Airworthiness Directives; The Boeing Company Airplanes, 18208-18219 [2018-08951]

Download as PDF 18208 Federal Register / Vol. 83, No. 81 / Thursday, April 26, 2018 / Rules and Regulations this section within 20 working days of the individual’s or Manager’s receipt of the Administrative Judge’s decision; (d) The copy of any request for further review of the individual’s case by the cognizant Under Secretary filed by the Manager shall be provided to the individual by the Manager. (e) The party filing a request for review of the individual’s case by the cognizant Under Secretary shall include with the request a statement identifying the issues on which it wishes the cognizant Under Secretary to focus. (f) The Administrative Judge’s decision shall be considered final if a written request for review is not filed in accordance with paragraph (c) of this section. § 712.24 Final decision by DOE Under Secretary. (a) Within 10 calendar days of receipt of the written request for review, the Associate Under Secretary for Environment, Health, Safety and Security should forward to the cognizant Under Secretary the written request for review, the Administrative Judge’s decision, and the administrative record. (b) Upon receipt of the written request for review, the Administrative Judge’s decision, and the administrative record, the cognizant Under Secretary, in consultation with the DOE General Counsel, will issue a final written decision. The cognizant Under Secretary may delegate this authority. In issuing a final decision, the cognizant Under Secretary shall expressly state that he or she is either revoking or restoring an individual’s HRP certification. A copy of this decision must be sent by certified mail (return receipt requested) to the Manager and to the individual. (c) The cognizant Under Secretary shall consider only that evidence and information in the administrative record at the time of the Administrative Judge’s decision. rmajette on DSKBCKNHB2PROD with RULES § 712.25 Cooperation by the individual. (a) It is the responsibility of the HRP candidate or HRP certified individual to provide full, frank, and truthful answers to relevant and material questions, and when requested, furnish, or authorize others to furnish, information that DOE deems pertinent to reach a decision regarding HRP certification or recertification. This obligation to cooperate applies at any stage, including but not limited to initial certification, recertification, temporary removal, revocation, and/or hearing. The individual or candidate may elect not to cooperate; however, such refusal may prevent DOE from reaching an VerDate Sep<11>2014 14:41 Apr 25, 2018 Jkt 244001 affirmative finding required for granting or continuing HRP certification. In this event, any HRP certification then in effect may be revoked, or, for HRP candidates, may not be granted. (b) An HRP certified individual who receives notification of the Manager’s decision to revoke his or her certification due to failure to cooperate may choose one of the following options: (1) Take no action; or (2) Within 20 working days after the individual received notice of the Manager’s revocation decision, submit a written request by certified mail to the Manager for reconsideration. The request must include the individual’s response to the information that gave rise to the revocation decision. (c) Upon receipt of the request for reconsideration, the Manager shall notify the individual, in writing, within 20 calendar days of receipt of the written appeal, as to whether the action to revoke certification was appropriate. If the Manager determines that the action was inappropriate, he or she shall reverse revocation. § 712.34 [Amended] 3. Section 712.34 is amended by removing the language, ‘‘Director, Office of Health and Safety’’ in paragraphs (a), (b) introductory text, (c), and (d) and adding in its place ‘‘Associate Under Secretary for Environment, Health, Safety and Security’’. ■ 4. Section 712.35 is amended by revising the section heading and in the introductory text by removing the language, ‘‘Director, Office of Health and Safety’’ and adding in its place ‘‘Associate Under Secretary for Environment, Health, Safety and Security’’. The revision reads as follows: ■ § 712.35 Associate Under Secretary for Environment, Health, Safety and Security. * * § 712.36 * * * [Amended] 5. Section 712.36 is amended by: a. Removing the language, ‘‘Director, Office of Health and Safety’’ in paragraphs (d)(1) and (d)(3) and adding in its place ‘‘Associate Under Secretary for Environment, Health, Safety and Security’’. ■ b. Removing paragraph (i). ■ ■ [FR Doc. 2018–08697 Filed 4–25–18; 8:45 am] BILLING CODE 6450–01–P PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0304; Product Identifier 2018–NM–065–AD; Amendment 39–19261; AD 2018–09–05] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for The Boeing Company Model 787–8 and 787– 9 airplanes powered by Rolls-Royce plc (RR) Trent 1000–A2, Trent 1000–AE2, Trent 1000–C2, Trent 1000–CE2, Trent 1000–D2, Trent 1000–E2, Trent 1000– G2, Trent 1000–H2, Trent 1000–J2, Trent 1000–K2, and Trent 1000–L2 turbofan engines. This AD requires revising the airplane flight manual (AFM) to limit extended operations (ETOPS). This AD was prompted by a report from the engine manufacturer indicating that after an engine failure, prolonged operation at high thrust settings on the remaining engine during an ETOPS diversion may result in failure of the remaining engine before the diversion can be safely completed. We have determined that updated AFM limitations are needed to minimize the potential for intermediate pressure compressor (IPC) blade failures under certain conditions. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective April 26, 2018. We must receive comments on this AD by June 11, 2018. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. SUMMARY: E:\FR\FM\26APR1.SGM 26APR1 Federal Register / Vol. 83, No. 81 / Thursday, April 26, 2018 / Rules and Regulations 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–2018– 0304; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations (phone: 800–647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Tak Kobayashi, Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206– 231–3553; email: Takahisa.Kobayashi@ faa.gov. SUPPLEMENTARY INFORMATION: rmajette on DSKBCKNHB2PROD with RULES Discussion Over the past year, we have been aware of several engine failures of Trent 1000 Package C engines due to failed compressor and turbine blades and seals. Package C engines are RR Trent 1000–A2, Trent 1000–AE2, Trent 1000– C2, Trent 1000–CE2, Trent 1000–D2, Trent 1000–E2, Trent 1000–G2, Trent 1000–H2, Trent 1000–J2, Trent 1000– K2, and Trent 1000–L2 turbofan engines. During that same period, under the management programs for those engine issues, we have been aware of numerous reports of engine inspection findings of cracked blades resulting in unscheduled engine removals. Boeing reported to the FAA that the engine manufacturer recently determined that IPC stage 2 blades have a resonant frequency that is excited by the airflow conditions existing in the engine during operation at high thrust settings under certain temperature and altitude conditions. The resultant blade vibration can result in cumulative fatigue damage that can cause blade failure and consequent engine in-flight shutdown. In the event of a single engine in-flight shutdown during the cruise phase of flight, thrust on the remaining engine is normally increased to maximum continuous thrust (MCT). During a diversion following a single engine shutdown under an ETOPS flight, the remaining engine may operate at MCT for a prolonged period, during which the IPC stage 2 blades would be exposed to the resonant frequency condition. Therefore, an ETOPS diversion will put the remaining engine at an operating condition that would significantly increase the likelihood of failure of the remaining engine. In addition, if the remaining engine already had cracked IPC stage 2 blades, the likelihood of the remaining engine failing before a diversion can be safely completed will further increase. Related Rulemaking AD 2018–08–03, Amendment 39– 19256 (83 FR 16768, April 17, 2018) (‘‘AD 2018–08–03’’), also requires revising the AFM to limit ETOPS on Boeing Model 787–8 and 787–9 airplanes powered by RR Trent 1000– A2, Trent 1000–AE2, Trent 1000–C2, Trent 1000–CE2, Trent 1000–D2, Trent 1000–E2, Trent 1000–G2, Trent 1000– H2, Trent 1000–J2, Trent 1000–K2, and Trent 1000–L2 turbofan engines. Actions Since AD 2018–08–03 Was Issued Based on further review of the AFM limitations, Boeing has updated the information reflected within the figures of AD 2018–08–03. The FAA has determined it is necessary to update the AFM limitations accordingly to minimize the potential for IPC blade failures under certain conditions. The FAA has determined that operation under AD 2018–08–03 is acceptable for safe operation until the new AD limitations are mandated. FAA’s Determination We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. AD Requirements This AD requires revising the AFM to limit ETOPS, using the updated information referenced in figure 1 to paragraph (g) of this AD and figure 2 to paragraph (h) of this AD. Accomplishment of the AFM revisions required by this AD terminates all requirements of AD 2018–08–03. 18209 Interim Action This AD is interim action. The manufacturer is currently developing a modification that will address the unsafe condition identified in this AD. Once this modification is developed, approved, and available, we might consider additional rulemaking. FAA’s Justification and Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD without providing an opportunity for public comments prior to adoption. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because unrecoverable thrust loss on both engines could lead to a forced landing. Therefore, we find good cause that notice and opportunity for prior public comment are impracticable. In addition, for the reasons stated above, we find that good cause exists for making this amendment effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment. However, we invite you to send any written data, views, or arguments about this final rule. Send your comments to an address listed under the ADDRESSES section. Include the docket number FAA–2018–0304 and Product Identifier 2018–NM–065–AD at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this final rule. We will consider all comments received by the closing date and may amend this final rule because of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this final rule. Costs of Compliance We estimate that this AD affects 14 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost AFM revisions ......................... 