Unknown. Final rule

27,476 words·~125 min read·/register/2006/08/18/06-6910·

A research copy — for the controlling text, always check the official state or federal source. Not legal advice.

--- schema: federal-register doc_type: fedreg source_file: FR-2006-08-18.xml --- 71 160 Friday, August 18, 2006 Contents Army Army Department NOTICES Meetings: Armed Forces Epidemiological Board, 47782 06-7006 06-7008 Patent licenses; non-exclusive, exclusive, or partially exclusive: Biotherapeutics, Inc., 47782-47783 06-7007 Blind Blind or Severely Disabled, Committee for Purchase From People Who Are See Committee for Purchase From People Who Are Blind or Severely Disabled Centers Centers for Medicare & Medicaid Services RULES Medicare:

Hospital inpatient prospective payment systems; 2007 FY occupational mix adjustment to wage index; implementation, 47870-48351 06-6692 Medicare program: Inpatient rehabilitation facility prospective payment system (2007 FY), 48354-48434 06-6694 Children Children and Families Administration NOTICES Agency information collection activities; proposals, submissions, and approvals, 47813-47815 06-7013 06-7014 06-7015 Grants and cooperative agreements; availability, etc.: Community Economic Development Program, 47815 E6-13667 Coast Guard Coast Guard RULES Drawbridge operations:

Texas, 47737 E6-13665 Pollution: New oil pollution limits of liability for vessels, 47737-47738 E6-12936 Ports and waterways safety; regulated navigation areas, safety zones, security zones, etc.: Presque Isle Bay, PA, E6-13677 47738-47742 E6-13678 NOTICES Meetings: Towing Safety Advisory Committee, 47821-47822 E6-13666 Commerce Commerce Department See International Trade Administration See National Institute of Standards and Technology See National Oceanic and Atmospheric Administration Committee for Purchase Committee for Purchase From People Who Are Blind or Severely Disabled NOTICES Procurement list; additions and deletions, E6-13670 47772-47773 E6-13671 Correction, 47773-47774 E6-13672 Commodity Commodity Futures Trading Commission NOTICES Meetings;

Sunshine Act, 47780 06-7044 06-7047 06-7048 Defense Defense Department See Army Department NOTICES Privacy Act; systems of records, 47780-47782 06-7009 Education Education Department PROPOSED RULES Postsecondary education: Academic Competitiveness Grant and National Science and Mathematics Access to Retain Talent Grant Programs; grant and loan programs amendments, 47756-47758 E6-13642 NOTICES Agency information collection activities; proposals, submissions, and approvals, 47783-47785 E6-13619 E6-13673 E6-13674 Grants and cooperative agreements; availability, etc.:

Postsecondary education— Hurricane Education Recovery Awards, 47785-47787 E6-13641 Special education and rehabilitative services— Assistive technology reutilization model demonstrations, 48436-48443 06-7030 06-7031 Centers for Independent Living, 47787-47791 E6-13648 National Assistive Technology and Technical Assistance Center, 48443-48446 06-7032 Energy Energy Department See Energy Efficiency and Renewable Energy Office See Energy Information Administration See Federal Energy Regulatory Commission Energy Energy Efficiency and Renewable Energy Office NOTICES Federal energy management program:

Premium energy efficient electric motors; Federal acquisition standards, 47791-47793 E6-13691 Energy Energy Information Administration NOTICES Agency information collection activities; proposals, submissions, and approvals, E6-13689 47793-47795 E6-13694 EPA Environmental Protection Agency RULES Air quality implementation plans; approval and promulgation; various States: Virginia, 47742-47747 E6-13614 E6-13615 Superfund program: National oil and hazardous substances contingency plan— National priorities list update; correction, 47747-47748 E6-13611 PROPOSED RULES Air programs:

Outer Continental Shelf regulations— California; consistency update, 47758-47763 E6-13620 NOTICES Agency information collection activities; proposals, submissions, and approvals, 47805-47807 E6-13607 Confidential business information and data transfer, 47807 06-7004 Environmental statements; availability, etc.: Agency comment availability, 47807-47808 E6-13663 Agency weekly receipts, 47808-47809 E6-13662 Meetings: Acute Exposure Guideline Levels for Hazardous Substances National Advisory Committee, 47809-47810 E6-13658 Pesticide, food, and feed additive petitions:

BASF Corp., 47810-47811 E6-13657 FAA Federal Aviation Administration RULES Airworthiness directives: Airbus, 47706-47707 E6-13445 Cessna Aircraft Co., 47711-47714 E6-13442 Empresa Brasileira de Aeronautica S.A. (EMBRAER), 47725-47727 E6-13449 General Electric Co., 47717-47725 E6-13437 Grob-Werke, 47702-47706 E6-13439 McDonnell Douglas, 47707-47711 E6-13448 Mitsubishi Heavy Industries, 47697-47702 E6-13441 E6-13554 Stemme GmbH & Co., 47714-47717 E6-13440 Class D and E airspace, 47727-47729 06-6910 PROPOSED RULES Airworthiness directives:

Airbus, 47752-47754 E6-13647 Boeing, 47754-47756 E6-13649 Federal Emergency Federal Emergency Management Agency RULES Flood insurance; communities eligible for sale: Various States, 47748-47750 E6-13613 Federal Energy Federal Energy Regulatory Commission NOTICES Electric rate and corporate regulation combined filings, 47800-47801 E6-13629 Environmental statements; availability, etc.: F & B Wood Corp., 47801 E6-13768 Environmental statements; notice of intent: MoBay Storage Hub, Inc., 47801-47803 E6-13760 Hydroelectric applications, 47803-47804 E6-13627 E6-13767 Meetings:

Idaho Power Co., 47804-47805 E6-13624 *Applications, hearings, determinations, etc.:* ANR Pipeline Co., 47795-47796 E6-13770 Cheniere Creole Trail Pipeline, L.P., 47796 E6-13625 Entergy Texas Arkansas, 47796 E6-13628 GulfTerra Texas Pipeline, L.P., 47797 E6-13769 Nevada Power Co., Inc., 47797 E6-13764 Northern Border Pipeline Co., E6-13758 47797-47798 E6-13771 E6-13806 Portland Natural Gas Transmission System, 47798-47799 E6-13759 Regional Transmission Organizations, et al., 47799 E6-13807 Southwest Power Pool, Inc., 47799 E6-13763 Tri-County Electric Cooperative, Inc., et al., 47799-47800 E6-13765 Wabash Valley Power Association, 47800 E6-13808 Federal Highway Federal Highway Administration NOTICES Environmental statements; notice of intent:

Smith County, TX, 47861-47862 06-7012 FMC Federal Maritime Commission NOTICES Investigations, hearings, petitions, etc.: Team Ocean Services, 47811 E6-13634 Federal Railroad Federal Railroad Administration NOTICES Environmental statements; availability, etc.: Section 106 Programmatic Agreement; participation as concurring party, etc., 47862-47863 E6-13531 Federal Reserve Federal Reserve System NOTICES Banks and bank holding companies: Change in bank control, 47811-47812 E6-13605 E6-13655 Formations, acquisitions, and mergers, 47812 E6-13654 Fish Fish and Wildlife Service PROPOSED RULES Endangered and threatened species:

Findings on petitions, etc.— Sand wasps, et al., 47765-47771 E6-13109 NOTICES Environmental statements; availability, etc.: San Diego Bay National Wildlife Refuge; comprehensive conservation plan, 47824-47825 E6-13556 Food Food and Drug Administration RULES Food additives: Bacteriophage preparation, 47729-47732 E6-13621 NOTICES Agency information collection activities; proposals, submissions, and approvals, 47815-47816 E6-13609 Health Health and Human Services Department See Centers for Medicare & Medicaid Services See Children and Families Administration See Food and Drug Administration See National Institutes of Health NOTICES Meetings:

Vital and Health Statistics National Committee, 47812-47813 06-7023 Vital Health and Statistics National Committee, 47813 06-7024 Homeland Homeland Security Department See Coast Guard See Federal Emergency Management Agency Housing Housing and Urban Development Department NOTICES Agency information collection activities; proposals, submissions, and approvals, 47822-47823 E6-13606 Grants and cooperative agreements; availability, etc.: Homeless assistance; excess and surplus Federal properties, 47823 06-6934 Interior Interior Department See Fish and Wildlife Service See Land Management Bureau See National Park Service See Reclamation Bureau NOTICES Committees; establishment, renewal, termination, etc.:

Exxon Valdez Oil Spill Trustee Council, 47823-47824 06-7011 International International Trade Administration NOTICES Countervailing duties: Low-enriched uranium from— France, 47774-47775 E6-13683 Overseas trade missions: 2006 trade missions— Beijing and Shanghai, China; business development, 47775-47777 E6-13772 Justice Justice Department NOTICES Pollution control; consent judgments: A. Finkl & Sons Co., 47830 06-6993 Midland Refining Co. Inc., et al., 47830-47831 06-6992 Land Land Management Bureau NOTICES Coal leases, exploration licenses, etc.:

Montana, 47825-47826 E6-13608 Wyoming, 47826-47827 E6-13633 National Institute National Institute of Standards and Technology NOTICES Committees; establishment, renewal, termination, etc.: Malcolm Baldrige National Quality Award Board of Overseers, 47777 E6-13675 Malcolm Baldrige National Quality Award Judges Panel, 47777-47778 E6-13676 NIH National Institutes of Health NOTICES Meetings: National Cancer Institute, 06-7016 47816-47817 06-7017 06-7021 National Center on Minority Health and Health Disparities, 47817-47818 06-6999 National Eye Institute, 47818 06-7018 National Heart, Lung, and Blood Institute, 47818 06-6998 National Institute of Allergy and Infectious Diseases, 47820 06-7000 National Institute of Child Health and Human Development, 47821 06-7022 National Institute of Dental and Craniofacial Research, 47818-47819 06-6995 National Institute of Diabetes and Digestive and Kidney Diseases, 47820-47821 06-7019 National Institute of General Medical Sciences, 47819-47820 06-6997 National Institute on Deafness and Other Communication Disorders, 47819 06-6996 Recombinant DNA Advisory Committee, 47821 06-7020 National Labor National Labor Relations Board RULES Debt collection procedures, 47732-47737 E6-13688 NOAA National Oceanic and Atmospheric Administration NOTICES Endangered and threatened species permit applications, determinations, etc., 47778-47779 E6-13692 Meetings:

National Sea Grant Review Panel, 47779 E6-13696 Pacific albacore tuna fisheries; annual vessel list update, 47779-47780 E6-13693 National Park National Park Service NOTICES Environmental statements; availability, etc.: Lake Meredith National Recreation Area, TX, 47827 E6-13685 Native American human remains and associated funerary objects: Western Archeological and Conservation Center, Tuscon, AZ— Inventory from Cibola and McKinley Counties, NM, and Apache County, AZ; correction, 47827-47828 E6-13684 Native American human remains, funerary objects; inventory, repatriation, etc.:

Pacific Lutheran University, Tacoma, WA, 47828-47829 E6-13686 Thomas Burke Memorial, Washington State Museum, University of Washington, Seattle, WA, 47829 E6-13690 Reports and guidance documents; availability, etc.: Glen Canyon National Recreation Area; Comnet Four Corners, LLC; wireless telephone system installation and operation, 47829-47830 06-7025 Nuclear Nuclear Regulatory Commission PROPOSED RULES Rulemaking petitions: American National Standards N43.10 Committee, 47751-47752 E6-13632 NOTICES Regulatory guides; issuance, availability and withdrawal, 47831 E6-13635 *Applications, hearings, determinations, etc.:* STP Nuclear Operating Co., 47831 E6-13631 Reclamation Reclamation Bureau PROPOSED RULES Colorado River water in the lower basin; regulating non-contract use, 47763-47764 E6-13687 SEC Securities and Exchange Commission NOTICES Self-regulatory organizations; proposed rule changes:

American Stock Exchange LLC, 47831-47834 E6-13636 E6-13637 Chicago Board Options Exchange, Inc., 47834-47836 E6-13643 Chicago Stock Exchange, Inc., 47836-47850 E6-13618 National Association of Securities Dealers, Inc., 47850-47852 E6-13639 Options Clearing Corp., 47853-47856 E6-13616 E6-13617 Philadelphia Stock Exchange, Inc., 47856-47859 E6-13640 SBA Small Business Administration NOTICES Disaster loan areas: Alaska, 47859 E6-13645 Ohio, 47859 E6-13646 Meetings: National Advisory Council, 47859-47860 E6-13650 National Small Business Development Center Advisory Board, 47860 E6-13644 State State Department NOTICES Meetings:

Shipping Coordinating Committee, E6-13679 47860-47861 E6-13681 E6-13682 Presidential permit applications: TransCanada Keystone Pipeline, LP; pipeline facilities operation and maintenance at the U.S.-Canadian border, 47861 E6-13626 Thrift Thrift Supervision Office NOTICES Agency information collection activities; proposals, submissions, and approvals, 47866-47867 E6-13668 Transportation Transportation Department See Federal Aviation Administration See Federal Highway Administration See Federal Railroad Administration Treasury Treasury Department See Thrift Supervision Office NOTICES Agency information collection activities; proposals, submissions, and approvals, 47864-47865 E6-13610 E6-13612 Meetings:

Financial Literacy and Education Commission, 47865-47866 E6-13638 Veterans Veterans Affairs Department NOTICES Meetings: Veterans’ Disability Benefits Commission, 47867-47868 06-6991 Veterans’ Readjustment Advisory Committee, 47868 06-6994 Separate Parts In This Issue Part II Health and Human Services Department, Centers for Medicare & Medicaid Services, 47870-48351 06-6692 Part III Health and Human Services Department, Centers for Medicare & Medicaid Services, 48354-48434 06-6694 Part IV Education Department, 48436-48446 06-7030 06-7031 06-7032 Reader Aids Consult the Reader Aids section at the end of this issue for phone numbers, online resources, finding aids, reminders, and notice of recently enacted public laws.

To subscribe to the Federal Register Table of Contents LISTSERV electronic mailing list, go to http://listserv.access.gpo.gov and select Online mailing list archives, FEDREGTOC-L, Join or leave the list (or change settings); then follow the instructions. 71 160 Friday, August 18, 2006 Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2006-23884; Directorate Identifier 2006-CE-13-AD; Amendment 39-14726; AD 2006-17-05] RIN 2120-AA64 Airworthiness Directives;

Mitsubishi Heavy Industries MU-2B Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: The FAA adopts a new airworthiness directive

(AD)for all Mitsubishi Heavy Industries

(MHI)MU-2B series airplanes. This AD requires you to do flight checks of the rigging of the engine and propeller systems. This AD results from a recent safety evaluation that used a data-driven approach to evaluate the design, operation, and maintenance of the MU-2B series airplanes in order to determine their safety and define what steps, if any, are necessary for their safe operation. Part of that evaluation was the identification of unsafe conditions that exist or could develop on the affected type design airplanes. We are issuing this AD to detect and correct improper adjustment of the flight idle fuel flow setting. This condition, if uncorrected, could result in degraded performance and poor handling qualities with consequent loss of control of the airplane in certain situations. DATES: This AD becomes effective on September 22, 2006. As of September 22, 2006, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation. ADDRESSES: To get the service information identified in this AD, contact Mitsubishi Heavy Industries America, Inc., 4951 Airport Parkway, Suite 800, Addison, Texas 75001; telephone:

(972)934-5480; facsimile:

(972)934-5488. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-0001 or on the Internet at *http://dms.dot.gov* . The docket number is FAA-2006-23884; Directorate Identifier 2006-CE-13-AD. FOR FURTHER INFORMATION CONTACT: Rao Edupuganti, Aerospace Engineer, ASW-150, Fort Worth Aircraft Certification Office, 2601 Meacham Blvd., Fort Worth, Texas 76193; telephone:

(817)222-5284; facsimile:

(817)222-5960. SUPPLEMENTARY INFORMATION: Discussion On April 21, 2006, we issued a proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to all Mitsubishi Heavy Industries

(MHI)MU-2B series airplanes. This proposal was published in the **Federal Register** as a notice of proposed rulemaking

(NPRM)on April 28, 2006 (71 FR 25117). The NPRM proposed to require you to do flight checks of the rigging of the engine and propeller systems. Comments We provided the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal and FAA's response to each comment: Comment Issue No. 1: Revise the Manufacturer Contact Information Ralph Sorrells, Deputy General Manager of Mitsubishi Heavy Industries America, Inc., requests that we revise the manufacturer contact information from Mitsubishi Heavy Industries in Nagoya, Japan, to Mitsubishi Heavy Industries America, Inc. in Addison, Texas. We agree with the commenter and will incorporate the change into this final rule AD action. Comment Issue No. 2: Correct the Date of the Japanese AD Ralph Sorrells, Deputy General Manager of Mitsubishi Heavy Industries America, Inc., requests that we correct the date of Japanese AD No. TCD 4890-98 from October 7, 1998, to November 4, 1998. We agree with the commenter and will incorporate the change into this final rule AD action. Comment Issue No. 3: Remove Long-Body Models From Table 1, Paragraph (c)(1) The airplanes described in Table 1, paragraph (c)(1) are short-body airplanes. Models MU-2B-30, MU-2B-35, and MU-2B-36 are long-body airplanes. Ralph Sorrells, Deputy General Manager of Mitsubishi Heavy Industries America, Inc., requests that we remove reference of the long-body airplanes from Table 1, paragraph (c)(1). We agree with the commenter and will incorporate the change into this final rule AD action. Comment Issue No. 4: Remove the Requirement to Have the Flight Check Done by Two Individuals Richard W. Shine states that to require another pilot or mechanic to be on board in order to do the flight checks would require a specific flight just for that purpose. This requirement is unnecessarily burdensome and will add significant cost to their operation. The commenter states that he can and has successfully and safely performed the flight checks himself. He requests that we remove the two-person flight check requirement. We agree with the commenter that the flight checks required in paragraph

