FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS BIWEEKLY

Transcription

1 FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS BIWEEKLY 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 Oklahoma City, OK FAX

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3 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 Engine Components Inc. Appliance: See AD DG Flugzeugbau GmbH Sailplane: DG-800B and DG-500MB S Burkhardt Grob Luft-Und Raumfahrt Gmbh & Co Kg Sailplane: G103 Twin Astir, G103 Twin II, G103A Twin 11 Acro, G103C Twin III Acro, and G 103 Twin III SL S Turbomeca Engine: Artouste III B, B1, and D turboshaft Burkhardt Grob Luft-Und Sailplane: G103 Twin Astir Raumfahrt Gmbh & Co Kg E Pacific Aerospace Corporation 750XL Biweekly R1 R Turbomeca S.A. Engine: Arrius Models 2B, 2B1, and 2F American Champion Aircraft Corp. 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 Pacific Aerospace Corporation 750XL Ltd S Honeywell International Inc. 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 Cessna 208 and 208B E Raytheon 390 Biweekly Turbomeca Engine: Arriel 1B, 1D, 1D1, and 1S DG Flugzeugbau GmbH and Glaser-Dirks Flugzeugbau GmbH Sailplane: DG 100, DG 400, DG 500 Elan Series, and DG 500M FR Raytheon 390 Biweekly COR Glaser-Dirks Flugzeugbau Sailplane: DG-100, DC-400, DG-500 Elan, and DG-500M GmbH Aero Advantage Appliance: Vacuum Pumps Polskie Zaklady Lotnicze PZL M26 01 Biweekly Turbomeca Engine: Turbomeca Artouste III B, Artouste III B1, and Artouste III D turboshaft Biweekly R1 R Cessna 208 and 208B MT-Propeller Entwicklung GmbH Propeller: MT, MTV-1, MTV-2, MTV-3, MTV-5, MTV-6, MTV- 7, 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 Eurocopter France Rotorcraft: EC 155B and B Eurocopter France Rotorcraft: SA-365N, SA365N1, AS-365N2, and SA-366G S Cessna 208 and 208B E General Electric Engine: CT7-8A 3

4 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 COR GROB-WERKE G120A Lycoming Engines 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 C1D Turbomeca Engine: Arriel 1B, 1D, and 1D1 certain turboshaft Cirrus Design Corporation SR20, SR22 Biweekly COR Cessna 208 and 208B S S 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 Turbomeca Engine: Makila 1 A2 turboshaft S BURKHART GROB LUFT- Sailplane:G 103 C Twin III SL UND RAUMFAHRT GMBH & CO. KG Eurocopter France Rotorcraft: SA-360C, SA-365C, SA-365C1, and SA-365C2 Biweekly R1 R Air Tractor AT FR General Electric Engine: CT7-8A COR S 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 Brantly Helicopter Rotorcraft: B-2, B-2A, and B-2B Air Tractor AT-400, AT-401, AT-401B, AT-402, AT-402A, and AT-402B Air Tractor AT-802A Pilatus PC-12 and PC-12/ S MD Helicopters Rotorcraft: 600N Pratt & Whitney Canada Engine: PW535A Biweekly R1 COR Air Tractor AT-501 R COR Air Tractor AT-400, AT-401, AT-401B, AT-402, AT-402A, and AT-402B COR Air Tractor AT-802 and AT-802A Eurocopter France Rotorcraft: SA-365 N1, AS-365 N2, N3, SA 366 G1, and EC-155B and B1 Biweekly R1 COR Cessna 208 and 208B R COR Cessna 208 and 208B S Engine Components Inc. Appliance: See AD 4

