Airworthiness Directives; The Boeing Company Airplanes, 85129-85133 [2016-26809]

Download as PDF Federal Register / Vol. 81, No. 227 / Friday, November 25, 2016 / Rules and Regulations (f) Required Actions (1) Before further flight and thereafter at the following intervals, check the TGB oil level: (i) For Model SA–365N1, AS–365N2, and AS 365 N3 helicopters, at intervals not to exceed 10 hours time-in-service (TIS). (ii) For Model SA366G1 helicopters, before the first flight of each day. (iii) For Model EC 155B and EC155B1 helicopters, at intervals not to exceed 15 hours TIS. (iv) The actions required by paragraph (f)(1) of this AD may be performed by the owner/operator (pilot) holding at least a private pilot certificate and must be entered into the aircraft records showing compliance with this AD in accordance with 14 CFR 43.9 (a)(1) through (4) and 14 CFR 91.417(a)(2)(v). The record must be maintained as required by 14 CFR 91.417, 121.380, or 135.439. (2) If the oil level is not at maximum, before further flight, a qualified mechanic must fill it to the maximum level. (3) Within 15 hours TIS, replace the bearing P/N 704A33–651–093 or P/N 704A33–651–104 with a bearing P/N 704A33–651–245 or P/N 704A33–651–246. (4) Do not install bearing P/N 704A33– 651–093 or P/N 704A33–651–104 on any helicopter. ehiers on DSK5VPTVN1PROD with RULES (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: David Hatfield, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5116; email 9-ASWFTW-AMOC-Requests@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. (h) Additional Information (1) Airbus Helicopters Alert Service Bulletin No. AS365–01.00.67, No. EC155– 04A014, and No. SA366–01.29, each Revision 0 and dated May 4, 2016, which are not incorporated by reference, contain additional information about the subject of this final rule. For service information identified in this AD, contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at http://www.airbushelicopters.com/techpub. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N–321, Fort Worth, TX 76177. (2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2016–0097R1, dated May 25, 2016. You may view the EASA AD on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA–2016– 9396. VerDate Sep<11>2014 14:00 Nov 23, 2016 Jkt 241001 (i) Subject Joint Aircraft Service Component (JASC) Code: 6520 Tail Rotor Gearbox. Issued in Fort Worth, Texas, on November 2, 2016. Lance T. Gant, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2016–27638 Filed 11–23–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–5809; Directorate Identifier 2015–NM–055–AD; Amendment 39–18709; AD 2016–23–02] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2006–19– 12 for certain The Boeing Company Model 777–200 and –300 series airplanes. AD 2006–19–12 required inspecting the lower web of the aft fairing of the engine struts for any discoloration, and doing related investigative and corrective actions if necessary; inspecting the heat shield castings for any damage and doing corrective action if necessary; installing gap cover strips; and replacing insulation blankets with new insulation blankets. This new AD retains those requirements and also requires, depending on airplane configuration, one-time or repetitive detailed inspections for cracking and deformation, as applicable, of the aft fairing lower structure, and one-time or repetitive conductivity inspections of the aft fairing lower structure, and related investigative and corrective actions if necessary. This new AD also adds airplanes to the applicability. This AD was prompted by a report that an aft fairing lower spar web exceeded the allowable conductivity limits. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective December 30, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 30, 2016. The Director of the Federal Register approved the incorporation by reference SUMMARY: PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 85129 of a certain other publication listed in this AD as of October 30, 2006 (71 FR 55727, September 25, 2006). ADDRESSES: For service information identified in this final rule, 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–2015– 5809. 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–2015– 5809; 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 Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Sue Lucier, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057– 3356; telephone: 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 2006–19–12, Amendment 39–14769 (71 FR 55727, September 25, 2006) (‘‘AD 2006–19– 12’’). AD 2006–19–12 applied to certain Boeing Model 777–200 and –300 series airplanes. The NPRM published in the Federal Register on November 20, 2015 (80 FR 72621) (‘‘the NPRM’’). The NPRM was prompted by a report that an aft fairing lower spar web exceeded the allowable conductivity limits. The NPRM proposed to continue to require inspecting the lower web of the aft fairing of the engine struts for any E:\FR\FM\25NOR1.SGM 25NOR1 85130 Federal Register / Vol. 81, No. 227 / Friday, November 25, 2016 / Rules and Regulations discoloration, and doing related investigative and corrective actions if necessary; inspecting the heat shield castings for any damage and doing corrective action if necessary; installing gap cover strips; and replacing insulation blankets with new insulation blankets. The NPRM also proposed to require, depending on airplane configuration, one-time or repetitive detailed inspections for cracking and deformation, as applicable, of the aft fairing lower structure; one-time or repetitive conductivity inspections of the aft fairing lower structure; and related investigative and corrective actions if necessary. The NPRM also added airplanes to the applicability. We are issuing this AD to detect and correct degradation of the aft fairing lower web, which could lead to cracking of the web and could allow flammable fluids to leak into the heat shield pan castings, and increase the risk of an uncontained fire and subsequent structural damage. ehiers on DSK5VPTVN1PROD with RULES Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA’s response to each comment. Request To Exclude a Certain Line Number From the Applicability Boeing requested that we exclude line number (L/N) 940 from the applicability of the proposed AD. Boeing stated that the effectivity of Boeing Service Bulletin 777–54–0026, Revision 2, dated January 5, 2012; and Boeing Special Attention Service Bulletin 777–54–0038, dated March 6, 2015; erroneously included L/ N 940. Boeing commented that a modification (installation of new gap cover strip fillers, new Velcro strips, and improved aft fairing insulation blankets) was introduced in production starting on L/N 940. Boeing noted that Boeing Service Bulletin 777–54–0026, Revision 2, dated January 5, 2012, which is an