Rules and Regulations. Final rule

Agency: Federal Aviation Administration (FAA), Department of Transportation (DOT)
Action: Final rule
Citation: FR Doc. 06-55527 · RIN 2120-AA64 · 14 CFR 39

Summary

The FAA is adopting a new airworthiness directive (AD) for certain Honeywell COM units and transponders, installed on but not limited to certain transport category airplanes. This AD requires a revision to the Normal Procedures section of the airplane flight manual to advise the flightcrew to check the status of the transponder after changing the air traffic control (ATC) code. This AD also requires replacing certain identification plate(s) with new plate(s), testing certain COM units or transponders as applicable, and corrective action if necessary. For certain airplanes, this AD requires replacing the transponders of certain COM units with new or modified transponders. For certain other airplanes, this AD requires installing a modification into certain transponders. This AD results from the transponder erroneously going into standby mode if the flightcrew takes longer than five seconds when using the rotary knob of the radio management unit to change the ATC code. We are issuing this AD to prevent the transponder of the COM unit from going into standby mode, which could increase the workload on the flightcrew and result in improper functioning of the traffic alert and collision avoidance system.

Dates

This AD becomes effective October 17, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of October 17, 2006.

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 would apply to certain Honeywell RCZ-833J/K, -851J/K, and -854J communication (COM) units, equipped with XS-852E/F mode S transponders; and Honeywell XS-856A/B and -857A mode S transponders; installed on but not limited to certain transport category airplanes. That NPRM was published in the Federal Register on May 3, 2006 (71 FR 25984). That NPRM proposed to require a revision to the Normal Procedures section of the airplane flight manual (AFM) to advise the flightcrew to check the status of the transponder after changing the air traffic control (ATC) code. That NPRM also proposed to require replacing certain identification plate(s) with new plate(s), testing certain COM units or transponders as applicable, and corrective action if necessary. For certain airplanes, that NPRM proposed to require replacing the transponders of certain COM units with new or modified transponders. For certain other airplanes, that NPRM proposed to require installing a modification into certain transponders. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Support for NPRM The Air Line Pilots Association supports the NPRM. Request To Revise Applicability Dassault Falcon Jet (DFJ) requests that we delete Dassault Model Mystere-Falcon 900 airplanes and Model Falcon 2000 airplanes from the applicability of the NPRM. DFJ states that none of the discrepant communication units or transponders are installed on these model airplanes. According to DFJ, the discrepant parts are installed only on Model Falcon 900EX airplanes, serial number (S/N) 97 and S/Ns 120 and subsequent; and Model Falcon 2000EX airplanes, S/N 6 and S/Ns 28 and subsequent. We agree and have revised paragraph (c) of this AD accordingly. Request To Revise Compliance Time Empresa Brasileira de Aeronautica S.A. (EMBRAER) requests that we extend the compliance time for the AFM revision from 5 to 30 days. EMBRAER asserts that the loss of the transponder does not pose so great of a hazard to justify such an urgent compliance time. As justification for extending the compliance time, EMBRAER states that some of the affected airplanes might be on international trips, where it may not be possible to return an airplane to a convenient location and accomplish the AFM revision within 5 days after the effective date of this AD. We agree that the compliance times can be extended somewhat. We have determined that extending the compliance time to 14 days will not adversely affect safety. Therefore, we have revised paragraph (f) of this AD accordingly. Request To Revise Address of Part Manufacturer Honeywell states that its address, as provided in the NPRM, is no longer valid. Therefore, the commenter requests that we include the following address to acquire service information pertaining to this AD: 21111 North 19th Avenue, Phoenix, Arizona 85308. We agree and have verified with the United States Postal Service that the correct zip code for the address given above is 85027-2708. We have updated the commenter's address in the ADDRESSES section and in paragraph (n) of this AD. Request To Revise Requirements Honeywell disagrees with the proposed corrective action to reinstall MOD V into the transponder of the COM unit if the COM unit fails the test described in paragraph (g) of the NPRM. (We proposed to accomplish this corrective action in accordance with Honeywell Alert Service Bulletin 7517400-23-A6015, Revision 001, dated July 29, 2005.) The commenter states that Honeywell Alert Service Bulletin 7510700-23-A0048, dated January 27, 2006, recommends only to verify that MOD AT has been installed and update the part number (P/N) of the COM unit for tracking purposes. Honeywell believes that it would be preferable to have operators inspect the COM unit to determine if MOD AT (transponder MOD V) has been installed. Honeywell adds that if MOD AT is installed, the airplane should be allowed to keep flying even if the COM unit P/N has not been updated. Honeywell's justification is that the airplane has already received the fix and that updating the COM unit P/N adds no value. The commenter further proposes that the NPRM should advise operators that if a COM unit is returned to a shop for any reason, the replacement part must have the new P/N (with MOD AT) before it can be returned to the original equipment manufacturer (OEM) or operator. As justification, Honeywell states that a purge of all old P/Ns will take place once all OEMs have allowed the new P/Ns. We disagree. Honeywell proposes an alternative action only if a COM unit is inspected and determined to have MOD AT installed. However, the commenter offers no alternative if a COM unit is determined to not have MOD AT installed (i.e., fails the test described in paragraph (g) of this AD). MOD AT is accomplished by installing an XS-852E/F mode S transponder having MOD V into the COM unit. Therefore, if a COM unit fails the test described in paragraph (g) of this AD, we have determined that the corrective action is to reinstall MOD V into the transponder of the COM unit, thereby ensuring that MOD AT has been installed properly. Further, we do not find it acceptable to allow some COM units to remain in service without updated P/Ns, even if MOD AT has been installed. This would create a high rate of confusion among OEMs, operators, and other end users in determining which COM units are in compliance with this AD. We have not revised this AD in this regard. 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. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance There are about 1,365 airplanes of the affected design in the worldwide fleet. This AD affects about 1,023 airplanes of U.S. registry. Of those airplanes, about 603 airplanes are equipped with RCZ-833J/K, -851J/K, or -854J COM units, and about 420 airplanes are equipped with XS-856A/B or -857A mode S transponders. The following table provides the estimated costs, at an average labor rate of $80 per work hour, for U.S. operators to comply with this AD. Estimated Costs Action Work hours Parts Cost per airplane Number of U.S.-registered airplanes Fleet cost AFM revision 1 None $80 1,023 $81,840. Part identification, testing, and replacement for RCZ-833J/K, -851J/K, and -854J COM units 3 $35 $275 603 $165,825. Part identification, testing, and installation of software for XS-856A/B and -857A mode S transponders 3 to 8, depending on test procedure $175 $415 to $815, depending on testing procedure 420 $174,300 to $342,300, depending on testing procedure. 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): 2006-19-04 Honeywell International, Inc.: Amendment 39-14761. Docket No. FAA-2006-24639; Directorate Identifier 2005-NM-171-AD. Effective Date (a) This AD becomes effective October 17, 2006. Affected ADs (b) None. Applicability (c) This AD applies to the Honeywell parts identified in paragraphs (c)(1) and (c)(2) of this AD, approved under Technical Standard Order TSO-C112, installed on but not limited to Bombardier Model BD-700-1A10 and BD-700-1A11 airplanes; Cessna Model 550 and 560 airplanes; Cessna Model 650 airplanes; Dassault Model Falcon 900EX airplanes, serial number (S/N) 97 and S/Ns 120 and subsequent; Dassault Model Falcon 2000EX airplanes, S/N 6 and S/Ns 28 and subsequent; EMBRAER Model EMB-135BJ, -135ER, -135KE, -135KL, and -135LR airplanes; EMBRAER Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP airplanes; Learjet Model 45 airplanes; Lockheed Model 282-44A-05 (C-130B) airplanes; Lockheed Model 382G series airplanes; Raytheon Model Hawker 800 (including variant U-125A), 800XP, and 1000 airplanes; certificated in any category. (1) Communication (COM) unit RCZ-833J part numbers (P/Ns) 7510700-763 and -863; RCZ-833K P/Ns 7510700-765 and -875; RCZ-851J P/N 7510700-813; RCZ-851K P/N 7510700-815; and RCZ-854J P/Ns 7510700-725 and -825. (2) Mode S transponder XS-856A P/Ns 7517400-865 and -885; XS-856B P/Ns 7517400-866 and -886; and XS-857A P/Ns 7517400-876 and -896. Unsafe Condition (d) This AD results from the transponder erroneously going into standby mode if the flightcrew takes longer than five seconds when using the rotary knob of the radio management unit to change the air traffic control code. We are issuing this AD to prevent the transponder of the COM unit from going into standby mode, which could increase the workload on the flightcrew and result in improper functioning of the traffic alert and collision avoidance system. 