[Federal Register Volume 80, Number 236 (Wednesday, December 9, 2015)]
[Proposed Rules]
[Pages 76402-76403]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-30947]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-4076; Directorate Identifier 2015-NE-30-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) RB211-22B and RB211-524 turbofan engines 
with low-pressure turbine (LPT) support roller bearing, part number (P/
N) LK30313 or P/N UL29651, installed. This proposed AD was prompted by 
a report of a breach of the turbine casing and release of engine 
debris. This proposed AD would require removal of certain LPT support 
roller bearings installed in RR RB211-22B and RB211-524 engines. We are 
proposing this AD to prevent failure of the LPT support roller bearing, 
loss of radial position following LPT blade failure, uncontained part 
release, damage to the engine, and damage to the airplane.

DATES: We must receive comments on this proposed AD by February 8, 
2016.

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.

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-
4076; 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: Brian Kierstead, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; phone: 781-238-7772; 
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-2015-4076; 
Directorate Identifier 2015-NE-30-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 2015-0187, dated September 9, 2015 (referred to hereinafter as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states:

    An RB211-524G2-T engine experienced an in-service event that 
resulted in breach of a turbine casing and some release of core 
engine debris through a hole in the engine nacelle. The 
investigation of the event determined the primary cause to have been 
fracture and release of a Low Pressure (LP) turbine stage 2 blade. 
The blade release caused secondary damage to the LP turbine, 
producing significant out-of-balance forces. The event engine was 
fitted with an LP turbine support bearing where the roller retention 
cage is constructed from two halves that are riveted together. The 
LP turbine imbalance resulted in an overload of the LP turbine 
support bearing and caused separation of the riveted, two-piece 
roller retention cage. Radial location of the LP turbine shaft was 
lost, allowing further progression of the event that resulted in a 
breach of the IP turbine casing.

    RR introduced a modified LPT support roller bearing that can 
withstand greater loads when an LPT turbine blade release occurs, 
thereby preventing LPT rotor movement. 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-2015-4076.

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. 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 from service of the affected LPT support 
bearings.

Costs of Compliance

    We estimate that this proposed AD affects 9 engines installed on 
airplanes of U.S. registry. We also estimate it would take 0 hours to 
comply with this proposed AD since the proposed actions required by the 
AD would be performed during a shop visit, when major engine flanges 
are separated, which requires the removal of the LPT support roller 
bearing. Therefore, no additional time is needed to remove it. Parts 
would cost about $8,184 per engine. The average labor rate is $85 per 
hour. Based on these figures, we estimate the cost of this proposed AD 
on U.S. operators to be $73,656.

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

[[Page 76403]]

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-2015-4076; Directorate Identifier 
2015-NE-30-AD.

(a) Comments Due Date

    We must receive comments by February 8, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Rolls-Royce plc RB211-22B-02, RB211-22B (MOD 
72-8700), RB211-524B-02, RB211-524B-B-02, RB211-524B2-19, RB211-
524B2-B-19, RB211-524B3-02, RB211-524B4-02, RB211-524B4-D-02, RB211-
524C2-19, RB211-524C2-B-19, RB211-524D4-19, RB211-524D4-B-19, RB211-
524D4X-19, RB211-524D4X-B-19, RB211-524D4-39, RB211-524D4-B-39, 
RB211-524G2-19, RB211-524G3-19, RB211-524-G2-T-19, RB211-524G3-T-19, 
RB211-524H-36, RB211-524H2-19, RB211-524H-T-36, and RB211-524H2-T-19 
turbofan engines, all serial numbers, with low-pressure turbine 
(LPT) support roller bearing, part number (P/N) LK30313 or P/N 
UL29651, installed.

(d) Reason

    This AD was prompted by a report of a breach of the turbine 
casing and release of engine debris through a hole in the engine 
nacelle. We are issuing this AD to prevent failure of the LPT 
support roller bearing, loss of radial position following LPT blade 
failure, uncontained part release, damage to the engine, and damage 
to the airplane.

(e) Actions and Compliance

    Comply with this AD within the compliance times specified, 
unless already done. At the next shop visit or within 24 months 
after the effective date of this AD, whichever occurs first, remove 
from service LPT support roller bearing, P/N LK30313 or P/N UL29651, 
and replace with a part eligible for installation.

(f) Installation Prohibition

    After the effective date of this AD, do not install an LPT 
support roller bearing, P/N LK30313 or P/N UL29651, onto any engine.

(g) Definition

    For the purpose of this AD, a ``shop visit'' is defined as 
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.

(h) 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].

(i) Related Information

    (1) For more information about this AD, contact Brian Kierstead, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238-7772; fax: 781-238-7199; email: 
[email protected].
    (2) Refer to MCAI European Aviation Safety Agency AD 2015-0187, 
dated September 9, 2015, 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-2015-4076.

    Issued in Burlington, Massachusetts, on December 2, 2015.
Colleen M. D'Alessandro,
Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-30947 Filed 12-8-15; 8:45 am]
 BILLING CODE 4910-13-P