FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS BIWEEKLY 2006-22 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 2006-01 2005-26-10 2005-26-11 2005-26-12
S 2004-08-13
2005-26-13 2005-26-14
S 2002-22-11
2005-26-53
E
Engine Components Inc. DG Flugzeugbau GmbH Burkhardt Grob Luft-Und Raumfahrt Gmbh & Co Kg Turbomeca Burkhardt Grob Luft-Und Raumfahrt Gmbh & Co Kg Pacific Aerospace Corporation
Appliance: Engine Cylinder Assemblies Sailplane: DG-800B and DG-500MB Sailplane: G103 Twin Astir, G103 Twin II, G103A Twin 11 Acro, G103C Twin III Acro, and G 103 Twin III SL Engine: Artouste III B, B1, and D turboshaft Sailplane: G103 Twin Astir
Turbomeca S.A. American Champion Aircraft Corp.
Engine: Arrius Models 2B, 2B1, and 2F 7ECA, 7GCAA, 7GCBC, 8KCAB, and 8GCBC, 7AC, 7ACA, S7AC, 7BCM, 7CCM, S7CCM, 7DC, S7DC, 7EC, S7EC, 7ECA, 7FC, 7GC, 7GCA, 7GCAA, 7GCB, 7GCBA, 7GCBC, 7HC, 7JC, 7KC, 7KCAB, 8KCAB, and 8GCBC 750XL
750XL
Biweekly 2006-02 2001-08-14R1 2005-24-10
R 2001-08-14
2005-26-53 2006-01-05
S 87-12-05
Pacific Aerospace Corporation Ltd. Honeywell International Inc.
2006-01-11 2006-02-51
E
Cessna Raytheon
Engine: T5309, T5311, T5313B, T5317A, T5317A-1, and T5317B series turboshaft, T53-L-9, T53-L-11, T53-L-13B, T53-L-13BA, T53-L-13B S/SA, T53-L-13B S/SB, T53-L-13B/D, and T53-L-703 series turboshaft 208 and 208B 390
Biweekly 2006-03 2006-02-08 2006-02-12
2006-02-51
FR
Turbomeca DG Flugzeugbau GmbH and Glaser-Dirks Flugzeugbau GmbH Raytheon
Engine: Arriel 1B, 1D, 1D1, and 1S1 Sailplane: DG–100, DG–400, DG–500 Elan Series, and DG–500M
Glaser-Dirks Flugzeugbau GmbH Aero Advantage Polskie Zaklady Lotnicze
Sailplane: DG-100, DC-400, DG-500 Elan, and DG-500M
Turbomeca
Engine: Turbomeca Artouste III B, Artouste III B1, and Artouste III D turboshaft
Cessna MT-Propeller Entwicklung GmbH
208 and 208B Propeller: MT, MTV-1, MTV-2, MTV-3, MTV-5, MTV-6, MTV7, MTV-9, MTV-10, MTV-11, MTV-12, MTV-14, MTV-15, MTV-17, MTV-18, MTV-20, MTV-21, MTV-22, MTV-24, and MTV-25 Rotorcraft: EC 155B and B1 Rotorcraft: SA-365N, SA365N1, AS-365N2, and SA-366G1 208 and 208B Engine: CT7-8A
390
Biweekly 2006-04 2006-02-12
COR
2006-03-08 2006-03-17
Appliance: Vacuum Pumps PZL M26 01
Biweekly 2006-05 2006-04-15
Biweekly 2006-06 2006-01-11 R1 2006-05-05
2006-06-01 2006-06-02 2006-06-06 2006-06-51
R 2006-01-11
S 2005-07-01 E
Eurocopter France Eurocopter France Cessna General Electric
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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 2006-07 2005-13-09 2006-06-16
COR
2006-06-17 2006-07-06
GROB-WERKE Lycoming Engines
Turbomeca Cirrus Design Corporation
G120A Engine: AEIO–360–A1B6, AEIO–360–A1E6, IO–360–A1B6, IO– 360–A1B6D, IO–360–A3B6, IO–360–A3B6D, IO–360–C1C6, IO–360–B1G6, IO–360–C1G6, IO–360–C1E6, LO–360–A1G6D, LO–360–A1H6, O–360–A1F6, O–360–A1F6D, O–360–A1G6D, O–360–A1H6, O–360–E1A6D, O–360–F1A6, IO–360–C1D6, LIO–360–C1E6, LO–360–E1A6d, LIO–360–C1D6 Engine: Arriel 1B, 1D, and 1D1 certain turboshaft SR20, SR22
Cessna
208 and 208B
Thrush Aircraft Inc.
S–2R, S2R–G1, S2R–R1820, S2R–T15, S2R–T34, S2R–G10, S2R–G5, S2R–G6, S2RHG–T65, S2R–R1820, S2R–T34, S2R– T45, S2R–T65, 600 S2D, S–2R, S2R–R1340, S2R–R3S, S2R– T11, S2R–G1, S2R–G10, S2R–T34, S2R–G1, S2R–G10, S2R–G6, S2RHG–T34, S2R–T15, S2R–T34, S2R–T45, S–2R Engine: Makila 1 A2 turboshaft Sailplane:G 103 C Twin III SL
Biweekly 2006-08 2006-06-06 2006-07-15
COR S 2005-07-01 S 2003-07-01
2006-07-20 2006-08-01
S 97-24-09
2006-08-06
Turbomeca BURKHART GROB LUFTUND RAUMFAHRT GMBH & CO. KG Eurocopter France
Rotorcraft: SA-360C, SA-365C, SA-365C1, and SA-365C2
Biweekly 2006-09 2002-11-05-R1 2006-06-51 2006-07-15
2006-08-07 2006-08-08 2006-08-09 2006-08-11 2006-08-12 2006-08-13
R 2002-11-05 FR COR S 2003-07-01
S 2001-24-51
Air Tractor General Electric Thrush Aircraft Inc.
