Document ID: FAA-2018-0304-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: The Boeing Company Airplanes
Posted Date: 2018-04-26T04:00Z

[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]

=======================================================================
-----------------------------------------------------------------------

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]]

[GRAPHIC] [TIFF OMITTED] TR26AP18.003

[[Page 18213]]

[GRAPHIC] [TIFF OMITTED] TR26AP18.004

[[Page 18214]]

[GRAPHIC] [TIFF OMITTED] TR26AP18.005

[[Page 18215]]

[GRAPHIC] [TIFF OMITTED] TR26AP18.006

[[Page 18216]]

[GRAPHIC] [TIFF OMITTED] TR26AP18.007

[[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