[Federal Register Volume 80, Number 82 (Wednesday, April 29, 2015)]
[Proposed Rules]
[Pages 23737-23739]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-09816]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
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 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
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 

  Federal Register / Vol. 80, No. 82 / Wednesday, April 29, 2015 / 
Proposed Rules  

[[Page 23737]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0593; Directorate Identifier 2015-NE-08-AD]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Rolls-Royce plc (RR) RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-
C-37 turbofan engines. This proposed AD was prompted by RR updating the 
life limits for certain high-pressure turbine (HPT) disks. This 
proposed AD would require reducing the cyclic life limits for certain 
HPT disks, removing those disks that have exceeded the new life limit, 
and replacing them with serviceable parts. We are proposing this AD to 
prevent failure of the HPT disk, which could result in uncontained disk 
release, damage to the engine, and damage to the airplane.

DATES: We must receive comments on this proposed AD by June 29, 2015.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     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, Rolls-Royce 
plc, Corporate Communications, P.O. Box 31, Derby, England, DE24 8BJ; 
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-2015-
0593; 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 address for the Docket Office (phone: 800-
647-5527) is in the ADDRESSES section. Comments will be available in 
the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Wego Wang, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; phone: 781-238-7134; 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-2015-0593; 
Directorate Identifier 2015-NE-08-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.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD 2014-0249R1, dated February 18, 2015 (referred to hereinafter as 
``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    An engineering analysis, carried out by RR, of the lives of 
critical parts of the RB211-535E4-37 engine, has resulted in reduced 
cyclic life limits for certain high pressure (HP) turbine discs. The 
reduced limits are published in the RR RB211-535E4-37 Time Limits 
Manual (TLM): 05-10-01-800-000, current Revision dated July 2014.
    Operation of critical parts beyond these reduced cyclic life 
limits may result in part failure, possibly resulting in the release 
of high-energy debris, which may cause 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 Docket No. FAA-2015-0593.

Related Service Information Under 1 CFR Part 51

    We reviewed RR Non-Modification Service Bulletin (NMSB) No. RB.211-
72-G188, Revision No. 1, dated October 30, 2013, and RR RB211-535E4-37, 
Time Limits Manual (TLM): 05-10-01-800-000, Revision dated July 1, 
2014; and RR RB211-535E4-37, TLM: 05-00-01-800-000, Revision dated July 
1, 2014. The NMSB describes the updated lifing analysis of the affected 
HP turbine disks. The TLMs provide revised life limits for the affected 
HP turbine disks. This service information is reasonably available 
because the interested parties have access to it through their normal 
course of business or see ADDRESSES for other ways to access this 
service information.

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

[[Page 23738]]

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 reducing the cyclic life limits 
for certain HPT disks, removing those disks that have exceeded the new 
life limit, and replacing them with serviceable parts.

Costs of Compliance

    We estimate that this proposed AD affects 650 engines installed on 
airplanes of U.S. registry. We also estimate that it would take about 0 
hours per engine to comply with this proposed AD. The average labor 
rate is $85 per hour. Pro-rated cost of required parts cost would be 
about $12,213 per engine. Based on these figures, we estimate the cost 
of this proposed AD on U.S. operators to be $7,938,450.

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 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.

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. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

    Rolls-Royce plc: Docket No. FAA-2015-0593; Directorate 
Identifier 2015-NE-08-AD.

(a) Comments Due Date

    We must receive comments by June 29, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Rolls-Royce plc (RR), RB211-535E4-37, 
RB211-535E4-B-37, and RB211-535E4-C-37 turbofan engines.

(d) Reason

    This AD was prompted by RR updating the life limits for certain 
high-pressure turbine (HPT) disks. We are issuing this AD to prevent 
failure of the HPT disk, which could result in uncontained disk 
release, damage to the engine, and damage to the airplane.

(e) Actions and Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) After the effective date of this AD, use RR RB211-535E4-37 
Time Limits Manual (TLM): 05-10-01-800-000, Revision dated July 1, 
2014 (referred to hereafter as `the TLM'), to determine the new life 
limits for the affected engine models and configurations, with the 
exception of those engine models mentioned in paragraph (e)(2) of 
this AD.
    (2) For RR RB211-535E4-B-37 or RB211-535E4-C-37 engines with an 
affected HPT disk that was previously installed on an RB211-535E4-37 
engine operated under Flight Plan A, use task 05-00-01-800-000 in 
the TLM to re-calculate equivalent cycles since new to obtain the 
new life limit.
    (3) If an affected engine model has an HPT disk installed with 
P/N UL27681 or UL39767, remove the affected HPT disk before the 
accumulated cyclic life exceeds either 19,500 flight cycles (FCs) 
under Flight Plan A, or 14,700 FCs under Flight Plan B, or within 25 
FCs after the effective date of this AD, whichever occurs later.
    (4) For all affected engines, other than those specified in 
paragraph (e)(3) in this AD, remove each HPT disk before exceeding 
its applicable life limit as specified in the TLM.
    (5) Install an HPT disk eligible for installation.

(f) Definition

    For the purpose of this AD, a part eligible for installation is 
one with a part number listed in the TLM with a total accumulated 
cyclic life that is less than the applicable life limit specified in 
the TLM.

(g) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA, may approve AMOCs 
for this AD. Use the procedures found in 14 CFR 39.19 to make your 
request. You may email your request to: [email protected].

(h) Related Information

    (1) For more information about this AD, contact Wego Wang, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238-7134; fax: 781-238-7199; email: 
[email protected].
    (2) Refer to MCAI European Aviation Safety Agency AD 2014-
0249R1, dated February 18, 2015, 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-2015-0593.
    (3) RR Non-Modification Service Bulletin No. RB.211-72-G188, 
Revision No. 1, dated October 30, 2013, and RR RB211-535E4-37, TLM: 
05-10-01-800-000, Revision dated July 1, 2014; and RR RB211-535E4-
37, TLM: 05-00-01-800-000, Revision dated July 1, 2014, which are 
not incorporated by reference in this AD, can be obtained from 
Rolls-Royce plc, using the contact information in paragraph (h)(4) 
of this proposed AD.
    (4) For service information identified in this proposed AD, 
contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, 
Derby, England, DE24 8BJ; 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.
    (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.


[[Page 23739]]


    Issued in Burlington, Massachusetts, on April 22, 2015.
Colleen M. D'Alessandro,
Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-09816 Filed 4-28-15; 8:45 am]
 BILLING CODE 4910-13-P