[Federal Register Volume 78, Number 66 (Friday, April 5, 2013)]
[Proposed Rules]
[Pages 20507-20509]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-07931]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0052; Directorate Identifier 2013-NE-02-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 all 
Rolls-Royce plc (RR) RB211-535E4-37, RB211-535E4-B-37, RB211-535E4-C-
37, and RB211-535E4-B-75 turbofan engines. This proposed AD was 
prompted by RR updating the low-cycle-fatigue life analysis for the low 
pressure turbine (LPT) stage 2 discs. This proposed AD would require 
removal of affected parts using a drawdown plan. We are proposing this 
AD to prevent LPT stage 2 disc failure, which could result in 
uncontained engine damage and damage to the airplane.

DATES: We must receive comments on this proposed AD by June 4, 2013.

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 AD, contact Rolls-Royce 
plc, Corporate Communications, P.O. Box 31, Derby, England, DE248BJ; 
phone: 011-44-1332-242424; fax: 011-44-1332-249936; or email from 
http://www.rolls-royce.com/contact/civil_team.jsp; or download the 
publication from https://

[[Page 20508]]

www.aeromanager.com. 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 proposed AD, 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: [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-2013-0052; 
Directorate Identifier 2013-NE-02-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 2012-0266, dated December 18, 2012, to correct an unsafe condition 
for the specified products. That mandatory continuing airworthiness 
information (MCAI) states:

    A recent re-evaluation of Critical Part lives carried out by 
Rolls-Royce revealed changes to the thermal profile and stresses in 
certain features of the low pressure turbine (LPT) Stage 2 disc. 
These changes have resulted in a reduction of the cyclic life of the 
LPT stage 2 discs.
    Operation of an engine equipped with a Critical Part that has 
exceeded its cyclic life may result in Critical Part failure, 
consequent release of high energy debris, damage to the aeroplane 
and/or injury to occupants.

We are proposing this AD to prevent LPT stage 2 disc failure, which 
could result in uncontained engine damage and damage to the airplane. 
You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    RR has issued Alert Non-Modification Service Bulletin (NMSB) No. 
RB.211-72-AH029, dated December 13, 2012. The NMSB introduces new LPT 
stage 2 disc part lives that will be the drawdown plan retirement 
thresholds.

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 removal of 
affected LPT stage 2 discs using a drawdown plan.

Differences Between the AD and the MCAI or Service Information

    This AD differs from EASA AD 2012-0266, dated December 18, 2012, as 
follows: The EASA AD specifies replacing the affected critical parts 
during the module disassembly if the subsequent, anticipated time on 
wing (time before next shop visit) plus current life of the part will 
exceed the new provisional lives published in the RR Alert NMSB No. 
RB.211-72-AH029, dated December 13, 2012. We specify replacing at next 
shop visit (defined by the separation of a major flange).

Costs of Compliance

    We estimate that this proposed AD would affect about 220 engines 
installed on airplanes of U.S. registry. The average labor rate is $85 
per hour. We do not estimate any labor cost associated with this 
proposed AD because the affected parts are replaced during scheduled 
shop visits. Prorated cost of the parts adjusted for lost life is about 
$8,290 per engine. Based on these figures, we estimate the cost of the 
proposed AD on U.S. operators to be $1,823,800.

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); and
    (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

[[Page 20509]]

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. The FAA amends Sec.  39.13 by adding the following new AD:

Rolls-Royce plc: Docket No. FAA-2013-0052; Directorate Identifier 
2013-NE-02-AD.

(a) Comments Due Date

    We must receive comments by June 4, 2013.

(b) Affected Airworthiness Directives (ADs)

    None.

(c) Applicability

    This AD applies to all Rolls-Royce plc (RR) RB211-535E4-37, 
RB211-535E4-B-37, RB211-535E4-C-37, and RB211-535E4-B-75 turbofan 
engines.

(d) Reason

    This AD was prompted by RR updating the low-cycle-fatigue life 
analysis for the low pressure turbine (LPT) stage 2 discs. We are 
issuing this AD to prevent LPT stage 2 disc failure, which could 
result in uncontained engine damage and damage to the airplane.

(e) Actions and Compliance

    (1) Within 30 days after the effective date of this AD, re-
calculate the cyclic life since new of each LPT stage 2 disc. Use 
the part lives and prorated life formulas in Appendices 1, 2, and 3 
of RR Alert Non-Modification Service Bulletin (NMSB) No. RB.211-72-
AH029, dated December 13, 2012, to make that calculation.
    (2) Assign the Maximum Approved Lives defined in Appendix 1 of 
Alert NMSB No. RB.211-72-AH029, dated December 13, 2012, to the LPT 
stage 2 disc based on the flight profile that will be flown.
    (3) For engines that have an engine shop visit (ESV) after the 
effective date of this AD, remove the LPT stage 2 disc from service 
before the part exceeds the maximum approved life assigned in 
paragraph (e)(2) of this AD.
    (4) For those engines that do not have an ESV after the 
effective date of this AD before the part exceeds the part life 
assigned in paragraph (e)(2) of this AD, remove the part from 
service at the next ESV.

(f) Installation Prohibition

    With the exception of parts that can be reworked using RR 
Service Bulletin No. RB.211-72-D365, Revision 5, dated December 13, 
2012, do not reinstall any part removed per this AD into any engine.

(g) Definitions

    For the purpose of this AD, an ESV is whenever engine 
maintenance performed prior to reinstallation requires the 
separation of a pair of major mating engine module flanges. 
Separation of flanges solely for the purpose of shipment without 
subsequent internal maintenance is not a shop visit.

(h) 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.

(i) 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: 
[email protected].
    (2) Refer to European Aviation Safety Agency Airworthiness 
Directive 2012-0266, dated December 18, 2012, and RR Alert NMSB No. 
RB.211-72-AH029, dated December 13, 2012, for related information.
    (3) 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; or email from http://www.rolls-royce.com/contact/civil_team.jsp; or download the publication from https://www.aeromanager.com. 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.

    Issued in Burlington, Massachusetts, on March 28, 2013.
Colleen M. D'Alessandro,
Assistant Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2013-07931 Filed 4-4-13; 8:45 am]
BILLING CODE 4910-13-P