optional terminating action in the proposed AD, specifies procedures for that modification. Boeing stated that, therefore, the proposed AD would mandate that the service information be accomplished for L/N 940 even though the optional terminating action was already incorporated in production. Boeing commented that since the terminating action was incorporated in production for L/N 940, the unsafe condition stated in the proposed AD does not exist and the one-time inspection using Boeing Special Attention Service Bulletin 777– 54–0038, dated March 6, 2015, is not required for that airplane. VerDate Sep<11>2014 14:00 Nov 23, 2016 Jkt 241001 We agree with the commenter’s request. Since L/N 940 already has the terminating action incorporated during the airplane’s production, we have excluded L/N 940 from the applicability in paragraph (c) of this AD. Request To Change the Compliance Time Boeing requested that we change the compliance time in paragraph (j) of the proposed AD from ‘‘24 months after the effective date of this AD’’ to ‘‘750 days after the effective date of this AD.’’ Boeing stated that the compliance time of 750 days aligns with the proposed compliance time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 777–54– 0038, dated March 6, 2015. We disagree with the commenter’s request. The compliance time is expressed in months for ease of compliance time awareness. We converted days to months, and 750 days is equivalent to 24 months. We have not changed this AD in this regard. Request To Revise Inspection Language for Clarity Boeing requested that we revise paragraph (j) of the proposed AD to clarify that the detailed inspections of the aft fairing lower structure are intended to detect cracks and deformation, and the conductivity inspections of the aft fairing lower structure are intended to detect thermal degradation of the structure. We agree with the commenter’s request. We have revised paragraph (j) of this AD accordingly. Request To Address and Clarify Compliance for Certain Airplane Groups Air New Zealand requested that we clearly address compliance for certain airplane groups. Air New Zealand commented that we have not clearly addressed compliance in the proposed AD for Group 1, Configurations 2 and 4, airplanes; and Group 2, Configuration 2, airplanes. Air New Zealand stated it has airplanes that have accomplished the actions in Boeing Service Bulletin 777– 54–0026, dated March 29, 2011; and Boeing Service Bulletin 777–54–0026, Revision 1, dated August 23, 2011; but have yet to accomplish the actions in Boeing Special Attention Service Bulletin 777–54–0038, dated March 6, 2015. Air New Zealand stated that if Boeing Service Bulletin 777–54–0026, dated March 29, 2011; Boeing Service Bulletin 777–54–0026, Revision 1, dated August 23, 2011; or Boeing Service Bulletin 777–54–0026, Revision 2, dated January 5, 2012; have been PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 accomplished, the terminating action in paragraph (k) of the proposed AD is achieved by accomplishing Boeing Special Attention Service Bulletin 777– 54–0038, dated March 6, 2015. We partially agree with the commenter. We agree to clarify the airplane configurations to make the compliance requirements in paragraphs (j) and (k) of this AD easier to understand and follow. Although paragraph (j) of the proposed AD did not explicitly state the various configurations and groups for the initial inspection, it was intended that the initial inspection would be done for all airplanes and that the repetitive inspections would apply only to the configurations identified in paragraph (j) of the proposed AD in the sentence that specifies to do repetitive inspections. In paragraph (j)(1) of this AD, we have specified that the initial detailed inspections must be done for all configurations, including associated groups, within 24 months after the effective date of this AD. In paragraph (j)(2) of this AD, we have specified that repetitive inspections must be done (until the terminating action specified in paragraph (k) of this AD is done) for airplanes that belong to Group 1, Configurations l and 3, and for Group 2, Configuration 1, airplanes identified in Boeing Special Attention Service Bulletin 777–54–0038, dated March 6, 2015. For Group 1, Configurations 2 and 4, airplanes, and Group 2, Configuration 2, airplanes identified in Boeing Special Attention Service Bulletin 777–54– 0038, dated March 6, 2015, operators do not need to do the repetitive inspections on those airplanes. For those airplanes, the actions specified in Boeing Service Bulletin 777–54–0026 would have already been done and only the initial inspection required by paragraph (j)(1) of this AD would need to done. Note that those airplanes are listed in table 2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 777–54–0038, dated March 6, 2015, which does not specify repetitive inspections. We have modified paragraph (j) of this AD to clarify the airplane configurations by identifying which groups are affected. We have also modified paragraph (k) of this AD to accommodate the changes in paragraph (j) of this AD. Request To Use Boeing Information Notice Air New Zealand requested that we add Boeing Information Notice (IN) 777–54–0038, IN 01, dated December E:\FR\FM\25NOR1.SGM 25NOR1 Federal Register / Vol. 81, No. 227 / Friday, November 25, 2016 / Rules and Regulations 10, 2015 (‘‘Boeing IN 777–54–0038’’), to paragraph (j) of the proposed AD. Air New Zealand stated that the information notice shows the required parts needed to accomplish Boeing Special Attention Service Bulletin 777–54–0038, dated March 6, 2015. We acknowledge the intent of the commenter’s request. However, the parts identified in Boeing IN 777–54– 0038 do not affect the unsafe condition or the requirements of this AD as Boeing IN 777–54–0038 contains interchangeability information and the alternate parts are not required. Therefore, operators can comply with paragraph (j) of this AD by accomplishing the actions specified in the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–54–0038, dated March 6, 2015. In addition, it is not appropriate to cite Boeing INs as sources of service information in ADs because INs are not FAA-approved documents. We have not changed this final rule in this regard. Request To Clarify Required Actions Air New Zealand requested that we clarify the required actions in the proposed AD. Air New Zealand stated that it has airplanes on which the actions in Boeing Service Bulletin 777– 54–0026, dated March 29, 2011; Boeing Service Bulletin 777–54–0026, Revision 1, dated August 23. 