SB A601R---27---144

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Oct 02/2012

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

CL ---600 ---2B19 Canadair Regional Jet (CRJ) Aircraft

ALERT SERVICE BULLETIN A601R ---27 ---144

SUBJECT: Flight Controls --- Pitch Feel Simulator --- Functional Test of the Pilot Input

Lever of the Pitch Feel Simulator (PFS) P/N 601R92300 ---3 and P/N

601R92300 ---5

This page transmits:

Revision E of Alert Service Bulletin A601R --- 27 --- 144,

pages 1 thru 12, dated Oct 02/2012

and

Revision A of Appendix A, pages A1 thru A2, dated Dec 20/2006.

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

incorporated a previous issue of this service bulletin.

Reason:

Revised Planning Information, paragraph 1., to:

Remove Aircraft 8111 from the Aircraft Affected paragraph.

Instructions:

Discard the copy of Alert Service Bulletin A601R --- 27 --- 144, Revision D, dated Nov

25/2011. Replace with the copy attached.

KEEP APPENDIX A.

Service Bulletin History:

Initial issue, dated Sep 15/2005.

Revision A, dated Feb 14/2006.

Revision B, dated Dec 20/2006.

Revision C, dated Jul 21/2008.

Revision D, dated Nov 25/2011.

1
SB A601R---27---144

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Sep 15/2005

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ALERT SERVICE BULLETIN

Technical

Publications

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

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 REGIONAL AIRCRAFT DIVISION HAS INCLUDED THE NEW OPERATOR

AIRCRAFT, THIS SERVICE BULLETIN MUST BE SENT TO THE LESSEE. IF THE OPERATOR

ON THE DISTRIBUTION LIST.

ATA SYSTEM: 27 ---31 NUMBER: A601R ---27 ---144

SUBJECT: Flight Controls --- Pitch Feel Simulator --- Functional Test of the Pilot Input

Lever of the Pitch Feel Simulator (PFS) P/N 601R92300 ---3 and

P/N 601R92300 ---5

1. PLANNING INFORMATION

A. Effectivity

(1) Aircraft Affected:

Service Bulletin: CL ---600---2B19 Canadair Regional Jet (CRJ) Aircraft Serial

Numbers 7003 thru 7067, 7069 thru 7990, 8000 thru 8110.

Production: CL ---600---2B19 Canadair Regional Jet (CRJ) Aircraft Serial

Numbers 8111 thru 8999.
SERVICE BULLETIN 601R---27 ---144

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B. Reason

(1) Condition

There is a shear pin installed at the input rod of each PFSs, to limit the shear

load if a jam of the input rod on the elevator system occurs. This shear pin

can have a crack because of fatigue. If the crack increases, the shear pin can

break and cause a decrease in the pitch feel forces.

(2) Evidence

The shear pin on two of the PFS was found broken on aircraft in service.

(3) Objective/Benefit

This service bulletin gives instructions to do a functional test of the pilot input

lever of the pitch feel simulators. This will make sure that the PFSs operate.

C. Description

Circuit breakers are opened. Warning placards and safety devices are installed.

The external AC power is connected. The hydraulic system No.1, No.2 or No.3 is

pressurized. The functional test of the pilot input lever of the PFS is done. The

applicable hydraulic system is depressurized. If applicable, the PFS is replaced

with a serviceable one. If a PFS is replaced, a control-column feel-force and

centering check is done. The safety devices and warning placards are removed. A

report is sent to Bombardier Aerospace and the aircraft is returned to service.

D. Compliance

Alert Service Bulletin. For aircraft that have 4000 flight hours or more, Bombardier

Aerospace recommends that this service bulletin be done no more than 100 flight

hours from the release date on this service bulletin, and repeated every 100 flight

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

NOTE: It is not necessary to do this service bulletin when Service Bulletin

601R---27---139, Flight Controls --- Elevator Control System ---

Replacement of Pitch Feel Simulators (PFS) P/N 601R92300---3 and

P/N601R92300---5 by PFS P/N 601R92300---7 , is done.

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.
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F. Manpower

The man hours given above 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 Aerospace as directly

related to the accomplishment of this procedure.

