SB 670BA−27−066 Page 1 of 24 Jun 10/2013 

# SERVICE BULLETIN

Technical Publications

THIS SERVICE BULLETIN IS SENT TO EACH OPERATOR. IF THE OPERATOR HAS LEASED AIRCRAFT, TRANSFERRED SPARES IN THE LAST SIX MONTHS, SEND THIS SERVICE BULLETIN TO THE NEW OWNER, UNLESS CONFIRMATION WAS RECEIVED THAT BOMBARDIER COMMERCIAL AIRCRAFT HAS INCLUDED THE NEW OPERATOR ON THE DISTRIBUTION LIST. SEND THIS SERVICE BULLETIN TO THE LESSEE. IF THE OPERATOR HAS SOLD AIRCRAFT OR

ATA SYSTEM: 27-81 NUMBER: 670BA-27-066 SUBJECT: Flight Controls − Slat System − Replacement of The Locking Plates With Anti-Migration Assemblies at Tracks 3-1 and 3-3 of the Left and the Right No. 3 Slats

1. PLANNING INFORMATION A. Effectivity (1) Aircraft Affected:
AIRCRAFT MODEL SERVICE AIRCRAFT SERIAL NUMBERS PRODUCTION AIRCRAFT SERIAL NUMBERS CL-600-2C10 10002 thru 10335 10336 and subsequent serial numbers [1] CL-600-2D15 and CL-600-2D24 15001 thru 15293 15294 and subsequent serial numbers [1] CL-600-2E25 19002 thru 19036 19001, 19037 and subsequent serial numbers [1] [1] Aircraft will have this change incorporated before delivery. NOTE: The instructions in this service bulletin are only applicable to the systems and parts installed at the time of delivery of the aircraft or as changed by Bombardier Service Bulletins. Before you do this service bulletin, examine all Supplemental Type Certificates (STCs) and Supplemental Type Approvals (STAs) or equivalent action changes to make sure you can complete this service bulletin.

### SERVICE BULLETIN 670BA-27-066

SB 670BA−27−066 Page 2 of 24 Jun 10/2013 B. Reason (1) Condition It is possible for the eccentric pin of track 3-3 of the left and the right No. 3 slats to break and move out. This can cause the No. 3 slat panels to get disconnected from the wing. (2) Evidence As result of stress analysis done on CL-600-2E25, CL-600-2C10, CL-600-2D15 and CL-600-2D24 aircraft. (3) Objective/Benefit This service bulletin gives the procedure to replace the locking plate with an anti-migration assembly at the tracks 3-3 and 3-1 of the left and the right No. 3 slats. The installation of the new anti-migration assemblies will prevent the eccentric pin to move out, if it breaks. C. Description This service bulletin is divided into two parts: PART A and PART B. PART A - Replacement of Locking Plate P/N CC670-12076-1 With Anti-Migration Assembly P/N CC670-12370-1 on the Left No. 3 Slat The slats and the flaps are extended. Circuit breakers are opened. On Aircraft 10002 thru 10335 and 15001 thru 15293, the locking plates of tracks 3-1 and 3-3 on the left No. 3 slat are removed. The new anti-migration assemblies are installed. If the anti-migration assemblies cannot be installed with the slat in its current rigging position, the rigging of the slats is done. On Aircraft 19002 thru 19036, the locking plate of track 3-3 on the left No. 3 slat is removed. The new anti-migration assembly is installed. If the anti-migration assembly cannot be installed with the slat in its current rigging position, the rigging of the slats is done. The circuit breakers are closed. Electrical power is applied to the aircraft. The electrical retraction of the slats and flaps and the operational test of the flaps and the slats system are done. The electrical power is removed from the aircraft. The aircraft is returned to service.

