SB 670BA−27−066

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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

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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.
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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.
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-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.
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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.
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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
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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.
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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
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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).
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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
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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.
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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).
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(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).
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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 the

applicable 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."
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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).
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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
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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.
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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).
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(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 the

applicable 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

B fully deployed.

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

7

ba7755a02.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 Bolt

The 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.

1 
THANK 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 EVALUATION 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