Page 1 of 2 SB 601R---76---019 Sep 23/2010 

## SERVICE BULLETIN REVISION TRANSMITTAL SHEET CL ---600 ---2B19 Canadair Regional Jet (CRJ) Aircraft SERVICE BULLETIN 601R ---76 ---019
SUBJECT: Engine --- Throttles --- Inspection of the Throttle Control Gearbox (P/N 2100140 ---005 or P/N 2100140 ---007) These pages transmit: Revision D of Service Bulletin 601R --- 76 --- 019, pages 1 thru 21, dated Sep 23/2010. 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: Change the Service Bulletin Effectivity to 7003 thru 7067, 7069 thru 7990, 8000 thru 8078, 8080 and 8087 thru 8089. Change a reference. This revision also includes small editorial changes that do not have an effect on the technical content.
Instructions: Discard the copy of Service Bulletin 601R --- 76 --- 019, Revision C, dated Jul 05/2007. Replace with the copy attached. KEEP AEROCONTROLEX GROUP, TRANSDIGM INC. SERVICE BULLETIN 2100140---007---76---04.

### SERVICE BULLETIN 601R---76 ---019 REVISION TRANSMITTAL SHEET

Page 2 of 2 SB 601R---76---019 Sep 23/2010 Service Bulletin History: Initial issue, dated Aug 21/2003. Revision A, dated Feb 19/2004. Revision B, dated Feb 16/2005. Revision C, dated Jul 05/2007. 1S.B. 601R---76---019 Page 1 of 21 21 August 2003 Revision D, Sep 23/2010 

# 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: 76 ---11 NUMBER: 601R ---76 ---019 SUBJECT: Engine --- Throttles --- Inspection of the Throttle Control Gearbox (P/N 2100140 ---005 or P/N 2100140 ---007)

1. PLANNING INFORMATION A. Effectivity (1) AircraftAffected: Service Bulletin: CL ---600---2B19 Canadair Regional Jet (CRJ) Aircraft with the component part numbers/serial numbers that follow installed:

### SERVICE BULLETIN 601R---76 ---019

S.B. 601R---76---019 Page 2 of 21 21 August 2003 Revision D, Sep 23/2010 PART NUMBER: 228 ---58212 ---105 OR 228 ---58212 ---107 (2100140 ---005 OR 2100140 ---007) Installed at time of delivery on aircraft serial numbers: 7003 thru 7067, 7069 thru 7990, 8000 thru 8078, 8080 and 8087 thru 8089 Spares: Examine all spare parts. If a part is found, it is necessary to incorporate this service bulletin.
All CL ---600---2B19 If parts are installed on aircraft that were not identified at the time of delivery, on the same or on a different aircraft model, it is necessary to incorporate this service bulletin. Production: There is no production effectivity. NOTE: The instructions in this service bulletin are only applicable to the systems and parts installed at the time of delivery of the aircraft or as changed by Bombardier Aerospace Service Bulletin(s). Before you do this bulletin, examine all STC,STA or equivalent action changes to make sure this bulletin can be completed. B. Reason (1) Condition When the throttle is at the “climb/cruise” position, the teeth inside the throttle gearbox can wear. If the teeth wear too much, this can cause the throttle to jam or to move out of position (mis --- rigged). If there is a mis --- rigged condition, the movement of the throttle towards the IDLE position can corresponds to a position close to FUEL SHUT OFF. This can cause the engine to stop. It is not possible to restart the engine when this situation occurs (incorrect IDLE position). (2) Evidence It was reported on four aircraft in service that one engine stopped and could not be restarted. (3) Objective/Benefit This service bulletin gives the procedure to do an inspection and, if necessary, the replacement the throttle control gearbox P/N 2100140---005 or 2100140---007. The incorporation of this service bulletin increases the reliability of the throttle control system.

