TFE731-72-5222 Revision 2, 13 Oct 2021 Page

Honeywell International Inc.111 S. 34th StreetPhoenix, Arizona 85034-2802U.S.A.CAGE: 99193Telephone: 800-601-3099 (Toll Free U.S.A./Canada)Telephone: 602-365-3099 (International Direct)

Website: https://aerospace.honeywell.com

SERVICE BULLETINENGINE - COMPRESSOR SECTION - Install Front Frame Assembly That Has Additional CorrosionProtection Features

Legal Notice

This is a CATEGORY 2, RELIABILITY service bulletin.NOTICE:

ONLY THE FACILITIES LISTED IN THIS SERVICE BULLETIN AUTHORIZED TO PERFORM THEEDDY CURRENT INSPECTION WILL RECEIVE SERVICE BULLETIN ATTACHMENTS. ALLOTHER FACILITIES WILL RECEIVE ONLY THE BASIC SERVICE BULLETIN.

NOTICE:

Export Control

These items are controlled by the U.S. government and authorized for export only to the country of ultimatedestination for use by the ultimate consignee or end-user(s) herein identified. They may not be resold, transferred,or otherwise disposed of, to any other country or to any person other than the authorized ultimate consignee orend-user(s), either in their original form or after being incorporated into other items, without first obtaining approval

from the U.S. government or as otherwise authorized by U.S. law and regulations.

ECCN: 9E991

Proprietary Information

HONEYWELL - CONFIDENTIALTHIS DOCUMENT AND ALL INFORMATION AND EXPRESSION CONTAINED HEREIN ARE THE PROPERTYOF HONEYWELL INTERNATIONAL INC., ARE PROVIDED IN CONFIDENCE, AND MAY BE USED BYPERSONS REQUIRED BY FEDERAL AVIATION REGULATION PART 21.50 TO COMPLY WITH ANY OF THETERMS OF THESE INSTRUCTIONS. EXCEPT AS SET FORTH ABOVE, NO PERSON MAY, IN WHOLE ORIN PART, USE, DUPLICATE OR DISCLOSE THIS INFORMATION FOR ANY PURPOSE WITHOUT THE PRIORWRITTEN PERMISSION OF HONEYWELL INTERNATIONAL INC.

TFE731-72-522219 Aug 2011Page 1 of 22Revision 2, 13 Oct 2021

Publication Number D201103000013© Honeywell International Inc. Do not copy without express permission of Honeywell.

RELEASED FOR THE EXCLUSIVE USE BY: CAMP SYSTEMS INCU

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https://aerospace.honeywell.com

HONEYWELL MATERIALS LICENSE AGREEMENTThis document and the information contained herein (“the Materials”) are the proprietary data of Honeywell.These Materials are provided for the exclusive use of Honeywell-authorized Service Centers; Honeywell-authorizedrepair facilities; owners of a Honeywell aerospace product that is the subject of these Materials (“HoneywellProduct”) that have entered into a written agreement with Honeywell relating to the repair or maintenance ofHoneywell Product; and direct recipients of Materials from Honeywell viahttps://aerospace.honeywell.com/en/learn/about-us/about-myaerospace that own a Honeywell Product. 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TFE731-72-522219 Aug 2011Page 2Revision 2, 13 Oct 2021