1 work-hour × $85 per hour = $85 ......................................... VerDate Sep<11>2014 14:41 Apr 25, 2018 Jkt 244001 PO 00000 Frm 00015 Fmt 4700 Cost per product Parts cost Sfmt 4700 E:\FR\FM\26APR1.SGM $0 26APR1 $85 Cost on U.S. registered airplanes $1,190 18210 Federal Register / Vol. 83, No. 81 / Thursday, April 26, 2018 / Rules and Regulations 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. rmajette on DSKBCKNHB2PROD with RULES 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. VerDate Sep<11>2014 14:41 Apr 25, 2018 Jkt 244001 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. (c) Applicability List of Subjects in 14 CFR Part 39 (e) Unsafe Condition Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. This AD was prompted by a report from the engine manufacturer indicating that after an engine failure, prolonged operation at high thrust settings on the remaining engine during an extended-operation (ETOPS) diversion may result in failure of the remaining engine before the diversion can be safely completed. We are issuing this AD to address unrecoverable thrust loss on both engines, which could lead to a forced landing. 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. 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): 2018–09–05 The Boeing Company: Amendment 39–19261; Docket No. FAA–2018–0304; Product Identifier 2018–NM–065–AD. (a) Effective Date This AD is effective April 26, 2018. (b) Affected ADs This AD affects AD 2018–08–03, Amendment 39–19256 (83 FR 16768, April 17, 2018) (‘‘AD 2018–08–03’’). Frm 00016 Fmt 4700 Air Transport Association (ATA) of America Code 71, Power plant. Comply with this AD within the compliance times specified, unless already done. (g) Revision of Limitations Chapter in Airplane Flight Manual (AFM) [Amended] ■ PO 00000 (d) Subject (f) Compliance ■ § 39.13 This AD applies to The Boeing Company Model 787–8 and 787–9 airplanes, certificated in any category, powered by Rolls-Royce plc (RR) Trent 1000–A2, Trent 1000–AE2, Trent 1000–C2, Trent 1000–CE2, Trent 1000–D2, Trent 1000–E2, Trent 1000– G2, Trent 1000–H2, Trent 1000–J2, Trent 1000–K2, and Trent 1000–L2 turbofan engines. Sfmt 4700 Within 4 days after the effective date of this AD, revise the Certificate Limitations chapter of the applicable Boeing AFM Engine Appendix by incorporating the information in figure 1 to paragraph (g) of this AD. This may be accomplished by inserting a copy of this AD into the AFM. When information identical to that in figure 1 to paragraph (g) of this AD has been included in the Certificate Limitations chapter of the general revisions of the AFM, the general revisions may be inserted into the AFM, and the copy of this AD may be removed from the AFM. BILLING CODE 4910–13–P E:\FR\FM\26APR1.SGM 26APR1 Federal Register / Vol. 83, No. 81 / Thursday, April 26, 2018 / Rules and Regulations rmajette on DSKBCKNHB2PROD with RULES Concurrently with accomplishment of the requirements of paragraph (g) of this AD, revise the Performance chapter of the applicable Boeing AFM Engine Appendix by VerDate Sep<11>2014 14:41 Apr 25, 2018 Jkt 244001 incorporating the information in figure 2 to paragraph (h) of this AD. This may be accomplished by inserting a copy of this AD into the AFM. When information identical to that in figure 2 to paragraph (h) of this AD has been included in the Performance PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 chapter of the general revisions of the AFM, the general revisions may be inserted into the AFM, and the copy of this AD may be removed from the AFM. Guidance on flight path planning can be found in figure 3 to paragraph (h) of this AD. E:\FR\FM\26APR1.SGM 26APR1 ER26AP18.002</GPH> (h) Revision of Performance Chapter of AFM 18211 18212 Federal Register / Vol. 83, No. 81 / Thursday, April 26, 2018 / Rules and Regulations Figure 2 to paragraph (h) of this AD -AFM Performance Engine Appendix - Performance (Required by AD 2018-09-05) ETOPS ETOPS operation of a Model 787-8 or 787-9 airplane equipped with a RR Trent 1000 engine using A2, C2, or E2 thrust rating is prohibited. As outlined in the ETOPs Section of the Certificate Limitations chapter, the following table must be utilized when planning ETOPS flights. (D631Z003-9R64EF) 787-9 Trent 1000-AE2 Maximum En route Diversion Temperature* ISA+O Degrees C and Below ISA+ 10 Degrees C ISA+lSDegreesC ISA+20 Degrees C ISA+25 Degrees C Above ISA+25 Degrees C 19,000 19,000 18,800 18,500 18,300 Prohibited Without Forecast Icing LB5 Maximum Planned Weight at ETOP5 Entry Points and Equal KGS Time Points 499,000 497,400 477,500 453,000 422,000 226,360 225,650 216,620 205,480 191,410 