Airworthiness Directives; Rolls-Royce plc Turbofan Engines, 37167-37169 [2014-14954]
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Federal Register / Vol. 79, No. 126 / Tuesday, July 1, 2014 / Rules and Regulations
1972(1), 3106, 3108, 3310, 3331–3351, 3907,
and 3909; 15 U.S.C. 1681s, 1681w, 6801 and
6805.
4. Amend Appendix F to part 225, as
follows:
■ a. In section I.C.2.b., remove
‘‘§ 216.3(h)’’ and add in its place
‘‘§ 1016.3(i)’’; and
■ b. In section I.C.2.c., remove
‘‘§ 216.3(n)’’ and add in its place
‘‘§ 1016.3(p).’’
■
By order of the Board of Governors of the
Federal Reserve System, acting through the
Secretary of the Board under delegated
authority, June 25, 2014.
Robert deV. Frierson,
Secretary of the Board.
[FR Doc. 2014–15292 Filed 6–30–14; 8:45 am]
BILLING CODE 6210–01–P
FEDERAL HOUSING FINANCE
AGENCY
12 CFR Part 1238
[No. 2014–N–8]
Order: Supplemental Order on
Reporting by Regulated Entities of
Stress Testing Results as of
September 30, 2013
Federal Housing Finance
Agency.
ACTION: Orders.
AGENCY:
In this document, the Federal
Housing Finance Agency (FHFA)
provides notice that it issued an Order
to supplement its Orders dated
November 26, 2013 and December 13,
2013, with respect to the reporting of
each Federal Home Loan Banks’ results
under section 165(i)(2) of the DoddFrank Wall Street Reform and Consumer
Protection Act (Dodd-Frank Act).
DATES: Effective July 1, 2014. The Order
is applicable June 24, 2014.
FOR FURTHER INFORMATION CONTACT: Naa
Awaa Tagoe, Senior Associate Director,
Office of Financial Analysis, Modeling
and Simulations, (202) 649–3140,
naaawaa.tagoe@fhfa.gov; Stefan
Szilagyi, Examination Manager,
FHLBank Modeling, FHLBank Risk
Modeling Branch, (202) 649–3515,
stefan.szilagy@fhfa.gov; or Mark D.
Laponsky, Deputy General Counsel,
Office of General Counsel, (202) 649–
3054 (these are not toll-free numbers),
mark.laponsky@fhfa.gov. The telephone
number for the Telecommunications
Device for the Hearing Impaired is (800)
877–8339.
SUPPLEMENTARY INFORMATION:
pmangrum on DSK3VPTVN1PROD with RULES
SUMMARY:
I. Background
FHFA is responsible for ensuring that
the regulated entities operate in a safe
VerDate Mar<15>2010
15:01 Jun 30, 2014
Jkt 232001
and sound manner, including the
maintenance of adequate capital and
internal controls, that their operations
and activities foster liquid, efficient,
competitive, and resilient national
housing finance markets, and that they
carry out their public policy missions
through authorized activities. See 12
U.S.C. 4513. The Supplemental Order is
being issued under 12 U.S.C. 4514(a),
which authorizes the Director of FHFA
to require by Order that the regulated
entities submit regular or special reports
to FHFA and establishes remedies and
procedures for failing to make reports
required by Order. The Supplemental
Order provides to the Federal Home
Loan Banks a revised template to use in
reporting to the public the severely
adverse results of their respective stress
tests.
II. Order
For the convenience of the affected
parties, the text of the Order, without
appendices, follows below in its
entirety. You may access this Order
with its attachment from FHFA’s Web
site at https://www.fhfa.gov/
SupervisionRegulation/
LegalDocuments/Pages/Orders.aspx.
The Order will be available for public
inspection and copying at the Federal
Housing Finance Agency, Eighth Floor,
400 Seventh St. SW., Washington, DC
20024. To make an appointment, call
(202) 649–3804.
