# Bombardier Service Bulletin 604-57-007 Copy: Revision 01 ("604 57 007 rev01"), 26 pages: PDF https://openairdocs.org/files/sha256/37/9b/379b85efd1dd98b66961c606c9566cc0a31aa23631fa096f23442e15ffad9790; text https://openairdocs.org/service-documents/bombardier/sb-604-57-007/file/379b85efd1dd.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2014-0491; AD 2015-07-02 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. ## Details - Manufacturer: [Bombardier](https://openairdocs.org/service-documents/bombardier.md) - Type: Service bulletin (Service Bulletin) - Number: 604-57-007 - Latest revision known: 604-57-007, Revision 01, dated November 12, 2014 (OpenAirDocs) - Page: https://openairdocs.org/service-documents/bombardier/sb-604-57-007 ## ADs that cite it (1) (OpenAirDocs) Newest first, with the revision each names, as OpenAirDocs read it from the AD's text. - [AD 2015-07-02](https://openairdocs.org/ad/2015-07-02.md), effective Jun 4, 2015: Revision 01 Also cited in [1 proposed AD](https://openairdocs.org/service-documents/bombardier/sb-604-57-007/proposed.md). ## Text (26 pages) Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2014-0491; AD 2015-07-02 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. 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 1 604-57-007 Page 1 of 1 SERVICE BULLETIN REVISION TRANSMITTAL SHEET MODEL CL-600-2B16 Discard the Basic Issue of this Service Bulletin dated Sep 26/2013 and the Information Sheet dated Oct 02/2013, and replace in its entirety with this Revision 01. Service Bulletin No. 604-57-007 Date of Basic Issue Se p 26/2013 Revision No. 01 Dated Nov 12 /2014 This revision has no effect for aircraft on which the Basic Issue of this Service Bulletin was done thus no other action is necessary. Do not sign the log book if you have not done this revision. Keep the previous log book entry. You may make an entry as “Not Applicable” for this revision. This revision is issued to separate the procedure into Part A and Part B. The changes are as follows: 1. Change the Service Bulletin Summary Sheet to update the Manpower and add some notes. 2. Change Paragraph 1, Planning Information, to add the Airworthiness Directive data and recommendation for Part A. 3. Change Paragraph 1.C., Description, to add Part A, Part B and Testing. 4. Change Paragraph 1.F., Manpower, to update the man-hours for Part A and Part B. 5. Change Paragraph 2.A., Aircraft Setup, to update the access specific for Part A and Part B. 6. Change Paragraph 2.B., to update the procedur e specific into Part A and Part B. 7. Change Paragraph 2.F., to update the Recording instructions. 8. Change Paragraph 3.B., to split the parts list into Part A and Part B. 9. Make miscellaneous minor changes, as necessary, with no change of context. ### Page 2 Basic Issue: Sep 26/2013 604-57-007 Revision 01: Nov 12/2014 Page 1 of 1 SERVICE BULLETIN SUMMARY This Service Bulletin is available at: www.cic.bombardier.com MODEL CL-600-2B16 ATA 57-52 WINGS SPECIAL CHECK – FLAP HINGE BOX – FORWARD LUGS EDGE TO EDGE DISTANCE The information below is provided for your reference. For full details, please see corresponding paragraph contained within this bulletin. RECOMMENDED SPECIFIED TIME COMPLIANCE COMPLIANCE TIME Recommended prior to exceeding 7,800 flights or within 48 months from this Service Bulletin release date (Basic Issue), whichever comes first. EFFECTIVITY: A/C Serial No. 5301 to 5665 MANPOWER: 0.5 man-hours to do PART A Special Check if done in conjunction with SB A604-57-006, PART B. 18 man-hours to do PART A Special Check if not done in conjunction with SB A604-57-006, PART B. 27 man-hours to do PART B Special Check. CONTINUED AIRWORTHINESS (CAW) FLEET CAMPAIGN YES NO TLMC, CH 5 AFFECTED YES NO KITS and/or PARTS YES NO TOOLING/GSE YES NO PLANNING INFORMATION: See important information at the start of Paragraph 1. YES NO DEDICATED SCHEDULE YES NO PREREQUISITE SERVICE BULLETINS: N/A NOTES: 1. To minimize aircraft downtime and cost, it is recommended to do PART A of this SB in conjunction with the Alert Service Bulletin A604-57-006, PART B. 2. The Basic Issue of this SB604-57-007 is equivalent to PART A and PART B of the current revision of this Service Bulletin. 