FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS BIWEEKLY 2006-15 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.
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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
AIRWORTHINESS DIRECTIVE
U.S. Department of Transportation
www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html
Federal Aviation Administration
2006-14-08 Mitsubishi Heavy Industries: Amendment 39-14679; Docket No. FAA-2006-23644; Directorate Identifier 2006-CE-03-AD. Effective Date (a) This AD becomes effective on August 21, 2006. Affected ADs (b) None. Applicability (c) This AD affects the following airplane models and serial numbers that are certificated in any category: Model (1) MU–2B–26A and MU–2B–40 (2) MU–2B–36A and MU–2B–60
Serial No. 321SA, 348SA, 350SA through 419SA, 421SA, 422SA, and 423SA. 661SA, 697SA through 747SA, 749SA through 757SA, and 759SA through 773SA.
Unsafe Condition (d) This AD results from a recent safety evaluation that used a data-driven approach to analyze the design, operation, and maintenance of the MU-2B series airplanes in order to determine their safety and define what steps, if any, are necessary for their safe operation. Part of that evaluation was the identification of unsafe conditions that exist or could develop on the affected type design airplanes. The actions specified in this AD are intended to prevent incorrect flight idle blade angle settings. This unsafe condition, if not corrected, could lead to an asymmetric thrust situation in certain flight conditions, which could result in airplane controllability problems. Compliance (e) To address this problem, you must do the following: Actions Verify that the current flight idle blade angles are set at 12 degrees. If not already set to 12 degrees, set the flight idle blade angles to 12 degrees.
Compliance Within the next 100 hours time-in-service after August 21, 2006 (the effective date of this AD).
7
Procedures Follow Mitsubishi Aircraft International, Inc. Service Bulletin No. SB016/61–001, dated March 18, 1980.
BW 2006-15
2006-14-08 2
Alternative Methods of Compliance (AMOCs) (f) The Manager, Forth Worth Aircraft Certification Office (ACO), FAA, ATTN: Rao Edupuganti, Aerospace Engineer, Fort Worth ACO, ASW-150, Rotorcraft Directorate, FAA, 2601 Meacham Boulevard, Fort Worth, Texas 76137-4298; telephone: 817-222-5284; facsimile: 817-2225960, 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 Mitsubishi Aircraft International, Inc. Service Bulletin No. SB016/61-001, dated March 18, 1980. 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 Mitsubishi Heavy Industries, Ltd., 4951 Airport Parkway, Suite 800, Addison, Texas 75001 telephone: 972-9345480; facsimile: 972-934-5488. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2006-23644; Directorate Identifier 2006-CE-03-AD. Issued in Kansas City, Missouri, on July 5, 2006. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 06-6179 Filed 7-14-06; 8:45 am] BILLING CODE 4910-13-P
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BW 2006-15
AIRWORTHINESS DIRECTIVE
U.S. Department of Transportation
www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html
Federal Aviation Administration
2006-15-01 Twin Commander Aircraft Corporation: Amendment 39-14681; Docket No. FAA2006-23785; Directorate Identifier 2006-CE-10-AD. Effective Date (a) This AD becomes effective on August 21, 2006. Affected ADs (b) None. Applicability (c) This AD affects Models 690, 690A, and 690B airplanes, all serial numbers, that are certificated in any category. Unsafe Condition (d) This AD results from reports of cracks found in the support structures for the inboard and center aileron hinge fittings on both wings. The actions specified in this AD are intended to detect and correct cracks in the support structures for the inboard and center aileron hinge fittings on both wings, which could result in aileron failure. This failure could lead to reduced controllability or loss of control of the airplane. Compliance (e) To address this problem, you must do the following: Actions (1) Inspect, visually and using fluorescent dye penetrant, the support structures for the inboard and center aileron hinge fittings on both wings for cracks. (2) If you do not find cracks during the inspection required in paragraph (e)(1) of this AD, reinforce the support structures for the inboard and center aileron hinge fittings on both wings that are crack free.
Compliance Within the next 150 hours time-in-service or 12 months after August 21, 2006 (the effective date of this AD), whichever occurs first. Before further flight after the inspection required in paragraph (e)(1) of this AD. After doing the reinforcement, no further action is required.
