Airworthiness Directives; Fokker Model F.27 Mark 050 and F.28 Mark 0100 Airplanes, 43625-43629 [E9-20576]

Download as PDF Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations § 39.13 Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: ■ PART 39—AIRWORTHINESS DIRECTIVES [Amended] 2. FAA amends § 39.13 by adding the following new AD: ■ 2009–18–04 Air Tractor, Inc.: Amendment 39–16000; Docket No. FAA–2009–0489; Directorate Identifier 2009–CE–025–AD. Effective Date (a) This AD becomes effective on October 1, 2009. Affected ADs (b) None. 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. Applicability (c) This AD applies to Models AT–802 and AT–802A airplanes, serial numbers 802/ Actions Before further flight after October 1, 2009 (the effective date of this AD) until the installation of the rudder-aileron interconnect cable shield kit required in paragraph (e)(2) of this AD is done. No later than December 31, 2009 ................... (2) Install the following rudder-aileron interconnect cable shield kit, as applicable. (i) For all airplanes equipped for agricultural spray operations and all fire-fighting airplanes retrofitted with Gen II Fire Retardant Delivery System relay box, install cable shield kit SL#274. (ii) For all fire-fighting airplanes not equipped with Gen II Fire Retardant Delivery System relay box, install cable shield kit SL#274–2. (iii) Installation of the applicable cable shield kit SL#274 or SL#274–2 terminates the requirement of paragraph (e)(1) of this AD. Unsafe Condition (d) This AD results from a report of the rudder pedal cable becoming jammed in flight. We are proposing this AD to prevent jamming of the rudder-aileron interconnect cables by unsecured items in the baggage compartment, which could result in failure of the rudder-aileron interconnect cable system. This failure could lead to loss of control. Compliance (e) To address this problem, you must do the following, unless already done: Procedures Alternative Methods of Compliance (AMOCs) (f) The Manager, Fort Worth Airplane Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Andy McAnaul, Aerospace Engineer, 10100 Reunion Pl., Ste. 650, San Antonio, Texas 78216; telephone: (210) 308–3365; fax: (210) 308–3370. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. srobinson on DSKHWCL6B1PROD with RULES 802A–001 through 802/802A–0319, that are certificated in any category. Compliance (1) Secure any items stowed in the baggage compartment using tie down straps and/or a cargo net. this AD at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the Central Region, call (816) 329–3768. (4) You may also review copies of the service information incorporated by reference for this AD at 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. Material Incorporated by Reference (g) You must use Snow Engineering Co., Service Letter #274, Revision A, dated April 6, 2009, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Air Tractor, Inc., P.O. Box 485, Olney, Texas 76374; telephone: (940) 564–5616; facsimile: (940) 564–5612; e-mail: parts@airtractor.com; Internet: http:// www.airtractor.com. (3) You may review copies of the service information incorporated by reference for Issued in Kansas City, Missouri, on August 18, 2009. Scott A. Horn, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–20385 Filed 8–26–09; 8:45 am] VerDate Nov<24>2008 16:19 Aug 26, 2009 Jkt 217001 BILLING CODE 4910–13–P PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 43625 Not applicable. Snow Engineering Co., Service Letter #274, Revision A, dated April 6, 2009. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0496; Directorate Identifier 2008–NM–139–AD; Amendment 39–16001; AD 2009–18–05] RIN 2120–AA64 Airworthiness Directives; Fokker Model F.27 Mark 050 and F.28 Mark 0100 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: E:\FR\FM\27AUR1.SGM 27AUR1 43626 Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations Several incidents have been reported where an electrical burning smell was noted in the cockpit, originating from the Electrical Power Centre. Troubleshooting revealed a partly molten terminal, which normally attaches a wire or bus bar to a stud of an Electrical Power Contactor, Part Number (P/N) SG02206. Furthermore, heat damage to the contactor stud itself was found. * * * * * * * * This condition, if not corrected, could lead to further cases of overheating of terminals and studs of Electrical Power Contactors P/N SG02206, possibly resulting in the loss of electrical power systems, electrical arcing and fire/smoke in the cockpit. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective October 1, 2009. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of October 1, 2009. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1137; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion srobinson on DSKHWCL6B1PROD with RULES We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on June 2, 2009 (74 FR 26322). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: Several incidents have been reported where an electrical burning smell was noted in the cockpit, originating from the Electrical Power Centre. Troubleshooting revealed a partly molten terminal, which normally attaches a wire or bus bar to a stud of an Electrical Power Contactor, Part Number (P/N) SG02206. Furthermore, heat damage to the contactor stud itself was found. Material investigation revealed that the terminal, which was attached to the stud, was not properly torque tightened when the incident occurred. Loss of torque is considered to have occurred during operation, for reasons not fully understood. Further loosening may have taken place in-service under influence of vibration. As a result, poor contact caused VerDate Nov<24>2008 16:19 Aug 26, 2009 Jkt 217001 electrical arcing during which extremely high temperatures were developed, leading to partial melting of the terminal. Investigation of some other burned contactors revealed evidence (flat spring lock washer) of a fully torqued terminal/stud connection when the overheating occurred. The exact cause for the increase in temperature in the contactor and the terminal/stud could not be determined. However, it could not be excluded that an increase of the temperature inside the contactor could lead to reduction of the reliability of the contactor stud/terminal connection due to loss of lock washer tension. The affected Electrical Power Contactor is used on several