SB 670BA ---27---062

Page 1 of 1

Feb 13/2015

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

SERVICE BULLETIN 670BA ---27 ---062

SUBJECT: Flight Controls --- Elevator Control System --- Modification of the Elevator

Lever Assemblies and the Control Rods

This page transmits:

Revision C of Service Bulletin 670BA --- 27 --- 062, dated Feb 13/2015.

The changes in this revision have no effect on aircraft that have had

this service bulletin incorporated.

Reason:

Revised Accomplishment Instructions, paragraph 2., to:

Change and add some steps.

Change an illustration.

This revision also includes small editorial changes that do not have an effect on the technical

content.

Instructions:

Discard the copy of Service Bulletin 670BA --- 27 --- 062, Revision B, dated Oct 10/2014.

Replace with the copy attached.

Service Bulletin History:

Initial issue, dated Dec 12/2013

Revision A, dated Apr 01/2014

Revision B, dated Oct 10/2014

1
SB 670BA−27−062

Page 1 of 45

Dec 12/2013

Revision C, Feb 13/2015

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 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−27−062

SUBJECT: Flight Controls − Elevator Control System − Modification of the Elevator

Lever Assemblies and the Control Rods

1. PLANNING INFORMATION

A. Effectivity

(1) Aircraft Affected:

AIRCRAFT MODEL SERVICE AIRCRAFT

SERIAL NUMBERS

PRODUCTION AIRCRAFT

SERIAL NUMBERS

CL−600−2C10 10002 thru 10337 10338 and subsequent

serial numbers [1]

CL−600−2D15 and

CL−600−2D24

15001 thru 15298 15299 and subsequent

serial numbers [1]

[1] Aircraft will have an equivalent modification 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),

Supplemental Type Approvals (STAs) or equivalent action changes

to make sure you can complete this service bulletin.
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 2 of 45

Dec 12/2013

Revision C, Feb 13/2015

B. Reason

(1) Condition

A break between one of the elevator control rod and a lever assembly can

occur. This can cause a difference between the position of the left and the

right elevator control surface more than the permitted limits.

(2) Evidence

This condition was found during the certification of the CL−600−2E25 aircraft

and confirmed on the CL−600−2C10, CL−600−2D15, and CL−600−2D24

aircraft.

(3) Objective/Benefit

This service bulletin gives the procedure to replace the left and the right fixed

control rods and the lever assemblies. This will prevent a break between the

components of the elevator system, if a failure occurs.

C. Description

The elevator control surfaces are moved in the neutral position. The hydraulic

pressure is released from the systems. Circuit breakers are opened. Some access

panels from the vertical stabilizer are removed. The fixed control rods and the lever

assemblies are replaced. The access panels are installed. The circuit breakers are

closed. The operational test of the elevator control system and the functional test of

the pitch feel system are done.

D. Compliance

Recommended Service Bulletin. Bombardier recommends that this service bulletin

be done at no more than 9200 flight hours from the release date of this service

bulletin, unless otherwise directed by the airworthiness authority of the operator.

NOTE: This service bulletin supersedes Service Bulletin 670BA−27−022, Flight

Controls − Elevator Control System − Replacement of the Elevator Lever

Assemblies.

NOTE: For aircraft that have had Service Bulletin 670BA−27−022 incorporated,

it is necessary to incorporate this service bulletin.

NOTE: If it is not possible to complete all the instructions in this service bulletin

because of the configuration of the aircraft, speak with a representative

of Bombardier in the CRC at 1−844−272−2720 (1−844−CRC−CRC0)

or 1−514−855−8500 or e-mail at thd.crj@aero.bombardier.com for

analysis and to get an approved disposition to complete this service

bulletin.

This service bulletin does not affect Airworthiness Limitations (AWLs) or Damage

Tolerance Inspections (DTIs).
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 3 of 45

Dec 12/2013

Revision C, Feb 13/2015

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.

NOTE: For on-site labor assistance, please speak with a Fleet Services

representative for an estimate. Call the Fleet Services Team through the

CRC at 1−844−272−2720 (1−844−CRC−CRC0) or 1−514−855−8500 or

e-mail at thd.crj@aero.bombardier.com.

It will take an estimated 14.0 man-hours to complete this service bulletin. The

man-hours are divided in the table that follows:

TASK MAN-HOURS

(1) Job Set-Up 1.5

(2) Procedure 10.0

(3) Test 1.5

(4) Job Close-Out 1.0
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 4 of 45

Dec 12/2013

Revision C, Feb 13/2015

G. Material − Price and Availability

(1) The kits in the table that follows are available from Bombardier.

NOTE: For a list of kit contents, refer to paragraph 3.A.

KIT NUMBER NAME

670BA27062K1 [1] Kit − Elevator Disconnect Modification

670BA27062K2 [2] Blank Idler Aft Brackets

[1] One kit is necessary for each aircraft.

[2] A limited quantity of kits are available for each operator and can 

 be necessary until P/N AV670−21569−009SB and P/N

 AV670−21569−010SB replace P/N AV670−21569−009 and

 P/N AV670−21569−010 in kit 670BA27062K1 or later kit revisions.

(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

(1) The tool kit in the table that follows is available from Bombardier.

NOTE: For a list of the kit contents, refer to paragraph 3.A.

KIT NUMBER NAME

670BA27062K90 Kit − Reamers
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 5 of 45

Dec 12/2013

Revision C, Feb 13/2015

(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.

I. Weight and Balance

For CL−600−2C10 aircraft

WEIGHT ARM MOMENT 

+1.2 lb +1311.8 in. +1.574 (1000 lb-in)

+0.54 kg +33.32 m +0.0181 (1000 kg-m)

The value in the Moment column is divided by 1000.

Refer to Weight and Balance Manual.

For CL−600−2D15 and CL−600−2D24 aircraft

WEIGHT ARM MOMENT 

+1.2 lb +1463.8 in. +1.757 (1000 lb-in)

+0.54 kg +37.18 m +0.0202 (1000 kg-m)

The value in the Moment column is divided by 1000.

Refer to Weight and Balance Manual.

J. Electrical Load Data

Not changed.
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 6 of 45

Dec 12/2013

Revision C, Feb 13/2015

K. References

Refer to the SB Introduction document for definition or explanation of service

bulletin content.

