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Web site: htt p : / /p o rta l

. h o n eywe l l

. co m/ w ps/p o rta l/ae ro 

# SERVICE BULLETIN ALERT

ENGINE - TURBINE SECTION - Inspect Specific Serial Number First Stage Turbine Disks, PN 3101520-1 and PN 3107079-1 (Part of First Stage Turbine Rotor Assembly, PN 3101603-1, or PN 3101603-8, or PN 3101603-10, or PN 3101603-12, or PN 3108164-1, or PN 3108164-2) Legal Notice
NOTICE: This is a CATEGORY 1, SAFETY service bulletin. Export Control This document contains technical data and is subject to U.S. export regulations. These commodities, technology, or software were exported from the United States in accordance with the export administration regulations. Diversion contrary to U.S. law is prohibited. ECCN: EAR99, NLR Eligible. Proprietary Information Honeywell - Confidential THIS DOCUMENT AND ALL INFORMATION AND EXPRESSION CONTAINED HEREIN ARE THE PROPERTY OF HONEYWELL INTERNATIONAL INC., ARE PROVIDED IN CONFIDENCE, AND MAY BE USED BY PERSONS REQUIRED BY FEDERAL AVIATION REGULATION PART 21.50 TO COMPLY WITH ANY OF THE TERMS OF THESE INSTRUCTIONS. EXCEPT AS SET FORTH ABOVE, NO PERSON MAY, IN WHOLE OR IN PART, USE, DUPLICATE OR DISCLOSE THIS INFORMATION FOR ANY PURPOSE WITHOUT THE PRIOR WRITTEN PERMISSION OF HONEYWELL INTERNATIONAL INC.

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Honeywell Materials License Agreement The documents and information contained herein ("the Materials") are the proprietary data of Honeywell International Inc. and Honeywell Intellectual Properties Inc. (collectively "Honeywell"). These Materials are provided for the exclusive use of Honeywell Service Centers; Honeywell-authorized repair facilities; operators of Honeywell aerospace products subject to an applicable product support agreement, their wholly owned-subsidiaries or a formally designated third party service provider; and direct recipients of Materials from Honeywell’s Aerospace Technical Publication Distribution. The terms and conditions of this License Agreement govern your use of these Materials, except to the extent that any terms and conditions of another applicable agreement with Honeywell regarding the operation, maintenance, or repair of Honeywell aerospace products conflict with the terms and conditions of this License Agreement, in which case the terms and conditions of the other agreement will govern. However, this License Agreement will govern in the event of a conflict between its terms and conditions and those of a purchase order or acknowledgement. 1. License Grant - If you are a party to an applicable product support agreement, a Honeywell Service Center agreement, or an authorized repair facility agreement, Honeywell hereby grants you a limited, non-exclusive license to use these Materials to operate, maintain, or repair Honeywell aerospace products only in accordance with that agreement. If you are a direct recipient of these Materials from Honeywell’s Aerospace Technical Publication Distribution and are not a party to an agreement related to the operation, maintenance or repair of Honeywell aerospace products, Honeywell hereby grants you a limited, non-exclusive license to use these Materials to maintain or repair the subject Honeywell aerospace products only at the facility to which these Materials have been shipped ("the Licensed Facility"). Transfer of the Materials to another facility owned by you is permitted only if the original Licensed Facility retains no copies of the Materials and you provide prior written notice to Honeywell. 2. Rights In Materials - Honeywell retains all rights in these Materials and in any copies thereof that are not expressly granted to you, including all rights in patents, copyrights, trademarks, and trade secrets. No license to use any Honeywell trademarks or patents is granted under this License Agreement. 3. Confidentiality - You acknowledge that these Materials contain information that is confidential and proprietary to Honeywell. You agree to take all reasonable efforts to maintain the confidentiality of these Materials. 4. Assignment And Transfer - This License Agreement may be assigned to a formally designated service designee or transferred to a subsequent owner or operator of an aircraft containing the subject Honeywell aerospace products. However, the recipient of any such assignment or transfer must assume all of your obligations under this License Agreement. No assignment or transfer shall relieve any party of any obligation that such party then has hereunder. 5. Copies of Materials - Unless you have the express written permission of Honeywell, you may not make or permit making of copies of the Materials. Notwithstanding the foregoing, you may make copies of only portions of the Material for your internal use. You agree to return the Materials and any copies thereof to Honeywell upon the request of Honeywell. 6. Term - This License Agreement is effective until terminated as set forth herein. This License Agreement will terminate immediately, without notice from Honeywell, if you fail to comply with any provision of this License Agreement or will terminate simultaneously with the termination or expiration of your applicable product support agreement, authorized repair facility agreement, or your formal designation as a third party service provider. Upon termination of this License Agreement, you will return these Materials to Honeywell without retaining any copies and will have one of your authorized officers certify that all Materials have been returned with no copies retained. 7. Remedies - Honeywell reserves the right to pursue all available remedies and damages resulting from a breach of this License Agreement. 8. Limitation of Liability - Honeywell does not make any representation regarding the use or sufficiency of the Materials. THERE ARE NO OTHER WARRANTIES, WHETHER WRITTEN OR ORAL, EXPRESS, IMPLIED OR STATUTORY, INCLUDING, BUT NOT LIMITED TO , (i) WARRANTIES ARISING FROM COURSE OF

