AD 00-5009

12085 Federal Register / Vol. 65, No. 46 / Wednesday, March 8, 2000 / Rules and Regulations supports the commenter’s ideas and suggestions is extremely helpful in evaluating the effectiveness of the AD action and determining whether additional rulemaking action would be needed. Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify the 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 that summarizes each FAA-public contact concerned with the substance of this AD 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 99–NE–59–AD.’’ The postcard will be date stamped and returned to the commenter. Regulatory Impact The regulations adopted herein will 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. Therefore, it is determined that this final rule does not have federalism implications under Executive Order 13132. The FAA has determined that this regulation is a nonsignificant regulation that may be issued immediately to correct an unsafe condition in engines, and is not a ‘‘significant regulatory action’’ under Executive Order 12866. It has been determined further that this action involves a nonsignificant regulation under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979). If it is determined that this regulation otherwise would be significant under DOT Regulatory Policies and Procedures, a final regulatory evaluation will be prepared and placed in the Rules Docket. A copy of it, if filed, may be obtained from the Rules Docket at the location provided under the caption ADDRESSES . List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment 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 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. Section 39.13 is amended by adding the following new airworthiness directive: 2000–04–22 Rolls-Royce plc: Amendment 39–11605. Docket 99-NE–59-AD. Applicability: RB211–524G2-T–19; RB211– 524G3-T–19; RB211–524H2-T–19; and RB211 Trent 768–60 and 772–60 turbofan engines installed on, but not limited to Airbus Industrie A330 series and The Boeing Co. 747 series airplanes. Note 1: 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 (b) 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. To prevent failure of the HPC-to-HPT joint bolt assemblies, which could result in a cracked stage 6 HPC disk, possible uncontained engine failure, and damage to the airplane accomplish the following: Replacement of HPC-to-HPT Joint Bolt Assemblies (a) Replace INCO 909 HPC-to-HPT joint bolt assemblies, part number BLT5543, with INCO 718 HPC-to-HPT joint bolt assemblies, P/N BLT5541, before further flight, in accordance with the section 3.A., Accomplishment Instructions, of Rolls-Royce Mandatory service bulletin (SB) RB.211–72– C491, Revision 1, dated October 8, 1999. Alternate Methods of Compliance (b) 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 requests 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 (c) 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. Incorporation by Reference (d) Perform the actions required by this AD in accordance with Rolls-Royce Mandatory SB RB.211–72-C491, Revision 1, dated October 8, 1999. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Rolls-Royce plc, PO Box 31, Derby, England; telephone: International Access Code 011, Country Code 44, 1332– 249428, fax: International Access Code 011, Country Code 44, 1332–249223. Copies may be inspected at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC. (e) This amendment becomes effective on April 7, 2000. Issued in Burlington, Massachusetts, on February 21, 2000. David A. Downey, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 00–4929 Filed 3–7–00; 8:45 am] BILLING CODE 4910–13–U DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 99–NE–34–AD; Amendment 39– 11607; AD 2000–04–24] RIN 2120–AA64 Airworthiness Directives; Honeywell International (formerly AlliedSignal Inc.) 36–300(A), 36–280(B), and 36– 280(D) Series Auxiliary Power Units AGENCY : Federal Aviation Administration, DOT. ACTION : Final rule. SUMMARY : This amendment adopts a new airworthiness directive (AD), applicable to Honeywell International (formerly AlliedSignal Inc.) 36–300(A), 36–280(B), and 36–280(D) series Auxiliary Power Units (APUs). This amendment requires installation of an external load compressor containment shield, or installation of a load compressor impeller with lower stress concentrations. This amendment is prompted by reports of load compressor impeller failures. The actions specified by this AD are intended to prevent an VerDate 07<MAR>2000 21:27 Mar 07, 2000 Jkt 190000 PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 E:\FR\FM\08MRR1.SGM pfrm08 PsN: 08MRR1