### SERVICE BULLETIN 601R---76 ---019

S.B. 601R---76---019 Page 3 of 21 21 August 2003 Revision D, Sep 23/2010 C. Description PART A Inspection of the Engine Throttle Gearbox for Wear The circuit breakers are opened. The engine access cowls are opened and/or removed. The throttle control rod is disconnected from the main---fuel control---lever. The engine throttle control cable is disconnected from the throttle control gearbox. An inspection is done inside the throttle control gearbox as described in the AeroControlex Group, TransDigm Inc. service bulletin 2100140---007---76---04. The throttle control rod is connected to the main---fuel control---lever. The throttle control cable is connected to the throttle control gearbox. The circuit breakers are closed. A functional test of the throttle system is done. A functional Test of the Auto ---Throttle Retard and Throttle Lock is done. The engine cowls are closed and/or installed. The aircraft is returned to service. PART B Replacement of the Engine Throttle Gearbox The circuit breakers are opened. The engine access cowls are opened and/or removed. The throttle control gearbox is removed. A new throttle control gearbox is installed. The circuit breakers are closed. A rigging of the Auto ---Throttle Retarder (ATR) control is done and a functional test of the throttle system is done. A functional Test of the Auto ---Throttle Retard and Throttle Lock is done. An idle speed check is done. The aircraft is returned to service. D. Compliance Recommended Service Bulletin. Bombardier Aerospace recommends that PART A of this service bulletin be completed no later than 1000 flight hours from the issue date on this service bulletin unless otherwise directed by the operator’s airworthiness authority. If the inspection results are 0.010 in. (0.254 mm) and above on one or both engine throttle control gearboxes, PART B is done before next flight on the applicable control gearbox(es). If the results are between 0.006 in. (0.152 mm) and 0.010 in. (0.254 mm) on the left and the right throttle gearboxes, PART B is done on the gearbox with the higher wear value before next flight. PART B is done on the other gearbox within the next 1000 flight hours

. If the result is between 0.006 in. (0.152 mm) and 0.010 in. (0.254 mm) on one throttle gearbox only, PART B is done within the 1000 next flight hours on this gearbox. If the results are below 0.006 in. (0.152 mm) on the left and the right engine throttle gearboxes, no further action is required.

### SERVICE BULLETIN 601R---76 ---019

S.B. 601R---76---019 Page 4 of 21 21 August 2003 Revision D, Sep 23/2010 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 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, 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. PART A: Inspection Engine Throttle Gearbox for Wear It will take an estimated 6 man---hours to complete this service bulletin. The breakdown of the man---hours is shown inthe table that follows (elapsed cure time is not included in the man---hours summary given above): TASK MAN ---HOURS MAX. PERSONS ELAPSED TIME (1) Job Set ---Up 1 2 0.5 (2) Procedure 2 2 1 (3) Test 2 2 1 (4) Close---Out 1 2 0.5 (5) Cure Time N/A N/A 0.25 NOTE: This estimate does include the 1 man---hour (0.5 man---hour for each engine) required to do the AeroControlex Group, TransDigm Inc. service bulletin 2100140---007---76---04.

### SERVICE BULLETIN 601R---76 ---019

S.B. 601R---76---019 Page 5 of 21 21 August 2003 Revision D, Sep 23/2010 PART B: Replacement of the Engine Throttle Gearbox It will take an estimated 13 man---hours to complete this service bulletin. The breakdown of the man---hours is shown inthe table that follows (elapsed cure time is not included in the man---hours summary given above): TASK MAN ---HOURS MAX. PERSONS ELAPSED TIME (1) Job Set ---Up 1 2 0.5 (2) Procedure 3 2 1.5 (3) Test 8 2 4 (4) Close---Out 1 2 0.5 (5) Cure Time N/A N/A 0.25 Labor costs for this modification are not covered by Bombardier Aerospace Regional Aircraft. G. Material --- Price and Availability (1) The throttle control gearbox P/N 2100140---005 or ---007 is part of a rotable pool and is provided free of charge. Contact AeroControlex Group, TransDigm Inc. at the address that follows to order and schedule the part(s) as applicable. AeroControlex Group, TransDigm Inc. 313 Gillett Street Painesville, Ohio 44077 USA Tel.: (440) 352---6182 Fax.: (440) 354---2912 H. Tooling --- Price and Availability Refer to paragraph 3.D. and to the AeroControlex Group, TransDigm Inc. service bulletin 2100140---007---76---04. I. Weight and Balance Not Changed. J. Electrical Load Data Not Changed.

