Airworthiness Directives; Rolls-Royce plc Turbofan Engines, 11719-11721 [2014-04350]
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Federal Register / Vol. 79, No. 41 / Monday, March 3, 2014 / Proposed Rules
interface, which could result in reduced
structural integrity of the airframe.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Retained Inspection With Reduced
Compliance Times and Revised Service
Information
This paragraph restates the requirements of
paragraph (f)(1) of AD 2008–14–17,
Amendment 39–15612 (73 FR 40958, July 17,
2008), with reduced compliance times and
revised service information. For Airbus
Model A330–200 series airplanes, as
identified in paragraph (c) of this AD, on
which Modification 45012 has been
embodied in production: Within the
applicable compliance times specified in
paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of
this AD, do the HFEC inspection for cracking,
and corrective actions as applicable; and
modify the upper shell structure of the
fuselage; in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A330–53–3152,
Revision 3, dated December 22, 2011. Do all
applicable corrective actions before further
flight.
(1) For airplanes pre-modification 48827
with short range utilization: At the later of
the times specified in paragraph (g)(1)(i) or
(g)(1)(ii) of this AD.
(i) Prior to 24,400 total flight cycles or
85,400 total flight hours, whichever occurs
first.
(ii) Within 12 months after the effective
date of this AD without exceeding 25,400
total flight cycles.
(2) For airplanes pre-modification 48827
with long range utilization: At the later of the
times specified in paragraph (g)(2)(i) or
(g)(2)(ii) of this AD.
(i) Prior to 18,900 total flight cycles or
122,900 total flight hours, whichever occurs
first.
(ii) Within 12 months after the effective
date of this AD without exceeding 25,400
total flight cycles.
(3) For airplanes post-modification 48827
with short range utilization: At the later of
the times specified in paragraph (g)(3)(i) or
(g)(3)(ii) of this AD.
(i) Prior to 16,400 total flight cycles or
57,400 total flight hours, whichever occurs
first.
(ii) Within 12 months after the effective
date of this AD without exceeding 17,100
total flight cycles or 94,700 total flight hours,
whichever occurs first.
(4) For airplanes post-modification 48827
with long range utilization: At the later of the
times specified in paragraph (g)(4)(i) or
(g)(4)(ii) of this AD.
(i) Prior to 12,700 total flight cycles or
82,700 total flight hours, whichever occurs
first.
(ii) Within 12 months after the effective
date of this AD without exceeding 17,100
total flight cycles or 94,700 total flight hours,
whichever occurs first.
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16:22 Feb 28, 2014
Jkt 232001
(h) Retained Modification With Revised
Formatting
This paragraph restates the requirements of
paragraph (f)(2) of AD 2008–14–17,
Amendment 39–15612 (73 FR 40958, July 17,
2008). For Airbus Model A330–200 and
A340–300 series airplanes as identified in
paragraph (c) of this AD, on which
Modification 45012 has not been embodied
in production: At the later of the compliance
times specified in paragraphs (h)(1) and
(h)(2) of this AD, modify the upper shell
structure of the fuselage, in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A330–53–3157 or Airbus
Service Bulletin A340–53–4163, both dated
July 5, 2006, as applicable.
(1) For the airplanes identified in
paragraphs (h)(1)(i) and (h)(1)(ii) of this AD.
(i) For Model A330–200 series airplanes,
prior to 6,600 total flight cycles.
(ii) For Model A340–300 series airplanes,
prior to 14,000 total flight cycles.
(2) Within 90 days after August 21, 2008
(the effective date of AD 2008–14–17,
Amendment 39–15612 (73 FR 40958, July 17,
2008)).
(i) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraph (g) of this AD, if those
actions were performed before the effective
date of this AD using the service information
specified in paragraph (i)(1), (i)(2), or (i)(3) of
this AD.
(1) Airbus Mandatory Service Bulletin
A330–53–3152, dated April 10, 2007.
(2) Airbus Mandatory Service Bulletin
A330–53–3152, Revision 1, dated May 5,
2009.
(3) Airbus Mandatory Service Bulletin
A330–53–3152, Revision 2, dated July 27,
2011.
(j) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, 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 International Branch, send it to ATTN:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone (425) 227–1138; fax (425) 227–
1149. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov.
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. The AMOC
approval letter must specifically reference
this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer, use these actions if they are
FAA-approved. Corrective actions are
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Sfmt 4702
11719
considered FAA-approved if they were
approved by the State of Design Authority (or
its delegated agent, or by the DAH with a
State of Design Authority’s design
organization approval, as applicable). You
are required to ensure the product is
airworthy before it is returned to service.
