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ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - On Wing Stage 3 LPTR Disk Ultrasonic Inspection

GE PROPRIETARY INFORMATION The information contained in this document is GE proprietary information and is disclosed in con fi dence. It is the property of GE and shall not be used, disclosed to others or reproduced without the express written consent of GE, including, but without limitation, it is not to be used in the creation, manufacture, development, or derivation of any repairs, modi fi cations, spare parts, designs, or con fi guration changes or to obtain FAA or any other government or regulatory approval to do so. If consent is given for reproduction in whole or in part, this notice and the notice set forth on each page of this document shall appear in any such reproduction in whole or in part. The information contained in this document may also be controlled by U.S. export control laws. Unauthorized export or re-export is prohibited.All technical documentation and information contained herein, with respect to assembly and disassembly, cleaning, inspection methods and limits, repair methods and limits, operational limits, life limits and the like, have been developed and approved for use with engines and parts that have been manufactured and/or approved by GE and that have been maintained in accordancewith GE technical documentation and recommendations. GE has no contractual or legal obligation for, nor knowledge of, non-GE-approved parts and repairs. Accordingly, this document is not intended to apply to non-GE-approved parts and repairs. Copyright (2010) General Electric Company, U.S.A.

August 09, 2010 CF6-50 S/B 72-1312 Revision 01, October 18, 2010 PAGE 1 of 28

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ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - On Wing Stage 3 LPTR Disk Ultrasonic Inspection

TRANSMITTAL INFORMATION REVISION 1 TO SERVICE BULLETIN 72-1312 Revision 1 is issued to update paragraphs 1., P LA N N I N G I N F O R M A T I O N and 4., A P P E N D I X

- A I N S P E C T I O N P R O C E D U R E F S T P R O C E D U R E 2 0 7 5

. The original was issued August 09, 2010. Revision bars in the left margin identify changes. 1. P LA N N I N G I N F O R M A T I O N A. E f f e cti v i ty CF6-45A/A2 CF6-50A/C/CA/C1/C2/C2B/C2D/C2F/C2R/E/E1/E2 B. D e s cr i pt i o n This Service Bulletin recommends a one-time on wing ultrasonic inspection (USI) of the forward spacer arm of the stage 3 low pressure turbine rotor (LPTR) disk. N OT E : This Service Bulletin is in addition to CF6-50 S/B 72-1307, Revision 01, that de fi nes the repetitive inspection requirements for the stage 1 and stage 2 high pressure turbine (HPT) blade airfoils along with recommendations for performing continuous engine trend monitoring, troubleshooting, and conditional maintenance checks. This Service Bulletin is in addition to CF6-50 S/B 72-1313, Revision 01, that defi nes an on wing vibration check. C. C o m p l i a n ce Category 2 GE recommends that you do this Service Bulletin within 30 days of the issue date of this Service Bulletin revision unless exempt (see N OT E 1 ) or already complied with. N OT E 1 : E n g i n e s e xe m p t fro m co m p l i a n ce w i t h t h i s S e r v i ce B u l l e t i n : Engines which have complied with CF6-50 S/B 72-1309 after June 03, 2010. N OT E 2 : This Service Bulletin can be accomplished on wing. This Service Bulletin is offered to improve the reliability or performance of your GE product, or to help prevent the occurrence of the event or condition described in this Service Bulletin. If the operator elects not to participate in the bulletin, that decision will be taken into consideration by GE in evaluating future product performance issues that may arise in the operator’s fl eet. D. C o n c u r re n t R e q u i re m e n ts None. August 09, 2010 CF6-50 S/B 72-1312 Revision 01, October 18, 2010 PAGE 2 GE PROPRIETARY INFORMATION - Subject to the restrictions on the cover or fi rst page.

