FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS BIWEEKLY

FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS BIWEEKLY 2007-03 This electronic copy may be printed and used in lieu of the FAA biweekly paper copy. U.S. Department of Transportation Federal Aviation Administration Regulatory Support Division Delegation and Airworthiness Programs Branch, AIR-140 P. O. Box 26460 Oklahoma City, OK 73125-0460 FAX 405-954-4104

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SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS AD No. Information Manufacturer Applicability Info: E - Emergency; COR - Correction; S - Supersedes; R - Revision; - See AD for additional information; Biweekly 2007-01 2006-26-03 Alpha Aviation Design Limited R2160 2006-26-07 Turbomeca Engine: Arrius 2B1, 2B1A, and 2B2 turboshaft 2006-26-08 Raytheon Aircraft Company 390 Biweekly 2007-02 2007-01-03 Stemme GMBH & Co. KG Gliders: S10-VT 2007-01-04 Turbomeca Engine: Artouste III B and III B1 turboshaft 2007-01-05 Sikorsky Aircraft Corporation Rotorcraft: S-61L, N, R, and NM 2007-01-06 S 2004-24-08 Bell Helicopter Textron Canada Rotorcraft: 206A, B, L, L-1, L-3, and L-4 Biweekly 2007-03 2007-02-04 SOCATA-Groupe Aerospatiale TB 20 and TB 21 2007-02-08 EADS SOCATA TBM 700 2007-02-11 S 2002-22-11 EXTRA Flugzeugproduktionsund EA-300, EA-300L, EA-300S, EA-300/200 Vertriebs-GmbH 2007-02-12 Reims Aviation F406 2007-02-13 DORNIER LUFTFAHRT 228-212 2007-02-17 Turbomeca Engine: Arriel -1A, -1A1, -1A2, -1B, -1B2, -1C, -1C1, -1C2, -1D, -1D, -1D1, -1K1, -1E, -1E2, -1S, and -1S1 series 2007-03-06 Pilatus Aircraft Limited PC-12 and PC-12/45 2007-03-08 Pilatus Aircraft Ltd. PC-6, PC-6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC- 6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 2007-03-14 Turbomeca Engine: Arriel 2B1 3 BW 2007-03

FAA Aircraft Certification Service AIRWORTHINESS DIRECTIVE www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html 2007-02-04 SOCATA-Groupe Aerospatiale: Amendment 39-14891; Docket No. FAA-2006-26236; Directorate Identifier 2006-CE-66-AD. Effective Date Affected ADs (a) This airworthiness directive (AD) becomes effective February 26, 2007. (b) None. Applicability (c) This AD applies to SOCATA Models TB 20 and TB 21 airplanes, serial numbers 1 through 9999 without repair REP 20.031 implemented on both sides, certificated in any category. Reason (d) The mandatory continuing airworthiness information (MCAI) states there are reports of interference between the wing spar lower boom and the wheel fairing attaching screw causing an unsafe condition. The interference could, if left uncorrected, reduce the fatigue life of the wing spar with potentially catastrophic results. The MCAI requires inspections and repairs as necessary to correct this unsafe condition. Actions and Compliance (e) Unless already done, do the following actions. (1) Within the next 100 hours time-in-service or 12 months after the effective date of this AD, whichever occurs first, perform an inspection of the wing spar lower boom and repair it as necessary, in accordance with the accomplishment instructions of the EADS SOCATA TB Aircraft Mandatory Service Bulletin SB 10-148, ATA No. 57, dated December 2005. (2) If defect dimensions exceed the acceptable values given in the EADS SOCATA TB Aircraft Mandatory Service Bulletin SB 10-148, ATA No. 57, dated December 2005, or if the defect is not located in areas depicted in figure 2 of the EADS SOCATA TB Aircraft Mandatory Service Bulletin SB 10-148, ATA No. 57, dated December 2005, then the Type 1 or Type 2 repair solutions are not applicable. A written report shall be sent to the manufacturer as mentioned in section A.5 of the EADS SOCATA TB Aircraft Mandatory Service Bulletin SB 10-148, ATA No. 57, dated December 2005. In this case, all flight is prohibited until EADS SOCATA provides a repair solution or otherwise agrees to further flight. 4 BW 2007-03