### SERVICE BULLETIN 601R---76 ---019

S.B. 601R---76---019 Page 6 of 21 21 August 2003 Revision D, Sep 23/2010 K. References Restriction and/or Special Instruction (RSI), C ---A019, Revision E. AeroControlex Group, TransDigm Inc. Service Bulletin 2100140---007---76---04, dated July 22, 2003. Aircraft Maintenance Manual, CSP A ---001, Revision 27. For Bombardier Aerospace reference only: PCA 04219, 04509 and 04452. L. Other Publications Affected None. M. Relationship Chart None.

### SERVICE BULLETIN 601R---76 ---019

S.B. 601R---76---019 Page 7 of 21 21 August 2003 Revision D, Sep 23/2010 2. ACCOMPLISHMENT INSTRUCTIONS NOTE: The TASK references in the procedures that follow are to the Aircraft Maintenance Manual, CSP A ---001, unless otherwise noted. The first six numbers in the TASK number refer to the Chapter ---Section---Subject where the referenced TASK is found. PART A: Engine Throttle Control Gearbox Wear Inspection A. JobSet ---Up Reference Information Table
TASK Title AMM 71---11---01---400---801 Installation of the Upper Translating ---Cowl Door AMM 71---11---01---410---801 Close the Upper Translating ---Cowl Door AMM 71---11---01---410---802 Close the Lower Translating ---Cowl Door AMM 71---12---01---000---801 Removal of the Upper Core---Cowl Door AMM 71---12---01---010---801 Open the Upper Core---Cowl Door AMM 71---12---01---010---803 Open the Lower Core---Cowl Door AMM 71---12---01---400---801 Installation of the Upper Core---Cowl Door AMM 71---12---01---410---802 Close the Upper Core---Cowl Door AMM 71---12---01---410---804 Close the Lower Core---Cowl Door AMM 76---10---00---720---805 Functional Test of the Throttle Control System AMM 78---30---00---720---804 Functional Test of the Auto ---Throttle Retard and Throttle Lockout

### SERVICE BULLETIN 601R---76 ---019

S.B. 601R---76---019 Page 8 of 21 21 August 2003 Revision D, Sep 23/2010 (1) Open, safety, and tag the circuit breakers that follows:
CB PANEL CB NO. NAME ZONE

CBP ---1 A2 HYD PUMP 3B 221 CBP ---1 A5 HYD PUMP 2 221 CBP ---1 M3 ENG IGN B 221 CBP ---2 A2 HYD PUMP 3A 222 CBP ---2 A5 HYD PUMP 1 222 CBP ---3 B7 ENG IGN A 221 CBP ---4 B5 THRUST REV AUTO STOW 1 222 CBP ---4 B6 THRUST REV AUTO STOW 2 222 CBP ---5 B1 ENG IGN B 311
For Aircraft 7003 thru 7067 and 7069 thru 7890 CB PANEL CB NO. NAME ZONE

CBP ---1 M2 ENG IGN A 221 For Aircraft 7891 thru 7990, 8000 thru 8078, 8080 and 8087 thru 8089 CB PANEL CB NO. NAME ZONE

CBP ---4 C6 ENG IGN A 222
For all Aircraft (2) On the left engine do as follows: (a) Open the lower core---cowl door (Refer to AMM 71---12---01---010---803). (b) Open the upper core---cowl door (Refer to AMM 71---12---01---010---801). (3) On the right engine do as follows: (a) Open the lower core---cowl door (Refer to AMM 71---12---01---010---803). (b) Remove the upper core---cowl door (Refer to AMM 71---12---01---000---801).

