Proposed Rules. Notice of tribal consultation meeting

Agency: U.S. Small Business Administration
Action: Notice of tribal consultation meeting
Citation: 72 FR (No. 196) · FR Doc. 07-5001 · 13 CFR 8, 124

Summary

The U.S. Small Business Administration (SBA) announces that it is holding a tribal consultation meeting in Fairbanks, Alaska on the topic of the 8(a) Business Development (BD) program regulations. Testimony presented at this tribal consultation meeting will become part of the administrative record for SBA's consideration when the Agency deliberates on approaches to changes in the regulations pertaining to the 8(a) BD program.

Dates

The Tribal Consultation meeting date is October 24, 2007, 9 a.m. to 4 p.m. (ATZ), Fairbanks, Alaska. The Tribal Consultation meeting pre-registration deadline date is October 17, 2007.

Supplementary Information

Background SBA is in the process of reassessing its rules relating to the 8(a) BD program, particularly those directly affecting tribally-owned and ANC-owned 8(a) firms. 13 CFR 124.506, 124.513, and 124.519. Part of SBA's analysis pertains to a recent report issued by the Government Accountability Office (GAO) titled “Increased Use of Alaska Native Corporations’ Special 8(a) Provisions Calls for Tailored Oversight” (GAO-06-399). This GAO report concluded that SBA needs to tailor its regulations and policies to provide greater oversight over its ANCs' 8(a) procurements. GAO determined that without sufficient oversight, there is the potential for unintended consequences or abuse. In response, SBA is considering regulatory changes to the 8(a) BD program to address the issues and concerns raised in the report, particularly those relating to ANC and tribal participation in the 8(a) BD mentor/protégé program. It is SBA's intent that any changes contemplated and instituted will incorporate the business development intent and mission of the 8(a) BD program as established by the Small Business Act. This notice provides information for the purpose, format, scheduling, and registration for the tribal consultation meeting. Tribal Consultation Meeting The purpose of this tribal consultation meeting is to conform to the requirements of Executive Order 13175, Tribal Consultations; to provide interested parties with an opportunity to discuss their views on the issues; and for SBA to obtain the views of these SBA's stakeholders on approaches to the 8(a) BD program regulations. SBA considers tribal consultation meetings a valuable component of its deliberations and believes that this tribal consultation meeting will allow for constructive dialogue with the tribal community, Tribal Leaders, Elders and elected members of Alaska Native Villages or their appointed representatives. The format will consist of a panel of SBA representatives who will represent the Agency and moderate the discussions. Oral and written testimony will become part of the record for SBA's consideration. Written testimony may be submitted in lieu of oral testimony. SBA will analyze the testimony, both oral and written, along with any written comments received. SBA officials may ask questions of a presenter to clarify or further explain the testimony. The purpose of the tribal consultation meeting is to assist SBA with gathering information to potentially develop new proposals. SBA respectfully requests that the testimony focus on the issues as discussed in the GAO report, general issues as they pertain to the 8(a) BD program regulations and the mentor protégé program, or the unique concerns of the tribal communities. SBA respectfully requests that presenters do not raise issues pertaining to other SBA small business programs. Presenters may provide a written copy of their testimony. SBA will accept written material that the presenter wishes to provide that further supplements his or her testimony. Electronic or digitized copies are encouraged. The tribal consultation meeting will be held for one day. The meeting will begin at 9 a.m. and end at 4 p.m. (ATZ), with a break from 12 p.m. to 1 p.m. SBA will adjourn early if all those scheduled have delivered their testimony. Venue Information Location Address Date Registration closing date Fairbanks, Alaska Pioneer Park, The Alaska Centennial Center for the Arts, 2300 Airport Road Fairbanks, AK 99701 October 24, 2007 October 17, 2007. Registration SBA respectfully requests that any elected or appointed representative of the tribal communities that are interested in attending please pre-register in advance and indicate whether you would like to testify at the hearing. Registration requests should be received by SBA at least 5 business days prior to the tribal consultation meeting date. Please contact Ms. Delcine Montgomery of SBA's Office of Native American Affairs in writing at Delcine.Montgomery@SBA.gov or by facsimile to 202/481-1597. If you are interested in testifying please include the following information relating to the person testifying: Name, Organization affiliation, Address, Telephone number, E-mail address and Fax number. SBA will attempt to accommodate all interested parties that wish to present testimony. Based on the number of registrants it may be necessary to impose time limits to ensure that everyone who wishes to testify has the opportunity to do so. SBA will confirm in writing the registration of presenters and attendees. Authority: 15 U.S.C. 634. Stephen D. Kong, Deputy General Counsel. [FR Doc. E7-19962 Filed 10-10-07; 8:45 am] BILLING CODE 8025-01-P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2007-0024; Directorate Identifier 2007-NM-086-AD] RIN 2120-AA64 Airworthiness Directives; Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for all Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This proposed AD would require repetitive