2007-02-04 2 FAA AD Differences Note: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (f) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Staff, FAA, ATTN: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4059; fax: (816) 329-4090, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120-0056. Related Information (g) Refer to European Aviation Safety Agency (EASA) Airworthiness Directive No.: 2006-0123, dated May 16, 2006; and EADS SOCATA TB Aircraft Mandatory Service Bulletin SB 10-148, ATA No. 57, dated December 2005, for related information. Material Incorporated by Reference (h) You must use EADS SOCATA TB Aircraft Mandatory Service Bulletin SB 10-148, ATA No. 57, dated December 2005, 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 EADS SOCATA, Direction des Services, 65921 Tarbes Cedex 9, France; telephone: 33 (0)5 62.41.73.00; fax: 33 (0)5 62.41.76.54; or SOCATA Aircraft, INC., North Perry Airport, 7501 Airport Road, Pembroke Pines, Florida 33023; telephone: (954) 893-1400; fax: (954) 964-4141. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; or 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/cfr/ibr-locations.html. Issued in Kansas City, Missouri, on January 11, 2007. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-706 Filed 1-19-07; 8:45 am] 5 BW 2007-03

FAA Aircraft Certification Service AIRWORTHINESS DIRECTIVE www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html 2007-02-08 EADS SOCATA: Amendment 39-14895; Docket No. FAA-2006-26232; Directorate Identifier 2006-CE-62-AD. Effective Date Affected ADs (a) This airworthiness directive (AD) becomes effective February 26, 2007. (b) None. Applicability (c) This AD applies to SOCATA Model TBM 700 airplanes, all serial numbers, certificated in any category. Reason (d) The mandatory continuing airworthiness information (MCAI) states there was a report of a master cylinder yoke failure. The AD requirements are to detect defective yokes on aircraft and replace them. The aim of this AD is to ensure that normal braking is available at any time to prevent possible runway excursions in the event of failure of the master cylinder yoke. Actions and Compliance (e) Unless already done, do the following actions. (1) For the serial numbers indicated below, within the next 100 hours time in service or 12 months after the effective date of this AD, whichever occurs first: (i) For airplane serial numbers 269 and 339 and up, check the aircraft records to determine whether the original cylinder yoke or yokes in the master cylinder assembly (both left-hand and righthand) delivered with the airplane are installed. This check can be done by an owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7). (A) If you can positively identify that the original yokes in the master cylinder assemblies (both left-hand and right-hand) delivered with the airplane are installed, then make an entry in the aircraft records showing compliance with this AD per section 43.9 of the Federal Aviation Regulations (14 CFR 43.9). (B) If you cannot positively identify that the original yokes in the master cylinder assemblies (both left-hand and right-hand) delivered with the airplane are installed or if any of the master cylinder yokes have been replaced, then proceed to paragraph (e)(1)(ii) of this AD. 6 BW 2007-03

2007-02-08 2 (ii) For all airplane serial numbers, unless the action is shown not to apply per paragraph (e)(1)(i)(a) of this AD, inspect for misalignment of the master cylinder yokes from their threaded pins, as instructed in the EADS SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-136, ATA No. 32, dated December 2005, accomplishment instructions paragraph. (A) If a yoke is found satisfactory, proceed to its re-installation on aircraft. (B) If a yoke is found defective, prior to further flight, discard the yoke and install a new part number T700A324004810000 (or FAA-approved equivalent part number) yoke in accordance with EADS SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-136, ATA No. 32, dated December 2005. (2) For all airplane serial numbers, as of the effective date of this AD, do not install part number ZOO.N7134732200 yokes or yokes in master cylinder assembly part number ZOO.N6068757280 (left hand side) and ZOO.N6068757281 (right hand side), unless EADS SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-136, ATA No. 32, dated December 2005, is complied with. FAA AD Differences Note: This AD differs from the MCAI and/or service information as follows: (1) It does not allow interim use of yokes found defective during inspection. FAA policy is to replace defective parts on critical systems. (2) It applies to all serial numbers. This will assure that, if any of the airplanes had the affected part number yokes installed after delivery of the airplane, the unsafe condition is still addressed. It also will assure that any of the affected part number yokes are inspected per the AD and service bulletin before future installation of these parts. Other FAA AD Provisions (f) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Staff, FAA, ATTN: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329 4059; fax: (816) 329 4090, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA approved. Corrective actions are considered FAA approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120 0056. Material Incorporated by Reference (g) You must use EADS SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-136, ATA No. 32, dated December 2005, 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. 7 BW 2007-03

