Flight Controls − Rudder Travel Limiting System − Inspection of the Return

Springs and the Primary Actuator of the Rudder Travel Limiter

This page transmits:

Revision A of Service Bulletin 670BA−27−055,

pages 1 thru 24, dated Aug 06/2010.

The changes in this revision have no effect on aircraft that have incorporated a

previous issue of this service bulletin.

Reason:

Revised Material Information, paragraph 3., to:

In the Consumables Information, change the Specification and the Reference

of the polyurethane topcoat.

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

technical content.

Document Instructions:

Discard the copy of Service Bulletin 670BA−27−055, dated May 11/2010. Replace with the

copy attached.

Service Bulletin History:

Initial issue, dated May 11/2010.

SERVICE BULLETIN 670BA−27−055

S.B. 670BA−27−055

Page 1 of 1

Aug 06/2010

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

CL−600−2C10, CL−600−2D15 and CL−600−2D24

CANADAIR REGIONAL JET (CRJ) AIRCRAFT

SUBJECT:
Flight Controls − Rudder Travel Limiting System − Inspection of the Return

Springs and the Primary Actuator of the Rudder Travel Limiter

1. PLANNING INFORMATION

A. Effectivity

(1) Aircraft Affected:

Service Bulletin: CL−600−2C10 Canadair Regional Jet (CRJ)

Aircraft Serial Numbers 10003 thru 10999.

Production: There is no production effectivity at this time.

Service Bulletin: CL−600−2D15 Canadair Regional Jet (CRJ) and

CL−600−2D24 Canadair Regional Jet (CRJ)

Aircraft Serial Numbers 15001 thru 15990.

Production: There is no production effectivity at this time.

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 Bulletin(s). Before you do this

bulletin, examine all STC, STA or equivalent action changes to

make sure this bulletin can be completed.

SERVICE BULLETIN

ATA SYSTEM: 27−25 NUMBER: 670BA−27−055

S.B. 670BA−27−055

Page 1 of 24

May 11/2010

Revision A, Aug 06/2010

Technical

Publications

THIS SERVICE BULLETIN IS SENT TO EACH OPERATOR. IF THE OPERATOR HAS LEASED AIRCRAFT,

THIS SERVICE BULLETIN MUST BE SENT TO THE LESSEE. IF THE OPERATOR HAS SOLD AIRCRAFT OR

TRANSFERRED SPARES IN THE LAST SIX MONTHS, THIS SERVICE BULLETIN MUST BE SENT TO THE

NEW OWNER, UNLESS CONFIRMATION WAS RECEIVED THAT BOMBARDIER COMMERCIAL AIRCRAFT

DIVISION HAS INCLUDED THE NEW OPERATOR ON THE DISTRIBUTION LIST.

SUBJECT:
B. Reason

(1) Condition

It is possible for the return springs of the rudder travel limiter to break

because of fatigue or chafing by the primary actuator.

(2) Evidence

Return springs broke during endurance test.

(3) Objective/Benefit

This service bulletin gives the procedure to do a detailed visual inspection of

the return springs and the primary actuator casing of the rudder travel limiter.

This will make sure that the return springs are installed correctly on the

rudder travel limiter.

C. Description

The rudder is moved to the neutral position. A rigging pin is installed in the rudder

travel limiter. The electrical power is removed from the aircraft. Circuit breakers

are opened. Access panels are removed.

A detailed visual inspection of the return springs and the casing of the primary

actuator is done.

The rigging pin is removed from the rudder travel limiter. Circuit breakers are

closed. If return springs are replaced, applicable return−to−service tests are

done. Access panels are installed.

D. Compliance

Recommended Service Bulletin.

For aircraft that have 4000 flight hours or less, Bombardier recommends that this

service bulletin be done before the aircraft have 6000 flight hours, unless

otherwise directed by the airworthiness authority of the operator.

For aircraft that have more than 4000 flight hours, Bombardier recommends that

this service bulletin be done no more than 2000 flight hours from the release date

on this service bulletin, unless otherwise directed by the airworthiness authority

of the operator.

