# Dowty Propellers Service Bulletin 61-A1124: Revision 2 - Rights: © Dowty Propellers. Filed by the FAA in regulations.gov docket FAA-2010-1270; AD 2005-25-10 R1 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Dowty Propellers Service Bulletin 61-A1124](https://openairdocs.org/service-documents/dowty-propellers/61-a1124.md) - Title as filed: U.S. DOT/FAA - Service Bulletin 61-A1124 Transmittal Letter for Revision No.2 - Pages: 35 - PDF: https://openairdocs.org/files/sha256/3b/e2/3be2e012242d8751cbc853b2195c1f6cffa865978d19745890181e04fd028f8c - Page: https://openairdocs.org/service-documents/dowty-propellers/61-a1124/file/3be2e012242d ## Text Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 Part of GE’s Aviat i on Business SERVICE BULLETIN . SERVICE BULLETIN SERVICE BULLETIN 61-A1124 TRANSMITTAL LETTER FOR REVISION NO.2 Dated Aug 25/10 1. REASON A. Service Bulletin compliance changed to ALERT. B. To advise operators that the requirement for the continued inspection of hub assemblies Part No. 660709201 can be terminated by the introduction of a revised hub assembly in accordance with Dowty Propellers Service Bulletin 61-1144. C. Service bulletin reformatted. 2. ACTION A. Remove and destroy existing pages 1 to 3 of the service bulletin and replace with revised pages 1 to 3 dated Aug 25/10. B. Remove and destroy existing pages 1 to 6 of Appendix A and replace with revised pages 1 to 6 dated Aug 25/10. C. Remove and destroy existing pages 1 of Appendix B and replace with revised pages 1 dated Aug 25/10. D. Remove and destroy existing pages 1 to 13 of Appendix C and replace with revised pages 1 to 13 dated Aug 25/10. E. Remove and destroy existing pages 1 to 7 of Appendix D and replace with revised pages 1 to 7 dated Aug 25/10. Dowty Propellers Anson Business Park, Cheltenham Road East, Gloucester, GL2 9QN ENGLAND Telephone: 01452 716000 Facsimile: 01452 716001 ### Page 2 (No text on this page.) ### Page 3 Page 1 of 3 ALERT CAGE CODE: U7387 For Europe, Africa, India and Middle East contact: Dowty Propellers Anson Business Park Cheltenham Road East, Gloucester, GL2 9QN, United Kingdom T: + 44 (0)1452 716000 F: + 44 (0)1452 716001 For Asia, Australasia and the Pacific contact: Dowty Propellers Anson Business Park Cheltenham Road East, Gloucester, GL2 9QN, United Kingdom T: + 44 (0)1452 716000 F: + 44 (0)1452 716001 For the Americas contact: Dowty Propellers 114 Powers Court Sterling, VA 20166 United States of America T: + 1 (703) 421 4434 F: + 1 (703) 450 0087 Copyright (2010), GE Aviation Systems Ltd., U.K The information contained in this document is GE Aviation Systems Ltd proprietary information and is disclosed in confidence. I t is the property of GE Aviation Systems Ltd and shall not be used, disclosed to others or reproduced without the express written consen t of GE Aviation Systems Ltd, including, but without limitation, it is not to be used in the creation, manufacture, development, or derivation of any repairs, modifications, spare parts, designs, or configuration chan ges or to obtain FAA, CAA, EASA, 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. All technical documentation and information contained herein, with respect to assembly and disassembly, cleaning, inspection me thods and limits, repair methods and limits, operational limits, life limits and the like, have been developed and approved for use w ith this equipment and parts that have been manufactured and/or approved by GE and that have been maintained in accordance with GE technical documentation and recommendations. GE has no contractual or legal obligation for, nor knowlege of, non-GE-approved p arts and repairs. Accordingly, this document is not intended to apply to non-GE-approved parts and repairs. Manual Ref: 61-10-24 SERVICE BULLETIN PROPELLER - HUB WALL CRACKING 1. Planning Information WARNING: FAILURE TO IMPLEMENT ANY INSTRUCTION GIVEN HERE, AS AMENDED FROM TIME TO TIME BY DOWTY PROPELLERS, MAY ENDANGER HEALTH AND SAFETY . A. B. Effectivity Aircraft affected : Jetstream Series 3100 and 3200 Unit affected : Propeller Part/Type No. : All R333/4-82-F/12 propellers C. Reason (1) On a similar propeller type, there have been reports of cracks originating from around the threaded insert holes of the rear half hub which in one instance has resulted in a complete propeller separation from the engine flange. (2) To inspect for cracks in the rear wall of propeller hub assemblies Part No. 660709201. D. Description (1) Hub assemblies Part No. 660709201 are to be inspected in accordance with Appendix A or Appendix D of this bulletin. Non. Mod. May 07/02 61-A1124 Aug 25/10 (Revision 2) ### Page 4 Pa r t of GE ’s Avi ati on Busi ne ss SERVICE BULLETIN Page 2 GE Aviation Systems Ltd Proprietary Information Use o r disclosure of data contain ed on this sheet is su bject to the rest rictions on the cover or first page ALERT E. Compliance: ALERT (1) Hub assemblies Part No. 660709201 included in propellers installed on aircraft must: - have a repetitive inspection at an interval of not more than 1000 flying hours. (2) Hub assemblies Part No. 660709201 included in propellers in storage must: - have a repetitive inspection at an interval of not more than 1000 flying hours after the installation of the propeller to an aircraft. (3) Hub assemblies Part No. 660709201 in storage must: - have a repetitive inspection at an interval of not more than 1000 flying hours after the installation of the hub assembly onto an aircraft. (4) The requirement for the continued inspection of hub assemblies Part No. 660709201 can be terminated by the introduction of a revised hub assembly in accordance with Dowty Propellers Service Bulletin 61-1144. F. Approval (1) This