(e)of the proposed AD can safely be conducted with one rated pilot. This procedure is consistent with the referenced service bulletin and current practices. We inadvertently added the requirement for two individuals to do this check. We will incorporate the change into this final rule AD action and remove that requirement. Comment Issue No. 5: Add Procedures for Checking the Flight Idle Fuel Flow on the Ground Michael Machinski requests that we change the proposed AD to incorporate maintenance procedures for checking the flight idle fuel flow on the ground. We do not agree with the commenter. Doing the flight idle flow check in flight is consistent with the referenced service bulletins and current practices. The procedures in the service bulletins for doing this check have remained unchanged over the past 8 years. Those procedures have proven to be good and acceptable; therefore, we are not changing the final rule AD action based on this comment. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed except for the changes above and minor editorial corrections. We have determined that these changes and minor corrections: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Costs of Compliance We estimate that this AD affects 397 airplanes in the U.S. registry. We estimate the following costs to accomplish the initial flight check: Labor cost Parts cost Total cost per airplane Total cost on U.S. operators 1 work-hour × $80 per hour = $80 Not applicable $80 $31,760 The FAA is committed to updating the aviation community of expected costs associated with the MU-2B series airplane safety evaluation conducted in 2005. As a result of that commitment, the accumulating expected costs of all ADs related to the MU-2B series airplane safety evaluation may be found in the Final Report section at the following Web site: *http://www.faa.gov/aircraft/air_cert/design_approvals/small_airplanes/cos/mu2_foia_reading_library/.* 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 AD. 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 this AD: 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 other information as included in the Regulatory Evaluation) and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES. Include “Docket No. FAA-2006-23884; Directorate Identifier 2006-CE-13-AD” in your request. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, 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 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. FAA amends § 39.13 by adding a new AD to read as follows: **2006-17-05 Mitsubishi Heavy Industries:** Amendment 39-14726; Docket No. FAA-2006-23884; Directorate Identifier 2006-CE-13-AD. Effective Date

(a)This AD becomes effective on September 22, 2006. Affected ADs

(b)None. Applicability

(c)This AD affects the following airplane models and serial numbers that are certificated in any category: Table 1.—Applicability Type certificate Models Serial Nos.

(1)A2PC MU-2B, MU-2B-10, MU-2B-15, MU-2B-20, MU-2B-25, and MU-2B-26 008 through 312, 314 through 320, and 322 through 347.

(2)A2PC MU-2B-30, MU-2B-35, and MU-2B-36 501 through 651, 653 through 660, and 662 through 696.

(3)A10SW MU-2B-25, MU-2B-26, and MU-2B-26A, and MU-2B-40 313SA, 321SA, and 348SA through 459SA.

(4)A10SW MU-2B-35, MU-2B-36A, and MU-2B-60 652SA, 661SA, and 697SA through 1569SA. Unsafe Condition

(d)This AD results from a recent safety evaluation that used a data-driven approach to analyze the design, operation, and maintenance of the MU-2B series airplanes in order to determine their safety and define what steps, if any, are necessary for their safe operation. Part of that evaluation was the identification of unsafe conditions that exist or could develop on the affected type design airplanes. The actions specified in this AD are intended to detect and correct improper adjustment of the flight idle fuel flow setting. The above issue, if uncorrected, could result in degraded performance and poor handling qualities with consequent loss of control of the airplane in certain situations. Compliance

(e)To address this problem, you must do the following: Table 2.—Actions/Compliance/Procedures Actions Compliance Procedures Do flight checks of the rigging of the engine and propeller systems and make any necessary corrections. The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may do these actions. Make an entry into the aircraft logbook showing compliance with this portion of the AD in accordance with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9) Check within 100 hours time-in-service

(TIS)after September 22, 2006 (the effective date of this AD), and repetitively thereafter at intervals not to exceed 100 hours TIS. If any corrections are necessary, make the corrections before further flight *For airplanes listed in TCDS A2PC:* Follow MHI MV-2 Service Bulletin No. 234, dated October 7, 1998. *For airplanes listed in TCDS A10SW:* Follow MHI MV-2 Service Bulletin No. 097/73-001, dated July 24, 1998. Alternative Methods of Compliance (AMOCs)

(f)The Manager, Fort Worth ACO, FAA, ATTN: Rao Edupuganti, Aerospace Engineer, ASW-150, 2601 Meacham Blvd., Fort Worth, Texas 76193; telephone:

(817)222-5284; facsimile:

(817)222-5960, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information

(g)Japan Civil Aviation Bureau Airworthiness Directive No. TCD 4890-98, dated November 4, 1998; and MHI MV-2 Service Bulletins No. 234, dated October 7, 1998; and No. 097/73-001, dated July 24, 1998, also address the subject of this AD. Material Incorporated by Reference

(h)You must do the actions required by this AD following the instructions in Mitsubishi Heavy Industries MV-2 Service Bulletin No. 234, dated October 7, 1998; and Mitsubishi Heavy Industries MV-2 Service Bulletin No. 097/73-001, dated July 24, 1998. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of these service bulletins, contact Mitsubishi Heavy Industries America, Inc., 4951 Airport Parkway, Suite 800, Addison, Texas 75001; telephone:

(972)934-5480; facsimile:

(972)934-5488. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: *http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html* or call

(202)741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-0001 or on the Internet at *http://dms.dot.gov.* The docket number is FAA-2006-23884; Directorate Identifier 2006-CE-13-AD. Issued in Kansas City, Missouri, on August 11, 2006. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-13554 Filed 8-17-06; 8:45 am] BILLING CODE 4910-13-P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2006-23883; Directorate Identifier 2006-CE-12-AD; Amendment 39-14722; AD 2006-17-01] RIN 2120-AA64 Airworthiness Directives; Mitsubishi Heavy Industries MU-2B Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: The FAA adopts a new airworthiness directive

(AD)for all Mitsubishi Heavy Industries

(MHI)MU-2B series airplanes. This AD requires you to incorporate power assurance charts into the Limitations Section of the Airplane Flight Manual (AFM), inspect the engine torque indication system, and recalibrate the torque pressure transducers as required. This AD results from a recent safety evaluation that used a data-driven approach to analyze the design, operation, and maintenance of the MU-2B series airplanes in order to determine their safety and define what steps, if any, are necessary for their safe operation. Part of that evaluation was the identification of unsafe conditions that exist or could develop on the affected type design airplanes. We are issuing this AD to detect and correct torque transducers that are out of calibration. The above issue, if uncorrected, could result in degraded performance and poor handling qualities with consequent loss of control of the airplane in certain situations. DATES: This AD becomes effective on September 22, 2006. As of September 22, 2006, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation. ADDRESSES: To get the service information identified in this AD, contact Mitsubishi Heavy Industries America, Inc., 4951 Airport Parkway, Suite 800, Addison, Texas 75001; telephone:

(972)934-5480; facsimile:

(972)934-5488. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-0001 or on the Internet at *http://dms.dot.gov.* The docket number is FAA-2006-23883; Directorate Identifier 2006-CE-12-AD. FOR FURTHER INFORMATION CONTACT: Rao Edupuganti, Aerospace Engineer, ASW-150, Fort Worth Aircraft Certification Office, 2601 Meacham Blvd., Fort Worth, Texas 76193; telephone:

(817)222-5284; facsimile:

(MHI)MU-2B series airplanes. This proposal was published in the **Federal Register** as a notice of proposed rulemaking

(NPRM)on April 28, 2006 (71 FR 25120). The NPRM proposed to detect and correct torque transducers that are out of calibration. The above issue, if uncorrected, could result in degraded performance and poor handling qualities with consequent loss of control of the airplane in certain situations. Comments We provided the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal and FAA's response to each comment: Comment Issue No. 1: Revise the Manufacturer Contact Information Ralph Sorrells, Deputy General Manager of Mitsubishi Heavy Industries America, Inc., requests that we revise the manufacturer contact information from Mitsubishi Heavy Industries in Nagoya, Japan, to Mitsubishi Heavy Industries America, Inc. in Addison Texas. We agree with the commenter and will incorporate the change into this final rule AD action. Comment Issue No. 2: Correct the Date of the Japanese AD Ralph Sorrells, Deputy General Manager of Mitsubishi Heavy Industries America, Inc., requests that we correct the date of Japanese AD No. TCD 4889-98 from October 7, 1998, to November 5, 1998. We agree with the commenter and will incorporate the change into this final rule AD action. Comment Issue No. 3: Remove Long-Body Models From Table 1, Paragraph (c)(1) The airplanes described in Table 1, paragraph (c)(1) are short-body airplanes. Models MU-2B-30, MU-2B-35, and MU-2B-36 are long-body airplanes. Ralph Sorrells, Deputy General Manager of Mitsubishi Heavy Industries America, Inc., requests that we remove reference of the long-body airplanes from Table 1, paragraph (c)(1). We agree with the commenter and will incorporate the change into this final rule AD action. Comment Issue No. 4: Add the Following Rows to TABLE 3.—AFM INSERTION PAGES: Ralph Sorrells, Deputy General Manager of Mitsubishi Heavy Industries America, Inc., request that we add the following rows to TABLE 3.—AFM INSERTION PAGES: MU-2B-25 AFM, Section 6, Revision 9, dated January 14, 1999 6-19 MU-2B-26 AFM, Section 6, Revision 9, dated January 14, 1999 6-19 MU-2B-35 AFM, Section 6, Revision 10, dated January 14, 1999 6-19 We agree with the commenter and will incorporate the change into this final rule AD action. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed except for the changes above and minor editorial corrections. We have determined that these changes and minor corrections: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Costs of Compliance We estimate that this AD affects 397 airplanes in the U.S. registry. We estimate the following costs to accomplish the inspection: Labor cost Parts cost Total cost per airplane Total cost on U.S. operators 5 work-hours × $80 = $400 Not applicable $400 $158,800 The FAA is committed to updating the aviation community of expected costs associated with the MU-2B series airplane safety evaluation conducted in 2005. As a result of that commitment, the accumulating expected costs of all ADs related to the MU-2B series airplane safety evaluation may be found in the Final Report section at the following Web site: *http://www.faa.gov/aircraft/air_cert/design_approvals/small_airplanes/cos/mu2_foia_reading_library/.* 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 AD. 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 this AD: 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 other information as included in the Regulatory Evaluation) and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES. Include “Docket No. FAA-2006-23883; Directorate Identifier 2006-CE-12-AD” in your request. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, 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 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. FAA amends § 39.13 by adding a new AD to read as follows: **2006-17-01 Mitsubishi Heavy Industries:** Amendment 39-14722; Docket No. FAA-2006-23883; Directorate Identifier 2006-CE-12-AD. Effective Date

(a)This AD becomes effective on September 22, 2006. Affected ADs

(b)None. Applicability

(c)This AD affects the following airplane models and serial numbers that are certificated in any category: Table 1.—Applicability Type certificate Models Serial Nos.

(1)A2PC MU-2B, MU-2B-10, MU-2B-15, MU-2B-20, MU-2B-25, and MU-2B-26 008 through 312, 314 through 320, and 322 through 347.

(2)A2PC MU-2B-30, MU-2B-35, and MU-2B-36 501 through 651, 653 through 660, and 662 through 696.

(3)A10SW MU-2B-25, MU-2B-26, MU-2B-26A, and MU-2B-40 313SA, 321SA, and 348SA through 459SA.

(4)A10SW MU-2B-35, MU-2B-36, MU-2B-36A, and MU-2B-60 652SA, 661SA, and 697SA through 1569SA. Unsafe Condition

(d)This AD is the result of a recent safety evaluation that used a data-driven approach to analyze the design, operation, and maintenance of the MU-2B series airplanes in order to determine their safety and define what steps, if any, are necessary for their safe operation. Part of that evaluation was the identification of unsafe conditions that exist or could develop on the affected type design airplanes. The actions specified in this AD are intended to detect and correct torque transducers that are out of calibration. The above issue, if uncorrected, could result in degraded performance and poor handling qualities and lead to loss of control of the airplane in certain situations. Compliance

(e)To address this problem, you must do the following: Table 2.—Actions/Compliance/Procedures Actions Compliance Procedures

(1)Incorporate the following pages from the Airplane Flight Manual

(AFM)charts listed in TABLE 3.—AFM INSERTION PAGES, paragraph

(f)of this AD, into the Limitations Section of the FAA-approved AFM Within 100 hours time-in-service

(TIS)after September 22, 2006 (the effective date of this AD) The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may do the flight manual changes requirement of this AD. Make an entry into the aircraft records showing compliance with this portion of the AD in accordance with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9).

(2)Inspect the engine torque indication system and recalibrate the torque pressure transducers as required. This inspection requires the use of the power assurance charts referenced in paragraph (e)(1) of this AD and in TABLE 3, paragraph

(f)of this AD Within 100 hours TIS after September 22, 2006 (the effective date of this AD)

(i)For airplanes listed in Type Certificate No. A2PC follow Mitsubishi Heavy Industries, Ltd.

(MHI)MV-2 Service Bulletin No. 233A, dated January 14, 1999.

(ii)For airplanes listed Type Certificate No. A10SW follow MHI Service Bulletin No. MV-2 095/77-002, dated July 15, 1998.

(f)Use the following power assurance charts when doing the ground check portion of the inspection required in paragraph (e)(2) of this AD. Table 3.—AFM Insertion Pages Model of airplane affected Date and version of AFM Page number from AFM

(i)MU-2B AFM, Section 6, Revision 9, dated January 14, 1999 6-34.

(ii)MU-2B-15 AFM, Section 6, Revision 9, dated January 14, 1999 6-19.

(iii)MU-2B-20 AFM, Section 6, Revision 9, dated January 14, 1999 6-20.

(iv)MU-2B-25 AFM, Section 6, Reissued March 25, 1986; and AFM, Section 6, Revision 9, dated January 14, 1999 6-18 and 6-19 6-19.

(v)MU-2B-26 AFM, Section 6, Reissued March 25, 1986; and AFM, Section 6, Revision 9, dated January 14, 1999 6-17 and 6-18 6-19.

(vi)MU-2B-26A AFM, Section 6, Reissued March 25, 1986 6-17 and 6-18.

(vii)MU-2B-35 AFM, Section 6, Reissued March 25, 1986; and AFM, Section 6, Revision 9, dated January 14, 1999 6-18 and 6-19 6-19.

(viii)MU-2B-36A AFM, Section 6, Reissued February 28, 1986 6-20 and 6-21.

(ix)MU-2B-40 AFM, Section 6, Reissued March 25, 1986 6-17 and 6-18.

(x)MU-2B-60 AFM, Section 6, Reissued September 24, 1985 6-19 and 6-20.

(xi)MU-2B-10 AFM, Section 6, Revision 9, dated January 14, 1999 6-19.

(xii)MU-2B-30 AFM, Section 6, Revision 10, dated January 14, 1999 6-19.

