Basic Issue: Sep 26/2013 

# A601-0627 Page 1 of 1



# ALERT SERVICE BULLETIN SUMMARY

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

### MODEL CL-600-2A12 & CL-600-2B16

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. 3001 to 3066 A/C Serial No. 5001 to 5194
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 601-0631 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 Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or by any means without the prior written consen t 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 

# A601-0627 Page 1 of 18 

# ALERT SERVICE BULLETIN

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

### MODEL CL-600-2A12 & CL-600-2B16

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 601-0631 in conjunction with PART B of this Service Bulletin. A. Effectivity CL-600-2A12 aircraft, Serial No. 3001 to 3066

. CL-600-2B16 aircraft, Serial No. 5001 to 5194

. 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 forw ard hinge fitting 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 instructions to inspect and repair the forward fasteners attaching the forwar d fittings at WS 76.50 and WS 127.25 at both wings.MODEL CL-600-2A12 & CL-600-2B16

Basic Issue: Sep 26/2013 

# A601-0627 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. In PART C, to :

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

–Do the necessary testing to ensure t hat 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 implem ented 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-600-2A12 & CL-600-2B16

Basic Issue: Sep 26/2013 

# A601-0627 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 esti mates 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 601-0002. 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 Servic e Facilities (ASF), and (ii) this 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 the kit and part 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-600-2A12 & CL-600-2B16

Basic Issue: Sep 26/2013 

# A601-0627 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 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-600-2A12 & CL-600-2B16

Basic Issue: Sep 26/2013 

# A601-0627 Page 5 of 18 K. References

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

–CL-601 Maintenance Manual, PSP 601-2, Chapters 6, 12, 24, 28, and 57.

–CL-601 Illustrated Parts Catal og (IPC), PSP 601-4, Chapter 57.

–CL-601 Structural Repair Manual (SRM), PSP 607, Chapter 51.

–CL-601 Illustrated Tool and E quipment 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, Ki t Drawing K600-10110, Rev. --.

–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 600 aircraft, use SB A600-0763.


### 2. ACCOMPLISHMENT INSTRUCTIONS
NOTES : 1. If no other manual references are given, the procedures that follow are from the Maintenance M anual, PSP601-2, unless otherwise specified. 2. All references made to zones, access panels and/or doors, are from the Maintenance Manual PSP601-2, 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. (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.MODEL CL-600-2A12 & CL-600-2B16

Basic Issue: Sep 26/2013 

# A601-0627 Page 6 of 18 (6) Open and tag the circuit breakers that follow:

CB NO. CB PANEL

(A/C: 3001–3066) (A/C: 5001–5194) NAME ZONE

CBP-A 20 20 FLAP MOTOR 1 221 CBP-A 77 77 FLAP CONT 1 221 CBP-B 176 20 FLAP MOTOR 2 222 CBP-B 233 77 FLAP CONT 2 222 CBP-B 188 - BATT CHGR 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 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 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.MODEL CL-600-2A12 & CL-600-2B16

Basic Issue: Sep 26/2013 

# A601-0627 Page 7 of 18 Figure 2 (ii) If any of the forward fast eners heads are found missing as per Figure 2, proceed to PART B in Paragraph 2.C. (iii) If any of the forward fastener s 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 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 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 HingeMODEL CL-600-2A12 & CL-600-2B16

Basic Issue: Sep 26/2013 

# A601-0627 Page 8 of 18 (3) Obey all the fuel system safety pr ecautions. 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. (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 3MODEL CL-600-2A12 & CL-600-2B16

Basic Issue: Sep 26/2013 

# A601-0627 Page 9 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 601-2), 20-80-00 Safetying Devices. (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-600-2A12 & CL-600-2B16

Basic Issue: Sep 26/2013 

# A601-0627 Page 10 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 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), was hers (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-600-2A12 & CL-600-2B16

Basic Issue: Sep 26/2013 

# A601-0627 Page 11 of 18 (b) Carefully pull the flap hinge box (1 ) downward to allow access to the forward attachment fitting.