SERVICE BULLETIN 670BA−27−055

S.B. 670BA−27−055

Page 2 of 24

May 11/2010

Revision A, Aug 06/2010
Bombardier recommends that this service bulletin be repeated every 6000 flight

hours from the initial inspection date of this service bulletin, unless otherwise

directed by the airworthiness authority of the operator.

NOTE: It is not necessary to do Service Bulletin 670BA−27–047, Flight Controls

− Rudder Travel Limiting System − Replacement of the Return Springs

and Pulleys and Removal of the Torsion Spring, when this service

bulletin is done.

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 an estimate for direct labor done by an

experienced crew on an aircraft prepared for maintenance.

This estimate does not include the time necessary for:

− Administrative functions such as planning, liaison, 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 any on−site labor assistance, please speak with a Fleet Services

representative for a quote. The Fleet Services team can be contacted

via the CRC at 514−855−8500 or email at

thd.crj@aero.bombardier.com.

It will take an estimated 6.5 man−hours to complete this service bulletin. The

man−hours are divided as shown in the table that follows :

SERVICE BULLETIN 670BA−27−055

S.B. 670BA−27−055

Page 3 of 24

May 11/2010

Revision A, Aug 06/2010
TASK MAN−HOURS

(1) Job Set−Up 1.0

(2) Procedure 0.5 [1] [2]

(3) Test 4.0 [3]

(4) Job Close−Out 1.0

NOTE: [1] The man−hours given are for the inspection only. Add 3.0

man−hours to replace the return springs and the primary actuator.

NOTE: [2] The man−hours given are for the inspection only. Add 2.0

man−hours to replace the return springs.

NOTE: [3] The return−to−service tests are only applicable when return springs

are replaced.

G. Material − Price and Availability

(1) There are no kits for this service bulletin. If necessary, use the parts in the

table that follows to do this service bulletin. The parts are available from

Bombardier commercial aircraft. Refer to the paragraph(s) below for terms

and conditions.

For Rudder Travel Limiter P/N KBA670−93402−1, KBA670−93402−3, KBA670−93402−5 and

BA670−93470−15

PART NUMBER NAME QUANTITY

BA670−93465−1 Spring, Return Maximum two for each

aircraft

For Rudder Travel Limiter P/N BA670−30000−7969, BA670−93470−7, BA670−93470−9,

BA670−93470−13, BA670−93470−963, BA670−93470−979, BA670−93470−981,

BA670−93470−987, BA670−93470−2001, KBA670−93470−1 and KBA670−93470−3

PART NUMBER NAME QUANTITY

E0650−069−2750S Spring, Return Maximum two for each

aircraft

SERVICE BULLETIN 670BA−27−055

S.B. 670BA−27−055

Page 4 of 24

May 11/2010

Revision A, Aug 06/2010
For all Aircraft

PART NUMBER NAME QUANTITY

BA670−93490−1 or

BA670−93490−3

Actuator, Linear Maximum one for each

aircraft

(2) Please send a purchase order to the address below to schedule the part(s):

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 your 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.

(1) 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−27−1217−00, Revision B.

− Aircraft Maintenance Manual (AMM), CSP B−001.

− Structural Repair Manual (SRM), CSP B−008.

SERVICE BULLETIN 670BA−27−055

S.B. 670BA−27−055

Page 5 of 24

May 11/2010

Revision A, Aug 06/2010
− For Bombardier reference only: PCA 73983.

L. Other Publications Affected

None.

M. Relationship Chart

Not applicable.

SERVICE BULLETIN 670BA−27−055

S.B. 670BA−27−055

Page 6 of 24

May 11/2010

Revision A, Aug 06/2010
2. ACCOMPLISHMENT INSTRUCTIONS

A. Job Set−Up

(1) Reference Information

REFERENCE DESIGNATION

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

Maintenance

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

AMM 20−51−00−000−801 Removal of Cotter Pins

AMM 20−51−00−400−801 Installation of Cotter Pins

AMM 24−00−00−861−802 Remove Electrical Power from the

Aircraft

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

Precautions

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

AMM 27−21−00−710−801 Operational Test of the

Rudder−Control−System

AMM 27−21−00−864−801 Move the Rudder Control Surface in

the Neutral Position

AMM 27−25−00−710−801 Operational Test of the Rudder

Travel Limiter

AMM 27−25−03−000−801 Removal of the Rudder Travel

Limiter Actuator

AMM 27−25−03−400−801 Installation of the Rudder Travel

Limiter Actuator

AMM 27−25−03−820−801 Rigging Check of the Rudder Travel

Limiter Actuator

AMM 27−61−05−740−801 Self Test of the Spoiler and

Stabilizer Control Units

AMM 55−32−32−000−801 Removal of the Elevator−Quadrant

Access Door (325EL/325ER)