Brantly Helicopter Air Tractor Air Tractor Pilatus MD Helicopters Pratt & Whitney Canada
AT-501 Engine: CT7-8A S–2R, S2R–G1, S2R–R1820, S2R–T15, S2R–T34, S2R–G10, S2R–G5, S2R–G6, S2RHG–T65, S2R–R1820, S2R–T34, S2R– T45, S2R–T65, 600 S2D, S–2R, S2R–R1340, S2R–R3S, S2R– T11, S2R–G1, S2R–G10, S2R–T34, S2R–G1, S2R–G10, S2R–G6, S2RHG–T34, S2R–T15, S2R–T34, S2R–T45, S–2R Rotorcraft: B-2, B-2A, and B-2B AT-400, AT-401, AT-401B, AT-402, AT-402A, and AT-402B AT-802A PC-12 and PC-12/45 Rotorcraft: 600N Engine: PW535A
Air Tractor
AT-501
Air Tractor Air Tractor Eurocopter France
AT-400, AT-401, AT-401B, AT-402, AT-402A, and AT-402B AT-802 and AT-802A Rotorcraft: SA-365 N1, AS-365 N2, N3, SA 366 G1, and EC-155B and B1
Cessna
208 and 208B
Cessna
208 and 208B
Engine Components Inc.
Appliance: Engine Connecting Rods
Biweekly 2006-10 2002-11-05-R1 2006-08-08 2006-08-09 2006-09-10
COR R 2002-11-05 COR COR
Biweekly 2006-11 2006-01-11 R1 2006-06-06 2006-10-21
COR R 2006-01-11 COR S 2005-07-01
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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 2006-12 2003-21-09 R1 2006-11-14 2006-11-16
R 2003-21-09 S 98-22-11
Eurocopter France Sikorsky Honeywell International Inc.
S 2005-26-10
Eurocopter France Pacific Aerospace Corporation Ltd. DORNIER LUFTFAHRT GmbH Engine Components Inc.
2006-11-17 2006-11-18 2006-11-19 2006-12-07
Rotorcraft: AS355E, F, F1, F2, and N Rotorcraft: S-92A Engine: T5311A, T5311B, T5313B, T5317A, T5317A-1, and T5317B series, T53-L-11B, T53-L-11D, T53-L-13B, T53-L13B/D, and T53-L-703 series turboshaft Rotorcraft: AS350B, BA, B1, B2, B3, C, D, and D1 750XL 228-100, 228-101, 228-200, 228-201, 228-202, and 228-212 Appliance: Engine Cylinder Assemblies
Biweekly 2006-13 68-17-03R1
2006-10-19 2006-10-21 2006-12-25 2006-13-05 2006-13-06
R 68-17-03
COR S 2005-26-53
Pilatus Aircraft Ltd.
Eurocopter France Engine Components Inc. General Machine - Diecron, Inc. Pacific Aerospace Corp. Ltd. Rolls-Royce Corp.
2006-13-11
S 2002-21-08
Pilatus Aircraft Ltd.
2006-13-12
S 98-12-01
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, PC6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 Rotocraft: EC130 B4 Appliance: Engine Connecting Rods Appliance: Actuator Nut Assembly 750XL Engine: 250-B17, -B17B, -B17C, -B17D, -B17E, -B17F, -B17F/1, -B17F/2, 250-C18, -C20, -C20B, -C20F, -C20J, -C20R, -C20R/1, C20R/2, -C20R/4, -C20S, and ''C20W series turboprop and turboshaft 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, PC6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 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, PC6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2
Biweekly 2006-14 2006-13-10 2006-13-14 2006-13-15
2006-14-03
S 92-07-05
Raytheon Aircraft Company Bell Helicopter Textron Mitsubishi Heavy Industries
Honeywell International Inc.
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See AD Rotorcraft: 222, 222B, 222U, 230 and 430 MU-2B-10, MU-2B-15, MU-2B-20, MU-2B-25, MU-2B-26, MU2B-26A, MU-2B-30, MU-2B-35, MU-2B-36, MU-2B-36A, MU2B-40, MU-2B-60 Engine: TPE331-1, -1U, -1UA, -2, -2UA, -3U, -3UW, -3W, -5, 5A, -5AB, -5B, -5U, -6, -6A, -6U, -8, -8A, -9, -9U, -10, -10A, 10AV, -10B, -10G, -10GP, -10GR, -10GT, -10J, -10N, -10P, -10R, -10T, -10U, -10UA, -10UF, -10UG, -10UGR, -10UJ, -10UK, 10UR, -11U, -11UA, -12, -12B, -12JR, -12UA, -12UAR, -12UER, and -12UHR series turboprop and TSE331-3U model turboshaft
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 2006-15 2006-14-08 2006-15-01 2006-15-02
S 2003-09-01
Mitsubishi Heavy Industries Twin Commander Aircraft Corporation Pilatus Aircraft Ltd.
2006-15-03
S 2003-13-04
Pilatus Aircraft Ltd.
2006-15-07
Mitsubishi Heavy Industries, LTD.
2006-15-08
Honeywell International Inc.
MU–2B–26A, MU–2B–36A, MU–2B–40, and MU–2B–60 690, 690A, and 690B 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, PC6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 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, PC6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 MU–2B, MU–2B–10, MU–2B–15, MU–2B–20, MU–2B–25, MU–2B–26, MU–2B–26A, MU–2B–30, MU–2B–35, MU–2B–36, MU–2B–36A, MU–2B–40, and MU–2B–60 Engine: TPE331-1, -2, -2UA, -3U, -3UW, -5, -5A, -5AB, -5B, -6, 6A, -10, -10AV, -10GP, -10GT, -10P, -10R, -10T, -10U, -10UA, 10UF, -10UG, -10UGR, -10UR, -11U, -12JR, -12UA, -12UAR, and -12UHR turboprop
Biweekly 2006-16 2004-16-15 R1 2006-15-14 2006-15-19 2006-16-04
R 2004-16-15
Eurocopter France
S 2004-24-04
Eurocopter Canada Limited Sikorsky Aircraft Corporation Rolls-Royce Corporation
Rotorcraft: AS-365N2, AS 365 N3, EC 155B, EC155B1, SA365N, N1, and SA-366G1 Rotorcraft: BO 105 LS A-3 Rotorcraft: S-92A Engine: 250-B and 250-C series turboshaft and turboprop
Biweekly 2006-17 2006-02-08R1 2006-16-13 2006-16-19 2006-16-20 2006-17-01
R 2006-02-08
Turbomeca Pilatus Aircraft Ltd. B-N Group Ltd. DG Flugzeugbau GmbH Mitsubishi Heavy Industries
2006-17-02 2006-17-03 2006-17-04 2006-17-05
S 84-09-05
Grob-Werke Stemme GmbH & Co. KG Cessna Mitsubishi Heavy Industries
2006-17-51
E
Agusta S.p.A.