3. This Service Bulletin is the subject of the Airworthiness Directive CF-2014-01 which makes it necessary to implement this Service Bulletin. To place an order for parts or kits, please call Bombardier Aerospace Parts Services at: 514-855-2999 or 1-866-538-1247 ### Page 3 Refer to applicable governmental agency regulations and requirements and make sure that the work described in this Service Bulletin is performed in compliance with manufacturer’s recommendations and/or acceptable industry standards. This document is proprietary to Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or by any means without the prior written consent of Bombardier Inc. and/or its affiliates. © 2013 - 2014 Bombardier Inc. All rights reserved Learjet, Challenger, Global, are registered trademarks of Bombardier Inc. or its subsidiaries. Basic Issue: Sep 26/2013 604-57-007 Revision 01: Nov 12/2014 Page 1 of 21 SERVICE BULLETIN This Service Bulletin is available at: www.cic.bombardier.com MODEL CL-600-2B16 ATA 57-52 WINGS SPECIAL CHECK – FLAP HINGE BOX – FORWARD LUGS EDGE TO EDGE DISTANCE 1. PLANNING INFORMATION NOTES: 1. To minimize aircraft downtime and cost, it is recommended to do PART A of this SB in conjunction with the Alert Service Bulletin A604-57-006, PART B. 2. The Basic Issue of this SB604-57-007 is equivalent to PART A and PART B of the current revision of this Service Bulletin. 3. You can do PART A or PART B of this Service Bulletin independently. This Service Bulletin can only be closed and in compliance with Transport Canada Airworthiness Directive CF-2014-01, Paragraph D, when the special check in PART A and PART B are completed. 4. Special tool is required for bushing removal. See Appendix 2 for details, or commercially available tool is acceptable. A. Effectivity CL-600-2B16 aircraft, Serial No. 5301 to 5665. NOTE: The instructions given in this Service Bulletin are only applicable to the systems and parts installed at the time of delivery of the aircraft or as changed by Bombardier Aerospace Service Bulletin(s). Before you do this bulletin, examine all STC, STA or equivalent action changes to make sure that this bulletin can be completed. ### Page 4 MODEL CL-600-2B16 Basic Issue: Sep 26/2013 604-57-007 Revision 01: Nov 12/2014 Page 2 of 21 B. Reason During production inspection of the flap hinge box assembly, it was found that the material around the forward lugs on the inboard and outboard flap hinge boxes was below the minimum requirements. This Service Bulletin gives instructions to inspect the affected lugs and compare them with the limits stated in this Service Bulletin. If necessary, instructions are given if the limits are not met. C. Description This Service Bulletin gives instructions to: – Remove the inboard and outboard forward flap-hinge fairings. – PART A, to: – Disconnect the wing fitting/lugs of the inboard flap hinge boxes, – Measure the forward lugs of the inboard flap hinge boxes, and – Reconnect the wing fitting/lugs of the inboard flap hinge boxes, – PART B, to: – Disconnect the wing fitting/lugs of the outboard flap hinge boxes, – Measure the forward lugs of the outboard flap hinge boxes, and – Reconnect the wing fitting/lugs of the outboard flap hinge boxes. – Testing, to: – Install the inboard and/or outboar d forward flap-hinge fairings, and – Do the necessary tests to make sure that the inboard and outboard flaps operate correctly. D. Compliance Recommended prior to exceeding 7,800 flights or within 48 months from this Service Bulletin release date (Basic Issue), whichever comes first. E. Approval The technical content of this Service Bulletin has been approved under the authority of Transport Canada Civil Aviation (TCCA) Design Approval Organization (DAO) No. DAO #93-Q-02. NOTES: 1. The technical content of this Service Bulletin is accepted by the FAA under the Canada/USA bilateral Aviation Safety Agreement. 2. The technical content of this Service Bulletin is accepted by EASA in accordance with established procedures. ### Page 5 MODEL CL-600-2B16 Basic Issue: Sep 26/2013 604-57-007 Revision 01: Nov 12/2014 Page 3 of 21 F. Manpower NOTES: 1. The man-hours given are estimates to help you schedule the tasks given in this bulletin. The estimates are for direct labor performed by an experienced crew and do not include the time for familiarization, planning, aircraft preparation in hangar such as towing and positioning of scaffolds, removal of interior furnishings, repainting, supervision and inspection. For more information related to the manpower estimates, refer to SB 604-00-002. 