SB 601R---27---162

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April 05/2013

SERVICE BULLETIN

Technical

Publications

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

TRANSFERRED SPARES IN THE LAST SIX MONTHS, SEND THIS SERVICE BULLETIN TO THE NEW

OWNER, UNLESS CONFIRMATION WAS RECEIVED THAT BOMBARDIER COMMERCIAL AIRCRAFT

HAS INCLUDED THE NEW OPERATOR ON THE DISTRIBUTION LIST.

SEND THIS SERVICE BULLETIN TO THE LESSEE. IF THE OPERATOR HAS SOLD AIRCRAFT OR

ATA SYSTEM: 27 ---21 NUMBER: 601R ---27 ---162

SUBJECT: Flight Controls --- Rudder Control System --- Inspection of Rudder Pedal

Tubes P/N 600 ---90204 ---3 for Cracks and Replacement of the Rudder Bar

Assemblies on the Pilot’s Rudder Pedal Assembly

1. PLANNING INFORMATION

A. Effectivity

(1) Aircraft Affected:

Service: CL ---600---2B19 aircraft with serial numbers 7003 thru 7067,

7069 thru 7990, and 8000 thru 8999.

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 service bulletins. Before you do this service

bulletin, examine all Supplemental Type Certificates (STCs),

Supplemental Type Approvals (STAs) or equivalent changes to make

sure you can complete this service bulletin.
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B. Reason

(1) Condition

It is possible that there are cracks on P/N 600---90204---3 rudder pedal tubes

installed on the pilot’s rudder pedal assembly.

(2) Evidence

Two rudder pedal mechanism incidents occurred on in-service aircraft.

(3) Objective/Benefit

This service bulletin gives the procedure to do a detail visual inspection or an

eddy current inspection on P/N 600---90204---3 rudder pedal tubes, on the

pilot’s side, for cracks. Also, the procedure to replace the rudder bar

assemblies on the pilot’s rudder pedal assembly is given.

The detailed visual inspection or the eddy current inspection on P/N

600---90204---3 rudder pedal tubes or the replacement of the rudder bar

assemblies will prevent rudder pedal mechanism incidents.

C. Description

This service bulletin is divided into two parts: PART A and PART B.

PART A --- Detail Visual Inspection or Eddy Current Inspection of P/N

600 ---90204 ---3 Rudder Pedal Tubes, on the Pilot’s Side, for Cracks

Access panels are removed. If necessary, the pilot’s rudder pedal assembly is

removed. A detail visual inspection or an eddy current inspection is done on P/N

600---90204---3 rudder pedal tubes of the pilot’s rudder pedal assembly.

If no cracks are found, the removed access panels are installed. If removed, the

pilot’s rudder pedal assembly is installed.

If a crack is found, PART B of this service bulletin is done.

PART B --- Replacement of the Rudder Bar Assemblies on the Pilot’s Rudder

Pedal Assembly

The pilot’s rudder pedal assembly is removed. The rudder bar assemblies are

replaced. The pilot’s rudder pedal assembly is installed.
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D. Compliance

Recommended Service Bulletin. Bombardier recommends that PART A of this

service bulletin be done as shown in the table below, unless otherwise directed by

the airworthiness authority of the operator.

NOTE: It is not necessary to do PART A of this service bulletin if PART B of this

service bulletin is done before.

AIRCRAFT

FLIGHT CYCLES

TIME LIMIT TO DO PART A OF

THIS SERVICE BULLETIN

TIME LIMIT TO DO

REPEATED

INSPECTION

<20,000 Before 23,000 flight cycles

It is necessary to do a

repeated inspection at

intervals of 600 flight

cycles from the detail

visual inspection

or

It is necessary to do a

repeated inspection at

intervals of 1000 flight

cycles from the eddy

current inspection

20,000± to <25,000 In 3,000 flight cycles or less or

before 26,300 flight cycles

25,000± to <30,000 In 1,300 flight cycles or less or

before 30,800 flight cycles

30,000± to <33,000 In 800 flight cycles or less or

before 33,500 flight cycles

33,000± to <37,000 In 500 flight cycles or less or

before 37,300 flight cycles

>37,000 In 300 flight cycles or less

Bombardier recommends that PART B of this service bulletin be done at the earliest

convenience of the operator, unless otherwise directed by the airworthiness

authority of the operator.