Engine: Arriel 1B, 1D, 1D1, and 1S1 PC-12 and PC-12/45 BN-2, BN-2A, BN-2B, BN-2T, and BN-2T-4R series Sailplane: DG-1000S MU-2B, MU-2B-10, MU-2B-15, MU-2B-20, MU-2B-25, MU-2B-26, MU-2B-26A, MU-2B-30, MU-2B-35, MU-2B-36, MU-2B-36A, MU-2B-40, and MU-2B-60 Sailplane: G102 ASTIR CS Sailplane: S10, S10-V, and S10-VT 172R, 172S, 182T, T182T, 206H, and T206H MU-2B, MU-2B-10, MU-2B-15, MU-2B-20, MU-2B-25, MU-2B-26, MU-2B-26A, MU-2B-30, MU-2B-35, MU-2B-36, MU-2B-36A, MU-2B-40, and MU-2B-60 Rotorcraft: AB139
Biweekly 2006-18 2006-16-13 2006-16-18
COR
Pilatus Aircraft Ltd Sandel Avionics Incorporated
2006-17-51 2006-18-01 2006-18-51
FR S 2004-23-15 E
Agusta S.p.A. MD Helicopters, Inc. Raytheon
PC-12 and PC-12/45 Appliance: Terrain awareness warning system/radio magnetic indicator (TAWS/RMI) units Rotorcraft: AB139 Rotorcraft: MD900 1900, 1900C, and 1900D
Biweekly 2006-19 2006-18-15 2006-18-16 2006-18-51 2006-19-01 2006-19-05
FR
Hartzell Propeller Inc. Raytheon Raytheon Eurocopter France See AD
Propeller: ( )HC-( )2Y( )-( ) series 390 1900, 1900C (C-12J), 1900D Rotorcraft: AS350B, B1, B2, B3, BA, D, and AS355E Rotorcraft: HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH1F, UH-1H, UH-1L, UH-1P, and SW204, SW204HP, SW205, and SW205A-1
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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 2006-20 2006-19-08 2006-19-09 2006-19-10 2006-19-11 2006-20-07
2006-20-09
Lycoming Engines
2006-20-10
Air Tractor, Inc.
Sailplane: S10-VT B300 SR20 and SR22 GA8 Engine: 250-C30, -C30G, -C30G/2, -C30M, -C30P, -C30R, C30R/1, -C30R/3, -C30R/3M, -C30S, -C30U, -C40B, -C47B, and -C47M turboshaft Engine: (L)O-360, (L)IO-360, AEIO-360, O-540, IO-540, AEIO540, (L)TIO-540, IO-580, and IO-720 series reciprocating AT-802 and AT-802A
Fuji Heavy Industries, Ltd. Cirrus Design Corporation
FA-200 series SR20, SR22
Turbomeca Turbomeca AeroSpace Technologies of Australia Pty Ltd Various Aircraft Air Tractor, Inc. Schempp-Hirth Gmbh & Co. KG EADS SOCATA Hartzell Propeller Inc
Engine: Arriel 2B, 2B1, and 2B1A turboshaft Engine: Turmo IV A and IV C series turboshaft N22B, N22S, and N24A
S 2005-17-19
Stemme GmbH & Co. KG Raytheon Cirrus Design Corporation Gippsland Aeronautics Pty. Ltd. Rolls-Royce
Biweekly 2006-21 2006-20-13 2006-21-03
Biweekly 2006-22 2006-21-10 2006-21-11 2006-21-12 2006-22-05 2006-22-08 2006-22-10 2006-22-11 2006-22-12
S 2003-22-13 S 2003-04-06
S 2004-21-01
7
SEE AD AT-602, AT-802, and AT-802A Sailplane: Mini-Nimbus B and Mini-Nimbus HS-7 TBM 700 Propeller: HC-B5MP-3( )/M10282A( )+6 and HC-B5MP-3( )/M10876( )( )( )( ) five-bladed
AIRWORTHINESS DIRECTIVE
U.S. Department of Transportation
www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html
Federal Aviation Administration
2006-21-10 Turbomeca: Amendment 39-14795. Docket No. FAA-2005-23809; Directorate Identifier 2005-NE-52-AD. Effective Date (a) This airworthiness directive (AD) becomes effective November 24, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Turbomeca Arriel 2B, 2B1, and 2B1A turboshaft engines. These engines are installed on, but not limited to, Eurocopter AS350B3 and EC130B4 helicopters. Unsafe Condition (d) This AD results from reports of uncommanded in-flight shutdowns of engines. We are issuing this AD to detect wear on the splines of the high-pressure (HP) pump drive gear shaft and the coupling shaft assembly, which could interrupt the fuel flow and cause an uncommanded in-flight shutdown of the engine on a single-engine helicopter. The in-flight shutdown of the engine could result in a forced autorotation landing or accident. 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 Visual Inspection (f) Perform an initial visual inspection of the splines of the coupling assembly and the HP pump drive gear shaft for wear. Use 2.A. through 2.C.(2) of the Instructions to be Incorporated of Turbomeca Mandatory Service Bulletin (MSB) No. 292 73 2812, Update No. 2, dated June 28, 2005, as follows: (1) For hydraulic mechanical units (HMUs) that have accumulated 450 or more hours timesince-new (TSN) or time-since-overhaul (TSO) on the effective date of this AD, inspect within 50 hours after the effective date of this AD. Replace the HMU if worn beyond limits. (2) For HMUs that have fewer than 450 hours TSN or TSO on the effective date of this AD, inspect after accumulating 450 hours TSN or TSO, but before accumulating 500 hours TSN or TSO. Replace the HMU if worn beyond limits.