2007-02-08 3 (2) For service information identified in this AD, contact EADS SOCATA, Direction des Services, 65921 Tarbes Cedex 9, France; telephone: 33 (0)5 62 41 73 00; fax: 33 (0)5 62 41 76 54; or SOCATA AIRCRAFT, INC., North Perry Airport, 7501 South Airport Rd., Pembroke Pines, FL 33023; telephone: (954) 893-1400; fax: (954) 964-4141. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; or 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/cfr/ibr-locations.html. Issued in Kansas City, Missouri, on January 12, 2007. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-685 Filed 1-19-07; 8:45 am] 8 BW 2007-03

FAA Aircraft Certification Service AIRWORTHINESS DIRECTIVE www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html 2007-02-11 EXTRA Flugzeugproduktions-und Vertriebs-GmbH: Amendment 39-14898; Docket No. FAA-2006-26134; Directorate Identifier 2006-CE-56-AD. Effective Date Affected ADs Applicability (a) This AD becomes effective on February 28, 2007. (b) This AD supersedes AD 2002-21-11, Amendment 39-12917. (c) This AD applies to the following airplanes that are certificated in any category: Models EA-300 01 through 62 EA-300L Serial Numbers 01 through 71, 73 through 77, 79 through 83, 85 through 89, 91, and 92 EA-300S 01 through 29 EA-300/200 01 through 31 and 1032 through 1039 Unsafe Condition (d) This AD is the result from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified in this AD are intended to detect, correct, and prevent cracks in the upper longeron at the horizontal stabilizer attachment, which could result in structural failure of the aft fuselage. This failure could lead to loss of control. 9 BW 2007-03

2007-02-11 2 Compliance (e) To address this problem, you must do the following, unless already done: Actions Compliance Procedures (i) For Models EA-300S Follow Part I of airplanes: Upon accumulating EXTRA Service 250 hours time-in-service (TIS) Bulletin No. after December 17, 2002 (the 300-2-95, Issue: F, effective date of AD 2002-21-11) Dated: July 10, or within the next 50 hours TIS 2006. after February 28, 2007 (the effective date of this AD), whichever occurs first. (ii) For Models EA-300, EA-300L, and EA-300/200 airplanes: Within the next 50 hours TIS after February 28, 2007 (the effective date of this AD). (iii) For all affected airplanes: If the modifications specified in Part II and Part III of EXTRA Service Bulletin No. 300-2-95, Issue: F, Dated: July 10, 2006, have already been incorporated, no further action is required. (1) Inspect, using a fluorescent dye penetrant method, the upper longeron at the horizontal stabilizer attachment for cracks, as applicable. You may take unless already done credit for the inspections if you previously used Extra Service Bulletin No. 300-2-95 (pages 2-6 at Issue: C, dated July 15, 1998; and pages 1 and 7 through 11 at Issue: D, dated January 30, 2001). (2) If cracks are found during the inspection required in paragraph (e)(1) of this AD in areas A, B, and C (as shown in Figure 1 of EXTRA Service Bulletin No. 300-2-95, Issue: F, Dated: July 10, 2006), weld the crack and modify the upper longeron at the horizontal stabilizer attachment by installing the applicable modification kit (or FAAapproved equivalent parts). (3) If no cracks are found during the inspection required in paragraph (e)(1) of this AD, modify the upper longeron at the horizontal stabilizer attachment by installing the applicable modification kit (or FAA-approved equivalent parts). For all affected airplanes: Before further flight after the inspection required in paragraph (e)(1) of this AD in which cracks are found, unless already done. For all affected airplanes: Within the next 100 hours TIS after February 28, 2007 (the effective date of this AD), unless already done. Follow Part II of EXTRA Service Bulletin No. 300-2-95, Issue: F, Dated: July 10, 2006. Follow Part II of EXTRA Service Bulletin No. 300-2-95, Issue: F, Dated: July 10, 2006. 10 BW 2007-03

