# A604-57-006 Page 1 of 2 

# ALERT SERVICE BULLETIN REVISION TRANSMITTAL SHEET

MODEL CL-600-2B16

Discard the Basic Issue of this Alert Service Bulletin dated Dec 20/2012, and replace in its entirety with this Revision 01.

Service Bulletin No. A 604-57-006
Date of Basic Issue Dec 201/2012
Revision No. 01 Dated Se p 26 / 2013

For action applicable to aircraft on which this Service Bulletin was done, refer to the retroactive action box on Page 1 of this Service Bulletin.

This revision is a complete reissue, theref ore revision bars were intentionally omitted. This revision is issued to provide instructions in PART B and PART C of this Service Bulletin. The changes are as follows: 1. Revise the Service Bulletin Summary Sheet, to add the manpower, the kit information and a note applicable to PART B. 2. Add a Retroactive Action Box. 3. Add a note to the Planning Information of Paragraph 1. 4. Add a paragraph and table to Paragraph 1. A. to include information on PART B of the Service Bulletin. 5. Revise Paragraph 1.C, to add, PART B, PART C and the testing description. 6. Add information to Paragraph 1.D. about PART B of the Service Bulletin. 7. Revise Paragraph 1.F., to add the manpower applicable to PART B. 8. Revise Paragraph 1.G, Paragraph 3.A, and Paragraph 3.B, to add the kit and part details applicable to PART B. 9. Revise Paragraph 1.H, to add the additional tools applicable to PART B.MODEL CL-600-2B16



# A604-57-006 Page 2 of 2 10. Change, in Paragraph 1.K., the revision of the Restriction and/or Special Instruction (RSI), C-4095, to Rev. B. 11. Add, in Paragraph 1.K, references to Stru ctural Repair Manual (SRM), Standard Practices Manual (SPM), Repair Engineering Order (REO ), 600-57-26-001, Repair Engineering Order (REO), 604-57-26-023, Repair Engineering Order (REO), 604-57- 26-024, Appendix 1, Appendix 2 and add chapter references to the AMM. 12. Add, in Paragraph 1.M, referenc es to the 600 & 601 Service Bulletins. 13. Revise Paragraph 2.A., to add additional instructions in the aircraft setup. 14. Revise Paragraph 2.B., to add clar ification for the special check. 15. Revise Paragraph 2.C., to add the modifi cation instructions applicable to PART B. 16. Revise Paragraph 2.D., to add the instructions applicable to PART C. 17. Revise Paragraph 2.E., to add the test ing instructions applicable to PART B. 18. Revise Paragraph 3.C., to add the consumables information applicable to this Service Bulletin. 19. Add Appendix 1. 20. Add Appendix 2. 21. Make miscellaneous minor changes, as necessary, with no change of context.Basic Issue: Dec 20/2012 

# A604-57-006 Revision 01: Sep 26/2013 Page 1 of 1



# ALERT SERVICE BULLETIN SUMMARY

This Service Bulletin is available at: www.cic.bombardier.com 

### MODEL CL-600-2B16
ATA 57-52

WINGS
SPECIAL CHECK/MODIFICATION – INBOARD FLAP HINGE BOX – FORWARD ATTACHMENT FITTINGS FASTENERS The information below is provided for y our reference. For full details, please see corresponding paragraph contained within this bulletin. 

# ALERT

SPECIFIED TIME COMPLIANCE 

## COMPLIANCE TIME PART A is recommended within 100 landings from this Alert Service Bulletin release date (Basic Issue) and must be repeated every 100 landings until modification in PART B is complied with or PART C is completed. PART B is recommended no later than 48 months from this Service Bulletin release date (Revision 01). EFFECTIVITY: A/C Serial No. 5301 to 5665 MANPOWER: 1 man-hour for the special check in PART A 58 man-hours for the modification in PART B CONTINUED AIRWORTHINESS (CAW) FLEET CAMPAIGN 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. Defueling and venting of the fuel tanks mu st be done to do PART B of this Service Bulletin. 2. To minimize aircraft downtime and co st, it is recommended to do Service Bulletin 604-57-007 in conjunction with PAR T B of this Service Bulletin. To place an order for parts or kits, please call Bombardier Aerospace Parts Services at: 514-855-2999 or 1-866-538-1247Refer 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 Bombardi er 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. © 2011 - 2013 Bombardier Inc. All rights reserved Learjet, Challenger, Global, are registered trademarks of Bombardier Inc. or its subsidiaries.
Basic Issue: Dec 20/2012 