Restriction and/or Special Instruction (RSI) C−27−1254−00, Revision E

Modification Summary 670T040513, Revision J

Aircraft Maintenance Manual (AMM)

Structural Repair Manual (SRM)

For Bombardier reference only: PCA 74115

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

AV670−21569−001 or

AV670−21569−005 Idler bracket, aft KBA670−93707−3 [1] Idler bracket, aft

AV670−21569−002 or

AV670−21569−006 Idler bracket, aft KBA670−93707−4 [2] Idler bracket, aft

BA670−92367−3 Lever assembly,

forward KBA670−93707−5 Lever assembly,forward

BA670−92602−39 Control rod,

fixed BA670−93722−3 Link assembly

BA670−93786−1,

BA670−93772−1, or

BA670−93772−3

Lever assembly,

aft

BA670−93787−3, or

BA670−93787−951

Lever assembly,

aft

BA670−93771−1, or

BA670−93771−3 Lever assembly BA670−93784−3 Lever assembly

[1] P/N AV670−21569−009 was installed during the incorporation of the initial issue 

 or Revision A of this service bulletin.

[2] P/N AV670−21569−010 was installed during the incorporation of the initial issue

 or Revision A of this service bulletin.
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 7 of 45

Dec 12/2013

Revision C, Feb 13/2015

For Aircraft 10150 thru 10226, 10228, and 15024 thru 15039 pre-SB 670BA−27−022

PRE-SB

PART NUMBER NAME POST-SB

PART NUMBER NAME

BA670−30000−8955,

BA670−30000−9993,

BA690−30000−496, or

BA690−30000−4989

Control rod BA670−92602−13 Control rod
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 8 of 45

Dec 12/2013

Revision C, Feb 13/2015

2. ACCOMPLISHMENT INSTRUCTIONS

Reference Information

REFERENCE DESIGNATION

AMM 12−00−00−867−801 Standard Aircraft Configuration for Maintenance

AMM 12−00−06−862−802 Release Hydraulic Pressure of Systems No.1

and No.2

AMM 12−00−06−862−804 Release Hydraulic Pressure of System No.3

AMM 20−21−00−910−801 Torquing of Threaded Fasteners

AMM 20−31−00−400−801 Thermal Installation of Interference Fit

Bushings

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 20−51−00−000−807 Removal of Safety Cables

AMM 20−51−00−400−807 Installation of Safety Cables

AMM 24−00−00−910−801 Electrical/Electronic Safety Precautions

AMM 27−00−00−910−802 Flight-Control Safety Precautions

AMM 27−31−00−710−801 Operational Test of the Elevator Control System

AMM 27−31−00−720−805 Functional Test of the Pitch Feel System

AMM 27−31−00−864−801 Move the Elevator Control Surfaces in the Neutral Position

AMM 27−31−25−000−810 Removal of the Vertical Stabilizer Control−Rod

from FS1308.44 to FS1317.47

AMM 55−32−32−000−801 Removal of the Elevator-Quadrant Access Door

(325EL/325ER)

AMM 55−32−32−400−801 Installation of the Elevator-Quadrant Access

Door (325EL/325ER)
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 9 of 45

Dec 12/2013

Revision C, Feb 13/2015

REFERENCE DESIGNATION

AMM 55−32−32−000−804 Removal of the Load-Limiter Access Door

(325FL)

AMM 55−32−32−400−804 Installation of the Load-Limiter Access Door

(325FL)

AMM 55−32−32−000−805 Removal of the Gain-Changer Access Door

(325BL)

AMM 55−32−32−400−805 Installation of the Gain-Changer Access Door

(325BL)

AMM 55−32−86−000−805 Removal of the Lower Fairing Panel

(326BL/326BR)

AMM 55−32−86−400−805 Installation of the Lower Fairing Panel

(326BL/326BR)

AMM 55−32−86−000−807 Removal of the Lower Visor Fairing

(326CL/326CR)

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 51−41−02−001−001 Bolts, Screws and Related Items

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−27−062

SB 670BA−27−062

Page 10 of 45

Dec 12/2013

Revision C, Feb 13/2015

A. Job Set-Up

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.

(1) Make sure that the aircraft is in standard configuration for maintenance

(refer to AMM 12−00−00−867−801).

(2) Move the elevator control surfaces in the neutral position

(refer to AMM 27−31−00−864−801).

(3) Obey all the flight-control safety precautions

(refer to AMM 27−00−00−910−802).

(4) Release the pressure of hydraulic systems No.1 and No.2

(refer to AMM 12−00−06−862−802).

(5) Release the pressure of hydraulic system No.3

(refer to AMM 12−00−06−862−804).

(6) Obey all the electrical/electronic safety precautions

(refer to AMM 24−00−00−910−801).

(7) 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 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
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 11 of 45

Dec 12/2013

Revision C, Feb 13/2015

(8) Remove the access panels that follow:

PANEL NAME REFERENCE

325BL Gain-Changer Access

Door

AMM 55−32−32−000−805

325EL/325ER Elevator-Quadrant

Access Door

AMM 55−32−32−000−801

325FL Load-Limiter Access

Door

AMM 55−32−32−000−804

326CL/326CR Lower Visor Fairing AMM 55−32−86−000−807

(9) If necessary, remove the access panel that follows:

PANEL NAME REFERENCE

326BL/326BR Lower Fairing Panel AMM 55−32−86−000−805

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 1.

(1) Install rigging pins P1 and P2.

(2) Remove and discard the vertical stabilizer control-rods (1) from, FS1308.44 to

FS1317.47, and their related hardware (refer to AMM 27−31−25−000−810).

Refer to Figure 2.

(3) Remove the cotter pin (3), the nut (4), the washer (5), the bolt (6), and the

upper end of the load limiter (1) from the forward lever assembly (2) (refer to

AMM 20−51−00−000−801). Discard the cotter pin (3) and the nut (4).

(4) Remove the centering springs (7), the link (8), and the adjustable studs (9)

from the aft lever assembly (10) as follows:

(a) Remove the lockwire from the jam nut (13) 

(refer to AMM 20−51−00−000−802).
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 12 of 45

Dec 12/2013

Revision C, Feb 13/2015

(b) Remove and discard the jam nuts (13) and the locking devices (14) from

the adjustable studs (9).

(c) Remove the cotter pin (3), the nut (4), the washer (11), the bolt (12), and

the link (8) from the aft lever assembly (10) (refer to AMM

20−51−00−000−801). Discard the cotter pin (3), the nut (4), the washer

(11), and the bolt (12).

(5) Remove the forward end of the horizontal stabilizer control-rod (15) from the

aft lever assembly (10) as follows:

(a) Remove the cotter pin (3), the nut (4), the washer (11), the bushing (16),

the countersunk washer (17), and the bolt (12) from the aft lever

assembly (10) (refer to AMM 20−51−00−000−801).

(b) Discard the cotter pin (3), the nut (4), the washer (11), the bushing (16),

and the bolt (12).

Refer to Figure 3.

(6) Remove the lever assemblies (1) and (2) and the idler brackets (3) and (4) as

follows:

(a) Remove the nuts (5) and (6), the washers (7) and (8), the bolts (9) and

(10), and the idler forward bracket (3) from the canted rib. Discard the

nuts (5) and (6).

