Airworthiness Directives; The Boeing Company Airplanes, 59570-59575 [2015-24677]

Download as PDF 59570 Federal Register / Vol. 80, No. 191 / Friday, October 2, 2015 / Rules and Regulations (ii) Reserved. (3) For Lockheed service information identified in this AD, contact Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, Airworthiness Office, Dept. 6A0M, Zone 0252, Column P–58, 86 S. Cobb Drive, Marietta, GA 30063; telephone 770–494–5444; fax 770–494–5445; email ams.portal@lmco.com; Internet http:// www.lockheedmartin.com/ams/tools/ TechPubs.html. (4) 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on September 18, 2015. Dorr M. Anderson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–24839 Filed 10–1–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0128; Directorate Identifier 2013–NM–133–AD; Amendment 39–18278; AD 2015–19–16] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for The Boeing Company Model 777 airplanes equipped with Rolls-Royce Trent 800 series engines. This AD was prompted by reports of in-flight separation of the engine’s aft plug from the forward plug, which are the two parts of the turbine exhaust plug assembly. This AD requires installation of a serviceable turbine exhaust plug assembly (for certain airplanes), and a general visual inspection (for certain airplanes) to determine the diameter of the bolt used at the forward and aft plug interface, and applicable corrective actions. We are issuing this AD to prevent separation of the aft plug from the forward plug of the turbine exhaust plug assembly, which could result in parts departing the airplane and hitting the asabaliauskas on DSK5VPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 20:30 Oct 01, 2015 Jkt 238001 empennage, and destabilizing the airplane during a critical flight phase. In addition, parts remaining on a runway could pose a hazard to another airplane. DATES: This AD is effective November 6, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 6, 2015. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https:// www.myboeingfleet.com. You may 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–2014– 0128. 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–2014– 0128; 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: Kevin Nguyen, Aerospace Engineer, Propulsion Branch, ANM–140S, Seattle Aircraft Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6501; fax: 425–917–6590; email: kevin.nguyen@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to The Boeing Company Model 777 airplanes equipped with RollsRoyce Trent 800 series engines. The NPRM published in the Federal Register on March 3, 2014 (79 FR 11725); corrected March 11, 2014 (79 FR PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 13592). The NPRM was prompted by reports of in-flight separation of the engine’s aft plug from the forward plug, which are the two parts of the turbine exhaust plug assembly. The NPRM proposed to require installation of a serviceable turbine exhaust plug assembly (for certain airplanes), and a general visual inspection (for certain airplanes) to determine the diameter of the bolt used at the forward and aft plug interface, and applicable corrective actions. We are issuing this AD to prevent separation of the aft plug from the forward plug of the turbine exhaust plug assembly, which could result in parts departing the airplane and hitting the empennage, and destabilizing the airplane during a critical flight phase. In addition, parts remaining on a runway could pose a hazard to another airplane. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (79 FR 11725, March 3, 2014; corrected March 11, 2014 (79 FR 13592); and the FAA’s response to each comment. Request To Match Compliance Time Cathay Pacific requested that we ensure that the AD compliance date will be the same as the compliance time of Boeing Special Attention Service Bulletin 777–78–0051, Revision 3, dated August 23, 2012; or Boeing Special Attention Service Bulletin 777–78– 0051, Revision 4, dated February 7, 2014. Cathay Pacific reasoned that paragraph (i) of the proposed AD specified compliance within 60 months after the effective date of the proposed AD, and both revisions of this service information specify a compliance time that is within 60 months after the Revision 3 date of the service bulletin. We infer that Cathay Pacific is requesting that we reduce the compliance time of this final rule to match the compliance time listed in the service information. We do not agree with the commenter’s request. In developing an appropriate compliance time for this action, we considered not only the degree of urgency associated with addressing the subject unsafe condition, but the manufacturer’s recommendation for an appropriate compliance time, the time required for the rulemaking process, the availability of required parts, and the practical aspect of installing the required modification within an interval of time that corresponds to the typical scheduled maintenance for the majority of affected operators. Under the provisions of paragraph (l) of this AD, E:\FR\FM\02OCR1.SGM 02OCR1 Federal Register / Vol. 80, No. 191 / Friday, October 2, 2015 / Rules and Regulations we may approve requests for adjustments to the compliance time, if data are submitted to substantiate that such an adjustment would provide an acceptable level of safety. We have not changed the AD in this regard. asabaliauskas on DSK5VPTVN1PROD with RULES Request To Define ‘‘Serviceable’’ To Include Pre-Boeing Service Bulletin 777–78–0051 Plug Assemblies Cathay Pacific requested that we revise paragraph (j) of the proposed AD; corrected March 11, 2014 (79 FR 13592) to define ‘‘serviceable’’ plug assemblies. Cathay Pacific reasoned that both preand post-Boeing Service Bulletin 777– 78–0051 plug assemblies can be installed, and the modification can be completed before the required compliance time of the NPRM (79 FR 11725, March 3, 2014; corrected March 11, 2014 (79 FR 13592)). We do not agree to revise paragraph (j) of this AD because serviceable assemblies are already defined in paragraph (h) of this AD. This definition applies to the entire AD. Also, preBoeing Service Bulletin 777–78–0051 plug assemblies do not meet the definition of serviceable, as specified in the service information. Request To Revise Definition of a Serviceable Assembly American Airlines (AA) requested that we revise paragraph (h) of the proposed AD to add another definition: Serviceable plug assemblies, as those maintained in accordance with the operator’s continued airworthiness maintenance program (CAMP), prior to issuance of Boeing Special Attention Service Bulletin 777–78–0051, Revision 3, dated August 23, 2012. AA explained that prior to release of Boeing Special Attention Service Bulletin 777–78– 0051, Revision 3, dated August 23, 2012, due to reported events of exhaust plug losses by other operators, AA recognized that multiple removals of the exhaust aft plug causes the 3/16″ nutplate locking feature to wear out, which could then result in loss of the aft plug. As a result, AA implemented a maintenance program as part of its CAMP, which offers a level of safety equivalent to that of Boeing Special Attention Service Bulletin 777–78– 0051, Revision 3, dated August 23, 2012. During every engine removal, for a refurbishment or overhaul shop visit, the pre-Boeing Special Attention Service Bulletin 777–78–0051, Revision 3, dated August 23, 2012, exhaust aft plug nutplates are replaced with new nutplates. In addition, AA stated that the holes are inspected for elongation and cracks in accordance with procedures VerDate Sep<11>2014 20:30 Oct 01, 2015 Jkt 238001 equivalent to Boeing Special Attention Service Bulletin 777–78–0051 inspection procedures. Model 777 Airplane Maintenance Manual Chapter 78–11–02–400–803–R00, requires that the minimum fastener run-on torque of 2 in-lbs is met during every installation of the aft exhaust plug. In addition, each of the exhaust aft plug fasteners receives a general visual check, using a ladder/ stand and a bright light, every 150 flight hours. AA expressed that it is currently the largest Model 777–200 Trent 800 operator in the worldwide fleet and has not lost an exhaust aft plug due to loose or missing fasteners, as its CAMP demonstrates an equivalent level of safety to the service information. As an alternative, AA requested that we revise the NPRM (79 FR 11725, March 3, 2014; corrected March 11, 2014 (79 FR 13592)) to include, as serviceable exhaust aft plugs, those maintained in accordance with the operator’s own maintenance program, such as AA’s approved CAMP prior to issuance of Boeing Special Attention Service Bulletin 777–78–0051, Revision 3, dated August 23, 2012, and to remain in service until the next engine removal for refurbishment or overhaul shop visit, or 60 months from the effective date of the AD, whichever is later. We do not agree to include the requested provision. The maintenance program described by AA is likely to be acceptable in lieu of direct compliance with portions of this AD; however, the description of that program provided in AA’s comment is not sufficient to serve as engineering data for the FAA to approve as an optional method of compliance in this AD. Operators