FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS BIWEEKLY 2005-10 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 2005-01 2004-26-09 Rolls-Royce Corporation Engine: 250-B17, -B17B, -B17C, -B17D, -B17E, 250-C20, -C20B, -C20F, -C20J, -C20S, and -C20W Series Turboprop and Turboshaft 2004-26-11 Bell Helicopter Textron Canada Rotorcraft: 222, 222B, 222U, 230, 430 2005-01-04 S 98-15-13 Raytheon Aircraft Company 65-90, 65-A90, B90, C90, C90A, C90B, E90, F90, H90, 100, A100, A100-1, (RU-21J), B100, 200, 200C, 200CT, 200T, A200, A200C, A200CT, B200, B200C, B200CT, B200T, 300, B300, B300C, 99, 99A, A99,, A99A, B99, C99 2005-01-10 S 74-06-01 The New Piper Aircraft, Inc PA-23-235, PA-23-250, and PA-E23-250 2005-01-11 Pilatus Aircraft Ltd. PC-12 and PC-12/45 Biweekly 2005-02 98-20-38 R1 R Raytheon Aircraft Company Beech 200 (A100-1 (U-21J)), Beech 200C, Beech 200CT, Beech 200T, Beech A200 (C-12A) or (C-12C), Beech A200C (UC-12B), Beech A200CT (C-12D), (FWC-12D), (RC-12D), (C-12F), (RC-12G), (RC-12H), (RC-12K), or (RC-12P), B200CT, and B200T 2005-01-14 S 2002-21-16 Bombardier-Rotax GmbH Engine: 912 F, 912 S, and 914 F Series Reciprocating 2005-01-17 S 98-03-14 EXTRA Flugzeugbau GmbH EA 300 and EA 300/S 2005-01-18 S 93-25-07 Raytheon Aircraft Company A100 1 (U 21J), 200, B200, A200 (C 12A), A200 (C 12C), A200C (UC 12B), A200CT (C 12D), A200CT (FWC 12D), A200CT (RC 12D), A200CT (C 12F), A200CT (RC 12G), A200CT (RC 12H), A200CT (RC 12K), A200CT (RC 12P), A200CT (RC 12K), 200C, B200C, 200CT, 200T, B200C (C-12F), B200C (UC 12F), B200C (UC 12M), B200CT, 300, B300, B300C, and B300C 2005-01-19 S 2004-10-15 GARMIN International Inc Appliance: GTX 33, GTX 33D, GTX 330, and GTX 330D Mode S Transponders 2005-02-01 The Lancair Company LC40 550FG and LC42 550FG Biweekly 2005-03 2005-01-04 COR S 98-15-13 2005-01-18 COR S 93-25-07 Raytheon Aircraft Company 65 90, 65 A90, B90, C90, C90A, E90, F90, H90, 100, A100, A100 1 (RU 21J), B100, 200, 200C, 200CT, 200T, A200, A200C, A200CT, B200, B200C, B200CT, B200T, 300, B300, B300C, 99, 99A, A99, A99A, B99, and C99 Raytheon Aircraft Company 2005-02-11 COR Gippsland Aeronautics Pty. Ltd. GA8 2005-03-04 Pacific Aerospace Corp., Ltd. 750XL Biweekly 2005-04 2005-01-04 COR S 98-15-13 A100 1 (U 21J), 200, B200, A200 (C 12A), A200 (C 12C), A200C (UC 12B), A200CT (C 12D), A200CT (FWC 12D), A200CT (RC 12D), A200CT (C 12F), A200CT (RC 12G), A200CT (RC 12H), A200CT (RC 12K), A200CT (RC 12P), A200CT (RC 12K), 200C, B200C, 200CT, B200CT, 200T, B200T, B200C (C 12F), B200C (UC 12F), B200C (UC 12M), B200CT, 300, B300C, and B300C Raytheon Aircraft Company 65 90, 65 A90, B90, C90, C90A, E90, F90, H90, 100, A100, A100 1 (RU 21J), B100, 200, 200C, 200CT, 200T, A200, A200C, A200CT, B200, B200C, B200CT, B200T, 300, B300, B300C, 99, 99A, A99, A99A, B99, C99 2005-03-07 Bell Helicopter Textron Canada Rotorcraft: 407 2005-03-08 Eurocopter France Rotorcraft: AS350B, BA, B1, B2, B3, C, D, D1, and EC130 B4 2005-03-09 Eurocopter France Rotorcraft: EC 155B, EC155B1, SA-360C, SA-365C, SA-365C1, SA-365C2, SA-365N, SA-365N1, AS-365N2, AS 365 N3, and SA-366G1 2005-03-10 S 2002-08-54 Bell Helicopter Textron Rotorcraft: 222, 222B, 222U, and 230 2005-04-09 S 2004-26-11 Bell Helicopter Textron Canada Rotorcraft: 222, 222B, 222U, 230, and 430 3
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 2005-05 2005-04-08 Hartzell Propeller Inc. Propeller: HC-B3TN-5( )/T10282( ) 2005-04-10 General Electric Company Engine: CT58-140-1, CT58-140-2, and surplus military T58-GE-5, -10, -100, and ''402 turboshaft 2005-04-16 Pilatus Aircraft Ltd. PC-12 and PC-12/45 2005-05-51 E Cessna Aircraft Company 402C and 414A 2005-05-52 E, S 2005-05-51 Cessna Aircraft Company 402C and 414A 2005-05-53 E Cessna Aircraft Company 172R, 172S, 182T, and T182T 2005-05-53 R1 E, R, S 2005-05- 53 Cessna Aircraft Company 172R, 172S, 182T, and T182T Biweekly 2005-06 2005-05-14 Eagle Aircraft (Malaysia) Eagle 150B 2005-05-15 Honeywell International Inc. Engine: TFE731-2 and -2C series, and TFE731-3, -3A, -3AR, -3B, -3BR, and -3R series turbofan 2005-06-01 Eurocopter France Rotorcraft: EC 155B and EC 155B1 Biweekly 2005-07 2005-05-52 FR, S 2005-05-51 Cessna 402C and 414A and 2000-23-01 2005-05-53 R1 R, 2005-05-53 Cessna 172R, 172S, 182T, and T182T 2005-06-13 S 99-0602 Fairchild Aircraft, Inc. SA226-AT, SA226-TC, SA226-T, SA226-T(B), SA227-TT, SA227-TT(300), SA227-AC, SA227-AT, SA227-BC, and SA227- CC/DC 2005-07-01 Cessna 208 and 208B Biweekly 2005-08 83-08-01 R2 R, S 83-08-01 R1 Hartzell Propeller Inc. Propeller: HC-B3TN-2, HC-B3TN-3, HC-B3TN-5, HC-B4TN-3, HC-B4TN-5, HC-B4MN-5, and HC-B5MP-3 turbopropellers 2005-07-01 COR Cessna 208 and 208B 2005-07-27 S 2000-18-04 Aviointeriors S.p.A. Appliance: Model 312 Seats Biweekly 2005-09 2005-08-06 Centrair Glider: 101, 101A, 101AP, and 101P 2005-08-07 Pilatus Aircraft Limited Sailplane: B4-PC11, B4-PC11A, and B4-PC11AF 2005-08-12 Centrair Glider: 101, 101A, 101AP, and 101P 2005-08-13 Glaser-Dirks Flugzeugbau Sailplane: DG-800B GmbH 2005-08-14 LET a.s. Sailplane: Blanik L-13 AC 2005-09-51 E Turbomeca S.A. Engine: Arrius 2F Turboshaft Biweekly 2005-10 2004-25-16 R1 R, 2004-25-16 Kelly Aerospace Power Systems Appliance: Fuel regulator shutoff valve 2005-08-06 COR Centrair Glider: 101 Series 2005-09-05 Eurocopter France Rotorcraft: EC120B 2005-09-06 Agusta S.p.A. Rotorcraft: A119 2005-09-07 Agusta S.p.A. Rotorcraft: A109E 4
BW 2005-10 KELLY AEROSPACE POWER SYSTEMS AIRWORTHINESS DIRECTIVE APPLIANCE REVISION SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2004-25-16 R1 Kelly Aerospace Power Systems (formerly owned by ElectroSystems, JanAero Devices, Janitrol, C&D Airmotive Products, FL Aerospace, and Midland-Ross Corporation): Amendment 39-14076; Docket No. FAA-2004-19693; Directorate Identifier 2004-CE-40-AD; revises AD 2004-25-16, Amendment 39-13904. When Does This AD Become Effective? (a) This AD becomes effective on June 20, 2005. What Other ADs Are Affected By This Action? (b) This AD revises AD 2004-25-16, Amendment 39-13904. What Airplanes Are Affected by This AD? (c) This AD applies to aircraft equipped with a fuel regulator shutoff valve part number (P/N) 14D11, A14D11, B14D11, C14D11, 23D04, A23D04, B23D04, C23D04, or P23D04 used with B1500, B2030, B2500, B3040, B3500, B4050, or B4500 B-Series combustion heaters. The following is a list of aircraft where the B-Series combustion heater could be installed. This is not a comprehensive list and aircraft not on this list that have the heater installed through field approval or other methods are still affected by this AD: Manufacturer Aircraft models/series (1) Bombardier Inc CL 215, CL 215T, and CLT 415. (2) Cessna Aircraft Company 208, T303, 310F, 310G, 310H, 310I, 310J, 310K, 310L, 310N, 310P, 310Q, 320C, 320D, 320E, 320F, 337 Series, 340, 340A, 414, 414A, 421, 421A, 421B, and 421C. (3) The New Piper PA 23 Series, PA 30, PA 31 Series, PA 34 Series, PA 39, and PA 44 Aircraft Inc (4) Raytheon Aircraft Corporation Series. 95 B55 Series, 58, 58TC, 58P, 60, A60, and 76. Note 1: The B1500, B2030, B2500, B3040, B3500, B4050, or B4500 B-Series combustion heaters were previously manufactured by Janitrol, C&D Airmotive Products, FL Aerospace, and Midland-Ross Corporation. 5
2004-25-16 R1 2 What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of numerous reports of fuel regulator shutoff valves leaking fuel. We are issuing this AD to prevent failure of the fuel regulator shutoff valve, which could result in fuel leakage in aircraft with these combustion heaters. This failure could result in an aircraft fire. What Must I Do To Address This Problem? (e) To address this problem, you must do the following: Actions Compliance Procedures Within the next 25 hours aircraft time-in-service (TIS) after January 5, 2005, (the effective date of AD 2004 25 16), unless already done within the last 75 hours aircraft TIS (e.g., compliance with AD 2001 08 01 or 2001 17 13). Repetitively inspect thereafter at intervals not to exceed 100 hours aircraft TIS or 12 months, whichever occurs first. This is established to coincide with 100- hour and annual with 100-hour and annual inspections. the pressure test. (1) Visually inspect or pressure test