FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS BIWEEKLY 2005-11 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
2004-26-11 2005-01-04
2005-01-10 2005-01-11
Rolls-Royce Corporation
S 98-15-13
S 74-06-01
Bell Helicopter Textron Canada Raytheon Aircraft Company
The New Piper Aircraft, Inc Pilatus Aircraft Ltd.
Engine: 250-B17, -B17B, -B17C, -B17D, -B17E, 250-C20, -C20B, -C20F, -C20J, -C20S, and -C20W Series Turboprop and Turboshaft Rotorcraft: 222, 222B, 222U, 230, 430 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 PA-23-235, PA-23-250, and PA-E23-250 PC-12 and PC-12/45
Biweekly 2005-02 98-20-38 R1
R
Raytheon Aircraft Company
2005-01-14 2005-01-17 2005-01-18
S 2002-21-16 S 98-03-14 S 93-25-07
Bombardier-Rotax GmbH EXTRA Flugzeugbau GmbH Raytheon Aircraft Company
2005-01-19
S 2004-10-15
GARMIN International Inc
2005-02-01
The Lancair 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 Engine: 912 F, 912 S, and 914 F Series Reciprocating EA–300 and EA–300/S 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 Appliance: GTX 33, GTX 33D, GTX 330, and GTX 330D Mode S Transponders LC40–550FG and LC42–550FG
Biweekly 2005-03 2005-01-04
COR S 98-15-13
Raytheon Aircraft Company
2005-01-18
COR S 93-25-07
Raytheon Aircraft Company
2005-02-11 2005-03-04
COR
Gippsland Aeronautics Pty. Ltd. Pacific Aerospace Corp., Ltd.
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 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 GA8 750XL
Biweekly 2005-04 2005-01-04
COR S 98-15-13
2005-03-07 2005-03-08 2005-03-09
2005-03-10 2005-04-09
Raytheon Aircraft Company
Bell Helicopter Textron Bell Helicopter Textron Canada
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 Rotorcraft: 407 Rotorcraft: AS350B, BA, B1, B2, B3, C, D, D1, and EC130 B4 Rotorcraft: EC 155B, EC155B1, SA-360C, SA-365C, SA-365C1, SA-365C2, SA-365N, SA-365N1, AS-365N2, AS 365 N3, and SA-366G1 Rotorcraft: 222, 222B, 222U, and 230 Rotorcraft: 222, 222B, 222U, 230, and 430
Hartzell Propeller Inc. General Electric Company
Propeller: HC-B3TN-5( )/T10282( ) Engine: CT58-140-1, CT58-140-2, and surplus military T58-GE-5,
Bell Helicopter Textron Canada Eurocopter France Eurocopter France
S 2002-08-54 S 2004-26-11
Biweekly 2005-05 2005-04-08 2005-04-10
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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;
2005-04-16 2005-05-51 2005-05-52 2005-05-53 2005-05-53 R1
E E, S 2005-05-51 E E, R, S 2005-0553
-10, -100, and ''402 turboshaft PC-12 and PC-12/45 402C and 414A 402C and 414A 172R, 172S, 182T, and T182T 172R, 172S, 182T, and T182T
Pilatus Aircraft Ltd. Cessna Aircraft Company Cessna Aircraft Company Cessna Aircraft Company Cessna Aircraft Company
Biweekly 2005-06 2005-05-14 2005-05-15
Eagle Aircraft (Malaysia) Honeywell International Inc.
2005-06-01
Eurocopter France
Eagle 150B Engine: TFE731-2 and -2C series, and TFE731-3, -3A, -3AR, -3B, -3BR, and -3R series turbofan Rotorcraft: EC 155B and EC 155B1
Cessna
402C and 414A
Cessna Fairchild Aircraft, Inc.
172R, 172S, 182T, and T182T SA226-AT, SA226-TC, SA226-T, SA226-T(B), SA227-TT, SA227-TT(300), SA227-AC, SA227-AT, SA227-BC, and SA227CC/DC 208 and 208B
Biweekly 2005-07 2005-05-52 2005-05-53 R1 2005-06-13
FR, S 2005-05-51 and 2000-23-01 R, 2005-05-53 S 99-0602
2005-07-01
Cessna
Biweekly 2005-08 83-08-01 R2
R, S 83-08-01 R1
Hartzell Propeller Inc.
