FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS BIWEEKLY 2007-01 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 3 BW 2007-01
FAA Aircraft Certification Service AIRWORTHINESS DIRECTIVE www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html 2006-26-03 Alpha Aviation Design Limited (Type Certificate No. A48EU formerly held by APEX Aircraft and AVIONS PIERRE ROBIN): Amendment 39-14861; Docket No. FAA-2006-26492; Directorate Identifier 2006-CE-77-AD. Effective Date Affected ADs (a) This AD becomes effective on January 30, 2007. (b) None. Applicability (c) This AD applies to Model R2160 airplanes, serial numbers 142, 143, 144, 147, 148, and 151 through 155, that are certificated in any category. Unsafe Condition (d) This AD is the result of the possibility of fuel leakage at the end of the adapter in the fuel pressure indication system. We are issuing this AD to detect and correct fuel leaks in the fuel pressure indicating system. This failure could allow fuel to leak near the exhaust manifold and lead to a fire. Compliance (e) To address this problem, you must do the following, unless already done: Actions Compliance Procedures (1) Inspect the fuel pressure system indication adaptor (part number 52.46.11.000 or FAA approved equivalent part number) for indication of fuel leakage. (2) If any leak is found, repair the leak. Before further flight after January 30, 2007 (the effective date of this AD) and thereafter at intervals not to exceed 50 hours time-in-service. Before further flight after inspection required by paragraph (e)(1) of this AD. Perform a visual inspection. Figure 1 of Robin Aviation Service Letter No 37 rev. 2 dated April 4, 2000, shows a view of the fuel pressure indicator system. Perform a repair program approved specifically for this AD by the FAA. 4 BW 2007-01
2006-26-03 2 Alternative Methods of Compliance (AMOCs) (f) The Manager, Standards Staff, FAA, ATTN: Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4146; fax: (816) 329-4090, 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 the Civil Aviation Authority of New Zealand AD DCA/R2000/33, dated June 29, 2006, which references Direction Generale de l'aviation Civile (DGAC) AD F-2001-391(a), dated October 3, 2001. Material Incorporated by Reference (h) None. Issued in Kansas City, Missouri, on December 15, 2006. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-21923 Filed 12-22-06; 8:45 am] 5 BW 2007-01
FAA Aircraft Certification Service AIRWORTHINESS DIRECTIVE www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html 2006-26-07 Turbomeca: Amendment 39-14865; Docket No. FAA-2006-26138; Directorate Identifier 2006-NE-38-AD. Effective Date Affected ADs (a) This airworthiness directive (AD) becomes effective January 18, 2007. (b) None. Applicability (c) This AD applies to Turbomeca Model Arrius 2B1, 2B1A, and 2B2 turboshaft engines that do not embody modification TU122. These engines are used on, but not limited to Eurocopter EC135 T1 and T2 helicopters. Reason (d) European Aviation Safety Agency (EASA) AD, 2006-0142, dated May 29, 2006 states: Investigations of incidents which occurred on ARRIUS 2 turboshaft engines have revealed the interruption of engine lubrication further [due] to oil passage blockage within the lubrication unit check valve. This blockage comes from the excessive swelling of the check valve piston o-ring. The level of swelling of the o-ring depends on the class of the oil used (Standard (STD) or High-Thermal Stability (HTS)) and the engine operating time. This phenomenon only affects ARRIUS 2 engines which do not embody modification Tu122 (i.e.: check-valve piston without o-ring). A simultaneous interruption of the lubrication on both engines may lead to a double non-commanded in-flight shutdown. The oil usually being the same on both engines, available data put into evidence that this risk has to be considered and that measures to restore the level of safety have to be imposed on ARRIUS 2 engines without modification Tu122 embodied. The condition described in the EASA AD can lead to a forced autorotation landing or an accident. Actions and Compliance (e) Unless already done, do the following actions. 6 BW 2007-01
2006-26-07 2 (1) Replace the check-valve piston o-ring according to paragraph 2 of Turbomeca Alert Service Bulletin No A319 79 2832, Update 1, dated April 3, 2006, within the next 50 operating hours when the number of operating hours is greater than: (i) 300 hours for engines operating with HTS-class oil and engines for which the history of the oils used is not available or engines which used to operate with HTS-class oil and which no longer do so. (ii) 450 hours for engines operating with STD class-oil since their introduction into service. (2) Repeat operation of paragraph (1): (i) Every 300 hours for engines operating with HTS-class oil and engines for which the history of the oils used is not available or engines which used to operate with HTS-class oil and which no longer do so. (ii) Every 500 hours for engines operating with STD class-oil since their introduction into service. 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) Contact Christopher Spinney, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238-7175; fax (781) 238-7199 for more information about this AD. (i) Refer to the EASA Mandatory Continuing Airworthiness Information (MCAI) Airworthiness Directive 2006-0142, dated May 29, 2006, and Turbomeca Service Bulletin A319 79 2122, dated March 14, 2006, for related information. 7 BW 2007-01