service bulletin was approved and classified as MANDATORY by the United Kingdom Civil Aviation Authority. The technical content of this bulletin which affects airworthiness was approved by a representative of the United Kingdom Civil Aviation Authority dated Apr 24/02. G. Manpower (1) Normal time for propeller removal and installation plus approximately 0.5 manhour to carry out the NDT inspections. NOTE : The above manhours are given for shop planning purposes only. Dowty Propellers will not be responsible for the cost of these manhours. The estimate assumes that the equipment has been placed in a maintenance status and does not include preparation or administrative functions. H. Material (1) None. I. Tooling (1) Equipment and materials as listed in Appendix A or Appendix D of this bulletin. Equipment in Appendix A, para 2.B. and 2.C. and Appendix D, para 2.B. is available from Dowty Propellers on request. J. Weight and Balance (1) None. May 07/02 61-A1124 Aug 25/10 (Revision 2) ### Page 5 Pa r t of GE ’s Avi ati on Busi ne ss SERVICE BULLETIN Page 3 GE Aviation Systems Ltd Proprietary Information Use o r disclosure of data contain ed on this sheet is su bject to the rest rictions on the cover or first page ALERT K. References (1) Aircraft Maintenance Manual. (2) Dowty Propellers Aircraft Maintenance Manual Pub. No. 1008. (3) Dowty Propellers Component Maintenance Manual 61-10-24. (4) Appendices A, B, C and D of this bulletin. L. Other Publications Affected (1) None. 2. Material Information A. None. 3. Accomplishment Instructions A. Embodiment Instructions (1) Inspect the propeller hub rear half rear wall to the instructions at Appendix A or Appendix D of this bulletin. Record all data from the inspections carried out on Appendix B and forward all reports to Dowty Propellers as per para 3. B. (1). Defective hubs, if any, are to be returned to Dowty Propellers for further investigation. B. Reporting Instructions (1) Reports of all inspections are to be forwarded by FAX to the Technical Support Manager, Dowty Propellers, Fax. No. 44 1452 716001. The following information is required. (a) Hub serial number. (b) Hub total flying time since new. (c) Hub flying time since overhaul. (d) Hub crack details if found, or report ‘Satisfactory’ if uncracked. (e) Confirmation of use of NDT methods specified in this service bulletin. (f) A photocopy of the hub log cards. C. Recording Instructions (1) Record the compliance with the instructions of this service bulletin in the propeller log book. May 07/02 61-A1124 Aug 25/10 (Revision 2) ### Page 6 (No text on this page.) ### Page 7 Pa r t of GE ’s Avi ati on Busi ne ss SERVICE BULLETIN Page 1 of 6 GE Aviation Systems Ltd Proprietary Information Use o r disclosure of data contain ed on this sheet is su bject to the rest rictions on the cover or first page ALERT APPENDIX A THE ULTRASONIC INSPECTION OF THE JETSTREAM PROPELLER HUB (REAR HALF) 1. Introduction A. This technique is designed for the detection of fatigue cracking originating from and around the threaded insert holes. (Figure 1). B. This technique will necessitate removal of the propeller. It is not necessary to remove the backplate. C. The scan area as shown in Figure 1 must be clean and free from surface damage. 2. Equipment Required A. Ultrasonic flaw detector operating in the 1 to 15 Mhz range. (A Sonatest Masterscan 335 was used in the preparation of this technique, operating at 15 Mhz). B. A 3 mm (0.125 in) diameter 5Mhz longitudinal probe type No. Panametrics V1091 or equivalent. C. Reference block Part No. DAPT 09-0001-00 detail 9 (Apply to Dowty Propellers for a manufacturing drawing. Appendix C includes NDT 5DAP which is required for the manufacture of the reference block). D. Suitable couplant. 3. Calibration Procedure. A. Using a suitable couplant, place the probe on the reference block. B. Using standard calibration procedure establish the probe zero position. C. By probe movement identify the signal from the flat bottom hole and set at 6.0 on the timebase. (See Figure 3). D. Maximise this signal and set amplitude to 80% full screen height. (See Figure 3). 4. Inspection Procedure A. Apply couplant to hub mounting face in scan area and position probe as shown in Figure 1. B. A back wall echo will appear at approx. 6.0 on the timebase. (See Figure 4). This signal will vary in amplitude from 5 - 100% full screen height due to the inside face geometry. C. Scan 360 _ of scan area. D. Discontinuity indications may appear at any position along the timebase, between 1.0 and the back wall echo signals. They may appear as a single indication or a multiple peak indication as shown in Figure 5. 5. Inspection Standard A. Any indication which, after careful cross-checking of calibration procedure, is 20% of full screen height or more is to be considered as a defect and rejected. NOTE : Indications from the thread flanks may appear up to 15% full screen height. (See Figure 4). B. Mark up a ’Status Report’ reproduced from Appendix B of this service bulletin. Supply all the information required in lines 1 to 9. Record all data from the inspection and FAX to the Product Support Manager, Dowty Propellers, Fax. No. 44 1452 716001. C. Rejected hubs are to be returned to Dowty Propellers for further investigation. May 07/02 61-A1124 Aug 25/10 (Revision 2) Appendix A ### Page 8 Pa r t of GE ’s Avi ati on Busi ne ss SERVICE BULLETIN Page 2 of 6 GE Aviation Systems Ltd Proprietary Information Use o r disclosure of data contain ed on this sheet is su bject to the rest rictions on the cover or first page ALERT Scan Areas A Figure 1 61-10-27 May 07/02 61-A1124 Aug 25/10 ( Revision 2) Appendix A ### Page 9 Pa r t of GE ’s Avi ati on Busi