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

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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

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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

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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

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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

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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)
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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

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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

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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.

(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
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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.
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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

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(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.
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(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.
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(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).
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(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.
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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 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
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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 applicable

logbooks: 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."
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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.
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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.
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Control Rods − Disconnection/Connection

Figure 2 

ba7672a01.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
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Fairlead Block − Removal/Installation

Figure 3 

ba7674a01.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 4 

ba7675a01.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 5 

ba7676a01.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, cotter

The 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 QTY NAME

BAMS 565−009 As

necessary

Polyurethane

Topcoat

07−022 

MIL−PRF−81733,

Type II or IV

As

necessary

Sealing Compounds 09−022 or 09−024



BAMS 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.

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 : 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