FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS BIWEEKLY 2006-18 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
6
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
AIRWORTHINESS DIRECTIVE
U.S. Department of Transportation
www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html
Federal Aviation Administration
CORRECTION: [Federal Register: August 25, 2006 (Volume 71, Number 165); Page 50506; www.access.gpo.gov/su_docs/aces/aces140.html] 2006-16-13 PILATUS AIRCRAFT LTD: Amendment 39-14713; Docket No. FAA-2006-24954; Directorate Identifier 2006-CE-30-AD. Effective Date (a) This airworthiness directive (AD) becomes effective September 18, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Models PC-12 and PC-12/45 airplanes; manufacturer serial numbers 101 through 617 inclusive, certificated in any U.S. category. Reason (d) The mandatory continuing airworthiness information (MCAI) states that the aircraft manufacturer has identified drill damage on some Frame 21 (FR21) lug fittings on the production line and during a number of midlife wing lug inspections. It is thought that the damage found on the FR21 lug fittings occurred during assembly of the airplane. Depending on the size and location of the possible damage, if not corrected, the fatigue life of the wing attachment lugs on FR21 may be affected. The MCAI requires a one-time inspection of the FR21 adjacent to the wing upperattachment lugs, left and right, and a repair if necessary. Actions and Compliance (e) Unless already done, do the following except as stated in paragraph (f) below. (1) Within the next 100 hours time-in-service (TIS) after September 18, 2006 (the effective date of this AD), perform an inspection of FR21 in the area of the outer sidewall frame attachment lug forward and aft side faces, left and right, to determine if there is any damage that may have been made with a drill. Follow Pilatus Aircraft Ltd. PC12 Service Bulletin No. 53-004, dated February 10, 2006. (2) Within the next 100 hours TIS after September 18, 2006 (the effective date of this AD), perform an inspection of FR21 in the area of the top surface of the wing upper-attachment lugs, left and right, to determine if there is any damage that may have been made with a drill. Follow Pilatus Aircraft Ltd. PC12 Service Bulletin No. 53-004, dated February 10, 2006. (3) If during the inspection required by paragraph (e)(1) of this AD any damage less than 0.1 mm (0.0040 inch) on any FR21 is found, prior to further flight, repair the damaged FR21 in accordance with Pilatus Aircraft Ltd. PC12 Service Bulletin No. 53-004, dated February 10, 2006.
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2006-16-13 2
(4) If during the inspection required in paragraph (e)(1) of this AD any damage equal to or greater than 0.1 mm (0.0040 inch) on any FR21 is found, prior to further flight contact Pilatus Aircraft Ltd. for an FAA-approved repair solution and incorporate the repair. (5) If during the inspection required by paragraph (e)(2) of this AD any damage less than 1 mm (0.040 inch) depth on any FR21 wing attachment lug top surface is found, prior to further flight, repair the damaged FR21 in accordance with Pilatus Aircraft Ltd. PC12 Service Bulletin No. 53-004, dated February 10, 2006. (6) If during the inspection required by paragraph (e)(2) of this AD any damage equal to or greater than 1 mm (0.040 inch) depth on any FR21 wing attachment lug top surface is found, prior to further flight contact Pilatus Aircraft Ltd. for an FAA-approved repair solution and incorporate the repair. 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, ATTN: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri, 64106; telephone: (816) 329-4059; facsimile: (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 Federal Office for Civil Aviation AD HB-2006-223, effective date April 20, 2006, which references Pilatus Aircraft Ltd. PC12 Service Bulletin No. 53-004, dated February 10, 2006. Material Incorporated by Reference (i) You must use Pilatus Aircraft Ltd. PC12 Service Bulletin No. 53-004, dated February 10, 2006, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact the Pilatus Aircraft Ltd., Customer Support Manager, CH-6371 STANS, Switzerland; telephone: 41 41 619 6208; facsimile: +41 41 619 7311; email:
[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.