ne ss SERVICE BULLETIN Page 3 of 6 GE Aviation Systems Ltd Proprietary Information Use o r disclosure of data contain ed on this sheet is su bject to the rest rictions on the cover or first page ALERT Possible Crack Orientation Figure 2 61-10-27-1 May 07/02 61-A1124 Aug 25/10 (revision 2) Appendix A ### Page 10 Pa r t of GE ’s Avi ati on Busi ne ss SERVICE BULLETIN Page 4 of 6 GE Aviation Systems Ltd Proprietary Information Use o r disclosure of data contain ed on this sheet is su bject to the rest rictions on the cover or first page ALERT Signal From Reference Block Figure 3 May 07/02 61-A1124 Aug 25/10 (Revision 2) Appendix A ### Page 11 Pa r t of GE ’s Avi ati on Busi ne ss SERVICE BULLETIN Page 5 of 6 GE Aviation Systems Ltd Proprietary Information Use o r disclosure of data contain ed on this sheet is su bject to the rest rictions on the cover or first page ALERT Back Wall Echo And Thread Signal Figure 4 Appendix A May 07/02 61-A1124 Aug 25/10 (Revision 2) ### Page 12 Pa r t of GE ’s Avi ati on Busi ne ss SERVICE BULLETIN Page 6 of 6 GE Aviation Systems Ltd Proprietary Information Use o r disclosure of data contain ed on this sheet is su bject to the rest rictions on the cover or first page ALERT Typical Crack Signal Figure 5 Appendix A May 07/02 61-A1124 Aug 25/10 (Revision 2) ### Page 13 Pa r t of GE ’s Avi ati on Busi ne ss SERVICE BULLETIN Page 1 of 1 GE Aviation Systems Ltd Proprietary Information Use o r disclosure of data contain ed on this sheet is su bject to the rest rictions on the cover or first page ALERT APPENDIX B STATUS REPORT THE ULTRASONIC INSPECTION OF THE JETSTREAM PROPELLER HUB (REAR HALF) 1. Operator ............................................................. 2. Aircraft Serial No. .............................................. 3. Propeller Installation (delete whichever is not applicable) 4. Propeller Serial No. ......................................... 5. Hub Serial No. .................................................. 6. Hub total flying hours since new ..................... Flying Hours 7. Hub total flying hours since overhaul ..................... Flying Hours 8. Crack indications and details if any (illustrate above) ..................................................................... ...................... .............................................................................................................................................................................. Report ‘Satisfactory if no cracks are found. 9. Inspectors stamp or signature ............................................................................................... ............................... 61-10-27-2 May 07/02 61-A1124 Aug 25/10 (Revision 2) Appendix B Left Right ### Page 14 (No text on this page.) ### Page 15 Pa r t of GE ’s Avi ati on Busi ne ss SERVICE BULLETIN ALERT Page 1 of 13 GE Aviation Systems Ltd Proprietary Information Use o r disclosure of data contain ed on this sheet is su bject to the rest rictions on the cover or first page APPENDIX C NDT 5DAP ULTRASONIC FLAW DETECTION 1. Scope. A. NDT 5DAP supersedes NDT 5 for all future Dowty Aerospace Propellers contracts. Where existing drawings/documents call up NDT 5, NDT 5DAP must be used in lieu. B. This specification explains the control and calibration requirements for all ultrasonic inspection equipment (sets, probes and reference blocks) at DAP. Sub-contracting agencies must also meet the requirements described here-in when inspecting components for DAP . Wherever possible National or International standards have been referenced, this is planned to reduce the need for frequent re-issues, and make this specification easier to adhere to. C. Individual inspection procedures are issued at DAP as separate documents. E.g. for Immersion longitudinal or Contact etc. In addition to these procedures an individual technique must be raised to each component or part number. These procedures and techniques must be approved by an appropriate level III NDT engineer, and, technique numbers must be referenced on the relative drawing or layout. Sub- contracting agencies must maintain Procedures and techniques relevant to their own equipment. D. The requirements to carry out ultrasonic flaw detection on raw materials are given in BS L100 and BS S100 such ultrasonic inspection is normally the responsibility of the supplier. When carried out at DAP, the methods and standards referred to in the British Standards shall be applied. Sample inspection may be applied in this case. E. Where parts are manufactured by DAP on a sub-contract basis, the ultrasonic inspection requirements of the main contractor will apply unless agreement has been reached to apply this specification. F. Repair and overhaul ultrasonic inspection of parts for the purpose of detection of in-service defects, is covered by techniques associated with service bulletins or Ministry of Defence instructions, usually servicing instructions (SI’s) or special technical instructions (STI’s). These techniques are usually derived from product support techniques prepared by DAP NDT technicians. NOTE : Where deemed necessary DAP may use the product support technique system for cases not covered by paragraph F. When the repair or overhaul of a part uses methods or processes used on production to which ultrasonic inspection would apply, the same inspection technique shall be applied to the repair of the used part. 2. Personnel Requirements. A. Personnel operating this inspection procedure at DAP must be qualified in accordance with the requirements of NDT 10DAP. Sub-contracting agencies must maintain their own personnel certification scheme, this in turn, must be approved by DAP. May 07/02 61-A1124 