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Procedures Follow Twin Commander Aircraft LLC Alert Service Bulletin 236A and Alert Service Bulletin 238, both dated December 21, 2004, as applicable. Follow Twin Commander Aircraft LLC Alert Service Bulletin 236A and Alert Service Bulletin 238, both dated December 21, 2004, as applicable.
BW 2006-15
2006-15-01 2
Actions (3) If you find cracks during the inspection required in paragraph (e)(1) of this AD, replace and reinforce the cracked support structure.
Compliance Before further flight after the inspection required in paragraph (e)(1) of this AD. After doing the replacement and reinforcement, no further action is required.
Procedures Follow Twin Commander Aircraft LLC Alert Service Bulletin 236A and Alert Service Bulletin 238, both dated December 21, 2004, as applicable.
Alternative Methods of Compliance (AMOCs) (f) The Manager, Seattle Aircraft Certification Office (ACO), FAA, ATTN: Vince Massey, Aerospace Engineer, Seattle, ACO, 1601 Lind Avenue SW., Renton, WA 98057; telephone: (425) 917-6475; facsimile: (425) 917-6590, 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 Twin Commander Aircraft LLC Alert Service Bulletin 236A and Twin Commander Aircraft LLC Alert Service Bulletin 238, both dated December 21, 2004. The Director of the Federal Register approved the incorporation by reference of these service bulletins in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact Twin Commander Aircraft LLC, 19010 59th Drive NE., Arlington, WA 98223, telephone: (360) 435-9797; facsimile: (360) 435-1112. 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; US 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-2006-23785; Directorate Identifier 2006-CE-10-AD. Issued in Kansas City, Missouri, on July 7, 2006. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 06-6225 Filed 7-14-06; 8:45 am] BILLING CODE 4910-13-M
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BW 2006-15
AIRWORTHINESS DIRECTIVE
U.S. Department of Transportation
www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html
Federal Aviation Administration
2006-15-02 Pilatus Aircraft Ltd.: Amendment 39-14682; Docket No. FAA-2006-24092; Directorate Identifier 2006-CE-18-AD. Effective Date (a) This AD becomes effective on August 23, 2006. Affected ADs (b) This AD supersedes AD 2003-09-01, Amendment 39-13130. Applicability (c) This AD affects the following Models 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, PC-6/B2-H2, PC-6/B2H4, PC-6/C-H2, and PC-6/C1-H2 airplanes that are certificated in any category: (1) Group 1 (maintains the actions from AD 2003-09-01): All manufacturer serial numbers (MSN) up to and including 939. (2) Group 2: MSN 2001 through 2092. Note: These airplanes are also identified as Fairchild Republic Company PC-6 airplanes, Fairchild Industries PC-6 airplanes, Fairchild Heli Porter PC-6 airplanes, or Fairchild-Hiller Corporation PC-6 airplanes. Unsafe Condition (d) This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland that requires retaining the actions of AD 2003-09-01 and adding MSN 2001 through 2092 for all the models of the PC-6 airplanes listed in the type certificate data sheet of Type Certificate No. 7A15. We are issuing this AD to detect and correct increased friction in the aileron control bellcrank assemblies, which could result in failure of the aileron flightcontrol system. Such failure could lead to problems in controlling flight. Compliance (e) To address this problem, you must do the following:
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BW 2006-15
2006-15-02 2
Actions (1) Inspect, before removal of the wing bellcrank assemblies, part numbers (P/N) 6132.0071.51 and 6132.0071.52, for installed circlips, P/N N237. (i) If circlips are installed, do the actions required in paragraphs (e)(5) and (e)(6) of this AD. (ii) If circlips are not installed, perform all actions required by paragraphs (e)(3), (e)(4), (e)(5), (e)(6), and (e)(7) of this AD. (2) Inspect, before removal of the fuselage bellcrank assembly, P/N 6232.0118.00, for the circlip installed on the housing to prevent axial movement of the bellcrank on its bearing and the flange of the housing to the rear. If the fuselage bellcrank assembly has either no circlip and/or it is not installed as required, perform the actions in paragraphs (e)(8) and (e)(9) of this AD. (3) Remove the wing bellcrank assemblies, P/Ns 6132.0071.51 and 6132.0071.52, and inspect for worn or damaged bearings. Replace worn or damaged bearings. (4) Stake and lock the bearing in the housing of the wing bellcranks, P/Ns 6132.0071.51 and 6132.0071.52.
