Airworthiness Directives; General Electric Company CT64-820-4 Turboprop Engines, 20001-20005 [06-3724]

Download as PDF Federal Register / Vol. 71, No. 75 / Wednesday, April 19, 2006 / Rules and Regulations Note 1: The FAA recommends that you return all replaced backrest tubes to Pilatus Aircraft Ltd., Structural Analysis Group ECE, Ch–6371 Stans, Switzerland. Include the following information: crew seat P/N and serial number, aircraft manufacturer serial number, aircraft flying hours, number of flights, and replacement date of the replaced backrest tubes. Note 2: Pilatus PC–12 Aircraft Maintenance Manual Revision 17/Interactive Electronic Technical Publication (IETP) Revision 9, Chapter 4, section 04–00–00, references the crew seat bucket assembly replacements. Alternative Methods of Compliance (AMOCs) (f) The Manager, Standards Office, Small Airplane Directorate, FAA, ATTN: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4059; fax: (816) 329–4090, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information (g) Swiss AD Number HB–2005–470, Effective Date: December 30, 2005, also addresses the subject of this AD. Issued in Kansas City, Missouri, on April 12, 2006. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–3725 Filed 4–18–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–23705; Directorate Identifier 2005–NE–45–AD; Amendment 39– 14567; AD 2006–08–10] RIN 2120–AA64 Airworthiness Directives; General Electric Company CT64–820–4 Turboprop Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. rmajette on PROD1PC67 with RULES1 AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CT64–820–4 turboprop engines with certain part number (P/N) rotating parts. The parts are in the compressor rotor assembly, gas generator turbine rotor assembly, and power turbine rotor assembly that are subject to low-cycle fatigue. This AD requires removing from service these affected rotating parts at reduced VerDate Aug<31>2005 15:12 Apr 18, 2006 Jkt 208001 compliance times. This AD results from the manufacturer’s discovery of cracks in some rotating parts. We are issuing this AD to prevent cracks in the rotating parts that could cause compressor and turbine wheel fracture and uncontained engine failure. An uncontained engine failure could cause possible damage to the airplane. DATES: This AD becomes effective May 24, 2006. ADDRESSES: Use one of the following addresses to comment on this AD: • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 0001. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact GE Aircraft Engines Customer Support Center, M/D 285, 1 Neumann Way, Evendale, OH 45215, telephone (513) 552–3272; fax (513) 552–3329; email address: GEAE.csc@ae.ge.com, for the service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Anthony W. Cerra Jr., Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone 781– 238–7128; fax 781–238–7199; e-mail address: anthony.cerra@faa.gov. SUPPLEMENTARY INFORMATION: GE has informed us that cracks have been found in certain P/N rotating parts. The manufacturer reported that cracks were found in the outer rim of a stage 1 aft cooling plate, P/N 4022T37P01, installed on the gas generator turbine (GGT) rotor of a military T64 engine. They also found cracks in the sawcut slots of the GGT rear air seals of stage 2 aft cooling plates, P/N 4022T36P01, in the CT64–820–4 engine model and a similar military T64 engine model. There have been at least 13 reports of cracked GGT rear air seals. Investigation by the manufacturer showed that compressor rotor assemblies, GGT rotor assemblies, and power turbine rotor assemblies have small feature locations. A ‘‘small feature’’ location is any rotating PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 20001 hardware feature with drawing radii less than 0.020 inch. Engineering analysis determined that the small feature locations and other life-limited locations of the rotating parts identified in this action have levels of stress during engine operation that are higher than originally anticipated and could result in cracks on these parts. This condition, if not corrected, could cause compressor and turbine wheel fracture and uncontained engine failure. An uncontained engine failure could cause possible damage to the airplane. FAA’s Determination and Requirements of This AD Although no airplanes registered in the United States use these engines, the possibility exists that the engines could be used on airplanes that are registered in the United States in the future. The unsafe condition described previously is likely to exist or develop on other GE CT64–820–4 turboprop engines of the same type design. We are issuing this AD to prevent cracks in the rotating parts that could cause compressor and turbine wheel fracture and uncontained engine failure. An uncontained engine failure could cause possible damage to the airplane. This AD requires removing from service these affected life-limited rotating parts at reduced compliance times. FAA’s Determination of the Effective Date Since there are currently no domestic operators of this engine model, notice and opportunity for public comment before issuing this AD are unnecessary. A situation exists that allows the immediate adoption of this regulation. Comments Invited This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to send us any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES. Include ‘‘AD Docket No. FAA–2006–23705; Directorate Identifier 2005–NE–45–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify it. We will post all comments we receive, without change, to https://dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this AD. Using the search function of the DMS Web site, E:\FR\FM\19APR1.SGM 19APR1 20002 Federal Register / Vol. 71, No. 75 / Wednesday, April 19, 2006 / Rules and Regulations anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78) or you may visit https://dms.dot.gov. Examining the AD Docket You may examine the docket that contains the AD, any comments received, and any final disposition in person at the Docket Management Facility Docket Offices between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in ADDRESSES. Comments will be available in the AD docket shortly after the DMS receives them. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. Adoption of the Amendment Under 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: I PART 39—AIRWORTHINESS DIRECTIVES Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD 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. For the reasons discussed above, I certify that the 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. 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. We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary at the address listed under ADDRESSES. 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: I 2006–08–10 General Electric Company: Amendment 39–14567. Docket No. FAA–2006–23705; Directorate Identifier 2005–NE–45–AD. Effective Date (a) This airworthiness directive (AD) becomes effective May 24, 2006. Affected ADs (b) None. Applicability (c) This AD applies to General Electric Company (GE) CT64–820–4 turboprop engines that use any of the rotating parts listed in Table 1 of this AD. These engines are installed on, but not limited to, DeHavilland DHC–5D Buffalo airplanes. TABLE 1.