Aug 25/10 (Revision 2) Appendix C ### Page 16 Pa r t of GE ’s Avi ati on Busi ne ss SERVICE BULLETIN ALERT Page 2 of 13 GE Aviation Systems Ltd Proprietary Information Use o r disclosure of data contain ed on this sheet is su bject to the rest rictions on the cover or first page 3. References A. BS L100 Inspection & testing of wrought aluminium and aluminium alloys. B. BS S100 Inspection & testing of wrought steel. C. ASTM E 114 Practice for ultrasonic pulse-echo straight beam testing by the contract method. D. ASTM E 127 Practice for fabricating and checking aluminium alloy ultrasonic standard reference blocks. E. ASTM E 214 Practice for immersed ultrasonic examination by the reflection method using pulsed longitudinal waves. F. ASTM E 317 Practice for evaluating performance characteristics of pulse-echo testing systems without the use of electronic measurement instruments. G. NDT 10DAP Approval of personnel for NDT Inspection. 4. Procedure and Techniques A. The procedures in use at DAP are separate documents to this specification. In addition to the procedures, an individual technique for each component or part number is required. (See paragraph 1.C.). As a minimum each technique shall include the following:- (1) Company Name (2) Technique Number (3) Related Inspection Procedure (4) Acceptance Class (Refer to international/national standards or drawing requirements) (5) Inspection Scan Cover (6) Part No. & Material (7) Manufacturing Stage (8) Transducer Type Diameter & Frequency (9) Couplant (10) Transfer Method (If Used) (11) Reference Standards Appendix C May 07/02 61-A1124 Aug 25/10 (Revision 2) ### Page 17 Pa r t of GE ’s Avi ati on Busi ne ss SERVICE BULLETIN ALERT Page 3 of 13 GE Aviation Systems Ltd Proprietary Information Use o r disclosure of data contain ed on this sheet is su bject to the rest rictions on the cover or first page 5. Equipment Calibration Requirements. A. Electronic Flaw Detector Unit. (1) Calibration Requirements:- (a) Electronic Flaw Detector units which are to be used for immersion techniques are to be calibrated annually in accordance with the procedure stated in paragraphs 5.A.(2) (a) to (e). This is to be carried out by a level II or III approved NDT Technician and tagged with a calibration label. All calibration graphs are to be kept on file in the calibration control area. (b) Electronic Flaw Detector units which are to be used in the contact mode alone are to be calibrated in accordance with the procedure stated in paragraphs 5.A (2) (a), (b) and (e). This calibration is to be carried out be a level II or II approved NDT Technician on a6 monthly basis and tagged with a calibration label. All calibration graphs are to be kept on file in the calibration control area. (2) Calibration Procedure This procedure is based on the requirements and methods described in ASTM-E-317. If this procedure is used for evaluating contact sets consistent and uniform coupling must be ensured. When used for immersion equipment ensure the probe exit surface and test blocks are free form air bubbles, always allow time for equipment to stabilise. (a) Horizontal limit and linearity Select an appropriate test block that when coupled to the search unit (either by contact or immersion) will produce eleven back reflections on the flaw detector which is being checked. Use the instrument gain, delay and calibration settings to set the leading edge of the third and ninth back reflection at 20% and 80% scale division respectively (when reading reflection positions always set at the amplitude of that reflection to 50% full screen height). Once the third and ninth reflections are positioned at 20% and 80%, read and record the scale position of each other multiple. Interpretation of results:- The horizontal limit is given by the maximum available trace length falling within the screen graticule. This must, in all cases be 100%. Failure to obtain full scale deflection may indicate an equipment malfunction. Horizontal linearity results are best plotted in graphical form as shown in figure 3. The deviation is given by the displacement (in % of full scale) from the straight line through the set up points, which represents ideal linearity. The maximum displacement allowed is 5% of full scale. May 07/02 61-A1124 Aug 25/10 (Revision 2) Appendix C ### Page 18 Pa r t of GE ’s Avi ati on Busi ne ss SERVICE BULLETIN ALERT Page 4 of 13 GE Aviation Systems Ltd Proprietary Information Use o r disclosure of data contain ed on this sheet is su bject to the rest rictions on the cover or first page (b) Vertical limit and linearity This check requires the use of a test block which, when coupled to a suitable search unit will produce signals having an amplitude ratio of 2 to 1 on the flaw detector being examined. (Signals do not have to be successive or in any particular order). Designate these signals HA and HB (HA being larger) and ensure that there is sufficient range in the gain control to vary HA from 10% fsh to 100% fsh. Set signal H A to 60% fsh, this should give a resultant H B signal of 30% fsh (some deviation allowed see Table 1). Once this is set adjust the gain control to increase H A up to 100 fsh in increments of 10% or less. At each step read and record the amplitude of H A and corresponding amplitude H B. Return gain setting to original position and check that H A and HB are also at original levels. Now, reduce gain to bring HA to 10% fsh in increments of 10% or less, read and record HA/HB values at each increment. Interpretation of results:- Vertical limit is given by the maximum vertical deflection within the graticule range that can be obtained from a large reflector. This figure must in all cases be 100% of full