83 FR 16768 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 74 (April 17, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 74 (April 17, 2018)
| Page Range | 16768-16773 | |
| FR Document | 2018-08127 |
[Federal Register Volume 83, Number 74 (Tuesday, April 17, 2018)] [Rules and Regulations] [Pages 16768-16773] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-08127] ======================================================================= ----------------------------------------------------------------------- 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. [[Page 16770]] [GRAPHIC] [TIFF OMITTED] TR17AP18.014 (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 [[Page 16771]] [GRAPHIC] [TIFF OMITTED] TR17AP18.015 [[Page 16772]] [GRAPHIC] [TIFF OMITTED] TR17AP18.016 [[Page 16773]] [GRAPHIC] [TIFF OMITTED] TR17AP18.017 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
![16768 Federal Register / Vol. 83, No. 74 / Tuesday, April 17, 2018 / Rules and Regulations
Signed in Washington, DC, on April 12, p.m., Monday through Friday, except condition. Therefore, an ETOPS
2018. Federal holidays. diversion will put the remaining engine
Heather Manzano, at an operating condition that would
Examining the AD Docket
Acting Manager, Federal Crop Insurance significantly increase the likelihood of
Corporation. You may examine the AD docket on failure of the remaining engine. In
[FR Doc. 2018–08016 Filed 4–16–18; 8:45 am] the internet at http:// addition, if the remaining engine
BILLING CODE 3410–08–P www.regulations.gov by searching for already had cracked IPC stage 2 blades,
and locating Docket No. FAA–2018– the likelihood of the remaining engine
0299; or in person at Docket Operations failing will further increase before a
DEPARTMENT OF TRANSPORTATION between 9 a.m. and 5 p.m., Monday diversion can be safely completed.
through Friday, except Federal holidays.
The AD docket contains this final rule, FAA’s Determination
Federal Aviation Administration
the regulatory evaluation, any We are issuing this AD because we
14 CFR Part 39 comments received, and other evaluated all the relevant information
information. The street address for and determined the unsafe condition
[Docket No. FAA–2018–0299; Product
Docket Operations (phone: 800–647– described previously is likely to exist or
Identifier 2018–NM–060–AD; Amendment
39–19256; AD 2018–08–03] 5527) is in the ADDRESSES section. develop in other products of the same
Comments will be available in the AD type design.
RIN 2120–AA64 docket shortly after receipt.
AD Requirements
FOR FURTHER INFORMATION CONTACT: Tak
Airworthiness Directives; The Boeing
Kobayashi, Aerospace Engineer, This AD requires revising the AFM to
Company Airplanes
Propulsion Section, FAA, Seattle ACO limit ETOPS operation.
AGENCY: Federal Aviation Branch, 2200 South 216th Street, Des
Moines, WA 98198; phone and fax: 206– Interim Action
Administration (FAA), DOT.
ACTION: Final rule; request for 231–3553; email: Takahisa.Kobayashi@ This AD is interim action. The
comments. faa.gov. manufacturer is currently developing a
SUPPLEMENTARY INFORMATION: modification that will address the
SUMMARY: We are adopting a new unsafe condition identified in this AD.
airworthiness directive (AD) for The Discussion Once this modification is developed,
Boeing Company Model 787–8 and 787– Over the past year, we have been approved, and available, we might
9 airplanes powered by Rolls-Royce plc aware of several engine failures of Trent consider additional rulemaking.
(RR) Trent 1000–A2, Trent 1000–AE2, 1000 Package C engines due to failed
Trent 1000–C2, Trent 1000–CE2, Trent FAA’s Justification and Determination
compressor and turbine blades and of the Effective Date
1000–D2, Trent 1000–E2, Trent 1000– seals. Package C engines are Rolls-Royce
G2, Trent 1000–H2, Trent 1000–J2, plc (RR) Trent 1000–A2, Trent 1000– An unsafe condition exists that
Trent 1000–K2, and Trent 1000–L2 AE2, Trent 1000–C2, Trent 1000–CE2, requires the immediate adoption of this
turbofan engines. This AD requires Trent 1000–D2, Trent 1000–E2, Trent AD without providing an opportunity
revising the airplane flight manual to 1000–G2, Trent 1000–H2, Trent 1000– for public comments prior to adoption.