SERVICE BULLETINTFE731


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or any person or entity whose actions or functions are intended to support “military end uses.” “Military End Uses”includes use of an item to support or contribute to the operation, installation, maintenance, repair, overhaul,refurbishing, development, or production of military items. In addition, you will not divert or in any way utilize orsell Honeywell products, materials, technology, or technical data to any entity that is a Chinese, Russian, orVenezuelan Military End User or for Military End Uses, as stated above. You shall immediately notify Honeywelland cease all activities associated with the transaction in question if it knows or has a reasonable suspicion thatthe products, materials, technical data, plans, or specifications may be exported, reexported, or transferred insupport of a prohibited Military End Use or to a Military End User. Failure to comply with this provision is a materialbreach of your order and agreement with Honeywell and Honeywell is entitled to immediately seek all remediesavailable under law and in equity (including without limitation, termination), without any liability to Honeywell.3. Rights In Materials - Honeywell retains all rights in these Materials and in any copies thereof that are notexpressly granted to you, including all rights in patents, copyrights, trademarks, and trade secrets. The Materialsare licensed and not sold under this License Agreement. No license to use any Honeywell trademarks or patentsis granted under this License Agreement.4. Changes - Honeywell reserves the right to change the terms and conditions of this License Agreement at anytime, including the right to change or impose charges for continued use of the Materials. Honeywell may add,delete or otherwise modify any portion of the Materials (“Updated Materials”) at any time. You agree to stopusing outdated Materials upon issuance of any Updated Materials.5. Confidentiality - You acknowledge that these Materials contain information that is confidential and proprietaryto Honeywell. You agree to take all reasonable efforts to maintain the confidentiality of these Materials.6. Assignment and Transfer - This License Agreement may be assigned to a service center approved and formallydesignated as a service center by Honeywell, provided, however, that you retain no copies of the Materials inwhole or in part. However, the recipient of any such assignment or transfer must assume all of your obligationsand liabilities under this License Agreement. No assignment or transfer shall relieve any party of any obligationthat such party then has hereunder. Otherwise, neither this License Agreement nor any rights, licenses orprivileges granted under this License Agreement, nor any of its duties or obligations hereunder, nor any interestor proceeds in and to the Materials shall be assignable or transferable (in insolvency proceedings, by merger,by operation of law, by purchase, by change of control or otherwise) by you without Honeywell’s written consent.7. Copies of Materials - Unless you have the express written permission of Honeywell, you may not make orpermit making of copies, digital or printed, of the Materials. You agree to return the Materials and any such copiesthereof to Honeywell upon the request of Honeywell.8. Term - This License Agreement is effective until terminated as set forth herein. This License Agreement willterminate immediately, without notice from Honeywell, if you fail to comply with any provision of this LicenseAgreement or will terminate simultaneously with the termination or expiration of your applicable agreement withHoneywell relating to the repair or maintenance of the subject Honeywell Product. Upon termination of thisLicense Agreement, you will return these Materials to Honeywell without retaining any copies, in whole or in part,and will have one of your authorized officers certify that all Materials have been returned with no copies retained.9. Audit Rights - Honeywell, through its authorized representatives, with no less than thirty (30) calendar daysnotice from Honeywell, has the right during normal business hours during the term of this License Agreementand for three (3) years thereafter to visit you and have access to the inside and outside of your facility for thepurpose of inspecting, observing and evaluating your compliance under this License Agreement.10. Remedies - Honeywell reserves the right to pursue all available remedies and damages resulting from abreach of this License Agreement.11. Limitation of Liability - Honeywell makes no representations or warranties regarding the use or sufficiencyof the Materials. THERE ARE NO OTHER WARRANTIES, WHETHER WRITTEN OR ORAL, EXPRESS, IMPLIEDOR 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 WILLHONEYWELL BE LIABLE FOR ANY INCIDENTAL DAMAGES, CONSEQUENTIAL DAMAGES, SPECIALDAMAGES, INDIRECT DAMAGES, LOSS OF PROFITS, LOSS OF REVENUES, OR LOSS OF USE, EVEN IFINFORMED OF THE POSSIBILITY OF SUCH DAMAGES. TO THE EXTENT PERMITTED BY APPLICABLELAW, THESE LIMITATIONS AND EXCLUSIONS WILL APPLY REGARDLESS OF WHETHER LIABILITYARISES FROM BREACH OF CONTRACT, WARRANTY, INDEMNITY, TORT (INCLUDING BUT NOT LIMITEDTO NEGLIGENCE), BY OPERATION OF LAW, OR OTHERWISE.12. Controlling Law - This License Agreement shall be governed and construed in accordance with the laws ofthe State of New York without regard to the conflict of laws provisions thereof.13. Severability - In the event any provision of this License Agreement is determined to be illegal, invalid, orunenforceable, the validity and enforceability of the remaining provisions of this License Agreement will not beaffected and, in lieu of such illegal, invalid, or unenforceable provision, there will be added as part of this LicenseAgreement one or more provisions as similar in terms as may be legal, valid and enforceable under controllinglaw.14. Integration and Modification - This License Agreement sets forth the entire agreement and understandingbetween the parties on the subject matter of the License Agreement and merges all prior discussions andnegotiations among them.

