A604-57-006

Page 1 of 1 

ALERT SERVICE BULLETIN 

REVISION TRANSMITTAL SHEET 

MODEL CL-600-2B16 

 Discard the Revision 03 of this Service Bulletin dated Aug 19/2014 and the 

Information Sheet dated Aug 27/2014 and replace in its entirety with this Revision 04. 

Service Bulletin No. A604-57-006

Date of Basic Issue Dec 20/2012

Revision No. 01 Dated Sep 26/2013

Revision No. 02 Dated Jan 22/2014

Revision No. 03 Dated Aug 19/2014

Revision No. 04 Dated Nov 12/2014

For action applicable to aircraft on which the Basic Issue, Revision 01, 

Revision 02 or Revision 03 of this Service Bulletin was done, refer to the 

retroactive action box on Page 1 of this Service Bulletin.

This revision has no effect for aircraft on which PART B or PART C 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: 

1. Change the Service Bulletin Summary Sheet, NOTE 2 and the Planning Information 

NOTE, to update the recommended SB information. 

2. Add, in the Service Bulletin Summary Sheet, in the Planning Information NOTE and 

in Paragraph 1.D., Compliance, a NOTE for the Airworthiness Directive 

3. Change the retroactive action box to add action applicable to Revision 03. 

4. Change Paragraph 1.F., to incorporate the data from the Information Sheet dated 

Aug 27/2014. 

5. Change, in Paragraph 1.K., the revision of the Restriction and/or Special Instruction 

(RSI), C-4095, to Rev. D. 

6. Change Paragraph 3.B., to add the part number and NOTE 2 for fasteners with a 

longer grip length. 

7. Make miscellaneous minor changes, as necessary, with no change of context. 
Basic Issue: Dec 20/2012 A604-57-006

Revision 04: Nov 12/2014 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 your 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) or within 50 landings from this Alert Service 

Bulletin release date (Revision 03) and must be 

repeated every 10 landings until modification in 

PART B is complied with or PART C is completed. 

PART B is recommended no later than 24 months 

from this Alert Service Bulletin release date 

(Revision 03).

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 

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. Defueling and venting of the fuel tanks must be done to do PART B of this 

Service Bulletin. 

2. To minimize aircraft downtime and cost, it is recommended to do Service Bulletin 

604-57-007, PART A, in conjunction with PART B of this Service Bulletin. 

3. This Service Bulletin is mandated by emergency Airworthiness Directive (AD) 

CF-2014-27R1 and FAA AD 2014-17-51.

To place an order for parts or kits, please call Bombardier Aerospace Parts Services at: 

514-855-2999 or 1-866-538-1247
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. 

© 2012 - 2014 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 04: Nov 12/2014 Page 1 of 22 

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. RETROACTIVE ACTION APPLICABLE TO AIRCRAFT THAT HAVE 

INCORPORATED THE BASIC ISSUE, REVISION 01, REVISION 02 OR 

REVISION 03 OF PART A OF THIS SERVICE BULLETIN: 

A. FOR THE AIRCRAFT WITH THE INCORRECTLY ORIENTED FORWARD 

FASTENERS HEADS (FIGURE 2 in PART A), PART A MUST BE DONE 

WITHIN 10 LANDINGS FROM THIS ALERT SERVICE BULLETIN RELEASE 

DATE (REVISION 03) AND MUST BE REPEATED EVERY 10 LANDINGS 

UNTIL PART B IS COMPLIED WITH. 

– NO FURTHER ACTION IS REQUIRED, ONCE PART B IS 

INCORPORATED. 

OR 

B. FOR THE AIRCRAFT WITH THE CORRECTLY ORIENTED FORWARD 

FASTENERS HEADS (FIGURE 1 in PART A). 

– NO FURTHER ACTION IS REQUIRED, ONCE PART C IS COMPLETED. 

2. NO RETROACTIVE ACTION IS REQUIRED FOR AIRCRAFT THAT HAVE 

INCORPORATED PART B OR PART C OF THE BASIC ISSUE, REVISION 01, 

REVISION 02 OR REVISION 03 OF THIS SERVICE BULLETIN. 
MODEL CL-600-2B16

Basic Issue: Dec 20/2012 A604-57-006

Revision 04: Nov 12/2014 Page 2 of 22 

1. PLANNING INFORMATION 

NOTES: 1. To minimize aircraft downtime and cost, it is recommended to do Service 

Bulletin 604-57-007, PART A, in conjunction with PART B of this Service 

Bulletin. 

