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[Federal Register Volume 79, Number 133 (Friday, July 11, 2014)]
[Rules and Regulations]
[Pages 39956-39958]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-16184]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0876; Directorate Identifier 2013-NE-27-AD; 
Amendment 39-17895; AD 2014-14-01]
RIN 2120-AA64

Airworthiness Directives; Rolls-Royce plc Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Rolls-Royce plc (RR) RB211 Trent 768-60, 772-60, and 772B-60 turbofan 
engines. This AD requires modification of the engine by removing an 
electronic engine control (EEC) incorporating EEC software standard A14 
or earlier and installing an EEC eligible for installation. This AD was 
prompted by an uncontained multiple turbine blade failure on an RR 
RB211 Trent 772B turbofan engine. We are issuing this AD to prevent 
failure of the intermediate-pressure (IP) turbine disk drive arm or 
burst of the high-pressure turbine disk, which could lead to 
uncontained engine failure and damage to the airplane.

DATES: This AD becomes effective August 15, 2014.

ADDRESSES: 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; or Web site: 
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-2013-
0876; or in person at the Docket Management Facility 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 address for the Docket Office (phone: 800-647-5527) is

[[Page 39957]]

Document Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.

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: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to the specified products. The 
NPRM was published in the Federal Register on March 3, 2014 (79 FR 
11722). The NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    An operator of an A330 aeroplane fitted with RR Trent 772B 
engines experienced an engine uncontained multiple turbine blade 
failure. Investigation results showed that High-Pressure/
Intermediate-Pressure (HP/IP) oil vent tubes may be affected by 
carbon deposit and may also be damaged by their outer heat shields, 
which in this case led to combustion inside the tube. The consequent 
chain of events resulted in an engine internal fire which caused the 
failure of the IP turbine disc drive arm.
    This condition, if not corrected, could lead to uncontained 
multiple turbine blade failures or an HP/IP turbine disc burst, 
possibly resulting in damage to, and reduced control of, the 
aeroplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received.

Request To Modify Description of Failure Mode

    RR requested that we define the failure mode as IP turbine disc 
drive arm failure and multiple IP turbine blade release to be 
consistent with descriptions in the RR service bulletin and the 
European Aviation Safety Agency (EASA) AD.
    We disagree. EASA AD 2013-0190, dated August 20, 2013, states that 
the failure mode is multiple turbine blade failures or HP/IP turbine 
disc burst. We did not change this AD.

Request That FAA Require the Same Compliance Date as the EASA AD

    RR requested that we modify the compliance date to be consistent 
with the compliance date required in EASA AD 2013-0190, dated August 
20, 2013.
    We disagree. EASA AD 2013-0190, dated August 20, 2013 required 
compliance by December 31, 2018. We proposed compliance at next shop 
visit or December 31, 2018, whichever comes first, to achieve more 
timely mitigation of the unsafe condition. We did not change this AD.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
the AD as proposed.

Costs of Compliance

    We estimate that this AD affects about 72 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. There are no required parts. Based on these figures, we 
estimate the cost of this AD on U.S. operators to be $6,120.

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 
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):

2014-14-01 Rolls-Royce plc: Amendment 39-17895; Docket No. FAA-2013-
0876; Directorate Identifier 2013-NE-27-AD.

(a) Effective Date

    This AD becomes effective August 15, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Rolls-Royce plc (RR) RB211 Trent 768-60, 
772-60, and 772B-60 turbofan engines prior to engine serial number 
42066.

(d) Reason

    This AD was prompted by an uncontained multiple turbine blade 
failure on an RR RB211 Trent 772B turbofan engine. We are issuing 
this AD to prevent failure of the intermediate-pressure turbine disc 
drive arm or burst of the high-pressure turbine disk, which could 
lead to uncontained engine failure and damage to the airplane.

(e) Actions and Compliance

    After the effective date of this AD, at the next engine shop 
visit or by December 31, 2018, whichever occurs first, modify the 
engine by removing any electronic engine control (EEC) that 
incorporates EEC software standard A14 or earlier and installing an 
EEC eligible for installation.

(f) Installation Prohibition

    After modification of an engine as required by paragraph (e) of 
this AD, do not install an EEC with software standard A14 or earlier 
into that engine.

[[Page 39958]]

(g) Definitions

    (1) For the purpose of this AD, an ``engine shop visit'' is the 
induction of an engine into the shop for maintenance involving the 
separation of pairs of major mating engine flanges, except that the 
separation of engine flanges solely for the purposes of 
transportation without subsequent engine maintenance does not 
constitute an engine shop visit.
    (2) For the purpose of this AD, an EEC ``eligible for 
installation'' is any EEC that does not contain software standard 
A14 or earlier.

(h) Credit for Previous Actions

    If before the effective date of this AD you removed from an 
engine any EEC that had EEC software standard A14 or earlier and 
your engine no longer has an EEC with software standard A14 or 
earlier, you have met the requirements of this AD.

(i) 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.

(j) 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 2013-0190, 
dated August 20, 2013, for more information. You may examine the 
MCAI in the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2013-0876.
    (3) RR Alert Service Bulletin No. RB.211-73-AG829, dated April 
18, 2012, which is not incorporated by reference in this AD, can be 
obtained from Rolls-Royce plc, using the contact information in 
paragraph (j)(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; 
or Web site: 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.

(k) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on June 30, 2014.
Colleen M. D'Alessandro,
Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-16184 Filed 7-10-14; 8:45 am]
BILLING CODE 4910-13-P
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