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PERFORMANCE, DEALING, USAGE, OR TRADE, WHICH ARE HEREBY EXPRESSLY DISCLAIMED, OR (ii) WARRANTIES AGAINST INFRINGEMENT OF INTELLECTUAL PROPERTY RIGHTS OF THIRD PARTIES, EVEN IF HONEYWELL HAS BEEN ADVISED OF ANY SUCH INFRINGEMENT. IN NO EVENT WILL HONEYWELL BE LIABLE FOR ANY INCIDENTAL DA MAGES, CONSEQUENTIAL DAMAGES, SPECIAL DAMAGES, INDIRECT DAMAGES, LOSS OF PROFITS, LOSS OF REVENUES, OR LOSS OF USE, EVEN IF INFORMED OF THE POSSIBILITY OF SUCH DAMAGES. TO THE EXTENT PERMITTED BY APPLICABLE LAW, THESE LIMITATIONS AND EXCLUSIONS WILL APPLY REGARDLESS OF WHETHER LIABILITY ARISES FROM BREACH OF CONTRACT, WARRANTY, TORT (INCLUDING BUT NOT LIMITED TO NEGLIGENCE), BY OPERATION OF LAW, OR OTHERWISE. 9. Controlling Law - This License shall be governed and construed in accordance with the laws of the State of New York without regard to the conflicts of laws provisions thereof. This license sets forth the entire agreement between you and Honeywell and may only be modified by a writing duly executed by the duly authorized representatives of the parties. Safety Advisory WARNING: BEFORE THE MATERIALS CALLED OUT IN THIS PUBLICATION ARE USED, KNOW THE HANDLING, STORAGE AND DISPOSAL PRECAUTIONS RECOMMENDED BY THE MANUFACTURER OR SUPPLIER. FAILURE TO OBEY THE MANUFACTURERS’ OR SUPPLIERS’ RECOMMENDATIONS CAN RESULT IN PERSONAL INJURY OR DISEASE. This publication describes physical and chemical processes which can make it necessary to use chemicals, solvents, paints, and other commercially available materials. The user of this publication must get the Material Safety Data Sheets (OSHA Form 174 or equivalent) from the manufacturers or suppliers of the materials to be used. The user must know the manufacturer/ supplier data and obey the procedures, recommendations, warnings and cautions set forth for the safe use, handling, storage, and disposal of the materials. Warranty/Liability Advisory WARNING: HONEYWELL ASSUMES NO RESPONSIBILITY FOR ANY HONEYWELL EQUIPMENT WHICH IS NOT MAINTAINED AND/OR REPAIRED IN ACCORDANCE WITH HONEYWELL’S PUBLISHED INSTRUCTIONS AND/OR HONEYWELL’S FAA/SFAR 36 REPAIR AUTHORIZATION. NEITHER DOES HONEYWELL ASSUME RESPONSIBILITY FOR SPECIAL TOOLS AND TEST EQUIPMENT FABRICATED BY COMPANIES OTHER THAN HONEYWELL. WARNING: INCORRECTLY REPAIRED COMPONENTS CAN AFFECT AIRWORTHINESS OR DECREASE THE LIFE OF THE COMPONENTS. INCORRECTLY FABRICATED SPECIAL TOOLING OR TEST EQUIPMENT CAN RESULT IN DAMAGE TO THE PRODUCT COMPONENTS OR GIVE UNSATISFACTORY RESULTS. 

## Copyright - Notice Copyright 2008 Honeywell International Inc. All rights reserved. Honeywell is a registered trademark of Honeywell International Inc. All other marks are owned by their respective companies.

THIS IS THE SB FOSI - DATE: 20080902, VERSION 0017A (HT)

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Transmittal Information ATA Number TPE331-72-A2156 (Publication Number D200808000053) Summary This is the INITIAL release. Revision History This service bulletin has had no revision(s) as shown in Table 1. Table 1. Revision History Revision Number Revision Date Initial Release 2 Dec 2008

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1. P l a n n i n g I n fo r m at i o n A. Effectivity (1) This is a CATEGORY 1, SAFETY service bulletin. (2) This service bulletin is applicable to the first stage turbine disks shown in Table 2. Table 2. Applicable Component(s) PN Serial Number 3101520-1, 3107079-1 1-03501-4275 thru 1-03501-4306 inclusive 1-03501-4308 thru 1-03501-4339 inclusive 1-03501-4341 thru 1-03501-4438 inclusive 1-03501-4440 thru 1-03501-4471 inclusive 1-03501-4473 thru 1-03501-4504 inclusive 1-03501-4506 thru 1-03501-4537 inclusive 1-03501-4539 thru 1-03501-4570 inclusive 1-03501-4572 thru 1-03501-4599 inclusive 2-03501-2260 thru 2-03501-2272 inclusive 2-03501-2274 thru 2-03501-2298 inclusive (3) The component(s) shown in Table 2 are used on turboprop aircraft engines. This service bulletin is applicable to the serial numbers shown in Table 3. Table 3. Applicable Engine(s)