 2. This Service Bulletin is mandated by emergency Airworthiness Directive 

(AD) CF-2014-27R1 and FAA AD 2014-17-51. 

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 the 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 fitting at Wing Station (WS) 76.50 was 

found with its head missing. 

The investigation shows that when installed with their head outside, those 

fasteners will experience premature failure caused by higher pre-load due to 

clamping and alignment. 

This Alert Service Bulletin provides instruction to inspect and repair the forward 

fasteners attaching the forward fittings at WS 76.50 and WS 127.25 at both wings. 
MODEL CL-600-2B16

Basic Issue: Dec 20/2012 A604-57-006

Revision 04: Nov 12/2014 Page 3 of 22 

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 fasteners heads are correctly oriented. 

Testing, to: 

– Do the necessary testing to ensure that the inboard flaps operate correctly. 

D. Compliance 

PART A is recommended within 100 landings from this Alert Service Bulletin 

release date (Basic Issue) or within 50 landings from this Alert Service Bulletin 

release date (Revision 03) and must be repeated every 10 landings until 

modification in PART B is complied with or until PART C is completed to confirm 

that the forward fasteners heads are correctly oriented. 

PART B is recommended no later than 24 months from this Alert Service Bulletin 

release date (Revision 03). 

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 oriented as per PART C, no further 

action is required. 

 3. This Service Bulletin is mandated by emergency Airworthiness 

Directive (AD) CF-2014-27R1 and FAA AD 2014-17-51. 
MODEL CL-600-2B16

Basic Issue: Dec 20/2012 A604-57-006

Revision 04: Nov 12/2014 Page 4 of 22 

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 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 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. 

The 58 man-hours required to do this Service Bulletin in PART B, is at no cost if: 

(i) the work is done at Bombardier Business Aviation Services (BBAS) 

or Authorized Service Facilities (ASF), and 

(ii) this Service Bulletin is carried out in less than 24 months from 

its release date (Revision 03). 
MODEL CL-600-2B16

Basic Issue: Dec 20/2012 A604-57-006

Revision 04: Nov 12/2014 Page 5 of 22 

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 correctly 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 the 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 24 months from this Alert Service Bulletin 

release date (Revision 03). 

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 04: Nov 12/2014 Page 6 of 22 

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 available 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 Illustrated 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 04: Nov 12/2014 Page 7 of 22 

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. D. 

– CL-604 Aircraft Maintenance Manual (AMM), Chapters 6, 12, 24, 27, 28, 

51 and 57. 

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

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

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

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

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

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

– Bombardier Aerospace, Repair Engineering 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 04: Nov 12/2014 Page 8 of 22 

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, access 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. Refer 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 forward attachments of the inboard flap 

hinge boxes at WS 76. 50 and WS 127.25. Refer to Figure 1 and Figure 2. 

Figure 1 
MODEL CL-600-2B16

Basic Issue: Dec 20/2012 A604-57-006

Revision 04: Nov 12/2014 Page 9 of 22 

(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 fasteners 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 forward inboard flap fasteners, hinge box 

wing forward fitting, must be repeated every 10 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 the 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 Fairing 
MODEL CL-600-2B16

Basic Issue: Dec 20/2012 A604-57-006

Revision 04: Nov 12/2014 Page 10 of 22 

(3) Obey the fuel system safety precautions. 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 unit (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-LOK/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. 

(14) If it is not possible to follow all instructions from Appendix 1, Part A or Part B 

(REO 600-57-26-001) due to the configuration of the aircraft structures, submit 

an SRPSA to Customer Support Engineering (CSE) for evaluation and to 

obtain an Approved Repair in order to allow completion of the Service Bulletin, 

by email at: SRPSA@aero.bombardier.com

Figure 3 
MODEL CL-600-2B16

Basic Issue: Dec 20/2012 A604-57-006

Revision 04: Nov 12/2014 Page 11 of 22 

(15) 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 cotter 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 04: Nov 12/2014 Page 12 of 22 

(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 (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 5 

(aa) Inspect the hinge bushings, Part No. 600-10300-611 (13) for 

damage and/or corrosion, if applicable, replace any damaged 

or corroded hinge bushings. 