The text of the Supplemental Order is
as follows:
Federal Housing Finance Agency
Order No. 2014–OR–B–1
SUPPLEMENTAL ORDER ON REPORTING
BY REGULATED ENTITIES OF STRESS
TESTING RESULTS AS OF SEPTEMBER 30,
2013
Whereas, section 165(i)(2) of the DoddFrank Wall Street Reform and Consumer
Protection Act (‘‘Dodd-Frank Act’’) requires
certain financial companies with total
consolidated assets of more than $10 billion,
and which are regulated by a primary Federal
financial regulatory agency, to conduct
annual stress tests to determine whether the
companies have the capital necessary to
absorb losses as a result of adverse economic
conditions;
Whereas, FHFA’s rule implementing
section 165(i)(2) of the Dodd-Frank Act is
codified as 12 CFR part 1238 and requires
that ‘‘[e]ach regulated entity must file a
report in the manner and form established by
FHFA.’’ 12 CFR § 1238.5(b);
Whereas, on November 26, 2013, FHFA
issued an Order to each regulated entity
accompanied by appendices numbered 1
through 10 and amended Summary
Instructions and Guidance relating to the
performance of stress tests as of September
30, 2013, and the reporting of the results of
such tests;
PO 00000
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37167
Whereas, on December 13, 2013, FHFA
issued a Supplemental Order to each
regulated entity providing two additional
appendices for use in reporting stress testing
results as of September 30, 2013;
Whereas, each of the Federal Home Loan
Banks timely submitted its stress test results
pursuant to 12 CFR part 1238 and the
implementing Orders, instructions, and
guidance;
Whereas, after analyzing the results of each
of the Federal Home Loan Banks’ stress
testing and the methodologies and practices
used in testing, FHFA has determined that
the original template designed for public
disclosure of the severely adverse test results
should be revised; and
Whereas, section 1314 of the Safety and
Soundness Act, 12 U.S.C. § 4514(a)
authorizes the Director of FHFA to require
regulated entities, by general or specific
order, to submit such reports on their
management, activities, and operations as the
Director considers appropriate.
Now Therefore, it is hereby ordered as
follows:
Each of the Federal Home Loan Banks
shall publicly report as required by 12
CFR part 1238 the severely adverse
results of the required stress testing
using the template provided herewith as
Attachment 1.
It is so ordered, this 24th day of June
2014
This Order is effective immediately.
Signed at Washington, DC, this 24th day of
June, 2014.
Melvin L. Watt,
Director, Federal Housing Finance Agency.
Dated: June 24, 2014.
Melvin L. Watt,
Director, Federal Housing Finance Agency.
[FR Doc. 2014–15396 Filed 6–30–14; 8:45 am]
BILLING CODE 8070–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0953; Directorate
Identifier 2013–NE–32–AD; Amendment 39–
17877; AD 2014–13–02]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
plc Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Rolls-Royce plc (RR) RB211-Trent 875–
17, 877–17, 884–17, 884B–17, 892–17,
892B–17, and 895–17 turbofan engines.
This AD requires inspection of the
SUMMARY:
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01JYR1
37168
Federal Register / Vol. 79, No. 126 / Tuesday, July 1, 2014 / Rules and Regulations
pmangrum on DSK3VPTVN1PROD with RULES
affected low-pressure (LP) turbine
bearing support and exhaust case
assembly and, if necessary, its
replacement with a part eligible for
installation. This AD was prompted by
thin-walled LP turbine bearing support
and exhaust case assemblies having
been delivered into service. We are
issuing this AD to prevent failure of the
LP turbine bearing support and exhaust
case assembly, which could lead to
engine separation and damage to the
airplane.
DATES: This AD becomes effective
August 5, 2014.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of August 5, 2014.
ADDRESSES: For service information
identified in this AD, contact RollsRoyce plc, Corporate Communications,
P.O. Box 31, Derby, England, DE248BJ;
phone: 011–44–1332–242424; fax: 011–
44–1332–249936; email: https://
www.rolls-royce.com/contact/civil_
team.jsp; Internet: https://
www.aeromanager.com. You may view
this service information at the FAA,
Engine & Propeller Directorate, 12 New
England Executive Park, Burlington,
MA. For information on the availability
of this material at the FAA, call (781)
238–7125.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2013–
0953; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the mandatory
continuing airworthiness information
(MCAI), the regulatory evaluation, any
comments received, and other
information. The address for the Docket
Office (phone: (800) 647–5527) is
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Eugene Triozzi, Aerospace Engineer,
Engine Certification Office, FAA, Engine
& Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
phone: (781) 238–7148; fax: (781) 238–
7199; email: eugene.triozzi@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
VerDate Mar<15>2010
15:01 Jun 30, 2014
Jkt 232001
part 39 by adding an AD that would
apply to the specified products. The
NPRM was published in the Federal
Register on March 3, 2014 (79 FR
11719). The NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
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.