inspections for cracking in and around the upper and lower hinge cutouts of the forward entry and forward galley service doorways, and corrective actions if necessary. This proposed AD results from multiple reports of cracks found in the skin, bearstrap, and/or frame outer chord in the hinge cutout areas of the forward entry and forward galley service doorways. We are proposing this AD to detect and correct such cracking, which could result in rapid decompression of the airplane. DATES: We must receive comments on this proposed AD by November 26, 2007. ADDRESSES: Use one of the following addresses to submit comments on this proposed 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: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Fax: (202) 493-2251. • Hand Delivery: Room W12-140 on the ground floor of the West Building, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207, for the service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Howard Hall, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6430; fax (425) 917-6590. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number “FAA-2007-0024; Directorate Identifier 2007-NM-086-AD” at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed 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 with FAA personnel concerning this proposed AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review DOT's complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477-78), or you may visit http://dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Operations office (telephone (800) 647-5527) is located on the ground floor of the West Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion We have received multiple reports of cracks found in the skin, bearstrap, and/or frame outer chord in the hinge cutout areas of the forward entry and forward galley service doorways. Cracks in the forward entry door bearstrap were reported on an airplane with as few as 24,538 total flight cycles. Cracks in the forward galley service door bearstrap were reported on an airplane with as few as 44,938 total flight cycles. One operator reported a severed bearstrap, a severed station (STA) 291.5 frame, and a 14.5-inch crack in the skin at the lower hinge cutout of the forward galley service doorway. The airplane had accumulated 61,297 total flight cycles. Such cracking, if not corrected, could result in rapid decompression of the airplane. The fatigue cracks are caused by cyclic cabin pressure loads and are not due to manufacturing defects in the bearstrap. The unsafe condition is unrelated to any previous investigation related to suspected unapproved parts. Relevant Service Information We have reviewed Boeing Alert Service Bulletin 737-53A1200, dated April 13, 2006. The service bulletin describes procedures for repetitive inspections for cracking in and around the upper and lower hinge cutouts of the forward entry and forward galley service doorways. The service bulletin describes the following inspections: • External detailed inspection of the skin; • High frequency eddy current (HFEC) hole probe inspection of the skin, bonded doubler, bearstrap, and frame chord at specified fastener locations; • HFEC hole probe inspection of the skin, bonded doubler, and bearstrap at specified fastener locations aft of the frame chord; • HFEC inspection of the skin hinge cutout trim; • Low frequency eddy current (LFEC) hole probe inspection of the skin, bonded doubler, and bearstrap at specific fastener locations aft of the frame chord; • LFEC hole probe inspection of the skin, bonded doubler, bearstrap, and frame chord at specific fastener locations. The service bulletin provides two options for the inspections, as follows: Compliance Times Option Inspections Threshold, in total flight cycles Grace period, in flight cycles Repetitive interval, in flight cycles A 1 External detailed inspection; HFEC inspection of the skin hinge cutout trim; and HFEC rotary probe inspection of the entire zone Entry door: 20,000 Service door: 40,000. 3,000 18,000 B External detailed inspection; HFEC inspection of the skin hinge cutout trim; and LFEC inspection of the entire zone Entry door: 20,000 Service door: 40,000. 3,000 3,000 HFEC rotary probe inspection of the aft zone (required only for Group 1, Configuration 1, and only for the entry door) Entry door: 20,000 Service door: 40,000. 6,000 18,000 1 Option A is mandatory for the forward entry door, upper and lower hinge cutouts, on Model 737-200C airplanes. The service bulletin specifies contacting Boeing for crack repair instructions. The service bulletin also states that the service bulletin might in the future be revised to include a preventive modification that will eliminate the need for the repetitive inspections. The service bulletin specifies contacting Boeing for information about this modification. FAA's Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other airplanes of this same type design. For this reason, we are proposing this AD, which would require accomplishing the actions specified in the service information described previously, except as discussed below. Difference Between the Proposed AD and the Service Bulletin The service bulletin specifies contacting the manufacturer for instructions for crack repair and for an optional modification that would terminate the repetitive inspections. But this proposed AD would require doing the repair and optional modification in one of the following ways: • Using a method that we approve; or • Using data that meet the certification basis of the airplane, and that have been approved by an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization whom we have authorized to make those findings. Costs of Compliance There are about 2,437 airplanes of the affected design in the worldwide fleet. The following table provides the estimated costs for U.S. operators to comply with this proposed AD, per inspection cycle. Estimated Costs Work hours Average hourly labor rate Cost per airplane Number of U.S.