Basic Issue: Sep 26/2013 A600-0763

 Page 1 of 1 

ALERT SERVICE BULLETIN SUMMARY 

This Service Bulletin is available at: 

www.cic.bombardier.com

MODEL CL-600-1A11

ATA 57-40 

WINGS 

SPECIAL CHECK/MODIFICATION – ATTACHMENT FITTINGS – 

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) 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 (Basic Issue). 

EFFECTIVITY: A/C Serial No. 1004 to 1085 

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 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 600-0762 in conjunction with PART B of this Service Bulletin. 

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

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

© 2013 Bombardier Inc. All rights reserved 

Learjet, Challenger, Global, are registered trademarks of Bombardier Inc. or its subsidiaries. 

Basic Issue: Sep 26/2013 A600-0763

 Page 1 of 18 

ALERT SERVICE BULLETIN 

This Alert Service Bulletin is available at: 

www.cic.bombardier.com 

MODEL CL-600-1A11

ATA 57-40 

WINGS 

SPECIAL CHECK/MODIFICATION – ATTACHMENT FITTINGS – 

INBOARD FLAP HINGE BOX FORWARD ATTACHMENT FITTINGS FASTENERS 

1. PLANNING INFORMATION 

NOTE: To minimize aircraft downtime and cost, it is recommended to do Service 

Bulletin 600-0762 in conjunction with PART B of this Service Bulletin. 

A. Effectivity 

CL-600-1A11 aircraft, Serial No. 1004 to 1085. 

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. 
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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) and must be repeated every 100 landings until 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 48 months from this Service Bulletin 

release date (Basic Issue). 

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. 

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 EASA 

in accordance with established procedures. 
MODEL CL-600-1A11 

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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 600-0002. 

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 labor required to do the modification 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 Alert Service Bulletin is scheduled in less than 48 months from its 

release date (Basic Issue). 

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. 

When applicable, submit an SRPSA to Customer Support Engineering (CSE) 

to obtain kit and parts details necessary to do PART B of this modification. 

If applicable, the kit for PART B is available at no cost if a no-charge purchase 

order is sent to Bombardier Aerospace in less than 48 months from this Service 

Bulletin release date (Basic Issue). 

Bombardier does not pay for the bushings that may be 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-600-1A11 

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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 S4933959−501 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 S4933959−501 Tag, Circuit Breaker 

28-00-06 8320000 Fuel Fumes Detector 

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) 

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 Illustrated Tool and Equipment Manual (ITEM), PSP611 

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. 

I. Weight and Balance 

No change. 

J. Electrical Load Data 

No change. 
MODEL CL-600-1A11 

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K. References 

– Bombardier Aerospace, Restriction and/or Special Instruction (RSI), 

C-4095, Rev. B. 

– CL-600 Maintenance Manual, PSP 602, Chapters 6, 12, 24, 28, and 57. 

– CL-600 Illustrated Parts Catalog (IPC), PSP 604, Chapter 57. 

– CL-600 Structural Repair Manual (SRM), PSP 607, Chapter 51. 

– CL-600 Illustrated Tool and Equipment Manual (ITEM), PSP 611, Chapters 24 

and 28. 

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

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

– 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 604 aircraft, use SB A604-57-006. 

– For the Challenger 601 aircraft, use SB A601-0627. 
MODEL CL-600-1A11 

Basic Issue: Sep 26/2013 A600-0763

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2. ACCOMPLISHMENT INSTRUCTIONS 

NOTES: 1. If no other manual references are given, the procedures that follow 

are from the Maintenance Manual, PSP602, unless otherwise specified. 

2. All references made to zones, access panels and/or doors, are 

from the Maintenance Manual PSP602, 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) Obey all electrical/electronic safety precautions. Refer to Chapter 24-00-00, 

ELECTRICAL POWER - Removal/Installation. 

(3) Connect the external ac power. Refer to Chapter 12-00-00, SERVICING – 

General. 

(4) Set the flap control lever to 45 and make sure that the flaps are fully extended. 