(b) Remove the cotter pin (11), the nut (12), the washer (13), the bushing

(14), the countersunk washer (15), the bolt (16), and the forward lever

assembly (1) from the idler forward bracket (3) 

(refer to AMM 20−51−00−000−801). Discard the cotter pin (11), the nut

(12), the washer (13), and the bolt (16).

(c) Remove the nuts (5), the washers (7), the bolts (17), and the idler aft

bracket (4) from the canted rib. Discard the nuts (5).

NOTE: Keep the idler aft bracket (4), it can be used in a subsequent step

to drill the holes if a new blank idler aft bracket is used.

(d) Remove the cotter pin (11), the nut (12), the washer (13), the bushing

(18), the countersunk washer (15), the bolt (16) and the aft lever

assembly (2) from the idler aft bracket (4) 

(refer to AMM 20−51−00−000−801). Discard the cotter pin (11), the nut

(12), the washer (13), the bushing (18), the bolt (16), and the aft lever

assembly (2).
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 13 of 45

Dec 12/2013

Revision C, Feb 13/2015

Refer to Figure 4.

(7) Increase the diameter of the outboard hole for the left forward lever assembly

(1) and the inboard hole for the right forward lever assembly (1) as follows

(refer to View A):

(a) Assemble the reamer guide assembly on the forward lever assembly (1)

as follows:

1 Put the flange stopper (2) between the aft flanges of the forward

lever assembly (1).

2 With the alignment pin (3), install the guide bushing (4) through the

right flange of the forward lever assembly (1) and the flange

stopper (2).

3 Tighten the screws of the flange stopper (2).

4 Install the washer (5) and, with your hand, tighten the nut (6) on the

guide bushing (4).

5 Remove the alignment pin (3).

(b) With step reamer (7) P/N 670BA27062K90−13 and cutting fluid, ream

the hole to a diameter of 0.3050 to 0.3052 in. (7.747 to 7.752 mm).

(c) With step reamer (7) P/N 670BA27062K90−15 and cutting fluid, ream

the hole to a diameter of 0.3600 to 0.3602 in. (9.144 to 9.149 mm) .

(d) With final reamer (7) P/N 670BA27062K90−17 and cutting fluid, ream

the hole to a diameter of 0.3750 to 0.3752 in. (9.525 to 9.530 mm).

(e) Disassemble the reamer guide assembly as follows:

1 Loosen the screws of the flange stopper (2) to remove the reamer

guide assembly.

2 Remove the nut (6), the washer (5), the guide bushing (4), and the

flange stopper (2) from the forward lever assembly (1).

(f) Remove the burrs and the sharp edges.

(g) Apply chemical conversion coating on the bare metal areas

(refer to SRM 51−21−11−001−001).
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 14 of 45

Dec 12/2013

Revision C, Feb 13/2015

(h) With a clean cloth moist with solvent, remove the identification of the

forward lever assembly (1) (refer to SRM 51−26−00−001−001).

(i) If the identification number continues to be visible, apply one layer of

fluid-resistant primer over the identification (refer to SRM

51−25−06−001−001).

(j) With an indelible ink pen or equivalent, identify the forward lever

assembly (1) as KBA670−93707−5.

(k) Apply a layer of clear polyurethane topcoat on the identification (refer to

SRM 51−25−16−001−001).

NOTE: Let the ink dry for 30 minutes before you apply the clear

polyurethane topcoat.

Refer to Figure 11.

(8) If you have idler aft bracket (1), do as follows:

NOTE: The diameter of the holes in the canted rib are not increased.

(a) Increase the diameter of the four holes in the idler aft bracket (1) to

0.198−0.203 in. (5.03−5.16 mm).

(b) Remove the burrs and the sharp edges.

(c) Make sure the holes in the idler aft bracket (1) align with the holes in the

canted rib and the four bolts (3) can be installed.

(d) If the four bolts (3) can not be installed, idler aft bracket (1) is not used.

Go to step (9) to use idler aft bracket (2).

(e) Apply chemical conversion coating on the bare metal areas of the idler

aft bracket (1) (refer to SRM 51−21−11−001−001).

(f) With a clean cloth moist with solvent, remove the identification of the

idler aft bracket (1) (refer to SRM 51−26−00−001−001).

(g) If the identification number continues to be visible, apply one layer of

fluid−resistant primer over the identification (refer to SRM

51−25−06−001−001).
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 15 of 45

Dec 12/2013

Revision C, Feb 13/2015

(h) With an indelible ink pen or equivalent, identify the idler aft bracket (1) as

follows:

1 For the left idler aft bracket (1), identify as KBA670−93707−3.

2 For the right idler aft bracket (1), identify as KBA670−93707−4.

(i) Apply a layer of clear polyurethane topcoat on the identification (refer to

SRM 51−25−16−001−001).

NOTE: Let the ink dry for 30 minutes before you apply the clear

polyurethane topcoat.

Refer to Figure 3 and Figure 11.

(9) If you do not have idler aft bracket (1), or if it is not possible to install the idler

aft bracket (1), use the idler aft bracket (2) as follows:

NOTE: The diameter of the holes in the canted rib are not increased.

(a) Drill four holes in the blank idler aft bracket (2) to a diameter of

0.198−0.203 in. (5.03−5.16 mm) to align with the four holes in the

canted rib. Make sure you drill the holes so the idler aft bracket (2) is

installed at the same location as the idler aft bracket (4).

(b) Remove the burrs and the sharp edges.

(c) Apply chemical conversion coating on the bare metal areas

(refer to SRM 51−21−11−001−001).

(d) With a clean cloth moist with solvent, remove the identification of the

idler aft bracket (2) (refer to SRM 51−26−00−001−001).

(e) If the identification number continues to be visible, apply one layer of

fluid−resistant primer over the identification (refer to SRM

51−25−06−001−001).

(f) With an indelible ink pen or equivalent, identify the idler aft bracket (2) as

follows:

1 For the left idler aft bracket (2), identify as KBA670−93707−3.

2 For the right idler aft bracket (2), identify as KBA670−93707−4.
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 16 of 45

Dec 12/2013

Revision C, Feb 13/2015

(g) Apply a layer of clear polyurethane topcoat on the identification (refer to

SRM 51−25−16−001−001).

NOTE: Let the ink dry for 30 minutes before you apply the clear

polyurethane topcoat.

Refer to Figure 5.

(10) Make sure that the bolts (10), (16), and (17) are put in position on the idler

brackets (2) and (14) before the installation of the lever assemblies (1) and

(13).

(11) Install the aft lever assembly (1) on the idler aft bracket (2) with the bolt (3),

the countersunk washer (4), the bushing (5) and (6), the washer (7), the

self-locking nut (8), and the cotter pin (9) 

(refer to AMM 20−21−00−910−801, AMM 20−51−00−400−801, and 

SRM 51−41−02−001−001).