-registered airplanes Fleet cost 13 to 14 $80 $1,040 to $1,120 1,055 $1,097,200 to $1,181,600 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: 1. Is not a “significant regulatory action” under Executive Order 12866; 2. Is not a “significant rule” under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. 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 proposed 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, Safety. The Proposed 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 Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): Boeing: Docket No. FAA-2007-0024; Directorate Identifier 2007-NM-086-AD. Comments Due Date (a) The FAA must receive comments on this AD action by November 26, 2007. Affected ADs (b) None. Applicability (c) This AD applies to all Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes, certificated in any category. Unsafe Condition (d) This AD results from multiple reports of cracks found in the skin, bearstrap, and/or frame outer chord in the hinge cutout areas of the forward entry and forward galley service doorways. We are issuing this AD to detect and correct such cracking, which could result in rapid decompression of the airplane. 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. Repetitive Inspections (f) Except as provided by paragraph (g) of this AD, at the applicable times specified in paragraph 1.E. of Boeing Alert Service Bulletin 737-53A1200, dated April 13, 2006, do external detailed, low frequency eddy current, high frequency eddy current, and high frequency eddy current rotary probe inspections, as applicable, for cracks in and around the upper and lower hinge cutouts of the forward entry and forward galley service doorways, in accordance with the Accomplishment Instructions of the service bulletin, except as provided by paragraph (h) of this AD. Do not exceed the applicable repetitive interval for the previous inspection, as specified in the service bulletin as Option A or Option B. Repair any crack before further flight using a method approved in accordance with the procedures specified in paragraph (i) of this AD. Exceptions to Service Bulletin Specifications (g) Where the service bulletin specifies a compliance time after the release date of the service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD. (h) Although the service bulletin specifies contacting Boeing for information about installing an optional preventive modification that would terminate the repetitive inspections specified in this AD, this AD requires that any terminating action be done by using a method approved in accordance with the procedures specified in paragraph (i) of this AD. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization who has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. Issued in Renton, Washington, on October 1, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-20048 Filed 10-10-07; 8:45 am] BILLING CODE 4910-13-P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2007-29329; Directorate Identifier 2007-NM-205-AD] RIN 2120-AA64 Airworthiness Directives; McDonnell Douglas Model 717-200 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain McDonnell Douglas Model 717-200 airplanes. This proposed AD would require modification of the conduit for the forward boost pump of the center fuel tank. This proposed AD results from the finding that a potential chafing condition exists in the volute assembly of the forward boost pump for the center fuel tank. We are proposing this AD to prevent chafing of the forward boost pump wiring that could lead to arcing to the inside of the 45-degree angle fitting, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. DATES: We must receive comments on this proposed AD by November 26, 2007. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. • Governmentwide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Fax: (202) 493-2251. • Hand Delivery: Room W12-140 on the ground floor of the West Building, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 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 the service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Samuel S. Lee, Aerospace Engineer, Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; telephone (562) 627-5262; fax (562) 627-5210. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number “FAA-2007-29329; Directorate Identifier 2007-NM-205-AD” at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed 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 with FAA personnel concerning this proposed AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review DOT's complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477-78), or you may visit http://dms.dot.gov . Examining the Docket You may examine the AD docket on the Internet at http://dms.dot.gov , or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Operations office (telephone (800) 647-5527) is located on the ground level of the West Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion The FAA has examined the underlying safety issues involved in fuel tank explosions on several large transport airplanes, including the adequacy of existing regulations, the service history of airplanes subject to those regulations, and existing maintenance practices for fuel tank systems. As a result of those findings, we issued a regulation titled “Transport Airplane Fuel Tank System Design Review, Flammability Reduction and Maintenance and Inspection Requirements” (66 FR 23086, May 7, 2001). In addition to new airworthiness standards for transport airplanes and new maintenance