PN Model Number Serial Number Application 3102170-1, -2 TPE331-10-501C All CASA 212-200 3102170-5 TPE331-10-511C All CASA 212-200 3102190-1 TPE331-10-501K All Jetprop Commander 695/695A/695B 3102190-2 TPE331-10-511K All Jetprop Commander 695/695A/695B 3102180-1 TPE331-10-501M All Mitsubishi Marquise/Solitaire 3102180-2 TPE331-10-511M All Mitsubishi Marquise/Solitaire 3108150-1 TPE331-10AV-511B All Beech B100 3108200-1 TPE331-10AV-511M All Mitsubishi MU-2J/-2K/-2L/-2M 3108240-1 TPE331-10AV-511KA All Beech C90/E90 3108140-2 TPE331-10GP-511D All Dornier 228 3108140-1 TPE331-10GT-511D All Dornier 228 3103700-1 TPE331-10N-511S All Conquest II 3103700-2 TPE331-10N-512S All Conquest II

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Table 3. Applicable Engine(s) (Cont)

PN Model Number Serial Number Application 3103700-3 TPE331-10N-513S All Conquest II 3103700-4 TPE331-10N-514S All Conquest II 3103700-5 TPE331-10N-515S All Conquest II 3103700-6 TPE331-10N-531S All Conquest II 3103700-7 TPE331-10N-532S All Conquest II 3103700-8 TPE331-10N-533S All Conquest II 3103700-9 TPE331-10N-534S All Conquest II 310370 0-10 TPE331 -10N-535S All Conque st II 3108130-2 TPE331-10P-511D All Dornier 228 3102170-3 TPE331-10R-501C All CASA 212-200 3102170-4 TPE331-10R-502C All CASA 212-200 3102170-6 TPE331-10R-511C All CASA 212-200 3102170-7 TPE331-10R-512C All CASA 212-200 3102170-8 TPE331-10R-513C All CASA 212-200/-300 3108130-1 TPE331-10T-511D All Dornier 228 3108110-1 TPE331-10T-511K All Jetprop Commander 690C/690D 3108190-1 TPE331-10T-511M All Mitsubishi MU-2N/-2P 3108110-2 TPE331-10T-512K All Jetprop Commander 690B 3108110-3 TPE331-10T-513K All Jetprop Commander 690C/690D 3108120-1 TPE331-10T-515K All Jetprop Commander 690A/690B 3108120-2 TPE331-10T-516K All Jetprop Commander 690A/690B 3108120-3 TPE331-10T-517K All No Current Application 3102050-1, -2 TPE331-10U-501G All Merlin IIIB 3102050-3 TPE331-10U-502G All Merlin IIIB 3102050-4 TPE331-10U-511G All Merlin IIIB 3102050-5 TPE331-10U-512G All Merlin IIIB 3102940-1 TPE331-10U-503G All Merlin IIIC 3102940-2 TPE331-10U-513G All Merlin IIIC

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Table 3. Applicable Engine(s) (Cont)

PN Model Number Serial Number Application 3103230-1 TPE331-10UA-511G All Merlin III/IIIA/IV/IVA/ Metro/Metro II/Metro IIA 3102600-1 TPE331-10UF-501H All Jetstream 31 3102600-2 TPE331-10UF-511H All Jetstream 31 3102600-5 TPE331-10UF-512H All Jetstream 31 3102600-6 TPE331-10UF-513H All Jetstream 31 3102600-9 TPE331-10UF-514H All Jetstream 31 3102600-10 TPE331-10UF-515H All Jetstream 31 3102600-11 TPE331-10UF-516H All Jetstream 31 3103310-1 TPE331-10UG-513H All Jetstream 31 3103310-3 TPE331-10UG-514H All Jetstream 31 3103310-5 TPE331-10UG-515H All Jetstream 31 3103310-7 TPE331-10UG-516H All Jetstream 31 3103310-2 TPE331-10UGR-513H All Jetstream 31 3103310-4 TPE331-10UGR-514H All Jetstream 31 3103310-6 TPE331-10UGR-515H All Jetstream 31 3103310-8 TPE331-10UGR-516H All Jetstream 31 3102600-7 TPE331-10UR-513H All Jetstream 31 3102600-12 TPE331-10UR-516H All Jetstream 31 3102540-1, -5, -9 TPE331-11U-601G All Metro III/23/Merlin IVC 3102540-2 TPE331-11U-602G All Metro III/23/Merlin IVC 3102540-3, -6, -7, -10 TPE331-11U-611G All Metro III/23/Merlin IVC 3102540-4, -8, -11 TPE331-11U-612G All Metro III/23/Merlin IVC B. Concurrent Requirements (1) Review of the service bulletin(s) listed in Table 4 should be accomplished by the operator for possible incorporation at the time this service bulletin is accomplished.