locations in the electrical power system, i.e., Generator Line Contactor (GLC), Bus Tie Contactor (BTC), Auxiliary Power Contactor (APC) and External Power Contactor (EPC). This condition, if not corrected, could lead to further cases of overheating of terminals and studs of Electrical Power Contactors P/N SG02206, possibly resulting in the loss of electrical power systems, electrical arcing and fire/smoke in the cockpit. For the reasons described above, this EASA Airworthiness Directive (AD) requires the replacement of the current nut and spring washer of the standard contactor P/N SG02206 with a new self-locking nut. You may obtain further information by examining the MCAI in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD. Costs of Compliance We estimate that this AD will affect 5 products of U.S. registry. We also estimate that it will take about 8 workhours per product to comply with the PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 basic requirements of this AD. The average labor rate is $80 per work-hour. Required parts will cost about $5,715 per product. Where the service information lists required parts costs that are covered under warranty, we have assumed that there will be no charge for these parts. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $31,775, or $6,355 per product. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. Examining the AD Docket You may examine the AD docket on the Internet at http:// E:\FR\FM\27AUR1.SGM 27AUR1 Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains the NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA 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 FAA amends § 39.13 by adding the following new AD: ■ 2009–18–05 Fokker Services B.V.: Amendment 39–16001. Docket No. FAA–2009–0496; Directorate Identifier 2008–NM–139–AD. Effective Date (a) This airworthiness directive (AD) becomes effective October 1, 2009. Affected ADs (b) None. Applicability (c) This AD applies to Fokker Model F.27 Mark 050 and F.28 Mark 0100 airplanes, certificated in any category, all serial numbers. srobinson on DSKHWCL6B1PROD with RULES Subject (d) Air Transport Association (ATA) of America Code 24: Electrical power. Reason (e) The mandatory continuing airworthiness information (MCAI) states: Several incidents have been reported where an electrical burning smell was noted in the cockpit, originating from the Electrical Power Centre. Troubleshooting revealed a partly molten terminal, which normally attaches a wire or bus bar to a stud of an Electrical Power Contactor, Part Number (P/N) SG02206. Furthermore, heat damage to the contactor stud itself was found. Material investigation revealed that the terminal, which was attached to the stud, was not VerDate Nov<24>2008 16:19 Aug 26, 2009 Jkt 217001 properly torque tightened when the incident occurred. Loss of torque is considered to have occurred during operation, for reasons not fully understood. Further loosening may have taken place in-service under influence of vibration. As a result, poor contact caused electrical arcing during which extremely high temperatures were developed, leading to partial melting of the terminal. Investigation of some other burned contactors revealed evidence (flat spring lock washer) of a fully torqued terminal/stud connection when the overheating occurred. The exact cause for the increase in temperature in the contactor and the terminal/stud could not be determined. However, it could not be excluded that an increase of the temperature inside the contactor could lead to reduction of the reliability of the contactor stud/terminal connection due to loss of lock washer tension. The affected Electrical Power Contactor is used on several locations in the electrical power system, i.e. Generator Line Contactor (GLC), Bus Tie Contactor (BTC), Auxiliary Power Contactor (APC) and External Power Contactor (EPC). This condition, if not corrected, could lead to further cases of overheating of terminals and studs of Electrical Power Contactors P/N SG02206, possibly resulting in the loss of electrical power systems, electrical arcing and fire/smoke in the cockpit. For the reasons described above, this EASA Airworthiness Directive (AD) requires the replacement of the current nut and spring washer of the standard contactor P/N SG02206 with a new self-locking nut. Actions and Compliance (f) Unless already done, do the following actions: (1) Except as provided by paragraphs (f)(2) and (f)(3) of this AD: Within 36 months after the effective date of this AD, remove the standard nuts and lock washers from the contactors having P/N SG02206, install new self-locking nuts, and perform the applicable tests on the Alternating Current Bus Transfer system, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100–24–041 or SBF50– 24–031, both dated January 29, 2008, as applicable. If any test fails, before further flight, repair using a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or European Aviation Safety Agency (EASA) (or its delegated agent). (2) Accomplishment of paragraph (f)(1) of this AD is not required for Model F.28 Mark 0100 airplanes that have been modified in service in accordance with Fokker Service Bulletin SBF100–24–037, dated October 2, 2003. Accomplishment of Fokker Service Bulletin SBF100–24–037, dated October 2, 2003, within the compliance time specified in paragraph (f)(1) of this AD is considered an acceptable method of compliance with the requirements of paragraph (f)(1) of this AD. (3) Accomplishment of paragraph (f)(1) of this AD is not required for Model F.27 Mark PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 43627 050 airplanes that have been modified during production to incorporate Fokker Engineering Change Record (ECR) 51780, or for airplanes that have been modified in service in accordance with Fokker Service Bulletin SBF50–24–030, dated November 6, 2003. Accomplishment of Fokker Service Bulletin SBF50–24–030, dated November 6, 2003, within the compliance time specified in paragraph (f)(1) of this AD is considered an acceptable method of compliance with the requirements of paragraph (f)(1) of this AD. (4) As of 36 months after the effective date of this AD, no person may install a contactor having P/N SG02206 on any airplane unless it has been modified in accordance with Goodrich Power Systems Service Bulletin SG02206–24–01, dated March 4, 2008. FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: The MCAI does not include a corrective action for airplanes on which the test required by paragraph (f)(1) of this AD fails. This AD requires the corrective action specified in paragraph (f)(1) of this AD. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1137; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local flight Standards District Office. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (h) Refer to MCAI EASA Airworthiness Directive 2008–0091, dated May 13, 2008, and the service information listed in Tables 1, 2, and 3 of this AD for related information. E:\FR\FM\27AUR1.SGM 27AUR1 43628 Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations TABLE 1—SERVICE INFORMATION Service bulletin Date Fokker Service Bulletin SBF50–24–030, including the drawings identified in Table 2 of this AD ......................................... Fokker Service Bulletin SBF50–24–031 .................................................................................................................................. Fokker Service Bulletin SBF100–24–037, including Manual Change Notification—Maintenance Documentation MCNM F100–076, dated October 2, 2003, and including the drawings identified in Table 3 of this AD. Fokker Service Bulletin SBF100–24–041 ................................................................................................................................ Goodrich Power Systems Service Bulletin SG02206–24–01 ................................................................................................. November 6, 2003. January 29, 2008. October 2, 2003. January 29, 2008. March 4, 2008. TABLE 2—DRAWINGS INCLUDED IN FOKKER SERVICE BULLETIN SBF50–24–030 Fokker drawing— W7980–236 W7980–253 W7980–253 W7980–253 W7980–253 W7980–253 W7980–253 W7980–253 W7980–253 W7980–253 W7980–253 W7980–253 W7980–253 W7980–253 W7980–253 W7980–253 W7980–253 W7980–253 W7980–253 W7980–253 W7980–253 W7980–253 W7980–253 W7980–253 W7980–253 W7980–253 W7980–253 W7980–253 Sheet— ........................................................... ........................................................... ........................................................... ........................................................... ........................................................... ........................................................... ........................................................... ........................................................... ........................................................... ........................................................... ........................................................... ........................................................... ........................................................... ........................................................... ........................................................... ........................................................... ........................................................... ........................................................... ........................................................... ........................................................... ........................................................... ........................................................... ........................................................... ........................................................... ........................................................... ........................................................... ........................................................... ........................................................... Issue— 02 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 Dated— H ........................................................................... BK ......................................................................... BK ......................................................................... BK ......................................................................... BK ......................................................................... BL ......................................................................... BK ......................................................................... BL ......................................................................... BK ......................................................................... BK ......................................................................... BL ......................................................................... BL ......................................................................... BL ......................................................................... BL ......................................................................... BL ......................................................................... BK ......................................................................... BL ......................................................................... BL ......................................................................... BK ......................................................................... BL ......................................................................... BK ......................................................................... BK ......................................................................... BK ......................................................................... BK ......................................................................... BL ......................................................................... BK ......................................................................... BL ......................................................................... BK ......................................................................... August 1, 2003. September 17, 2003. September 17, 2003. September 17, 2003. September 17, 2003. September 17, 2003. September 17, 2003. September 17, 2003. September 17, 2003. September 17, 2003. September 17, 2003. September 17, 2003. September 17, 2003. September 17, 2003. September 17, 2003. September 17, 2003. September 17, 2003. September 17, 2003. September 17, 2003. September 17, 2003. September 17, 2003. September 24, 2003. September 24, 2003. September 24, 2003. September 24, 2003. September 24, 2003. September 24, 2003. September 24, 2003. TABLE 3—DRAWINGS INCLUDED IN FOKKER