8
BW 2006-22
2006-21-10 2
Repetitive Visual Inspections (g) Thereafter, perform a visual inspection of the splines of the coupling shaft assembly and the HP pump drive gear shaft for wear every time you remove or install the HMU. Use 2.A. through 2.C.(2) of the Instructions to be Incorporated of Turbomeca MSB No. 292 73 2812, Update No. 2, dated June 28, 2005. Replace the HMU and coupling shaft assembly if worn beyond limits. Alternative Methods of Compliance (h) 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 (i) DGAC airworthiness directive F-2005-188, dated November 23, 2005, also addresses the subject of this AD. Material Incorporated by Reference (j) You must use Turbomeca Mandatory Service Bulletin No. 292 73 2812, Update No. 2, dated June 28, 2005, to perform the visual inspections 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, 40220 Tarnos–France; Tel (33) 05 59 74 40 00; Telex 570 042; Fax (33) 05 59 74 45 15, for a copy of this service information. You may review copies at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; 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 Burlington, Massachusetts, on October 12, 2006. Thomas A. Boudreau, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E6-17326 Filed 10-18-06; 8:45 am]
9
BW 2006-22
AIRWORTHINESS DIRECTIVE
U.S. Department of Transportation
www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html
Federal Aviation Administration
2006-21-11 Turbomeca: Amendment 39-14796. Docket No. FAA-2006-25730; Directorate Identifier 2006-NE-31-AD. Effective Date (a) This airworthiness directive (AD) becomes effective November 3, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Turbomeca Turmo IV A and IV C series turboshaft engines with flexible lubrication pipes, part number (P/N) 0 249 92 813 0 or P/N 0 249 92 916 0, installed. These engines are installed on but not limited to, Aerospatiale SA 330–PUMA helicopters. Unsafe Condition (d) This AD results from 7 reports of oil leakage due to the deterioration of certain flexible lubrication pipes, part number (P/N) 0 249 92 813 0. We are issuing this AD to prevent dual-engine failure on a twin-engine helicopter. 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 Actions (f) Before further flight: (1) Identify the curing batch of the flexible lubrication pipes. (2) If the two engines installed on the same helicopter have pipes with a curing batch of ''2T03'' (meaning 2nd quarter of 2003) or subsequent batch, replace one of the pipes with a pipe having a curing batch before batch ''2T03''. (3) On the other engine, or on a helicopter that has only one engine affected by this AD, borescope-inspect the pipe for deterioration, visually inspect for oil leakage, and visually inspect the oil filter for black particle deterioration from the pipe. Replace the pipe if deterioration or leakage is found, with a pipe having a curing batch before batch ''2T03''. Repetitive Actions (g) Within every additional 25 operating hours, on engines still having an affected flexible lubrication pipe, borescope-inspect the pipe for deterioration, visually inspect pipe for oil leakage,
10
BW 2006-22
2006-21-11 2
and visually inspect the oil filter for black particle deterioration from the pipe. Replace the pipe if deterioration or leakage is found, with a pipe having a curing batch before batch ''2T03''. (h) Information on performing the initial and repetitive actions in this AD can be found in Turbomeca Alert Mandatory Service Bulletin No. A249 72 0802, Update No. 1, dated August 3, 2006. 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) European Aviation Safety Agency airworthiness directive No. 2006-0240-E, dated August 11, 2006, also addresses the subject of this AD. Issued in Burlington, Massachusetts, on October 12, 2006. Thomas A. Boudreau, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E6-17328 Filed 10-18-06; 8:45 am]
11
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AIRWORTHINESS DIRECTIVE
U.S. Department of Transportation
www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html
Federal Aviation Administration
2006-21-12 AeroSpace Technologies of Australia Pty Ltd.: Amendment 39-14797; Docket No. FAA-2006-25928; Directorate Identifier 2006-CE-53-AD. Effective Date (a) This AD becomes effective on November 8, 2006. Affected ADs (b) Supersedes AD 2003-22-13, Amendment 39-13361. Applicability (c) This AD affects Models N22B, N22S, and N24A airplanes, all serial numbers including airplanes with float/amphibian configuration, that are certificated in any category. Unsafe Condition (d) This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Australia. We are issuing this AD to prevent failure of the aileron due to undetected pre-existing aileron damage and airplane operation outside of the approved limits. Aileron failure could lead to reduced or loss of control of the airplane. Compliance (e) To address this problem, you must do the following:
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Actions
Compliance
Procedures
(1) Visually inspect the left-hand and right-hand ailerons for damage (i.e., distortion, bending, impact marks). Repair or replace any damaged aileron found.
(i) For Models N22B and Following the applicable N24A airplanes (airplanes maintenance manual. previously affected by AD 2003-22-13): Inspect within the next 50 hours time-in-service (TIS) after December 23, 2003 (the effective date of AD 200322-13), unless already done. (ii) For Model N22S airplanes (airplanes not previously affected by AD 2003-22-13): Inspect within the next 10 hours TIS or 30 days, whichever occurs first, after the effective date of this AD, unless already done. (iii) For all affected airplanes: Repair or replace before further flight after the inspection.
(2) Adjust the engine power lever actuated landing gear "up" aural warning microswitches and then perform a ground test. If deficiencies are detected during the ground test, make the necessary adjustments.
(i) For Models N22B and N24A airplanes (airplanes previously affected by AD 2003-22-13): Within the next 50 hours TIS after December 23, 2003 (the effective date of AD 200322-13), unless already done following Nomad Alert Service Bulletin ANMD57-18, dated December 19, 2002. (ii) For Model N22S airplanes (airplanes not previously affected by AD 2003-22-13): Within the next 10 hours TIS or 30 days, whichever occurs first, after the effective date of this AD, unless already done.
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Following Nomad Alert Service Bulletin ANMD-5718, Rev 1, dated August 14, 2006, and the applicable maintenance manual.
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(3) For Model N22B airplanes: (i) fabricate placards that incorporate the following words (using at least 1/8inch letters) and install these placards on the instrument panel within the pilot's clear view: (A) "RECOMMENDED APPROACH FLAPS 10 OR 20 DEG AT 90 KIAS"; (B) "USE 10° OR 20° FLAP FOR TAKE-OFF AND LANDING WARNING - DO NOT EXCEED 20° FLAP EXTENSION DURING FLIGHT, LANDING GEAR UP WARNING WILL INITIATE FOR A TORQUE PRESSURE OF LESS THAN 30 PSI"; and (ii) incorporate the following information into the Limitations section of the Airplane Flight Manual (AFM): (A) limit the maximum flap extension to 20 degrees; and (B) limit flaps down operations for landing to 10° or 20° flap.
Within the next 50 hours TIS after December 23, 2003 (the effective date of AD 2003-22-13), unless already done following Nomad Alert Service Bulletin ANMD-57-18, dated December 19, 2002.
Following Nomad Alert Service Bulletin ANMD-5718, Rev 1, dated August 14, 2006. To show compliance with paragraphs (e)(3)(ii)(A) and (e)(3)(ii)(B) of this AD, a copy of this AD may be inserted into the Limitations section of the AFM. 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 insertion and the placard requirements of paragraphs (e)(3)(i)(A) and (e)(3)(i)(B) of this AD. Make an entry into the aircraft records showing compliance with these portions of the AD following section 43.9 of the Federal Aviation Regulations (14 CFR 43.9).