2007-02-11 2 (4) For Models EA-300S and EA-300L airplanes only: Reinforce the fuselage frame underneath the horizontal stabilizer main spar attachment bracket by installing the applicable modification kit (or FAA-approved equivalent parts). (i) For Model EA-300S: Within the next 200 hours TIS after December 17, 2002 (the effective date of AD 2002-21-11) or within the next 100 hours TIS after February 28, 2007 (the effective date of this AD), whichever occurs first, unless already done. (ii) For Model EA-300L: Within the next 100 hours TIS after February 28, 2007 (the effective date of this AD), unless already done. Follow Part III of EXTRA Service Bulletin No. 300-2-95, Issue: F, Dated: July 10, 2006. Alternative Methods of Compliance (AMOCs) (f) The Manager, Standards Office, Small Airplane Directorate, FAA, ATTN: Karl Schletzbaum, Aerospace Engineer, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4146; fax: (816) 329-4090, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (g) AMOCs approved for AD 2002-21-11 are approved for this AD. Related Information (h) The European Aviation Safety Agency (EASA) AD No. 2006-0281, dated September 14, 2006, also addresses the subject of this AD. Material Incorporated by Reference (i) You must use EXTRA Service Bulletin No. 300-2-95, Issue: F, Dated: July 10, 2006 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 EXTRA Flugzeugproduktions- und Vertriebs- GmbH, Schwarze Heide 21, D-46569 Huenxe, Germany; fax: (+49)-2858-9137-42. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or 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. Issued in Kansas City, Missouri on January 12, 2007. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-775 Filed 1-23-07; 8:45 am] 11 BW 2007-03

FAA Aircraft Certification Service AIRWORTHINESS DIRECTIVE www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html 2007-02-12 Reims Aviation S.A.: Amendment 39-14899; Docket No. FAA-2006-26694; Directorate Identifier 2006-CE-91-AD. Effective Date Affected ADs (a) This airworthiness directive (AD) becomes effective February 13, 2007. (b) None. Applicability (c) This AD applies to the following model and serial number airplanes, certificated in any category. Model Serial Nos F406 0002, 0003, 0004, 0006, 0008, 0009, 0010, 0012, 0013, 0017, 0024, 0025, 0039, 0042, 0044, 0045, 0066, 0070, 0073, 0074, 0075, 0077, 0080 through 0090, and 0092 Reason (d) The mandatory continuing airworthiness information (MCAI) states: * * * several reports regarding discovery of cracks about the rudder pulley bracket part number 6015511-1. This pulley bracket is installed with the Camera Hole option. This condition, if left uncorrected, could result in the loss of rudder control on the airplane. Actions and Compliance (e) Unless already done, do the following actions. (1) Within the next 10 hours time-in-service (TIS) after February 13, 2007. (the effective of this AD), perform the initial inspection as specified in REIMS AVIATION INDUSTRIES Service Bulletin No. F406-58, Rev. 1, dated October 27, 2006. (2) If no cracking is found following the initial inspection required in paragraph (e)(1) of this AD, repeat the inspection every 50 flight hours or 1 month, whichever occurs first, until the conditions specified in paragraph (e)(3) of this AD are met. (3) Within the next 100 hours TIS or 2 months after February 13, 2007. (the effective of this AD), whichever occurs first, install the modified pulley bracket as specified in REIMS AVIATION INDUSTRIES Service Bulletin No F406-58, Rev. 1, dated October 27, 2006. 12 BW 2007-03

