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[Federal Register Volume 78, Number 228 (Tuesday, November 26, 2013)]
[Rules and Regulations]
[Pages 70487-70489]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-28221]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0750; Directorate Identifier 2013-NE-25-AD; 
Amendment 39-17672; AD 2013-23-17]
RIN 2120-AA64

Airworthiness Directives; Rolls-Royce plc Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for Rolls-
Royce plc (RR) RB211-535E4-37, -535E4-B-37, -535E4-C-37, RB211Trent 
768-60, 772-60, and 772B-60 turbofan engines. This AD requires removal 
of certain high-pressure (HP) and intermediate-pressure (IP) turbine 
discs before their accumulated cyclic lives have reached the revised 
limits. This AD was prompted by a report of an HP disc contaminated 
with a steel inclusion. We are issuing this AD to prevent failure of 
the HP or IP turbine disc, uncontained engine failure, and damage to 
the airplane.

DATES: This AD becomes effective December 11, 2013.
    We must receive comments on this AD by January 10, 2014.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, 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: 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 AD, contact Rolls-Royce 
plc, Corporate Communications, P.O. Box 31, Derby, DE24 8BJ, UK; phone: 
44-0-1332-242424; fax: 44-0-1332-249936; email: http://www.rolls-royce.com/contact/civil_team.jsp. You may view this service 
information at the FAA, Engine & Propeller Directorate, 12 New England 
Executive Park, Burlington, MA 01803. 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; 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 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: Frederick Zink, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; phone: 781-238-7779; 
fax: 781-238-7199; email: frederick.zink@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD 2013-0155, dated July 18, 2013 (referred to herein after as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states:

    During a recent inspection of a high pressure (HP) turbine disc 
forged by a specific supplier, the disc was found to be contaminated 
with a steel inclusion, due to an inadequate cleaning procedure in 
the operation of the melt furnace, following a steel melt. Analysis 
of melt and inspection data concluded that all discs manufactured 
from the batch of material in which this steel inclusion was found, 
had a significant risk of containing steel inclusions. Rolls-Royce 
has carried out an analysis of the effect of the

[[Page 70488]]

steel inclusions on the Declared Safe Cyclic Lives (DSCL) of the 
affected HP and intermediate pressure (IP) turbine discs. This 
analysis concluded that the currently published DSCL cannot be 
supported for several discs containing the subject inclusions.
    This condition, if not corrected, could lead to an uncontained 
HP or IP turbine disc failure, possibly resulting in damage to, and 
reduced control of, the aeroplane.
    For the reasons described above, this AD requires removal from 
service of certain HP and IP turbine discs before their accumulated 
cyclic lives have reached the revised limits.

    You may obtain further information by examining the MCAI in the AD 
docket on the Internet at http://www.regulations.gov by searching for 
and locating it in Docket No. FAA-2013-0750.

FAA's Determination and Requirements of This 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 issuing 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.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule. Therefore, 
we determined that notice and opportunity for public comment before 
issuing this AD are impracticable and that good cause exists for making 
this amendment effective in fewer than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2013-0750; Directorate 
Identifier 2013-NE-25-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD because of 
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 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).

Costs of Compliance

    We estimate that this AD will affect 20 engines installed on 
airplanes of U.S. registry. We also estimate that it will take about 0 
hours per engine to comply with this AD. The average labor rate is $85 
per hour. Required parts will cost about $4,000 per engine. Based on 
these figures, we estimate the total cost of this AD to U.S. operators 
is $80,000.

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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this 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.

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):

2013-23-17 Rolls-Royce plc: Amendment 39-17672; Docket No. FAA-2013-
0750; Directorate Identifier 2013-NE-25-AD.

(a) Effective Date

    This AD is effective December 11, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Rolls-Royce plc (RR) RB211-535E4-37, -535E4-
B-37, -535E4-C-37, RB211 Trent 768-60, 772-60, and 772B-60 turbofan 
engines with turbine disc part numbers (P/Ns) and serial numbers (S/
Ns) listed in Table 1 to paragraph (c) of this AD.

