Federal Aviation Administration, DOT.
Notice of proposed rulemaking (NPRM).
The Federal Aviation Administration (FAA) proposes to adopt a new airworthiness directive (AD) that is applicable to Honeywell International Inc. (formerly AlliedSignal Inc., Garrett Turbine Engine Company and AiResearch Manufacturing Company of Arizona) TPE331-3, −5, −6, −8, −10, and −11 series turboprop and TSE331-3 series turboshaft engines. This proposal would require removing weld repaired first stage compressor impellers from service. This proposal is prompted by an uncontained TPE331-11U turboprop engine failure and an in-flight shutdown due to the separation of the first stage Ti 6-4 compressor impeller. The actions specified by the proposed AD are intended to prevent uncontained Start Printed Page 48578engine failures, in-flight shutdowns, and secondary damage.
Comments must be received by September 23, 2002.
Submit comments in triplicate to the Federal Aviation Administration (FAA), New England Region, Office of the Regional Counsel, Attention: Rules Docket No. 2001-NE-11-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: “email@example.com”. Comments sent via the Internet must contain the docket number in the subject line. The service information referenced in the proposed rule may be obtained from Honeywell Engines, Systems and Services, Technical Data Distribution, M/S 2101-201, PO Box 52170, Phoenix, AZ 85072-2170; telephone: (602) 365-2493 (General Aviation), (602) 365-5535 (Commercial); fax: (602) 365-5577 (General Aviation and Commercial). 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.Start Further Info
FOR FURTHER INFORMATION CONTACT:
Joseph Costa, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood CA 90712-4137; telephone: (562) 627-5246; fax (562) 627-5210.End Further Info End Preamble Start Supplemental Information
Interested persons are invited to participate in the making of the proposed 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 above. All communications received on or before the closing date for comments, specified above, will be considered before taking action on the proposed rule. The proposals contained in this action may be changed in light of the comments received.
Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with the substance of this proposal 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 2001-NE-11-AD.” The postcard will be date stamped and returned to the commenter.
Availability of NPRM's
Any person may obtain a copy of this NPRM by submitting a request to the FAA, New England Region, Office of the Regional Counsel, Attention: Rules Docket No. 2001-NE-11-AD, 12 New England Executive Park, Burlington, MA 01803-5299.
On November 16, 1994, a TPE331-11U turboprop uncontained engine failure and in-flight shutdown occurred due to the separation of the first stage Ti 6-4 compressor impeller. The failed impeller, part number (P/N) 896223-3, which was weld repaired at 3,983 cycles-since-new (CSN), had accumulated 27,456 CSN. The crack initiated in the backface at the fillet adjacent to the curvic arm and propagated forward along the bore in low cycle fatigue (LCF). Compressor impellers, P/N's 896223-1, −2, −3 and −7 and 3107109-2, are similarly designed to P/N 896223-3, and are affected by this proposal. The FAA has determined that weld repairs and the associated heat treatment on these impellers reduce LCF mechanical properties and may contribute to impeller failures. Failure of the first stage compressor impeller, if not corrected, could result in an uncontained separation of the impeller, in-flight shutdown and secondary engine and aircraft damage.
Manufacturer's Service Information
The FAA has reviewed and approved the technical contents of Honeywell International Inc. Alert Service Bulletin (ASB) TPE331-A72-2083, Revision 1, dated May 17, 2002, which provides a listing of certain impellers by serial number which have been weld repaired and provides impeller replacement information.
FAA's Determination of an Unsafe Condition and Proposed Actions
Since an unsafe condition has been identified that is likely to exist or develop on other Honeywell International Inc TPE331-3, −5, −6, −8, −10, and −11 series turboprop and TSE331-3 series turboshaft engines of the same type design, the proposed AD would require the replacement of suspect impellers with serviceable impellers. The actions would be required to be done in accordance with the ASB described previously.