2007-02-12 2 (4) If any cracking is found during the inspection required in paragraph (e)(1) of this AD, prior to next flight, install the modified pulley bracket as specified in REIMS AVIATION INDUSTRIES Service Bulletin No F406-58, Rev. 1, dated October 27, 2006. (5) The modified pulley bracket specified in REIMS AVIATION INDUSTRIES Service Bulletin No F406-58, Rev. 1, dated October 27, 2006, may be installed at any time after the inspection required in paragraph (e)(1) of this AD, but must be installed prior to further flight if cracking is found. FAA AD Differences Note: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (f) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Staff, FAA, Small Airplane Directorate, ATTN: Mike Kiesov, Aerospace Engineer, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4144; fax: (816) 329-4090, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et.seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120-0056. Related Information (g) Refer to Direction Generale de L'Aviation Civile AD No. F-2005-080, Issue date: May 25, 2005, and REIMS AVIATION INDUSTRIES Service Bulletin No. F406-58, Rev. 1, dated October 27, 2006, for related information. Material Incorporated by Reference (h) You must use REIMS AVIATION INDUSTRIES Service Bulletin No. F406-58, Rev. 1, dated October 27, 2006, 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 REIMS AVIATION INDUSTRIES, Aerodrome de Reims Prunay, 51360 Prunay, France, A l'attention du Support Client; telephone 03.26.48.46.53; fax: 03.26.49.18.57. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or 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. Issued in Kansas City, Missouri on January 12, 2007. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-774 Filed 1-23-07; 8:45 am] 13 BW 2007-03

FAA Aircraft Certification Service AIRWORTHINESS DIRECTIVE www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html 2007-02-13 DORNIER LUFTFAHRT: Amendment 39-14900; Docket No. FAA-2006-26597; Directorate Identifier 2006-CE-86-AD. Effective Date Affected ADs (a) This AD becomes effective on March 1, 2007. (b) None. Applicability (c) This AD applies to DORNIER LUFTFAHRT GmbH Model 228-212 airplanes, all serial numbers, if Carbon Brake Assemblies with Part Number (P/N) 5009850-1, 5009850-2, 5009850-3 or 5009850-4 are installed, that are certificated in any category. Unsafe Condition (d) This AD is the result of loose bolts and nuts being detected on the landing gear carbon brake assembly during a maintenance inspection. We are issuing this AD to require an inspection to detect loose bolts and self-locking nuts on the landing gear carbon brake assembly, which, if not corrected, could result in the brake assembly detaching and malfunctioning, degrading brake performance, and potentially causing loss of control of the aircraft during landing or roll-out. Compliance (e) To address this problem, you must do the following, unless already done, before the next flight after the effective date of this AD: Inspect the landing gear carbon brake assembly in accordance with the instructions contained in DORNIER LUFTFAHRT GmbH Dornier 228 Alert Service Bulletin ASB-228-265 dated November 17, 2006, and, if necessary, replace the affected brake assembly. Alternative Methods of Compliance (AMOCs) (f) The Manager, Standards Staff, FAA, ATTN: Karl Schletzbaum, Aerospace Engineer, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4146; fax: (816) 329-4090, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information (g) This AD is related to EASA EAD No. 2006-0352-E, dated November 24, 2006, which references Dornier Luftfahrt GmbH ASB-228-265, dated November 17, 2006. 14 BW 2007-03

2007-02-13 2 Material Incorporated by Reference (h) You must use DORNIER LUFTFAHRT GmbH Service Bulletin No. ASB-228-265, dated November 17, 2006, 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 RVAG Aerospace Services GmbH, Dornier 228 Customer Support, P.O. Box 1253, D-82231 Wessling, Federal Republic of Germany. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or 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. Issued in Kansas City, Missouri, on January 12, 2007. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-900 Filed 1-24-07; 8:45 am] 15 BW 2007-03

