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 BO X 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 (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 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 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 1-866-538-1247Refer 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 copi ed 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 BO X FORWARD ATTACHMENT FITTINGS FASTENERS



### 1. PLANNING INFORMATION

NOTE : To minimize aircraft downtime and co st, 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 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 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-600-1A11

Basic Issue: Sep 26/2013 

# A600-0763 Page 2 of 18 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. 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 (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 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 EASA in accordance with established procedures.MODEL CL-600-1A11

Basic Issue: Sep 26/2013 

# A600-0763 Page 3 of 18 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 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 co rrectly oriented as per PART C. When applicable, submit an SRPSA to Cu stomer 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 avail able 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

Basic Issue: Sep 26/2013 

# A600-0763 Page 4 of 18 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 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 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

Basic Issue: Sep 26/2013 

# A600-0763 Page 5 of 18 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 Cata log (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, Modifica tion Summary IS600-57-0001, Rev. A.

–Bombardier Aerospace, Repair E ngineering 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 Page 6 of 18 

### 2. ACCOMPLISHMENT INSTRUCTIONS

NOTES : 1. If no other manual references are given, the procedures that follow are from the Maintenance Manual, PSP 602, 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. Re fer 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 222MODEL CL-600-1A11

Basic Issue: Sep 26/2013 

# A600-0763 Page 7 of 18 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 forw ard 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 head s 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 2MODEL CL-600-1A11

Basic Issue: Sep 26/2013 

# A600-0763 Page 8 of 18 (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 forwar d inboard flap fasteners, hinge box wing forward fitting, must be r epeated 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 t he wing surface and the inboard flap respectively. Refer to SRM, C hapter 51-57-00, SEALING - Description. (2) Remove the forward and aft inboard fl ap 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 prec autions. 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 TA NKS – 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

Basic Issue: Sep 26/2013 

# A600-0763 Page 9 of 18 (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-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-600-1A11

Basic Issue: Sep 26/2013 

# A600-0763 Page 10 of 18 (11) For each wing, disconnect one flap hinge box at a time from the forward attachment fitting and aft attach ment 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 SAFET YING 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 Page 11 of 18 (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. (aa) Inspect the hinge bushings , Part No. 600-10300-609 (18) for damage and/or corrosion, if applic able, 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 Page 12 of 18 (b) Carefully pull the flap hinge box (1) downward to allow access to the forward attachment fitting.

Figure 6MODEL CL-600-1A11

Basic Issue: Sep 26/2013 

# A600-0763 Page 13 of 18 (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 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-600-1A11

Basic Issue: Sep 26/2013 

# A600-0763 Page 14 of 18 (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 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 lb f in (2.26 to 2.82 Nm). Refer to Maintenance Manual, PSP 602, C hapter 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, C hapter 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.MODEL CL-600-1A11

Basic Issue: Sep 26/2013 

# A600-0763 Page 15 of 18 (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 t he aircraft. Refer to Chapter 24-00-00, ELECTRICAL POWER - Maintenance Practices. (18) Proceed to the Test ing in Paragraph 2.E. 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-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. Re fer 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 installi ng the flap hinge-fairings. Refer to Chapter 27-50-00, WING FLAP SYST EM – 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:MODEL CL-600-1A11

Basic Issue: Sep 26/2013 

# A600-0763 Page 16 of 18 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. Re fer 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 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 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 mo ment to fill out our easy on-line Alert Service Bulletin survey: http://csefeedback.aero.bombardier.comMODEL CL-600-1A11

Basic Issue: Sep 26/2013 

# A600-0763 Page 17 of 18 

### 3. MATERIAL INFORMATION

A. Kit When applicable, submit an SRPSA to Cu stomer 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 Cu stomer Support Engineering (CSE) to obtain kit and parts details necessary to do PART B of this modification.
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: EMODEL CL-600-1A11

Basic Issue: Sep 26/2013 

# A600-0763 Page 18 of 18 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. 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 – “A600-0763”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

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.
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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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