Document ID: FAA-2012-1055-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives; Rolls-Royce Deutschland Ltd&Co KG Turbofan Engines
Posted Date: 2012-11-16T05:00Z

[Federal Register Volume 77, Number 222 (Friday, November 16, 2012)]
[Proposed Rules]
[Pages 68714-68716]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-27824]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1055; Directorate Identifier 2012-NE-33-AD]
RIN 2120-AA64

Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG 
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 all 
Rolls-Royce Deutschland Ltd & Co KG (RRD) BR700-710A1-10 and BR700-
710A2-20 turbofan engines, and certain BR700-710C4-11 model engines. 
This proposed AD was prompted by RRD performing an evaluation that 
determined that certain high-pressure turbine (HPT) stage 1 and stage 2 
discs from a specific supplier may contain steel inclusions that may 
cause the discs to fail before they reach their current life limits. 
This proposed AD would require reducing the life limits for certain HPT 
stage 1 and stage 2 discs. We are proposing this AD to prevent failure 
of the HPT stage 1 and stage 2 discs, which could result in uncontained 
failure of the engine and damage to the airplane.

DATES: We must receive comments on this proposed AD by January 15, 
2013.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     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 proposed AD, contact 
Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, Dahlewitz, 15827 
Blankenfelde-Mahlow, Germany; phone: 49 0 33-7086-1883; fax: 49 0 33-
7086-3276. 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; 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 regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (phone: 800-647-5527) is the 
same as the Mail address provided in the ADDRESSES section. Comments 
will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Robert Morlath, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; phone: 781-238-7154; 
fax: 781-238-7199; email: robert.c.morlath@faa.gov.

[[Page 68715]]

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-2012-1055; 
Directorate Identifier 2012-NE-33-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. Using the search 
function of the Web site, anyone can find and read the comments in any 
of our dockets, including, if provided, the name of the individual who 
sent the comment (or signed the comment on behalf of an association, 
business, labor union, etc.). You may review the DOT's complete Privacy 
Act Statement in the Federal Register published on April 11, 2000 (65 
FR 19477-78).

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD 2012-0166, dated August 30, 2012 (referred to hereinafter as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states:

    The results of a recent quality review of high pressure turbine 
(HPT) stage 1 and stage 2 discs identified potential for steel 
inclusions in some production scale parts. Further investigation 
concluded that all affected parts were manufactured by Udimet 720I 
and melted by a certain supplier. Subsequent evaluation concluded 
that the affected parts life limitation values declared in the 
engine Time Limits Manual cannot be supported for discs with 
potential steel inclusion.
    This condition, if not corrected, could lead to an uncontained 
HPT disc failure, potentially resulting in damage to, and/or reduced 
control of the aeroplane.

The FAA has further determined that the risk to the engine is increased 
by installing an HPT stage 1 disc and an HPT stage 2 disc from the 
affected population, on the same engine. Therefore the FAA is 
prohibiting the installation of an HPT stage 1 and HPT stage 2 disc 
from the affected population in the same engine. You may obtain further 
information by examining the MCAI in the AD docket.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of 
Germany, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with Germany, they have 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 reducing the life limits for 
certain HPT stage 1 and HPT stage 2 discs that have a serial number 
listed in this proposed AD.

Costs of Compliance

    We estimate that this proposed AD would affect about 10 engines 
installed on airplanes of U.S. registry. Prorated parts life will cost 
about $210,000. Based on these figures, we estimate the cost of the 
proposed AD on U.S. operators to be $2,100,000. Our cost estimate is 
exclusive of possible warranty coverage.

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); and
    3. 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

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

    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]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Rolls-Royce Deutschland Ltd & Co KG (Formerly Rolls-Royce 
Deutschland GmbH, formerly BMW Rolls-Royce GmbH): Docket No. FAA-
2012-1055; Directorate Identifier 2012-NE-33-AD.

(a) Comments Due Date

    We must receive comments by January 15, 2013.

(b) Affected Airworthiness Directives (ADs)

    None.

(c) Applicability

    This AD applies to the following Rolls-Royce Deutschland Ltd & 
Co KG (RRD) turbofan engines that have any of the high-pressure 
turbine (HPT) stage 1 or stage 2 discs with a serial number (S/N) 
listed in Table 1 to paragraph (c) of this AD, installed:
    (1) RRD BR700-710A1-10 and BR700-710A2-20 turbofan engines; and
    (2) BR700-710C4-11 model engines that have hardware 
configuration standard 710C4-11 or 710C4-11/10 engraved on the 
engine data plate.

[[Page 68716]]

    Table 1 to Paragraph (c)--Affected HPT Stage 1 and Stage 2 Discs
------------------------------------------------------------------------
S/Ns of HPT Stage 1 discs, Part No.     S/Ns of HPT Stage 2 discs, P/N
           (P/N) BRR23952                          BRR22008
------------------------------------------------------------------------
             LDRQA05719                           LDRQA05791
             LDRQA05720                           LDRQA05944
             LDRQA05721                           LDRQA05945
             LDRQA05722
             LDRQA05723
             LDRQA05724
             LDRQA05726
             LDRQA05727
             LDRQA05841
             LDRQA05842
------------------------------------------------------------------------

(d) Reason

    This AD was prompted by RRD performing an evaluation that 
determined that certain HPT stage 1 and stage 2 discs from a 
specific supplier may contain steel inclusions that may cause the 
discs to fail before they reach their current life limits. We are 
issuing this AD to prevent failure of the HPT stage 1 and stage 2 
discs, which could result in uncontained failure of the engine and 
damage to the airplane.

(e) Actions and Compliance

    Unless already done, remove from service the HPT stage 1 and 
stage 2 discs listed by S/N in Table 1 to paragraph (c) of this AD, 
at the following:
    (1) For BR700-710A1-10, BR700-710A2-20, and BR700-710C4-11 
engine models (without RRD Mod 72-101466), remove the HPT stage 1 
and stage 2 discs from service before accumulating 3,000 cycles-
since-new (CSN).
    (2) For the BR700-710C4-11 engine model (with RRD Mod 72-
101466), remove the HPT stage 1 and stage 2 discs from service 
before accumulating 2,300 CSN.

(f) Installation Prohibition

    After the effective date of this AD, do not install an HPT stage 
1 and an HPT stage 2 disc, identified by S/N in Table 1 to paragraph 
(c) of this AD, in the same engine.

(g) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, may approve AMOCs for 
this AD. Use the procedures found in 14 CFR 39.19 to make your 
request.

(h) Related Information

    (1) For more information about this AD, contact Robert Morlath, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238-7154; fax: 781-238-7199; email: 
robert.c.morlath@faa.gov.
    (2) Refer to European Aviation Safety Agency Airworthiness 
Directive 2012-0166, dated August 30, 2012, and Rolls-Royce 
Deutschland Ltd & Co KG Alert Service Bulletin SB-BR700-72-A900508, 
dated July 26, 2012, for related information. Contact Rolls-Royce 
Deutschland Ltd & Co KG, Eschenweg 11, Dahlewitz, 15827 
Blankenfelde-Mahlow, Germany; phone: 49 0 33-7086-1883; fax: 49 0 
33-7086-3276, for a copy of this service information.
    (3) 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.

    Issued in Burlington, Massachusetts, on November 5, 2012.
Colleen M. D'Alessandro,
Assistant Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2012-27824 Filed 11-15-12; 8:45 am]
BILLING CODE 4910-13-P