With Forecast Icing Maximum LBS Planned Weight at ETOPS Entry Points and Equal Time KGS Points 425,900 417,000 396,300 367,300 338,200 Minimum Engine-Out Cruise Altitude (ft) Prohibited Prohibited 193,210 189,170 179,800 166,610 153,420 VerDate Sep<11>2014 14:41 Apr 25, 2018 Jkt 244001 PO 00000 Frm 00018 Fmt 4700 Sfmt 4725 E:\FR\FM\26APR1.SGM 26APR1 ER26AP18.003</GPH> rmajette on DSKBCKNHB2PROD with RULES *Interpolation between temperature columns is allowed. Federal Register / Vol. 83, No. 81 / Thursday, April 26, 2018 / Rules and Regulations 18213 (D631Z003-9R7072F) and (D631Z003-9R7072E) 787-9 Trent 1000-D2 Maximum En route Diversion Temperature* ISA+O Degrees C and Below ISA+ 10 Degrees C ISA+lSDegreesC ISA+20 Degrees C ISA+25 Degrees C Above ISA+25 Degrees C 19,100 19,100 18,900 18,700 18,500 Prohibited Without Forecast Icing LB5 Maximum Planned Weight at ETOPS Entry Points and Equal KGS Time Points 510,300 508,400 488,200 465,800 441,800 231,500 230,640 221,480 211,310 200,390 With Forecast Icing Maximum LBS 438,300 429,300 408,400 383,800 359,300 198,830 194,760 185,240 174,110 162,970 Minimum Engine-Out Cruise Altitude (ft) Planned Weight at ETOPS Entry Points and Equal Time Points Prohibited Prohibited KGS *Interpolation between temperature columns is allowed. (D631Z003-9R74F) and (D631Z003-9R74E) 787-9 Trent 1000-J2 Maximum En route Diversion Temperature* ISA+O Degrees C and Below ISA+lO Degrees C ISA+lS Degrees C ISA+20 Degrees C ISA+25 Degrees C Above ISA+25 Degrees C 19,300 19,300 19,100 18,800 18,500 Prohibited LBS 528,900 526,800 507,800 479,500 451,100 KGS 239,900 238,950 230,370 217,510 204,640 LBS 455,200 446,600 430,200 401,400 372,500 KGS 206,470 202,580 195,140 182,070 169,000 Minimum Engine-Out Cruise Altitude (ft) Without Forecast Icing Maximum Planned Weight at ETOPS Entry Points and Equal Time Points With Forecast Icing Maximum Prohibited Planned Weight at ETOPS Entry Points and Equal Time Points Prohibited VerDate Sep<11>2014 14:41 Apr 25, 2018 Jkt 244001 PO 00000 Frm 00019 Fmt 4700 Sfmt 4725 E:\FR\FM\26APR1.SGM 26APR1 ER26AP18.004</GPH> rmajette on DSKBCKNHB2PROD with RULES *Interpolation between temperature columns is allowed. 18214 Federal Register / Vol. 83, No. 81 / Thursday, April 26, 2018 / Rules and Regulations (D631Z003-R7475F) and (D631Z003-R7475E) 787-9 Trent 1000-K2 Maximum En route Diversion Temperature* ISA-10 Degrees C and Below ISA+lO Degrees C ISA+lS Degrees C ISA+20 Degrees C ISA+25 Degrees C Above ISA+25 Degrees C 19,300 19,300 19,100 18,800 18,500 Prohibited LB5 528,900 526,800 507,800 479,500 451,100 KGS 239,900 238,950 230,370 217,510 204,640 With Forecast Icing Maximum LBS 455,200 446,600 430,200 401,400 372,500 206,470 202,580 195,140 182,070 169,000 Minimum Engine-Out Cruise Altitude (ft) Without Forecast Icing Maximum Planned Weight at Prohibited ETOPS Entry Points and Equal Time Points Planned Weight at ETOPS Prohibited Entry Points and Equal Time KGS Points *Interpolation between temperature columns is allowed. (D631Z003-R70EF) 787-8 Trent 1000-CE2 Maximum En route Diversion Temperature* ISA-10 Degrees C and Below ISA+lO Degrees C ISA+lS Degrees C ISA+20 Degrees C ISA+25 Degrees C Above ISA+25 Degrees C 19,300 19,300 19,100 18,900 18,600 Prohibited LBS 502,500 502,500 499,600 476,300 450,100 KGS 227,930 227,930 226,610 216,040 204,160 With Forecast Icing Maximum LBS 446,700 438,600 419,400 396,300 372,400 202,650 198,970 190,260 179,790 168,910 Minimum Engine-Out Cruise Altitude (ft) Without Forecast Icing Maximum Planned Weight at Prohibited ETOPS Entry Points and Equal Time Points Planned Weight at ETOPS Prohibited Entry Points and Equal Time Points KGS VerDate Sep<11>2014 14:41 Apr 25, 2018 Jkt 244001 PO 00000 Frm 00020 Fmt 4700 Sfmt 4725 E:\FR\FM\26APR1.SGM 26APR1 ER26AP18.005</GPH> rmajette on DSKBCKNHB2PROD with RULES *Interpolation between temperature columns is allowed. Federal Register / Vol. 83, No. 81 / Thursday, April 26, 2018 / Rules and Regulations 18215 (D631Z003-R7072F) and (D631Z003-R7072E) 787-8 Trent 1000-D2 Maximum En route Diversion Temperature* I SA-tO Degrees C and Below ISA+lO Degrees c ISA+lS Degrees c ISA+20 Degrees c ISA+25 Degrees c Above ISA+25 Degrees C 19,300 19,300 19,100 18,900 18,600 Prohibited LBS 502,500 502,500 499,600 476,300 450,100 KGS 227,930 227,930 226,610 216,040 204,160 With Forecast Icing Maximum LBS 446,700 438,600 419,400 396,300 372,400 202,650 198,970 190,260 179,790 168,910 Minimum Engine-Out Cruise Altitude (ft) Without Forecast Icing Maximum Planned Weight at Prohibited ETOPS Entry Points and Equal Time Points Planned Weight at ETOPS Prohibited Entry Points and Equal Time KGS Points *Interpolation between temperature columns is allowed. (D631Z003-R70LF) 787-8 Trent 1000-L2 Maximum En route Diversion Temperature* ISA-10 Degrees C and Below ISA+lO Degrees C ISA+lS Degrees C ISA+20 Degrees C ISA+25 Degrees C Above ISA+25 Degrees C 19,300 19,300 19,100 18,900 18,600 Prohibited LBS 502,500 502,500 499,600 476,300 450,100 KGS 227,930 227,930 226,610 216,040 204,160 With Forecast Icing Maximum LBS 446,700 438,600 419,400 396,300 372,400 202,650 198,970 190,260 179,790 168,910 Minimum Engine-Out Cruise Altitude (ft) Without Forecast Icing Maximum Planned Weight at Prohibited ETOPS Entry Points and Equal Time Points Planned Weight at ETOPS Prohibited Entry Points and Equal Time Points KGS VerDate Sep<11>2014 14:41 Apr 25, 2018 Jkt 244001 PO 00000 Frm 00021 Fmt 4700 Sfmt 4725 E:\FR\FM\26APR1.SGM 26APR1 ER26AP18.006</GPH> rmajette on DSKBCKNHB2PROD with RULES *Interpolation between temperature columns is allowed. 