bulletin 777– 57A0050, Revision 4, dated September 28, 2015, applies to Groups 1 through 43. (3) Where Figure 100 of Boeing Service Bulletin 777–57A0050, Revision 4, dated September 28, 2015, specifies ‘‘Groups 5 through 43, Configuration 2,’’ for this AD, Figure 100 of Boeing Service Bulletin 777– 57A0050, Revision 4, dated September 28, 2015, applies to Groups 5 through 43. (l) Credit for Previous Actions (1) This paragraph provides credit for the actions specified in paragraph (g)(1) of this AD, if those actions were performed before January 20, 2011 (the effective date of AD 2010–24–12), using Boeing Alert Service Bulletin 777–57A0050, dated January 26, 2006; or Revision 1, dated August 2, 2007; provided that the applicable additional work specified in Boeing Service Bulletin 777– 57A0050, Revision 2, dated May 14, 2009, is done within the compliance time specified in paragraph (g) of this AD. The additional work must be done in accordance with Boeing Service Bulletin 777–57A0050, Revision 2, dated May 14, 2009. (2) This paragraph provides credit for the actions specified in paragraph (g)(3) of this AD, if those actions were performed before January 20, 2011 (the effective date of AD 2010–24–12), using Boeing Alert Service Bulletin 777–57A0057, dated August 7, 2006. (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 PO 00000 Frm 00039 Fmt 4702 Sfmt 4702 47087 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (n)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, 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 previously for AD 2011–26–03 are approved as AMOCs for the corresponding provisions of this AD. (n) Related Information (1) For more information about this AD, contact Suzanne Lucier, Aerospace Engineer, Propulsion Branch, ANM 140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6438; fax: 425–917–6590; email: suzanne.lucier@faa.gov. (2) 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 view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on July 8, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–16906 Filed 7–19–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF VETERANS AFFAIRS 38 CFR Part 14 RIN 2900–AP51 Recognition of Tribal Organizations for Representation of VA Claimants Department of Veterans Affairs. Proposed rule. AGENCY: ACTION: The Department of Veterans Affairs (VA) is proposing to amend its regulations concerning recognition of SUMMARY: E:\FR\FM\20JYP1.SGM 20JYP1

Agencies

[Federal Register Volume 81, Number 139 (Wednesday, July 20, 2016)]
[Proposed Rules]
[Pages 47084-47087]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-16906]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-8179; Directorate Identifier 2015-NM-201-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2011-26-
03, which applies to certain The Boeing Company Model 777-200, -200LR, 
-300, and -300ER series airplanes. AD 2011-26-03 currently requires 
installing Teflon sleeving under the clamps of certain wire bundles 
routed along the fuel tank boundary structure, and cap sealing certain 
penetrating fasteners of the main and center fuel tanks. AD 2011-26-03 
resulted from fuel system reviews conducted by the manufacturer. Since 
we issued AD 2011-26-03, we have received a report indicating that 
additional airplanes are affected by the identified unsafe condition. 
This proposed AD would add airplanes to the applicability. This AD 
would also add, for certain airplanes, detailed inspections of certain 
wire bundle clamps, certain Teflon sleeves, and certain fasteners; 
corrective actions if necessary; and installation of Teflon sleeves 
under certain wire bundle clamps. We are proposing this AD to prevent 
electrical arcing on the fuel tank boundary structure or inside the 
fuel tanks, which could result in a fire or explosion.

DATES: We must receive comments on this proposed AD by September 6, 
2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, 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 view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at the 
FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
8179.

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-
8179; 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 proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Suzanne Lucier, Aerospace Engineer, 
Propulsion Branch, ANM 140S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6438; fax: 425-917-6590; email: suzanne.lucier@faa.gov.