SERVICE BULLETIN SBF100–24–037 Fokker drawing— W43255 W43255 W43255 W43255 W43255 W43255 W43255 Sheet— ................................................................. ................................................................. ................................................................. ................................................................. ................................................................. ................................................................. ................................................................. srobinson on DSKHWCL6B1PROD with RULES Material Incorporated by Reference (i) You must use the service information contained in Table 4 of this AD, as applicable, to do the actions required by this AD, unless the AD specifies otherwise. If you do the optional actions specified in this AD, you must use the service information specified in Tables 2, 3, and 5 of this AD, as applicable, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. VerDate Nov<24>2008 16:19 Aug 26, 2009 Jkt 217001 Issue— 01 02 03 04 05 06 07 Dated— A ........................................................................... Original ................................................................. A ........................................................................... A ........................................................................... Original ................................................................. A ........................................................................... A ........................................................................... July 30, 2003. July 30, 2003. August 4, 2003. July 30, 2003. July 30, 2003. July 30, 2003. August 4, 2003. (2) For Fokker service information identified in this AD, contact Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands; telephone + 31 (0)252–627–350; fax + 31 (0)252–627–211; e-mail technicalservices.fokkerservices@stork.com; Internet http://www.myfokkerfleet.com. (3) For Goodrich service information identified in this AD, contact Goodrich Corporation, Power Systems, 1555 Corporate Woods Parkway, Uniontown, Ohio 44685– 8799; telephone 330–487–2007; fax 330–487– 1902; e-mail twinsburg.techpubs@goodrich.com; Internet http://www.goodrich.com/TechPubs. PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 (4) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. (5) You may also review copies of the service information that is incorporated by reference at 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. E:\FR\FM\27AUR1.SGM 27AUR1 43629 Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations TABLE 4—DOCUMENTS INCORPORATED BY REFERENCE FOR ACTIONS REQUIRED BY THIS AD Service bulletin Date Fokker Service Bulletin SBF50–24–031 .................................................................................................................................. Fokker Service Bulletin SBF100–24–041 ................................................................................................................................ Goodrich Power Systems Service Bulletin SG02206–24–01 ................................................................................................. January 29, 2008. January 29, 2008. March 4, 2008. TABLE 5—DOCUMENTS INCORPORATED BY REFERENCE FOR OPTIONAL ACTIONS SPECIFIED IN THIS AD Service bulletin Date Fokker Service Bulletin SBF50–24–030 including the drawings identified in Table 2 of this AD .......................................... Fokker Service Bulletin SBF100–24–037, including Manual Change Notification—Maintenance Documentation MCNM F100–076, dated October 2, 2003, and including the drawings identified in Table 3 of this AD. Issued in Renton, Washington, on August 17, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–20576 Filed 8–26–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0477; Directorate Identifier 2008–NM–191–AD; Amendment 39–16003; AD 2009–18–07] RIN 2120–AA64 Airworthiness Directives; Boeing Model 747–100, –100B, –100B SUD, –200B, and –300 Series Airplanes; and Model 747SP and 747SR Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. srobinson on DSKHWCL6B1PROD with RULES AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747 series airplanes. That AD currently requires repetitive inspections to detect cracks in various areas of the fuselage internal structure, and related investigative/corrective actions if necessary. This new AD requires additional repetitive inspections for cracking of certain fuselage structure, and related investigative/corrective actions if necessary. This AD results from fatigue tests and analysis by Boeing that identified areas of the fuselage where fatigue cracks can occur. VerDate Nov<24>2008 16:19 Aug 26, 2009 Jkt 217001 We are issuing this AD to prevent the loss of the structural integrity of the fuselage, which could result in rapid depressurization of the airplane. DATES: This AD becomes effective October 1, 2009. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of October 1, 2009. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124– 2207; telephone 206–544–5000, extension 1, fax 206–766–5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is the Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6437; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 November 6, 2003. October 2, 2003. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 2005–20–30, amendment 39–14327 (70 FR 59252, October 12, 2005). The existing AD applies to certain Boeing Model 747 series airplanes. That NPRM was published in the Federal Register on May 26, 2009 (74 FR 24712). That NPRM proposed to continue to require repetitive inspections to detect cracks in various areas of the fuselage internal structure, and related investigative/corrective actions if necessary. That NPRM also proposed to require additional repetitive inspections for cracking of certain fuselage structure, and related investigative/corrective actions if necessary. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comment that has been received on the NPRM. Boeing concurs with the NPRM. Conclusion We have carefully reviewed the available data, including the comment that has been received, and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance There are about 209 airplanes of the affected design in the worldwide fleet. 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. E:\FR\FM\27AUR1.SGM 27AUR1