Rolls-Royce has identified that limitations
in the drawing definition for the Trent 800
low-pressure (LP) turbine bearing support
and exhaust case assembly (EIPC 72–52–51,
03–300, also known as the tail bearing
housing or TBH) may have resulted in thinwall section parts being delivered into
service. Further analysis has concluded that
under certain circumstances, the structural
integrity of a thin-walled part may be
insufficient to withstand a fan blade failure
event.
This condition, if not detected and
corrected, could, in case of fan blade failure,
lead to a loss of integrity of the TBH and
leave the engine unsupported at the rear
mount, possibly resulting in damage to, or
reduced control of, the aeroplane.
We determined that 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,
(2) Is not a ‘‘significant rule’’ under
the DOT Regulatory Policies and
Procedures (44 FR 11034, February 26,
1979),
(3) Will not affect intrastate aviation
in Alaska to the extent that it justifies
making a regulatory distinction, 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.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comments received. The
commenters support the NPRM (79 FR
11719, March 3, 2014).
Conclusion
We reviewed the available data,
including the comments received, and
determined that air safety and the
public interest require adopting the AD
as proposed.
Costs of Compliance
We estimate that this AD affects about
110 engines installed on airplanes of
U.S. registry. We also estimate that it
will take about 1 hour per engine to
comply with this AD. The average labor
rate is $85 per hour. Required parts cost
about $9,250 per engine. Based on these
figures, we estimate the cost of this AD
on U.S. operators to be $92,600.
Regulatory Findings
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
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
PO 00000
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Fmt 4700
Sfmt 4700
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2014–13–02 Rolls-Royce plc: Amendment
39–17877; Docket No. FAA–2013–0953,
Directorate Identifier 2013–NE–32–AD.
(a) Effective Date
This AD becomes effective August 5, 2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Rolls-Royce plc (RR)
RB211-Trent 875–17, 877–17, 884–17, 884B–
17, 892–17, 892B–17, and 895–17 turbofan
engines, except those that have been
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01JYR1
Federal Register / Vol. 79, No. 126 / Tuesday, July 1, 2014 / Rules and Regulations
reworked in accordance with RR Service
Bulletin (SB) No. RB.211–72–G604, dated
March 18, 2013.
(d) Reason
This AD was prompted by the
identification by RR of limitations in the
drawing definition for the Trent 800 lowpressure (LP) turbine bearing support and
exhaust case assembly, which resulted in
thin-wall section parts being delivered into
service. We are issuing this AD to prevent
failure of the LP turbine bearing support and
exhaust case assembly, which could lead to
engine separation and damage to the
airplane.
(e) Actions and Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(1) For engines that have an LP turbine
bearing support and exhaust case assembly
identified by part number (P/N) and serial
number (S/N) in Table 1 to paragraph (e) of
this AD, installed, at the next engine shop
visit after the effective date of this AD, but
not later than June 30, 2017, replace the
assembly with one that is eligible for
installation.
(2) For engines with an LP turbine bearing
support and exhaust case assembly not
identified by P/N and S/N in Table 1 to
paragraph (e) of this AD, installed, at the next
piece-part exposure of the LP turbine bearing
support and exhaust case assembly after the
effective date of AD:
(i) Inspect the hub to conical panel weld
line thickness using paragraphs 3.B.(3)(a)
through 3.B.(3)(d)(iii) of RR Alert Service
Bulletin (ASB) No. RB.211–72–AG644, dated
April 30, 2013; and
(ii) Inspect the hub to conical panel flange
thickness using paragraphs 3.B.(4)(a) through
3.B.(4)(c)(v) of RR ASB No. RB.211–72–
AG644, dated April 30, 2013.
(iii) If the LP turbine bearing support and
exhaust case assembly does not pass the
inspections required by paragraphs (e)(2)(i)
and (e)(2)(ii) of this AD, replace the LP
turbine bearing support and exhaust case
assembly with one that is eligible for
installation.
TABLE 1 TO PARAGRAPH (e)—LP TURBINE BEARING SUPPORT AND EXHAUST CASE ASSEMBLY P/NS AND
S/NS
pmangrum on DSK3VPTVN1PROD with RULES
P/Ns
FK31446
FK31446
FK31446
FK31446
FK32232
FK32085
FK32085
FK31446
FK31446
...................................