Safety AdvisoryWARNING: BEFORE THE MATERIALS CALLED OUT IN THIS PUBLICATION ARE USED, KNOW THEHANDLING, STORAGE AND DISPOSAL PRECAUTIONS RECOMMENDED BY THE MANUFACTURER ORSUPPLIER. FAILURE TO OBEY THE MANUFACTURERS' OR SUPPLIERS' RECOMMENDATIONS CANRESULT 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 MaterialSafety Data Sheets (OSHA Form 174 or equivalent) from the manufacturers or suppliers of the materials to beused. The user must know the manufacturer/supplier data and obey the procedures, recommendations, warningsand cautions set forth for the safe use, handling, storage, and disposal of the materials.

Warranty/Liability AdvisoryWARNING: HONEYWELL ASSUMES NO RESPONSIBILITY FOR ANY HONEYWELL EQUIPMENT WHICHIS NOT MAINTAINED AND/OR REPAIRED IN ACCORDANCE WITH HONEYWELL'S PUBLISHEDINSTRUCTIONS AND/OR HONEYWELL'S FAA/SFAR 36 REPAIR AUTHORIZATION. NEITHER DOESHONEYWELL ASSUME RESPONSIBILITY FOR SPECIAL TOOLS AND TEST EQUIPMENT FABRICATEDBY COMPANIES OTHER THAN HONEYWELL.

WARNING: INCORRECTLY REPAIRED COMPONENTS CAN AFFECT AIRWORTHINESS OR DECREASETHE LIFE OF THE COMPONENTS. INCORRECTLY FABRICATED SPECIAL TOOLING OR TEST EQUIPMENTCAN RESULT IN DAMAGE TO THE PRODUCT COMPONENTS OR GIVE UNSATISFACTORY RESULTS.

Copyright - NoticeCopyright 2011, 2021 Honeywell International Inc. All rights reserved.

Honeywell is a registered trademark of Honeywell International Inc.All other marks are owned by their respective companies.





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Transmittal Information

ATA Number TFE731-72-5222 (Publication Number D201103000013)

Summary

The equipment changed in the revision(s) before this service bulletin may need additional changes. Refer toParagraph 3.

This revision is a FULL replacement. This revision includes the changes that follow:

• Paragraph 3.B.(3). Table 13. Added Duncan Aviation to the Facilities Authorized to Accomplish Eddy CurrentCorrosion Inspection table.

• Changed the content and format to agree with Honeywell processes in effect at the time of the release of thisrevision.

The information that is identified with revision bars is listed in the Highlights section. Revision bars are not usedbefore Paragraph 1.A. The editorial changes and information that was moved or reformatted is not identified withrevision bars.

Refer to Paragraph 4.A. for a list of the acronyms and abbreviations used in this service bulletin.

Revision History

This service bulletin has had two revision(s) as shown in Table 1.

Table 1. Revision History

Revision DateRevision Number

19 Aug 20110

1 May 20121

13 Oct 20212

Highlights

This section issues Revision 2 to Service Bulletin, ATA Number TFE731-72-5222 (Publication NumberD201103000013), and contains these changes:

The list of highlights tells the users about the changes that the revision makes. The list has three columns. The"Page" column shows the block of data that the revision changes and the page on which the block begins. Theblock can be a section, subsection, graphic, table, etc. Revision marks give the location of the change in theblock. The "Description" column tells the user about the change or changes in each block. A paragraph, table,or figure reference often comes before the description. The "Effectivity" column tells the user about the partnumber(s) to which the block of information applies. The default value for this column is "All." "All" means thatthe block applies to all parts.

EffectivityDescriptionPage

AllParagraph 3.B.(3) Table 13. Added Duncan Aviation to the Facilities Authorizedto Accomplish Eddy Current Corrosion Inspection table.

16





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1. Planning Information

A. Effectivity

(1) This is a CATEGORY 2, RELIABILITY service bulletin.

(2) This service bulletin is applicable to the front frame assemblies shown in Table 2.

NOTE: Engines in compliance with Service Bulletin TFE731-72-5217 are not affectedby this service bulletin.

Table 2. Applicable Component(s)

Prior to Serial NumberPN

All3060171-6, -7

All3060236-4, -5

All3060421-1, -2

All3060439-1

All3061505-3

(3) The component(s) shown in Table 2 are used on turbofan aircraft engines. This servicebulletin is applicable to the serial numbers shown in Table 3.