# A604-57-006 Revision 01: Sep 26/2013 Page 1 of 20 

# ALERT SERVICE BULLETIN

This Alert Service Bulletin is available at: www.cic.bombardier.com 

### MODEL CL-600-2B16
ATA 57-52

WINGS

SPECIAL CHECK/MODIFICATION – INBOARD FLAP HINGE BOX – FORWARD ATTACHMENT FITTINGS FASTENERS

RETROACTIVE ACTION 1. FOR THE AIRCRAFT WITH THE I NCORRECTLY ORIENTED FORWARD FASTENERS HEADS (FIGURE 2 in PART A), PART A MUST BE REPEATED EVERY 100 LANDINGS UNTIL PART B IS COMPLIED WITH.

–NO FURTHER ACTION IS REQUIRED , ONCE PART B IS INCORPORATED. OR
2. FOR THE AIRCRAFT WITH THE CORRECTLY ORIENTED FORWARD FASTENERS HEADS (FIGURE 1 in PART A).

–NO FURTHER ACTION IS REQUIR ED, ONCE PART C IS COMPLETED.


### 1. PLANNING INFORMATION
NOTE : To minimize aircraft downtime and co st, it is recommended to do Service Bulletin 604-57-007 in conjunction with PAR T B of this Service Bulletin.MODEL CL-600-2B16

Basic Issue: Dec 20/2012 

# A604-57-006 Revision 01: Sep 26/2013 Page 2 of 20 A. Effectivity CL-600-2B16 aircraft, Serial No. 5301 to 5665

. The intent of this Service Bulletin PART B was met on the aircraft that follow with the Repair Engineering Orders (REO) and Service Requests for Product Support Action (SRPSA) listed in the table that follows:

AIRCRAFT SERIAL NO. DRAWING. SRPSA NO.
5488 REO 604-57-26-023 33112 5516 REO 604-57-26-024 31436
NOTE : The instructions given in this Alert Service Bulletin are only applicable to the systems and parts installed at t he time of delivery of the aircraft or as changed by Bombardier Aerospace Alert 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. B. Reason On a Challenger 605 zonal inspection, one of the two forward fasteners attaching the inboard flap hinge box forward hinge fi tting at Wing Station (WS) 76.50 was found with its head missing. The investigation shows that when in stalled with their head outside, those fasteners will experience premature failu re caused by higher pre-load due to clamping and alignment. This Alert Service Bulletin provides inst ruction to inspect and repair the forward fasteners attaching the forward fittings at WS 76.50 and WS 127.25 at both wings. C. Description This Alert Service Bulletin gives instructions in: PART A, to :

–Do the inspection of the forward inboard flap fasteners on the hinge box wing forward fitting. PART B, to :

–Remove the forward and aft inboard flap hinge-fairings,

–Remove the applicable upper and lower access panels,

–Do the inboard flap fasteners modifications as per APPENDIX 1 on the hinge box wing forward fittings,

–Install the removed wing upper and lower access panels, and

–Re-install the forward and aft inboard flap hinge-fairings. PART C, to :

–Confirm that the forward fast eners heads are correctly oriented. Testing, to :

–Do the necessary testing to ensure that the inboard flaps operate correctly.MODEL CL-600-2B16

