[Federal Register Volume 68, Number 88 (Wednesday, May 7, 2003)]
[Proposed Rules]
[Pages 24383-24384]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-11267]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 68, No. 88 / Wednesday, May 7, 2003 / 
Proposed Rules  

[[Page 24383]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NE-08-AD]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc RB211 Trent 800 Series 
Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for Rolls-Royce plc (RR) RB211 Trent 875-17, Trent 877-17, Trent 884-
17, Trent 892-17, Trent 892B-17, and Trent 895-17 turbofan engines with 
intermediate pressure (IP) turbine discs, part numbers (P/Ns) FK21117 
and FK33083 installed. This proposed AD would require removal from 
service of these IP turbine discs in accordance with newly established 
reduced turbine disc life limits. This proposed AD is prompted by 
reports of two IP turbine blade release incidents as a result of dust 
caps separating from the blades, and subsequent improved modeling 
analysis. The actions specified in this proposed AD are intended to 
prevent uncontained IP turbine disc failure and damage to the airplane.

DATES: We must receive any comments on this proposed AD by July 7, 
2003.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD:
    [sbull] Federal Aviation Administration (FAA), New England Region, 
Office of the Regional Counsel, Attention: Rules Docket No. 2003-NE-08-
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: 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: 

Comments Invited

    We invite you to submit any written relevant data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. 2003-NE-08-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 proposed 
AD. If a person contacts us through a nonwritten communication, and 
that contact relates to a substantive part of this proposed 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 
proposed 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 that affect you. You may get more information about 
plain language at 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.

Discussion

    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 875-17, Trent 877-17, 
Trent 884-17, Trent 892-17, Trent 892B-17, and Trent 895-17 turbofan 
engines. The CAA advises that reports were received of two IP turbine 
blade release incidents as a result of dust caps separating from the 
blades. Subsequently, the manufacturer applied improved modeling 
techniques for analysis, which revealed higher than predicted operating 
temperatures at the IP turbine disc rim and surrounding area due to 
inflow of annulus exhaust gases. As a result of this analysis, the 
manufacturer has assigned new lower life limits of 8,600 cycles-since-
new (CSN) for IP turbine disc P/N FK21117, and 3,000 CSN for IP turbine 
disc P/N FK33083.

FAA's Determination and Requirements of the Proposed AD

    These RR RB211 Trent 875-17, Trent 877-17, Trent 884-17, Trent 892-
17, Trent 892B-17, and Trent 895-17 turbofan engines, manufactured in 
the U.K., are 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. Pursuant to this bilateral airworthiness agreement, the CAA 
has kept us informed of the situation described above. We have examined 
the CAA's findings, 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. Therefore, we are 
proposing this AD, which would require replacing IP turbine discs, P/Ns 
FK21117 and FK33083, at or before reaching the new reduced life cycle 
limits of 8,600 CSN and 3,000 CSN respectively.

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

    On July 10, 2002, we published a new version of 14 CFR part 39 (67 
FR 47997, July 22, 2002), which governs the FAA's AD system. This 
regulation now includes material that relates to altered products, 
special flight permits, and alternative methods of compliance. 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.

Costs of Compliance

    There are approximately 350 RR RB211 Trent 875-17, Trent 877-17,

[[Page 24384]]

Trent 884-17, Trent 892-17, Trent 892B-17, and Trent 895-17 turbofan 
engines of the affected design in the worldwide fleet. We estimate that 
114 engines installed on airplanes of U.S. registry would be affected 
by this proposed AD. We also estimate that the prorated cost of the 
life reduction per engine would be approximately $246,000. Based on 
these figures, the total cost of the proposed AD is estimated to be 
$28,044,000.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 proposed 
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. Would 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 proposal 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-08-AD'' in your request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 14 
CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    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]

    2. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive:

Rolls-Royce plc: Docket No. 2003-NE-08-AD.

Comments Due Date

    (a) The Federal Aviation Administration must receive comments on 
this airworthiness directive (AD) action by July 7, 2003.

Affected ADs

    (b) None.

Applicability

    (c) This AD is applicable to Rolls-Royce plc (RR) RB211 Trent 
875-17, Trent 877-17, Trent 884-17, Trent 892-17, Trent 892B-17, and 
Trent 895-17 turbofan engines with intermediate pressure (IP) 
turbine discs P/Ns FK21117 and FK33083 installed. These engines are 
installed on, but not limited to Boeing 777 airplanes.

Unsafe Condition

    (d) This AD was prompted by reports of two IP turbine blade 
release incidents as a result of dust caps separating from the 
blades. Subsequently, the manufacturer applied improved modeling 
techniques for analysis, which revealed higher than predicted 
operating temperatures at the IP turbine disc rim and surrounding 
area due to inflow of annulus exhaust gases. The actions specified 
in this AD are intended to prevent uncontained IP turbine disc 
failure and damage to the airplane.

Compliance

    (e) Compliance with this AD is required as indicated, unless 
already done.
    (f) To prevent uncontained IP turbine disc failure and damage to 
the airplane, do the following:
    (1) Remove IP turbine disc P/N FK21117 from service at or before 
accumulating 8,600 cycles-since-new (CSN), and remove IP turbine 
disc P/N FK33083 from service at or before accumulating 3,000 CSN.
    (2) After the effective date of this AD, do not install any IP 
turbine disc P/N FK21117, that exceeds 8,600 CSN, or any IP turbine 
disc P/N FK33083, that exceeds 3,000 CSN.

Alternative Methods of Compliance

    (g) Alternative methods of compliance must be requested in 
accordance with 14 CFR part 39.19, and must be approved by the 
Manager, Engine Certification Office, Engine and Propeller 
Directorate, FAA.

Material Incorporated by Reference

    (h) None.

Related Information

    (i) The subject of this AD is addressed in CAA airworthiness 
directive 002-01-2003, dated January 14, 2003.

    Issued in Burlington, Massachusetts, on April 30, 2003.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 03-11267 Filed 5-6-03; 8:45 am]
BILLING CODE 4910-13-P