FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS BIWEEKLY 2006-14 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: See AD 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: See AD
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: See AD
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: See AD 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
AIRWORTHINESS DIRECTIVE
U.S. Department of Transportation
www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html
Federal Aviation Administration
2006-13-10 Raytheon Aircraft Company (Formerly Beech): Amendment 39-14663; Docket No. FAA-2005-23319; Directorate Identifier 2005-CE-52-AD. Effective Date (a) This AD becomes effective on August 7, 2006. Affected ADs (b) This AD supersedes AD 92-07-05; Amendment 39-8201. Applicability (c) This AD affects the following airplane models and serial numbers that are certificated in any category: (1) Group 1 (maintains the actions from AD 92-07-05): Model (i) 65–90, 65–A90, B90, C90, and C90A (ii) E90 (iii) 99, 99A, A99, A99A, B99, and C99 (iv) 100 and A100 (v) B100 (vi) 65–A90–1 (U–21A, JU–21A, RU–21D, RU–21H, RU–21A, U–21G) (vii) 65–A90–2 (RU–21B) (viii) 65–A90–3 (RU–21C) (ix) 65–A90–4 (RU–21EA, U–21H, RU–21H) (x) H90 (T–44A) (xi) 99A (FACH) (xii) A100 (U–21F)
Serial Nos. LJ–1 through LJ–1280. LW–1 through LW–347. U–1 through U–136 and U–146 through U–239. B1 through B–94, B–100 through B–204, and B– 206 through B247. BE–1 through BE–137. LM–1 through LM–141. LS–1, LS–2, and LS–3. LT–1 and LT–2. LU–1 through LU–16. LL–1 through LL–61. U–137 through U–145. B95 through B–99.
(2) Group 2: Model C90A, serial numbers LJ-1281 through LJ-1732. Unsafe Condition (d) This AD results from receiving and evaluating new service information that requires the actions of AD 92-07-05 for the added serial numbers LJ-1281 through LJ-1732 for the Model C90A airplanes. The actions specified in this AD are intended to prevent water accumulation in the rudder trim tab, which could result in a change in the mass properties and possibly a lower flutter speed of the airplane. A lower airplane flutter speed could result in failure and loss of control of the airplane.
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Compliance (e) To address this problem, you must do the following: Actions Compliance (1) For Group 1 Airplanes: Inspect Within 150 hours time-in-service the rudder trim tab for proper (TIS) after April 30, 1992 (the moisture drainage provisions. effective date of AD 92–07–05), unless already done. (2) For Group 1 Airplanes: If the Before further flight after the correct drainage provisions do not inspection required by paragraph exist, modify the rudder trim tab. (e)(1) of this AD. (3) For Group 2 Airplanes: Inspect Within 150 hours TIS after August the rudder trim tab for proper 7, 2006 (the effective date of this moisture drainage provisions. AD), unless already done.
(4) For Group 2 Airplanes: If the correct drainage provisions do not exist, modify the rudder trim tab.
Before further flight after the inspection required by paragraph (e)(3) of this AD.
Procedures Follow Beech Service Bulletin No. 2365, Revision 1, dated December 1991. Follow Beech Service Bulletin No. 2365, Revision 1, dated December 1991. Follow Raytheon Aircraft Company Service Bulletin No. SB 55–2365, Revision 2, Issued: January 1991, Revised: October 2005. Follow Raytheon Aircraft Company Service Bulletin No. SB 55–2365, Revision 2, Issued: January 1991, Revised: October 2005.
Alternative Methods of Compliance (AMOCs) (f) The Manager, Wichita Aircraft Certification Office (ACO), FAA, ATTN: Steven E. Potter, Aerospace Engineer, Wichita ACO, FAA, 1801 Airport Road, Wichita, Kansas 67209; telephone: (316) 946-4124; facsimile: (316) 946-4107, 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 92-07-05 are not approved for this AD. Material Incorporated by Reference (h) You must do the actions required by this AD following the instructions in Beechcraft Mandatory Service Bulletin No. 2365, Revision 1, dated December 1991, and Raytheon Aircraft Company Service Bulletin No. SB 55-2365, Revision 2, Issued: January 1991, Revised: October 2005. 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 Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-0085; telephone: (800) 429-5372 or (316) 676-3140. 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 PL401, Washington, DC 20590-001 or on the Internet at http://dms.dot.gov. The docket number is FAA2005-23319; Directorate Identifier 2005-CE-52-AD.