Compliance (A) For Group 1 Airplanes: Within the next 100 hours time-in-service (TIS) after June 17, 2003 (the effective date of AD 2003– 09–01), unless already done. (B) For Group 2 Airplanes: Within the next 100 hours TIS after August 23, 2006 (the effective date of this AD), unless already done.
Procedures Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002.
Before further flight after the inspection required in paragraph (e)(1) of this AD.
Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002.
Before further flight after the inspections required in paragraphs (e)(1) and (e)(2) of this AD, as applicable.
Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002.
Before further flight after the inspections required in paragraphs (e)(1) and (e)(2) of this AD, as applicable. Before further flight after the inspections required in paragraphs (e)(1) and (e)(2) of this AD, as applicable.
Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002. Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002.
(5) Inspect the wing bellcranks control-cable attachment bolts for correct type and for signs of rub damage on the heads. Replace bolts that are damaged and/or have a total length (including head) of more than 21.5 mm (0.85 in.). (6) Inspect the wing bellcranks Before further flight after the support plate for signs of rub damage inspections required in paragraphs caused by the bolts. If damage is (e)(1) and (e)(2) of this AD. found: (i) Obtain a repair scheme from the manufacturer through FAA at the address specified in paragraph (f) of this AD. (ii) Incorporate this repair scheme.
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Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002.
BW 2006-15
2006-15-02 3
(7) Reinstall wing bellcrank assemblies
Before further flight after the inspections required in paragraphs (e)(1) and (e)(2) of this AD.
(8) Remove the fuselage bellcrank assembly, P/N 6232.0118.00, and inspect the housing for wear, damage, and signs of axial movement of the bearing in the housing. Replace worn or damaged bearings. If any signs of axial movement of a bearing are found: (i) Obtain a repair scheme from the manufacturer through FAA at the address specified in paragraph (f) of this AD. (ii) Incorporate this repair scheme. (9) Reinstall the fuselage bellcrank assembly. Ensure that the fuselage bellcrank assembly is installed so that the surface of the bellcrank with the flange of the housing is installed to the rear. The effect of this is to lock the bellcrank on the bearing tube and thus prevent movement. (10) Do not install any bellcrank assemblies, P/Ns 6132.0071.51, 6132,0071.52, and 6232.0118.00 (or FAA-approved equivalent part numbers), unless the aileron assembly has been inspected, modified, and installed.
Before further flight after the inspections required in paragraphs (e)(1) and (e)(2) of this AD.
Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002. Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002.
Before further flight after the Follow Pilatus Aircraft inspections required in paragraphs Ltd. PC–6 Service (e)(1), (e)(2), and (e)(8) of this AD. Bulletin No. 27–001, dated June 5, 2002.
(A) For Group 1 Airplanes: As of June 17, 2003 (the effective date of AD 2003–09–01). (B) For Group 2 Airplanes: As of August 23, 2006 (the effective date of this AD), unless already done.
Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002.
(f) Axial movement of serviceable bearings in the housings of the wing bellcranks is permitted provided no wear or damage to the bearing is found. (g) Any sign of axial movement of a bearing in the housing of the fuselage bellcrank assembly requires that you obtain a repair scheme from the manufacturer through FAA at the address specified in paragraph (i) of this AD and incorporate the repair scheme. (h) 14 CFR 21.303 allows for replacement parts through parts manufacturer approval (PMA). The phrase ‘‘or FAA-approved equivalent part number'' in this AD is intended to signify those parts that are PMA approved through identicality to the design of the part under the type certificate and replacement parts to correct the unsafe condition under PMA (other than identicality). If parts are installed that are identical to the unsafe parts, then the corrective actions of the AD affect these parts also. In addition, equivalent replacement parts to correct the unsafe condition under PMA (other than identicality) may also be installed provided they meet current airworthiness standards, which include those actions cited in this AD.