[[Page 47085]]


SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-8179; 
Directorate Identifier 2015-NM-201-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The FAA has examined the underlying safety issues involved in fuel 
tank explosions on several large transport airplanes, including the 
adequacy of existing regulations, the service history of airplanes 
subject to those regulations, and existing maintenance practices for 
fuel tank systems. As a result of those findings, we issued a 
regulation titled ``Transport Airplane Fuel Tank System Design Review, 
Flammability Reduction and Maintenance and Inspection Requirements'' 
(66 FR 23086, May 7, 2001). In addition to new airworthiness standards 
for transport airplanes and new maintenance requirements, this rule 
included Special Federal Aviation Regulation No. 88 (``SFAR 88''), 
Amendment 21-78. Subsequently, SFAR 88 was amended by: Amendment 21-82 
(67 FR 57490, September 10, 2002; corrected at 67 FR 70809, November 
26, 2002) and Amendment 21-83 (67 FR 72830, December 9, 2002; corrected 
at 68 FR 37735, June 25, 2003, to change ``21-82'' to ``21-83'').
    Among other actions, SFAR 88 requires certain type design (i.e., 
type certificate (TC) and supplemental type certificate (STC)) holders 
to substantiate that their fuel tank systems can prevent ignition 
sources in the fuel tanks. This requirement applies to type design 
holders for large turbine-powered transport airplanes and for 
subsequent modifications to those airplanes. It requires them to 
perform design reviews and to develop design changes and maintenance 
procedures if their designs do not meet the new fuel tank safety 
standards. As explained in the preamble to the rule, we intended to 
adopt airworthiness directives to mandate any changes found necessary 
to address unsafe conditions identified as a result of these reviews.
    In evaluating these design reviews, we have established four 
criteria intended to define the unsafe conditions associated with fuel 
tank systems that require corrective actions. The percentage of 
operating time during which fuel tanks are exposed to flammable 
conditions is one of these criteria. The other three criteria address 
the failure types under evaluation: Single failures, combination of 
failures, and unacceptable (failure) experience. For all three failure 
criteria, the evaluations included consideration of previous actions 
taken that may mitigate the need for further action.
    We have determined that the actions identified in this proposed AD 
are necessary to reduce the potential of ignition sources inside fuel 
tanks, which, in combination with flammable fuel vapors, could result 
in fuel tank explosions and consequent loss of the airplane.
    On December 5, 2011, we issued AD 2011-26-03, Amendment 39-16893 
(76 FR 78138, December 16, 2011) (``AD 2011-26-03''), for certain The 
Boeing Company Model 777-200, -200LR, -300, and -300ER series 
airplanes. AD 2011-26-03 requires installing Teflon sleeving under the 
clamps of certain wire bundles routed along the fuel tank boundary 
structure, and cap sealing certain penetrating fasteners of the main 
and center fuel tanks. AD 2011-26-03 resulted from fuel system reviews 
conducted by the manufacturer. We issued AD 2011-26-03 to prevent 
electrical arcing on the fuel tank boundary structure or inside the 
fuel tanks, which could result in a fire or explosion.

Actions Since AD 2011-26-03 Was Issued

    Since we issued AD 2011-26-03, we have received a report indicating 
that additional airplanes are affected by the identified unsafe 
condition.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Service Bulletin 777-57A0050, Revision 4, dated 
September 28, 2015. The service information describes procedures for 
installing Teflon sleeving under the clamps of certain wire bundles 
routed along the fuel tank boundary structure, and cap sealing certain 
penetrating fasteners of the main and center fuel tanks; as well as 
detailed inspections of certain wire bundle clamps, certain Teflon 
sleeves, and certain fasteners; corrective actions if necessary; and 
installation of Teflon sleeves under certain wire bundle clamps. This 
service information is reasonably available because the interested 
parties have access to it through their normal course of business or by 
the means identified in the ADDRESSES section.