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. Airplane Flight Manual (AFM) Revision (f) For all airplanes: Within 14 days after the effective date of this AD, revise the Normal Procedures section of the applicable AFM to include the following statement: “After completion of any 4096 ATC Code change (also referred to as Mode A Code), check the status of the transponder. If the transponder indicates that it is in standby mode, re-select the desired mode (i.e., the transponder should be in the active mode).” This may be done by inserting a copy of this AD in the AFM. Accomplishing the actions specified in paragraph (h) or (j), as applicable, of this AD terminates the requirement of this paragraph. Replacement of Identification Plates for Certain COM Units (g) For airplanes equipped with any COM unit identified in paragraph (c)(1) of this AD: Within 18 months after the effective date of this AD, replace the product signature plate, identification plate, and MOD plate of the COM unit with new plates and test the COM unit, in accordance with the Accomplishment Instructions of Honeywell Alert Service Bulletin 7510700-23-A0048, dated January 27, 2006. If the COM unit fails the test, before further flight, reinstall MOD V into the transponder of the COM unit in accordance with Honeywell Alert Service Bulletin 7517400-23-A6015, Revision 001, dated July 29, 2005. Replacement of Certain Transponders (h) For airplanes equipped with any COM unit identified in paragraph (c)(1) of this AD: Before or concurrently with the actions required by paragraph (g) of this AD, replace the XS-852E/F mode S transponder of the COM unit with a new or modified XS-852E/F mode S transponder that has MOD V installed, in accordance with Honeywell Alert Service Bulletin 7510700-23-A0047, Revision 001, dated July 29, 2005. After accomplishing the replacement required by this paragraph, the AFM revision required by paragraph (f) of this AD may be removed from the AFM. Note 1: Honeywell Alert Service Bulletin 7510700-23-A0047, Revision 001, dated July 29, 2005, refers to Honeywell Alert Service Bulletin 7517400-23-A6015, Revision 001, dated July 29, 2005, as an additional source of service information for installing MOD V into an XS-852E/F mode S transponder. Replacement of Identification Plate for Certain Transponders (i) For airplanes equipped with any transponder identified in paragraph (c)(2) of this AD: Within 18 months after the effective date of this AD, replace the modification plate of the transponder with a new plate and test the transponder, in accordance with the Accomplishment Instructions of Honeywell Alert Service Bulletin 7517400-23-A0017, dated January 23, 2006. If the transponder fails the test, before further flight, reinstall MOD Y into the transponder as specified in paragraph (j) of this AD. Installation of MOD Y Into Certain Transponders (j) For airplanes equipped with any transponder identified in paragraph (c)(2) of this AD: Before or concurrently with the actions required by paragraph (i) of this AD, install MOD Y into the applicable mode S transponder, in accordance with the Accomplishment Instructions of Honeywell Alert Service Bulletin 7517400-23-A6016, dated August 30, 2005. After accomplishing the replacement required by this paragraph, the AFM revision required by paragraph (f) of this AD may be removed from the AFM. Parts Installation (k) For all airplanes: As of the effective date of this AD, no person may install any part identified in paragraph (c)(1) or (c)(2) on any airplane, unless the applicable software modification has been installed in the transponder in accordance with paragraph (h) or (j) of this AD, as applicable. No Reporting Requirement (l) Although the service bulletins referenced in this AD specify to submit certain information to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (m)(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) 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. Material Incorporated by Reference (n) You must use the service information identified in Table 1 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. Table 1.—Material Incorporated by Reference Service bulletin Revision level Date Honeywell Alert Service Bulletin 7510700-23-A0047 001 July 29, 2005. Honeywell Alert Service Bulletin 7510700-23-A0048 Original January 27, 2006. Honeywell Alert Service Bulletin 7517400-23-A6015 001 July 29, 2005. Honeywell Alert Service Bulletin 7517400-23-A6016 Original August 30, 2005. Honeywell Alert Service Bulletin 7517400-23-A0017 Original January 23, 2006. (Only the first and second pages of Honeywell Alert Service Bulletin 7510700-23-A0047 and Honeywell Alert Service Bulletin 7517400-23-A6015 contains the revision level of the document.) The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Go to https://pubs.cas.honeywell.com/ or contact Honeywell International, Inc., Commercial Electronic Systems, 21111 North 19th Avenue, Phoenix, Arizona 85027-2708, 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 h ttp://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html . Issued in Renton, Washington, on August 31, 2006. Kalene C. Yanamura, Acting Manager,Transport Airplane Directorate,Aircraft Certification Service. [FR Doc. E6-14940 Filed 9-11-06; 8:45 am] BILLING CODE 4910-13-P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2006-24787; Directorate Identifier 2006-NM-043-AD; Amendment 39-14760; AD 2006-19-03] RIN 2120-AA64 Airworthiness Directives; McDonnell Douglas Model DC-10-10 and DC-10-10F Airplanes; Model DC-10-15 Airplanes; Model DC-10-30 and DC-10-30F (KC-10A and KDC-10) Airplanes; Model DC-10-40 and DC-10-40F Airplanes; 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 adopting a new airworthiness directive (AD) for certain McDonnell Douglas transport category airplanes. This AD requires fabrication and installation of a wire harness guard in the right wheel well of the main landing gear (MLG), and related investigative and corrective actions as necessary. For certain airplanes, this AD also requires replacement of the electrical connectors of the auxiliary hydraulic pumps with improved electrical connectors and related investigative and corrective actions. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent damage to the wire support bracket and wiring of the auxiliary hydraulic pump and, for certain airplanes, water intrusion through the electrical connectors of the auxiliary hydraulic pump. These conditions could lead to a potential ignition source in the right wheel well of the MLG around the fuel tank, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. DATES: This AD becomes effective October 17, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of October 17, 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 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: Ken Sujishi, Aerospace Engineer, Cabin Safety/Mechanical and Environmental Systems Branch, ANM-150L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; telephone (562) 627-5353; 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 would apply to certain McDonnell Douglas Model DC-10-10 and DC-10-10F airplanes; Model DC-10-15 airplanes; Model DC-10-30 and DC-10-30F (KC-10A and KDC-10) airplanes; Model DC-10-40 and DC-10-40F airplanes; Model MD-10-10F and MD-10-30F airplanes; and Model MD-11 and MD-11F airplanes. That NPRM was published in the Federal Register on May 17, 2006 (71 FR 28622). That NPRM proposed to require fabrication and installation of a wire harness guard in the right wheel well of the main landing gear (MLG), and related investigative and corrective actions as necessary. For certain airplanes, that NPRM also proposed to require replacement of the electrical connectors of the auxiliary hydraulic pumps with improved electrical connectors and related investigative and corrective actions. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Support for the NPRM Two private citizens support the NPRM. Request To Allow Replacement With FAA-Approved Equivalent Parts The Modification and Replacement Parts Association (MARPA) requests that we append the language in paragraph (f)(2) of the NPRM to add the following words, “or FAA-approved equivalent part number.” MARPA contends that the addition of those words would remove any possible conflict with 14 CFR 21.303 that may be raised with respect to the unmodified text in paragraph (f)(2) of the NPRM. We infer that the commenter would like the AD to permit installation of any equivalent parts manufacturer approval (PMA) parts so that it is not necessary for an operator to request approval of an alternative method of compliance (AMOC) in order to install an “equivalent” PMA part. Whether an alternative part is “equivalent” in adequately resolving the unsafe condition can only be determined on a case-by-case basis based on a complete understanding of the unsafe condition. The Transport Airplane Directorate's policy is that, in order for operators to replace a part with one that is not specified in the AD, they must request an AMOC. This is necessary so that we can make a specific determination that an alternative part is or is not susceptible to the same unsafe condition. In response to the commenter's statement regarding a “possible conflict with 14 CFR 21.303,” under which the FAA issues PMAs, this statement appears to reflect a misunderstanding of the relationship between ADs and the certification procedural regulations of part 21 of the Federal Aviation Regulations (14 CFR part 21). Those regulations, including section 21.303 of the Federal Aviation Regulations (14 CFR 21.303), are intended to ensure that aeronautical products comply with the applicable airworthiness standards. But ADs are issued when, notwithstanding those procedures, we become aware of unsafe conditions in these products or parts. Therefore, an AD takes precedence over design approvals when we identify an unsafe condition, and mandating installation of a certain part number in an AD is not at variance with section 21.303. The AD provides a means of compliance for operators to ensure that the identified unsafe condition is addressed appropriately. For an unsafe condition attributable to a part, the AD normally identifies the replacement parts necessary to obtain that compliance. As stated in section 39.7 of the Federal Aviation Regulations (14 CFR 39.7): “Anyone who operates a product that does not meet the requirements of an applicable airworthiness directive is in violation of this section.” Unless an operator obtains approval for an AMOC, replacing a part with one not specified by the AD would make the operator subject to an enforcement action and result in a civil penalty. No change to the AD is necessary in this regard. Request for Agreement on Parts Replacement MARPA also points out that another AD issued from a Directorate other than the Transport Airplane Directorate does contain the wording that he has requested. The commenter contends that, “when two parallel departments of the same government agency maintain policies and practices that conflict one with the other, indeed even to opposite ends, there needs to evolve a solution that will remove the conflict.” MARPA further contends that “to harbor an inherent conflict in how an issue is treated is an invitation for the courts to remove that conflict and is [sic] so doing invalidates those orders based upon the interpretation found to be defective.” The commenter, therefore, requests that the FAA agree, in a timely manner, on how the matter is to be treated. The FAA acknowledges that the Directorates are not consistent in their policies and practices on this issue. We recognize the need for standardization on this issue and currently are in the process of reviewing it at the national level. The Transport Airplane Directorate considers that to delay this particular 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. Therefore, no change has been made to the final rule in this regard. 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 as proposed. Costs of Compliance There are about 627 airplanes of the affected design in the worldwide fleet. This AD affects about 303 airplanes of U.S. registry. The following table provides the estimated costs, at an average labor rate of $80 per hour, for U.S. operators to comply with this AD. Estimated Costs Models Action Work hours Parts Cost per airplane Number of U.S.- registered airplanes Fleet cost DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, and MD-10-30F airplanes Fabrication and installation 3 $889 $1,129 206 $232,574 Replacement 2 290 450 206 92,700 MD-11 and MD-11F airplanes Fabrication and installation 3 866 1,106 97 107,282 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): 2006-19-03 McDonnell Douglas: Amendment 39-14760. Docket No. FAA-2006-24787; Directorate Identifier 2006-NM-043-AD. Effective Date (a) This AD becomes effective October 17, 2006. Affected ADs (b) None. Applicability (c) This AD applies to the McDonnell Douglas airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category. (1) Model DC-10-10 and DC-10-10F airplanes; Model DC-10-15 airplanes; Model DC-10-30 and DC-10-30F (KC-10A and KDC-10) airplanes; Model DC-10-40 and DC-10-40F airplanes; and Model MD-10-10F and MD-10-30F airplanes; fuselage numbers (F/Ns) 1 through 446 inclusive. (2) Model MD-11 and MD-11F airplanes; F/Ns 0447, 0448, 0449, 0451 through 0464 inclusive, 0466 through 0489 inclusive, 0491 through 0517 inclusive, 0519 through 0552 inclusive, and 0554 through 0646 inclusive. Unsafe Condition (d) This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent damage to the wire support bracket and wiring of the auxiliary hydraulic pump and, for certain airplanes, water intrusion through the electrical connectors of the auxiliary hydraulic pump. These conditions could lead to a potential ignition source in the right wheel well of the main landing gear (MLG) around the fuel tank, which, in combination with flammable fuel vapors, could result in fuel tank explosions 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. Installation and Replacement for Certain Airplanes (f) For Model DC-10-10 and DC-10-10F airplanes; Model DC-10-15 airplanes; Model DC-10-30 and DC-10-30F (KC-10A and KDC-10) airplanes; Model DC-10-40 and DC-10-40F airplanes; and Model MD-10-10F and MD-10-30F airplanes: Within 60 months after the effective date of this AD, do the actions specified in paragraph (f)(1) and (f)(2) of this AD. (1) Fabricate a wire harness guard and install it in the right wheel well of the MLG, and do all related investigative and applicable corrective actions, by accomplishing all of the actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin DC10-29A146, Revision 1, dated April 6, 2005; except as provided by paragraph (h) of this AD. Do all applicable corrective actions before further flight. If any debris is found in the area around the wiring of the auxiliary hydraulic pump, before further flight, clean the area of the debris. (2) Replace any electrical connector having part number (P/N) DC62E24-10SN or FC6DE24-10S of the auxiliary hydraulic pumps at the right wheel well of the MLG with improved electrical connectors having P/N DC62F24-10SN, and do the related investigative action before further flight, by accomplishing all of actions specified in the Accomplishment Instructions of McDonnell Douglas DC-10 Service Bulletin 29-135, dated September 8, 1993. If the auxiliary hydraulic system fails the test, before further flight, repair the auxiliary hydraulic system according to a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA. Chapter 29-20-00 of the Boeing DC-10 Aircraft Maintenance Manual is one approved method. Installation for Other Certain Airplanes (g) For Model MD-11 and MD-11F airplanes: Within 60 months after the effective date of this AD, fabricate and install a wire harness guard in the right wheel well of the MLG, and do all related investigative and applicable corrective actions, by accomplishing all of the actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin MD11-29A060, dated April 30, 2001; except as provided by paragraph (h) of this AD. Do all applicable corrective actions before further flight. If any debris is found in the area around the wiring of the auxiliary hydraulic pump, before further flight, clean the area of the debris. Rivet P/N MS20470AD5-7, shown in the parts and material table in paragraph 2.C.2 of the service bulletin, is not a valid P/N; the correct P/N that must be used is P/N MS20470AD6-7. Exception to Service Bulletins (h) Where the Accomplishment Instructions of Boeing Alert Service Bulletin DC10-29A146, Revision 1, dated April 6, 2005; and Boeing Alert Service Bulletin MD11-29A060, dated April 30, 2001, specify doing a visual inspection of the wiring installations of the auxiliary hydraulic pump in the right main wheel well at station Y=1381 for chafing, do a general visual inspection. 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.” Credit for Original Issue of Service Bulletin (i) For Model DC-10-10 and DC-10-10F airplanes; Model DC-10-15 airplanes; Model DC-10-30 and DC-10-30F (KC-10A and KDC-10) airplanes; Model DC-10-40 and DC-10-40F airplanes; and Model MD-10-10F and MD-10-30F airplanes: Actions done before the effective date of this AD in accordance with Boeing Alert Service Bulletin DC10-29A146, dated April 30, 2001, are acceptable for compliance with the corresponding requirements of this AD. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, Los Angeles 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) 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. Material Incorporated by Reference (k) You must use the service information identified in Table 1 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. Table 1—Material Incorporated by Reference Service bulletin Revision level Date Boeing Alert Service Bulletin DC10-29A146 1 April 6, 2005. Boeing Alert Service Bulletin MD11-29A060 Original April 30, 2001. McDonnell Douglas DC-10 Service Bulletin 29-135 Original September 8, 1993. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 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 September 1, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-14939 Filed 9-11-06; 8:45 am] BILLING CODE 4910-13-P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2006-25047; Directorate Identifier 2006-NM-028-AD; Amendment 39-14759; AD 2006-19-02] RIN 2120-AA64 Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model A300 C4-605R Variant F Airplanes (Collectively Called A300-600 Series 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 Airbus Model A300-600 series airplanes. That AD currently requires repetitive eddy current inspections to detect cracks of the outer skin of the fuselage at certain frames, and repair or reinforcement of the structure at the frames, if necessary. That AD also requires eventual reinforcement of the structure at certain frames, which, when accomplished, terminates the repetitive inspections. This new AD requires, for airplanes that were previously reinforced but not repaired in accordance with the existing AD, a one-time inspection for cracking of the fuselage outer skin at frames 28A and 30A above stringer 30, and repair if necessary. This AD results from a report that the previously required actions were not sufficient to correct cracking before the structural reinforcement was installed. We are issuing this AD to prevent such fatigue cracking, which could result in reduced structural integrity, and consequent rapid decompression of the airplane. DATES: This AD becomes effective October 17, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of October 17, 2006. On August 4, 1997 (62 FR 35072, June 30, 1997), the Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A300-53-6045, dated March 21, 1995, as revised by Change Notice No. O.A., dated June 1, 1995; and Airbus Service Bulletin A300-53-6037, dated March 21, 1995. 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: Tom Stafford, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-1622; fax (425) 227-1149. 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 97-14-02, amendment 39-10059 (62 FR 35072, June 30, 1997). The existing AD applies to certain Airbus Model A300-600 series airplanes. That NPRM was published in the Federal Register on June 15, 2006 (71 FR 34563). That NPRM proposed to continue to require repetitive eddy current inspections to detect cracks of the outer skin of the fuselage at certain frames, and repair or reinforcement of the structure at the frames, if necessary. That NPRM also proposed to continue to require eventual reinforcement of the structure at certain frames, which, when accomplished, terminates the repetitive inspections. That NPRM also proposed to require, for airplanes that were previously reinforced but not repaired in accordance with the existing AD, a one-time inspection for cracking of the fuselage outer skin at frames 28A and 30A above stringer 30, and repair if necessary. Comments We provided the public the opportunity to participate in the development of this AD. No comments have been received on the NPRM 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. Costs of Compliance This AD will affect about 53 airplanes of U.S. registry. The following table provides the estimated costs for U.S. operators to comply with this AD. The average labor rate is $80 per work hour. Estimated Costs Action Work hours Parts Cost per airplane Fleet cost Inspection (required by AD 97-14-02) 1 None $80, per inspection cycle $4,240, per inspection cycle. Reinforcement (required by AD 97-14-02) 93 $7,200 $14,640 $775,920. Inspection (new required action) 1 None $80 $4,240. 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 removing amendment 39-10059 (62 FR 35072, June 30, 1997) and by adding the following new airworthiness directive (AD): 2006-19-02 Airbus: Amendment 39-14759. Docket No. FAA-2006-25047; Directorate Identifier 2006-NM-028-AD. Effective Date (a) This AD becomes effective October 17, 2006. Affected ADs (b) This AD supersedes AD 97-14-02. Applicability (c) This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes, certificated in any category, except those on which Airbus Modification 8683 has been done. Unsafe Condition (d) This AD results from a report that the previously required actions were not sufficient to correct cracking before the structural reinforcement was installed. We are issuing this AD to prevent fatigue cracking of the outer skin of the fuselage at certain frames, which could result in reduced structural integrity, and consequent 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. Restatement of the Requirements of AD 97-14-02 (f) Prior to the accumulation of 14,100 total flight cycles, or within 12 months after August 4, 1997 (the effective date of AD 97-14-02), whichever occurs later, conduct an eddy current inspection to detect cracking of the fuselage outer skin at frames 28A and 30A above stringer 30, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6045, dated March 21, 1995, as revised by Change Notice No. O.A., dated June 1, 1995; or Airbus Service Bulletin A300-53-6045, Revision 03, dated October 28, 2004. After the effective date of this AD, only Revision 03 may be used. After the effective date of this AD, the initial eddy current inspection and all applicable repairs required by this paragraph must be done before doing the reinforcement specified in paragraph (g) of this AD. (1) If no cracking is found, repeat the eddy current inspection thereafter at intervals not to exceed 4,500 flight cycles. (2) If any cracking is found that is within the limits specified in the service bulletin: Prior to further flight do the actions in paragraph (f)(2)(i) or (f)(2)(ii) of this AD. After the effective date of this AD, only Airbus Service Bulletin A300-53-6045, Revision 03, dated October 28, 2004, may be used for the repair specified in paragraph (f)(2)(i) of this AD; and the reinforcement option specified in paragraph (f)(2)(ii) of this AD is not allowed in accordance with this paragraph. (i) Repair in accordance with paragraph 2.D. of the Accomplishment Instructions of Airbus Service Bulletin A300-53-6045, dated March 21, 1995, as revised by Change Notice No. O.A., dated June 1, 1995; or paragraph 3.C. of the Accomplishment Instructions of Airbus Service Bulletin A300-53-6045, Revision 03, dated October 28, 2004. After the repair, repeat the eddy current inspection thereafter at intervals not to exceed 4,500 flight cycles. (ii) Reinforce the structure at frames 28 and 29, and at frames 30 and 31, between stringers 29 and 30, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6037, dated March 21, 1995; or Airbus Service Bulletin A300-53-6037, Revision 02, dated October 28, 2004. Such reinforcement constitutes terminating action for the repetitive inspections required by this AD. (3) If any cracking is found that is outside the limits specified in the service bulletin: Prior to further flight, reinforce the structure at frames 28 and 29, and at frames 30 and 31, between stringers 29 and 30, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6037, dated March 21, 1995; or Airbus Service Bulletin A300-53-6037, Revision 02, dated October 28, 2004. After the effective date of this AD, only Revision 02 may be used. Such reinforcement constitutes terminating action for the repetitive inspections required by this AD. (g) Within 5 years after August 4, 1997: Reinforce the structure at frames 28 and 29, and at frames 30 and 31, between stringers 29 and 30, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6037, dated March 21, 1995; or Airbus Service Bulletin A300-53-6037, Revision 02, dated October 28, 2004. After the effective date of this AD, only Revision 02 may be used. Such reinforcement constitutes terminating action for the repetitive inspections required by this AD. After the effective date of this AD, the initial eddy current inspection and all applicable repairs required by paragraph (f) of this AD must be done before doing the reinforcement. New Requirements of This AD Inspection and Corrective Action (h) For airplanes that meet the conditions of both paragraphs (h)(1) and (h)(2) of this AD: Within 2,400 flight cycles or 18 months after the effective date of this AD, whichever occurs first, conduct an eddy current inspection to detect cracking of the fuselage outer skin at frames 28A and 30A above stringer 30, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6045, Revision 03, dated October 28, 2004. If no cracking is found: No further action is required by this paragraph. If any cracking is found: Before further flight, repair the cracking using a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Direction Générale de l'Aviation Civile (DGAC) (or its delegated agent). (1) Airplanes that were reinforced before the effective date of this AD in accordance with any service bulletin specified in Table 1 of this AD. Table 1.