the fuel regulator shutoff valve for any signs of fuel leaks. (2) If no fuel leaks or no signs of fuel stains are found during each inspection required by paragraph (e)(1) of this AD, make a log book entry with the date of inspection (month/year). Prior to further flight after each inspection required in paragraph (e)(1) of this AD. Locate the pressure shutoff valve in the installation using the applicable maintenance manual for valve location, removal, and installation instructions. Follow the procedures in Kelly Aerospace Power Systems Service Bulletin No. A 107A, Issue Date: September 6, 2002, for the visual inspection or Follow the procedures in Kelly Aerospace Power Systems Service Bulletin No. A 107A, Issue Date: September 6, 2002. 6
(3) If any signs of fuel leaks or any signs of fuel stains are found during any inspection required in paragraph (e)(1) of this AD, replace the valve with a new valve of appropriate part number (P/N) that has a manufacturer s date code of 02/02 or later. For Piper PA 31 350 model aircraft, replace P/N A23D04 7.5 valve with P/N P23D04 7.5 Ensure there are no fuel leaks in the replacement valve by following the inspection and documentation requirements in paragraphs (e)(1) and (e)(2) of this AD. (4) As an alternative method of compliance to this AD, you may disable the heater provided you immediately comply with inspection, identification, and replacement requirements of this AD when you bring the heater back into service. Do the following actions when disabling: (i) Cap the fuel supply line upstream of the fuel regulator and shutoff valve; (ii) Disconnect the electrical power and ensure that the connections are properly secured to reduce the possibility of electrical spark or structural damage; (iii) Inspect and test to ensure that the cabin heater system is disabled; (iv) Ensure that no other aircraft system is affected by this action; (v) Ensure there are no fuel leaks; and (vi) Fabricate a placard with the words: System Inoperative. Install this placard at the heater control valve within the pilot s clear view. (5) Only install a fuel regulator shutoff valve with a manufacture date code of 02/02 or later. Before further flight after the inspection where any fuel leak was found. If you choose this option, you must do it before the next required inspection specified in paragraph (e)(1) of this AD. To bring the heater back into service, you must do the actions of paragraphs (e)(1), (e)(2), and (e)(3) of this AD (inspection, identification, and replacement, as necessary). As of January 5, 2005, (the effective date of AD 2004 25 16). 2004-25-16 R1 3 Follow Kelly Aerospace Power Systems Service Bulletin No. A 107A, Issue Date: September 6, 2002; Piper Vendor Service Publication VSP 150, dated January 31, 2003; and the applicable maintenance manual. Not Applicable. Not Applicable. 7
2004-25-16 R1 4 May I Request an Alternative Method of Compliance? (f) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.19. (1) Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, Manager, Atlanta ACO, FAA. For information on any already approved alternative methods of compliance, contact Kevin L. Brane, Aerospace Engineer, Atlanta Aircraft Certification Office, FAA, One Crown Center, 1985 Phoenix Boulevard, Suite 450, Atlanta, GA 30349; telephone: (770) 703-6063; facsimile: (770) 703-6097. (2) Alternative methods of compliance approved for AD 2004-25-16, which is revised by this AD, are approved as alternative methods of compliance with this AD. Does This AD Incorporate Any Material By Reference? (g) You must do the actions required by this AD following the instructions in Kelly Aerospace Power Systems Service Bulletin No. A-107A, Issue Date: September 6, 2002; and Piper Vendor Service Publication VSP-150, dated January 31, 2003. (1) On January 5, 2005 (69 FR 75228, December 16, 2004), and in accordance with 5 U.S.C. 552(a) and 1 CFR part 51, the Director of the Federal Register previously approved the incorporation by reference. (2) To get a copy of the service information, contact Kelly Aerospace Power Systems, P.O. Box 273, Fort Deposit, Alabama 36032; telephone: (334) 227-8306; facsimile: (334) 227-8596; Internet: http://www.kellyaerospace.com. To review copies of the service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2004-19693; Directorate Identifier 2004-CE-40-AD. Issued in Kansas City, Missouri, on April 28, 2005. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-8884 Filed 5-5-05; 8:45 am] BILLING CODE 4910-13-P 8