(xiii)MU-2B-36 AFM, Section 6, Revision 9, dated January 14, 1999 6-20. Note: AFM, Section 6, Reissued March 25, 1986 (FAA-approved) TCDS A10SW. AFM, Section 6, Revision 9 and Revision 10, dated January 14, 1999 (JCAB-approved). Alternative Methods of Compliance (AMOCs)

(g)The Manager, Fort Worth Aircraft Certification Office, FAA, ATTN: Rao Edupuganti, Aerospace Engineer, ASW-150, Fort Worth ACO, 2601 Meacham Blvd., Fort Worth, Texas 76193; telephone:

(817)222-5284; facsimile:

(817)222-5960, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information

(h)Japan Civil Aviation Bureau Airworthiness Directive No. TCD 4889-98, dated November 5, 1998, also addresses the subject of this AD. Material Incorporated by Reference

(i)You must do the actions required by this AD following the instructions in Mitsubishi Heavy Industries, Ltd. MV-2 Service Bulletins No. 233A, dated January 14, 1999; and No. 095/77-002, dated July 15, 1998. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact Mitsubishi Heavy Industries America, Inc., 4951 Airport Parkway, Suite 800, Addison, Texas 75001; telephone:

(972)934-5480; facsimile:

(202)741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-0001 or on the Internet at *http://dms.dot.gov* . The docket number is FAA-2006-23883; Directorate Identifier 2006-CE-12-AD. Issued in Kansas City, Missouri, on August 9, 2006. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-13441 Filed 8-17-06; 8:45 am] BILLING CODE 4910-13-P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2006-24253; Directorate Identifier 2006-CE-23-AD; Amendment 39-14723; AD 2006-17-02] RIN 2120-AA64 Airworthiness Directives; GROB-WERKE GMBH & CO KG Model G102 ASTIR CS Sailplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: The FAA supersedes Airworthiness Directive

(AD)84-09-05, which applies to certain GROB-WERKE GMBH & CO KG (previously identified as BURKHART-GROB FLUGZEUGBAU INDUSTRIESTRABE) Model G102 ASTIR CS sailplanes. AD 84-09-05 requires you to install a modified spherical locking bolt and nut in the forward horizontal stabilizer connection to the vertical stabilizer and install new locking pins in the aft connecting plate for the horizontal stabilizer. Since we issued AD 84-09-05, fatigue cracks were found in the modified spherical locking bolt. Consequently, this AD requires you to replace the modified spherical locking bolt, the retaining pins (collar bolts), and associated hardware; add a life limit on the spherical locking bolt and the retaining pins; and repetitively inspect the front and rear horizontal stabilizer attachment. This AD results from mandatory continuing airworthiness information

(MCAI)issued by the airworthiness authority for Germany. We are issuing this AD to prevent cracks in the spherical locking bolt, which could result in failure of the horizontal stabilizer connection. This failure could lead to loss of control. DATES: This AD becomes effective on September 22, 2006. As of September 22, 2006, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation. ADDRESSES: For service information identified in this AD, contact GROB Luft-und Raumfahrt, Lettenbachstrasse 9, D-86874 Tussenhausen-Mattsies, Federal Republic of Germany; telephone: 011 49 8268 998139; fax: 011 49 8268 998200; e-mail: *productsupport@grob-aerospace.de.* To view the AD docket, go to the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-0001 or on the Internet at *http://dms.dot.gov.* The docket number is FAA-2006-24253; Directorate Identifier 2006-CE-23-AD. FOR FURTHER INFORMATION CONTACT: Gregory A. Davison, Aerospace Engineer, ACE-112, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone:

(816)329-4130; facsimile:

(816)329-4090. SUPPLEMENTARY INFORMATION: Discussion On May 30, 2006, we issued a proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to certain GROB-WERKE GMBH & CO KG (previously identified as BURKHART-GROB FLUGZEUGBAU INDUSTRIESTRABE) Model G102 ASTIR CS sailplanes. This proposal was published in the **Federal Register** as a notice of proposed rulemaking

(NPRM)on June 6, 2006 (71 FR 32484). The NPRM proposed to supersede AD 84-09-05 with a new AD that would require you to do the following: • Remove the existing spherical locking bolt, nut, retaining pins (collar bolts), self-locking nut, and the lock washer; and replace with a new spherical locking bolt, P/N 102-3500.21, that has revision letter “b” permanently marked on the bottom of the bolt, a new nut, P/N 102-3510.21, new retaining pins (collar bolts), P/N 102-2142.46, a new self-locking nut, P/N LN9348-M8, and a new lock washer, P/N DIN 6797-10,5PHR; • Add a life limit on the new spherical locking bolt and the retaining pins; and • Inspect (repetitively) the front and rear horizontal stabilizer attachment assembly after the initial replacements. Comments We provided the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal and FAA's response to each comment: Comment Issue No. 1: Address the Intent of the AD as It Affects Parts Manufacturer Approval

(PMA)Alternatives to the Original Equipment Manufacturer

(OEM)Part The Modification and Replacement Parts Association (MARPA) provides comments to the mandatory continuing airworthiness information

(MCAI)AD process pertaining to how the FAA addresses PMA parts. The commenter would like to see the FAA more fully address the intent of the AD as it affects PMA alternatives to the unsafe OEM part. We acknowledge the need to ensure that unsafe parts are identified and addressed in MCAI-related ADs. For this AD, we use the phrase “or FAA-approved equivalent part number” to address the PMA issue. We are currently examining all aspects of this issue, including input from industry. Once we have made a final determination, we will consider how our policy regarding PMA parts in ADs needs to be revised. We consider that to delay this AD action would be inappropriate since we have determined that an unsafe condition exists and that replacement of certain parts must be accomplished to ensure continued safety. We have not changed the final rule AD action based on this comment. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed except for minor editorial corrections. We have determined that these minor corrections: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Differences Between This AD and the Service Information The service information specifies using a 20X magnifying glass for doing the inspections. This AD specifies using a dye penetrant method and a 10X magnifying glass for doing the inspections. This difference is because 20X magnifiers are not readily available in the field. The requirements of this AD take precedence over the provisions in the service information. Costs of Compliance We estimate that this AD will affect 56 sailplanes in the U.S. registry. We estimate the following costs to do the replacements: Labor cost Parts cost Total cost for each sailplane Total cost on U.S. operators 2 work-hours × $80 per hour = $160 $253 $413 $23,128 We estimate the following costs to do each inspection: Labor cost Parts cost Total cost for each sailplane Total cost on U.S. operators 2 work-hours × $80 per hour = $160 Not applicable $160 $8,960 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 AD. 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 this AD: 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 other information as included in the Regulatory Evaluation) and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES. Include “Docket No. FAA-2006-24253; Directorate Identifier 2006-CE-23-AD” in your request. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, 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 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. FAA amends § 39.13 by removing Airworthiness Directive

(AD)84-09-05, Amendment 39-4849, and adding the following new AD: **2006-17-02 GROB-WERKE GMBH & CO KG (previously identified as BURKHART-GROB FLUGZEUGBAU INDUSTRIESTRABE):** Amendment 39-14723; Docket No. FAA-2006-24253; Directorate Identifier 2006-CE-23-AD. Effective Date

(a)This AD becomes effective on September 22, 2006. Affected ADs

(b)This AD supersedes 84-09-05, Amendment 39-4849. Applicability

(c)This AD affects Model G102 ASTIR CS sailplanes, serial numbers 1001 through 1536, that are certificated in any category. Unsafe Condition

(d)This AD results from mandatory continuing airworthiness information

(e)To address this problem, you must do the following: Actions Compliance Procedures

(1)Remove and replace as follows:

(i)Remove the existing retaining pins (collar bolts) and the self-locking nut and replace with new retaining pins, part numbers (P/N) 102-2142.46, and self-locking nut, P/N LN9348-M8 (or FAA-approved equivalent part numbers), on the T-plate;

(ii)Remove the existing spherical locking bolt and replace with a new spherical locking bolt, P/N 102-3500.21, that has revision letter “b” permanently marked on the bottom of the bolt (or FAA-approved equivalent part number). Return replaced spherical locking bolts, P/N 102-3500.21, to Grob Systems, Inc., Aircraft Division, 1070 Navajo Drive, Bluffton, Ohio 45817; Within the next 90 days after September 22, 2006 (the effective date of this AD), unless already done. After doing the replacements, the spherical locking bolt and the retaining pins have a life limit of 10 years and must be replaced at that time As specified in GROB Service Bulletin MSB306-38/1, dated November 28, 2005, following the Accomplishment Instructions in GROB Service Bulletin MSB306-38, dated February 12, 2004, and the Annual Inspection procedures on pages 7 and 8 of the Astir CS Maintenance Manual, Rev. 9, dated Nov. 2005.

(iii)Remove the existing nut and replace with a new nut, 102-3510.21 (or FAA-approved equivalent part number); and

(iv)Remove the existing lock washer and replace with a new lock washer, P/N DIN 6797-10,5PHR (or FAA-approved equivalent part number)

(2)Using a dye-penetrant method along with a minimum 10X magnifying glass, repetitively inspect the front and rear horizontal stabilizer attachment assembly for excessive movement, cracks, and/or damage in the spherical locking bolt. This inspection method takes precedence over the procedures outlined in GROB Service Bulletin MSB306-38, dated February 12, 2004 Initially inspect within the next 100 hours time-in-service

(TIS)or at the next annual inspection after the replacement required in paragraph (e)(1) of this AD, whichever occurs first. Repetitively inspect thereafter at 12-month intervals or at intervals not to exceed 100 hours TIS, whichever occurs first As specified in GROB Service Bulletin MSB306-38/1, dated November 28, 2005, following the Accomplishment Instructions in GROB Service Bulletin MSB306-38, dated February 12, 2004, and the Annual Inspection procedures on pages 7 and 8 of the Astir CS Maintenance Manual, Rev. 9, dated Nov. 2005.

(3)If, during any inspection required in paragraph (e)(2) of this AD, you find excessive movement:

(i)In the front horizontal stabilizer attachment, you must replace the spherical locking bolt with a new part. Before further flight after each inspection required in paragraph (e)(2) of this AD. After each replacement, the spherical locking bolt and the retaining pins have a life limit of 10 years and must be replaced at that time As specified in GROB Service Bulletin MSB306-38/1, dated November 28, 2005, following the Accomplishment Instructions in GROB Service Bulletin MSB306-38, dated February 12, 2004, and the Annual Inspection procedures on pages 7 and 8 of the Astir CS Maintenance Manual, Rev. 9, dated Nov. 2005.

(ii)In the rear horizontal stabilizer attachment, you must replace the retaining pins with new parts

(iii)In the front and rear horizontal stabilizer attachment after doing the replacement(s) required in paragraph (e)(3)(i) and (e)(3)(ii) of this AD, you must replace the bearings in the stabilizer spar web

(4)If, during any inspection required in paragraph (e)(2) of this AD, you do not find excessive movement in the front and rear horizontal stabilizer attachment:

(i)Inspect the spherical locking bolt for cracks and damage using a dye-penetrant method along with a minimum 10X magnifying glass

(ii)If you find cracks or damage on the spherical locking bolt, during the inspection required in paragraph (e)(4)(i) of this AD, you must replace the bolt with a new bolt Before further flight after each inspection required in paragraph (e)(2) of this AD. After each replacement, the spherical locking bolt and the retaining pins have a life limit of 10 years and must be replaced at that time As specified in GROB Service Bulletin MSB306-38/1, dated November 28, 2005, following the Accomplishment Instructions in GROB Service Bulletin MSB306-38, dated February 12, 2004, and the Annual Inspection procedures on pages 7 and 8 of the Astir CS Maintenance Manual, Rev. 9, dated Nov. 2005.

(5)Do not install any spherical locking bolt, P/N 102-3500.21 (or FAA-approved equivalent part number), that does not have revision letter “b” permanently marked on the bottom of the bolt As of September 22, 2006 (the effective date of this AD) Not applicable.

(6)14 CFR 21.303 allows for replacement parts through parts manufacturer approval (PMA). The phrase “or FAA-approved equivalent part number” in this AD is intended to signify those parts that are PMA parts approved through identicality to the design of the part under the type certificate and replacement parts to correct the unsafe condition under PMA (other than identicality). If parts are installed that are identical to the unsafe parts, then the corrective actions of the AD affect these parts also. In addition, equivalent replacement parts to correct the unsafe condition under PMA (other than identicality) may also be installed provided they meet current airworthiness standards, which include those actions cited in this AD Not applicable Not applicable. Note: During ground handling, it has been noted that a tendency exists for the ground crew to move these gliders by using the horizontal stabilizer as a lifting point. This practice may facilitate damage to the stabilizer assembly and should be avoided. See Caution note in GROB Service Bulletin MSB306-38, dated February 12, 2004. Alternative Methods of Compliance (AMOCs)

(f)The Manager, Standards Office, Small Airplane Directorate, FAA, ATTN: Gregory A. Davison, Aerospace Engineer, ACE-112, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone:

(816)329-4130; facsimile:

(816)329-4090, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19.

(g)AMOCs approved for AD 84-09-05 are not approved for this AD. Related Information

(h)German AD Number D-2004-168, dated March 23, 2004, also addresses the subject of this AD. Material Incorporated by Reference

(i)You must do the actions required by this AD following the instructions in GROB Service Bulletin MSB306-38, dated February 12, 2004, and GROB Service Bulletin MSB306-38/1, dated November 28, 2005. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact GROB Luft-und Raumfahrt, Lettenbachstrasse 9, D-86874 Tussenhausen-Mattsies, Federal Republic of Germany; telephone: 011 49 8268 998139; fax: 011 49 8268 998200; e-mail: *productsupport@grob-aerospace.de.* To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: *http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html* or call

(202)741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-0001 or on the Internet at * http:// dms.dot.gov. * The docket number is FAA-2006-24253; Directorate Identifier 2006-CE-23-AD. Issued in Kansas City, Missouri, on August 9, 2006. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-13439 Filed 8-17-06; 8:45 am] BILLING CODE 4910-13-P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2006-23889; Directorate Identifier 2005-NM-252-AD; Amendment 39-14714; AD 2006-16-14] RIN 2120-AA64 Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: The FAA is adopting a new airworthiness directive

(AD)for certain Airbus Model A318, A319, A320, and A321 airplanes. This AD requires inspecting to determine the part number of the twin motor actuators, and related investigative and corrective actions if necessary. This AD results from a report of a low pressure valve of the twin motor actuator found partially open, although the valve detection system indicated that the valve was closed. Investigation revealed that the locating pin in the actuator was too short to engage with the valve slot, resulting in incorrect alignment of the actuator and the drive assembly, causing the valve to remain partially open. We are issuing this AD to ensure that, in the event of an engine fire, the valve actuator functions properly to block the fuel flow to the engine and prevent an uncontrollable fire. DATES: This AD becomes effective September 22, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of September 22, 2006. ADDRESSES: You may examine the AD docket on the Internet at *http://dms.dot.gov* or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-5356; telephone

(425)227-2125; fax

(425)227-1149. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the AD docket on the Internet at *http://dms.dot.gov* or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone

(800)647-5227) is located on the plaza level of the Nassif Building at the street address stated in the ADDRESSES section. Discussion The FAA issued a supplemental notice of proposed rulemaking

(NPRM)to amend 14 CFR part 39 to include an AD that would apply to certain Airbus Model A318, A319, A320, and A321 airplanes. That supplemental NPRM was published in the **Federal Register** on May 18, 2006 (71 FR 28825). That supplemental NPRM proposed to require inspecting to determine the part number of the twin motor actuators, and related investigative and corrective actions if necessary. That supplemental NPRM also proposed to revise the original NPRM by expanding the applicability. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the single comment received. Request To Add Revised Service Information to Applicability Section Airbus advises that the service bulletin specified in the supplemental NPRM has been revised. Airbus notes that Airbus Service Bulletin A320-28-1122, Revision 01, including Appendix 01, dated April 11, 2006 (the original issue of the service bulletin was referenced in the supplemental NPRM for accomplishing the specified actions), changes the recommended status of the original issue to mandatory in Revision 01. We agree with Airbus. We have reviewed Revision 01 of the service bulletin and note that it does not necessitate additional work. We have revised paragraph

(f)of the AD to reflect Revision 01 of the service bulletin. In addition, we have added a new paragraph

(g)to this AD specifying that accomplishing the actions specified in paragraph

(f)of the AD in accordance with the original issue of the service bulletin is considered to be an acceptable method of compliance. Subsequent paragraphs of the AD have been re-identified accordingly. Conclusion We have carefully reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD with the changes described previously. These changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance This AD affects about 763 airplanes of U.S. registry. The inspection takes about 1 work hour per airplane, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost of this AD on U.S. operators is $61,040, or $80 per airplane. 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 this AD:

(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. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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. The Federal Aviation Administration

(FAA)amends § 39.13 by adding the following new airworthiness directive (AD): **2006-16-14 Airbus:** Amendment 39-14714. Docket No. FAA-2006-23889; Directorate Identifier 2005-NM-252-AD. Effective Date

(a)This AD becomes effective September 22, 2006. Affected ADs

(b)None. Applicability

(c)This AD applies to Airbus Model A318, A319, A320, and A321 airplanes, certificated in any category, except airplanes having manufacturer serial numbers

(MSN)2155 and subsequent. Unsafe Condition

(d)This AD results from a report of a low pressure valve of the twin motor actuator found partially open, although the valve detection system indicated that the valve was closed. Investigation revealed that the locating pin in the actuator was too short to engage with the valve slot, resulting in incorrect alignment of the actuator and the drive assembly, causing the valve to remain partially open. We are issuing this AD to ensure that, in the event of an engine fire, the valve actuator functions properly to block the fuel flow to the engine and prevent an uncontrollable fire. Compliance

(e)You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Inspection/Related Investigative and Corrective Actions

(f)Within 6,000 flight hours or 24 months after the effective date of this AD, whichever is first: Inspect to determine the part number (P/N) of the twin motor actuators in accordance with Airbus Service Bulletin A320-28-1122, Revision 01, including Appendix 01, dated April 11, 2006.

(1)For airplanes having any actuator with P/N FRH010041 or P/N FRH010034, no further action is required by this paragraph.

(2)For airplanes having any actuator with P/N HTE190001-2, where the actuator serial number is not identified in Appendix 01 of the service bulletin, no further action is required by this paragraph.

(3)For airplanes having any actuator with P/N HTE190001 or HTE190001-1, do all applicable related investigative and corrective actions before further flight, in accordance with the service bulletin.