### SERVICE BULLETIN 670BA-27-066

SB 670BA−27−066 Page 3 of 24 Jun 10/2013 PART B - Replacement of Locking Plate P/N CC670-12076-1 With Anti-Migration Assembly P/N CC670-12370-1 on the Right No. 3 Slat The slats and the flaps are extended. Circuit breakers are opened. On Aircraft 10002 thru 10335 and 15001 thru 15293, the locking plates of tracks 3-1 and 3-3 on the right No. 3 slat are removed. The new anti-migration assemblies are installed. If the anti-migration assemblies cannot be installed with the slat in its current rigging position, the rigging of the slats is done. On Aircraft 19002 thru 19036, the locking plate of track 3-3 on the right No. 3 slat is removed. The new anti-migration assembly is installed. If the anti-migration assembly cannot be installed with the slat in its current rigging position, the rigging of the slats is done. The circuit breakers are closed. Electrical power is applied to the aircraft. The electrical retraction of the slats and flaps and the operational test of the flaps and the slats system are done. The electrical power is removed from the aircraft. The aircraft is returned to service. D. Compliance Recommended Service Bulletin. Bombardier recommends that this service bulletin be done at no more than 6000 flight hours from the release date on this service bulletin or no later than 30 months from the release date on this service bulletin, whichever comes first, unless otherwise directed by the airworthiness authority of the operator. This service bulletin does not affect Airworthiness Limitations (AWLs) or Damage Tolerance Inspections (DTIs). E. Approval The technical content of this service bulletin has been approved under the authority of the TCCA Design Approval Organization No: DAO #93-Q-02. F. Manpower The man-hours given below are estimates for direct labor done by an experienced crew on an aircraft prepared for maintenance. These estimates do not include the time necessary for: -Administrative functions such as planning, liaising, familiarization, and report writing. -Non-productive elapsed time such as rest time, having meals, and crew shift changes. -Elapsed time such as for paint to dry, sealant to cure, and fuel tank venting. -Preparation for modification (unless specified in the Accomplishment Instructions) such as cleaning and getting parts, tools, consumables, and ground equipment.

### SERVICE BULLETIN 670BA-27-066

SB 670BA−27−066 Page 4 of 24 Jun 10/2013 -Quality assurance inspections, troubleshooting and/or correction of discrepancies found when a task is done. -All other activities that are not considered by Bombardier as directly related to the accomplishment of this procedure. NOTE: For on-site labor assistance, please speak with a Fleet Services representative for a quote. Contact the Fleet Services Team through the CRC at 514-855-8500 or email at thd.crj@aero.bombardier.com. For PART A For Aircraft 10002 thru 10335 and 15001 thru 15293 It will take an estimated 4.5 man-hours to complete PART A of this service bulletin. The man-hours are divided in the table that follows: TASK MAN-HOURS (1) Job Set-Up 0.5 (2) Procedure 3.0 (3) Test 0.5 (4) Job Close-Out 0.5

NOTE: The man-hours for the procedure do not include the hours to do the rigging of the slats. The rigging of the slats is only necessary if the anti-migration assemblies cannot be installed with the slat in its current rigging position.

### SERVICE BULLETIN 670BA-27-066

SB 670BA−27−066 Page 5 of 24 Jun 10/2013 For Aircraft 19002 thru 19036 It will take an estimated 3.0 man-hours to complete PART A of this service bulletin. The man-hours are divided in the table that follows:
TASK MAN-HOURS (1) Job Set-Up 0.5 (2) Procedure 1.5 (3) Test 0.5 (4) Job Close-Out 0.5

NOTE: The man-hours for the procedure do not include the hours to do the rigging of the slats. The rigging of the slats is only necessary if the anti-migration assemblies cannot be installed with the slat in its current rigging position. For PART B For Aircraft 10002 thru 10335 and 15001 thru 15293 It will take an estimated 4.5 man-hours to complete PART B of this service bulletin. The man-hours are divided in the table that follows:
TASK MAN-HOURS (1) Job Set-Up 0.5 (2) Procedure 3.0 (3) Test 0.5 (4) Job Close-Out 0.5

NOTE: The man-hours for the procedure do not include the hours to do the rigging of the slats. The rigging of the slats is only necessary if the anti-migration assemblies cannot be installed with the slat in its current rigging position.

### SERVICE BULLETIN 670BA-27-066

SB 670BA−27−066 Page 6 of 24 Jun 10/2013 For Aircraft 19002 thru 19036 It will take an estimated 3.0 man-hours to complete PART B of this service bulletin. The man-hours are divided in the table that follows: TASK MAN-HOURS (1) Job Set-Up 0.5 (2) Procedure 1.5 (3) Test 0.5 (4) Job Close-Out 0.5

NOTE: The man-hours for the procedure do not include the hours to do the rigging of the slats. The rigging of the slats is only necessary if the anti-migration assemblies cannot be installed with the slat in its current rigging position. G. Material - Price and Availability (1) The kits in the tables that follow are available from Bombardier Commercial Aircraft. NOTE: For a list of kit contents, refer to paragraph 3.A.