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Issued in Kansas City, Missouri, on June 13, 2006. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 06-5586 Filed 6-23-06; 8:45 am] BILLING CODE 4910-13-P
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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
2006-13-14 Bell Helicopter Textron Canada: Amendment 39-14667. Docket No. FAA-200625098; Directorate Identifier 2006-SW-12-AD. Applicability Models 222, serial number (S/N) 47006 through 47089; 222B, S/N 47131 through 47156; 222U, S/N 47501 through 47574; 230, S/N 23001 through 23038; and 430, S/N 49001 through 49105, with tail rotor counterweight bellcrank (bellcrank), part number (P/N) 222-012-727-003 or 222-012-727-105, without two prefix letters in the serial number, installed, certificated in any category. Compliance Required as indicated. To prevent bellcrank failure, loss of a weighted portion of the bellcrank, and subsequent loss of control of the helicopter, accomplish the following: (a) Within the next 10 hours time-in-service (TIS), unless done previously, and at intervals not to exceed 50 hours TIS: (1) Inspect each bellcrank for external damage, cracking, looseness, or bearing set roughness by rotating the bellcrank while applying a load to the bearing set in both axial and radial directions. (2) If a bellcrank has external damage, cracking, roughness, looseness between the bearing set and bellcrank or bearing set axial play exceeding 0.015 inch, before further flight, replace it with bellcrank, P/N 222-012-727-105, with two prefix letters in the part serial number. Note 1: The following Bell Helicopter Textron Canada Alert Service Bulletins pertain to the subject of this AD: Nos. 222-04-99, 222U-04-70, 230-04-30, and 430-04-30, all Revision C, all dated February 16, 2006; and Nos. 222-04-101, 222U-04-72, 230-04-32, and 430-04-32, all Revision B, all dated March 15, 2006. (b) Replacing each bellcrank, P/N 222-012-727-003 and P/N 222-012-727-105, without two prefix letters in the part serial number, with a bellcrank, P/N 222-012-727-105, with two prefix letters in the part serial number, is terminating action for the inspection requirements of this AD. (c) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Rotorcraft Directorate, Regulations and Guidance Group, FAA, ATTN: Sharon Miles, Aviation Safety Engineer, Fort Worth, Texas 76193-0111, telephone (817) 222-5122, fax (817) 222-5961, for information about previously approved alternative methods of compliance. (d) This amendment becomes effective on July 11, 2006. Note 2: The subject of this AD is addressed in Transport Canada (Canada) AD CF-200527R1, dated March 15, 2006. 9
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Issued in Fort Worth, Texas, on June 16, 2006. Mark R. Schilling, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 06-5651 Filed 6-23-06; 8:45 am] BILLING CODE 4910-13-P
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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
2006-13-15 Mitsubishi Heavy Industries, Ltd.: Amendment 39-14668; Docket No. FAA-200623578; Directorate Identifier 2006-CE-01-AD. Effective Date (a) This AD becomes effective on August 11, 2006. Affected ADs (b) None. Applicability (c) This AD affects the following airplane models and serial numbers that are certificated in any category: Model 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 MU–2B–60
Serial Nos. 101 through 120 (Except 102, 114, 115, and 118). 114, 115, and 118. 102, and 121 through 238. 239 through 318 (Except 313), and 313SA. 319 through 347 (Except 321), and 349SA. 321SA, 348SA, and 350SA through 394SA (Except 365SA). 502 through 547. 548 through 654 (Except 652), and 652SA. 501, and 655 through 696 (Except 661). 661SA, and 697SA through 730SA (Except 700SA). 365SA. 700SA.
Unsafe Condition (d) This AD results from a recent safety evaluation that used a data-driven approach to evaluate 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 to identify 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 cracks, corrosion, fractures, and incorrect torque values in the wing attach barrel nuts, which could result in failure of the wing attach barrel nuts and/or associated wing attachment hardware. This failure could lead to in-flight separation of the outer wing from the center wing section and result in loss of controlled flight.
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Compliance (e) To address this problem, you must do the following, unless already done: Actions (1) Remove each wing attach barrel nut, bolt, and retainer and do a visual inspection for cracks, corrosion, and fractures.
