[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
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Replace or rework LP
compressor fan
For engines installed on: Engine model: blades at or before
accumulating:
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(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]
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