FAA's Determination

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

Proposed AD Requirements

    This proposed AD would retain all of the requirements of AD 2011-
26-03. This proposed AD would also revise the applicability by adding 
Boeing Model 777-200LR and 777F series airplanes. This proposed AD 
would also require accomplishing the actions specified in the service 
information described previously, except as described in ``Differences 
Between this Proposed AD and the Service Information''. For information 
on the procedures and compliance times, see this service information at 
http://www.regulations.gov by searching for and locating Docket No. 
FAA-2016-8179.
    The phrase ``corrective actions'' is used in this proposed AD. 
``Corrective actions'' correct or address any condition found. 
Corrective actions in an AD could include, for example, repairs.

Differences Between This Proposed AD and the Service Information

    Boeing has issued Alternative Method of Compliance (AMOC) Notice 
777-57A0050 AMOC 02, dated February 15, 2016, to provide the correct 
group applicability for ``WORK PACKAGE 21: More Work: Rear Spar Wire 
Bundle Teflon sleeve Installation,'' Figure 3, and Figure 100 of Boeing 
Service Bulletin 777-57A0050, Revision 4, dated September 28, 2015. We 
have included these changes in paragraphs (k)(1), (k)(2), and (k)(3) of 
this AD.

Costs of Compliance

    We estimate that this proposed AD affects 182 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

[[Page 47086]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
            Action                Labor cost       Parts cost       Cost per product     Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Install Teflon sleeving and    Up to 358 work-           $2,241  Up to $32,671........  Up to $5,946,122.
 cap sealing (retained          hours x $85 per
 actions from AD 2011-26-03).   hour = $30,430.
Detailed inspections and       Up to 53 work-             \1\ 0  Up to $4,505.........  Up to $819,910.
 installation of Teflon         hours x $85 per
 sleeves (new proposed          hour = $4,505.
 actions).
----------------------------------------------------------------------------------------------------------------
\1\ We have received no definitive data that would enable us to provide parts cost estimates for the
  installation of Teflon sleeves (new proposed action) specified in this proposed AD.

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

Authority for This Rulemaking

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

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 the proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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) 
2011-26-03, Amendment 39-16893 (76 FR 78138, December 16, 2011), and 
adding the following new AD:

The Boeing Company: Docket No. FAA-2016-8179; Directorate Identifier 
2015-NM-201-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by September 6, 
2016.

(b) Affected ADs

    This AD replaces AD 2011-26-03, Amendment 39-16893 (76 FR 78138, 
December 16, 2011) (``AD 2011-26-03'').

(c) Applicability

    This AD applies to The Boeing Company airplanes, certificated in 
any category, as identified in the applicable service information 
specified in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this 
AD.
    (1) For The Boeing Company Model 777-200, -200LR, -300, -300ER, 
and 777F airplanes: Boeing Service Bulletin 777-57A0050, Revision 4, 
dated September 28, 2015.
    (2) For The Boeing Company Model 777-200 and -300 airplanes: 
Boeing Alert Service Bulletin 777-57A0051, dated May 15, 2006.
    (3) For The Boeing Company Model 777-200, -300, and -300ER 
airplanes: Boeing Alert Service Bulletin 777-57A0057, Revision 1, 
dated August 2, 2007.
    (4) For The Boeing Company Model 777-200, -200LR, -300, and -
300ER airplanes: Boeing Alert Service Bulletin 777-57A0059, dated 
October 30, 2008.

(d) Subject

    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 electrical arcing on 
the fuel tank boundary structure or inside the main and center fuel 
tanks, which could result in a fire or explosion.

(f) Compliance

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

(g) Retained Corrective Actions (Installing Teflon Sleeving, Cap 
Sealing, One-Time Inspection), With Revised Service Information

