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SB A601R- - - 27- - - 144 Page 1 of 1 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 T est 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.
SB A601R- - - 27- - - 144 Page 1 of 12 Sep 15/2005 Revision E, Oct 02/2012
ALERT SERVICE BULLETIN T echnical 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 T est 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 SB A601R- - - 27- - - 144 Page 2 of 12 Sep 15/2005 Revision E, Oct 02/2012 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.
SERVICE BULLETIN 601R- - -27- - -144 SB A601R- - - 27- - - 144 Page 3 of 12 Sep 15/2005 Revision E, Oct 02/2012 F. M a n p o w e r 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 M A N --- H O U R S ( 1 ) J o b S e t --- U p N/A
(2) Procedure 0.25
(3) T est 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.
SERVICE BULLETIN 601R- - -27- - -144 SB A601R- - - 27- - - 144 Page 4 of 12 Sep 15/2005 Revision E, Oct 02/2012 G. Material - - - Price and Availability T o replace a defective PFS, refer to Bombardier service bulletin 601R- - - 27- - - 139.
H. T ooling - - - 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 SB A601R- - - 27- - - 144 Page 5 of 12 Sep 15/2005 Revision E, Oct 02/2012
2. ACCOMPLISHMENT INSTRUCTIONS A . J o b S e t --- U p Reference Information
REFERENCE DESIGNATION A M M 1 2 --- 0 0 --- 0 6 --- 8 6 3 --- 8 0 1Pressurize Hydraulic System No. 1 or No. 2 A M M 1 2 --- 0 0 --- 0 6 --- 8 6 3 --- 8 0 2 Release Hydraulic Pressure - - - System No.1 or No. 2 A M M 1 2 --- 0 0 --- 0 6 --- 8 6 3 --- 8 0 3 Pressurize Hydraulic System No. 3 A M M 1 2 --- 0 0 --- 0 6 --- 8 6 3 --- 8 0 4Release Hydraulic Pressure System No. 3 A M M 1 2 --- 0 0 --- 0 7 --- 8 6 1 --- 8 0 1 Connect External AC Power A M M 2 7 --- 3 1 --- 0 0 --- 2 2 0 --- 8 0 7 Control-Column Feel Force and Centering Check A M M 2 7 --- 3 1 --- 2 0 --- 0 0 0 --- 8 0 1 Removal of the Pitch Feel Simulator Unit A M M 2 7 --- 3 1 --- 2 0 --- 4 0 0 --- 8 0 1Installation of the Pitch Feel Simulator Unit A M M 2 9 --- 0 0 --- 0 0 --- 9 1 0 --- 8 0 1 Hydraulic Safety Precautions A M M 5 5 --- 3 2 --- 0 5 --- 0 0 0 --- 8 0 1 Removal of the Forward Access Panels A M M 5 5 --- 3 2 --- 0 5 --- 4 0 0 --- 8 0 1Installation 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:
--- F L I G H T C O N T R O L S --- F L I G H T C O N T R O L S U R FA C E S
- - - 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)
SERVICE BULLETIN 601R- - -27- - -144 SB A601R- - - 27- - - 144 Page 6 of 12 Sep 15/2005 Revision E, Oct 02/2012 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.
SERVICE BULLETIN 601R- - -27- - -144 SB A601R- - - 27- - - 144 Page 7 of 12 Sep 15/2005 Revision E, Oct 02/2012 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 _Cf o r 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 SB A601R- - - 27- - - 144 Page 8 of 12 Sep 15/2005 Revision E, Oct 02/2012 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 a p p l i c a b l e ( R e f e r t o A M M 1 2 --- 0 0 --- 0 6 --- 8 6 3 --- 8 0 2 o r A M M 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 C B P --- 1 F5 PITCH FEEL CH 1 221 C B P --- 2 B8 STAB CH 1 HSTA 222 C B P --- 2 F5 STAB CH 1 HSTCU 222 C B P --- 2 F14 PITCH FEEL CH2 222 C B P --- 3 A5 STAB CH 2 HSTA 221 C B P --- 4 A1 STAB CH 2 HSTCU 222
SERVICE BULLETIN 601R- - -27- - -144 SB A601R- - - 27- - - 144 Page 9 of 12 Sep 15/2005 Revision E, Oct 02/2012 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 W o l v e r h a m p t o nW V 1 07 E H England United Kingdom Attention : T ony Cooper.
4 Install a serviceable PFS (Refer to AMM 27- - - 31- - - 20- - - 400- - - 801).
5 R e m o v et h et a g sa n dc l o s et h ec i r c u i tb r e a k e r st h a tf o l l o w :
CB PANEL CB NO. NAME ZONE C B P --- 1 F5 PITCH FEEL CH 1 221 C B P --- 2 B8 STAB CH 1 HSTA 222 C B P --- 2 F5 STAB CH 1 HSTCU 222 C B P --- 2 F14 PITCH FEEL CH 2 222 C B P --- 3 A5 STAB CH 2 HSTA 221 C B P --- 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).
SERVICE BULLETIN 601R- - -27- - -144 SB A601R- - - 27- - - 144 Page 10 of 12 Sep 15/2005 Revision E, Oct 02/2012 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 T est of the Pilot Input Lever of the Pitch Feel Simulator (PFS) P/N 601R92300- - - 3 and P/N 601R92300- - - 5, incorporated.”
SERVICE BULLETIN 601R- - -27- - -144 SB A601R- - - 27- - - 144 Page 11 of 12 Sep 15/2005 Revision E, Oct 02/2012 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