[Federal Register Volume 68, Number 210 (Thursday, October 30, 2003)]
[Rules and Regulations]
[Pages 61739-61742]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-27153]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NE-37-AD; Amendment 39-13350; AD 2003-22-03]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc Trent 768-60 and Trent 
772-60 Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Rolls-Royce plc (RR) RB211 Trent 768-60 and Trent 772-60 
turbofan engines. This AD requires reworking the low

[[Page 61740]]

pressure (LP) turbine nozzle vane case, the LP turbine bearing support 
exhaust case, and the support arm bracket assemblies. This AD is 
prompted by a report of an LP stage 4 blade failure at the blade shank, 
resulting in severe radial distortion of the rear flange of the LP 
turbine case and failure of a number of attaching bolts, resulting in 
enough flange separation to allow the release of high energy debris. We 
are issuing this AD to prevent possible uncontained LP turbine case 
failure and damage to the airplane.

DATES: Effective November 14, 2003. The Director of the Federal 
Register approved the incorporation by reference of certain 
publications listed in the regulations as of November 14, 2003.
    We must receive any comments on this AD by December 29, 2003.

ADDRESSES:
    Use one of the following addresses to submit comments on this AD:

[sbull] By mail: The Federal Aviation Administration (FAA), New England 
Region, Office of the Regional Counsel, Attention: Rules Docket No. 
2003-NE-37-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
[sbull] By fax: (781) 238-7055.
[sbull] By e-mail: [email protected].

    You can get the service information referenced in this AD from 
Rolls-Royce plc, P.O. Box 31, Derby, England, DE248BJ; telephone: 011-
44-1332-242424; fax: 011-44-1332-245418.
    You may examine the AD docket, by appointment, at the FAA, New 
England Region, Office of the Regional Counsel, 12 New England 
Executive Park, Burlington, MA. You may examine the service 
information, by appointment, at the FAA, New England Region, Office of 
the Regional Counsel, 12 New England Executive Park, Burlington, MA; or 
at the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park; telephone (781) 238-7176; fax (781) 238-
7199.

SUPPLEMENTARY INFORMATION: The Civil Aviation Authority, (CAA), which 
is the airworthiness authority for the United Kingdom (U.K.), recently 
notified the FAA that an unsafe condition may exist on RR RB211 Trent 
768-60 engines with serial numbers (SNs) before SN 41056 and RB211 
Trent 772-60 engines with SNs before SN 41056. The CAA advises that an 
LP turbine stage 4 blade failed during a development test. Examination 
of the LP turbine case and attaching bolts, which had been subjected to 
the stage 4 blade failure at the shank, showed severe radial distortion 
of the rear flange and a number of bolts which had failed in shear or a 
combination of shear and tension. The initial distortion and flange 
separation occurred locally at the blade impact point and allowed 
debris to become trapped between the flanges. This debris then 
contacted with the remaining rotating blades resulting in enough flange 
separation to allow release of high-energy debris.

Relevant Service Information

    We have reviewed and approved the technical contents of RR 
Mandatory Service Bulletin (MSB) No. RB.211-72-C224, Revision 4, dated 
April 12, 2002, that describes the procedures for reworking the LP 
turbine nozzle vane case, the LP turbine bearing support exhaust case, 
and the support arm bracket assemblies. The CAA classified this service 
bulletin as mandatory and issued AD 010-03-99, dated April 12, 2002, in 
order to ensure the airworthiness of these RR plc engines in the U.K.

Bilateral Airworthiness Agreement

    This engine model is manufactured in the U.K. and is type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Under this bilateral 
airworthiness agreement, the CAA has kept the FAA informed of the 
situation described above. We have examined the findings of the CAA, 
reviewed all available information, and determined that AD action is 
necessary for products of this type design that are certificated for 
operation in the United States.

FAA's Determination and Requirements of This AD

    Although no airplanes that are registered in the United States use 
these engines, the possibility exists that the engines could be used on 
airplanes that are registered in the United States in the future. The 
unsafe condition described previously is likely to exist or develop on 
other RR Trent 768-60 and Trent 772-60 engines of the same type design. 
We are issuing this AD to prevent possible uncontained LP turbine case 
failure and damage to the airplane. This AD requires reworking the LP 
turbine nozzle vane case, the LP turbine bearing support exhaust case, 
and the support arm bracket assemblies. You must use the service 
information described previously to perform the actions required by 
this AD.

FAA's Determination of the Effective Date

    Since there are currently no domestic operators of this engine 
model, notice and opportunity for public comment before issuing this AD 
are unnecessary. Therefore, a situation exists that allows the 
immediate adoption of this regulation.

Changes to 14 CFR Part 39--Effect on the AD

    On July 10, 2002, we issued a new version of 14 CFR part 39 (67 FR 
47997, July 22, 2002), which governs our AD system. This regulation now 
includes material that relates to special flight permits, alternative 
methods of compliance, and altered products. This material previously 
was included in each individual AD. Since this material is included in 
14 CFR part 39, we will not include it in future AD actions.