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ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - On Wing Stage 3 LPTR Disk Ultrasonic Inspection

E. Re a s o n (1) Objective: To reduce signi fi cant events and stage 3 LPTR disk separations. (2) Condition: Cracks have occurred on the inner diameter of the forward spacer arm of the stage 3 LPTR disk. Cracks gone undetected have led to 360 degree through cracks and have resulted in uncontained stage 3 LPTR disk separations. (3) Cause: A high pressure turbine rotor (HPTR) imbalance that drives an excitation of a stage 3 LPTR disk-blade mode initiating an indication that could propagate into a 360 degree through crack that separates the forward spacer arm of the stage 3 LPTR disk, resulting in an uncontained separation. (4) Inspection: This Service Bulletin defi nes a one-time on wing USI to fi nd a cracked stage 3 LPTR forward spacer arm. (5) Substantiation: Substantiation is by analysis and test. The new USI probe was speci fi cally designed to detect cracks in the forward spacer arm of the stage 3 LPTR disk. It has been demonstrated and validated both in the lab and in the fi eld. F. A p p rova l This Service Bulletin contains no modi fi cation information that revises the approved con fi guration and therefore does not require governmental or other regulatory agency approval. G. M a n p owe r After you get access to the stage 3 LPTR disk, you will need approximately 4 man-hours for each engine to do this Service Bulletin. H. We i g h t a n d B a l a n ce Weight and balance are not changed. I. Re f e re n ce s (Use the latest version of these documents) Airbus A300 Aircraft Maintenance Manual (AMM) Boeing 747 Aircraft Maintenance Manual (AMM)
August 09, 2010 CF6-50 S/B 72-1312 Revision 01, October 18, 2010 PAGE 3 GE PROPRIETARY INFORMATION - Subject to the restrictions on the cover or fi rst page.

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ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - On Wing Stage 3 LPTR Disk Ultrasonic Inspection
McDonnell Douglas DC-10-15/DC-10-30 Aircraft Maintenance Manual (AMM) KC-10 Aircraft Maintenance Manual (AMM) GEK 50481, CF6-50 Engine Manual (EM) GEK 28495-2, CF6-50 Illustrated Parts Catalog (IPC) CF6-50 S/B 72-1307, Revision 01, ENGINE - High Pressure Turbine Rotor (72-53-00) - Repetitive Engine Maintenance, Inspections and Troubleshooting to Minimize Stage 1 and Stage 2 HPT Blade Missing Material CF6-50 S/B 72-1309, ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - Stage 3 Low Pressure Turbine Rotor Disk Fluorescent Penetrant Inspection and/or Ultrasonic Inspection at Shop Visit CF6-50 S/B 72-1313, Revision 01, ENGINE - Low Pressure Turbine Rotor (72-00-00) - On Wing Vibration Check All Operators Wire (AOW), Message Number: 08/CF6/017, Subject: CF6-50 Uncontained Event, July 10, 2008 All Operators Wire (AOW), Message Number: 09/CF6/015, Subject: CF6-50 Uncontained Event, April 3, 2009 GEAE internal use only: CID 457197 All Operators Wire (AOW), Message Number: 09/CF6/030, Subject: CF6-50 Uncontained Event, December 21, 2009 All Operators Wire (AOW), Message Number: 10/CF6/017, Subject: CF6-50 Uncontained Event, July 27, 2010 General Electric Company: Amendment 39-16331. Docket No. FAA-2010-0068; Directorate Identi fi er 2010-NE-05-AD; AD 2010-12-10 N OT E : The reference documents listed below are for the engine manufacturer’s internal use only: BPP: 10-72-56-04 Field Support Technology (FST) Procedure 2075 J. P u b l i cat i o n s Af f e cte d None. K. I n te rc h a n g e a b i l i ty Not applicable. L. S of twa re Acco m p l i s h m e n t S u m m a ry Not applicable.
August 09, 2010 CF6-50 S/B 72-1312 Revision 01, October 18, 2010 PAGE 4 GE PROPRIETARY INFORMATION - Subject to the restrictions on the cover or fi rst page.

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ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - On Wing Stage 3 LPTR Disk Ultrasonic Inspection

2. M A T E R I A L I N F O R M A T I O N A. M a te ri a l

- P ri ce a n d Ava i l a b i l i ty (1) Parts necessary to do this Service Bulletin: None. (2) Other Spare Parts: None. (3) Consumables: C o d e N u m b e r D e s c ri pt i o n G-33 Laboratory Grade Glycerin/Water Mixture B. I n d u s t ry S u p p o rt I n fo rm at i o n None. C. C o n fi g u ra ti o n C h a rt None. D. P a rts D i s p os i t i o n An unacceptable (reject) USI fi nding will make the engine unserviceable and require the replacement of the stage 3 LPTR disk. E. T o o l i n g - P ri ce a n d A va i l a b i l i ty T

o o l P a rt N u m b e r D e s c r i pt i o n GE-FQAP-622 Ultrasonic Inspection Kit GE Aviation Quality Technology Center Attn.: FST Tooling Group 10270 St. Rita Lane Cincinnati, OH 45215 U.S.A. Fax: (513) 552-1386 OR E-mail: ndttooling@ge.com

August 09, 2010 CF6-50 S/B 72-1312 Revision 01, October 18, 2010 PAGE 5 GE PROPRIETARY INFORMATION - Subject to the restrictions on the cover or fi rst page.