    This paragraph restates the requirements of paragraph (g) of AD 
2011-26-03, with revised service information. Within 60 months after 
January 20, 2011 (the effective date of AD 2010-24-12, Amendment 39-
16531 (75 FR 78588, December 16, 2010) (``AD 2010-24-12'')), do the 
applicable actions specified in paragraph (g)(1), (g)(2), (g)(3), or 
(g)(4) of this AD, except as required by paragraph (k)(2) of this 
AD.
    (1) For airplanes identified in Boeing Service Bulletin 777-
57A0050, Revision 2, dated May 14, 2009: Install Teflon sleeving 
under the clamps of certain wire bundles routed along the fuel tank 
boundary structure, and cap seal certain penetrating fasteners of 
the fuel tanks, in accordance with the Accomplishment Instructions 
of Boeing Service Bulletin 777-57A0050, Revision 2, dated May 14, 
2009; or Revision 4, dated September 28, 2015. As of the effective 
date of this AD, only use Boeing Service Bulletin 777-57A0050, 
Revision 4, dated September 28, 2015, for accomplishing the actions 
required by this paragraph.
    (2) For airplanes identified in Boeing Alert Service Bulletin 
777-57A0051, dated May 15, 2006: Cap seal certain penetrating 
fasteners of the fuel tanks, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 777-57A0051, dated May 
15, 2006.
    (3) For airplanes identified in Boeing Alert Service Bulletin 
777-57A0057, Revision 1, dated August 2, 2007: Do a general visual 
inspection to determine if certain fasteners are cap sealed, and do 
all applicable corrective actions, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 777-
57A0057, Revision 1, dated August 2, 2007. Do all applicable 
corrective actions before further flight.

[[Page 47087]]

    (4) For Model 777-200, -300, and -300ER airplanes identified in 
Boeing Alert Service Bulletin 777-57A0059, dated October 30, 2008: 
Cap seal the fasteners in the center fuel tanks that were not sealed 
during production, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 777-57A0059, dated 
October 30, 2008.

(h) Retained Cap Sealing the Fasteners, With No Changes

    This paragraph restates the requirements of paragraph (i) of AD 
2011-26-03, with no changes. For Model 777-200LR airplanes 
identified in Boeing Alert Service Bulletin 777-57A0059, dated 
October 30, 2008: Within 60 months after January 3, 2012 (the 
effective date of AD 2011-26-03), cap seal the fasteners in the 
center fuel tanks that were not sealed during production, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 777-57A0059, dated October 30, 2008.

(i) New Detailed Inspection and Corrective Actions

    For Group 1, Configurations 2 through 4 airplanes; Groups 2 
through 4, Configurations 3 through 5 airplanes; Groups 5 through 
43, Configuration 1 airplanes; and Groups 44 and 45 airplanes; as 
identified in Boeing Service Bulletin 777-57A0050, Revision 4, dated 
September 28, 2015: Within 60 months after the effective date of 
this AD, do the applicable actions specified in paragraphs (i)(1), 
(i)(2), and (i)(3) of this AD, except as required by paragraph 
(k)(2) of this AD.
    (1) For Group 1, Configurations 2 through 4 airplanes; Groups 2 
through 4, Configurations 3 through 5 airplanes; Groups 5 through 
43, Configuration 1 airplanes; and Groups 44 and 45 airplanes; as 
identified in Boeing Service Bulletin 777-57A0050, Revision 4, dated 
September 28, 2015: Do a detailed inspection for installation of 
Teflon sleeves on certain wire bundle clamps, as applicable; a 
detailed inspection to determine the type of wire bundle clamp; and 
do all applicable corrective actions; in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 777-57A0050, 
Revision 4, dated September 28, 2015. Do all applicable corrective 
actions before further flight.
    (2) For Group 1, Configurations 2 through 4 airplanes; and 
Groups 2 through 4, Configurations 3 through 5 airplanes; as 
identified in Boeing Service Bulletin 777-57A0050, Revision 4, dated 
September 28, 2015: Do a detailed inspection for correct 
installation of certain Teflon sleeves, as applicable; and do all 
applicable corrective actions; in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin 777-57A0050, Revision 4, 
dated September 28, 2015. Do all applicable corrective actions 
before further flight.
    (3) For Group 1, Configurations 2 through 4 airplanes; and 
Groups 2 through 4, Configurations 3 through 5 airplanes; as 
identified in Boeing Service Bulletin 777-57A0050, Revision 4, dated 
September 28, 2015: Do a detailed inspection for cap sealing of 
certain fasteners, as applicable; and do all applicable corrective 
actions; in accordance with the Accomplishment Instructions of 
Boeing Service Bulletin 777-57A0050, Revision 4, dated September 28, 
2015. Do all applicable corrective actions before further flight.

