[Federal Register Volume 84, Number 148 (Thursday, August 1, 2019)]
[Rules and Regulations]
[Pages 37570-37573]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-16329]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0567; Product Identifier 2019-NE-21-AD; Amendment
39-19698; AD 2019-15-05]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG
Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
Rolls-Royce Deutschland Ltd & Co KG (RRD) Trent 1000-AE3, Trent 1000-
CE3, Trent 1000-D3, Trent 1000-G3, Trent 1000-H3, Trent 1000-J3, Trent
1000-K3, Trent 1000-L3, Trent 1000-M3, Trent 1000-N3, Trent 1000-P3,
Trent 1000-Q3 and Trent 1000-R3 engines. This AD requires removal of
the affected high-pressure turbine (HPT) disk front cover plate before
reaching its new life limit. This AD was prompted by a recent analysis
that determined the HPT disk front cover plate may have a safe life
below its declared life limit. The FAA is issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective August 16, 2019.
The FAA must receive comments on this AD by September 16, 2019.
[[Page 37571]]
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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this final rule, contact
Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, United
Kingdom, DE24 8BJ; phone: 011-44-1332-242424; fax: 011-44-1332-249936;
email: royce.com">corporate.care@rolls-royce.com; internet: https://customers.rolls-royce.com/public/rollsroycecare. You may view this
service information at the FAA, Engine and Propeller Standards Branch,
1200 District Avenue, Burlington, MA 01803. For information on the
availability of this material at the FAA, call 781-238-7759. It is also
available on the internet at http://www.regulations.gov by searching
for and locating Docket No. FAA-2019-0567.
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-2019-
0567; 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 mandatory continuing airworthiness information
(MCAI), the regulatory evaluation, any comments received, and other
information. The street address for Docket Operations is listed above.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Besian Luga, Aerospace Engineer, ECO
Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-
238-7750; fax: 781-238-7199; email: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
The European Union Aviation Safety Agency (EASA), which is the
Technical Agent for the Member States of the European Community, has
issued EASA AD 2018-0164R1, dated March 14, 2019 (corrected copy dated
March 21, 2019) (referred to after this as ``the MCAI''), to address an
unsafe condition for the specified products. The MCAI states:
Following a recent analysis of the material condition used in
manufacture of these parts, it was established that the HP turbine
disc front cover plate may have a safe life below its declared safe
cyclic life (DSCL).
This condition, if not corrected, could lead to premature
failure of an affected part, possibly resulting in damage to the
engine and reduced control of the aeroplane.
To address this potential unsafe condition, RR published the
NMSB to provide the new DSCL and replacement instructions.
Consequently, EASA issued AD 2018-0164 to require implementation of
the reduced DSCL and removal from service of those affected parts
that have exceeded the reduced DSCL.
Since that [EASA] AD was issued, further analysis has resulted
in the approval of an extended life for the affected parts. RR has
published the TLM Task for this extended limit and it is expected
the NMSB will be cancelled accordingly.
You may obtain further information by examining the MCAI in the AD
docket on the internet at http://www.regulations.gov by searching for
and locating Docket No. FAA-2019-0567.
Related Service Information
The FAA reviewed Rolls-Royce plc (RR) Alert Service Bulletin (ASB)
TRENT1000 72-AK057, Initial Issue, dated April 10, 2018. The service
information describes procedures for either removing the engine
containing the affected HPT disk front cover plate or replacing the HPT
disk front cover plate during a shop visit.
FAA's Determination
This product has been approved by EASA and is approved for
operation in the United States. Pursuant to our bilateral agreement
with the European Community, EASA has notified us of the unsafe
condition described in the MCAI and service information referenced
above. The FAA is issuing this AD because we evaluated all the relevant
information provided by EASA 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 removal of the affected HPT disk front cover plate
from service before reaching its new life limit and replacing it with a
part eligible for installation.
Differences Between This AD and the MCAI or Service Information
This AD and EASA AD 2018-0164R1, dated March 14, 2019 (corrected
copy dated March 21, 2019) require removal of the affected HPT disk
front cover plate before accumulating 1,250 cycles since first
installation on an engine. RR ASB Trent1000 72-AK057, Initial Issue,
dated April 10, 2018, requires removal of the affected HPT disk front
cover plate before accumulating 865 cycles since first installation.