18216 Federal Register / Vol. 83, No. 81 / Thursday, April 26, 2018 / Rules and Regulations (D631Z003-R67F) and (D631Z003-R67E) 787-8 Trent 1000-G2 Maximum En route Diversion Temperature* I SA-tO Degrees C and Below ISA+lO Degrees c ISA+lS Degrees c ISA+20 Degrees c ISA+25 Degrees c Above ISA+25 Degrees C 19,200 19,200 19,000 18,700 18,400 Prohibited LBS 502,500 502,500 488,900 461,500 430,400 KGS 227,930 227,930 221,780 209,340 195,220 With Forecast Icing Maximum LBS 436,300 426,700 405,700 383,400 355,300 197,910 193,550 184,020 173,910 161,160 Minimum Engine-Out Cruise Altitude (ft) Without Forecast Icing Maximum Planned Weight at Prohibited ETOPS Entry Points and Equal Time Points Planned Weight at ETOPS Prohibited Entry Points and Equal Time KGS Points *Interpolation between temperature columns is allowed. (D631Z003-R64EF) and (D631Z003-R64EE) 787-8 Trent 1000-AE2 Maximum En route Diversion Temperature* ISA-10 Degrees C and Below ISA+lO Degrees C ISA+lS Degrees C ISA+20 Degrees C ISA+25 Degrees C Above ISA+25 Degrees C 19,200 19,200 19,000 18,700 18,400 Prohibited LBS 502,500 502,500 488,900 461,500 430,400 KGS 227,930 227,930 221,780 209,340 195,220 With Forecast Icing Maximum LBS 436,300 426,700 405,700 383,400 355,300 197,910 193,550 184,020 173,910 161,160 Minimum Engine-Out Cruise Altitude (ft) Without Forecast Icing Maximum Planned Weight at Prohibited ETOPS Entry Points and Equal Time Points Planned Weight at ETOPS Prohibited Entry Points and Equal Time Points KGS VerDate Sep<11>2014 14:41 Apr 25, 2018 Jkt 244001 PO 00000 Frm 00022 Fmt 4700 Sfmt 4725 E:\FR\FM\26APR1.SGM 26APR1 ER26AP18.007</GPH> rmajette on DSKBCKNHB2PROD with RULES *Interpolation between temperature columns is allowed. Federal Register / Vol. 83, No. 81 / Thursday, April 26, 2018 / Rules and Regulations 18217 (D631Z003-R58F) 787-8 Trent 1000-H2 Maximum En route Diversion Temperature* ISA+O Degrees C and Below ISA+ 10 Degrees C ISA+lSDegreesC ISA+20 Degrees C ISA+25 Degrees C Above ISA+25 Degrees C 18,900 18,800 18,600 18,200 17,900 Prohibited LBS 474,000 471,600 447,400 416,700 386,000 KGS 215,000 213,940 202,970 189,040 175,100 LBS 404,400 394,900 371,700 346,700 321,700 KGS 183,470 179,120 168,630 157,270 145,910 Minimum Engine-Out Cruise Altitude (ft) Without Forecast Icing Maximum Planned Weight at Prohibited ETOPS Entry Points and Equal Time Points With Forecast Icing Maximum Planned Weight at ETOPS Prohibited Entry Points and Equal Time Points VerDate Sep<11>2014 14:41 Apr 25, 2018 Jkt 244001 PO 00000 Frm 00023 Fmt 4700 Sfmt 4725 E:\FR\FM\26APR1.SGM 26APR1 ER26AP18.008</GPH> rmajette on DSKBCKNHB2PROD with RULES *Interpolation between temperature columns is allowed. 18218 Federal Register / Vol. 83, No. 81 / Thursday, April 26, 2018 / Rules and Regulations Figure 3 to paragraph (h) of this AD- Guidance on flight path planning Guidance on flight path planning 1. Utilize the one-engine inoperative LRC speed for the ETOPS engine-out planning speed and establish that the planned maximum diversion time is not greater than 140 minutes. Critical fuel decompression scenarios should utilize the M0.55 speeds for both all engine and engine inoperative scenarios. 2. Determine if forecast icing is expected along the planned flight plan path and in the planned diversionary track(s) between the ETOPS Entry Point(s) (EEP) and the first ETOPS Equal-Time Point (ETPl). Accomplish the same determination for the subsequent ETOPS segment (i.e., between ETPl and ETP2 or the (ETOPS Exit Point) EXP). 3. Verify the planned maximum weight at the EEP is derived based upon the maximum forecast temperature at FL200 between the EEP and ETP1 and the planned weight at the EEP is no greater than the maximum planned weight corresponding to either the without-forecast icing or with-forecast icing (if icing is probable between the EEP and ETPl along the flight plan track or along the planned diversionary track at FL200) table values at the appropriate maximum diversion temperature. If the EEP gross weight is less than the table limits, continue with the flight planning. If the EEP maximum planned weight is greater than the appropriate value provided in the table, a takeoff weight reduction will be required to establish that the maximum planned weight at the EEP is equal to or less than the table values. 