Airworthiness Directives; Rolls-Royce plc RB211-524G2, -524G2-T, -524G3, -524G3-T, -524H, -524H-T, -524H2, and -524H2-T Series, and Models RB211 Trent 768-60, 772-60, and 772B-60 Turbofan Engines

[Federal Register Volume 68, Number 137 (Thursday, July 17, 2003)]
[Rules and Regulations]
[Pages 42242-42244]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-18078]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NE-20-AD; Amendment 39-13242; AD 2003-14-23]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc RB211-524G2, -524G2-T, 
-524G3, -524G3-T, -524H, -524H-T, -524H2, and -524H2-T Series, and 
Models RB211 Trent 768-60, 772-60, and 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) RB211-524G2, -524G2-T, -524G3, -524G3-T, -524H, -
524H-T, -524H2, and -524H2-T series, and models RB211 Trent 768-60, 
772-60, and 772B-60 turbofan engines with high pressure compressor 
(HPC) rotor stage 1 through stage 6 drums, part numbers (P/Ns) FK25502 
and FW20195 installed. This AD is prompted by reports of cracks found 
in loading slots of HPC rotor stage 1 through stage 6 drums. We are 
issuing this AD to prevent crack initiation and propagation leading to 
uncontained failure of the HPC rotor stage 1 through stage 6 drum, and 
damage to the airplane.

DATES: Effective August 1, 2003.
    We must receive any comments on this AD by September 15, 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-20-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
    [sbull] By fax: (781) 238-7055.
    [sbull] By e-mail: [email protected]
    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.

FOR FURTHER INFORMATION CONTACT: Antonio Cancelliere, Aerospace 
Engineer, Engine Certification Office, FAA, Engine and Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; 
telephone (781) 238-7751; 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 RR RB211-524G2, -524G2-T, -524G3, 
-524G3-T, -524H, -524H-T, -524H2, and -524H2-T series, and models RB211 
Trent 768-60, -772-60, and 772B-60 turbofan engines with HPC stage 1 
through stage 6 drums, P/Ns FK25502 and FW20195 installed. The CAA 
advises that reports have been received of a number of RR Trent 700 
series HPC rotor stage 1 through stage 6 drums found with cracks in the 
blade loading slots. The RB211-524G2, -524G2-T, -524G3, -524G3-T, -
524H, -524H-T, -524H2, and -524H2-T series turbofan engines use an 
identical HPC rotor stage 1 through stage 6 drum. To date, one drum has 
been found with cracks. The manufacturer's investigation has revealed 
that the mechanism inducing

[[Page 42243]]

the cracking is a function of engine operating time and temperature, 
and is initiating cracks in the area of peak stress location. This AD 
requires removal from service of affected HPC rotor stage 1 through 
stage 6 drums at a newly established reduced cyclic life limit. We are 
requiring certain actions in this AD to prevent crack initiation and 
propagation leading to uncontained failure of the HPC rotor stage 1 
through stage 6 drum, and damage to the airplane.

FAA's Determination and Requirements of This AD

    Although none of these affected engine models are used on any 
airplanes that are 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 RB211-524G2, -524G2-T, -524G3, -524G3-T, -524H, -
524H-T, -524H2, and -524H2-T series, and models RB211 Trent 768-60, 
772-60, and 772B-60 turbofan engines of this same type design, we are 
issuing this AD to prevent crack initiation and propagation leading to 
uncontained failure of the HPC rotor stage 1 through stage 6 drum, and 
damage to the airplane. This AD requires removal of HPC rotor stage 1 
through stage 6 drums, P/Ns FK25502 and FW20195, at a newly established 
reduced cyclic life limit of 4,200 cycles-since-new.

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 
Sec.  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 AD action 
is necessary 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 prior public comment 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.

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-20-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 through 
a nonwritten communication, 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://www.plainlanguage.gov.

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-20-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:

2003-14-23 Rolls-Royce plc: Amendment 39-13242. Docket No. 2003-NE-
20-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective August 
1, 2003.

Affected ADs

    (b) None.

Applicability:

    (c) This AD applies to Rolls-Royce plc RB211-524G2, -524G2-T, -
524G3, -524G3-T, -524H, -524H-T, -524H2, and ``524H2-T series, and 
models RB211 Trent 768-60, 772-60, and 772B-60 turbofan engines with 
high pressure compressor (HPC) rotor stage 1 through stage 6 drums, 
part numbers (P/Ns) FK25502 and FW20195 installed. These engines are 
installed on, but not limited to, Airbus A330 series, Boeing 747-400 
series, and 767-300 series airplanes.

Unsafe Condition

    (d) This AD is prompted by reports of cracks found in loading 
slots of HPC rotor stage 1 through stage 6 drums. We are issuing 
this AD to prevent crack initiation and propagation leading to 
uncontained failure of the HPC rotor stage 1 through stage 6 drum, 
and damage to the airplane.

Compliance:

    (e) If you have not already performed the actions required sby 
this AD, you must

[[Page 42244]]

perform the actions within the compliance cycles specified in this 
AD.

Required Actions

    (f) Remove HPC rotor stage 1 through stage 6 drums, P/Ns FK25502 
and FW20195, from service at or before accumulating 4,200 cycles-
since-new (CSN).
    (g) After the effective date of this AD, do not install any HPC 
rotor stage 1 through stage 6 drum, P/N FK25502 or FW20195, that 
exceeds 4,200 CSN.

Alternative Methods of Compliance (AMOCs)

    (h) You must request AMOCs as specified in 14 CFR part 39.19. 
All AMOCs must be approved by the Manager, Engine Certification 
Office, FAA.

Material Incorporated by Reference

    (i) None.

Related Information

    (j) CAA airworthiness directive 004-02-2003, dated April 2003, 
also addresses the subject of this AD.

    Issued in Burlington, Massachusetts, on July 11, 2003.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 03-18078 Filed 7-16-03; 8:45 am]
BILLING CODE 4910-13-U

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