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Table 4. Optional Service Bulletin(s) Service Bulletin Number Service Bulletin Title TPE331-72-0180 ENGINE - Service Life Limits Of Critical Life Limited Components and Periodic Maintenance Schedules TPE331-A72-2102 ENGINE - TURBINE SECTION - Inspect Specific Serial Number First Stage Turbine Disks, Part No. 3101520-1 and 3107079-1 (Part of First Stage Turbine Rotor Assembly, Part No. 3101603-1, or 3101603-8, or 3101603-10, or 3101603-12, or 3108164-1, or 3108164-2) TPE331-A72-2130 ENGINE - SERVICE LIFE - Service Life Limits of Critical Life Limited Components - Special Use Operation - Partial Cycle Counting TPE331-72-A2150 ENGINE - TURBINE SECTION - Remove from Service Specific Serial Number First Stage Turbine Disks, PN 3101520-1 and PN 3107079-1 (Part of First Stage Turbine Rotor Assembly, PN 3101603-1, -8, -10, -12, or PN 3108164-1, -2)
W

A R N I N G : UNCONTAINED TURBINE DISK SEPARATION CAN RESULT IN THE RELEASE OF METAL FRAGMENTS THAT CAN CAUSE SEVERE PERSONAL INJURY AND/OR DEATH, AND DAMAGE TO OR LOSS OF THE AIRCRAFT. C. Reason (1) Problem: The forging alloy melting process may have resulted in alloy depleted regions (white spots) in the material used in first stage turbine disks. These alloy depleted regions, if present in the first stage turbine disk, PN 3101520-1 or PN 3107079-1, may lead to a crack in service and result in an uncontained turbine disk separation and/or engine shutdown. Uncontained turbine disk separation can result in the release of metal fragments. N OT E : First stage turbine disks, PN 3101520-1 and PN 3107079-1 are components of the first stage turbine disk rotor assembly, PN 3101603-1, -8, -10, -12, or PN 3108164-1, -2. (2) Background: Service Bulletin TPE331-72-A2150 addresses the identification and disposition of first stage turbine disks that may contain oxide inclusions which were caused by the forging alloy melting process. Other first stage turbine disks in this particular material lot (reference TPE331-72-A2150) may be affected with alloy depleted regions (white spots) in the material. Suspect turbine disks are identified as either PN 3101520-1 or PN 3107079-1 (converted from PN 3101520-1) with the serial numbers listed in Table 2. (3) Action: The engine manufacturer recommends that disks from the subject forging lot be subjected to additional in-service inspections as specified in Paragraph 1.E. and Paragraph 3 of this service bulletin. D. Description (1) This service bulletin provides requirements, authorization, and additional in-service inspections of first stage turbine disks, PN 3101520-1 and PN 3107079-1 from the suspect forging lot. Refer to serial numbers in Table 2.

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E. Compliance (1) This is a CATEGORY 1, SAFETY service bulletin. N OT E : The procedures outlined in this service bulletin may be accomplished at the Major Service Center level or greater. (2) The warranty/program data is listed in Table 5. Table 5. Warranty/Program Data Warranty/Program Yes No MSP X Warranty/Special Program X (3) Honeywell recommends that this service bulletin be complied with in accordance with the following schedule: (a) For uninstalled first stage turbine disks, PN 3101520-1 and PN 3107079-1, with serial numbers listed in Table 2, inspect in accordance with Paragraph 3 prior to installation in an engine. Repeat inspection in accordance with Paragraph 3 at each individual hot section inspection thereafter until the disk is retired from service. (b) For installed first stage turbine disks, PN 3101520-1 and PN 3107079-1, with serial numbers listed in Table 2, which have less than or equal to 4100 cycles since new, inspect in accordance with Paragraph 3 at next access, but not later than 4500 cycles since new. Repeat inspection in accordance with Paragraph 3 at scheduled hot section inspection thereafter until the disk is retired from service. (c) For installed first stage turbine disks, PN 3101520-1 and PN 3107079-1, with serial numbers listed in Table 2, which have more than 4100 cycles since new, inspect in accordance with Paragraph 3 at next access, but not later than 400 additional cycles after receipt of this service bulletin. Repeat inspection in accordance with Paragraph 3 at each scheduled hot section inspection thereafter until the disk is retired from service. F. Approval (1) The accomplishment instructions are FAA approved. G. Manpower (1) An estimated 10 man hour(s) is/are required for this change when accomplished at the maintenance level. H. Weight and Balance (1) No change. I. Electrical Load Data (1) Not applicable.

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J. Software Accomplishment Summary (1) Not applicable. K. References (1) The sources of information used in the preparation of this service bulletin include Honeywell engineering documentation and the documents listed in Table 6. Table 6. Sources of Information