can submit a request for approval of an alternative method of compliance (AMOC), with a more detailed proposal to use the maintenance program, if sufficient data are submitted to substantiate that the change would provide an acceptable level of safety. We have not changed this AD in this regard. Request To Change Compliance Time of Parts Installation Limitation Boeing and Cathay Pacific requested that we revise paragraph (j) of the proposed AD to change the installation limitation from the effective date of the AD to the compliance deadline for the AD. Boeing reasoned that paragraph (j) of the proposed AD currently creates an alternative and indeterminate compliance deadline. Boeing explained that during the compliance interval and prior to the AD deadline, operators may be required, due to unforeseen circumstances, to install a unit that is not a serviceable unit, and that under PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 59571 the current wording, this would unnecessarily ground the airplane. We do not agree to revise paragraph (j) of this AD to change the installation limitation from the effective date of the AD to the compliance date of the AD. Grace period compliance times are provided in ADs in recognition that an immediate unscheduled modification requirement would be disruptive. A grace period is included to give operators a reasonable period of time to schedule and perform actions that are required by the AD and that otherwise would not have occurred. A parts installation limitation is included in some cases to require that, if the parts affected by the AD are already being removed for a reason other than the AD itself, that opportunity to correct the unsafe condition should be taken. We determine whether such a parts installation limitation should be included in the AD, and what the specific requirements of the limitation will be, based on the risk level associated with the unsafe condition and the expected availability of required replacement parts. In this case, we made a determination that the risk warranted the consideration of a parts installation limitation. We also determined that sufficient parts would be available to meet that limitation, and that sufficient time to perform any required actions to make a nozzle assembly serviceable as defined in paragraph (h) of this AD would exist in situations where the nozzle might be removed in maintenance. Specifically, we considered the case of an unscheduled engine change where an operator may not have included a serviceable nozzle assembly with the replacement engine. Modification of a nozzle assembly to meet the definition of a serviceable nozzle can be performed in roughly the same or less elapsed time than it takes to perform the engine replacement itself. We did not foresee any other commonly occurring situation where an engine nozzle assembly would be removed for maintenance. However, as discussed in response to the comment issue ‘‘Request to Revise Definition of a Serviceable Assembly,’’ if an operator specifically and adequately addresses the management of this unsafe condition within its CAMP, we will consider AMOC approvals to allow installation of nozzle assemblies that do not meet the definition of serviceable nozzle in paragraph (h) of this AD. We clarified paragraph (j) of this AD as a result of these comments. We considered the explanatory statements about the intent of the parts installation limitation language used in several E:\FR\FM\02OCR1.SGM 02OCR1 59572 Federal Register / Vol. 80, No. 191 / Friday, October 2, 2015 / Rules and Regulations recent ADs, and determined that different language should be used in this case to more clearly convey the intent of the parts installation limitation contained in this AD. We have added the words ‘‘or re-install’’ to paragraph (j) to clarify that any installation of a nozzle assembly, regardless of the reason for the removal of the nozzle assembly and regardless of the source of the replacement nozzle assembly, is subject to the parts installation limitation of paragraph (j) of this AD. asabaliauskas on DSK5VPTVN1PROD with RULES Request To Clarify Paragraph (j) of the Proposed AD AA requested that we clarify paragraph (j) of the proposed AD. AA explained that paragraph (j) of the proposed AD allows that only a serviceable turbine exhaust plug assembly may be installed on any airplane as of the effective date of this AD, while paragraph (i) of the proposed AD requires a compliance time within a certain time after the effective date of this AD, without any referral to serviceable turbine exhaust plug assembly. AA reasoned that as written, these steps are confusing and could lead operators to believe the actions required by the AD are due as of the effective date of this AD. We agree with the commenter and have clarified paragraph (j) of this AD by including references to paragraphs (h)(1) and (h)(2) of this AD. Request To Clarify the AMOC Paragraph Boeing requested that we revise paragraph (k)(3) of the proposed AD (paragraph (l)(3) of this AD) to indicate that an AMOC, approved for a repaired serviceable unit is to be attached to, and travel with, the repaired serviceable unit. Boeing explained that the AMOC approval should apply to the deviation on the serviceable unit and thereby travel with the serviceable unit, which is rotable and could be installed on numerous airplanes during its service life. Boeing also explained that a unit repaired in accordance with an approved AMOC will fulfill the intent of airplane safety when the unit is installed on an airplane, and that the unit will be in compliance with the AD as long as the part is serviceable as defined by the AD. We agree with the commenter and have revised paragraph (l)(3) of this AD accordingly. Request To Use the CAMP AA requested that we revise the NPRM (79 FR 11725, March 3, 2014; corrected March 11, 2014 (79 FR 13592)), to include language that allows VerDate Sep<11>2014 20:30 Oct 01, 2015 Jkt 238001 the optional re-identification of the exhaust plug with the correct postBoeing Special Attention Service Bulletin 777–78–0051, part number identity in accordance with a method approved by the operator’s approved CAMP, as the CAMP provides an equivalent level of safety. AA explained that prior to the release of Boeing Special Attention Service Bulletin 777– 78–0051, Revision 3, dated August 23, 2012, AA implemented a maintenance program to install data plates on the forward and aft exhaust plug. The plates were installed because the manufacturer part number and serial number, which were chemical-etched on the exhaust plug skin by the manufacturer, were no longer legible. AA stated that the data plates contain the original part number, a company-assigned serial number, and the text ‘‘MATCHED SET. DO NOT SEPARATE.’’ AA added that the installed identification plates are in the same location as, but a different length than, the plates specified in Boeing Special Attention Service Bulletin 777– 78–0051, Revision 3, dated August 23, 2012. We agree to allow alternative permanent part-marking methods. If the markings contain the required information and are permanent, the intent of the marking requirement is addressed, and additional flexibility is provided to operators. Therefore, partmarking methods for the CAMP might be approved, provided that the markings are permanent and contain the information specified in Boeing Special Attention Service Bulletin 777–78– 0051, Revision 4, dated February 7, 2014. We have added this information to paragraph (g) of this AD accordingly. Request To Eliminate AMOC Approval Requirement for Previous Repairs AA requested that we revise paragraph (h) of the proposed AD, to allow repairs accomplished prior to the release of this AD, in accordance with Boeing instructions and approved per 14 CFR part 121.379, or a Boeing ODA, to be included as acceptable repairs in this AD, without the requirement to obtain a Boeing ODA AMOC or Seattle Aircraft Certification Office AMOC approval. AA explained that, prior to release of the NPRM (79 FR 11725, March 3, 2014; corrected March 11, 2014 (79 FR 13592)); exhaust aft plugs have received repairs at the exhaust aft plug mate line during inspection or during incorporation of Boeing Special Attention Service Bulletin 777–78– 0051, Revision 3, dated August 23, 2012, utilizing procedures provided by Boeing without Boeing ODA approval; PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 rather, the repair was approved per 14 CFR part 121.379. AA expressed that paragraph (h) of the proposed AD specifies using a repair method approved in accordance with the procedures specified in paragraph (k) of the proposed AD, and these previously accomplished repairs, which followed Boeing repair instructions, offer an equivalent level of safety to the NPRM. We partially agree with the request. We agree to add paragraph (l)(4) in this AD to eliminate the requirement for subsequent AMOC approval for repairs that were previously approved by the Boeing ODA, using an FAA Form 8100– 9, and having met the requirements of paragraph (h) of this AD, for the definition of serviceable turbine exhaust plug assemblies. We are confident that the Boeing ODA repair approval process ensures that each repair is reviewed