[Federal Register: November 12, 2003 (Volume 68, Number 218)]
[Proposed Rules]
[Page 64001-64002]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr12no03-12]
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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.
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[[Page 64001]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NE-46-AD]
RIN 2120-AA64
Airworthiness Directives; General Electric Company CF6-80C2
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 General Electric Company (GE) CF6-80C2 series turbofan engines.
This proposed AD would require replacing certain high pressure turbine
(HPT) stage 1 disks at or before reaching a new reduced life cycle
limit. This proposed AD is prompted by an updated low-cycle-fatigue
(LCF) analysis of the HPT stage 1 disk. We are proposing this AD to
prevent LCF cracking and failure of the HPT stage 1 disk due to
exceeding the life limit, which could result in an uncontained engine
failure and damage to the airplane.
DATES: We must receive any comments on this proposed AD by January 12,
2004.
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-46-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
[sbull] By fax: (781) 238-7055. [sbull] By e-mail: 9-ane-adcomment@faa.gov.
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: Karen Curtis, Aerospace Engineer,
Aircraft Certification Office, FAA, Engine and Propeller Directorate,
12 New England Executive Office Park, Burlington, MA 01803; telephone
(781) 238-7192; 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-46-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. 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 can 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
GE has completed an updated LCF analysis for the CF6-80C2A5F, CF6-
80C2B5F, CF6-80C2B7F, and CF6-80C2D1F HPT stage 1 disks, part numbers
(P/Ns) 1531M84G10 and 1531M84G12, and has established a new reduced
life cycle limit of 10,720 cycles-since-new (CSN) for these disks. In
January 2003, the FAA became aware of GE's in-process analysis and
material testing of HPT stage 1 disks, P/Ns 1531M84G10 and 1531M84G12.
The FAA approved temporary revisions (TRs) to Chapter 5, Life Limits,
of the engine manual (EM), to incorporate revised life limits for these
disks based on initial analytical results. The original life limit of
13,200 CSN for these disks was last published in EM GEK 92451, Revision
57, dated March 1, 2003. TRs 05-0093 and 05-0094, dated May 15, 2003,
revised this life limit from 13,200 CSN to 9,000 CSN. The FAA chose to
wait for final analytical results before taking action to mandate a
lower life limit. This wait was possible due to the young age of the
affected disks. The high-cycle disk has accumulated fewer than 7,500
CSN at this time, which is well below the interim limit of 9,000 CSN
and the final mandated limit. The FAA now approves GE's final
analytical results and the reduced life limit of 10,720 CSN. GE issued
TRs 05-0096 and 05-0097 on June 19, 2003 to revise the life limits
section of the EM for CF6-80C2A5F, CF6-80C2B5F, CF6-80C2B7F, and CF6-
80C2D1F HPT stage 1 disks, P/Ns 1531M84G10 and 1531M84G12, to 10,720
CSN. Although interim publications of the EM showed lower life limits
for this part, those limits were not mandated by an AD. Therefore, an
AD is now required to mandate the approved 10,720 CSN life limit.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other products
of this same type design. Therefore, we are proposing this AD, which
would require replacing HPT stage 1 disks, P/Ns 1531M84G10 and
1531M84G12 at or before reaching a new reduced life cycle limit of
10,720 CSN.
Changes to 14 CFR Part 39--Effect on the Proposed AD
On July 10, 2002, we issued a new version of 14 CFR part 39 (67 FR
47998, 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
[[Page 64002]]
is included in 14 CFR part 39, we will not include it in future AD
actions.
Costs of Compliance
There are about 526 CF6-80C2A5F, CF6-80C2B5F, CF6-80C2B7F, and CF6-
80C2D1F turbofan engines of the affected design in the worldwide fleet.
We estimate that 208 engines installed on airplanes of U.S. registry
would be affected by this proposed AD. The proposed action does not
impose any additional labor costs. The prorated cost of a new HPT stage
1 disk would cost approximately $43,306 per engine. Based on these
figures, and on the prorating for the usage of the HPT stage 1 disks,
the cost of the proposed AD on U.S. operators is estimated to be
$9,007,648.
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-46-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:
General Electric Company: Docket No. 2003-NE-46-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by January 12,
2004.
Affected ADs
(b) None.
Applicability
(c) This AD applies to General Electric Company (GE) CF6-
80C2A5F, CF6-80C2B5F, CF6-80C2B7F, and CF6-80C2D1F turbofan engines
with high pressure turbine (HPT) stage 1 disks, part numbers (P/Ns)
1531M84G10 or 1531M84G12 installed. These engines are installed on,
but not limited to, Airbus Industrie A300 and A330 series, Boeing
747 and 767 series, and McDonnell Douglas MD-11 airplanes.
Unsafe Condition
(d) This AD was prompted by an updated low-cycle-fatigue (LCF)
analysis of the HPT stage 1 disk. We are issuing this AD to prevent
LCF cracking and failure of the HPT stage 1 disk due to exceeding
the life limit, which could result in an uncontained engine failure
and damage to the airplane.
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.
(f) Replace HPT stage 1 disks, P/Ns 1531M84G10 and 1531M84G12,
at or before the disk accumulates 10,720 cycles-since-new (CSN).
(g) After the effective date of this AD, do not install any HPT
stage 1 disk, P/N 1531M84G10 or 1531M84G12, that exceeds 10,720 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) None.
Issued in Burlington, Massachusetts, on November 4, 2003.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 03-28323 Filed 11-10-03; 8:45 am]
BILLING CODE 4910-13-P