Part/Model Number Engine Overhaul Manual Engine Maintenance Manual 1 Illustrated Parts Catalog 1 TPE331-10-501C NA 72-00-28 72-01-17 TPE331-10-501K NA 72-00-29 72-01-18 TPE331-10-501M NA 72-00-27 72-01-16 TPE331-10-511C NA 72-00-28 72-01-17 TPE331-10-511K NA 72-00-29 72-01-18 TPE331-10-511M NA 72-00-27 72-01-16 TPE331-10-511KA NA 72-01-46 72-01-45 TPE331-10AV-511B NA 72-01-32 72-01-30 TPE331-10AV-511M NA 72-01-32 72-01-30 TPE331-10GP-511D NA 72-01-22 72-01-20 TPE331-10GT-511D NA 72-01-22 72-01-20 TPE331-10N-511S NA 72-00-13 72-00-11 TPE331-10N-512S NA 72-00-13 72-00-11 TPE331-10N-513S NA 72-00-13 72-00-11 TPE331-10N-514S NA 72-00-13 72-00-11 TPE331-10N-515S NA 72-00-13 72-00-11 TPE331-10N-531S NA 72-00-13 72-00-11 TPE331-10N-532S NA 72-00-13 72-00-11 TPE331-10N-533S NA 72-00-13 72-00-11 TPE331-10N-534S NA 72-00-13 72-00-11 TPE331-10N-535S NA 72-00-13 72-00-11 TPE331-10P-511D NA 72-01-22 72-01-20 TPE331-10R-501C NA 72-00-28 72-01-17 TPE331-10R-502C NA 72-00-28 72-01-17 TPE331-10R-511C NA 72-00-28 72-01-17

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Table 6. Sources of Information (Cont)

Part/Model Number Engine Overhaul Manual Engine Maintenance Manual 1 Illustrated Parts Catalog 1 TPE331-10R-512C NA 72-00-28 72-01-17 TPE331-10R-513C NA 72-00-28 72-01-17 TPE331-10T-511D NA 72-01-22 72-01-20 TPE331- 10T-511K NA 72-00-2 9 72-01-1 8 TPE331-10T-511M NA 72-00-27 72-01-16 TPE331-10T-512K NA 72-00-29 72-01-18 TPE331-10T-513K NA 72-00-29 72-01-18 TPE331-10T-515K NA 72-00-29 72-01-18 TPE331-10T-516K NA 72-00-29 72-01-18 TPE331-10T-517K NA 72-00-29 72-01-18 TPE331-10U-501G NA 72-00-23 72-01-15 TPE331-10U-502G NA 72-00-23 72-01-15 TPE331-10U-503G NA 72-00-30 72-01-19 TPE331-10U-511G NA 72-00-23 72-01-15 TPE331-10U-512G NA 72-00-23 72-01-15 TP E331-10U-513G NA 72 -00-30 72 -01-19 TPE331-10UA-511G NA 72-00-45 72-00-44 TPE331-10UF-501H NA 72-00-42 72-00-41 TPE331-10UF-511H NA 72-00-42 72-00-41 TPE331-10UF-512H NA 72-00-42 72-00-41 TPE331-10UF-513H NA 72-00-42 72-00-41 TPE331-10UF-514H NA 72-00-42 72-00-41 TPE331-10UF-515H NA 72-00-42 72-00-41 TPE331-10UF-516H NA 72-00-42 72-00-41 TPE331-10UG-513H NA 72-00-42 72-00-41 TPE331-10UG-514H NA 72-00-42 72-00-41 TPE331-10UG-515H NA 72-00-42 72-00-41 TPE331-10UG-516H NA 72-00-42 72-00-41 TPE331-10UGR-513H NA 72-00-42 72-00-41

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Table 6. Sources of Information (Cont)

Part/Model Number Engine Overhaul Manual Engine Maintenance Manual 1 Illustrated Parts Catalog 1 TPE331-10UGR-514H NA 72-00-42 72-00-41 TPE331-10UGR-515H NA 72-00-42 72-00-41 TPE331-10UGR-516H NA 72-00-42 72-00-41 TPE331- 10UR-513H NA 72-00-42 72-00-4 1 TPE331-10UR-516H NA 72-00-42 72-00-41 TPE331-11U-601G NA 72-00-25 72-00-24 TPE331-11U-602G NA 72-00-25 72-00-24 TPE331-11U-611G NA 72-00-25 72-00-24 TPE331-11U-612G NA 72-00-25 72-00-24 NOTE: 1. Affected Chapter/Section/Subject 72-50-07. (2) Inspection/Repair Manual 72-IR-15. L. Other Publications Affected (1) Same as those listed under Paragraph 1.K.(1). M. Interchangeability or Intermixability of Parts (1) Not applicable.

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2. M ate r i a l I nfo r m at i o n A. Material - Price and Availability (1) Not applicable. B. Industry Support Information (1) For special program information contact: Honeywell International Inc. Complete Customer Care Center Telephone (800) 601-3099 (Toll Free U.S.A./Canada) Telephone (602) 365-3099 (International Direct) Telephone 00-800-601-30999 (EMEA Toll Free) Telephone 420-234-625-500 (EMEA Direct) C. Material Necessary for Each Engine (1) Not applicable. D. Material Necessary for Each Spare (1) Not applicable. E. Reidentified Parts (1) Not applicable. F. Tooling - Price and Availability (1) No special tooling is required except that already listed in publications referenced in Paragraph 1.K.(1).

