Airworthiness Directives; General Electric Company CF6-50 Series Turbofan Engines

[Federal Register Volume 68, Number 82 (Tuesday, April 29, 2003)]
[Rules and Regulations]
[Pages 22592-22593]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-10508]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NE-35-AD; Amendment 39-13135; AD 2003-09-06]
RIN 2120-AA64


Airworthiness Directives; General Electric Company CF6-50 Series 
Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), that 
is applicable to General Electric Company (GE) CF6-50 series turbofan 
engines. This amendment requires removal from service of eight serial 
number (SN) low-pressure turbine (LPT) stage 1 disks, part number (P/N) 
9061M21P03, at the next engine shop visit. This amendment is prompted 
by a report of the potential for iron-rich inclusions introduced during 
manufacture in the affected disks. The actions specified by this AD are 
intended to prevent LPT stage 1 disk cracking, due to iron-rich 
inclusions introduced during manufacture, leading to uncontained disk 
failure.

DATES: Effective June 3, 2003.

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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an AD that is 
applicable to General Electric Company (GE) CF6-50 series turbofan 
engines was published in the Federal Register on December 27, 2002 (67 
FR 79007). That action proposed to require removal from service of 
eight SN LPT stage 1 disks, P/N 9061M21P03, at the next engine shop 
visit.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public. The FAA 
has determined that air safety and the public interest require the 
adoption of the rule as proposed.

Economic Analysis

    There are approximately 2,101 CF6-50 series turbofan engines of the 
affected design in the worldwide fleet. The FAA estimates that no more 
than eight of the 469 engines installed on airplanes of U.S. registry 
will be affected by this AD, that it will take approximately 32 work 
hours per engine to perform the required actions, and that the average 
labor rate is $60 per work hour. Required parts will cost approximately 
$75,490 per engine. Based on these figures, the total cost of the AD to 
eight U.S. operators is estimated to be $619,280.

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

[[Page 22593]]

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) 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

0
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

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. Section 39.13 is amended by adding a new airworthiness directive to 
read as follows:

2003-09-06 General Electric Company: Amendment 39-13135. Docket No. 
2002-NE-35-AD.

    Applicability: This airworthiness directive (AD) is applicable 
to General Electric Company CF6-50 series turbofan engines with low 
pressure turbine (LPT) stage 1 disks, part number (P/N) 9061M21P03, 
serial numbers (SNs) SNL17693, SNL17694, SNL44200, SNL47624, 
SNL47625, SNL47626, SNL47627, and SNL47628 installed. These engines 
are installed on, but not limited to Airbus Industrie A300, Boeing 
747, and McDonnell Douglas DC-10 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 LPT stage 1 disk cracking due to the potential for 
iron-rich inclusions introduced during manufacture, leading to 
uncontained disk failure, do the following:
    (a) Remove from service LPT stage 1 disks P/N 9061M21P03, SNs 
SNL17693, SNL17694, SNL44200, SNL47624, SNL47625, SNL47626, 
SNL47627, and SNL47628 at the next engine shop visit.
    (b) After the effective date of this AD, do not install any of 
the LPT stage 1 disks listed in paragraph (a) of this AD into any 
engine.

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 request 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 
Sec. Sec.  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 3, 2003.

    Issued in Burlington, Massachusetts, on April 22, 2003.
Robert E. Guyotte,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 03-10508 Filed 4-28-03; 8:45 am]
BILLING CODE 4910-13-P

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