5 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 R1 R Eurocopter France Rotorcraft: AS355E, F, F1, F2, and N Sikorsky Rotorcraft: S-92A S Honeywell International Inc. Engine: T5311A, T5311B, T5313B, T5317A, T5317A-1, and T5317B series, T53-L-11B, T53-L-11D, T53-L-13B, T53-L- 13B/D, and T53-L-703 series turboshaft Eurocopter France Rotorcraft: AS350B, BA, B1, B2, B3, C, D, and D Pacific Aerospace Corporation 750XL Ltd DORNIER LUFTFAHRT , , , , , and GmbH S Engine Components Inc. Appliance: See AD Biweekly R1 R 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, PC- 6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H Eurocopter France Rotocraft: EC130 B COR Engine Components Inc. Appliance: See AD General Machine - Diecron, Inc. Appliance: Actuator Nut Assembly S Pacific Aerospace Corp. Ltd. 750XL Rolls-Royce Corp. 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 S 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, PC- 6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H S 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, PC- 6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 Biweekly S Raytheon Aircraft Company See AD Bell Helicopter Textron Rotorcraft: 222, 222B, 222U, 230 and Mitsubishi Heavy Industries 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 Honeywell International Inc. 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 5

6 AIRWORTHINESS DIRECTIVE U.S. Department of Transportation Federal Aviation Administration Raytheon Aircraft Company (Formerly Beech): Amendment ; Docket No. FAA ; Directorate Identifier 2005-CE-52-AD. Effective Date Affected ADs Applicability (a) This AD becomes effective on August 7, (b) This AD supersedes AD ; Amendment (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 ): Model Serial Nos. (i) 65 90, 65 A90, B90, C90, and C90A LJ 1 through LJ (ii) E90 LW 1 through LW 347. (iii) 99, 99A, A99, A99A, B99, and C99 U 1 through U 136 and U 146 through U 239. (iv) 100 and A100 B1 through B 94, B 100 through B 204, and B 206 through B247. (v) B100 BE 1 through BE 137. (vi) 65 A90 1 (U 21A, JU 21A, RU 21D, LM 1 through LM 141. RU 21H, RU 21A, U 21G) (vii) 65 A90 2 (RU 21B) LS 1, LS 2, and LS 3. (viii) 65 A90 3 (RU 21C) LT 1 and LT 2. (ix) 65 A90 4 (RU 21EA, U 21H, RU 21H) LU 1 through LU 16. (x) H90 (T 44A) LL 1 through LL 61. (xi) 99A (FACH) U 137 through U 145. (xii) A100 (U 21F) B95 through B 99. (2) Group 2: Model C90A, serial numbers LJ-1281 through LJ Unsafe Condition (d) This AD results from receiving and evaluating new service information that requires the actions of AD 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. 6 BW

7 Compliance (e) To address this problem, you must do the following: Actions Compliance Procedures Within 150 hours time-in-service (TIS) after April 30, 1992 (the effective date of AD ), unless already done. (1) For Group 1 Airplanes: Inspect the rudder trim tab for proper moisture drainage provisions. (2) For Group 1 Airplanes: If the correct drainage provisions do not exist, modify the rudder trim tab. (3) For Group 2 Airplanes: Inspect the rudder trim tab for proper moisture drainage provisions. (4) For Group 2 Airplanes: If the correct drainage provisions do not exist, modify the rudder trim tab. Alternative Methods of Compliance (AMOCs) Before further flight after the inspection required by paragraph (e)(1) of this AD. Within 150 hours TIS after August 7, 2006 (the effective date of this AD), unless already done. Before further flight after the inspection required by paragraph (e)(3) of this AD. Follow Beech Service Bulletin No. 2365, Revision 1, dated December Follow Beech Service Bulletin No. 2365, Revision 1, dated December Follow Raytheon Aircraft Company Service Bulletin No. SB , Revision 2, Issued: January 1991, Revised: October Follow Raytheon Aircraft Company Service Bulletin No. SB , Revision 2, Issued: January 1991, Revised: October (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) ; facsimile: (316) , has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR (g) AMOCs approved for AD 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 , Revision 2, Issued: January 1991, Revised: October 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 ; telephone: (800) or (316) 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: ibr_locations.html or call (202) 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 or on the Internet at The docket number is FAA ; Directorate Identifier 2005-CE-52-AD. 7 BW