2011; or Boeing Service Bulletin 777–54–0026, Revision 2, dated January 5, 2012; has been accomplished, but the actions in Boeing Special Attention Service Bulletin 777– 54–0038, dated March 6, 2015, have not been accomplished. Air New Zealand stated that it thinks if Boeing Service Bulletin 777–54–0026 has been previously complied with, terminating action is achieved once Boeing Special Attention Service Bulletin 777–54– 0038, dated March 6, 2015, is accomplished. We agree to clarify the actions in this AD. We infer Air New Zealand is requesting credit for having done Boeing Service Bulletin 777–54–0026, dated March 29, 2011; or Boeing Service Bulletin 777–54–0026, Revision 1, dated August 23. 2011. Paragraph (k) of this AD describes terminating action for paragraph (j)(2) of this AD and refers to Boeing Service Bulletin 777–54–0026, Revision 2, dated January 5, 2012. We have added a new paragraph (l) to this AD to give credit for prior accomplishment of the actions in Boeing Service Bulletin 777–54–0026, dated March 29, 2011; and Boeing Service Bulletin 777–54–0026, Revision 1, dated August 23, 2011. We have redesignated the subsequent paragraphs accordingly. Request To Clarify the Word ‘‘New’’ in the Proposed AD Boeing requested that we revise the Related Service Information under 1 CFR part 51 paragraph of the NPRM and paragraph (k) of the proposed AD to replace the words ‘‘new aft fairing insulation blankets’’ with ‘‘improved aft fairing insulation blankets with new batting material.’’ Boeing stated that the insulation blankets specified in Boeing Service Bulletin 777–54–0026, Revision 2, dated January 5, 2012, have improved thermal protection properties to the insulation blankets, as specified in Boeing Special Attention Service Bulletin 777–54–0021, Revision 1, dated March 16, 2006, due to being made from different materials. Boeing stated that, therefore, to avoid confusion between paragraphs (g)(4) and (k) of the proposed AD when referring to ‘‘new’’ insulation blankets, the distinction needs to be made. We agree with the commenter’s request. We have changed this final rule accordingly. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the 85131 public interest require adopting this AD with the changes described previously, and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Service Bulletin 777–54–0026, Revision 2, dated January 5, 2012. The service information describes procedures for a detailed inspection of the gap cover strips and heat shield pan castings for damage, corrective actions, and installation of new gap cover strip fillers, new Velcro strips, and improved aft fairing insulation blankets with new batting material. We also reviewed Boeing Special Attention Service Bulletin 777–54– 0038, dated March 6, 2015. The service information describes procedures for one-time and repetitive detailed inspections for any cracking and deformation, as applicable, of the aft fairing lower structure; conductivity inspections of the aft fairing lower structure; and related investigative and corrective actions. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 99 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Labor cost Parts cost Cost per product Inspection and other actions [retained actions from AD 2006–19–12]. Inspections [new action] ehiers on DSK5VPTVN1PROD with RULES Action Up to 11 work-hours × $85 per hour = $935, depending on airplane configuration. Up to 24 work-hours × $85 per hour = $2,040, depending on airplane configuration. Up to $16,179, depending on airplane configuration. $0 .................................. Up to $17,114, depending on airplane configuration. Up to $2,040, depending on airplane configuration. We estimate the following costs to do any necessary related investigative and corrective actions that will be required VerDate Sep<11>2014 17:12 Nov 23, 2016 Jkt 241001 based on the results of the inspection. We have no way of determining the PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 Cost on U.S. operators Up to $1,694,286, depending on airplane configuration. Up to $201,960, depending on airplane configuration. number of aircraft that might need these inspections and replacements: E:\FR\FM\25NOR1.SGM 25NOR1 85132 Federal Register / Vol. 81, No. 227 / Friday, November 25, 2016 / Rules and Regulations ON-CONDITION COSTS Action Labor cost Related investigative actions ... Up to 36 work-hours × $85 per hour = $3,060, depending on airplane configuration. Up to 38 work-hours × $85 per hour = $3,230, depending on airplane configuration. Corrective actions .................... According to the manufacturer, all of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. ehiers on DSK5VPTVN1PROD 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 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: (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. VerDate Sep<11>2014 14:00 Nov 23, 2016 Jkt 241001 Parts cost Cost per product $0 Up to $3,060, depending on airplane configuration. $0 Up to $3,230, depending on airplane configuration. 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) 2006–19–12, Amendment 39–14769 (71 FR 55727, September 25, 2006), and adding the following new AD: ■ 2016–23–02 The Boeing Company: Amendment 39–18709; Docket No. FAA–2015–5809; Directorate Identifier 2015–NM–055–AD. (a) Effective Date This AD is effective December 30, 2016. (b) Affected ADs This AD replaces AD 2006–19–12, Amendment 39–14769 (71 FR 55727, September 25, 2006) (‘‘AD 2006–19–12’’). (c) Applicability This AD applies to The Boeing Company Model 777–200, –200LR, –300, –300ER, and 777F series airplanes, certified in any category, as identified in Boeing Special Attention Service Bulletin 777–54–0038, dated March 6, 2015; except for line number 940. (d) Subject Air Transport Association (ATA) of America Code 54, Nacelles/pylons. (e) Unsafe Condition This AD was prompted by a report that an aft fairing lower spar web exceeded the allowable conductivity limits. An investigation concluded that wear to the pan casting and gap cover strips allowed increased heat into the aft fairing heat shield cavity. We are issuing this AD to detect and correct degradation of the aft fairing lower web, which could lead to cracking of the web and could allow flammable fluids to leak into PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 the heat shield pan castings, and increase the risk of an uncontained fire and subsequent structural damage. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspection, Installation, and Replacement Actions, With No Changes This paragraph restates the actions required by paragraph (f) of AD 2006–19–12, with no changes. For Model 777–200 and –300 series airplanes identified in Boeing Special Attention Service Bulletin 777–54– 0021, Revision 1, dated March 16, 2006: Except as provided by paragraph (h) of this AD, within 12 months after October 30, 2006 (the effective date of AD 2006–19–12), do the actions specified in paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of this AD, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–54–0021, Revision 1, dated March 16, 2006. (1) Do a general visual inspection of the lower web of the aft fairing for any discoloration and do any related investigative action. (2) Do a general visual inspection of the heat shield castings for any damage (crack(s), dent(s), gouge(s), warpage, fretting, or missing/loose nutplates). (3) Install gap cover strips on the heat shield pans. (4) Replace insulation blankets on the heat shield pans with new insulation blankets. (h) Retained Repair Instructions, With No Changes This paragraph restates the actions required by paragraph (g) of AD 2006–19–12, with no changes. If any damage, discoloration, heat damage, or crack is found during any inspection required by paragraph (g) of this AD: Before further flight, do all applicable corrective actions, in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, or in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–54– 0021, Revision 1, dated March 16, 2006. (i) Retained Credit for Previous Actions, With Revised Format This paragraph restates the credit provided by paragraph (h) of AD 2006–19–12, with a revised format. This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before October 30, 2006 (the effective date of AD 2006–19–12), using Boeing Special E:\FR\FM\25NOR1.SGM 25NOR1 Federal Register / Vol. 81, No. 227 / Friday, November 25, 2016 / Rules and Regulations Attention Service Bulletin 777–54–0021, dated June 23, 2005, except where Boeing Special Attention Service Bulletin 777–54– 0021, dated June 23, 2005, does not provide an international annealed copper standard (IACS) value for determining the results of the inspection for heat damage, the maximum acceptable IACS value is 42 percent. (j) New Requirements: Detailed and Conductivity Inspections and Related Investigative and Corrective Actions (Repetitive Inspections for Certain Airplanes) (1) For Group 1, Configurations 1, 2, 3, and 4, airplanes; and Group 2, Configurations 1 and 2, airplanes; identified in Boeing Special Attention Service Bulletin 777–54–0038, dated March 6, 2015: Within 24 months after the effective date of this AD, do a detailed inspection of the aft fairing lower structure for any cracking and deformation, and do a conductivity inspection of the aft fairing lower structure for the IACS value (thermal degradation indication), as applicable, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–54– 0038, dated March 6, 2015. Do all applicable related investigative and corrective actions before further flight. (2) For Group 1, Configurations 1 and 3, airplanes, and Group 2, Configuration 1, airplanes, identified in Boeing Special Attention Service Bulletin 777–54–0038, dated March 6, 2015: Repeat the inspections specified in paragraph (j)(1) of this AD thereafter at intervals not to exceed 24 months until the terminating action specified in paragraph (k) of this AD is done. ehiers on DSK5VPTVN1PROD with RULES (k) Optional Terminating Action Accomplishing a detailed inspection of the gap cover strips and heat shield pan castings for damage and applicable corrective actions, and installation of new gap cover strip fillers, new Velcro strips, and improved aft fairing insulation blankets with new batting material, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777–54–0026, Revision 2, dated January 5, 2012, prior to or concurrently with accomplishing detailed and conductivity inspections and all applicable related investigative and corrective actions required by paragraph (j)(1) of this AD, terminates the repetitive inspections specified in paragraph (j)(2) of this AD; except, where Boeing Service Bulletin 777–54–0026, Revision 2, dated January 5, 2012, specifies to contact the manufacturer, repair using a method approved in accordance with the procedures specified in paragraph (m) of this AD. (l) Credit for Previous Actions This paragraph provides credit for the actions specified in paragraph (k) of this AD that are identified in Boeing Service Bulletin 777–54–0026, Revision 2, dated January 5, 2012, if those actions were performed before the effective date of this AD using Boeing Service Bulletin 777–54–0026, dated March 29, 2011; or Boeing Service Bulletin 777–54– 0026, Revision 1, dated August 23, 2011. VerDate Sep<11>2014 14:00 Nov 23, 2016 Jkt 241001 (m) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle 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-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 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. For a repair method to be approved, the repair must meet the certification basis of airplane, and the approval must specifically refer to this AD. (4) AMOCs approved for AD 2006–19–12 are approved as AMOCs for the corresponding provisions of paragraphs (g), (h), and (i) of this AD. (5) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (m)(5)(i) and (m)(5)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or substep is labeled ‘‘RC Exempt,’’ then the RC requirement is removed from that step or substep. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (n) Related Information (1) For more information about this AD, contact Sue Lucier, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: 425–917–6438; fax: 425–917–6590; email: suzanne.lucier@ faa.gov. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (o)(5) and (o)(6) of this AD. (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. PO 00000 Frm 00029 Fmt 4700 Sfmt 4700 85133 (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 December 30, 2016. (i) Boeing Service Bulletin 777–54–0026, Revision 2, dated January 5, 2012. (ii) Boeing Special Attention Service Bulletin 777–54–0038, dated March 6, 2015. (4) The following service information was approved for IBR on October 30, 2006, Amendment 39–14769 (71 FR 55727, September 25, 2006). (i) Boeing Special Attention Service Bulletin 777–54–0021, Revision 1, dated March 16, 2006. (ii) Reserved. (5) For Boeing 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.myboeing fleet.com. (6) You may view this service information at FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives. gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on October 28, 2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–26809 Filed 11–23–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2016–6413; Airspace Docket No. 16–AWP–11] Establishment of Class E Airspace, Silver Springs, NV Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: This action establishes Class E airspace extending upward from 700 feet above the surface at Silver Springs Airport, Silver Springs, NV. The FAA found establishment of airspace necessary for the safety and management of Instrument Flight Rules (IFR) operations under new Area Navigation (RNAV) Standard Instrument Approach Procedures at the airport. DATES: Effective 0901 UTC, March 2, 2017. The Director of the Federal SUMMARY: E:\FR\FM\25NOR1.SGM 25NOR1