2. This Service Bulletin may require consumable materials that have specific curing times (refer to Paragraph 3). The accumulated curing time is not included in the labor estimates and should be considered for planning purposes before you schedule this Service Bulletin. 0.5 man-hours are necessary to do PART A, Special Check, if done in conjunction with SB A604-57-006, PART B. 18 man-hours are necessary to do PART A, Special Check if not done in conjunction with SB A604-57-006, PART B. 27 man-hours are necessary to do PART B, Special Check. Bombardier Aerospace does not pay for the labor to do this Special Check. G. Material - Cost and Availability The parts listed in Paragraphs 3.B. may be necessary to do this modification. Bombardier Aerospace does not pay for the parts in Paragraph 3.B. to do this modification. The Smart Parts Plus Program does not pay for the parts in Paragraph 3.B. H. Tooling The equipment and tools listed below are necessary to do this Special Check: GSE REFERENCE NO. PART NO. DESCRIPTION 24-00-24 - Tag, Circuit Breaker Commercially Available - Torque Wrench 20 to 25 lbf in (2.26 to 2.82 Nm) Commercially Available - Torque Wrench 30 to 35 lbf in (3.39 to 3.95 Nm) Commercially Available - C-Clamp ### Page 6 MODEL CL-600-2B16 Basic Issue: Sep 26/2013 604-57-007 Revision 01: Nov 12/2014 Page 4 of 21 The tool listed below or a commercially available equivalent tool is required for the removal of the bushings. GSE REFERENCE NO. PART NO. DESCRIPTION See Note 3 - Support Block NOTES: 1. Refer to the CL-604 Illustrat ed Tool and Equipment Manual (ITEM) to make sure that you use the correct equipment configuration. 2. Refer to the Liability Statement in the ITEM for acceptable GSE equivalents. 3. For the support block manufacturing details, refer to Appendix 2. I. Weight and Balance No change. J. Electrical Load Data No change. K. References – Bombardier Aerospace, Restriction and/or Special Instruction (RSI), C-4093, Rev. A2. – CL-604 Aircraft Illustrated Parts Catalog (AIPC), Chapter 57. – CL-604 Aircraft Illustrated Tool and Equipment Manual, Chapter 24. – CL-604 Aircraft Maintenance Manual (AMM), Chapters 6, 12, 27 and 57. – CL-604 Standard Practice M anual (SPM), Chapter 51. – CL-604 Standard Practice M anual (SRM), Chapter 51. – CL-604 Time Limits and Maintenance Checks (TLMC), Chapter 5. – Bombardier Aerospace, Modifica tion Summary IS600-57-0001, Rev. A. – Appendix 1 – Information Feedback Sheet (attached). – Appendix 2 – Support Block (attached). L. Other Publications Affected – None. M. Equivalent Service Bulletins – For the Challenger 600 aircraft, use SB 600-0762. – For the Challenger 601 aircraft, use SB 601-0631. – For the Challenger 605 aircraft, use SB 605-57-005. ### Page 7 MODEL CL-600-2B16 Basic Issue: Sep 26/2013 604-57-007 Revision 01: Nov 12/2014 Page 5 of 21 2. ACCOMPLISHMENT INSTRUCTIONS NOTES: 1. All TASKs given in the procedures that follow are from the Aircraft Maintenance Manual unless otherwise specified. 2. All references made to zones, a ccess panels and/or doors, are from the Aircraft Maintenance Manual, Chapter 6. A. Aircraft Setup (1) Install the safety devices and the warning signs in the applicable locations and the warning placard on the flap control lever. (2) Obey all electrical/electronic safety precautions. Refer to TASK 24-00-00-910-801. (3) Connect and energize the exter nal AC power. Refer to TASK 12-00-07-861-801. (4) Set the flap control lever to 45 degrees and make sure that the flaps are fully extended. (5) Remove the external AC power. Refer to TASK 12-00-07-861-802. (6) Open and tag the circuit breakers that follow: CB PANEL CB NO. NAME ZONE CBP-2 B5 FLAP MOTOR 2 222 CBP-2 F3 FLAP CONT 2 222 CBP-3 B11 FLAP MOTOR 1 221 CBP-4 A9 FLAP CONT 1 222 (7) For PART A, remove fillet sealant fr om perimeter around the forward inboard flap hinge-fairings, making contact with the wing surface and the inboard flap respectively. Refer to SPM-MM 51-23-00-100-801. Remove the left and right inboard flap hinge-fairings that follow: Refer to TASK 57-26-03-000-801. ACCESS DESIGNATION 571AB (671AB) Fairing, Forward Inboard – Flap Hinge 571EB (671EB) Fairing, Forward Inboard – Flap Hinge ### Page 8 MODEL CL-600-2B16 Basic Issue: Sep 26/2013 604-57-007 Revision 01: Nov 12/2014 Page 6 of 21 (8) For