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ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - On Wing Stage 3 LPTR Disk Ultrasonic Inspection

N OT E : (1) Due to local shipping restrictions customers might have to obtain item G-33 from local sources. To obtain a kit, additional items or replacement tooling, contact Field Support Technology through one of the following methods. Email is the preferred method. E-mail: ndttooling@ae.ge.com OR FAX: (513) 552-1386 OR GE Aviation Field Support Technology 1 Neumann Way MD Q8 Cincinnati OH 45215 U.S.A. 3. A C C O M P L I S H M E N T I N S T R U C T I O N S A. G e n e ra l CA U T I O N : THE ENGINE MUST BE COOLED TO 100 F (37.7 C) DEGREES OR LESS TO PREVENT PERMANENT DAMAGE TO THE ULTRASONIC PROBE. CA U T I O N : THE PROBES ARE DELICATE INSTRUMENTS. PLEASE HANDLE WITH CARE. (1) Prepare the aircraft to provide access to the LPT boroscope plug “B5-3” per applicable AMM procedure. (2) Do a USI of the stage 3 LPTR disk to detect fl aws in the forward spacer arm. Refer to APPENDIX A – INSPECTION PROCEDURE FST PROCEDURE 2075. (3) Replace the engine or return the engine to service per applicable AMM.

August 09, 2010 CF6-50 S/B 72-1312 Revision 01, October 18, 2010 PAGE 6 GE PROPRIETARY INFORMATION - Subject to the restrictions on the cover or fi rst page.

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ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - On Wing Stage 3 LPTR Disk Ultrasonic Inspection

4. A P P E N D I X A

- I N S P E C T I O N P R O C E D U R E F S T P R O C E D U R E 2 0 7 5 (1) Scope: (a) The following sections describe the equipment, technique, and procedure required for conducting an USI of the CF6-50 stage 3 LPTR disk. This technique should be applied when the engine is fully assembled. The purpose of this inspection is to detect cracks that may occur in the forward spacer arm of the stage 3 LPTR disk. Refer to Figure 1 (sheet 1 and 2). (b) This inspection applies to all CF6-50 stage 3 LPTR disks. Access to the stage 3 LPTR forward spacer arm is gained through the “B5-3” borescope port. Refer to Figure 2. (c) This document describes the general procedure and equipment approved to accomplish this inspection. For speci fi c cases where the procedure/equipment described herein cannot be applied in their total content, speci fi c exceptions should be obtained in writing from GE Aviation. (2) Applicable Documents: (a) Appropriate instrument instruction manuals. (3) Personnel Requirements: (a) Personnel performing this inspection shall be certi fi ed in accordance with one of the following:



# . NAS410



# . American Society of Non Destructive Testing (SNT-TC-1A)



# . Air Transport Association Speci fi cation No. 105 (ATA 105)



# . COSAC



# . Locally approved certi fi cation program. (b) Personnel that perform this inspection shall receive practical training in the use of this procedure and must demonstrate pro fi ciency in calibration of the inspection equipment, inspection of hardware, and evaluation of indications before the authority to accept and reject hardware is delegated. (c) Training which may be provided regarding the performance of this inspection does not imply that the requirements of step 4.(3)(a) have been met. (4) Equipment Requirements: (a) The instruments listed in Table 1 are approved for use with this procedure, but are not supplied with the inspection kit. Contact GE Aviation for information regarding approval of additional instruments.

August 09, 2010 CF6-50 S/B 72-1312 Revision 01, October 18, 2010 PAGE 7 GE PROPRIETARY INFORMATION - Subject to the restrictions on the cover or fi rst page.

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ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - On Wing Stage 3 LPTR Disk Ultrasonic Inspection
(b) The following items are supplied with USI kit GE-FQAP-622.