Agencies

[Federal Register Volume 74, Number 165 (Thursday, August 27, 2009)]
[Rules and Regulations]
[Pages 43625-43629]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-20576]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0496; Directorate Identifier 2008-NM-139-AD; 
Amendment 39-16001; AD 2009-18-05]
RIN 2120-AA64


Airworthiness Directives; Fokker Model F.27 Mark 050 and F.28 
Mark 0100 Airplanes

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

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD results from mandatory continuing 
airworthiness information (MCAI) originated by an aviation authority of 
another country to identify and correct an unsafe condition on an 
aviation product. The MCAI describes the unsafe condition as:


[[Page 43626]]


    Several incidents have been reported where an electrical burning 
smell was noted in the cockpit, originating from the Electrical 
Power Centre. Troubleshooting revealed a partly molten terminal, 
which normally attaches a wire or bus bar to a stud of an Electrical 
Power Contactor, Part Number (P/N) SG02206. Furthermore, heat damage 
to the contactor stud itself was found. * * *
* * * * *
    This condition, if not corrected, could lead to further cases of 
overheating of terminals and studs of Electrical Power Contactors P/
N SG02206, possibly resulting in the loss of electrical power 
systems, electrical arcing and fire/smoke in the cockpit.
* * * * *
We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective October 1, 2009.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of October 1, 
2009.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1137; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on June 2, 2009 (74 FR 
26322). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    Several incidents have been reported where an electrical burning 
smell was noted in the cockpit, originating from the Electrical 
Power Centre. Troubleshooting revealed a partly molten terminal, 
which normally attaches a wire or bus bar to a stud of an Electrical 
Power Contactor, Part Number (P/N) SG02206. Furthermore, heat damage 
to the contactor stud itself was found. Material investigation 
revealed that the terminal, which was attached to the stud, was not 
properly torque tightened when the incident occurred. Loss of torque 
is considered to have occurred during operation, for reasons not 
fully understood. Further loosening may have taken place in-service 
under influence of vibration. As a result, poor contact caused 
electrical arcing during which extremely high temperatures were 
developed, leading to partial melting of the terminal.
    Investigation of some other burned contactors revealed evidence 
(flat spring lock washer) of a fully torqued terminal/stud 
connection when the overheating occurred. The exact cause for the 
increase in temperature in the contactor and the terminal/stud could 
not be determined. However, it could not be excluded that an 
increase of the temperature inside the contactor could lead to 
reduction of the reliability of the contactor stud/terminal 
connection due to loss of lock washer tension. The affected 
Electrical Power Contactor is used on several locations in the 
electrical power system, i.e., Generator Line Contactor (GLC), Bus 
Tie Contactor (BTC), Auxiliary Power Contactor (APC) and External 
Power Contactor (EPC).
    This condition, if not corrected, could lead to further cases of 
overheating of terminals and studs of Electrical Power Contactors P/
N SG02206, possibly resulting in the loss of electrical power 
systems, electrical arcing and fire/smoke in the cockpit.
    For the reasons described above, this EASA Airworthiness 
Directive (AD) requires the replacement of the current nut and 
spring washer of the standard contactor P/N SG02206 with a new self-
locking nut.

