Document ID: FAA-2014-0705-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Rolls-Royce plc Turbofan Engines
Posted Date: 2014-10-30T04:00Z

[Federal Register Volume 79, Number 210 (Thursday, October 30, 2014)]
[Rules and Regulations]
[Pages 64504-64506]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-25739]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0705; Directorate Identifier 2014-NE-13-AD; 
Amendment 39-18006; AD 2014-22-02]
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) Trent 1000-A, 1000-C, 1000-D, 1000-E, 1000-G, and 
1000-H turbofan engines. This AD requires removing engine electronic 
controller (EEC) software earlier than standard MB6.15 and replacing 
with a software standard eligible for installation. This AD was 
prompted by a finding that an intermediate pressure

[[Page 64505]]

(IP) shaft failure may not be detected by EEC software earlier than 
standard MB6.15. We are issuing this AD to detect IP shaft failure and 
prevent IP compressor turbine burst, uncontained engine failure, and 
damage to the airplane.

DATES: This AD becomes effective November 14, 2014.
    We must receive comments on this AD by December 15, 2014.

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: 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, 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-2014-
0705; 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), 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: Kenneth Steeves, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; phone: 781-238-7765; 
fax: 781-238-7199; email: kenneth.steeves@faa.gov.

SUPPLEMENTARY INFORMATION:

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-2014-0705; Directorate 
Identifier 2014-NE-13-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.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD 2014-0192, dated September 1, 2014 (referred to hereinafter as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states:

    An investigation carried out by RR has identified the risk of 
Intermediate Pressure (IP) shaft failure that may not be detected 
and accommodated by the engine control system. An IP shaft failure 
that is not detected may result in IP turbine overspeed.
    This condition, if not corrected, could lead to IP turbine burst 
and consequent release of high energy debris, possibly resulting in 
damage to, and reduced control of, the aeroplane.

    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-2014-0705.

Relevant Service Information

    RR has issued Alert Service Bulletin (ASB) No. TRENT 1000 73-AH914, 
dated July 23, 2014. The ASB describes procedures for removing software 
earlier than standard MB6.15, and installing a software standard 
eligible for installation.

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 removing EEC software earlier 
than standard MB6.15, and replacing with a software standard eligible 
for installation.

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.

Costs of Compliance

    We estimate that this AD affects no engines installed on airplanes 
of U.S. registry. We also estimate that it will take about 1 hour per 
engine to comply with this AD. The average labor rate is $85 per hour. 
Required parts cost is about $200 per engine. Based on these figures, 
we estimate the cost of this AD on U.S. operators to be $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, or on the distribution of power and

[[Page 64506]]

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.

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):

2014-22-02 Rolls-Royce plc: Amendment 39-18006; Docket No. FAA-2014-
0705; Directorate Identifier 2014-NE-13-AD.

(a) Effective Date

    This AD is effective November 14, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Rolls-Royce plc (RR) Trent 1000-A, 1000-
C, 1000-D, 1000-E, 1000-G, and 1000-H turbofan engines.

(d) Reason

    This AD was prompted by a finding that an intermediate pressure 
(IP) shaft failure may not be detected by engine electronic 
controller (EEC) software earlier than standard MB6.15. We are 
issuing this AD to detect IP shaft failure and prevent IP compressor 
turbine burst, 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) Within 30 days or 180 flight cycles after the effective date 
of this AD, whichever occurs first, remove from the engine any EEC 
software standard earlier than software standard MB6.15.
    (2) Install EEC software eligible for installation.

(f) Installation Prohibition

    After the effective date of this AD, do not install any EEC 
containing a software standard earlier than software standard of 
MB6.15, into any engine.

(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. You may email your request to: ANE-AD-AMOC@faa.gov.

(h) Related Information

    (1) For more information about this AD, contact Kenneth Steeves, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238-7765; fax: 781-238-7199; email: 
kenneth.steeves@faa.gov.
    (2) Refer to MCAI European Aviation Safety Agency AD 2014-0192, 
dated September 1, 2014, 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-2014-0705.
    (3) RR Alert Service Bulletin No. TRENT 1000 73-AH914, dated 
July 23, 2014, which is 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, 
England, DE248BJ; 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.

(i) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on October 17, 2014.
Colleen M. D'Alessandro,
Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-25739 Filed 10-29-14; 8:45 am]
BILLING CODE 4910-13-P