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BW 2006-18
2006-16-13 3
Issued in Kansas City, Missouri, on August 4, 2006. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-13016 Filed 8-11-06; 8:45 am]
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BW 2006-18
AIRWORTHINESS DIRECTIVE
U.S. Department of Transportation
www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html
Federal Aviation Administration
2006-16-18 Sandel Avionics Incorporated: Amendment 39-14718. Docket No. FAA-2006-24101; Directorate Identifier 2005-NM-103-AD. Effective Date (a) This AD becomes effective September 25, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Sandel Avionics Incorporated (Sandel) Model ST3400 terrain awareness warning system/radio magnetic indicator (TAWS/RMI) units approved under Technical Standard Order(s) C113, C151a, or C151b; as identified in Sandel ST3400 Service Bulletin SB340001, Revision B, dated September 15, 2004; as installed on various small and transport category airplanes, certificated in any category, including, but not limited, to the airplane models listed in Table 1 of this AD. Table 1.–Manufacturers/Airplane Models Manufacturer
Airplane model(s)
Airbus
A300
Avions Marcel Dassault Breguet Aviation (AMD/BA) Boeing
Falcon 10 727, 737, 747
Bombardier (LearJet)
24, 35, 36, 55
British Aerospace (Operations) Limited Cessna
Jetstream Series 3101 208, 208B, 421C; 501, 525, 550, 560, 650, S550
Embraer
EMB-120
Dassault-Aviation
Mystere-Falcon 50, Mystere-Falcon 200
Gulfstream
G-I, G-1159A (G-III)
Israel Aircraft Industries (IAI)
1124, 1125 Westwind Astra
McDonnell Douglas
DC-10
Piper
PA-31T2
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2006-16-18 2
Manufacturer
Airplane model(s)
Raytheon
Sabreliner
58; 1900D, 400; A36; BAe.125 Series 800A; HS.125 Series 600A/700A; Hawker 800-XP; 200, 300, 350, A200, B100, B200, B300, C90, C90A, C90B, E90, F90, MU-300-10 60 (NA-265-60)
Twin Commander
500-A, 695A
Viking Air Limited
DHC-6
Unsafe Condition (d) This AD results from a report that an in-flight bearing error occurred in a Model ST3400 TAWS/RMI unit configured to receive bearing information from a very high frequency omnidirectional range (VOR) receiver interface via a composite video signal, due to a combination of input signal fault and software error. We are issuing this AD to prevent a bearing error, which could lead to an airplane departing from its scheduled flight path, which could result in a reduction in separation from, and a possible collision with, other aircraft 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. Installing Placard (f) Within 14 days after the effective date of this AD: Install a placard on the TAWS/RMI which states, ''NOT FOR PRIMARY VOR NAVIGATION,'' in accordance with Sandel ST3400 Service Bulletin SB3400-01, Revision B, dated September 15, 2004. Revising Airplane Flight Manual (AFM) (g) Within 14 days after the effective date of this AD: Revise the Limitations section of the applicable AFM to include the following statement: ''Use of ST3400 TAWS/RMI for primary VOR navigation is prohibited unless the indicator has 3.07 or A3.06 software or later.'' This may be done by inserting a copy of this AD into the AFM. Updating Software (h) Within 90 days after the effective date of this AD, in accordance with Sandel ST3400 Service Bulletin SB3400-01, Revision B, dated September 15, 2004: Field-load the TAWS/RMI with updated software having revision 3.07 (for units having serial numbers (S/Ns) under 2000) or revision A3.06 (for units having S/Ns 2000 and subsequent). The placard and AFM limitations revision installed as required by paragraphs (f) and (g) of this AD may be removed after the software upgrade required by paragraph (h) of this AD has been accomplished.
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Parts Installation (i) As of 90 days after the effective date of this AD, no person may install, on any airplane, an ST3400 TAWS/RMI unit, unless it has been modified in accordance with Sandel ST3400 Service Bulletin SB3400-01, Revision B, dated September 15, 2004. Alternative Methods of Compliance (AMOCs) (j)(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 (k) You must use Sandel ST3400 Service Bulletin SB3400-01, Revision B, dated September 15, 2004 (only the first page of the document shows the date of the document), 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 this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Sandel Avionics Incorporated (Sandel), 2401 Dogwood Way, Vista, California, 92081, 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 August 3, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-13447 Filed 8-18-06; 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
2006-17-51 Agusta S.p.A.: Amendment 39-14747. Docket No. FAA-2006-25703; Directorate Identifier 2006-SW-20-AD. Applicability Model AB139 helicopters, with tailpipe assembly left hand, part number (P/N) 3G7800L00131 and right hand, P/N 3G7800L00231, installed, certificated in any category. Compliance Required as indicated, unless accomplished previously. To prevent a fire due to the structure in the cowling area overheating, separation of part of each tailpipe assembly, and subsequent loss of control of the helicopter, do the following: (a) Before further flight, and thereafter at intervals not to exceed 25 hours time-in-service, access the rear areas of each tailpipe assembly by removing the rear cowlings. (1) Visually inspect each tailpipe assembly inside the cowling for a crack. Note 1: Bollettino Tecnico No. 139-069, dated August 11, 2006 (BT), pertains to the subject of this AD. Note 2: Aircraft Maintenance Publication (AMP) AB139 pertains to the subject of this AD. (2) Inspect the structure surrounding each tailpipe assembly for overheating. If you find areas of overheating, inspect for heat damage to the surrounding structure. Inspect for overheating in the area of each tailpipe assembly outside the cowling. Inspect the internal part of each tailpipe assembly in the areas depicted in Areas A, Figure 1, of this AD.