requirements, this rule included Special Federal Aviation Regulation No. 88 (“SFAR 88,” Amendment 21-78, and subsequent Amendments 21-82 and 21-83). Among other actions, SFAR 88 requires certain type design (i.e., type certificate (TC) and supplemental type certificate (STC)) holders to substantiate that their fuel tank systems can prevent ignition sources in the fuel tanks. This requirement applies to type design holders for large turbine-powered transport airplanes and for subsequent modifications to those airplanes. It requires them to perform design reviews and to develop design changes and maintenance procedures if their designs do not meet the new fuel tank safety standards. As explained in the preamble to the rule, we intended to adopt airworthiness directives to mandate any changes found necessary to address unsafe conditions identified as a result of these reviews. In evaluating these design reviews, we have established four criteria intended to define the unsafe conditions associated with fuel tank systems that require corrective actions. The percentage of operating time during which fuel tanks are exposed to flammable conditions is one of these criteria. The other three criteria address the failure types under evaluation: Single failures, single failures in combination with a latent condition(s), and in-service failure experience. For all four criteria, the evaluations included consideration of previous actions taken that may mitigate the need for further action. We have determined that the actions identified in this proposed AD are necessary to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. We have received a report indicating that a potential chafing condition exists in the volute assembly of the forward boost pump for the center fuel tank, on McDonnell Douglas Model 717-200 airplanes. Boeing discovered this condition during an investigation of the wiring installations for the fuel boost pump. The wiring that provides electrical power to the forward boost pump for the center fuel tank is installed in a flexible conduit inside the right wing fuel tank and is routed to the volute assembly. The potential chafing area exists at the 45-degree angle fitting (made of anodized aluminum) of the volute assembly. This angle fitting has been found to have an internal uncontrolled edge that could cause damage to the wiring insulation. Chafed wiring could lead to arcing to the inside of the 45-degree angle fitting. This condition, if not corrected, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. Relevant Service Information We have reviewed Boeing Service Bulletin 717-28-0007, Revision 1, dated September 23, 2003. The service bulletin describes procedures for modifying the conduit for the forward boost pump of the center fuel tank. The modification includes removing conduit from the 45-degree angle fitting of the forward boost pump and routing the conduit to the existing straight fitting in the bottom of the pump volute located in the right wing fuel tank. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. FAA's Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other airplanes of this same type design. For this reason, we are proposing this AD, which would require accomplishing the actions specified in the service information described previously, except as discussed under “Difference between the Proposed AD and Service Bulletin.” Difference Between the Proposed AD and Service Bulletin Although the service bulletin recommends accomplishing the modification at “a scheduled maintenance period when manpower, materials, and facilities are available,” we have determined that this compliance time is imprecise and would not address the identified unsafe condition in a timely manner. In developing an appropriate compliance time for this AD, we considered not only the manufacturer's recommendation, but the degree of urgency associated with addressing the subject unsafe condition, the average utilization of the affected fleet, and the time necessary to perform the modification. In light of all of these factors, we find a compliance time of 78 months for completing the required actions to be warranted, in that it represents an appropriate interval of time for affected airplanes to continue to operate without compromising safety. We have coordinated this difference with Boeing. Costs of Compliance There are about 77 airplanes of the affected design in the worldwide fleet. This proposed AD would affect about 61 airplanes of U.S. registry. The proposed actions would take about 9 work hours per airplane, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost of the proposed AD for U.S. operators is $43,920, or $720 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: 1. Is not a “significant regulatory action” under Executive Order 12866; 2. Is not a “significant rule” under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. 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 proposed 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, Safety. The Proposed 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 Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): McDonnell Douglas: Docket No. FAA-2007-29329; Directorate Identifier 2007-NM-205-AD. Comments Due Date (a) The FAA must receive comments on this AD action by November 26, 2007. Affected ADs (b) None. Applicability (c) This AD applies to McDonnell Douglas Model 717-200 airplanes, certificated in any category; as identified in Boeing Service Bulletin 717-28-0007, Revision 1, dated September 23, 2003. Unsafe Condition (d) This AD results from a finding that a potential chafing condition exists in the volute assembly of the forward boost pump for the center fuel tank. We are issuing this AD to prevent chafing of the forward boost pump wiring that could lead to arcing to the inside of the 45-degree angle fitting, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. 