AD 2003-18-09

[Federal Register Volume 68, Number 174 (Tuesday, September 9, 2003)]
[Rules and Regulations]
[Pages 53030-53032]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 03-22888]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NE-29-AD; Amendment 39-13300; AD 2003-18-09]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc Trent 768-60, Trent 
772-60, and Trent 772B-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 
Rolls-Royce plc (RR) Trent 768-60, Trent 772-60, and Trent 772B-60 
turbofan engines. This AD requires removal from service of certain part 
numbers of high pressure (HP) compressor rotor shafts, based on a newly 
established reduced life limit. This AD is prompted by reports of HP 
compressor drums with small cracks in blade loading slots found at 
overhaul inspection. The HP compressor drums are an integral part of 
the HP compressor rotor shaft. We are issuing this AD to prevent 
possible uncontained HP compressor drum failure, which could result in 
damage to the airplane.

DATES: Effective September 24, 2003.
    We must receive any comments on this AD by November 10, 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-29-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
    [sbull] By fax: (781) 238-7055.
    [sbull] By e-mail: <a href="/cdn-cgi/l/email-protection#645d49050a01490500070b0909010a10240205054a030b12"><span class="__cf_email__" data-cfemail="f9c0d498979cd4989d9a9694949c978db99f9898d79e968f">[email&#160;protected]</span></a>.
    You may examine the AD docket at the FAA, New England Region, 
Office of the Regional Counsel, 12 New England Executive Park, 
Burlington, MA.

FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone (781) 
238-7176; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The Civil Aviation Authority, (CAA), which 
is the airworthiness authority for the U.K., recently notified the FAA 
that an unsafe condition may exist on Rolls-Royce plc Trent 768-60, 
Trent 772-60, and Trent 772B-60 turbofan engines. The CAA advises that 
it has received overhaul inspection reports of HP compressor drums with 
small cracks in blade loading slots. The HP compressor drums are an 
integral part of the HP compressor rotor shaft. The manufacturer is 
currently analyzing parts from the field, and has not yet

[[Page 53031]]

determined the root cause of the cracking or established a full 
understanding of the crack propagation rate. Through coordination with 
the CAA, the manufacturer has reduced the declared lives of the 
affected HP compressor rotor shafts to 4,200 cycles-since-new (CSN). 
The FAA has confirmed through the CAA that there are no affected in-
service parts close to accumulating 4,200 CSN. The manufacturer may 
introduce a design change to increase the declared lives of HP 
compressor rotor shafts in the future.

FAA's Determination and Requirements of This AD

    Although none of these affected engine models are used on any 
airplanes registered in the United States, the possibility exists that 
the engine models could be used on airplanes that are registered in the 
United States in the future. Since an unsafe condition has been 
identified that is likely to exist or develop on other Rolls-Royce plc 
Trent 768-60, Trent 772-60, and Trent 772B-60 turbofan engines of the 
same type design, we are issuing this AD to prevent possible 
uncontained HP compressor drum failure, which could result in damage to 
the airplane. The HP compressor drums are an integral part of the HP 
compressor rotor shaft. This AD requires removal from service of 
certain part numbers of HP compressor rotor shafts, based on a newly 
established reduced life limit of 4,200 CSN.

Bilateral Airworthiness Agreement

    This engine model is manufactured in the U.K., and is type 
certificated for operation in the United States under section 21.29 of 
the Federal Aviation Regulations (14 CFR 21.29) and the applicable 
bilateral airworthiness agreement. In keeping with 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 we need to 
issue an AD for products of this type design that are certificated for 
operation in the United States.

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, we can adopt this regulation immediately.

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.

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-29-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 <a href="http://www.faa.gov/language">http://www.faa.gov/language</a> and <a href="http://www.plainlanguage.gov">http://www.plainlanguage.gov</a>.

Examining the AD Docket

    You may examine the AD Docket (including any comments), between 
8:00 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-29-AD'' in your request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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:

2003-18-09 Rolls-Royce plc: Amendment 39-13300. Docket No. 2003-NE-
29-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective 
September 24, 2003.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Rolls-Royce plc (RR) Trent 768-60, Trent 
772-60, and Trent 772B-60 turbofan engines. These engines are 
installed on, but not limited to Airbus A330 series airplanes.

Unsafe Condition

    (d) This AD is prompted by reports of high pressure (HP) 
compressor drums with small cracks in blade loading slots found at 
overhaul inspection. We are issuing this AD to prevent possible 
uncontained HP compressor drum failure, which could result in damage 
to the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within

[[Page 53032]]

the compliance cycles specified unless the actions have already been 
done.
    (f) Remove HP compressor rotor shafts, part numbers (P/Ns) 
FK24031 (pre RR Service Bulletin (SB) RB.211-72-B172), FK22745 (SB 
RB.211-72-B172), FK23313 (SB RB.211-72-B261 and pre SB RB.211-72-
B653), FK25502 (SB RB.211-72-B653), FK26185 (SB RB.211-72-B921), 
FK32129 (SB RB.211-72-C746), FW20195 (SB RB.211-72-D533), FW20196 
(SB RB.211-72-D533), FW20197 (SB RB.211-72-D533), and FW20638 (SB 
RB.211-72-D533) from service at or before accumulating 4,200 cycles-
since-new (CSN).
    (g) After the effective date of this AD, do not install any HP 
compressor rotor shaft, P/Ns FK24031 (pre RR SB RB.211-72-B172), 
FK22745 (SB RB.211-72-B172), FK23313 (SB RB.211-72-B261 and pre SB 
RB.211-72-B653), FK25502 (SB RB.211-72-B653), FK26185 (SB RB.211-72-
B921), FK32129 (SB RB.211-72-C746), FW20195 (SB RB.211-72-D533), 
FW20196 (SB RB.211-72-D533), FW20197 (SB RB.211-72-D533), or FW20638 
(SB RB.211-72-D533), that exceeds 4,200 CSN.

Alternative Methods of Compliance

    (h) 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

    (i) None.

Related Information

    (j) CAA airworthiness directive 003-12-2001, dated February 26, 
2002, and Rolls-Royce plc Mandatory Service Bulletin No. RB.211-72-
D586, Revision 1, dated February 26, 2002, also address the subject 
of this AD.

    Issued in Burlington, Massachusetts, on September 3, 2003.
Marc J. Bouthillier,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 03-22888 Filed 9-8-03; 8:45 am]
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