Table 3. Applicable Engine(s)

ApplicationPrior to SerialNumberModel NumberPN

Learjet 40/4513222323TFE731-20AR-1B3060082-2, -3, -4, -6, -7

Learjet 40/40XR/45/45XR45TFE731-20BR-1B3060084-1, -2

Learjet 451112231TFE731-20R-1B3060020-8 thru -14

Falcon 50EX/50-401154501TFE731-40-1C3060050-1

G100 (Astra SPX)1132801TFE731-40R-200G3060040-4, -5

G1501262966TFE731-40AR-200G3062020-1

Hawker 900XP122419TFE731-50R-1H3060090-1

Falcon 900EX/900DX/900LX1129907TFE731-60-1C3060000-4

NOTES:

1. Projected serial number for future production.2. Production Incorporation Point. Applicability also includes Engine Model Number TFE731-20AR-1B, Engine

Serial Numbers 116101 thru 116999.3. Effectivity also applies to Engine Serial Numbers 111101C thru 111222C, which were originally Engine Model

Number TFE731-20R-1B, and subsequently converted to Engine Model Number TFE731-20AR-1B.4. Effectivity applies to Engine Serial Numbers 111101C thru 111222C, which were originally Engine Model Number

TFE731-20R-1B, and subsequently converted to Engine Model Number TFE731-20BR-1B.





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5. Effectivity also applies to Engine Serial Numbers 116101C thru 116999C and 132101C thru 132223C, whichwere originally Engine Model Number TFE731-20AR-1B and subsequently converted to Engine Model NumberTFE731-20BR-1B.

6. Production Incorporation Point. Effectivity also applies to Engine Serial Numbers 113263C, 113264C, 113267C,113268C, 113271C, and 113274C thru 113279C, which were originally Engine Model Number TFE731-40R-200G,and subsequently converted to Engine Model Number TFE731-40AR-200G.

7. Production Incorporation Point.

B. Concurrent Requirements

(1) The service bulletin(s) listed in Table 4 shall be accomplished prior to or concurrent withthis service bulletin. The accomplishment instructions outlined in each service bulletinstand alone; therefore, compliance with this service bulletin does not indicate compliancewith any other service bulletin.

Table 4. Concurrent Service Bulletin(s)

Service Bulletin TitleService Bulletin Number

ENGINE - BYPASS SECTION - Inspect or Replace Composite Bypass DuctsTFE731-72-5224

(2) Review of the service bulletin(s) listed in Table 5 should be accomplished by the operatorfor possible incorporation at the time this service bulletin is accomplished.

Table 5. Optional Service Bulletin(s)


ENGINE - COMPRESSOR SECTION - Provide Eddy Current Corrosion Inspectionand Rework Instructions for the Front Frame Assemblies

TFE731-72-5228RWK

C. Reason

(1) Problem:

(a) Several engines have exhibited evidence of corrosion to the front frame assemblyaft flange at the bypass duct interface. Engines that had composite bypassducts installed and were operating in humid or marine environments were foundto have more significant corrosion. Investigation of the corrosion revealed thecause to be galvanic action between the carbon fibers within the compositebypass ducts and the aluminum front frame assembly.

(2) Background:

(a) Extensive testing was performed to determine the cause of the corrosion andto determine the serviceable corrosion limit for front frame assemblies. ServiceBulletin TFE731-72-5228RWK contains the specialized eddy current inspectionequipment and procedures that were developed to accurately measure thedepth of any corrosion. Because of the special equipment and techniquesrequired to accomplish the eddy current inspection, only facilities that have beenapproved by Honeywell may accomplish the eddy current inspection. Additional





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corrosion preventive features were also identified to increase corrosion protectionof the front frame assembly aft flange to bypass duct interface. Front frameassemblies that meet the serviceable limit for corrosion will be reworked byreceiving a chemical conversion treatment followed by the application of epoxypaint and will be reidentified. If corrosion is found that exceeds the serviceablelimit, there is currently no repair and the front frame assembly will be scrapped.Front frame assemblies removed from engines that had aluminum fan ductsinstalled do not require the eddy current inspection. They do, however, requirerework to apply a chemical conversion treatment and epoxy paint to the aftflange area and will be reidentified. The rework of front frame assembliesremoved from engines that had aluminum fan ducts installed may beaccomplished by any facility having the necessary equipment to apply thechemical conversion treatment and epoxy paint.