—Reinforcement Service Bulletins Airbus service bulletin Revision level Date A300-53-6037 Original March 21, 1995. 1 February 3, 1999. 02 October 28, 2004. (2) Airplanes that were not inspected and repaired in accordance with any service bulletin specified in Table 2 of this AD. Table 2.—Inspection and Repair Service Bulletins Airbus service bulletin Revision level Date A300-53-6045 Original March 21, 1995. 01 August 25, 1997. 02 May 2, 1999. 03 October 28, 2004. 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-2005-002, dated January 5, 2005, also addresses the subject of this AD. Material Incorporated by Reference (k) You must use the service information identified in Table 3 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. Table 3.—Material Incorporated by Reference Airbus service bulletin Revision level Date A300-53-6037 Original March 21, 1995. A300-53-6037 02 October 28, 2004. A300-53-6045 03 October 28, 2004. A300-53-6045, as revised by Change Notice No. O.A., dated June 1, 1995 Original March 21, 1995. (1) The Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A300-53-6037, Revision 02, dated October 28, 2004; and Airbus Service Bulletin A300-53-6045, Revision 03, dated October 28, 2004; in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On August 4, 1997 (62 FR 35072, June 30, 1997), the Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A300-53-6045, dated March 21, 1995, as revised by Change Notice No. O.A., dated June 1, 1995; and Airbus Service Bulletin A300-53-6037, dated March 21, 1995. (3) 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 September 1, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-14942 Filed 9-11-06; 8:45 am] BILLING CODE 4910-13-P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2006-25746; Directorate Identifier 2006-NM-151-AD; Amendment 39-14750; AD 2006-18-11] RIN 2120-AA64 Airworthiness Directives; Boeing Model 737-200, -300, -400, and -500 Series Airplanes Equipped With an Auxiliary Fuel System Installed in Accordance With Supplemental Type Certificate (STC) SA83NE, SA1078NE, SA725NE, ST00040NY, or ST01337NY AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-200, -300, -400, and -500 series airplanes equipped with an auxiliary fuel system installed in accordance with STC SA83NE, SA1078NE, SA725NE, ST00040NY, or ST01337NY. This AD requires a one-time deactivation of the auxiliary fuel system, repetitive venting of the auxiliary fuel tanks, and revising the Limitations section of the airplane flight manual to limit the maximum cargo weight. This AD results from a re-evaluation of the floor structure and cargo barriers conducted by the STC holder. We are issuing this AD to prevent structural overload of the auxiliary fuel tank support structure, which could cause the floor beams to fail and resultant damage to the primary flight controls and the auxiliary power unit fuel lines that pass through the floor beams, and consequent loss of control of the airplane. We are also issuing this AD to prevent structural overload of the cargo barriers, which could cause the barriers to fail, allowing the cargo to shift, resulting in possible damage to the auxiliary fuel tanks, residual fuel leakage, and consequent increased risk of a fire. DATES: This AD becomes effective September 27, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of September 27, 2006. We must receive comments on this AD by November 13, 2006. ADDRESSES: Use one of the following addresses to submit comments 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. • Fax: (202) 493-2251. • Hand Delivery: Room PL-401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact PATS Aircraft, LLC, Product Support, 21652 Nanticoke Avenue, Georgetown, Delaware 19947, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Jon Hjelm, Aerospace Engineer, Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228-7323; fax (516) 794-5531. SUPPLEMENTARY INFORMATION: Discussion PATS Aircraft (holder of Supplemental Type Certificates (STC) SA83NE, SA1078NE, SA725NE, ST00040NY, and ST01337NY) notified us that it has determined that Boeing Model 737-200, -300, -400, and -500 series airplanes equipped with an auxiliary fuel tank system installed by STC SA83NE, SA1078NE, SA725NE, ST00040NY, or ST01337NY, have insufficient structural strength in the auxiliary fuel tank support structure. The STC holder has also determined that the cargo barriers have insufficient structural strength if subjected to emergency landing loads with the cargo load weights listed in the existing airplane flight manual (AFM) supplements. These determinations were based on a new structural analysis resulting from a re-evaluation of the floor structure and cargo barriers conducted by the STC holder. Structural overload of the auxiliary fuel tank support structure could cause the floor beams to fail, resulting in damage to the primary flight controls and the auxiliary power unit (APU) fuel lines that pass through the floor beams, and consequent loss of control of the airplane. Structural overload of the cargo barriers could cause the barriers to fail, allowing the cargo to shift, resulting in possible damage to the auxiliary fuel tanks, residual fuel leakage, and consequent increased risk of a fire. Relevant Service Information We have reviewed the PATS Aircraft service bulletins listed in the table below. These service bulletins describe procedures for deactivating the auxiliary fuel system, which, for certain airplanes, includes installing new cargo loading weight limit and “INOP” placards, depending on the airplane configuration. The service bulletins also describe procedures for venting any residual air pressure from the auxiliary fuel tanks following each flight. For certain airplanes, paragraph I.D. (“Description”) of the service bulletins describes limiting the maximum cargo weight (as specified on the new cargo weight placards) in the forward and aft cargo compartments, as applicable, depending on the STC configuration of the airplane. Table—Applicable Service Bulletins For model— Having serial number(s) (S/N)— STC— Use PATS aircraft service bulletin— 737-200 series airplanes 22431 and 22628 SA83NE SA83NE-28-SB-002_IR, dated June 7, 2006. 737-200 series airplanes 22600 SA1078NE SA1078NE-28-SB-005_A, Revision A, dated June 21, 2006. 737-200, -300, -400, and -500 series airplanes 23800, 22620, 23124, 23468, 26333, 26307, 27456, 27426, and 27906 SA725NE SA725NE-28-SB-007_B, Revision B, dated July 27, 2006. 737-500 series airplanes 24970 ST00040NY ST00040NY-28-SB-003_IR, dated June 7, 2006. 737-500 series airplanes 28866 ST01337NY ST01337NY-28-SB-002_IR, dated June 7, 2006. We have also reviewed the PATS Aircraft AFM supplements to the Limitations section of the applicable Boeing AFMs, which are listed in the following table. These AFM supplements provide revised maximum cargo weight limits. Table—AFM Supplements for Revised Maximum Cargo Weight Limits For model— Having S/N(s)— STC— STC configuration(s)— Use PATS aircraft AFM Supplement— 737-200 series airplanes 23124 SA725NE 2 148, dated May 31, 2006. 737-200 series airplanes 22620 and 23468 SA725NE 3 and 8 149, Revision A, dated August 11, 2006. 737-200 series airplanes 22600 SA1078NE 3 Tank forward 152, dated May 31, 2006. 737-200 series airplanes 22431 and 22628 SA83NE 2 155, dated May 31, 2006. 737-300 series airplanes 27456, 26307, and 26333 SA725NE 1 and 6 147, dated May 31, 2006. 737-300 series airplanes 23800 SA725NE 7 151, dated May 31, 2006. 737-400 and -500 series airplanes 27906 and 27426 SA725NE 4 and 5 150, dated May 31, 2006. 737-500 series airplanes 28866 ST01337NY Aft 3-tank 153, Revision A, dated August 3, 2006. 737-500 series airplanes 24970 ST00040NY 7 154, dated May 31, 2006. FAA's Determination and Requirements of This AD The unsafe condition described previously is likely to exist or develop on other airplanes of the same type design. For this reason, we are issuing this AD to prevent structural overload of the auxiliary fuel tank support structure, which could cause the floor beams to fail and resultant damage to the primary flight controls and the APU fuel lines that pass through the floor beams, and consequent loss of control of the airplane. We are also issuing this AD to prevent structural overload of the cargo barriers, which could cause the barriers to fail, allowing the cargo to shift, resulting in possible damage to the auxiliary fuel tanks, residual fuel leakage, and consequent increased risk of a fire. This AD requires accomplishing the actions specified in the service information described previously, except as discussed under “Difference Between the AD and the Service Bulletins.” Difference Between the AD and the Service Bulletins The PATS Aircraft service bulletins do not specify a compliance time for deactivating the auxiliary fuel system or implementing the new cargo weight limits. In developing an appropriate compliance time for those actions in this AD, we considered the degree of urgency associated with the subject unsafe condition, the average utilization of the affected fleet, and the time necessary to perform the deactivation (3 work hours) and AFM revision. In light of all of these factors, we find that a 30-day compliance time represents an appropriate interval of time for affected airplanes to continue to operate without compromising safety. Interim Action We consider this AD interim action. If final action is later identified, we may consider further rulemaking then. 