(4) For Model N22S airplanes: (i) fabricate a placard that incorporates the following words (using at least 1/8inch letters) and install this placard on the instrument panel within the pilot's clear view: "USE 10° FLAP FOR TAKE-OFF AND LANDING WARNING - DO NOT EXCEED 10° FLAP EXTENSION DURING FLIGHT, LANDING GEAR UP WARNING WILL INITIATE FOR A TORQUE PRESSURE OF LESS THAN 30 PSI"; and (ii) incorporate the following information into the Limitations section of the AFM: (A) limit the maximum flap extension to 10 degrees; and (B) limit flaps down operations for landing to 10° flap.
Within the next 10 hours TIS or 30 days, whichever occurs first, after the effective date of this AD, unless already done.
Following Nomad Alert Service Bulletin ANMD-5718, Rev 1, dated August 14, 2006. To show compliance with paragraphs (e)(4)(ii)(A) and (e)(4)(ii)(B) of this AD, a copy of this AD may be inserted into the Limitations section of the AFM. 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 insertion and the placard requirement of paragraph (e)(4)(i) of this AD. Make an entry into the aircraft records showing compliance with these portions of the AD following section 43.9 of the Federal Aviation Regulations (14 CFR 43.9).
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(5) For Model N24A airplanes: (i) fabricate a placard that incorporates the following words (using at least 1/8inch letters) and install this placard on the instrument panel within the pilot's clear view: "USE 10° FLAP FOR TAKE-OFF AND LANDING WARNING - DO NOT EXCEED 10° FLAP EXTENSION DURING FLIGHT, LANDING GEAR UP WARNING WILL INITIATE FOR A TORQUE PRESSURE OF LESS THAN 30 PSI"; and (ii) incorporate the following information into the Limitations section of the AFM: (A) limit the maximum flap extension to 10 degrees; and (B) limit flaps down operations for landing to 10° flap.
Within the next 50 hours TIS after December 23, 2003 (the effective date of AD 2003-22-13), unless already done following Nomad Alert Service Bulletin ANMD-57-18, dated December 19, 2002.
Following Nomad Alert Service Bulletin ANMD-5718, Rev 1, dated August 14, 2006. To show compliance with paragraphs (e)(5)(ii)(A) and (e)(5)(ii)(B) of this AD, a copy of this AD may be inserted into the Limitations section of the AFM. 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 insertion and the placard requirement of paragraph (e)(5)(i) of this AD. Make an entry into the aircraft records showing compliance with these portions of the AD following section 43.9 of the Federal Aviation Regulations (14 CFR 43.9).
Alternative Methods of Compliance (AMOCs) (f) The Manager, Standards Staff, FAA, ATTN: Doug Rudolph, Aerospace Engineer, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 3294059; 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 2003-22-13 are not approved for this AD. Related Information (h) This AD relates to Australian AD/GAF-N22/69, Amendment 5, dated September 14, 2006, which references Nomad Alert Service Bulletin ANMD-57-18, Rev 1, dated August 14, 2006. Material Incorporated by Reference (i) You must use Nomad Alert Service Bulletin ANMD-57-18, Rev 1, dated August 14, 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 Nomad Operations, Aerospace Support Division, Boeing Australia, PO Box 767, Brisbane, QLD 4000 Australia; telephone 61 7 3306 3366; fax 61 7 3306 3111.
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(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 October 13, 2006. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-17425 Filed 10-18-06; 8:45 am]
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AIRWORTHINESS DIRECTIVE
U.S. Department of Transportation
www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html
Federal Aviation Administration
2006-22-05 Various Aircraft: Amendment 39-14802. Docket No. FAA-2005-20080; Directorate Identifier 2003-NM-193-AD. Effective Date (a) This AD becomes effective December 1, 2006. Affected ADs (b) This AD supersedes AD 2003-04-06. Applicability (c) This AD applies to aircraft, certificated in any category, equipped with a Honeywell Primus II RNZ-850( )/-851( ) integrated navigation unit (INU) having a part number identified in Table 1 of this AD; including, but not limited to, BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes; Bombardier Model BD-700-1A10 series airplanes; Model Bombardier CL215-6B11 (CL-415 variant) series airplanes; Cessna Model 560, 560XL, and 650 airplanes; Dassault Model Mystere-Falcon 50 series airplanes; AvCraft Dornier Model 328-100 and -300 series airplanes; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 airplanes and Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP airplanes; Learjet Model 45 airplanes; Raytheon Model Hawker 800XP and Hawker 1000 airplanes; and Sikorsky Model S76A, S-76B, and S-76C aircraft. Table 1 – INU Part Numbers Part Numbers 7510100-811 through 7510100-814 inclusive 7510100-831 through 7510100-834 inclusive 7510100-901 through 7510100-904 inclusive 7510100-911 through 7510100-914 inclusive 7510100-921 through 7510100-924 inclusive
7510100-931 through 7510100-934 inclusive Note 1: This AD applies to Honeywell Primus II RNZ-850( )/-851( ) INUs installed on any aircraft, regardless of whether the aircraft has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For aircraft that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (m) of this AD. The request should include an assessment of the effect of themodification, alteration, or repair on the
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unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Unsafe Condition (d) This AD results from reports indicating that erroneous glideslope indications have occurred on certain aircraft equipped with the subject INUs. We are issuing this AD to ensure that the flightcrew has an accurate glideslope deviation indication. An erroneous glideslope deviation indication could lead to the aircraft making an approach off the glideslope, which could result in impact with an obstacle or terrain. 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. Requirements of AD 2003-04-06 Compliance Time For Action (f) Within 5 days after March 11, 2003 (the effective date of AD 2003-04-06), accomplish the requirements of either paragraph (g) or (h) of this AD. After the effective date of this AD, only accomplishing the requirements of paragraph (g) of this AD is acceptable for compliance with this paragraph. Inspection To Determine Part Number (g) Perform a one-time general visual inspection of the modification plate for the Honeywell Primus II NV-850 Navigation Receiver Module (NRM); part number 7510134-811, -831, -901, or 931; which is part of the Honeywell Primus II RNZ-850( )/-851( ) INU; to determine if Mod L has been installed. The modification plate is located on the bottom of the Honeywell Primus II RNZ-850( )/-851( ) INU, is labeled NV-850, and contains the part number and serial number for the Honeywell Primus II NV-850 NRM. If Mod L is installed, the letter L will be blacked out. Honeywell Alert Service Bulletin 7510100-34-A0035, dated July 11, 2003, is an acceptable source of service information for the inspection required by this paragraph. (1) If Mod L is installed, before further flight, do paragraph (h) or (j) of this AD. After the effective date of this AD, only accomplishment of paragraph (j) is acceptable for compliance with this paragraph. (2) If Mod L is not installed, no further action is required by this paragraph. Note 2: For the purposes of this AD, a general visual inspection is defined as: ''A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.''