2005-07-01 2005-07-27
COR S 2000-18-04
Cessna Aviointeriors S.p.A.
Propeller: HC-B3TN-2, HC-B3TN-3, HC-B3TN-5, HC-B4TN-3, HC-B4TN-5, HC-B4MN-5, and HC-B5MP-3 turbopropellers 208 and 208B Appliance: Model 312 Seats
Biweekly 2005-09 2005-08-06 2005-08-07 2005-08-12 2005-08-13 2005-08-14 2005-09-51
E
Centrair Pilatus Aircraft Limited Centrair Glaser-Dirks Flugzeugbau GmbH LET a.s. Turbomeca S.A.
Glider: 101, 101A, 101AP, and 101P Sailplane: B4-PC11, B4-PC11A, and B4-PC11AF Glider: 101, 101A, 101AP, and 101P Sailplane: DG-800B
Kelly Aerospace Power Systems Centrair Eurocopter France Agusta S.p.A. Agusta S.p.A.
Appliance: Fuel regulator shutoff valve Glider: 101 Series Rotorcraft: EC120B Rotorcraft: A119 Rotorcraft: A109E
Sailplane: Blanik L-13 AC Engine: Arrius 2F Turboshaft
Biweekly 2005-10 2004-25-16 R1 2005-08-06 2005-09-05 2005-09-06 2005-09-07
R, 2004-25-16 COR
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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 2005-11 2005-09-51 2005-10-12 2005-10-13
FR
Turbomeca S.A. Schweizer Aircraft Corporation Rolls-Royce Corporation
2005-10-14 2005-10-23
S 2004-01-51
2005-10-24
S 2003-14-20
Eurocopter France DG Flugzeubau GmbH and Glaser-Dirks Flugzeubau GmbH AeroSpace Technologies of Australia Pty. Ltd. Turbomeca S.A.
2005-11-01
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Engine: Arrius 2F turboshaft Rotorcraft: 269C, C-1, and D Engine: 250-B17B, -B17C, -B17D, -B17E, -C20, -C20B, -C20F, C20J, -C20S, and -C20W turboprop and turboshaft Rotorcraft: AS355E, F, F1, F2, and N Glider:DG-500MB and DG-800B N22B, N22S and N24A Engine: Arrius 1A turboshaft
BW 2005-11 TURBOMECA AIRWORTHINESS DIRECTIVE ENGINE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-09-51 Turbomeca: Amendment 39-14099. Docket No. FAA-2005-21155; Directorate Identifier 2005-NE-14-AD. Effective Date (a) This airworthiness directive (AD) becomes effective June 3, 2005, to all persons except those persons to whom it was made immediately effective by emergency AD 2005-09-51, issued April 28, 2005, which contained the requirements of this amendment. Affected ADs (b) None. Applicability (c) This AD applies to certain Turbomeca Arrius 2F turboshaft engines listed by serial number (SN) in Table 1 of this AD. These engines are installed on, but not limited to, Eurocopter EC 120B Helicopters.
Engine SN 34416 34417 34418 34419 34420 34421 34422 34423 34424 34425 34426 34427 34428
TABLE 1.—ENGINE AND MODULE SERIAL NUMBERS Module 2 SN Engine SN Module 2 SN Engine SN 01045 34429 01097 34442 01063 34430 01098 34443 01052 34431 01099 34444 01053 34432 01102 34445 01067 34433 01103 34446 01068 34434 01109 34447 01051 34435 01110 34448 01078 34436 01121 34449 01079 34437 01122 34450 01080 34438 01123 Not Installed 01083 34439 01136 34033 01089 34440 01139 34177 01090 34441 01140
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Module 2 SN 01138 01141 01142 01146 01147 01148 01164 01165 01177 01149 00125 00446
2005-09-51 2
Unsafe Condition (d) This AD results from failure of a high pressure turbine (HPT) blade and damage to two other HPT blades in a Turbomeca Arrius 2F turboshaft engine on March 31, 2005. We are issuing this AD to prevent failure of the engine and subsequent loss of power. Compliance (e) You are responsible for having the actions required by this AD performed before further flight, unless the actions have already been done. Replacing the Module 2 (f) Before further flight, on Turbomeca Arrius 2F engines that have a SN listed in Table 1 of this AD, remove the Module 2 and replace the Module with a Module 2 that was overhauled or that has a SN not listed in Table 1 of this AD. Alternative Methods of Compliance (g) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Related Information (h) Direction General De L'Aviation Civile Emergency airworthiness directive No. UF-2005073, dated April 27, 2005, also addresses the subject of this AD. Issued in Burlington, Massachusetts, on May 13, 2005. Robert J. Ganley, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05-9982 Filed 5-18-05; 8:45 am] BILLING CODE 4910-13-P
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BW 2005-11 SCHWEIZER AIRCRAFT CORPORATION AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS
2005-10-12 Schweizer Aircraft Corporation: Amendment 39-14089. Docket No. FAA-200521217; Directorate Identifier 2005-SW-06-AD. Applicability Model 269C, serial number (S/N) 1865 through 1874 with a prefix of S; Model 269C-1, S/N 0169 through 0191; and Model 269D, Configuration A, S/N 0044 through 0050 with an A suffix, helicopters, with a lateral control trim actuator assembly, part number (P/N) 269A7316-13, installed, except for an actuator assembly containing a 30 drilled hole in the lateral trim control housing through the wall of the inner spring tube socket, certificated in any category. Compliance Required as indicated, unless accomplished previously. To prevent separation of the inner spring tube from the lateral trim control housing, the associated loss of trim control, increased local resistance to right cyclic stick movement, and subsequent emergency landing or loss of control of the helicopter, accomplish the following: (a) For Model 269C, S/N 1865 through 1874, with a prefix of S, and Model 269C-1, S/N 0169 through 0191, before further flight, inspect the lateral control trim actuator assembly for a scuffmark, indentation, or outer spring guide tube deformation. Inspect for security of the inner spring tube in the socket of the lateral trim control housing by rotating and pulling on the inner spring tube. Examine the resin bead around the base of the inner spring tube and housing socket. Resin should be translucent dark pink in color to indicate a good bond. Conduct the inspection by following the Procedures in Part I of Schweizer Service Bulletin B-283.1 or C1B-017.1, both dated March 4, 2005, respectively, as applicable. (1) If a scuffmark, indentation, or deformation exists on the outer spring tube, or the inner spring tube is loose or has motion, or the bonding is separated, before further flight, remove the lateral control trim actuator assembly; modify the trim control housing and the inner spring tube; and test run the actuator assembly. Modify and test run the actuator assembly by following the Procedures in Part II of Schweizer Service Bulletin B-283.1 or C1B-017.1, both dated March 4, 2005, as applicable. (2) If no scuffmark, indentation, or deformation exists on the outer spring tube, or the inner spring tube is not loose, or the bonding is not separated, within the next 25 hours time-in-service (TIS), modify the lateral control trim actuator assembly as required by paragraph (a)(1) of this AD. (b) For Model 269D, Configuration A, S/N 0044 through 0050 with a suffix of A, within the next 50 hours TIS, modify the lateral control trim actuator assembly by following the Procedures in Schweizer Service Bulletin DB-012, paragraphs a through i, dated February 8, 2005.
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2005-10-12 2
(c) 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 New York Aircraft Certification Office, FAA, for information about previously approved alternative methods of compliance. (d) Inspect, modify, and test the affected lateral control trim actuator assembly by following Schweizer Service Bulletin DB-012, dated February 8, 2005, or B-283.1, or C1B-017.1, both dated March 4, 2005, as applicable. 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 Schweizer Aircraft Corporation, 1250 Schweizer Road, Horseheads, New York 14845. 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 2, 2005. Issued in Fort Worth, Texas, on May 6, 2005. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 05-9764 Filed 5-17-05; 8:45 am] BILLING CODE 4910-13-P
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BW 2005-11 ROLLS-ROYCE CORPORATION AIRWORTHINESS DIRECTIVE ENGINE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS
2005-10-13 Rolls-Royce Corporation (formerly Allison Engine Company): Amendment 3914090. Docket No. FAA-2004-19648; Directorate Identifier. 2004-NE-31-AD. Effective Date (a) This airworthiness directive (AD) becomes effective June 22, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Rolls-Royce Corporation (RRC) (formerly Allison Engine Company) 250-B17B, B17C, -B17D, -B17E, -C20, -C20B, -C20F, -C20J, -C20S, and -C20W turboprop and turboshaft engines that do not have turbine energy absorbing ring, RRC part number (P/N) 23035175, or an equivalent FAA-approved serviceable turbine energy absorbing ring, installed. These engines are installed on, but not limited to, the following aircraft: Agusta A109 Agusta A109A Agusta A109A II B-N Group BN-2T Bell 206A Bell 206B Bell 206L Bell Helicopter Textron 47G-2A (Supplemental Type Certificate (STC) SH657NW) Bell Helicopter Textron 47G-2A-1 (STC SH657NW) Bell Helicopter Textron 47G-3B (STC SH657NW) Bell Helicopter Textron 47G-3B-1 (TH-13T) (STC SH657NW) Bell Helicopter Textron 47G-3B-2 (STC SH657NW) Bell Helicopter Textron 47G-3B-2A (STC SH657NW) Bell Helicopter Textron 47G-4 (STC SH657NW) Bell Helicopter Textron 47G-4A (STC SH657NW) Bell Helicopter Textron 47G-5 (STC SH657NW) Bell Helicopter Textron 47G-5A (STC SH657NW) Eurocopter Deutchland BO-105C Eurocopter Deutchland BO-105C (STC SH218NW-D) Eurocopter Deutchland BO-105S