Figure 6MODEL CL-600-2A12 & CL-600-2B16

Basic Issue: Sep 26/2013 

# A601-0627 Page 12 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 fo rward 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-600-2A12 & CL-600-2B16

Basic Issue: Sep 26/2013 

# A601-0627 Page 13 of 18 (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 601-2), 20-20-00 Torquing. (h) Attach the control rod (2) and el ectrical 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 601- 2), 20-20-00 Torquing. (iv) Install the cotter pin (4). Refer to Maintenance Manual (PSP 601-2), 20-80-00 Safetying Devices. (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 601-2, C hapter 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 601-2, 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. (16) Remove the DO NOT CONNECT

− FUEL TANK MAINTENANCE placard from the ac and the dc ground power receptacles.MODEL CL-600-2A12 & CL-600-2B16

Basic Issue: Sep 26/2013 

# A601-0627 Page 14 of 18 (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 I nboard 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 Se rvice Bulletin and no further action is required, proceed to the Clo se-out in Paragraph 2.F. E. Testing (1) Remove the tags and close the circuit breakers that follow:

CB NO. CB PANEL

(A/C: 3001–3066) (A/C: 5001–5194) NAME ZONE

CBP-A 20 20 FLAP MOTOR 1 221 CBP-A 77 77 FLAP CONT 1 221 CBP-B 176 20 FLAP MOTOR 2 222 CBP-B 233 77 FLAP CONT 2 222 CBP-B 188 - BATT CHGR 222 (2) Connect the external ac power. Refer to Chapter 12-00-00, SERVICING. (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 NO. CB PANEL

(A/C: 3001–3066) (A/C: 5001–5194) NAME ZONE

CBP-A 20 20 FLAP MOTOR 1 221 CBP-A 77 77 FLAP CONT 1 221 CBP-B 176 20 FLAP MOTOR 2 222 CBP-B 233 77 FLAP CONT 2 222 CBP-B 188 - BATT CHGR 222MODEL CL-600-2A12 & CL-600-2B16

Basic Issue: Sep 26/2013 

# A601-0627 Page 15 of 18 (6) Install the forward and aft inboard flap hinge-fairings that follow. 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 (7) Install fillet seal around perimeterof forward and aft inboard flap hingefairings making contact with the wing surface and the inboard flap respectively. Refer to SRM, C hapter 51-57-00, SEALING – Description, Aerodynamic Sealing. (8) Remove the tags and close the circuit breakers that follow:

CB NO. CB PANEL

(A/C: 3001–3066) (A/C: 5001–5194) NAME ZONE

CBP-A 20 20 FLAP MOTOR 1 221 CBP-A 77 77 FLAP CONT 1 221 CBP-B 176 20 FLAP MOTOR 2 222 CBP-B 233 77 FLAP CONT 2 222 CBP-B 188 - BATT CHGR 222 (9) Connect the external ac power. Re fer to Chapter 12-00-00, SERVICING. (10) Carry out a flap operational test and check corresponding flap position indications in the flight compartmen t. 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 NO. CB PANEL

(A/C: 3001–3066) (A/C: 5001–5194) NAME ZONE

CBP-A 20 20 FLAP MOTOR 1 221 CBP-A 77 77 FLAP CONT 1 221 CBP-B 176 20 FLAP MOTOR 2 222 CBP-B 233 77 FLAP CONT 2 222 CBP-B 188 - BATT CHGR 222 (2) Remove all tools, equipment and unwanted materials from the aircraft.MODEL CL-600-2A12 & CL-600-2B16

Basic Issue: Sep 26/2013 

# A601-0627 Page 16 of 18 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 No tice 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


### 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, ar e 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: AMODEL CL-600-2A12 & CL-600-2B16

Basic Issue: Sep 26/2013 

# A601-0627 Page 17 of 18 DESCRIPTION PART No./NAME SPECIFICATION QUANTITY SUPPLIER (See Note) Durathane High

Gloss Enamel

CT: (12 hours) 7600 line BAMS 565-002 As Necessary Code: B

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

Conversion

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

Fuel Tank Coatings (Primer Yellow)

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

Anti-Seize Lubricant WD-40 - As Necessary Code: E

Brush, Natural or Synthetic Bristle - - As Necessary Code: E
Scraper, Non-Metallic - - As Necessary Code: E

Spatula - - 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-600-2A12 & CL-600-2B16

Basic Issue: Sep 26/2013 

# A601-0627 Page 18 of 18 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: A601-0627 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 – “A601-0627”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

A601-0627 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-- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- --



### 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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