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(i) Clean the end of each tailpipe assembly with a cloth. While applying slight pressure on it, inspect for a crack using a flashlight. (ii) Inspect each tailpipe assembly toward the centerline of the helicopter for a crack using a flashlight. (iii) Inspect each tailpipe assembly toward the outboard side of the helicopter for a crack using a mirror and a flashlight. (3) If you find a crack, before further flight, replace the tailpipe assembly with an airworthy tailpipe assembly. (b) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Safety Management Group, FAA, ATTN: Ed Cuevas, Aviation Safety Engineer, Fort Worth, Texas 76193-0111, telephone (817) 2225355, fax (817) 222-5961, for information about previously approved alternative methods of compliance. Note 3: The subject of this AD is addressed in the European Aviation Safety Agency (EASA) AD 2006-0242-E, dated August 11, 2006. Note 4: This AD differs from the BT and the EASA AD in that the BT and EASA AD allow repairs of certain cracks in each tailpipe assembly. (c) This amendment becomes effective on September 18, 2006, to all persons except those persons to whom it was made immediately effective by Emergency AD 2006-17-51 issued August 15, 2006, which contained the requirements of this amendment. Issued in Fort Worth, Texas, on August 24, 2006. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E6-14548 Filed 8-31-06; 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
2006-18-01 MD Helicopters, Inc.: Amendment 39-14739. Docket No. FAA-2006-24631; Directorate Identifier 2005-SW-01-AD. Supersedes AD 2004-23-15, Amendment 39-13870, Docket No. FAA-2004-19613, Directorate Identifier 2004-SW-38-AD. Applicability Model MD900 helicopters, with a Notar fan system that has a tension-torsion (TT) strap, part number (P/N) 900R3442009-103, 900R6442009-103, 900R3442009-101, or 500N5311-5, installed, certificated in any category. Compliance Required as indicated. To prevent failure of a TT strap in the Notar fan system, loss of directional control, and subsequent loss of control of the helicopter, accomplish the following: (a) Before further flight, unless accomplished previously, for TT Straps, P/N 900R3442009103 and 900R6442009-103, reduce the life limit from 3,034 to 2,500 hours time-in-service (TIS) and revise the life limit on the component history card or equivalent record to reflect this reduced retirement life. (b) Within 10 hours TIS, unless accomplished previously, for any TT strap that has accumulated 1,190 or more hours TIS, and then at intervals not to exceed 300 hours TIS, remove the TT strap from the helicopter and do a visual and an X-ray inspection in accordance with the Inspection Instructions, paragraph 2.B.(1). through (5)., and Figures 1 and 2 of MD Helicopters Service Bulletin SB900-095, dated November 3, 2004 (SB). Replace any unairworthy TT strap before further flight. (c) Before the TT strap accumulates 1,200 hours TIS, for any TT strap with less than 1,190 hours TIS, and then at intervals not to exceed 300 hours TIS, remove the TT strap from the helicopter and do a visual and an X-ray inspection in accordance with the Inspection Instructions, paragraph 2.B.(1). through (5)., and Figures 1 and 2 of the SB. Replace any unairworthy TT strap before further flight. (d) The X-ray inspection of the TT strap must be performed by a Level II or higher X-ray technician who is qualified under the guidelines established by MIL-STD-410E, ATA Specification 105, AIA-NAS-410, or an FAA-accepted equivalent for qualification standards. (e) This AD revises the Airworthiness Limitations section of the maintenance manual by reducing the life limit of the TT straps, P/N 900R3442009-103 and 900R6442009-103, from 3,034 hours TIS to 2,500 hours TIS. Additionally, this AD revises the Airworthiness Limitations section of the maintenance manual by adding repetitive inspection requirements at intervals not to exceed 300 hours TIS for TT straps, P/N 900R3442009-103, 900R6442009-103, 900R3442009-101, and 500N5311-5, that have 1,200 or more hours TIS until the TT strap reaches its retirement life.