For Aircraft 10002 thru 10335 and 15001 thru 15293 A quantity of four kits 670BA27066K1 is necessary to do this service bulletin. Two kits for PART A and two kits for PART B.

KIT NUMBER NAME 670BA27066K1 Anti-migration assembly kit

### SERVICE BULLETIN 670BA-27-066

SB 670BA−27−066 Page 7 of 24 Jun 10/2013 For Aircraft 19002 thru 19036 A quantity of two kits 670BA27066K1 is necessary to do this service bulletin. One kit for PART A and one kit for PART B.

KIT NUMBER NAME 670BA27066K1 Anti-migration assembly kit

For all Aircraft A small quantity of kits 670BA27066K2 is available for each operator.
KIT NUMBER NAME 670BA27066K2 Anti-migration assemblies kit
NOTE: Kit 670BA27066K2 contains anti-migration assemblies that can be used to make the installation of the anti-migration assembly attachment bolts easier. (2) Please send a purchase order to the address below to schedule kit delivery: Bombardier Service Bulletin Kit Support Team 123 Garratt Blvd, N42-24 Toronto, Ontario Canada M3K 1Y5 Fax: 416-375-3060 Phone: 416-375-3920 Email: sbkits@aero.bombardier.com Please contact the Service Bulletin Kit Support Team at the address above for terms and conditions. (3) Refer to paragraph 3.B. for a list of consumables for this service bulletin. H. Tooling - Price and Availability There are no tool kits for this service bulletin. Refer to paragraph 3.C. for a list of special tools and equipment for this service bulletin. I. Weight and Balance Not changed.

### SERVICE BULLETIN 670BA-27-066

SB 670BA−27−066 Page 8 of 24 Jun 10/2013 J. Electrical Load Data Not changed. K. References Refer to the SB Introduction document for definition or explanation of service bulletin content. Restriction and/or Special Instruction (RSI) C-27-1549-00, Revision B Modification Summary 670T014094, Revision B3 Modification Summary 698T014094, Revision C1 Structural Repair Manual (SRM) Aircraft Maintenance Manual (AMM) For Bombardier reference only: PCA 75218 L. Other Publications Affected Aircraft Maintenance Manual (AMM) Aircraft Illustrated Parts Catalogue (AIPC) M. Relationship Chart

PRE-SB PART NUMBER NAME POST-SB PART NUMBER NAME

CC670-12076-1 Locking plate CC670-12370-1 Anti-migration assembly

### SERVICE BULLETIN 670BA-27-066

SB 670BA−27−066 Page 9 of 24 Jun 10/2013 2. ACCOMPLISHMENT INSTRUCTIONS PART A - Replacement of Locking Plate P/N CC670-12076-1 With Anti-Migration Assembly P/N CC670-12370-1 on the Left No. 3 Slat Reference Information
REFERENCE DESIGNATION AMM 12-00-00-867-801 Standard Aircraft Configuration for Maintenance AMM 20-21-00-910-801 Torquing of Threaded Fasteners AMM 20-51-00-000-801 Removal of Cotter Pins AMM 20-51-00-400-801 Installation of Cotter Pins AMM 24-00-00-861-801 Connect Electrical Power to the Aircraft AMM 24-00-00-861-802 Remove Electrical Power from the Aircraft AMM 24-00-00-910-801 Electrical/Electronic Safety Precautions AMM 27-00-00-910-802 Flight-Control Safety Precautions AMM 27-50-00-710-801 Operational Test of the Flaps and Slats System AMM 27-52-00-864-801 Electrical Extension of the Slats and Flaps AMM 27-52-00-864-802 Electrical Retraction of the Slats and Flaps AMM 27-81-25-820-801 Rigging of the No. 3 Slat Panels SRM 51-41-02-001-001 Bolts, Screws and Related Items A. Job Set-Up (1) Make sure that the aircraft is in standard configuration for maintenance (refer to AMM 12-00-00-867-801). (2) Obey all electrical/electronic safety precautions (refer to AMM 24-00-00-910-801). (3) Obey all flight control safety precautions (refer to AMM 27-00-00-910-802).