This service bulletin affects Airworthiness Limitations (AWLs) and/or Damage

Tolerance Inspections (DTIs). Reference applicable Maintenance Requirements

Manual (MRM).

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 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, liaising, 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 on-site labor assistance, please speak with a Fleet Services

representative for a quote. Contact the Fleet Services Team

through the CRC at 514-855-8500 or email at

thd.crj@aero.bombardier.com.

For PART A

It will take an estimated 3.0 man-hours to complete PART A of this service bulletin.

The man-hours are divided in the table that follows:

TASK MAN-HOURS

(1) Job Set-Up 0.5

(2) Procedure 2.0

(3) Test N/A

(4) Job Close-Out 0.5

NOTE: These estimates do not include the man-hours necessary to remove and

install the pilot’s rudder pedal assembly.
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For PART B

It will take an estimated 6.0 man-hours to complete PART B of this service bulletin.

The man-hours are divided in the table that follows:

TASK MAN-HOURS

(1) Job Set-Up 0.5

(2) Procedure 4.0

(3) Test 0.5

(4) Job Close-Out 1.0

G. Material --- Price and Availability

For PART A

(1) There are no kits for PART A of this service bulletin. The parts in the table that

follows are necessary to do PART A of this service bulletin and are available

from Bombardier Commercial Aircraft.

PART NUMBER NAME QTY

AN386---2---14 Pin, taper 4

AN975---3 Washer, taper pin 4

MS17826---3 Nut, self locking 4

MS24665---132 Pin, cotter 4

For PART B

(2) The kit in the table that follow is available from L ---3 Communications.

NOTE: For a list of kit contents, refer to paragraph 3.A.

PART NUMBER NAME QTY

601R27---162K1 Rudder Bar Assembly ---

Replacement kit

1
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(3) Please send a purchase order to the address below to schedule kit delivery:

L3 Communications

10,000 Helen-Bristol Street

Mirabel, Quebec

Canada J7N 1H3

Fax: 450---476---4434

Phone: 450---476---4908

Email: sbkits.mas@L ---3 com.com

(4) 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. Refer to paragraph 3.C. for a list of

special tools and equipment for this service bulletin.

I. Weight and Balance

For PART A

Not changed.

For PART B

WEIGHT ARM MOMENT ¡

0.6 lb 90 in. 0.054 ( 1000 lb-in.)

0.27 kg 2.29 m 0.0006 (1000 kg-m)

¡ The value in the Moment column is divided by 1000.

Refer to Weight and Balance Manual CSP A ---041.

J. Electrical Load Data

Not changed.

K. References

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

bulletin content.

Restriction and/or Special Instruction (RSI) C ---A281, Revision C

Modification Summary TC601R18282, Revision A

Aircraft Maintenance Manual (AMM)

Structural Repair Manual (SRM)

For Bombardier reference only: PCA 6744 and 6749
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L. Other Publications Affected

Aircraft Illustrated Parts Catalogue (AIPC)

Maintenance Requirement Manual (MRM)

M. Relationship Chart

For PART A

Not applicable.

For PART B

PRE-SB

PART NUMBER NAME POST-SB

PART NUMBER NAME

600---90204---9

OR

BA670---93408---1

Bar assembly,

rudder BA670---93413---1 Bar assembly,rudder

600---90204---10

OR

BA670---93408---2

Bar assembly,

rudder BA670---93413---2 Bar assembly,rudder
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2. ACCOMPLISHMENT INSTRUCTIONS

PART A --- Detail Visual Inspection or Eddy Current Inspection of P/N 600 ---90204 ---3

Rudder Pedal Tubes, on the Pilot’s Side, for Cracks

Reference Information

REFERENCE DESIGNATION

AMM 06---41---00---00 Fuselage Access --- Description and Operation

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

AMM 12---00---07---861---802 Remove External AC Power

AMM 20---24---00---910---801 Cotter Pins --- Maintenance Practices

AMM 20---24---00---910---802 Lockwire --- Maintenance Practices

AMM 27---21---00---710---801 Operational Test of the Rudder Control

System

AMM 51---26---00---110---801 Solvent Cleaning

AMM 53---10---34---000---801 Removal of the Forward Fuselage Access Panels

AMM 53---10---34---400---801 Installation of the Forward-Fuselage Access

Panels

SRM 51---26---00 Fluid-Resistant (FR) Epoxy Primer

SRM 51---41---04 Torque Procedures --- Bolts and Screws

SRM 51---43---00 Taper Pins

A. Job Set-Up

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, AND

---COMPONENTS THAT MOVE

MAKE SURE THAT THERE ARE NO PERSONS OR EQUIPMENT ON OR

NEAR THE CONTROL SURFACES. ACCIDENTAL MOVEMENT OF THE

FLIGHT CONTROLS CAN CAUSE INJURIES TO PERSONS AND/OR

DAMAGE TO EQUIPMENT.
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(1) Install placards on the pilot’s and the copilot’s control columns to give

warnings against movement of the rudder pedals.