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Alternative Methods of Compliance (AMOCs) (i) The Manager, Standards Office, ATTN: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 3294059; facsimile: (816) 329-4090, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (j) AMOCs approved for AD 2003-09-01 are approved for this AD. Related Information (k) Swiss AD Number HB 2005-289, effective date August 23, 2005, also addresses the subject of this AD. Material Incorporated by Reference (l) You must do the actions required by this AD following the instructions in Pilatus Aircraft Ltd. PC-6 Service Bulletin No. 27-001, dated June 5, 2002. (1) As of June 17, 2003 (68 FR 22582, April 29, 2003), the Director of the Federal Register previously approved the incorporation by reference of Pilatus Service Bulletin No. 27-001, dated June 5, 2002, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) To get a copy of this service information, contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans, Switzerland; telephone: +41 41 619 63 19; facsimile: +41 41 619 6224. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2006-24092; Directorate Identifier 2006-CE-18-AD. Issued in Kansas City, Missouri, on July 10, 2006. Steven W. Thompson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-11333 Filed 7-18-06; 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
2006-15-03 Pilatus Aircraft Ltd.: Amendment 39-14683; Docket No. FAA-2006-24093; Directorate Identifier 2006-CE-19-AD. Effective Date (a) This AD becomes effective on August 23, 2006. Affected ADs (b) This AD supersedes AD 2003-13-04, Amendment 39-13204. Applicability (c) This AD affects the following Models 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, PC-6/B2-H2, PC-6/B2H4, PC-6/C-H2, and PC-6/C1-H2 airplanes that are equipped with turbo-prop engines and are certificated in any category: (1) Group 1 (maintains the actions from AD 2003-13-04): All manufacturer serial numbers (MSN) up to and including 939. (2) Group 2: MSN 2001 through 2092. Note: These airplanes are also identified as Fairchild Republic Company PC-6 airplanes, Fairchild Industries PC-6 airplanes, Fairchild Heli Porter PC-6 airplanes, or Fairchild-Hiller Corporation PC-6 airplanes. Unsafe Condition (d) This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland that requires retaining the actions of AD 2003-13-04 and adding MSN 2001 through 2092 for all the models of the PC-6 airplanes listed in the type certificate data sheet of Type Certificate (TC) No. 7A15. We are issuing this AD to detect and correct cracks in the ribs of the inboard integral fuel tanks in the left and right wings, which could lead to wing failure during flight with consequent loss of control of the airplane. Compliance (e) To address this problem, you must do the following:
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Actions (1) Inspect: (i) The ribs in the inboard integral fuel tanks and related structure in the left and right wings for crack damage; (ii) The upper and lower wing skins for damage; and (iii) The inboard fuel tank area to determine if the inboard fuel tank ventilating system is installed. (2) If any crack damage is found: (i) Correct the crack damage designated as repairable in the service bulletin. (ii) For other crack damage, obtain a repair scheme from the manufacturer through FAA at the address specified in paragraph (f) of this AD and incorporate this repair scheme. (3) If wing distortion is found, obtain a repair scheme from the manufacturer through FAA at the address specified in paragraph (f) of this AD and incorporate this repair scheme. (4) If the inboard fuel tank ventilating system is not installed, install the inboard fuel tank ventilating system.
Compliance (A) For Group 1 Airplanes: Within the next 100 hours timein-service (TIS) after August 15, 2003 (the effective date of AD 2003–13–04), unless already done. (B) For Group 2 Airplanes: Within the next 90 days or 100 hours TIS, whichever occurs first, after August 23, 2006 (the effective date of this AD), unless already done. Before further flight after the inspections required in paragraph (e)(1) of this AD.
Procedures Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 57–002, dated November 27, 2002.
Before further flight after the inspections required in paragraph (e)(1) of this AD.
Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 57–002, dated November 27, 2002.
Before further flight after the inspections required in paragraph (e)(1) of this AD.
Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 118, dated December 1972.
Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 57–002, dated November 27, 2002.
Alternative Methods of Compliance (AMOCs) (f) The Manager, Standards Office, ATTN: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 3294059; facsimile: (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 2003-13-04 are approved for this AD. Related Information (h) Swiss AD Numbers HB 2003-092, dated February 17, 2003, and HB 2005-289, effective date August 23, 2005, also address the subject of this AD.