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3. Ac co m p l i s h m e n t I n st r u ct i o n s A. General Information (1) Obey the precautions. N OT E : This is a CATEGORY 1, SAFETY service bulletin. N OT E : Paragraph 4.B. of this service bulletin provides applicable fluorescent penetrant inspection (F PI) instructions for the first stage turbine disks with serial numbers listed in Table 2. N OT E : Publications listed in Paragraph 1.K.(1) provide applicable disassembly, cleaning, inspection, reassembly, and testing instructions and shall be referred to during the accomplishment of the following instructions. (2) Refer to Service Bulletin TPE331-72-0180 for instructions to update the life limited part log card. B. Inspect First Stage Turbine Disks, PN 3101520-1 and PN 3107079-1 (1) For uninstalled first stage turbine disks, PN 3101520-1 and PN 3107079-1, with serial numbers listed in Table 2, do Paragraph 3.B.(3) thru Paragraph 3.B.(6) and Paragraph 3.B.(11). (2) If installed, remove first stage turbine rotor assembly, PN 3101603-1, PN 3101603-8, PN 3101603- 10, PN 3101603-12, PN 3108164-1, or PN 3108164-2, with serial numbers listed in Table 2, in accordance with the engine maintenance manual and update the life limited part log cards for the first stage turbine disk and seal plate. CA U T I O N : REFER TO SERVICE BULLETINS TPE331-A72-2130 AND TPE331-72-0180 FOR LIFE LIMITED COMPONENTS. (3) Make sure remaining cycle life of the first stage turbine disk and seal plate will allow return to service if the disk passes inspection per this service bulletin. Replace disk and/or seal plate if necessary and process life limited part log card(s) in accordance with the i nstructions in Service Bulletin TPE331-72-0180. N OT E : First stage turbine disks, PN 3101520-1 and PN 3107079-1 are part of first stage turbine rotor assembly, PN 3101603-1, PN 3101603-8, PN 3101603-10, PN 3101603-12, PN 3108164-1, or PN 3108164-2. N OT E : It is not necessary to de-blade the first stage turbine rotor assembly to accompli sh this inspection. (4) Perform fluorescent penetrant inspection (FPI) of the first stage turbine disk in accordance with the procedure in Paragraph 4.B.

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# SERVICE BULLETIN

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(5) Reject any first stage turbine disk that does not pass fluorescent penetrant inspection. Process life limited part log card in accordance with instructions in Service Bulletin TPE331-72-0180. Make an entry on the life limited part log card indicating the disk has failed the fluorescent penetrant inspection requirement of this service bulletin. Send rejected first stage turbine disk and life limited part log card(s) to: Honeywell International Inc. 1944 East Sky Harbor Circle Phoenix, AZ 8 5034-3440 Attn: Fast Shop Contact: Honeywell NDE Engineering Fax: 602-365-4577 N OT E : It is not necessary to de-blade the first stage turbine rotor assembly to accomplish this inspecti on. (6) If first stage turbine disk passes fluorescent penetrant inspection, a special eddy current inspection must be conducted by Honeywell. Make an entry on the life limited part log card indicating the disk has passed the fluorescent penetrant inspection requirement of this service bulletin and that a special eddy current inspection is required. Send first stage rotor assembly or first stage turbine disk and life limited part log card(s) to: Honeywell International Inc. 1944 East Sky Harbor Circle Phoenix, AZ 85034-3440 Attn: Fast Shop Fax: 602-365-4577 (7) Install a serviceable first stage turbine rotor assembly in accordance with the engine maintenanc e manual. (8) Upon completion of engine reassembly, check and ensure proper engine operation in accordance with the engine test instructions. (9) Make entry in engine log book noting date of compliance, engine operating time, part number(s) and serial number(s) of installed component(s) (as applicable) and compliance with this service bulletin (and service bulletin revision number if applicable). (10) Reidentification of equipment is not required. (11) Complete th e Compliance Certificate form in Paragraph 4.A. and send to Honeywell.

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# SERVICE BULLETIN

TPE331

4. Ap p e n d ix A. Appendix A, Certificate of Compliance To: Operator or Service Center Performing Modification Upon modification of equipment, please fill in the information requested below, then mail or fax the completed certificate to: Honeywell International Inc. 111 S 34th Street, Mail Stop 503-320 Phoenix, AZ 85034-2802 Fax: (602) 231-3014 Owner/Operator

Aircraft Model Aircraft Serial Number I certify that the following engine/equipment has been modified in accordance with the listed service bulletins. Table 7. ENGINE/EQUIPMENT NUMBER 1 NUMBER 2 NUMBER 3 NUMBER 4 PART NUMBER PART NUMBER PART NUMBER PART NUMBER
MODEL NUMBER MODEL NUMBER MODEL NUMBER MODEL NUMBER
SERIAL NUMBER SERIAL NUMBER SERIAL NUMBER SERIAL NUMBER
TSN/TSO TSN/TSO TSN/TSO TSN/TSO
CYCLES CYCLES CYCLES CYCLES
SERVICE BULLETIN NUMBER REV. NUMBER SERVICE BULLETIN NUMBER REV. NUMBER SERVICE BULLETIN NUMBER REV. NUMBER SERVICE BULLETIN NUMBER REV. NUMBER

