SB 670BA−27−064 Page 1 of 25 Dec 11/2012 

# 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: 27−31 NUMBER: 670BA−27−064 SUBJECT: Flight Controls − Elevator Control System − Replacement of the Bellcrank Supports on the Inner Rear Spar of the Horizontal Stabilizer

1. PLANNING INFORMATION A. Effectivity (1) Aircraft Affected:
AIRCRAFT MODEL SERVICE AIRCRAFT SERIAL NUMBERS PRODUCTION AIRCRAFT SERIAL NUMBERS CL−600−2C10 10002 thru 10999 none [1] CL−600−2D15 and CL−600−2D24 15001 thru 15990 none [1]
CL−600−2E25 19001 thru 19990 none [1] [1] There is no production effectivity. 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 STC, STA or equivalent action changes to make sure you can complete this service bulletin.

### SERVICE BULLETIN 670BA−27−064

SB 670BA−27−064 Page 2 of 25 Dec 11/2012 B. Reason (1) Condition The elevator centering mechanism and the friction in the bearing of the bellcrank support together, can cause an increase of the elevator breakout force. This can also cause irregular pitch movements and constant pitch correction from the autopilot. (2) Evidence Irregular pitch movements were reported on aircraft in service. (3) Objective/Benefit This service bulletin gives the procedure to replace the bellcrank supports, that possibly have bearings with increased wear, with bellcrank supports that include a new bearing. This replacement will prevent the irregular pitch movements. C. Description NOTE: This description is applicable to the left and the right bellcrank supports. The description that follows is written for the left bellcrank support. The differences are given. The horizontal stabilizer is put in a neutral position and warning placards are installed. Circuit breakers are opened. The electrical power is removed from the aircraft. The access panels for the upper fairing assembly, the lower visor fairing and the elevator power control units doors are removed. The aft side of the horizontal stabilizer control-rod, installed between FS1317.47 and FS1330.42, is disconnected from the lower elevator lever. The inboard side of the horizontal stabilizer control-rod, installed between Rib No.1 and Rib No.2, is disconnected from the upper elevator lever. On the left side of the rear spar, a fairlead block is removed from the hydraulic tubes and the bracket assembly. The upper and the lower elevator levers are removed from the bellcrank support. The bellcrank support is removed. A bracket assembly is removed from the left bellcrank support. The bracket assembly is installed on the new left bellcrank support. The bellcrank support is installed The lower and the upper elevator levers are installed on the bellcrank support. On the left side of the rear spar, the fairlead block is installed on the hydraulic tubes and the bracket assembly. The control rods are connected to the lower and the upper elevator levers. The rigging of the control rods is done. The circuit breakers are closed and the electrical power is applied. The operational test of the elevator control system is done. The access panels for the upper fairing assembly, the lower visor fairing and the elevator power control units doors are closed. The warning placards are removed.

### SERVICE BULLETIN 670BA−27−064

SB 670BA−27−064 Page 3 of 25 Dec 11/2012 D. Compliance
Recommended Service Bulletin. Bombardier recommends that this service bulletin be done as shown in the table below, unless otherwise directed by the airworthiness authority of the operator: AIRCRAFT FLIGHT HOURS TIME LIMITATION Aircraft flight hours 18,000 Before the aircraft has 24,600 flight hours. 18,000 < Aircraft flight hours 23,400 Within 6,600 flight hours from the released date of this service bulletin. 23,400 < Aircraft flight hours 28,500 Before the aircraft has 30,000 flight hours. 28,500 < Aircraft flight hours Within 1,500 flight hours from the released date of this service bulletin. 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. −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.

### SERVICE BULLETIN 670BA−27−064

SB 670BA−27−064 Page 4 of 25 Dec 11/2012 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. It will take an estimated 7.0 man-hours to complete this service bulletin. The man-hours are divided in the table that follows (elapsed cure time is not included in the man-hour summary given above): TASK MAN-HOURS (1) Job Set-Up 1.0 (2) Procedure 4.0 (3) Test 0.5 (4) Job Close-Out 1.5
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.