### SERVICE BULLETIN 601R---76 ---019

S.B. 601R---76---019 Page 9 of 21 21 August 2003 Revision D, Sep 23/2010 B. Procedure NOTE: The procedure that follows is applicable to the left and right side. Differences are identified. Refer to Figure 1. (1) Make sure that the bolts (6) and (7) are correctly torqued to 20---25 lbf⋅in (2.25---2.82 N⋅m). If the torque is not correct, tighten to the correct torque and send a report to Bombardier Aerospace In---Service Engineering (Engine Group) at fax: (450) 476---7321. (2) Disconnect the throttle control cable (1) from the gearbox (2) as follows: (a) Move the throttle control lever to the MAX POWER position. (b) Remove and discard the lockwire from the union nut (3) at the gearbox (2). (c) Loosen the union nut (3) that attaches the engine throttle---control cable to the throttle control gearbox (2). (d) Disconnect the inner element (4) from the throttle control gearbox (2). (3) Disconnect the throttle control rod (8) from the main fuel---control lever (13) as follows: (a) Remove the cotter pin (9), nut (10), washer (11), and bolt (12) that attach the throttle control rod (8) to the main fuel---control lever (13). (4) Do AeroControlex Group, TransDigm Inc. service bulletin 2100140---007---76---04. (5) If the wear value is above 0.010 in. (0.254 mm) on one or both engine throttle control gearboxes, do PART B on the applicable gearbox. (6) If the wear value is between 0.006 in. (0.152 mm) and 0.010 in. (0.254 mm) on both the left and the right throttle gearbox, do PART B on the gearbox with the higher wear value. (7) If the wear value is between 0.006 in. (0.152 mm) and 0.010 in. (0.254 mm) on one throttle gearbox only, go to the ‘Close---Out’ or do PART B. (8) If the wear value is below 0.006 in. (0.152 mm) on both gearboxes, go to the ‘Close---out’ section of this service bulletin.

### SERVICE BULLETIN 601R---76 ---019

S.B. 601R---76---019 Page 10 of 21 21 August 2003 Revision D, Sep 23/2010 (9) Install the throttle control rod (8) as follows: (a) Attach the throttle control rod (8) to the main fuel---control lever (13) with the bolt (12), washer (11), nut (10) and cotter pin (9). (10) Attach the engine throttle---control cable (1) to the gearbox (2) as follows: (a) Fill the internal opening on the gearbox rack (5) half full of sealant. (b) Connect the tang ---end of the engine throttle---control cable inner ---element (4) into the opening of the gearbox rack (5) until it is fully engaged. CAUTION: MAKE SURE THAT YOU CLEAN ALL THE SEALANT THAT COMES OUT OF THE CONNECTION AFTER THE CONTROL CABLE IS FULLY ENGAGED INTO THE OPENING OF THE GEARBOX RACK. REMAINING SEALANT CAN CAUSE THE THROTTLE CONTROL TO BECOME STIFF. (c) Remove the unwanted sealant that comes out of the connection with a clean cloth. (d) Let the sealant cure for 15 minutes. (e) Apply a thin layer of anti ---seize compound on the external threads of the gearbox (2). (f) Connect the engine throttle---control cable (1) to the gearbox (2) with the union nut (3). (g) Torque the union nut (3) to 80 lbf•in to 100 lbf•in (9.04 NSm to 11.30 NSm). (h) Safety the union nut (3) with lockwire.

### SERVICE BULLETIN 601R---76 ---019

S.B. 601R---76---019 Page 11 of 21 21 August 2003 Revision D, Sep 23/2010 C. CloseOut (1) Do a functional test of the throttle control system (Refer to AMM 76---10---00---720---805). (2) On the left engine do as follows: (a) Close the upper core---cowl door (Refer to AMM 71---12---01---410---802). (b) Close the lower core---cowl door (Refer to AMM 71---12---01---410---804). (c) Close the upper translating ---cowl door (Refer to AMM 71---11---01---410---801). (d) Close the lower translating ---cowl door (Refer to AMM 71---11---01---410---802). (3) On the right engine do as follows: (a) Install the upper core---cowl door (Refer to AMM 71---12---01---400---801). (b) Close the lower core---cowl door (Refer to AMM 71---12---01---410---804). (c) Install the upper translating ---cowl door (Refer to AMM 71---11---01---400---801). (d) Close the lower translating ---cowl door (Refer to AMM 71---11---01---410---802). (4) Remove the tags and close the circuit breakers that follows: CB PANEL CB NO. NAME ZONE