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. Modification (f) Within 78 months after the effective date of this AD, modify the conduit for the forward boost pump of the center fuel tank, by accomplishing all of the actions specified in the Accomplishment Instructions of Boeing Service Bulletin 717-28-0007, Revision 1, dated September 23, 2003. Alternative Methods of Compliance (AMOCs) (g)(1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Issued in Renton, Washington, on October 1, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-20049 Filed 10-10-07; 8:45 am] BILLING CODE 4910-13-P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2007-29330; Directorate Identifier 2007-NM-199-AD] RIN 2120-AA64 Airworthiness Directives; McDonnell Douglas Model 717-200 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain McDonnell Douglas Model 717-200 airplanes. This proposed AD would require electrical bonding of the fill valves for the right and left main fuel tanks, the fill valve and pipe assembly for the center wing fuel tank, and the defuel shutoff valve. This proposed AD results from a fuel system review conducted by the manufacturer. We are proposing this AD to prevent improper bonding of the fill valves and defuel shutoff valve for the main fuel tanks and center wing tank, which, in combination with a lightning strike, could result in a fuel tank explosion and consequent loss of the airplane. DATES: We must receive comments on this proposed AD by November 26, 2007. ADDRESSES: Use one of the following addresses to submit comments on this proposed 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: U.S. Department of Transportation, Docket Operations, M-30, West Building, Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Fax: (202) 493-2251. • Hand Delivery: Room W12-140 on the ground floor of the West Building, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 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 the service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Samuel S. Lee, Aerospace Engineer, Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; telephone (562) 627-5262; fax (562) 627-5210. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number “FAA-2007-29330; Directorate Identifier 2007-NM-199-AD” at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed 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 with FAA personnel concerning this proposed AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review DOT's complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477-78), or you may visit http://dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Operations office (telephone (800) 647-5527) is located on the ground level of the West Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion The FAA has examined the underlying safety issues involved in fuel tank explosions on several large transport airplanes, including the adequacy of existing regulations, the service history of airplanes subject to those regulations, and existing maintenance practices for fuel tank systems. As a result of those findings, we issued a regulation titled “Transport Airplane Fuel Tank System Design Review, Flammability Reduction and Maintenance and Inspection Requirements” (66 FR 23086, May 7, 2001). In addition to new airworthiness standards for transport airplanes and new maintenance requirements, this rule included Special Federal Aviation Regulation No. 88 (“SFAR 88,” Amendment 21-78, and subsequent Amendments 21-82 and 21-83). Among other actions, SFAR 88 requires certain type design (i.e., type certificate (TC) and supplemental type certificate (STC)) holders to substantiate that their fuel tank systems can prevent ignition sources in the fuel tanks. This requirement applies to type design holders for large turbine-powered transport airplanes and for subsequent modifications to those airplanes. It requires them to perform design reviews and to develop design changes and maintenance procedures if their designs do not meet the new fuel tank safety standards. As explained in the preamble to the rule, we intend to adopt airworthiness directives to mandate any changes found necessary to address unsafe conditions identified as a result of these reviews. In evaluating these design reviews, we have established four criteria intended to define the unsafe conditions associated with fuel tank systems that require corrective actions. The percentage of operating time during which fuel tanks are exposed to flammable conditions is one of these criteria. The other three criteria address the failure types under evaluation: Single failures, single failures in combination with a latent condition(s), and in-service failure experience. For all four criteria, the evaluations included consideration of previous actions taken that may mitigate the need for further action. We have determined that the actions identified in this proposed AD are necessary to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. We have received a report indicating that, during fuel tank design review of Model 717-200 airplanes, Boeing found that the fill valves and defuel shutoff valve of the right wing leading edge fuel tank were not electrically bonded to the attaching structure mounting flanges. Investigation revealed that the electrical bonding design requirement was inadvertently omitted during production. Although no reports or incidents have resulted from this condition, electrical bonds should be installed to ensure that lightning-induced high amperage current levels have the correct flow path to the wing fuel tank structure. Improper bonding of the fill valves and defuel shutoff valve for the main fuel tanks and center wing tank, if not corrected, in combination with a lightning strike, could result in a fuel tank explosion and consequent loss of the airplane. Relevant Service Information We have reviewed Boeing Service Bulletin 717-28-0012, Revision 1, dated June 7, 2006. The service bulletin describes procedures for electrical bonding of the fill valves for the right and left main fuel tanks, the fill valve and pipe assembly for the center wing fuel tank, and the defuel shutoff valve. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. FAA's Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other airplanes of this same type design. For this reason, we are proposing this AD, which would require accomplishing the actions specified in the service information described previously. Costs of Compliance There are about 134 airplanes of the affected design in the worldwide fleet. This proposed AD would affect about 104 airplanes of U.S. registry. The proposed actions would take about 4 work hours per airplane, at an average labor rate of $80 per work hour. Required parts would cost about $9 per airplane. Based on these figures, the estimated cost of the proposed AD for U.S. operators is $34,216, or $329 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: 1. Is not a “significant regulatory action” under Executive Order 12866; 2. Is not a “significant rule” under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. 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 proposed 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, Safety. The Proposed 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 Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): McDonnell Douglas: Docket No. FAA-2007-29330; Directorate Identifier 2007-NM-199-AD. Comments Due Date (a) The FAA must receive comments on this AD action by November 26, 2007. Affected ADs (b) None. Applicability (c) This AD applies to McDonnell Douglas Model 717-200 airplanes, certificated in any category, as identified in Boeing Service Bulletin 717-28-0012, Revision 1, dated June 7, 2006. Unsafe Condition (d) This AD results from a fuel system review conducted by the manufacturer. We are issuing this AD to prevent improper bonding of the fill valves and defuel shutoff valve for the main fuel tanks and center wing tank, which, in combination with a lightning strike, could result in a fuel tank explosion and consequent loss of the airplane. 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. Electrical Bonding (f) Within 60 months after the effective date of this AD, accomplish the electrical bonding of the fill valves for the right and left main fuel tanks, the fill valve and pipe assembly for the center wing fuel tank, and the defuel shutoff valve, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 717-28-0012, Revision 1, dated June 7, 2006. Credit for Actions Done Using the Previous Service Information (g) Actions accomplished before the effective date of this AD in accordance with Boeing Service Bulletin 717-28-0012, dated April 16, 2004, are considered acceptable for compliance with the corresponding actions specified in paragraph (f) of this AD. Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Issued in Renton, Washington, on October 1, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-20051 Filed 10-10-07; 8:45 am] BILLING CODE 4910-13-P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2006-26490; Directorate Identifier 2006-CE-75-AD] RIN 2120-AA64 Airworthiness Directives; Alpha Aviation Design Limited (Type Certificate No. A48EU Previously Held by APEX Aircraft and Avions Pierre ROBIN) Model R2160 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: To prevent failure of the wing structure and assembly components due to undetected fatigue and corrosion * * * The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by November 13, 2007. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493-2251. • Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone (800) 647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4146; fax: (816) 329-4090. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include “Docket No. FAA-2006-26490; Directorate Identifier 2006-CE-75-AD” at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The Civil Aviation Authority (CAA), which is the airworthiness authority for New Zealand, has issued AD DCA/R2000/28, dated September 28, 2006 (referred to after this as “the MCAI”), to correct an unsafe condition for the specified products. The MCAI states: To prevent failure of the wing structure and assembly components due to undetected fatigue and corrosion * * * The MCAI requires that you inspect the wing structure and fuselage attachment and repair any defects that you find. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Avions Pierre Robin (recent type certificate responsibility was with APEX Aircraft and current responsibility with Alpha Aviation Design Limited) has issued Service Bulletin No. 123, revision 2, dated November 14, 1995; and Mandatory Service Bulletin No. 123, revision 3, issued December 23, 1999. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA's Determination and Requirements of the Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with this State of Design Authority, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. Differences Between This Proposed AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have proposed different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are described in a separate paragraph of the proposed AD. These requirements, if ultimately adopted, will take precedence over the actions copied from the MCAI. Costs of Compliance We estimate that this proposed AD will affect 10 products of U.S. registry. We also estimate that it will take about 15 work-hours per product to comply with basic requirements of this proposed AD. The average labor rate is $80 per work-hour. Required parts will cost about $1,326 per product. Based on these figures, we estimate the cost of this proposed AD to the U.S. operators to be $25,260 or $2,526 per product. We have no way to determine what aircraft will need replacement parts that may be required based on the results of any inspection. 