KIT NUMBER NAME 670BA27064K1 Bellcrank bracket installation (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

### SERVICE BULLETIN 670BA−27−064

SB 670BA−27−064 Page 5 of 25 Dec 11/2012 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. J. Electrical Load Data Not changed. K. References Restriction and/or Special Instruction (RSI) C−27−1540−00, Revision A Aircraft Maintenance Manual (AMM) Structural Repair Manual (SRM) Refer to the SB Introduction document for definition or explanation of Service Bulletin content. For Bombardier reference only: PCA 75129 L. Other Publications Affected None M. Relationship Chart Not applicable.

### SERVICE BULLETIN 670BA−27−064

SB 670BA−27−064 Page 6 of 25 Dec 11/2012 2. ACCOMPLISHMENT INSTRUCTIONS

Reference Information

REFERENCE DESIGNATION AMM 12−00−00−867−801 Standard Aircraft Configuration for Maintenance AMM 12−00−06−862−801 Pressurize Hydraulic System No. 1 and No. 2 AMM 12−00−06−862−802 Release Hydraulic Pressure of System No. 1 and No. 2 AMM 12−00−06−862−803 Pressurize Hydraulic System No. 3 AMM 12−00−06−862−804 Release Hydraulic Pressure of System No. 3 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 20−51−00−000−802 Removal of Lockwire AMM 20−51−00−400−802 Installation of Lockwire AMM 24−00−00−910−801 Electrical/Electronic Safety Precautions 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 27−00−00−910−802 Flight-Control Safety Precautions AMM 27−31−00−710−801 Operational Test of the Elevator Control System AMM 51−80−00−760−801 Electrical Bonding Test AMM 55−12−32−000−801 Removal of the Elevator Power Control Unit (PCU) Door (332AB/342AB) AMM 55−12−32−400−801 Installation of the Elevator Power Control Unit (PCU) Door (332AB/342AB) AMM 55−32−86−000−803 Removal of the Upper Fairing Assembly (326BT) AMM 55−32−86−000−804 Removal of the Aft Fairing (326CT)

### SERVICE BULLETIN 670BA−27−064

SB 670BA−27−064 Page 7 of 25 Dec 11/2012 REFERENCE DESIGNATION AMM 55−32−86−000−805 Removal of the Lower Fairing Panel (326BL/326BR) AMM 55−32−86−000−806 Removal of the Upper Visor Fairing (326DL/326DR) AMM 55−32−86−000−807 Removal of the Lower Visor Fairing (326CL/326CR) AMM 55−32−86−400−803 Installation of the Upper Fairing Assembly (326BT) AMM 55−32−86−400−804 Installation of the Aft Fairing (326CT) AMM 55−32−86−400−805 Installation of the Lower Fairing Panel (326BL/326BR) AMM 55−32−86−400−806 Installation of the Upper Visor Fairing (326DL/326DR) AMM 55−32−86−400−807 Installation of the Lower Visor Fairing (326CL/326CR) SRM 51−21−11−001−001 Corrosion Prevention Procedures SRM 51−23−00−001−001 Pressure, Environmental, Fuel Tank and Firewall Sealing SRM 51−25−06−001−001 Fluid-Resistant (FR) Epoxy Primer SRM 51−25−16−001−001 Fluid-Resistant (FR) Polyurethane Topcoat SRM 51−26−00−001−001 Cleaning SRM 51−42−06−001−001 Solid Rivets Tolerance Information Linear Tolerances Angular Tolerance X.XX in. (X.X mm) X.X in. (X mm) +/−0° 30" +/− 0.03 in. +/− 0.1 in. +/− 0.8 mm +/− 3 mm NOTE: The tolerances above apply to the dimensions given in this service bulletin, except when specified differently.

### SERVICE BULLETIN 670BA−27−064

SB 670BA−27−064 Page 8 of 25 Dec 11/2012 A. Job Set-Up (1) Make sure that the aircraft is in standard configuration for maintenance (Refer to AMM 12−00−00−867−801). WARNING: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU DO MAINTENANCE ON OR NEAR ELECTRICAL/ELECTRONIC EQUIPMENT. IF YOU DO NOT OBEY THE SAFETY PRECAUTIONS, INJURIES TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT CAN OCCUR. (2) Obey all the electrical/electronic safety precautions (Refer to AMM 24−00−00−910−801). (3) Obey all the flight-control safety precautions (Refer to AMM 27−00−00−910−802). (4) Apply electrical power to the aircraft (Refer to AMM 24−00−00−861−801). (5) Pressurize hydraulic system No.3 (Refer to AMM 12−00−06−862−803). (6) Operate the elevator control surfaces fully up and fully down, 5 times. (7) Put the horizontal stabilizer in the neutral position as follows: (a) On the STAB TRIM/MACH TRIM control panel, push the CH 1 pushbutton. (b) On the pilot control wheel, use the pitch trim switch to put the stabilizer trim indicator at 2.0. (8) Make sure the elevator control surfaces are in the neutral position as follows: (a) On the EICAS FLIGHT CONTROLS synoptic page, the elevator position pointers are in the neutral position. (b) If necessary, move the control columns to put the elevator control surfaces in the neutral position. (9) Release the pressure of the hydraulic system No.3 (Refer to AMM 12−00−06−862−804). (10) Remove the electrical power from the aircraft (Refer to AMM 24−00−00−861−802).