(4)For airplanes have any actuator with P/N HTE190001-2, where the actuator serial number is identified in Appendix 01 of the service bulletin, do all applicable related investigative and corrective actions before further flight, in accordance with the service bulletin. Note 1: Airbus Service Bulletin A320-28-1122, Revision 01, dated April 11, 2006, refers to FR-HiTEMP Service Bulletin HTE190001-28-003, dated March 30, 2004, as an additional source of service information for determining the P/N of the twin motor actuators and accomplishing any related investigative and corrective actions. Acceptable for Compliance

(g)Accomplishment of the actions required by paragraph

(f)of this AD before the effective date of this AD in accordance with Airbus Service Bulletin A320-28-1122, including Appendix 01, dated November 19, 2004, is acceptable for compliance with the requirements of that paragraph. Parts Installation

(h)As of the effective date of this AD: No person may install an actuator with P/N HTE190001, HTE190001-1, or HTE190001-2, and a serial number identified in Appendix 01 of Airbus Service Bulletin A320-28-1122, Revision 01, dated April 11, 2006, on any airplane unless all applicable related investigative and corrective actions have been done in accordance with the requirements of paragraph (f)(3) of this AD. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19.

(2)Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information

(j)French airworthiness directive F-2005-189, dated November 23, 2005, also addresses the subject of this AD. Material Incorporated by Reference

(k)You must use Airbus Service Bulletin A320-28-1122, Revision 01, including Appendix 01, dated April 11, 2006, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL-401, Nassif Building, Washington, DC; on the Internet at *http://dms.dot.gov* ; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call

(202)741-6030, or go to *http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html* . Issued in Renton, Washington, on August 3, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-13445 Filed 8-17-06; 8:45 am] BILLING CODE 4910-13-P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2006-23850; Directorate Identifier 2005-NM-126-AD; Amendment 39-14715; AD 2006-16-15] RIN 2120-AA64 Airworthiness Directives; McDonnell Douglas Model MD-10-10F and MD-10-30F Airplanes and Model MD-11 and MD-11F Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to certain McDonnell Douglas Model MD-11 series airplanes. That AD currently requires a revision of the airplane flight manual

(AFM)to alert the flightcrew that both flight management computers

(FMCs)must be installed and operational. That AD also requires an inspection to determine the serial number of the FMCs; and follow- on corrective actions, if necessary, which terminate the AFM revision. That AD also requires an inspection to verify if a certain modification is on the identification plates of the FMCs; and applicable follow-on and corrective actions. This new AD requires installation of upgraded FMC software, which would terminate the existing AD. This new AD also adds airplanes to the applicability, including adding Model MD-10-10F and MD-10-30F airplanes. This AD results from a report that the FMC does not acknowledge the pre-set glareshield control panel

(GCP)altitude when profile

(PROF)mode is engaged in descent mode. We are issuing this AD to prevent the un-commanded descent of an airplane below the selected level-off altitude, which could result in an unacceptable reduction in the separation between the airplane and nearby air traffic or terrain. DATES: This AD becomes effective September 22, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of September 22, 2006. On November 26, 2001 (66 FR 53335, October 22, 2001), the Director of the Federal Register approved the incorporation by reference of McDonnell Douglas Service Bulletin MD11-34-085, Revision 01, dated September 20, 1999. ADDRESSES: You may examine the AD docket on the Internet at *http://dms.dot.gov* or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC. Contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1-L5A (D800-0024), for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Natalie Phan-Tran, Aerospace Engineer, Systems and Equipment Branch, ANM-130L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; telephone

(562)627-5343; fax

(562)627-5210. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive

(AD)docket on the Internet at *http://dms.dot.gov* or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone

(800)647-5227) is located on the plaza level of the Nassif Building at the street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking

(NPRM)to amend 14 CFR part 39 to include an AD that supersedes AD 2001-21-05, amendment 39-12476 (66 FR 53335, October 22, 2001). The existing AD applies to certain McDonnell Douglas Model MD-11 series airplanes. That NPRM was published in the **Federal Register** on February 15, 2006 (71 FR 7880). That NPRM proposed to retain all requirements of AD 2001-21-05 and require installation of upgraded flight management computer

(FMC)software, which would terminate the existing AD. That NPRM also proposed to add airplanes to the applicability, including adding Model MD-10-10F and MD-10-30F airplanes. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments that have been received on the NPRM. Support for NPRM The Air Line Pilots Association supports the NPRM. Request To Supersede AD 2001-21-05 and AD 2004-18-04 UPS requests that the NPRM be rewritten to supersede both AD 2001-21-05 and AD 2004-18-04, amendment 39-13782 (69 FR 53794, September 21, 2004), and allow compliance by installing FMCs part number (P/N) 4059050-921 in accordance with Boeing Service Bulletin MD11-34-129, dated September 22, 2004. We acknowledge the commenter's request; however we do not agree that this AD should supersede both ADs. This AD is a supersedure of AD 2001-21-05 and does allow compliance by installing FMC P/N 4059050-921. As specified in paragraphs (j)(2), (j)(3), and (j)(4) of this AD, operators that install FMC P/N 4059050-921 must do so in accordance with Boeing Service Bulletin MD11-34-129, dated September 22, 2004, and as specified in paragraph

(j)of this AD, doing the installation is terminating action for the requirements of paragraphs

(f)through

(i)of this AD (paragraphs

(f)through

(i)are a restatement of the requirements of AD 2001-21-05). This AD does not supersede AD 2004-18-04 because that AD contains requirements for airplanes that are not in the applicability of this AD. AD 2004-18-04 is applicable to all McDonnell Douglas Model MD-10-10F, MD-10-30F, MD-11, MD-11F, and 717-200 airplanes. This AD is applicable only to certain Model MD-10-10F and MD-10-30F airplanes and all Model MD-11 and MD-11F airplanes. However, as specified in paragraph (n)(4) of this AD, doing the applicable software/hardware upgrades required by paragraph

(j)or

(k)of this AD is approved as an alternative method of compliance for the actions required by AD 2004-18-04. We have not revised this AD in this regard. Request To Clarify That Airplanes Having FMC P/N 4059050-921 Installed Are Not Applicable to the NPRM The same commenter requests that the NPRM be clarified to indicate that it is not effective for any airplanes that already have P/N 4059050-921 installed. We disagree with the commenter that this AD is not applicable to airplanes that already have P/N 4059050-921 installed. This AD is applicable to all Model MD-11 and MD-11F airplanes and certain Model MD-10-10F and MD-10-30F airplanes and requires installation of upgraded FMC software. For Model MD-11 and MD-11F airplanes, installing P/N 4059050-921 is an acceptable method of compliance with paragraph

(j)of this AD. As specified in paragraph

(e)of this AD, if the actions have already been done, then operators are in compliance with the applicable requirements of this AD. We have not revised this AD in this regard. Request To Clarify That Any FMC P/N 4059050-921 Is Acceptable Regardless of Origin The same commenter requests that the NPRM be clarified to specify that any FMC P/N 4059050-921 is acceptable for compliance with the NPRM regardless of the origin of the part (original manufacture, factory conversion, or on-aircraft conversion). We agree with the commenter that any FMC P/N 4059050-921 is acceptable for compliance. Paragraphs (j)(2), (j)(3), and (j)(4) of this AD specify installing FMC P/N 4059050-921 in accordance with the service information specified in those paragraphs. Any FMC P/N 4059050-921 regardless of its origin is acceptable provided it is installed in accordance with the service information. No change is necessary. If operators install P/N 4059050-921 in accordance with a method that is not specified in the service information identified in this AD, operators must request approval of an alternate of method of compliance as specified in paragraph

(n)of this AD. Clarification of Service Bulletin Date In the NPRM, we inadvertently referred to the date of Boeing Service Bulletin MD11-34-068, Revision 3, as April 6, 2004. The correct date is April 6, 2005. We have revised this AD accordingly. Conclusion We have carefully reviewed the available data, including the comments that have been submitted, and determined that air safety and the public interest require adopting the AD with the change described previously. We have determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance There are about 230 airplanes of the affected design in the worldwide fleet and about 117 U.S.-registered airplanes. The following table provides the estimated costs for U.S. operators to comply with this AD. The average labor rate per hour is $65. Estimated Costs Action Work hours Parts Cost per airplane Number of U.S.-registered airplanes Fleet cost Airplane Flight Manual Revision, Inspections and Software Installation (required by AD 2001-21-05) 2 $0 $130 59 $7,670 Upgrade Software/Hardware (new action) 2 0 130 117 15,210 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 this AD:

(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

(FAA)amends § 39.13 by removing amendment 39-12476 (66 FR 53335, October 22, 2001) and by adding the following new airworthiness directive (AD): **2006-16-15 McDonnell Douglas:** Amendment 39-14715. Docket No. FAA-2006-23850; Directorate Identifier 2005-NM-126-AD. Effective Date

(a)This AD becomes effective September 22, 2006. Affected ADs

(b)This AD supersedes AD 2001-21-05. Applicability

(c)This AD applies to McDonnell Douglas airplanes, as specified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category.

(1)Model MD-10-10F and MD-10-30F airplanes, as identified in Boeing Service Bulletin MD10-31-053, Revision 1, dated June 14, 2005.

(2)All Model MD-11 and MD-11F airplanes. Unsafe Condition

(d)This AD results from a report that the flight management computer

(FMC)does not acknowledge the pre-set glareshield control panel

(GCP)altitude when profile

(e)You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Restatement of Requirements of AD 2001-21-05 Airplane Flight Manual

(AFM)Revision

(f)For MD-11 and MD-11F airplanes having manufacturer's fuselage numbers 0447 through 0552 inclusive, and 0554 through 0621 inclusive: Within 5 days after May 20, 1998 (the effective date of AD 98-10-01, amendment 39-10512), revise Section 1, page 5-1, of the Limitations Section of the FAA-approved AFM to include the following statement. This may be accomplished by inserting a copy of this AD into the AFM. “Prior to dispatch of the airplane, both Flight Management Computer 1 (FMC-1) and FMC-2 must be installed and operational.” Inspection

(g)For MD-11 and MD-11F airplanes having manufacturer's fuselage numbers 0447 through 0552 inclusive, and 0554 through 0621 inclusive: Within 90 days after November 26, 2001 (the effective date of AD 2001-21-05), do an inspection to verify that modification “AS” is on the front and rear identification plates of FMC-1 and FMC-2, per McDonnell Douglas Service Bulletin MD11-34-085, Revision 01, dated September 20, 1999. After the inspection has been done, the AFM revision required by paragraph

(f)of this AD may be removed from the AFM. Condition 1 (Modification “AS” Is Installed)

(h)If modification “AS” is found installed during the inspection required by paragraph

(g)of this AD, before further flight, do the actions specified in paragraphs (h)(1) and (h)(2) of this AD, per McDonnell Douglas Service Bulletin MD11-34-085, Revision 01, dated September 20, 1999.

(1)Do a test of the FMCs in the flight compartment to ensure that modification “AS” is operational, and do applicable corrective actions, if necessary. Both FMCs must have modification “AS” installed and pass the test before loading new software per paragraph (h)(2) of this AD.

(2)Install new software and reidentify FMC-1 and FMC-2 as part number (P/N) 4059050-912. Note 1: McDonnell Douglas Service Bulletin MD11-34-085, Revision 01, dated September 20, 1999, references Honeywell Service Bulletin 4059050-34-6020, Revision 1, dated April 30, 1999, as an additional source of service information for the installation and reidentification requirements of paragraphs (h)(2) and (i)(2) of this AD. Condition 2 (Modification “AS” Is Not Installed)

(i)If modification “AS” is NOT found installed during the inspection required by paragraph

(g)of this AD, before further flight, do the actions specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD, per McDonnell Douglas Service Bulletin MD11-34-085, Revision 01, dated September 20, 1999.

(1)Remove FMC-1 and FMC-2.

(2)Install modification “AS” and new software, and reidentify FMC-1 and FMC-2 as P/N 4059050-912.

(3)Install modified and reidentified FMC-1 and FMC-2. New Requirements of This AD Upgrade Software/Hardware—Model MD-11 and MD-11F Airplanes

(j)For Model MD-11 and MD-11F airplanes: Within 18 months after the effective date of this AD, upgrade the FMC software, and hardware as applicable, by doing the applicable actions specified in paragraph (j)(1), (j)(2), (j)(3), or (j)(4) of this AD. Doing this upgrade terminates the requirements of paragraphs

(f)through

(i)of this AD.

(1)For airplanes on which FMC P/N 4059050-906 through -912 is installed: Install new software in the main avionics rack, and reidentify FMC-1 and FMC-2 as P/N 4059050-913, in accordance with the Accomplishment Instructions of Boeing Service Bulletin MD11-34-130, dated March 16, 2005. Note 2: Boeing Service Bulletin MD11-34-130 refers to Honeywell Alert Service Bulletin 4059050-34-A6024, dated March 9, 2005, as an additional source of service information for doing the actions specified in paragraph (j)(1) of this AD.

(2)For airplanes on which FMC P/N 4059050-920 is installed: Install new software in the main avionics rack, and reidentify FMC-1 and FMC-2 as P/N 4059050-921, in accordance with the Accomplishment Instructions of Boeing Service Bulletin MD11-34-129, dated September 22, 2004. Note 3: Boeing Service Bulletin MD11-34-129 refers to Honeywell Alert Service Bulletin 4059050-34-A6023, dated September 22, 2004, as an additional source of service information for doing the actions specified in paragraph (j)(2) of this AD.

(3)For airplanes on which FMC P/N 4059050-906 through -911 is installed: In lieu of doing the software upgrade specified in paragraph (j)(1) of this AD, install new hardware and software and reidentify FMC-1 and FMC-2 as P/N 4059050-921, by doing all the applicable actions specified in the Accomplishment Instructions of McDonnell Douglas Service Bulletin MD11-34-085, Revision 01, dated September 20, 1999; Boeing Service Bulletin MD11-34-068, Revision 3, dated April 6, 2005; and Boeing Service Bulletin MD11-34-129, dated September 22, 2004. Note 4: McDonnell Douglas Service Bulletin MD11-34-085 references Honeywell Service Bulletin 4059050-34-6020, Revision 1, dated April 30, 1999; Boeing Service Bulletin MD11-34-068 references Honeywell Service Bulletin 4059050-34-0010, dated March 19, 2003; and Boeing Service Bulletin MD11-34-129 refers to Honeywell Alert Service Bulletin 4059050-34-A6023, dated September 22, 2004; as additional sources of service information for doing the actions specified in paragraph (j)(3) of this AD.

(4)For airplanes on which FMC P/N 4059050-912 is installed: In lieu of doing the software upgrade specified in paragraph (j)(1) of this AD, install new hardware and software and reidentify FMC-1 and FMC-2 as P/N 4059050-921, by doing all the applicable actions specified in the Accomplishment Instructions of Boeing Service Bulletin MD11-34-068, Revision 3, dated April 6, 2005; and Boeing Service Bulletin MD11-34-129, dated September 22, 2004. Note 5: Boeing Service Bulletin MD11-34-068 references Honeywell Service Bulletin 4059050-34-0010, dated March 19, 2003; and Boeing Service Bulletin MD11-34-129 refers to Honeywell Alert Service Bulletin 4059050-34-A6023, dated September 22, 2004; as additional sources of service information for doing the actions specified in paragraph (j)(4) of this AD. Upgrade Software—Model MD-10-10F and MD-10-30F Airplanes

(k)For Model MD-10-10F and MD-10-30F airplanes: Within 18 months after the effective date of this AD, install new software in the main avionics rack and reidentify the versatile integrated avionics

(VIA)digital computer as P/N 4081580-903, in accordance with the Accomplishment Instructions of Boeing Service Bulletin MD10-31-053, Revision 1, dated June 14, 2005. Note 6: Boeing Service Bulletin MD10-31-053 refers to Honeywell Alert Service Bulletin 4081580-31-A6002, dated January 14, 2005, as an additional source of service information for doing the actions specified in paragraph

(k)of this AD. Parts Installation

(l)For Model MD-11 and MD-11F airplanes: As of the effective date of this AD, no person may install an FMC, P/N 4059050-906 through -912, or -920, on any airplane; except as required by the actions specified in paragraphs (h), (i), and

(j)of this AD.

(m)For MD-10-10F and MD-10-30F airplanes: As of the effective date of this AD, no person may install a VIA digital computer, P/N 4081580-901 or 4081580-902, on any airplane. Alternative Methods of Compliance (AMOCs) (n)(1) The Manager, Los Angeles Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19.

(3)AMOCs approved previously in accordance with AD 2001-21-05 are approved as AMOCs for the corresponding provisions of paragraphs

(f)through

(i)of this AD.

(4)Doing the actions required by paragraph

(j)or

(k)of this AD, as applicable, is approved as an AMOC for the actions required by AD 2004-18-04, amendment 39-13782. Material Incorporated by Reference

(o)You must use the applicable service bulletins listed in Table 1 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. Table 1.—All Material Incorporated by Reference Service Bulletin Revision level Date Boeing Service Bulletin MD10-31-053 1 June 14, 2005. Boeing Service Bulletin MD11-34-068 3 April 6, 2005. Boeing Service Bulletin MD11-34-129 Original September 22, 2004. Boeing Service Bulletin MD11-34-130 Original March 16, 2005. McDonnell Douglas Service Bulletin MD11-34-085 01 September 20, 1999.

