Honeywell International Inc.

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Phoenix, Arizona 85034-2802

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Web site: http://portal.honeywell.com/wps/portal/aero

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.

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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.

2 Dec 2008 TPE331-72-A2156

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2 Dec 2008 TPE331-72-A2156

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WARNING: HONEYWELL ASSUMES NO RESPONSIBILITY FOR ANY HONEYWELL EQUIPMENT

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RESULTS.

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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)

2 Dec 2008 TPE331-72-A2156

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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

2 Dec 2008 TPE331-72-A2156

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1. Planning Information

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

3103700-10 TPE331-10N-535S All Conquest 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)

WARNING: 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.

NOTE: 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.

NOTE: 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 72-00-29 72-01-18

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

TPE331-10U-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 72-00-41

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. Material Information

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. Accomplishment Instructions

A. General Information

(1) Obey the precautions.

NOTE: This is a CATEGORY 1, SAFETY service bulletin.

NOTE: Paragraph 4.B. of this service bulletin provides applicable fluorescent penetrant

inspection (FPI) instructions for the first stage turbine disks with serial numbers

listed in Table 2.

NOTE: 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.

CAUTION: 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 instructions in Service Bulletin TPE331-72-0180.

NOTE: 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.

NOTE: It is not necessary to de-blade the first stage turbine rotor assembly to

accomplish 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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(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 85034-3440

Attn: Fast Shop

Contact: Honeywell NDE Engineering

Fax: 602-365-4577

NOTE: It is not necessary to de-blade the first stage turbine rotor assembly to accomplish

this inspection.

(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

maintenance 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 the Compliance Certificate form in Paragraph 4.A. and send to Honeywell.

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4. Appendix

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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FAX TO U.S.A.

(602) 231-3014

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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.

NOTE: 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.

NOTE: 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.

NOTE: 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.

NOTE: Pre/post cleaning shall be performed by qualified personal only.

NOTE: 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.

WARNING: 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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3 Maintain temperature of cleaning solution at 150 ±10 F (66 ±6 C).

CAUTION: DO NOT IMMERSE TURBINE DISKS IN SOLUTION

FOR MORE THAN 30 MINUTES, THIS INCLUDES

RE-CLEANING.

NOTE: 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.

WARNING: 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.

NOTE: 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.

NOTE: 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.

NOTE: 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.

NOTE: Rinse water shall be free of contaminants that could leave

residue or that is detrimental to the inspection of the part.

NOTE: Pre-rinse shall occur under UV lighting.

NOTE: 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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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.

NOTE: Rinse water shall be free of contaminants that could leave residue

or that is detrimental to the inspection of the part.

NOTE: Final-rinse shall occur under UV lighting.

NOTE: 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.

NOTE: Drying time shall be only that necessary to adequately dry the

turbine disk.

NOTE: Turbine disks shall not be placed in oven with pooled water on

surfaces.

NOTE: 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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2 Remove turbine disk from oven immediately after drying.

(g) Apply developer to turbine disk.

NOTE: Components shall be completely dry before developer application.

NOTE: 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.

NOTE: For adequate coverage it may be necessary to adjust (flip or rotate)

components in the dust chamber.

NOTE: Inspection shall be completed 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.

NOTE: When handling parts, care should be taken to avoid smudging or

eliminating indications by excessive or careless handling.

NOTE: 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.

NOTE: Eyeglasses equipped with permanently tinted or light sensitive

(Photo chromatic) lenses shall not be worn while processing or

inspecting parts.

NOTE: 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.

NOTE: Background fluorescence is not permitted on turbine disk bore

or on adjacent forward and aft surfaces.

NOTE: An indication is defined as, a response or evidence from a

fluorescent penetrant inspection.

NOTE: 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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NOTE: 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.

NOTE: 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.

NOTE: 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.

NOTE: Indications which, after interpretation, are deemed to be caused

by mechanical 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 relevant 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

indications 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 turbine disk.

1 Clean turbine disk in accordance withParagraph 4.B.(2)(a)1

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