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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
No text on this page: it may be a figure. Open the PDF to see it.
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)
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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)
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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)
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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
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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
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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
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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
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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)
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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)