Airworthiness Directives; The Boeing Company Airplanes, 16768-16773 [2018-08127]

Download as PDF 16768 Federal Register / Vol. 83, No. 74 / Tuesday, April 17, 2018 / Rules and Regulations Signed in Washington, DC, on April 12, 2018. Heather Manzano, Acting Manager, Federal Crop Insurance Corporation. p.m., Monday through Friday, except Federal holidays. [FR Doc. 2018–08016 Filed 4–16–18; 8:45 am] BILLING CODE 3410–08–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0299; Product Identifier 2018–NM–060–AD; Amendment 39–19256; AD 2018–08–03] 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 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 are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective April 17, 2018. We must receive comments on this AD by June 1, 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 daltland on DSKBBV9HB2PROD with RULES SUMMARY: VerDate Sep<11>2014 16:15 Apr 16, 2018 Jkt 244001 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– 0299; 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 Street, Des Moines, WA 98198; phone and fax: 206– 231–3553; email: Takahisa.Kobayashi@ faa.gov. 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 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. 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 intermediate pressure compressor (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 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, under which the IPC stage 2 blades would be exposed to the resonant frequency PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 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 will further increase before a diversion can be safely completed. 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 operation. 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–2018–0299 and Product Identifier 2018–NM–060–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 E:\FR\FM\17APR1.SGM 17APR1 Federal Register / Vol. 83, No. 74 / Tuesday, April 17, 2018 / Rules and Regulations 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. 16769 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 ......................................... 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 and associated appliances to the Director of the System Oversight Division. Regulatory Findings daltland on DSKBBV9HB2PROD with RULES 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 VerDate Sep<11>2014 16:15 Apr 16, 2018 Jkt 244001 Cost per product Parts cost 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: $0 Cost on U.S. operators $85 $1,190 (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 PART 39—AIRWORTHINESS DIRECTIVES Comply with this AD within the compliance times specified, unless already done. 1. The authority citation for part 39 continues to read as follows: (g) Revision of Limitations Chapter in Airplane Flight Manual (AFM) ■ 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): ■ 2018–08–03 The Boeing Company: Amendment 39–19256; Docket No. FAA–2018–0299; Product Identifier 2018–NM–060–AD. (a) Effective Date This AD is effective April 17, 2018. (b) Affected ADs None. PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 Within 3 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. Where figure 1 to paragraph (g) of this AD refers to a ‘‘Trent 1000 2 engine,’’ this term means all engines identified in paragraph (c) 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. E:\FR\FM\17APR1.SGM 17APR1 Federal Register / Vol. 83, No. 74 / Tuesday, April 17, 2018 / Rules and Regulations (h) Revision of Performance Chapter of AFM daltland on DSKBBV9HB2PROD 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 16:15 Apr 16, 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 00004 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. BILLING CODE 4910–13–P E:\FR\FM\17APR1.SGM 17APR1 ER17AP18.014</GPH> 16770 Federal Register / Vol. 83, No. 74 / Tuesday, April 17, 2018 / Rules and Regulations 16771 Figure 2 to paragraph (h) of this AD - AFM Performance Engine Appendix - Performance ETOPS ETOPS operation of a Model 787-8 or 787-9 airplane equipped with a RR Trent 1000 A2, C2, or E2 series engine 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 Enroute Diversion Temperature ISA+O Degrees C and Below ISA+ 10 Degrees C ISA+ 15 Degrees C ISA+20 Degrees C ISA+25 Degrees C Above ISA+25 Degrees C 19,000 19,000 18,800 18,500 18,300 Prohibited Maximum Planned Weight at LBS ETOPS Entry Point without KGS Forecast Icing 499,000 497,400 477,500 453,000 428,400 226,360 225,650 216,620 205,480 194,350 Maximum Planned Weight at LBS ETOPS Entry Point with KGS Forecast Icing 425,900 417,000 396,300 367,300 338,200 193,210 189,170 179,800 166,610 153,420 Minimum Engine-Out Cruise Altitude (ft) Prohibited Prohibited (D631Z003-9R7072F) and (D631Z003- 9R7072E) 787-9 Trent 1000-D2 Enroute 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 19,100 19,100 18,900 18,700 18,500 Prohibited Maximum Planned Weight at LBS ETOPS Entry Point without KGS Forecast Icing 510,300 508,400 488,200 465,800 443,400 231,500 230,640 221,480 211,310 201,130 Maximum Planned Weight at LBS ETOPS Entry Point with KGS Forecast lei ng 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) Prohibited Prohibited (D631Z003-9R74F) and (D631Z003-9R74E) 787-9 Trent 1000-J2 Enroute Diversion Temperature I 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 Maximum Planned Weight at LBS ETOPS Entry Point without KGS Forecast lei ng 530,400 527,800 507,800 479,500 451,100 240,600 239,430 230,370 217,510 204,640 Maximum Planned Weight at LBS ETOPS Entry Point with KGS Forecast Icing 455,200 446,600 430,200 401,400 372,500 206,470 202,580 195,140 182,070 169,000 daltland on DSKBBV9HB2PROD with RULES Altitude (ft) VerDate Sep<11>2014 16:15 Apr 16, 2018 Jkt 244001 Prohibited Prohibited PO 00000 Frm 00005 Fmt 4700 Sfmt 4725 E:\FR\FM\17APR1.SGM 17APR1 ER17AP18.015</GPH> Minimum Engine-Out Cruise 16772 Federal Register / Vol. 83, No. 74 / Tuesday, April 17, 2018 / Rules and Regulations (D631Z003-R7475F) and (D631Z003-R7475E 787-9 Trent 1000-K2 Enroute 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 Maximum Planned Weight at LBS ETOPS Entry Point without KGS Forecast Icing 530,400 527,800 507,800 479,500 451,100 240,600 239,430 230,370 217,510 204,640 Maximum Planned Weight at LBS ETOPS Entry Point with KGS Forecast Icing 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) Prohibited Prohibited D631Z003-R70EF) 787-8 Trent 1000-CE2 Enroute 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 18,900 18,600 Prohibited Maximum Planned Weight at LBS ETOPS Entry Point without KGS Forecast Icing 525,100 523,100 501,400 476,300 451,100 238,200 237,310 227,450 216,040 204,630 Maximum Planned Weight at LBS ETOPS Entry Point with KGS Forecast Icing 446,700 438,600 419,400 396,300 373,300 202,650 198,970 190,260 179,790 169,330 Minimum Engine-Out Cruise Altitude (ft) Prohibited Prohibited D631Z003-R7072F) and (D631Z003-R7072E) 787-8 Trent 1000-D2 Enroute Diversion Temperature ISA+O Degrees C and Below ISA+10 Degrees C ISA+ 15 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 Maximum Planned Weight at LBS ETOPS Entry Point without KGS Forecast Icing 525,100 523,100 501,400 476,300 451,100 238,200 237,310 227,450 216,040 204,630 Maximum Planned Weight at LBS ETOPS Entry Point with KGS Forecast Icing 446,700 438,600 419,400 396,300 373,300 202,650 198,970 190,260 179,790 169,330 Minimum Engine-Out Cruise Altitude (ft) Prohibited Prohibited D631Z003-R70LF) 787-8 Trent 1000-L2 Enroute Diversion Temperature ISA+O Degrees C and Below ISA+10 Degrees C ISA+ 15 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 Maximum Planned Weight at LBS ETOPS Entry Point without KGS Forecast Icing 525,100 523,100 501,400 476,300 451,100 238,200 237,310 227,450 216,040 204,630 Maximum Planned Weight at LBS ETOPS Entry Point with KGS Forecast Icing 446,700 438,600 419,400 396,300 373,300 202,650 198,970 190,260 179,790 169,330 daltland on DSKBBV9HB2PROD with RULES Altitude (ft) VerDate Sep<11>2014 16:15 Apr 16, 2018 Jkt 244001 Prohibited Prohibited PO 00000 Frm 00006 Fmt 4700 Sfmt 4725 E:\FR\FM\17APR1.SGM 17APR1 ER17AP18.016</GPH> Minimum Engine-Out Cruise Federal Register / Vol. 83, No. 74 / Tuesday, April 17, 2018 / Rules and Regulations daltland on DSKBBV9HB2PROD with RULES (i) 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 (j) 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 VerDate Sep<11>2014 16:15 Apr 16, 2018 Jkt 244001 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. Moines, WA 98198; phone and fax: 206–231– 3553; email: Takahisa.Kobayashi@faa.gov. (k) Material Incorporated by Reference None. Issued in Des Moines, Washington, on April 12, 2018. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–08127 Filed 4–16–18; 8:45 am] BILLING CODE 4910–13–P (j) Related Information For more information about this AD, contact Tak Kobayashi, Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch, 2200 South 216th Street, Des PO 00000 Frm 00007 Fmt 4700 Sfmt 9990 E:\FR\FM\17APR1.SGM 17APR1 ER17AP18.017</GPH> BILLING CODE 4910–13–C 16773