BW 2005-10 CENTRAIR AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-08-06 Centrair: Amendment 39-14058; Docket No. FAA-2004-19616; Directorate Identifier 2004-CE-38-AD. When Does This AD Become Effective? (a) The effective date of this AD (2005-08-06) remains June 2, 2005. What Other ADs Are Affected by This Action? (b) None. What Gliders Are Affected by This AD? (c) This AD affects Models 101, 101A, 101AP, and 101P gliders, serial numbers as specified below, that are certificated in any catergory: (1) Serial numbers 101A600 through 101A637 where the original manufacturer's hinge pins are installed; and (2) All gliders that had hinge pins replaced with hinge pins that Centrair delivered between February 20, 1995, and February 28, 2001. What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified in this AD are intended to replace incorrectly heat-treated elevator or aileron hinge pins, which could result in failure of the elevator or ailerons. Such failure during takeoff, landing, or flight operations could lead to loss of glider control. (e) To address this problem, you must do the following: 9
2005-08-06 2 Actions Compliance Procedures Within the next 25 Follow Société hours time-in-service Nouvelle Centrair (TIS) after June 2, Service Bulletin 2005 (the effective No. 101 22, dated date of this AD), March 13, 2001. unless already done. (1) For serial numbers 101A600 through 101A637 where the original manufacturer s hinge pins are installed and all gliders that had hinge pins replaced with hinge pins that Centrair delivered between February 20, 1995, and February 28, 2001: replace the hinge pins with part number (P/N) SY991A hinge pins. (2) For all serial numbers: Do not install any elevator and aile-ron hinge pins that are not P/N SY991A hinge pins. May I Request an Alternative Method of Compliance? As of June 2, 2005 (the effective date of this AD). Not Applicable. (f) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, Small Airplane Directorate, FAA. For information on any already approved alternative methods of compliance, contact Greg Davison, Aerospace Engineer, FAA, Small Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4130; facsimile: (816) 329-4090. Is There Other Information That Relates to This Subject? AD. (g) French AD Number 2001-247(A), dated June 27, 2001, also addresses the subject of this Does This AD Incorporate Any Material by Reference? (h) You must do the actions required by this AD following the instructions in Societe Nouvelle Centrair Service Bulletin No. 101-22, dated March 13, 2001. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact CENTRAIR, Aerodome B.P.N. 44, 36300 Le Blanc, France; telephone: 02.54.37.07.96; facsimile: 02.54.37.48.64. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2004-19616. Issued in Kansas City, Missouri, on May 3, 2005. Kim Smith, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-9271 Filed 5-9-05; 8:45 am] BILLING CODE 4910-13-P 10
BW 2005-10 EUROCOPTER FRANCE AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-09-05 Eurocopter France: Amendment 39-14073. Docket No. FAA-2005-20289; Directorate Identifier 2003-SW-55-AD. Applicability Model EC120B helicopters, serial number 1362 and below, certificated in any category. Compliance Required within 50 hours time-in-service (TIS) for helicopters with 500 or more hours TIS; or no later than 550 hours TIS for helicopters with less than 500 hours TIS, unless accomplished previously. To detect incorrect positioning of the tail rotor drive shaft (drive shaft) damper half-clamps (half-clamps), and to prevent interference of the half-clamps with the drive shaft, which could result in scoring on