PART B, remove fillet sealant from perimeter around the forward outboard flap hinge-fairings, making contact with the wing surface and the outboard flap respectively. Refer to SPM-MM 51-23-00-100-801 Remove the left and right outboard forward flap-hinge-fairings that follow: Refer to TASK 57-26-05-000-801. ACCESS DESIGNATION 581BB (681BB) Fairing, Forward Outboard 581DB (681DB) Fairing, Forward Outboard 581FB (681FB) Fairing, Forward Outboard B. PART A: Measurement of the Inboard Forward-Lug Edge to Edge Distance of the Flap-Hinge-Boxes, Part No. 600-10116, 600-10117. CAUTION: ONLY ONE FLAP HINGE BOX IS TO BE DISCONNECTED AND INSPECTED AT A TIME. THE FLAP HINGE BOX MUST BE SUPPORTED DURING THE INSPECTION SO AS NOT TO DAMAGE THE FLAPS AND ATTACHED COMPONENTS. (1) For each wing, disconnect one flap hinge box at a time from the wing forward- attachment fitting and wing aft-attachment fitting. NOTES: 1. The flap will be supported by the other attached flap hinge box/arm and both actuators. 2. To reduce the load on the other attached flap hinge box/arm and actuators, the flaps should also be supported per best shop practice or with a bench and padding. Refer to Figure 1. Figure 1 ### Page 9 MODEL CL-600-2B16 Basic Issue: Sep 26/2013 604-57-007 Revision 01: Nov 12/2014 Page 7 of 21 (2) Disconnect the inboard flap hinge box (1) at location WS 76.50 and WS 127.25 as follows: Refer to Figures 1, 2, 3 and 4. NOTE: It is not necessary to remove t he flap hinge boxes from the aircraft for the lug edge to edge distance measurement. Refer to Figure 2 for the recommendations to disconnect the flap hinge box. Flap Hinge Box Figure 2 (a) If necessary, remove and keep the hardware that attach the bonding jumpers to the flap hinge box (1). (b) For the flap hinge box (1) located at WS 76.50 only, do as follows: (i) If necessary, disconnect the electrical connector wire (3) from any attached location on the structure, to allow downward movement of the flap hinge box. Support for the flap hinge box Disconnect flap hinge box from fittings. CAUTION: Make sure that there is no contact between the flap hinge box and fairing to avoid damage when lowering the flap hinge box. If required, remove flap hinge box bonding jumper. Lower flap hinge box enough to permit measurement of the lug edge to edge distance. ### Page 10 MODEL CL-600-2B16 Basic Issue: Sep 26/2013 604-57-007 Revision 01: Nov 12/2014 Page 8 of 21 WARNING: WEAR EYE PROTECTION WHEN YOU CUT THE COTTER PIN. WHEN THE COTTER PIN IS CUT, PIECES CAN HIT YOUR EYES AND CAUSE INJURIES. (ii) Remove and discard the cotter pin (4). Refer to SPM-MM 20-50-00-000-802. (iii) Remove the nut (5), washer (6) and bolt (7) and disconnect the control rod (2) from the lever (8) of the flap position transmitter. (iv) If disconnected, put protective cove rs on the open ends of the electrical connector (3) and on the electrical connection of the position transmitter. (c) Remove and keep the nuts (9), washers (10) and (11), bolts (12), to disconnect the flap hinge box (1) from the forward attachment fitting. CAUTION: TO REMOVE AND INSTALL THE HINGE BUSHINGS USE A C-CLAMP METHOD WITH THE SUPPORT BLOCK. USE LIGHT ANTI- SEIZE LUBRICANT (LPS-1 OR SIMILAR) IF THE BUSHINGS ARE SEIZED OR DIFFICULT TO REMOVE. MAKE SURE THAT THE LATERAL FORCE DOES NOT EXCEED 200 LBS AND DO NOT USE A HAMMER TO REMOVE THE BUSHINGS, THIS CAN CAUSE DAMAGE. BEFORE YOU INSTALL THE C-CLAMP, MAKE SURE YOU INSTALL A SUPPORT BLOCK BETWEEN THE FITTINGS, SHIMS IN ALL GAPS AS REQUIRED TO AVOID BENDING AND DAMAGE FROM THE CLAMP FORCE. OTHER METHOD THAN C-CLAMP COULD BE USED, PROVIDED LUGS ARE SUPPORTED AND LATERAL FORCE DOES NOT EXCEED 200 LBS TO AVOID DAMAGE. Figure 3 Install the support block, manufactured as per Appendix 2 or an equivalent commercially available tool between the fittings. Shim all gaps as required. ### Page 11 MODEL CL-600-2B16 Basic Issue: Sep 26/2013 604-57-007 Revision 01: Nov 12/2014 Page 9 of 21 (d) Remove bushings (13) to disconnec t the flap hinge box (1) from the forward attachment fitting. Keep bushings (13) if not damaged to re-install later. Refer to Figures 3 and 4. CAUTION: HOLD THE FLAP HINGE BOX WHILE THE BOLTS ARE REMOVED. IF THE FLAP HINGE BOX FALLS, IT WILL CAUSE DAMAGE TO THE FLAP HINGE BOX AND ATTACHED COMPONENTS. (e) Remove and keep the nuts (14), washers (15) and (16), and bolts (17), to