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 to make this AD effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements that affect flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any relevant written data, views, or arguments regarding this AD. Send your comments to an address listed in the ADDRESSES section. Include “Docket No. FAA-2006-25746; Directorate Identifier 2006-NM-151-AD” at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD that might suggest a need to modify it. 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 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 the 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 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 DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III, section 44701, “General requirements.” Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the regulation: 1. Is not a “significant regulatory action” under Executive Order 12866; 2. Is not a “significant rule” under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a 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): 2006-18-11 Boeing: Amendment 39-14750. Docket No. FAA-2006-25746; Directorate Identifier 2006-NM-151-AD. Effective Date (a) This AD becomes effective September 27, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Boeing Model 737-200, -300, -400, and -500 series airplanes, certificated in any category; equipped with an auxiliary fuel system installed in accordance with Supplemental Type Certificate (STC) SA83NE, SA1078NE, SA725NE, ST00040NY, or ST01337NY; having serial numbers (S/N) listed in Table 1 of this AD. Table 1.—Applicability For model— Having S/N(s)— As identified in PATS aircraft service bulletin— 737-200 series airplanes 22431 and 22628 SA83NE-28-SB-002-IR, dated June 7, 2006. 737-200 series airplanes 22600 SA1078NE-28-SB-005-A, Revision A, dated June 21, 2006. 737-200, -300, -400, and -500 seriesairplanes 23800, 22620, 23124, 23468, 26333, 26307, 27456, 27426, and 27906 SA725NE-28-SB-007-B, Revision B, dated July 27, 2006. 737-500 series airplanes 24970 ST00040NY-28-SB-003-IR, dated June 7, 2006. 737-500 series airplanes 28866 ST01337NY-28-SB-002-IR, dated June 7, 2006. Unsafe Condition (d) This AD results from a re-evaluation of the floor structure and cargo barriers conducted by the STC holder. We are issuing this AD to prevent structural overload of the auxiliary fuel tank support structure, which could cause the floor beams to fail and resultant damage to the primary flight controls and the auxiliary power unit fuel lines that pass through the floor beams, and consequent loss of control of the airplane. We are also issuing this AD to prevent structural overload of the cargo barriers, which could cause the barriers to fail, allowing the cargo to shift, resulting in possible damage to the auxiliary fuel tanks, residual fuel leakage, and consequent increased risk of a 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. Service Bulletin References (f) The term “service bulletin,” as used in this AD, means the Part IV “Accomplishment Instructions,” and Part V “Maintenance Requirements,” of the applicable PATS Aircraft service bulletin identified in Table 1 of this AD. Deactivate the Auxiliary Fuel System/Revise the Maximum Cargo Weight Limits (g) Within 30 days after the effective date of this AD: Do the actions in paragraphs (g)(1) and (g)(2) of this AD. (1) Deactivate the auxiliary fuel system by doing all of the actions specified in Part IV of the applicable service bulletin. (2) Revise the Limitations section of the applicable Boeing airplane flight manual (AFM) to include revised maximum cargo weight limits specified in the applicable PATS Aircraft AFM supplement identified in Table 2 of this AD. Operate the airplane according to the limitations in the applicable AFM supplement. Table 2.—AFM Supplements for Revised Maximum Cargo Weight Limits For model— Having S/N(s)— STC— STC configuration(s)— Use PATS aircraft AFM supplement— 737-200 series airplanes 23124 SA725NE 2 148, dated May 31, 2006. 737-200 series airplanes 22620 and 23468 SA725NE 3 and 8 149, Revision A, dated August 11, 2006. 737-200 series airplanes 22600 SA1078NE 3 Tank forward 152, dated May 31, 2006. 737-200 series airplanes 22431 and 22628 SA83NE 2 155, dated May 31, 2006. 737-300 series airplanes 27456, 26307, and 26333 SA725NE 1 and 6 147, dated May 31, 2006. 737-300 series airplanes 23800 SA725NE 7 151, dated May 31, 2006. 737-400 and -500 series airplanes 27906 and 27426 SA725NE 4 and 5 150, dated May 31, 2006. 737-500 series airplanes 28866 ST01337NY Aft 3-tank 153, Revision A, dated August 3, 2006. 737-500 series airplanes 24970 ST00040NY 7 154, dated May 31, 2006. Repetitive Venting of the Built-Up Pressure in the Auxiliary Fuel Tanks (h) After deactivating the auxiliary fuel system as specified in paragraph (g) of this AD: Following each flight, vent the auxiliary fuel tanks by doing all of the actions specified in paragraph A. of Part V of the applicable service bulletin. Special Flight Permits (i) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the airplane can be modified, provided the airplane is operated with the auxiliary fuel tanks empty of useable fuel. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, New York 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. (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. Material Incorporated by Reference (k) You must use the PATS Aircraft service bulletins specified in Table 3 of this AD and the PATS Aircraft airplane flight manual supplements specified in Table 4 of this AD, as applicable, to perform the actions that are required by this AD, unless the AD specifies otherwise. Table 3.—Service Bulletins Incorporated by Reference PATS aircraft service bulletin— Revision level— Dated— SA1078NE-28-SB-005-A A June 21, 2006. SA725NE-28-SB-007-B B July 27, 2006. SA83NE-28-SB-002-IR Original June 7, 2006. ST00040NY-28-SB-003-IR Original June 7, 2006. ST01337NY-28-SB-002-IR Original June 7, 2006. Table 4.—Airplane Flight Supplements Incorporated by Reference PATS aircraft airplane flight manual supplement— Revision level— Dated— To the— 147 Original May 31, 2006 Boeing 737-300 Airplane Flight Manual. 148 Original May 31, 2006 Boeing 737-200 Airplane Flight Manual. 149 A August 11, 2006 Boeing 737-200 Airplane Flight Manual. 150 Original May 31, 2006 Boeing 737-400/500 Airplane Flight Manual. 151 Original May 31, 2006 Boeing 737-300 Airplane Flight Manual. 152 Original May 31, 2006 Boeing 737-200 Airplane Flight Manual. 153 A August 3, 2006 Boeing 737-500 Airplane Flight Manual. 154 Original May 31, 2006 Boeing 737-500 Airplane Flight Manual. 155 Original May 31, 2006 Boeing 737-200 Airplane Flight Manual. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact PATS Aircraft, LLC, Product Support, 21652 Nanticoke Avenue, Georgetown, Delaware 19947, 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 23, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-14618 Filed 9-11-06; 8:45 am] BILLING CODE 4910-13-P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 97 [Docket No. 30511 Amdt. No. 3182] Standard Instrument Approach Procedures, Weather Takeoff Minimums; Miscellaneous Amendments AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: This amendment establishes, amends, suspends, or revokes Standard Instrument Approach Procedures (SIAPs) and/or Weather Takeoff Minimums for operations at certain airports. These regulatory actions are needed because of the adoption of new or revised criteria, or because of changes occurring in the National Airspace System, such as the commissioning of new navigational facilities, addition of new obstacles, or changes in air traffic requirements. These changes are designed to provide safe and efficient use of the navigable airspace and to promote safe flight operations under instrument flight rules at the affected airports. DATES: This rule is effective September 12, 2006. The compliance date for each SIAP and/or Weather Takeoff Minimums is specified in the amendatory provisions. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of September 12, 2006. ADDRESSES: Availability of matters incorporated by reference in the amendment is as follows: For Examination— 1. FAA Rules Docket, FAA Headquarters Building, 800 Independence Avenue, SW., Washington, DC 20591; 2. The FAA Regional Office of the region in which the affected airport is located; 3. The National Flight Procedures Office, 6500 South MacArthur Blvd., Oklahoma City, OK 73169 or, 4. The National Archives and Records Administration(NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. For Purchase— Individual SIAP and Weather Takeoff Minimums copies may be obtained from: 1. FAA Public Inquiry Center (APA-200), FAA Headquarters Building, 800 Independence Avenue, SW., Washington, DC 20591; or 2. The FAA Regional Office of the region in which the affected airport is located. By Subscription— Copies of all SIAPs and Weather Takeoff Minimums mailed once every 2 weeks, are for sale by the Superintendent of Documents, U.S. Government Printing Office, Washington, DC 20402. FOR FURTHER INFORMATION CONTACT: Donald P. Pate, Flight Procedure Standards Branch (AFS-420), Flight Technologies and Programs Division, Flight Standards Service, Federal Aviation Administration, Mike Monroney Aeronautical Center, 6500 South MacArthur Blvd., Oklahoma City, OK 73169 (Mail Address: P.O. Box 25082, Oklahoma City, OK 73125) telephone: (405) 954-4164. SUPPLEMENTARY INFORMATION: This amendment to Title 14 of the Code of Federal Regulations, Part 97 (14 CFR part 97), establishes, amends, suspends, or revokes SIAPs and/or Weather Takeoff Minimums. The complete regulatory description of each SIAP and/or Weather Takeoff Minimums is contained in official FAA form documents which are incorporated by reference in this amendment under 5 U.S.C. 552(a), 1 CFR part 51, and 14 CFR part 97.20. The applicable FAA Forms are identified as FAA Forms 8260-3, 8260-4, 8260-5 and 8260-15A. Materials incorporated by reference are available for examination or purchase as stated above. The large number of SIAPs and/or Weather Takeoff Minimums, their complex nature, and the need for a special format make their verbatim publication in the Federal Register expensive and impractical. Further, airmen do not use the regulatory text of the SIAPs and/or Weather Takeoff Minimums but refer to their depiction on charts printed by publishers of aeronautical materials. Thus, the advantages of incorporation by reference are realized and publication of the complete description of each SIAP and/or Weather Takeoff Minimums contained in FAA form documents is unnecessary. The provisions of this amendment state the affected CFR sections, with the types and effective dates of the SIAPs and/or Weather Takeoff Minimums. This amendment also identifies the airport, its location, the procedure identification and the amendment number. The Rule This amendment to 14 CFR part 97 is effective upon publication of each separate SIAP and/or Weather Takeoff Minimums as contained in the transmittal. Some SIAP and/or Weather Takeoff Minimums amendments may have been previously issued by the FAA in a Flight Data Center (FDC) Notice to Airmen (NOTAM) as an emergency action of immediate flight safety relating directly to published aeronautical charts. The circumstances which created the need for some SIAP, and/or Weather Takeoff Minimums amendments may require making them effective in less than 30 days. For the remaining SIAPs and/or Weather Takeoff Minimums, an effective date at least 30 days after publication is provided. Further, the SIAPs and/or Weather Takeoff Minimums contained in this amendment are based on the criteria contained in the U.S. Standard for Terminal Instrument Procedures (TERPS). In developing these SIAPs and/or Weather Takeoff Minimums, the TERPS criteria were applied to the conditions existing or anticipated at the affected airports. Because of the close and immediate relationship between these SIAPs and/or Weather Takeoff Minimums and safety in air commerce, I find that notice and public procedure before adopting these SIAPs and/or Weather Takeoff Minimums are impracticable and contrary to the public interest and, where applicable, that good cause exists for making some SIAPs and/or Weather Takeoff Minimums effective in less than 30 days. Conclusion 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. 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. For the same reason, the FAA certifies that this amendment will not have a significant economic impact on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 97 Air Traffic Control, Airports, Incorporation by reference, and Navigation (Air). Issued in Washington, DC, on August 25, 2006. James J. Ballough, Director, Flight Standards Service. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me, under Title 14, Code of Federal Regulations, Part 97 (14 CFR part 97) is amended by establishing, amending, suspending, or revoking Standard Instrument Approach Procedures and Weather Takeoff Minimums effective at 0901 UTC on the dates specified, as follows: PART 97—STANDARD INSTRUMENT APPROACH PROCEDURES 1. The authority citation for part 97 continues to read as follows: Authority: 49 U.S.C. 106(g), 40103, 40106, 40113, 40114, 40120, 44502, 44514, 44701, 44719, 44721-44722. 2. Part 97 is amended to read as follows: Effective 28 September 2006 Cordova, AK, Merle K. (Mudhole) Smith, NDB/DME-A, Amdt 1A, CANCELLED Kenai, AK, Kenai Muni, DF RWY 19R, Orig, CANCELLED Kotzebue, AK, Ralph Wien Memorial, DF RWY 08, Orig, CANCELLED Kotzebue, AK, Ralph Wien Memorial, DF RWY 26, Orig, CANCELLED Port Heiden, AK, Port Heiden, DF RWY 13, Orig, CANCELLED Sitka, AK, Sitka Rocky Gutierrez, NDB-A, Amdt 1, CANCELLED Camden, AR, Harrell Field, NDB RWY 18, Amdt 11, CANCELLED Forrest City, AR, Forrest City Muni, NDB RWY 36, Amdt 4B, CANCELLED Harrison, AR, Boone County, NDB-B, Amdt 3A, CANCELLED Mountain Home, AR, Ozark Regional, VOR/DME RNAV RWY 5, Amdt 1C, CANCELLED Newport, AR, Newport Muni, NDB RWY 36, Amdt 7A, CANCELLED West Memphis, AR, West Memphis Muni, NDB-B, Amdt 3A, CANCELLED Phoenix, AZ, Phoenix Sky Harbor Intl, VOR/DME-A, Orig, CANCELLED Phoenix, AZ, Phoenix Sky Harbor Intl, VOR/DME RWY 25R, Amdt 1B, CANCELLED Phoenix, AZ, Phoenix Sky Harbor Intl, LOC BC RWY 25R, Amdt 9B, CANCELLED Prescott, AZ, Ernest A. Love Field, VOR/DME RNAV RWY 21L, Amdt 3A, CANCELLED Tucson, AZ, Ryan Field, NDB OR GPS-D, Amdt 1A, CANCELLED Tucson, AZ, Tucson Intl, VOR OR TACAN RWY 11L, Amdt 1 Apple Valley, CA, Apple Valley, RNAV (GPS) Y RWY 18, Amdt 1 Apple Valley, CA, Apple Valley, RNAV (GPS) Z RWY 18, Orig Concord, CA, Buchanan Field, NDB RWY 19R, Amdt 1, CANCELLED Lincoln, CA, Lincoln Regional, VOR RWY 15, Amdt 4, CANCELLED Marysville, CA, Yuba County, VOR RWY 14, Amdt 9D, CANCELLED Merced, CA, Merced Muni-MacReady Field, VOR RWY 12, Amdt 7B, CANCELLED Merced, CA, Merced Muni-MacReady Field, VOR RWY 30, Amdt 18B, CANCELLED Modesto, CA, Modesto City-Co-Harry Sham Fld, VOR RWY 28R, Amdt 11, CANCELLED Oakland, CA, Metropolitan Oakland Intl, VOR/DME RWY 29, Amdt 1, CANCELLED Ontario, CA, Ontario Intl, VOR/DME RWY 8L, Amdt 1, CANCELLED Ontario, CA, Ontario Intl, VOR OR TACAN RWY 26R, Amdt 10A, CANCELLED San Jose, CA, Norman Y. Mineta San Jose Intl, NDB/DME RWY 30L, Amdt 6, CANCELLED Santa Ana, CA, John Wayne-Orange County, RNAV (GPS) RWY 19R, Amdt 1 Fort Pierce, FL, St. Lucie County Intl, NDB RWY 9, Orig-A, CANCELLED Perry, FL, Perry-Foley, NDB RWY 36, Amdt 4, CANCELLED Tampa, FL, Tampa Intl, NDB OR GPS RWY 36L, Amdt 13B, CANCELLED Atlanta, GA, Hartsfield-Jackson Atlanta Intl, ILS OR LOC RWY 28; ILS RWY 28 (CAT II), Orig-A Rome, GA, Richard B. Russell, NDB OR GPS-A, Amdt 6A, CANCELLED Agana, GU, Guam International, RNAV (GPS) Y RWY 6L, Amdt 1 Agana, GU, Guam International, RNAV (RNP) Z RWY 6L, Orig Agana, GU, Guam International, RNAV (GPS) Z RWY 6L, Orig-C, CANCELLED Agana, GU, Guam International, RNAV (RNP) Z RWY 6R, Orig Agana, GU, Guam International, RNAV (GPS) Y RWY 24L, Amdt 1 Agana, GU, Guam International, RNAV (GPS) Y RWY 24R, Amdt 1 Agana, GU, Guam International, RNAV (RNP) Z RWY 24L, Orig Lewiston, ID, Lewiston-Nez Perce County, VOR RWY 8, Amdt 6 Alton/St. Louis, IL, St Louis Regional, NDB RWY 29, Amdt 11, CANCELLED Belleville, IL, Scott AFB/MIDAMERICA, NDB RWY 32L, Orig, CANCELLED Chicago/Aurora, IL, Aurora Muni, VOR/DME RNAV RWY 27, Amdt 1, CANCELLED Chicago/Waukegan, IL, Waukegan Regional, NDB RWY 23, Amdt 3, CANCELLED Chicago/Waukegan, IL, Waukegan Regional, VOR/DME RNAV RWY 5, Amdt 3, CANCELLED Joliet, IL, Joliet Regional, VOR/DME RNAV RWY 12, Amdt 12A, CANCELLED Kankakee, IL, Greater Kankakee, VOR/DME RNAV RWY 22, Amdt 3A, CANCELLED Macomb, IL, Macomb Muni, NDB RWY 27, Amdt 3, CANCELLED Moline, IL, Quad City, VOR/DME RNAV RWY 31, Amdt 10, CANCELLED Peoria, IL, Greater Peoria Regional, VOR/DME RNAV RWY 4, Amdt 6A, CANCELLED Peoria, IL, Greater Peoria Regional, VOR/DME RNAV RWY 22, Amdt 8, CANCELLED Springfield, IL, Abraham Lincoln Capital, NDB RWY 4, Amdt 19, CANCELLED Springfield, IL, Abraham Lincoln Capital, NDB RWY 22, Amdt 1, CANCELLED Auburn, IN, De Kalb County, RNAV (GPS) RWY 9, Orig Auburn, IN, De Kalb County, RNAV (GPS) RWY 27, Orig Auburn, IN, De Kalb County, GPS RWY 9, Orig, CANCELLED Auburn, IN, De Kalb County, GPS RWY 27, Orig-A, CANCELLED Auburn, IN, De Kalb County, Takeoff Minimums and Textual DPs, Amdt 1 Columbus, IN, Columbus Muni, NDB RWY 23, Amdt 11, CANCELLED Elkhart, IN, Elkhart Muni, VOR/DME RNAV OR GPS RWY 18, Amdt 3, CANCELLED Lafayette, IN, Purdue University, VOR/DME RNAV RWY 28, Amdt 6, CANCELLED Muncie, IN, Delaware County-Johnson Field, NDB RWY 32, Amdt 12A, CANCELLED South Bend, IN, South Bend Regional, NDB RWY 27L, Amdt 29, CANCELLED