Basic Issue: Dec 20/2012 

# A604-57-006 Revision 01: Sep 26/2013 Page 3 of 20 D. Compliance PART A is recommended within 100 landings from this Alert Service Bulletin release date (Basic Issue) and must be repeated every 100 landings until PART B is complied with or until PART C is comp leted to confirm that the forward fasteners heads are correctly oriented. PART B is recommended no later than 48 months from this Service Bulletin release date (Revision 01). NOTES : 1. At any time, if any of the forward fasteners heads are found missing, PART B must be implemented before further flight. 2. If the modification in PART B is incorporated or if the forward fasteners heads are correctly orient ed as per PART C, no further action is required. 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 Alert 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 the JAA and by EASA in accordance with established procedures. F. Manpower NOTES : 1. The man-hours given are estimates to help you schedule the tasks given in this bulletin. The estimate s 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 t he manpower estimates, refer to SB 604-00-002. 2. This Alert 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 Alert Service Bulletin. 1 man-hour is necessary to do the special check in PART A. 58 man-hours are necessary to do this modification in PART B. Bombardier does not pay for the special check in PART A and the Fuel Disposal fee at any time.MODEL CL-600-2B16

Basic Issue: Dec 20/2012 

# A604-57-006 Revision 01: Sep 26/2013 Page 4 of 20 For aircraft out of warranty, refer to the steps that follows for the labor covered to do the modification, if: (i) the work is done at Bombardier Business Aviation Services (BBAS) or Authorized Service Facilities (ASF), and (ii) the modification in PART B is carri ed out as per the table that follows:
OUT-OF-WARRANTY COVERAGE LABOR COVERAGE COVERAGE PERIOD 52 man-hours This Service Bulletin is carried out at the Next 96 Month Maintenance Inspection and within 48 months from the time of release of this Service Bulletin (Revision 01). 58 man-hours This Service Bulletin is carried out after the 96 Month Maintenance Inspection and within 48 months from the time of release of this Service Bulletin (Revision 01). G. Material - Cost and Availability No kits or parts are necessary to do the special check in PART A or to confirm that the forward fasteners heads are co rrectly oriented as per PART C. Kit 605K57-004 is necessary to do PART B of this modification:
KIT NO. PRICE 605K57-004 Please contact Bombardier Aerospace Parts Services, in Montreal, for delivery

lead times and confirmation of prices. Sufficient kits will be kept for t he estimated amount of orders. This kit for PART B is available at no cost if a no-charge purchase order is sent to Bombardier Aerospace in less than 48 mont hs from this Alert Service Bulletin release date (Revision 01). Bombardier does not pay for the bushings that maybe necessary, to do PART B, of this Service Bulletin. Bombardier does not pay for the Fuel Disposal fee at any time. During or after the above free period, Smart Parts Plus does not pay for the kit.MODEL CL-600-2B16

Basic Issue: Dec 20/2012 

# A604-57-006 Revision 01: Sep 26/2013 Page 5 of 20 H. Tooling The tools that follow, or equivalent, are necessary to do PART A of this Alert Service Bulletin:

GSE REFERENCE NO. PART NO. DESCRIPTION 24-00-24 - Tag, Circuit Breaker Commercially Available - Borescope The tools that follow, or equivalent, are necessary to do PART B of this Alert Service Bulletin:

GSE REFERENCE NO. PART NO. DESCRIPTION 24-00-24 - Tag, Circuit Breaker Commercially Available - Torque Wrench 17 to 19 lbf in (1.92 to 2.14 Nm) Commercially Available - Torque Wrench 20 to 25 lbf in (2.26 to 2.82 Nm) Commercially Available - Torque Wrench 23 to 27 lbf in (2.60 to 3.05 Nm) Commercially Available - Torque Wrench 30 to 35 lbf in (3.39 to 3.95 Nm) The tools listed below or commercially av ailable equivalent tools are required for the removal of the bushings.
REFERENCE NO. PART NO. DESCRIPTION Commercially Available - C-Clamp 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 Introduction of the publication listed in NOTE 1 for acceptable GSE equivalents. 3. For the support block manufacturing details, refer to Appendix 2.MODEL CL-600-2B16

Basic Issue: Dec 20/2012 

# A604-57-006 Revision 01: Sep 26/2013 Page 6 of 20 I. Weight and Balance No change. J. Electrical Load Data No change. K. References

–Bombardier Aerospace, Restriction and/or Special Instruction (RSI), C-4095, Rev. B.

–CL-604 Aircraft Maintenance Manual (A MM), Chapters 6, 12, 24, 27, 28, 51 and 57.

