[Federal Register Volume 79, Number 126 (Tuesday, July 1, 2014)]
[Rules and Regulations]
[Pages 37167-37169]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-14954]
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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.
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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:
http://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 http://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: [email protected].
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
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P/Ns S/Ns
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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
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(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:
[email protected].
(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 http://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: http://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: http://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]
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