SERVICE BULLETIN 670BA−27−055

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Revision A, Aug 06/2010
REFERENCE DESIGNATION

AMM 55−32−32−000−802 Removal of the Turnbuckle

Autopilot−Controls Access Door

(325DL)

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

Access Door (325EL/325ER)

AMM 55−32−32−400−802 Installation of the Turnbuckle

Autopilot−Controls Access Door

(325DL)

NDT M51−20−009−210 Visual – Inspection Procedures

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

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

(AMM 12−00−00−867−801).

(3) Obey all the electrical/electronic safety precautions (AMM

24−00−00−910−801).

(4) Obey all the flight−control safety precautions (AMM 27−00−00−910−802).

(5) Remove the access panels that follow:

PANEL NAME REFERENCE

325DL Turnbuckle Autopilot−Controls

Access Door

AMM 55−32−32−000−802

325EL Elevator−Quadrant Access Door AMM 55−32−32−000−801

(6) Move the rudder control surface in the neutral position (AMM

27−21−00−864−801).

SERVICE BULLETIN 670BA−27−055

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Revision A, Aug 06/2010
Refer to Figure 1.

(7) Install rigging pin P1 in the rudder travel limiter.

(8) Remove electrical power from the aircraft (AMM 24−00−00−861−802).

(9) Open, safety, and tag the circuit breakers that follow:

CB−PANEL CB NO. NAME

CBP−1 F1 SSCU 1 CH A

CBP−1 F2 P FEEL 1 RTL 1

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 SSCU2 CH A

CBP−2 LOWER R4 SSCU2 CH B

CBP−2 LOWER R5 P FEEL 2 RTL 2

(10) Install warning placards on the rudder pedals to give warning not to move

the rudder control surface.

(11) Install warning placards on the control columns to give warning not to

operate or move the flight controls.

B. Procedure

Refer to Figure 1 .

(1) Do a detailed visual inspection of the casing of the primary actuator (1) for

signs of chafing and make sure that the return springs (2) are not broken as

follows:

SERVICE BULLETIN 670BA−27−055

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Revision A, Aug 06/2010
(a) If there is no sign of chafing on the casing of the primary actuator (1)

and the return springs (2) are not broken, go to the Job Close−Out.

(b) If there is a sign of chafing on the casing of the primary actuator (1), do

as follows:

1 If damage does not go through the casing of the primary actuator

(1), do the steps that follow:

a Disconnect the electrical connector A203P1 (24) from the

receptacle.

b Install protective covers on the electrical connector A203P1

(24) and on the receptacle of the primary actuator (1).

c Remove the nut (3), the lock washer (4), the washer (5) and

the bonding jumper (6).

d Remove the spring (7) from the RTL spring bracket as follows:

1) Remove and discard the cotter pin (8).

WARNING: BE CAREFUL WHEN YOU REMOVE THE

SPRING. THE SPRING CAN HAVE LOAD AND

CAUSE INJURIES TO PERSONS.

2) Hold the pulley (9) and the spring (7).

3) Remove the nut (10), the washers (11) and the bolt (12).

4) Remove the pulley (9) from the spring (7).

e Remove the bottom end of the primary actuator (1) as follows:

1) Remove the nut (13), the washer (14) and the screw (15).

2) Remove and discard the cotter pin (17).

3) Hold the primary actuator (1).

For Aircraft 10003−10265 and 15001−15181 Pre−SB 670BA−27−047

4) Remove the nut (18), the washers (19) and (20), the

springs (23), the bushing (21) and the bolt (22).