scale deflection failure to obtain full scale deflection may indicate an equipment malfunction. Vertical linearity results are best displayed graphically as shown in figure 3. Ideal linearity is indicated by a line from the origin through the set up point (HA60, HB30) to full scale. Actual linearity must be within ± 5% of ideal linearity. (c) Resolution Any method for determination of equipment resolution may be used, if authorised by an approved level III NDT Engineer. This section describes one method, it is an overall system check, therefore it may be used for both search units and flaw detector sets. This check requires the use of test block number DAPT 09-0045-00. The block incorporates both front and back surface flat bottom hole references of 2/64, 3/64 and 5/64ths ″ diameter, each at distances of 0.060″, 0.125″ and 0.250″ from the respective front or back surface (see drawing DAPT 09-0045-00). First, couple the search unit to the near surface check area of the block, and determine by careful probe movement the smallest hole diameter detectable and the shortest metal trace distance it can be resolved from the entry surface indication. A hole is said to be resolved when a signal of 80% fsh can be established from that hole; it is clearly separated from the adjacent interface indication down to at least 20% fsh, and there are no residual indications over 20% fsh throughout the test region. Next move the probe to the back surface check section of the block and repeat process, this time establish the smallest hole size resolvable, at the shortest metal travel distance from the back wall echo. Interpretation of results:- Record the smallest resolvable hole diameter, at the shortest metal path distance from front and back surfaces on the relevant test certificate. This information may then be used to verify the suitability of equipment for a certain task. May 07/02 61-A1124 Aug 25/10 (Revision 2) Appendix C ### Page 19 Pa r t of GE ’s Avi ati on Busi ne ss SERVICE BULLETIN ALERT Page 5 of 13 GE Aviation Systems Ltd Proprietary Information Use o r disclosure of data contain ed on this sheet is su bject to the rest rictions on the cover or first page (d) Sensitivity and Noise This check requires the use of ASTM-E-127 light alloy reference standards, various blocks are suggested for various search unit frequencies:- Test Frequency 0.4-1.5Mhz 1.0-2.5Mhz 2.0-10Mhz 5.0300 to 2.0300 to 1.0300 to 8.0300 6.0300 5.0300 With the instrument sensitivity at maximum, determine the smallest hole size that will give an indication having an amplitude of at least 60% fsh and baseline noise of no more than 20% fsh in the test region. If the dimensions of the test block allow move the search unit just away from the hole and determine that noise at maximum sensitivity exceeds 20% fsh, reduce the gain until 20% fsh is obtained and determine the smallest hole that will then produce a 60% fsh or greater indication. Record the block number, noise level, signal amplitude and reduced gain. If the indication from the smallest hole available exceeds 100% fsh use the gain control to lower the hole indication to 60% fsh, and record the remaining available gain that does not cause the noise to exceed 20% fsh. Interpretation of results:- Record all the information derived i.e. Block No. noise level, signal amplitude, reduced gain (if applicable) and gain in hand (if applicable) on the appropriate calibration certificate. This information may then be used to verify the suitability of equipment for a certain task. (e) Linearity of equipment gain This check relies upon the vertical linearity of the flaw detector previously being established as acceptable [see paragraph 5.A.(2) (b)]. Using test block ASTM-E-127 5-0300 establish by probe manipulation and flaw detector adjustments, an 80% fsh indication from the flat bottomed hole. Note the gain setting and designate this XdB. Next, ensuring constant probe coupling and no other flaw detector alterations adjust the gain settings by the dB amounts shown in Table 2, and record the resultant % fsh indications from the flat bottomed hole. Interpretation of results. All the indications must lie between the maximum and minimum limits as designated in Table 2. B. Calibration and Control of Transducers. (Probes). This section covers calibration of contact probes (both compressional and shear wave) and immersion probes (focused and unfocused). All immersion probes must be calibrated annually, the calibration certificate kept on file and the probe tagged with a calibration due date. For all probe calibrations use a flaw detector calibrated to paragraph 5.A. (1) Contact Transducers Providing a contact transducer meets the set-up and calibration requirements of a specific technique it can be used for that technique, therefore there would be no requirement to assess the transducer for parameters such as dead zone, beam profile, resolution, sensitivity etc. May 07/02 61-A1124 Aug 25/10 (Revision 2) Appendix C ### Page 20 Pa r t of GE ’s Avi ati on Busi ne ss SERVICE BULLETIN ALERT Page 6 of 13 GE Aviation Systems Ltd Proprietary Information Use o r disclosure of data contain ed on this sheet is su bject to the rest rictions on the cover or first page (2) Calibration of Unfocused immersion transducers (a) This procedure is to be carried out on all unfocused water immersion probes. (b) Equipment 1 An immersion tank of suitable size with an adjustable probe manipulator is to be used. 2 A 12,5 mm diameter ball is to be used as the target. 