(1)The Director of the Federal Register approved the incorporation by reference of the documents listed in Table 2 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Table 2.—New Material Incorporated by Reference Service Bulletin Revision level Date Boeing Service Bulletin MD10-31-053 1 June 14, 2005. Boeing Service Bulletin MD11-34-068 3 April 6, 2005. Boeing Service Bulletin MD11-34-129 Original September 22, 2004. Boeing Service Bulletin MD11-34-130 Original March 16, 2005.

(2)On November 26, 2001 (66 FR 53335, October 22, 2001), the Director of the Federal Register approved the incorporation by reference of McDonnell Douglas Service Bulletin MD11-34-085, Revision 01, dated September 20, 1999.

(3)Contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1-L5A (D800-0024), for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL-401, Nassif Building, Washington, DC; on the Internet at *http://dms.dot.gov;* or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call

(202)741-6030, or go to *http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.* Issued in Renton, Washington, on August 3, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-13448 Filed 8-17-06; 8:45 am] BILLING CODE 4910-13-P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2006-25262; Directorate Identifier 2006-CE-39-AD; Amendment 39-14725; AD 2006-17-04] RIN 2120-AA64 Airworthiness Directives; The Cessna Aircraft Company Models 172R, 172S, 182T, T182T, 206H, and T206H Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. SUMMARY: The FAA is adopting a new airworthiness directive

(AD)for certain The Cessna Aircraft Company (Cessna) Models 172R, 172S, 182T, T182T, 206H, and T206H airplanes. This AD requires you to inspect the two end fittings on each of the flexible fuel hoses located in the engine compartment for the correct torque values, and, if any incorrect torque values are found during the inspection, tighten the hose end fittings to the correct torque values. This AD results from one report of loose fuel hose connections to the fuel injector servo on a Cessna Model 172S airplane. We are issuing this AD to detect and correct any incorrect torque values of the end fittings of flexible fuel hoses in the engine compartment, which could result in the loss of fuel flow and fuel leakage. Loss of fuel flow could result in partial or complete loss of engine power and fuel leakage could result in an engine compartment fire. DATES: This AD becomes effective on September 1, 2006. As of September 1, 2006, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation. We must receive any comments on this AD by October 17, 2006. ADDRESSES: Use one of the following addresses to comment on this AD. • *DOT Docket Web site:* Go to *http://dms.dot.gov* and follow the instructions for sending your comments electronically. • *Government-wide rulemaking Web site:* Go to *http://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. To get the service information identified in this AD, contact The Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277-7706; telephone:

(316)517-5800; facsimile:

(316)942-9006. To view the comments to this AD, go to *http://dms.dot.gov.* The docket number is FAA-2006-25262; Directorate Identifier 2006-CE-39-AD. FOR FURTHER INFORMATION CONTACT: Jeff Janusz, Aerospace Engineer, FAA, Wichita ACO, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone:

(316)946-4148; facsimile:

(316)946-4107. SUPPLEMENTARY INFORMATION: Discussion We have received one report of loose fuel hose connections to the fuel injector servo on a Cessna Model 172S airplane. This condition, if not corrected, could result in the loss of fuel flow and fuel leakage. Loss of fuel flow could result in partial or complete loss of engine power and fuel leakage could result in an engine compartment fire. Relevant Service Information We reviewed Cessna Service Bulletin No. SB06-71-02, dated June 19, 2006. The service information describes procedures for inspecting the two end fittings on each of the flexible fuel hoses located in the engine compartment for the correct torque values, and, if any incorrect torque values are found during the inspection, tighten the hose end fittings to the correct torque values. FAA's Determination and Requirements of This AD We are issuing this AD because we evaluated all the information and determined the unsafe condition described previously is likely to exist or develop on other products of the same type design. This AD requires you to do the actions in the referenced service bulletin. In preparing this rule, we contacted type clubs and aircraft operators to get technical information and information on operational and economic impacts. We did not receive any information through these contacts. If received, we would have included a discussion of any information that may have influenced this action in the rulemaking docket. FAA's Determination of the Effective Date Since an unsafe condition exists that requires the immediate adoption of this AD, we determined that notice and opportunity for public comment before issuing this AD are impracticable, and that good cause exists for making this amendment effective in fewer than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and an opportunity for public comment. We invite you to send any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number “FAA-2006-25262; Directorate Identifier 2006-CE-39-AD” at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD. We will consider all comments received by the closing date and may amend the AD in light of those comments. We will post all comments we receive, without change, to *http://dms.dot.gov,* including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive concerning this AD. 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 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 this AD:

(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. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. Examining the AD Docket You may examine the AD docket that contains the AD, the regulatory evaluation, any comments received, and other information on the Internet at *http://dms.dot.gov;* or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone

(800)647-5227) is located at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): **2006-17-04 The Cessna Aircraft Company:** Amendment 39-14725; Docket No. FAA-2006-25262; Directorate Identifier 2006-CE-39-AD. Effective Date

(a)This AD becomes effective on September 1, 2006. Affected ADs

(b)None. Applicability

(c)This AD affects the following airplane models and serial numbers that are certificated in any category: Table 1.—Applicability and Airplane Groups Group Model Serial Nos.

(1)Group 1 Airplanes: All models *not* equipped with the Garmin G1000 System

(i)172R

(ii)172S 17281244 through 17281334. 172S9809 through 172S10219.

(iii)182T 18281527 through 18281832.

(iv)T182T T18208381 through T18208583.

(v)206H 20608231 through 20608265.

(vi)T206H T20608515 through T20608635.

(2)Group 2 Airplanes: All models equipped with the Garmin G1000 System

(i)172R

(ii)172S 17281244 through 17281334. 172S9809 through 172S10219.

(iii)182T 18281527 through 18281832.

(iv)T182T T18208381 through T18208583.

(v)206H 20608231 through 20608265.

(vi)T206H T20608515 through T20608635. Unsafe Condition

(d)This AD is the result of one report of loose fuel hose connections to the fuel injector servo on a Cessna Aircraft Company Model 172S airplane. We are issuing this AD to detect and correct any incorrect torque values of the end fittings of flexible fuel hoses in the engine compartment, which could result in the loss of fuel flow and fuel leakage. Loss of fuel flow could result in partial or complete loss of engine power and fuel leakage could result in an engine compartment fire. Compliance

(e)*For Group 1 Airplanes not equipped with the Garmin G1000 System:* To address this problem, you must do the following: Table 2.—Actions, Compliance, and Procedures for Group 1 Airplanes Actions Compliance Procedures

(1)Inspect the two end fittings on each of the following hoses in the engine compartment for the correct torque values

(i)Fuel strainer to engine fuel pump.

(ii)Engine fuel pump to fuel injector server (except T206).

(iii)T206 only: Engine fuel pump to the union at the aft vertical cooling baffle.

(iv)T206 only: Union at the aft vertical cooling baffle to the fuel injector servo.

(v)Fuel injector servo to fuel manifold valve (except turbo models).

(vi)Turbo models only: Fuel injector servo to fuel flow transducer.

(vii)Turbo models only: Fuel flow transducer to fuel manifold valve.

(viii)Fuel injector servo return to firewall fitting. Within the next 5 hours time-in-service

(TIS)after September 1, 2006 (the effective date of this AD), on airplanes that have not had a 100-hour or annual inspection of the engine installation fuel hoses for security and tightness of the end fittings Follow Cessna Service Bulletin No. SB06-71-02, dated June 19, 2006.

(2)If any incorrect torque values are found during the inspection required by paragraph (e)(1) of this AD, clean and dry the threads of all fittings, and tighten the hose end fittings to the correct torque values as defined in Table 4 Before further flight after the inspection required by paragraph (e)(1) of this AD, in which any incorrect torque values are found Follow Cessna Service Bulletin No. SB06-71-02, dated June 19, 2006.

(f)*For Group 2 Airplanes equipped with the Garmin G1000 System:* To address this problem, you must do the following: Table 3.—Actions, Compliance, and Procedures for Group 2 Airplanes Actions Compliance Procedures

(1)Inspect the two end fittings on each of the following hoses in the engine compartment for the correct torque values

(i)Fuel strainer to engine fuel pump.

(ii)Engine fuel pump to fuel injector servo (except T206).

(iii)T206 only: Engine fuel pump to the union at the aft vertical cooling baffle. Within the next 5 hours TIS after September 1, 2006 (the effective date of this AD), on airplanes that have not had a 100-hour or annual inspection of the engine installation fuel hoses for security and tightness of the end fittings Follow Cessna Service Bulletin No. SB06-71-02, dated June 19, 2006.

(iv)T206 only: Union at the aft vertical cooling baffle to the fuel injector servo.

(v)Fuel injector servo to fuel flow transducer.

(vi)Fuel flow transducer to fuel manifold valve.

(vii)Fuel injector servo return to firewall fitting.

(2)If any incorrect torque values are found during the inspection required by paragraph (f)(1) of this AD, clean and dry the threads of all fittings, and tighten the hose end fittings to the correct torque values as defined in Table 4 Before further flight after the inspection required by paragraph (f)(1) of this AD, in which any incorrect torque values are found Follow Cessna Service Bulletin No. SB06-71-02, dated June 19, 2006.

(g)Use the following table for the correct torque values to tighten the hose end fittings as required in paragraphs (e)(2) and (f)(2) of this AD: Table 4.—Torque Values for Hose End Fittings Flare hex sizes in fractions of an inch Hose size Correct torque in inch-pounds Minimum Maximum 9/16 −4 135 150 11/16 −6 270 300 7/8 −8 450 500 Alternative Methods of Compliance (AMOCs)

(h)The Manager, Wichita Aircraft Certification Office (ACO), FAA, ATTN: Jeff Janusz, Aerospace Engineer, FAA, Wichita ACO, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone:

(316)946-4148; facsimile:

(316)946-4107, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Material Incorporated by Reference

(i)You must do the actions required by this AD following the instructions in Cessna Service Bulletin No. SB06-71-02, dated June 19, 2006. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact The Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277-7706; telephone:

(316)517-5800; facsimile:

(316)942-9006. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: *http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html* or call

(202)741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-0001 or on the Internet at *http://dms.dot.gov.* The docket number is FAA-2006-25262; Directorate Identifier 2006-CE-39-AD. Issued in Kansas City, Missouri, on August 9, 2006. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-13442 Filed 8-17-06; 8:45 am] BILLING CODE 4910-13-P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2006-24641; Directorate Identifier 2006-CE-27-AD; Amendment 39-14724; AD 2006-17-03] RIN 2120-AA64 Airworthiness Directives; Stemme GmbH & Co. KG Models S10, S10-V, and S10-VT Sailplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: The FAA adopts a new airworthiness directive

(AD)for certain Stemme GmbH & Co. KG (Stemme) Models S10, S10-V, and S10-VT sailplanes. This AD requires you to inspect the connection between the aileron push-rod and the connecting shaft to determine if a safety washer is installed. If there is no safety washer installed, this AD requires you to modify the aileron control assembly. This AD results from mandatory continuing airworthiness information

(MCAI)issued by the airworthiness authority for Germany. We are issuing this AD to prevent a loose bearing in the aileron control lever, which could result in separation of the aileron control system. Separation of the aileron control system could lead to loss of aileron control. DATES: This AD becomes effective on September 22, 2006. As of September 22, 2006, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation. ADDRESSES: To get the service information identified in this AD, contact STEMME AG, Flugplatzstraβe F 2, Nr. 7, D-15344 Strausberg, Germany; telephone: + 49.33.41/36 12-0; facsimile: + 49.33.41/36 12-30; e-mail: *P.Ellwanger@stemme.de.* To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-001 or on the Internet at *http://dms.dot.gov.* The docket number is FAA-2006-24641; Directorate Identifier 2006-CE-27-AD. FOR FURTHER INFORMATION CONTACT: Gregory A. Davison, Aerospace Engineer, ACE-112, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone:

(816)329-4130; facsimile:

(816)329-4090. SUPPLEMENTARY INFORMATION: Discussion On May 24, 2006, we issued a proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to certain Stemme Models S10, S10-V, and S10-VT sailplanes. This proposal was published in the **Federal Register** as a notice of proposed rulemaking

(NPRM)on June 2, 2006 (71 FR 31980). The NPRM proposed to require you to inspect the joint between the aileron control rod, part number (P/N) 10SQ-RMB, and the connecting shaft, P/N 10SQ-RMW, to determine if a safety washer is installed. If a safety washer is not installed, the NPRM proposed to require you to modify this area by replacing the joint bolt (P/N LN9037-06042), installing a safety washer (P/N D440-06), and installing washer (P/N 10M-282). Comments We provided the public the opportunity to participate in developing this AD. We received no comments on the proposal or on the determination of the cost to the public. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed except for minor editorial corrections. We have determined that these minor corrections: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Costs of Compliance We estimate that this AD will affect 105 sailplanes in the U.S. registry. We estimate the following costs to do the inspection: Labor cost Parts cost Total cost per sailplane Total cost on U.S. operators 1 work-hour × $80 per hour = $80 N/A $80 105 × $80 = $8,400 We estimate the following costs to do any necessary replacements that will be required based on the results of the inspection. We have no way of determining the number of sailplanes that may need this replacement: Labor cost Parts cost Total cost per sailplane 2 work-hours × $80 per hour = $160 $30 $160 + $30 = $190 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 AD. 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 this AD: 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 other information as included in the Regulatory Evaluation) and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES . Include “Docket No. FAA-2006-24641; Directorate Identifier 2006-CE-27-AD” in your request. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, 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 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. FAA amends § 39.13 by adding a new AD to read as follows: **2006-17-03 Stemme GmbH & Co. KG:** Amendment 39-14724; Docket No. FAA-2006-24641; Directorate Identifier 2006-CE-27-AD. Effective Date

(a)This AD becomes effective on September 22, 2006. Affected ADs

(b)None.

(c)This AD affects the following sailplane models and serial numbers that are certificated in any category: Model Serial Nos. S10 10-03 through 10-56. S10-V 14-001 through 14-030 (including all converted versions 14-003M through 14-056M). S10-VT 11-001 through 11-089. Unsafe Condition

(d)This AD results from mandatory continuing airworthiness information

(e)To address this problem, you must do the following: Actions Compliance Procedures

(1)Inspect the joint between the aileron control rod, part number (P/N) 10SQ-RMB (or FAA-approved equivalent part number), and the connecting shaft, P/N 10SQ-RMW (or FAA-approved equivalent part number), to determine if a safety washer, P/N DIN 440-06 (or FAA-approved equivalent part number), is installed Within the next 20 hours time-in-service after September 22, 2006 (the effective date of this AD) Follow Stemme Service Bulletin Document Number: A31-10-069, Am.-Index 01.a, dated September 10, 2004

(2)If after the inspection required in paragraph (e)(1) of this AD, you can positively determine that a safety washer, P/N DIN 440-06 (or FAA-approved equivalent part number), is installed between the joint in the aileron control rod and the connecting shaft, no further action is required Not applicable Not applicable

(3)If after the inspection required in paragraph (e)(1) of this AD, you cannot positively determine that a safety washer is installed between the joint in the aileron control rod and the connecting shaft, do the following Before further flight after the inspection required in paragraph (e)(1) of this AD Follow Stemme Service Bulletin Document Number: A31-10-069, Am.-Index 01.a, dated September 10, 2004.

