AD 2015-07-01

[Federal Register Volume 80, Number 64 (Friday, April 3, 2015)]
[Rules and Regulations]
[Pages 18083-18084]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2015-07492]



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Federal Register / Vol. 80, No. 64 / Friday, April 3, 2015 / Rules 
and Regulations

[[Page 18083]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0904; Directorate Identifier 2014-NE-14-AD; 
Amendment 39-18129; AD 2015-07-01]
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) RB211-524 turbofan engines with certain part 
number (P/N) low-pressure turbine (LPT) stage 3 turbine blades 
installed. This AD requires implementation of a life limit for certain 
P/N LPT stage 3 turbine blades and replacement of affected blades that 
reach or exceed the life limit. This AD was prompted by reports of LPT 
stage 3 turbine blade failures, release of blades, and subsequent in-
flight shutdowns. We are issuing this AD to prevent failure of LPT 
stage 3 turbine blades and subsequent release of blade debris, which 
could lead to failure of one or more engines, loss of thrust control, 
and damage to the airplane.

DATES: This AD becomes effective May 8, 2015.

ADDRESSES: 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: 
<a href="http://www.rolls-royce.com/contact/civil_team.jsp">http://www.rolls-royce.com/contact/civil_team.jsp</a>; Internet: <a href="https://www.aeromanager.com">https://www.aeromanager.com</a>. 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. It is also available on the Internet at 
<a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. 
FAA-2014-0904.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2014-
0904; 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 
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: <a href="/cdn-cgi/l/email-protection#bed5dbd0d0dbcad690cdcadbdbc8dbcdfed8dfdf90d9d1c8"><span class="__cf_email__" data-cfemail="6f040a01010a1b07411c1b0a0a190a1c2f090e0e41080019">[email&#160;protected]</span></a>.

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 December 2, 2014 (79 FR 
71363). The NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    Since 2006, a number of low pressure turbine (LPT) Stage 3 blade 
failures have been reported, each resulting in engine in-flight 
shut-down. Engineering analysis on those occurrences indicates that 
blades with an accumulated life of 11,000 flight cycles (FC) or more 
have an increased risk of failure.
    This condition, if not detected and corrected, could lead to 
release of LPT Stage 3 blade debris and consequent (partial or 
complete) loss of engine power, possibly resulting in reduced 
control of the aeroplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received. The commenter supports the 
NPRM (79 FR 71363, December 2, 2014).

Conclusion

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

Costs of Compliance

    We estimate that this AD affects 2 engines installed on airplanes 
of U.S. registry. We also estimate that it will take about 120 hours 
per engine to comply with this AD. The average labor rate is $85 per 
hour. Parts cost is zero. Based on these figures, we estimate the cost 
of this AD on U.S. operators to be $20,400.

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:

[[Page 18084]]

    (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):

2015-07-01 Rolls-Royce plc: Amendment 39-18129; Docket No. FAA-2014-
0904; Directorate Identifier 2014-NE-14-AD.

(a) Effective Date

    This AD becomes effective May 8, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Rolls-Royce plc (RR) RB211-524B-02, 
RB211-524B-B-02, RB211-524B2-19, RB211-524B2-B-19, RB211-524B3-02, 
RB211-524C2-19, and RB211-524C2-B-19 turbofan engines with low-
pressure turbine (LPT) stage 3 turbine blade, part number (P/N) 
LK55386, LK86483, or LK86503, installed.

(d) Reason

    This AD was prompted by reports of LPT stage 3 turbine blade 
failure, release of blades, and subsequent in-flight shutdown. We 
are issuing this AD to prevent failure of LPT stage 3 turbine blades 
and subsequent release of blade debris, which could lead to failure 
of one or more engines, loss of thrust control, and damage to the 
airplane.

(e) Actions and Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Remove from service before further flight any LPT stage 3 
turbine blade, P/N LK55386, LK86483, or LK86503, that exceeds 11,000 
flight cycles since new.
    (2) If you cannot determine the accumulated flight cycles, 
remove any LPT stage 3 turbine blade, P/N LK55386, LK86483, or 
LK86503, within 200 flight cycles after the effective date of this 
AD.
    (3) After the effective date of this AD, do not install any LPT 
stage 3 turbine blade, P/N LK55386, LK86483, or LK86503, on any 
engine if the blade has accumulated 11,000 or more flight cycles 
since new.

(f) 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: <a href="/cdn-cgi/l/email-protection#d899969df5999cf59995979b98beb9b9f6bfb7ae"><span class="__cf_email__" data-cfemail="a8e9e6ed85e9ec85e9e5e7ebe8cec9c986cfc7de">[email&#160;protected]</span></a>.

(g) 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: 
<a href="/cdn-cgi/l/email-protection#f9929c97979c8d91d78a8d9c9c8f9c8ab99f9898d79e968f"><span class="__cf_email__" data-cfemail="157e707b7b70617d3b66617070637066557374743b727a63">[email&#160;protected]</span></a>.
    (2) Refer to MCAI European Aviation Safety Agency AD 2014-0210, 
dated September 19, 2014, for more information. You may examine the 
MCAI in the AD docket on the Internet at <a href="http://www.regulations.gov/#!documentDetail">http://www.regulations.gov/#!documentDetail</a>;D=FAA-2014-0904-0002.
    (3) RR Alert Non-Modification Service Bulletin No. RB.211-72-
AH790, Revision 1, dated November 5, 2014, which is not incorporated 
by reference in this AD, can be obtained from Rolls-Royce plc, using 
the contact information in paragraph (g)(4) of this AD.
    (4) 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: <a href="http://www.rolls-royce.com/contact/civil_team.jsp">http://www.rolls-royce.com/contact/civil_team.jsp</a>; 
Internet: <a href="https://www.aeromanager.com">https://www.aeromanager.com</a>.
    (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.

(h) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on March 26, 2015.
Colleen M. D'Alessandro,
Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-07492 Filed 4-2-15; 8:45 am]
 BILLING CODE 4910-13-P