...................................
...................................
...................................
...................................
...................................
...................................
...................................
...................................
S/Ns
118–01
209–01
216–01
232–01
113–01
268–01
269–01
022–01
028–01
(f) Definitions
The following definitions apply for the
purpose of this AD:
(1) An LP turbine bearing support and
exhaust case assembly is eligible for
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15:01 Jun 30, 2014
Jkt 232001
installation if it has passed the inspections of
paragraphs (e)(2)(i) and (e)(2)(ii) of this AD;
or has been reworked in accordance with RR
SB No. RB.211–72–G604, dated March 18,
2013.
(2) ‘‘Piece-part exposure’’ occurs whenever
the LP turbine bearing support and exhaust
case assembly is sufficiently exposed to do
the inspections required by paragraphs
(e)(2)(i) and (e)(2)(ii) of this AD.
(3) An ‘‘engine shop visit’’ is the induction
of an engine into the shop for maintenance
involving the separation of pairs of major
mating engine flanges, except that the
separation of engine flanges solely for the
purposes of transportation without
subsequent engine maintenance is not an
engine shop visit.
(g) Alternative Methods of Compliance
(AMOCs)
The Manager, Engine Certification Office,
FAA, may approve AMOCs to this AD. Use
the procedures found in 14 CFR 39.19 to
make your request.
(h) Related Information
(1) For more information about this AD,
contact Eugene Triozzi, Aerospace Engineer,
Engine Certification Office, FAA, Engine &
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
phone: (781) 238–7148; fax: (781) 238–7199;
email: eugene.triozzi@faa.gov.
(2) Refer to MCAI European Aviation
Safety Agency AD 2013–0223, dated
September 19, 2013, for more information.
You may examine the MCAI in the AD
docket on the Internet at https://
www.regulations.gov by searching for and
locating it in Docket No. FAA–2013–0953.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Rolls-Royce plc Service Bulletin No.
RB.211–72–G604, including Supplement,
dated March 18, 2013.
(ii) Rolls-Royce plc Alert Service Bulletin
No. RB.211–72–AG644, dated April 30, 2013.
(3) For RR service information identified in
this AD, contact Rolls-Royce plc, Corporate
Communications, P.O. Box 31, Derby,
England, DE248BJ; phone: 011–44–1332–
242424; fax: 011–44–1332–249936; email:
https://www.rolls-royce.com/contact/civil_
team.jsp; Internet: https://
www.aeromanager.com.
(4) You may view this service information
at FAA, Engine & Propeller Directorate, 12
New England Executive Park, Burlington,
MA. For information on the availability of
this material at the FAA, call (781) 238–7125.
(5) You may view this service information
at the National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
(202) 741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
PO 00000
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37169
Issued in Burlington, Massachusetts, on
June 16, 2014.
Colleen M. D’Alessandro,
Assistant Directorate Manager, Engine &
Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2014–14954 Filed 6–30–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0241; Directorate
Identifier 2014–CE–008–AD; Amendment
39–17880; AD 2014–13–05]
RIN 2120–AA64
Airworthiness Directives; British
Aerospace Regional Aircraft Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2007–10–
16 for all British Aerospace Regional
Aircraft Jetstream Model 3201 airplanes.
This AD results from mandatory
continuing airworthiness information
(MCAI) issued by an aviation authority
of another country to identify and
correct an unsafe condition on an
aviation product. The MCAI describes
the unsafe condition as the need to
incorporate revisions to the
Airworthiness Limitations section of the
Instructions for Continued
Airworthiness. We are issuing this AD
to require actions to address the unsafe
condition on these products.