NOTE: The countersunk side of the washer (4) must be installed under the head

of the bolt (3).

NOTE: The bushing (6) must be installed between the idler aft bracket (2) and

the aft lever assembly (1).

(12) Install the idler aft bracket (2) on the canted rib with the bolts (10), the

washers (11), and the self-locking nuts (12) 

(refer to AMM 20−21−00−910−801 and SRM 51−41−02−001−001).

(13) Install the forward lever assembly (13) on the idler forward bracket (14) with

the bolt (3), the countersunk washer (4), the bushing (15), the washer (7), the

self-locking nut (8), and the cotter pin (9) 

(refer to AMM 20−21−00−910−801, AMM 20−51−00−400−801, and 

SRM 51−41−02−001−001).

NOTE: The countersunk side of the washer (3) must be installed under the head

of the bolt (4).

(14) Install the idler forward bracket (14) on the canted rib with the bolts (16) and

(17), the washers (11) and (18), and the self-locking nuts (12) and (19) 

(refer to AMM 20−21−00−910−801 and SRM 51−41−02−001−001).
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 17 of 45

Dec 12/2013

Revision C, Feb 13/2015

Refer to Figure 6.

(15) Install the link assembly (1) as follows:

(a) Install the link assembly (1) on the aft lever assembly (2) with the bolt

(3), the washer (4), the self-locking nut (5), the washer key (6), the

bushing (7), the bolt (8), the washer (9), the flat washer (10), the

self-locking nut (11), and the cotter pin (12) 

(refer to AMM 20−51−00−400−801 and SRM 51−41−02−001−001).

(b) Torque the self-locking nut (11) from 30 to 40 lbf•in. (3.4 to 4.5 N•m)

(refer to AMM 20−21−00−910−801).

(c) Install the link assembly (1) on the forward lever assembly (13) with the

bolt (14), the countersunk washer (15), the bushings (16) and (17), the

washer (18), the self-locking nut (11), and the cotter pin (12) 

(refer to AMM 20−21−00−910−801, AMM 20−31−00−400−801, 

AMM 20−51−00−400−801, and SRM 51−41−02−001−001).

NOTE: The countersunk side of the washer (15) must be installed under

the head of the bolt (14).

NOTE: The bushing (16) is installed between the link assembly (1) and the

lug of the forward lever assembly (13).

Refer to Figure 7.

(16) Install rigging pin P3.

(17) Align the fastener hole of the load limiter (1) with the fastener hole of the

forward lever assembly (2).

(18) If the fastener hole of the load limiter (1) does not align with the fastener hole

of the forward lever assembly (2), do the steps that follow:

(a) Remove the lockwire or the safety cable from the jam nut (3) 

(refer to AMM 20−51−00−000−802 or 20−51−00−000−807).

(b) Loosen the jam nut (3) of the load limiter (1) sufficiently to disengage the

locking device (4).

(c) Adjust the length of the load limiter (1) to align the fastener hole of the

load limiter (1) with the fastener hole of the forward lever assembly (2).

(d) Tighten the jam nut (3) of the load limiter (1) sufficiently to engage the

locking device (4).
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 18 of 45

Dec 12/2013

Revision C, Feb 13/2015

(19) Install the aft end of the load limiter (1) to the forward lever assembly (2) with

the bolt (5), the washer (6), the self-locking nut (7), and the cotter pin (8) 

(refer to AMM 20−21−00−910−801, AMM 20−51−00−400−801, and 

SRM 51−41−02−001−001).

(20) Make sure that rigging pins P1 and P3 move easily.

(21) If the lockwire or the safety cable was removed, safety the jam nuts (3) of the

load limiter (1) with lockwire or safety cable 

(refer to AMM 20−51−00−400−802 or 20−51−00−400−807).

(22) Install rigging pin P4.

(23) Remove rigging pins P1 and P3.

(24) Remove the cotter pin (9), the nut (10), the washer (11), the bolt (12), and the

control rod (13) from the elevator quadrant 

(refer to AMM 20−51−00−000−801). Discard the cotter pins (9).

(25) Remove the cotter pin (9), the nut (14), the washer (15), the bolt (16), and the

control rod (17) from the gain-changer (refer to AMM 20−51−00−000−801).

Discard the cotter pins (9).

(26) Install the centering springs (18) with the link (19) and the adjustable studs

(20) as follows:

(a) Apply Mastinox compound or corrosion inhibiting compound on the

hooks of the centering springs (18).

(b) Install the link (19) and the centering springs (18) on the aft lever

assembly (21) with the bolt (22), the washer (23), the self-locking nut

(24), and the cotter pin (8) (refer to AMM 20−21−00−910−801, 

AMM 20−51−00−400−801, and SRM 51−41−02−001−001).

(c) Install the adjustable studs (20) on the canted rib bracket with the

locking devices (25) wet with Mastinox compound or corrosion inhibiting

compound and the jam nuts (26) (refer to SRM 51−23−00−001−001).

(d) Adjust the jam nuts (26) of the adjustable studs (20) until rigging pin P3

can be installed and moved easily.

(e) Remove rigging pin P3.

(27) Move the control rod (17) quickly to operate the centering springs (18).

(28) Temporarily install rigging pin P3.
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 19 of 45

Dec 12/2013

Revision C, Feb 13/2015

(29) Make sure that rigging pin P3 moves easily.

(30) Remove rigging pin P3.

(31) Safety the two forward jam nuts (26) of the adjustable studs (20) together with

lockwire (refer to AMM 20−51−00−400−802).

NOTE: Do not install the lockwire through the locking devices (25).

(32) Safety the two aft jam nuts (26) of the adjustable studs (20) together with

lockwire (refer to AMM 20−51−00−400−802).

NOTE: Do not install the lockwire through the locking devices (25).

(33) Install the control rod (17) to the gain-changer with the bolt (16), the washer

(15), the nut (14), and the cotter pin (9) (refer to AMM 20−21−00−910−801,

AMM 20−51−00−400−801, and SRM 51−41−02−001−001).

(34) Align the fastener hole of the horizontal stabilizer control-rod (27) with the

fastener hole of the aft lever assembly (21).

(35) If the fastener hole of the horizontal stabilizer control-rod (27) does not align

with the fastener hole of the aft lever assembly (21), do as follows:

(a) Remove the cotter pin (9), the self-locking nut (28), the washers (29) and

(30), the bolt (31), and the horizontal stabilizer control-rod (27) from the

bearing rod end (refer to AMM 20−51−00−000−801). Discard the

cotter pin (9).

(b) Remove the lockwire or safety cable from the jam nut (32) of the

horizontal stabilizer control-rod (27) (refer to AMM 20−51−00−000−802

and AMM 20−51−00−000−807).

(c) Loosen the jam nut (32) of the horizontal stabilizer control-rod (27)

sufficiently to disengage the locking device (33).