It will take an estimated 0.25 man-hours to complete this service bulletin. The

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

TASK MAN ---HOURS

(1) Job Set ---Up N/A

(2) Procedure 0.25

(3) Test N/A

(4) Job Close---Out N/A

(5) Cure Time N/A

NOTE: The man-hours for the procedure do not include the hours to replace

damaged parts. Add 1.0 hour if a check for the condition of the input lever

is done.

Bombardier Aerospace does not cover the labor costs to do this service bulletin.
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G. Material --- Price and Availability

To replace a defective PFS, refer to Bombardier service bulletin 601R---27---139.

H. Tooling --- Price and Availability

There are no tool kits for this service bulletin.

I. Weight and Balance

Not changed.

J. Electrical Load Data

Not changed.

K. References

Modsum TC601R18004, Revision C ---1.

Restriction and/or Special Instruction (RSI) C ---A024, Revision F.

Aircraft Maintenance Manual (AMM).

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

Bulletin content.

For Bombardier Aerospace reference only: PCA 04194, 05038, and 06086.

L. Other Publications Affected

None.

M. Relationship Chart

Not applicable.
SERVICE BULLETIN 601R---27 ---144

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2. ACCOMPLISHMENT INSTRUCTIONS

A. Job Set ---Up

Reference Information

REFERENCE DESIGNATION

AMM 12---00---06---863---801 Pressurize Hydraulic System No. 1 or No. 2

AMM 12---00---06---863---802 Release Hydraulic Pressure ---

System No.1 or No. 2

AMM 12---00---06---863---803 Pressurize Hydraulic System No. 3

AMM 12---00---06---863---804 Release Hydraulic Pressure System No. 3

AMM 12---00---07---861---801 Connect External AC Power

AMM 27---31---00---220---807 Control-Column Feel Force and

Centering Check

AMM 27---31---20---000---801 Removal of the Pitch Feel Simulator Unit

AMM 27---31---20---400---801 Installation of the Pitch Feel Simulator Unit

AMM 29---00---00---910---801 Hydraulic Safety Precautions

AMM 55---32---05---000---801 Removal of the Forward Access Panels

AMM 55---32---05---400---801 Installation of the Forward Access Panels

WARNING: PUT THE SAFETY DEVICES, THE WARNING SIGNS, AND THE

WARNING PLACARDS IN POSITION BEFORE YOU START A

PROCEDURE ON OR NEAR:

--- FLIGHT CONTROLS

--- FLIGHT CONTROL SURFACES

--- COMPONENTS THAT MOVE.

MAKE SURE THAT THERE ARE NO PERSONS OR EQUIPMENT ON OR

NEAR THE FLIGHT CONTROL SURFACES. ACCIDENTAL MOVEMENT

OF THE FLIGHT CONTROLS CAN CAUSE INJURIES TO PERSONS

AND/OR DAMAGE TO EQUIPMENT.

(1) Install the applicable placards on the pilot’s and copilot’s control columns and

the STAB/MACH TRIM panel.

(2) Install the applicable safety devices and warning signs at the elevator control

surfaces.

(3) Connect the external AC power (Refer to AMM 12---00---07---861---801)
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WARNING: OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO

WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM

COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES

TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

(4) Obey all the hydraulic safety precautions

(Refer to AMM 29---00---00---910---801).

(5) Pressurize hydraulic system No.1, No.2 or No.3

(Refer to AMM 12---00---06---863---801 or AMM 12---00---06---863---803).

WARNING: MAKE SURE THAT THE FLIGHT CONTROL SURFACES ARE CLEAR OF

PERSONS AND EQUIPMENT DURING THE FULL RANGE OF TRAVEL.

FLIGHT CONTROL MOVEMENT CAN CAUSE INJURIES TO PERSONS

AND/OR DAMAGE TO EQUIPMENT.

(6) Make sure that the flap selector is set to zero and that the flaps are fully

retracted.

(7) Make sure that the horizontal stabilizer is trimmed to the neutral position as

follows:

(a) On the STAB TRIM/MACH TRIM panel in the flight compartment, push

the CH1/CH2 switches to engage the horizontal stabilizer trim control

unit (HSTCU).