12086 Federal Register / Vol. 65, No. 46 / Wednesday, March 8, 2000 / Rules and Regulations uncontained APU failure and damage to the airplane. DATES : Effective May 8, 2000. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of May 8, 2000. ADDRESSES : The service information referenced in this AD may be obtained from Honeywell International, Inc., Attn: Data Distribution, M/S 64–3/2101– 201, PO Box 29003, Phoenix, AZ 85038– 9003; telephone 602–365–2493, fax 602–365–5577. This information may be examined at the Federal Aviation Administration (FAA), New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC. FOR FURTHER INFORMATION CONTACT : Roger Pesuit, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 90712–4137; telephone 562–627–5251, fax 562–627–5210. SUPPLEMENTARY INFORMATION : A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to Honeywell International (formerly AlliedSignal Inc.) 36–300(A), 36–280(B), and 36– 280(D) series Auxiliary Power Units (APUs) was published in the Federal Register on September 8, 1999 (64 FR 48723). That action proposed to require installation of an external load compressor containment shield at the next shop visit, or 6 months after the effective date of this AD, whichever occurs first. An additional compliance option would be installation of a load compressor impeller, part number (P/N) 3822270–5, to extend cyclic service life to 26,000 cycles-since-new (CSN) before mandatory installation of the containment shield. Operators cannot operate with a load compressor installed, P/N 3822270–5, past 26,000 CSN unless they have installed an external containment shield. That action was prompted by three incidents where the load compressor impellers separated, resulting in uncontained APU failures and debris entering the APU compartment. That condition, if not corrected, could result in an uncontained APU failure and damage to the airplane. Comments Received Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the comments received. Expand the Applicability One commenter requests to add load compressor impeller, P/Ns 3822270–1 and 3822270–3, to the applicability in addition to P/Ns 3822270–4 and 3822270–5. Both load compressor impellers, P/Ns 3822270–1 and 3822270–3, are affected by the same damper ring groove condition as the impellers already affected by the proposal. The FAA does not concur. While impellers, P/Ns 3822270–1 and 3822270–3, are subject to the same failure mode as P/N 3822270–4 load compressor impellers affected by this AD, all load compressor impellers, P/Ns 3822270–1 and 3822270–3, were required to be reworked to the P/N 3822270–4 configuration by AD 92–21– 05. The FAA has added a note referring to the requirement of AD 92–21–05 to remind operators that the old load compressor impeller designs shall no longer be used in service. Clarification of Cyclic Determination One commenter requests clarification in how to determine the number of cycles on load compressor impellers in service. The commenter wishes to use its existing system for determining the number of cycles on the load compressor impellers instead of the method described by the manufacturer in its applicable service bulletin (SB). The FAA concurs. Since the AD does not require the use of the SB’s cycle counting methodology, operators may use their own approved system to calculate cycles. A note has been added following paragraph (b) to address acceptable methods of determining part cycles. Subsequent Serial Number (S/N) Parts The same commenter notes that the AlliedSignal Inc. SB does not list all P/ N 3822270–5 impellers in service. The FAA concurs. When the SB was written all subsequent S/N parts that would be produced could not have been anticipated. Since all S/Ns are affected, the applicability paragraph in this final rule has been rewritten to clarify that this AD applies to APUs with P/N 3822270–4 or –5 impellers installed. The applicability paragraph of the AD takes precedence over the AlliedSignal Inc. SB’s list of S/Ns. For parts not listed specifically in the SB, the SB provides a procedure to obtain the required information. Clarification of Compliance Times The same commenter requests clarification on the compliance times for load compressor impellers, P/N 3822270–5. The commenter notes there appears to be contradictory requirements between paragraphs (b) and (c) of the proposal. Paragraph (b) of the proposal allows operating impellers, P/N 3822270–5, above 26,000 CSN, for six months