There are approximately 2,040 engines of the affected design in the worldwide fleet. The FAA estimates that 1,020 engines installed on aircraft of U.S. registry would be affected by this proposed AD. The FAA estimates that 1,000 engines will have the required actions done during a scheduled engine overhaul. The FAA also estimates that it would take approximately 2 work hours per engine to do the proposed actions during scheduled engine overhauls and 80 work hours per engine during unscheduled engine overhauls, and that the average labor rate is $60 per work hour. Required parts would cost approximately $9,600 per engine to do the proposed actions during scheduled engine overhauls and $14,600 per engine which includes consumables, during unscheduled engine overhauls. Based on these figures, the total cost of the proposed AD on U.S. operators is estimated to be $10,108,000.
This proposed 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 proposed rule.
For the reasons discussed above, I certify that this 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) 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 copy of the draft regulatory evaluation prepared for this action 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 Start Printed Page 48579
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new airworthiness directive:
Honeywell International Inc.: Docket No. 2001-NE-11-AD.
This airworthiness directive (AD) is applicable to Honeywell International Inc. (formerly AlliedSignal Inc., Garrett Turbine Engine Company and AiResearch Manufacturing Company of Arizona) TPE331-3, −5, −6, −8, −10, and −11 series turboprop and TSE331-3 series turboshaft engines equipped with first stage compressor impeller, part number (P/N) 896223-1, −2, −3, −7, or 3107109-2. These engines are installed on, but not limited to: Ayres S-2R series; Beech 18 and 45 series and Models JRB-6, 3N, 3NM, 3TM, and B100; Cessna Model 441; Construcciones Aeronauticas, S.A. (CASA) C-212 series; De Havilland DH 104 series 7AXC (Dove); Dornier 228 series; Fairchild SA226 and SA227 series (Swearingen Merlin and Metro series); Grumman American G-164 series; Jetstream 3101; Mitsubishi MU-2B series (MU-2 series); Prop-Jets, Inc. Model 400; Rockwell Commander S-2R; Shorts Brothers and Harland, Ltd. SC7 (Skyvan); Pilatus PC-6 series (Fairchild Porter and Peacemaker); and Schweizer G-164 series; and Twin Commander Aircraft Corp. (Jetprop Commander) Models 695 and 695A airplanes; and Sikorsky S-55 series (Helitec Corp. S55T) helicopters.
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 with this AD is required as indicated, unless already done.
To prevent a uncontained engine failure, in-flight shutdown, and secondary damage, do the following:
Removal of Weld Repaired First Stage Compressor Impellers From Service
(a) Remove from service weld repaired first stage compressor impellers, P/N's 896223-1, −2, −3, and −7 and 3107109-2, with SN's listed in Table 1 and Table 2 of the Accomplishment Instructions in 2.A.(1) and 2.A.(2) of Honeywell Alert Service Bulletin TPE331-A72-2083, Revision 1, dated May 17, 2002, in accordance with the following schedule:
(1) Remove impellers with no record of cycles since weld repair, within 3,600 cycles-in-service (CIS) or at the next engine overhaul, or at the next major Continuous Airworthiness Maintenance (CAM) compressor section inspection, after the effective date of this AD, whichever occurs first.
(2) Remove impellers with more than 8,900 cycles since “weld repair,” within 3,600 CIS, or at the next engine overhaul, or at the next major CAM compressor section inspection after the effective date of this AD, whichever occurs first.
(3) Remove impellers with 8,900 or less cycles since “weld repair,” before reaching 12,500 cycles since weld repair after the effective date of this AD.
(b) For purposes of this AD, weld repaired or weld repair is defined as an impeller repair which involved heat treating and that was performed from 1980 through 1997 at Honeywell Aerospace Services, Aftermarket-Phoenix Repair and Overhaul, 1944 E. Sky Harbor Circle, Phoenix, AZ 85034 (FAA Certificate Number ZN3R030M). Former names and FAA certificate numbers for Honeywell's Repair and Overhaul Facility are listed in Section 2.A. of the Accomplishment Instructions in Honeywell Alert Service Bulletin TPE331-A72-2083, Revision 1, dated May 17, 2002.
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, Los Angeles Aircraft Certification Office (ACO). Operators must submit their request through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles ACO.
Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from, Los Angeles ACO.
(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 aircraft to a location where the requirements of this AD can be done.
Issued in Burlington, Massachusetts, on July 18, 2002.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification Service.
[FR Doc. 02-18816 Filed 7-24-02; 8:45 am]
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