limit extended operations (ETOPS). This J2, Trent 1000–K2, and Trent 1000–L2 The FAA has found that the risk to the
AD was prompted by a report from the turbofan engines. During that same flying public justifies waiving notice
engine manufacturer indicating that period, under the management programs and comment prior to adoption of this
after an engine failure, prolonged for those engine issues, we have been rule because unrecoverable thrust loss
operation at high thrust settings on the aware of numerous reports of engine on both engines could lead to a forced
remaining engine during an ETOPS inspection findings of cracked blades landing. Therefore, we find good cause
diversion may result in failure of the resulting in unscheduled engine that notice and opportunity for prior
remaining engine before the diversion removals. Boeing reported to the FAA public comment are impracticable. In
can be safely completed. We are issuing that the engine manufacturer recently addition, for the reasons stated above,
this AD to address the unsafe condition determined that intermediate pressure we find that good cause exists for
on these products. compressor (IPC) stage 2 blades have a making this amendment effective in less
DATES: This AD is effective April 17, resonant frequency that is excited by the than 30 days.
2018. airflow conditions existing in the engine
We must receive comments on this Comments Invited
during operation at high thrust settings
AD by June 1, 2018. under certain temperature and altitude This AD is a final rule that involves
ADDRESSES: You may send comments, conditions. The resultant blade requirements affecting flight safety and
using the procedures found in 14 CFR vibration can result in cumulative was not preceded by notice and an
11.43 and 11.45, by any of the following fatigue damage that can cause blade opportunity for public comment.
methods: failure and consequent engine However, we invite you to send any
• Federal eRulemaking Portal: Go to shutdown. In the event of a single written data, views, or arguments about
http://www.regulations.gov. Follow the engine in-flight shutdown during the this final rule. Send your comments to
instructions for submitting comments. cruise phase of flight, thrust on the an address listed under the ADDRESSES
• Fax: 202–493–2251. remaining engine is normally increased section. Include the docket number
• Mail: U.S. Department of to maximum continuous thrust (MCT). FAA–2018–0299 and Product Identifier
daltland on DSKBBV9HB2PROD with RULES
Transportation, Docket Operations, M– During a diversion following a single 2018–NM–060–AD at the beginning of
30, West Building Ground Floor, Room engine shutdown under an ETOPS your comments. We specifically invite
W12–140, 1200 New Jersey Avenue SE, flight, the remaining engine may operate comments on the overall regulatory,
Washington, DC 20590. at MCT for a prolonged period, under economic, environmental, and energy
• Hand Delivery: Deliver to Mail which the IPC stage 2 blades would be aspects of this final rule. We will
address above between 9 a.m. and 5 exposed to the resonant frequency consider all comments received by the
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![Federal Register / Vol. 83, No. 74 / Tuesday, April 17, 2018 / Rules and Regulations 16769
closing date and may amend this final personal information you provide. We Costs of Compliance
rule because of those comments. will also post a report summarizing each We estimate that this AD affects 14
We will post all comments we substantive verbal contact we receive airplanes of U.S. registry. We estimate
receive, without change, to http:// about this final rule. the following costs to comply with this
www.regulations.gov, including any AD:
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
AFM revisions ......................... 1 work-hour × $85 per hour = $85 ......................................... $0 $85 $1,190
Authority for This Rulemaking responsibilities among the various (c) Applicability
Title 49 of the United States Code levels of government. This AD applies to The Boeing Company
For the reasons discussed above, I Model 787–8 and 787–9 airplanes,
specifies the FAA’s authority to issue
certify that this AD: certificated in any category, powered by
rules on aviation safety. Subtitle I,
(1) Is not a ‘‘significant regulatory Rolls-Royce plc (RR) Trent 1000–A2, Trent
section 106, describes the authority of
action’’ under Executive Order 12866, 1000–AE2, Trent 1000–C2, Trent 1000–CE2,
the FAA Administrator. ‘‘Subtitle VII: (2) Is not a ‘‘significant rule’’ under Trent 1000–D2, Trent 1000–E2, Trent 1000–
Aviation Programs’’ describes in more DOT Regulatory Policies and Procedures G2, Trent 1000–H2, Trent 1000–J2, Trent
detail the scope of the Agency’s (44 FR 11034, February 26, 1979), 1000–K2, and Trent 1000–L2 turbofan
authority. (3) Will not affect intrastate aviation engines.