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Material Incorporated by Reference (i) You must do the actions required by this AD following the instructions in Pilatus Aircraft Ltd. PC-6 Service Bulletin No. 57-002, dated November 27, 2002, and Pilatus Aircraft Ltd. PC-6 Service Bulletin No. 118, dated December 1972. (1) As of August 15, 2003 (68 FR 37394, June 24, 2003), the Director of the Federal Register previously approved the incorporation by reference of Pilatus Aircraft Ltd. PC-6 Service Bulletin No. 57-002, dated November 27, 2002; and Pilatus Aircraft Ltd. PC-6 Service Bulletin No. 118, dated December 1972, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) To get a copy of this service information, contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans, Switzerland; telephone: +41 41 619 63 19; facsimile: +41 41 619 6224. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2006-24093; Directorate Identifier 2006-CE-19-AD. Issued in Kansas City, Missouri, on July 11, 2006. Steven W. Thompson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-11339 Filed 7-18-06; 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
2006-15-07 Mitsubishi Heavy Industries, LTD.: Amendment 39-14687; Docket No. FAA-200623645; Directorate Identifier 2006-CE-04-AD. Effective Date (a) This AD becomes effective on August 24, 2006. Affected ADs (b) None. Applicability (c) This AD affects the following airplane models and serial numbers that are certificated in any category: Type certificate (1) A2PC (2) A2PC (3) A10SW (4) A10SW
Models MU–2B, MU–2B–10, MU–2B–15, MU– 2B–20, MU–2B– 25, and MU–2B–26. MU–2B–30, MU–2B–35, and MU–2B– 36 MU–2B–25, MU–2B–26, MU–2B–26A, and MU–2B–40 MU–2B–35, MU–2B–36, MU–2B–36A, and MU–2B–60
Serial Nos. 008 through 312, 314 through 320, and 322 through 347. 501 through 651, 653 through 660, and 662 through 696. 313SA, 321SA, and 348SA through 459SA. 652SA, 661SA, and 697SA through 1569SA.
Unsafe Condition (d) This AD results from a recent safety evaluation that used a data-driven approach to analyze the design, operation, and maintenance of the MU-2B series airplanes in order to determine their safety and define what steps, if any, are necessary for their safe operation. Part of that evaluation was the identification of unsafe conditions that exist or could develop on the affected type design airplanes. The actions specified in this AD are intended to detect and correct improper rigging of the propeller feathering linkage. The above issue if uncorrected could result in degraded performance and poor handling qualities with consequent loss of control of the airplane. Compliance (e) To address this problem, you must do the following:
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Actions Incorporate the following information into the Limitations Section of the FAA-approved Airplane Flight Manual (AFM): (1) For airplanes listed in Type Certificate No. A2PC insert pages 3 and 4 from Mitsubishi Heavy Industries, Ltd. (MHI) MU–2 Service Bulletin No. 229, dated February 20, 1996. (2) For airplanes listed in Type Certificate No. A10SW insert page 3 of 3 from MHI MU–2 Service Bulletin No. 090/76– 003, dated January 22, 1997. (3) For all of the above airplanes the logbook entry required after each pilot check on page 3 of MHI MU–2 Service Bulletin No. 090/76–003, dated January 22, 1997, and page 4 of MHI MU–2 Service Bulletin No. 229, dated February 20, 1996, is not required.
Compliance Within 100 hours time-in-service after August 24, 2006 (the effective date of this AD).
Procedures 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 insert the information into the AFM as specified in paragraph (e) of this AD. Make an entry into the aircraft records showing compliance with this portion of the AD in accordance with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9).