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2005-10-13 2
Eurocopter France AS355E Eurocopter France AS355F Eurocopter France AS355F1 Eurocopter France AS355F2 FH-1100 Manufacturing Corp FH-1100 Hiller Aviation UH-12D (Army UH-23D) (STC SH177WE) MDHI 369D MDHI 369E MDHI 369HM MDHI 369HS MDHI 369HE Rogerson Hiller Corporation UH-12E (STC SH178WE) Rogerson Hiller Corporation UH-12E-L (STC SH178WE) SIAI Marchetti s.r.l. SF600 Unsafe Condition (d) This AD results from an unacceptable rate of uncontained 1st stage turbine wheel failures. We are issuing this AD to minimize the risk of uncontained 1st stage turbine wheel fragments from causing damage to the aircraft or damage to the second engine on twin-engine installations, which could lead to loss of control and loss of the aircraft. Compliance (e) You are responsible for having the actions required by this AD performed at the next time the gas producer turbine rotor is disassembled for any reason, or within 1,750 hours time-since-lastoverhaul, time-since-new, time-since-last-heavy-maintenance, or time-since-last-hot section inspection after the effective date of this AD, whichever occurs first, but no later than October 31, 2011, unless already done. Required Actions (f) Install a turbine energy absorbing ring, RRC P/N 23035175, or an equivalent FAAapproved turbine energy absorbing ring, in the plane of the 1st stage turbine wheel, using paragraphs 1.M., 2.A., and 2.B. of Rolls-Royce Corporation Alert Commercial Engine Bulletin No. CEB-A1255, Revision 4, dated September 29, 2004, to do the installation. Alternative Methods of Compliance (g) The Manager, Chicago Aircraft Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Related Information (h) None.
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2005-10-13 3
Material Incorporated by Reference (i) You must use Rolls-Royce Corporation Alert Commercial Engine Bulletin No. CEB-A1255, Revision 4, dated September 29, 2004, to perform the actions required by this AD. 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. Contact Rolls-Royce Corporation, P.O. Box 420, Indianapolis, IN 46206-0420; telephone (317) 230-2712; fax (317) 230-3381 for the service information identified in this AD for a copy of this service information. You may review copies at the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-001, on the internet at http://dms.dot.gov, or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Issued in Burlington, Massachusetts, on May 10, 2005. Robert Ganley, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05-9660 Filed 5-17-05; 8:45 am] BILLING CODE 4910-13-P
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BW 2005-11 EUROCOPTER FRANCE AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS
2005-10-14 Eurocopter France: Amendment 39-14091 . Docket No. FAA-2005-20293; Directorate Identifier 2004-SW-34-AD. Supersedes AD 2004-01-51, Amendment 39-13495, Docket No. 2003SW-56-AD. Applicability Model AS355E, F, F1, F2, and N helicopters with a pre-MOD 077212 combiner gearbox that has 10 or less hours time-in-service installed, certificated in any category. Compliance Before further flight, unless accomplished previously. To prevent an engine overspeed, an engine shutdown, and subsequent loss of control of the helicopter, accomplish the following: (a) Before further flight, replace each pre-MOD 077212 combiner gearbox with a combiner gearbox modified by replacing the freewheel rollers in accordance with MOD 077212. Note 1: Eurocopter France Alert Telex No. 63.00.21 R2, dated February 4, 2004, pertains to the subject AD. (b) Performing paragraph (a) of this AD is terminating action for the requirements of this AD. (c) 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, FAA, for information about previously approved alternative methods of compliance. (d) Special flight permits will not be issued. (e) This amendment becomes effective on June 21, 2005. Note 2: The subject of this AD is addressed in Direction Generale de L'Aviation Civile, France, AD No. F-2004-021, dated March 3, 2004. Issued in Fort Worth, Texas, on May 9, 2005. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 05-9766 Filed 5-16-05; 8:45 am] BILLING CODE 4910-13-P
