AD 2002-01-04

[Federal Register Volume 67, Number 20 (Wednesday, January 30, 2002)]
[Rules and Regulations]
[Pages 4326-4328]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-1692]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-45-AD; Amendment 39-12595; AD 2002-01-04]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to General Electric Company CF6-80E1 model turbofan 
engines. This action requires flex borescope inspections of high 
pressure turbine (HPT) stage two (S2) nozzle guide vanes (NGV) 
installed in CF6-80E1 model turbofan engines. This amendment is 
prompted by an uncontained engine failure attributed to HPT S2 NGV 
distress. The actions specified in this AD are intended to prevent 
blade failure from HPT S2 NGV distress, which could result in an 
uncontained engine failure.

DATES: Effective February 14, 2002. The incorporation by reference of 
certain publications listed in the rule is approved by the Director of 
the Federal Register as of February 14, 2002.
    Comments for inclusion in the Rules Docket must be received on or 
before April 1, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation

[[Page 4327]]

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. Comments may be inspected at 
this location, by appointment, between 8:00 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. Comments may also be sent via 
the Internet using the following address: ``<a href="/cdn-cgi/l/email-protection#9da4b0fcf3f8b0fcf9fef2f0f0f8f3e9ddfbfcfcb3faf2eb"><span class="__cf_email__" data-cfemail="546d79353a31793530373b3939313a20143235357a333b22">[email&#160;protected]</span></a>''. 
Comments sent via the Internet must contain the docket number in the 
subject line.
    The service information referenced in this AD may be obtained 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. This information may be examined, by 
appointment, at the Federal Aviation Administration (FAA), New England 
Region, Office of the Regional Counsel, 12 New England Executive Park, 
Burlington, MA; or at the Office of the Federal Register, 800 North 
Capitol Street, NW., suite 700, Washington, DC.

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 July 25, 2001, an uncontained engine 
failure (engine case only) and in flight shutdown (IFSD) occurred on a 
CF6-80E1 engine installed in an Airbus A330 airplane. There was no 
nacelle penetration or aircraft damage as a result of this event. 
However, similar events have occurred on other CF6 engine models with 
similar design HPT S2 NGV's that have resulted in nacelle penetration 
and minor airplane damage. HPT NGV's modified per GE Aircraft Engines 
(GE) Service Bulletin (SB) 72-0164, part numbers (P/N's) 1647M84G09/
G10, are more susceptible to airfoil outer fillet cracking. This 
cracking can propagate to a condition where the nozzle segment sags 
backward and contacts the HPT Stage 2 blade row. This contact can 
progress to notching of the blade airfoil at the root and lead to blade 
failure. The actions specified in this AD are intended to prevent blade 
failure from HPT S2 NGV distress, which could result in an uncontained 
engine failure.

Manufacturer's Service Information

    The FAA has reviewed and approved the technical contents of GE SB 
CF6-80E1 S/B 72-0217, dated October 25, 2001, and S/B 72-0217, Revision 
1, dated January 14, 2002 that describe procedures for initial and 
repetitive flex borescope inspection of HPT S2 NGV P/N's 1647M84G09/
G10.

FAA's Determination of an Unsafe Condition and Required Actions

    Although none of these affected engine models are used on any 
airplanes that are registered in the United States, the possibility 
exists that the engine models could be used on airplanes that are 
registered in the United States in the future. This AD is being issued 
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 NGV's installed in CF6-80E1 model turbofan 
engines. The actions are required to be done in accordance with the 
service bulletin described previously.

Immediate Adoption of This AD

    Since there are currently no domestic operators of this engine 
model, notice and opportunity for prior public comment are unnecessary. 
Therefore, a situation exists that allows the immediate adoption of 
this regulation.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications should identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NE-45-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Analysis

    This final rule does not have federalism implications, as defined 
in Executive Order 13132, because it 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. Accordingly, 
the FAA has not consulted with state authorities prior to publication 
of this final rule.
    For the reasons discussed above, I certify that this action (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) if promulgated, 
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. A final evaluation has been prepared for 
this action and it is contained in the Rules Docket. A copy of it may 
be obtained by contacting the Rules Docket at the location provided 
under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to 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

    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. Section 39.13 is amended by adding the following new 
airworthiness directive:


[[Page 4328]]


2002-01-04  General Electric Company: Amendment 39-12595. Docket No. 
2001-NE-45-AD.