CAUTION: OBEY THE DUTY CYCLE OF THE HORIZONTAL ---STABILIZER

PITCH---TRIM ACTUATOR (2 MINUTES ON, THEN 2 MINUTES

OFF). IF YOU DO NOT DO THIS, YOU CAN CAUSE DAMAGE TO

THE EQUIPMENT.

(b) On the EICAS control panel, push the STAT button to set the status page

on the EICAS secondary display (ED 2).

(c) Operate the horizontal stabilizer to the 2.0 (neutral) position on the

EICAS secondary display (ED 2).

(8) Make sure that the control surfaces are centered.

(9) Pull pitch disconnect handle fully up and rotate it 90 degrees to isolate the left

control column from the right control column.
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B. Procedure

(1) In the flight compartment, compare the applied force between the left and the

right control columns to see if a PFS input lever is disconnected as follows:

NOTE: Always do the column check with the cabin temperature at normal

operating conditions. When exposed to temperature below 0_C for

more than one hour with the power OFF, increase the cabin temperature

to normal operating conditions.

(a) For the left control column:

1 With very light force, pull the control column aft until it reaches the

aft stop.

2 Release the control column and monitor the rate that it goes back

to the center position.

3 With very light force and from the center position, push the control

column fwd until it reaches the fwd stop.

4 Release the control column and monitor the rate that it goes back

to the center position.

(b) For the right control column:

1 With very light force, pull the control column aft until it reaches the

aft stop.

2 Release the control column and monitor the rate that it goes back

to the center position.

3 With very light force and from the center position, push the control

column fwd until it reaches the fwd stop.

4 Release the control column and monitor the rate that it goes back

to the center position.

(c) If necessary, do steps 2.B.(1)(a) and 2.B.(1)(b) again.

(2) If the forces to pull and push the control columns are the same for the left and

the right, and if the rate that the control column went back to the center

position was the same for the left and the right, go to the Close---Out section.

(3) If the force is unusually less on one control column compared to the other, or if

one control column does not go back to the center position at the normal rate, do

a check of the PFS input lever condition on the side with less force or lower

column rate return as follows:
SERVICE BULLETIN 601R---27 ---144

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WARNING: MAKE SURE THAT THE FLIGHT CONTROL SURFACES ARE

CLEAR OF PERSONS AND EQUIPMENT DURING THE FULL

RANGE TRAVEL. FLIGHT CONTROL MOVEMENT CAN CAUSE

INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

(a) Release the hydraulic pressure from the system No.1, No.2 or No.3 as

applicable (Refer to AMM 12---00---06---863---802 or AMM

12---00---06---863---804).

Refer to Figure 1.

(b) On the vertical stabilizer, remove the forward access panel 326EL (for

the LH side) or 326ER (for the RH side) as applicable

(Refer to AMM 55---32---05---000---801).

(c) Remove the cotter pins (2), the nut (3), the washer (4),

and the bolt (5) that attach the control rod (6) to the PFS input lever (1).

(4) Do a check of the input lever (1) condition as follows:

(a) Move the input lever (1) fully FWD and fully AFT.

(b) If a force is necessary to move the input lever (the lever does not move

freely), the PFS is serviceable. Do as follows:

1 Attach the control rod (6) to the input lever (1) with the bolt (5),

washer (4), nut (3), and cotter pins (2).

2 Install the forward access panel 326EL or 326ER as applicable

(Refer to AMM 55---32---05---400---801).

3 Go to the Close-Out section of this service bulletin.

(c) If the input lever moves freely, or the input lever is loose, the PFS is

defective. Replace the PFS as follows:

1 Open, safety and tag the circuit breakers that follow:

CB PANEL CB NO. NAME ZONE

CBP ---1 F5 PITCH FEEL CH 1 221

CBP ---2 B8 STAB CH 1 HSTA 222

CBP ---2 F5 STAB CH 1 HSTCU 222

CBP ---2 F14 PITCH FEEL CH2 222

CBP ---3 A5 STAB CH 2 HSTA 221

CBP ---4 A1 STAB CH 2 HSTCU 222
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2 Remove the defective PFS (Refer to AMM 27---31---20---000---801).