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Note 3: For more information on the inspection specified in paragraph (g) of this AD, refer to Honeywell Technical Newsletter A23-3850-001, Revision 1, dated January 21, 2003. Aircraft Flight Manual (AFM) Revision (h) Revise the Limitations section of the AFM to include the following statements (which may be accomplished by inserting a copy of the AD into the AFM): ''Flight Limitations When crossing the Outer Marker on glideslope, the altitude must be verified with the value on the published procedure. For aircraft with a single operating glideslope receiver, the approach may be flown using normal procedures no lower than Localizer Only Minimum Descent Altitude (MDA). For aircraft with two operating glideslope receivers, the aircraft may be flown to the published minimums for the approach using normal procedures if both glideslope receivers are tuned to the approach and both crew members are monitoring the approach using independent data and displays.'' Parts Installation (i) As of March 11, 2003, no person may install a Honeywell Primus II NV-850 NRM on which Mod L has been installed, on the Honeywell Primus II RNZ-850( )/-851( ) INU of any aircraft, unless paragraph (h) or (k) of this AD is accomplished. As of the effective date of this AD, only accomplishment of paragraph (k) is acceptable for compliance with this paragraph. New Requirements of This AD Inspection To Determine Modification Level of NRM (j) For aircraft on which Mod L was found to be installed during the inspection required by paragraph (g) of this AD, or for aircraft on which paragraph (h) of this AD was accomplished: Within 24 months after the effective date of this AD, do an inspection of the modification plate on the Honeywell Primus II NV-850 NRM; part number 7510134-811, -831, -901, or -931; which is part of the Honeywell Primus II RNZ-850( )/-851( ) INU; to determine if Mod L, N, P, R or T is installed. The modification plate located on the bottom of the Honeywell Primus II RNZ-850( )/-851( ) INU is labeled NV-850, and contains the part number and serial number for the Honeywell Primus II NV850 NRM. If Mod L, N, P, R or T is installed, the corresponding letter on the modification plate will be blacked out. Honeywell Alert Service Bulletin 7510100-34-A0035, dated July 11, 2003, is an acceptable source of service information for this inspection. If Mod T is installed, no further action is required by this paragraph. If Mod L, N, P, or R is installed, before further flight, do all applicable related investigative, corrective, and other specified actions, in accordance with the Accomplishment Instructions of Honeywell Alert Service Bulletin 7510100-34-A0035, dated July 11, 2003; and Honeywell Service Bulletin 7510100-34-0037, dated July 8, 2004; to ensure that the NRM is at the Mod T configuration. Once the actions in this paragraph are completed, the AFM revision required by paragraph (h) of this AD may be removed from the AFM. Note 4: Honeywell Alert Service Bulletin 7510100-34-A0035, dated July 11, 2003, refers to Honeywell Alert Service Bulletin 7510100-34-A0034, dated February 28, 2003, as an additional source of service information for inspecting to determine the NRM part number, marking the modification plates of the NRM and INU accordingly, testing the INU for discrepant signals, and 19
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replacing the unit with a new or modified INU, as applicable. Honeywell Alert Service Bulletin 7510100-34-A0034 refers to Honeywell Alert Service Bulletin 7510134-34-A0016, currently at Revision 001, dated March 4, 2003, as an additional source of service information for marking the modification plates of the NRM and INU. Note 5: Honeywell Service Bulletin 7510100-34-0037, dated July 8, 2004, refers to Honeywell Service Bulletin 7510134-34-0018, dated July 8, 2004, as an additional source of service information for modifying the NRM to the Mod T configuration. (k) If the inspection specified in paragraph (j) of this AD is done within the compliance time specified in paragraph (f) of this AD, paragraph (g) of this AD does not need to be done. No Reporting Requirement (l) Where Honeywell Alert Service Bulletin 7510100-34-A0035, dated July 11, 2003 (or any of the related service information referenced therein), specifies to submit certain information to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (m)(1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with 14 CFR 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Material Incorporated by Reference (n) You must use Honeywell Alert Service Bulletin 7510100-34-A0035, dated July 11, 2003; and Honeywell Service Bulletin 7510100-34-0037, dated July 8, 2004, to perform the actions that are required by this AD, unless the AD specifies otherwise. 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. Go to https://pubs.cas.honeywell.com or contact Honeywell International, Inc., Commercial Electronic Systems, 21111 North 19th Avenue, Phoenix, Arizona 85027-2708, 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., Room PL-401, Nassif Building, Washington, DC; 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 the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_ locations.html. Issued in Renton, Washington, on October 13, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-17658 Filed 10-26-06; 8:45 am]
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AIRWORTHINESS DIRECTIVE
U.S. Department of Transportation
www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html
Federal Aviation Administration
2006-22-08 Air Tractor, Inc.: Amendment 39-14805; Docket No. FAA-2006-24228; Directorate Identifier 2006-CE-22-AD. Effective Date (a) This AD becomes effective on December 1, 2006. Affected ADs (b) None. Applicability (c) This AD affects all Models AT-602, AT-802, and AT-802A airplanes, all serial numbers, that are certificated in any category. Unsafe Condition (d) This AD results from reports of cracked engine mounts. We are issuing this AD to detect and correct cracks in the engine mount, which could result in failure of the engine mount. Such failure could lead to separation of the engine from the airplane. Compliance (e) To address this problem, you must do the following: Actions (1) Visually inspect the engine mount for any cracks.
Compliance Initially inspect upon accumulating 4,000 hours time-in-service (TIS) or within the next 100 hours TIS after December 1, 2006 (the effective date of this AD), whichever occurs later, unless already done. Thereafter, repetitively inspect every 300 hours TIS.
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Procedures Follow Snow Engineering Co. Service Letter #253, dated December 12, 2005.
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(2) If you find any crack damage, do one of the following: (i) Obtain an FAA-approved repair scheme and incorporate this repair scheme; or (ii) Replace the engine mount with a new engine mount.
Before further flight after any inspection required by paragraph (e)(1) of this AD where crack damage is found. If you repair the cracked engine mount, then continue to reinspect at intervals not to exceed 300 hours TIS, unless the repair scheme states differently. If you replace the engine mount, then initially inspect upon accumulating 4,000 hours TIS and repetitively at intervals not to exceed 300 hours TIS thereafter.
For obtaining a repair scheme: Follow Snow Engineering Co. Service Letter #253, dated December 12, 2005. For the replacement: The maintenance manual includes instructions for the replacement.