—AFFECTED ROTATING PARTS Rotor assembly Part nomenclature Compressor ................................................................................. Shaft, Front ................................................................................ Disk, Stage 1 ............................................................................. Retainer, Disk, Stage 1 .............................................................. Disk, Stage 2 ............................................................................. Spacer, Disk, Stage 2 ................................................................ Disk, Stage 3 ............................................................................. Spool, Rotor, Front .................................................................... Spool, Rotor, Rear ..................................................................... Shaft, Rear ................................................................................. Disk and Shaft, Stage 1 ............................................................. Disk, Stage 2 ............................................................................. Ring, Torque .............................................................................. Seal, Air, Stage 1 ....................................................................... Plate, Cooling ............................................................................. Plate, Cooling ............................................................................. Seal, Interstage .......................................................................... Seal, Air, Rear ........................................................................... Seal, Air, Rear ........................................................................... Disk, Stage 3 ............................................................................. Disk, Stage 4 ............................................................................. Disk, Stage 4 ............................................................................. Seal, Interstage .......................................................................... Shaft, Main ................................................................................. Shaft, Main ................................................................................. Tiebolt, Power Turbine Rotor ..................................................... Gas Generator Turbine ............................................................... rmajette on PROD1PC67 with RULES1 Power Turbine ............................................................................. VerDate Aug<31>2005 15:12 Apr 18, 2006 Jkt 208001 PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 E:\FR\FM\19APR1.SGM 19APR1 Part No. 5007T03P03 5015T92P01 5013T71P01 5015T93P01 5015T94P01 5015T95P01 6003T84P02 6005T18P01 6005T26P01 6014T70P02 4007T83P02 3008T60P02 4007T94G02 3008T52P02 4022T37P01 5006T54P02 4022T36P01 4022T36P03 4008T65P02 5006T16P03 5006T16P04 4008T29P01 5009T73P02 6012T83P02 3008T44P02 20003 Federal Register / Vol. 71, No. 75 / Wednesday, April 19, 2006 / Rules and Regulations Unsafe Condition (d) This AD results from the manufacturer’s discovery of cracks in some rotating parts. We are issuing this AD to prevent cracks in the rotating parts that could cause compressor and turbine wheel fracture and uncontained engine failure. An uncontained engine failure could cause possible damage to the airplane. Definition of ‘‘Data Fleet’’ and ‘‘No-Data’’ Fleet Engines (e) For the purposes of this AD, ‘‘Data Fleet’’ is defined as a category of engines for which the engine serial numbers (SNs) are listed in Table 2 of this AD, and the following information has been provided to the manufacturer and included in the data analysis: (1) Current configuration of all life-limited parts. (2) Current cycles of life-limited parts. (3) Engine utilization rate (hours/month). TABLE 2.—ENGINE SNS IN THE DATA FLEET 268504 268505 268509 268511 268514 268529 268534 268535 268537 268545 268549 268562 268565 268569 268573 268574 268575 268580 268583 268588 268589 268590 268596 268603 268605 268606 268608 268620 268622 268636 268637 268638 268641 268642 268643 268644 268646 268647 268648 268649 268650 268653 268655 268656 268658 268659 268660 268661 (f) For the purposes of this AD, ‘‘No-Data Fleet’’ is defined as a category of engines for which the engine SNs are not listed in Table 2 of this AD. The operators of the ‘‘No Data Fleet’’ engines did not supply the data listed in paragraph (e) to the manufacturer. (h) If performing the actions required by this AD for ‘‘Data Fleet’’ engines, follow paragraphs (j) through (o). (i) If performing the actions required by this AD for ‘‘No-Data Fleet’’ engines, follow paragraphs (p) through (u). Compliance Data Fleet Rotating Part Removal Requirements (g) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. (j) For parts listed in Table 3 of this AD and installed in serviceable engines (those that are in service or have met the requirements for and have been approved for return to 268662 268666 268667 268669 268670 268672 268674 268679 268686 268689 268690 268691 service) on the effective date of this AD, do the following: (1) If the cycles-since-new (CSN) of a part listed in Table 3 of this AD are equal to or more than Table 3, Limit 2 as of the effective date of this AD, remove the part before exceeding 900 additional cycles-in-service (CIS) or Table 3, Limit 1, whichever occurs first, but not later than July 31, 2013. (2) If the CSN for a part listed in Table 3 of this AD are fewer than Table 3, Limit 2 as of the effective date of this AD, remove the part from service before exceeding Table 3, Limit 3, but not later than July 31, 2013. TABLE 3.—AFFECTED DATA FLEET ROTATING PART REMOVAL REQUIREMENTS Rotor Nomenclature Compressor ....................................... Shaft, Front ...................................... Disk, Stage 1 ................................... Retainer, Disk, Stage 1 ................... Disk, Stage 2 ................................... Spacer, Disk, Stage 2 ...................... Disk, Stage 3 ................................... Spool, Rotor, Front .......................... Spool, Rotor, Rear ........................... Shaft, Rear ....................................... Disk and Shaft, Stage 1 .................. Disk, Stage 2 ................................... Ring, Torque .................................... Seal, Air, Stage 1 ............................ Plate, Cooling .................................. Plate, Cooling .................................. Seal, Interstage ................................ Seal, Air, Rear ................................. Seal, Air, Rear ................................. Disk, Stage 3 ................................... Disk, Stage 4 ................................... Disk, Stage 4 ................................... Seal, Interstage ................................ Shaft, Main ....................................... Shaft, Main ....................................... Tiebolt, Power Turbine Rotor .......... Gas Generator Turbine ..................... rmajette on PROD1PC67 with RULES1 Power Turbine ................................... (k) For all rotating parts listed in Table 3 of this AD and put into service after the VerDate Aug<31>2005 15:12 Apr 18, 2006 Jkt 208001 Part No. 5007T03P03 5015T92P01 5013T71P01 5015T93P01 5015T94P01 5015T95P01 6003T84P02 6005T18P01 6005T26P01 6014T70P02 4007T83P02 3008T60P02 4007T94G02 3008T52P02 4022T37P01 5006T54P02 4022T36P01 4022T36P03 4008T65P02 5006T16P03 5006T16P04 4008T29P01 5009T73P02 6012T83P02 3008T44P02 effective date of this AD, remove from service PO 00000 Frm 00019 Fmt 4700 Limit 1 (cycles) Sfmt 4700 30,000 13,000 30,000 23,000 30,000 9,000 5,100 19,000 30,000 7,000 11,300 30,000 30,000 5,000 5,000 5,100 5,000 5,000 30,000 30,000 30,000 30,000 13,000 13,000 13,000 Limit 2 (cycles) 29,100 8,100 29,100 8,100 8,100 8,100 2,100 3,500 8,100 6100 5,400 6,100 11,700 4,100 4,100 4,200 4,100 4,100 12,100 12,100 12,100 12,100 12,100 12,100 12,100 Limit 3 (cycles) 30,000 9,000 30,000 9,000 9,000 9,000 3,000 4,400 9,000 7000 6,300 7,000 12,600 5,000 5,000 5,100 5,000 5,000 13,000 13,000 13,000 13,000 13,000 13,000 13,000 before the CSN exceeds Table 3, Limit 3, but not later than July 31, 2013. E:\FR\FM\19APR1.SGM 19APR1 20004 Federal Register / Vol. 71, No. 75 / Wednesday, April 19, 2006 / Rules and Regulations (l) After the effective date of this AD: (1) Do not install any part listed in Table 3 of this AD that has a CSN equal to or more than Table 3, Limit 3. (2) If the CSN for a part listed in Table 3 of this AD are fewer than Table 3, Limit 3: (i) Until July 31, 2007, you may return the part to service, if the part passes the applicable inspections specified in the CT64– 820–4 Engine Overhaul Manual, SEI–448. (ii) You must remove the part from service before Table 3, Limit 3 is exceeded, but no later than July 31, 2013. (iii) After July 31, 2007, do not install any part listed in Table 3 of this AD. (m) On July 31, 2007, for engines in service that have a part listed in Table 3 of this AD, remove the affected part before exceeding Table 3, Limit 3, but no later than July 31, 2013. (n) For main shafts, P/N 5009T73P02, and P/N 6012T83P02, and power turbine rotor tiebolt, P/N 3008T44P02, with unknown CSN do the following: (1) Assign each part a CSN value of 7,400 CSN as of the effective date of this AD and refer to Table 3 of this AD for removal requirements. (2) Continue to track the parts starting from 7,400 CSN and remove from service as specified in paragraphs (j) through (n) of this AD, but no later than July 31, 2013. (o) For rear air seal, P/N 4022T36P03, and power turbine stage 4 disk, P/N 5006T16P04, with unknown CSN, remove the part before exceeding 10 additional cycles, but no later than July 31, 2013. No-Data Fleet Rotating Part Removal Requirements (p) For parts listed in Table 4 of this AD and installed in serviceable engines (those that are in service, or have met the requirements for and have been approved for return to service) on the effective date of this AD, do the following: (1) If the CSN of a part listed in Table 4 of this AD are equal to or more than Table 4, Limit 2 as of the effective date of this AD, remove the part before exceeding 50 additional CIS or Table 4, Limit 1, whichever occurs first, but not later than July 31, 2013. (2) If the CSN for a part listed in Table 4 of this AD are fewer than Table 4, Limit 2 as of the effective date of this AD, remove the part from service before exceeding Table 4, Limit 3, but not later than July 31, 2013. (q) For all rotating parts listed in Table 4 of this AD and put into service after the effective date of this AD, remove from service before the CSN exceeds Table 4, Limit 3, but not later than July 31, 2013. TABLE 4.—AFFECTED NO-DATA FLEET ROTATING PART REMOVAL REQUIREMENTS Rotor Nomenclature Compressor ....................................... Shaft, Front ...................................... Disk, Stage 1 ................................... Retainer, Disk, Stage 1 ................... Disk, Stage 2 ................................... Spacer, Disk, Stage 2 ...................... Disk, Stage 3 ................................... Spool, Rotor, Front .......................... Spool, Rotor, Rear ........................... Shaft, Rear ....................................... Disk and Shaft, Stage 1 .................. Disk, Stage 2 ................................... Ring, Torque .................................... Seal, Air, Stage 1 ............................ Plate, Cooling .................................. Plate, Cooling .................................. Seal, Interstage ................................ Seal, Air, Rear ................................. Seal, Air, Rear ................................. Disk, Stage 3 ................................... Disk, Stage 4 ................................... Disk, Stage 4 ................................... Seal, Interstage ................................ Shaft, Main ....................................... Shaft, Main ....................................... Tiebolt, Power Turbine Rotor .......... Gas Generator Turbine ..................... rmajette on PROD1PC67 with RULES1 Power Turbine ................................... (r) After the effective date of this AD: (1) Do not install any part listed in Table 4 of this AD that has a CSN equal to or more than Table 4, Limit 3. (2) If the CSN for a part listed in Table 4 of this AD are fewer than Table 4, Limit 3: (i) Until July 31, 2007, you may return the part to service, if the part passes the applicable inspections specified in the CT64– 820–4 Engine Overhaul Manual, SEI–448. (ii) You must remove the part from service before Table 4, Limit 3 is exceeded, but no later than July 31, 2013. (iii) After July 31, 2007, do not install any part listed in Table 4 of this AD. (s) On July 31, 2007, for engines in service that have a part listed in Table 4 of this AD, remove the affected part before exceeding Table 4, Limit 3, but no later than July 31, 2013. VerDate Aug<31>2005 15:12 Apr 18, 2006 Jkt 208001 Part No. Limit 1 (cycles) 5007T03P03 5015T92P01 5013T71P01 5015T93P01 5015T94P01 5015T95P01 6003T84P02 6005T18P01 6005T26P01 6014T70P02 4007T83P02 3008T60P02 4007T94G02 3008T52P02 4022T37P01 5006T54P02 4022T36P01 4022T36P03 4008T65P02 5006T16P03 5006T16P04 4008T29P01 5009T73P02 6012T83P02 3008T44P02 Limit 2 (cycles) 30,000 13,000 30,000 23,000 30,000 9,000 5,100 19,000 30,000 7,000 11,300 30,000 30,000 5,000 5,000 5,100 5,000 5,000 30,000 30,000 30,000 30,000 13,000 13,000 13,000 Limit 3 (cycles) 29,950 8,950 29,950 8,950 8,950 8,950 2,950 4,350 8,950 6,950 6,250 6,950 12,550 4,950 4,950 5,050 4,950 4,950 12,950 12,950 12,950 12,950 12,950 12,950 12,950 30,000 9,000 30,000 9,000 9,000 9,000 3,000 4,400 9,000 7,000 6,300 7,000 12,600 5,000 5,000 5,100 5,000 5,000 13,000 13,000 13,000 13,000 13,000 13,000 13,000 (t) For main shafts P/N 5009T73P02, and P/N 6012T83P02, and power turbine rotor tiebolt, PN 3008T44P02, with unknown CSN, remove the part before exceeding 50 additional cycles (u) For rear air seal, P/N 4022T36P03, and power turbine stage 4 disk, P/N 5006T16P04, with unknown CSN, remove the part before exceeding 10 additional cycles, but no later than July 31, 2013. (2) Note in the Engine Log Book that AD 2006–08–10 has been complied with. Log Book Entry (x) GE Aircraft Engines CT64 Alert Service Bulletin CT64 S/B 72–A0130, dated January 24, 2006, pertains to the subject of this AD. (v) For all engines, calculate the cycles remaining on the affected rotating parts and make an entry in the Engine Log Book marked with the engine S/N and its fleet category, either ‘‘DATA FLEET’’ or ‘‘NODATA FLEET.’’ (1) Date and file the record in the Engine Log Book. PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 Alternative Methods of Compliance (w) 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. Related Information E:\FR\FM\19APR1.SGM 19APR1 Federal Register / Vol. 71, No. 75 / Wednesday, April 19, 2006 / Rules and Regulations Issued in Burlington, Massachusetts, on April 12, 2006. Francis A. Favara, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 06–3724 Filed 4–18–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF HOMELAND SECURITY Bureau of Customs and Border Protection 19 CFR Parts 101 and 122 USCBP–2005–0030 and [CBP Dec. 06– 10] Establishment of Port of Entry at New River Valley, VA, and Termination of the User-Fee Status of New River Valley Airport AGENCY: Customs and Border Protection, DHS. ACTION: Final rule. rmajette on PROD1PC67 with RULES1 SUMMARY: This document amends Department of Homeland Security regulations pertaining to the field organization of the Bureau of Customs and Border Protection by conditionally establishing a new port of entry at New River Valley, Virginia, and terminating the user-fee status of New River Valley Airport. The new port of entry consists of all the area surrounded by the continuous outer boundaries of the Montgomery, Pulaski and Roanoke counties in the Commonwealth of Virginia, including New River Valley Airport, which currently is operated as a user-fee airport. These changes will assist the Bureau of Customs and Border Protection in its continuing efforts to provide better service to carriers, importers and the general public. EFFECTIVE DATE: May 19, 2006. FOR FURTHER INFORMATION CONTACT: Dennis Dore, Office of Field Operations, 202–344–2776. SUPPLEMENTARY INFORMATION: Background In a Notice of Proposed Rulemaking published in the Federal Register (70 FR 38637) on July 5, 2005, the Department of Homeland Security (DHS), Bureau of Customs and Border Protection (CBP), proposed to amend 19 CFR 101.3(b)(1) by conditionally establishing a new port of entry at New River Valley, VA. The new port of entry, as proposed, would include the area surrounded by the continuous outer boundaries of the Montgomery, Pulaski and Roanoke counties in the VerDate Aug<31>2005 15:12 Apr 18, 2006 Jkt 208001 Commonwealth of Virginia. This area includes New River Valley Airport, located in the town of Dublin, Virginia, which currently operates and is listed as a user-fee airport at 19 CFR 122.15(b). The change of status for New River Valley Airport, from a user-fee airport to inclusion within the boundaries of a port of entry, would subject the airport to the passenger processing fee provided for at 19 U.S.C. 58c(a)(5)(B). CBP proposed to establish the new port of entry based on its review of the level and pace of development in the New River Valley area. CBP evaluated whether there is a sufficient volume of import business (actual or potential) to justify the expense of maintaining a new office or expanding service in the New River Valley area based on the criteria for port of entry designations set forth in Treasury Decision (T.D.) 82–37 (Revision of Customs Criteria for Establishing Ports of Entry and Stations, 47 FR 10137), as revised by T.D. 86–14 (51 FR4559) and T.D. 87–65 (52 FR 16328). New River Valley was proposed to be a conditional port of entry based on the potential of the area. The actual and potential workload statistics of the area were set forth in the Notice of Proposed Rulemaking. See 70 FR at 38637–38. Analysis of Comments and Conclusion Several comments were received in response to the Notice of Proposed Rulemaking. All of the comments were favorable to the proposal. Each comment was favorable in the entirety; no alternate courses of action, limitations or possible problems were presented by the commenters. Because CBP continues to believe that the potential volume of import business in New River Valley supports a new port of entry there, and that the establishment of the new port of entry will assist CBP in its continuing efforts to provide better service to carriers, importers and the general public, CBP is conditionally establishing the new port of entry as proposed. In three years, CBP will review the actual workload generated within the new port of entry. If that review indicates that the actual workload is below the criteria set forth under T.D. 82–37 standards (as amended), CBP may institute procedures to revoke the port of entry status. In such case, New River Valley airport may reapply to become a userfee airport under the provisions of 19 U.S.C. 58b. Description of the New Port of Entry Limits The geographical limits of the new New River Valley port of entry are as PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 20005 follows: The continuous outer boundaries of the Montgomery, Pulaski and Roanoke counties in the Commonwealth of Virginia. Authority This change is made under the authority of 5 U.S.C. 301 and 19 U.S.C. 2, 66, and 1624, and the Homeland Security Act of 2002, Public Law 107– 296 (November 25, 2002). The Regulatory Flexibility Act and Executive Order 12866 With DHS approval, CBP establishes, expands and consolidates CBP ports of entry throughout the United States to accommodate the volume of CBP-related activity in various parts of the country. The Office of Management and Budget has determined that this final rule is not a significant regulatory action under Executive Order 12866. This action also will not have a significant economic impact on a substantial number of small entities. Accordingly, it is certified that this document is not subject to the additional requirements of the provisions of the Regulatory Flexibility Act (5 U.S.C. 601 et seq.). Signing Authority The signing authority for this document falls under 19 CFR 0.2(a) because the establishment of a new port of entry and the termination of the userfee status of an airport are not within the bounds of those regulations for which the Secretary of the Treasury has retained sole authority. Accordingly, this final rule may be signed by the Secretary of Homeland Security or his delegate. List of Subjects 19 CFR Part 101 Customs duties and inspection, Customs ports of entry, Exports, Imports, Organization and functions (Government agencies). 19 CFR Part 122 Customs duties and inspection, Airports, Imports, Organization and functions (Government agencies). Amendments to CBP Regulations For the reasons set forth above, part 101, CBP Regulations (19 CFR part 101), and part 122, CBP Regulations (19 CFR part 122), are amended as set forth below. I PART 101—GENERAL PROVISIONS 1. The general authority citation for part 101 and the specific authority citation for section 101.3 continue to read as follows: I E:\FR\FM\19APR1.SGM 19APR1