B. Procedure

Refer to Figure 1.

(1) If necessary, remove the pilot’s rudder pedal assembly (refer to AMM

27---21---01---000---801) or do the steps that follow:

(a) Set the flight controls as follows:

1 Connect the external AC power (refer to AMM

12---00---07---861---801).

2 On the center console, operate the RUD TRIM knob to put the

rudder trim to neutral on the Engine Indication and Crew Alerting

System (EICAS) secondary-display status page (trim position

pointer in green on the rudder-trim position scale).

3 Remove the external AC power (refer to AMM

12---00---07---861---802).

(b) Open access panel 221HZ.

(c) Remove rudder pedal console 221GZ.

(d) Remove the forward-fuselage access panel 131AL (refer to AMM

53---10---34---000---801).

(e) Install the rigging pin (P1) in the lever (L1) of the forward pivot assembly

on the left side (refer to View A).

(2) Do the steps that follow to get access to the two aft tapered holes in the

rudder pedal tubes (5):

NOTE: The procedure that follows is applicable for one rudder pedal tube (5).

The procedure for the other rudder pedal tube (5) is the same.

(a) Remove and discard the lockwire from the bolt (8) (refer to AMM

20---24---00---910---802).

(b) Remove the bolt (8) and the washer (9) that connect the control rod

assembly (7) to the connecting rod fitting (6).

(c) Remove and discard the two cotter pins (1), nuts (2), washers (3), and

the taper pins (4) that connect the connecting rod fitting (6) to the rudder

pedal tube (5) (refer to SRM 51---43---00).
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(d) Move the connecting rod fitting (6) along the rudder pedal tube (5) to

expose the two aft tapered holes (refer to View B).

(e) Clean the area around the two aft tapered holes (refer to View C)

(Refer to AMM 51---26---00---110---801).

(3) Do a detail visual inspection or an eddy current inspection for cracks around

the two aft tapered holes in the rudder pedal tubes (5).

NOTE: You must use a 10X Triplet magnifying glass or better to do the detail

visual inspection or the procedure given in Appendix A, of this service

bulletin, to do the eddy current inspection.

(4) If no cracks are found around the aft tapered holes in the rudder pedal tubes

(5), do the steps that follow:

(a) Install the connecting rod fitting (6) on the rudder pedal tube (5) with the

new taper pins (4) wet with fluid-resistant epoxy primer, the new washers

(3), and the new nuts (2) (refer to SRM 51---43---00 and SRM

51---25---06).

(b) Torque the nuts (2) to 20---28 lbf ̄in.(2.26---3.16 N ̄m)(refer to SRM

51---41---04).

(c) Safety the nuts (2) with the cotter pins (1) (refer to AMM

20---24---00---910---801).

(d) Connect the control rod assembly (7) to the connecting rod fitting (6)

with the bolt (8) and the washer (9).

(e) Tighten the bolt (8) (refer to SRM 51---41---04).

(f) Safety the bolt (8) with lockwire (refer to AMM 20---24---00---910---802).

(g) Remove the rigging pin (P1) from the level (L1) of the forward pivot

assembly on the left side (refer to View A).

(h) Continue to the Job Close-Out section.

(5) If a crack is found around the aft tapered holes in the rudder pedal tubes (5),

do PART B of this service bulletin before next flight.

(6) If damage is found at a different location on the rudder pedal tubes (5), speak

with a representative of Bombardier at the Technical Help Desk, before next

flight, at phone number 514-855-8500 for an approved disposition.
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C. Job Close-Out

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

(2) If removed, install the pilot’s rudder pedal assembly (refer to AMM

27---21---01---400---801)

(3) Install rudder pedal console 221GZ.

(4) Close access panel 221HZ.