(3) Report any cracks that you find to the FAA at the address specified in paragraph (f) of this AD. Include in your report: (i) Airplane serial number; (ii) Airplane and engine mount hours TIS; (iii) Crack location(s) and size(s); (iv) Corrective action taken; and (v) Point of contact name and telephone number.
Within the next 10 days after you find the cracks or within the next 10 days after December 1, 2006 (the effective date of this AD), whichever occurs later.
The Office of Management and Budget (OMB) approved the information collection requirements contained in this regulation under the provisions of the Paperwork Reduction Act and assigned OMB Control Number 2120-0056.
Alternative Methods of Compliance (AMOCs) (f) The Manager, Fort Worth Airplane Certification Office, FAA, Attn: Andrew McAnaul, Aerospace Engineer, ASW-150 (c/o MIDO-43), 10100 Reunion Place, Suite 650, San Antonio, Texas 78216; telephone: (210) 308-3365; facsimile: (210) 308-3370, 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 do the actions required by this AD following the instructions in Snow Engineering Co. Service Letter 253, dated December 12, 2005. 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 Air Tractor, Inc., P.O. Box 485, Olney, Texas 76374; telephone: (940) 564-5616; facsimile: (940) 564-5612. 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-2006-24228; Directorate Identifier 2006-CE-22-AD.
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Issued in Kansas City, Missouri, on October 13, 2006. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-17828 Filed 10-26-06; 8:45 am]
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AIRWORTHINESS DIRECTIVE
U.S. Department of Transportation
www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html
Federal Aviation Administration
2006-22-10 Schempp-Hirth Gmbh & Co. KG: Amendment 39-14807; Docket No. FAA-200625171; Directorate Identifier 2006-CE-35-AD. Effective Date (a) This airworthiness directive (AD) becomes effective December 1, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Models Mini-Nimbus B and Mini-Nimbus HS-7 sailplanes, all serial numbers, that are certificated in any U.S. category. Reason (d) The mandatory continuing airworthiness information (MCAI) states that the aircraft manufacturer has identified, during the daily check after assembling a Mini Nimbus C, a failure in the flap actuating circuit. An investigation showed that the lever at the torsional drive in the fuselage failed at the weld. If not corrected, this condition could lead to a failure in the flap actuating circuit, which could result in reduced controllability of the sailplane. Actions and Compliance (e) Unless already done, do the following except as stated in paragraph (f) below. (1) Within the next 90 days after December 1, 2006 (the effective date of this AD), reinforce the flap drive. (2) Do the reinforcement following Schempp-Hirth Flugzeugbau GmbH. Technical Note No. 286-35/No. 328-13, EASA approved on: July 1, 2005. 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, Standards Staff, FAA, Small Airplane Directorate, ATTN: Gregory Davison, Aerospace Engineer, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4130; fax: (816) 329-4090, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19.
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(2) Return to Airworthiness: When complying with this AD, perform FAA-approved corrective actions before returning the product to an airworthy condition. (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) This AD is related to German AD D-2005-239, Effective Date: July 22, 2005, which references Schempp-Hirth Flugzeugbau GmbH. Technical Note No. 286-35/No. 328-13, EASA approved on: July 1, 2005. Material Incorporated by Reference (i) You must use Schempp-Hirth Flugzeugbau GmbH. Technical Note No. 286-35/No. 32813, EASA approved on: July 1, 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 Schempp-Hirth, Flugzeugbau GmbH, Postfach 14 43, D-73222 Kirchheim/Teck, Germany; telephone: ++ 49 7021 7298-0; fax: ++ 49 7021 7298-199; Web site: http://www.schempp-hirth.com, e-mail:
[email protected]. (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 202-7416030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Kansas City, Missouri, on October 19, 2006. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-17870 Filed 10-26-06; 8:45 am]
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AIRWORTHINESS DIRECTIVE
U.S. Department of Transportation
www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html
Federal Aviation Administration
2006-22-11 EADS SOCATA: Amendment 39-14808; Docket No. FAA-2006-25332; Directorate Identifier 2006-CE-40-AD. Effective Date (a) This airworthiness directive (AD) becomes effective December 1, 2006. Affected ADs (b) None. Applicability (c) This AD applies to the following Model TBM 700 airplanes that are certificated in any U.S. category: Serial numbers 1 through 32, 34, 36 through 69, 71 through 76, 79, 81 through 92, 96 through 98, 101, 102, 107 through 109, 112 through 114, 116, 118 through 124, 126 through 130, 132 through 135, 137, 138, 140 through 145, 148 through 155, 157, 158, 161 through 268, and 270 through 304. Reason (d) The mandatory continuing airworthiness information (MCAI) states that the aircraft manufacturer has determined that unsatisfactory initial elevator trim actuator greasing may lead to the icing of the elevator trim and generate an untrimmed nose-up attitude after an autopilot disconnection. If not corrected, this condition could result in pitch-up, out-of-trim condition when the autopilot is disconnected. Actions and Compliance (e) Unless already done, do the following except as stated in paragraph (f) below. (1) Within the next 25 hours time-in-service after December 1, 2006 (the effective date of this AD), lubricate the elevator trim tab actuator rods without removal. (2) Do the action required in paragraph (e)(1) of the AD in accordance with EADS SOCATA TBM Aircraft Mandatory Service Bulletin SB70-124, Amendment 1, ATA No. 27, dated January 2005. FAA AD Differences (f) None. Other FAA AD Provisions (g) The following provisions also apply to this AD:
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(1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Staff, FAA, Small Airplane Directorate, ATTN: Gunnar Berg, Aerospace Engineer, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4141; 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) Return to Airworthiness: When complying with this AD, perform FAA-approved corrective actions before returning the product to an airworthy condition. (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) This AD is related to French AD No. F-2005-034, Issue date: February 16, 2005, which references EADS SOCATA TBM Aircraft Mandatory Service Bulletin SB70-124, Amendment 1, ATA No. 27, dated January 2005. Material Incorporated by Reference (i) You must use EADS SOCATA TBM Aircraft Mandatory Service Bulletin SB70-124, Amendment 1, ATA No. 27, dated January 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 202-7416030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Kansas City, Missouri, on October 19, 2006. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-17930 Filed 10-26-06; 8:45 am]
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AIRWORTHINESS DIRECTIVE
U.S. Department of Transportation
www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html
Federal Aviation Administration
2006-22-12 Hartzell Propeller Inc. (formerly Hartzell Propeller Products Division): Amendment 39-14809. Docket No. FAA-2006-25841; Directorate Identifier 86-ANE-7. Effective Date (a) This airworthiness directive (AD) becomes effective November 13, 2006. Affected ADs (b) This AD supersedes AD 2004-21-01. Applicability (c) This AD applies to Hartzell Propeller Inc. model HC-B5MP-3( )/M10282A( )+6 and HCB5MP-3( )/M10876( )( )( )( ) five-bladed propellers. These propellers are installed on the following: Airplane manufacturer
Model
Propeller/blade
Nord
262(A) Frakes (Mohawk)
HC–B5MP–3(A)/M10282A(B)+6
Short Brothers
SD3–30 (Sherpa)
HC–B5MP–3A/M10282AB+6.