Valparaiso, IN, Porter County Muni, VOR/DME RNAV RWY 9, Amdt 4, CANCELLED Augusta, KS, Augusta Muni, VOR/DME RNAV RWY 36, Orig-A, CANCELLED Emporia, KS, Emporia Muni, VOR/DME RNAV RWY 19, Amdt 8, CANCELLED Baton Rouge, LA, Baton Rouge Metropolitan, Ryan Field, LOC BC RWY 4L, Amdt 6D, CANCELLED Hammond, LA, Hammond Northshore Regional, NDB OR GPS RWY 18, Amdt 2B, CANCELLED Houma, LA, Houma-Terrebonne, NDB RWY 18, Amdt 4B, CANCELLED College Park, MD, College Park, VOR/DME RNAV RWY 15, Amdt 3A, CANCELLED Cumberland, MD, Greater Cumberland Regional, NDB-A, Amdt 8B, CANCELLED Ann Arbor, MI, Ann Arbor Muni, VOR/DME RNAV RWY 24, Amdt 6A, CANCELLED Bellaire, MI, Antrim County, NDB RWY 2, Amdt 2B, CANCELLED Boyne Falls, MI, Boyne Mountain, VOR/DME RNAV OR GPS-B, Amdt 3, CANCELLED Cadillac, MI, Wexford County, VOR/DME RNAV RWY 7, Amdt 8, CANCELLED Cadillac, MI, Wexford County, VOR/DME RNAV RWY 25, Amdt 7, CANCELLED Detroit, MI, Willow Run, NDB RWY 5R, Amdt 12, CANCELLED Grand Haven, MI, Grand Haven Meml Airpark, VOR/DME RNAV RWY 27, Amdt 6, CANCELLED Holland, MI, Tulip City, VOR/DME RNAV RWY 8, Amdt 2B, CANCELLED Holland, MI, Tulip City, VOR/DME RNAV RWY 26, Amdt 5B, CANCELLED Marquette, MI, Sawyer Intl, VOR/DME RWY 1, Orig, CANCELLED Canby, MN, Myers Field, RNAV (GPS) RWY 12, Orig, CANCELLED Grand Rapids, MN, Grand Rapids/Itasca Co-Gordon Newstrom, NDB RWY 34, Amdt 7, CANCELLED Minneapolis, MN, Minneapolis-St Paul Intl/Wold Chamberlain, ILS PRM RWY 12L, Amdt 4B, CANCELLED (Simultaneous Close Parallel) Minneapolis, MN, Minneapolis-St Paul Intl/Wold Chamberlain, ILS PRM RWY 30R, Amdt 6C, CANCELLED (Simultaneous Close Parallel) Minneapolis, MN, Minneapolis-St Paul Intl/Wold Chamberlain, ILS PRM RWY 30L, Amdt 5C, CANCELLED (Simultaneous Close Parallel) Minneapolis, MN, Minneapolis-St Paul Intl/Wold Chamberlain, ILS PRM RWY 12R, Amdt 3B, CANCELLED (Simultaneous Close Parallel) Redwood Falls, MN, Redwood Falls Muni, VOR/DME RNAV RWY 30, Amdt 1A, CANCELLED Warroad, MN, Warroad Intl-Swede Carlson Field, VOR/DME RNAV RWY 31, Amdt 4, CANCELLED Kansas City, MO, Charles B Wheeler Downtown, ILS OR LOC RWY 19, Amdt 21 Lebanon, MO, Floyd W Jones Lebanon, NDB RWY 36, Amdt 6A, CANCELLED Monett, MO, Monett Muni, VOR/DME RNAV RWY 18 Amdt 1, CANCELLED Clarksdale, MS, Fletcher Field, NDB-A, Amdt 2, CANCELLED Kosciusko, MS, Kosciusko-Attala County, NDB RWY 14, Amdt 6, CANCELLED Kosciusko, MS, Kosciusko-Attala County, NDB RWY 32, Amdt 5, CANCELLED Missoula, MT, Missoula International, VOR-C, Amdt 2, CANCELLED Oak Island, NC, Brunswick County, NDB-A, Orig, CANCELLED Plymouth, NC, Plymouth Muni, NDB RWY 3, Amdt 3, CANCELLED Wilson, NC, Wilson Industrial Air Center, NDB RWY 3, Amdt 6A, CANCELLED Wilson, NC, Wilson Industrial Air Center, NDB RWY 21, Amdt 1C, CANCELLED Beatrice, NE, Beatrice Municipal, NDB-A, Amdt 3B, CANCELLED Omaha, NE, Millard, VOR/DME RNAV RWY 12, Amdt 6A, CANCELLED Atlantic City, NJ, Atlantic City International, ILS OR LOC RWY 13, Amdt 7 Buffalo, NY, Buffalo Niagara Intl, ILS OR LOC RWY 5, Amdt 14 Buffalo, NY, Buffalo Niagara Intl, ILS OR LOC RWY 23, Amdt 29 Buffalo, NY, Buffalo Niagara Intl, NDB RWY 5, Amdt 11 Buffalo, NY, Buffalo Niagara Intl, RNAV (GPS) RWY 5, Amdt 1 Buffalo, NY, Buffalo Niagara Intl, RNAV (GPS) RWY 23, Amdt 1 Buffalo, NY, Buffalo Niagara Intl, Takeoff Minimums and Textual DP, Amdt 4 Wellsville, NY, Wellsville Muni Arpt, Tarantine Fld, NDB OR GPS RWY 28, Amdt 6B, CANCELLED Circleville, OH, Pickaway County Memorial, NDB RWY 19, Orig-A, CANCELLED Cleveland, OH, Cleveland-Hopkins Intl, NDB RWY 6R, Amdt 6, CANCELLED Cleveland, OH, Cleveland-Hopkins Intl, VOR/DME RNAV OR GPS RWY 10, Amdt 12A, CANCELLED Dayton, OH, Dayton-Wright Brothers, RNAV (GPS) RWY 2, Orig Dayton, OH, Dayton-Wright Brothers, RNAV (GPS) RWY 20, Orig Dayton, OH, Dayton-Wright Brothers, NDB-A, Amdt 2 Dayton, OH, Dayton-Wright Brothers, LOC/DME RWY 20, Orig Dayton, OH, Dayton-Wright Brothers, LOC RWY 20, Amdt 5, CANCELLED Dayton, OH, Dayton-Wright Brothers, Takeoff Minimums and Textual DPs, Amdt 3 Findlay, OH, Findlay, NDB RWY 36, Amdt 11, CANCELLED Newark, OH, Newark-Heath, VOR/DME RNAV RWY 27, Amdt 6A, CANCELLED Toledo, OH, Toledo Express, VOR/DME RNAV RWY 16, Amdt 5B, CANCELLED Altus, OK, Altus/Quartz Mountain Regional, VOR/DME RNAV RWY 17, Amdt 2B, CANCELLED Alva, OK, Alva Regional, NDB RWY 35, Amdt 4A, CANCELLED Ardmore, OK, Ardmore Downtown Executive, VOR/DME RNAV RWY 17, Amdt 7, CANCELLED Ardmore, OK, Ardmore Downtown Executive, VOR/DME RNAV RWY 35, Amdt 5B, CANCELLED Bristow, OK, Jones Meml, NDB RWY 35, Amdt 2, CANCELLED Chickasha, OK, Chickasha Muni, VOR/DME RNAV RWY 35, Amdt 2, CANCELLED Oklahoma City, OK, Sundance Airpark, VOR/DME RNAV RWY 35, Amdt 1A, CANCELLED Ponca City, OK, Ponca City Rgnl, NDB RWY 35, Amdt 4A, CANCELLED Ponca City, OK, Ponca City Rgnl, VOR/DME RNAV RWY 35, Amdt 2B, CANCELLED Klamath Falls, OR, Kingsley Field, NDB OR GPS RWY 32, Amdt 1, CANCELLED Galeton, PA, Cherry Springs, VOR/DME-A, Orig-A, CANCELLED Galeton, PA, Cherry Springs, Takeoff Minimums and Textual DP, Amdt 1, CANCELLED Harrisburg, PA, Capital City, RNAV (GPS) RWY 26, Orig Harrisburg, PA, Capital City, GPS RWY 26, Orig-B, CANCELLED Philadelphia, PA, Wings Field, NDB RWY 6, Amdt 9A, CANCELLED St Marys, PA, St Marys Muni, RNAV (GPS) RWY 10, Amdt 1 St Marys, PA, St Marys Muni, RNAV (GPS) RWY 28, Amdt 1 State College, PA, University Park, VOR/DME RNAV OR GPS RWY 6, Amdt 6C, CANCELLED State College, PA, University Park, RNAV (GPS) RWY 6, Orig Ponce, PR, Mercedita, RNAV (GPS) RWY 30, Orig Charleston, SC, Charleston Executive, VOR/DME RNAV RWY 9, Amdt 5B, CANCELLED Laurens, SC, Laurens County, NDB RWY 8, Amdt 1B, CANCELLED Orangeburg, SC, Orangeburg Muni, Takeoff Minimums and Textual DP, Amdt 3 Chattanooga, TN, Lovell Field, NDB RWY 20, Amdt 31, CANCELLED Jacksboro, TN, Campbell County, NDB RWY 23, Amdt, 5, CANCELLED Lewisburg, TN, Ellington, VOR/DME RNAV RWY 20, Orig, CANCELLED Lexington, TN, Franklin Wilkins, VOR OR GPS RWY 33, Amdt 10A, CANCELLED Nashville, TN, Nashville Intl, NDB RWY 2L, Amdt 7, CANCELLED Parsons, TN, Scott Field, VOR/DME OR GPS-A, Amdt 2, CANCELLED Parsons, TN, Scott Field, VOR/DME OR GPS-B, Amdt 1, CANCELLED Baytown, TX, R W J Airpark, VOR/DME RWY 32, Amdt 5, CANCELLED Cleburne, TX, Cleburne Muni, VOR/DME-A, Orig-A, CANCELLED Giddings, TX, Giddings-Lee County, VOR/DME RNAV RWY 35, Amdt 1, CANCELLED Greenville, TX, Majors, NDB RWY 17, Amdt 6, CANCELLED Greenville, TX, Majors, NDB RWY 35, Amdt 2, CANCELLED Houston, TX, Sugar Land Rgnl, VOR/DME RNAV RWY 35, Amdt 8A, CANCELLED Kerrville. TX, Kerrville Muni/Louis Schreiner Field, VOR/DME RNAV RWY 12, Amdt 3, CANCELLED Laredo, TX, Laredo Intl, NDB RWY 17R, Amdt 10, CANCELLED Mesquite, TX, Mesquite Metro, NDB OR GPS RWY 17 Amdt 5B, CANCELLED Rocksprings, TX, Edwards County, VOR RWY 14, Amdt 5 Rocksprings, TX, Edwards County, Takeoff Minimums and Textual DP, Orig Wichita Falls, TX, Kickapoo Downtown, NDB-A, Amdt 6A, CANCELLED Culpeper, VA, Culpeper Regional, NDB RWY 22, Amdt 1A, CANCELLED Norfolk, VA, Norfolk Intl, NDB RWY 5, Orig-C, CANCELLED Norfolk, VA, Norfolk Intl, NDB/DME RWY 23, Orig-B, CANCELLED Winchester, VA, Winchester Regional, NDB OR GPS-B, Amdt 1, CANCELLED Richland, WA, Richland, NDB RWY 19, Amdt 6, CANCELLED Seattle, WA, Seattle-Tacoma Intl, RNAV (GPS) RWY 16C, Orig-D Shelton, WA, Sanderson Field, Takeoff Minimums and Textual DP, Amdt 4 Wenatchee, WA, Pangborn Memorial, ILS Y RWY 12, Orig Delavan, WI, Lake Lawn, NDB RWY 18, Orig, CANCELLED Marshfield, WI, Marshfield Muni, NDB RWY 34, Orig, CANCELLED Platteville, WI, Platteville Municipal, VOR/DME RNAV OR GPS RWY 25, Amdt 6A, CANCELLED Sturgeon Bay, WI, Door County Cherryland, NDB RWY 2, Amdt 11, CANCELLED Huntington, WV, Tri-State/Milton J. Ferguson Field, NDB RWY 12, Amdt 18, CANCELLED The FAA published an Amendment in Docket No. 30508, Amdt No. 3180 to Part 97 of the Federal Aviation Regulations (Vol 161, FR No. 71, pages 48471 & 48473; dated Monday, August 21, 2006) under § 97.33 effective 28 SEP 2006, which is hereby rescinded: Greeley, CO, Greeley-Weld County, NDB RWY 34, Orig, CANCELLED Houston, TX, David Wayne Hooks Memorial, VOR/DME RNAV RWY 35L, Amdt 4, CANCELLED The FAA published an Amendment in Docket No. 30498, Amdt No. 3170 to Part 97 of the Federal Aviation Regulations (Vol 71, FR 114, page 34247; dated Wednesday, June 14, 2006) under § 97.33 effective 28 SEP 2006, which is hereby rescinded: Portland, OR, Portland-Hillsboro, NDB-B, Amdt 2, CANCELLED Shelton, WA, Sanderson Field, NDB OR GPS-A, Amdt 2, CANCELLED [FR Doc. E6-14731 Filed 9-11-06; 8:45 am] BILLING CODE 4910-13-P DEPARTMENT OF HEALTH AND HUMAN SERVICES Food and Drug Administration 21 CFR Part 880 General Hospital and Personal Use Devices CFR Correction In Title 21 of the Code of Federal Regulations, parts 800 to 1299, revised as of April 1, 2006, on page 410, in § 880.5950, paragraph (b) is corrected to read as follows: § 880.5950 Umbilical occlusion device. (b) Classification. Class I (general controls). The device is exempt from the premarket notification procedures in subpart E of part 807 of this chapter, subject to the limitations in § 880.9. [FR Doc. 06-55527 Filed 9-11-06; 8:45 am]