5) Hold the anti−rotation pad (16) when you move the bottom

end of the primary actuator (1) from the limiter arm.

SERVICE BULLETIN 670BA−27−055

S.B. 670BA−27−055

Page 10 of 24

May 11/2010

Revision A, Aug 06/2010
For Aircraft 10003−10265 and 15001−15181 Post−SB 670BA−27−047 and for Aircraft

10266−10999 and 15182−15990

6) Remove the nut (18), the washers (19) and (20), the

bushing (21) and the bolt (22).

7) Hold the anti−rotation pad (16) when you move the bottom

end of the primary actuator (1) from the limiter arm.

For all Aircraft

8) Move the bottom end of the primary actuator (1) and

attach it to the adjacent structure.

f Apply fluid−resistant primer to the damaged area on the casing

of the primary actuator (1).

g Apply polyurethane topcoat to the damaged area on the casing

of the primary actuator (1).

h Remove and discard the return springs (2).

For Rudder Travel Limiter P/N KBA670−93402−1, KBA670−93402−3, KBA670−93402−5 and

BA670−93470−15

i Install new return springs (2) P/N BA670−93465−1.

For Rudder Travel Limiter P/N BA670−30000−7969, BA670−93470−7, BA670−93470−9,

BA670−93470−13, BA670−93470−963, BA670−93470−979, BA670−93470−981,

BA670−93470−987, BA670−93470−2001, KBA670−93470−1 and KBA670−93470−3

j Install new return springs (2) P/N E0650−069−2750S.

For all Aircraft

k Connect the primary actuator (1) of the rudder travel limiter as

follows:

1) Make sure that the primary actuator (1) of the rudder travel

limiter is correctly rigged as follows:

a) Put the primary actuator (1), the bushing (21) and the

bolt (22) in position temporarily.

b) Make sure that it is possible to install the bolt (22) and

the bushing (21).

SERVICE BULLETIN 670BA−27−055

S.B. 670BA−27−055

Page 11 of 24

May 11/2010

Revision A, Aug 06/2010
c) If it is not possible to install the bolt (22) and the

bushing (21), do the rigging check of the

rudder−travel limiter actuator (AMM

27−25−03−820−801).

2) Continue the installation of the primary actuator (1) as

follows:

a) Put the anti−rotation pad (16) and the bottom end of

the primary actuator (1) in position on the rudder

travel limiter.

b) Align the holes in the anti−rotation pad (16) with the

holes in the limiter arm.

c) Clean the bushing (21) with solvent.

d) Apply Mastinox or fluid−resistant primer to the

bushing (21).

For Aircraft 10003−10265 and 15001−15181 Pre−SB 670BA−27−047

e) Put the bushing (21) and the springs (23) in position in

the limiter arm.

For Aircraft 10003−10265 and 15001−15181 Post−SB 670BA−27−047 and for Aircraft

10266−10999 and 15182−15990

f) Put the bushing (21) in position in the limiter arm.

For all Aircraft

g) Make sure that the link assemblies align with the

bushing (21).

h) Install the bolt (22), the washers (19) and (20), and

the nut (18).

i) Attach the anti−rotation pad (16) with the bolt (15), the

washer (14) and the nut (13).

j) Safety the nut (18) with the cotter pin (17).

3) Install the spring (7) on the RTL spring bracket as follows:

a) Attach the pulley (9) and the spring (7) together.

SERVICE BULLETIN 670BA−27−055

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Revision A, Aug 06/2010
WARNING: BE CAREFUL WHEN YOU INSTALL THE

SPRING. THE SPRING CAN HAVE LOAD

AND CAUSE INJURIES TO PERSONS.

b) Install the pulley (9) and the spring (7) on the RTL

spring bracket with the bolt (12), the washers (11) and

the nut (10).

c) Safety the nut (10) with the cotter pin (8).

4) Install the bonding jumper (6), the washer (5), the lock

washer (4) and the nut (3).

5) Remove the protective covers from the electrical

connector A203P1 (24) and the receptacle of the primary

actuator (1).

6) Connect the electrical connector A203P1 (24) to the

receptacle.

l Go to the Job Close−Out.