after the effective date of the AD. Paragraph (c) requires that an external containment shield be in place before operating the APU past 26,000 CSN. The FAA concurs. Paragraph (c) of this final rule has been modified to clarify that the calendar time requirement applies along with the cycle time limit. Can an Operator Remove the Containment Shield With a Lower Time Impeller Installed? The same commenter requests clarification on the possibility of removal of the external load compressor containment shield when a lower time impeller is installed. The same commenter also asks why APUs containing P/N 3822270–5 load compressor impellers are not managed to a 26,000 CSN life limit. The commenter states that the proposal does not specifically prohibit removing the external containment shield when P/N 3822270–5 load compressor impellers with less than 26,000 CSN are installed. Operating to a 26,000 CSN limit would be preferred to incorporation of an external load compressor containment shield because it would avoid the potential for APU damage in the event that an impeller does fail. The FAA concurs in part. The commenter may choose, within the requirements of this final rule, to operate with low time P/ N 3822270–5 impellers installed without external load compressor containment shields, or with P/N 3822270–5 impellers with more than 26,000 CSN and external load compressor containment shields installed. Extend Calendar End-Date One commenter requests an extension from six months to two years for the calendar end-date for APUs containing P/N 3822270–5 load compressor impellers. The commenter believes that there is inadequate information available to accurately determine the actual number of cycles on load compressor impellers. The commenter therefore believes that the only practical means of complying with the AD is the calendar method. Extension from six months to two years would allow for orderly scheduling of the installation of the containment shield with scheduled maintenance intervals. The FAA concurs in part. Although detailed load VerDate 07<MAR>2000 21:27 Mar 07, 2000 Jkt 190000 PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 E:\FR\FM\08MRR1.SGM pfrm08 PsN: 08MRR1

12087 Federal Register / Vol. 65, No. 46 / Wednesday, March 8, 2000 / Rules and Regulations compressor impeller cycle times are not known for all APUs, the AlliedSignal SB procedure provides a method for assigning cyclic times which are reasonable based upon review of APU operating history. The FAA has determined that for impellers, P/N 3822270–5, an extension of the calendar end-date from six months to one year would be reasonable to allow incorporation of the containment shield with scheduled maintenance intervals while maintaining an adequate safety level. APU Model Numbers The APUs affected by this AD are sometimes referred to as GTCP36– 300(A), GTCP36–280(B) and GTCP36– 280(D) series APUs. The presence or absence of the letters ‘‘GTCP’’ preceding the model number does not affect the applicability of this AD on those APUs. The FAA has added a note to clarify that the AD applies to the specified APU series whether or not the letters ‘‘GTCP’’ appear on the dataplate. New Company Name Since publication of the proposal, AlliedSignal has adopted the Honeywell International, Inc. name. This final rule has been altered accordingly to refer to the new company name with AlliedSignal Inc. listed as the former company name. Concur With Proposal One commenter concurs with the rule as proposed. Conclusion After careful review of the available data, including the comments noted above, the FAA has determined that air safety and the public interest require the adoption of the rule with the changes described previously. The FAA has determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Economic Analysis There are approximately 1,044 APUs of the affected design in the worldwide fleet. The FAA estimates that 465 APUs installed on airplanes of US registry will be affected by this AD, that it will take approximately 6 work hours per Model 36–300(A) APU (85 units) to accomplish the proposed actions, and 8 work hours per Model 36–280(D) APU (380 units), and that the average labor rate is $60 per work hour. Required parts will cost approximately $3,103 per APU. Fifteen installations on domestic Boeing 737 aircraft (Model 36–280(B)) will require a tube assembly kit, which would cost approximately $1,042. The manufacturer has informed the FAA that it may offset some of these costs thereby lowering the total cost to operators. Based on these figures, the total cost impact of the AD on US operators is estimated to be $1,725,270. Regulatory Impact The regulations adopted herein will 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. Therefore, it is determined that this final rule does not have federalism implications under Executive Order 13132. 