(d) Adjust the length of the horizontal stabilizer control-rod (27) to align the

fastener hole of the horizontal stabilizer control-rod (27) with the fastener

hole of the bearing rod end and the aft lever assembly (21).

(e) Tighten the jam nut (32) of the horizontal stabilizer control-rod (27)

sufficiently to engage the locking device (33).

(f) Install the aft end of the horizontal stabilizer control-rod (27) to the

bearing rod end with the bolt (31), the washers (29) and (30), the

self-locking nut (28), and the cotter pin (9) 

(refer to AMM 20−51−00−400−801).
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 20 of 45

Dec 12/2013

Revision C, Feb 13/2015

(36) Install the forward end of the horizontal stabilizer control-rod (27) to the aft

lever assembly (21) with the bolt (34), the countersunk washer (35), the

bushing (36), the washer (37), the self-locking nut (24), and the cotter pin (8)

(refer to AMM 20−21−00−910−801, AMM 20−51−00−400−801, and 

SRM 51−41−02−001−001).

NOTE: The countersunk side of the washer (35) must be installed under the

head of the bolt (34).

(37) Make sure that rigging pin P2 moves easily.

(38) Temporarily install rigging pin P3.

(39) Make sure that rigging pin P3 moves easily.

(40) Remove rigging pins P3.

(41) If the lockwire or the safety cable was removed, safety the jam nuts (32) of the

horizontal stabilizer control-rod (27) with lockwire or safety cable 

(refer to AMM 20−51−00−400−802 or 20−51−00−400−807).

(42) Install the control rod (13) to the elevator quadrant with the bolt (12), the

washer (11), the nut (10), and the cotter pin (9) 

(refer to AMM 20−21−00−910−801, AMM 20−51−00−400−801, and 

SRM 51−41−02−001−001).

(43) Install rigging pin P3.

(44) Remove rigging pin P4.

Refer to Figure 8.

For Aircraft 10150 thru 10226, 10228, and 15024 thru 15039 pre-SB 670BA−27−022

(45) Remove the arrow and the FWD" marking from the horizontal stabilizer

control-rod (1) as follows:

(a) With a Scotchbrite pad, lightly rub the area to remove the clear coating

applied on the marks.

(b) Make sure that you remove the clear coating only.

(c) With a clean cloth moist with solvent, remove the arrow and the FWD"

marking from the horizontal stabilizer control-rod (1) 

(refer to SRM 51−26−00−001−001).

(d) If the arrow and/or the FWD" marking continues to be visible, apply one

layer of polyurethane topcoat on the arrow and/or the FWD" marking

(refer to SRM 51−25−16−001−001).
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 21 of 45

Dec 12/2013

Revision C, Feb 13/2015

(46) With a indelible ink pen or equivalent, identify the horizontal stabilizer

control-rod (1) as BA670−92602−13.

(a) Apply a layer of clear polyurethane topcoat on the identification (refer to

SRM 51−25−16−001−001).

NOTE: Let the ink dry for 30 minutes before you apply the clear

polyurethane topcoat.

For all aircraft

Refer to Figure 9.

(47) Remove rigging pins P2 and P3.

Refer to Figure 10.

(48) Make sure that the clearance between the aft lever assembly and the

fasteners of the lower skin is 0.250 in. (6.35 mm) minimum throughout the full

travel of the elevator.

(49) Make sure that the clearance between the head of the bolt that attaches the

forward lever assembly to the link assembly and the pivot fitting of the

horizontal stabilizer is 0.200 in. (5.08 mm) minimum through the full travel of

the elevator.

(50) If it is not possible to complete all the instructions in this service bulletin

because of the configuration of the aircraft, speak with a representative of

Bombardier in the CRC at 1−844−272−2720 (1−844−CRC−CRC0) or

1−514−855−8500 or e-mail at thd.crj@aero.bombardier.com for analysis

and to get an approved disposition to complete this service bulletin.

C. Job Close-Out

(1) Remove all tools, equipment, and unwanted materials from the work area.
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 22 of 45

Dec 12/2013

Revision C, Feb 13/2015

(2) Install the access panels that follow:

PANEL NAME REFERENCE

325BL Gain-Changer Access

Door

AMM 55−32−32−400−805

325EL/325ER Elevator-Quadrant

Access Door

AMM 55−32−32−400−801

325FL Load-Limiter Access

Door

AMM 55−32−32−400−804

326CL/326CR Lower Visor Fairing AMM 55−32−86−400−807

(3) If removed, install the access panel that follows:

PANEL NAME REFERENCE

326BL/326BR Lower Fairing Panel AMM 55−32−86−400−805

(4) 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 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

(5) Do the operational test of the elevator control system 

(refer the AMM 27−31−00−710−801).

(6) Do the functional test of the pitch feel system 

(refer the AMM 27−31−00−720−805).
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 23 of 45

Dec 12/2013

Revision C, Feb 13/2015

(7) When this service bulletin is completed, add the weight and balance data

shown in paragraph 1.I. of this service bulletin to the Weight and Balance

Manual. Under ‘Description of Change’ enter Service Bulletin

670BA−27−062, Revision C, incorporated."

(8) When this service bulletin is completed, make this entry in the applicable

logbooks: Service Bulletin 670BA−27−062, Revision C, Flight Controls −

Elevator Control System − Modification of the Elevator Lever Assemblies and

the Control Rods, incorporated."
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 24 of 45

Dec 12/2013

Revision C, Feb 13/2015

Rigging Pins − Installation

Figure 1 (Sheet 1 of 1)

ba7599a01.cgm, cr, 02−apr−2013

B

C

A

CONTROL ROD

(REF)

P2

BEARING

ROD END

(REF)

P1

A

LOAD LIMITER

(REF)

1

C

B

GAIN−CHANGER

(REF)

NOTE

Left side shown,

right side opposite.

CONTROL

ROD (REF)

LEGEND

P. Rigging pin.

1. Vertical stabilizer control−rod.
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 25 of 45

Dec 12/2013

Revision C, Feb 13/2015

Load Limiter, Control Rod, and Centering Springs − Removal

Figure 2 (Sheet 1 of 2)

ba7602a01.cgm, sc, 16 oct 2012

3

4

5

6

2

LEGEND

1. Load limiter.

2. Forward lever assembly.

3. Cotter pin.

4. Nut.

5. Washer.

6. Bolt.

Left side shown,

right side opposite.

NOTE

1

A

B

A PRE−MOD

B
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 26 of 45

Dec 12/2013

Revision C, Feb 13/2015

Load Limiter, Control Rod, and Centering Springs − Removal

Figure 2 (Sheet 2 of 2)

ba7602a02.cgm, sc, 16 oct 2012

Left side shown,

right side opposite.