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(f) 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 Manager, Los Angeles Aircraft Certification, FAA, ATTN: Roger Durbin, Aviation Safety Engineer, Airframe Branch, 3960 Paramount Blvd., Lakewood, California 90712, telephone (562) 627-5233, fax (562) 627-5210, for information about previously approved alternative methods of compliance. (g) The X-ray inspection shall be done in accordance with the specified portions of MD Helicopters Service Bulletin SB900-095, dated November 3, 2004. The incorporation by reference of that document was approved previously by the Director of the Federal Register, in accordance with 5 U. S.C. 552(a) and 1 CFR part 51, as of December 7, 2004 (69 FR 67806, November 22, 2004). Copies may be obtained from MD Helicopters Inc., Attn: Customer Support Division, 4555 E. McDowell Rd., Mail Stop M615, Mesa, Arizona 85215-9734, telephone 1-800-388-3378, fax 480346-6813, or on the web at http://www.mdhelicopters.com. 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. (h) This amendment becomes effective on October 3, 2006. Issued in Fort Worth, Texas, on August 22, 2006. Mark R. Schilling, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E6-14291 Filed 8-28-06; 8:45 am] BILLING CODE 4910-13-P
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EMERGENCY AIRWORTHINESS DIRECTIVE U.S. Department of Transportation
Aircraft Certification Service Washington, DC
Federal Aviation Administration
www.faa.gov/aircraft/safety/alerts/
DATE: August 31, 2006 AD #: 2006-18-51 Send to all owners and operators of Raytheon Aircraft Company (RAC) Models 1900, 1900C, and 1900D airplanes. This AD applies to certain RAC Models 1900, 1900C, and 1900D airplanes. Discussion The FAA received recent reports of cracks found in the wings of two RAC 1900D airplanes. During routine maintenance, the wing rear spar lower caps and rear spar web were found to have significant cracks. The RAC Structural Inspection Manual requires a thorough inspection of the wing rear spar at 17,500 hours time-in-service (TIS) with repetitive inspections at intervals of 3,000 hours TIS. One airplane had 19,126 hours TIS when cracks were found. The cracks were in the lower aft spar cap flange, but the cracks extended upward into the web and terminated at the lightening hole in the spar web. Fasteners were also found missing in the spar cap and wing cove splice plate. There were no discrepancies recorded from the initial inspection at 17,500 hours TIS on this airplane. Early indications show similar cracking on the other airplane. We continue to gather information on this airplane. Analysis shows that similar cracks could also develop in the wings of the Models 1900 and 1900C airplanes. FAA’s Determination After careful review of all available information related to the subject presented above, we have identified an unsafe condition that is likely to exist or develop on other products of this same type design. For this reason, the FAA has determined that AD action should be taken to detect and correct cracking in the wing rear spar lower caps of the affected airplanes before the cracks grow to failure. Such a wing failure could result in the wing separating from the airplane with consequent loss of control.
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2006-18-51 2 AD Requirements This AD requires the following: •
A one-time visual inspection of both the left and right wing rear spar lower caps for cracking and other damage such as loose or missing fasteners.
•
Repair of any cracks or damage found.
•
Report of any cracks or damage found to the FAA and RAC.
Provisions are included in this emergency AD to position the airplane to a home base, hangar, maintenance facility, etc. with limitations. This is considered interim action. The FAA will use the data from the reporting requirement to determine what additional action is necessary, which could result in future AD action. Presentation of the Actual AD This rule is issued under 49 U.S.C. Section 44701 (formerly section 601 of the Federal Aviation Act of 1958), pursuant to the authority delegated to me by the Administrator, and is effective immediately upon receipt of this action. 2006-18-51 RAYTHEON AIRCRAFT COMPANY (RAC): Directorate Identifier 2006-CE-48-AD. Effective Date (a) This emergency AD becomes effective upon receipt. Affected ADs (b) None. Applicability (c) This AD applies to the following airplane models and serial numbers that are certificated in any category: Models 1) 1900 2) 1900C (C-12J) 3) 1900D
Serial Numbers UA-3 UB-1 through UB-74, UC-1 through UC174, and UD-1 through UD-6 UE-1 through UE-439
Unsafe Condition (d) This AD is the result of extensive cracks found in the wing rear spar lower caps and rear spar web of two of the affected airplanes. One of the airplanes also had missing fasteners. We are issuing this AD to detect and correct cracking and other damage in the wing rear spar lower caps of the affected airplanes before the cracks or damage lead to failure. Such a wing failure could result in the wing separating from the airplane with consequent loss of control. 19
2006-18-51 3 Compliance (e) To address this problem, you must do the following: Actions
Compliance
(1) A one-time visual inspection of both the left and right wing rear spar lower caps for cracks and other damage such as loose or missing fasteners.