4. Verify the planned maximum weight at ETP1 is derived based upon the maximum forecast temperature at FL200 between the ETP 1 and ETP2 (or the EXP) and the planned weight at the ETP 1 is no greater than the maximum planned weight corresponding to either, the without-forecast icing or with-forecast icing (if icing is probable between the ETPl and ETP2 along the flight plan track or along the planned diversionary track at FL200) table values at the appropriate maximum diversion temperature. If the ETP1 planned maximum weight is less than the table limits, continue with the flight planning. If the ETP 1 maximum planned weight is greater than the appropriate value provided in the table, a takeoff weight reduction will be required to establish that the maximum planned weight at the ETPs is equal to or less than the table values. 6. Upon verification of the planned maximum weight limits at the EEP and each of the ETPs required to complete the mission, validate the engine inoperative maximum diversion time is no greater than 140 minutes. VerDate Sep<11>2014 14:41 Apr 25, 2018 Jkt 244001 PO 00000 Frm 00024 Fmt 4700 Sfmt 4725 E:\FR\FM\26APR1.SGM 26APR1 ER26AP18.009</GPH> rmajette on DSKBCKNHB2PROD with RULES 5. Verify the planned maximum weights at each subsequent ETP are no greater than the appropriate weight provided in the table accounting for the effects of forecast icing, if probable, and the appropriate forecast temperature. Federal Register / Vol. 83, No. 81 / Thursday, April 26, 2018 / Rules and Regulations Accomplishment of the actions required by paragraphs (g) and (h) of this AD terminates all requirements of AD 2018–08–03. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle ACO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (k) of this AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO Branch, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (k) Related Information For more information about this AD, contact Tak Kobayashi, Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, Alberta E. Mills, Secretary, Consumer Product Safety Commission. [FR Doc. 2018–08742 Filed 4–25–18; 8:45 am] BILLING CODE 6355–01–P WA 98198; phone and fax: 206–231–3553; email: Takahisa.Kobayashi@faa.gov. (l) Material Incorporated by Reference None. Issued in Des Moines, Washington, on April 24, 2018. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–08951 Filed 4–25–18; 8:45 am] BILLING CODE 4910–13–C CONSUMER PRODUCT SAFETY COMMISSION 16 CFR Chapter II [Docket No. CPSC–2016–2019] Labeling of Certain Household Products Containing Methylene Chloride; Supplemental Guidance; Correction Consumer Product Safety Commission. ACTION: Guidance; correction. AGENCY: The Consumer Product Safety Commission is correcting supplemental guidance on the Labeling of Certain Household Products Containing Methylene Chloride, which appeared in the Federal Register of March 21, 2018. The document provides guidance regarding labeling to warn of acute hazards associated with paint strippers containing methylene chloride. This SUMMARY: DEPARTMENT OF DEFENSE Office of the Secretary 32 CFR Part 292 [Docket ID: DOD–2017–OS–0022] RIN 0790–AJ63 Defense Intelligence Agency (DIA) Freedom of Information Act rmajette on DSKBCKNHB2PROD with RULES AGENCY: Defense Intelligence Agency, DoD. ACTION: Final rule. This final rule removes DoD’s regulation concerning the Defense Intelligence Agency (DIA) Freedom of Information Act program. On February 6, 2018, the DoD published a revised SUMMARY: VerDate Sep<11>2014 14:41 Apr 25, 2018 Jkt 244001 PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 correction provides the appropriate link to the petition briefing package and the format of a warning label. DATES: This correction is effective April 26, 2018. As established in the supplemental guidance, the guidance document became applicable on the date of its publication in the Federal Register, March 21, 2018. FOR FURTHER INFORMATION CONTACT: Carol Afflerbach, Office of Compliance and Field Operations, U.S. Consumer Product Safety Commission, 4330 EastWest Highway, Bethesda, MD 20814; email: cafflerbach@cpsc.gov; telephone: (301) 504–7529. SUPPLEMENTARY INFORMATION: In FR Doc. 2018–05580, appearing on page 12254 in the Federal Register of March 21, 2018, the following corrections are made: 1. On page 12255, in the middle column, correct the link at the end of the first paragraph to read as follows: ‘‘(https://www.cpsc.gov/s3fs-public/ Petition%20HP%2016-1%20to %20Amend%20Statement%20of%20 Interpretation%20and%20 Enforcement%20Policy%20 Household%20Products%20 Containing%20Methylene% 20Chloride%20-%20May%2026%20 2017.pdf?5OEQaiEtuOaf0ytaU.z3.n4 Lz5t0ku_J).’’ 2. On page 12257, in the third column, correct the format of the ‘‘Updated Example of Cautionary Labeling’’ to read as follows: FOIA program rule as a result of the FOIA Improvement Act of 2016. When the DoD FOIA program rule was revised, it included DoD component information and removed the requirement for component supplementary rules. The DoD now has one DoD-level rule for the FOIA program at 32 CFR part 286 that contains all the codified information required for the Department. Therefore, this part can be removed from the CFR. DATES: This rule is effective on April 26, 2018. FOR FURTHER INFORMATION CONTACT: Alesia Williams at 301–394–5188. SUPPLEMENTARY INFORMATION: It has been determined that publication of this CFR part removal for public comment is impracticable, unnecessary, and E:\FR\FM\26APR1.SGM 26APR1 ER26AP18.000</GPH> (i) Terminating Action for AD 2018–08–03 18219