(3) Action:

(a) At the next compressor zone inspection (CZI), accomplish a special eddy currentcorrosion inspection (as applicable) of the aft flange of front frame assembliesidentified with part numbers listed in Table 2, in accordance with the instructionsin Service Bulletin TFE731-72-5228RWK. Only front frame assemblies removedfrom engines that had composite bypass ducts installed are required to havethe eddy current inspection. All front frame assemblies, regardless of whetherthey were removed from engines having composite or aluminum fan ductsinstalled, must have an additional corrosion protection chemical treatment andthe addition of epoxy paint to the aft flange area.

D. Description

(1) This service bulletin provides the requirement to accomplish an eddy current corrosioninspection in accordance with the instructions in Service Bulletin TFE731-72-5228RWKto front frame assemblies that have been removed from engines that had compositebypass ducts installed. It also provides the rework instructions to apply additionalcorrosion protection features (chemical film treatment and painting of aft flange surface)for those parts that pass the inspection criteria.

(2) It also provides rework instructions to apply additional corrosion protection features(chemical film treatment and painting of aft flange surface) for front frame assembliesthat were removed from engines that had aluminum fan ducts installed that do not requireeddy current inspection.

E. Compliance

(1) Compliance addresses a substantial improvement to reliability.

(2) The warranty/program data is listed in Table 6.

NOTE: The procedures outlined in this service bulletin may be accomplished at theHeavy Service Center/Maintenance level or greater.





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Table 6. Warranty/Program Data

NoYesWarranty/Program

XCommercial Warranty(Standard new engine warranty)

XSpare Part Warranty(Standard new spare part warranty)

XSpecial Extended Warranty Program Number(Extension of either standard commercial warranty or spare part warranty may apply)

XSpecial Program Number 83(Programs in which special pricing and/or special conditions may apply)

XSpecial Pricing Notice Number(Reduction from catalog list pricing, i.e., “P” condition pricing may apply)

XMSP

(3) Honeywell recommends that this service bulletin be accomplished at the next CZI.

F. Approval

(1) The eddy current inspection and rework authorized by this service bulletin comply withapplicable Federal Aviation Regulations and are FAA approved.

G. Manpower

(1) For front frame assemblies removed from engines that have composite bypass ductsinstalled, no additional man-hour(s) is/are required to prepare the front frame assemblyand ship to an approved eddy current inspection facility when accomplished as part ofa scheduled CZI.

(2) For front frame assemblies removed from engines that have aluminum fan ducts installed,an estimated 4.0 man-hour(s) is/are required to accomplish the front frame assemblyrework (addition of chemical film treatment and painting of aft flange surface) afteraccess to front frame assembly is obtained.

H. Weight and Balance

(1) None.

I. Electrical Load Data

(1) Not applicable.

J. Software Accomplishment Summary

(1) Not applicable.





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K. References

(1) The sources of information used in the preparation of this service bulletin includeHoneywell engineering documentation and the documents listed in Table 7.

Table 7. Sources of Information

Illustrated Parts Catalog1Light MaintenanceManual1

Heavy MaintenanceManual1Part/Model Number

72-03-0572-03-0672-03-07TFE731-20AR-1B

72-03-0572-03-0672-03-07TFE731-20BR-1B

72-03-0572-03-0672-03-07TFE731-20R-1B

72-03-0972-03-0672-03-07TFE731-40-1C

72-03-0972-03-0672-03-07TFE731-40AR-200G

72-03-0972-03-0672-03-07TFE731-40R-200G

72-03-1772-03-0672-03-07TFE731-50R-1H

72-03-1372-03-0672-03-07TFE731-60-1C

NOTE:

1. Affected Chapter/Section/Subject 72-30-10.

(2) Also referenced is the TFE731 Inspection and Repair Manual (IRM), 72-IR-02.

(3) The service bulletin(s) listed in Table 8 is/are referenced in this service bulletin.

Table 8. Service Bulletin References


ENGINE - COMPRESSOR SECTION - Provide Eddy Current Corrosion Inspectionand Rework Instructions for the Front Frame Assemblies

TFE731-72-5228RWK

L. Other Publications Affected

(1) Same as those listed under Paragraph 1.K.(1).

M. Interchangeability of Parts

(1) Not applicable.

N. Interchangeability or Intermixability of Parts

(1) Not applicable.





