AD 2000-03-04

[Federal Register Volume 65, Number 28 (Thursday, February 10, 2000)]
[Rules and Regulations]
[Pages 6533-6534]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-2988]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-ANE-79-AD; Amendment 39-11561; AD 2000-03-04]
RIN 2120-AA64


Airworthiness Directives; General Electric Company CF6-80C2 
Series Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to General Electric Company (GE) CF6-80C2 series turbofan 
engines. This amendment requires removal from service of affected fan 
mid shafts prior to reaching a new, lower cyclic life limit, and 
replacement with serviceable parts. This amendment is prompted by 
recent component test data. The actions specified by this AD are 
intended to prevent fan mid shaft failure, which could result in an 
uncontained engine failure and damage to the aircraft.

EFFECTIVE DATE: April 10, 2000.

ADDRESSES: 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 at the Federal Aviation Administration (FAA), New England 
Region, Office of the Regional Counsel, 12 New England Executive Park, 
Burlington, MA.

FOR FURTHER INFORMATION CONTACT: William S. Ricci, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone 781-
238-7742, fax 781-238-7199.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to General Electric Company (GE) CF6-
80C2 series turbofan engines was published in the Federal Register on 
October 26, 1999 (64 FR 57608). That action proposed to require removal 
from service of affected fan mid shafts prior to reaching a new, lower 
cyclic life limit, and replacement with serviceable parts. That action 
was prompted by recent component test data. That condition, if not 
corrected, could result in fan mid shaft failure, which could result in 
an uncontained engine failure and damage to the aircraft.

Comments Received

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.
    Two commenters concur with the rule as proposed.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.

Economic Analysis

    There are approximately 1,796 engines of the affected design in the 
worldwide fleet. The FAA estimates that 230 engines installed on 
aircraft of US registry will be affected by this AD and that required 
parts will cost approximately $90,085 per engine. Based on these 
figures, the total cost impact of the AD on US operators is estimated 
to be $20,719,600.

Regulatory Impact

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order (EO) 13132.
    For the reasons discussed above, I certify that this action (1) Is 
not a ``significant regulatory action'' under EO 12866; (2) is not a 
``significant rule'' under 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. A final 
evaluation has been prepared for this action and it is contained in the 
Rules Docket. A copy of it may be obtained from 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:

2000-03-04  General Electric Company: Amendment 39-11561. Docket 98-
ANE-79-AD.

    Applicability: General Electric Company (GE) CF6-80C2 series 
turbofan engines, with fan mid shafts, part number (P/N) 9326M74P04 
or P/N 9326M74P05, installed. These engines are installed on but not 
limited to Airbus Industrie A300 and A310 series, Boeing 747 and 767 
series, and McDonnell Douglas MD-11 series aircraft.

    Note 1: This airworthiness directive (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: Required as indicated, unless accomplished 
previously.
    To prevent fan mid shaft failure, which could result in an 
uncontained engine failure and damage to the aircraft, accomplish 
the following:
    (a) Remove from service affected fan mid shafts and replace with 
a serviceable part, as follows:

    Note 2: GE CF6-80C2 Service Bulletin (SB) No. 72-958, dated 
December 10, 1998, contains information on this subject.

    (1) For fan mid shafts that have accumulated 9,000 or more 
cycles-since-new (CSN) on the effective date of this AD, remove from 
service within 3,500 cycles-in-service (CIS) after the effective 
date of this AD, or prior to accumulating 15,000 CSN, whichever 
occurs first.
    (2) For fan mid shafts that have accumulated 1,800 CSN or more, 
but less

[[Page 6534]]

than 9,000 CSN on the effective date of this AD, remove from service 
within 5,000 CIS after the effective date of this AD, or prior to 
accumulating to 12,500 CSN, whichever occurs first.
    (3) For fan mid shafts that have accumulated less than 1,800 CSN 
on the effective date of this AD, remove from service prior to 
accumulating 6,800 CSN.

    Note 3: GE CF6-80C2 SB 72-750, Revision 2, dated September 4, 
1998, contains information on reworking fan mid shafts that results 
in changing the P/N. After that rework, this AD would not apply to 
engines containing the reworked fan mid shaft.

New Life Limits

    (b) Except for the provisions of paragraph (a) of this AD, no 
fan mid shafts, P/N 9326M74P04 or 9326M74P05, may remain in service 
beyond 6,800 CSN.

Alternate Method 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 shall submit their request through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, ECO.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive, 
if any, may be obtained from the ECO.

Ferry Flights

    (d) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the aircraft to a location where 
the requirements of this AD can be accomplished.
    (e) This amendment becomes effective on April 10, 2000.

    Issued in Burlington, Massachusetts, on February 2, 2000.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 00-2988 Filed 2-9-00; 8:45 am]
BILLING CODE 4910-13-U