### SERVICE BULLETIN 670BA-27-066

SB 670BA−27−066 Page 10 of 24 Jun 10/2013 WARNING: PUT SAFETY DEVICES, WARNING SIGNS, AND PLACARDS IN POSITION BEFORE YOU START A PROCEDURE ON OR NEAR: -FLIGHT CONTROLS -FLIGHT CONTROL SURFACES -COMPONENTS THAT MOVE

MOVEMENT OF FLIGHT CONTROL COMPONENTS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT (4) Install the warning placards near the flaps and the slats to give a warning of control movement. (5) Connect the electrical power to the aircraft (refer to AMM 24-00-00-861-801). (6) Do the electrical extension of the slats and flaps (refer to AMM 27-52-00-864-801). (7) Remove the electrical power from the aircraft (refer to AMM 24-00-00-861-802). (8) Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME CBP-1 L5 FLAPS CONT CH 2 CBP-1 L6 SLATS CONT CH 2 CBP-2 LOWER R1 FLAPS CONT CH 1 CBP-2 LOWER R2 SLATS CONT CH 1

### SERVICE BULLETIN 670BA-27-066

SB 670BA−27−066 Page 11 of 24 Jun 10/2013 B. Procedure For Aircraft 10002 thru 10335 and 15001 thru 15293 Refer to Figure 1. (1) On the left side of the wing, at the No. 3 slat track 3-1, remove the locking plate (1) as follows: (a) Put an alignment mark on the head of the eccentric pin and on the slat track. NOTE: The alignment mark on the head of the eccentric pin must not be done across the head of the eccentric pin. (b) Remove and discard the cotter pin (7) (refer to AMM 20-51-00-000-801). (c) Remove and discard the nut (6). (d) Carefully remove and discard the bolt (3) and the washers (4). Make sure not to damage the seal. NOTE: 90-degree angle pliers can help the removal of the bolt (3). (e) Remove and discard the locking plate (1). (f) Make sure that the alignment marks on the eccentric pin and on the slat track align to their initial position. (g) If the alignment marks do not align, turn the eccentric pin to align the marks to their initial position. (h) Install the anti-migration assembly (2) and make sure that the hole for the bolt (3) in the anti-migration assembly (2) aligns with the hole of the slat track. Also, make sure that the alignment marks on the eccentric pin and the slat track align to their initial position. (i) If the holes do not align and the bolt (3) cannot be installed, do the steps that follow:
1 Remove the anti-migration assembly (2).
2 Try other anti-migration assemblies (2) until the hole for the bolt (3) aligns with the hole of the slat track and the bolt (3) can be installed. Also, make sure that the alignment marks on the eccentric pin and the slat track align to their initial position.

### SERVICE BULLETIN 670BA-27-066

SB 670BA−27−066 Page 12 of 24 Jun 10/2013 NOTE: Kit 670BA27066K2 contains anti-migration assemblies that can be used to make the installation of the bolts (3) easier. Or 3 If the holes do not align and the bolt (3) cannot be installed, do the rigging of the No. 3 slat panels (refer to AMM 27-81-25-820-801). (j) If the holes align and the alignment marks on the eccentric pin and the slat track align to their initial position, continue to the next step. (k) Carefully install the bolt (3) with the washer (5) and make sure not to damage the seal (refer to SRM 51-41-02-001-001). NOTE: 90-degree angle pliers can help the installation of the bolt (3). (l) Install the washer (4) and the nut (6) (refer to SRM 51-41-02-001-001). (m) Torque the nut (6) (refer to AMM 20-21-00-910-801). (n) Install the cotter pin (7) (refer to AMM 20-51-00-400-801). For all Aircraft (2) On the left side of the wing, at the No. 3 slat track 3-3, remove the locking plate (1) as follows: (a) Put an alignment mark on the head of the eccentric pin and on the slat track. NOTE: The alignment mark on the head of the eccentric pin must not be done across the head of the eccentric pin. (b) Remove and discard the cotter pin (7) (refer to AMM 20-51-00-000-801). (c) Remove and discard the nut (6). (d) Carefully remove and discard the bolt (3) and the washers (4). Make sure not to damage the seal. NOTE: 90-degree angle pliers can help the removal of the bolt (3). (e) Remove and discard the locking plate (1).

