Airworthiness Directives; General Electric Company CF6-80E1 Model Turbofan Engines

[Federal Register Volume 69, Number 91 (Tuesday, May 11, 2004)]
[Rules and Regulations]
[Pages 26027-26029]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-10371]


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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:
    <bullet> 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.
    <bullet> By fax: (781) 238-7055.
    <bullet> By e-mail: [email protected].
    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]
BILLING CODE 4910-13-P

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