disconnect the hinge box (1) from the aft attachment fitting. (f) Remove bushings (18) to disconnec t the hinge box (1) from the aft attachment fitting. Keep bushings (18) if not damaged to re-install later. Refer to Figures 3 and 4. CAUTION: MAKE SURE THERE IS NO CONTACT BETWEEN THE FLAP HINGE BOX AND AFT FAIRING TO AVOID DAMAGE TO THE AIRCRAFT STRUCTURE WHEN YOU LOWER THE FLAP HINGE BOX DOWNWARD FOR ACCESS. (3) Carefully pull the flap hinge box (1) downw ard to allow access to the forward lugs for the lug edge to edge distance measurement. ### Page 12 (OCR) CHALLENGER 604 MODEL CL-600-2B16 FLAP POSITION TRANSMITTER FAIRING BRACKET SUPPORT CAUTION: ONLY ONE FLAP HINGE BOX IS TO BE DISCONNECTED AT A TIME. THE FLAP HINGE BOX MUST BE SUPPORTED DURING THE MODIFICATION SO AS NOT TO DAMAGE THE FLAPS AND ATTACHED COMPONENTS. AFT ATTACHMENT FITTING 17- FORWARD ATTACHMENT FITTING 16 AREA OF INSPECTION 9 Inboard Flap-Hinge-Box Figure 4 Basic Issue: Sep 26/2013 604-57-007 • Revision 01: Nov 12/2014 Page 10 of 21 ### Page 13 MODEL CL-600-2B16 Basic Issue: Sep 26/2013 604-57-007 Revision 01: Nov 12/2014 Page 11 of 21 (4) Measure and record the minimum lug edge to edge distance of the forward lugs of the inboard flap hinge boxes at locations WS 76.50 and WS 127.25. Refer to Figure 5. NOTE: LEFT SIDE SHOWN, RIGHT SIDE OPPOSITE. WS 76.50 and WS 127.25 Inboard Flap-Hinge-Box Forward-Lug Edge to Edge Distance Limits Figure 5 ### Page 14 MODEL CL-600-2B16 Basic Issue: Sep 26/2013 604-57-007 Revision 01: Nov 12/2014 Page 12 of 21 (5) If any of the inboard flap-hinge-box forw ard lug edge to edge distance is below the 0.256 in (6.50 mm) minimum limit do the steps that follow: (a) Fill-in Appendix 1 with the data (minimum edge to edge distance, hole diameter, lug thickness & lug location) applicable to the faulty Flap Hinge Box(es), then, (b) Submit Appendix 1 with an SRPSA to Customer Support Engineering (CSE) for evaluation and an approved repair by e-mail at: SRPSA@aero.bombardier.com. (6) If the measured forward-lug edge to edge distance of the inboard flap-hinge- boxes are equal or above the minimum limit, no corrective action is required. Attach the inboard flap-hinge-box in the steps that follow. (7) Install the inboard flap hinge box (1) at locations WS 76.50 and WS 127.25 as follows: Refer to Figure 4. (a) Apply a layer of Mastinox 6856K to t he bushings (13) and (18) on installation. (b) Put the flap-hinge-box (1) in position. (c) Install the bushings (18) on the flap hinge box (1) and aft attachment fitting. (d) Install the bushings (13) on the forw ard lugs of the flap hinge box (1) and forward attachment fitting. (e) Install bolts (17), washers (15) and (16), and nuts (14) to attach the flap hinge box (1) to the aft attachment fitting. NOTE: Make sure the sum of the gap measurement between the aft attachment fitting and lower surface of bolt head (17), and between the aft attachment fitting and the lower surface of washer (15), is 0.020 in to 0.105 in (0.508 mm to 2.667 mm). Refer to TASK 57-52-01-400-801. (f) Install the bolts (12), washers (10) and (11), and nuts (9) to attach the flap hinge box (1) to the forward attachment fitting. NOTE: Make sure the sum of the gap measurement between the forward attachment fitting and lower surface of bolt head (12), and between the forward attachment fitting and the lower surface of washer (10), is 0.015 in to 0.060 in (0.381mm to 1.524 mm). Refer to TASK 57-52-01-400-801. (g) Torque the nuts (9) and (14) from 30 to 35 lbf in (3.39 to 3.95 Nm). Refer to SPM-MM 20-21-00-910-801. (h) Attach the control rod (2) and electrical connector (3) to the flap position transmitter as follows: (i) Align the eye of the control rod (2) with the lever (8). (ii) Install the bolt (7), washer (6) and the nut (5). ### Page 15 MODEL CL-600-2B16 Basic Issue: Sep 26/2013 604-57-007 Revision 01: Nov 12/2014 Page 13 of 21 (iii) Torque the nut (5) from 20 to 25 lbf in (2.26 to 2.82 Nm). Refer to SPM- MM 20-21-00-910-801. WARNING: WEAR EYE PROTECTION WHEN YOU CUT THE COTTER PIN. WHEN THE COTTER PIN IS CUT, PIECES CAN HIT YOUR EYES AND CAUSE INJURIES. (iv) Install the cotter pin (4). Refer to SPM-MM 20-50-00-400-802. (v) Remove the protective covers from the open ends of the electrical connector (3) and from the electrical connection of the position transmitter. (vi) If disconnected, connect