(k) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) European
Aviation Safety Agency Airworthiness
Directive 2013–0158, dated July 22, 2013, for
related information. This MCAI may be
found in the AD docket on the Internet at
https://www.regulations.gov by searching for
and locating Docket No. FAA–2014–0121.
(2) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330–A340@airbus.com;
Internet https://www.airbus.com. You may
view this service information at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information
on the availability of this material at the
FAA, call 425–227–1221.
Issued in Renton, Washington, on February
14, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–04501 Filed 2–28–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0953; Directorate
Identifier 2013–NE–32–AD]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
plc Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to adopt 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.
The proposed AD was prompted by
thin-walled low pressure (LP) turbine
bearing support and exhaust case
assemblies having been delivered into
service. This proposed AD would
require inspection of the affected LP
turbine bearing support and exhaust
case assembly and, if necessary, its
replacement with a part eligible for
installation. We are proposing this AD
to prevent failure of the LP turbine
E:\FR\FM\03MRP1.SGM
03MRP1
11720
Federal Register / Vol. 79, No. 41 / Monday, March 3, 2014 / Proposed Rules
bearing support and exhaust case
assembly, which could lead to engine
separation and damage to the airplane.
DATES: We must receive comments on
this proposed AD by May 2, 2014.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov and follow
the instructions for sending your
comments electronically.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 1200
New Jersey Avenue SE., West Building
Ground Floor, Room W12–140,
Washington, DC 20590–0001.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
• Fax: 202–493–2251.
For service information identified in
this proposed 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; Web site: 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.
mstockstill on DSK4VPTVN1PROD with PROPOSALS
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
Operations office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The AD docket
contains this proposed AD, the
mandatory continuing airworthiness
information (MCAI), the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (phone:
800–647–5527) is the same as the Mail
address provided in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
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:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
VerDate Mar<15>2010
16:22 Feb 28, 2014
Jkt 232001
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2013–0953; Directorate Identifier
2013–NE–32–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of the Web
site, anyone can find and read the
comments in any of our dockets,
including, if provided, the name of the
individual who sent the comment (or
signed the comment on behalf of an
association, business, labor union, etc.).
You may review the DOT’s complete
Privacy Act Statement in the Federal
Register published on April 11, 2000
(65 FR 19477–78).
Relevant Service Information
Discussion
Costs of Compliance
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA AD 2013–
0223, dated September 19, 2013
(referred to hereinafter as ‘‘the MCAI’’),
to correct an unsafe condition for the
specified products. The MCAI states:
We estimate that this proposed AD
would affect about 110 engines installed
on airplanes of U.S. registry. We also
estimate that it would take about 1 hour
per product to comply with this
proposed AD. The average labor rate is
$85 per hour. Required parts cost about
$9,250. Based on these figures, we
estimate the cost of the proposed AD on
U.S. operators to be $92,600.
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.
This condition, if not addressed, may
allow failure of the LP turbine bearing
support and exhaust case assembly,
which could lead to engine separation
and damage to the airplane. 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.
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Fmt 4702
Sfmt 4702
RR has issued Alert Service Bulletin
(ASB) No. RB.211–72–AG644, dated
April 30, 2013. The ASB provides
guidance for rework or inspection of the
LP turbine bearing support and exhaust
case assembly.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of the United
Kingdom 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. We are proposing this
AD because we evaluated all
information provided by EASA and
determined the unsafe condition exists
and is likely to exist or develop on other
products of the same type design. This
proposed AD would require inspection
of the affected LP turbine bearing
support and exhaust case assembly and,
if necessary, its replacement with a part
eligible for installation.
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.
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Federal Register / Vol. 79, No. 41 / Monday, March 3, 2014 / Proposed Rules
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would 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 proposed regulation:
(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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 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.
§ 39.13
[Amended]
2. Amend § 39.13 by adding the
following new airworthiness directive
(AD):
■
reworked in accordance with RR Service
Bulletin (SB) RB.211–72–G604, dated March
18, 2013.
(d) Reason
This AD was prompted by 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) 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 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/N
FK31446
FK31446
FK31446
FK31446
FK32232
FK32085
FK32085
FK31446
FK31446
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Rolls-Royce plc: Docket No. FAA–2013–
0953; Directorate Identifier 2013–NE–
32–AD.
(a) Comments Due Date
We must receive comments by May 2,
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
VerDate Mar<15>2010
16:22 Feb 28, 2014
Jkt 232001
S/N
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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Sfmt 9990
11721
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
Service Bulletin (SB) 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.