CBP ---1 A2 HYD PUMP 3B 221 CBP ---1 A5 HYD PUMP 2 221 CBP ---1 M3 ENG IGN B 221 CBP ---2 A2 HYD PUMP 3A 222 CBP ---2 A5 HYD PUMP 1 222 CBP ---3 B7 ENG IGN A 221 CBP ---4 B5 THRUST REV AUTO STOW 1 222 CBP ---4 B6 THRUST REV AUTO STOW 2 222 CBP ---5 B1 ENG IGN B 311

### SERVICE BULLETIN 601R---76 ---019

S.B. 601R---76---019 Page 12 of 21 21 August 2003 Revision D, Sep 23/2010 For Aircraft 7003 thru 7067 and 7069 thru 7890 CB PANEL CB NO. NAME ZONE

CBP ---1 M2 ENG IGN A 221 For Aircraft 7891 thru 7990, 8000 thru 8078, 8080 and 8087 thru 8089 CB PANEL CB NO. NAME ZONE

CBP ---4 C6 ENG IGN A 222
For all Aircraft (5) When PART A of this service bulletin is completed, make this entry in the applicable logbook: “Service Bulletin 601R---76---019, Revision D, Inspection of the Throttle Control Gearbox (P/N 2100140---005 and P/N 2100140---007), PART A,incorporated.”

### SERVICE BULLETIN 601R---76 ---019

S.B. 601R---76---019 Page 13 of 21 21 August 2003 Revision D, Sep 23/2010 PART B: Replacement of the Engine Throttle Control Gearbox D. JobSet ---Up Reference Information Table
TASK Title AMM 71---00---00---868---813 Idle Speed Adjustment AMM 71---00---00---868---807 Engine Shutdown (Normal) AMM 71---11---01---400---801 Installation of the Upper Translating ---Cowl Door AMM 71---11---01---410---801 Close the Upper Translating ---Cowl Door AMM 71---11---01---410---802 Close the Lower Translating ---Cowl Door AMM 71---12---01---000---801 Removal of the Upper Core---Cowl Door AMM 71---12---01---010---801 Open the Upper Core---Cowl Door AMM 71---12---01---010---803 Open the Lower Core---Cowl Door AMM 71---12---01---400---801 Installation of the Upper Core---Cowl Door AMM 71---12---01---410---802 Close the Upper Core---Cowl Door AMM 71---12---01---410---804 Close the Lower Core---Cowl Door AMM 76---10---00---720---805 Functional Test of the Throttle Control System AMM 78---30---00---720---804 Functional Test of the Auto ---Throttle Retard and Throttle Lockout AMM 78---35---01---830---802 Rigging of the ATR Control

### SERVICE BULLETIN 601R---76 ---019

S.B. 601R---76---019 Page 14 of 21 21 August 2003 Revision D, Sep 23/2010 (1) Open, safety, and tag the circuit breakers that follows:
CB PANEL CB NO. NAME ZONE

CBP ---1 A2 HYD PUMP 3B 221 CBP ---1 A5 HYD PUMP 2 221 CBP ---1 M3 ENG IGN B 221 CBP ---2 A2 HYD PUMP 3A 222 CBP ---2 A5 HYD PUMP 1 222 CBP ---3 B7 ENG IGN A 221 CBP ---4 B5 THRUST REV AUTO STOW 1 222 CBP ---4 B6 THRUST REV AUTO STOW 2 222 CBP ---5 B1 ENG IGN B 311
For Aircraft 7003 thru 7067 and 7069 thru 7890 CB PANEL CB NO. NAME ZONE

CBP ---1 M2 ENG IGN A 221 For Aircraft 7891 thru 7990, 8000 thru 8078, 8080 and 8087 thru 8089 CB PANEL CB NO. NAME ZONE

CBP ---4 C6 ENG IGN A 222
For all Aircraft (2) On the left engine do as follows: (a) Open the lower core---cowl door (Refer to AMM 71---12---01---010---803). (b) Open the upper core---cowl door (Refer to AMM 71---12---01---010---801). (3) On the right engine do as follows: (a) Open the lower core---cowl door (Refer to AMM 71---12---01---010---803). (b) Remove the upper core---cowl door (Refer to AMM 71---12---01---000---801).