by qualified engineering staff with knowledge of the original airplane design and compliance substantiation. At the same time, we want to ensure that those repairs would have a configuration that meets the definition of serviceable turbine exhaust plug assemblies as defined in the service information. We have added paragraph (l)(4) in this AD to state that repairs approved prior to the effective date of this AD, by the Boeing ODA using FAA Form 8100–9, and having met the requirements of paragraph (h) of this AD for the definition of serviceable turbine exhaust plug assemblies, do not require AMOC approval. We disagree, however, to eliminate the AMOC approval requirement for repairs approved by other means. Even though Boeing Service Engineering may have provided a ‘‘no technical objection’’ statement, qualified engineering staff with knowledge of the original airplane design and compliance substantiation may not have been involved in evaluating the repair. We have not changed this AD in this regard. Additional Changes to This AD We have revised this AD to refer to Boeing Special Attention Service Bulletin 777–78–0051, Revision 4, dated February 7, 2014, as the appropriate source of service information for the required actions. Among other things, this service information adds Group 2 airplanes to paragraph 1.E., ‘‘Compliance;’’ includes a maintenance records check; adds a general visual inspection to determine the diameter of the bolt used at the forward and aft plug interface; and adds applicable corrective actions—all of which we have clarified in new paragraph (g)(4) of this AD. Paragraphs (g)(3) and (c) of the proposed AD already accounted for the Group 2 E:\FR\FM\02OCR1.SGM 02OCR1 59573 Federal Register / Vol. 80, No. 191 / Friday, October 2, 2015 / Rules and Regulations airplanes defined in Boeing Special Attention Service Bulletin 777–78– 0051, Revision 4, dated February 7, 2014. Paragraph (g)(2) of the proposed AD accounted for the required actions. We have also added a new paragraph (k) to this AD to provide credit for certain actions, if those actions were performed before the effective date of this AD using Boeing Special Attention Service Bulletin 777–78–0051, Revision 3, dated August 23, 2012. We have redesignated the subsequent paragraphs of this AD 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 (79 FR 11725, March 3, 2014; corrected March 11, 2014 (79 FR 13592)) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 11725, March 3, 2014; corrected March 11, 2014 (79 FR 13592)). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. 0051, Revision 4, dated February 7, 2014. Among other things, this service information adds Group 2 airplanes to paragraph 1.E., ‘‘Compliance;’’ includes a maintenance records check; adds a general visual inspection to determine the diameter of the bolt used at the forward and aft plug interface; and adds applicable 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 of this AD. Related Service Information Under 1 CFR Part 51 We estimate that this AD affects 35 airplanes of U.S. registry. We estimate the following costs to comply with this AD: We reviewed Boeing Special Attention Service Bulletin 777–78– Costs of Compliance ESTIMATED COSTS Action Labor cost Installation ....................................................... General visual inspection ................................ 5 work-hours × $85 per hour = $425 ............. 2 work-hours × $85 per hour = $170 ............. We estimate the following costs to do any necessary replacement that would be required based on the results of the inspection. We have no way of Cost per product Parts cost $0 $0 Cost on U.S. operators $425 $170 $14,875 $5,950 determining the number of aircraft that might need this replacement: ON-CONDITION COSTS Labor cost Parts cost Cost per product 5 work-hours × $85 per hour = $425 ........................... $0 $425 Action Replacement (replacing the inch bolts). ⁄ -inch bolts with 3 16 ⁄ - 14 asabaliauskas on DSK5VPTVN1PROD with RULES Authority for This Rulemaking Regulatory Findings List of Subjects in 14 CFR Part 39 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. 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. Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. VerDate Sep<11>2014 20:30 Oct 01, 2015 Jkt 238001 PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 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 adding the following new airworthiness directive (AD): ■ 2015–19–16 The Boeing Company: Amendment 39–18278; Docket No. FAA–2014–0128; Directorate Identifier 2013–NM–133–AD. E:\FR\FM\02OCR1.SGM 02OCR1 59574 Federal Register / Vol. 80, No. 191 / Friday, October 2, 2015 / Rules and Regulations (a) Effective Date This AD is effective November 6, 2015. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 777–200, –200LR, –300,–300ER, and 777F series airplanes; certificated in any category; equipped with Rolls-Royce Trent 800 series engines. (d) Subject Air Transport Association (ATA) of America Code 78, Engine Exhaust. (h) Definition of Serviceable Assembly (e) Unsafe Condition This AD was prompted by reports of inflight separation of the engine’s aft plug from the forward plug, which are the two parts of the turbine exhaust plug assembly. We are issuing this AD to prevent separation of the aft plug from the forward plug of the turbine exhaust plug assembly, which could result in parts departing the airplane and hitting the empennage or hitting a person on the ground, and destabilizing the airplane during a critical flight phase; parts remaining on a runway could cause damage to another airplane. asabaliauskas on DSK5VPTVN1PROD with RULES (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Installation and General Visual Inspection At the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 777–78– 0051, Revision 4, dated February 7, 2014, except as provided by paragraph (i) of this AD, do the applicable 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 777–78– 0051, Revision 4, dated February 7, 2014. Alternative part marking methods are allowed for the requirements of this paragraph, if approved by the FAA principal maintenance inspector, provided that the markings are permanent and contain the information required by Boeing Special Attention Service Bulletin 777–78–0051, Revision 4, dated February 7, 2014. (1) For airplanes identified as Group 1, Configuration 1, in Boeing Special Attention Service Bulletin 777–78–0051, Revision 4, dated February 7, 2014: Install a serviceable turbine exhaust plug assembly. (2) For airplanes identified as Group 1, Configurations 2 and 3, in Boeing Special Attention Service Bulletin 777–78–0051, Revision 4, dated February 7, 2014: Do a general visual inspection to determine the diameter of the bolt used at the forward and aft plug interface, and before further flight, do all applicable corrective actions. (3) For airplanes listed in paragraph (c) of this AD that are not listed in the ‘‘Effectivity’’ section of Boeing Special Attention Service Bulletin 777–78–0051, Revision 4, dated February 7, 2014: Do a general visual inspection to determine if a serviceable VerDate Sep<11>2014 20:30 Oct 01, 2015 Jkt 238001 turbine exhaust plug assembly is installed. If a serviceable turbine exhaust plug assembly is not installed, before further flight, install a serviceable turbine exhaust plug assembly. (4) For airplanes identified as Group 2, in Boeing Special Attention Service Bulletin 777–78–0051, Revision 4, dated February 7, 2014: Do a maintenance records check to determine affected turbine exhaust plug assemblies, and for affected assemblies, do a general visual inspection to determine the diameter of the bolt used at the forward and aft plug interface, and before further flight, do all applicable corrective actions. For the purposes of this AD, an acceptable serviceable turbine exhaust plug assembly must meet the conditions specified in paragraph (h)(1) or (h)(2) of this AD. (1) A new assembly with part number 314W5520–22. (2) A serviceable assembly as defined in the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–78– 0051, Revision 4, dated February 7, 2014; except, for any assembly on which the actions specified in Part 2 or Part 3 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–78– 0051, Revision 4, dated February 7, 2014, are done, and Boeing Special Attention Service Bulletin 777–78–0051, Revision 4, dated February 7, 2014, specifies to contact Boeing for repair instructions, this AD requires repair before further flight, using a method approved in accordance with the procedures specified in paragraph (l)(1) of this AD. (i) Exception to Service Information Specifications Where paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 777–78–0051, Revision 4, dated February 7, 2014, specifies a compliance time ‘‘after the Revision 3 date of this service bulletin,’’ or ‘‘after the Revision 4 date of this service bulletin,’’ this AD requires compliance within the applicable time after the effective date of this AD. (l) 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 (m) 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 the airplane, and the approval must specifically refer to this AD. An AMOC approved as described in this paragraph for a specific serviceable nozzle assembly may be transferred with that nozzle assembly to another aircraft without an additional AMOC approval being required. (4) Repairs approved prior to the effective date of this AD by the Boeing ODA do not require AMOC approval if those repairs were approved using FAA Form 8100–9 and those repairs meet the definition of a serviceable assembly contained in the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–78–0051, Revision 4, dated February 7, 2014. (j) Parts Installation Limitation As of the effective date of this AD, only a serviceable turbine exhaust plug assembly that meets the requirements of paragraph (h)(1) or (h)(2) of this AD may be installed or reinstalled on any airplane. (m) Related Information (1) For more information about this AD, contact Kevin Nguyen, Aerospace Engineer, Propulsion Branch, ANM–140S, Seattle Aircraft Certification Office (ACO) FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6501; fax: 425–917–6590; email: kevin.nguyen@faa.gov. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (n)(3) and (n)(4) of this AD. (k) Credit for Previous Actions This paragraph provides credit for the actions specified in paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Boeing Special Attention Service Bulletin 777–78–0051, Revision 3, dated August 23, 2012 (which is not incorporated by reference in this AD), provided that for Group 1, Configuration 2, airplanes, on which the condition defined in Table 2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 777–78–0051, Revision 3, dated August 23, 2012, was found (i.e., only 1⁄4 inch diameter bolts are found installed at all 33 locations forward and aft plug interface), the reidentification of the forward and aft plug was done before further flight after the inspection. (n) 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. (i) Boeing Special Attention Service Bulletin 777–78–0051, Revision 4, dated February 7, 2014. (ii) Reserved. (3) 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 PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 E:\FR\FM\02OCR1.SGM 02OCR1 Federal Register / Vol. 80, No. 191 / Friday, October 2, 2015 / Rules and Regulations 206–544–5000, extension 1; fax 206–766– 5680; Internet https:// www.myboeingfleet.com. (4) 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on September 16, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–24677 Filed 10–1–15; 8:45 am] BILLING CODE 4910–13–P COMMODITY FUTURES TRADING COMMISSION 17 CFR Parts 15, 18, 36, 40, 140 RIN 3038–AE10 Repeal of the Exempt Commercial Market and Exempt Board of Trade Exemptions Commodity Futures Trading Commission. ACTION: Final rule. AGENCY: The Commodity Futures Trading Commission (the ‘‘Commission’’) is taking final action to revise its regulations by removing the part 36 regulations. Those regulations implemented provisions of the Commodity Exchange Act (‘‘CEA’’) that established exempt boards of trade and exempt commercial markets—two categories of derivatives-trading platforms that were eliminated from the CEA by the Dodd-Frank Wall Street Reform and Consumer Protection Act (the ‘‘Dodd-Frank Act’’). This action also removes various cross-references in other Commission regulations implicating exempt boards of trade and exempt commercial markets. DATES: This rulemaking is effective on October 2, 2015. FOR FURTHER INFORMATION CONTACT: Commodity Futures Trading Commission, Three Lafayette Centre, 1155 21st Street NW., Washington, DC 20581; Dana R. Brown, Division of Market Oversight, telephone (202) 418– 5093 and email dbrown@cftc.gov. SUPPLEMENTARY INFORMATION: I. Background On July 21, 2010, President Obama signed the Dodd-Frank Act into law. 1 Title VII of the Dodd-Frank Act 2 amended the CEA 3 to establish a comprehensive framework for the regulation of over-the-counter derivatives, also known as swaps. Among other reforms, Title VII requires that any person who operates a facility to trade swaps register as a designated contract market (‘‘DCM’’) or a swap execution facility (‘‘SEF’’); 4 the latter is a category of trading market newly established under the law. Concurrently, Title VII eliminated from the CEA two categories of exempt markets for the trading of derivatives originally established in the CEA by the Commodity Futures Modernization Act of 2000 (‘‘CFMA’’): 5 exempt commercial markets (‘‘ECMs’’) and exempt boards of trade (‘‘EBOTs’’). Under the CFMA’s revisions to the CEA, ECMs could trade exempt commodities 6 (i.e. any commodity other than an excluded commodity 7 and agricultural commodities) on electronic trading facilities between eligible commercial entities 8 without complying with comprehensive designation criteria and core principles that were applicable to designated contract markets. A facility that elected to operate as an ECM was generally exempt from regulation, but was still required to comply with certain informational and recordkeeping requirements, if the market satisfied the asabaliauskas on DSK5VPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 20:30 Oct 01, 2015 Jkt 238001 1 Public Law 111–203, 124 Stat. 1376 (July 21, 2010). 2 Pursuant to Section 701 of the Dodd-Frank Act, Title VII may be cited as the ‘‘Wall Street Transparency and Accountability Act of 2010.’’ 3 7 U.S.C. 1 et seq. (2012). 4 Dodd-Frank Act Section 733 (amending the CEA to add new section 5h). 5 Public Law 106–554, 114 Stat. 2763 (December 21, 2000). 6 See CFMA Section 101(4) (amending CEA to add definition of ‘‘Exempt Commodity,’’ currently codified as CEA Section 1(a)(20), 7 U.S.C. 1a(20) (2012). 7 ‘‘Excluded Commodity’’ is also a statutorily defined term, currently codified as CEA Section 1(a)(19), 7 U.S.C. 1a(19) (2012). Generally characterized, the term captures, among other things specified financial instruments, measures, and indexes (e.g., securities and security indexes, currencies, interest rates, debt instruments, and credit ratings); any ‘‘other rate, differential, index, or measure of economic or commercial risk, return or value’’ not substantially based on the value of a narrow commodity group or solely based on a commodity or commodities with no cash value; and other economic or commercial indexes, or occurrences and contingencies associated with an economic consequence, beyond the control of parties to the relevant contract, agreement or transaction. 8 The definition of ‘‘Eligible Commercial Entity’’ is found in Section 1a(17) of the CEA. 7 U.S.C. 1a(17) (2006). PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 59575 conditions for the exemption found in Sections 2(h)(3) through (5) of the CEA, 7 U.S.C. 2(h)(3)–(5), including a requirement that the ECM notify the Commission of its intent to rely upon the exemption.9 Under CEA Section 5d, 7 U.S.C. 7a– 3, EBOTs were facilities that traded commodities (other than securities or securities indexes) that had a nearly inexhaustible deliverable supply and either no cash market or a cash market so liquid that any contract traded on the commodity was highly unlikely to be susceptible to manipulation. EBOT transactions were limited to eligible contract participants 10 and subject to minimal trading prohibitions, including anti-fraud and anti-manipulation restrictions. EBOTs were required to file notice with the Commission of their election to operate as an EBOT.11 Section 723 of the Dodd-Frank Act repealed CEA Section 2(h)(3) as it then existed,12 thus eliminating the ECM category. Section 734 of the Dodd-Frank Act similarly repealed CEA Section 5d,13 thus eliminating the EBOT category. Both Sections 723 and 734 of the Dodd-Frank Act contain grandfather provisions allowing existing ECMs and EBOTs to petition the Commission to continue to operate as ECMs and EBOTs subject to the requirements of the CEA Sections 2(h)(3) and 5d, respectively, for a limited period of time.14 Pursuant to these grandfather provisions, the Commission issued an order in September 2010 granting petitioning ECMs and EBOTs up to one year of grandfather relief from the general effective date of the Dodd-Frank Act amendments to the CEA (‘‘Grandfather Relief Order’’).15 Subsequent to the Grandfather Relief Order, the Commission issued a series 9 The Commission’s part 36 regulations established similar requirements for EBOTs. 10 The definition of ‘‘Eligible Contract Participant’’ is found in Section 1a(18) of the CEA, 7 U.S.C. 1a(18) (2012). 11 The Commission’s Part 36 regulations established similar requirements for ECMs. 12 The Dodd-Frank Act amended Section 2(h) of the CEA effective July 16, 2011, H.R. 4173, Section 723(a)(1), Public Law 111–203, 124 Stat. 1376, by striking existing subsection (h)—‘‘Transactions in exempt commodities’’ and inserting new subsection (h)—‘‘Clearing requirement’’ not addressed to exempt commercial markets. 13 The Dodd-Frank Act repealed Section 5d of the CEA effective July 16, 2011, H.R. 4173, Section 734(a), Public Law 111–203, 124 Stat. 1376 (2010). 14 ECMs and EBOTs were permitted to continue operations until July 16, 2012 pursuant to a grandfather relief order issued by the Commission pursuant to Sections 723(c)(2)(B) and 734(c)(2) of the Dodd-Frank Act, respectively. 15 75 FR 56513 (September 16, 2010). E:\FR\FM\02OCR1.SGM 02OCR1