Short Brothers
SD3–60
HC–B5MP–3C/M10876ASK.
Short Brothers
SD3–60–200 (Sherpa)
HC–B5MP–3C/M10876ANSK.
PZL Mielec
PZL–M18( ) (Dromader)
HC–B5MP–3C/M10876(A)( )
Supplemental type certificate SA2369SW
SA1014GL
(d) The parentheses appearing in the propeller model number indicates the presence or absence of an additional letter(s) that varies the basic propeller model. This AD still applies regardless of whether these letters are present or absent in the propeller model designation. Unsafe Condition (e) This AD results from reports of fretting wear still occurring between the engine and propeller mounting flanges. The fretting wear results in loss of mounting bolt preload, causing failure of the mounting bolts. The actions specified in this AD are intended to prevent propeller separation from the airplane. Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done.
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Bolt Torque Inspections on Mounting Flanges Not Resurfaced (g) If on the effective date of this AD, either the propeller mounting flange or the engine mounting flange has not been resurfaced using either Hartzell Propeller Inc. Alert Service Bulletin (SB) No. A203A, dated January 5, 1995, or SB No. HC-SB-61-275, dated June 2, 2005; and either flange: (1) Has 3,000 or more operating hours time-since-new (TSN), then: (i) Perform a torque inspection of the propeller mounting bolts before further flight, if the bolt torque inspection has never been done. (ii) For bolts last inspected using AD 2004-21-01, perform a torque inspection of the propeller mounting bolts within 120 operating hours from the last inspection, or from the effective date of this AD, whichever occurs first, unless already done. (2) Has fewer than 3,000 operating hours TSN, then perform a torque inspection of the propeller mounting bolts upon reaching 3,000 operating hours TSN. (h) Thereafter, repeat the torque inspections within every 120 operating hours. (i) Use paragraphs 3.A. through 3.A.(4) of the Accomplishment Instructions of Hartzell Propeller Inc. SB No. HC-SB-61-275, dated June 2, 2005 to do the inspections. (j) If the torque of any one bolt is found to be less than 90 ft-lbs, remove and inspect the propeller, and resurface the flanges as necessary. (k) Use paragraphs 3.B. through 3.B.(5) of the Accomplishment Instructions of Hartzell Propeller Inc. SB No. HC-SB-61-275, dated June 2, 2005, to do the inspection and resurfacing. Replace all mounting bolts with new mounting bolts. Bolt Torque Inspections on Mounting Flanges Resurfaced (l) If the propeller and engine mounting flanges have been resurfaced using either Hartzell Propeller Inc. Alert SB No. A203A, dated January 5, 1995, or SB No. HC-SB-61-275, dated June 2, 2005, and a fretting disk was not installed, then: (1) Within 120 operating hours after reaching 1,500 operating hours from the time the flanges were last resurfaced, perform a torque inspection of the propeller mounting bolts. (2) Thereafter, repeat the torque inspection within every 120 operating hours. (3) Use paragraphs 3.A. through 3.A.(4) of the Accomplishment Instructions of Hartzell Propeller Inc. SB No. HC-SB-61-275, dated June 2, 2005 to do the inspections. (m) If the torque of any one bolt is found to be less than 90 ft-lbs, remove and inspect the propeller, and resurface the flanges as necessary. (n) Use paragraphs 3.B. through 3.B.(5) of the Accomplishment Instructions of Hartzell Propeller Inc. SB No. HC-SB-61-275, dated June 2, 2005 to do the inspection and resurfacing. Replace all mounting bolts with new mounting bolts. Inspection of Propeller and Engine Mounting Flanges (o) If the propeller and engine mounting flanges have been resurfaced, using either Hartzell Propeller Inc. Alert SB No. A203A, dated January 5, 1995, or SB No. HC-SB-61-275, dated June 2, 2005, and a fretting disk was installed, then: 29
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(1) Within 120 operating hours after reaching 1,500 operating hours from the time the flanges were last resurfaced, remove the propeller, and inspect the propeller and engine mounting flanges. Resurface the flanges if necessary and replace the fretting disk. (2) Thereafter, remove the propeller and repeat the flange inspections within every 1,500 operating hours and replace the fretting disk. (3) Use paragraphs 3.B. through 3.B.(5) of the Accomplishment Instructions of Hartzell Propeller Inc. SB No. HC-SB-61-275, dated June 2, 2005 to do the inspection and resurfacing. Replace all mounting bolts with new mounting bolts. (p) Whenever the propeller is removed from the engine: (1) Inspect the propeller and engine mounting flanges and resurface the flanges if necessary. (2) Use paragraphs 3.B. through 3.B.(5) of the Accomplishment Instructions of Hartzell Propeller Inc. SB No. HC-SB-61-275, dated June 2, 2005 to do the inspection and resurfacing. Replace all mounting bolts with new mounting bolts. (q) Whenever a propeller is removed from an engine to be installed on an airplane model not listed in this AD: (1) Inspect the propeller and engine mounting flanges before installation and resurface the flanges if necessary. (2) Use paragraphs 3.B. through 3.B.(5) of the Accomplishment Instructions of Hartzell Propeller Inc. SB No. HC-SB-61-275, dated June 2, 2005 to do the inspection and resurfacing. Replace all mounting bolts with new mounting bolts. Alternative Methods of Compliance (r) 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. Material Incorporated by Reference (s) You must use Hartzell Propeller Inc. SB No. HC-SB-61-275, dated June 2, 2005 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 Hartzell Propeller Inc. Technical Publications Department, One Propeller Place, Piqua, OH 45356; telephone (937) 778-4200; fax (937) 778-4391, for a copy of this service information. You may review copies at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; 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 Burlington, Massachusetts, on October 20, 2006. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E6-17925 Filed 10-26-06; 8:45 am]
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