(5) Install forward-fuselage access panel 131AL

(refer to AMM 53---10---34---400---801).

(6) Do the operational test of the rudder control system (refer to AMM

27---21---00---710---801).

(7) When PART A of this service bulletin is completed, make this entry in the

applicable logbooks: “Service Bulletin 601R---27---162, Flight Controls ---

Rudder Control System --- Inspection of Rudder Pedal Tubes P/N

600---90204---3 for Cracks and Replacement of the Rudder Bar Assemblies on

the Pilot’s Rudder Pedal Assembly, PART A, incorporated.”
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Rudder Pedal Tubes Tapered Holes --- Locator

Figure 1 (Sheet 1 of 1)

rsb601r27162_003.cgm, sc/cr, 5--mar--2013

A

A

B

B

1

2 3

4

LEGEND

1. Pin, cotter

MS24665--132.

2. Nut, self--locking

MS17826--3.

3. Washer

AN975--3.

4. Pin, tapered

AN386--2--14.

5. Tube, rudder pedal

600--90204--3.

6. Fitting, connecting rod.

7. Rod assembly, control.

8. Bolt.

9. Washer.

0.250 in.

(6.35 mm)

RUDDER

PEDAL

(REF)

INSPECTION

AREA

C

TYPICAL

C

5

6

9 8

7

P1

AFT TAPERED HOLES

(REF)
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PART B --- Replacement of the Rudder Bar Assemblies on the Pilot’s Rudder Pedal

Assembly

REFERENCE DESIGNATION

AMM 20---24---00---910---801 Cotter Pins --- Maintenance Practices

AMM 27---21---01---000---801 Removal of the Rudder Pedal Assembly

AMM 27---21---01---400---801 Installation of the Rudder Pedal Assembly

AMM 32---43---14---820---801 Adjustment of the Brake Pedal Rod

SRM 51---41---04 Torque Procedures --- Bolts and Screws

SRM 51---21---16 Finish Codes

D. Job Set-Up

WARNING: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU DO

MAINTENANCE ON OR NEAR ELECTRICAL/ELECTRONIC

EQUIPMENT. IF YOU DO NOT OBEY THE SAFETY PRECAUTIONS,

INJURIES TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT CAN

OCCUR.

E. Procedure

(1) Remove the pilot’s rudder pedal assembly (refer to AMM

27---21---01---000---801).

Refer to Figure 2.

(2) Do the steps that follow to remove the rudder bar assemblies (1) on the pilot’s

rudder pedal assembly.

NOTE: The procedure that follows is applicable for one rudder bar assembly

(1). The procedure for the other rudder bar assembly (1) is the same.

(a) At the pedal assembly (2), remove and discard the cotter pin (5).

(b) Remove the nut (6) and the washer (7) that connect the pedal assembly

(2) to the rudder bar assembly (1) and the pedal link (8). Discard the nut

(6).

(c) Remove the pedal assembly (2).

(d) At the brake control lever (4), remove and discard the cotter pin (9).

(e) Remove the nut (10), the washers (11), and the bolt (12), that connect

the brake control rod (3) to the brake control lever (4). Discard the nut

(10)
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(f) Remove and keep the brake control rod (3) and the pedal link (8).

NOTE: The pedal link (8) must not be disconnected from the brake

control rod (3).

(g) At the outboard end of the rudder pedal assembly, remove and discard

the cotter pin (13).

(h) Remove the nut (14) and the washer (15) from the pivot bolt (16).

Discard the nut (14).

(i) Remove the pivot bolt (16) and the brake control levers (4).

(j) Remove and discard the rudder bar assemblies (1).

(3) Do the steps that follow to install the new rudder bar assemblies (1) on the

pilot’s rudder pedal assembly.

NOTE: The procedure that follows is applicable for one rudder bar assembly

(1). The procedure for the other rudder bar assembly (1) is the same.

(a) Put the outboard brake control lever (4) in position between the

outboard rudder bar assembly (1) and the outboard face of the center

attachment lug on the torque tube assembly (17).

(b) Put the inboard brake control lever (4) in position between the inboard

rudder bar assembly (1) and the inboard face of the center attachment

lug on the torque tube assembly (17).

(c) Align the inner bores of the inboard and the outboard rudder bar

assemblies (1), the inboard and the outboard brake control levers (4),

and the three attachment lugs on the torque tube assembly.

