[Federal Register Volume 68, Number 205 (Thursday, October 23, 2003)]
[Proposed Rules]
[Pages 60627-60629]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-26720]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NE-38-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) models RB211 Trent 875-17, Trent 877-17, Trent 
884-17, Trent 892-17, Trent 892B-17, and Trent 895-17 turbofan engines, 
with low pressure (LP) compressor fan blades part number (P/N) FW18548 
installed. This proposed AD would require LP compressor fan blade 
replacement with new or previously reworked blades, or rework of the 
existing LP compressor fan blades. This proposed AD is prompted by a 
number of new production LP compressor fan blades found with surfaces 
formed outside of design intent. Findings included sharp edges, burrs, 
and damage present in the area at the top of the shear key slots. We 
are proposing this AD to prevent possible multiple uncontained LP 
compressor fan blade failure, due to cracking in the blade root caused 
by increased stresses in the shear key slots.

DATES: We must receive any comments on this proposed AD by December 22, 
2003.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD:
    [sbull] By mail: Federal Aviation Administration (FAA), New England 
Region, Office of the Regional Counsel, Attention: Rules Docket No. 
2003-NE-38-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 identified in this proposed AD 
from Rolls-Royce plc, PO 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.

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-38-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 verbally, 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.

[[Page 60628]]

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.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.

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 Rolls-Royce plc RB211 Trent 800 series 
turbofan engines. The CAA advises that the results of a recent 
examination of a number of new production LP compressor fan blades, 
found surfaces in the area of the shear key slot and the junction of 
the blade root profile, to be formed outside of design intent. Findings 
included sharp edges, burrs, and damage present in the area at the top 
of the shear key slots. This can lead to cracking in the blade root, 
causing multiple uncontained LP compressor fan blade failure.

Relevant Service Information

    We have reviewed and approved the technical contents of service 
bulletin No. RB.211-72-E044, Revision 1, dated May 2, 2003, that 
describes procedures for reworking LP compressor fan blades, P/N 
FW18548.

FAA's Determination and Requirements of the Proposed AD

    These Rolls-Royce plc (RR) models 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, at or before the accumulation of certain cycles-since-new 
based on engine application, replacement of LP compressor fan blades, 
P/N FW18548, with new or previously reworked LP compressor fan blades, 
or rework of the existing blades.

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 about 350 RR models RB211 Trent 875-17, Trent 877-17, 
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 
106 engines installed on airplanes of U.S. registry would be affected 
by this proposed AD. We also estimate that it would take about 100 work 
hours per engine to perform blade rework, and that the average labor 
rate is $65 per work hour. Based on these figures, we estimate the 
total cost of the proposed AD to U.S. operators to be $689,000.

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-38-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-38-AD.

Comments Due Date

    (a) The FAA must receive comments on this airworthiness 
directive (AD) action by December 22, 2003.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Rolls-Royce plc (RR) models RB211 Trent 
875-17, Trent 877-17, Trent 884-17, Trent 892-17, Trent 892B-17, and 
Trent 895-17 turbofan engines, with low pressure (LP) compressor fan 
blades, part number (P/N) FW18548 installed. These engines are 
installed on, but not limited to, Boeing 777 series airplanes.

Unsafe Condition

    (d) This AD was prompted by a number of new production LP 
compressor blades found with surfaces formed outside of design 
intent. Findings included sharp edges, burrs, and damage present in 
the area at the top of the shear key slots. We are issuing this AD 
to prevent possible multiple uncontained LP compressor fan blade 
failure, due to cracking in the blade root caused by increased 
stresses in the shear key slots.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified unless the 
actions have already been done.

Actions Required for LP Compressor Fan Blades

    (f) Replace LP compressor fan blades with new or previously 
reworked LP compressor blades at or before accumulating the 
specified cycles in the following Table 1, or rework the existing 
blades as specified in paragraph (g) of this AD.
    (g) Rework LP compressor fan blades at or before accumulating 
the specified cycles in the following Table 1. Follow paragraphs 
3.A. through 3.B.(22) of Accomplishment Instructions of RR service 
bulletin (SB) No.

[[Page 60629]]

RB.211-72-E044, Revision 1, dated May 2, 2003, to do the blade 
rework.

    Table 1.--LP Compressor Fan Blade Replacement or Rework Schedule
------------------------------------------------------------------------
                                                    Replace or rework LP
                                                       compressor fan
  For engines installed on:       Engine model:      blades at or before
                                                        accumulating:
------------------------------------------------------------------------
(1) Boeing 777-300..........  Trent 884-17 and      2,400 cycles-since-
                               Trent 892-17.         new (CSN).
(2) Boeing 777-200IGW.......  (i) Trent 892-17....  4,100 CSN.
                              (ii) Trent 895-17...  3,200 CSN.
(3) Boeing 777-200ER........  Trent 892B-17.......  4,100 CSN.
(4) Boeing 777-200..........  Trent 875-17, Trent   4,100 CSN.
                               877-17, and Trent
                               884-17.
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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) You must use RR SB No. RB.211-72-E044, Revision 1, dated May 
2, 2003, to perform the blade rework required by this AD.

Related Information

    (j) CAA airworthiness directive 001-05-2003, dated June 20, 
2003, also addresses the subject of this AD, and RR SB No. RB.211-
72-E055, Revision 1, dated June 20, 2003, pertains to the subject of 
this AD.

    Issued in Burlington, Massachusetts, on October 16, 2003.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 03-26720 Filed 10-22-03; 8:45 am]
BILLING CODE 4910-13-P