Since publication of the ASB, the manufacturer has revised its
analysis, which has resulted in an extension of the life limit for this
part to 1,250 cycles.
FAA's Justification and Determination of the Effective Date
No domestic operators use this product. Therefore, the FAA finds
good cause that notice and opportunity for prior public comment are
unnecessary. In addition, for the reason stated above, the FAA finds
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, the FAA invites 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-2019-
0567 and Product Identifier 2019-NE-21-AD at the beginning of your
comments. The FAA specifically invites comments on the overall
regulatory, economic, environmental, and energy aspects of this final
rule. The FAA will consider all comments received by the closing date
and may amend this final rule because of those comments.
The FAA will post all comments we receive, without change, to
http://www.regulations.gov, including any personal information you
provide. The FAA will also post a report summarizing each substantive
verbal contact we receive about this final rule.
Regulatory Flexibility Act
The requirements of the Regulatory Flexibility Act (RFA) do not
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt
a rule without prior notice and comment. Because the FAA has determined
that it has good cause to adopt this rule without notice and comment,
RFA analysis is not required.
[[Page 37572]]
Costs of Compliance
The FAA estimates that this AD affects 0 engines installed on
airplanes of U.S. registry.
The FAA estimates the following costs to comply with this AD:
Estimated Costs
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Replace HPT disk front cover plate.... 7 work-hours x $85 per $307,137 $307,732 $0
hour = $595.
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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.
The FAA is 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 engines, propellers, and
associated appliances to the Manager, Engine and Propeller Standards
Branch, Policy and Innovation 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 this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866, and
(2) Will not affect intrastate aviation in Alaska.
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):
2019-15-05 Rolls-Royce Deutschland Ltd & Co KG: Amendment 39-19698;
Docket No. FAA-2019-0567; Product Identifier 2019-NE-21-AD.
(a) Effective Date
This AD is effective August 16, 2019.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Rolls-Royce Deutschland Ltd & Co KG (RRD)
Trent 1000-AE3, Trent 1000-CE3, Trent 1000-D3, Trent 1000-G3, Trent
1000-H3, Trent 1000-J3, Trent 1000-K3, Trent 1000-L3, Trent 1000-M3,
Trent 1000-N3, Trent 1000-P3, Trent 1000-Q3 and Trent 1000-R3
engines.
(d) Subject
Joint Aircraft System Component (JASC) Code 7250, Turbine
Section.
(e) Unsafe Condition
This AD was prompted by recent analysis of the material
condition used in the manufacture of these parts that determined the
high-pressure turbine (HPT) disk front cover plate may have a safe
life below its declared safe cyclic life. The FAA is issuing this AD
to prevent failure of the HPT disk front cover plate. The unsafe
condition, if not addressed, could result in uncontained release of
the HPT turbine disk front cover plate, damage to the engine, and
damage to the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
Remove the HPT disk front cover plate, part number KH59279, from
service prior to it reaching 1,250 engine cycles since first
installation on an engine and replace with a part eligible for
installation.
(h) Installation Prohibition
Do not install any HPT disk front cover plate, part number
KH59279, into any engine, or any engine onto any airplane, if that
part has exceeded 1,250 engine cycles since first installation on an
engine.
(i) Alternative Methods of Compliance (AMOCs)
(1) The Manager, ECO 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.
(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.
(j) Related Information
(1) For more information about this AD, contact Besian Luga,
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue,
Burlington, MA 01803; phone: 781-238-7750; fax: 781-238-7199; email:
[email protected].
(2) Refer to European Union Aviation Safety Agency (EASA) AD
2018-0164R1, dated March 14, 2019 (corrected copy dated March 21,
2019), for more information. You may examine the EASA AD in the AD
docket on the internet at http://www.regulations.gov by searching
for and locating it in Docket No. FAA-2019-0567.
(k) Material Incorporated by Reference
None.
[[Page 37573]]
Issued in Burlington, Massachusetts, on July 26, 2019.
Karen M. Grant,
Acting Manager, Engine and Propeller Standards Branch, Aircraft
Certification Service.
[FR Doc. 2019-16329 Filed 7-31-19; 8:45 am]
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