(d) Assemble the rudder bar assembly (1) together with the pivot bolt (16)

wet with CA1000 corrosion inhibiting compound or Mastinox compound

(refer to SRM 51---21---16).

(e) Install the washer (15) and the new nut (14) on the bolt (16).

(f) Torque the nut (14) to 200---300 lbf ̄in.(23---34 N ̄m) (refer to SRM

51---41---04, Class 2).

(g) Safety the nut (14) with the cotter pin (13) (refer to AMM

20---24---00---910---801).
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(h) Connect the brake control rod (3) to the brake control lever (4) with the

bolt (12) and the washer (11), and the new nut (10). Make sure that the

bolt (12) is installed so that it points towards the center-line of the rudder

pedal assembly.

(i) Torque the nut (10) (refer to SRM 51---41---04).

(j) Safety the nut (10) with the cotter pin (9) (refer to AMM

20---24---00---910---801).

(k) Connect the pedal assembly (2) to the rudder bar assembly (1) and the

pedal link (8) with the washer (7) and the new nut (6).

(l) Torque the nut (6) to 150---200 lbf ̄ in.(17---23 Nm) (refer to SRM

51---41---04, Class 2).

(m) Safety the nut (6) with the cotter pin (5) (refer to AMM

20---24---00---910---801).

(4) With an indelible ink pen or equivalent, identify the rudder bar assemblies as

shown in the table that follows:

NOTE: The new part number must be written below the serial number of the

rudder bar assemblies (1).

RUDDER BAR

ASSEMBLY PART

NUMBER

PEDAL ASSEMBLY

PART NUMBER

NEW PART NUMBER

OF THE RUDDER BAR

ASSEMBLY

BA670---93413---1 600---90240---1 K601R90200---3

BA670---93413---2 600---90240---2 K601R90200---4

BA670---93413---1 600---90240---3 K601R90200---5

BA670---93413---2 600---90240---4 K601R90200---6

(5) Install the pilot’s rudder pedal assembly (refer to AMM

27---21---01---400---801).

(6) At the applicable rudder pedal cover, turn the stature control crank to move

the rudder pedals to the fully aft position. Push on the rudder pedals to move

them through their full range of travel. Make sure that there is a minimum

clearance of 0.250 inch (6.35 mm) between the brake control lever (4) (and its

related attaching parts) and the adjacent brake control lever, other

components, or structure.
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(7) Turn the stature control crank to move the rudder pedals to the fully forward

position. Push on the rudder pedals to move them through their full range of

travel. Make sure that there is a minimum clearance of 0.250 inch (6.35 mm)

between the brake control lever (4) (and its related attaching parts) and the

adjacent brake control lever, other components, or structure.

(8) Turn the stature control crank to set the rudder pedals to the middle position

again (count the number of turns from fully forward to fully aft and divide by

two).

(9) Make sure that there is a clearance of 0.125 in. (3.175 mm) between the side

panel, the adjacent parts, and the rudder bar assembly (1) during the

movement of the pedal assemblies (2) (refer to View C ---C).

F. Job Close-Out

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

(2) Do the adjustment of the brake pedal rods (refer to AMM

32---43---13---820---801).

(3) When PART B of this service bulletin is completed, make this entry in the

applicable logbooks: “Service Bulletin 601R---27---162, Flight Controls ---

Rudder Control System --- Inspection of Rudder Pedal Tubes P/N

600---90204---3 for Cracks and Replacement of the Rudder Bar Assemblies on

the Pilot’s Rudder Pedal Assembly, PART B, incorporated.”
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Rudder Bar Assemblies --- Replacement

Figure 2 (Sheet 1 of 2)

rsb601r27162_001.cgm, sc/cr, 13--mar--2013

5

6 7 8

A

A

1

16

3

10 9

4

12

15

13

14

2

17

LEGEND

1. Rudder bar assembly

600--90204--9 or

600--90204--10 or

BA670--93408--2 (Pre--Mod),

BA670--93413--1 or

BA670--93413--2 (Post--Mod).

2. Pedal assembly.

3. Control rod, rudder pedal brake.

4. Lever, brake assembly.

5. Pin, cotter

MS24665--372.

7. Washer.

8. Link, pedal.

9. Pin, cotter

MS24665--153.

10. Nut

MS17826--3.

11. Washer.

12. Bolt.

13. Pin, cotter

MS24665--372.