8 Issued in Kansas City, Missouri, on June 13, James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc Filed ; 8:45 am] BILLING CODE P 8 BW

9 AIRWORTHINESS DIRECTIVE U.S. Department of Transportation Federal Aviation Administration Bell Helicopter Textron Canada: Amendment Docket No. FAA ; Directorate Identifier 2006-SW-12-AD. Applicability Models 222, serial number (S/N) through 47089; 222B, S/N through 47156; 222U, S/N through 47574; 230, S/N through 23038; and 430, S/N through 49105, with tail rotor counterweight bellcrank (bellcrank), part number (P/N) or , 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 inch, before further flight, replace it with bellcrank, P/N , 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 , 222U-04-70, , and , all Revision C, all dated February 16, 2006; and Nos , 222U-04-72, , and , all Revision B, all dated March 15, (b) Replacing each bellcrank, P/N and P/N , without two prefix letters in the part serial number, with a bellcrank, P/N , 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 Contact the Manager, Rotorcraft Directorate, Regulations and Guidance Group, FAA, ATTN: Sharon Miles, Aviation Safety Engineer, Fort Worth, Texas , telephone (817) , fax (817) , for information about previously approved alternative methods of compliance. (d) This amendment becomes effective on July 11, Note 2: The subject of this AD is addressed in Transport Canada (Canada) AD CF R1, dated March 15, BW

10 Issued in Fort Worth, Texas, on June 16, Mark R. Schilling, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc Filed ; 8:45 am] BILLING CODE P 10 BW

11 AIRWORTHINESS DIRECTIVE U.S. Department of Transportation Federal Aviation Administration Mitsubishi Heavy Industries, Ltd.: Amendment ; Docket No. FAA ; Directorate Identifier 2006-CE-01-AD. Effective Date Affected ADs (a) This AD becomes effective on August 11, (b) None. Applicability (c) This AD affects the following airplane models and serial numbers that are certificated in any category: Model Serial Nos. MU 2B through 120 (Except 102, 114, 115, and 118). MU 2B , 115, and 118. MU 2B , and 121 through 238. MU 2B through 318 (Except 313), and 313SA. MU 2B through 347 (Except 321), and 349SA. MU 2B 26A 321SA, 348SA, and 350SA through 394SA (Except 365SA). MU 2B through 547. MU 2B through 654 (Except 652), and 652SA. MU 2B , and 655 through 696 (Except 661). MU 2B 36A 661SA, and 697SA through 730SA (Except 700SA). MU 2B SA. MU 2B SA. 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. 11 BW

12 Compliance (e) To address this problem, you must do the following, unless already done: Actions Compliance Procedures 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. 10, 2006, as applicable. (1) Remove each wing attach barrel nut, bolt, and retainer and do a visual inspection for cracks, corrosion, and fractures. (2) If any signs of cracks, corrosion, or fractures are found on any wing attach barrel nut during the inspection required in paragraph (e)(1) of this AD, replace that wing attach barrel nut, bolt, and retainer with new parts and install to the correct torque value. (3) If no signs of cracks, corrosion, or fractures are found during the inspection required in paragraph (e)(1) of this AD, you may reuse the wing attach barrel nuts and bolts if they have been inspected and are free of deformation and irregularities in the threads and meet the minimum breakaway torque requirement. Reinstall inspected parts to the correct torque value. 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) Before further flight after the inspection required in paragraph (e)(1) of this AD, unless already done. Before further flight after the inspection required in paragraph (e)(1) of this AD, unless already done. 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 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. 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. (f) The Manager, Fort Worth Airplane Certification Office, FAA, ATTN: Andrew McAnaul, Aerospace Engineer, ASW-150 (c/o MIDO-43), Reunion Place, Suite 650, San Antonio, Texas 78216; telephone: (210) ; facsimile: (210) , has the authority to approve alternative methods of compliance for this AD, if requested using the procedures found in 14 CFR 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. 12 BW