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2. Material Information

A. Material - Price and Availability

(1) Information regarding price and availability of parts may be obtained from aHoneywell-authorized service facility. (Refer to SIL F731-3.) You can also use the “Dealerand Service Center Locator” tool at https://aerospace.honeywell.com to find approvedservice locations. Get the price and availability of parts from the Honeywell ProductCatalog at https://aerospace.honeywell.com. If the part is not in the catalog, go toHoneywell, Aerospace Contact Team, Telephone: 800-601-3099 (Toll FreeU.S.A./Canada), 602-365-3099 (International Direct).

B. Industry Support Information

(1) A special/warranty program may be available for this modification, under certainconditions, provided compliance recommendations of Paragraph 1.E. are met. Informationon special/warranty program and availability of parts may be obtained from aHoneywell-authorized service facility. (Refer to SIL F731-3.) You can also use the “Dealerand Service Center Locator" tool at https://aerospace.honeywell.com to find approvedservice locations.

C. Material Necessary for Each Engine

(1) The parts required to accomplish the instructions outlined in this service bulletin areshown in Table 9. Refer to Table 10 for the Instructions/Disposition Codes.

NOTE: Applicable illustrated parts catalogs and spare parts bulletins, dated laterthan the original issue date of this service bulletin, may introduce differentparts for installation. Refer to these documents before ordering parts.

NOTE: Expendable parts, discarded in gaining access to the affected area of theequipment, are not included.

NOTE: The inclusion of vendor names/addresses and part numbers in the followingparts listing shall not be construed as an authorization of the vendor, pursuantto FAA regulations, to ship directly to the user. Neither shall it be construedas a certification by Honeywell that parts shipped by vendors directly to userswill conform to the type design or that such parts are airworthy or safe forinstallation.

Table 9. Operator-Purchased Material

Instructions/DispositionCodes

UnitPrice1QtyOld PNKeyword/ NomenclatureNew PN

C, R, S, T13060171-6 or3060171-7

Front frame assembly3060171-623 or3060171-7234 or3060421-335





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Table 9. Operator-Purchased Material (Cont)

Instructions/DispositionCodes

UnitPrice1QtyOld PNKeyword/ NomenclatureNew PN

C, R, S, T13060236-4 or3060236-5


C, R, S, T13060421-1 or3060421-2


C, R, S, T13060439-1Front frame assembly3060439-126 or3060439-256

C, R, S, T13061505-3Front frame assembly3061505-328 or3061505-458

NOTES:

1. Refer to Paragraph 2.A. for information regarding price and availability of parts.2. Must be marked with a -P35092 or -P34706 suffix following the part number.3. Use with Engine Model Number TFE731-40R-200G.4. Use with Engine Model Number(s) TFE731-20R-1B, TFE731-40-1C.5. Post Service Bulletin TFE731-72-5228RWK.6. Use with Engine Model Number TFE731-60-1C.7. Use with Engine Model Number(s) TFE731-20AR, TFE731-20BR, TFE731-40AR-200G.8. Use with Engine Model Number TFE731-50R-1H.

Table 10. Instructions/Disposition Codes

DescriptionCode

Rework part as specified in this service bulletin.Disposition Code C

Send the old part to Honeywell International Inc., Material Receiving, 1944 E. Sky HarborCircle, Phoenix, AZ 85034-3440 for evaluation.

Disposition Code R

If part fails eddy current inspection, send the old part to Honeywell International Inc.,Material Receiving, 1944 E. Sky Harbor Circle, Phoenix, AZ 85034-3440 for evaluation.Make sure the shipping documents indicate that the front frame assembly is beingreturned in accordance with Service Bulletin TFE731-72-5222.

Disposition Code S

Old part will continue to be available as a reworked part and reidentified with a -P35092or a -P34706 suffix added to the original part number.

Disposition Code T





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(2) Material(s) supplied by operator is/are given in Table 11.

NOTE: The materials given in Table 11 are the consumable products used in themodification of the unit.

Table 11. Materials

SourceDescriptionNumber

NOTE: Equivalent substitutes may be used for listed items.

Commercially availableMasking tape (Commercial ItemDescription A-A-883)

SAE AMS-T-21595

Primer (green epoxy-amine)535K020/930K097

Abrasive plastic media (AbrasivesUnlimited)

Poly-Plus plastic media (20 to 30mesh)

Alodine coating material (Alodine1200)

MIL-DTL-81706

D. Material Necessary for Each Spare

(1) Not applicable.

