[Federal Register: May 11, 2004 (Volume 69, Number 91)]
[Rules and Regulations]
[Page 26027-26029]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr11my04-19]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NE-45-AD; Amendment 39-13625; AD 2004-09-34]
RIN 2120-AA64
Airworthiness Directives; General Electric Company CF6-80E1 Model
Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for General Electric Company (GE) CF6-80E1 model turbofan engines
with high pressure turbine (HPT) stage 2 (S2) nozzle guide vanes (NGVs)
part number (P/N) 1647M84G09 or 1647M84G10, installed. That AD
currently requires flex borescope inspections of HPT S2 NGVs installed
in CF6-80E1 model turbofan engines. This AD requires the same actions
but at reduced compliance intervals. This AD results from inspection
findings of HPT S2 NGVs that show cracks from distress could occur
sooner and grow faster than originally predicted. We are issuing this
AD to prevent failure of HPT rotor blades from HPT S2 NGV distress,
which could result in an uncontained engine failure.
DATES: Effective May 26, 2004. The Director of the Federal Register
approved the incorporation by reference of certain publications listed
in the regulations as of May 26, 2004.
We must receive any comments on this AD by July 12, 2004.
ADDRESSES: Use one of the following addresses to submit comments on
this AD:
By mail: The Federal Aviation Administration (FAA), New
England Region, Office of the Regional Counsel, Attention: Rules Docket
No. 2001-NE-45-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
By fax: (781) 238-7055.
By e-mail: 9-ane-adcomment@faa.gov.
You can get the service information referenced in this AD from
General Electric Company via Lockheed Martin Technology Services, 10525
Chester Road, Suite C, Cincinnati, Ohio 45215, telephone (513) 672-
8400, fax (513) 672-8422.
You may examine the AD docket, at the FAA, New England Region,
Office of the Regional Counsel, 12 New England Executive Park,
Burlington, MA. You may examine the service information, by
appointment, at the FAA, New England Region, Office of the Regional
Counsel, 12 New England Executive Park, Burlington, MA; or at the
National Archives and Records Administration (NARA). For information on
the availability of this material at NARA, call 202-741-6030, or go to:
http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
FOR FURTHER INFORMATION CONTACT: Karen Curtis, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone: (781)
238-7192; fax: (781) 238-7199.
SUPPLEMENTARY INFORMATION: On January 15, 2002, the FAA issued AD 2002-
01-04, Amendment 39-12595 (67 FR 4326, January 30, 2002). That AD
requires flex borescope inspections of HPT S2 NGVs installed in CF6-
80E1 model turbofan engines. That AD was the result of an uncontained
engine failure attributed to HPT S2 NGV distress. That condition, if
not corrected, could result in failure of HPT rotor blades from HPT S2
NGV distress, which could result in an uncontained engine failure.
Actions After AD 2002-01-04 Was Issued
After AD 2002-01-04 was issued, GE received inspection findings of
HPT S2 NGVs that show cracks from distress. GE and the FAA have
determined that cracks from this distress could occur sooner and
propagate faster than originally predicted, and have also determined
that the inspection compliance intervals of AD 2002-01-04 are too long.
Relevant Service Information
We have reviewed and approved the technical contents of GE Service
Bulletin (SB) No. CF6-80E1 S/B 72-0217, Revision 2, dated January 5,
2004, that describes procedures for initial and repetitive flex
borescope inspection of HPT S2 NGV P/Ns 1647M84G09 and 1647M84G10.
[[Page 26028]]
FAA's Determination and Requirements of This AD
Although no airplanes that are registered in the United States use
these GE CF6-80E1 model turbofan engines, the possibility exists that
the engine model could be used on airplanes that are registered in the
United States in the future. The unsafe condition described previously
is likely to exist or develop on other GE CF6-80E1 model turbofan
engines of the same type design. We are issuing this AD to prevent
blade failure from HPT S2 NGV distress, which could result in an
uncontained engine failure. This AD requires flex borescope inspections
of HPT S2 NGVs installed in GE CF6-80E1 model turbofan engines. These
actions are required at initial and repetitive compliance intervals
that are reduced from the intervals in AD 2002-01-04. You must use the
service information described previously to perform the actions
required by this AD.