13 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, 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) ; fax: (972) , or Turbine Aircraft Services, Inc., 4550 Jimmy Doolittle Drive, Addison, Texas 75001; telephone: (972) ; facsimile: (972) 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: or call (202) 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 or on the Internet at The docket number is FAA ; Directorate Identifier 2006-CE-01-AD. Issued in Kansas City, Missouri, on June 19, James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc Filed ; 8:45 am] BILLING CODE P 13 BW

14 AIRWORTHINESS DIRECTIVE U.S. Department of Transportation Federal Aviation Administration Honeywell International Inc. (formerly AlliedSignal Inc., Garrett Engine Division; Garrett Turbine Engine Company; and AiResearch Manufacturing Company of Arizona): Amendment Docket No. FAA ; Directorate Identifier 2006-NE-02-AD. Effective Date Affected ADs (a) This airworthiness directive (AD) becomes effective August 9, (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 Airplane model Aero Planes, LLC (formerly McKinnon Enterprises) G 21G. Allied AG Cat Productions (formerly Schweizer) G 164 series. Ayres S 2R series. British Aerospace Ltd (formerly Jetstream) 3201 series, and HP.137 Jetstream MK.1. Cessna Aircraft Company 441 Conquest. Construcciones Aeronauticas, s.a. (CASA) C 212 series. DeHavilland DH104 series 7AXC (Dove). Dornier 228 series. Fairchild 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 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 E BW

15 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 A , dated Use ASB Table 1. and TSE331 3U model. November 12, 2002 (B) TPE331 8 through 9 series TPE331 A , dated February Use ASB table 1. 8, 2006 (C) TPE through 11 series TPE331 A , dated Use ASB Table 1. September 27, 2005 (D) TPE series TPE331 A , dated September 27, 2005 Use ASB Table 1. (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: 15 BW

16 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/TSE , Revision 22, TSE331 3U model dated May 16, (B) TPE331 8 through 9 series AlliedSignal SB No. TPE , Revision 11, dated November 13, (C) TPE through 11 series Honeywell SB No. TPE , Revision 31, dated November 7, (D) TPE series Honeywell SB No. TPE , Revision 27, dated September 17, (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 BW

17 (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 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 , P.O. Box 52170, Phoenix, AZ ; telephone: (602) (General Aviation); (602) (Commercial); fax: (602) (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 , or go to: TABLE C. INCORPORATION BY REFERENCE Service Bulletin (SB) Page Revision Date 1 22 May 16, March 3, May 16, Honeywell SB No. TPE/TSE Total Pages: 16 AlliedSignal SB No. TPE Total Pages: 10 Honeywell SB No. TPE Total Pages: March 3, November 13, May 24, November 13, November 7, August 23, November 7, August 23, November 7, February 23, November 7, February 23, November 7, BW

18 Service Bulletin (SB) Page Revision Date August 23, November 7, August 23, November 7, August 23, Honeywell SB No. TPE (continued) Total Pages: 54 Honeywell SB No. TPE Total pages: November 7, September 17, May 24, September 17, May 24, September 17, May 24, July 26, May 24, September 17, May 24, July 26, May 24, September 17, May 24, September 17, May 24, September 17, May 24, September 17, May 24, Alert Service Bulletin (ASB) Page Revision Date Honeywell ASB No. TPE331 A ALL Original November 12, Total Pages: 12 Honeywell ASB No. TPE331 A ALL Original February 8, Total Pages: 12 Honeywell ASB No. TPE331 A ALL Original September 27, Total Pages: 16 Honeywell ASB No. TPE331 A Total Pages: 14 ALL Original September 27, Issued in Burlington, Massachusetts, on June 26, Francis A. Favara, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc Filed ; 8:45 am] BILLING CODE P 18 BW