E. Reidentified Parts

(1) Refer to Table 12 for the reidentified parts data.

Table 12. Reidentified Parts

Old PNKeyword/NomenclatureNew PN

3060171-6Front frame assembly3060171-6-P350921 or3060171-6-P347062


3060236-4Front frame assembly3060236-4-P347062





NOTES:

1. Reworked front frame assemblies that were removed from engines that had aluminum fan bypass ducts installedand did not receive an eddy current corrosion inspection shall be reidentifed with the -P35092 suffix.





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2. Front frame assemblies that were removed from engines that had composite bypass ducts installed and passedthe eddy current corrosion inspection shall be reidentified with the -P34706 suffix.

F. Tooling - Price and Availability

(1) Only the facilities listed in Table 13 are authorized to perform the eddy current corrosioninspection detailed in Service Bulletin TFE731-72-5228RWK. Refer to Service BulletinTFE731-72-5228RWK for the tooling requirements for eddy current inspection of eachfront frame assembly.





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3. Accomplishment Instructions

A. General Information

(1) Obey the precautions.

NOTE: Publications listed in Paragraph 1.K.(1) provide applicable disassembly, cleaning,inspection, reassembly, and testing instructions and shall be referred to during theaccomplishment of the following instructions.

NOTE: The accomplishment instructions are to be performed as part of a CZI.

NOTE: The accomplishment instructions are divided into two paragraphs:

• Paragraph 3.B. provides instructions for engine disassembly/reassembly to gainaccess to the front frame assembly. It also provides front frame disposition,depending on if it was removed from an engine that had composite bypass duct(s)or aluminum bypass duct(s) installed.

• Paragraph 3.C. provides rework instructions for front frame assemblies that wereremoved from engines that had aluminum fan ducts installed. These front frameassemblies do not require the eddy current inspection, but do require theapplication of a chemical conversion coating and application of epoxy paint to thefront frame assembly aft flange. This rework may be accomplished by any facilityhaving the necessary equipment.

B. Removal of Front Frame Assembly for Inspection and Rework

(1) Disassemble the engine as required to gain access to and remove the front frameassembly. Refer to the instructions in the engine light maintenance manual (LMM) andheavy maintenance manual (HMM).

(2) Clean and inspect the front frame assembly. Refer to the instructions in the engineHMM.

(3) For front frame assemblies removed from engines that had composite bypass ductsinstalled, ship the front frame assembly to a facility approved to accomplish the frontframe assembly eddy current corrosion inspection in accordance with instructions inService Bulletin TFE731-72-5228RWK. Refer to Table 13 for a list of approved facilities.Indicate on the part identification tag and shipping documents that the front frameassembly was removed for compliance with Service Bulletin TFE731-72-5222. Specifythat the front frame assembly was removed from an engine that had composite bypassducts and that an eddy current corrosion inspection IS required.

Table 13. Facilities Authorized to Accomplish Eddy Current Corrosion Inspection

Honeywell International Inc.Attn: Front Frame Eddy Current Corrosion Inspection Fast Shop1944 E. Sky Harbor CirclePhoenix, AZ 85034





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Table 13. Facilities Authorized to Accomplish Eddy Current Corrosion Inspection (Cont)

StandardAero AugustaBush Field Airport1550 Hanger RdAugusta, GA 30906-9684

Duncan Aviation3701 Aviation RoadLincoln NE 68524

(4) If the front frame assembly is rejected, refer to Table 9 for replacement front frameassembly part numbers that may be used as replacement parts.

(5) For front frame assemblies removed from engines that had aluminum fan ducts installed,rework the front frame assembly in accordance with Paragraph 3.C.

NOTE: If the front frame assembly was removed from an engine that had aluminumfan ducts installed and is being shipped to another facility for the chemicalconversion treatment and application of epoxy coating, make sure to tag thepart as removed for compliance with Service Bulletin TFE731-72-5222.Specify that the front frame assembly was removed from an engine that hadaluminum fan ducts installed and that an eddy current corrosion inspectionIS NOT required.

(6) Reassemble the engine with a new or reworked front frame assembly identified with anapplicable part number listed in Table 9. Refer to the instructions in the engine LMMand HMM.

(7) Upon completion of engine reassembly, check and ensure proper engine operation inaccordance with the engine test instructions.