### SERVICE BULLETIN 670BA−27−064

SB 670BA−27−064 Page 9 of 25 Dec 11/2012 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. (11) Install warning placards on the control columns to give warnings not to move the elevators. (12) Install the warning placards on the control wheels to give warnings not to operate the pitch trim switches. (13) Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME

CBP−1 F1 SSCU 1 CH A CBP−1 F11 HYD SYST AC PUMP CONT 3B CBP−1 F14 HYD SYST AC PUMP CONT 2 CBP−2 F1 SSCU 1 CH B CBP−2 F2 RUDDER TRIM CBP−2 F13 HYD SYST AC PUMP CONT 1 CBP−2 F14 HYD SYST AC PUMP CONT 3A CBP−2 LOWER R3 SSCU 2 CH A CBP−2 LOWER R4 SSCU 2 CH B
(14) Remove the access panels that follow:

PANEL NAME REFERENCE 326BL Lower Fairing Panel AMM 55−32−86−000−805 326BR Lower Fairing Panel AMM 55−32−86−000−805 326BT Upper Fairing Assembly AMM 55−32−86−000−803

### SERVICE BULLETIN 670BA−27−064

SB 670BA−27−064 Page 10 of 25 Dec 11/2012 PANEL REFERENCE NAME 326CL Lower Visor Fairing AMM 55−32−86−000−807 326CR Lower Visor Fairing AMM 55−32−86−000−807 326CT Aft Fairing AMM 55−32−86−000−804 326DL Upper Visor Fairing AMM 55−32−86−000−806 326DR Upper Visor Fairing AMM 55−32−86−000−806 332AB Elevator Power Control Unit (PCU) Door AMM 55−12−32−000−801
342AB Elevator Power Control Unit (PCU) Door AMM 55−12−32−000−801
Refer to Figure 1 . (15) Install the rigging pins P5, and P7.

### SERVICE BULLETIN 670BA−27−064

SB 670BA−27−064 Page 11 of 25 Dec 11/2012 B. Procedure NOTE: This procedure is applicable to the left and the right sides. The procedure that follows is written for the left side. The differences are given. Refer to Figure 2 . (1) Disconnect the control rod (1) from the lower elevator lever (9) of the elevator as follows: (a) Remove and discard the cotter pin (2) and the self locking nut (3). (b) Remove the washers (4) and (5), and the bolt (6). (c) Disconnect the control rod (1) from the lower elevator lever (9). (2) Disconnect the control rod (10) from the upper elevator lever (14) of the elevator as follows: (a) Remove and discard the cotter pin (2) and the self locking nut (3). (b) Remove the washers (4) and (5), and the bolt (11). (c) Disconnect the control rod (10) from the upper elevator lever (14). Refer to Figure 3 . (3) Near the bellcrank support (5) installed on the left side, remove the fairlead block (1) as follows: (a) Remove the screws (2) and the washers (3) from the fairlead block (1). (b) Remove the fairlead block (1) from the hydraulic tubes and the bracket assembly (4). Refer to Figure 4 . (4) Remove the bellcrank support (5) from the structure as follows: (a) Remove and discard the cotter pin (6) and the self locking nut (7). (b) Remove the washer (8) and the bolt (9) from the lower elevator lever (10). (c) Remove the lower elevator lever (10) from the bellcrank support (5).