Agencies

[Federal Register Volume 80, Number 191 (Friday, October 2, 2015)]
[Rules and Regulations]
[Pages 59570-59575]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-24677]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0128; Directorate Identifier 2013-NM-133-AD; 
Amendment 39-18278; AD 2015-19-16]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for The 
Boeing Company Model 777 airplanes equipped with Rolls-Royce Trent 800 
series engines. This AD was prompted by reports of in-flight separation 
of the engine's aft plug from the forward plug, which are the two parts 
of the turbine exhaust plug assembly. This AD requires installation of 
a serviceable turbine exhaust plug assembly (for certain airplanes), 
and a general visual inspection (for certain airplanes) to determine 
the diameter of the bolt used at the forward and aft plug interface, 
and applicable corrective actions. We are issuing this AD to prevent 
separation of the aft plug from the forward plug of the turbine exhaust 
plug assembly, which could result in parts departing the airplane and 
hitting the empennage, and destabilizing the airplane during a critical 
flight phase. In addition, parts remaining on a runway could pose a 
hazard to another airplane.

DATES: This AD is effective November 6, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of November 6, 
2015.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may 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-2014-
0128.

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-2014-
0128; 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: Kevin Nguyen, Aerospace Engineer, 
Propulsion Branch, ANM-140S, Seattle Aircraft Certification Office 
(ACO), FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-
917-6501; fax: 425-917-6590; email: kevin.nguyen@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to The Boeing Company Model 
777 airplanes equipped with Rolls-Royce Trent 800 series engines. The 
NPRM published in the Federal Register on March 3, 2014 (79 FR 11725); 
corrected March 11, 2014 (79 FR 13592). The NPRM was prompted by 
reports of in-flight separation of the engine's aft plug from the 
forward plug, which are the two parts of the turbine exhaust plug 
assembly. The NPRM proposed to require installation of a serviceable 
turbine exhaust plug assembly (for certain airplanes), and a general 
visual inspection (for certain airplanes) to determine the diameter of 
the bolt used at the forward and aft plug interface, and applicable 
corrective actions. We are issuing this AD to prevent separation of the 
aft plug from the forward plug of the turbine exhaust plug assembly, 
which could result in parts departing the airplane and hitting the 
empennage, and destabilizing the airplane during a critical flight 
phase. In addition, parts remaining on a runway could pose a hazard to 
another airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (79 
FR 11725, March 3, 2014; corrected March 11, 2014 (79 FR 13592); and 
the FAA's response to each comment.

Request To Match Compliance Time

    Cathay Pacific requested that we ensure that the AD compliance date 
will be the same as the compliance time of Boeing Special Attention 
Service Bulletin 777-78-0051, Revision 3, dated August 23, 2012; or 
Boeing Special Attention Service Bulletin 777-78-0051, Revision 4, 
dated February 7, 2014. Cathay Pacific reasoned that paragraph (i) of 
the proposed AD specified compliance within 60 months after the 
effective date of the proposed AD, and both revisions of this service 
information specify a compliance time that is within 60 months after 
the Revision 3 date of the service bulletin.
    We infer that Cathay Pacific is requesting that we reduce the 
compliance time of this final rule to match the compliance time listed 
in the service information. We do not agree with the commenter's 
request. In developing an appropriate compliance time for this action, 
we considered not only the degree of urgency associated with addressing 
the subject unsafe condition, but the manufacturer's recommendation for 
an appropriate compliance time, the time required for the rulemaking 
process, the availability of required parts, and the practical aspect 
of installing the required modification within an interval of time that 
corresponds to the typical scheduled maintenance for the majority of 
affected operators. Under the provisions of paragraph (l) of this AD,

[[Page 59571]]

we may approve requests for adjustments to the compliance time, if data 
are submitted to substantiate that such an adjustment would provide an 
acceptable level of safety. We have not changed the AD in this regard.