I T E M QTY P A RT N U M B E R D E S C R I P T I O N 1 2 389-071-161 Ultrasonic Probe Assembly 2 1 UT-2075 Calibration Standard 3 1 SGP-127 Calibration Standard Holder 4 2 C-012 Coaxial Cable 5 500 ml G-33 Laboratory Grade Glycerin/Water Mixture (4:1) 6 1 03-409-22C Couplant Dispensing Bottle 7 1 N/A Label 8 1 IM2600 Storm Case w/Foam 9 1 387-008-164 Probe Assembly Guide Tube (guide tube) 10 1 Q404 Action Marker – Size 33 fi ne N O T E : To obtain a USI kit, additional items, or replacement tooling, contact Field Support Technology. Refer to paragraph 2.E., T o o l i n g - P ri ce a n d Ava i l a b i l i ty for contact information. (5) Pre-Part Inspection Preparation: (a) Remove the plug at borescope port “B5-3”. Refer to Figure 2. (b) Perform a visual inspection of the stage 3 LPTR disk forward spacer arm utilizing a “0 degree” borescope. If there is visual evidence of existing through wall cracking, this inspection is not required. Refer to step 4.(11) for disposition. (c) Reference marks on the inside of the fan case and a stage 1 fan blade will be used to track the rotation of the stage 3 LPTR disk during inspection. Place the reference marks as follows: 1 Mark near the leading edge of an arbitrarily chosen stage 1 fan blade using an approved marker. 2 Make another mark on the inside of the fan case that is in line with the mark on the fan blade. N O T E : If there is access to the stage 4 LPT blades through the turbine rear frame (TRF), this marking technique can be used from the AFT side of the engine. Reference marks can be placed on the inside of the TRF and an arbitrarily chosen stage 4 LPT blade.

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ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - On Wing Stage 3 LPTR Disk Ultrasonic Inspection
(6) Initial Equipment Setup: (a) Turn the ultrasonic instrument on and allow it to warm up per manufacturers recommendations or at least 10 minutes. (b) Adjust the instrument to the initial settings listed in TABLE 1. (c) Fill the syringe attached to the ultrasonic probe handle with couplant (4 parts glycerin; 1 part water) in the following manner. 1 Remove the plunger and fi ll the syringe until it is approximately 3/4 full. 2 Replace the plunger and with the wedge assembly pointing up, depress the plunger until all trapped air has escaped. (d) Connect the ultrasonic probe to the ultrasonic instrument with coaxial cable provided. (7) System Calibration: (a) Place the probe on the calibration standard, (Figure 4), so that the probe cams are seated in the radius from the spacer arm to dovetail posts. Depress the syringe plunger to apply a small amount of couplant. (b) Make sure the transducer wedge is seated properly. The wedge is seated properly when the wedge cams are fully extended, fi rmly in the radius, and the wedge is seated fi rmly to the contour of the calibration standard. Refer to Figure 5. (c) Slowly scan the transducer across the calibration standard until the electrodischarge machining (EDM) Notch is located. While scanning, make sure the probe cams are fi rmly seated in the radius. Obtain the peak signal from the EDM notch. (d) Observe the instrument display. The fi rst signal at the left side of the instrument display will be the initial pulse. A second peak signal on the right side of the display, at approximately 9.0 on the horizontal baseline, will be the response from the EDM notch. Refer to Figure 6. (e) Place the initial pulse at 0.0 on the horizontal baseline using the delay control. (f) Adjust the instrument range control to place the leading edge of the EDM notch response to 9.0 on the horizontal baseline. N O T E : If necessary, alternately adjust the delay and range controls to make sure the initial pulse is at 0.0 and the EDM notch response is at 9.0. (g) With the delay control only, position the response from the EDM notch to 5.0. Refer to Figure 7.