[[Page 70489]]

   Table 1 to Paragraph (c)--New Reduced Cyclic Life Limits for High-Pressure (HP)/Intermediate-Pressure (IP)
                                                  Turbine Discs
----------------------------------------------------------------------------------------------------------------
                                                                                         New reduced cyclic life
                Engine                           P/Ns                     S/Ns                    limit
----------------------------------------------------------------------------------------------------------------
RB211-535E4-37,-535E4-B-37, -535E4-C-  UL39767................  LDRCZ19900.............  11,400 flight cycles
 37.                                                                                      (FCs).
                                       UL39767................  LDRCZ19903.............
                                       UL39767................  LDRCZ19904.............
RB211 Trent 768-60, 772-60, and 772B-  FK26893................  LDRCZ19901.............  8,687 FCs.
 60.
                                       FK26893................  LDRCZ20081.............
                                       FK26893................  LDRCZ20082.............
                                       FK26893................  LDRCZ20084.............
                                       FK26893................  LDRCZ20088.............
                                       FK26893................  LDRCZ20089.............
                                       FK26893................  LDRCZ20090.............
                                       FK26893................  LDRCZ20093.............
                                       FK26893................  LDRCZ20094.............
                                       FK26893................  LDRCZ20097.............
                                       FK26893................  LDRCZ20099.............
                                       FK26893................  LDRCZ20100.............
                                       FK20795 or FW53118.....  LDREB12176.............  9,270 FCs.
                                       FK20795 or FW53118.....  LDREB12177.............
                                       FK20795 or FW53118.....  LDREB12178.............
                                       FK20795 or FW53118.....  LDREB12179.............
                                       FK20795 or FW53118.....  LDREB12180.............
----------------------------------------------------------------------------------------------------------------

(d) Reason

    This AD was prompted by a report of an HP disc contaminated with 
a steel inclusion. We are issuing this AD to prevent failure of the 
HP or IP turbine disc, uncontained engine failure, and damage to the 
airplane.

(e) Actions and Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Remove from service, within 30 days, any HP or IP disc 
identified in Table 1 to paragraph (c) of this AD that has exceeded 
the new cyclic life limit, or before the disc accumulates flight 
cycles that equal the new reduced cyclic life limit listed in Table 
1 to paragraph (c) of this AD, whichever is later.
    (2) Do not approve for return to service any engine with any 
installed HP or IP turbine disc listed in Table 1 to paragraph (c) 
of this AD, if the disc exceeds the new reduced cyclic life limit 
listed in Table 1 to paragraph (c) of this AD.

(f) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, may approve AMOCs for 
this AD. Use the procedures found in 14 CFR 39.19 to make your 
request.

(g) Related Information

    (1) For more information about this AD, contact Frederick Zink, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238-7779; fax: 781-238-7199; email: 
frederick.zink@faa.gov.
    (2) Refer to MCAI European Aviation Safety Agency AD 2012-0155, 
dated July 18, 2013. 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-2013-0750.
    (3) Rolls-Royce plc, Alert Non-Modification Service Bulletin No. 
RB.211-72-AH215, dated December 6, 2012 and RB.211-72-AH152, 
Revision 1, dated July 3, 2013, which are not incorporated by 
reference in this AD, can be obtained from RR using the contact 
information in paragraph (g)(4) of this AD.
    (4) For service information identified in this AD, contact 
Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, DE24 
8BJ, UK; phone: 44-0-1332-242424; fax: 44-0-1332-249936; email: 
http://www.rolls-royce.com/contact/civil_team.jsp.
    (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.

(h) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on November 8, 2013.
Colleen M. D'Alessandro,
Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2013-28221 Filed 11-25-13; 8:45 am]
BILLING CODE 4910-13-P
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