2 If the damage goes through the casing of the primary actuator (1),

do the steps that follow:

a Remove the A203 primary actuator (1) (AMM

27−25−03−000−801).

b Remove and discard the return springs (2).

For Rudder Travel Limiter P/N KBA670−93402−1, KBA670−93402−3, KBA670−93402−5 and

BA670−93470−15

c Install the new return springs (2) P/N BA670−93465−1.

For Rudder Travel Limiter P/N BA670−30000−7969, BA670−93470−7, BA670−93470−9,

BA670−93470−13, BA670−93470−963, BA670−93470−979, BA670−93470−981,

BA670−93470−987, BA670−93470−2001, KBA670−93470−1 and KBA670−93470−3

d Install the new return springs (2) P/N E0650−069−2750S.

For all Aircraft

e Install the new A203 primary actuator (1) (AMM

27−25−03−400−801).

SERVICE BULLETIN 670BA−27−055

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Revision A, Aug 06/2010
(c) If there is no sign of chafing on the casing of the primary actuator (1)

and the return spring(s) (2) is broken, do the steps that follow:

1 Disconnect the electrical connector A203P1 (24) from receptacle.

2 Install protective covers on the electrical connector A203P1 (24)

and on the receptacle of the primary actuator (1).

3 Remove the spring (7) from the RTL spring bracket as follows:

a Remove and discard the cotter pin (8).

WARNING: BE CAREFUL WHEN YOU REMOVE THE SPRING.

THE SPRING CAN HAVE LOAD AND CAUSE

INJURIES TO PERSONS.

b Hold the pulley (9) and the spring (7).

c Remove the nut (10), the washers (11) and the bolt (12).

d Remove the pulley (9) from the spring (7).

4 Remove the bottom end of the primary actuator (1) as follows:

a Remove the nut (13), the washer (14) and the screw (15).

b Remove and discard the cotter pin (17).

c Hold the primary actuator (1).

For Aircraft 10003−10265 and 15001−15181 Pre−SB 670BA−27−047

d Remove the nut (18), the washers (19) and (20), the springs

(23), the bushing (21) and the bolt (22).

e Hold the anti−rotation pad (16) when you move the bottom end

of the primary actuator (1) from the limiter arm.

For Aircraft 10003−10265 and 15001−15181 Post−SB 670BA−27−047 and for Aircraft

10266−10999 and 15182−15990

f Remove the nut (18), the washers (19) and (20), the bushing

(21) and the bolt (22).

g Hold the anti−rotation pad (16) when you move the bottom end

of the primary actuator (1) from the limiter arm.

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Revision A, Aug 06/2010
For all Aircraft

h Move the bottom end of the primary actuator (1) and attach it to

the adjacent structure.

5 Remove and discard the broken return spring(s) (2).

For Rudder Travel Limiter P/N KBA670−93402−1, KBA670−93402−3, KBA670−93402−5 and

BA670−93470−15

6 Install the new return spring(s) (2) P/N BA670−93465−1.

For Rudder Travel Limiter P/N BA670−30000−7969, BA670−93470−7, BA670−93470−9,

BA670−93470−13, BA670−93470−963, BA670−93470−979, BA670−93470−981,

BA670−93470−987, BA670−93470−2001, KBA670−93470−1 and KBA670−93470−3

7 Install the new return spring(s) (2) P/N E0650−069−2750S.

For all Aircraft

8 Connect the primary actuator (1) of the rudder travel limiter as

follows:

a Make sure that the primary actuator (1) of the rudder travel

limiter is correctly rigged as follows:

1) Put the primary actuator (1), the bushing (21) and the bolt

(22) in position temporarily.

2) Make sure that it is possible to install the bolt (22) and the

bushing (21).

3) If it is not possible to install the bolt (22) and the bushing

(21), do the rigging check of the rudder−travel limiter

actuator (AMM 27−25−03−820−801).

b Continue the installation of the primary actuator (1) as follows:

1) Put the anti−rotation pad (16) and the bottom end of the

primary actuator (1) in position on the rudder travel limiter.