### SERVICE BULLETIN 670BA-27-066

SB 670BA−27−066 Page 13 of 24 Jun 10/2013 (f) Make sure that the alignment marks on the eccentric pin and on the slat track align to their initial position. (g) If the alignment marks do not align, turn the eccentric pin to align the marks to their initial position. (h) Install the anti-migration assembly (2) and make sure that the hole for the bolt (3) in the anti-migration assembly (2) aligns with the hole of the slat track. Also, make sure that the alignment marks on the eccentric pin and the slat track align to their initial position. (i) If the holes do not align and the bolt (3) cannot be installed do the steps that follow:
1 Remove the anti-migration assembly (2). 2 Try other anti-migration assemblies (2) until the hole for the bolt (3) aligns with the hole of the slat track and the bolt (3) can be installed. Also, make sure that the alignment marks on the eccentric pin and the slat track align to their initial position. NOTE: Kit 670BA27066K2 contains anti-migration assemblies that can be used to make the installation of the bolts (3) easier. Or 3 If the holes do not align and the bolt (3) cannot be installed, do the rigging of the slat (refer to AMM 27-81-25-820-801). (j) If the holes align and the alignment marks on the eccentric pin and the slat track align to their initial position, continue to the next step. (k) Carefully install the bolt (3) with the washer (5) and make sure not to damage the seal (refer to SRM 51-41-02-001-001). NOTE: 90-degree angle pliers can help the installation of the bolt (3). (l) Install the washer (4) and the nut (6) (refer to SRM 51-41-02-001-001). (m) Torque the nut (6) (refer to AMM 20-21-00-910-801). (n) Install the cotter pin (7) (refer to AMM 20-51-00-400-801).

### SERVICE BULLETIN 670BA-27-066

SB 670BA−27−066 Page 14 of 24 Jun 10/2013 C. Job Close-Out (1) Remove all tools, equipment, and unwanted materials from the work area. (2) Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME CBP-1 L5 FLAPS CONT CH 2 CBP-1 L6 SLATS CONT CH 2 CBP-2 LOWER R1 FLAPS CONT CH 1 CBP-2 LOWER R2 SLATS CONT CH 1
(3) Connect the electrical power to the aircraft (refer to AMM 24-00-00-861-801). (4) Do the electrical retraction of the slats and flaps (refer to AMM 27-52-00-864-802). (5) Do the operational test of the flaps and slats system (refer to AMM 27-50-00-710-801). (6) Remove the electrical power from the aircraft (refer to AMM 24-00-00-861-802). (7) Remove safety devices, warning signs and placards related to the slats and flaps. (8) When PART A of this service bulletin is completed, make this entry in theapplicable logbooks: Service Bulletin 670BA-27-066, Flight Controls − Slat System − Replacement of The Locking Plates With Anti-Migration Assemblies at Tracks 3-1 and 3-3 of the Left and the Right No. 3 Slats, PART A, incorporated."

### SERVICE BULLETIN 670BA-27-066

SB 670BA−27−066 Page 15 of 24 Jun 10/2013 PART B - Replacement of Locking Plate P/N CC670-12076-1 With Anti-Migration Assembly P/N CC670-12370-1 on the Right No. 3 Slat Reference Information
REFERENCE DESIGNATION AMM 12-00-00-867-801 Standard Aircraft Configuration for Maintenance AMM 20-21-00-910-801 Torquing of Threaded Fasteners AMM 20-51-00-000-801 Removal of Cotter Pins AMM 20-51-00-400-801 Installation of Cotter Pins AMM 24-00-00-861-801 Connect Electrical Power to the Aircraft AMM 24-00-00-861-802 Remove Electrical Power from the Aircraft AMM 24-00-00-910-801 Electrical/Electronic Safety Precautions AMM 27-00-00-910-802 Flight-Control Safety Precautions AMM 27-50-00-710-801 Operational Test of the Flaps and Slats System AMM 27-52-00-864-801 Electrical Extension of the Slats and Flaps AMM 27-52-00-864-802 Electrical Retraction of the Slats and Flaps AMM 27-81-25-820-801 Rigging of the No. 3 Slat Panels SRM 51-41-02-001-001 Bolts, Screws and Related Items D. Job Set-Up (1) Make sure that the aircraft is in standard configuration for maintenance (refer to AMM 12-00-00-867-801). (2) Obey all electrical/electronic safety precautions (refer to AMM 24-00-00-910-801). (3) Obey all flight control safety precautions (refer to AMM 27-00-00-910-802).

