Federal Aviation Administration (FAA), DOT.
Notice of proposed rulemaking (NPRM).
The FAA proposes to adopt a new airworthiness directive (AD) for General Electric Company (GE) CT58-140-1, CT58-140-2, and T58-GE-5, -10, -100, and -402 series turboshaft engines with certain serial numbers (SNs) of stage 1 compressor disks, part number (P/N) 5001T20P01, installed. This proposed AD would require removing certain stage 1 compressor disks from service before reaching a reduced low-cycle-fatigue (LCF) life limit. This proposed AD results from two reports of low blade tip clearances in the compressor. We are proposing this AD to prevent LCF cracking and failure of the stage 1 compressor disk, an uncontained engine failure, and damage to the helicopter.
We must receive any comments on this proposed AD by April 26, 2004.
Use one of the following addresses to submit comments on this proposed AD:
- By mail: Federal Aviation Administration (FAA), New England Region, Office of the Regional Counsel, Attention: Rules Docket No. 2003-NE-59-AD, 12 New England Executive Park, Burlington, MA 01803-5299.
- By fax: (781) 238-7055.
- By e-mail: email@example.com
You can get the service information identified in this proposed AD from GE Aircraft Engines Customer Support Center, M/D 285, 1 Neumann Way, Evendale, OH 45215, telephone (513) 552-3272; fax (513) 552-3329, email GEAE.firstname.lastname@example.org.
You may examine the AD docket, by appointment, at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA.Start Further Info
FOR FURTHER INFORMATION CONTACT:
Norman Brown, Senior Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park; telephone (781) 238-7181; fax (781) 238-7199.End Further Info End Preamble Start Supplemental Information
We invite you to submit any written relevant data, views, or arguments regarding this proposal. Send your comments to an address listed under ADDRESSES. Include “AD Docket No. 2003-NE-59-AD” in the subject line of your comments. If you want us to acknowledge receipt of your mailed comments, send us a self-addressed, stamped postcard with the docket number written on it; we will date-stamp your postcard and mail it back to you. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. If a person contacts us verbally, and that contact relates to a substantive part of this proposed AD, we will summarize the contact and place the summary in the docket. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments.
We are reviewing the writing style we currently use in regulatory documents. We are interested in your comments on whether the style of this document is clear, and your suggestions to improve the clarity of our communications that affect you. You can get more information about plain language at http://www.faa.gov/language and http://www.plainlanguage.gov.
Examining the AD Docket
You may examine the AD Docket (including any comments and service information), by appointment, between 8 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. See ADDRESSES for the location.
On May 1, 2003, GE informed the FAA that 320 stage 1 compressor disks, P/N 5001T20P01, have high-peak stresses. GE has identified the affected stage 1 compressor disks by SN. An investigation by GE revealed that the tangential positioning of the blade dovetail slot resulted in the high-peak stresses. This proposed AD would require removing those stage 1 compressor disks, PN 5001T20P01, from service before reaching a reduced LCF life limit of 2,100 hours time-since-new (TSN) or by December 31, 2008, whichever occurs first. This condition, if not corrected, could result in LCF cracking and failure of the stage 1 compressor disk, an uncontained engine failure, and damage to the helicopter.
Relevant Service Information
We have reviewed and approved the technical contents of GE Alert Service Bulletin (ASB) No. CT58 S/B 72-A0196, dated July 24, 2003, that describes the procedures for replacing the stage 1 compressor disk.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other products of this same type design. Therefore, we are proposing this AD which would require removing certain stage 1 compressor disks from service at or before reaching a reduced LCF life limit of 2,100 hours TSN or by December 31, 2008, whichever occurs first.
Changes to 14 CFR Part 39—Effect on the Proposed AD
On July 10, 2002, we issued a new version of 14 CFR part 39 (67 FR 47998, July 22, 2002), which governs the FAA's AD system. This regulation now includes material that relates to altered products, special flight permits, and alternative methods of compliance. This material previously was included in each individual AD. Since this material is included in 14 CFR part 39, we will not include it in future AD actions.
These actions are interim actions and we may take further rulemaking actions in the future.
Costs of Compliance
There are about 320 GE CT58-140-1, CT58-140-2, and T58-GE-5, -10, -100, and -402 series turboshaft engines of Start Printed Page 8876the affected design in the worldwide fleet. We estimate that 45 engines installed on helicopters of U.S. registry would be affected by this proposed AD. The proposed action does not impose any additional labor costs. A new disk would cost about $7,965 per engine. We estimate that the prorated cost of the life reduction would be about $4,181 per engine. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $188,172.
We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD 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.
For the reasons discussed above, I certify that the proposed regulation:
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. Would not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this proposal and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES. Include “AD Docket No. 2003-NE-59-AD” in your request.Start List of Subjects
List of Subjects in 14 CFR Part 39End List of Subjects
The Proposed Amendment
Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 14 CFR part 39 as follows:Start Part
PART 39—AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
2. The FAA amends § 39.13 by adding the following new airworthiness directive:
General Electric Company: Docket No. 2003-NE-59-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by April 26, 2004.
(c) This AD applies to General Electric Company (GE) CT58-140-1, CT58-140-2, and T58-GE-5, -10, -100, and -402 series turboshaft engines with stage 1 compressor disks, part number (P/N) 5001T20P01, that have a serial number (SN) listed in the following Table 1:
|Start Printed Page 8877|
These engines are installed on, but not limited to Agusta S.p.A AS-61N, AS-61N1, Sikorsky S-61L, S-61N, S-61R, and S-61NM helicopters, and the following surplus military helicopters that have been certified in accordance with sections 21.25 or 21.27 of the Federal Aviation Regulations (14 CFR 21.25 or 21.27): Sikorsky S-61D and S-61V, Glacier CH-3E, Siller CH-3E and SH-3A, and Robinson Crane CH-3C, CH-3E, HH-3C, HH-3E, and Carson S-61L helicopters.
(d) This AD results from two reports of low blade tip clearances in the compressor. We are issuing this AD to prevent low-cycle-fatigue (LCF) cracking and failure of the stage 1 compressor disk, an uncontained engine failure, and damage to the helicopter. Start Printed Page 8878
(e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done.
Replacement of Stage 1 Compressor Disks
(f) If you have a stage 1 compressor disk, P/N 5001T20P01, with a SN listed in Table 1 of this AD, replace that stage 1 compressor disk at or before reaching a reduced LCF life limit of 2,100 hours time-since-new (TSN) or by December 31, 2008, whichever occurs first. GE Alert Service Bulletin (ASB) No. CT58 S/B 72-A0196, dated July 24, 2003, contains information on replacing the stage 1 compressor disk.
(g) After the effective date of this AD, do not install any stage 1 compressor disk, P/N 5001T20P01, that has a SN listed in Table 1 of this AD and has 2,100 hours TSN or more, into any engine.
Alternative Methods of Compliance
(h) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19.
Material Incorporated by Reference
(j) GE Alert Service Bulletin (ASB) No. CT58 S/B 72-A0196, dated July 24, 2003, pertains to the subject of this AD.
Issued in Burlington, Massachusetts, on February 17, 2004.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service.
[FR Doc. 04-4101 Filed 2-25-04; 8:45 am]
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