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BW 2005-11 DG FLUGZEUGBAU GMBH AND GLASER-DIRKS FLUGZEUGBAU GMBH AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS
2005-10-23 DG Flugzeugbau GmbH and Glaser-Dirks Flugzeugbau GmbH: Amendment 3914101; Docket No. FAA-2004-19959; Directorate Identifier 2004-CE-46-AD. When Does This AD Become Effective? (a) This AD becomes effective on June 30, 2005. What Other ADs Are Affected By This Action? (b) None. What Sailplanes Are Affected By This AD? (c) This AD affects all Model DG-500MB and DG-800B sailplanes that are: (1) Certificated in any category; and (2) Equipped with a Solo engine. 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 Germany. The actions specified in this AD are intended to detect and correct damage to the propeller, which could result in failure of the propeller to perform properly. This failure could lead to reduced or loss of control of the sailplane. What Must I Do To Address This Problem? (e) To address this problem, you must do the following: Actions Compliance (1) Inspect the propeller for any signs of Within 25 hours damage. time-in-service (TIS) after June 30, 2005 (the effective date of this AD).
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Procedures Follow DG Flugzeugbau Technical Note No. 843/19 (LBA approved on April 7, 2004; EASA approved on April 26, 2004); and DG Flugzeugbau Technical Note 873/29 (LBA approved on April 7, 2004; EASA approved April 26, 2004), as applicable.
2005-10-23 2
(2) If any damage is found during the inspection required in paragraph (e)(1) of this AD, replace the propeller.
Before further flight after the inspection required in paragraph (e)(1) approved on this AD. (3) Insert the following language in the Within 25 hours Limitations Section of the AFM:. TIS after June ‘‘Caution: With high temperatures 30, 2005 (the (temperature on ground above 25 °C/77 effective date of °F) there is the risk of overheating the this AD). propeller after engine retraction. To avoid damage, extend the engine again via the manual switch (approx. 1 second) to open the engine doors. Retract again after 5 minutes.’’
Follow DG Flugzeugbau Technical Note No. 843/19 (LBA approved on April 7, 2004; EASA approved on April 26, 2004); and DG Flugzeugbau Technical Note 873/29 (LBA approved on April 7, 2004; EASA approved April 26, 2004), as applicable. 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 flight manual changes requirement of this AD. Make an entry in the aircraft records showing compliance with this portion of the AD following section 43.9 of the Federal Aviation Regulations (14 CFR 43.9).
Note: For Model DG-500MB sailplanes, FAA recommends you install a polyurethane shock absorber at the retaining cable mounting in the fuselage. This is specified in DG Flugzeugbau Technical Note No. 843/19 (LBA approved on April 7, 2004; EASA approved on April 26, 2004). The approximate cost to install the shock absorber is $520 (4 work hours x $65 per hour for labor = $260 + $260 for parts). Starting with serial number 5E243B20 and on, this shock absorber is being installed at production. 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. 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, Standards Office, Small Airplane Directorate, FAA. For information on any already approved alternative methods of compliance, contact Gregory Davison, Aerospace Engineer, FAA, Small Airplane Directorate, ACE-112, Room 301, 901 Locust, Kansas City, Missouri 64106; telephone: 816-329-4130; facsimile: 816-329-4090. Is There Other Information That Relates to This Subject? (g) German AD Number D-2004-195 and AD Number D-2004-196, both dated April 23, 2004, also address the subject of this AD. Does This AD Incorporate Any Material by Reference? (h) You must do the actions required by this AD following the DG Flugzeugbau Technical Note No. 843/19 (LBA approved on April 7, 2004; EASA approved on April 26, 2004); and DG Flugzeugbau Technical Note 873/29 (LBA approved on April 7, 2004; EASA approved April 26, 2004). The Director of the Federal Register approved the incorporation by reference of these service bulletins in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service
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2005-10-23 3