Request To Define ``Serviceable'' To Include Pre-Boeing Service 
Bulletin 777-78-0051 Plug Assemblies

    Cathay Pacific requested that we revise paragraph (j) of the 
proposed AD; corrected March 11, 2014 (79 FR 13592) to define 
``serviceable'' plug assemblies. Cathay Pacific reasoned that both pre- 
and post-Boeing Service Bulletin 777-78-0051 plug assemblies can be 
installed, and the modification can be completed before the required 
compliance time of the NPRM (79 FR 11725, March 3, 2014; corrected 
March 11, 2014 (79 FR 13592)).
    We do not agree to revise paragraph (j) of this AD because 
serviceable assemblies are already defined in paragraph (h) of this AD. 
This definition applies to the entire AD. Also, pre- Boeing Service 
Bulletin 777-78-0051 plug assemblies do not meet the definition of 
serviceable, as specified in the service information.

Request To Revise Definition of a Serviceable Assembly

    American Airlines (AA) requested that we revise paragraph (h) of 
the proposed AD to add another definition: Serviceable plug assemblies, 
as those maintained in accordance with the operator's continued 
airworthiness maintenance program (CAMP), prior to issuance of Boeing 
Special Attention Service Bulletin 777-78-0051, Revision 3, dated 
August 23, 2012. AA explained that prior to release of Boeing Special 
Attention Service Bulletin 777-78-0051, Revision 3, dated August 23, 
2012, due to reported events of exhaust plug losses by other operators, 
AA recognized that multiple removals of the exhaust aft plug causes the 
3/16'' nutplate locking feature to wear out, which could then result in 
loss of the aft plug. As a result, AA implemented a maintenance program 
as part of its CAMP, which offers a level of safety equivalent to that 
of Boeing Special Attention Service Bulletin 777-78-0051, Revision 3, 
dated August 23, 2012. During every engine removal, for a refurbishment 
or overhaul shop visit, the pre-Boeing Special Attention Service 
Bulletin 777-78-0051, Revision 3, dated August 23, 2012, exhaust aft 
plug nutplates are replaced with new nutplates.
    In addition, AA stated that the holes are inspected for elongation 
and cracks in accordance with procedures equivalent to Boeing Special 
Attention Service Bulletin 777-78-0051 inspection procedures. Model 777 
Airplane Maintenance Manual Chapter 78-11-02-400-803-R00, requires that 
the minimum fastener run[hyphen]on torque of 2 in[hyphen]lbs is met 
during every installation of the aft exhaust plug. In addition, each of 
the exhaust aft plug fasteners receives a general visual check, using a 
ladder/stand and a bright light, every 150 flight hours. AA expressed 
that it is currently the largest Model 777-200 Trent 800 operator in 
the worldwide fleet and has not lost an exhaust aft plug due to loose 
or missing fasteners, as its CAMP demonstrates an equivalent level of 
safety to the service information.
    As an alternative, AA requested that we revise the NPRM (79 FR 
11725, March 3, 2014; corrected March 11, 2014 (79 FR 13592)) to 
include, as serviceable exhaust aft plugs, those maintained in 
accordance with the operator's own maintenance program, such as AA's 
approved CAMP prior to issuance of Boeing Special Attention Service 
Bulletin 777-78-0051, Revision 3, dated August 23, 2012, and to remain 
in service until the next engine removal for refurbishment or overhaul 
shop visit, or 60 months from the effective date of the AD, whichever 
is later.
    We do not agree to include the requested provision. The maintenance 
program described by AA is likely to be acceptable in lieu of direct 
compliance with portions of this AD; however, the description of that 
program provided in AA's comment is not sufficient to serve as 
engineering data for the FAA to approve as an optional method of 
compliance in this AD. Operators can submit a request for approval of 
an alternative method of compliance (AMOC), with a more detailed 
proposal to use the maintenance program, if sufficient data are 
submitted to substantiate that the change would provide an acceptable 
level of safety. We have not changed this AD in this regard.

Request To Change Compliance Time of Parts Installation Limitation

    Boeing and Cathay Pacific requested that we revise paragraph (j) of 
the proposed AD to change the installation limitation from the 
effective date of the AD to the compliance deadline for the AD. Boeing 
reasoned that paragraph (j) of the proposed AD currently creates an 
alternative and indeterminate compliance deadline. Boeing explained 
that during the compliance interval and prior to the AD deadline, 
operators may be required, due to unforeseen circumstances, to install 
a unit that is not a serviceable unit, and that under the current 
wording, this would unnecessarily ground the airplane.
    We do not agree to revise paragraph (j) of this AD to change the 
installation limitation from the effective date of the AD to the 
compliance date of the AD. Grace period compliance times are provided 
in ADs in recognition that an immediate unscheduled modification 
requirement would be disruptive. A grace period is included to give 
operators a reasonable period of time to schedule and perform actions 
that are required by the AD and that otherwise would not have occurred. 
A parts installation limitation is included in some cases to require 
that, if the parts affected by the AD are already being removed for a 
reason other than the AD itself, that opportunity to correct the unsafe 
condition should be taken. We determine whether such a parts 
installation limitation should be included in the AD, and what the 
specific requirements of the limitation will be, based on the risk 
level associated with the unsafe condition and the expected 
availability of required replacement parts.
    In this case, we made a determination that the risk warranted the 
consideration of a parts installation limitation. We also determined 
that sufficient parts would be available to meet that limitation, and 
that sufficient time to perform any required actions to make a nozzle 
assembly serviceable as defined in paragraph (h) of this AD would exist 
in situations where the nozzle might be removed in maintenance. 
Specifically, we considered the case of an unscheduled engine change 
where an operator may not have included a serviceable nozzle assembly 
with the replacement engine. Modification of a nozzle assembly to meet 
the definition of a serviceable nozzle can be performed in roughly the 
same or less elapsed time than it takes to perform the engine 
replacement itself. We did not foresee any other commonly occurring 
situation where an engine nozzle assembly would be removed for 
maintenance. However, as discussed in response to the comment issue 
``Request to Revise Definition of a Serviceable Assembly,'' if an 
operator specifically and adequately addresses the management of this 
unsafe condition within its CAMP, we will consider AMOC approvals to 
allow installation of nozzle assemblies that do not meet the definition 
of serviceable nozzle in paragraph (h) of this AD.
    We clarified paragraph (j) of this AD as a result of these 
comments. We considered the explanatory statements about the intent of 
the parts installation limitation language used in several

[[Page 59572]]

recent ADs, and determined that different language should be used in 
this case to more clearly convey the intent of the parts installation 
limitation contained in this AD. We have added the words ``or re-
install'' to paragraph (j) to clarify that any installation of a nozzle 
assembly, regardless of the reason for the removal of the nozzle 
assembly and regardless of the source of the replacement nozzle 
assembly, is subject to the parts installation limitation of paragraph 
(j) of this AD.

