
[Federal Register Volume 78, Number 228 (Tuesday, November 26, 2013)]
[Rules and Regulations]
[Pages 70489-70491]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-28178]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0880; Directorate Identifier 2013-NE-28-AD; 
Amendment 39-17667; AD 2013-23-12]
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 all 
Rolls-Royce plc (RR) RB211 Trent 553-61, 553A2-61, 556-61, 556A2-61, 
556B-61, 556B2-61, 560-61, and 560A2-61 turbofan engines. This AD 
requires replacement or repair of the low-pressure (LP) compressor fan 
blade set before reaching a specified number of flight cycles since new 
(FCSN) or flight cycles since last leading edge profile blade repair 
(FCSLR). This AD was prompted by reports of erosion of the leading edge 
profile of the LP compressor blade set contributing to fan blade 
flutter. We are issuing this AD to prevent failure of the LP compressor 
blades, which could lead to an 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.

[[Page 70490]]


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: 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 
Airworthiness Directive 2013-0214, dated September 16, 2013 (referred 
to herein after as ``the MCAI''), to correct an unsafe condition for 
the specified products. The MCAI states:

    Erosion of the leading edge profile of Trent 500 engines' low 
pressure (LP) compressor blades is proven to contribute to fan 
flutter, a risk that is mitigated by regular restoration of the 
leading edge of these blades. Recently, Rolls-Royce has conducted a 
review regarding the in-service restoration of the leading edge 
profile of LP compressor blades. The results of this review 
concluded that not all LP compressor blades have been restored as 
intended.
    This condition, if not corrected, could lead to fan flutter, LP 
compressor blade cracking and uncontained LP compressor blade 
failures, possibly resulting in damage to, and reduced control of, 
the aeroplane.
    For the reasons described above, this AD requires initial and 
repetitive leading edge restoration of the LP compressor blades.

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-2013-0880.

Relevant Service Information

    RR has issued Alert Non-Modification Service Bulletin No. RB.211-
72-AH149, Revision 1, dated May 3, 2013 and RB.211-72-H464, dated 
August 28, 2013. The actions described in this service information are 
intended to correct the unsafe condition identified in the MCAI.

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

    No domestic operators use this product. Therefore, we find that 
notice and opportunity for prior public comment are unnecessary and 
that good cause exists for making this amendment effective in less 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-2013-0880; Directorate 
Identifier 2013-NE-28-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 would affect 0 engines installed on 
airplanes of U.S. registry. We also estimate that it would take about 6 
hours per engine to comply with this AD. The average labor rate is $85 
per hour. Based on these figures, we estimate the total cost of this AD 
to U.S. operators is $0.

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,

[[Page 70491]]

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):

2013-23-12 Rolls-Royce plc: Amendment 39-17667; Docket No. FAA-2013-
0880; Directorate Identifier 2013-NE-28-AD.

(a) Effective Date

    This AD is effective December 11, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Rolls-Royce plc (RR) RB211 Trent 553-61, 
553A2-61, 556-61, 556A2-61, 556B-61, 556B2-61, 560-61, and 560A2-61 
turbofan engines.

(d) Reason

    This AD was prompted by reports of erosion of the leading edge 
profile of the low-pressure (LP) compressor blade set contributing 
to fan blade flutter. We are issuing this AD to prevent failure of 
the LP compressor blades, which could lead to an 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) If on the effective date of this AD, the LP compressor fan 
blades:
    (i) Have less that 3,750 flight cycles since new (FCSN) or 
flight cycles since last leading edge profile blade repair (FCSLR), 
replace or repair the LP compressor fan blade set before 
accumulating 4,000 FCSN or FCSLR;
    (ii) Have 3,750 or more FCSN or FCSLR, but less than 4,400 FCSN 
or FCSLR, replace or repair the LP compressor fan blade set within 
250 flight cycles (FC), but not later than 4,500 FCSN or FCSLR;
    (iii) Have 4,400 FCSN or FCSLR or more, replace or repair the LP 
compressor fan blade set within 100 FC; or
    (iv) Have FCSN or FCSLR that are unknown, replace or repair the 
LP compressor fan blade set within 100 FC.
    (2) Thereafter, replace or repair the LP compressor fan blade 
set within every 4,000 FCSN or FCSLR.

(f) Definition

    LP compressor fan blades eligible for installation are:
    (1) LP compressor fan blades with less than 4,000 FCSN; or
    (2) LP compressor fan blades with less than 4,000 FCSLR, if LP 
compressor fan blades were repaired using RR Alert Non-Modification 
Service Bulletin No. RB.211-72-AH149, Revision 1, dated May 3, 2013 
or earlier version or, for initial restoration only, RB.211-72-H464, 
dated August 28, 2013.

(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 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 2013-0214, 
dated September 16, 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-2013-0880.
    (3) Rolls-Royce plc Alert Non-Modification Service Bulletin No. 
RB.211-72-AH149, Revision 1, dated May 3, 2013 and RB.211-72-H464, 
dated August 28, 2013, which are not incorporated by reference in 
this AD, can be obtained from RR, 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, 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.

(i) 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. 2013-28178 Filed 11-25-13; 8:45 am]
BILLING CODE 4910-13-P