### SERVICE BULLETIN 670BA−27−064

SB 670BA−27−064 Page 12 of 25 Dec 11/2012 (d) Remove and discard the self locking nuts (11) from the four Hi-Lite pins. Make sure that the Hi-Lite pins do not turn in the rear spar structure. NOTE: The four Hi-Lite pins are not removed. (e) Remove the bellcrank support (5) from the structure. (f) Remove the upper elevator lever (12) from the bellcrank support (5). (g) Discard the bellcrank support (5) that was installed on the right side. Refer to Figure 5 . (5) Remove the rivets (13) and the bracket assembly (4) from the bellcrank support (5) that was installed on the left side. (6) Discard the left bellcrank support (5). Refer to Figure 3 and Figure 5 . (7) On the left side of the rear spar, install the bracket assembly (4) on the new bellcrank support (5) as follows: (a) Make sure that the two pilot holes in the bellcrank support (5) are aligned with the two holes in the bracket assembly (4). (b) Temporarily install the bellcrank support (5) on the rear spar. (c) Temporarily install the bracket assembly (4), the fairlead block (1), the washers (3) and the screws (2) on the hydraulic tubes. (d) Put the bracket assembly (4) in position below the flange of the bellcrank support (5). (e) Make sure that the pitch distance of the holes in the bellcrank support (5) align the pitch distance of the hole in the bracket assembly (4). (f) Make sure there is no tension on the hydraulic tubes. (g) Temporarily attach the bellcrank support (5) and the bracket assembly (4). (h) Put ink marks on the bellcrank support (5) to show the location of the diameter of the holes and the pitch distance.

### SERVICE BULLETIN 670BA−27−064

SB 670BA−27−064 Page 13 of 25 Dec 11/2012 (i) Remove the screws (2), the washers (3) and the fairlead block (1) from the bracket assembly (4). (j) Remove the bellcrank support (5) from the rear spar. (k) Backdrill two holes to a diameter of 0.160 to 0.164 in. (4.064 to 4.166 mm) from the bracket assembly (4) to the new bellcrank support (5). (l) Remove the burrs and sharp edges from the new bellcrank support (5). (m) Apply chemical conversion coating in the bare metal areas of the new bellcrank support (5) and the bracket assembly (4). (n) Apply a layer of of fluid-resistant primer in the bare metal areas of the new bellcrank support (5) and the bracket assembly (4). (o) Wet-install the rivets (13) in the bellcrank support (5) and the bracket assembly (4). (p) Apply a layer of fluid-resistant primer on the rivets (13). (q) Apply a layer of grey polyurethane topcoat on the rivets (13). Refer to Figure 4 . (8) Install the new bellcrank support (5) on the structure as follows: (a) Install the lower elevator lever (10) and the upper elevator lever (12) in the bellcrank support (5). Make sure that the master splines in the lower lever (10) and the upper lever (12) are aligned. Refer to Figure 1 . (b) Install rigging pin P6 through the bellcrank support and the lower elevator lever. Refer to Figure 4 . (c) Install the bolt (9) in the lower elevator lever (10) and in the groove of the upper elevator lever (12). (d) Install the washer (8) and the self locking nut (7) on the bolt (9). (e) Install the bellcrank support (5) with the self locking nuts (11) on the structure.

### SERVICE BULLETIN 670BA−27−064

SB 670BA−27−064 Page 14 of 25 Dec 11/2012 (f) Torque the self locking nuts (11) to 80−85 lbf·in (9.04−9.60 N·m). Make sure the Hi-Lite pins do not turn in the rear structure. (g) Install the cotter pin (6) in the self locking nut (7). Refer to Figure 3 . (9) On the left side of the rear spar, install the fairlead block (1) on the hydraulic tubes and on the bracket assembly (4) with the screws (2) and the washers (3). Refer to Figure 2 . (10) Install the control rod (1) on the lower elevator lever (9) as follows: (a) Align the control rod (1) with the lower elevator lever (9). (b) Put the bolt (6) in the lower elevator lever (9) and the control rod (1). (c) Make sure that the bolt (6) moves freely in the hole of the lower elevator lever (9) and the control rod (1). (d) If the bolt (6) does not move freely, adjust the length of the control rod (1) as follows: 1 Remove and discard the lockwire from the jam nut (7) and the locking device (8). 2 Loosen the jam nut (7) sufficiently to disengage the locking device (8). 3 Adjust the length of the control rod (1) until you can connect the rod end.
4 Tighten the jam nut (7) sufficiently to engage the locking device (8). 5 Safety the jam nut (7) with the lockwire. (e) Install the control rod (1) on the lower elevator lever (9) with the bolt (6), the washers (4) and (5), the self locking nut (3) and the cotter pin (2).