You may obtain further information by examining the MCAI in the AD 
docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have required different actions in this AD from those 
in the MCAI in order to follow our FAA policies. Any such differences 
are highlighted in a NOTE within the AD.

Costs of Compliance

    We estimate that this AD will affect 5 products of U.S. registry. 
We also estimate that it will take about 8 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $80 per work-hour. Required parts will cost about $5,715 per 
product. Where the service information lists required parts costs that 
are covered under warranty, we have assumed that there will be no 
charge for these parts. As we do not control warranty coverage for 
affected parties, some parties may incur costs higher than estimated 
here. Based on these figures, we estimate the cost of this AD to the 
U.S. operators to be $31,775, or $6,355 per product.

Authority for This Rulemaking

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

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://

[[Page 43627]]

www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains the NPRM, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

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

2009-18-05 Fokker Services B.V.: Amendment 39-16001. Docket No. FAA-
2009-0496; Directorate Identifier 2008-NM-139-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective October 
1, 2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Fokker Model F.27 Mark 050 and F.28 Mark 
0100 airplanes, certificated in any category, all serial numbers.

Subject

    (d) Air Transport Association (ATA) of America Code 24: 
Electrical power.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    Several incidents have been reported where an electrical burning 
smell was noted in the cockpit, originating from the Electrical 
Power Centre. Troubleshooting revealed a partly molten terminal, 
which normally attaches a wire or bus bar to a stud of an Electrical 
Power Contactor, Part Number (P/N) SG02206. Furthermore, heat damage 
to the contactor stud itself was found. Material investigation 
revealed that the terminal, which was attached to the stud, was not 
properly torque tightened when the incident occurred. Loss of torque 
is considered to have occurred during operation, for reasons not 
fully understood. Further loosening may have taken place in-service 
under influence of vibration. As a result, poor contact caused 
electrical arcing during which extremely high temperatures were 
developed, leading to partial melting of the terminal.
    Investigation of some other burned contactors revealed evidence 
(flat spring lock washer) of a fully torqued terminal/stud 
connection when the overheating occurred. The exact cause for the 
increase in temperature in the contactor and the terminal/stud could 
not be determined. However, it could not be excluded that an 
increase of the temperature inside the contactor could lead to 
reduction of the reliability of the contactor stud/terminal 
connection due to loss of lock washer tension. The affected 
Electrical Power Contactor is used on several locations in the 
electrical power system, i.e. Generator Line Contactor (GLC), Bus 
Tie Contactor (BTC), Auxiliary Power Contactor (APC) and External 
Power Contactor (EPC).
    This condition, if not corrected, could lead to further cases of 
overheating of terminals and studs of Electrical Power Contactors P/
N SG02206, possibly resulting in the loss of electrical power 
systems, electrical arcing and fire/smoke in the cockpit.
    For the reasons described above, this EASA Airworthiness 
Directive (AD) requires the replacement of the current nut and 
spring washer of the standard contactor P/N SG02206 with a new self-
locking nut.