Request To Clarify Paragraph (j) of the Proposed AD

    AA requested that we clarify paragraph (j) of the proposed AD. AA 
explained that paragraph (j) of the proposed AD allows that only a 
serviceable turbine exhaust plug assembly may be installed on any 
airplane as of the effective date of this AD, while paragraph (i) of 
the proposed AD requires a compliance time within a certain time after 
the effective date of this AD, without any referral to serviceable 
turbine exhaust plug assembly. AA reasoned that as written, these steps 
are confusing and could lead operators to believe the actions required 
by the AD are due as of the effective date of this AD.
    We agree with the commenter and have clarified paragraph (j) of 
this AD by including references to paragraphs (h)(1) and (h)(2) of this 
AD.

Request To Clarify the AMOC Paragraph

    Boeing requested that we revise paragraph (k)(3) of the proposed AD 
(paragraph (l)(3) of this AD) to indicate that an AMOC, approved for a 
repaired serviceable unit is to be attached to, and travel with, the 
repaired serviceable unit. Boeing explained that the AMOC approval 
should apply to the deviation on the serviceable unit and thereby 
travel with the serviceable unit, which is rotable and could be 
installed on numerous airplanes during its service life. Boeing also 
explained that a unit repaired in accordance with an approved AMOC will 
fulfill the intent of airplane safety when the unit is installed on an 
airplane, and that the unit will be in compliance with the AD as long 
as the part is serviceable as defined by the AD.
    We agree with the commenter and have revised paragraph (l)(3) of 
this AD accordingly.

Request To Use the CAMP

    AA requested that we revise the NPRM (79 FR 11725, March 3, 2014; 
corrected March 11, 2014 (79 FR 13592)), to include language that 
allows the optional re-identification of the exhaust plug with the 
correct post-Boeing Special Attention Service Bulletin 777-78-0051, 
part number identity in accordance with a method approved by the 
operator's approved CAMP, as the CAMP provides an equivalent level of 
safety. AA explained that prior to the release of Boeing Special 
Attention Service Bulletin 777-78-0051, Revision 3, dated August 23, 
2012, AA implemented a maintenance program to install data plates on 
the forward and aft exhaust plug. The plates were installed because the 
manufacturer part number and serial number, which were chemical-etched 
on the exhaust plug skin by the manufacturer, were no longer legible. 
AA stated that the data plates contain the original part number, a 
company-assigned serial number, and the text ``MATCHED SET. DO NOT 
SEPARATE.'' AA added that the installed identification plates are in 
the same location as, but a different length than, the plates specified 
in Boeing Special Attention Service Bulletin 777-78-0051, Revision 3, 
dated August 23, 2012.
    We agree to allow alternative permanent part-marking methods. If 
the markings contain the required information and are permanent, the 
intent of the marking requirement is addressed, and additional 
flexibility is provided to operators. Therefore, part-marking methods 
for the CAMP might be approved, provided that the markings are 
permanent and contain the information specified in Boeing Special 
Attention Service Bulletin 777-78-0051, Revision 4, dated February 7, 
2014. We have added this information to paragraph (g) of this AD 
accordingly.

Request To Eliminate AMOC Approval Requirement for Previous Repairs

    AA requested that we revise paragraph (h) of the proposed AD, to 
allow repairs accomplished prior to the release of this AD, in 
accordance with Boeing instructions and approved per 14 CFR part 
121.379, or a Boeing ODA, to be included as acceptable repairs in this 
AD, without the requirement to obtain a Boeing ODA AMOC or Seattle 
Aircraft Certification Office AMOC approval.
    AA explained that, prior to release of the NPRM (79 FR 11725, March 
3, 2014; corrected March 11, 2014 (79 FR 13592)); exhaust aft plugs 
have received repairs at the exhaust aft plug mate line during 
inspection or during incorporation of Boeing Special Attention Service 
Bulletin 777-78-0051, Revision 3, dated August 23, 2012, utilizing 
procedures provided by Boeing without Boeing ODA approval; rather, the 
repair was approved per 14 CFR part 121.379. AA expressed that 
paragraph (h) of the proposed AD specifies using a repair method 
approved in accordance with the procedures specified in paragraph (k) 
of the proposed AD, and these previously accomplished repairs, which 
followed Boeing repair instructions, offer an equivalent level of 
safety to the NPRM.
    We partially agree with the request. We agree to add paragraph 
(l)(4) in this AD to eliminate the requirement for subsequent AMOC 
approval for repairs that were previously approved by the Boeing ODA, 
using an FAA Form 8100-9, and having met the requirements of paragraph 
(h) of this AD, for the definition of serviceable turbine exhaust plug 
assemblies. We are confident that the Boeing ODA repair approval 
process ensures that each repair is reviewed by qualified engineering 
staff with knowledge of the original airplane design and compliance 
substantiation. At the same time, we want to ensure that those repairs 
would have a configuration that meets the definition of serviceable 
turbine exhaust plug assemblies as defined in the service information. 
We have added paragraph (l)(4) in this AD to state that repairs 
approved prior to the effective date of this AD, by the Boeing ODA 
using FAA Form 8100-9, and having met the requirements of paragraph (h) 
of this AD for the definition of serviceable turbine exhaust plug 
assemblies, do not require AMOC approval.
    We disagree, however, to eliminate the AMOC approval requirement 
for repairs approved by other means. Even though Boeing Service 
Engineering may have provided a ``no technical objection'' statement, 
qualified engineering staff with knowledge of the original airplane 
design and compliance substantiation may not have been involved in 
evaluating the repair. We have not changed this AD in this regard.

Additional Changes to This AD

    We have revised this AD to refer to Boeing Special Attention 
Service Bulletin 777-78-0051, Revision 4, dated February 7, 2014, as 
the appropriate source of service information for the required actions. 
Among other things, this service information adds Group 2 airplanes to 
paragraph 1.E., ``Compliance;'' includes a maintenance records check; 
adds a general visual inspection to determine the diameter of the bolt 
used at the forward and aft plug interface; and adds applicable 
corrective actions--all of which we have clarified in new paragraph 
(g)(4) of this AD. Paragraphs (g)(3) and (c) of the proposed AD already 
accounted for the Group 2

[[Page 59573]]

airplanes defined in Boeing Special Attention Service Bulletin 777-78-
0051, Revision 4, dated February 7, 2014. Paragraph (g)(2) of the 
proposed AD accounted for the required actions.
    We have also added a new paragraph (k) to this AD to provide credit 
for certain actions, if those actions were performed before the 
effective date of this AD using Boeing Special Attention Service 
Bulletin 777-78-0051, Revision 3, dated August 23, 2012. We have 
redesignated the subsequent paragraphs of this AD 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 (79 FR 11725, March 3, 2014; corrected March 11, 2014 (79 FR 
13592)) for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 11725, March 3, 2014; corrected 
March 11, 2014 (79 FR 13592)).
    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 Special Attention Service Bulletin 777-78-0051, 
Revision 4, dated February 7, 2014. Among other things, this service 
information adds Group 2 airplanes to paragraph 1.E., ``Compliance;'' 
includes a maintenance records check; adds a general visual inspection 
to determine the diameter of the bolt used at the forward and aft plug 
interface; and adds applicable 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 of this AD.