Agencies

[Federal Register Volume 83, Number 74 (Tuesday, April 17, 2018)]
[Rules and Regulations]
[Pages 16768-16773]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-08127]


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

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0299; Product Identifier 2018-NM-060-AD; Amendment 
39-19256; AD 2018-08-03]
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 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 are issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective April 17, 2018.
    We must receive comments on this AD by June 1, 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.

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-
0299; 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 Street, 
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 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. 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 intermediate 
pressure compressor (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 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, under 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 will further increase before a 
diversion can be safely completed.

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 operation.

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-
0299 and Product Identifier 2018-NM-060-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

[[Page 16769]]

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 per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
AFM revisions......................  1 work-hour x $85 per hour               $0             $85          $1,190
                                      = $85.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

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

2018-08-03 The Boeing Company: Amendment 39-19256; Docket No. FAA-
2018-0299; Product Identifier 2018-NM-060-AD.

(a) Effective Date

    This AD is effective April 17, 2018.

(b) Affected ADs

    None.

(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 3 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. Where figure 1 to paragraph (g) of this AD refers to 
a ``Trent 1000 2 engine,'' this term means all engines identified in 
paragraph (c) 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.

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(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.
BILLING CODE 4910-13-P

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BILLING CODE 4910-13-C

(i) 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 (j) 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.

(j) Related Information

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

(k) Material Incorporated by Reference

    None.

    Issued in Des Moines, Washington, on April 12, 2018.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2018-08127 Filed 4-16-18; 8:45 am]
 BILLING CODE 4910-13-P