Compliance Within the next 200 hours time-in-service or 12 months after August 11, 2006 (the effective detailed date of this AD), whichever occurs first, unless already done. (2) If any signs of cracks, corrosion, or Before further flight after fractures are found on any wing attach the inspection required in barrel nut during the inspection required in paragraph (e)(1) of this paragraph (e)(1) of this AD, replace that AD, unless already done. wing attach barrel nut, bolt, and retainer with new parts and install to the correct torque value.
Procedures Follow Mitsubishi Heavy Industries, Ltd. MU–2 Service Bulletins referenced as JCAB T.C.: No. 241, dated July 14, 2004, and FAA T.C.: No. 103/57–004A, dated March 10, 2006, as applicable. Follow Mitsubishi Heavy Industries, Ltd. MU–2 Service Bulletins referenced as JCAB T.C.: No. 241, dated July 14, 2004, and FAA T.C.: No. 103/57–004A, dated March 10, 2006, as applicable, and the appropriate maintenance manual. (3) If no signs of cracks, corrosion, or Before further flight after Follow Mitsubishi Heavy fractures are found during the inspection the inspection required in Industries, Ltd. MU–2 Service required in paragraph (e)(1) of this AD, paragraph (e)(1) of this Bulletins referenced as JCAB you may reuse the wing attach barrel nuts AD, unless already done. T.C.: No. 241, dated July 14, and bolts if they have been inspected and 2004, and FAA T.C.: No. are free of deformation and irregularities 103/57–004A, dated March in the threads and meet the minimum 10, 2006, as applicable, and breakaway torque requirement. Reinstall the appropriate maintenance inspected parts to the correct torque value. manual. If the wing attach barrel nuts and bolts are not free of deformation and irregularities in the threads or do not meet the minimum breakaway torque requirement, install new parts to the correct torque value. 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 alternative methods of compliance for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information (g) Mitsubishi Heavy Industries, Ltd. MU-2 Service Bulletins JCAB T.C.: No. 241, dated July 14, 2004, and FAA T.C.: No. 103/57-004A, dated March 10, 2006, pertain to the subject of this AD.
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Material Incorporated by Reference (h) You must do the actions required by this AD following Mitsubishi Heavy Industries, Ltd. MU-2 Service Bulletins referenced as JCAB T.C.: No. 241, dated July 14, 2004, and FAA T.C.: No. 103/57-004A, pages 1 and 4 dated March 10, 2006, pages 2, 3, 5, 6, and 7 dated August 2, 2004. 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 America, Inc., 4951 Airport Parkway, Suite 800, Addison, Texas 95001; telephone: (972) 934-5480; fax: (972) 934-5488, or Turbine Aircraft Services, Inc., 4550 Jimmy Doolittle Drive, Addison, Texas 75001; telephone: (972) 248-3108; facsimile: (972) 2483321. 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-2006-23578; Directorate Identifier 2006-CE-01-AD. Issued in Kansas City, Missouri, on June 19, 2006. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 06-5653 Filed 6-28-06; 8:45 am] BILLING CODE 4910-13-P
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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
2006-14-03 Honeywell International Inc. (formerly AlliedSignal Inc., Garrett Engine Division; Garrett Turbine Engine Company; and AiResearch Manufacturing Company of Arizona): Amendment 39-14674. Docket No. FAA-2006-23704; Directorate Identifier 2006-NE-02-AD. Effective Date (a) This airworthiness directive (AD) becomes effective August 9, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Honeywell International Inc. 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 engines. These engines are installed on, but not limited to, the following aircraft: Manufacturer Aero Planes, LLC (formerly McKinnon Enterprises) Allied AG Cat Productions (formerly Schweizer) Ayres British Aerospace Ltd (formerly Jetstream) Cessna Aircraft Company Construcciones Aeronauticas, s.a. (CASA) DeHavilland Dornier Fairchild
Airplane model G–21G. G–164 series. S–2R series. 3201 series, and HP.137 Jetstream MK.1. 441 Conquest. C–212 series. DH104 series 7AXC (Dove). 228 series. SA226 AND SA227 series (Swearingen Merlin and Metro series). Grumman American G–164 series. Mitsubishi MU–2B series (MU–2 series). Pilatus PC–6 series (Fairchild Porter and Peacemaker). Polskie Zaklady Lotnicze Spolka (formerly Wytwornia PZL M18, PZL M18A, PZL M18B. Sprzetu Komunikacyjnego). Prop-Jets, Inc. 400. Raytheon Aircraft (formerly Beech) 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) Manufacturer Sikorsky
Airplane model SC7 (Skyvan) series. S–2R. 680 and 690 series. Helicopter Model S–55 series (Helitec Corp. S55T).