Costs of Compliance

    We estimate that this AD affects 35 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Installation..........................  5 work-hours x $85 per                $0            $425         $14,875
                                         hour = $425.
General visual inspection.............  2 work-hours x $85 per                $0            $170          $5,950
                                         hour = $170.
----------------------------------------------------------------------------------------------------------------

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement (replacing the \3/16\-inch bolts   5 work-hours x $85 per hour =                $0             $425
 with \1/4\-inch bolts).                        $425.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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 adding the following new airworthiness 
directive (AD):

2015-19-16 The Boeing Company: Amendment 39-18278; Docket No. FAA-
2014-0128; Directorate Identifier 2013-NM-133-AD.

[[Page 59574]]

(a) Effective Date

    This AD is effective November 6, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 777-200, -200LR, -
300,-300ER, and 777F series airplanes; certificated in any category; 
equipped with Rolls-Royce Trent 800 series engines.

(d) Subject

    Air Transport Association (ATA) of America Code 78, Engine 
Exhaust.

(e) Unsafe Condition

    This AD was prompted by reports of in-flight separation of the 
engine's aft plug from the forward plug, which are the two parts of 
the turbine exhaust plug assembly. We are issuing this AD to prevent 
separation of the aft plug from the forward plug of the turbine 
exhaust plug assembly, which could result in parts departing the 
airplane and hitting the empennage or hitting a person on the 
ground, and destabilizing the airplane during a critical flight 
phase; parts remaining on a runway could cause damage to another 
airplane.

(f) Compliance

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

(g) Installation and General Visual Inspection

    At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Special Attention Service Bulletin 777-78-
0051, Revision 4, dated February 7, 2014, except as provided by 
paragraph (i) of this AD, do the applicable 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 777-78-0051, Revision 4, dated February 
7, 2014. Alternative part marking methods are allowed for the 
requirements of this paragraph, if approved by the FAA principal 
maintenance inspector, provided that the markings are permanent and 
contain the information required by Boeing Special Attention Service 
Bulletin 777-78-0051, Revision 4, dated February 7, 2014.
    (1) For airplanes identified as Group 1, Configuration 1, in 
Boeing Special Attention Service Bulletin 777-78-0051, Revision 4, 
dated February 7, 2014: Install a serviceable turbine exhaust plug 
assembly.
    (2) For airplanes identified as Group 1, Configurations 2 and 3, 
in Boeing Special Attention Service Bulletin 777-78-0051, Revision 
4, dated February 7, 2014: Do a general visual inspection to 
determine the diameter of the bolt used at the forward and aft plug 
interface, and before further flight, do all applicable corrective 
actions.
    (3) For airplanes listed in paragraph (c) of this AD that are 
not listed in the ``Effectivity'' section of Boeing Special 
Attention Service Bulletin 777-78-0051, Revision 4, dated February 
7, 2014: Do a general visual inspection to determine if a 
serviceable turbine exhaust plug assembly is installed. If a 
serviceable turbine exhaust plug assembly is not installed, before 
further flight, install a serviceable turbine exhaust plug assembly.
    (4) For airplanes identified as Group 2, in Boeing Special 
Attention Service Bulletin 777-78-0051, Revision 4, dated February 
7, 2014: Do a maintenance records check to determine affected 
turbine exhaust plug assemblies, and for affected assemblies, do a 
general visual inspection to determine the diameter of the bolt used 
at the forward and aft plug interface, and before further flight, do 
all applicable corrective actions.

(h) Definition of Serviceable Assembly

    For the purposes of this AD, an acceptable serviceable turbine 
exhaust plug assembly must meet the conditions specified in 
paragraph (h)(1) or (h)(2) of this AD.
    (1) A new assembly with part number 314W5520-22.
    (2) A serviceable assembly as defined in the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 777-78-
0051, Revision 4, dated February 7, 2014; except, for any assembly 
on which the actions specified in Part 2 or Part 3 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 777-78-0051, Revision 4, dated February 7, 2014, are done, 
and Boeing Special Attention Service Bulletin 777-78-0051, Revision 
4, dated February 7, 2014, specifies to contact Boeing for repair 
instructions, this AD requires repair before further flight, using a 
method approved in accordance with the procedures specified in 
paragraph (l)(1) of this AD.

(i) Exception to Service Information Specifications

    Where paragraph 1.E., ``Compliance,'' of Boeing Special 
Attention Service Bulletin 777-78-0051, Revision 4, dated February 
7, 2014, specifies a compliance time ``after the Revision 3 date of 
this service bulletin,'' or ``after the Revision 4 date of this 
service bulletin,'' this AD requires compliance within the 
applicable time after the effective date of this AD.

(j) Parts Installation Limitation

    As of the effective date of this AD, only a serviceable turbine 
exhaust plug assembly that meets the requirements of paragraph 
(h)(1) or (h)(2) of this AD may be installed or reinstalled on any 
airplane.

(k) Credit for Previous Actions

    This paragraph provides credit for the actions specified in 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using Boeing Special Attention Service 
Bulletin 777-78-0051, Revision 3, dated August 23, 2012 (which is 
not incorporated by reference in this AD), provided that for Group 
1, Configuration 2, airplanes, on which the condition defined in 
Table 2 of paragraph 1.E., ``Compliance,'' of Boeing Special 
Attention Service Bulletin 777-78-0051, Revision 3, dated August 23, 
2012, was found (i.e., only \1/4\ inch diameter bolts are found 
installed at all 33 locations forward and aft plug interface), the 
re-identification of the forward and aft plug was done before 
further flight after the inspection.

(l) 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 (m) 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 the airplane, and the approval must 
specifically refer to this AD. An AMOC approved as described in this 
paragraph for a specific serviceable nozzle assembly may be 
transferred with that nozzle assembly to another aircraft without an 
additional AMOC approval being required.
    (4) Repairs approved prior to the effective date of this AD by 
the Boeing ODA do not require AMOC approval if those repairs were 
approved using FAA Form 8100-9 and those repairs meet the definition 
of a serviceable assembly contained in the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 777-78-
0051, Revision 4, dated February 7, 2014.

(m) Related Information

    (1) For more information about this AD, contact Kevin Nguyen, 
Aerospace Engineer, Propulsion Branch, ANM-140S, Seattle Aircraft 
Certification Office (ACO) FAA, 1601 Lind Avenue SW., Renton, WA 
98057-3356; phone: 425-917-6501; fax: 425-917-6590; email: 
kevin.nguyen@faa.gov.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (n)(3) and (n)(4) of this AD.

(n) 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.
    (i) Boeing Special Attention Service Bulletin 777-78-0051, 
Revision 4, dated February 7, 2014.
    (ii) Reserved.
    (3) 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

[[Page 59575]]

206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
    (4) 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.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on September 16, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-24677 Filed 10-1-15; 8:45 am]
 BILLING CODE 4910-13-P