NOTE

3 7

4 11

8

12

16 17 12

11

4

3

15

10

13

14 13

9

13

C

A PRE−MOD

C

LEGEND

 3. Cotter pin.

 4. Nut.

 7. Centering spring.

 8. Link.

 9. Adjustable stud.

10. Aft lever assembly.

11. Washer.

12. Bolt.

13. Jam nut.

14. Locking device.

15. Horizontal stabilizer control−rod.

16. Bushing.

17. Countersunk washer.
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 27 of 45

Dec 12/2013

Revision C, Feb 13/2015

Lever Assemblies and Idler Brackets − Removal

Figure 3 (Sheet 1 of 1)

ba7600a01.cgm, YL, Feb 20, 2014

A PRE−MOD

B

NOTE

Left side shown,

right side opposite.

A

B

1

11

12

13

14

15

16

3

5

6

7

8

10 9

11

12

13 15

18

17

17

4

16

7

5

2

CANTED

RIB (REF)

LEGEND

 1. Forward lever assembly

 BA670−92367−3.

 2. Aft lever assembly

 BA670−93786−1 or

 BA670−93772−1 or

 BA670−93772−3.

 3. Idler forward bracket.

 4. Idler aft bracket

 AV670−21569−001 or

 AV670−21569−005 (LH),

 AV670−21569−002 or

 AV670−21569−006 (RH).

 5. Nut.

 6. Nut.

 7. Washer.

 8. Washer.

 9. Bolt.

 10. Bolt.

11. Cotter pin.

12. Nut.

13. Washer.

14. Bushing.

15. Countersunk washer.

16. Bolt.

17. Bolt.

18. Bushing.
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 28 of 45

Dec 12/2013

Revision C, Feb 13/2015

 Forward Lever Assembly − Modification

Figure 4 (Sheet 1 of 1)

1

ba7705a01.cgm, cr/kp, Jan. 6, 2015

LEGEND

 1. Forward lever assembly

 BA670−92367−3 (pre−mod)

 KBA670−93707−5 (post−mod).

 2. Flange stopper

 670BA27062K90−7.

 3. Alignment pin

 670BA27062K90−27.

 4. Guide bushing

 670BA27062K90−3.

 5. Washer

 670BA27062K90−11.

 6. Nut

 670BA27062K90−5.

 7. Reamer.

REAMER (ITEM 7)

PART NUMBER

670BA27062K90−13

670BA27062K90−15

670BA27062K90−17

0.3050 to 0.3052 in. (7.747 to 7.752 mm)

0.3600 to 0.3602 in. (9.144 to 9.149 mm)

0.3750 to 0.3752 in. (9.525 to 9.530 mm)

HOLE − FINAL DIAMETER

A

A 2

4

3

7

DRILL (REF)

5

6

SCREW (REF)

OUT BOARD HOLE FOR THE

LEFT ASSEMBLY, INBOARD

HOLE FOR THE RIGHT

ASSEMBLY (REF).

B

B
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 29 of 45

Dec 12/2013

Revision C, Feb 13/2015

Lever Assemblies and Idler Brackets − Installation

Figure 5 (Sheet 1 of 1)

13

9

8

7

15 4

3

14

12

19 11

18

17 16

6

4

10

10

2

3

11

12

ba7618a01.cgm, yl/kl, 11 June 2014

A POST−MOD 1

5

CANTED

RIB (REF)

C

A

C

LEGEND

 1. Aft lever assembly

 BA670−93787−3 or

 BA670−93787−951.

 2. Idler aft bracket

 KBA670−93707−3 (LH),

 KBA670−93707−4 (RH).

 3. Bolt.

 NAS6305−27D.

 4. Countersunk washer.

 5. Bushing

 B0309008−05−040.

 6. Bushing

 B0309008−05−006.

 7. Washer

 NAS1149E0563P.

 8. Self−locking nut

 B0203011L5.

 9. Cotter pin

 MS24665−153.

10. Bolt.

11. Washer.

12. Self−locking nut

 MS21042L3.

13. Forward lever assembly

 KBA670−93707−5.

14. Idler forward bracket.

15. Bushing.

16. Bolt.

17. Bolt.

18. Washer.

19. Self−locking nut

 MS21042L4.

9 8 7

1

NOTE

For the left and right side,

the bushing (item 15) is

installed on the outboard

side of the bracket (item 14).

1
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 30 of 45

Dec 12/2013

Revision C, Feb 13/2015

 Link Assembly − Installation

Figure 6 (Sheet 1 of 1)

A

A

B

B

ba7603a01.cgm, kp, March 10, 2013

LEGEND

 1. Link assembly

 BA670−93722−3.

 2. Aft lever assembly.

 3. Bolt

 NAS6304U21D.

 4. Washer

 NAS1149E0432R.

 5. Self−locking nut

 MS21083C6.

 6. Washer key

 BA698−93726−3.

 7. Bushing

 S10008−782A.

 8. Bolt

 BA698−93725−3.

 9. Washer

 B0202013C1614−16.

10. Flat washer

 NAS620C416P.

11. Self−locking nut

 B0203011L4.

12. Cotter pin

 MS24665−153.

13. Fwd lever assembly.

14. Bolt

 NAS2814C15DP.

15. Countersunk washer

 MS20002C4.

16. Bushing

 NAS76A4−004P.

17. Bushing

 NAS76A4−009P.

18. Washer

 NAS1149E0463P.

12

16

15

14

18

8

11

10

9

13

12

11

6 5

4 3

7

14

12

11

15

18

16

17

1

2
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 31 of 45

Dec 12/2013

Revision C, Feb 13/2015

Load Limiter, Control Rod, and Centering Springs − Installation

Figure 7 (Sheet 1 of 4)

ba7619a01.cgm, sc/cr, 31− jan−2013

A POST−MOD

A

P3

5

1

IDLER ASSEMBLY

(REF)

4

3

8

7 6

2

1. Left side shown,

 right side opposite.

NOTES

LEGEND

 1. Load limiter.

 2. Forward lever assembly.

 3. Jam nut.

 4. Locking device.

 5. Bolt.

 6. Washer

 7. Self−locking nut

 MS14145L4.

 8. Cotter pin

 MS24665−153.

 P. Rigging pin.
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 32 of 45

Dec 12/2013

Revision C, Feb 13/2015

Load Limiter, Control Rod, and Centering Springs − Installation

Figure 7 (Sheet 2 of 4)

ba7619a02.cgm, sc, 14 oct 2012

1. Left side shown,

 right side opposite.