### SERVICE BULLETIN 601R---76 ---019

S.B. 601R---76---019 Page 15 of 21 21 August 2003 Revision D, Sep 23/2010 E. Procedure NOTE: The procedure that follows is applicable to the left and right side. Differences are identified. Refer to Figure 1. (1) Remove the throttle control gearbox (Refer to AMM 76---11---17---000---801). (2) Send the Throttle control gearbox to AeroControlex Group, TransDigm Inc. Refer to AeroControlex Group, TransDigm Inc. service bulletin 2100140---007---76---04 for the address. (3) Install the throttle control gearbox (Refer to AMM 76---11---17---400---801). (4) Torque the bolts (6) and (7) to 20 lbf•in to 25 lbf•in (2.25 NSm to 2.82 NSm). (5) Do a functional test of the throttle control system (Refer to AMM 76---11---00---720---801).

### SERVICE BULLETIN 601R---76 ---019

S.B. 601R---76---019 Page 16 of 21 21 August 2003 Revision D, Sep 23/2010 F. CloseOut (1) Remove the tags and close the circuit breakers that follows: For All Aircraft CB PANEL CB NO. NAME ZONE

CBP ---1 A2 HYD PUMP 3B 221 CBP ---1 A5 HYD PUMP 2 221 CBP ---1 M3 ENG IGN B 221 CBP ---2 A2 HYD PUMP 3A 222 CBP ---2 A5 HYD PUMP 1 222 CBP ---3 B7 ENG IGN A 221 CBP ---4 B5 THRUST REV AUTO STOW 1 222 CBP ---4 B6 THRUST REV AUTO STOW 2 222 CBP ---5 B1 ENG IGN B 311
For Aircraft 7003 thru 7067 and 7069 thru 7890 CB PANEL CB NO. NAME ZONE

CBP ---1 M2 ENG IGN A 221 For Aircraft 7891 thru 7990, 8000 thru 8078, 8080 and 8087 thru 8089 CB PANEL CB NO. NAME ZONE

CBP ---4 C6 ENG IGN A 222
For all Aircraft (2) Do a rigging of the ATR control (Refer to AMM 78---35---01---830---802). (3) Do a functional test of the throttle control system ( Refer to AMM 76---10---00---720---805).

### SERVICE BULLETIN 601R---76 ---019

S.B. 601R---76---019 Page 17 of 21 21 August 2003 Revision D, Sep 23/2010 (4) Do a functional test of the auto ---throttle retard and throttle lock (Refer to AMM78---30---00---720---804). (5) On the left engine do as follows: (a) Close the upper core---cowl door (Refer to AMM 71---12---01---410---802). (b) Close the lower core---cowl door (Refer to AMM 71---12---01---410---804). (c) Close the upper translating ---cowl door (Refer to AMM 71---11---01---410---801). (d) Close the lower translating ---cowl door (Refer to AMM 71---11---01---410---802). (6) On the right engine do as follows: (a) Install the upper core---cowl door (Refer to AMM 71---12---01---400---801). (b) Close the lower core---cowl door (Refer to AMM 71---12---01---410---804). (c) Install the upper translating ---cowl door (Refer to AMM 71---11---01---400---801). (d) Close the lower translating ---cowl door (Refer to AMM 71---11---01---410---802). (7) Do an idle speed check (Refer to AMM 71---00---00---868---813). (8) When PART B of this service bulletin is completed, make this entry in the applicable logbook: “Service Bulletin 601R---76---019, Revision D, Inspection of the Throttle Control Gearbox (P/N 2100140---005 and P/N 2100140---007), PART B , incorporated.”