the electrical connector (3) to the flap position transmitter. NOTE: If detached, attach the electrical connector wire to the necessary locations on the structure. (i) If removed, install the bonding jumper on the flap hinge box (1). Refer to SPM 51-80-00-400-801. (j) If necessary, do the electrical bonding test for the applicable flap hinge box (1). Refer to SPM-MM 51-80-00-760-801. C. PART B: Measurement of the Outboard Forward-Lug Edge to Edge Distance of the Flap-Hinge-Boxes, Part No. 600-10118, 600-10119, and 600-10120. (1) Disconnect the outboard flap hinge box (19) at locations WS 178.00, WS 220.00, and WS 264.00 as follows: Refer to Figures 1, 2, 3 and 6. NOTE: It is not necessary to remove the flap hinge boxes from the aircraft for the lug edge to edge distance measurement. Refer to Figure 2 for the recommendations to disconnect the flap hinge box. (a) If necessary, remove and keep the hardw are that attach the bonding jumpers to the flap hinge box (19). (b) Disconnect the control rod (23) from th e BUTE door fitting in the steps that follows: WARNING: WEAR EYE PROTECTION WHEN YOU CUT THE COTTER PIN. WHEN THE COTTER PIN IS CUT, PIECES CAN HIT YOUR EYES AND CAUSE INJURIES. (i) Remove and discard the cotter pin (20). Refer to SPM-MM 20-50-00-000-802. (ii) Remove and keep the pin (21) and washer (22) to disconnect the control rod (23) from the BUTE door fitting. (c) Remove and keep the nuts (24), washers (25) and (26), and bolts (27), to disconnect the hinge box (19) from the forward attachment fitting. ### Page 16 MODEL CL-600-2B16 Basic Issue: Sep 26/2013 604-57-007 Revision 01: Nov 12/2014 Page 14 of 21 (d) Remove bushings (28), to disconnect the hinge box (19) from the forward attachment fitting. Keep bushings if not damaged to re-install later. Refer to Figures 3 and 6. CAUTION: HOLD THE FLAP HINGE BOX WHILE THE BOLTS ARE REMOVED. IF THE FLAP HINGE BOX FALLS, IT WILL CAUSE DAMAGE TO THE FLAP HINGE BOX AND ATTACHED COMPONENTS. (e) Remove and keep the nuts (29), washer s (30) and (31), and bolts (32), to disconnect the hinge box (19) from the aft attachment fitting. (f) Remove bushings (33), to disconnec t the hinge box (19) from the aft attachment fitting. Keep bushings if not damaged to re-install later. Refer to Figure 3 and 6. CAUTION: MAKE SURE THERE IS SUFFICIENT CLEARANCE BETWEEN THE FLAP HINGE BOX AND AFT FAIRING TO AVOID DAMAGE TO THE AIRCRAFT STRUCTURE WHEN YOU LOWER THE FLAP HINGE BOX DOWNWARD FOR ACCESS. (2) Carefully pull the flap hinge box (19) downward to allow access to the forward lugs for the edge to edge distance inspection. ### Page 17 MODEL CL-600-2B16 Basic Issue: Sep 26/2013 604-57-007 Revision 01: Nov 12/2014 Page 15 of 21 19 24 27 19 29 30 33 31 32 DSB57050_004 FORWARD ATTACHMENT FITTTING AFT ATTACHMENT FITTTING AREA OF INSPECTION 25 28 26 27 22 21 20 23 FITTING BUTE DOOR Outboard Flap-Hinge-Box Figure 6 ### Page 18 MODEL CL-600-2B16 Basic Issue: Sep 26/2013 604-57-007 Revision 01: Nov 12/2014 Page 16 of 21 (3) Measure and record the minimum lug edge to edge distance of the forward lugs of the outboard flap hinge boxes at location WS 178.00, WS 220.00, and WS 264.00. Refer to Figure 7. NOTE: LEFT SIDE SHOWN, RIGHT SIDE OPPOSITE. WS 178.00, WS 230.00 and WS 264.00 Outboard Flap-Hinge-Box Forward-Lug Edge to Edge Distance Limits Figure 7 ### Page 19 MODEL CL-600-2B16 Basic Issue: Sep 26/2013 604-57-007 Revision 01: Nov 12/2014 Page 17 of 21 (4) If any of the outboard flap-hinge-box fo rward-lug edge to edge distance is below the 0.182 in (4.62 mm) minimum limit do the steps that follow: (a) Fill-in Appendix 1 with the data (minimum lug edge to edge distance, hole diameter, lug thickness & lug location) applicable to the faulty Flap Hinge Box(es), then, (b) Submit Appendix 1 with an SRPSA to Customer Support Engineering (CSE) for evaluation and an approved repair by e-mail at: SRPSA@aero.bombardier.com. (5) If the measured forward-lug edge to edge distance of the outboard flap-hinge- boxes are equal or above the minimum limit, no corrective action is required. Follow the next steps to install the outboard flap hinge box. (6) Install the outboard flap hinge box (19) at locations WS 178.00, WS 220.00, and WS 264.00 as follows: Refer to Figure 6. (a) Apply a layer of Mastinox 6856K to the bushings (28) and (33) on installation. (b) Put the flap-hinge-box (19) in