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ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - On Wing Stage 3 LPTR Disk Ultrasonic Inspection
(h) Adjust the instrument gain until the response from the EDM notch is set to 80 percent of full screen height (FSH),or the appropriate correction factor. N O T E : Calibration Standard Correction Factors: As a result of the differences in the response resulting from possible variations in the fabrication process, calibration standards may have amplitude correction factors (equivalent responses) applied to them. The Quality Technology Laboratory will establish these equivalent responses by comparing the response from the GE Laboratory Master Standard to the response from each subordinate standard. In cases where an equivalent response is required, this equivalent response applies to the calibration only and does alter the amplitudes speci fi ed for indication evaluation. (i) Scan the transducer across the calibration standard several times to make sure the peak response is obtained. Make sure the signal is at 80 percent FSH, or the appropriate correction factor, and at 5.0 on the horizontal baseline. (j) Record all calibration data on the inspection data sheet, Form 2075-1. (8) Hardware Inspection: (a) Calibrate the equipment in accordance with the calibration section of this document. (b) Gain Access to the stage 3 LPTR disk forward spacer arm through borescope port “B5-3” located at the 4:00 o’clock position aft looking forward (ALF), just below the split line of the LPT case. Refer to Figure 2. (c) Insert the guide tube 387-008-164, into the borescope port and turn the guide until it seats against the outer diameter (OD) of the stage 3 vane. This creates an insertion path for the transducer wedge. (d) Rotate the stage 1 fan blades (or stage 4 LPT blades) until the previously made reference marks are in line. This will be the starting point of the inspection. (e) Insert the transducer wedge into the guide tube 387-008-164 as follows. 1 Compress the cams on the transducer wedge so the wedge can be inserted into the guide tube 387-008-164. Each cam can be compressed one at a time as they enter the guide tube 387-008-164. 2 When the probe shoe clears the inside of the stage 3 vane shroud the cams will automatically actuate into the proper position. Make sure the fl at on the probe handle is pointed up. This will position the bend in the probe stem in the correct position. Angle the probe AFT (handle forward) until it moves between the trailing edges of the stage 3 vanes. 3 Continue to insert the probe until it touches the stage 3 LPTR forward spacer arm. 4 At this point, it may be necessary to remove the guide tube 387-008-164. August 09, 2010 CF6-50 S/B 72-1312 Revision 01, October 18, 2010 PAGE 10 GE PROPRIETARY INFORMATION - Subject to the restrictions on the cover or fi rst page.

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ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - On Wing Stage 3 LPTR Disk Ultrasonic Inspection

5 Actuate the transducer wedge so that it seats properly on the stage 3 LPTR forward spacer arm. The wedge is fully actuated when the alignment mark on the probe stem is in line with the outside surface of the borescope port or guide tube 387-008-164. (f) Move the transducer wedge AFT (handle forward) until the cams on the wedge come in contact with the dovetail posts on the stage 3 LPTR disk. (g) Move the transducer wedge back and forth in the axial direction until both cams are in contact with the disk posts at the same time. Use slight inward pressure on the handle to aid in seating the probe properly. (h) Depress the syringe to apply couplant to the inspection surface. When the cams are in contact with the disk posts, the fl at on the handle is pointed upward, and there is a front surface signal at approximately 2.0 on the horizontal baseline, the probe is seated properly. Refer to Figure 8. CA U T I O N : THE DESIGN OF THE TRANSDUCER WEDGE CAMS ALLOW FOR ROTATION OF THE STAGE 3 LPTR DISK IN ONLY ONE DIRECTION WHILE YOU DO THE SCAN. THE STAGE 3 LPTR DISK SHOULD ALWAYS BE ROTATED IN THE CLOCKWISE (CW) DIRECTION, ALF. THIS WILL KEEP THE WEDGE CAMS IN THE FULLY EXTENDED POSITION AND THE TRANSDUCER WEDGE IN THE PROPER LOCATION. (i) Starting at the previously marked reference, begin rotation of the stage 3 LPTR disk. Maintain slight pressure on the syringe to keep a continuous fl ow of couplant. Scan speed shall not exceed two degree per second. At this scan speed it should take three minutes for one complete revolution of the stage 3 LPTR disk. 1 If the stage 1 fan blades are used to rotate the stage 3 LPTR disk, rotate the fan blades in the counterclockwise (CCW) direction, forward looking aft (FLA). 2 If the stage 4 LPT blades are used to rotate the stage 3 LPTR disk, rotate the turbine blades in the CW direction, ALF. (j) Monitor the instrument display. There should be a small front surface roll at approximately 2.0 on the horizontal baseline. There should also be 10 percent to 20 percent background noise between 3.0 and 7.0 of the instrument display. Refer to Figure 8. (k) If there is no front surface roll or background noise, the transducer wedge is not seated properly or there is insuf fi cient couplant. Stop the rotation of the stage 3 LPTR disk and repeat steps 4.(8)(f) though 4.(8)(j). N O T E : Indication evaluation should be performed at the time an indication is observed. Upon completion of any indication evaluation, return the disk to the area before the evaluation was performed to make sure no area is missed.