2) Align the holes in the anti−rotation pad (16) with the holes

in the limiter arm.

3) Clean the bushing (21) with solvent.

SERVICE BULLETIN 670BA−27−055

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Revision A, Aug 06/2010
4) Apply Mastinox or fluid−resistant primer to the bushing

(21).

For Aircraft 10003−10265 and 15001−15181 Pre−SB 670BA−27−047

5) Put the bushing (21) and the springs (23) in position in the

limiter arm.

For Aircraft 10003−10265 and 15001−15181 Post−SB 670BA−27−047 and for Aircraft

10266−10999 and 15182−15990

6) Put the bushing (21) in position in the limiter arm.

For all Aircraft

7) Make sure that the link assemblies align with the bushing

(21).

8) Install the bolt (22), the washers (19) and (20), and the nut

(18).

9) Attach the anti−rotation pad (16) with the bolt (15), the

washer (14) and the nut (13).

10) Safety the nut (18) with the cotter pin (17).

c Install the spring (7) on the RTL spring bracket as follows:

1) Attach the pulley (9) and the spring (7) together.

WARNING: BE CAREFUL WHEN YOU INSTALL THE

SPRING. THE SPRING CAN HAVE LOAD AND

CAUSE INJURIES TO PERSONS.

2) Install the pulley (9) and the spring (7) on the RTL spring

bracket with the bolt (12), the washers (11) and the nut

(10).

3) Safety the nut (10) with the cotter pin (8).

d Install the bonding jumper (6), the washer (5), the lock washer

(4) and the nut (3).

e Remove the protective covers from the electrical connector

A203P1 (24) and the receptacle of the primary actuator (1).

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f Connect the electrical connector A203P1 (24) to the

receptacle.

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Revision A, Aug 06/2010
ba6402a01.cgm

A

ROTATED AT 90° CLOCKWISE

B

B

1

2

A

LEGEND

1. Primary actuator (BA670−93490−1

 or BA670−93490−3).

2. Return springs (BA670−93465−1

 or E0650−069−2750S).

CASING (REF.)

SERVICE BULLETIN 670BA−27−055

Primary Actuator of the Rudder Travel Limiter

Figure 1 (Sheet 1 of 3)

S.B. 670BA−27−055

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Revision A, Aug 06/2010
ba6401a02.cgm

D

A

NOTES

Installed on aircraft 10003−10265 and 15001−15181 Pre−SB 670BA−27−047 only.

MS24665−132 is installed on aircraft 10003−10265 and 15001−15181 Pre−SB 670BA−27−047.

MS24665−69 is installed on aircraft 10003−10265 and 15001−15181 Post−SB 670BA−27−047 and

10266−10999 and 15182−15990.

1

2

 1. Primary actuator.

 2. Return springs (BA670−93465−1

 or E0650−069−2750S).

13. Nut.

14. Washer.

15. Screw.

16. Anti−rotation pad.

17. Cotter pin

 MS24665−69 or

 MS24665−132.

18. Nut.

19. Washer.

20. Washer.

21. Bushing.

22. Bolt.

23. Spring.

LEGEND

22 15

21

LINK

ASSEMBLY

(REF)

20

18

17

19

23

1

16

14

13

LINK

ASSEMBLY

(REF)

D

LIMITER

ARM

(REF)

1

2

2

SERVICE BULLETIN 670BA−27−055

Primary Actuator of the Rudder Travel Limiter

Figure 1 (Sheet 2 of 3)

S.B. 670BA−27−055

Page 19 of 24

May 11/2010

Revision A, Aug 06/2010
ba6401a01.cgm

3

4

5

24

1

6

SECONDARY

ACTUATOR (REF)

RECEPTACLE

(REF)

P1

A

B

C

A

B

C

1

12

9

11

11

10 8 7

RTL SPRING

BRACKET (REF)

LEGEND

 1. Primary actuator.

 3. Nut.

 4. Lock washer. 

 5. Washer.

 6. Bonding jumper.

 7. Spring.

 8. Cotter pin MS24665−69.

 9. Pulley.

10. Nut.

11. Washer.

12. Bolt.

24. Electrical connector A203P1.

 P. Rigging pin.

SERVICE BULLETIN 670BA−27−055

Primary Actuator of the Rudder Travel Limiter

Figure 1 (Sheet 3 of 3)

S.B. 670BA−27−055

Page 20 of 24

May 11/2010

Revision A, Aug 06/2010
C. Job Close−Out

(1) Remove all tools, equipment, and unwanted materials from the work area.