Agencies

[Federal Register Volume 81, Number 227 (Friday, November 25, 2016)]
[Rules and Regulations]
[Pages 85129-85133]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-26809]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-5809; Directorate Identifier 2015-NM-055-AD; 
Amendment 39-18709; AD 2016-23-02]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2006-19-12 for 
certain The Boeing Company Model 777-200 and -300 series airplanes. AD 
2006-19-12 required inspecting the lower web of the aft fairing of the 
engine struts for any discoloration, and doing related investigative 
and corrective actions if necessary; inspecting the heat shield 
castings for any damage and doing corrective action if necessary; 
installing gap cover strips; and replacing insulation blankets with new 
insulation blankets. This new AD retains those requirements and also 
requires, depending on airplane configuration, one-time or repetitive 
detailed inspections for cracking and deformation, as applicable, of 
the aft fairing lower structure, and one-time or repetitive 
conductivity inspections of the aft fairing lower structure, and 
related investigative and corrective actions if necessary. This new AD 
also adds airplanes to the applicability. This AD was prompted by a 
report that an aft fairing lower spar web exceeded the allowable 
conductivity limits. We are issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective December 30, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of December 30, 
2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
October 30, 2006 (71 FR 55727, September 25, 2006).

ADDRESSES: For service information identified in this final rule, 
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-2015-
5809.

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-2015-
5809; 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 Docket Management Facility, U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Sue Lucier, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 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 2006-19-12, Amendment 39-14769 (71 FR 55727, 
September 25, 2006) (``AD 2006-19-12''). AD 2006-19-12 applied to 
certain Boeing Model 777-200 and -300 series airplanes. The NPRM 
published in the Federal Register on November 20, 2015 (80 FR 72621) 
(``the NPRM''). The NPRM was prompted by a report that an aft fairing 
lower spar web exceeded the allowable conductivity limits. The NPRM 
proposed to continue to require inspecting the lower web of the aft 
fairing of the engine struts for any

[[Page 85130]]

discoloration, and doing related investigative and corrective actions 
if necessary; inspecting the heat shield castings for any damage and 
doing corrective action if necessary; installing gap cover strips; and 
replacing insulation blankets with new insulation blankets. The NPRM 
also proposed to require, depending on airplane configuration, one-time 
or repetitive detailed inspections for cracking and deformation, as 
applicable, of the aft fairing lower structure; one-time or repetitive 
conductivity inspections of the aft fairing lower structure; and 
related investigative and corrective actions if necessary. The NPRM 
also added airplanes to the applicability. We are issuing this AD to 
detect and correct degradation of the aft fairing lower web, which 
could lead to cracking of the web and could allow flammable fluids to 
leak into the heat shield pan castings, and increase the risk of an 
uncontained fire and subsequent structural damage.

Comments

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

Request To Exclude a Certain Line Number From the Applicability

    Boeing requested that we exclude line number (L/N) 940 from the 
applicability of the proposed AD. Boeing stated that the effectivity of 
Boeing Service Bulletin 777-54-0026, Revision 2, dated January 5, 2012; 
and Boeing Special Attention Service Bulletin 777-54-0038, dated March 
6, 2015; erroneously included L/N 940.
    Boeing commented that a modification (installation of new gap cover 
strip fillers, new Velcro strips, and improved aft fairing insulation 
blankets) was introduced in production starting on L/N 940. Boeing 
noted that Boeing Service Bulletin 777-54-0026, Revision 2, dated 
January 5, 2012, which is an optional terminating action in the 
proposed AD, specifies procedures for that modification. Boeing stated 
that, therefore, the proposed AD would mandate that the service 
information be accomplished for L/N 940 even though the optional 
terminating action was already incorporated in production. Boeing 
commented that since the terminating action was incorporated in 
production for L/N 940, the unsafe condition stated in the proposed AD 
does not exist and the one-time inspection using Boeing Special 
Attention Service Bulletin 777-54-0038, dated March 6, 2015, is not 
required for that airplane.
    We agree with the commenter's request. Since L/N 940 already has 
the terminating action incorporated during the airplane's production, 
we have excluded L/N 940 from the applicability in paragraph (c) of 
this AD.

Request To Change the Compliance Time

    Boeing requested that we change the compliance time in paragraph 
(j) of the proposed AD from ``24 months after the effective date of 
this AD'' to ``750 days after the effective date of this AD.'' Boeing 
stated that the compliance time of 750 days aligns with the proposed 
compliance time specified in paragraph 1.E., ``Compliance,'' of Boeing 
Special Attention Service Bulletin 777-54-0038, dated March 6, 2015.
    We disagree with the commenter's request. The compliance time is 
expressed in months for ease of compliance time awareness. We converted 
days to months, and 750 days is equivalent to 24 months. We have not 
changed this AD in this regard.