the drive shaft, failure of the drive shaft, and subsequent loss of control of the helicopter, accomplish the following: (a) Inspect the half-clamps, part number C651A4103201 or C651A4103202, to determine if they are centered on the friction ring, using the Operational Procedure, paragraph 2.B., of Eurocopter Alert Telex No. 65A004 R1, dated January 27, 2004 (Alert Telex). If the half-clamps are not centered on the friction ring, center the half-clamps on the friction ring in accordance with the Operational Procedure, paragraph 2.B, and Rework Sheet No. EC 120-53-02-04 in Appendix 1 of the Alert Telex. (b) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Safety Management Group, Rotorcraft Directorate, FAA, for information about previously approved alternative methods of compliance. (c) Special flight permits will not be issued. (d) The inspection and modification shall be done in accordance with Eurocopter Alert Telex No. 65A004 R1, dated January 27, 2004. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527. Copies may be inspected 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) This amendment becomes effective on June 13, 2005. 11
2005-09-05 2 Note: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) AD No. UF-2003-465, dated December 22, 2003, and AD No. F-2003-465, Revision A, dated January 21, 2004. Issued in Fort Worth, Texas, on April 27, 2005. Carl F. Mittag, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 05-8951 Filed 5-6-05; 8:45 am] BILLING CODE 4910-13-P 12
BW 2005-10 AGUSTA S.P.A. AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-09-06 Agusta S.p.A.: Amendment 39-14074. Docket No. FAA-2005-20291; Directorate Identifier 2004-SW-25-AD. Applicability Model A119 helicopters, serial numbers 14001 through 14037, except serial number 14036, certificated in any category. Compliance Required as indicated, unless accomplished previously. To detect a fracture, a crack, or looseness of a main transmission support fitting (fitting) attachment bolt (bolt) and prevent fatigue failure of a fitting bolt and subsequent loss of control of the helicopter, accomplish the following: (a) Within 5 hours time-in-service (TIS), and then at intervals not to exceed 10 hours TIS until a torque inspection of each fitting bolt is accomplished in accordance with paragraph (b) of this AD, inspect each fitting bolt, part number NAS625-14 and NAS625-18, for a fracture, a crack, or looseness, using a light and a mirror. (1) On each of the 4 fittings, if a fracture or a crack is found in any bolt, replace all 4 bolts in the fitting with airworthy fitting bolts before further flight. (2) If looseness is found in any bolt in any fitting, inspect each of the 4 bolts on each of the 4 fittings (16 bolts total) to determine if the torque is between 11.3-15.8 Nm (100-140 inch-pounds). If the indicated torque is not within the acceptable range on any bolt in a fitting, before further flight, remove all 4 bolts in the fitting and replace them with airworthy fitting bolts in accordance with Part II, steps 4.1 through 5., of Agusta Bollettino Tecnico No. 119-8, dated April 7, 2004 (BT). (b) Within 25 hours TIS, inspect each bolt in each fitting to determine if the torque is between 11.3-15.8 Nm (100-140 inch-pounds). If the indicated torque is not within the acceptable range on any bolt, before further flight, remove all 4 bolts in the fitting and replace them with airworthy fitting bolts in accordance with Part II, steps 4.1 through 5., of the BT. (c) Accomplishing the inspections specified in paragraphs (a) and (b) constitute terminating actions for the requirements of this AD. (d) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Safety Management Group, Rotorcraft Directorate, FAA, for information about previously approved alternative methods of compliance. 13