(3) RR SB No. RB.211–72–G604, dated
March 18, 2013, which is not incorporated by
reference in this AD, can be obtained from
Rolls-Royce plc using the contact information
in paragraph (h)(4) of this AD.
(4) 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; Web site: https://
www.aeromanager.com.
(5) 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.
Issued in Burlington, Massachusetts, on
February 20, 2014.
Colleen M. D’Alessandro,
Assistant Directorate Manager, Engine &
Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2014–04350 Filed 2–28–14; 8:45 am]
BILLING CODE 4910–13–P
E:\FR\FM\03MRP1.SGM
03MRP1
Agencies
[Federal Register Volume 79, Number 41 (Monday, March 3, 2014)]
[Proposed Rules]
[Pages 11719-11721]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-04350]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0953; Directorate Identifier 2013-NE-32-AD]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt 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. The proposed AD was
prompted by thin-walled low pressure (LP) turbine bearing support and
exhaust case assemblies having been delivered into service. This
proposed AD would require inspection of the affected LP turbine bearing
support and exhaust case assembly and, if necessary, its replacement
with a part eligible for installation. We are proposing this AD to
prevent failure of the LP turbine
[[Page 11720]]
bearing support and exhaust case assembly, which could lead to engine
separation and damage to the airplane.
DATES: We must receive comments on this proposed AD by May 2, 2014.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 1200 New Jersey Avenue SE., West Building Ground Floor,
Room W12-140, Washington, DC 20590-0001.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Fax: 202-493-2251.
For service information identified in this proposed 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; Web site: 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 Operations office between 9 a.m. and 5
p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the mandatory continuing airworthiness
information (MCAI), the regulatory evaluation, any comments received,
and other information. The street address for the Docket Operations
office (phone: 800-647-5527) is the same as the Mail address provided
in the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
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:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2013-0953;
Directorate Identifier 2013-NE-32-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact
with FAA personnel concerning this proposed AD. Using the search
function of the Web site, anyone can find and read the comments in any
of our dockets, including, if provided, the name of the individual who
sent the comment (or signed the comment on behalf of an association,
business, labor union, etc.). You may review the DOT's complete Privacy
Act Statement in the Federal Register published on April 11, 2000 (65
FR 19477-78).
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
AD 2013-0223, dated September 19, 2013 (referred to hereinafter as
``the MCAI''), 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.
This condition, if not addressed, may allow failure of the LP
turbine bearing support and exhaust case assembly, which could lead to
engine separation and damage to the airplane. 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.
Relevant Service Information
RR has issued Alert Service Bulletin (ASB) No. RB.211-72-AG644,
dated April 30, 2013. The ASB provides guidance for rework or
inspection of the LP turbine bearing support and exhaust case assembly.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of the
United Kingdom 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. We are proposing this AD because
we evaluated all information provided by EASA and determined the unsafe
condition exists and is likely to exist or develop on other products of
the same type design. This proposed AD would require inspection of the
affected LP turbine bearing support and exhaust case assembly and, if
necessary, its replacement with a part eligible for installation.
Costs of Compliance
We estimate that this proposed AD would affect about 110 engines
installed on airplanes of U.S. registry. We also estimate that it would
take about 1 hour per product to comply with this proposed AD. The
average labor rate is $85 per hour. Required parts cost about $9,250.
Based on these figures, we estimate the cost of the proposed 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.
[[Page 11721]]
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 proposed
regulation:
(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.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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. Amend Sec. 39.13 by adding the following new airworthiness
directive (AD):
Rolls-Royce plc: Docket No. FAA-2013-0953; Directorate Identifier
2013-NE-32-AD.
(a) Comments Due Date
We must receive comments by May 2, 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 reworked in accordance with RR
Service Bulletin (SB) RB.211-72-G604, dated March 18, 2013.
(d) Reason
This AD was prompted by 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) 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 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/N S/N
------------------------------------------------------------------------
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 Service Bulletin (SB) 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.
(3) RR SB No. RB.211-72-G604, dated March 18, 2013, which is not
incorporated by reference in this AD, can be obtained from Rolls-
Royce plc using the contact information in paragraph (h)(4) of this
AD.
(4) 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;
Web site: https://www.aeromanager.com.
(5) 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.
Issued in Burlington, Massachusetts, on February 20, 2014.
Colleen M. D'Alessandro,
Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2014-04350 Filed 2-28-14; 8:45 am]
BILLING CODE 4910-13-P