Request To Revise Inspection Language for Clarity

    Boeing requested that we revise paragraph (j) of the proposed AD to 
clarify that the detailed inspections of the aft fairing lower 
structure are intended to detect cracks and deformation, and the 
conductivity inspections of the aft fairing lower structure are 
intended to detect thermal degradation of the structure.
    We agree with the commenter's request. We have revised paragraph 
(j) of this AD accordingly.

Request To Address and Clarify Compliance for Certain Airplane Groups

    Air New Zealand requested that we clearly address compliance for 
certain airplane groups. Air New Zealand commented that we have not 
clearly addressed compliance in the proposed AD for Group 1, 
Configurations 2 and 4, airplanes; and Group 2, Configuration 2, 
airplanes. Air New Zealand stated it has airplanes that have 
accomplished the actions in Boeing Service Bulletin 777-54-0026, dated 
March 29, 2011; and Boeing Service Bulletin 777-54-0026, Revision 1, 
dated August 23, 2011; but have yet to accomplish the actions in Boeing 
Special Attention Service Bulletin 777-54-0038, dated March 6, 2015. 
Air New Zealand stated that if Boeing Service Bulletin 777-54-0026, 
dated March 29, 2011; Boeing Service Bulletin 777-54-0026, Revision 1, 
dated August 23, 2011; or Boeing Service Bulletin 777-54-0026, Revision 
2, dated January 5, 2012; have been accomplished, the terminating 
action in paragraph (k) of the proposed AD is achieved by accomplishing 
Boeing Special Attention Service Bulletin 777-54-0038, dated March 6, 
2015.
    We partially agree with the commenter. We agree to clarify the 
airplane configurations to make the compliance requirements in 
paragraphs (j) and (k) of this AD easier to understand and follow.
    Although paragraph (j) of the proposed AD did not explicitly state 
the various configurations and groups for the initial inspection, it 
was intended that the initial inspection would be done for all 
airplanes and that the repetitive inspections would apply only to the 
configurations identified in paragraph (j) of the proposed AD in the 
sentence that specifies to do repetitive inspections.
    In paragraph (j)(1) of this AD, we have specified that the initial 
detailed inspections must be done for all configurations, including 
associated groups, within 24 months after the effective date of this 
AD. In paragraph (j)(2) of this AD, we have specified that repetitive 
inspections must be done (until the terminating action specified in 
paragraph (k) of this AD is done) for airplanes that belong to Group 1, 
Configurations l and 3, and for Group 2, Configuration 1, airplanes 
identified in Boeing Special Attention Service Bulletin 777-54-0038, 
dated March 6, 2015.
    For Group 1, Configurations 2 and 4, airplanes, and Group 2, 
Configuration 2, airplanes identified in Boeing Special Attention 
Service Bulletin 777-54-0038, dated March 6, 2015, operators do not 
need to do the repetitive inspections on those airplanes. For those 
airplanes, the actions specified in Boeing Service Bulletin 777-54-0026 
would have already been done and only the initial inspection required 
by paragraph (j)(1) of this AD would need to done. Note that those 
airplanes are listed in table 2 of paragraph 1.E., ``Compliance,'' of 
Boeing Special Attention Service Bulletin 777-54-0038, dated March 6, 
2015, which does not specify repetitive inspections.
    We have modified paragraph (j) of this AD to clarify the airplane 
configurations by identifying which groups are affected. We have also 
modified paragraph (k) of this AD to accommodate the changes in 
paragraph (j) of this AD.

Request To Use Boeing Information Notice

    Air New Zealand requested that we add Boeing Information Notice 
(IN) 777-54-0038, IN 01, dated December

[[Page 85131]]

10, 2015 (``Boeing IN 777-54-0038''), to paragraph (j) of the proposed 
AD. Air New Zealand stated that the information notice shows the 
required parts needed to accomplish Boeing Special Attention Service 
Bulletin 777-54-0038, dated March 6, 2015.
    We acknowledge the intent of the commenter's request. However, the 
parts identified in Boeing IN 777-54-0038 do not affect the unsafe 
condition or the requirements of this AD as Boeing IN 777-54-0038 
contains interchangeability information and the alternate parts are not 
required. Therefore, operators can comply with paragraph (j) of this AD 
by accomplishing the actions specified in the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 777-54-0038, 
dated March 6, 2015. In addition, it is not appropriate to cite Boeing 
INs as sources of service information in ADs because INs are not FAA-
approved documents. We have not changed this final rule in this regard.

Request To Clarify Required Actions

    Air New Zealand requested that we clarify the required actions in 
the proposed AD. Air New Zealand stated that it has airplanes on which 
the actions in Boeing Service Bulletin 777-54-0026, dated March 29, 
2011; Boeing Service Bulletin 777-54-0026, Revision 1, dated August 23. 
2011; or Boeing Service Bulletin 777-54-0026, Revision 2, dated January 
5, 2012; has been accomplished, but the actions in Boeing Special 
Attention Service Bulletin 777-54-0038, dated March 6, 2015, have not 
been accomplished. Air New Zealand stated that it thinks if Boeing 
Service Bulletin 777-54-0026 has been previously complied with, 
terminating action is achieved once Boeing Special Attention Service 
Bulletin 777-54-0038, dated March 6, 2015, is accomplished.
    We agree to clarify the actions in this AD. We infer Air New 
Zealand is requesting credit for having done Boeing Service Bulletin 
777-54-0026, dated March 29, 2011; or Boeing Service Bulletin 777-54-
0026, Revision 1, dated August 23. 2011. Paragraph (k) of this AD 
describes terminating action for paragraph (j)(2) of this AD and refers 
to Boeing Service Bulletin 777-54-0026, Revision 2, dated January 5, 
2012. We have added a new paragraph (l) to this AD to give credit for 
prior accomplishment of the actions in Boeing Service Bulletin 777-54-
0026, dated March 29, 2011; and Boeing Service Bulletin 777-54-0026, 
Revision 1, dated August 23, 2011. We have redesignated the subsequent 
paragraphs accordingly.