2005-09-06 2 (e) Special flight permits may be issued in accordance with 14 CFR 21.197 and 21.199 to operate the helicopter to a location where the requirements of this AD can be accomplished, provided that no fracture, crack, or looseness was found during the inspections required by this AD. (f) The inspections and replacements shall be done in accordance with Agusta Bollettino Tecnico No. 119-8, dated April 7, 2004. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Agusta, 21017 Cascina Costa di Samarate (VA) Italy, Via Giovanni Agusta 520, telephone 39 (0331) 229111, fax 39 (0331) 229605-222595. Copies may be inspected 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. (g) This amendment becomes effective on June 13, 2005. Note: The subject of this AD is addressed in Ente Nazionale per l'aviazione Civile (Italy) AD No. 2004-108, dated April 8, 2004. Issued in Fort Worth, Texas, on April 27, 2005. Carl Mittag, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 05-8953 Filed 5-6-05; 8:45 am] BILLING CODE 4910-13-U 14
BW 2005-10 AGUSTA S.P.A. AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-09-07 Agusta S.p.A.: Amendment 39-14075. Docket No. FAA-2005-20292; Directorate Identifier 2004-SW-26-AD. Applicability Model A109E helicopters, certificated in any category. Compliance Required as indicated, unless accomplished previously. To detect a fracture, a crack, or looseness of a main transmission support fitting (fitting) attachment bolt (bolt), and prevent fatigue failure of a fitting bolt and subsequent loss of control of the helicopter, accomplish the following: (a) Within 5 hours time-in-service (TIS), and then at intervals not to exceed 10 hours TIS until a torque inspection of each fitting bolt is accomplished in accordance with paragraph (b) of this AD, inspect each fitting bolt, part number NAS625-14, for a fracture, a crack, or looseness using a light and a mirror in accordance with Part I, steps 1. through 4., of Agusta Bollettino Tecnico No. 109EP- 43, dated March 25, 2004 (BT). (1) On each of the 4 fittings, if a fracture or a crack is found in any bolt, replace all 4 bolts in the fitting with airworthy fitting bolts before further flight. (2) If looseness is found in any bolt in any fitting, inspect each of the 4 bolts on each of the 4 fittings (16 bolts total) to determine if the torque is between 11.3-15.8 Nm (100-140 inch-pounds). If the indicated torque is not within the acceptable range on any bolt in a fitting, before further flight, remove all 4 bolts in the fitting and replace them with airworthy fitting bolts in accordance with Part II, steps 5.1 through 9. of the BT. (b) Within 25 hours TIS, inspect each bolt in each fitting to determine if the torque is between 11.3-15.8 Nm (100-140 inch-pounds). If the indicated torque is not within the acceptable range on any bolt, before further flight, remove all 4 bolts in the fitting and replace them with airworthy fitting bolts in accordance with Part II, steps 5.1 through 9., of the BT. (c) Accomplishing the inspections specified in paragraphs (a) and (b) constitute terminating actions for the requirements of this AD. (d) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Safety Management Group, Rotorcraft Directorate, FAA, for information about previously approved alternative methods of compliance. 15
2005-09-07 2 (e) Special flight permits may be issued in accordance with 14 CFR 21.197 and 21.199 to operate the helicopter to a location where the requirements of this AD can be accomplished, provided that no fracture or crack or looseness was found during the inspections required by this AD. (f) The inspections and replacements shall be done in accordance with Agusta Bollettino Tecnico No. 109EP-43, dated March 25, 2004. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Agusta, 21017 Cascina Costa di Samarate (VA) Italy, Via Giovanni Agusta 520, telephone 39 (0331) 229111, fax 39 (0331) 229605-222595. Copies may be inspected 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. (g) This amendment becomes effective on June 13, 2005. Note: The subject of this AD is addressed in Ente Nazionale per l'aviazione Civile (Italy) AD No. 2004-099, dated March 29, 2004. Issued in Fort Worth, Texas, on April 27, 2005. Carl F. Mittag, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 05-8952 Filed 5-6-05; 8:45 am] BILLING CODE 4910-13-P 16