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ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - On Wing Stage 3 LPTR Disk Ultrasonic Inspection
(l) Monitor the instrument display for any indication equal to or greater than 60 percent FSH between 3.0 and 7.0 on the horizontal baseline. Indications equal to or greater than 60 percent FSH, shall be evaluated per the indication evaluation section of this Service Bulletin. Refer to Figure 9. (m) Continue the inspection for two complete revolutions of the stage 3 LPTR disk forward spacer arm making sure to overlap the start position to assure full coverage. (n) Once complete, remove the transducer assembly from the engine in the following manner. N O T E : Alternate lighting may be necessary to aid in probe removal. 1 Remove the guide tube 387-008-164 from the borescope port. 2 Move the transducer wedge away from the dovetail posts and the stage 3 LPTR disk forward spacer arm. 3 Pull the retractor pull knob on the probe handle. Refer to Figure 3. Turn the retractor knob CW until it locks in the retracted position. This will place the probe wedge assembly in the proper alignment to extract the probe. 4 Slowly pull the probe outward until the wedge is up against the inner borescope port of the stage 3 vane. 5 Visually align the wedge so it can be pulled through the borescope ports. The probe wedge cams are designed to automatically fold in upon removal. (o) Remove any unused couplant from the transducer syringe before storage. (p) Document the inspection results on the inspection data sheet, Form 2075-1. (9) Post Calibration: (a) A calibration check shall be performed upon the completion of each inspection, whenever any system component or operator is changed, at least once every hour, or any time the operator suspects a change may have occurred in the system. (b) Place the transducer wedge on the calibration standard and depress the syringe plunger to apply a small amount of couplant. (c) Make sure the probe shoe is seated properly and scan the transducer wedge across the calibration standard. Observe the response from the EDM notch. (d) If the calibration repeats within +/- 10 percent FSH of the initial calibration amplitude, the test was acceptable. (e) If the response has decreased by more than 10 percent FSH, the system must be re-calibrated and hardware inspected since the last acceptable calibration must be re-inspected. August 09, 2010 CF6-50 S/B 72-1312 Revision 01, October 18, 2010 PAGE 12 GE PROPRIETARY INFORMATION - Subject to the restrictions on the cover or fi rst page.

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ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - On Wing Stage 3 LPTR Disk Ultrasonic Inspection
(f) If the notch response has increased by more the 10 percent FSH, the system must be re-calibrated prior to inspection of additional hardware and any rejected hardware must be re-inspected. (10) Indication Evaluation: (a) All indications equal to or greater than 60 percent FSH shall be evaluated. (b) Any indication should be evaluated at the time it is found. If an indication is con fi rmed to be valid, the inspection can be discontinued. (c) Assure that the calibration amplitude is 80 percent FSH or the appropriate correction factor. Con fi rm the EDM notch signal is at 5.0 on the horizontal baseline. (d) Reposition the transducer in the suspect area and re-scan. (e) If the indication is still present and equal to or greater than 60 percent FSH, the indication is considered valid. (f) If the indication is not present or less than 60 percent FSH, the indication is not valid and the indication shall be considered acceptable. (11) Disposition Criteria: (a) If there is visual evidence of existing through wall cracking, the disk is not serviceable and shall be removed from service. (b) Any stage 3 LPTR disk with an ultrasonic indication that is equal to or greater than 60 percent FSH between 3.0 and 7.0 on the horizontal baseline shall be considered rejected by this procedure and removed from service. (12) Records: (a) As a minimum, record all requested information on the inspection data sheet, the L P T D i s c/E n g i n e D ata S h e et , and forward to the local GE Aviation representative or directly to GE referencing this Service Bulletin to:

Aviation Operations Center (AOC) GE Aviation Subject: CF6-50 S/B 72-1312 One Neumann Way Cincinnati, OH 45215-1988 U.S.A. OR Aviation Operations Center (AOC) GE Aviation Subject: CF6-50 S/B 72-1312 FAX: (1-513) 552-3329 OR August 09, 2010 CF6-50 S/B 72-1312 Revision 01, October 18, 2010 PAGE 13 GE PROPRIETARY INFORMATION - Subject to the restrictions on the cover or fi rst page.

