Federal Aviation Administration, DOT.
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.
Effective June 3, 2003.Start Further Info
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.End Further Info End Preamble Start Supplemental 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.
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.
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.
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 Start Printed Page 22593the 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.Start List of Subjects
List of Subjects in 14 CFR Part 39End List of Subjects
Adoption of the AmendmentStart Amendment Part
Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (End Amendment Part Start Part
PART 39—AIRWORTHINESS DIRECTIVESEnd Part Start Amendment Part
1. The authority citation for part 39 continues to read as follows:End Amendment Part
2. Section 39.13 is amended by adding a new airworthiness directive to read as follows:End Amendment Part
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.
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.
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 §§ 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.
(e) This amendment becomes effective on June 3, 2003.Start Signature
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