Signature Date Repair Facility

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# SERVICE BULLETIN

TPE331

FAX TO U.S.A. (602) 231-3014

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# SERVICE BULLETIN

TPE331
B. Appendix B, Fluorescent Penetrant Inspection (FPI) Instructions for First Stage Turbine Disks, PN 3101520-1 and PN3107079-1 (1) Refer to Table 8 for cleaning materials needed to perform the FPI inspection. Table 8. Cleaning Materials Material or Compound Manufacturer Degreaser (Daraclean 282) Magnaflux, A Division of Illinois Tool Works Inc, 3624 W Lake Ave, Glenview, IL 60025 Degreaser (Formula 815 GD) Brulin Corp, P.O. Box 270, 2920 Dr. Andrew J Brown Ave, Indianapolis, IN 46205 (2) Perform fluorescent penetrant inspection. N OT E : Inspection personnel who interpret indications shall be qualified in accordance with NAS 410 (or equivalent foreign certifying agency) and be certified to a minimum equivalency of NAS410 Level II penetrant inspector. N OT E : Inspection shall be performed with Type I, Method D, Sensitivity 4 penetrant process only. Only penetrant inspection materials listed, and approved on QPL-AMS-2644 (or equivalent) shall be used for testing. (a) Pre-clean turbine disk. N OT E : Turbine disk must be free of all contamination, oils, water, grease, dirt, paint, etc. If the part is not free of contamination, return part to clean area for additional cleaning. N OT E : Pre/post cleaning shall be performed by qualified personal only. N OT E : Make sure all foreign materials, (i.e., oils, water, grease, dirt, paint, etc.) that could prevent the penetrant from entering discontinuities, suppress dye performance, or produce unacceptable background is removed. 1 Clean turbine disk by aqueous degreasing as follows. W

A R N I N G : DEGREASER (DARACLEAN 282 OR FORMULA 815 GD) AT 100 PERCENT CONCENTRATION IS AN EYE IRRITANT. WEAR EYE PROTECTION WHEN MIXING CLEANING SOLUTION. 2 Mix degreaser (Daraclean 282 or Formula 815 GD) with tap water in a dip tank to a concentration of 8 to 12 percent.

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# SERVICE BULLETIN

TPE331

3 Maintain temperature of cleaning solution at 150 ±10 F (66 ±6 C). CA U T I O N : DO NOT IMMERSE TURBINE DISKS IN SOLUTION FOR MORE THAN 30 MINUTES, THIS INCLUDES RE-CLEANING. N OT E : If a parts washer is used in the following step, use of degreaser (Formula 815 GD) is not recommended. Excess foaming action will occur. 4 Dip, soak, or agitate turbine disk. Agitation is recommended process for best results. Propeller mixing or solution spraying under the solution level are preferred methods of agitation. Do not immerse turbine disks in solution for more than 30 minutes, this includes recleaning. 5 Rinse turbine disks using hot tap water. If required, perform a soap and water scrub using a stiff plastic fiber brush to remove any excess grease or oil residue, then rinse parts using hot tap water. W

A R N I N G : COMPRESSED AIR USED FOR CLEANING CAN CREATE AIRBORNE PARTICLES THAT MAY ENTER THE EYES. EYE PROTECTION IS REQUIRED. AIR PRESSURE SHALL NOT EXCEED 30 PSIG (207 KPA). 6 Dry parts using low pressure compressed air (20 psig (138 kPa)). Make sure that no entrapment of solution is present after drying. N OT E : Turbine disk, penetrant, and ambient temperature shall all be at a temperature of between 50 to 125 F (10 to 52 C). (b) Apply penetrant to the turbine disk by either manual spraying or electrostatic spray method. Make sure there is 100% coverage. N OT E : Dwell time shall be that period of time when penetrant covers the turbine disk. 1 Dwell time shall be a minimum of 30 minutes not to exceed 2 hours. N OT E : If dwell time exceeds 2 hours, the turbine disk shall be cleaned and re-processed with penetrant. 2 Rotate or move turbine disk if pooling of penetrant is evident during dwell. N OT E : Rinse water shall be free of contaminants that could leave residue or that is detrimental to the inspection of the part. N OT E : Pre-rinse shall occur under UV lighting. N OT E : Pre-rinse only for the minimum time required to remove excess surface penetrant. (c) Pre emulsification rinse. 1 Rinse (pre-rinse) excess penetrant from turbine disk surfaces with water using coarse spray water nozzles (tri-con or equivalent) at a