–CL-604 Aircraft Illustrated Part s Catalog (AIPC), Chapter 57.

–CL-604 Structural Repair Manual (SRM), Chapter 51.

–Bombardier Aerospace, Standard Pr actices Manual (SPM), Chapter 51.

–Bombardier Aerospace, Modifica tion Summary IS600-57-0001, Rev. A.

–Bombardier Aerospace, Repair Engi neering Order (REO), 600-57-26-001.

–Bombardier Aerospace, Repair Engi neering Order (REO), 604-57-26-023.

–Bombardier Aerospace, Repair Engi neering Order (REO), 604-57-26-024.

–Bombardier Aerospace, Appendix 1 (attached).

–Bombardier Aerospace, Appendix 2 (attached). L. Other Publications Affected None M. Equivalent Service Bulletins

–For the Challenger 605 aircraft, use SB A605-57-004.

–For the Challenger 601 aircraft, use SB A601-0627.

–For the Challenger 600 aircraft, use SB A600-0763.MODEL CL-600-2B16

Basic Issue: Dec 20/2012 

# A604-57-006 Revision 01: Sep 26/2013 Page 7 of 20 

### 2. ACCOMPLISHMENT INSTRUCTIONS
NOTES : 1. All TASKs given in the procedures that follow are from the CL-604 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 positions and the warning placard on the flap control lever. (2) Connect and energize the external AC power. Refer to TASK 12-00-07-861-801. (3) Set the flap control lever to 45 degrees and make sure that the flaps are fully extended. (4) Remove the external AC power. Refer to TASK 12-00-07-861-802. (5) Open and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP-1 B5 FLAP MOTOR 1 221 CBP-2 B5 FLAP MOTOR 2 222 B. PART A: Special Check − Inboard Flap Fasteners on the Hinge Box Wing Forward Fitting (1) Do a detailed borescope inspection of the inboard flap fasteners of the hinge box wing forward fitting of both wings. Re fer to the steps that follow, Figure 1 and Figure 2. NOTE : If the fairing is already removed, a visual inspection can be carried out instead of a borescope inspection. (a) Examine the orientation of the fo rward attachments of the inboard flap hinge boxes at WS 76. 50 and WS 127.25. Refer to Figure 1 and Figure 2.

Figure 1MODEL CL-600-2B16

Basic Issue: Dec 20/2012 

# A604-57-006 Revision 01: Sep 26/2013 Page 8 of 20 (i) If all of the forward fasteners heads of the inboard flap hinge boxes at WS 76.50 and WS 127.25 of both wings, are correctly oriented as per Figure 1, proceed to PART C in Paragraph 2.D.

Figure 2 (ii) If any of the forward fast eners heads are found missing as per Figure 2, proceed to PART B in Paragraph 2.C. (iii) If any of the forward fasteners heads are incorrectly oriented as per Figure 2 but no fasteners heads are found missing, then the borescope inspection of the forwar d inboard flap fasteners, hinge box wing forward fitting, must be repeat ed every 100 landings, until the modification, provided in PART B of this SB is complied with. Proceed to the Close-out in Paragraph 2.F. C. PART B: Modification − Incorrectly Oriented Inboard Flap Fasteners on the Hinge Box Wing Forward Fitting (1) Remove fillet seal from perimeter around the forward and aft inboard flap hinge-fairings, making contact with t he wing surface and the inboard flap respectively. Refer to SPM TASK 51-23-00-100-801. (2) Remove the left and right forward and aft inboard flap hinge-fairings that follow: Refer to TASK 57-26-03-000-801.
ACCESS DESIGNATION 571AB (671AB) Forward Inboard – Flap Hinge Fairing 571EB (671EB) Forward Inboard – Flap Hinge Fairing 572DB (672DB) Aft Inboard – Flap Hinge Fairing 572GB (672GB) Aft Inboard – Flap Hinge FairingMODEL CL-600-2B16

