
[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]


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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: 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 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]
BILLING CODE 4910-13-P