(5) Remove the external ac power. Refer to Chapter 12-00-00, SERVICING – 

General. 

(6) Open and tag the circuit breakers that follow: 

CB PANEL CB NO. NAME ZONE 

CBP-A 20 (19, 21) FLAP MOTOR 1 221 

CBP-A 77 FLAP CONT 1 221 

CBP-B 176 (175, 178) FLAP MOTOR 2 222 

CBP-B 233 FLAP CONT 2 222 

CBP-B 188 (187, 189) BATT CHGR 222 
MODEL CL-600-1A11 

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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 

(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 
MODEL CL-600-1A11 

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(ii) If any of the forward fastener 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 100 landings, until the 

modification, provided in PART B of this SB is complied with. As 

applicable, Proceed to PART B or 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 SRM, Chapter 51-57-00, SEALING - Description. 

(2) Remove the forward and aft inboard flap hinge-fairings that follow, to gain 

access to inboard flap hinge boxes. Refer to Chapter 6-53-00, REMOVABLE 

FAIRINGS - General: 

ACCESS DESIGNATION 

571-CB (671-CB) Fairing, Forward Inboard Flap Hinge 

571-FB (671-FB) Fairing, Forward Inboard Flap Hinge 

572-DB (672-DB) Fairing, Rear Inboard Flap Hinge 

572-GB (672-GB) Fairing, Rear Inboard Flap Hinge 

(3) Obey all the fuel system safety precautions. Refer to Chapter 28-10-11, FUEL 

TANKS - Maintenance Practices. 

(4) Defuel the aircraft. Refer to Chapter 12-10-28, FUEL SYSTEM - 

Replenishing. 

(5) Drain, purge and prepare the main left and right fuel tanks for access. Refer 

to Chapter 28-10-11, FUEL TANKS – Maintenance Practices. 

(6) Remove the access panels that follow. Refer to Chapter 6-51-00, ACCESS 

PANELS AND DOORS: 

ACCESS DESIGNATION 

571BB (671BB) Wing Lower Surface – Access Panel 

571AB (671AB) Wing Lower Surface – Access Panel 

540FB (640FB) Fuel Tank – Access Panels 

540GB (640GB) Fuel Tank – Access Panels 

NOTE: You can use the Fuel Fumes Detector, Part No. 8320000, as an 

alternative to the explosiometer. 
MODEL CL-600-1A11 

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(7) Remove and isolate the electrical power from the aircraft. Refer to Chapter 

24-00-00, ELECTRICAL POWER - Maintenance Practices. 

(8) Put a DO NOT CONNECT − FUEL TANK MAINTENANCE placard on the 

battery. 

(9) Put a DO NOT CONNECT − FUEL TANK MAINTENANCE placard on the ac 

and the dc ground power receptacles. 

(10) 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. 

Figure 3 
MODEL CL-600-1A11 

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(11) 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 Maintenance 

Manual (PSP 602), 20-80-00 SAFETYING DEVICES, Cotter 

Pins. 

(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-600-1A11 

Basic Issue: Sep 26/2013 A600-0763

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(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 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. 

(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. 

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-600-1A11 

Basic Issue: Sep 26/2013 A600-0763

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(b) Carefully pull the flap hinge box (1) downward to allow access to the 

forward attachment fitting. 

Figure 6 
MODEL CL-600-1A11 

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(12) 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 

(13) 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. 

(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-600-1A11 

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(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). 

(g) Torque the nuts (9), and (14) from 30 to 35 lbf in (3.39 to 3.95 Nm). 

Refer to Maintenance Manual, PSP 602, Chapter 20-20-11, THREADED 

FASTENERS. 

(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 

Maintenance Manual, PSP 602, Chapter 20-20-11, THREADED 

FASTENERS. 

(iv) Install the cotter pin (4). Refer to Maintenance Manual, PSP 602, 

Chapter 20-80-00, SAFETYING DEVICES, Cotter Pins. 