Note: The language in the service information states the procedure is an ‘‘inspection,'' but the procedure is a ‘‘pilot check.'' Alternative Methods of Compliance (AMOCs) (f) The Manager, Fort Worth Aircraft Certification Office (ACO), FAA, ATTN: Rao Edupuganti, Aerospace Engineer, ASW-150, Fort Worth ACO, 2601 Meacham Blvd., Fort Worth, Texas 76193; telephone: (817) 222-5284; facsimile: (817) 222-5960, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information (g) Japan Civil Aviation Bureau Airworthiness Directive No. TCD 4379-96, dated February 20, 1996, addresses the subject of this AD. (h) For service information related to this AD, contact Mitsubishi Heavy Industries America, Inc., 4951 Airport Parkway, Suite 800, Addison, Texas 75001; telephone: (972) 934-5480; facsimile: (972) 934-5488. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2006-23645; Directorate Identifier 2006-CE-04-AD. Issued in Kansas City, Missouri, on July 11, 2006. Steven W. Thompson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-11419 Filed 7-19-06; 8:45 am] 19
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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
2006-15-08 Honeywell International Inc. (formerly AlliedSignal Inc., Garrett Engine Division; Garrett Turbine Engine Company; and AiResearch Manufacturing Company of Arizona): Amendment 39-14688; Docket No. FAA-2006-23706; Directorate Identifier 2006-NE-03-AD. Effective Date (a) This airworthiness directive (AD) becomes effective August 24, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Honeywell International Inc. 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 engines with the part numbers (P/Ns) of Woodward fuel control unit (FCU) assemblies listed in this AD, installed. These engines are installed on, but not limited to, the following airplanes: Manufacturer AERO PLANES, LLC (formerly McKinnon Enterprises) ALLIED AG CAT PRODUCTIONS (formerly Schweizer) AYRES BRITISH AEROSPACE LTD (formerly Jetstream) CONSTRUCCIONES AERONAUTICAS, S.A. (CASA) DEHAVILLAND DORNIER FAIRCHILD
GRUMMAN AMERICAN MITSUBISHI PILATUS POLSKIE ZAKLADY LOTNICZE SPOLKA (formerly Wytwornia Sprzetu Komunikacyjnego). PROP-JETS, INC. RAYTHEON AIRCRAFT (formerly Beech)
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Model G–21G. G–164 Series. S–2R Series. 3101 and 3201 Series, and HP.137 JETSTREAM MK.1. C–212 Series. DH104 Series 7AXC (DOVE). 228 Series. SA226 and SA227 Series (SWEARINGEN MERLIN and METRO SERIES). G–164 Series. MU–2B Series (MU–2 Series). PC–6 Series (FAIRCHILD PORTER and PEACEMAKER). PZL M18, PZL M18A, PZL M18B. 400. C45G, TC–45G, C–45H, TC–45H, TC–45J, G18S, E18S–9700, D18S, D18C, H18, RC–45J, JRB–6, UC– 45J, 3N, 3NM, 3TM, B100, C90 and E90.
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Manufacturer SHORTS BROTHERS and HARLAND, LTD. THRUSH (ROCKWELL COMMANDER) TWIN COMMANDER (JETPROP COMMANDER)
Model SC7 (SKYVAN) Series. S–2R. 680, 690 and 695 Series.
Unsafe Condition (d) This AD results from reports of loss of the fuel control drive, leading to engine overspeed, overtorque, overtemperature, uncontained rotor failure, and asymmetric thrust in multi-engine airplanes. We are issuing this AD to prevent destructive overspeed that could result in uncontained rotor failure, and damage to the airplane. 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 Inspection of Engines With Affected FCU Assemblies (f) At the next scheduled inspection of the fuel control drive, but within 1,000 hours-inservice after the effective date of this AD: (1) Perform an initial dimensional inspection of the fuel control drive for wear or damage. Information on spline inspection can be found in Section 72-00-00 of the applicable maintenance manuals. (2) Repair or replace the fuel pump, if the spline fails the dimensional inspection, with any serviceable fuel pump. (3) Repair or replace the FCU assembly, if the splines fail the dimensional inspection, with a serviceable modified FCU assembly. Repetitive Inspections of Engines With Affected FCU Assemblies (g) Thereafter, within 1,000 hours since-last-inspection: (1) Perform repetitive dimensional inspections of the fuel control drive, for wear or damage. Information on spline inspection can be found in Section 72-00-00 of the applicable maintenance manuals. (2) Repair or replace the fuel pump, if the spline fails the dimensional inspection, with any serviceable fuel pump. (3) Repair or replace the FCU assembly if the splines fail the dimensional inspection, with a serviceable modified FCU assembly. TPE331-1, -2, and -2UA Series Engines (h) For TPE331-1, -2, and -2UA series engines, replace Woodward FCU assemblies, P/Ns 869199-13/ -20/ -21/ -22/ -23/ -24/-25/ -26/ -27/ -28/ -29/ -31/ -32/ -33/ -34, and -35, with a serviceable, modified FCU assembly the next time the FCU assembly is removed for cause that requires return, or when the FCU assembly requires overhaul, but not later than December 31, 2012. Information on replacement FCU assembly P/Ns, configuration management, rework, and replacement information, can be found in Honeywell Alert Service Bulletin (ASB) No. TPE331-A730271, Revision 1, dated January 25, 2006.