### SERVICE BULLETIN 670BA-27-066

SB 670BA−27−066 Page 16 of 24 Jun 10/2013 WARNING: PUT SAFETY DEVICES, WARNING SIGNS, AND PLACARDS IN POSITION BEFORE YOU START A PROCEDURE ON OR NEAR: -FLIGHT CONTROLS -FLIGHT CONTROL SURFACES -COMPONENTS THAT MOVE MOVEMENT OF FLIGHT CONTROL COMPONENTS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT (4) Install the warning placards near the flaps and the slats to give a warning of control movement. (5) Connect the electrical power to the aircraft (refer to AMM 24-00-00-861-801). (6) Do the electrical extension of the slats and flaps (refer to AMM 27-52-00-864-801). (7) Remove the electrical power from the aircraft (refer to AMM 24-00-00-861-802). (8) Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME CBP-1 L5 FLAPS CONT CH 2 CBP-1 L6 SLATS CONT CH 2 CBP-2 LOWER R1 FLAPS CONT CH 1 CBP-2 LOWER R2 SLATS CONT CH 1

### SERVICE BULLETIN 670BA-27-066

SB 670BA−27−066 Page 17 of 24 Jun 10/2013 E. Procedure For Aircraft 10002 thru 10335 and 15001 thru 15293 Refer to Figure 1. (1) On the right side of the wing, at the No. 3 slat, track 3-1, remove the locking plate (1) as follows: (a) Put an alignment mark on the head of the eccentric pin and on the slat track. NOTE: The alignment mark on the head of the eccentric pin must not be done across the head of the eccentric pin. (b) Remove and discard the cotter pin (7) (refer to AMM 20-51-00-000-801). (c) Remove and discard the nut (6). (d) Carefully remove and discard the bolt (3) and the washers (4). Make sure not to damage the seal. NOTE: 90-degree angle pliers can help the removal of the bolt (3). (e) Remove and discard the locking plate (1). (f) Make sure that the alignment marks on the eccentric pin and on the slat track align to their initial position. (g) If the alignment marks do not align, turn the eccentric pin to align the marks to their initial position. (h) Install the anti-migration assembly (2) and make sure that the hole for the bolt (3) in the anti-migration assembly (2) aligns with the hole of the slat track. Also, make sure that the alignment marks on the eccentric pin and the slat track align to their initial position. (i) If the holes do not align and the bolt (3) cannot be installed, do the steps that follow:
1 Remove the anti-migration assembly (2).
2 Try other anti-migration assemblies (2) until the hole for the bolt (3) aligns with the hole of the slat track and the bolt (3) can be installed. Also, make sure that the alignment marks on the eccentric pin and the slat track align to their initial position.

### SERVICE BULLETIN 670BA-27-066

SB 670BA−27−066 Page 18 of 24 Jun 10/2013 NOTE: Kit 670BA27066K2 contains anti-migration assemblies that can be used to make the installation of the bolts (3) easier. Or 3 If the holes do not align and the bolt (3) cannot be installed, do the rigging of the No. 3 slat panels (refer to AMM 27-81-25-820-801). (j) If the holes align and the alignment marks on the eccentric pin and the slat track align to their initial position, continue to the next step. (k) Carefully install the bolt (3) with the washer (5) and make sure not to damage the seal (refer to SRM 51-41-02-001-001). NOTE: 90-degree angle pliers can help the installation of the bolt (3). (l) Install the washer (4) and the nut (6) (refer to SRM 51-41-02-001-001). (m) Torque the nut (6) (refer to AMM 20-21-00-910-801). (n) Install the cotter pin (7) (refer to AMM 20-51-00-400-801). For all Aircraft (2) On the right side of the wing, at the No. 3 slat track 3-3, remove the locking plate (1) as follows: (a) Put an alignment mark on the head of the eccentric pin and on the slat track. NOTE: The alignment mark on the head of the eccentric pin must not be done across the head of the eccentric pin. (b) Remove and discard the cotter pin (7) (refer to AMM 20-51-00-000-801). (c) Remove and discard the nut (6). (d) Carefully remove and discard the bolt (3) and the washers (4). Make sure not to damage the seal. NOTE: 90-degree angle pliers can help the removal of the bolt (3). (e) Remove and discard the locking plate (1).