Agencies

[Federal Register Volume 71, Number 75 (Wednesday, April 19, 2006)]
[Rules and Regulations]
[Pages 20001-20005]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-3724]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23705; Directorate Identifier 2005-NE-45-AD;
Amendment 39-14567; AD 2006-08-10]
RIN 2120-AA64

Airworthiness Directives; General Electric Company CT64-820-4
Turboprop Engines

AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
General Electric Company (GE) CT64-820-4 turboprop engines with certain
part number (P/N) rotating parts. The parts are in the compressor rotor
assembly, gas generator turbine rotor assembly, and power turbine rotor
assembly that are subject to low-cycle fatigue. This AD requires
removing from service these affected rotating parts at reduced
compliance times. This AD results from the manufacturer's discovery of
cracks in some rotating parts. We are issuing this AD to prevent cracks
in the rotating parts that could cause compressor and turbine wheel
fracture and uncontained engine failure. An uncontained engine failure
could cause possible damage to the airplane.

DATES: This AD becomes effective May 24, 2006.

ADDRESSES: Use one of the following addresses to comment on this AD:
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-0001.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact GE Aircraft Engines Customer Support Center, M/D 285, 1
Neumann Way, Evendale, OH 45215, telephone (513) 552-3272; fax (513)
552-3329; e-mail address: GEAE.csc@ae.ge.com, for the service
information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Anthony W. Cerra Jr., Aerospace
Engineer, Engine Certification Office, FAA, Engine and Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803;
telephone 781-238-7128; fax 781-238-7199; e-mail address:
anthony.cerra@faa.gov.

SUPPLEMENTARY INFORMATION: GE has informed us that cracks have been
found in certain P/N rotating parts. The manufacturer reported that
cracks were found in the outer rim of a stage 1 aft cooling plate, P/N
4022T37P01, installed on the gas generator turbine (GGT) rotor of a
military T64 engine. They also found cracks in the sawcut slots of the
GGT rear air seals of stage 2 aft cooling plates, P/N 4022T36P01, in
the CT64-820-4 engine model and a similar military T64 engine model.
There have been at least 13 reports of cracked GGT rear air seals.
Investigation by the manufacturer showed that compressor rotor
assemblies, GGT rotor assemblies, and power turbine rotor assemblies
have small feature locations. A ``small feature'' location is any
rotating hardware feature with drawing radii less than 0.020 inch.
Engineering analysis determined that the small feature locations and
other life-limited locations of the rotating parts identified in this
action have levels of stress during engine operation that are higher
than originally anticipated and could result in cracks on these parts.
This condition, if not corrected, could cause compressor and turbine
wheel fracture and uncontained engine failure. An uncontained engine
failure could cause possible damage to the airplane.