Agencies

[Federal Register Volume 83, Number 81 (Thursday, April 26, 2018)]
[Rules and Regulations]
[Pages 18208-18219]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-08951]


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

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0304; Product Identifier 2018-NM-065-AD; Amendment 
39-19261; AD 2018-09-05]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for The 
Boeing Company Model 787-8 and 787-9 airplanes powered by Rolls-Royce 
plc (RR) Trent 1000-A2, Trent 1000-AE2, Trent 1000-C2, Trent 1000-CE2, 
Trent 1000-D2, Trent 1000-E2, Trent 1000-G2, Trent 1000-H2, Trent 1000-
J2, Trent 1000-K2, and Trent 1000-L2 turbofan engines. This AD requires 
revising the airplane flight manual (AFM) to limit extended operations 
(ETOPS). This AD was prompted by a report from the engine manufacturer 
indicating that after an engine failure, prolonged operation at high 
thrust settings on the remaining engine during an ETOPS diversion may 
result in failure of the remaining engine before the diversion can be 
safely completed. We have determined that updated AFM limitations are 
needed to minimize the potential for intermediate pressure compressor 
(IPC) blade failures under certain conditions. We are issuing this AD 
to address the unsafe condition on these products.

DATES: This AD is effective April 26, 2018.
    We must receive comments on this AD by June 11, 2018.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

[[Page 18209]]

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-2018-
0304; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this final rule, the regulatory evaluation, any comments received, and 
other information. The street address for Docket Operations (phone: 
800-647-5527) is in the ADDRESSES section. Comments will be available 
in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Tak Kobayashi, Aerospace Engineer, 
Propulsion Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des 
Moines, WA 98198; phone and fax: 206-231-3553; email: 
[email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    Over the past year, we have been aware of several engine failures 
of Trent 1000 Package C engines due to failed compressor and turbine 
blades and seals. Package C engines are RR Trent 1000-A2, Trent 1000-
AE2, Trent 1000-C2, Trent 1000-CE2, Trent 1000-D2, Trent 1000-E2, Trent 
1000-G2, Trent 1000-H2, Trent 1000-J2, Trent 1000-K2, and Trent 1000-L2 
turbofan engines. During that same period, under the management 
programs for those engine issues, we have been aware of numerous 
reports of engine inspection findings of cracked blades resulting in 
unscheduled engine removals. Boeing reported to the FAA that the engine 
manufacturer recently determined that IPC stage 2 blades have a 
resonant frequency that is excited by the airflow conditions existing 
in the engine during operation at high thrust settings under certain 
temperature and altitude conditions. The resultant blade vibration can 
result in cumulative fatigue damage that can cause blade failure and 
consequent engine in-flight shutdown. In the event of a single engine 
in-flight shutdown during the cruise phase of flight, thrust on the 
remaining engine is normally increased to maximum continuous thrust 
(MCT). During a diversion following a single engine shutdown under an 
ETOPS flight, the remaining engine may operate at MCT for a prolonged 
period, during which the IPC stage 2 blades would be exposed to the 
resonant frequency condition. Therefore, an ETOPS diversion will put 
the remaining engine at an operating condition that would significantly 
increase the likelihood of failure of the remaining engine. In 
addition, if the remaining engine already had cracked IPC stage 2 
blades, the likelihood of the remaining engine failing before a 
diversion can be safely completed will further increase.

Related Rulemaking

    AD 2018-08-03, Amendment 39-19256 (83 FR 16768, April 17, 2018) 
(``AD 2018-08-03''), also requires revising the AFM to limit ETOPS on 
Boeing Model 787-8 and 787-9 airplanes powered by RR Trent 1000-A2, 
Trent 1000-AE2, Trent 1000-C2, Trent 1000-CE2, Trent 1000-D2, Trent 
1000-E2, Trent 1000-G2, Trent 1000-H2, Trent 1000-J2, Trent 1000-K2, 
and Trent 1000-L2 turbofan engines.

Actions Since AD 2018-08-03 Was Issued

    Based on further review of the AFM limitations, Boeing has updated 
the information reflected within the figures of AD 2018-08-03. The FAA 
has determined it is necessary to update the AFM limitations 
accordingly to minimize the potential for IPC blade failures under 
certain conditions.
    The FAA has determined that operation under AD 2018-08-03 is 
acceptable for safe operation until the new AD limitations are 
mandated.

FAA's Determination

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

AD Requirements

    This AD requires revising the AFM to limit ETOPS, using the updated 
information referenced in figure 1 to paragraph (g) of this AD and 
figure 2 to paragraph (h) of this AD. Accomplishment of the AFM 
revisions required by this AD terminates all requirements of AD 2018-
08-03.

Interim Action

    This AD is interim action. The manufacturer is currently developing 
a modification that will address the unsafe condition identified in 
this AD. Once this modification is developed, approved, and available, 
we might consider additional rulemaking.