NOTES

A POST−MOD

P1

P3

LOAD

LIMITER

(REF)

IDLER

ASSEMBLY

(REF)

B C

17

13

B

P4

12 13

9

10

11

ELEVATOR

QUADRANT

(REF)

C

16

17

GAIN−CHANGER

(REF)

15

9

14

LEGEND

 9. Cotter pin.

10. Nut.

11. Washer.

12. Bolt.

13. Control rod.

14. Nut.

15. Washer.

16. Bolt.

17. Control rod.

 P. Rigging pin.
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 33 of 45

Dec 12/2013

Revision C, Feb 13/2015

Load Limiter, Control Rod, and Centering Springs − Installation

Figure 7 (Sheet 3 of 4)

ba7619a03.cgm, sc/cr,29 jan 20113

8

18

24

23

19

22

35 34

37

24

8

27

21

26

25 26

20

A POST−MOD

Left side shown,

right side opposite.

The bolt for the left

and the right lever

assembly is in the same

direction.

NOTES

2

1.

2

CANTED RIB

BRACKET

(REF)

2

26

D

LINK ASSEMBLY NOT SHOWN FOR CLARITY

D

P3

36

LEGEND

 8. Cotter pin

 MS24665−153.

18. Centering spring.

19. Link.

20. Adjustable stud.

21. Aft lever assembly.

22. Bolt

 NAS6304−8D.

23. Washer

 NAS1149E0463P.

24. Self−locking nut

 B0203011L4.

25. Locking device

 NAS559−1

26. Jam nut

 NAS1423C4.

27. Horizontal stabilizer control−rod.

34. Bolt

 NAS6304−17D.

35. Countersunk washer.

36. Bushing

 B0309008−04−027.

37. Washer

 NAS1149E0463R.

 P. Rigging pin.
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 34 of 45

Dec 12/2013

Revision C, Feb 13/2015

Load Limiter, Control Rod, and Centering Springs − Installation

Figure 7 (Sheet 4 of 4)

ba7619a04.cgm, sc, 14 oct 2012

Left side shown,

right side opposite.

NOTES

1.

A POST−MOD

LEGEND

 9. Cotter pin.

27. Horizontal stabilizer control−rod.

28. Self−locking nut.

29. Washer.

30. Washer.

31. Bolt.

32. Jamnut.

33. Locking device.

 P. Rigging pin.

E

E

P2

27

33

32

9

28

29

30

31

BEARING

ROD END

(REF)
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 35 of 45

Dec 12/2013

Revision C, Feb 13/2015

 Horizontal Stabilizer Control-Rod − Identification

Figure 8 (Sheet 1 of 1)

ba7601a01.cgm, sc, 3 oct 2012

A

LEGEND

1. Horizontal−stabilizer control−rod

 BA670−30000−8955,

 BA670−30000−9993,

 BA690−30000−496, or

 BA690−30000−4989 (Pre−Mod),

 BA670−92602−13 (Post−Mod).

A PRE−MOD

1

NOTES

1. Left side shown,

 right side opposite.

2. For Aircraft 10150 thru 10226, 10228

 and 15024 thru 15039 pre−SB

 670BA−27−022.

1

A POST−MOD

 
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 36 of 45

Dec 12/2013

Revision C, Feb 13/2015

Rigging Pins − Removal

Figure 9 (Sheet 1 of 1)

ba7610a01.cgm, sc/kp, July 16, 2014

LEGEND

P. Rigging pin.

NOTE

Left side shown,

right side opposite.

A

CONTROL ROD

(REF)

P2

BEARING

ROD END

(REF)

B

A

LOAD LIMITER

(REF)

CONTROL ROD

(REF)

B

C

AFT LEVER

ASSEMBLY

 (REF)

CONTROL

ROD (REF)

P3 C
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 37 of 45

Dec 12/2013

Revision C, Feb 13/2015

Lever Assemblies − Clearances

Figure 10 (Sheet 1 of 2)

ba8127a01.cgm, cr, 013−nov−2013

0.250 in. (6.35 mm)

MINIMUM

BL0.00

CONTROL

ROD (REF)

AFT LEVER

ASSEMBLY

(REF)

CONTROL

ROD (REF)

VIEW LOOKING FORWARD

LOWER

SKIN

(REF)

A

AFT LEVER

ASSEMBLY

(REF)

0.250 in.

(6.35 mm)

MINIMUM

NOTE:

Hardware are not

shown for clarity.

B

B A

B B

FASTENER

(REF)

C

C
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 38 of 45

Dec 12/2013

Revision C, Feb 13/2015

Lever Assemblies − Clearances

Figure 10 (Sheet 2 of 2)

b8127a02.cgm, cr, 13−nov−2013

C C

BL0.00

HORIZONTAL

STABILIZER

PIVOT FITTING

(REF)

0.200 in.

(5.08 mm)

MINIMUM

0.200 in.

(5.08 mm)

MINIMUM

FORWARD LEVER

ASSEMBLY (REF)

VIEW LOOKING UP

LINK

ASSEMBLY

(REF)
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 39 of 45

Dec 12/2013

Revision C, Feb 13/2015

Idler Aft Bracket − Modification

Figure 11 (Sheet 1 of 1)

ba8260a01.cgm, kl, 15 July 2014

A

B

LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE

B

LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE

2

LEGEND

1. Idler aft bracket

 AV670−21569−009 (LH),

 AV670−21569−010 (RH),

 KBA670−93707−3 (LH, Post−Mod),

 KBA670−93707−4 (RH, Post−Mod).

2. Idler aft bracket

 AV670−21569−009SB (LH),

 AV670−21569−010SB (RH),

 KBA670−93707−3 (LH, Post−Mod),

 KBA670−93707−4 (RH, Post−Mod).

3. Bolt.

1

A

B

3

CANTED

RIB (REF)
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 40 of 45

Dec 12/2013

Revision C, Feb 13/2015

3. MATERIAL INFORMATION

A. Kit Information

Kit Contents:

KIT 670BA27062K1 

PART NUMBER QTY NAME ALTERNATE PARTS NOTES

AV670−21569−009 1 Idler bracket assembly AV670−21569−009SB [1]

AV670−21569−010 1 Idler bracket assembly AV670−21569−010SB [2]

B0202013C1614−16 2 Washer − −

B0203011L4 8 Nut, self-locking − −

B0203011L5 4 Nut, self-locking − −

B0309008−04−027 2 Bushing, straight − −

B0309008−05−006 2 Bushing, straight − −

B0309008−05−040 2 Bushing, straight − −

BA670−93722−3 2 Link assembly − −

BA670−93787−3 2 Riveted (aft) lever

assembly

BA670−93787−951 −

BA698−93725−3 2 Bolt − −

BA698−93726−3 2 Washer − −

MS14145L4 2 Nut, self-locking − −

MS20002C4 2 Washer, countersunk − −

MS21042L3 12 Nut, self-locking − −

MS21042L4 2 Nut, self-locking − −

MS21083C6 2 Nut, self-locking − −

MS24665−153 14 Cotter pin − −

NAS1149E0432R 2 Washer − −

NAS1149E0463P 4 Washer − −

NAS1149E0463R 2 Washer − −
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 41 of 45

Dec 12/2013

Revision C, Feb 13/2015

PART NUMBER NOTES QTY NAME ALTERNATE PARTS

NAS1149E0563P 4 Washer − −

NAS1423C4 8 Nut − −

NAS2814C15DP 2 Bolt − −

NAS559−1 4 Locking device − −

NAS620C416P 2 Washer − −

NAS6304−17D 2 Bolt − −

NAS6304−8D 2 Bolt − −

NAS6304U21D 2 Bolt − −

NAS6305−27D 4 Bolt − −

NAS76A4−004P 2 Bushing − −

NAS76A4−009P 2 Bushing − −

S10008−782A 2 Bushing, straight − −

The kit can contain more hardware and/or material than necessary.

