AD 2002-10-04

[Federal Register Volume 67, Number 95 (Thursday, May 16, 2002)]
[Rules and Regulations]
[Pages 34826-34827]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-12050]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NE-06-AD; Amendment 39-12750; AD 2002-10-04]
RIN 2120-AA64


Airworthiness Directives; General Electric Company CF6-80E1A2 
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 (GE) CF6-80E1A2 turbofan 
engines. This action requires replacing a certain low pressure turbine 
rotor (LPTR) shaft at or before reaching a new reduced life cycle 
limit. This amendment is prompted by an updated low cycle fatigue (LCF) 
analysis of the LPTR shaft. The actions specified in this AD are 
intended to prevent LCF cracking and failure of the LPTR shaft due to 
exceeding the life limit, which could result in an uncontained engine 
failure and damage to the airplane.

DATES: Effective June 20, 2002.
    Comments for inclusion in the Rules Docket must be received on or 
before July 15, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2002-NE-06-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at 
this location, by appointment, between 8 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#39001458575c14585d5a5654545c574d795f5858175e564f"><span class="__cf_email__" data-cfemail="ffc6d29e919ad29e9b9c9092929a918bbf999e9ed1989089">[email&#160;protected]</span></a>''. 
Comments sent via the Internet must contain the docket number in the 
subject line.
    This information may be examined, 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, 
Engine 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: GE has completed an updated low cycle 
fatigue (LCF) analysis for the CF6-80E1A2 LPTR shaft, part number (P/N) 
1778M39P01, and has established a new reduced life cycle limit of 
17,900 cycles-since-new (CSN) for this shaft. In January 2001, the FAA 
became aware of GE's in-process analysis and material testing of LPTR 
shaft, P/N 1778M39P01. The FAA approved temporary revisions (TR's) to 
Chapter 5, Life Limits, of the engine manual, to incorporate revised 
life limits for this shaft based on initial analytical results. The 
original life limit of 20,000 CSN for this part was last published in 
the engine manual revision dated February 15, 2001. TR 05-0019, dated 
March 7, 2001, revised this life limit from 20,000 CSN to 11,300 CSN. 
Subsequent issues of the engine manual, published August 15, 2001 and 
February 15, 2002, carried forward this revised lower life limit. The 
FAA chose to wait for the final analytical results and the updated 
material test data before taking action to mandate a lower life limit. 
This wait was made possible due to the young age of the affected parts. 
The high time shaft has accumulated less than 7,000 CSN at this time, 
which is well below the interim limit of 11,300 CSN and final approved 
life limit. The FAA now approves GE's final analytical results and the 
reduced life limit of 17,900 CSN. GE issued TR 05-0030 on February 28, 
2002 to revise the life limits section of the engine manual for CF6-
80E1A2 LPTR shaft, 
P/N 1778M39P01, to 17,900 CSN. Although interim publications of the 
engine manual showed lower life limits for this part, those limits were 
not mandated by an AD. Therefore, an AD

[[Page 34827]]

is now required to mandate the approved 17,900 CSN life limit.

FAA's Determination of an Unsafe Condition and Required Actions

    Although this affected engine model is not used on any airplanes 
that are registered in the United States, the possibility exists this 
engine model could be used on airplanes that are registered in the 
United States in the future. This AD is being issued to prevent LCF 
cracking and failure of the LPTR shaft due to exceeding the life limit, 
which could result in an uncontained engine failure and damage to the 
airplane. This AD requires replacing CF6-80E1A2 LPTR shafts, 
P/N 1778M39P01, at or before reaching the new reduced life cycle limit 
of 17,900 CSN.

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 2002-NE-06-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, 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:

2002-10-04  General Electric Company: Amendment 39-12750. Docket No. 
2002-NE-06-AD.

Applicability

    This airworthiness directive (AD) is applicable to General 
Electric Company CF6-80E1A2 turbofan engines. These engines are 
installed on, but not limited to, Airbus Industrie A330 series 
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 (c) 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 low cycle fatigue (LCF) cracking and failure of the 
low pressure turbine rotor (LPTR) shaft, due to exceeding the life 
limit, which could result in an uncontained engine failure and 
damage to the airplane, do the following:
    (a) Replace LPTR shafts, part number (P/N) 1778M39P01, at or 
before the shaft accumulates 17,900 cycles-since-new (CSN).
    (b) After the effective date of this AD, do not install any LPTR 
shaft, P/N 1778M39P01, that exceeds 17,900 CSN.

Alternative Methods of Compliance

    (c) 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 ECO.

Special Flight Permits

    (d) 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.

Effective Date

    (e) This amendment becomes effective on June 20, 2002.

    Issued in Burlington, Massachusetts, on May 8, 2002.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 02-12050 Filed 5-15-02; 8:45 am]
BILLING CODE 4910-13-P