3 An instrument, capable of measurement of 0,025 mm or better is to be used to measure beam width. (c) Procedure NOTE : For the Beam Axis alignment procedure which follows, use the bracketed alternative position when NF is less than 150 mm. 1 Carry out the following calculations. a Calculate the theoretical Near Field (NF) distance for the probe: NF=(D x F) where D = Probe diameter 8c F = Frequency of probe c = Speed of sound in immersion fluid water = 1483 m/s at 20°C b Calculate the 2/3 rds NF distance c Where NF is 150 mm or greater, calculate the 5/6th NF distance. 2 Mount the ball at least 75 mm below water level. 3 Position the probe against the ball and adjust such that the crystal is concentric with the ball. 4 Move the probe back to the 2/3 rds NF position. Using Tilt and Vertical adjustment, obtain the maximum amplitude signal, ensuring the crystal remains concentric with the ball. 5 At the 2/3 rds NF distance, obtain maximum amplitude signal using the Swing and Lateral adjustments. 6 At the 5/6 ths NF distance check that no increase in amplitude can be obtained by Vertical or Lateral adjustment. 7 Carry out the same check at full NF distance. Adjustments must be made such that maximum amplitude signal can be obtained at the three positions without alteration of adjustments. This ensures that the ball remains on Beam Axis with probe movement. 8 Move the probe over the theoretical NF distance. A maximum amplitude signal should be obtained in the middle region. Adjust its amplitude to just below full screen height, or to the upper linear limit. May 07/02 61-A1124 Aug 25/10 (Revision 2) Appendix C ### Page 21 Pa r t of GE ’s Avi ati on Busi ne ss SERVICE BULLETIN ALERT Page 7 of 13 GE Aviation Systems Ltd Proprietary Information Use o r disclosure of data contain ed on this sheet is su bject to the rest rictions on the cover or first page 9 Position the probe 5 mm from the ball and record the amplitude of the signal. Repeat at 5 mm increments over the 2/3 rd NF range. Continue at 10 mm increments until the signal has reduced at approximately 1/5 th screen height. NOTE : The following procedure of adjustment will eliminate errors due to backlash in the lateral movement. 10 Beam width is now measured, starting at this final probe position. Adjust the signal amplitude to 80% screen height. Using lateral adjustment, move the probe until the signal reduces to below 40% of screen height. Carefully adjust in the opposite direction until the signal is 40% screen height (6dB down). Using the measuring instrument, measure and record the position of the carriage. Continue the lateral movement of the carriage such that the signal increases, then decreases to the 40% height. Care must be taken not to overshoot this position. Measure and record the carriage position. Deduct the smaller from the larger reading to obtain beam width. 11 Repeat this beam width measurement procedure at the 5/6 th and 2/3 rd position. 12 Beam width measurements are to be taken at gradually reduced increments as the probe is advanced closer to the ball. Prior to each position measurements at less than 2/3 rds NF, the probe is to be returned to beyond the 2/3 rds position and maximum height signal obtained on the lateral movement. 13 Using figure 1 ‘Probe Calibration’ sheet, record details and readings, and plot the Distance/Amplitude Curve and Beam Width. (d) Assessment of Results 1 A good result has been achieved when beam width is wide when amplitude is low, and narrow when amplitude is high. The result must satisfy this before acceptance. 2 Mark on the curve the near and far positions where the signal amplitude falls to 50% of maximum. From this, the following Optimum Operational Data is to be entered on the sheet. a Water Gap Distance to the ’near’ mark b Working Range Distance between the two marks in water (Divide by 4 for steel or aluminium) c Scan Index Beam width at ’near’ mark. This should be in excess of 3mm for standard search probes. (3) Calibration of focused immersion transducers (a) This procedure is to be carried out on all focused water immersion probes. (b) Equipment 1 An immersion tank of suitable size, is to be used. 2 A 12.5 mm diameter steel ball is to be used as the target. 3 An instrument capable of measurement of 0,025 mm or better is to be used to make beam profile measurements. May 07/02 61-A1124 Aug 25/10 (Revision 2) Appendix C ### Page 22 Pa r t of GE ’s Avi ati on Busi ne ss SERVICE BULLETIN ALERT Page 8 of 13 GE Aviation Systems Ltd Proprietary Information Use o r disclosure of data contain ed on this sheet is su bject to the rest rictions on the cover or first page (c) Procedure 1 Obtain the manufacturer’s nominal focal distance for the probe. 2 Mount the ball at least 75 mm below water level. 3 Position the probe against the ball and adjust such that the crystal is concentric with the ball. 4 Move the probe back to the nominal focal distance. Using Tilt and Vertical adjustment, obtain the maximum amplitude signal, ensuring the crystal remains concentric to the ball. 5 Still at the nominal focal distance, obtain the maximum amplitude signal using the Swing and Lateral adjustments. 6 Increase the distance of the probe to the ball by 20 mm. Check for increase in amplitude by Vertical and Lateral adjustment. Carry out adjustments until maximum signal is obtained at nominal focal distance and at this position + 20 mm without any further adjustment being necessary. This ensures that the ball remains on Beam Axis with probe movement. It may be necessary to check this maximum at a third position. 7 Move the probe towards the ball until maximum signal is obtained. Adjust signal to upper Linearity limit for the equipment. Re-check concentricity of probe and ball. 8 Position the probe 5 mm from the ball and record the amplitude of the signal. Repeat at 5 mm intervals (or less where necessary) over the nominal focal distance. Continue at 10 mm intervals until the signal has reduced to approximately 1/10 th screen height. 