Unsafe Condition (d) This AD results from several reports of uncontained turbine rotor separation on engines used in special-use operations. We are issuing this AD to prevent uncontained failure of the turbine rotor due to low-cycle-fatigue (LCF), and damage to the aircraft. 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. Turbine Rotors Installed Before the Effective Date of This AD (f) For turbine rotors installed before the effective date of this AD, and currently or previously used in special-use operations: (1) Within 100 major cycles-in-service after the effective date of this AD, or upon removal of the turbine rotor(s) from the engine, whichever occurs first, do the following: (i) Determine the total equivalent cycles accrued for turbine rotors. Use paragraph 2.A. of the Accomplishment Instructions of the applicable Honeywell Alert Service Bulletin (ASB) for your model engines listed in the following Table A, to make the determination. TABLE A.—HONEYWELL ASBS FOR DETERMINING TOTAL EQUIVALENT CYCLES For engines Use ASB No. Turbine rotor removal schedule (A) TPE331–1 through –6 series TPE331–A72–2111, dated Use ASB Table 1. and TSE331–3U model. November 12, 2002 (B) TPE331–8 through –9 series TPE331–A72–2123, dated February Use ASB table 1. 8, 2006 (C) TPE331–10 through–11 series TPE331–A72–2130, dated Use ASB Table 1. September 27, 2005 (D) TPE331–12 series TPE331–A72–2131, dated Use ASB Table 1. September 27, 2005 (ii) If you are unable to determine equivalent cycles for prior special-use operations due to the absence of actual data regarding the number of takeoffs and landings per major cycle, you must use a onetime ratio of six takeoffs and landings per major cycle to estimate prior special-use equivalent cycles for each turbine rotor. (iii) For each turbine rotor affected on the Life Limited Part Log Card, record the total equivalent cycles accrued, as determined in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD, by complying with the recording requirements for your model engine listed in the following Table B:
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TABLE B.—SERVICE BULLETINS (SBS) FOR RECORDING TOTAL EQUIVALENT CYCLES For engines Record using (A) TPE331–1 through –6 series and Honeywell SB No. TPE/TSE331–72–0019, Revision 22, TSE331–3U model dated May 16, 2001. (B) TPE331–8 through –9 series AlliedSignal SB No. TPE331–72–0117, Revision 11, dated November 13, 1997. (C) TPE331–10 through –11 series Honeywell SB No. TPE331–72–0180, Revision 31, dated November 7, 2003. (D) TPE331–12 series Honeywell SB No. TPE331–72–0476, Revision 27, dated September 17, 2003. (2) Remove from service turbine rotors affected by paragraph (f) of this AD using the applicable Turbine Rotor Removal Schedule in Table A of this AD, or, within nine months after the effective date of this AD, whichever occurs later. Used Turbine Rotors Installed On or After the Effective Date of this AD (g) For used turbine rotors installed on or after the effective date of this AD, and currently or previously used in special-use operations: (1) Before further flight, determine and record total equivalent cycles using paragraphs (f)(1)(i) through (f)(1)(iii) of this AD. (2) Remove from service, turbine rotors affected by paragraph (g) of this AD using the applicable Turbine Rotor Removal Schedule in Table A of this AD. New (Zero Cycles) Turbine Rotors Installed On or After the Effective Date of This AD (h) For all new (zero cycles) turbine rotors installed on or after the effective date of this AD used in special-use operations: (1) Use the new counting method by counting and recording minor and major cycles when accrued, and determine equivalent cycles by the method described in paragraphs (f)(1)(i) and (f)(1)(iii) of this AD. (2) Using the ratio of six takeoffs and landings per major cycle for unknown cycle history, as referenced in paragraph (f)(1)(ii) of this AD, is not permitted. Definitions (i) An engine used in special-use operations