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# SERVICE BULLETIN

TPE331
maximum pressure of 40 psi (276 kPa), and a temperature between 50 and 100 F (10 to 38 C), and at a minimum distance of 12 inches (30.5 cm). 2 If over-washing occurs, the turbine disk shall be cleaned and reprocessed with penetrant. (d) Apply the Hydrophilic Remover by immersion emulsification method or by spray emulsification method. 1 Immersion emulsification method. 2 Immerse turbine disk in a mildly agitated solution for a minimum time sufficient to remove excess penetrant but not to exceed 30 seconds. 3 Spray emulsification method. 4 Apply emulsifier solution to turbine disk surfaces to remove excess penetrant using coarse spray water nozzles (tri-con or equivalent) at a maximum pressure of 40 psi (276 kPa) and a temperature between 50 and 100 F (10 to 38C). 5 Place turbine disk on suitable surface for a dwell time necessary to develop a satisfactory background, but shall not exceed 2 minutes. (e) Final Rinse. N OT E : Rinse water shall be free of contaminants that could leave residue or that is detrimental to the inspection of the part. N OT E : Final-rinse shall occur under UV lighting. N OT E : Final-rinse for the minimum time required to remove surface penetrant only. 1 Rinse (final-rinse) turbine disk surfaces with water using coarse spray water nozzles (tri-con or equivalent) at a maximum pressure of 40 psi (276 kPa) and a temperature between 50 and 100 F (10 and 38 C), and at a minimum distance of 12 inches (30.5 cm). 2 If over-washing occurs, the turbine disk shall be cleaned and reprocessed with penetrant. 3 Drain excess water from turbine disk. Filtered shop air (20 psi (138 kPa), maximum) may be blown across the turbine disk to prevent water pooling (f) Dry turbine disk. N OT E : Drying time shall be only that necessary to adequately dry the turbine disk. N OT E : Turbine disks shall not be placed in oven with pooled water on surfaces. N OT E : Turbine disk temperature shall not exceed 160 F (71 C) during drying. Part time in oven shall not exceed 30 minutes. 1 Dry turbine disk in a re-circulating drying oven with a maximum temperature of 160 F (71 C)

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# SERVICE BULLETIN

TPE331

2 Remove turbine disk from oven immediately after drying. (g) Apply developer to turbine disk. N OT E : Components shall be completely dry before developer application. N OT E : Dry developer shall be applied in such a manner as to contact all surfaces to be inspected by evidence of visible dust on part surface. N OT E : For adequate coverage it may be necessary to adjust (flip or rotate) components in the dust chamber. N OT E : Inspection shall be com pleted within 4 hours of developer application. Turbine disks that are not inspected within 4 hours of developer application must be cleaned and reprocessed with penetrant. 1 Apply dry developer by spray (dust chamber or bulb) to lightly coat all surfaces to be inspected. Allow to dwell for not less than 10 minutes or for no more than 4 hours. 2 Remove excess developer after dwell by lightly tapping turbine disk. Filtered shop air (5 psi (35 kPa) maximum) may be used to remove excess developer. (h) Inspect turbine disk. N OT E : When handling parts, care should be taken to avoid smudging or eliminating indications by excessive or careless handling. N OT E : Inspections shall be performed in a darkened area with a maximum ambient white light intensity of 2-foot candles, (21.5 lux). Allow at least 5 minutes warm-up time for black light to reach the required operational intensity. Black lights shall provide a minimum of 1200 microwatts per square-centimeter when measured at a minimum distance of 15 inches (38 cm) from the front of the bulb or sensing element. The minimum black light intensity at the inspection surface shall be 1200 micro watts per centimeter square. N OT E : Eyeglasses equipped with permanently tinted or light sensitive (Photo chromatic) lenses shall not be worn while processing or inspecting parts. N OT E : Inspectors shall wait a minimum of 1-minute dark adaptation time (prior to evaluating parts) each time the overhead white light is turned on or the inspector looks directly into the beam of the black light. N OT E : Background fluorescence is not permitted on turbine disk bore or on adjacent forward and aft surfaces. N OT E : An indication is defined as, a response or evidence from a fluorescent penetrant inspection. N OT E : A relevant indication is defined , as an indication that is caused by a condition or type of discontinuity that requires evaluation.

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# SERVICE BULLETIN

TPE331

N OT E : A nonrelevant indication is defined, as an indication that is caused by a condition or type of discontinuity that is not rejectable. False indications are nonrelevant. N OT E : A discontinuity is defined as a lack of continuity or cohesion; an intentional or unintentional interruption in the physical structure or configuration of a material or component. N OT E : Indications shall be interpreted by wiping the indication once with a solvent dampened swab or brush, taking care not to flood the area with solvent. If indication is accidentally flooded, clean and re-process the component/area. Allow the area to dry, and redevelop. If the indication reappears and is rejectable in size, the part may be rejected before the full developer dwell time has lapsed. Otherwise, development time before the re-interpretation of the indication shall be as long as the original required development time. If no indication appears, the original indication is considered non-relevant. This procedure may only be performed once for any given original indication. N OT E : Indications which, after interpretation, are deemed to be caused by mechan ical retention or penetrant from component features such as studs, rivets, press fits, or fasteners, shall be considered non-relevant. 1 Inspect turbine disk using magnification of 7X to 10X. All areas of fluorescence shall be interpreted. 2 No releva nt linear indications are allowed Linear indications are defined as those with at least a 3 to 1 ratio of length to width. 3 No relevant rounded indications with a diameter exceeding 0.015 inch (0.038 cm) are allowed. 4 Reject any first stage turbine disk that exhibits any relevant linear indicat ions and/or relevant rounded indications exceeding 0.015 inch (0.038 cm) in diameter. 5 Turbine disks with no indications or non linear indications that do not exceed the limits of Paragraph 4.B.(2)(h)2 and Paragraph 4.B.(2)(h)3 shall be accepted (i) Clean tu rbine disk. 1 Clean turbine disk in accordance withParagraph 4.B.(2)(a)1

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