Federal Aviation Administration, DOT.
Notice of proposed rulemaking (NPRM).
This document proposes the adoption of a new airworthiness directive (AD) that is applicable to Pratt & Whitney Canada (P&WC) PT6A-25C and -114A turboprop engines. This proposal would require initial and repetitive visual inspections, and eventual replacement of the compressor bleed valve assembly, with a redesigned valve assembly for the -114A engines, and initial and repetitive visual inspections only for -25C engines. This proposal is prompted by reports of two occurrences of uncommanded engine power loss. The actions specified by the proposed AD are intended to detect wear in the compressor bleed valve assembly which may cause valve orifice blockage, resulting in a loss of power, inability of engine acceleration, and in-flight shut down.
Comments must be received by November 20, 2000.
Submit comments to the Federal Aviation Administration (FAA), New England Region, Office of the Regional Counsel, Attention: Rules Docket No. 2000-NE-26-AD, 12 New England Executive Park, Burlington, MA 01803-5299. Comments may also be sent via the Internet using the following address: “firstname.lastname@example.org”. Comments sent via the Internet must contain the docket number in the subject line. Comments may be inspected at this location between 8:00 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays.
The service information referenced in the proposed rule may be obtained from Pratt & Whitney Canada, 1000 Marie-Victorin, Longueuil, Quebec, Canada J4G1A1. This information may be examined 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:
James Rosa, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; telephone: (781) 238-7152, fax: (781) 238-7199.End Further Info End Preamble Start Supplemental Information
This proposal would require initial and repetitive visual inspections, and replacement if necessary, of certain compressor bleed valve assembly components on PT6A-25C and -114A turboprop engines, in accordance with P&WC Service Bulletin (SB) No. 1574 Revision 2, dated October 14, 1999. This proposal would also require eventual replacement of compressor bleed valve assemblies with redesigned valve assemblies, on PT6A-114A turboprop engines, in accordance with P&WC SB No. 1588, dated February 18, 2000.
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 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 notice 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 notice must submit a self-addressed, stamped postcard on which the following statement is made: “Comments to Docket Number 2000-NE-26-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. 2000-NE-26-AD, 12 New England Executive Park, Burlington, MA 01803-5299.
Transport Canada (TC), which is the airworthiness authority for Canada, recently notified the FAA that an unsafe condition may exist on P&WC PT6A-25C and -114A series turboprop engines, which are installed on but not limited to Pilatus PC-7 and Cessna 208 Caravan airplanes. TC advises that engines, which have incorporated P&WC SB No. 1510, may experience cotter pin and diaphragm wear and fatigue inside the compressor bleed valve assembly. Separation of sections of the cotter pin and particles from diaphragm wear may cause blockage of one or both valve orifices, resulting in a power loss, inability of the engine to accelerate and/or in-flight shut down. P&WC has issued SB No. 1574, Revision 2, dated October 14, 1999, which specifies initial visual inspection of compressor bleed valve assembly cover, guide pin shaft, cotter pin, and diaphragm for wear, and, replacement of these parts if necessary. TC classified this SB as mandatory by issuing AD No. CF-99-23, dated September 14, 1999 in order to assure the continued airworthiness of these airplanes in Canada. P&WC has also issued SB No. 1588, dated February 18, 2000, for PT6A-114A turboprop engines that specify compressor bleed valve assembly replacement with a redesigned valve assembly. Start Printed Page 56820
Bilateral Airworthiness Agreement
These engine models are manufactured in Canada and are type certificated for operation in the United States under the provisions of § 21.29 of Title 14 of the Code of Federal Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, Transport Canada has kept the FAA informed of the situation described above. The FAA has examined the findings of Transport Canada, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States.
Since an unsafe condition has been identified that is likely to exist or develop on other engines of the same type design registered in the United States, the proposed AD would require initial visual inspection of certain compressor bleed valve assembly components within 150 flight hours after the effective date of this AD, repetitive visual inspections within 600 flight hours after the last inspection, and if necessary, the replacement of certain components. The proposed AD would also require replacement of compressor bleed valve assemblies on PT6A-114A engines which have had Pratt & Whitney Canada SB No. 1510 incorporated, with a redesigned valve assembly at the next shop visit but no later than five years after the effective date of this AD. The actions would be required to be accomplished in accordance with the SB's described previously.
There are about 504 engines of the affected design in the worldwide fleet. The FAA estimates that 353 engines installed on aircraft of U.S. registry would be affected by this proposed AD, that it would take about 2 work hours per engine to accomplish the initial inspections, and 1 hour to accomplish the replacement of the valve, and that the average labor rate is $60 per work hour. Required parts would cost about $7,458.00 per engine. Based on these figures, the total cost impact of the proposed AD on U.S. operators is estimated to be $2,696,214.00.
This proposal 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 proposal.
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 39
- Air transportation
- Aviation safety
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:
Pratt & Whitney Canada: Docket No. 2000-NE-26-AD.
Applicability: This airworthiness directive (AD) applies to PT6A-25C and -114A Series turboprop engines, installed on but not limited to the following airplanes: Pilatus PC-7, Cessna 208 Caravan.
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 (e) 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.
Initial and Repetitive Inspections
To detect wear on the compressor bleed valve assembly cover, guide pin shaft, cotter pin, and to detect particles from diaphragm wear, which may cause blockage of one or both valve orifices, resulting in a loss of power, inability of the engine to accelerate, and/or in-flight shut down, accomplish the following:
(a) Perform an initial visual inspection of the compressor bleed valve assembly components within 150 flight hours after the effective date of this AD in accordance with Accomplishment Instructions, Section 3A through 3B of Pratt & Whitney Canada (P&WC) Service Bulletin (SB) No. 1574 Revision 2, dated October 14, 1999.
(b) Thereafter, perform repetitive visual inspections of the compressor bleed valve assembly components within 600 flight hours after the last inspection in accordance with Accomplishment Instructions, Section 3A through 3B of Pratt & Whitney Canada (P&WC) Service Bulletin (SB) No. 1574 Revision 2, dated October 14, 1999.
(c) For PT6A-114A series turboprop engines, replacement of compressor bleed valve assemblies at the next shop visit, with the redesigned valve assembly, in accordance with P&WC SB No. 1588, dated February 18, 2000, is considered terminating action for the repetitive inspection. This action must be done at the next shop visit but no later than five years from the effective date of this AD.
(d) For the purpose of this AD: A shop visit is defined as when the subassembly (i.e. module, accessories, components or build groups) is disassembled and access is available to the compressor bleed valve assembly.
Alternative Methods of Compliance
(e) 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.
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
(f) 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.
Issued in Burlington, Massachusetts, on September 13, 2000.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service.
[FR Doc. 00-24114 Filed 9-19-00; 8:45 am]
BILLING CODE 4910-13-P