(8) Make an entry in the engine log book noting date of compliance, engine operating time,part number(s) and serial number(s) of installed component(s) (as applicable), andcompliance with this service bulletin and service bulletin revision number.

(a) If a pre Service Bulletin TFE731-72-5217 front frame assembly was replacedwith front frame assembly, PN 3060421-3, PN 3060439-2, or PN 3061505-4(as applicable), also note compliance with Service Bulletin TFE731-72-5217.

(9) Complete the Certificate of Compliance form in Paragraph 4.B. and send to Honeywell.

C. Rework of Front Frame Assemblies Removed From Engines That Had Aluminum FanBypass Ducts Installed

(1) Use poly-plus plastic media (20 to 30 mesh), abrasive plastic media (Abrasives Unlimited- Southwest, ITS-AUI Inc., 4857 S 36th St., Phoenix, AZ 85040) to plastic media blastthe front frame assembly aft flange in preparation for chemical film treatment andapplication of epoxy paint. Refer to Figure 1.

(2) Use SAE AMS-T-21595, masking tape (Commercial Item Description A-A-883)(commercially available) to mask off aft flange to prevent chemical film conversionsolution from contacting areas not to be treated. Refer to Figure 1.





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Figure 1. (Sheet 1 of 1) Aft Flange Surfaces for Chemical Conversion Treatment and Epoxy Paint





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(3) Brush, swab, or spray on MIL-DTL-81706, alodine coating material (Alodine 1200) for0.5 to 3.0 minutes to achieve required coating in accordance with MIL-C-5541, Class1A or AMS 2473.

(4) Use SAE AMS-T-21595, masking tape (Commercial Item Description A-A-883)(commercially available) to mask off the surfaces adjacent to the aft flange that are notto receive 535K020/930K097, primer (green epoxy-amine). Refer to Figure 1.

(5) Prepare 535K020/930K097, primer (green epoxy-amine) in accordance with IRM72-IR-02, Appendix 2 - Repair, Method Number 402J. Hand-swab 535K020/930K097,primer (green epoxy-amine) on all aft flange attachment bolt hole inner diameters (IDs).

NOTE: Bushing IDs and face surfaces are not to be painted (refer to Figure 1).Application of 535K020/930K097, primer (green epoxy-amine) to the outerdiameter (OD) of bushings is recommended to provide a seal at thebushing/flange interface.

(6) Spray a thin coat (approximately 0.0006 to 0.0012 inch (0.015 to 0.030 mm) thick) of535K020/930K097, primer (green epoxy-amine) on the aft flange surfaces as indicatedin Figure 1. Allow 535K020/930K097, primer (green epoxy-amine) to cure in accordancewith the manufacturer's instructions.

(7) Reidentify the front frame assembly, as applicable, by adding part number suffix -P35092after the existing part number using the vibropeen method to a maximum depth of 0.010inch (0.25 mm) in accordance with Aerospace Standard AS478-2D. Refer to Table 13.

(8) Proceed to Paragraph 3.B.(6) for reinstallation of the reworked front frame assembly.





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4. Appendix

Appendix A, Acronyms and AbbreviationsA.

(1) Refer to Table 14 for a list of the acronyms and abbreviations used in this service bulletin.

Table 14. List of Acronyms and Abbreviations

Full TermTerm

Air Transport AssociationATA

commercial and government entityCAGE

compressor zone inspectionCZI

Export Control Classification NumberECCN

Federal Aviation AdministrationFAA

heavy maintenance manualHMM

inner diameterID

Inspection and Repair ManualIRM

light maintenance manualLMM

Maintenance Service ProgramMSP

outer diameterOD

Occupational Safety and Health AdministrationOSHA

Parts Manufacturer ApprovalPMA

part numberPN

quantityQty

Special Federal Aviation RegulationSFAR

service information letterSIL





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B. Appendix B, Certificate of Compliance

To: Operator or Service Center Performing Modification

Upon modification of equipment, please fill in the information requested below, then mail or email the completedCertificate of Compliance (refer to Figure 2) to:

Honeywell International Inc.111 S 34th Street, Mail Stop 503-320Phoenix, AZ 85034-2802Email: [email protected]

Figure 2. (Sheet 1 of 1) Certificate of Compliance





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EMAIL [email protected]





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Documents

TFE731-72-5222 Revision 2, 13 Oct 2021 Page