Document ID: FAA-2012-0418-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Rolls-Royce PLC Turbofan Engines
Posted Date: 2012-05-31T04:00Z

[Federal Register Volume 77, Number 105 (Thursday, May 31, 2012)]
[Rules and Regulations]
[Pages 32007-32009]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-13081]

[[Page 32007]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0418; Directorate Identifier 2012-NE-12-AD; 
Amendment 39-17064; AD 2012-11-01]
RIN 2120-AA64

Airworthiness Directives; Rolls-Royce plc Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Rolls-Royce plc (RR) RB211-Trent 800 series turbofan engines. This AD 
requires removal from service of certain critical engine parts based on 
reduced life limits. This AD was prompted by RR adding a new flight 
profile and an associated set of life limits. We are issuing this AD to 
prevent the failure of critical rotating parts, which could result in 
uncontained failure of the engine and damage to the airplane.

DATES: This AD becomes effective June 15, 2012.
    We must receive comments on this AD by July 16, 2012.

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: 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: 011-44-1332-245418 or email from http://www.rolls-royce.com/contact/civil_team.jsp, or download the 
publication from https://www.aeromanager.com. You may review copies of 
the referenced 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 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: Alan Strom, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; phone: 781-238-7143; fax: 
781-238-7199; email: alan.strom@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD 2012-0051, dated March 26, 2012 (referred to after this as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states:

    Flight Profiles (FP) define the limits of engine operation 
within which the engine will qualify for use of an associated set of 
Critical Parts life limits. The Rolls-Royce RB211-Trent 800 engine 
previously had seven such FPs and associated sets of life limits 
published in the RR Time Limits Manual.
    However, the results of a recent review of operational flight 
data determined that the existing FPs do not encompass the full 
range of Trent 800 operations. To account for the consequent 
increased rate of fatigue life usage on the life limited Critical 
Parts, a new FP and associated set of reduced life limits for 
Critical Parts has been developed, defined as FP ``MAX'', that 
defines a new level of operation which is outside the ``HEAVY'' FP, 
previously the most arduous.

    We are issuing this AD to prevent the failure of critical rotating 
parts, which could result in uncontained failure of the engine and 
damage to the airplane. You may obtain further information by examining 
the MCAI in the AD docket.

FAA's Determination and Requirements of This AD

    This product has been approved by 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 issuing 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.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because some 
parts may require immediate removal upon recalculation of the part 
lives in accordance with the AD. Therefore, we determined that notice 
and opportunity for public comment before issuing this AD are 
impracticable and that good cause exists for making this amendment 
effective in fewer than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2012-0418; Directorate 
Identifier 2012-NE-12-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD because of 
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 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).

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.

[[Page 32008]]

    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); 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.
    4. We prepared a regulatory evaluation of the estimated costs to 
comply with this 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.

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 AD:

2012-11-01 Rolls-Royce plc: Amendment 39-17064; Docket No. FAA-2012-
0418; Directorate Identifier 2012-NE-12-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective June 15, 
2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Rolls-Royce plc (RR) RB211-Trent 875-17, 877-
17, 884-17, 884B-17, 892-17, 892B-17, and 895-17 turbofan engines.

(d) Reason

    This AD was prompted by RR adding a new flight profile and an 
associated set of life limits. We are issuing this AD to prevent the 
failure of critical rotating parts, which could result in 
uncontained failure of the engine and damage to the airplane.

(e) Actions and Compliance

    Compliance is required within 30 days after the effective date 
of this AD, unless already done.
    (f) After the effective date of this AD, remove from service the 
parts listed by part number (P/N) in Table 1 of this AD before 
exceeding the new life limit indicated.

                        Table 1--Reduced Part Lives--Life in Cycles Using the MAX Profile
----------------------------------------------------------------------------------------------------------------
                                                                                 New life limit in  MAX profile
           Part nomenclature                             P/N                                 cycles
----------------------------------------------------------------------------------------------------------------
(1) Low-pressure (LP) Compressor Rotor  FK14399, FK30901.....................  10,080.
 Disc.
(2) LP Compressor Rotor Shaft.........  FK20840..............................  7,950.
(3) Intermediate-pressure (IP)          FK24100, FK24496.....................  8,140.
 Compressor Rotor Shaft.
(4) IP Rear Shaft.....................  FK23564, FW18545.....................  15,000.
(5) High-pressure (HP) Compressor       FK24009..............................  MAX profile cycles prohibited.
 Stage 1 to 4 Rotor Discs Shaft.
(6) HP Compressor Stage 1 to 4 Rotor    FK26167, FK32580, FW88724............  4,500.
 Discs Shaft.
(7) HP Compressor Stage 1 to 4 Rotor    FW11590, FW61622, FW88723, FW88725...  6,000.
 Discs Shaft.
(8) HP Compressor Stage 5 and 6 Discs   FK25230, FK27899.....................  4,500.
 and Cone.
(9) HP Compressor Stage 5 and 6 Discs   FW24633..............................  5,800.
 and Cone.
(10) HP Compressor Stage 5 and 6 Discs  FW24634..............................  5,060.
 and Cone.
(11) HP Turbine Rotor Disc............  FK24651, FK24790.....................  4,500.
(12) HP Turbine Rotor Disc............  FK26893..............................  5,540.
(13) IP Turbine Rotor Disc............  FK21117, FK33049.....................  8,400.
(14) IP Turbine Rotor Disc............  FK33083..............................  MAX profile cycles prohibited.
(15) IP Turbine Rotor Shaft...........  FK23295, FK25180, FW18550, FW19626...  10,380.
(16) LP Turbine Stage 1 Rotor Disc....  FK24971..............................  15,000.
(17) LP Turbine Stage 2 Rotor Disc....  FK23208, FK26625.....................  15,000.
(18) LP Turbine Stage 3 Rotor Disc....  FK24199, FK26626.....................  15,000.
(19) LP Turbine Stage 4 Rotor Disc....  FK23210..............................  15,000.
(20) LP Turbine Stage 5 Rotor Disc....  FK24200..............................  15,000.
(21) LP Turbine Rotor Shaft...........  FK20817..............................  7,360.
----------------------------------------------------------------------------------------------------------------

(g) Installation Prohibition

    After the effective date of this AD, do not install any IP 
turbine rotor discs, P/N FK33083, into any engine.

(h) 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.

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(i) Related Information

    (1) You may find additional information on calculating MAX 
Profile Cycles, in RB211 Trent 800 Propulsion Systems Alert Service 
Bulletin (ASB) No. RB.211-72-AG801 and RR Time Limits Manual 05-00-
01-800-801, Recording and Control of the Lives of Parts.
    (2) For more information about this AD, contact Alan Strom, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238-7143; fax: 781-238-7199; email: 
alan.strom@faa.gov.
    (3) Refer to European Aviation Safety Agency Airworthiness 
Directive 2012-0051, dated March 26, 2012, and RB211 Trent 800 
Propulsion Systems ASB No. RB.211-72-AG801, dated December 8, 2011, 
for related information.
    (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: 011-44-1332-245418 
or email from http://www.rolls-royce.com/contact/civil_team.jsp.

(i) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on May 16, 2012.
Peter A. White,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-13081 Filed 5-30-12; 8:45 am]
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