information, contact DG Flugzeugbau, Postbox 41 20, 76625 Bruchsal, Germany; telephone, 49 7257 890; fax, 49 7257 8922. 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 20590001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2004-19959; Directorate Identifier 2004-CE-46-AD. Issued in Kansas City, Missouri, on May 13, 2005. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-9975 Filed 5-20-05; 8:45 am] BILLING CODE 4910-13-P
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BW 2005-11 AEROSPACE TECHNOLOGIES OF AUSTRALIA PTY LTD AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-10-24 Aerospace Technologies of Australia Pty Ltd.: Amendment 39-14102; Docket No. FAA-2005-20439; Directorate Identifier 2005-CE-04-AD; Supersedes AD 2003-14-20, Amendment 39-13239. When Does This AD Become Effective? (a) This AD becomes effective on June 30, 2005. What Other ADs Are Affected By This Action? (b) This AD supersedes AD 2003-14-20, Amendment 39-13239. What Airplanes Are Affected By This AD? (c) This AD affects Models N22B, N22S, and N24A airplanes, all serial numbers, that are certificated in any category. What Is The Unsafe Condition Presented in This AD? (d) This AD is the result of continuing airworthiness information (MCAI) issued by the airworthiness authority for Australia. The actions specified in this AD are intended to detect and correct cracks in the rudder control lever torque shafts and discrepancies in the thickness of the lever shaft side plates, which could result in failure of the rudder control lever torque shaft. Such failure could lead to reduced controllability of the airplane. What Must I Do To Address This Problem? (e) To address this problem, you must do the following:
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Actions (1) Inspect the following: (i) The rudder control level shafts, part numbers (P/N) 1/N–45–1102, 2/N–45–1102, 1/N–45–1103, and 1/N–45–1104 (or FAA-approved equivalent part numbers) for cracks. Use dye penetrant inspection while the shaft is installed. Use either dye penetrant or magnetic particle inspection if the shaft is removed; and (ii) All lever shaft side plates on P/Ns 1/N–45–1102, 2/N–45–1102, 1/N–45–1103, and 1/N–45–1104 (or FAA-approved equivalent part numbers) by measuring the thickness for discrepancies. (2) If no cracks are found in the rudder control lever shafts during the inspection required in paragraph (e)(1)(i) of this AD, repetitively inspect rudder control lever shafts P/Ns 1/N–45–1102, 2/N–45– 1102, 1/N–45–1103, ands 1/N–45–1104 (or FAAapproved equivalent part numbers) for cracks.
Compliance Initially inspect within the next 50 hours time-inservice (TIS) or 30 days after June 30, 2005 (the effective date of this AD), whichever occurs first, unless already done.
Procedures Following Nomad Alert Service Bulletin ANMD– 27–51, Rev. 2, dated April 29, 2004, and the applicable maintenance manual.
Repetitively inspect thereafter at intervals not to exceed 300 hours TIS after the initial inspection required in paragraph (e)(1) of this AD. (3) If cracks or discrepancies are found during any Before further inspection required by this AD, do the following: flight after any (i) For rudder control lever shafts found with crack inspection required damage, replace with new or serviceable parts. by this AD in After replacement, continue with the repetitive which cracks or inspections required in paragraph (e)(2) of this AD. discrepancies are (ii) If the thickness of the lever shaft side plates is less found. than 0.050 inches, replace the lever shaft side plate with a new plate that measures at least 0.050 inches in thickness. (4) If at any time certain operating conditions occur Before further that caused abnormal rudder pedal loads, inspect flight. the rudder control lever shafts as specified in paragraph (e)(2) of this AD. Examples of such conditions are: heavy use of nosewheel steering over rough ground; excessive steering angle under towl; towing with rudder gust lock fitted; engine failure on takeoff; and aircraft left parked outside with rudder gust lock not fitted.
Following Nomad— Series N22 & N24 Inspection Requirements Manual, Temporary Revision 26, Fatigue Critical Areas, dated May 27, 2004.
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Following Nomad Alert Service Bulletin ANMD– 27–51, Rev. 2, dated April 29, 2004, and the applicable maintenance manual.
Following Nomad— Series N22 & N24 Inspection Requirements Manual, Temporary Revision 26, Fatigue Critical Areas, dated May 27, 2004.
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(5) Do not install a new lever shaft side plate that is less than 0.050 inches in thickness.