### SERVICE BULLETIN 670BA-27-066

SB 670BA−27−066 Page 19 of 24 Jun 10/2013 (f) Make sure that the alignment marks on the eccentric pin and on the slat track align to their initial position. (g) If the alignment marks do not align, turn the eccentric pin to align the marks to their initial position. (h) Install the anti-migration assembly (2) and make sure that the hole for the bolt (3) in the anti-migration assembly (2) aligns with the hole of the slat track. Also, make sure that the alignment marks on the eccentric pin and the slat track align to their initial position. (i) If the holes do not align and the bolt (3) cannot be installed do the steps that follow:
1 Remove the anti-migration assembly (2). 2 Try other anti-migration assemblies (2) until the hole for the bolt (3) aligns with the hole of the slat track and the bolt (3) can be installed. Also, make sure that the alignment marks on the eccentric pin and the slat track align to their initial position. NOTE: Kit 670BA27066K2 contains anti-migration assemblies that can be used to make the installation of the bolts (3) easier. Or 3 If the holes do not align and the bolt (3) cannot be installed, do the rigging of the No. 3 slat panels (refer to AMM 27-81-25-820-801). (j) If the holes align and the alignment marks on the eccentric pin and the slat track align to their initial position, continue to the next step. (k) Carefully install the bolt (3) with the washer (5) and make sure not to damage the seal (refer to SRM 51-41-02-001-001). NOTE: 90-degree angle pliers can help the installation of the bolt (3). (l) Install the washer (4) and the nut (6) (refer to SRM 51-41-02-001-001). (m) Torque the nut (6) (refer to AMM 20-21-00-910-801). (n) Install the cotter pin (7) (refer to AMM 20-51-00-400-801).

### SERVICE BULLETIN 670BA-27-066

SB 670BA−27−066 Page 20 of 24 Jun 10/2013 F. Job Close-Out (1) Remove all tools, equipment, and unwanted materials from the work area. (2) Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME CBP-1 L5 FLAPS CONT CH 2 CBP-1 L6 SLATS CONT CH 2 CBP-2 LOWER R1 FLAPS CONT CH 1 CBP-2 LOWER R2 SLATS CONT CH 1
(3) Connect the electrical power to the aircraft (refer to AMM 24-00-00-861-801). (4) Do the electrical retraction of the slats and flaps (refer to AMM 27-52-00-864-802). (5) Do the operational test of the flaps and slats system (refer to AMM 27-50-00-710-801). (6) Remove the electrical power from the aircraft (refer to AMM 24-00-00-861-802). (7) Remove safety devices, warning signs and placards related to the slats and flaps. (8) When PART B of this service bulletin is completed, make this entry in theapplicable logbooks: Service Bulletin 670BA-27-066, Flight Controls − Slat System − Replacement of The Locking Plates With Anti-Migration Assemblies at Tracks 3-1 and 3-3 of the Left and the Right No. 3 Slats, PART B, incorporated."

### SERVICE BULLETIN 670BA-27-066

SB 670BA−27−066 Page 21 of 24 Jun 10/2013 Anti-Migration Assemblies of Tracks 3-1 and 3-3 on the Left and the Right No. 3 Slats - Removal/Installation Figure 1 (Sheet 1 of 2)ba7755a01.cgm, sd,27−mai−2013 A SLAT TRACK 3

− 1 (REF)

SLAT No.3 (REF) SEAL(REF) B
1

Applicable to Aircraft 10002

− 10335 and 15001

− 15293 only. NOTES 1

2. Left side shown, right side opposite. 3. The slats are fully deployed. B POST

− MOD PRE
− MOD 5 ECCENTRIC PIN (REF)

1 2

7 4 6 SLAT TRACK 3

− 1 (REF) B TYPICAL SEAL (REF)

4 3 LEGEND 1. Locking plate CC670

− 12076

− 1 (Pre

− Mod) 2. Anti

− migration assembly CC670

− 12370

− 1 (Post

− Mod). 3. Bolt NAS6303U3D. 4. Washer NAS1149C0316R. 5. Washer B0202013C1312

− 16. 6. Nut B0203011L3. 7. Cotter pin MS24665

− 86.