(iv) For the flap hinge box (1) located 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 04: Nov 12/2014 Page 13 of 22 

(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 6 
MODEL CL-600-2B16

Basic Issue: Dec 20/2012 A604-57-006

Revision 04: Nov 12/2014 Page 14 of 22 

(16) 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. 

(17) If it is not possible to follow all instructions from Appendix 1, Part A or Part B 

(REO 600-57-26-001) due to the configuration of the aircraft structures, submit 

an SRPSA to Customer Support Engineering (CSE) for evaluation and to 

obtain an Approved Repair in order to allow completion of the Service Bulletin, 

by email at : SRPSA@aero.bombardier.com

Figure 7 

(18) 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 flap hinge box (1) and aft attachment fitting. 

(d) Install the bushings (13) on the forward lugs of the flap hinge box (1) and 

forward attachment fitting. 
MODEL CL-600-2B16

Basic Issue: Dec 20/2012 A604-57-006

Revision 04: Nov 12/2014 Page 15 of 22 

(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). 

(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. 

(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) 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 the applicable flap hinge box (1). Refer 

to SPM-MM 51-80-00-760-801. 

(19) 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 
MODEL CL-600-2B16

Basic Issue: Dec 20/2012 A604-57-006

Revision 04: Nov 12/2014 Page 16 of 22 

(20) Remove the DO NOT CONNECT − FUEL TANK MAINTENANCE placard from 

the battery. 

(21) Remove the DO NOT CONNECT − FUEL TANK MAINTENANCE placard from 

the ac and the dc ground power receptacles. 

(22) Connect the main battery. Refer to TASK 24-32-00-440-801. 

(23) Connect the APU battery. Refer to TASK 24-32-00-440-802. 

(24) Proceed to the Testing in Paragraph 2.E. 

D. PART C: Correctly Oriented Inboard 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 Bulletin 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 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. 

(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 
MODEL CL-600-2B16

Basic Issue: Dec 20/2012 A604-57-006

Revision 04: Nov 12/2014 Page 17 of 22 

(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 2 222 

(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 completed, 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 moment to fill out our easy on-line Alert 

Service Bulletin survey: 

http://csefeedback.aero.bombardier.com
MODEL CL-600-2B16

Basic Issue: Dec 20/2012 A604-57-006

Revision 04: Nov 12/2014 Page 18 of 22 

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 

Discard 
MODEL CL-600-2B16

Basic Issue: Dec 20/2012 A604-57-006

Revision 04: Nov 12/2014 Page 19 of 22 

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 the 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 (1st) oversize holes. 
MODEL CL-600-2B16

Basic Issue: Dec 20/2012 A604-57-006

Revision 04: Nov 12/2014 Page 20 of 22 

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 

The parts that follow may be necessary, to do PART B of this Alert Service Bulletin 

if fasteners with longer grip length are required and are available from Bombardier 

Aerospace Parts Services, Montreal: 

NEW 

PART NO. 

QTY ITEM USED 

PART NO. 

INSTRUCTIONS -

DISPOSITION 

B0206033AG8-13 

(HST54AG8-13) 0 to16 Pin (HI-LITE) 

HL912AP-8-12 

or 

HST54AG8-12 

Discard 

NOTES: 1. The part numbers for the items listed above are subject to change without 

revision to this Service Bulletin. In case of discrepancy between this list 

and any other list, the Illustrated Parts Catalog prevails and shall be used 

to determine the latest part number. 

 2. When required, to suit installation as per the REO in Appendix 1, contact 

Parts Services in Montreal, to order other fasteners with longer grip 

length. 
MODEL CL-600-2B16

Basic Issue: Dec 20/2012 A604-57-006

Revision 04: Nov 12/2014 Page 21 of 22 

C. Material 

The materials that follow, or equivalent, are necessary to do PART B of this 

Alert 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)

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)

20P1-21 BAMS 565-010 As 

Necessary Code: D 

Anti-Seize 

Lubricant LPS-1 - 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 04: Nov 12/2014 Page 22 of 22 

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. 04 DATED: Nov 12/2014 

 

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. Please 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” 

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

 Alert Service 

Bulletin Number 

 Rev. * Parts 

Completed 

YES NO N/A Remarks/Reason 

 A604-57-006 04 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
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Bombardier Business Aircraft Customer Services (BBACS) 

P.O. Box 6087, Station Centre-ville 

Montreal, Québec, Canada H3C 3G9 

Attention: Customer Support Department, Maintenance Engineering 

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