### SERVICE BULLETIN 601R---76 ---019

S.B. 601R---76---019 Page 18 of 21 21 August 2003 Revision D, Sep 23/2010rsb601r76019_001.dg, rm/rm, 30/01/04

ITEMS SHOWN ASSEMBLED 1. Engine throttle control cable. 2. Throttle control gearbox. 3. Union nut. 4. Inner element. 5. Rack. LEGEND

1

2 3 4 5

GEARBOX BRACKET (REF)
5 4 SEALANT FIXED CORE COWL (REF) ATR CONTROL CABLE LEFT ENGINE

6 7 6. Bolt (P/N NAS1203--1) 7. Bolt (P/N 228--58200--111) 8. Throttle control rod. 9. Cotter pin. 10. Nut. 11. Washer. 12. Bolt. 13. Lever.

8

9 10 11 12
13

Removal/Installation of the Throttle Control Cable at the Gearbox Assembly Figure 1 (Sheet 1 of 2)

### SERVICE BULLETIN 601R---76 ---019

S.B. 601R---76---019 Page 19 of 21 21 August 2003 Revision D, Sep 23/2010rsb601r76019_002.dg, rm/rm 30/01/04 1 2

3 4 5

GEARBOX BRACKET

(REF) ATR CONTROL CABLE RIGHT ENGINE

6

6

7 1. Engine throttle control cable. 2. Throttle control gearbox. 3. Union nut. 4. Inner element. 5. Rack. LEGEND

6. Bolt (P/N NAS1203--1) 7. Bolt (P/N 228--58200--111) 8. Throttle control rod. 9. Cotter pin. 10. Nut. 11. Washer. 12. Bolt. 13. Lever.

8

9 10 11 12

13

Removal/Installation of the Throttle Control Cable and Control rod Figure 1 (Sheet 2 of 2)

### SERVICE BULLETIN 601R---76 ---019

S.B. 601R---76---019 Page 20 of 21 21 August 2003 Revision D, Sep 23/2010 3. MATERIAL INFORMATION
A. Kit Information None. B. Rotable Information Refer to AeroControlex Group, TransDigm Inc. service bulletin 2100140---007---76---04. C. Consumables Required The materials that follow are required to complete this service bulletin and can be ordered as single items from Bombardier Aerospace Regional Aircraft or purchased directly from industry sources. If the material is ordered from Bombardier Aerospace Regional Aircraft, there can be some lead time because of shelf life requirements. CONSUMABLES SPECIFICATION QUANTITY NAME REFERENCE MS20995C32 AR Lockwire 05---004¡ MIL ---PRF---907 AR Anti---seize compound 06---024¡
RTV 730 AR Sealant 09---028 ¡ ¡ Refer to AMM 51---31---00---990---801 For a complete list of consumables, refer to the AeroControlex Group, TransDigm Inc. service bulletin 2100140---007---76---04 and to the TASK references in this service bulletin.

### SERVICE BULLETIN 601R---76 ---019

S.B. 601R---76---019 Page 21 of 21 21 August 2003 Revision D, Sep 23/2010 D. Special Tools and Equipment
SPECIAL TOOLS AND EQUIPMENT PART NUMBER ¡ QUANTITY NAME ALTERNATE PART(S)

G601R760001---1 1 Kit --- power plant rigging (for single spline main fuel control lever) G601R760002---1 1 Kit --- power plant rigging (for double spline main fuel control level) G601R200003---1 1 Dial Indicator NOTES ¡ Refer to the Illustrated Tool And Equipment Manual (CSP A ---007) For a complete list of special tools and equipment, refer to the AeroControlex Group,, TransDigm Inc. service bulletin 2100140---007---76---04 and to the TASK references in this service bulletin. E. Disposition of Existing Parts Refer to AeroControlex Group,, TransDigm Inc. vendor service bulletin 2100140---007---76---04. 1THANK 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 : ISSUE:

STRONGLY DISAGREE NEUTRAL AGREE STRONGLY DISAGREE AGREE
x Instructions to do the Service Bulletin were accurate. Comments: 

##    

x Illustration(s), figure(s), picture(s) and/or kit drawing(s) were helpful to carry out instructions. Comments: 

##    

x If a parts kit was required, did the kit contents received agree with the contents listed in the bulletin? Comments: 

##    

x Aircraft hands-on work was accomplished in estimated time. Comments: 

##    

x 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 601R-76-019 D