9 Beam width measurement is now carried out in the same way as outlines in para 10 of Part 2(c). Measurements are taken at 5 mm intervals from the ball to at least 20 mm past the maximum height position. Thereafter at 10 mm intervals over the remainder of the Distance Amplitude plot. 10 Record all details and construct graphs of Distance/ Amplitude and Beam Width on the left half of figure 2. 11 Beam Profile measurements are now carried out at the actual maximum amplitude distance from the ball and at approximately 1.3 times this distance, e.g.: If actual max. amplitude distance is 30 mm., the second position could be taken as 40 mm. 12 At the 1.3 times max. position, set the signal amplitude to the upper linearity limit. Using the lateral adjustment on the rig, move the probe in increments of 0,25 mm one direction, recording amplitude, until below 5% fsh. Repeat in the opposite direction. 13 This is repeated at the maximum amplitude position in two planes at 90 ° (i.e. rotate probe in holder for second run). The probe is to be moved at least 5 mm each side of centre line and any side lobes are to be plotted. 14 Plot the results on the right hand half of figure 2. May 07/02 61-A1124 Aug 25/10 (Revision 2) Appendix C ### Page 23 Pa r t of GE ’s Avi ati on Busi ne ss SERVICE BULLETIN ALERT Page 9 of 13 GE Aviation Systems Ltd Proprietary Information Use o r disclosure of data contain ed on this sheet is su bject to the rest rictions on the cover or first page (d) Assessment of Results 1 Actual Focal Distance - This is the distance on the Distance/ Amplitude Curve at which the amplitude is at maximum. This may differ considerably from the nominal figure given by the manufacturer, but should be similar for probes of the same specification. Record this distance in the Block on figure 2. 2 Focal Spot Size - This is to be measured at Actual Focal Distance and recorded in the Block in figure 2. 3 Beam Profile - This is to be assessed for symmetry about the centreline and side lobe conditions. 4 Symmetry:- The ratio of distance each side of centreline at which amplitude is 50% of max. - should not exceed 1.5 to 1. 5 Side lobes:- Amplitude must not exceed 20% of maximum. C. Calibration of Ultrasonic Reference Blocks (1) General Requirements (a) It is advisable to calibrate reference blocks by comparing them to other reference blocks of known accuracy. In the case of Aluminium Alloy and Steel standard reference blocks, this can be done by comparing them with blocks of known accuracy. (b) Master Reference Blocks. Master reference blocks shall be used only for calibrating other reference blocks of the same part number. They shall not be used as a working block. Calibration is carried out at initial issue, to the relevant drawing. (c) Working Reference Blocks Working reference blocks are to be calibrated on initial issue and 5 yearly thereafter. Blocks that are to be used with contact techniques only may be calibrated by the contact method using an instrument qualified to section 5A and a suitable transducer. When blocks are to be used with immersion techniques an instrument, qualified to section 5A, is to be used in conjunction with a 10 MHz, 10mm diameter standard water immersion probe, calibrated to section 5C. The serial numbers of the instrument and Probe are to be entered on the calibration certificate (DAP 614). When re-calibration is being carried out, the same Instrument and Probe combination as originally employed should be used. If an alternative probe is necessary, select one with calibration curve nearest to the original. (d) When it is required to compare a flat bottomed hole of a different diameter to the master the following factors are to be used. 1/64 to 2/64″ = 12dB 2/64 to 3/64″ = 7dB 3/64 to 5/64″ = 9dB 5/64 to 6/64 = 8dB (e) The amplitude of the signal form a block being calibrated must be within ± 3dB of the master reference block. Blocks within tolerance are to have their error marked on them. When the signal is less in amplitude than the master, the correction factor is to be marked positive, and vice-versa. May 07/02 61-A1124 Aug 25/10 (Revision 2) Appendix C ### Page 24 Pa r t of GE ’s Avi ati on Busi ne ss SERVICE BULLETIN ALERT Page 10 of 13 GE Aviation Systems Ltd Proprietary Information Use o r disclosure of data contain ed on this sheet is su bject to the rest rictions on the cover or first page Table 1 Acceptable Initial Values for HA and HB Table 2 SET-UP LIMITS RATIO 2.2 2.0 1.8 HA HB MIN. H B NOM. H B MAX. 65 64 63 62 61 30 29 29 28 27 33 32 32 31 31 36 36 35 34 34 PREFERRED 60 27 30 33 59 58 57 56 55 27 26 26 25 25 30 29 29 28 28 33 32 32 31 31 Nominal HA values are preferred for any give HB value. Gain Setting Expected % fsh Response Maximum % Minimum % X+2dB 100 100+ 90 XdB 80 - - X - 6 d B 4 04 53 5 X-18dB 10 12 8 X-24dB 5 - Signal must be visible above base line May 07/02 61-A1124 Aug 25/10 (Revision 2) Appendix C ### Page 25 (OCR) POWTY Part of GE's Aviation Business SERVICE BULLETIN ALERT N.D.T. DEPARTMENT. BISTANCE - AMPLITUDE CURVE AND BEAM HIDTH (58%) PROBE DETAILS EQUIPMENT DETAILS MAKE CRYSTAL FREQUENCY DIAMETER DISTINCE APLIUE WIDTH DOWTY REROSPACE PROPELLERS 100 80 015 PROBE CALIBRATION ТЕД ЛІН НОШ -• Figure 1 Appendix C May 07/02 61-A1124 Aug 25/10 (Revision 2) Page 11 of 13 GE Aviation Systems Ltd Proprietary Information Use or disdosure of data contained on this sheet is subject to the restrictions on the cover or first page ### Page 26 Pa r t of GE ’s Avi ati on Busi ne ss SERVICE BULLETIN ALERT Page 12 of 13 GE Aviation Systems Ltd Proprietary Information Use