2006-26-07 3 Material Incorporated by Reference (j) You must use Turbomeca Alert Service Bulletin A319 79 2832, Update 1, dated April 3, 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 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 December 21, 2006. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E6-22272 Filed 12-29-06; 8:45 am] 8 BW 2007-01
FAA Aircraft Certification Service AIRWORTHINESS DIRECTIVE www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html 2006-26-08 Raytheon Aircraft Company: Amendment 39-14866; Docket No. FAA-2006-25745; Directorate Identifier 2006-CE-47-AD. Effective Date Affected ADs Applicability (a) This AD becomes effective on December 28, 2006. (b) This AD supersedes AD 2006-02-51; Amendment 39-14459. (c) This AD applies to Model 390 airplanes, all serial numbers, that are certificated in any category: Unsafe Condition (d) This AD is the result of several hydraulic pump outlet tube failures after issuance of AD 2006-02-51. We are issuing this AD to prevent failure of the hydraulic pump outlet tubes and consequent leaking of hydraulic fluid. Such leakage could result in a fire. There is also a risk of loss of hydraulic system functions including normal gear extensions, speed brakes, roll spoilers, lift dump, and normal brakes. Compliance (e) To address this problem, you must do the following, unless already done: 9 BW 2007-01
2006-26-08 2 Actions Compliance Procedures (1) Visually inspect the hydraulic pump outlet tube for evidence of chafing, excessive vibration, wear, deterioration, or hydraulic fluid leakage, as follows: (i) For the left-hand (LH) engine: Remove the clamp, perform the inspection, and replace the clamp with a new one as specified in Raytheon Mandatory Service Bulletin No. SB 29-3771 after each inspection. (ii) For the right-hand (RH) engine: Perform the inspection. Removal and replacement of the clamps are not necessary. Initially at whichever of the following occurs first and thereafter at intervals not to exceed 25 hours time-in-service (TIS): (A) Within the next 25 hours TIS after December 28, 2006 (the effective date of this AD); or (B) At the next inspection required by AD 2006-02-51. Inspect following Raytheon Safety Communique No. 267, dated January 2006. Raytheon Safety Communique No. 267, dated January 2006, addresses the LH engine. Use the same inspection procedures for the RH engine hydraulic pump outlet tube (P/N 390-580037). Remove and replace the clamp (LH only) following Raytheon Mandatory Service Bulletin No. SB 29-3771, dated January, 2006. 10 BW 2007-01
2006-26-08 3 (2) Replace the hydraulic pump outlet tube, Part Number (P/N) 390-580035 (or FAA-approved equivalent) for the LH engine or P/N 390-580037 (or FAA-approved equivalent) for the RH engine. (3) Incorporate Raytheon Aircraft Company Part Number 390-590001-0003C3TC6, dated September 16, 2006 into the Airplane Flight Manual (AFM). Each and every time any of the following occurs: (i) Prior to further flight after any inspection from paragraph (e)(1) of this AD where evidence of chafing, excessive vibration, wear, deterioration, or hydraulic fluid leakage is found; and (ii) Within 1 hour TIS following identification of an intended or unintended engine operation with the hydraulic valve closed. Within 5 days after December 28, 2006 (the effective date of this AD). Raytheon Aircraft Premier 1 Model 390 Maintenance Manual, P/N 390-590001-0015. The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may do the AFM changes requirement of this AD. Make an entry into the aircraft records showing compliance with this portion of the AD in accordance with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9). Alternative Methods of Compliance (AMOCs) (f) The Manager, Wichita Aircraft Certification Office, FAA, ATTN: James P. Galstad, Propulsion Aerospace Engineer, ACE 116W, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-4135; fax: (316) 946-4107, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Material Incorporated by Reference (g) You must use Raytheon Mandatory Service Bulletin No. SB 29-3771, dated January 2006; and Raytheon Safety Communique No. 267, dated January 2006, to do the actions required by this AD, unless the AD specifies otherwise. 11 BW 2007-01
2006-26-08 4 (1) The Director of the Federal Register previously approved this incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part 51 on February 2, 2006 (71 FR 5581, February 2, 2006). (2) For service information identified in this AD, contact Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-0085; telephone: (800) 625-7043. (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 December 22, 2006. Kim Smith, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-22382 Filed 12-27-06; 8:45 am] 12 BW 2007-01