[1] Modification and re−identification to P/N KBA670−93707−3 by this SB.

[2] Modification and re−identification to P/N KBA670−93707−4 by this SB.

KIT 670BA27062K2 

PART NUMBER QTY NAME ALTERNATE

PARTS NOTES

AV670−21569−009SB 1 Idler bracket assembly − [1]

AV670−21569−010SB 1 Idler bracket assembly − [2]

Can be necessary until P/N AV670−21569−009SB and P/N

 AV670−21569−010SB replace P/N AV670−21569−009 and P/N

 AV670−21569−010 in kit 670BA27062K1 or later kit revisions.

[1] Modification and re−identification to P/N KBA670−93707−3 by this SB.

[2] Modification and re−identification to P/N KBA670−93707−4 by this SB.
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 42 of 45

Dec 12/2013

Revision C, Feb 13/2015

KIT 670BA27062K90 

PART NUMBER QTY NAME ALTERNATE

PARTS NOTES

670BA27062K90−1 1 Fwd Elevator Lever −

Reamers Kit

− −

Refer to paragraph 1.H. for special terms and conditions.

NOTE: For permitted superseded parts, refer to the Parts Supersession Cross

References Lists at www.iflybombardier.com under Resources −

Engineering Documents.

NOTE: Some parts listed in the kit content of this service bulletin are supplied in

a temporary condition of supply configuration. These parts are identified

with a −SB, /SB, SB or other suffix after the Bombardier engineering part

number. When the parts are installed, with the instructions given in the

Accomplishment Instructions of this service bulletin, the parts agree with

the requirements of the engineering configuration. Refer to the SB

Introduction document for more explanation.

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

− As necessary Paper, abrasive,

aluminum oxide, 100−

to 400-grit, wet or dry

05−176 

Scotchbrite

− As necessary Cloth clean, dry,

lint-free cotton

05−332 

− As necessary Cutting fluid Commercially

available

6856K As necessary Corrosion inhibitor,

Mastinox

13−001 SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 43 of 45

Dec 12/2013

Revision C, Feb 13/2015

SPECIFICATION REFERENCE QTY NAME

BAMS 552−010,

type 1

As necessary Compound,

non-chromate,

corrosion inhibiting,

jointing

15−035 

CA 1000

BAMS 565−001 As necessary Fluid resistant epoxy

primer, color green

13−006 

BAMS 565−002 As necessary Fluid resistant Enamel

for aircraft interior

07−019 

(Color grey

#16473 per

FED−STD−595)

CMS 516−07 As necessary Marker, ink 05−041 

CMS 565−02 As necessary Fluid resistant Enamel

for aircraft interior,

clear

16−012 

MIL−C−81706,

class 1A

As necessary Compound, chemical

conversion, for coating

aluminum and

aluminum alloys

(Alodine 1200S)

05−025 

MS24665−153 As necessary Cotter pin Commercially

available

MS20995C32 As necessary Lockwire,

corrosion-resistant

steel

05−004 

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.
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 44 of 45

Dec 12/2013

Revision C, Feb 13/2015

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.

SPECIAL TOOLS AND EQUIPMENT

PART NUMBER QTY NAME ALTERNATE PARTS

G601R270001−1 1 Kit − Flight Controls

Rigging Pins

−

Refer to the Illustrated Tool and Equipment Manual (ITEM)

NOTE: To complete this list of special tools and equipment, refer to the different

tasks that are given as references in this service bulletin.

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.

PRE-SB

PART NUMBER

NAME QTY DC POST-SB 

PART NUMBER

NAME

AV670−21569−001

or

AV670−21569−005

Idler

bracket, aft 1 SAL KBA670−93707−3 [1]

Idler

bracket,

aft

AV670−21569−002

or

AV670−21569−006

Idler

bracket, aft 1 SAL KBA670−93707−4 [2]

Idler

bracket,

aft

BA670−92367−3

Lever

assembly,

forward

2 RWK KBA670−93707−5

Lever

assembly,

forward

BA670−92602−39 Control rod,

fixed 2 DIS BA670−93722−3 Linkassembly

BA670−93786−1,

BA670−93772−1, or

BA670−93772−3

Lever

assembly,

aft

2 DIS BA670−93787−3 or

BA670−93787−951

Lever

assembly,

aft
SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062

Page 45 of 45

Dec 12/2013

Revision C, Feb 13/2015

PRE-SB

PART NUMBER

POST-SB NAME

PART NUMBER

NAME DCQTY

BA670−30000−8955,

BA670−30000−9993,

BA690−30000−496,

or

BA690−30000−4989

Control rod 2 RWK BA670−92602−13 Control

rod

[1] P/N AV670−21569−009 was installed during the incorporation of the initial issue

 or Revision A of this service bulletin.

[2] P/N AV670−21569−010 was installed during the incorporation of the initial issue

 or Revision A of this service bulletin.

Disposition code (DC):

DIS: Discard Part.

RWK: Rework part as shown in this service bulletin.

SAL: Salvage.

1 
the evolution of mobility

THANK YOU FOR YOUR COMMENTS

SERVICE BULLETIN FEEDBACK FORM/COMPLIANCE SHEET

(YOUR COMMENTS HELP US WRITE BETTER SERVICE BULLETINS)

Service Bulletin No.: 670BA-27-062 Revision: C

Aircraft Serial Number: Date:

STRONGLY

DISAGREE

DISAGREE AGREE STRONGLY

AGREE

Instructions to do the service bulletin are

accurate.

Comments:

- - - -

Figure(s), picture(s), and/or Appendix

were helpful to do the service bulletin.

Comments:

- - - -

Part(s) or kit(s) agreed with the service

bulletin requirement.

Comments:

- - - -

The service bulletin was accomplished

within the estimated time given.

Comments:

- - - -

Overall, I was satisfied with this service

bulletin.

Comments:

- - - -

Operator: Service Centre:

Name: Telephone or Fax:

FAX your comments or feedback to (450) 476---7300

or e-mail to crj_sb_evaluation_form@aero.bombardier.com