Actions and Compliance

    (f) Unless already done, do the following actions:
    (1) Except as provided by paragraphs (f)(2) and (f)(3) of this 
AD: Within 36 months after the effective date of this AD, remove the 
standard nuts and lock washers from the contactors having P/N 
SG02206, install new self-locking nuts, and perform the applicable 
tests on the Alternating Current Bus Transfer system, in accordance 
with the Accomplishment Instructions of Fokker Service Bulletin 
SBF100-24-041 or SBF50-24-031, both dated January 29, 2008, as 
applicable. If any test fails, before further flight, repair using a 
method approved by either the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or European Aviation 
Safety Agency (EASA) (or its delegated agent).
    (2) Accomplishment of paragraph (f)(1) of this AD is not 
required for Model F.28 Mark 0100 airplanes that have been modified 
in service in accordance with Fokker Service Bulletin SBF100-24-037, 
dated October 2, 2003. Accomplishment of Fokker Service Bulletin 
SBF100-24-037, dated October 2, 2003, within the compliance time 
specified in paragraph (f)(1) of this AD is considered an acceptable 
method of compliance with the requirements of paragraph (f)(1) of 
this AD.
    (3) Accomplishment of paragraph (f)(1) of this AD is not 
required for Model F.27 Mark 050 airplanes that have been modified 
during production to incorporate Fokker Engineering Change Record 
(ECR) 51780, or for airplanes that have been modified in service in 
accordance with Fokker Service Bulletin SBF50-24-030, dated November 
6, 2003. Accomplishment of Fokker Service Bulletin SBF50-24-030, 
dated November 6, 2003, within the compliance time specified in 
paragraph (f)(1) of this AD is considered an acceptable method of 
compliance with the requirements of paragraph (f)(1) of this AD.
    (4) As of 36 months after the effective date of this AD, no 
person may install a contactor having P/N SG02206 on any airplane 
unless it has been modified in accordance with Goodrich Power 
Systems Service Bulletin SG02206-24-01, dated March 4, 2008.

FAA AD Differences

    Note 1:  This AD differs from the MCAI and/or service 
information as follows: The MCAI does not include a corrective 
action for airplanes on which the test required by paragraph (f)(1) 
of this AD fails. This AD requires the corrective action specified 
in paragraph (f)(1) of this AD.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, FAA, has the authority to approve AMOCs for 
this AD, if requested using the procedures found in 14 CFR 39.19. 
Send information to ATTN: Tom Rodriguez, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone 
(425) 227-1137; fax (425) 227-1149. Before using any approved AMOC 
on any airplane to which the AMOC applies, notify your appropriate 
principal maintenance inspector (PMI) or principal avionics 
inspector (PAI), as appropriate, or lacking a principal inspector, 
your local flight Standards District Office.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act, the 
Office of Management and Budget (OMB) has approved the information 
collection requirements and has assigned OMB Control Number 2120-
0056.

Related Information

    (h) Refer to MCAI EASA Airworthiness Directive 2008-0091, dated 
May 13, 2008, and the service information listed in Tables 1, 2, and 
3 of this AD for related information.

[[Page 43628]]



                      Table 1--Service Information
------------------------------------------------------------------------
          Service bulletin                           Date
------------------------------------------------------------------------
Fokker Service Bulletin SBF50-24-     November 6, 2003.
 030, including the drawings
 identified in Table 2 of this AD.
Fokker Service Bulletin SBF50-24-031  January 29, 2008.
Fokker Service Bulletin SBF100-24-    October 2, 2003.
 037, including Manual Change
 Notification--Maintenance
 Documentation MCNM F100-076, dated
 October 2, 2003, and including the
 drawings identified in Table 3 of
 this AD.
Fokker Service Bulletin SBF100-24-    January 29, 2008.
 041.
Goodrich Power Systems Service        March 4, 2008.
 Bulletin SG02206-24-01.
------------------------------------------------------------------------