o r disclosure of data contain ed on this sheet is su bject to the rest rictions on the cover or first page Figure 2 May 07/02 61-A1124 Aug 25/10 (Revision 2) Appendix C ### Page 27 (OCR) POWTY Part of GE's A viation Business SERVICE BULLETIN ALERT Dowty Aerospace Propellers NOT Department Ultrasonic Flaw Detector Calibration Record NDT 5DAP PROBE DETAILS MANUFACTURER FREQUENCY DIAMETER SERIAL No. MODE OF USE FLAW DETECTOR DETAILS MANUFACTURER MODEL SERIAL NO. 70 80 00 100 IT PULL DEALE DATA PLOT OF HORIZONTAL LINEARITY TEST PARAMETER HORIZONTAL LIMIT - 189-142 VERTICAL LIMIT RESOLUTION HOLE DIAMETER METAL PATH SENSITIVITY AND NOISE REFERENCE BLOCK SIGNAL AMPLITUDE NOISE LEVEL GAIN (Reduced/In Hand) LINEARITY OF EQUIPMENT GAIN +2dB • 10.03 -&dB 20 30 40 -18dB 4O PERCENT OF PULL BEALE -24dB DATA PLOT OF VERTICAL LINEARITY DATE: SIGNATURE/STAMP CALIBRATION NEXT DUE DATE DAP616 Figure 3 Appendix C May 07/02 61-A1124 Aug 25/10 (Revision 2) Page 13 of 13 GE Aviation Systems Ltd Proprietary Information Use or disdosure of data contained on this sheet is subject to the restrictions on the cover or first page ### Page 28 (No text on this page.) ### Page 29 Pa r t of GE ’s Avi ati on Busi ne ss SERVICE BULLETIN Page 1 of 7 GE Aviation Systems Ltd Proprietary Information Use o r disclosure of data contain ed on this sheet is su bject to the rest rictions on the cover or first page ALERT APPENDIX D NDT UT72 THE ULTRASONIC INSPECTION OF THE GENERAL AVIATION 3 & 4 METAL BLADED PROPELLER HUBs 1. Scope. A. This technique details the contact pulse echo method of ultrasonic inspection for the detection of fatigue cracking from the 8 threaded insert holes, on the rear half hub. B. It will be necessary to remove the propeller from the engine drive flange remove the backplate and slip ring. C. The ultrasonic equipment is to be calibrated in accordance with NDT 5DAP. D. Personnel carrying out this technique must be qualified to NDT 10DAP. 2. Equipment Required. A. Ultrasonic flaw detector operating in the 1 to 15 Mhz range. (A Sonatest Masterscan 335 was used in the preparation of this technique). B. A 3 mm (0.125 in) diameter 5Mhz longitudinal probe type No. Panametrics V1091 or equivalent. C. Suitable couplant. 3. Calibration Procedure. A. Using a suitable couplant, place the probe on the hub adjacent to the dowel hole as shown in Figures 1 and 2. B. Using standard calibration procedure establish the probe zero position. C. By probe movement identify the signal from the dowel hole and set at 1.6 on the timebase. (SeeFigure 4). D. Maximise this signal and set amplitude to 80% full screen height, (see Figure 4), then add 6dB. 4. Inspection Procedure. A. Apply couplant to hub mounting face in scan area and position probe as shown in Figures 2 and 3. B. A back wall echo will appear at approx. 6.0 on the timebase. (See Figure 5). This signal will vary in amplitude from 5 - 100% full screen height due to the inside face geometry. C. Scan 360 ° of scan area. D. Discontinuity indications may appear at any position along the timebase, between 1.0 and the back wall echo signals. They may appear as a single indication or a multiple peak indication as shown in Figure 6. 5. Inspection Standard. A. Any indication which, after careful cross-checking of calibration procedure, is 20% of full screen height or more is to be considered as a defect and rejected. NOTE : Indications from the thread flanks may appear up to 15% full screen height. (See Figure 5). B. Rejected hubs are to be returned to Dowty Propellers for further investigation. May 07/02 61-A1124 Aug 25/10 (Revision 2) Appendix D ### Page 30 Pa r t of GE ’s Avi ati on Busi ne ss SERVICE BULLETIN Page 2 of 7 GE Aviation Systems Ltd Proprietary Information Use o r disclosure of data contain ed on this sheet is su bject to the rest rictions on the cover or first page ALERT Probe Position for Calibration Figure 1 UT 72 F1 PROBE POSITION FOR CALIBRATION May 07/02 61-A1124 Aug 25/10 ( Revision 2) Appendix D ### Page 31 Pa r t of GE ’s Avi ati on Busi ne ss SERVICE BULLETIN Page 3 of 7 GE Aviation Systems Ltd Proprietary Information Use o r disclosure of data contain ed on this sheet is su bject to the rest rictions on the cover or first page ALERT Figure 2 UT 72 F2 May 07/02 61-A1124 Aug 25/10 (revision 2) Appendix D ### Page 32 Pa r t of GE ’s Avi ati on Busi ne ss SERVICE BULLETIN Page 4 of 7 GE Aviation Systems Ltd Proprietary Information Use o r disclosure of data contain ed on this sheet is su bject to the rest rictions on the cover or first page ALERT Typical Crack Orientation Figure 3 UT 72 F3 May 07/02 61-A1124 Aug 25/10 (Revision 2) Appendix D ### Page 33 Pa r t of GE ’s Avi ati on Busi ne ss SERVICE BULLETIN Page 5 of 7 GE Aviation Systems Ltd Proprietary Information Use o r disclosure of data contain ed on this sheet is su bject to the rest rictions on the cover or first page ALERT Signal From Hub Dowel Hole Figure 4 Appendix D May 07/02 61-A1124 Aug 25/10 (Revision 2) ### Page 34 Pa r t of GE ’s Avi ati on Busi ne ss SERVICE BULLETIN Page 6 of 7 GE Aviation Systems Ltd Proprietary Information Use o r disclosure of data contain ed on this sheet is su bject to the rest rictions on the cover or first page ALERT Signals From Back Wall Echo and Threads Figure 5 Appendix D May 07/02 61-A1124 Aug 25/10 (Revision 2) ### Page 35 Pa r t of GE ’s Avi ati on Busi ne ss SERVICE BULLETIN Page 7 of 7 GE Aviation Systems Ltd Proprietary Information Use o r disclosure of data contain ed on this sheet is su bject to the rest rictions on the cover or first page ALERT Typical Crack Signal Figure 6 Appendix D May 07/02 61-A1124 Aug 25/10 (Revision 2) --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.