Applicability

    This airworthiness directive (AD) is applicable to General 
Electric Company CF6-80E1 engine models with high pressure turbine 
(HPT) stage 2 (S2) nozzle guide vane (NGV) part numbers (P/N's) 
1647M84G09 or 1647M84G10. These engines are installed on, but not 
limited to, Airbus A330 airplanes.

    Note 1: This AD applies to each engine identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For engines that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (f) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

Compliance

    Compliance with this AD is required as indicated, unless already 
done. To prevent blade failure from HPT S2 NGV distress, which could 
result in an uncontained engine failure, do the following.

Previously Flex Borescope Inspected NGV's

    (a) For NGV P/N's 1647M84G09 or 1647M84G10 that have been flex 
borescope inspected before the effective date of this AD, re-
reinspect the NGV's in accordance with Conditions and Re-inspection 
intervals listed in the ``Inspection Table for Cracking in the 
Airfoil Outer Fillet,'' Figure 5, of GE Aircraft Engines (GE) 
Service Bulletin (SB) CF6-80E1 S/B 72-0217, dated October 25, 2001 
or S/B 72-0217, Revision 1, dated January 14, 2002, or within 250 
cycles-in-service-since-last inspection (CSLI), whichever is 
earlier.

NGV's Not Previously Inspected

    (b) For NGV's P/N's 1647M84G09 or 1647M84G10 not previously flex 
borescope inspected, inspect in accordance with the Accomplishment 
Instructions of GE SB CF6-80E1 S/B 72-0217, Revision 1, dated 
January 14, 2002, as follows:
    (1) For NGV's with 1,200 or more cycles-since-overhaul (CSO) on 
the effective date of this AD, flex borescope inspect within 50 
cycles-in-service (CIS) after the effective date of this AD.
    (2) For NGV's with 1,200 or fewer CSO on the effective date of 
this AD, flex borescope inspect at the first regular HPT blade 
inspection after 1,200 CSO, but before reaching 1,250 CSO.

Reinspection

    (c) Re-inspect or remove from service NGV's in accordance with 
the Conditions and Re-inspection intervals listed in the 
``Inspection Table for Cracking in the Airfoil Outer Fillet,'' 
Figure 5, of GE SB CF6-80E1 S/B 72-0217, Revision 1, dated January 
14, 2002.

Cycles-Since-Overhaul Defined

    (d) For the purposes of this proposed AD, cycles-since-overhaul 
(CSO) is defined as cycles since repair as described in GE SB CF6-
80E1 S/B 72-0164, dated March 16, 1999.

Engines Not Affected by this AD

    (e) Engines configured with HPT S2 NGV P/N's 1647M84G05 or 
1647M84G06, or 2080M47G01 or 2080M47G02 are not affected by this AD.

Alternative Methods of Compliance

    (f) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Engine Certification Office (ECO). 
Operators must submit their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, ECO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive, 
if any, may be obtained from the Boston ECO.

Special Flight Permits

    (g) Special flight permits may be issued in accordance with 
Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 
21.197 and 21.199) to operate the airplane to a location where the 
requirements of this AD can be done.

Documents That Have Been Incorporated by Reference

    (h) The inspection must be done in accordance with GE Aircraft 
Engines Service Bulletin CF6-80E1 S/B 72-0217, dated October 25, 
2001 or S/B 72-0217, Revision 1, dated January 14, 2002. This 
incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained 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. Copies may be inspected, by appointment, at the FAA, New 
England Region, Office of the Regional Counsel, 12 New England 
Executive Park, Burlington, MA; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Effective Date

    (i) This amendment becomes effective on February 14, 2002.

    Issued in Burlington, Massachusetts, on January 15, 2002.
Thomas A. Boudreau,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 02-1692 Filed 1-29-02; 8:45 am]
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