Basic Issue: Dec 20/2012 

# A604-57-006 Revision 01: Sep 26/2013 Page 9 of 20 (3) Obey the fuel system safety precaut ions. Refer to TASK 28-00-00-910-801. (4) Defuel the main fuel tank. Refer to TASK 12-11-28-650-803. (5) Gravity defuel the main fuel tank. Refer to TASK 12-11-28-650-804. (6) Remove the external ac power . Refer to TASK 12-00-07-861-802. (7) Remove the external dc power . Refer to TASK 12-00-07-861-804. (8) Disconnect the main battery. Refer to TASK 24-32-00-040-801. (9) Disconnect the auxiliary power uni t (APU) battery. Refer to TASK 24-32-00-040-802. (10) Put a DO NOT CONNECT

− FUEL TANK MAINTENANCE placard on the battery. (11) Put a DO NOT CONNECT

− FUEL TANK MAINTENANCE placard on the ac and the dc ground power receptacles. (12) Remove the access panels that follow:
ACCESS DESIGNATION TASK 571BB (671BB) Wing Lower Surface – Access Panel 57

− 21

− 04

− 000

− 803 541AT (641AT) Wing Upper Surface – Access Panel 57

− 21

− 01

− 000

− 802 540EB (640EB) Fuel Tank – Access Panels 28

− 11

− 01

− 000

− 801 540FB (640FB) Fuel Tank – Access Panels 28

− 11

− 01

− 000

− 801 (13) Remove and replace each of the HI-L OK/Hi-LITE forward fasteners on the left and right wing at WS 76.50 and WS 127.25 as per Appendix 1, PART A , and Figure 3.

Figure 3MODEL CL-600-2B16

Basic Issue: Dec 20/2012 

# A604-57-006 Revision 01: Sep 26/2013 Page 10 of 20 (14) For each wing, disconnect one flap hinge box at a time from the forward attachment fitting and aft attachment fitting. Refer to the steps that follow: 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. 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 4.

Figure 4 (a) Disconnect the inboard flap hinge box (1) at location WS 76.50 and WS 127.25 as follows: Refer to Figure 5 and Figure 6. (i) If necessary, remove and keep the hardware that attach the bonding jumpers to the flap hinge box (1). (ii) For the flap hinge box (1) located at WS 76.50 only, do as follows: (aa) If necessary, disconnect the electrical connector wire from any attached location on the structure, to allow downward movement of the flap hinge box. (bb) Remove and discard the cotte r pin (4). Refer to SPM-MM 20-50-00-000-802. (cc) Remove and keep the nut (5), washer (6) and bolt (7) and disconnect the control rod (2) from the lever (8) of the flap position transmitter. (dd) If necessary, put protective covers on the open ends of the electrical connector (3) and on the electrical connection of the position transmitter.MODEL CL-600-2B16

Basic Issue: Dec 20/2012 

# A604-57-006 Revision 01: Sep 26/2013 Page 11 of 20 (iii) For the flap hinge box (1) located WS 76.50 and WS 127.25, remove and keep the nuts (9), washers (10) and (11), bolts (12), and hinge bushings (13), to disconnect the flap hinge box (1) from the forward attachment fitting. Refer to Figure 5 and Figure 6.

CAUTION : TO REMOVE AND INSTALL THE HINGE BUSHINGS USE A C-CLAMP METHOD WITH THE SUPPORT BLOCK. USE LIGHT ANTISEIZE LUBRICANT (WD-40 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 5 (aa) Inspect the hinge bushings , Part No. 600-10300-611 (13) for damage and/or corrosion, if applic able, replace any damaged or corroded hinge bushings

. (iv) For the flap hinge box (1) loca ted WS 76.50 and WS 127.25, remove and keep the nuts (14), washers (15) and (16), bolts (17), and hinge bushings (18), to disconnect the hinge box (1) from the aft attachment fitting. Refer to Figure 5 and Figure 6.

Install the support block, manufactured as per Appendix 2 or an equivalent commercially available tool between the fittings.
Shim all gaps as required.MODEL CL-600-2B16

Basic Issue: Dec 20/2012 

# A604-57-006 Revision 01: Sep 26/2013 Page 12 of 20 (aa) Inspect the hinge bushings , Part No. 600-10300-609 (18) for damage and/or corrosion, if applicable, replace any damaged or corroded hinge bushings

. (b) Carefully pull the flap hinge box (1) downward to allow access to the forward attachment fitting.

