Airworthiness Directives; Rolls-Royce plc. (RR) RB211 Trent 900 Series Turbofan Engines

[Federal Register Volume 74, Number 173 (Wednesday, September 9, 2009)]
[Rules and Regulations]
[Pages 46329-46331]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-20830]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0771; Directorate Identifier 2009-NE-14-AD; 
Amendment 39-16009; AD 2009-18-13]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc. (RR) RB211 Trent 900 
Series 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 the 
products listed above. This AD results from mandatory continuing 
airworthiness information (MCAI) issued by an aviation authority of 
another country to identify and correct an unsafe condition on an 
aviation product. The MCAI describes the unsafe condition as:

    Evidence from development testing and flight test Trent 900 
engines has identified cracking on some HP Turbine Nozzle Guide

[[Page 46330]]

Vane (NGV) Convex Surfaces. Analysis of test data and review of the 
manufacturing process has revealed compounding effects that may 
contribute to a shortfall in component life and an increased 
likelihood of premature cracking in this region. Excessive cracking 
on the Convex Surface may lead to the release of NGV material or the 
blockage of Turbine gas flow. This results in a risk of fracture to 
the HP Turbine Blade.

    We are issuing this AD to prevent the release of a high-pressure 
(HP) turbine blade, which could result in an engine power loss or in-
flight shut down of one or more engines, resulting in an inability to 
continue safe flight.

DATES: This AD becomes effective October 14, 2009.
    We must receive comments on this AD by October 9, 2009.
    The Director of the Federal Register approved the incorporation by 
reference of RR Alert Service Bulletin (ASB) RB.211-72-AF995, Revision 
2, dated February 9, 2009, listed in the AD as of September 24, 2009.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
    <bullet> Mail: U.S. Department of Transportation, 1200 New Jersey 
Avenue, SE., West Building Ground Floor, Room W12-140, Washington, DC 
20590-0001.
    <bullet> Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    <bullet> Fax: (202) 493-2251.

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 (telephone (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: Ian Dargin, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park; Burlington, MA 01803; e-mail: 
[email protected]; telephone (781) 238-7178; fax (781) 238-7199.

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 
Airworthiness Directive 2009-0051, dated March 5, 2009 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    Evidence from development testing and flight test Trent 900 
engines has identified cracking on some HP Turbine Nozzle Guide Vane 
(NGV) Convex Surfaces. Analysis of test data and review of the 
manufacturing process has revealed compounding effects that may 
contribute to a shortfall in component life and an increased 
likelihood of premature cracking in this region. Excessive cracking 
on the Convex Surface may lead to the release of NGV material or the 
blockage of Turbine gas flow. This results in a risk of fracture to 
the HP Turbine Blade.
    Not all NGV assemblies are affected. It is believed that the 
problem, if it exists, will manifest itself below 1000 cycles.

    You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Rolls-Royce plc. has issued Alert Service Bulletin RB.211-72-AF995, 
Revision 2, dated February 9, 2009. The actions described in this 
service information are intended to correct the unsafe condition 
identified in the MCAI.

FAA's Determination and Requirements of This 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 United Kingdom, they have 
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

    Since no domestic operators use this product, notice and 
opportunity for public comment before issuing this AD are unnecessary. 
Therefore, we are adopting this regulation immediately.

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-2009-0771; Directorate 
Identifier 2009-NE-14-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.
    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 46331]]

    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 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

0
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:

2009-18-13 Rolls-Royce plc: Amendment 39-16009.; Docket No. FAA-
2009-0771; Directorate Identifier 2009-NE-14-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective October 
14, 2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Rolls-Royce plc (RR) model RB211 Trent 
970-84, 970B-84, 972-84, 972B-84, 977-84, 977B-84, and 980-84 
turbofan engines that do not incorporate RR modification Service 
Bulletin (SB) RB.211-72-G025. These engines are installed on, but 
not limited to, Airbus A380 airplanes.

Reason

    (d) Evidence from development testing and flight test Trent 900 
engines has identified cracking on some HP Turbine Nozzle Guide Vane 
(NGV) Convex Surfaces. Analysis of test data and review of the 
manufacturing process has revealed compounding effects that may 
contribute to a shortfall in component life and an increased 
likelihood of premature cracking in this region. Excessive cracking 
on the Convex Surface may lead to the release of NGV material or the 
blockage of Turbine gas flow. This results in a risk of fracture to 
the HP Turbine Blade.
    We are issuing this AD to prevent the release of a high-pressure 
(HP) turbine blade, which could result in an engine power loss or 
in-flight shut down of one or more engines, resulting in an 
inability to continue safe flight.

Actions and Compliance

First Inspection

    (e) Before accumulating 400 total cycles, inspect the HPT NGV 
Convex Surfaces, in accordance with the accomplishment instructions 
in section 3.A of Rolls-Royce RB211-Trent 900 Alert Non Modification 
Service Bulletin (NMSB) RB.211-72-AF995 Revision 2, dated February 
9, 2009.

Reinspection

    (f) If no damage is identified at first inspection:
    (1) Repeat the inspection at intervals less than 250 Cycles 
apart.
    (2) If repeat inspections reveal no damage at 1000 cycles revert 
to normal inspection maintenance as detailed in the Rolls-Royce 
RB211-Trent 900 Maintenance Planning Document (MPD), and sign off 
this AD as complied with; no further inspections are required by 
this AD.
    (g) If any damage is identified, refer to the Table 1 and Table 
2 in section 3.B. of Rolls-Royce RB211-Trent 900 Alert NMSB RB.211-
72-AF995 Revision 2, dated February 9, 2009, for reinspection 
intervals and rejection criteria.

FAA AD Differences

    (h) None.

Other FAA AD Provisions

    (i) Alternative Methods of Compliance (AMOCs): The Manager, 
Engine Certification Office, FAA, has the authority to approve AMOCs 
for this AD, if requested using the procedures found in 14 CFR 
39.19.

Related Information

    (j) Refer to MCAI EASA Airworthiness Directive 2009-0051, dated 
March 5, 2009.
    (k) Contact Ian Dargin, Aerospace Engineer, Engine Certification 
Office, FAA, Engine and Propeller Directorate, 12 New England 
Executive Park; Burlington, MA 01803; e-mail: [email protected]; 
telephone (781) 238-7178; fax (781) 238-7199, for more information 
about this AD.

Material Incorporated by Reference

    (l) You must use RR Alert Non Mandatory Service Bulletin RB.211-
72-AF995 Revision 2, dated February 9, 2009, to do the actions 
required by this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Rolls-Royce plc, P.O. Box 31, DERBY, DE24 8BJ, UK; telephone 44 (0) 
1332 242424; fax 44 (0) 1332 249936.
    (3) You may review copies at the FAA, New England Region, 12 New 
England Executive Park, Burlington, MA; or at the National Archives 
and Records Administration (NARA). For information on the 
availability of this material at NARA, call (202) 741-6030, or go 
to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on August 20, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-20830 Filed 9-8-09; 8:45 am]
BILLING CODE 4910-13-P

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