FAA Aircraft Certification Service AIRWORTHINESS DIRECTIVE www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html 2007-02-17 Turbomeca: Amendment 39-14904. Docket No. FAA-2006-26091; Directorate Identifier 2006-NE-28-AD. Effective Date Affected ADs (a) This airworthiness directive (AD) becomes effective March 2, 2007. (b) None. Applicability (c) This AD applies to Turbomeca Arriel -1A, -1A1, -1A2, -1B, -1B2, -1C, -1C1, -1C2, -1D, - 1D, -1D1, -1K1, -1E, -1E2, -1S, and -1S1 series turboshaft engines. These engines are installed on, but not limited to, Augusta A 109 series, Eurocopter AS 350, AS 365, SA 365, EC 155, and BK 117 series, and Sikorsky S-76A and S-76C series helicopters. Reason (d) European Aviation Safety Agency (EASA) AD No. 2006-0068, dated March 24, 2006, states: In operation, fuel leaks at the level of start electro valve fuel coupling were observed. A lack of power or an uncommanded in-flight shutdown may result from these fuel leaks. The condition described in the EASA AD may result in a forced autorotation landing, the inability to continue safe flight or a fire. Actions and Compliance (e) Within 90 days after the effective date of this AD, unless already done, do the following actions: (1) Check the condition of the three fuel unions and the ignition solenoid valve/start drain valve assembly, and check for their proper assembly. (2) Correct the installations if necessary. (3) Use Turbomeca Alert Service Bulletin No. A292 73 0251, Update No. 2, dated February 5, 2001, to do the checks and corrections. AD Differences (f) None. 16 BW 2007-03

2007-02-17 2 Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Engine Certification Office, FAA has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120-0056. Related Information (h) Contact Christopher Spinney, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238-7175, fax (781) 238-7199; e-mail: christopher.spinney@faa.gov for more information about this AD. (i) Refer to EASA AD No. 2006-0068, dated March 24, 2006, for related information. Material Incorporated by Reference (j) You must use Turbomeca Alert Service Bulletin No. A292 73 0251, Update No. 2, dated February 5, 2001, to do the checks and corrections 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 Turbomeca, 40220 Tarnos, France; telephone 33 05 59 74 40 00, fax 33 05 59 74 45 15. (3) You may review copies 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/cfr/ibr-locations.html. Issued in Burlington, Massachusetts, on January 19, 2007. Robert G. Mann, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7-1082 Filed 1-25-07; 8:45 am] 17 BW 2007-03

FAA Aircraft Certification Service AIRWORTHINESS DIRECTIVE www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html 2007-03-06 Pilatus Aircraft Limited: Amendment 39-14917; Docket No. FAA-2006-26371; Directorate Identifier 2006-CE-70-AD. Effective Date Affected ADs (a) This airworthiness directive (AD) becomes effective March 8, 2007. (b) None. Applicability (c) This AD applies to PC-12 and PC-12/45 airplanes, serial numbers 101 through 683, that are: (1) Certificated in any category; and (2) Equipped with executive passenger seats Model Number 4006 manufactured by DeCrane Aircraft Seating Company, Inc. Vendor Part Number (VPN) 403150-1 or 403150-2 with Serial Numbers (S/N) identified in DeCrane Aircraft Mandatory Service Bulletin SB05147 Revision B, dated June 26, 2006. Reason (d) The mandatory continuing airworthiness information (MCAI) states that executive seats equipped with pedestal legs were produced using a material that deviates from the approved design data. As a consequence the pedestal legs may not perform as intended under emergency landing conditions. In order to correct and control the situation, this AD requires a one time inspection to identify the VPN of the pedestal legs and the S/N of the executive seat and the replacement of the pedestal legs if necessary. Actions and Compliance (e) Unless already done, do the following actions. (1) Within 30 days after the effective date of this AD: (i) Perform an inspection to identify the VPN of the pedestal legs and the S/N of the executive seat following the accomplishment instructions in Pilatus PC-12 Service Bulletin No.: 25-032, dated October 2, 2006. (ii) If during the inspection required by paragraph (e)(1)(i) of this AD any pedestal legs with a VPN and executive seats with a S/N which correspond with the data in DeCrane Aircraft Mandatory Service Bulletin SB05147 Revision B, dated June 26, 2006, are found, prior to further flight, replace the affected pedestal legs following the accomplishment instructions in Pilatus PC-12 Service Bulletin No.: 25-032, dated October 2, 2006, with new pedestal legs with VPN 431005-17 and 431005-18. The removed parts must be returned to Pilatus. 18 BW 2007-03