is defined as an engine that accrues major and minor cycles and is installed in an aircraft that makes multiple takeoffs and landings without engine shutdown. (j) Total equivalent cycles, is that combination of major and minor cycles as specified in the Honeywell ASBs listed in Table A of this AD. (k) Total equivalent cycle life limits listed in the ASBs, are the cycle life limits specified in the SBs listed in Table B of this AD. (l) The ''recording of total equivalent cycles on the Life Limited Part Log Card'' is that same procedure specified for ''accumulated cycles'' or ''total cycles'' in the SBs listed in Table B of this AD. 16
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(m) ''Turbine rotors'' include first, second, and third stage seal plates, air seals, rotor disks, wheels, and assemblies, and are parts that have part numbers specified in the ASBs listed in Table A of this AD. (n) A major cycle is an engine start, takeoff, landing, and shutdown. (o) A minor cycle, which occurs within a major cycle, is an additional landing with an engine speed reduction to ground idle with no engine shutdown followed by a takeoff. (p) A ''used turbine rotor'' is a turbine rotor whose cycles-since-new are more than zero. Alternative Methods of Compliance (q) 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. Material Incorporated by Reference (r) You must use the service information specified in Table C of this AD to perform the actions required by this AD. The Director of the Federal Register approved the incorporation by reference of the documents listed in Table C of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Honeywell Engines, Systems & Services, Technical Data Distribution, M/S 2101-201, P.O. Box 52170, Phoenix, AZ 85072-2170; telephone: (602) 365-2493 (General Aviation); (602) 365-5535 (Commercial); fax: (602) 365-5577 (General Aviation and Commercial) 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. TABLE C.—INCORPORATION BY REFERENCE Service Bulletin (SB) Page Revision Honeywell SB No. TPE/TSE331–72–0019 1 22 Total Pages: 16 2–11 21 12 22 13–16 21 AlliedSignal SB No. TPE331–72–0117 1 11 Total Pages: 10 2 9 3–10 11 Honeywell SB No. TPE331–72–0180 1 31 Total Pages: 54 2–3 29 4–5 31 6–7 29 8–13 31 14 27 15–17 31 18 27 19 31 17
Date May 16, 2001. March 3, 2000. May 16, 2001. March 3, 2000. November 13, 1997. May 24, 1995. November 13, 1997. November 7, 2003. August 23, 2002. November 7, 2003. August 23, 2002. November 7, 2003. February 23, 2001. November 7, 2003. February 23, 2001. November 7, 2003. BW 2006-14
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Service Bulletin (SB) Honeywell SB No. TPE331–72–0180 (continued) Total Pages: 54
Page
Honeywell SB No. TPE331–72–0476 Total pages: 46
Alert Service Bulletin (ASB) Honeywell ASB No. TPE331–A72–2111 Total Pages: 12 Honeywell ASB No. TPE331–A72–2123 Total Pages: 12 Honeywell ASB No. TPE331–A72–2130 Total Pages: 16 Honeywell ASB No. TPE331–A72–2131 Total Pages: 14
20 21 22–24 25 26 27–54 1–2 3 4 5 6 7–14 15 16–22 23–27 28–32 33 34 35 36 37–41 42 43 44 45 46 Page ALL
Revision 29 31 29 31 29 31 27 25 27 25 27 25 26 25 27 25 26 25 27 25 27 25 27 25 27 25 Revision Original
Date August 23, 2002. November 7, 2003. August 23, 2002. November 7, 2003. August 23, 2002. November 7, 2003. September 17, 2003. May 24, 2002. September 17, 2003. May 24, 2002. September 17, 2003. May 24, 2002. July 26, 2002. May 24, 2002. September 17, 2003. May 24, 2002. July 26, 2002. May 24, 2002. September 17, 2003. May 24, 2002. September 17, 2003. May 24, 2002. September 17, 2003. May 24, 2002. September 17, 2003. May 24, 2002. Date November 12, 2002.
ALL
Original
February 8, 2006.
ALL
Original
September 27, 2005.
ALL
Original
September 27, 2005.
Issued in Burlington, Massachusetts, on June 26, 2006. Francis A. Favara, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 06-5929 Filed 7-3-06; 8:45 am] BILLING CODE 4910-13-P
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