As of June 30, As specified in Nomad 2005 (the effective Alert Service Bulletin date of this AD). ANMD–27–51, Rev. 2, dated April 29, 2004; and Nomad—Series N22 & N24 Inspection Requirements Manual, Temporary Revision 26, Fatigue Critical Areas, dated May 27, 2004.
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, Standards Office, Small Airplane Directorate, FAA. For information on any already approved alternative methods of compliance, contact Doug Rudolph, Aerospace Engineer, Small Airplane Directorate, ACE-112, 901 Locust, Rm 301, Kansas City, Missouri, 64106; telephone: (816) 329-4059; facsimile: (816) 3294090. (2) Alternative methods of compliance approved for AD 2003-14-20 are not considered approved as alternative methods of compliance for this AD. Is There Other Information That Relates to This Subject? (g) Australian AD GAF-N22/44, Amendment 2, dated November 2004, also addresses the subject of this AD. Does This AD Incorporate Any Material By Reference? (h) You must do the actions required by this AD following the instructions in Nomad–Series N22 & N24 Inspection Requirements Manual, Temporary Revision 26, Fatigue Critical Areas, dated May 27, 2004, and Nomad Alert Service Bulletin ANMD-27-51, Rev. 2, dated April 29, 2004, which incorporates the following pages: Pages Revision level 1 and 3 2 2 2 1 4 1 Original issue.
Date April 29, 2004. Jan. 29, 2004. Sept. 13, 2002.
(1) The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) To get a copy of this service information, contact Nomad Operations, Aerospace Support Division, Boeing Australia, PO Box 767, Brisbane, QLD 4001 Australia; telephone 61 7 3306 3366; facsimile 61 7 3306 3111. 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. 19
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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 FAA2005-20439; Directorate Identifier 2005-CE-04-AD. Issued in Kansas City, Missouri, on May 13, 2005. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-9976 Filed 5-20-05; 8:45 am] BILLING CODE 4910-13-P
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BW 2005-11 TURBOMECA S.A. AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-11-01 Turbomeca S.A.: Amendment 39-14103. Docket No. FAA-2005-21273; Directorate Identifier 2005-NE-15-AD. Effective Date (a) This airworthiness directive (AD) becomes effective June 13, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Turbomeca S.A. Arrius 1A turboshaft engines. These engines are installed on, but not limited to, Eurocopter AS355N Twinstar helicopters. Unsafe Condition (d) This AD results from an investigation into the Digital Electronic Control Unit (DECU) that revealed a malfunction of the Free Turbine Overspeed Protection System can exist despite the DECU passing all functional tests specified in the Engine Maintenance Manual. We are issuing this AD to prevent uncontained engine failure in the event of a free turbine overspeed. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. Initial Testing (f) Within 25 flight hours after the effective date of this AD, test the DECU Free Turbine Overspeed Protection System, using paragraph 2.B. of the Instructions to be Incorporated of Turbomeca Alert Mandatory Service Bulletin No. A319 77 0804, dated March 24, 2005. (g) If the DECU Free Turbine Overspeed Protection System fails the test specified in paragraph (f) of this AD, replace the DECU before further flight.
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Repetitive Testing (h) Repeat the testing specified in paragraph (f) of this AD at each functional test of the DECU Free Turbine Overspeed Protection System. Information on the functional tests of the DECU Free Turbine Overspeed Protection System can be found in the Engine Maintenance Manual, Section 77-30-01. Recommended intervals for the functional test of the Turbine Overspeed Protection System can be found in the Engine Maintenance Manual, Section 05-10-02. Alternative Methods of Compliance (i) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Related Information (j) DGAC airworthiness directive F-2005-063, dated April 27, 2005, and UF-2005, 063 R1, dated May 4, 2005, also address the subject of this AD. Material Incorporated by Reference (k) You must use Turbomeca Alert Mandatory Service Bulletin No. A319 77 0804, dated March 24, 2005, to perform the tests required by this AD. 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. Contact Turbomeca S.A., 40220 Tarnos, France; telephone 33 05 59 74 40 00, fax 33 05 59 74 45 15, for a copy of this service information. You may review copies at the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-001, on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Issued in Burlington, Massachusetts, on May 17, 2005. Robert E. Guyotte, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05-10295 Filed 5-26-05; 8:45 am] BILLING CODE 4910-13-P
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