FAA's Determination and Requirements of This AD

Although no airplanes registered in the United States use these
engines, the possibility exists that the engines could be used on
airplanes that are registered in the United States in the future. The
unsafe condition described previously is likely to exist or develop on
other GE CT64-820-4 turboprop engines of the same type design. We are
issuing this AD to prevent cracks in the rotating parts that could
cause compressor and turbine wheel fracture and uncontained engine
failure. An uncontained engine failure could cause possible damage to
the airplane. This AD requires removing from service these affected
life-limited rotating parts at reduced compliance times.

FAA's Determination of the Effective Date

Since there are currently no domestic operators of this engine
model, notice and opportunity for public comment before issuing this AD
are unnecessary. A situation exists that allows the immediate adoption
of this regulation.

Comments Invited

This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment; however, we invite you to send us any written relevant data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. FAA-2006-23705;
Directorate Identifier 2005-NE-45-AD'' in the subject line of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify it. We will post all comments we receive,
without change, to https://dms.dot.gov, including any personal
information you provide. We will also post a report summarizing each
substantive verbal contact with FAA personnel concerning this AD. Using
the search function of the DMS Web site,

[[Page 20002]]

anyone can find and read the comments in any of our dockets, including
the name of the individual who sent the comment (or signed the comment
on behalf of an association, business, labor union, etc.). You may
review the DOT's complete Privacy Act Statement in the Federal Register
published on April 11, 2000 (65 FR 19477-78) or you may visit https://
dms.dot.gov.

Examining the AD Docket

You may examine the docket that contains the AD, any comments
received, and any final disposition in person at the Docket Management
Facility Docket Offices between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The Docket Office (telephone (800)
647-5227) is located on the plaza level of the Department of
Transportation Nassif Building at the street address stated in
ADDRESSES. Comments will be available in the AD docket shortly after
the DMS receives them.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.

Regulatory Findings

We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD 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. For the
reasons discussed above, I certify that the 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. 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. We prepared a summary of the costs
to comply with this AD and placed it in the AD Docket. You may get a
copy of this summary at the address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

0
Under 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

0
1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13 [Amended]

0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:

2006-08-10 General Electric Company: Amendment 39-14567. Docket No.
FAA-2006-23705; Directorate Identifier 2005-NE-45-AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective May 24,
2006.

Affected ADs

(b) None.

Applicability

(c) This AD applies to General Electric Company (GE) CT64-820-4
turboprop engines that use any of the rotating parts listed in Table
1 of this AD. These engines are installed on, but not limited to,
DeHavilland DHC-5D Buffalo airplanes.

Table 1.--Affected Rotating Parts
------------------------------------------------------------------------
Rotor assembly Part nomenclature Part No.
------------------------------------------------------------------------
Compressor..................... Shaft, Front........... 5007T03P03
Disk, Stage 1.......... 5015T92P01
Retainer, Disk, Stage 1 5013T71P01
Disk, Stage 2.......... 5015T93P01
Spacer, Disk, Stage 2.. 5015T94P01
Disk, Stage 3.......... 5015T95P01
Spool, Rotor, Front.... 6003T84P02
Spool, Rotor, Rear..... 6005T18P01
Shaft, Rear............ 6005T26P01
Gas Generator Turbine.......... Disk and Shaft, Stage 1 6014T70P02
Disk, Stage 2.......... 4007T83P02
Ring, Torque........... 3008T60P02
Seal, Air, Stage 1..... 4007T94G02
Plate, Cooling......... 3008T52P02
Plate, Cooling......... 4022T37P01
Seal, Interstage....... 5006T54P02
Seal, Air, Rear........ 4022T36P01
Seal, Air, Rear........ 4022T36P03
Power Turbine.................. Disk, Stage 3.......... 4008T65P02
Disk, Stage 4.......... 5006T16P03
Disk, Stage 4.......... 5006T16P04
Seal, Interstage....... 4008T29P01
Shaft, Main............ 5009T73P02
Shaft, Main............ 6012T83P02
Tiebolt, Power Turbine 3008T44P02
Rotor.
------------------------------------------------------------------------

[[Page 20003]]

Unsafe Condition

(d) This AD results from the manufacturer's discovery of cracks
in some rotating parts. We are issuing this AD to prevent cracks in
the rotating parts that could cause compressor and turbine wheel
fracture and uncontained engine failure. An uncontained engine
failure could cause possible damage to the airplane.

Definition of ``Data Fleet'' and ``No-Data'' Fleet Engines

(e) For the purposes of this AD, ``Data Fleet'' is defined as a
category of engines for which the engine serial numbers (SNs) are
listed in Table 2 of this AD, and the following information has been
provided to the manufacturer and included in the data analysis:
(1) Current configuration of all life-limited parts.
(2) Current cycles of life-limited parts.
(3) Engine utilization rate (hours/month).

Table 2.--Engine SNs in the Data Fleet
----------------------------------------------------------------------------------------------------------------

----------------------------------------------------------------------------------------------------------------
268504 268565 268605 268646 268662
268505 268569 268606 268647 268666
268509 268573 268608 268648 268667
268511 268574 268620 268649 268669
268514 268575 268622 268650 268670
268529 268580 268636 268653 268672
268534 268583 268637 268655 268674
268535 268588 268638 268656 268679
268537 268589 268641 268658 268686
268545 268590 268642 268659 268689
268549 268596 268643 268660 268690
268562 268603 268644 268661 268691
----------------------------------------------------------------------------------------------------------------

(f) For the purposes of this AD, ``No-Data Fleet'' is defined as
a category of engines for which the engine SNs are not listed in
Table 2 of this AD. The operators of the ``No Data Fleet'' engines
did not supply the data listed in paragraph (e) to the manufacturer.

