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Sep 23/2010 SB 601R---76---019

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

Sep 23/2010 SB 601R---76---019

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.

1
S.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) Aircraft Affected:

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

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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

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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

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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 in the 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

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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 in the 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

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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

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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. Job Set ---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

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(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

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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

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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

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C. Close Out

(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

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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

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Revision D, Sep 23/2010

PART B: Replacement of the Engine Throttle Control Gearbox

D. Job Set ---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

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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).
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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).
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F. Close Out

(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).
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(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

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rsb601r76019_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

ATR CONTROL (REF) 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

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rsb601r76019_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.

1
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 : 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