FAA's Justification and Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD without providing an opportunity for public comments prior to 
adoption. The FAA has found that the risk to the flying public 
justifies waiving notice and comment prior to adoption of this rule 
because unrecoverable thrust loss on both engines could lead to a 
forced landing. Therefore, we find good cause that notice and 
opportunity for prior public comment are impracticable. In addition, 
for the reasons stated above, we find that good cause exists for making 
this amendment effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment. However, we invite you to send any written data, views, or 
arguments about this final rule. Send your comments to an address 
listed under the ADDRESSES section. Include the docket number FAA-2018-
0304 and Product Identifier 2018-NM-065-AD at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this final rule. We will 
consider all comments received by the closing date and may amend this 
final rule because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this final rule.

Costs of Compliance

    We estimate that this AD affects 14 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       registered
                                                                                      product        airplanes
----------------------------------------------------------------------------------------------------------------
AFM revisions......................  1 work-hour x $85 per hour               $0             $85          $1,190
                                      = $85.
----------------------------------------------------------------------------------------------------------------


[[Page 18210]]

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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes to 
the Director of the System Oversight Division.

Regulatory Findings

    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):

2018-09-05 The Boeing Company: Amendment 39-19261; Docket No. FAA-
2018-0304; Product Identifier 2018-NM-065-AD.

(a) Effective Date

    This AD is effective April 26, 2018.

(b) Affected ADs

    This AD affects AD 2018-08-03, Amendment 39-19256 (83 FR 16768, 
April 17, 2018) (``AD 2018-08-03'').

(c) Applicability

    This AD applies to The Boeing Company Model 787-8 and 787-9 
airplanes, certificated in any category, powered by Rolls-Royce plc 
(RR) Trent 1000-A2, Trent 1000-AE2, Trent 1000-C2, Trent 1000-CE2, 
Trent 1000-D2, Trent 1000-E2, Trent 1000-G2, Trent 1000-H2, Trent 
1000-J2, Trent 1000-K2, and Trent 1000-L2 turbofan engines.

(d) Subject

    Air Transport Association (ATA) of America Code 71, Power plant.

(e) Unsafe Condition

    This AD was prompted by a report from the engine manufacturer 
indicating that after an engine failure, prolonged operation at high 
thrust settings on the remaining engine during an extended-operation 
(ETOPS) diversion may result in failure of the remaining engine 
before the diversion can be safely completed. We are issuing this AD 
to address unrecoverable thrust loss on both engines, which could 
lead to a forced landing.

(f) Compliance

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

(g) Revision of Limitations Chapter in Airplane Flight Manual (AFM)

    Within 4 days after the effective date of this AD, revise the 
Certificate Limitations chapter of the applicable Boeing AFM Engine 
Appendix by incorporating the information in figure 1 to paragraph 
(g) of this AD. This may be accomplished by inserting a copy of this 
AD into the AFM. When information identical to that in figure 1 to 
paragraph (g) of this AD has been included in the Certificate 
Limitations chapter of the general revisions of the AFM, the general 
revisions may be inserted into the AFM, and the copy of this AD may 
be removed from the AFM.

BILLING CODE 4910-13-P

[[Page 18211]]

[GRAPHIC] [TIFF OMITTED] TR26AP18.002

(h) Revision of Performance Chapter of AFM

    Concurrently with accomplishment of the requirements of 
paragraph (g) of this AD, revise the Performance chapter of the 
applicable Boeing AFM Engine Appendix by incorporating the 
information in figure 2 to paragraph (h) of this AD. This may be 
accomplished by inserting a copy of this AD into the AFM. When 
information identical to that in figure 2 to paragraph (h) of this 
AD has been included in the Performance chapter of the general 
revisions of the AFM, the general revisions may be inserted into the 
AFM, and the copy of this AD may be removed from the AFM. Guidance 
on flight path planning can be found in figure 3 to paragraph (h) of 
this AD.

[[Page 18212]]

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[[Page 18213]]


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[[Page 18214]]


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[[Page 18215]]


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[[Page 18217]]


[GRAPHIC] [TIFF OMITTED] TR26AP18.008


[[Page 18218]]


[GRAPHIC] [TIFF OMITTED] TR26AP18.009


[[Page 18219]]



(i) Terminating Action for AD 2018-08-03

    Accomplishment of the actions required by paragraphs (g) and (h) 
of this AD terminates all requirements of AD 2018-08-03.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle ACO Branch, FAA, has the authority to 
approve AMOCs for this AD, if requested using the procedures found 
in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request 
to your principal inspector or local Flight Standards District 
Office, as appropriate. If sending information directly to the 
manager of the certification office, send it to the attention of the 
person identified in paragraph (k) of this AD. Information may be 
emailed to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair, modification, or alteration required by this AD 
if it is approved by the Boeing Commercial Airplanes Organization 
Designation Authorization (ODA) that has been authorized by the 
Manager, Seattle ACO Branch, to make those findings. To be approved, 
the repair method, modification deviation, or alteration deviation 
must meet the certification basis of the airplane, and the approval 
must specifically refer to this AD.

(k) Related Information

    For more information about this AD, contact Tak Kobayashi, 
Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch, 
2200 South 216th St., Des Moines, WA 98198; phone and fax: 206-231-
3553; email: [email protected].

(l) Material Incorporated by Reference

    None.

    Issued in Des Moines, Washington, on April 24, 2018.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2018-08951 Filed 4-25-18; 8:45 am]
 BILLING CODE 4910-13-C