80 FR 23741 - Airworthiness Directives; Rolls-Royce plc Turbofan Engines

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 82 (April 29, 2015)

We propose to adopt a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211-524B-02, RB211-524B2-19, RB211- 524B3-02, RB211-524B4-02, RB211-524B4-D-02, RB211-524C2-19, RB211- 524D4-19, RB211-524D4-39, and RB211-524D4X-19 turbofan engines. This proposed AD was prompted by several failures of affected high-pressure turbine (HPT) blades. This proposed AD would require removing affected HPT blades. We are proposing this AD to prevent failure of the HPT blade, which could lead to failure of one or more engines, loss of thrust control, and damage to the airplane.

[Federal Register Volume 80, Number 82 (Wednesday, April 29, 2015)]
[Proposed Rules]
[Pages 23741-23742]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-09815]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0095; Directorate Identifier 2015-NE-01-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 
certain Rolls-Royce plc (RR) RB211-524B-02, RB211-524B2-19, RB211-
524B3-02, RB211-524B4-02, RB211-524B4-D-02, RB211-524C2-19, RB211-
524D4-19, RB211-524D4-39, and RB211-524D4X-19 turbofan engines. This 
proposed AD was prompted by several failures of affected high-pressure 
turbine (HPT) blades. This proposed AD would require removing affected 
HPT blades. We are proposing this AD to prevent failure of the HPT 
blade, which could lead to failure of one or more engines, loss of 
thrust control, 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 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. 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-
0095; 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: Katheryn Malatek, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; phone: 781-238-7747; 
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-2015-0095; 
Directorate Identifier 2015-NE-01-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 2014-0250, dated November 19, 2014 (referred to hereinafter as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states:

    There were a number of pre-MOD/SB 72-7730 High Pressure Turbine 
(HPT) blade failures, with some occurring within a relatively short 
time. Engineering analysis carried out by RR on those occurrences 
indicates that certain pre-MOD/SB 72-7730 blades, Part Number (P/N) 
UL32958 and P/N UL21691 (hereafter referred to as `affected HPT 
blade'), with an accumulated life of 6500 flight hours (FH) since 
new or more, have an increased risk of in-service failure.
    This condition, if not corrected, could lead to HPT blade 
failure, release of debris and consequent (partial or complete) loss 
of engine power, possibly resulting in 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-2015-0095.

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 the 
affected HPT blades.

[[Page 23742]]

Costs of Compliance

    We estimate that this proposed AD affects 6 engines installed on 
airplanes of U.S. registry. We also estimate that it would take about 4 
hours per engine to comply with this proposed AD. The average labor 
rate is $85 per hour. Pro-rated cost of required parts is about 
$250,000 per engine. Based on these figures, we estimate the cost of 
this proposed AD on U.S. operators to be $1,502,040.

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-2015-0095; Directorate Identifier 
2015-NE-01-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) RB211-524B-02, 
RB211-524B2-19, RB211-524B3-02, RB211-524B4-02, RB211-524B4-D-02, 
RB211-524C2-19, RB211-524D4-19, RB211-524D4-39, and RB211-524D4X-19 
turbofan engines with high-pressure turbine (HPT) blades, part 
numbers (P/Ns) UL32958 and UL21691, installed.

(d) Reason

    This AD was prompted by several failures of affected HPT blades. 
We are issuing this AD to prevent failure of the HPT blade, 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.
    After the effective date of this AD, within 2 months or before 
exceeding 6,500 flight hours since first installation of HPT blades, 
P/Ns UL32958, and UL21691, on an engine, whichever occurs later, 
remove all affected HPT blades from service.

(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: [email protected].

(g) Related Information

    (1) For more information about this AD, contact Katheryn 
Malatek, Aerospace Engineer, Engine Certification Office, FAA, 
Engine & Propeller Directorate, 12 New England Executive Park, 
Burlington, MA 01803; phone: 781-238-7747; fax: 781-238-7199; email: 
[email protected].
    (2) Refer to MCAI European Aviation Safety Agency AD 2014-0250, 
dated November 19, 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-2015-0095.


    Issued in Burlington, Massachusetts, on April 22, 2015.
Colleen M. D'Alessandro,
Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-09815 Filed 4-28-15; 8:45 am]
 BILLING CODE 4910-13-P