Figure 6MODEL CL-600-2B16

Basic Issue: Dec 20/2012 

# A604-57-006 Revision 01: Sep 26/2013 Page 13 of 20 (15) Remove and replace each of the HI-LOK/Hi-LITE AFT fasteners on the left and right wing at WS 76.50 and WS 127.25 as per Appendix 1, PART B , and Figure 7.

Figure 7 (16) Attach the inboard flap hinge box (1) at locations WS 76.50 and WS 127.25. Refer to the steps that follow, Figure 5 and Figure 6: (a) Apply one layer of Mastinox 6856K to the hinge bushings (13) and hinge bushings (18) on installation. (b) Put the flap-hinge-box (1) in position. (c) Install the bushings (18) on the fl ap 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).MODEL CL-600-2B16

Basic Issue: Dec 20/2012 

# A604-57-006 Revision 01: Sep 26/2013 Page 14 of 20 (f) Install the bolts (12), washers (10) and (11), and nuts (9) to attach the flap hinge box (1) to the forw ard 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). (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). (iii) Torque the nut (5), from 20 to 25 lb f in (2.26 to 2.82 Nm). Refer to SPM-MM 20-21-00-910-801. (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 c onnection of the position transmitter. (vi) 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) Install the bonding jumper on the flap hinge box (1). Refer to SPM 51-80-00-400-801. (j) Do the electrical bonding test for t he applicable flap hinge box (1). Refer to SPM-MM 51-80-00-760-801. (17) Install the access panels that follow:
ACCESS DESIGNATION TASK 571BB (671BB) Wing Lower Surface – Access Panel 57

− 21

− 04

− 400

− 803 541AT (641AT) Wing Upper Surface – Access Panel 57

− 21

− 01

− 400

− 802 540EB (640EB) Fuel Tank – Access Panels 28

− 11

− 01

− 400

− 801 540FB (640FB) Fuel Tank – Access Panels 28

− 11

− 01

− 400

− 801 (18) Remove the DO NOT CONNECT

− FUEL TANK MAINTENANCE placard from the battery. (19) Remove the DO NOT CONNECT

− FUEL TANK MAINTENANCE placard from the ac and the dc ground power receptacles. (20) Connect the main battery. Refer to TASK 24-32-00-440-801. (21) Connect the APU battery. Refer to TASK 24-32-00-440-802. (22) Proceed to the Test ing in Paragraph 2.E.MODEL CL-600-2B16

Basic Issue: Dec 20/2012 

# A604-57-006 Revision 01: Sep 26/2013 Page 15 of 20 D. PART C: Correctly Oriented Inboa rd Flap Fasteners on the Hinge Box Wing Forward Fitting If the forward fasteners heads are correctly oriented as per Figure 1, you already meet the intention of this Service Bu lletin and no further action is required, proceed to the Close-out in Paragraph 2.F. E. Testing (1) Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP-1 B5 FLAP MOTOR 1 221 CBP-2 B5 FLAP MOTOR 2 222 (2) Connect and energize the external AC power. Refer to TASK 12-00-07-861-801. (3) Do an operational test of the inboard fl aps to make sure the flap hinge box assemblies move freely, before installi ng the flap hinge-fairings. Refer to TASK 27-54-00-710-801. (4) Remove the external AC power. Refer to TASK 12-00-07-861-802. (5) Open and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP-1 B5 FLAP MOTOR 1 221 CBP-2 B5 FLAP MOTOR 2 222 (6) Install the left and right forward and aft inboard flap hinge-fairings that follow: Refer to TASK 57-26-03-400-801.
ACCESS DESIGNATION 571AB (671AB) Forward Inboard – Flap Hinge Fairing 571EB (671EB) Forward Inboard – Flap Hinge Fairing 572DB (672DB) Aft Inboard – Flap Hinge Fairing 572GB (672GB) Aft Inboard – Flap Hinge Fairing (7) Apply a filet of sealant around the forward and aft inboard flap hinge fairings. Refer to SPM-MM 51-23-00-390-805. (8) Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP-1 B5 FLAP MOTOR 1 221 CBP-2 B5 FLAP MOTOR 2 222MODEL CL-600-2B16

Basic Issue: Dec 20/2012 

# A604-57-006 Revision 01: Sep 26/2013 Page 16 of 20 (9) Connect and energize the external AC power. Refer to TASK 12-00-07-861-801. (10) Do an operational test of the inboard and outboard flaps. Refer to TASK 27-54-00-710-801.