                       Table 2--Drawings Included in Fokker Service Bulletin SBF50-24-030
----------------------------------------------------------------------------------------------------------------
          Fokker drawing--                Sheet--              Issue--                      Dated--
----------------------------------------------------------------------------------------------------------------
W7980-236..........................                02  H.....................  August 1, 2003.
W7980-253..........................                40  BK....................  September 17, 2003.
W7980-253..........................                41  BK....................  September 17, 2003.
W7980-253..........................                42  BK....................  September 17, 2003.
W7980-253..........................                43  BK....................  September 17, 2003.
W7980-253..........................                44  BL....................  September 17, 2003.
W7980-253..........................                45  BK....................  September 17, 2003.
W7980-253..........................                46  BL....................  September 17, 2003.
W7980-253..........................                47  BK....................  September 17, 2003.
W7980-253..........................                48  BK....................  September 17, 2003.
W7980-253..........................                49  BL....................  September 17, 2003.
W7980-253..........................                50  BL....................  September 17, 2003.
W7980-253..........................                51  BL....................  September 17, 2003.
W7980-253..........................                52  BL....................  September 17, 2003.
W7980-253..........................                53  BL....................  September 17, 2003.
W7980-253..........................                54  BK....................  September 17, 2003.
W7980-253..........................                55  BL....................  September 17, 2003.
W7980-253..........................                56  BL....................  September 17, 2003.
W7980-253..........................                57  BK....................  September 17, 2003.
W7980-253..........................                58  BL....................  September 17, 2003.
W7980-253..........................                59  BK....................  September 17, 2003.
W7980-253..........................                60  BK....................  September 24, 2003.
W7980-253..........................                61  BK....................  September 24, 2003.
W7980-253..........................                62  BK....................  September 24, 2003.
W7980-253..........................                63  BL....................  September 24, 2003.
W7980-253..........................                64  BK....................  September 24, 2003.
W7980-253..........................                65  BL....................  September 24, 2003.
W7980-253..........................                66  BK....................  September 24, 2003.
----------------------------------------------------------------------------------------------------------------


                       Table 3--Drawings Included in Fokker Service Bulletin SBF100-24-037
----------------------------------------------------------------------------------------------------------------
          Fokker drawing--                Sheet--              Issue--                      Dated--
----------------------------------------------------------------------------------------------------------------
W43255.............................                01  A.....................  July 30, 2003.
W43255.............................                02  Original..............  July 30, 2003.
W43255.............................                03  A.....................  August 4, 2003.
W43255.............................                04  A.....................  July 30, 2003.
W43255.............................                05  Original..............  July 30, 2003.
W43255.............................                06  A.....................  July 30, 2003.
W43255.............................                07  A.....................  August 4, 2003.
----------------------------------------------------------------------------------------------------------------

Material Incorporated by Reference

    (i) You must use the service information contained in Table 4 of 
this AD, as applicable, to do the actions required by this AD, 
unless the AD specifies otherwise. If you do the optional actions 
specified in this AD, you must use the service information specified 
in Tables 2, 3, and 5 of this AD, as applicable, unless the AD 
specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For Fokker service information identified in this AD, 
contact Fokker Services B.V., Technical Services Dept., P.O. Box 
231, 2150 AE Nieuw-Vennep, the Netherlands; telephone + 31 (0)252-
627-350; fax + 31 (0)252-627-211; e-mail 
technicalservices.fokkerservices@stork.com; Internet http://www.myfokkerfleet.com.
    (3) For Goodrich service information identified in this AD, 
contact Goodrich Corporation, Power Systems, 1555 Corporate Woods 
Parkway, Uniontown, Ohio 44685-8799; telephone 330-487-2007; fax 
330-487-1902; e-mail twinsburg.techpubs@goodrich.com; Internet 
http://www.goodrich.com/TechPubs.
    (4) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221 or 425-227-1152.
    (5) You may also review copies of the service information that 
is incorporated by reference at 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.

[[Page 43629]]



  Table 4--Documents Incorporated by Reference for Actions Required by
                                 This AD
------------------------------------------------------------------------
          Service bulletin                           Date
------------------------------------------------------------------------
Fokker Service Bulletin SBF50-24-031  January 29, 2008.
Fokker Service Bulletin SBF100-24-    January 29, 2008.
 041.
Goodrich Power Systems Service        March 4, 2008.
 Bulletin SG02206-24-01.
------------------------------------------------------------------------


    Table 5--Documents Incorporated by Reference for Optional Actions
                          Specified in This AD
------------------------------------------------------------------------
          Service bulletin                           Date
------------------------------------------------------------------------
Fokker Service Bulletin SBF50-24-030  November 6, 2003.
 including the drawings identified
 in Table 2 of this AD.
Fokker Service Bulletin SBF100-24-    October 2, 2003.
 037, including Manual Change
 Notification--Maintenance
 Documentation MCNM F100-076, dated
 October 2, 2003, and including the
 drawings identified in Table 3 of
 this AD.
------------------------------------------------------------------------


    Issued in Renton, Washington, on August 17, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-20576 Filed 8-26-09; 8:45 am]
BILLING CODE 4910-13-P