At whichever occurs later after receipt of this emergency AD: (i) Within 24 hours; or (ii) Prior to further flight.
Follow the procedures in the Appendix to this AD.
(2) For the inspection in paragraph (e)(1) of this AD, you may return/position the airplane to a home base, hangar, maintenance facility, etc.
For this repositioning, you may operate the airplane up to 3 hours time-in-service provided the flight(s) occur(s) no later than 30 days after receipt of this emergency AD.
The following limitations are imposed for such a repositioning flight: (i) ONLY THE PILOT AND ANY ADDITIONAL FLIGHT CREW MEMBER REQUIRED FOR SAFE OPERATION IS ALLOWED FOR THIS FLIGHT; (ii) FLIGHT INTO KNOWN OR FORECAST MODERATE OR SEVERE TURBULENCE IS PROHIBITED; and (iii) INDICATED AIRSPEED IS LIMITED TO 175 KNOTS MAXIMUM.
(3) Repair any cracks or other damage such as loose or missing fasteners found during the inspection required in paragraph (e)(1) of this AD. Do this by obtaining and incorporating an FAAapproved repair scheme from RAC.
Before further flight after the inspection required by paragraph (e)(1) of this AD.
Contact RAC at Post Office Box 85, Wichita, Kansas 67201-0085; phone: 316-676-8366; fax: (316) 676-8745; email:
[email protected].
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Procedures
2006-18-51 4 (4) Report the inspection results to the FAA and RAC. For the 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.
Within 72 hours after completing the inspection required in paragraph (e)(1) of this AD.
Send your report to Steven E. Potter, FAA, 1801 Airport Road, Wichita, Kansas 67209; fax: (316) 946-4107; email:
[email protected]; and Tom Peay, Raytheon Aircraft Company, Post Office Box 85, Wichita, Kansas 67201-0085; fax: (316) 676-8745; email:
[email protected]. Include in your report the following information: (i) aircraft model and serial number; (ii) number of cycles; (iii) aircraft hours TIS; (iv) left and right wing lower spar cap hours TIS; (v) hours TIS on the spar cap since last inspection; (vi) answer yes or no whether cracking, missing fasteners, or other damage was found; and (vii) if cracking was found, identify size and location of cracks
Alternative Methods of Compliance (h) The Manager, Wichita Aircraft Certification Office, FAA, ATTN: Steven E. Potter, FAA, 1801 Airport Road, Wichita, Kansas 67209; telephone: (316) 946-4124; fax: (316) 946-4107, has the authority to approve AMOCs for this AD, if requested using the procedures in 14 CFR 39.
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2006-18-51 5 APPENDIX TO AD 2006-18-51 Inspection Instructions – Raytheon Aircraft Company 1900 Series Wing Rear Spar Step 1. Lower the wing flaps to provide visual access to the wing rear spar cove area. Although the pictures show the flaps removed, this AD does not require flap removal to do the inspection. Step 2. Using a strong, high-intensity light visually inspect the area of the wing rear spar identified in Figure 1. There is ample visual access from above the upper surface of the flap. Look for cracks (like those shown in Figures 2 and 3) and loose or missing fasteners. Step 3. Clean the wing rear spar area 10 inches inboard and outboard of the buttock line (BL) 114 area. Step 4. Repeat the Step 2 inspection.
Outboard Approx. Cracks BL 114 found here
Inspect spar in this area
Figure 1: View of R/H wing rear spar at BL 114 area looking forward (The inboard flap is removed in this figure, but removal of the flap is not required to do the inspection).
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2006-18-51 6
Outboard
Crack Lightening hole
Figure 2: Closeup view of R/H wing rear spar web crack at BL 114 area looking forward (The inboard flap is removed in this figure, but removal of the flap is not required to do the inspection).
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2006-18-51 7
Rear spar web
Up
Crack Rear spar aft flange
Cove skin splice Outboard
Figure 3: Closeup view of R/H wing rear spar cracks at BL 114 area looking forward (The inboard flap is removed in this figure, but removal of the flap is not required to do the inspection).
Issued in Kansas City, Missouri, on August 31, 2006.
David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.
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