(i)Install a safety washer, P/N DIN 440-06 (or FAA-approved equivalent part number);

(ii)Replace the existing bolt with bolt, P/N LN9037-06042 (or FAA-approved equivalent part number), from the modification kit; and

(iii)Install washer, P/N 10M-282 (or FAA-approved equivalent part number)

(4)14 CFR 21.303 allows for replacement parts through parts manufacturer approval (PMA). The phrase “or FAA-approved equivalent part number” in this AD is intended to signify those parts that are PMA parts approved through identicality to the design of the part under the type certificate and replacement parts to correct the unsafe condition under PMA (other than identicality). If parts are installed that are identical to the unsafe parts, then the corrective actions of the AD affect these parts also. In addition, equivalent replacement parts to correct the unsafe condition under PMA (other than identicality) may also be installed provided they meet current airworthiness standards, which include those actions cited in this AD Not applicable Not applicable. Alternative Methods of Compliance (AMOCs)

(816)329-4130; facsimile:

(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)German AD Number D-2004-443, dated September 27, 2004, addresses the subject of this AD. Material Incorporated by Reference

(h)You must do the actions required by this AD following the instructions in Stemme Service Bulletin Document Number: A31-10-069, Am.-Index 01.a, dated September 10, 2004. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact STEMME AG, Flugplatzstraβe F 2, Nr. 7, D-15344 Strausberg, Germany; telephone: + 49.33.41 / 36 12-0; facsimile: + 49.33.41 / 36 12-30. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: *http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html* or call

(202)741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-0001 or on the Internet at *http://dms.dot.gov.* The docket number is FAA-2006-24641; Directorate Identifier 2006-CE-27-AD. Issued in Kansas City, Missouri, on August 9, 2006. John R. Colomy, Acting Manager, Small Airplane Directorate,Aircraft Certification Service. [FR Doc. E6-13440 Filed 8-17-06; 8:45 am] BILLING CODE 4910-13-P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 2004-NE-05-AD; Amendment 39-14706; AD 2006-16-06] RIN 2120-AA64 Airworthiness Directives; General Electric Company

(GE)CF6-80 Series Turbofan Engines AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. SUMMARY: The FAA is superseding an existing airworthiness directive

(AD)for GE CF6-80 series turbofan engines with certain stage 1 high-pressure turbine

(HPT)rotor disks. That AD currently requires an initial inspection as a qualification for the mandatory rework procedures for certain disks, and repetitive inspections only for certain disks for which the rework procedures were not required. That action also requires reworking certain disks before further flight, and removes certain CF6-80E1 series disks from service. This AD requires the same actions but shortens the compliance schedule for HPT disks that have not been previously inspected using AD 2004-04-07, which this AD supersedes. This AD results from a recent report of an uncontained failure of a stage 1 HPT disk. We are issuing this AD to detect and prevent cracks in the bottoms of the dovetail slots that could propagate to failure of the disk and cause an uncontained engine failure. DATES: Effective September 5, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of September 5, 2006. The Director of the Federal Register previously approved the incorporation by reference of certain other publications listed in the regulations as of March 12, 2004 (69 FR 8801, February 26, 2004). We must receive any comments on this AD by October 17, 2006. ADDRESSES: Use one of the following addresses to submit comments on this ad: • By mail: Federal Aviation Administration (FAA), New England Region, Office of the Regional Counsel, Attention: Rules Docket No. 2004-NE-05-AD, 12 New England Executive Park, Burlington, MA 01803. • By fax:

(781)238-7055. • By e-mail: *9-ane-adcomment@faa.gov.* Contact General Electric Company via Lockheed Martin Technology Services, 10525 Chester Road, Suite C, Cincinnati, Ohio 45215, telephone

(513)672-8400, fax

(513)672-8422, for the service information identified in this AD. You may examine the AD docket, by appointment, at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA. You may examine the service information, by appointment, at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA. FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone:

(781)238-7176, fax:

(781)238-7199. SUPPLEMENTARY INFORMATION: On February 13, 2004, we issued AD 2004-04-07, Amendment 39-13488 (69 FR 38; February 26, 2004). That AD requires an initial inspection as a qualification for the mandatory rework procedures for certain disks, and repetitive inspections only for certain disks for which the rework procedures were not required. That action also requires reworking certain disks before further flight. That AD was the result of the manufacturer's investigation and development of a rework procedure to chamfer the aft breakedge of the dovetail slot bottom to reduce stresses. That condition, if not corrected, could result in cracks in the bottoms of the dovetail slots that could propagate to failure of the disk and cause an uncontained engine failure. Actions Since AD 2004-04-07 Was Issued Since AD 2004-04-07 was issued, a CF6-80A turbofan engine, installed on a Boeing 767 airplane, experienced an uncontained stage 1 HPT disk failure on June 2, 2006. The disk failure resulted in a fire and significant damage to the airplane. The event occurred during an on-ground maintenance operation. Relevant Service Information We reviewed and approved the technical contents of the following GE Service Bulletins

(SBs)and Alert Service Bulletin

(ASB)that describe procedures for removing, inspecting, and reworking certain stage 1 HPT rotor disks: • SB No. CF6-80E1 S/B 72-0251, dated January 22, 2004; • SB No. CF6-80A S/B 72-0779, Revision 1, dated January 22, 2004; • SB No. CF6-80A S/B 72-0788, Revision 3, dated July 20, 2006; • SB No. CF6-80A S/B 72-0822, dated July 20, 2006; • ASB No. CF6-80C2 S/B 72-A1026, Revision 2, dated January 22, 2004; • SB No. CF6-80C2 S/B 72-1089, Revision 3, dated July 20, 2006; • SB No. CF6-80C2 S/B 72-1217, dated July 20, 2006. FAA's Determination and Requirements of This AD The unsafe condition described previously is likely to exist or develop on other GE CF6-80 series turbofan engines of the same type design. This AD requires rework of the dovetail slot bottom of certain stage 1 rotor disks. The disks must pass an inspection to qualify for the rework. This AD also requires removal from service of certain disks for which the rework procedures were not previously required. This AD also tightens the compliance schedule for HPT disks that have not been previously inspected using AD 2004-04-07. Operators must use the compliance schedule carried forward from AD 2004-04-07 or the new compliance schedule below, whichever occurs first: • For stage 1 HPT rotor disks with 9,000 or more cycles-since-new

(CSN)on the effective date of this AD, within 250 cycles-in-service

(CIS)after the effective date of this AD, or by March 31, 2007, whichever occurs first. • For stage 1 HPT rotor disks with 6,900 or more but fewer than 9,000 CSN on the effective date of this AD, within 500 CIS after the effective date of this AD, or before accumulating 9,250 CSN, or by December 31, 2007, whichever occurs first. • For stage 1 HPT rotor disk with fewer than 6,900 CSN on the effective date of this AD, before accumulating 7,400 CSN, or by December 31, 2008, whichever occurs first. This AD also removes from service certain CF6-80E1 series disks. You must use the service information described previously to perform the actions required by this AD. FAA's Determination of the Effective Date Since an unsafe condition exists that requires the immediate adoption of this AD, we have found that notice and opportunity for public comment before issuing this AD are impracticable, and that good cause exists for making this amendment effective in less than 30 days. 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 submit any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES . Include “AD Docket No. 2004-NE-05-D” in the subject line of your comments. If you want us to acknowledge receipt of your mailed comments, send us a self-addressed, stamped postcard with the docket number written on it; we will date-stamp your postcard and mail it back to you. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify it. If a person contacts us verbally, and that contact relates to a substantive part of this AD, we will summarize the contact and place the summary in the docket. We will consider all comments received by the closing date and may amend the AD in light of those comments. Examining the AD Docket You may examine the AD Docket (including any comments and service information), by appointment, between 8 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. See ADDRESSES for the location. 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 by sending a request to us at the address listed under ADDRESSES . Include “AD Docket No. 2004-NE-05-AD” in your request. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, 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 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. The FAA amends § 39.13 by removing Amendment 39-13488 (69 FR 8801; February 26, 2004), and by adding a new airworthiness directive, Amendment 39-14706, to read as follows: **2006-16-06 General Electric Company:** Amendment 39-14706. Docket No. 2004-NE-05-AD. Effective Date

(a)This airworthiness directive

(AD)becomes effective September 5, 2006. Affected ADs

(b)This AD supersedes AD 2004-04-07 (69 FR 8801; February 26, 2004). Applicability

(c)This AD applies to the General Electric Company

(GE)CF6-80 turbofan engine models listed in the following Table 1: Table 1.—Applicability Models, Part Numbers, Airplanes Models Stage 1 high pressure turbine

(HPT)rotor disk part numbers (P/Ns) Engines installed on but not limited to CF6-80A, CF6-80A1, CF6-80A2, CF6-80A3 9234M67G22/G24/G25/G26, 9362M58G02/G06/G07/G09, 9367M45G02/G04/G09 Airbus A310 and Boeing 767 airplanes. CF6-80C2A1, CF6-80C2A2, CF6-80C2A3, CF6-80C2A5, CF6-80C2A8, CF6-80C2A5F, CF6-80C2B1, CF6-80C2B2, CF6-80C2B4, CF6-80C2B6, CF6-80C2B1F, CF6-80C2B2F, CF6-80C2B4F, CF6-80C2B5F, CF6-80C2B6F, CF6-80C2B6FA, CF6-80C2B7F, CF6-80C2D1F 1862M23G01, 9392M23G10/G12/G21, 1531M84G02/G06/G08/G10/G12 Airbus A300, A310, Boeing 747, 767, and McDonnell Douglas MD11 airplanes. CF6-80E1A2, CF6-80E1A4 1639M41P04 Airbus A330 airplanes. These engines are installed on, but not limited to, the airplanes listed in Table 1 of this AD. Unsafe Condition

(d)This AD results from a recent report of an uncontained failure of a stage 1 HPT disk. The actions specified in this AD are intended to detect and prevent cracks in the bottoms of the dovetail slots that could propagate to failure of the disk and cause an uncontained engine failure. Compliance

(e)You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. CF6-80A, -80A1, -80A2, and -80A3 Engines Stage 1 HPT Rotor Disks, P/N 9362M58G09, With Chamfered Breakedges

(f)At the next piece-part exposure, for stage 1 HPT rotor disks, P/N 9362M58G09, with serial numbers

(SNs)listed in Table 2 of this AD, do the following, unless already done using superseded AD 2004-04-07: Table 2.—SNs of CF6-80A Series Stage 1 HPT Rotor Disk P/N 9362M58G09—With Chamfered Breakedges GWN03RD7 GWN03TKG GWN03TKH GWN03TKJ GWN03W3M GWN03W3N GWN03W3R GWN042J3 GWN04FW2 GWN04FW3 GWN04FW4 GWN04FW5 GWN04H0M GWN04HRA GWN04HRD GWN04HRE GWN04HRF GWN04HRG GWN04HRH GWN04K8N GWN04M9J GWN04M9K GWN04M9L GWN04M9M GWN04M9R GWN04M9T GWN04M9W

(1)Visually inspect the rotor disks for the presence of a chamfer on the aft breakedges of the dovetail slot bottoms. Use paragraph 3.A. of GE Service Bulletin

(SB)No. CF6-80A S/B 72-0822, dated July 20, 2006, to do the inspection.

(2)For disks that have the chamfered breakedges, re-mark, fluorescent penetrant inspect (FPI), and eddy current inspect

(ECI)the rotor disk. Use paragraph 3.A.(1) of the Accomplishment Instructions of GE SB No. CF6-80A S/B 72-0822, dated July 20, 2006, to re-mark and inspect the rotor disk and remove from service as necessary.

(3)For disks that do not have the chamfered breakedges, remove the disk from service. Use paragraph 3.A(2) of the Accomplishment Instructions of GE SB No. CF6-80A S/B 72-0822, dated July 20, 2006. Stage 1 HPT Rotor Disks, P/Ns 9234M67G22, G24, G25, G26, 9367M45G04, G09, 9362M58G02, G06, G07, and 9362M58G09 with SNs not listed in Table 2 of this AD

(g)For stage 1 HPT rotor disks, P/Ns 9234M67G22, G24, G25, G26, 9367M45G04, G09, 9362M58G02, G06, G07, and 9362M58G09 with SNs not listed in Table 2 of this AD, inspect, rework, and re-mark the disks using paragraphs 3.A.(1) through 3.A.(2) of Accomplishment Instructions of GE SB No. CF6-80A S/B 72-0788, Revision 3, dated July 20, 2006, at the following, unless already done using superseded AD 2004-04-07:

(1)For both new and used stage 1 HPT rotor disks not installed in engines, inspect, rework, re-mark, and remove from service as necessary before further flight.

(2)For stage 1 HPT rotor disks that have been inspected using any version of GE SB No. CF6-80A S/B 72-0779, inspect, rework, re-mark, and remove from service as necessary at the next Engine Shop Visit

(ESV)using the compliance times in the following Table 3: Table 3.—Compliance Times for Inspection and Rework of CF6-80A Series Stage 1 HPT Rotor Disks, P/Ns 9234M67G22, G24, G25, G26, 9367M45G04, G09, 9362M58G02, G06, G07, and 9362M58G09 With SNs Not Listed in Table 2 of This AD—Previously Inspected Stage 1 HPT rotor disk cycles-since-last-inspection

(CSLI)on March 12, 2004 (effective date of superseded AD 2004-04-07) Compliance time for inspection and rework

(i)More than 1,500 CSLI At the next ESV after March 12, 2004 (effective date of superseded AD 2004-04-07), but not to exceed 4,500 CSLI.

(ii)1,500 CSLI or fewer At the next ESV after March 12, 2004 (effective date of superseded AD 2004-04-07), but not to exceed 3,500 CSLI.

(3)For stage 1 HPT rotor disks which have not been inspected using any version of GE SB No. CF6-80A S/B 72-0779, inspect, rework, re-mark, and remove from service as necessary using the following Table 4 or Table 4A compliance times, whichever occurs first: Table 4.—Compliance Times for Inspection and Rework of CF6-80A Series Stage 1 HPT Rotor Disks, P/Ns 9234M67G22, G24, G25, G26, 9367M45G04, G09, 9362M58G02, G06, G07, and 9362M58G09 With SNs Not Listed in Table 2 of This AD—Not Previously Inspected Stage 1 HPT rotor disk cycles-since-new

(CSN)on the effective date of this AD Compliance time for inspection and rework

(i)9,000 or more CSN Within 250 cycles-in-service

(CIS)after the effective date of this AD, or by March 31, 2007, whichever occurs first.

(ii)6,900 or more but fewer than 9,000 CSN Within 500 CIS after the effective date of this AD, but before accumulating 9,250 CSN, or by December 31, 2007, whichever occurs first.

(iii)Fewer than 6,900 CSN Before accumulating 7,400 CSN, or by December 31, 2008, whichever occurs first. Table 4A.—Compliance Times for Inspection and Rework of CF6-80A Series Stage 1 HPT Rotor Disks, P/Ns 9234M67G22, G24, G25, G26, 9367M45G04, G09, 9362M58G02, G06, G07, and 9362M58G09 With SNs Not Listed in Table 2 of This AD—Not Previously Inspected Stage 1 HPT rotor disk CSN on March 12, 2004 (effective date of superseded AD 2004-04-07) Compliance time for inspection and rework

(i)10,000 or more CSN At the next ESV or within 1,000 CIS after March 12, 2004 (effective date of superseded AD 2004-04-07), whichever occurs first.

(ii)5,000 or more CSN but fewer than 10,000 CSN At the next ESV or within 2,400 CIS after March 12, 2004 (effective date of superseded AD 2004-04-07), whichever occurs first, but before accumulating 11,000 CSN.

(iii)Fewer than 5,000 CSN At the next ESV or within 3,500 CIS after March 12, 2004 (effective date of superseded AD 2004-04-07), whichever occurs first, but before accumulating 7,400 CSN. Stage 1 HPT Rotor Disks, P/N 9367M45G02

(h)For stage 1 HPT rotor disks, P/N 9367M45G02, remove the disk from service at the following times:

(1)For stage 1 HPT rotor disks not installed in engines, remove from service before further flight.

(2)For stage 1 HPT rotor disks that have been inspected before the effective date of this AD using any version of GE SB No. CF6-80A S/B 72-0779, and had more than zero CSN at the time of that inspection, remove from service at next ESV.

(3)For stage 1 HPT rotor disks that have not been inspected, or were only inspected with zero CSN before the effective date of this AD using any version of GE SB No. CF6-80A S/B 72-0779, remove from service using the following Table 5 or Table 5A compliance times, whichever occurs first: Table 5.—Compliance Times for Removal of CF6-80A Series Stage 1 HPT Rotor Disks, P/N 9367M45G02—Not Previously Inspected Stage 1 HPT rotor disk CSN on the effective date of this AD Compliance time for removal

(i)9,000 or more CSN Within 250 CIS after the effective date of this AD, or by March 31, 2007, whichever occurs first.

(ii)6,900 or more but fewer than 9,000 CSN Within 500 CIS after the effective date of this AD, but before accumulating 9,250 CSN, or by December 31, 2007, whichever occurs first.

(iii)Fewer than 6,900 CSN Before accumulating 7,400 CSN, or by December 31, 2008, whichever occurs first. Table 5A.—Compliance Times for Removal of CF6-80A Series Stage 1 HPT Rotor Disks, P/N 9367M45G02—Not Previously Inspected Stage 1 HPT rotor disk CSN on March 12, 2004 (effective date of superseded AD 2004-04-07) Compliance time for removal

(i)10,000 or more CSN At the next ESV or within 1,000 CIS after March 12, 2004 (effective date of superseded AD 2004-04-07), whichever occurs first.