DATES: This AD is effective August 5,
2014.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of August 5, 2014.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0241; or in person at the Docket
Management Facility, U.S. Department
of Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
For service information identified in
this AD, contact BAE Systems
(Operations) Limited, Customer
Information Department, Prestwick
International Airport, Ayrshire, KA9
2RW, Scotland, United Kingdom;
telephone: +44 1292 675207; fax: +44
SUMMARY:
E:\FR\FM\01JYR1.SGM
01JYR1
]]>Agencies
[Federal Register Volume 79, Number 126 (Tuesday, July 1, 2014)]
[Rules and Regulations]
[Pages 37167-37169]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-14954]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0953; Directorate Identifier 2013-NE-32-AD;
Amendment 39-17877; AD 2014-13-02]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Rolls-Royce plc (RR) RB211-Trent 875-17, 877-17, 884-17, 884B-17, 892-
17, 892B-17, and 895-17 turbofan engines. This AD requires inspection
of the
[[Page 37168]]
affected low-pressure (LP) turbine bearing support and exhaust case
assembly and, if necessary, its replacement with a part eligible for
installation. This AD was prompted by thin-walled LP turbine bearing
support and exhaust case assemblies having been delivered into service.
We are issuing this AD to prevent failure of the LP turbine bearing
support and exhaust case assembly, which could lead to engine
separation and damage to the airplane.
DATES: This AD becomes effective August 5, 2014.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of August 5,
2014.
ADDRESSES: For service information identified in this AD, contact
Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, England,
DE248BJ; phone: 011-44-1332-242424; fax: 011-44-1332-249936; email:
https://www.rolls-royce.com/contact/civil_team.jsp; Internet: https://www.aeromanager.com. You may view this service information at the FAA,
Engine & Propeller Directorate, 12 New England Executive Park,
Burlington, MA. For information on the availability of this material at
the FAA, call (781) 238-7125.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2013-
0953; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the mandatory continuing airworthiness information
(MCAI), the regulatory evaluation, any comments received, and other
information. The address for the Docket Office (phone: (800) 647-5527)
is Document Management Facility, U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Eugene Triozzi, Aerospace Engineer,
Engine Certification Office, FAA, Engine & Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; phone: (781) 238-
7148; fax: (781) 238-7199; email: eugene.triozzi@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to the specified products. The
NPRM was published in the Federal Register on March 3, 2014 (79 FR
11719). The NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
Rolls-Royce has identified that limitations in the drawing
definition for the Trent 800 low-pressure (LP) turbine bearing
support and exhaust case assembly (EIPC 72-52-51, 03-300, also known
as the tail bearing housing or TBH) may have resulted in thin-wall
section parts being delivered into service. Further analysis has
concluded that under certain circumstances, the structural integrity
of a thin-walled part may be insufficient to withstand a fan blade
failure event.
This condition, if not detected and corrected, could, in case of
fan blade failure, lead to a loss of integrity of the TBH and leave
the engine unsupported at the rear mount, possibly resulting in
damage to, or reduced control of, the aeroplane.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comments received. The commenters support
the NPRM (79 FR 11719, March 3, 2014).
Conclusion
We reviewed the available data, including the comments received,
and determined that air safety and the public interest require adopting
the AD as proposed.
Costs of Compliance
We estimate that this AD affects about 110 engines installed on
airplanes of U.S. registry. We also estimate that it will take about 1
hour per engine to comply with this AD. The average labor rate is $85
per hour. Required parts cost about $9,250 per engine. Based on these
figures, we estimate the cost of this AD on U.S. operators to be
$92,600.
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.
Regulatory Findings
We determined that 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,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska to the extent
that it justifies making a regulatory distinction, 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):
2014-13-02 Rolls-Royce plc: Amendment 39-17877; Docket No. FAA-2013-
0953, Directorate Identifier 2013-NE-32-AD.
(a) Effective Date
This AD becomes effective August 5, 2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Rolls-Royce plc (RR) RB211-Trent 875-17,
877-17, 884-17, 884B-17, 892-17, 892B-17, and 895-17 turbofan
engines, except those that have been
[[Page 37169]]
reworked in accordance with RR Service Bulletin (SB) No. RB.211-72-
G604, dated March 18, 2013.
(d) Reason
This AD was prompted by the identification by RR of limitations
in the drawing definition for the Trent 800 low-pressure (LP)
turbine bearing support and exhaust case assembly, which resulted in
thin-wall section parts being delivered into service. We are issuing
this AD to prevent failure of the LP turbine bearing support and
exhaust case assembly, which could lead to engine separation and
damage to the airplane.
(e) Actions and Compliance
Comply with this AD within the compliance times specified,
unless already done.
(1) For engines that have an LP turbine bearing support and
exhaust case assembly identified by part number (P/N) and serial
number (S/N) in Table 1 to paragraph (e) of this AD, installed, at
the next engine shop visit after the effective date of this AD, but
not later than June 30, 2017, replace the assembly with one that is
eligible for installation.