Compliance

(g) You are responsible for having the actions required by this
AD performed within the compliance times specified unless the
actions have already been done.
(h) If performing the actions required by this AD for ``Data
Fleet'' engines, follow paragraphs (j) through (o).
(i) If performing the actions required by this AD for ``No-Data
Fleet'' engines, follow paragraphs (p) through (u).

Data Fleet Rotating Part Removal Requirements

(j) For parts listed in Table 3 of this AD and installed in
serviceable engines (those that are in service or have met the
requirements for and have been approved for return to service) on
the effective date of this AD, do the following:
(1) If the cycles-since-new (CSN) of a part listed in Table 3 of
this AD are equal to or more than Table 3, Limit 2 as of the
effective date of this AD, remove the part before exceeding 900
additional cycles-in-service (CIS) or Table 3, Limit 1, whichever
occurs first, but not later than July 31, 2013.
(2) If the CSN for a part listed in Table 3 of this AD are fewer
than Table 3, Limit 2 as of the effective date of this AD, remove
the part from service before exceeding Table 3, Limit 3, but not
later than July 31, 2013.

Table 3.--Affected Data Fleet Rotating Part Removal Requirements
--------------------------------------------------------------------------------------------------------------------------------------------------------
Limit 1 Limit 2 Limit 3
Rotor Nomenclature Part No. (cycles) (cycles) (cycles)
--------------------------------------------------------------------------------------------------------------------------------------------------------
Compressor..................................... Shaft, Front........................... 5007T03P03 30,000 29,100 30,000
Disk, Stage 1.......................... 5015T92P01 13,000 8,100 9,000
Retainer, Disk, Stage 1................ 5013T71P01 30,000 29,100 30,000
Disk, Stage 2.......................... 5015T93P01 23,000 8,100 9,000
Spacer, Disk, Stage 2.................. 5015T94P01 30,000 8,100 9,000
Disk, Stage 3.......................... 5015T95P01 9,000 8,100 9,000
Spool, Rotor, Front.................... 6003T84P02 5,100 2,100 3,000
Spool, Rotor, Rear..................... 6005T18P01 19,000 3,500 4,400
Shaft, Rear............................ 6005T26P01 30,000 8,100 9,000
Gas Generator Turbine.......................... Disk and Shaft, Stage 1................ 6014T70P02 7,000 6100 7000
Disk, Stage 2.......................... 4007T83P02 11,300 5,400 6,300
Ring, Torque........................... 3008T60P02 30,000 6,100 7,000
Seal, Air, Stage 1..................... 4007T94G02 30,000 11,700 12,600
Plate, Cooling......................... 3008T52P02 5,000 4,100 5,000
Plate, Cooling......................... 4022T37P01 5,000 4,100 5,000
Seal, Interstage....................... 5006T54P02 5,100 4,200 5,100
Seal, Air, Rear........................ 4022T36P01 5,000 4,100 5,000
Seal, Air, Rear........................ 4022T36P03 5,000 4,100 5,000
Power Turbine.................................. Disk, Stage 3.......................... 4008T65P02 30,000 12,100 13,000
Disk, Stage 4.......................... 5006T16P03 30,000 12,100 13,000
Disk, Stage 4.......................... 5006T16P04 30,000 12,100 13,000
Seal, Interstage....................... 4008T29P01 30,000 12,100 13,000
Shaft, Main............................ 5009T73P02 13,000 12,100 13,000
Shaft, Main............................ 6012T83P02 13,000 12,100 13,000
Tiebolt, Power Turbine Rotor........... 3008T44P02 13,000 12,100 13,000
--------------------------------------------------------------------------------------------------------------------------------------------------------

(k) For all rotating parts listed in Table 3 of this AD and put
into service after the effective date of this AD, remove from
service before the CSN exceeds Table 3, Limit 3, but not later than
July 31, 2013.

[[Page 20004]]

(l) After the effective date of this AD:
(1) Do not install any part listed in Table 3 of this AD that
has a CSN equal to or more than Table 3, Limit 3.
(2) If the CSN for a part listed in Table 3 of this AD are fewer
than Table 3, Limit 3:
(i) Until July 31, 2007, you may return the part to service, if
the part passes the applicable inspections specified in the CT64-
820-4 Engine Overhaul Manual, SEI-448.
(ii) You must remove the part from service before Table 3, Limit
3 is exceeded, but no later than July 31, 2013.
(iii) After July 31, 2007, do not install any part listed in
Table 3 of this AD.
(m) On July 31, 2007, for engines in service that have a part
listed in Table 3 of this AD, remove the affected part before
exceeding Table 3, Limit 3, but no later than July 31, 2013.
(n) For main shafts, P/N 5009T73P02, and P/N 6012T83P02, and
power turbine rotor tiebolt, P/N 3008T44P02, with unknown CSN do the
following:
(1) Assign each part a CSN value of 7,400 CSN as of the
effective date of this AD and refer to Table 3 of this AD for
removal requirements.
(2) Continue to track the parts starting from 7,400 CSN and
remove from service as specified in paragraphs (j) through (n) of
this AD, but no later than July 31, 2013.
(o) For rear air seal, P/N 4022T36P03, and power turbine stage 4
disk, P/N 5006T16P04, with unknown CSN, remove the part before
exceeding 10 additional cycles, but no later than July 31, 2013.