### SERVICE BULLETIN 670BA−27−064

SB 670BA−27−064 Page 15 of 25 Dec 11/2012 (11) Install the control rod (10) on the upper elevator lever (14) of the elevator as follows: (a) Put the control rod (10) in position on the upper elevator lever (14). (b) Put the bolt (11) in the upper elevator lever (14) and the control rod (10). (c) Make sure that the bolt (11) moves freely in the hole. (d) If the bolt (11) does not move freely, adjust the length of the control rod (10) as follows: 1 Remove and discard the lockwire from the jam nut (12) and the locking device (13). 2 Loosen the jam nut (12) sufficiently to disengage the locking device (13). 3 Adjust the length of the control rod (10) until you can connect the end of the control rod (10).
4 Tighten the jam nut (12) sufficiently to engage the locking device (13). (e) Safety the jam nut (12) with lockwire. (f) Install the control rod (10) on the upper elevator lever (14) with the bolt (11), the washers (4) and (5), the self locking nut (3), and the cotter pin (2). Refer to Figure 1 . (g) Make sure that rigging pins P5, P6, and P7 move freely. (12) Remove rigging pins P5, P6, and P7.

### SERVICE BULLETIN 670BA−27−064

SB 670BA−27−064 Page 16 of 25 Dec 11/2012 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 F1 SSCU 1 CH A CBP−1 F11 HYD SYST AC PUMP CONT 3B CBP−1 F14 HYD SYST AC PUMP CONT 2 CBP−2 F1 SSCU 1 CH B CBP−2 F2 RUDDER TRIM CBP−2 F13 HYD SYST AC PUMP CONT 1 CBP−2 F14 HYD SYST AC PUMP CONT 3A CBP−2 LOWER R3 SSCU 2 CH A CBP−2 LOWER R4 SSCU 2 CH B
(3) Apply electrical power to the aircraft (Refer to AMM 24−00−00−861−801). (4) Do the operational test of the elevator control system (Refer to AMM 27−31−00−710−801). (5) Install the access panels that follow:

PANEL NAME REFERENCE 326BL Lower Fairing Panel AMM 55−32−86−400−805 326BR Lower Fairing Panel AMM 55−32−86−400−805 326BT Upper Fairing Assembly AMM 55−32−86−400−803 326CL Lower Visor Fairing AMM 55−32−86−400−807

### SERVICE BULLETIN 670BA−27−064

SB 670BA−27−064 Page 17 of 25 Dec 11/2012 PANEL REFERENCE NAME 326CR Lower Visor Fairing AMM 55−32−86−400−807 326CT Aft Fairing AMM 55−32−86−400−804 326DL Upper Visor Fairing AMM 55−32−86−400−806 326DR Upper Visor Fairing AMM 55−32−86−400−806 332AB Elevator Power Control Unit (PCU) Door AMM 55−12−32−400−801
342AB Elevator Power Control Unit (PCU) Door AMM 55−12−32−400−801
(6) Remove warning placards from the control columns, the control wheels, the hydraulic control panel and the external service connections. (7) When this service bulletin is completed, make this entry in the applicablelogbooks: Service Bulletin 670BA−27−064, Flight Controls − Elevator Control System − Replacement of the Bellcrank Support on the Inner Rear Spar of the Horizontal Stabilizer, incorporated."

### SERVICE BULLETIN 670BA−27−064

SB 670BA−27−064 Page 18 of 25 Dec 11/2012 Rigging Pin − Installation Figure 1 (Sheet 1 of 2)ba7673a01.cgm BELLCRANK SUPPORT (REF) A

P6

LOWER LEVER, ELEVATOR (REF) B LEFT SIDE SHOWN RIGHT SIDE OPPOSITE

NOTE: The bracket assembly installed on the left bellcrank support is not shown on this figure. LEGEND P6. Rigging pin.

### SERVICE BULLETIN 670BA−27−064

SB 670BA−27−064 Page 19 of 25 Dec 11/2012 Rigging Pin Installation Figure 1 (Sheet 2 of 2)ba7673a02.cgm C D C

P5 D

P7 OUTBOARD LEVER (REF)
E E

LEGEND P5. Rigging pin. LEFT SIDE SHOWN RIGHT SIDE OPPOSITE

P7. Rigging pin.