Refer to Figure 1.

(2) Remove the rigging pin P1 from the rudder travel limiter.

(3) Remove the tags and close the circuit breakers that follow:

CB−PANEL CB NO. NAME

CBP−1 F1 SSCU 1 CH A

CBP−1 F2 P FEEL 1 RTL 1

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 SSCU2 CH A

CBP−2 LOWER R4 SSCU2 CH B

CBP−2 LOWER R5 P FEEL 2 RTL 2

(4) Install the access panels that follow:

PANEL NAME REFERENCE

325DL Turnbuckle Autopilot−Controls

Access Door

AMM 55−32−32−400−802

325EL Elevator−Quadrant Access Door AMM 55−32−32−400−801

SERVICE BULLETIN 670BA−27−055

S.B. 670BA−27−055

Page 21 of 24

May 11/2010

Revision A, Aug 06/2010
(5) Remove warning placards from the rudder pedals.

(6) Remove warning placards from the control columns.

(7) If return springs are replaced, do an operational test of the rudder travel

limiter (AMM 27−25−00−710−801).

(8) If return springs are replaced, do an operational test of the

rudder−control−system (AMM 27−21−00−710−801).

(9) If return springs are replaced, do a self test of the spoiler and stabilizer

control units (AMM 27−61−05−740−801).

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

logbook(s): "Service Bulletin 670BA−27−055, Revision A, Flight Controls −

Rudder Travel Limiting System − Inspection of the Return Springs and the

Primary Actuator of the Rudder Travel Limiter, incorporated."

SERVICE BULLETIN 670BA−27−055

S.B. 670BA−27−055

Page 22 of 24

May 11/2010

Revision A, Aug 06/2010
3. MATERIAL INFORMATION

A. Kit Information

None.

B. Consumable Information

The materials that follow are necessary to do this service bulletin and can be ordered

from Bombardier or purchased directly from industry sources. If the material is

ordered from Bombardier, there can be some lead time because of shelf life of the

material.

CONSUMABLES

SPECIFICATION QUANTITY NAME REFERENCE

BAMS 565−002 As

necessary

Polyurethane

Topcoat,

Fluid−Resistant

(Color grey

(16473),

FED−STD

595B)

07−019 [1]

6856K As

necessary

Mastinox,

Corrosion

Inhibitor

13−001 [1]

BAMS 565–001 As

necessary

Fluid−Resistant

Epoxy Primer

13–006 [1]

[1] Refer to AMM 51−31−00−992−801.

NOTE: To complete this list of consumables, refer to the different tasks given as

references in this service bulletin.

C. Special Tools and Equipment

SERVICE BULLETIN 670BA−27−055

S.B. 670BA−27−055

Page 23 of 24

May 11/2010

Revision A, Aug 06/2010
SPECIAL TOOLS AND EQUIPMENT

PART NUMBER QUANTITY NAME ALTERNATE

PART(S)

G601R270001−1 1 Pins Kit − Rigging or equivalent

[1] Refer to the Illustrated Tool and Equipment Manual (CSP B−007).

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

tasks given as references in this service bulletin.

D. Disposition of Parts

Not applicable.

SERVICE BULLETIN 670BA−27−055

S.B. 670BA−27−055

Page 24 of 24

May 11/2010

Revision A, Aug 06/2010
THANK YOU FOR ANSWERING THIS EVALUATION FORM 

UPON COMPLETION OF THIS EVALUATION FORM/COMPLIANCE SHEET, FAX TO 

450-476-7300

SERVICE BULLETIN EVALUATION FORM/COMPLIANCE SHEET 

(YOUR IDEAS WILL HELP US PROVIDE BETTER BULLETINS) 

SERVICE BULLETIN : 670BA-27-055 ISSUE: A

 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