(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 

Maintenance Manual, PSP 602, Chapter 57-40-01, FLAP HINGE BOX, 

Removal/Installation. 

(j) Do the electrical bonding test for the applicable flap hinge box (1). Refer 

to Maintenance Manual, PSP 602, Chapter 51-80-00, ELECTRICAL 

BONDING. 

(14) Install the access panels that follow: 

ACCESS DESIGNATION 

571BB (671BB) Wing Lower Surface – Access Panel 

571AB (671AB) Wing Lower Surface – Access Panel 

540FB (640FB) Fuel Tank – Access Panels 

540GB (640GB) Fuel Tank – Access Panels 

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

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

from the ac and the dc ground power receptacles. 

(17) Restore the electrical power on the aircraft. Refer to Chapter 24-00-00, 

ELECTRICAL POWER - Maintenance Practices. 

(18) 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-A 20 (19, 21) FLAP MOTOR 1 221 

CBP-A 77 FLAP CONT 1 221 

CBP-B 176 (175, 178) FLAP MOTOR 2 222 

CBP-B 233 FLAP CONT 2 222 

CBP-B 188 (187, 189) BATT CHGR 222 

(2) Connect the external ac power. Refer to Chapter 12-00-00, SERVICING – 

General. 

(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 

Chapter 27-50-00, WING FLAP SYSTEM – Maintenance Practices. 

(4) Remove the external ac power. Refer to Chapter 12-00-00, SERVICING. 

(5) Open and tag the circuit breakers that follow: 

CB PANEL CB NO. NAME ZONE 

CBP-A 20 (19, 21) FLAP MOTOR 1 221 

CBP-A 77 FLAP CONT 1 221 

CBP-B 176 (175, 178) FLAP MOTOR 2 222 

CBP-B 233 FLAP CONT 2 222 

CBP-B 188 (187, 189) BATT CHGR 222 

(6) Install the forward and aft inboard flap hinge-fairings that follow. Refer to 

Chapter 6-53-00, REMOVABLE FAIRINGS - General: 
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ACCESS DESIGNATION 

571-CB (671-CB) Fairing, Forward Inboard Flap Hinge 

571-FB (671-FB) Fairing, Forward Inboard Flap Hinge 

572-DB (672-DB) Fairing, Rear Inboard Flap Hinge 

572-GB (672-GB) Fairing, Rear Inboard Flap Hinge 

(7) Install fillet seal around perimeter of forward and aft inboard flap hinge-fairings 

making contact with the wing surface and the inboard flap respectively. Refer 

to SRM, Chapter 51-57-00, SEALING – Description, Aerodynamic Sealing. 

(8) Connect the external ac power. Refer to Chapter 12-00-00, SERVICING – 

General. 

(9) Carry out a flap operational test and check corresponding flap position 

indications in the flight compartment. Refer to Chapter 27-50-00, WING FLAP 

SYSTEM – Maintenance Practices. 

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-A 20 (19, 21) FLAP MOTOR 1 221 

CBP-A 77 FLAP CONT 1 221 

CBP-B 176 (175, 178) FLAP MOTOR 2 222 

CBP-B 233 FLAP CONT 2 222 

CBP-B 188 (187, 189) BATT CHGR 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 must be repeated every 100 landings and 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-600-1A11 

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 Page 17 of 18 

3. MATERIAL INFORMATION 

A. Kit 

When applicable, submit an SRPSA to Customer Support Engineering (CSE) to 

obtain kit and parts details necessary to do PART B of this modification. 

B. Parts 

When applicable, submit an SRPSA to Customer Support Engineering (CSE) to 

obtain kit and parts details necessary to do PART B of this modification. 

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)

20P1-10 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 
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DESCRIPTION PART 

No./NAME 

SPECIFICATION QUANTITY SUPPLIER

(See Note)

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. 

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: A600-0763 ISSUE: Basic DATED: Sep 26/2013 

 

TITLE: Special Check/Modification – Attachment Fittings – 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 – 

“A600-0763” 

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 

 A600-0763 Basic 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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