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ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - On Wing Stage 3 LPTR Disk Ultrasonic Inspection

FAX: 1-877-432-3329 E-mail: geae.aoc@ge.com Subject: CF6-50 S/B 72-1312
TABLE 1 - INITIAL INSTRUMENT SETTINGS U S N 5 8/6 0
BAS I C P L S R CV R P U L S E R RANGE: 0.542 in PULSER: Spike PROBE DELAY: 0.000 uS ENERGY: High VELOCITY: 0.1260 in/uS DAMPING: 150 ohms DISPLAY DELAY: 0.000 uS

R E C E I V E R FREQUENCY: 2-25 MHz BB GAIN: 35.0 dB RECTIFY: Fullwave DUAL: Off REJECT: Off / 0 percent

U S N 5 2 S e ri e s GAIN: 30.0 dB PULSER: Single RANGE: 0.542 in. RECTIFY: Full MATL. VELOCITY: 0.1260 in/uS DAMP: 150 ohms DELAY: 0.000 uS REJECT: 0 percent FREQUENCY: 0.4-10 MHz REP RATE: High

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ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - On Wing Stage 3 LPTR Disk Ultrasonic Inspection

S O N I C 1 0 0 0 a n d 1 2 0 0 S e ri e s P U L S E M E N U : RA N G E M E N U :

GAIN: 40.0 dB RANGE: 0.542 in. PULSE: 50ns DELAY: 0.00 in.

DAMP: 200 ohms VELOCITY: 0.1260 in/us MODE: Single VOLTAGE: 150V R CV R M E N U : DISPLAY: Fullwave FREQUENCY: 5 MHz REJECT: 0 percent

U S M 3 5 GAIN: 40.0 dB

B AS E P U L S E R RANGE: 0.542 in DAMPING: LOW MTL. VELOCITY: 126.0 in/mS POWER: LOW D-DELAY: 0.000 DUAL: OFF P-DELAY: 0.000 PRF MODE: 10

R E CV FINE G>: 0 REJECT: 0 percent FREQUENCY: 0.8 – 8 MHz RECTIFY: FULL-W

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ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - On Wing Stage 3 LPTR Disk Ultrasonic Inspection

E P O C H I I I M o d e l 2 3 0 0 GAIN: 38.0 dB FULLWAVE: Rectify REJECT: 0 percent PULSER: Medium RANGE: 0.542 in DAMPING: 150 ohms VELOCITY: 0.1260 in/us PULSE-ECHO: ZERO: 0.000 us

U S M 2 5 GAIN 40.0 dB

B AS E P U L S E R RANGE: 0.542 in DAMPING: High MTL. VELOCITY: 126.0 in/mS POWER: High D-DELAY: 0.000 DUAL: OFF P-DELAY: 0.000 PRF MODE: 10

R E CV FINE G>: 0 REJECT: 0 percent FREQUENCY: 2.0-20 MHz RECTIFY: FULL-W

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ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - On Wing Stage 3 LPTR Disk Ultrasonic Inspection

Stage 3 LPTR Disc Forward Spacer Arm Initiation Site Figure 1, ( Sheet 1 of 2 )

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ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - On Wing Stage 3 LPTR Disk Ultrasonic Inspection

Stage 3 LPTR Disc Forward Spacer Arm Initiation Site Figure 1, ( Sheet 2 )

August 09, 2010 CF6-50 S/B 72-1312 Revision 01, October 18, 2010 PAGE 18 GE PROPRIETARY INFORMATION - Subject to the restrictions on the cover or fi rst page.

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ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - On Wing Stage 3 LPTR Disk Ultrasonic Inspection

Borescope Port “B5-3” Location Figure 2

August 09, 2010 CF6-50 S/B 72-1312 Revision 01, October 18, 2010 PAGE 19 GE PROPRIETARY INFORMATION - Subject to the restrictions on the cover or fi rst page.

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ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - On Wing Stage 3 LPTR Disk Ultrasonic Inspection

Ultrasonic Transducer Assembly Figure 3

August 09, 2010 CF6-50 S/B 72-1312 Revision 01, October 18, 2010 PAGE 20 GE PROPRIETARY INFORMATION - Subject to the restrictions on the cover or fi rst page.