Interim Action

    These actions are interim actions and we may take further 
rulemaking actions in the future.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment; however, we invite you to submit any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. 2003-NE-37-AD'' in the 
subject line of your comments. If you want us to acknowledge receipt of 
your mailed comments, send us a self-addressed, stamped postcard with 
the docket number written on it; we will date-stamp your postcard and 
mail it back to you. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the rule 
that might suggest a need to modify it. If a person contacts us 
verbally, and that contact relates to a substantive part of this AD, we 
will summarize the contact and place the summary in the docket. We will 
consider all comments received by the closing date and may amend the AD 
in light of those comments.
    We are reviewing the writing style we currently use in regulatory 
documents. We are interested in your comments on whether the style of 
this document is clear, and your suggestions to improve the clarity of 
our communications with you. You may get more information about plain 
language at http://

[[Page 61741]]

www.faa.gov/language and http://www.plainlanguage.gov.

Examining the AD Docket

    You may examine the AD Docket (including any comments and service 
information), by appointment, between 8 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. See ADDRESSES for the 
location.

Regulatory Findings

    We have 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 that the 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 summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary by 
sending a request to us at the address listed under ADDRESSES. Include 
``AD Docket No. 2003-NE-37-AD'' in your request.

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 Federal Aviation Administration amends part 39 of the Federal 
Aviation Regulations (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:

2003-22-03 Rolls-Royce plc: Amendment 39-13350. Docket No. 2003-NE-
37-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective November 
14, 2003.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Rolls-Royce plc (RR) RB211 Trent 768-60 
turbofan engines with serial numbers (SNs) before SN 41056 and RB211 
Trent 772-60 turbofan engines with SNs before SN 41056. These 
engines are installed on, but not limited to, Airbus A330 series 
airplanes.

Unsafe Condition

    (d) This AD is prompted by a report of a low pressure (LP) stage 
4 blade failure at the blade shank, resulting in severe radial 
distortion of the rear flange of the LP turbine case and failure of 
a number of attaching bolts, resulting in enough flange separation 
to allow the release of high energy debris. We are issuing this AD 
to prevent possible uncontained LP turbine case failure and damage 
to the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within 15 months after the effective date of this AD, 
unless the actions have already been done.

Rework of Affected Components

    (f) Rework the LP turbine nozzle vane case, part numbers (P/Ns) 
FK19488 and FK22687. Use Accomplishment Instruction paragraph 3.B. 
of RR Mandatory Service Bulletin (MSB) No. RB.211-72-C224, Revision 
4, dated April 12, 2002.
    (g) Rework the LP turbine bearing support exhaust case, P/N 
FK22791. Use Accomplishment Instruction paragraph 3.C. of RR MSB No. 
RB.211-72-C224, Revision 4, dated April 12, 2002.
    (h) Rework the support arm bracket assembly, P/N FK29121. Use 
Accomplishment Instruction paragraph 3.D. of RR MSB No. RB.211-72-
C224, Revision 4, dated April 12, 2002.

Conditions for Installation

    (i) Reworked components identified in paragraphs (f), (g), and 
(h) of this AD must be installed as a complete set only.
    (j) Information on interchangeability of parts can be found in 
section 1.M. of RR MSB RB.211-72-C224, Revision 4, dated April 12, 
2002.
    (k) After the effective date of this AD, do not install any 
modules marked M08821AA, M08821AB, or core engines TRENT121AA, or 
TRENT122AA into any engine.

Alternative Methods of Compliance

    (l) The Manager, Engine Certification Office, has the authority 
to approve alternative methods of compliance for this AD if 
requested using the procedures found in 14 CFR 39.19.

Material Incorporated by Reference

    (m) You must use the service information specified in Table 1 to 
perform the actions required by this AD. The Director of the Federal 
Register approved the incorporation by reference of the documents 
listed in Table 1 of this AD in accordance with 5 U.S.C. 552(a) and 
1 CFR part 51. You can get a copy from Rolls-Royce plc, P.O. Box 31, 
Derby, England, DE248BJ; telephone: 011-44-1332-242424; fax: 011-44-
1332-245418. You may review copies at Federal Aviation 
Administration, New England Region, Office of the Regional Counsel, 
12 New England Executive Park, Burlington, MA; or at the Office of 
the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC. Table 1 follows:

                                      Table 1.--Incorporation by Reference
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            Service bulletin No.                 Page      Revision                      Date
----------------------------------------------------------------------------------------------------------------
Rolls-Royce plc Mandatory Service Bulletin            1          14   April 12, 2002.
 RB.211-72-C224.
                                                    2-3           3   September 12, 2001.
                                                    4-7           4   April 12, 2002.
                                                    8-9           3   September 12, 2001.
                                                  10-14           4   April 12, 2002.
                                                  15-16           3   September 12, 2001.
                                                     17           4   April 12, 2002.
                                                  18-36           3   September 12, 2001.
 Total Pages: 36.
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[[Page 61742]]

Related Information

    (n) CAA airworthiness directive 010-03-99, dated April 12, 2002, 
also addresses the subject of this AD.

    Issued in Burlington, Massachusetts, on October 20, 2003.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 03-27153 Filed 10-29-03; 8:45 am]
BILLING CODE 4910-13-P