position. (c) Install the bushings (33) on the flap hinge box (1) and aft attachment fitting. (d) Install the bushings (28) on the forw ard lugs of the flap hinge box (1) and forward attachment fitting. (e) Install bolts (32), washers (30) and (31), and nuts (29) to attach the flap hinge box (19) to the aft attachment fitting. NOTE: Make sure the sum of the gap measurement between the aft attachment fitting and lower surface of bolt head (32), and between the aft attachment fitting and the lower surface of washer (30), is 0.020 in to 0.105 in (0.508 mm to 2.667 mm). Refer to TASK 57-52-01-400-801. (f) Install the bolts (27), washers (25) and (26), and nuts (24) to attach the flap hinge box (19) to the forward attachment fitting. NOTE: Make sure the sum of the gap measurement between the forward attachment fitting and lower surface of bolt head (27), and between the forward attachment fitting and the lower surface of washer (25), is 0.015 in to 0.060 in (0.381mm to 1.524 mm). Refer to TASK 57-52-01-400-801. (g) Torque the nuts (24) and (29) from 30 to 35 lbf in (3.39 to 3.95 Nm). Refer to SPM-MM 20-21-00-910-801. (7) Connect the control rod (23) to the BUTE door fitting in the steps that follow: Refer to Figure 6. (i) Put the control rod (23) in position on the BUTE door fitting. (ii) Install the pin (21) and washer (22) to connect the control rod (23) to the BUTE door fitting. ### Page 20 MODEL CL-600-2B16 Basic Issue: Sep 26/2013 604-57-007 Revision 01: Nov 12/2014 Page 18 of 21 WARNING: WEAR EYE PROTECTION WHEN YOU CUT THE COTTER PIN. WHEN THE COTTER PIN IS CUT, PIECES CAN HIT YOUR EYES AND CAUSE INJURIES. (iii) Safety the pin (21) with the new cotter pin (20). Refer to SPM-MM 20-50-00-000-802. (8) If removed, install the bonding jumper s on the outboard flap hinge box (19). Refer to SPM 51-80-00-400-801. (9) If necessary, do the electrical bonding te st for the applicable flap hinge box (19). Refer to SPM-MM 51-80-00-760-801. D. Testing (1) Do an operational test of the inboard and outboard flaps to make sure the flap hinge box assemblies move freely, before installing the flap hinge-fairings. Refer to TASK 27-54-00-710-801. (2) Install the left and right inboard flap hi nge-fairings that follow: Refer to TASK 57-26-03-400-801. ACCESS DESIGNATION 571AB (671AB) Fairing, Forward Inboard – Flap Hinge 571EB (671EB) Fairing, Forward Inboard – Flap Hinge (3) Install the left and right outboard flap hi nge-fairings that follow: Refer to TASK 57-26-05-400-801. ACCESS DESIGNATION 581BB (681BB) Fairing, Forward Outboard 581DB (681DB) Fairing, Forward Outboard 581FB (681FB) Fairing, Forward Outboard (4) Apply a filet of sealant around the flap hinge fairings. Refer to SPM−MM 51-23-00-390-805. (5) Remove the tags and close the circuit breakers that follow: CB PANEL CB NO. NAME ZONE CBP-2 B5 FLAP MOTOR 2 222 CBP-2 F3 FLAP CONT 2 222 CBP-3 B11 FLAP MOTOR 1 221 CBP-4 A9 FLAP CONT 1 222 ### Page 21 MODEL CL-600-2B16 Basic Issue: Sep 26/2013 604-57-007 Revision 01: Nov 12/2014 Page 19 of 21 (6) Connect and energize the exter nal AC power. Refer to TASK 12-00-07-861-802. (7) Set the flap control lever lever to 0 and make sure that the flaps retract fully. (8) Do an operational test of the inboard and outboard flaps. Refer to TASK 27-54-00-710-801. (9) Remove the external AC power. Refer to TASK 12-00-07-861-802. E. Close-out Remove all tools, equipment and unwanted materials from the aircraft. F. Recording You can do PART A or PART B of this Service Bulletin independently. When any PART of this Service Bulletin is completed, make an entry in the aircraft log and send the attached Incorporation Notice to Bombardier Business Aircraft Customer Services (BBACS). This Service Bulletin can only be closed and in compliance with Transport Canada Airworthiness Directive CF-2014-01, Paragraph D, when the special check in PART A and PART B are completed. In an effort to improve the quality of our technical communications, we are requesting your feedback. Please take a moment to fill out our easy on-line Service Bulletin survey: http://csefeedback.aero.bombardier.com ### Page 22 MODEL CL-600-2B16 Basic Issue: Sep 26/2013 604-57-007 Revision 01: Nov 12/2014 Page 20 of 21 3. MATERIAL INFORMATION A. Kit No kit required. B. Parts The parts that follow are necessary to do PART A of this Service Bulletin and are available from