14. Nut,

MS17826--12.

15. Washer.

16. Bolt, pivot.

17. Torque tube.

BA670--93408--1 or

6. Nut

MS17826--9.

ATTACHMENT

LUG (REF)

11
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Rudder Bar Assemblies --- Replacement

Figure 2 (Sheet 2 of 2)

rsb601r27162_002.cgm, sc, 9 feb 2013

CONSOLE

(REF)

CONSOLE

(REF)

B

C

B

C -- C

C

RUDDER

BAR

(REF) SIDE

PANEL

(REF)

SIDE

PANEL

(REF)

A minimum clearance of

necessary between the

rudder bar assembly and

NOTE

0.125 in. (3.17 mm) is

the side panel.
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3. MATERIAL INFORMATION

A. Kit Information

Kit Contents:

KIT 601R27 ---162K1

PART NUMBER QTY NAME ALTERNATE

PARTS NOTES

BA670---93413---1 1 Bar assembly, rudder --- ---

BA670---93413---2 1 Bar assembly, rudder --- ---

MS17826---12 1 Nut, self locking MS14145L ---12 ---

MS17826---3 2 Nut, self locking MS14145L ---3 ---

MS17826---9 2 Nut, self locking MS14145L ---9 ---

MS24665---153 2 Pin, cotter --- ---

MS24665---372 2 Pin, cotter --- ---

B. Consumable Information

The materials that follow are necessary to do this service bulletin. You can order

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

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

of the material.

CONSUMABLES

SPECIFICATION QTY NAME REFERENCE

MS20995C20 As

necessary

Lockwire,

corrosion-resistant steel

05---003 ¡

¡ Refer to AMM 51---31---00---990---801

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

appendix that are given as references in this service bulletin

C. Special Tools and Equipment

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

appendix that are given as references in this service bulletin.
SERVICE BULLETIN 601R---27 ---162

SB 601R---27---162

Page 20 of 20

April 05/2013

D. Disposition of Parts

The table that follows shows the disposition of parts on the aircraft (or spares), and

the relationship between these parts to the new parts to be installed through the

incorporation of this service bulletin.

PRE-SB

PART NUMBER

NAME QTY DC POST-SB

PART NUMBER

NAME

600---90204---9

OR

BA670---93408---1

Bar

assembly,

rudder

1 DIS BA670---93413---1

Bar

assembly,

rudder

600---90204---10

OR

BA670---93408---2

Bar

assembly,

rudder

1 DIS BA670---93413---2

Bar

assembly,

rudder

Disposition code (DC):

DIS: Discard Part.

1
APPENDIX A

Page A1 of A10

Apr 05/2013

APPENDIX A

SERVICE BULLETIN 601R -- 27 -- 162

NON-DESTRUCTIVE TESTING (NDT) PROCEDURE

The procedure contained in this appendix is given as reference in the

Accomplishment Instructions of Service Bulletin 601R---27---162.
APPENDIX A

SERVICE BULLETIN 601R---27 ---162

APPENDIX A

Page A2 of A10

Apr 05/2013

SPECIAL DETAILED INSPECTION OF THE PILOT’S RUDDER PEDAL TUBES AT THE

CONNECTING ROD FITTING

1. General

A. The nondestructive testing procedure that follows is for the inspection of surface

cracks in the parts that follow:

---Pilot’s left and right Rudder Pedal Tubes at the Connecting Rod Fitting.

B. This inspection must be done by a Level II or Level III eddy current qualified

individual certified to an NDT Standard approved by the National Airworthiness

Authority.

2. Effectivity: All aircraft

3. Job Set-Up Information

A. Tools and Equipement

REFERENCE DESIGNATION

Hocking Phasec 2200 Eddy Current Instrument-Impedance --- Plane Type

Techna NDT SPEN92-5 Surface Probe 90 deg. Tip, 50 to 500 kHz frequency,

NFe, Absolute shielded 0.062 in. (1.57 mm) tip

diameter, 5.00 in. (12.7mm) length, 0.250 in. (6.35

mm) tip length

Al 29---32 Bombardier Aerospace CRS, made from Aluminum

alloy (Conductivity value of 29% to 32% IACS),

containing 0.008 in. (0.20 mm), 0.020 in. (0.5 mm)

and 0.040 in. (1.02 mm) deep electrical discharge

machined (EDM) notches. Refer to Figure 2

Commercially Available Coaxial Cable --- BNC to Microdot

Commercially Available Non-conductive plastic plug (insert)

Commercially Available Explosion proof light source
APPENDIX A

SERVICE BULLETIN 601R---27 ---162

APPENDIX A

Page A3 of A10

Apr 05/2013

NOTE: Equivalent equipment can be used for area access or personal selection. It

must satisfy the requirement of the task and resolve the reference notches in

the calibration reference standard at the required level of resolution and

sensitivity.