FAA's Determination of the Effective Date
Since there are currently no domestic operators of this engine
model, notice and opportunity for public comment before issuing this AD
are unnecessary. Therefore, a situation exists that allows the
immediate adoption of this regulation.
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. 2001-NE-45-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
verbally, 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.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.
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. 2001-NE-45-AD'' in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, 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 removing Amendment 39-12595 (67 FR
4326, January 30, 2002) and by adding a new airworthiness directive,
Amendment 39-13625, to read as follows:
2004-09-34 General Electric Company: Amendment 39-13625. Docket No.
2001-NE-45-AD. Supersedes AD 2002-01-04, Amendment 39-12595.
Effective Date
(a) This airworthiness directive (AD) becomes effective May 26,
2004.
Affected ADs
(b) This AD supersedes AD 2002-01-04.
Applicability
(c) This AD applies to General Electric Company (GE) CF6-80E1
engine models with high pressure turbine (HPT) stage 2 (S2) nozzle
guide vanes (NGVs), part number (P/N) 1647M84G09 or 1647M84G10,
installed. These engines are installed on, but not limited to,
Airbus A330 airplanes.
Unsafe Condition
(d) This AD results from inspection findings of HPT S2 NGVs that
show cracks from distress could occur sooner and propagate faster
than originally predicted. We are issuing this AD to prevent failure
of HPT rotor blades from HPT S2 NGV distress, which could result in
an uncontained engine failure.
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.
NGVs Previously Inspected by Flex Borescope
(f) For NGVs inspected by flex borescope before the effective
date of this AD, reinspect or remove from service the NGVs using the
Conditions and Reinspection intervals listed in the ``Inspection
Table for Cracking in the Airfoil Outer Fillet,'' Figure 5, of GE
Service Bulletin (SB) No. CF6-80E1 S/B 72-0217, Revision 2, dated
January 5, 2004, or within 200 cycles-in-service-since-last
inspection (CSLI), whichever is earlier.
NGVs Not Previously Inspected by Flex Borescope
(g) For NGVs not previously inspected by flex borescope, remove
from service, or inspect using the Accomplishment Instructions of GE
SB No. CF6-80E1 S/B 72-0217, Revision 2, dated January 5, 2004, at
the following:
(1) For NGVs with more than 800 cycles-since-overhaul (CSO) on
the effective date of this AD, within 50 cycles-in-service (CIS)
after the effective date of this AD.
(2) For NGVs with 800 or fewer CSO on the effective date of this
AD, at the first regular HPT blade inspection after 800 CSO, but
before reaching 900 CSO.
(3) Reinspect or remove from service NGVs using the Conditions
and Reinspection intervals listed in the ``Inspection Table for
Cracking in the Airfoil Outer Fillet,'' Figure 5, of GE SB No. CF6-
80E1 S/B 72-0217, Revision 2, dated January 5, 2004.
[[Page 26029]]
Cycles-Since-Overhaul Defined
(h) For the purposes of this AD, cycles-since-overhaul (CSO) is
defined as cycles since repair as described in GE SB No. CF6-80E1 S/
B 72-0164, dated March 16, 1999.
Engines Not Affected by this AD
(i) Engines configured with HPT S2 NGV P/Ns 1647M84G05,
1647M84G06, 2080M47G01, 2080M47G02, 2086M62G03, or 2086M62G04 are
not affected by this AD.
Alternative Methods of Compliance
(j) 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
(k) You must use General Electric Company Service Bulletin No.
CF6-80E1 S/B 72-0217, Revision 2, dated January 5, 2004, to perform
the inspections required by this AD. The Director of the Federal
Register approved the incorporation by reference of this service
bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You
can get a copy from General Electric Company via Lockheed Martin
Technology Services, 10525 Chester Road, Suite C, Cincinnati, Ohio
45215, telephone (513) 672-8400, fax (513) 672-8422. You may review
copies at the Federal Aviation Administration (FAA), New England
Region, Office of the Regional Counsel, 12 New England Executive
Park, Burlington, MA 01803-5299; or at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
Related Information
(l) None.
Issued in Burlington, Massachusetts, on April 29, 2004.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 04-10371 Filed 5-10-04; 8:45 am]
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