Bombardier Aerospace Parts Services, Montreal: NEW PART NO. QTY ITEM USED PART NO. INSTRUCTIONS - DISPOSITION MS24665-71 2 Cotter Pin - - The parts that follow are necessary to do PART B of this Service Bulletin and are available from Bombardier Aerospace Parts Services, Montreal: NEW PART NO. QTY ITEM USED PART NO. INSTRUCTIONS - DISPOSITION MS24665-151 6 Cotter Pin - - The parts that follow may be necessary, to do PART A of this Service Bulletin if the removed bushing(s) are damaged or found corroded: NEW PART NO. QTY ITEM USED PART NO. INSTRUCTIONS - DISPOSITION 600-10300-609 0 - 8 Sleeve Bushing - - 600-10300-611 0 - 8 Sleeve Bushing - - The parts that follow may be necessary to do PART B of this Service Bulletin if the removed bushing(s) are damaged or found corroded: NEW PART NO. QTY ITEM USED PART NO. INSTRUCTIONS - DISPOSITION 600-10300-613 0 - 12 Sleeve Bushing - - 600-10300-615 0 - 12 Sleeve Bushing - - ### Page 23 MODEL CL-600-2B16 Basic Issue: Sep 26/2013 604-57-007 Revision 01: Nov 12/2014 Page 21 of 21 C. Material The materials that follow, or equivalent, are necessary to do this Service Bulletin. These can be purchased from a local supplier. Bombardier Aerospace does not pay for these consumables. DESCRIPTION PART No./NAME SPECIFICATION QUANTITY SUPPLIER (See Note) Compound, Sealing CT: 2 Hours or 30 Minutes - MIL-S-81733 Type II, PS 870 Class B-2 or B-1/2 As Necessary Code: A Compound, Corrosion Inhibitor - Mastinox 6856K As Necessary Code: A NOTES: 1. Refer to the table that follows for each supplier’s address listed by codes. 2. The Curing Time (CT), if applicable, for each consumable material is indicated with the description of each product. 3. At time of release of this Service Bulletin, the information on the supplier was valid and accurate. In the event that this information has changed, the operator is encouraged to use the World Wide Web to find a local supplier. SUPPLIERS ADDRESSES BY CODES Code: A PRC – Desoto International 5430 San Fernando Road, PO Box 1800, Glendale, CA, U.S.A. 91209 Tel.: 1-800-228-5635 Fax: (818)-549-7790 Web Site: www.ppg.com/prc-desoto D. Publications No publications required. ### Page 24 SERVICE BULLETIN EVALUATION FORM (Your ideas will help us provide better bulletins) SERVICE BULLETIN: 604-57-007 ISSUE: Rev. 01 DATED: Nov 12/2014 TITLE: Special Check – Flap Hinge Box – Forward Lugs Edge to Edge Distance In an effort to improve the quality of our technical communications, we are replacing the standard Service Bulletin Evaluation Form with an on-line Service Bulletin Survey and we are requesting your feedback. Please take a moment to fill out our easy on-line Service Bulletin survey: http://csefeedback.aero.bombardier.com ### Page 25 SERVICE BULLETIN INCORPORATION SHEET – “604-57-007” BOMBARDIER SUBMISSION Upon completion of the Service Bulletin, please fill-in, fax to (514) 855-8798 or e-mail to Fracas at fracas.montreal@aero.bombardier.com If your aircraft is registered on CAMP and you are reporting to them, please do not send the incorporation sheet to Bombardier. If your aircraft is on another tracking system, please contact Bombardier to make arrangements for automated data submission. COMPLIED WITH Service Bulletin Number Rev. * Parts Completed YES NO N/A Remarks/Reason 604-57-007 01 PART A “ “ PART B - - - Actual hours to accomplish Service Bulletin: 1. Where the Service Bulletin is divided into a number of parts (e.g., PARTS A, B, C, D, etc.) which can be carried out separately, indicate only those parts completed at this time. 2. For repetitive checks (usually PART A) only the initial check should be reported unless otherwise stated in the Service Bulletin. * NOTES: 3. When more than one part is carried out at the same time, each part should be reported. Aircraft Serial No. Aircraft Reg. No. Airframe Hours: Airframe Landings S.B. Incorporation date Service Order No. (dd/mm/yy) Facility Incorporating S.B. Name Signature Date (dd/mm/yy) Signature not required if sent by E-Mail ### Page 26 -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- Bombardier Business Aircraft Customer Services (BBACS) P.O. Box 6087, Station Centre-ville Montreal, Québec, Canada H3C 3G9 Attention: Customer Support Department, Maintenance Engineering -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- --- 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.