To get access to the inspection area due to accessibility or user preference,

it is permissible to use a probe of different configuration from the one

specified. The test frequency used may range from 100 kHz to 2.0 MHz for

surface inspection.

B. Parts

ITEM No. DESIGNATION DRAWING NUMBER MATERIAL

1 Rudder Pedal Tube 600---90204---3 2024---T3

C. Reference Information

REFERENCE DESIGNATION

NDT 51---20---06 (Part 01) Eddy current --- General Information

AMM Rudder Pedal Assembly Removal/Installation

SRM Finish Codes

SRM Cleaning

4. Preparation and Cleaning

A. Make sure the inspection area is clean.

B. If the finish on the inspection area is damaged or deteriorated, removre the finish.
APPENDIX A

SERVICE BULLETIN 601R---27 ---162

APPENDIX A

Page A4 of A10

Apr 05/2013

5. Procedure

Refer to Figures 1, 2, and 3.

A. Do the steps that follow for the inspection of the Rudder Pedal Tubes at the

Connecting Rod Fitting.

NOTE: The manufacturer’s instrument instructions must be obeyed when you

operate the test equipment.

(1) Calibrate the equipment as follows:

(a) Connect probe SPEN92---5 with the coaxial cable to the eddy

current instrument.

(b) Turn the instrument ON. Adjust and set the instrument controls as

shown in Figure 1.

(c) Place the probe (coil) tip perpendicular to the surface of the AL

29---32 calibration reference standard (CRS), away from the 0.040

in. (1.02 mm) deep EDM notch and the edge.

(d) Balance [BAL] the eddy current instrument. Adjust the instrument

[PHASE] control to get a horizontal lift-off signal moving from

right-to-left (with increasing lift-off) across the screen display.

(e) Slide the probe (coil) tip across the 0.040 in. (1.02 mm) deep EDM

notch, and adjust the instrument sensitivity (gain) to get an

amplitude signal as shown in Figure 1, screen display.
APPENDIX A

SERVICE BULLETIN 601R---27 ---162

APPENDIX A

Page A5 of A10

Apr 05/2013

(2) Lift-Off Compensation verification:

(a) After the calibration, as outlined in paragraph 5.A.(1)., place the

probe (coil) tip perpendicular to the inspection surface. DO NOT

balance the instrument.

(b) Compare the screen displays between the operating point on the

inspection surface and the balance point on the CRS for the

following conditions.

(c) If the operating point on the inspection surface matches the

balance point on the CRS, no compensation for paint thickness is

required. Proceed to the inspection procedure.

(d) If the operating point on the inspection area does not match the

balance point on the CRS, but has moved to the LEFT,

compensation for the paint thickness is required. Do the following:

1 Attach a strip of nonconductive tape or shim to cover the CRS

surface including the EDM notches.

2 Place the probe (coil) perpendicular to the surface of the

CRS. DO NOT balance the instrument. Compare the

operating point on the inspection surface to the balance point

on the CRS.

3 If the operating point on the inspection surface is still left of

the balance point on the CRS, add an additional strip of tape

or shim until the balance point on the CRS matches the

operating point of the inspection area.

4 If the operating point on the inspection surface is to the right

of the

balance point on the CRS, remove a strip of tape or shim until

the balance point on the CRS matches the operating point of

the inspection area.

5 If lift-off compensation and calibration requirements cannot be

met, remove the paint or coating before the inspection.
APPENDIX A

SERVICE BULLETIN 601R---27 ---162

APPENDIX A

Page A6 of A10

Apr 05/2013

(3) Examine the Pilot’s Rudder Pedal Tubes at the Connecting Rod Fitting

holes as follows:

Refer to Figures 1 and 3.

NOTE: Monitor the screen display carefully at all times and make a note of all

distinct relevant indications. Include the screen height of each signal

and its relative location on the part.