(i)At the next piece-part exposure, for stage 1 HPT rotor disks, P/N 1531M84G10, with SNs listed in Table 6 (Group 1) of this AD, do the following, unless already done using superseded AD 2004-04-07: Table 6.—SNs of CF6-80C2 Series Stage 1 HPT Rotor Disks, P/N 1531M84G10, With Chamfered Breakedges, Group 1 GWN03111 GWN03114 GWN031N2 GWN031N3 GWN031N4 GWN031N5 GWN031N6 GWN031N7 GWN031N8 GWN031N9 GWN031NA GWN031NC GWN032G1 GWN032G2 GWN032G3 GWN032G4 GWN032G5 GWN032G6 GWN032G7 GWN032G8 GWN032G9 GWN032GE GWN0335P GWN0335R GWN033C5 GWN034KR GWN034KT GWN03501 GWN0350M GWN0350N GWN0350P GWN0350R GWN0350T GWN0350W GWN035M5 GWN035M6 GWN035M7 GWN035M8 GWN035M9 GWN035MA GWN035MC GWN035MD GWN035TH GWN035TJ GWN035TK GWN035TL GWN035TM GWN03699 GWN0369A GWN0369C GWN0369D GWN0369E GWN0369G GWN0369H GWN0369J GWN036JG GWN036JH GWN036JJ GWN036JK GWN036JL GWN036JM GWN036JN GWN03752 GWN03753 GWN03754 GWN03755 GWN03756 GWN03757 GWN03759 GWN0375A GWN0375C GWN0375D GWN0375E GWN037H2 GWN03981 GWN03982 GWN03983 GWN03984 GWN03985 GWN03986 GWN03987 GWN03988 GWN03989 GWN0398A GWN0398C GWN039PF GWN039PG GWN039PH GWN039PJ GWN039PK GWN039PL GWN039PM GWN039PN GWN03A4J GWN03A4K GWN03A4L GWN03A4M GWN03A4N GWN03A4P GWN03A4R GWN03A4T GWN03A4W GWN03C12 GWN03C13 GWN03C14 GWN03CA0 GWN03DC9 GWN03DCA GWN03DCC GWN03DCD GWN03DCE GWN03DCF GWN03DCG GWN03DCH GWN03DCJ GWN03DCK GWN03DCL GWN03DCM GWN03DCN GWN03DCP GWN03DCR GWN03DME GWN03DMF GWN03ER7 GWN03ER8 GWN03ER9 GWN03ERA GWN03FTN GWN03FTP GWN03FTR GWN03FTT GWN03FTW GWN03FW0 GWN03H56 GWN03H57 GWN03H58 GWN03HTL GWN03HTM GWN03HTN GWN03HTP GWN03HTR GWN03HTT GWN03J8T GWN03J8W GWN03J91 GWN03J92 GWN03JNN GWN03JNP GWN03K3C GWN03K3D GWN03K3F GWN03K3G GWN03K3H GWN03K3K GWN03K3L GWN03K3M GWN03K3N GWN03K3T GWN03K3W GWN03K40 GWN03K7R GWN03KR1 GWN03KR3 GWN03KR4 GWN03KR6 GWN03KR7 GWN03KR8 GWN03KRC GWN03L2D GWN03L2E GWN03L2F GWN03LNF GWN03LNJ GWN03LNK GWN03M88 GWN03M8C GWN03M8E GWN03M8J GWN03M8K GWN03NHN GWN03NHP GWN03NHR GWN03R74 GWN03R76 GWN03R78 GWN03R7E GWN03R7F GWN03R9G GWN03R9H GWN03R9M GWN03R9P GWN03R9T GWN03RA2 GWN03RA3 GWN03RA5 GWN03RA8 GWN03RPA GWN03RPC GWN03RPD GWN04026 GWN0402A GWN0402F GWN0402L GWN040R5 GWN04189 GWN0418A GWN0418D GWN0418E GWN0418F GWN0418H GWN0418J GWN0418L GWN0418N GWN0418R GWN04366 GWN044DP GWN0454H GWN0454M GWN0454N GWN045T0 GWN045T2 GWN045T8 GWN045TD GWN045TG GWN04722 GWN04729 GWN047LK GWN048CD GWN048CF GWN048CH GWN048CJ GWN048CK GWN049GJ GWN049M8 GWN049M9 GWN04AER GWN04ALR GWN04AM1 GWN04CGJ GWN04CGN GWN04CGT GWN04CGW GWN04CH3 GWN04CH5 GWN04CH8 GWN04CH9 GWN04D52 GWN04D54 GWN04D56 GWN04D57 GWN04D58 GWN04D59 GWN04DPW GWN04E9K GWN04E9L GWN04E9M GWN04EMA GWN04EMK GWN04EML GWN04EMM GWN04FTL GWN04FTM GWN04FTN

(1)Visually inspect the rotor disks for the presence of a chamfer on the aft breakedges of the dovetail slot bottoms. Use paragraph 3.A. of GE SB No. CF6-80C2 S/B 72-1217, dated July 20, 2006, to do the inspection.

(2)For disks that have the chamfered breakedges, re-mark, FPI, and ECI the rotor disk. Use paragraph 3.A.(1) of the Accomplishment Instructions of GE SB No. CF6-80C2 S/B 72-1217, dated July 20, 2006, to re-mark and inspect the rotor disk, and remove from service as necessary.

(3)For disks that do not have the chamfered breakedges, remove the disk from service. Use paragraph 3.A.(4) of the Accomplishment Instructions of GE SB No. CF6-80C2 S/B 72-1217, dated July 20, 2006. CF6-80C2 Series Engines Stage 1 HPT Rotor Disks, P/N 1531M84G10, With Chamfered Breakedges, Group 2

(j)For stage 1 HPT rotor disks, P/N 1531M84G10, with SNs listed in Table 6A of this AD, with chamfered breakedges, (Group 2):

(1)With more than 6,900 CSN, perform paragraphs (j)(3) through (j)(5) as applicable, at the next ESV, but within 500 CIS after the effective date of this AD, unless already done using superseded AD 2004-04-07.

(2)With 6,900 CSN or fewer, perform paragraphs (j)(3) through (j)(5) as applicable, at the next ESV, but before accumulating 7,400 CSN, unless already done using superseded AD 2004-04-07. Table 6A.—SNs of CF6-80C2 Series Stage 1 HPT Rotor Disks, P/N 1531M84G10, With Chamfered Breakedges, Group 2 GWN03J90 GWN03K3R GWN03K6J GWN03K7T GWN03KR2 GWN03KR5 GWN03KRA GWN03KRD GWN03M89 GWN03M8D GWN03M8F GWN03NHT GWN03R73 GWN03R75 GWN03R77 GWN03R79 GWN03R7A GWN03R7C GWN03R7D GWN03R7G GWN03R7H GWN03R9J GWN03R9K GWN03R9L GWN03R9N GWN03R9R GWN03R9W GWN03RA0 GWN03RA1 GWN03RA4 GWN03RA6 GWN03RA7 GWN03RP7 GWN03RP9 GWN03RPE GWN03RPF GWN03RPG GWN04027 GWN04028 GWN04029 GWN0402E GWN0402G GWN0402H GWN0402J GWN0402K GWN0402M GWN0402N GWN0402P GWN0418C GWN0418G GWN0418K GWN0418M GWN0418P GWN0418T GWN0418W GWN04190 GWN04191 GWN0454E GWN0454F GWN0454G GWN0454J GWN0454K GWN0454L GWN045T1 GWN045T3 GWN045T4 GWN045T5 GWN045T6 GWN045T7 GWN045T9 GWN045TA GWN045TC GWN045TE GWN045TF GWN045TH GWN046F6 GWN046F7 GWN046F8 GWN04726 GWN047LG GWN047LH GWN047LJ GWN047LL GWN048CG GWN048CM GWN048CN GWN048CP GWN048CR GWN049GH GWN049GK GWN049JL GWN049JM GWN049M7 GWN04AEP GWN04AET GWN04ALT GWN04ALW GWN04AM0 GWN04AM2 GWN04AM3 GWN04AM4 GWN04CGL GWN04CHA GWN04CHC GWN04D55 GWN04DR4 GWN04DR9 GWN04DRE GWN04DRJ GWN04E9N GWN04EM5 GWN04F8N GWN04F8P GWN04FTJ

(3)Visually inspect the rotor disks for the presence of a chamfer on the aft breakedges of the dovetail slot bottoms. Use paragraph 3.A. of GE SB No. CF6-80C2 S/B 72-1217, dated July 20, 2006, to do the inspection.

(4)For disks that have the chamfered breakedges, re-mark, FPI, and ECI the rotor disk. Use paragraph 3.A.(2) of the Accomplishment Instructions of GE SB No. CF6-80C2 S/B 72-1217, dated July 20, 2006, to re-mark and inspect the rotor disk, and remove from service as necessary.

(5)For disks that do not have the chamfered breakedges, remove the disk from service. Use paragraph 3.A.(4) of the Accomplishment Instructions of GE SB No. CF6-80C2 S/B 72-1217, dated July 20, 2006. CF6-80C2 Series Engines Stage 1 HPT Rotor Disks, P/N 1531M84G12, With Chamfered Breakedges

(k)For stage 1 HPT rotor disks, P/N 1531M84G12, with SNs listed in Table 6B of this AD, with chamfered breakedges:

(1)With more than 6,900 CSN, perform paragraph (k)(3) at the next ESV, but not to exceed 500 cycles after the effective date of this AD.

(2)With 6,900 CSN or fewer, perform paragraph (k)(3) at the next ESV, but before accumulating 7,400 CSN. Table 6B.—SNs of CF6-80C2 Series Stage 1 HPT Rotor Disks, P/N 1531M84G12, With Chamfered Breakedges GWN04CH6 GWN04G5H GWN04M03

(3)FPI and ECI the rotor disk. Use paragraph 3.A.(3) of the Accomplishment Instructions of GE SB No. CF6-80C2 S/B 72-1217, dated July 20, 2006, to re-mark and inspect the rotor disk, and remove from service as necessary. Stage 1 HPT Rotor Disks, P/Ns 9392M23G10, G12, G21, 1531M84G02, G06, G08, and 1531M84G10 with SNs not listed in Table 6 and Table 6A of this AD

(l)For stage 1 HPT rotor disks, P/Ns 9392M23G10, G12, G21, 1531M84G02, G06, G08, and 1531M84G10 with SNs not listed in Table 6 and Table 6A of this AD, inspect, rework, and re-mark the disks using paragraphs 3.A.(1) through 3.A.(2) of Accomplishment Instructions of GE SB No. CF6-80C2 S/B 72-1089, Revision 3, dated July 20, 2006, at the following, unless already done using superseded AD 2004-04-07:

(1)For both new and used stage 1 HPT rotor disks not installed in engines, inspect, rework, re-mark, and remove from service as necessary before further flight.

(2)For stage 1 HPT rotor disks that have been inspected before March 12, 2004 (effective date of superseded AD 2004-04-07) using GE ASB No. CF6-80C2 S/B 72-A1024, Revision 1, dated November 3, 2000, or any version of GE ASB No. CF6-80C2 S/B 72-A1026, inspect, rework, re-mark, and remove from service as necessary using the compliance times in the following Table 7: Table 7.—Compliance Times for Inspection and Rework of CF6-80C2 Series Stage 1 HPT Rotor Disks, P/Ns 9392M23G10, G12, G21, 1531M84G02, G06, G08, and 1531M84G10 With SNs Not Listed in Table 6 and Table 6A of This AD—Previously Inspected Stage 1 HPT rotor disk cycles-since-last-inspection

(CSLI)on March 12, 2004 (effective date of superseded AD 2004-04-07) Compliance time for inspection and rework

(i)More than 1,500 CSLI At the next ESV after March 12, 2004 (effective date of superseded AD 2004-04-07), but not to exceed 4,500 CSLI.

(ii)1,500 CSLI or fewer At the next ESV after March 12, 2004 (effective date of superseded AD 2004-04-07), but not to exceed 3,500 CSLI.

(3)For stage 1 HPT rotor disks that have not been inspected before March 12, 2004 (effective date of superseded AD 2004-04-07) using GE ASB No. CF6-80C2 S/B 72-A1024, Revision 1, dated November 3, 2000, or any version of GE ASB No. CF6-80C2 S/B 72-A1026, inspect, rework, re-mark, and remove from service as necessary using the following Table 8 or Table 8A compliance times, whichever occurs first: Table 8.—Compliance Times for Inspection and Rework of CF6-80C2 Series Stage 1 HPT Rotor Disks, P/Ns 9392M23G10, G12, G21, 1531M84G02, G06, G08, and 1531M84G10 With SNs Not Listed in Table 6 and Table 6A of This AD—Not Previously Inspected Stage 1 HPT rotor disk cycles-since-new

(CSN)on the effective date of this AD Compliance time for inspection and rework

(i)9,000 or more CSN Within 250 CIS after the effective date of this AD, or by March 31, 2007, whichever occurs first.

(ii)6,900 or more but fewer than 9,000 CSN Within 500 CIS after the effective date of this AD, but before accumulating 9,250 CSN, or by December 31, 2007, whichever occurs first.

(iii)Fewer than 6,900 CSN Before accumulating 7,400 CSN, or by December 31, 2008, whichever occurs first. Table 8A.—Compliance Times for Inspection and Rework of CF6-80C2 Series Stage 1 HPT Rotor Disks, P/Ns 9392M23G10, G12, G21, 1531M84G02, G06, G08, and 1531M84G10 With SNs Not Listed in Table 6 and Table 6A of This AD—Not Previously Inspected Stage 1 HPT rotor disk CSN on March 12, 2004 (effective date of superseded AD 2004-04-07) Compliance time for inspection and rework

(i)10,000 or more CSN At the next ESV or within 1,000 CIS after March 12, 2004 (effective date of superseded AD 2004-04-07), whichever occurs first.

(ii)5,000 or more CSN but fewer than 10,000 CSN At the next ESV or within 2,400 CIS after March 12, 2004 (effective date of superseded AD 2004-04-07), but before accumulating 11,000 CSN.

(m)For stage 1 HPT rotor disk, P/N 1862M23G01, remove the disk from service at the following times:

(1)For stage 1 HPT rotor disks not installed in engines, remove from service as necessary before further flight.

(2)For stage 1 HPT rotor disks that have been inspected before March 12, 2004 (effective date of superseded AD 2004-04-07), using any version of GE ASB No. CF6-80C2 S/B 72-A1026, and had more than zero CSN at the time of that inspection, remove from service at next ESV.

(3)For stage 1 HPT rotor disks that have not been inspected, or were only inspected with zero CSN before March 12, 2004 (effective date of superseded AD 2004-04-07), using any version of GE ASB No. CF6-80C2 S/B 72-A1026, remove from service using the following Table 9 or Table 9A compliance times, whichever occurs first: Table 9.—Compliance Times for Removal of CF6-80C2 Series Stage 1 HPT Rotor Disks, P/N 1862M23G01—Not Previously Inspected Stage 1 HPT rotor disk CSN on the effective date of this AD Compliance time for removal

(i)9,000 or more CSN Within 250 CIS after the effective date of this AD, or by March 31, 2007, whichever occurs first.

(ii)6,900 or more but fewer than 9,000 CSN Within 500 CIS after the effective date of this AD, but before accumulating 9,250 CSN, or by December 31, 2007, whichever occurs first.

(iii)Fewer than 6,900 CSN Before accumulating 7,400 CSN, or by December 31, 2008, whichever occurs first. Table 9A.—Compliance Times for Removal of CF6-80C2 Series Stage 1 HPT Rotor Disks, P/N 1862M23G01—Not Previously Inspected Stage 1 HPT rotor disk CSN on March 12, 2004 (effective date of superseded AD 2004-04-07) Compliance time for removal

(i)10,000 or more CSN At the next ESV or within 1,000 CIS after March 12, 2004 (effective date of superseded AD 2004-04-07), whichever occurs first.

(n)For stage 1 HPT rotor disks, P/N 1639M41P04, remove the rotor disks from service using paragraphs 3.A.(1) through 3.A.(2) of Accomplishment Instructions of GE SB No. CF6-80E1 S/B 72-0251, dated January 22, 2004, at the following times:

(1)For stage 1 HPT rotor disks currently in service, remove the disk using the compliance times in the following Table 10 or Table 10A compliance times, whichever occurs first: Table 10.—Compliance Times for Removal of CF6-80E1 Stage 1 HPT Rotor Disks, P/N 1639M41P04 Stage 1 HPT rotor disk CSN on the effective date of this AD Compliance Time For Removal

(i)9,000 or more CSN Within 250 CIS after the effective date of this AD, or by March 31, 2007, whichever occurs first.

(ii)6,900 or more but fewer than 9,000 CSN Within 500 CIS after the effective date of this AD, but before accumulating 9,250 CSN, or by December 31, 2007, whichever occurs first.

(iii)Fewer than 6,900 CSN Before accumulating 7,400 CSN, or by December 31, 2008, whichever occurs first. Table 10A.—Compliance Times for Removal of CF6-80E1 Stage 1 HPT Rotor Disks, P/N 1639M41P04 Stage 1 HPT rotor disk CSN on the March 12, 2004 ( effective date of superseded AD 2004-04-07) Compliance time for removal

(i)More than 10,000 CSN At the next ESV or within 600 CIS after March 12, 2004 (effective date of superseded AD 2004-04-07), whichever occurs first.

(ii)More than 5,000 CSN but fewer than or equal to 10,000 CSN At the next ESV or within 2,500 CIS after March 12, 2004 (effective date of superseded AD 2004-04-07), whichever occurs first, but before accumulating 10,600 CSN.

(iii)Fewer than or equal to 5,000 CSN At the next ESV or within 3,500 CIS after March 12, 2004 (effective date of superseded AD 2004-04-07), whichever occurs first, but before accumulating 7,500 CSN.