No-Data Fleet Rotating Part Removal Requirements

(p) For parts listed in Table 4 of this AD and installed in
serviceable engines (those that are in service, or have met the
requirements for and have been approved for return to service) on
the effective date of this AD, do the following:
(1) If the CSN of a part listed in Table 4 of this AD are equal
to or more than Table 4, Limit 2 as of the effective date of this
AD, remove the part before exceeding 50 additional CIS or Table 4,
Limit 1, whichever occurs first, but not later than July 31, 2013.
(2) If the CSN for a part listed in Table 4 of this AD are fewer
than Table 4, Limit 2 as of the effective date of this AD, remove
the part from service before exceeding Table 4, Limit 3, but not
later than July 31, 2013.
(q) For all rotating parts listed in Table 4 of this AD and put
into service after the effective date of this AD, remove from
service before the CSN exceeds Table 4, Limit 3, but not later than
July 31, 2013.

Table 4.--Affected No-Data Fleet Rotating Part Removal Requirements
--------------------------------------------------------------------------------------------------------------------------------------------------------
Limit 1 Limit 2 Limit 3
Rotor Nomenclature Part No. (cycles) (cycles) (cycles)
--------------------------------------------------------------------------------------------------------------------------------------------------------
Compressor..................................... Shaft, Front........................... 5007T03P03 30,000 29,950 30,000
Disk, Stage 1.......................... 5015T92P01 13,000 8,950 9,000
Retainer, Disk, Stage 1................ 5013T71P01 30,000 29,950 30,000
Disk, Stage 2.......................... 5015T93P01 23,000 8,950 9,000
Spacer, Disk, Stage 2.................. 5015T94P01 30,000 8,950 9,000
Disk, Stage 3.......................... 5015T95P01 9,000 8,950 9,000
Spool, Rotor, Front.................... 6003T84P02 5,100 2,950 3,000
Spool, Rotor, Rear..................... 6005T18P01 19,000 4,350 4,400
Shaft, Rear............................ 6005T26P01 30,000 8,950 9,000
Gas Generator Turbine.......................... Disk and Shaft, Stage 1................ 6014T70P02 7,000 6,950 7,000
Disk, Stage 2.......................... 4007T83P02 11,300 6,250 6,300
Ring, Torque........................... 3008T60P02 30,000 6,950 7,000
Seal, Air, Stage 1..................... 4007T94G02 30,000 12,550 12,600
Plate, Cooling......................... 3008T52P02 5,000 4,950 5,000
Plate, Cooling......................... 4022T37P01 5,000 4,950 5,000
Seal, Interstage....................... 5006T54P02 5,100 5,050 5,100
Seal, Air, Rear........................ 4022T36P01 5,000 4,950 5,000
Seal, Air, Rear........................ 4022T36P03 5,000 4,950 5,000
Power Turbine.................................. Disk, Stage 3.......................... 4008T65P02 30,000 12,950 13,000
Disk, Stage 4.......................... 5006T16P03 30,000 12,950 13,000
Disk, Stage 4.......................... 5006T16P04 30,000 12,950 13,000
Seal, Interstage....................... 4008T29P01 30,000 12,950 13,000
Shaft, Main............................ 5009T73P02 13,000 12,950 13,000
Shaft, Main............................ 6012T83P02 13,000 12,950 13,000
Tiebolt, Power Turbine Rotor........... 3008T44P02 13,000 12,950 13,000
--------------------------------------------------------------------------------------------------------------------------------------------------------

(r) After the effective date of this AD:
(1) Do not install any part listed in Table 4 of this AD that
has a CSN equal to or more than Table 4, Limit 3.
(2) If the CSN for a part listed in Table 4 of this AD are fewer
than Table 4, Limit 3:
(i) Until July 31, 2007, you may return the part to service, if
the part passes the applicable inspections specified in the CT64-
820-4 Engine Overhaul Manual, SEI-448.
(ii) You must remove the part from service before Table 4, Limit
3 is exceeded, but no later than July 31, 2013.
(iii) After July 31, 2007, do not install any part listed in
Table 4 of this AD.
(s) On July 31, 2007, for engines in service that have a part
listed in Table 4 of this AD, remove the affected part before
exceeding Table 4, Limit 3, but no later than July 31, 2013.
(t) For main shafts P/N 5009T73P02, and P/N 6012T83P02, and
power turbine rotor tiebolt, PN 3008T44P02, with unknown CSN, remove
the part before exceeding 50 additional cycles
(u) For rear air seal, P/N 4022T36P03, and power turbine stage 4
disk, P/N 5006T16P04, with unknown CSN, remove the part before
exceeding 10 additional cycles, but no later than July 31, 2013.

Log Book Entry

(v) For all engines, calculate the cycles remaining on the
affected rotating parts and make an entry in the Engine Log Book
marked with the engine S/N and its fleet category, either ``DATA
FLEET'' or ``NO-DATA FLEET.''
(1) Date and file the record in the Engine Log Book.
(2) Note in the Engine Log Book that AD 2006-08-10 has been
complied with.

Alternative Methods of Compliance

(w) 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.

Related Information

(x) GE Aircraft Engines CT64 Alert Service Bulletin CT64 S/B 72-
A0130, dated January 24, 2006, pertains to the subject of this AD.

[[Page 20005]]

Issued in Burlington, Massachusetts, on April 12, 2006.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 06-3724 Filed 4-18-06; 8:45 am]
BILLING CODE 4910-13-P

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