### SERVICE BULLETIN 670BA-27-066

SB 670BA−27−066 Page 22 of 24 Jun 10/2013 Anti-Migration Assemblies of Tracks 3-1 and 3-3 on the Left and the Right No. 3 Slats - Removal/Installation Figure 1 (Sheet 2 of 2) SEAL(REF)

SLAT No.3 (REF) SLAT TRACK 3

− 3 (REF)

PRE
− MOD POST

− MOD

1 2 ECCENTRIC PIN (REF) 5 3

4
6

7ba7755a02.cgm, sd, 27−mai−2013 NOTE 2. Left side shown, right side opposite. D

C E

E SLAT TRACK 3

− 3 (REF)

2. The slats are fully deployed. 4 LEGEND 1. Locking plate CC670

− 12076

− 1 (Pre

− Mod) 2. Anti

− migration plate CC670

− 12370

− 1 (Post

− Mod). 3. Bolt NAS6303U3D. 4. Washer NAS1149C0316R. 5. Washer B0202013C1312

− 16. 6. Nut B0203011L3. 7. Cotter pin MS24665

− 86.

### SERVICE BULLETIN 670BA-27-066

SB 670BA−27−066 Page 23 of 24 Jun 10/2013 3. MATERIAL INFORMATION A. Kit Information Kit Contents: KIT 670BA27066K1 PART NUMBER QTY NAME ALTERNATE PARTS NOTES
B0202013C1312-16 2 Washer B0203011L3 2 Nut CC670-12370-1 1 Anti-migration assembly MS24665-86 2 Cotter pin NAS1149C0316R 2 Washer NAS6303U3D 1 BoltThe kit contains more hardware than necessary.

KIT 670BA27066K2
PART NUMBER QTY NAME ALTERNATE PARTS NOTES
CC670-12370-1 4 Anti-migration assembly NOTE: Refer to paragraph 1.G. for special terms and conditions. NOTE: For allowable superseded parts, refer to the Parts Supersession Cross References Lists at www.iflybombardier.com under Resources − Engineering Documents. B. Consumable Information For a list of consumables, refer to the different tasks that are given as references in this service bulletin. C. Special Tools and Equipment For a list of special tools and equipment, refer to the different tasks that are given as references in this service bulletin.

### SERVICE BULLETIN 670BA-27-066

SB 670BA−27−066 Page 24 of 24 Jun 10/2013 D. Disposition of Parts The table that follows shows the disposition of parts on the aircraft (or spares), and the relationship between these parts to the new parts to be installed through the incorporation of this service bulletin. For Aircraft 10002 thru 10335 and 15001 thru 15293 PRE-SB

PART NUMBER NAME QTY DC POST-SB PART NUMBER NAME

CC670-12076-1 Locking plate 4 DIS CC670-12370-1 Anti-migration assembly
For Aircraft 19002 thru 19036 PRE-SB

PART NUMBER NAME QTY DC POST-SB PART NUMBER NAME

CC670-12076-1 Locking plate 2 DIS CC670-12370-1 Anti-migration assembly Disposition code (DC): DIS: Discard Part. 1THANK YOU FOR ANSWERING THIS EVALUATION FORM UPON COMPLETION OF THIS EVALUATION FORM/COMPLIANCE SHEET, FAX TO 450-476-7300 or email to CRJ_SB_Evaluation_Form@aero.bombardier.com 

### SERVICE BULLETIN EVALUATI ON FORM/COMPLIANCE SHEET (YOUR IDEAS WILL HELP US PROVIDE BETTER BULLETINS)
SERVICE BULLETIN : 670BA-27-066 ISSUE: -

STRONGLY DISAGREE NEUTRAL AGREE STRONGLY DISAGREE AGREE
 Instructions to do the Service Bulletin were accurate. Comments: 

##     

 Illustration(s), figure(s), picture(s) and/or kit drawing(s) were helpful to carry out instructions. Comments: 

##     

 If a parts kit was required, did the kit contents received agree with the contents listed in the bulletin? Comments: 

##     

 Aircraft hands-on work was accomplished in estimated time. Comments: 

##     

 Overall, I was satisfied with this Service Bulletin. Comments: 

##     

PLEASE SUPPLY US WITH THE FOLLOWING DATA AND FAX TO (450) 476-7300: OPERATOR: NAME (Please print) SERVICE CENTER: TELEPHONE: AIRCRAFT SERIAL NO.: FACSIMILE: DATE OF SB INCORPOARTION