(2)After March 12, 2004 (effective date of superseded AD 2004-04-07), do not install any stage 1 HPT rotor disk, P/N 1639M41P04, into any engine. Definitions

(o)For the purpose of this AD, the following definitions apply:

(1)An engine shop visit

(ESV)is when the engine is removed from an aircraft for maintenance and a major engine flange is disassembled. For stage 1 HPT rotor disks that have been inspected using any version of GE SB No. CF6-80A SB 72-0779 or any version of GE ASB No. CF6-80C2 ASB 72-A1026 or GE SB No. CF6-80C2 SB 72-A1024, Revision 1, dated November 3, 2000 or are listed in Table 6A or Table 6B, the following actions, either separately or in combination with each other, are not considered ESVs for the purpose of this AD:

(i)The removal of the upper compressor stator case solely for airfoil maintenance.

(ii)The module level inspection of the high-pressure compressor rotor 3-9 spool.

(iii)The replacement of stage 5 high-pressure compressor variable stator vane bushings or lever arms.

(2)Piece-part exposure is when according to the manufacturer's engine manual or other FAA-approved engine manual the stage 1 HPT rotor disk is considered completely disassembled. Reporting Requirements

(p)Within five calendar days of the inspection, report the results of inspections that equal or exceed the reject criteria to: Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone

(781)238-7176; fax

(781)238-7199. Reporting requirements have been approved by the Office of Management and Budget and assigned OMB control number 2120-0056. Be sure to include the following information:

(1)Engine model in which the stage 1 HPT rotor disk was installed.

(2)Part Number.

(3)Serial Number.

(4)Part CSN.

(5)Part CSLI.

(6)Date and location where inspection was done.

(q)We request that you record the inspection information and results on GE Form 1653-1, entitled CF6-80A/80C Stage 1 HPT Disk Dovetail Slot Bottom Inspection. This form is available in any version of GE SB CF6-80A S/B 72-0779, or GE ASB CF6-80C2 S/B 72-A1026. We also request that a copy of the data be sent to GE Airline Support Engineering, General Electric Aircraft Engines, Customer Support Center, 1 Neumann Way, Mail Drop RM285, Cincinnati, OH 45215. Alternative Methods of Compliance

(r)The manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Material Incorporated by Reference

(s)You must use the service information specified in Table 11 to perform the actions required by this AD. The Director of the Federal Register previously approved the incorporation by reference of General Electric Service Bulletins No. CF6-80E1 S/B 72-0251, dated January 22, 2004 and No. CF6-80A S/B 72-0779, Revision 1, dated January 22, 2004, and Alert Service Bulletin No. CF6-80C2 S/B 72-A1026, Revision 2, dated January 22, 2004, as of March 12, 2004 (69 FR 8801, February 26, 2004). The Director of the Federal Register approved the incorporation by reference of the other documents listed in Table 11 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You can get a copy from General Electric Company via Lockheed Martin Technology Services, 10525 Chester Road, Suite C, Cincinnati, Ohio 45215, telephone

(513)672-8400, fax

(513)672-8422. You may review copies 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. Table 11 follows: Table 11.—Incorporation by Reference Service Bulletin No. Page Revision Date GE SB No. CF6-80E1 S/B 72-0251 All Original January 22, 2004. Total Pages: 4 GE SB No. CF6-80A S/B 72-0779 ALL 1 January 22, 2004. Total Pages: 34 GE SB No. CF6-80A S/B 72-0788 ALL 3 July 20, 2006. Total Pages: 11 GE ASB No. CF6-80C2 S/B 72-A1026 ALL 2 January 22, 2004. Total Pages: 38 GE SB No. CF6-80C2 S/B 72-1089 ALL 3 July 20, 2006. Total Pages: 11 GE SB No. CF6-80C2 S/B 72-1217 ALL Original July 20, 2006. Total Pages: 12 GE SB No. CF6-80A S/B 72-0822 ALL Original July 20, 2006. Total Pages: 10 Related Information

(t)GE ASB No. CF6-80C2 S/B 72-A1024, Revision 1, dated November 3, 2000 also pertains to the subject of this AD. Issued in Burlington, Massachusetts, on August 10, 2006. Francis A. Favara, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E6-13437 Filed 8-17-06; 8:45 am] BILLING CODE 4910-13-P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2006-24366; Directorate Identifier 2006-NM-040-AD; Amendment 39-14716; AD 2006-16-16] RIN 2120-AA64 Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135BJ Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: The FAA is adopting a new airworthiness directive

(AD)for certain EMBRAER Model EMB-135BJ airplanes. This AD requires inspecting for missing fire blocking material on the left- and right-hand partitions of the forward baggage compartment door; replacing the seal on both partitions; and performing corrective action if necessary. This AD results from a report indicating that certain airplanes were delivered with the fire blocking material missing and the seal improperly installed on the partitions of the forward baggage compartment door. We are issuing this AD to detect and correct such discrepancies on the forward baggage compartment partition, which, in the event of a fire in the baggage compartment, could result in smoke propagating into the main cabin. DATES: This AD becomes effective September 22, 2006. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of September 22, 2006. ADDRESSES: You may examine the AD docket on the Internet at *http://dms.dot.gov* or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC. Contact Empresa Brasileira de Aeronautica S.A. (EMBRAER), P.O. Box 343—CEP 12.225, Sao Jose dos Campos—SP, Brazil, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone

(425)227-2125; fax

(425)227-1149. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive

(800)647-5227) is located on the plaza level of the Nassif Building at the street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking

(NPRM)to amend 14 CFR part 39 to include an AD that would apply to certain EMBRAER Model EMB-135BJ airplanes. That NPRM was published in the **Federal Register** on April 11, 2006 (71 FR 18247). That NPRM proposed to require inspecting for missing fire blocking material on the left- and right-hand partitions of the forward baggage compartment door; replacing the seal on both partitions; and performing corrective action if necessary. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Request To Add Revised Service Information to Applicability Section The manufacturer, EMBRAER, advises that the service bulletin specified in the NPRM has been revised. EMBRAER notes that EMBRAER Service Bulletin 145LEG-25-0060, Revision 01, dated March 3, 2006, extends the compliance time to coincide with the Brazilian airworthiness directive and contains minor changes. EMBRAER asks that we add the revised service bulletin to the applicability section. We agree with EMBRAER. We have reviewed Revision 01 of the service bulletin and note that it does not necessitate additional work. We have changed the applicability section of the AD to refer to Revision 01. We have also revised paragraph

(f)of the AD to reflect the revised service bulletin. In addition, we have added a new paragraph

(g)to this AD specifying that accomplishment of the actions specified in paragraph

(f)of the AD in accordance with the original issue of the service bulletin is considered to be an acceptable method of compliance. Subsequent paragraphs of the AD have been re-identified accordingly. Request To Change Terminology EMBRAER also asks that the statement of the unsafe condition specified in the NPRM be changed to the following: “We are issuing this AD to detect and correct such discrepancies on the partitions of the forward baggage compartment partition, which, in the event of a fire in the baggage compartment, could result in smoke propagating into the main cabin.” EMBRAER states that instead of the forward baggage compartment “door,” the subject area should be named the forward baggage compartment “partition.” We agree with EMBRAER and have changed the terminology throughout the AD as follows: “We are issuing this AD to detect and correct such discrepancies on the forward baggage compartment partition, which, in the event of a fire in the baggage compartment, could result in smoke propagating into the main cabin.” Conclusion We have carefully reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously. These changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this AD. Estimated Costs Action Work hours Average labor rate per hour Parts Cost per airplane Number of U.S.-registered airplanes Fleet cost Inspection 1 $80 None $80 23 $1,840 Seal Replacement 7 $80 Minimal $560 23 $12,880 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 this AD:

(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

(FAA)amends § 39.13 by adding the following new airworthiness directive (AD): **2006-16-16** **Empresa Brasileira de Aeronautica S.A. (EMBRAER):** Amendment 39-14716. FAA-2006-24366; Directorate Identifier 2006-NM-040-AD. Effective Date

(a)This AD becomes effective September 22, 2006. Affected ADs

(b)None. Applicability

(c)This AD applies to EMBRAER Model EMB-135BJ airplanes, certificated in any category; as identified in EMBRAER Service Bulletin 145LEG-25-0060, Revision 01, dated March 3, 2006. Unsafe Condition

(d)This AD results from a report indicating that certain airplanes were delivered with the fire blocking material missing and the seal improperly installed on the partitions of the forward baggage compartment door. We are issuing this AD to detect and correct such discrepancies on the forward baggage compartment partition, which, in the event of a fire in the baggage compartment, could result in smoke propagating into the main cabin. Compliance

(e)You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Inspection and Corrective Actions

(f)Within 24 months after the effective date of this AD: Do a general visual inspection for missing fire blocking material (an insulation blanket) on the left- and right-hand partitions of the forward baggage compartment door, replace the seal on both partitions with a new seal, and accomplish all applicable corrective actions, by doing all the actions specified in the Accomplishment Instructions of EMBRAER Service Bulletin 145LEG-25-0060, Revision 01, dated March 3, 2006. All applicable corrective actions must be done before further flight. Note 1: For the purposes of this AD, a general visual inspection is: “A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.” Acceptable for Compliance

(g)Accomplishment of the actions required by paragraph

(f)of this AD before the effective date of this AD in accordance with EMBRAER Service Bulletin 145LEG-25-0060, dated November 18, 2005, is acceptable for compliance with the requirements of that paragraph. Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19.

(i)Brazilian airworthiness directive 2006-02-02, effective February 24, 2006, also addresses the subject of this AD. Material Incorporated by Reference

(j)You must use EMBRAER Service Bulletin 145LEG-25-0060, Revision 01, dated March 3, 2006, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Empresa Brasileira de Aeronautica S.A. (EMBRAER), P.O. Box 343—CEP 12.225, Sao Jose dos Campos—SP, Brazil, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL-401, Nassif Building, Washington, DC; on the Internet at *http://dms.dot.gov;* or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call

(202)741-6030, or go to *http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.* Issued in Renton, Washington, on August 3, 2006. Ali Bahrami, Manager, Transport Airplane Directorate,Aircraft Certification Service. [FR Doc. E6-13449 Filed 8-17-06; 8:45 am] BILLING CODE 4910-13-P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA-2006-25499; Airspace Docket No. 06-ASW-09] Modification of Class D Airspace, Modification to Class E; Clovis, NM AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Direct final rule; request for comments. SUMMARY: This action modifies the Class D and the Class E airspace areas at Cannon AFB, Clovis, NM, to provide controlled airspace for Category

(CAT)E aircraft performing a circling approach within Class D and Class E Airspace. DATES: Effective 0901 UTC, November 23, 2006. Comments for inclusion in the Rules Docket must be received on or before October 23, 2006. ADDRESSES: Send comments on the rule to the Docket Management System, U.S. Department of Transportation, Room Plaza 401, 400 Seventh Street, SW., Washington, DC 20590-0001. You must identify the docket number, FAA-2006-25499/Airspace Docket No. 06-ASW-09, at the beginning of your comments. You may also submit comments on the Internet at the DOT docket Web site, *http://dms.dot.gov* or the government-wide Web site, *http://regulations.gov.* Anyone can find and read the comments received in this docket, including the name, address and any other personal information placed in the docket by a commenter. You may hand-deliver your comments and review the public docket containing any comments received and this Direct Final Rule in person at the Dockets Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone 1-800-647-5527) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated previously. An informal docket may also be examined during normal business hours at the office of the Central Service Area, System Support Group, Federal Aviation Administration, Southwest Region, 2601 Meacham Boulevard, Fort Worth, TX. Call the group manager, System Support Group, AJO-2C2, telephone

(817)222-5530; fax

(817)222-5981, to make arrangements for your visit. FOR FURTHER INFORMATION CONTACT: Joseph R. Yadouga, Central, Service Area, System Support Group, Federal Aviation Administration, Southwest Region, Fort Worth, TX 76193-0530; telephone:

(817)222-5597. SUPPLEMENTARY INFORMATION: This amendment to 14 CFR part 71 establishes a Class D airspace designation for an airspace area from the surface up to but not including 6,800 feet MSL at Cannon AFB, Clovis, NM, and will be published in paragraph 5000 of FAA Order 7400.9N, dated September 1, 2005, and effective September 16, 2005, which is incorporated by reference in 14 CFR 71.1. This amendment to 14 CFR part 71 also modifies the Class E airspace area extending upward from the surface at Cannon AFB, Clovis, NM, and will be published in paragraph 6000 of FAA Order 7400.9N, dated September 1, 2005, and effective September 16, 2005, which is incorporated by reference in 14 CFR 71.1. The Direct Final Rule Procedure The FAA anticipates that this regulation will not result in an adverse or negative comment, and, therefore, issues it as a direct final rule. The FAA has determined that this regulation only involves an established body of technical regulations for which frequent and routine amendments are necessary to keep them operationally current. Unless a written adverse or negative comment, or a written notice of intent to submit an adverse or negative comment is received within the comment period, the regulation will become effective on the date specified. After the close of the comment period, the FAA will publish a document in the **Federal Register** indicating that no adverse or negative comments were received and confirming the date on which the final rule will become effective. If the FAA does receive, within the comment period, an adverse or negative comment, or written notice of intent to submit such a comment, a document withdrawing the direct final rule will be published in the **Federal Register,** and a notice of proposed rulemaking may be published with a new comment period. Comments Invited Although this action is in the form of a direct final rule, and was not preceded by a notice of proposed rulemaking, interested persons are invited to comment on this rule by submitting such written data, views, or arguments as they may desire. Communications must identify both docket numbers. All communications received on or before the closing date for comments will be considered, and this rule may be amended or withdrawn in light of the comments received. Factual information that supports the commenter's ideas and suggestions is extremely helpful in evaluating the effectiveness of this 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 action will be filed in the Rules Docket. Agency Findings This rule does not have federalism implications, as defined in Executive Order No. 13132, because it does 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 rule. The FAA has determined that this regulation is noncontroversial and unlikely to result in adverse or negative comments. For the reasons discussed, I certify that this regulation

(1)is not a “significant regulatory action” under Executive Order 12866;

(2)is not a “significant rule” under Department of Transportation

(DOT)Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and

(3)does not warrant preparation of a Regulatory Evaluation as these routine matters will only affect air traffic procedures and air navigation. I certify that this rule will not have a significant economic impact on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. Authority for This Rulemaking The FAA authority to issue rules regarding aviation safety is found in Title 49 of the United States Code. 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. This rulemaking is promulgated under the authority described in Subtitle VII, Part A, Subpart 1, Section 4013, “Sovereignty and use of airspace.” Under that section, the FAA is charged with developing plans and policy for use of the navigatable airspace and assigning by regulation or order the airspace necessary to ensure the safety of aircraft and the efficient use of airspace. The FAA may modify or revoke an assignment when required in the public interest. This regulation is within the scope of that authority because it is in the public interest to provide greater control of the airspace for the safety of aircraft operating in the vicinity of the newly established airport traffic control tower. List of Subjects in 14 CFR Part 71 Airspace, Incorporation by reference, Navigation (air). Adoption of the Amendment Accordingly, pursuant to the authority delegated to me, the Federal Aviation Administration amends part 71 of the Federal Aviation Regulations (14 CFR part 71) as follows: PART 71—DESIGNATION OF CLASS A, CLASS B, CLASS C, CLASS D, AND CLASS E AIRSPACE AREAS; AIRWAYS; ROUTES; AND REPORTING POINTS 1. The authority citation for part 71 continues to read as follows: Authority: 49 U.S.C. 106(g), 40103, 40113, 40120; E.O. 10854, 24 FR 9565, 3 CFR, 1959-1963 Comp., p. 389. § 71.1 [Amended] 2. The incorporation by reference in 14 CFR 71.1 of Federal Aviation Administration Order 7400.9N, Airspace Designations and Reporting Points, dated September 1, 2005, and effective September 16, 2005, is amended as follows: Paragraph 5000 Class D Airspace Areas Extending Upward From the Surface of the Earth ASW NM D Clovis, NM [Revised] Cannon AFB, NM Lat. 34°22′58″ N, Long. 103°19′20″ W That airspace extending upward from the surface to and including 6,800 feet MSL within a 6-mile radius Cannon AFB. The Class D airspace area is effective during the specific dates and times established in advance by the Notice to Airmen. The effective time will thereafter be continuously published in the Airport/Facility Directory. Paragraph 6000 Class E Airspace Areas Extending Upward From the Surface of the Earth ASW NM E Clovis, NM [Revised] Cannon AFB, NM Lat. 34° 22′58″ N, Long. 103°19′20″ W Cannon ILS Localizer Lat. 34°22′25″ N, Long. 103°20′09″ W Cannon TACAN0 Lat. 34°22′51″ N, Long. 103°19′21″ W That airspace extending upward from the surface within a 6-mile radius of Cannon AFB. The Class E airspace area is effective during the specific dates and times established in advance by the Notice to Airmen. The effective time will thereafter be continuous published in the Airport/Facility Directory. Issued in Fort Worth, TX, on August 1, 2006. Donald R. Smith, System Support Group Manager, Central Service Area. [FR Doc. 06-6910 Filed 8-17-06; 8:45am]

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