
[Federal Register Volume 79, Number 5 (Wednesday, January 8, 2014)]
[Rules and Regulations]
[Pages 1315-1316]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-00083]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-1004; Directorate Identifier 2013-NE-34-AD; 
Amendment 39-17719; AD 2013-26-10]
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) RB211-524G2-19, RB211-524G3-19, RB211-524H-36, and 
RB211-524H2-19 turbofan engines. This AD requires a one-time reduction 
in the cyclic life of certain high-pressure (HP) compressor rotor stage 
1 and stage 2 discs, and removal of discs that exceed the reduced cycle 
life. This AD was prompted by a review by RR of the cyclic life of 
life-limited parts (LLPs) for RB211-524 series engines. We are issuing 
this AD to prevent the failure of certain LLPs, which could result in 
uncontained engine damage and damage to the airplane.

DATES: This AD becomes effective January 23, 2014.
    We must receive comments on this AD by February 24, 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: 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.

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-
1004; 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: Robert Green, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; phone: 781-238-7754; 
fax: 781-238-7199; email: robert.green@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 2013-0246, dated October 10, 2013 (referred to 
herein after as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

Rolls-Royce recently reviewed the cyclic lives of critical parts of 
the RB211-524 series engines, which has resulted in the 
identification of a reduced cyclic life limit for certain high-
pressure (HP) compressor Rotor Stage 1 and 2 Discs.
    Operation of critical parts beyond these reduced cyclic life 
limits could lead to part failure and consequent release of high-
energy debris, possibly resulting in damage to the aeroplane and/or 
injury to the occupants.

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-2013-1004.

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. This AD requires a one-time reduction in the 
cyclic life of certain HP compressor stage 1 and stage 2 discs, and 
removal of discs that exceed the reduced cycle life.

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-2013-1004; Directorate 
Identifier 2013-NE-34-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 0 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. The prorated cost of the parts, adjusted for lost life, is 
about $15,940 per engine. 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,

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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):

2013-26-10 Rolls-Royce plc: Amendment 39-17719; Docket No. FAA-2013-
1004; Directorate Identifier 2013-NE-34-AD.

(a) Effective Date

    This AD is effective January 23, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Rolls-Royce plc (RR) RB211-524G2-19, 
RB211-524G3-19, RB211-524H-36, and RB211-524H2-19 turbofan engines 
with high-pressure (HP) compressor rotor stage 1 and stage 2 discs, 
part number LK70608, LK76030, LK86621, UL19877, UL19878, UL19879, or 
UL24023, installed.

(d) Reason

    This AD was prompted by a review by RR of the cyclic life of 
critical-life-limited parts (LLPs) for RB211-524 series engines. We 
are issuing this AD to prevent the failure of certain LLPs, which 
could result in uncontained engine damage and damage to the 
airplane.

(e) Actions and Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Within 30 days after the effective date of this AD, reduce 
the cyclic life limit for the affected HP compressor rotor stage 1 
and stage 2 discs to 7,390 flight cycles (FC).
    (2) After the effective date of this AD, remove each affected HP 
compressor rotor stage 1 and stage 2 disc from service before the 
part exceeds 7,390 FC.
    (3) After the effective date of this AD, do not return to 
service any engine that has an HP compressor rotor stage 1 and stage 
2 disc installed, if the disc has more than 7,390 FC.

(f) 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.

(g) Related Information

    (1) For more information about this AD, contact Robert Green, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238-7754; fax: 781-238-7199; email: 
robert.green@faa.gov.
    (2) Refer to MCAI European Aviation Safety Agency AD 2013-0246, 
dated October 10, 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-2013-1004.

(h) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on December 23, 2013.
Carlos A. Pestana,
Acting Assistant Directorate Manager, Engine & Propeller Directorate, 
Aircraft Certification Service.
[FR Doc. 2014-00083 Filed 1-7-14; 8:45 am]
BILLING CODE 4910-13-P