(2) For engines with an LP turbine bearing support and exhaust
case assembly not identified by P/N and S/N in Table 1 to paragraph
(e) of this AD, installed, at the next piece-part exposure of the LP
turbine bearing support and exhaust case assembly after the
effective date of AD:
(i) Inspect the hub to conical panel weld line thickness using
paragraphs 3.B.(3)(a) through 3.B.(3)(d)(iii) of RR Alert Service
Bulletin (ASB) No. RB.211-72-AG644, dated April 30, 2013; and
(ii) Inspect the hub to conical panel flange thickness using
paragraphs 3.B.(4)(a) through 3.B.(4)(c)(v) of RR ASB No. RB.211-72-
AG644, dated April 30, 2013.
(iii) If the LP turbine bearing support and exhaust case
assembly does not pass the inspections required by paragraphs
(e)(2)(i) and (e)(2)(ii) of this AD, replace the LP turbine bearing
support and exhaust case assembly with one that is eligible for
installation.
Table 1 to Paragraph (e)--LP Turbine Bearing Support and Exhaust Case
Assembly P/Ns and S/Ns
------------------------------------------------------------------------
P/Ns S/Ns
------------------------------------------------------------------------
FK31446.................................................... 118-01
FK31446.................................................... 209-01
FK31446.................................................... 216-01
FK31446.................................................... 232-01
FK32232.................................................... 113-01
FK32085.................................................... 268-01
FK32085.................................................... 269-01
FK31446.................................................... 022-01
FK31446.................................................... 028-01
------------------------------------------------------------------------
(f) Definitions
The following definitions apply for the purpose of this AD:
(1) An LP turbine bearing support and exhaust case assembly is
eligible for installation if it has passed the inspections of
paragraphs (e)(2)(i) and (e)(2)(ii) of this AD; or has been reworked
in accordance with RR SB No. RB.211-72-G604, dated March 18, 2013.
(2) ``Piece-part exposure'' occurs whenever the LP turbine
bearing support and exhaust case assembly is sufficiently exposed to
do the inspections required by paragraphs (e)(2)(i) and (e)(2)(ii)
of this AD.
(3) An ``engine shop visit'' is the induction of an engine into
the shop for maintenance involving the separation of pairs of major
mating engine flanges, except that the separation of engine flanges
solely for the purposes of transportation without subsequent engine
maintenance is not an engine shop visit.
(g) Alternative Methods of Compliance (AMOCs)
The Manager, Engine Certification Office, FAA, may approve AMOCs
to this AD. Use the procedures found in 14 CFR 39.19 to make your
request.
(h) Related Information
(1) For more information about this AD, contact Eugene Triozzi,
Aerospace Engineer, Engine Certification Office, FAA, Engine &
Propeller Directorate, 12 New England Executive Park, Burlington, MA
01803; phone: (781) 238-7148; fax: (781) 238-7199; email:
eugene.triozzi@faa.gov.
(2) Refer to MCAI European Aviation Safety Agency AD 2013-0223,
dated September 19, 2013, for more information. You may examine the
MCAI in the AD docket on the Internet at https://www.regulations.gov
by searching for and locating it in Docket No. FAA-2013-0953.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Rolls-Royce plc Service Bulletin No. RB.211-72-G604,
including Supplement, dated March 18, 2013.
(ii) Rolls-Royce plc Alert Service Bulletin No. RB.211-72-AG644,
dated April 30, 2013.
(3) For RR service information identified in this AD, contact
Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby,
England, DE248BJ; phone: 011-44-1332-242424; fax: 011-44-1332-
249936; email: https://www.rolls-royce.com/contact/civil_team.jsp;
Internet: https://www.aeromanager.com.
(4) You may view this service information at FAA, Engine &
Propeller Directorate, 12 New England Executive Park, Burlington,
MA. For information on the availability of this material at the FAA,
call (781) 238-7125.
(5) You may view this service information at the National
Archives and Records Administration (NARA). For information on the
availability of this material at NARA, call (202) 741-6030, or go
to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Burlington, Massachusetts, on June 16, 2014.
Colleen M. D'Alessandro,
Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2014-14954 Filed 6-30-14; 8:45 am]
BILLING CODE 4910-13-P