(j) New Installation of Teflon Sleeves

    For Group 1, Configurations 2 through 5 airplanes; Groups 2 
through 4, Configurations 3 through 6 airplanes; and Groups 5 
through 43, Configuration 2 airplanes; as identified in Boeing 
Service Bulletin 777-57A0050, Revision 4, dated September 28, 2015: 
Within 60 months after the effective date of this AD, install Teflon 
sleeves under certain wire bundle clamps, as applicable, in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 777-57A0050, Revision 4, dated September 28, 2015, except 
as required by paragraphs (k)(1), (k)(2), and (k)(3) of this AD.

(k) Exception to the Service Information

    (1) Where ``WORK PACKAGE 21: More Work: Rear Spar Wire Bundle 
Teflon sleeve Installation'' of Boeing Service Bulletin 777-57A0050, 
Revision 4, dated September 28, 2015, specifies ``Groups 5 through 
43, Configuration 2,'' for this AD, ``WORK PACKAGE 21: More Work: 
Rear Spar Wire Bundle Teflon sleeve Installation'' of Boeing Service 
Bulletin 777-57A0050, Revision 4, dated September 28, 2015, applies 
to Groups 5 through 43.
    (2) Where Figure 3 of Boeing Service Bulletin 777-57A0050, 
Revision 4, dated September 28, 2015, specifies ``Groups 1 through 
7, and 9 through 43,'' for this AD, Figure 3 of Boeing Service 
Bulletin 777-57A0050, Revision 4, dated September 28, 2015, applies 
to Groups 1 through 43.
    (3) Where Figure 100 of Boeing Service Bulletin 777-57A0050, 
Revision 4, dated September 28, 2015, specifies ``Groups 5 through 
43, Configuration 2,'' for this AD, Figure 100 of Boeing Service 
Bulletin 777-57A0050, Revision 4, dated September 28, 2015, applies 
to Groups 5 through 43.

(l) Credit for Previous Actions

    (1) This paragraph provides credit for the actions specified in 
paragraph (g)(1) of this AD, if those actions were performed before 
January 20, 2011 (the effective date of AD 2010-24-12), using Boeing 
Alert Service Bulletin 777-57A0050, dated January 26, 2006; or 
Revision 1, dated August 2, 2007; provided that the applicable 
additional work specified in Boeing Service Bulletin 777-57A0050, 
Revision 2, dated May 14, 2009, is done within the compliance time 
specified in paragraph (g) of this AD. The additional work must be 
done in accordance with Boeing Service Bulletin 777-57A0050, 
Revision 2, dated May 14, 2009.
    (2) This paragraph provides credit for the actions specified in 
paragraph (g)(3) of this AD, if those actions were performed before 
January 20, 2011 (the effective date of AD 2010-24-12), using Boeing 
Alert Service Bulletin 777-57A0057, dated August 7, 2006.

(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 paragraph (n)(1) 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) An AMOC that provides an acceptable level of safety may be 
used for any repair, modification, or alteration required by this AD 
if it is approved by the Boeing Commercial Airplanes Organization 
Designation Authorization (ODA) that has been authorized by the 
Manager, Seattle ACO, 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 previously for AD 2011-26-03 are approved as 
AMOCs for the corresponding provisions of this AD.

(n) Related Information

    (1) For more information about this AD, contact Suzanne Lucier, 
Aerospace Engineer, Propulsion Branch, ANM 140S, FAA, Seattle 
Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, 
WA 98057-3356; phone: 425-917-6438; fax: 425-917-6590; email: 
suzanne.lucier@faa.gov.
    (2) 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 view this referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on July 8, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-16906 Filed 7-19-16; 8:45 am]
 BILLING CODE 4910-13-P