3 Send the defective PFS to the address below:

Goodrich Actuation Systems

Stafford Rd Fordhouses

Wolverhampton WV10 7EH

England

United Kingdom

Attention : Tony Cooper.

4 Install a serviceable PFS (Refer to AMM 27---31---20---400---801).

5 Remove the tags and close the circuit breakers that follow:

CB PANEL CB NO. NAME ZONE

CBP ---1 F5 PITCH FEEL CH 1 221

CBP ---2 B8 STAB CH 1 HSTA 222

CBP ---2 F5 STAB CH 1 HSTCU 222

CBP ---2 F14 PITCH FEEL CH 2 222

CBP ---3 A5 STAB CH 2 HSTA 221

CBP ---4 A1 STAB CH 2 HSTCU 222

6 Engage the pitch disconnect mechanism as follows:

a Return the control columns to the neutral position.

b Stow the pitch disconnect handle to engage the pitch

disconnect mechanism.

7 Do the control-column feel force and centering check

(Refer to AMM 27---31---00---220---807).
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C. Job Close-Out

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

(2) If not engaged, engage the pitch mechanism as follows:

(a) Return the control columns to the neutral position.

(b) Stow the pitch disconnect handle to engage the pitch disconnect

mechanism.

(3) Remove the warning placards from the control columns and the STAB

TRIM/MACH TRIM panel.

(4) Remove the safety devices and warning signs from the elevator control

surfaces.

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

logbook(s): “Alert Service Bulletin A601R---27---144, Revision E, Flight Controls

--- Pitch Feel Simulator --- Functional Test of the Pilot Input Lever of the Pitch

Feel Simulator (PFS) P/N 601R92300---3 and P/N 601R92300---5,

incorporated.”
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Pilot Input Lever of the PFSs

Figure 1

rsb601r27031_002.dg, pb/om, 22/07/05

5

1. Input lever.

2. Cotter pin.

3. Nut.

4. Washer.

5. Bolt.

6. Control rod.

LEGEND

PITCH FEEL

SIMULATOR

(REF)

6

4

2

3

2

rsb601r27144_001.dg, pb/om, 06/01/06

1
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3. MATERIAL INFORMATION

A. Kit Information

None.

B. Rotable Information

None.

C. Consumable Information

There are no consumables for this service bulletin.

D. Special Tools and Equipment

For a list of special tools and equipment, refer to the different tasks, given as

references in this service bulletin.

E. Disposition of Parts

Not applicable.

1
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Sep 15/2005 APPENDIX A

NO TAG

SB A601R---27---144

Revision A, Dec 20/2006

ALERT SERVICE BULLETIN

APPENDIX A

CL ---600 ---2B19 Canadair Regional Jet (CRJ) Aircraft

ALERT SERVICE BULLETIN A601R ---27 ---144

SUBJECT: Flight Controls --- Pitch Feel Simulator --- Functional Test of the Pilot Input

Lever of the Pitch Feel Simulator (PFS) P/N 601R92300 ---3 and

P/N 601R92300 ---5

DATA SHEET

The data sheet contained in this appendix is given as a reference in the

ACCOMPLISHMENT INSTRUCTIONS of Alert Service Bulletin A601R---27---144.
APPENDIX A

ALERT SERVICE BULLETIN A601R---27 ---144

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Sep 15/2005 APPENDIX A

NO TAG

SB A601R---27---144

Revision A, Dec 20/2006

OPERATOR NAME: ___________________________________________________

AIRCRAFT SERIAL NUMBER: __________________________________________

DATE OF INSPECTION: _______________________________________________

FLIGHT HOURS: _____________________________________________________

DATA SHEET

COMPONENT REMOVED LOCATION

PFS P/N PFS S/N PFS FLIGHT

HOURS

LEFT

n

RIGHT

n

Send this Data Sheet by Fax to: BOMBARDIER REGIONAL AIRCRAFT

CRJ Technical Help Desk

In---Service Engineering (Att: John Kahn)

13100 boul. Henri---Fabre

Mirabel, Quebec

J7N 3C6

FAX: 514---855---8501

thd.crj@aero.bombardier.com
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 : A601R-27-144 ISSUE: E

 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