Request To Clarify the Word ``New'' in the Proposed AD

    Boeing requested that we revise the Related Service Information 
under 1 CFR part 51 paragraph of the NPRM and paragraph (k) of the 
proposed AD to replace the words ``new aft fairing insulation 
blankets'' with ``improved aft fairing insulation blankets with new 
batting material.'' Boeing stated that the insulation blankets 
specified in Boeing Service Bulletin 777-54-0026, Revision 2, dated 
January 5, 2012, have improved thermal protection properties to the 
insulation blankets, as specified in Boeing Special Attention Service 
Bulletin 777-54-0021, Revision 1, dated March 16, 2006, due to being 
made from different materials. Boeing stated that, therefore, to avoid 
confusion between paragraphs (g)(4) and (k) of the proposed AD when 
referring to ``new'' insulation blankets, the distinction needs to be 
made.
    We agree with the commenter's request. We have changed this final 
rule accordingly.

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 changes described previously, and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Service Bulletin 777-54-0026, Revision 2, dated 
January 5, 2012. The service information describes procedures for a 
detailed inspection of the gap cover strips and heat shield pan 
castings for damage, corrective actions, and installation of new gap 
cover strip fillers, new Velcro strips, and improved aft fairing 
insulation blankets with new batting material.
    We also reviewed Boeing Special Attention Service Bulletin 777-54-
0038, dated March 6, 2015. The service information describes procedures 
for one-time and repetitive detailed inspections for any cracking and 
deformation, as applicable, of the aft fairing lower structure; 
conductivity inspections of the aft fairing lower structure; and 
related investigative and corrective actions.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 99 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                   Labor cost          Parts cost       Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection and other actions      Up to 11            Up to $16,179,      Up to $17,114,      Up to $1,694,286,
 [retained actions from AD 2006-   work[dash]hours x   depending on        depending on        depending on
 19-12].                           $85 per hour =      airplane            airplane            airplane
                                   $935, depending     configuration.      configuration.      configuration.
                                   on airplane
                                   configuration.
Inspections [new action]........  Up to 24            $0................  Up to $2,040,       Up to $201,960,
                                   work[dash]hours x                       depending on        depending on
                                   $85 per hour =                          airplane            airplane
                                   $2,040, depending                       configuration.      configuration.
                                   on airplane
                                   configuration.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary related 
investigative and corrective actions that will be required based on the 
results of the inspection. We have no way of determining the number of 
aircraft that might need these inspections and replacements:

[[Page 85132]]



                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                 Action                           Labor cost            Parts cost         Cost per product
----------------------------------------------------------------------------------------------------------------
Related investigative actions...........  Up to 36 work[dash]hours x              $0  Up to $3,060, depending on
                                           $85 per hour = $3,060,                      airplane configuration.
                                           depending on airplane
                                           configuration.
Corrective actions......................  Up to 38 work[dash]hours x              $0  Up to $3,230, depending on
                                           $85 per hour = $3,230,                      airplane configuration.
                                           depending on airplane
                                           configuration.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, all of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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:
    (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) 
2006-19-12, Amendment 39-14769 (71 FR 55727, September 25, 2006), and 
adding the following new AD:

2016-23-02 The Boeing Company: Amendment 39-18709; Docket No. FAA-
2015-5809; Directorate Identifier 2015-NM-055-AD.

(a) Effective Date

    This AD is effective December 30, 2016.

(b) Affected ADs

    This AD replaces AD 2006-19-12, Amendment 39-14769 (71 FR 55727, 
September 25, 2006) (``AD 2006-19-12'').

(c) Applicability

    This AD applies to The Boeing Company Model 777-200, -200LR, -
300, -300ER, and 777F series airplanes, certified in any category, 
as identified in Boeing Special Attention Service Bulletin 777-54-
0038, dated March 6, 2015; except for line number 940.

(d) Subject

    Air Transport Association (ATA) of America Code 54, Nacelles/
pylons.

(e) Unsafe Condition

    This AD was prompted by a report that an aft fairing lower spar 
web exceeded the allowable conductivity limits. An investigation 
concluded that wear to the pan casting and gap cover strips allowed 
increased heat into the aft fairing heat shield cavity. We are 
issuing this AD to detect and correct degradation of the aft fairing 
lower web, which could lead to cracking of the web and could allow 
flammable fluids to leak into the heat shield pan castings, and 
increase the risk of an uncontained fire and subsequent structural 
damage.

(f) Compliance

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

(g) Retained Inspection, Installation, and Replacement Actions, With No 
Changes

    This paragraph restates the actions required by paragraph (f) of 
AD 2006-19-12, with no changes. For Model 777-200 and -300 series 
airplanes identified in Boeing Special Attention Service Bulletin 
777-54-0021, Revision 1, dated March 16, 2006: Except as provided by 
paragraph (h) of this AD, within 12 months after October 30, 2006 
(the effective date of AD 2006-19-12), do the actions specified in 
paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of this AD, in 
accordance with the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 777-54-0021, Revision 1, dated March 16, 
2006.
    (1) Do a general visual inspection of the lower web of the aft 
fairing for any discoloration and do any related investigative 
action.
    (2) Do a general visual inspection of the heat shield castings 
for any damage (crack(s), dent(s), gouge(s), warpage, fretting, or 
missing/loose nutplates).
    (3) Install gap cover strips on the heat shield pans.
    (4) Replace insulation blankets on the heat shield pans with new 
insulation blankets.