### SERVICE BULLETIN 670BA−27−064

SB 670BA−27−064 Page 20 of 25 Dec 11/2012 Control Rods − Disconnection/Connection Figure 2ba7672a01.cgm A

P6

2 3 4 5 6

3 4 5 10
13 12 11

2 9

14

LEGEND

12. Jam nut. 13. Locking device. 14. Upper lever, elevator. P6. Rigging pin. 10. Control rod. 1. Control rod. 2. Cotter pin MS24665

− 134. 3. Nut, self locking MS14145L4. 4. Washer. 5. Washer. 6. Bolt.

11. Bolt. 9. Lower lever, elevator. 7. Jam nut. 8. Locking device. 8 7 1

LEFT SIDE SHOWN RIGHT SIDE OPPOSITE NOTE: The bracket assembly installed on the left bellcrank support is not shown on this figure. B

B A

### SERVICE BULLETIN 670BA−27−064

SB 670BA−27−064 Page 21 of 25 Dec 11/2012 Fairlead Block − Removal/Installation Figure 3ba7674a01.cgm REAR SPAR FRONT SPAR

HYDRAULIC TUBES (REF) 3

1

4 2

5 LEFT SIDE ONLY LEGEND 1. Fairlead block. 2. Screw. 3. Washer. 4. Bracket assembly AV670

− 75412

− 001. 5. Bellcrank support AV670

− 23350

− 001. B

B

### SERVICE BULLETIN 670BA−27−064

SB 670BA−27−064 Page 22 of 25 Dec 11/2012 Bellcrank Support − Removal/Installation Figure 4ba7675a01.cgm 11 10

5

7 6 8 12

9 B

C C

B MASTER SPLINES (REF) 12

10 5 GROOVE (REF)

D D A

A

LEGEND 5. Bellcrank support AV670

− 23350

− 001 (left), AV670

− 23350

− 002 (right). 6. Cotter pin MS24665

− 134. 7. Nut, self locking MS14145L5. 8. Washer. 9. Bolt. 10. Lower lever, elevator. 11. Nut, self locking. 12. Upper lever, elevator. GROOVE (REF) HI

− LITE PIN (REF)

### SERVICE BULLETIN 670BA−27−064

SB 670BA−27−064 Page 23 of 25 Dec 11/2012 Bracket Assembly − Removal/Installation Figure 5ba7676a01.cgm LEGEND 4. Bracket assembly AV670

− 75412

− 001. 5. Bellcrank support AV670

− 23350

− 001 (left). 13. Rivet MS20470AD5

− 7. A

13

4 5

A LEFT BELLCRANK SUPPORT ONLY

### SERVICE BULLETIN 670BA−27−064

SB 670BA−27−064 Page 24 of 25 Dec 11/2012 3. MATERIAL INFORMATION

A. Kit Information Kit Contents:
KIT 670BA27064K1 PART NUMBER QTY NAME ALTERNATE PARTS NOTES
AV670−23350−001 1 Support, bellcrank LH AV670−23350−002 1 Support, bellcrank RH MS14145L4 5 Nut, self locking MS14145L5 3 Nut, self locking MS20470AD5−7 3 Rivet MS21042L4 9 Nut, self locking MS24665−134 7 Pin, cotterThe kit can contain more hardware and/or material than necessary.

B. Consumable Information The materials that follow are necessary to do this service bulletin. You can order them from Bombardier or purchase them directly from industry sources. If the material is ordered from Bombardier, there can be some lead time because of the shelf life of the material. CONSUMABLES SPECIFICATION QTY NAME REFERENCE NASM20995C As necessary Lockwire, corrosion-resistant steel 05−004 MIL−C−81706 Class 1A As necessary Chemical Conversion Coating Alodine 1200 or equivalent 05−025 ### SERVICE BULLETIN 670BA−27−064

SB 670BA−27−064 Page 25 of 25 Dec 11/2012 SPECIFICATION REFERENCE NAME QTY BAMS 565−009 As necessary Polyurethane Topcoat 07−022 MIL−PRF−81733, Type II or IV As necessary Sealing Compounds 09−022 or 09−024BAMS 565−001 As necessary Fluid−Resistant Epoxy Primer 13−006 Refer to AMM 51−31−00−992−801
NOTE: To complete this 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.
D. Disposition of Parts Not applicable. 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 : 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