[Federal Register Volume 79, Number 41 (Monday, March 3, 2014)]
[Proposed Rules]
[Pages 11719-11721]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-04350]


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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]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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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 http://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: 
http://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 http://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: [email protected].

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 http://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 http://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: 
[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.
    (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: http://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]
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