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 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 from the Rules Docket at the location provided under the caption ADDRESSES . List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment 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 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. Section 39.13 is amended by adding the following new airworthiness directive: 2000–04–24 Honeywell International (formerly Allied Signal Inc.): Amendment 39–11607. Docket 99–NE–34– AD. Applicability: Honeywell International (formerly AlliedSignal Inc.) 36–300(A), 36– 280(B), and 36–280(D) series Auxiliary Power Units (APUs), with load compressor impellers, part numbers (P/Ns) 3822270–4, or 3822270–5, installed. These APUs are installed on but not limited to Airbus Industrie A319, A320, and A321 series; Boeing 737–300, –400, –500 series; and McDonnell Douglas MD–80 series airplanes. Note 1: This airworthiness directive (AD) applies to each APU 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 APUs 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 (f) 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. Note 2: The presence or absence of the letters ‘‘GTCP’’ preceding the model series does not affect the applicability of this AD to the specified model APUs. Note 3: AD 92–21–05 requires that all APUs with load compressor impellers, P/Ns 3822270–1 or 3822270–3, be reworked to the –4 configuration. Compliance: Required as indicated, unless accomplished previously. To prevent an uncontained APU failure and damage to the airplane, accomplish the following: Load Compressor Impellers, P/N 3822270–4 (a) For APUs with load compressor impellers, P/N 3822270–4, at the next shop visit, or within 6 months after the effective date of this AD, whichever occurs first, accomplish either of the following: (1) Install an external load compressor containment shield in accordance with AlliedSignal Inc. Service Bulletins (SBs) No. GTCP36–49–7471, dated April 20, 1999, GTCP36–49–7472, dated March 31, 1999, or GTCP36–49–7473, dated March 31, 1999, as applicable; or (2) Install load compressor impeller, P/N 3822270–5. Load Compressor Impellers, P/N 3822270–5 (b) For APUs with load compressor impellers, P/N 3822270–5, install an external load compressor containment shield within one year after the effective date of this AD, or prior to the impeller exceeding 26,000 cycles-since-new (CSN), whichever occurs later, in accordance with AlliedSignal Inc. SBs No. GTCP36–49–7471, dated April 20, 1999, GTCP36–49–7472, dated March 31, 1999, or GTCP36–49-7473, dated March 31, 1999, as applicable. Note 4: Operators may use their own FAA- approved tracking system for determining load compressor impeller cyclic count in lieu of the procedure described in the AlliedSignal Inc. SBs referenced in this AD. VerDate 07<MAR>2000 21:27 Mar 07, 2000 Jkt 190000 PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 E:\FR\FM\08MRR1.SGM pfrm08 PsN: 08MRR1

12088 Federal Register / Vol. 65, No. 46 / Wednesday, March 8, 2000 / Rules and Regulations 1 Regional Transmission Organizations, Order No. 2000, 65 FR 809 (January 6, 2000), FERC Stats. & Regs. ¶ 31,089 (2000). Cyclic Limit without External Containment Shield (c) Following one year after the effective date of this AD, operators cannot operate with a load compressor, P/N 3822270–5, installed, past 26,000 cycles unless they have installed an external load compressor containment shield. Definition (d) For the purpose of this AD, a shop visit is defined as when the APU is inducted into a shop for any reason. 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, Los Angeles Aircraft Certification Office. Operators shall submit their request through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles Aircraft Certification Office. Note 5: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Los Angeles Aircraft Certification Office. Ferry Flights (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 airplane to a location where the requirements of this AD can be accomplished. Incorporation by Reference (g) The actions required by this AD shall be done in accordance with the following AlliedSignal Inc. SBs: GTCP36–49–7471, dated April 20, 1999, GTCP36–49–7472, dated March 31, 1999, and GTCP36–49–7473, dated March 31, 1999. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Honeywell International, Inc., Attn: Data Distribution, M/S 64–3/2101–201, PO Box 29003, Phoenix, AZ 85038–9003; telephone 602–365–2493, fax 602–365–5577. Copies may be inspected at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC. (h) This amendment becomes effective on May 8, 2000. Issued in Burlington, Massachusetts, on February 25, 2000. Jay J. Pardee, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 00–5009 Filed 3–7–00; 8:45 am] BILLING CODE 4910–13–U DEPARTMENT OF ENERGY Federal Energy Regulatory Commission 18 CFR Part 35 [Docket No. RM99–2–001; Order No. 2000– A] Regional Transmission Organizations Issued February 25, 2000. AGENCY : Federal Energy Regulatory Commission, DOE. ACTION : Final rule; Order on rehearing. SUMMARY : The Federal Energy Regulatory Commission (Commission) reaffirms its basic determinations in Order No. 2000 and clarifies certain terms. Order No. 2000 requires that each public utility that owns, operates, or controls facilities for the transmission of electric energy in interstate commerce make certain filings with respect to forming and participating in an Regional Transmission Organization (RTO). Order No. 2000 also codifies minimum characteristics and functions that a transmission entity must satisfy in order to be considered an RTO. The Commission’s goal is to promote efficiency in wholesale electricity markets and to ensure that electricity consumers pay the lowest price possible for reliable service. EFFECTIVE DATE : Changes to Order No. 2000 made in this order on rehearing will become effective on April 7, 2000. FOR FURTHER INFORMATION CONTACT : Alan Haymes (Technical Information), Federal Energy Regulatory Commission, 888 First Street, N.E., Washington, D.C. 20426, (202) 219– 2919 Brian R. Gish (Legal Information), Federal Energy Regulatory Commission, 888 First Street, N.E., Washington, D.C. 20426, (202) 208– 0996 James Apperson (Collaborative Process), Federal Energy Regulatory Commission, 888 First Street, N.E., Washington, D.C. 20426, (202) 219– 2962 SUPPLEMENTARY INFORMATION : Table of Contents I. Introduction II. Summary III. Discussion A. Commission’s Approach to RTO Formation 1. Voluntary Approach 2. Legal Authority B. Minimum Characteristics of an RTO 1. Independence a. Definition of Market Participant b. Ownership Issues c. Section 205 Filing Rights 2. Scope and Regional Configuration 3. Short-Term Reliability C. Minimum Functions of an RTO 1. Tariff Administration and Design 2. Congestion Management 3. Ancillary Services 4. OASIS and Total Transmission Capability (TTC) and Available Transmission Capability (ATC) 5. Market Monitoring 6. Planning and Expansion 7. Interregional Coordination D. Open Architecture E. Transmission Ratemaking Policy for RTOs 1. Pancaked Rates 2. Uniform Access Charges 3. Service to Transmission-Owning Utilities That Do Not Participate in an RTO 4. Performance-Based Rate Regulation 5. Other RTO Transmission Ratemaking Reforms a. Levelized Rates b. Return on Equity c. Accelerated Depreciation and Incremental Pricing for New Transmission Investments d. Other Innovative Rate Issues 6. Additional Ratemaking Issues 7. Filing Procedures for Innovative Rate Proposals F. Other Issues 1. Public Power and Cooperative Participation in RTOs 2. Existing Transmission Contracts 3. Lighter Handed Regulation G. Implementation Issues 1. Filing Requirements 2. Deadline for RTO Operation IV. Regulatory Flexibility Act Certification V. Public Reporting Burden and Information Collection Statement VI. Effective Date VII. Document Availability Regulatory Text Appendix I. Introduction On December 20, 1999, the Commission issued a Final Rule (Order No. 2000) to advance the formation of Regional Transmission Organizations (RTOs). 1 Our objective in promulgating Order No. 2000 was to have all transmission-owning entities in the Nation, including non-public utility entities, place their transmission facilities under the control of appropriate RTOs in a timely manner. In Order No. 2000, the Commission concluded that regional institutions could address the operational and reliability issues confronting the industry, and eliminate undue discrimination in transmission services that can occur when the operation of the transmission system remains in the control of a vertically integrated utility. VerDate 07<MAR>2000 21:27 Mar 07, 2000 Jkt 190000 PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 E:\FR\FM\08MRR1.SGM pfrm08 PsN: 08MRR1