2007-3-06 2 (2) As of the effective date of this AD, no person shall install any executive seats model number 4006 produced by DeCrane Aircraft Seating Company, Inc., VPN 403150-1 or 403150-2 with S/Ns identified in DeCrane Aircraft Mandatory Service Bulletin SB05147 Revision B, dated June 26, 2006, on any Pilatus Models PC-12 and PC-12/45 airplane, unless the mandatory actions of this AD have been implemented. FAA AD Differences Note: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (f) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Staff, FAA, ATTN: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4059; fax: (816) 329-4090, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et. seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120-0056. Related Information (g) Refer to Federal Office of Civil Aviation (FOCA) AD HB-2006-444, dated November 7, 2006; Pilatus Aircraft Limited Service Bulletin No.: 25-032, dated October 2, 2006; and DeCrane Aircraft Mandatory Service Bulletin SB05147 Revision B, dated June 26, 2006, for related information. Material Incorporated by Reference (h) You must use Pilatus PC-12 Service Bulletin No.: 25-032, dated October 2, 2006; and DeCrane Aircraft Mandatory Service Bulletin SB05147 Revision B, dated June 26, 2006, 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 Pilatus Aircraft Ltd., Customer Support Manager, CH-6371 STANS, Switzerland; telephone: + 41 41 619 6208; fax: + 41 41 619 7311; e-mail: SupportPC12@pilatus-aircaft.com; or Pilatus Business Aircraft Ltd., Product Support Department, 11755 Airport Way, Broomfield, CO 80021; telephone: (303) 465-9099, fax: (303) 465-6040; e-mail: Productsupport@PilBal.com. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; or 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/cfr/ibr-locations.html. Issued in Kansas City, Missouri, on January 24, 2007. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-1398 Filed 1-31-07; 8:45 am] 19 BW 2007-03

FAA Aircraft Certification Service AIRWORTHINESS DIRECTIVE www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html 2007-03-08 Pilatus Aircraft Ltd., PC-6 Series Airplanes: Amendment 39-14919; Docket No. FAA-2006-25929; Directorate Identifier 2006-CE-54-AD. Effective Date Affected ADs (a) This airworthiness directive (AD) becomes effective March 8, 2007. (b) None. Applicability (c) This AD applies to Models PC-6, PC-6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350- H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C- H2, and PC-6/C1-H2 airplanes; manufacturer serial numbers (MSN) 101 through 949, MSN 951, and MSN 2001 through 2092; that are certificated in any category. These airplanes are also identified as Fairchild Republic Company PC-6 airplanes, Fairchild Industries PC-6 airplanes, Fairchild Heli Porter PC-6 airplanes, or Fairchild-Hiller Corporation PC-6 airplanes. Reason (d) The mandatory continuing airworthiness information (MCAI) states that exfoliation corrosion in the fittings of some PC-6 airplanes was found. These fittings are installed exterior to the bottom skin of the wing skin. If not corrected, undetected corrosion in this area could lead to failure of the fitting and subsequent loss of control of the airplane. Actions and Compliance (e) Unless already done, do the following actions. (1) Within 12 months after the effective date of this AD and repetitively thereafter at intervals not to exceed 12 months, perform an inspection required by paragraph 3.B.(2) of PILATUS PC-6 Service Bulletin (SB) No. 57-003, dated June 13, 2006, of the fittings Part Number (P/N) 6102.0041.00, P/N 111.35.06.055 or P/N 111.35.06.056 for signs of corrosion. Repair of minor surface corrosion is permitted according to the Repair and Overhaul Manual (ROM) (Report No. 1391), Chap. 2 and 4. Corrosion outside these limits is not permitted. (2) If during any of the inspections required by paragraph (e)(1) of this AD, any minor surface corrosion is found, prior to further flight, remove the minor surface corrosion (Ref. ROM. Chap. 2 and 4). (3) If during any of the inspections required by paragraph (e)(1) of this AD, any corrosion out of limits is found (Ref. ROM, Chap. 2 and 4), prior to further flight, replace the fittings in accordance with paragraph 4 of PILATUS PC-6 SB No. 57-003, dated June 13, 2006, with new (retrofit) fittings P/N 111.35.06.185 and/or P/N 111.35.06.186. 20 BW 2007-03