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TPE331-3U, -3UW, -5, -5A, -5AB, -5B, -6, -6A, -10AV, -10GP, -10GT, -10P, and -10T Series Engines (i) For TPE331-3U, -3UW, -5, -5A, -5AB, -5B, -6, -6A, -10AV, -10GP, -10GT, -10P, and 10T series engines, replace Woodward FCU assemblies, P/Ns 893561-7/ -8/ -9/ -10/ -11/ -14/ -15/ 16/ -20/ -26/ -27, and -29, and P/Ns 897770-1/ -3/ -7/ -9/ -10/ -11/ -12/ -14 / -15/ -16/ -25/ -26, and 28, with a serviceable, modified FCU assembly the next time the FCU assembly is removed for cause that requires return, or when the FCU assembly requires overhaul, but not later than December 31, 2012. Information on replacement FCU assembly P/Ns, configuration management, rework, and replacement information, can be found in Honeywell ASB No. TPE331-A73-0262, Revision 2, dated June 17, 2005. TPE331-10, -10R, -10U, -10UA, -10UF, -10UG, -10UGR, -10UR, -11U, -12JR, -12UA, -12UAR, and -12UHR Series Engines (j) For TPE331-10, -10R, -10U, -10UA, -10UF, -10UG, -10UGR, -10UR, -11U, -12JR, 12UA, -12UAR, and -12UHR series engines, replace Woodward FCU assemblies, P/Ns 897375-2/ 3/ -4/ -5/ -8/ -9/ -10/ -11/ -12/ -13/ -14/ -15/ -16/ -17/ -19/ -21/ -24/ -25/ -26, and -27, and P/Ns 897780-1/ -2/ -3/ -4/ -5/ -6/ -7/ -8/ -9/ -10/ -11/ -14/ -15/ -16/ -17/ -18/ -19/ -20/ -21/ -22/ -23/ -24/ 25/ -26/ -27/ -30/ -32/ -34/ -36/ -37, and -38, and P/Ns 893561-17/ -18, and -19, with a serviceable, modified FCU assembly the next time the FCU assembly is removed for cause that requires return, or when the FCU assembly requires overhaul, but not later than December 31, 2012. Information on replacement FCU assembly P/Ns, configuration management, rework, and replacement information, can be found in Honeywell ASB No. TPE331-A73-0254, Revision 2, dated June 17, 2005. Definitions (k) For the purposes of this AD: (1) A ‘‘serviceable, modified FCU assembly'' for engines affected by paragraph (h), (i), or (j) of this AD, is an FCU assembly with a P/N not listed in this AD. (2) The ‘‘fuel control drive'' is a series of mating splines located between the fuel pump and fuel control governor, consisting of the following four drive splines: The fuel pump internal spline, the fuel control external ‘‘quill shaft'' spline, and the stub shaft internal and external splines. (3) A ‘‘removal for cause that requires return'', for engines affected by paragraph (h), (i), or (j) of this AD, is an FCU assembly that has displayed an unserviceable or unacceptable operating condition requiring the FCU to be removed from service and sent to a repair or overhaul shop. Optional Method of Compliance for TPE331 Series Engines Installed On Single-Engine Airplanes (l) As an optional method of compliance to paragraph (h), (i), or (j) of this AD, for TPE331 series engines installed on single-engine airplanes, having an affected Woodward FCU assembly perform the following steps as necessary: (1) Continue repetitive dimensional inspections of the fuel control drive, for wear or damage as specified in paragraph (g)(1) of this AD. (2) Repair or replace the fuel pump or FCU assembly if the splines fail the dimensional inspection, with any serviceable fuel pump or FCU assembly. Terminating Action (m) Performing an FCU assembly replacement as specified in paragraph (h), (i), or (j) of this AD, is terminating action for the initial and repetitive inspections required by this AD. 22
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Alternative Methods of Compliance (n) The Manager, Los Angeles Aircraft Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Related Information (o) Information pertaining to operating recommendations for applicable engines after a fuel control drive failure is contained in OI 331-12R5 dated July 10, 2006, for multi-engine airplanes and in OI 331-18R3 dated July10, 2006, for single-engine airplanes. Issued in Burlington, Massachusetts, on July 14, 2006. Francis A. Favara, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E6-11540 Filed 7-19-06; 8:45 am]
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