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ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - On Wing Stage 3 LPTR Disk Ultrasonic Inspection

Calibration Standard and Holder Figure 4

August 09, 2010 CF6-50 S/B 72-1312 Revision 01, October 18, 2010 PAGE 21 GE PROPRIETARY INFORMATION - Subject to the restrictions on the cover or fi rst page.

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ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - On Wing Stage 3 LPTR Disk Ultrasonic Inspection

Calibration Technique Figure 5

August 09, 2010 CF6-50 S/B 72-1312 Revision 01, October 18, 2010 PAGE 22 GE PROPRIETARY INFORMATION - Subject to the restrictions on the cover or fi rst page.

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ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - On Wing Stage 3 LPTR Disk Ultrasonic Inspection

Initial Instrument Display Figure 6

August 09, 2010 CF6-50 S/B 72-1312 Revision 01, October 18, 2010 PAGE 23 GE PROPRIETARY INFORMATION - Subject to the restrictions on the cover or fi rst page.

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ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - On Wing Stage 3 LPTR Disk Ultrasonic Inspection

Calibration on the Instrument Display Figure 7

August 09, 2010 CF6-50 S/B 72-1312 Revision 01, October 18, 2010 PAGE 24 GE PROPRIETARY INFORMATION - Subject to the restrictions on the cover or fi rst page.

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ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - On Wing Stage 3 LPTR Disk Ultrasonic Inspection

Proper Coupling on the Instrument Display Figure 8

August 09, 2010 CF6-50 S/B 72-1312 Revision 01, October 18, 2010 PAGE 25 GE PROPRIETARY INFORMATION - Subject to the restrictions on the cover or fi rst page.

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ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - On Wing Stage 3 LPTR Disk Ultrasonic Inspection

Inspection Zone on the Instrument Display Figure 9

August 09, 2010 CF6-50 S/B 72-1312 Revision 01, October 18, 2010 PAGE 26 GE PROPRIETARY INFORMATION - Subject to the restrictions on the cover or fi rst page.

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ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - On Wing Stage 3 LPTR Disk Ultrasonic Inspection

F o rm 2 0 7 5

- 1

- I N S P E C T I O N DA T

A S H E E T DATE: INSTRUMENT MODEL: INSPECTOR: INSTRUMENT S/N: PROBE P/N: PROBE S/N: CAL. STD. P/N: CAL. STD. S/N:

FREQUENCY: DAMPING: GAIN: RECTIFICATION/ DISPLAY: RANGE: DELAY: VELOCITY: Engine S/N: Engine TSN/CSN: Disc S/N: Disc P/N:
IND. AMP% Baseline Position Comments

1 2 3 4

CALIBRATION ______%. POST CALIBRATION ______% Inspector: ______________________________Date:____________________________ Comments: :

............................................................................................................................... ........

............................................................................................................................... ........

August 09, 2010 CF6-50 S/B 72-1312 Revision 01, October 18, 2010 PAGE 27 GE PROPRIETARY INFORMATION - Subject to the restrictions on the cover or fi rst page.

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ENGINE - Low Pressure Turbine Rotor Assembly (72-57-00) - On Wing Stage 3 LPTR Disk Ultrasonic Inspection

L P T D i s c/ E n g i n e D a ta S h e e t Service provider - who performed the USI Date of the inspection Aircraft Tail number Aircraft Type (e.g. 747, DC10, A300) Aircraft Total Time (TT) - hours Aircraft Total Cycles (TC) - cycles
ESN Engine Position on Aircraft Engine Time Since New (TSN) Engine Cycles Since New (CSN) Engine Time Since Installation (TSI) Engine Cycles Since Installation (CSI) Date of last engine shop visit Engine Time Since Shop Visit (TSV) Engine Cycles Since Shop Visit (CSV)
LPT S3 Disc Serial Number LPT S3 Disc Part Number S3 Disc Total Time S3 Disc Total Cycles S3 Disc Total Time Since Installed S3 Disc Total Cycles Since Installed Date of last stage 3 LPT disc piece part Shop Visit S3 Disc Total Time since Last shop visit (FPI) S3 Disc Total Cycles since last shop visit (FPI)

August 09, 2010 CF6-50 S/B 72-1312 Revision 01, October 18, 2010 PAGE 28 GE PROPRIETARY INFORMATION - Subject to the restrictions on the cover or fi rst page.