(h) Retained Repair Instructions, With No Changes

    This paragraph restates the actions required by paragraph (g) of 
AD 2006-19-12, with no changes. If any damage, discoloration, heat 
damage, or crack is found during any inspection required by 
paragraph (g) of this AD: Before further flight, do all applicable 
corrective actions, in accordance with a method approved by the 
Manager, Seattle Aircraft Certification Office (ACO), FAA, or in 
accordance with the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 777-54-0021, Revision 1, dated March 16, 
2006.

(i) Retained Credit for Previous Actions, With Revised Format

    This paragraph restates the credit provided by paragraph (h) of 
AD 2006-19-12, with a revised format. This paragraph provides credit 
for actions required by paragraph (g) of this AD, if those actions 
were performed before October 30, 2006 (the effective date of AD 
2006-19-12), using Boeing Special

[[Page 85133]]

Attention Service Bulletin 777-54-0021, dated June 23, 2005, except 
where Boeing Special Attention Service Bulletin 777-54-0021, dated 
June 23, 2005, does not provide an international annealed copper 
standard (IACS) value for determining the results of the inspection 
for heat damage, the maximum acceptable IACS value is 42 percent.

(j) New Requirements: Detailed and Conductivity Inspections and Related 
Investigative and Corrective Actions (Repetitive Inspections for 
Certain Airplanes)

    (1) For Group 1, Configurations 1, 2, 3, and 4, airplanes; and 
Group 2, Configurations 1 and 2, airplanes; identified in Boeing 
Special Attention Service Bulletin 777-54-0038, dated March 6, 2015: 
Within 24 months after the effective date of this AD, do a detailed 
inspection of the aft fairing lower structure for any cracking and 
deformation, and do a conductivity inspection of the aft fairing 
lower structure for the IACS value (thermal degradation indication), 
as applicable, and do all applicable related investigative and 
corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 777-54-
0038, dated March 6, 2015. Do all applicable related investigative 
and corrective actions before further flight.
    (2) For Group 1, Configurations 1 and 3, airplanes, and Group 2, 
Configuration 1, airplanes, identified in Boeing Special Attention 
Service Bulletin 777-54-0038, dated March 6, 2015: Repeat the 
inspections specified in paragraph (j)(1) of this AD thereafter at 
intervals not to exceed 24 months until the terminating action 
specified in paragraph (k) of this AD is done.

(k) Optional Terminating Action

    Accomplishing a detailed inspection of the gap cover strips and 
heat shield pan castings for damage and applicable corrective 
actions, and installation of new gap cover strip fillers, new Velcro 
strips, and improved aft fairing insulation blankets with new 
batting material, in accordance with the Accomplishment Instructions 
of Boeing Service Bulletin 777-54-0026, Revision 2, dated January 5, 
2012, prior to or concurrently with accomplishing detailed and 
conductivity inspections and all applicable related investigative 
and corrective actions required by paragraph (j)(1) of this AD, 
terminates the repetitive inspections specified in paragraph (j)(2) 
of this AD; except, where Boeing Service Bulletin 777-54-0026, 
Revision 2, dated January 5, 2012, specifies to contact the 
manufacturer, repair using a method approved in accordance with the 
procedures specified in paragraph (m) of this AD.

(l) Credit for Previous Actions

    This paragraph provides credit for the actions specified in 
paragraph (k) of this AD that are identified in Boeing Service 
Bulletin 777-54-0026, Revision 2, dated January 5, 2012, if those 
actions were performed before the effective date of this AD using 
Boeing Service Bulletin 777-54-0026, dated March 29, 2011; or Boeing 
Service Bulletin 777-54-0026, Revision 1, dated August 23, 2011.

(m) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle 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 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. For a repair method to be approved, the repair must 
meet the certification basis of airplane, and the approval must 
specifically refer to this AD.
    (4) AMOCs approved for AD 2006-19-12 are approved as AMOCs for 
the corresponding provisions of paragraphs (g), (h), and (i) of this 
AD.
    (5) For service information that contains steps that are labeled 
as Required for Compliance (RC), the provisions of paragraphs 
(m)(5)(i) and (m)(5)(ii) of this AD apply.
    (i) The steps labeled as RC, including substeps under an RC step 
and any figures identified in an RC step, must be done to comply 
with the AD. If a step or substep is labeled ``RC Exempt,'' then the 
RC requirement is removed from that step or substep. An AMOC is 
required for any deviations to RC steps, including substeps and 
identified figures.
    (ii) Steps not labeled as RC may be deviated from using accepted 
methods in accordance with the operator's maintenance or inspection 
program without obtaining approval of an AMOC, provided the RC 
steps, including substeps and identified figures, can still be done 
as specified, and the airplane can be put back in an airworthy 
condition.

(n) Related Information

    (1) For more information about this AD, contact Sue Lucier, 
Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle ACO, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-917-
6438; fax: 425-917-6590; email: suzanne.lucier@faa.gov.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (o)(5) and (o)(6) of this AD.

(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 
December 30, 2016.
    (i) Boeing Service Bulletin 777-54-0026, Revision 2, dated 
January 5, 2012.
    (ii) Boeing Special Attention Service Bulletin 777-54-0038, 
dated March 6, 2015.
    (4) The following service information was approved for IBR on 
October 30, 2006, Amendment 39-14769 (71 FR 55727, September 25, 
2006).
    (i) Boeing Special Attention Service Bulletin 777-54-0021, 
Revision 1, dated March 16, 2006.
    (ii) Reserved.
    (5) For Boeing 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, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on October 28, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-26809 Filed 11-23-16; 8:45 am]
 BILLING CODE 4910-13-P