We are issuing this rulemaking under in Alaska, and (d) Subject
the authority described in Subtitle VII, (4) Will not have a significant
Part A, Subpart III, Section 44701: Air Transport Association (ATA) of
economic impact, positive or negative, America Code 71, Power plant.
‘‘General requirements.’’ Under that on a substantial number of small entities
section, Congress charges the FAA with under the criteria of the Regulatory (e) Unsafe Condition
promoting safe flight of civil aircraft in Flexibility Act. This AD was prompted by a report from
air commerce by prescribing regulations the engine manufacturer indicating that after
for practices, methods, and procedures List of Subjects in 14 CFR Part 39 an engine failure, prolonged operation at
the Administrator finds necessary for Air transportation, Aircraft, Aviation high thrust settings on the remaining engine
safety in air commerce. This regulation safety, Incorporation by reference, during an extended-operation (ETOPS)
is within the scope of that authority Safety. diversion may result in failure of the
because it addresses an unsafe condition remaining engine before the diversion can be
that is likely to exist or develop on Adoption of the Amendment safely completed. We are issuing this AD to
Accordingly, under the authority address unrecoverable thrust loss on both
products identified in this rulemaking
engines, which could lead to a forced
action. delegated to me by the Administrator,
landing.
This AD is issued in accordance with the FAA amends 14 CFR part 39 as
authority delegated by the Executive follows: (f) Compliance
Director, Aircraft Certification Service, Comply with this AD within the
as authorized by FAA Order 8000.51C. PART 39—AIRWORTHINESS compliance times specified, unless already
In accordance with that order, issuance DIRECTIVES done.
of ADs is normally a function of the (g) Revision of Limitations Chapter in
■ 1. The authority citation for part 39
Compliance and Airworthiness Airplane Flight Manual (AFM)
continues to read as follows:
Division, but during this transition Within 3 days after the effective date of
period, the Executive Director has Authority: 49 U.S.C. 106(g), 40113, 44701.
this AD, revise the Certificate Limitations
delegated the authority to issue ADs § 39.13 [Amended] chapter of the applicable Boeing AFM Engine
applicable to transport category Appendix by incorporating the information
airplanes and associated appliances to ■ 2. The FAA amends § 39.13 by adding in figure 1 to paragraph (g) of this AD. Where
the Director of the System Oversight the following new airworthiness figure 1 to paragraph (g) of this AD refers to
Division. directive (AD): a ‘‘Trent 1000 2 engine,’’ this term means all
2018–08–03 The Boeing Company: engines identified in paragraph (c) of this
Regulatory Findings Amendment 39–19256; Docket No. AD. This may be accomplished by inserting
This AD will not have federalism FAA–2018–0299; Product Identifier a copy of this AD into the AFM. When
2018–NM–060–AD. information identical to that in figure 1 to
implications under Executive Order paragraph (g) of this AD has been included
13132. This AD will not have a (a) Effective Date in the Certificate Limitations chapter of the
substantial direct effect on the States, on This AD is effective April 17, 2018. general revisions of the AFM, the general
the relationship between the national revisions may be inserted into the AFM, and
government and the States, or on the (b) Affected ADs the copy of this AD may be removed from the
distribution of power and None. AFM.
daltland on DSKBBV9HB2PROD with RULES
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Document Created: 2018-04-17 02:52:12
Document Modified: 2018-04-17 02:52:12
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule; request for comments. | |
| Dates | This AD is effective April 17, 2018. | |
| 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] | |
| FR Citation | 83 FR 16768 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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