F. Close-out (1) If not already done, remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP-1 B5 FLAP MOTOR 1 221 CBP-2 B5 FLAP MOTOR 2 222 (2) Remove all tools, equipment and unwanted materials from the aircraft. G. Recording You can do each PART of this Alert Service Bulletin independently. When any PART of this Alert Service Bulletin is comp leted, make an entry in the aircraft log and send the attached Incorporation Notice to Bombardier Business Aircraft Customer Services (BBACS). This Alert Service Bulletin can only be closed when: - The modification in PART B is completed,
or - PART C is completed to confirm that the forward fasteners heads are correctly oriented. In an effort to improve the quality of our technical communications, we are requesting your feedback. Please take a mo ment to fill out our easy on-line Alert Service Bulletin survey: http://csefeedback.aero.bombardier.comMODEL CL-600-2B16

Basic Issue: Dec 20/2012 

# A604-57-006 Revision 01: Sep 26/2013 Page 17 of 20 

### 3. MATERIAL INFORMATION
A. Kit Kit 605K57-004 is necessary to do PART B of this Alert Service Bulletin and contains the parts that follow:

NEW PART NO. QTY ITEM USED PART NO. INSTRUCTIONS - DISPOSITION 600-57-26-001-001 1 Shim - - 600-57-26-001-002 1 Shim - - 600-57-26-001-003 1 Shim - - 600-57-26-001-004 1 Shim - - 600-57-26-001-005 1 Shim - - 600-57-26-001-006 1 Shim - - 600-57-26-001-007 1 Shim - - 600-57-26-001-008 1 Shim - - HST54AG8-11 or HST54AC8-11 or HST54AP8-11 or HST54AZ8-11 (See NOTE 3) 4 Pin ( HI-LITE ) HL912AP-8-11 or HST54AG8-11 Discard

HST54AG8-12 or HST54AC8-12 or HST54AP8-12 or HST54AZ8-12 (See NOTE 3) 12 Pin ( HI-LITE ) HL912AP-8-12 or HST54AG8-12 Discard

HST154AG8-11 or HST154AC8-11 or HST154AP8-11 or HST154AZ8-11 (See NOTE 4) 1 Pin ( HI-LITE ) HL912AP-8-11 or HST54AG8-11 DiscardMODEL CL-600-2B16

Basic Issue: Dec 20/2012 

# A604-57-006 Revision 01: Sep 26/2013 Page 18 of 20 NEW PART NO. QTY ITEM USED PART NO. INSTRUCTIONS - DISPOSITION HST154AG8-12 or HST154AC8-12 or HST154AP8-12 or HST154AZ8-12 (See NOTE 4) 2 Pin ( HI-LITE ) HL912AP-8-12 or HST54AG8-12 Discard

KFN674-4 or B0203015-4 16 Self Locking Nuts HL75-8AW or B0203015-4 Discard

MS24665-71 2 Cotter Pin MS24665-71 Discard NOTES : 1. In case of discrepancy between this list and the “Alert Service Bulletin Kit Parts List” contained in the respective kit, then the latter list prevails. 2. The actual quantity for some of t he hardware contained in the kit can be greater than the amount shown in the table as these items are supplied in prepackaged quantities. 3. Require for nominal size holes. 4. If Required for First (1 st ) oversize holes. B. Parts The parts that follow may be necessary to do PART B of this Alert Service Bulletin if found damaged or corroded when removed and are available from Bombardier Aerospace Parts Services, Montreal:

NEW PART NO. QTY ITEM USED PART NO. INSTRUCTIONS - DISPOSITION

600-10300-609 0 to 8 Bushing, AFT Attachment Fitting 600-10300-609 Discard

600-10300-611 0 to 8 Bushing, FWD Attachment Fitting 600-10300-611 Discard

NOTE : The part numbers for the items list ed above are subject to change without revision to this Service Bulletin. In case of discrepancy between this list and any other list, the Illustrated Part s Catalog prevails and shall be used to determine the latest part number.MODEL CL-600-2B16

Basic Issue: Dec 20/2012 

# A604-57-006 Revision 01: Sep 26/2013 Page 19 of 20 C. Material The materials that follow, or equivalen t, are necessary to do PART B of this Alert Service Bulletin. These can be purc hased from a local supplier. Bombardier Aerospace does not pay for these consumables.
DESCRIPTION PART No./NAME SPECIFICATION QUANTITY SUPPLIER (See Note)
Corrosion

inhibitor Compound Mastinox 6856K - As Necessary Code: A
Integral Fuel Tank Sealant CT: (9 hours) B1/2 (20 hours) B2 P/S 870B MIL-PRF-81733 Type II As Necessary Code: A

Sealant CT: (12 hours) B1/2 (24 hours) B2 PR1776M B1/2 or PR1776M B2 - As Necessary Code: A
Durathane High

Gloss Enamel

CT: (12 hours) 7600 line BAMS 565-002 As Necessary Code: B
Epoxy Primer Grey CT: (2 hours) 4500-P-40B (16473, FS 595B) BAMS 565-001 As Necessary Code: B

Conversion

Coating Alodine 1201 MIL-DTL81706B Type II As Necessary Code: C
Epoxy Resin CT: (24 hours) Hysol EA9309.3NA AS9354002 As Necessary Code: C
Fuel Tank Coatings (Primer Yellow)

CT: (24 hours) 20P1-10 BAMS 565-010 As Necessary Code: D

Anti-Seize Lubricant WD-40 - As Necessary Code: E
Brush, Natural or Synthetic Bristle - - As Necessary Code: E Scraper, Non-Metallic - - As Necessary Code: E

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 Alert 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.MODEL CL-600-2B16

Basic Issue: Dec 20/2012 

# A604-57-006 Revision 01: Sep 26/2013 Page 20 of 20 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 Code: B Tempo Aerospace Inc

205 Fenmar Drive, Toronto, Ontario, Canada M9L 2X4 Tel.: 1-416-746-2233 Fax.: 1-416-746-2235 E-mail: sales@tempo-aerospace.com Web Site: www.tempo-aerospace.com
Code: C Henkel Corporation 2850 Willow Pass Road Bay Point, California 94565 Tel.: 1-925-458-8000 Fax: 1-925-458-8030 Web Site: www.henkelna.com Code: D AkzoNobel Aerospace Coatings. 1 East Water Street Waukegan, IL 60085 USA Tel.: 1-847-623-4200 Fax.: 1-847-625-3200 E-mail: customer.service@akzonobel.com Web Site: www.akzonobel.com

Code: E Commercially Available

D. Publications No publications required.

### ALERT SERVICE BULLETIN EVALUATION FORM (Your ideas will help us provide better bulletins)

SERVICE BULLETIN: A604-57-006 ISSUE: Rev. 01 DATED: Sep 26/2013

TITLE: Special Check/Modification – Inboard Flap Hinge Box – Forward Attachment Fittings Fasteners

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. Pl ease take a moment to fill out our easy on-line Service Bulletin survey:



### http://csefeedback.aero.bombardier.com

## ALERT SERVICE BULLETIN INCORPORATION SHEET – “A604-57-006”BOMBARDIERSUBMISSION 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 Alert Service Bulletin Number Rev. * Parts Completed YES NO N/A Remarks/Reason

A604-57-006 01 PART A “ “ PART B “ “ PART C

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-- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- --



### Bombardier Business Aircraft Customer Services (BBACS) P.O. Box 6087, Station Centre-ville Montreal, Québec, Canada H3C 3G9

Attention : Customer Support Department, Maintenance Engineering

-- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- --