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a “significant regulatory action” under Executive Order 12866; 2. Is not a “significant rule” under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. 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 proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed 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 AD: Alpha Aviation Design Limited (Type Certificate No. A48EU previously held by Apex Aircraft and Avions Pierre Robin): Docket No. FAA-2006-26490; Directorate Identifier 2006-CE-75-AD. Comments Due Date (a) We must receive comments by November 13, 2007. Affected ADs (b) None. Applicability (c) This AD applies to Model R2160 airplanes, serial numbers 001 through 378, certificated in any category. Reason (d) The mandatory continuing airworthiness information (MCAI) states: To prevent failure of the wing structure and assembly components due to undetected fatigue and corrosion * * * The MCAI requires that you inspect the wing structure and fuselage attachment and repair any defects that you find. Actions and Compliance (e) Unless already done, do the following actions: (1) For airplanes with less than 4,000 hours time-in-service (TIS): When the airplane reaches a total of 3,500 hours TIS or within the next 100 hours TIS after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 750 hours TIS, disassemble the wings from the fuselage and inspect the wing structure and assembly components following instruction No. 1 in Robin Aviation Service Bulletin No. 123, revision 3, dated December 23, 1999. If any defects are found, before further flight, repair following Robin Aviation Service Bulletin No. 123, revision 3, dated December 23, 1999; and Avions Pierre Robin Service Bulletin No. 123, revision 2, issued November 14, 1995. (2) For airplanes with 4,000 hours TIS or more that do not have the special instruction in paragraph E of Avions Pierre Robin Service Bulletin No. 123, revision 2, dated November 14, 1995, incorporated: Within the next 100 hours TIS after the effective date of this AD and thereafter at intervals not to exceed 750 hours TIS, disassemble the wings from the fuselage and inspect the wing structure and assembly components following instruction No. 1 in Robin Aviation Service Bulletin No. 123, revision 3, dated December 23, 1999. If any defects are found, before further flight, repair following Robin Aviation Service Bulletin No. 123, revision 3, dated December 23, 1999; and Avions Pierre Robin Service Bulletin No. 123, revision 2, issued November 14, 1995. (3) For airplanes with 4,000 hours TIS or more that have the special instruction in paragraph E of Avions Pierre Robin Service Bulletin No. 123, revision 2, dated November 14, 1995, incorporated: Within the next 750 hours TIS after the effective date of this AD and thereafter at intervals not to exceed 750 hours TIS, disassemble the wings from the fuselage and inspect the wing structure and assembly components following instruction No. 1 in Robin Aviation Service Bulletin No. 123, revision 3, dated December 23, 1999. If any defects are found, before further flight, repair following Robin Aviation Service Bulletin No. 123, revision 3, dated December 23, 1999; and Avions Pierre Robin Service Bulletin No. 123, revision 2, issued November 14, 1995. (4) For all airplanes: When the airplane reaches a total of 3,500 hours TIS after installation of the wing-to-fuselage bolts or within the next 100 hours TIS after the effective date of this AD, whichever occurs later, do a non-destructive inspection of the wing-to-fuselage retaining bolts and replace any bolts that do not pass this inspection following instruction No. 2 in Robin Aviation Service Bulletin No. 123, revision 3, dated December 23, 1999. (5) For all airplanes: Within the next 50 hours TIS after re-assembling the wing and thereafter at intervals not to exceed 100 hours TIS, inspect the wing-to-fuselage retaining bolts for correct torque settings following instruction No. 3 in Robin Aviation Service Bulletin No. 123, revision 3, dated December 23, 1999. The required torque value is 22 ft-lb with nut part number 95.24.39.010. Tighten to 16 ft-lb (pre-loading) and then torque from 16 to 22 ft-lb. FAA AD Differences Note: This AD differs from the MCAI and/or service information as follows: No Differences. Other FAA AD Provisions (f) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4146; fax: (816) 329-4090. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120-0056. Related Information (g) Refer to MCAI Civil Aviation Authority AD DCA/R2000/28, dated September 28, 2006; Avions Pierre Robin Service Bulletin No. 123, revision 2, issued November 14, 1995; and Robin Aviation Mandatory Service Bulletin No. 123, revision 3, issued December 23, 1999, for related information. Issued in Kansas City, Missouri, on October 4, 2007. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-20047 Filed 10-10-07; 8:45 am] BILLING CODE 4910-13-P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA-2007-29231; Airspace Docket No. 07-AGL-8] Proposed Establishment of Class E5 Airspace; Hinckley, MN AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking. SUMMARY: This action proposes to establish Class E airspace at Hinckley, MN. Additional controlled airspace is necessary to accommodate aircraft using new Area Navigation (RNAV) Global Positioning System (GPS) Instrument Approach Procedures (IAP) at Field of Dreams Airport. The FAA is proposing this action to enhance the safety and management of aircraft operations at Field of Dreams Airport, Hinckley, MN. DATES: Comments must be received on or before November 30, 2007. ADDRESSES: Send comments on this proposal to the Docket Management System, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590. You must identify the docket number FAA-2007-29231/Airspace Docket No. 07-AGL-8, at the beginning of your comments. You may also submit comments on the Internet at http://dms.dot.gov. You may review the public docket containing the proposal, any comments received, and any final disposition in person in 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 on the ground floor of the building at the above address. FOR FURTHER INFORMATION CONTACT: Grant Nichols, System Support, DOT Regional Headquarters Building, Federal Aviation Administration, 901 Locust, Kansas City, MO 64106; telephone (816) 329-2522. SUPPLEMENTARY INFORMATION: Comments Invited Interested parties are invited to participate in this proposed rulemaking by submitting such written data, views, or arguments, as they may desire. Comments that provide the factual basis supporting the views and suggestions presented are particularly helpful in developing reasoned regulatory decisions on the proposal. Comments are specifically invited on the overall regulatory, aeronautical, economic, environmental, and energy-related aspects of the proposal. Communications should identify both docket numbers and be submitted in triplicate to the address listed above. Commenters wishing the FAA to acknowledge receipt of their comments on this notice must submit with those comments a self-addressed, stamped postcard on which the following statement is made: “Comments to Docket No. FAA-2007-29231/Airspace Docket No. 07-AGL-8.” The postcard will be date/time stamped and returned to the commenter. Availability of NPRM's An electronic copy of this document may be downloaded through the Internet at http://dms.dot.gov. Recently published rulemaking documents can also be accessed through the FAA's web page at http://www.faa.gov or the Superintendent of Document's web page at http://www.access.gpo.gov/nara. Additionally, any person may obtain a copy of this notice by submitting a request to the Federal Aviation Administration (FAA), Office of Air Traffic Airspace Management, ATA-400, 800 Independence Avenue, SW., Washington, DC 20591, or by calling (202) 267-8783. Communications must identify both docket numbers for this notice. Persons interested in being placed on a mailing list for future NPRM's should contact the FAA's Office of Rulemaking (202) 267-9677, to request a copy of Advisory Circular No. 11-2A, Notice of Proposed Rulemaking Distribution System, which describes the application procedure. The Proposal This action proposes to amend Title 14, Code of Federal Regulations (14 CFR) part 71, by establishing a Class E airspace area extending upward from 700 feet above the surface at Field of Dreams Airport, Hinckley, MN. The establishment of RNAV (GPS) IAPs have made this action necessary. The intended effect of this proposal is to provide adequate controlled airspace for Instrument Flight Rules operations at Field of Dreams Airport, Hinckley, MN. The area would be depicted on appropriate aeronautical charts. Class E airspace areas extending upward from 700 feet or more above the surface of the earth are published in Paragraph 6005 of FAA Order 7400.9R, signed August 15, 2007, and effective September 15, 2007, which is incorporated by reference in 14 CFR 71.1. The Class E airspace designations listed in this document would be published subsequently in the Order. The FAA has determined that this proposed regulation only involves an established body of technical regulations for which frequent and routine amendments are necessary to keep them operationally current. It, therefore, (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) does not warrant preparation of a Regulatory Evaluation as the anticipated impact is so minimal. Since this is a routine matter that will only affect air traffic procedures and air navigation, it is certified that this rule, when promulgated, will not have a significant economic impact on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. This rulemaking is promulgated under the authority described in Subtitle VII, Part A, Subpart I, Section 40103. Under that section, the FAA is charged with prescribing regulations to assign the use of the airspace necessary to ensure the safety of aircraft and the efficient use of airspace. This regulation is within the scope of that authority as it would enhance the safety and management of aircraft operations at Field of Dreams Airport, Hinckley, MN. List of Subjects in 14 CFR Part 71 Airspace, Incorporation by reference, Navigation (Air). The Proposed Amendment In consideration of the foregoing, the Federal Aviation Administration proposes to amend 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 7400.9R, Airspace Designations and Reporting Points, signed August 15, 2007, and effective September 15, 2007, is amended as follows: Paragraph 6005 Class E airspace areas extending upward from 700 feet or more above the surface of the earth. AGL MN E5 Hinckley, MN [New] Field of Dreams Airport, Hinckley, MN (Lat. 46°01′22″ N., long. 92°53′44″ W.) That airspace extending upward from 700 feet above the surface within a 6.7-mile radius of the Field of Dreams Airport, Hinckley, MN. Issued in Forth Worth, TX, on September 25, 2007. Ronnie L. Uhlenhaker, Team Manager, System Support Group, ATO Central Service Center. [FR Doc. 07-5001 Filed 10-10-07; 8:45 am]