2007-03-08 2 (4) Replacement of the fittings with new (improved) fittings P/N 111.35.06.185 (left hand side) and/or 111.35.06.186 (right hand side) terminates the repetitive inspection for that side. FAA AD Differences Note: This AD differs from the MCAI and/or service information as follows: (1) The FAA AD is requiring repetitive inspections, not just a one-time inspection as required in the MCAI. (2) The Service Bulletin specifies subsequent inspections for corrosion will be included in Chapter 5 of the Aircraft Maintenance Manual (AMM). The only way we (FAA) can mandate these repetitive inspections is through an AD. Other FAA AD Provisions (f) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Staff, FAA, ATTN: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4059; fax: (816) 329-4090, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et.seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120-0056. Related Information (g) Refer to FOCA AD HB-2006-400, effective date September 28, 2006, which references Pilatus Aircraft Ltd. SB No. 57-003, dated June 13, 2006, for related information. Material Incorporated by Reference (h) You must use PILATUS PC-6 Service Bulletin (SB) No. 57-003, dated June 13, 2006, 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 Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans, Switzerland; telephone: +41 41 619 63 19; fax: +41 41 619 6224. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; or 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/cfr/ibr-locations.html. Issued in Kansas City, Missouri, on January 24, 2007. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-1494 Filed 1-31-07; 8:45 am] 21 BW 2007-03

FAA Aircraft Certification Service AIRWORTHINESS DIRECTIVE www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html 2007-03-14 Turbomeca: Amendment 39-14925; Docket No. FAA-2007-27009; Directorate Identifier 2007-NE-02-AD. Effective Date Affected ADs (a) This airworthiness directive (AD) becomes effective February 20, 2007. (b) None. Applicability (c) This AD applies to Turbomeca Arriel 2B1 turboshaft engines. These engines are installed on, but not limited to Eurocopter AS 350 B3 and EC 130 B4 helicopters. Reason states: (d) European Aviation Safety Agency (EASA) AD No. 2007-0006, dated January 9, 2007, This AD is prompted by several reported cases of rupture of the (hydro-mechanical metering unit (HMU)) constant delta pressure valve diaphragm on Arriel 2B1 engines, due to the wear of the delta P diaphragm fabric. Rupture can result in the loss of the automatic control mode of the helicopter, accompanied with a deterioration of the behavior of the auxiliary back-up mode (emergency mode). The loss of automatic control mode coupled with the deteriorated performance of the backup mode can lead to the inability to continue safe flight, forced autorotation landing, or an accident. Actions and Compliance (e) Unless already done, do the following actions. (1) Replace the HMU with a serviceable HMU before the HMU accumulates 2,000 hourssince-new, since-last-overhaul, or since-incorporation of Turbomeca Service Bulletin (SB) No. 292 73 2105; or within 30 days after the effective date of this AD, whichever occurs later. (2) Thereafter, replace HMUs with a serviceable HMU at every 2,000 hours-since-new, sincelast-overhaul, or since-incorporation of Turbomeca SB No. 292 73 2105, whichever occurs later. (3) For the purposes of this AD, a serviceable HMU is an HMU fitted with a new constant delta P diaphragm in accordance with Turbomeca Service Bulletin No. 292 73 2818, dated October 18, 2006. 22

2007-03-14 2 FAA AD Differences (f) None. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Engine Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (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 EASA Airworthiness Directive 2007-0006, dated January 9, 2007, and Turbomeca Mandatory Service Bulletin No. 292 73 2818, dated October 18, 2006, for related information. (i) Contact Christopher Spinney, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238-7175, fax (781) 238-7199; e-mail: christopher.spinney@faa.gov for more information about this AD. Material Incorporated by Reference (j) None. Issued in Burlington, Massachusetts, on January 29, 2007. Francis A. Favara, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7-1709 Filed 2-1-07; 8:45 am] 23