NOTE: Use a nonconductive plastic plug (insert) for circular scans around the

holes. No part of the plug (insert) shall cover the inspection surface to

minimize the distance between the probe coil and the hole.

(a) After the calibration, as outlined in step 5.A.(1). and 5.A.(2)., insert

the plastic plug into the aft tapered hole of the pilot’s left rudder

pedal tube and position the probe (coil) tip against the plug

(insert).

(b) Balance [BAL] the instrument. If necessary, adjust instrument

[PHASE] control to get a horizontal lift-off signal moving from

right-to-left across the screen display. Refer to Figure 1.

(c) Make a full circular (360 degrees) scan around the tapered hole

using the plug (insert) as a probe guide. Make sure that the probe

(coil) tip stays perpendicular to the inspection surface at all times

during the scan. Refer to the inspection area and typical scan path

shown in Figure 3.

(d) Continue making full circular (360 degrees) scans around the

tapered hole using a probe index of one probe diameter or less

between scans until a width of 0.250 in. is reached. Make sure that

the probe stays perpendicular to the inspection surface.

(e) Repeat steps 5.A.(3).(a). to 5.A.(3).(d), for the remaining aft

tapered hole.

(f) Repeat steps 5.A.(3).(a) to 5.A.(3).(e) for the pilot’s right side

rudder pedal tube.
APPENDIX A

SERVICE BULLETIN 601R---27 ---162

APPENDIX A

Page A7 of A10

Apr 05/2013

(4) Do the evaluation of Indications as follows:

(a) Any clear vertical deflection signal that occurs over a short scan

distance (one probe tip diameter) is considered a suspect

indication and is cause for further investigation.

(b) Any rapid up dot movement signal that stays at the up position

over a longer scan distance is considered a suspect indication and

is cause for further investigation.

(c) Make sure that the indication is not caused by edge effect, abrupt

change in geometry, localized variation in conductivity, permeability

or other non-relevant factors.

(d) Examine all suspect crack indications by comparing their phase

angle, amplitude and shape to the calibration standard notch EDM

signal.

(e) If a crack is detected, determine its length and location.

(5) Do the acceptance and rejection criteria as follows:

(a) Any clear vertical deflection signal which is equal to 50% or greater

than the response from the 0.040 in. (1.02 mm) deep EDM notch

as shown in Figure 1 is classified as a crack indication and cause

for rejection.

(b) Any rapid upward dot movement signal which equals to 50% or

greater than the response from the 0.040 in. (1.02 mm) deep EDM

notch as shown in Figure 1 and stays at the upward position

momentarily or over a longer period of time is classified as a crack

indication and cause for rejection.

(c) Record and report results in accordance with company guidelines

and policies.

(6) Close Out

(a) If the finish in the inspection area was removed, replace the finish.
APPENDIX A

SERVICE BULLETIN 601R---27 ---162

APPENDIX A

Page A8 of A10

Apr 05/2013

Calibration Data for CRS AL 29-32 (Hocking Phasec 2200 Eddy Current Instrument

and Probe SPEN92-5)

Figure 1 (Sheet 1 of 1)

rsb601r27162_004.cgm, sc, 15 feb 2013

CH 1 FREQ

CH 1 PHASE

CH 1

500 KHz

X --8 dB

INSTRUMENT SETTINGS SCREEN DISPLAY

ABS CH1

XY

342.0

44.5 dB

DC

200 Hz

47

40

--40

MODE

DISPLAY

VIEW

GAIN

HI--PASS

LO--PASS

BAL. LOAD

X--POS

Y--POS

X:Y

H

SIGNAL FROM

0.040 in. (1.02 mm)

DEEP EDM NOTCH

EDGE SIGNAL

100%

0%

LIFT--OFF SIGNAL

BALANCE

POINT

80%

FSH

NOTE: Values listed in Figure 1 can vary between instruments.
APPENDIX A

SERVICE BULLETIN 601R---27 ---162

APPENDIX A

Page A9 of A10

Apr 05/2013

Bombardier Aerospace Calibration Reference Standard AL 29-32

Figure 2 (Sheet 1 of 1)

3.

2.

NOTES

Material; 2024--T3, QQ--A--250/4.

Finish surface or better.

Penetrant inspect NDTM 51--20--08

Identification sticker, 0.125 in. (3.18 mm) letters black color.

1.

4

125

5. EDM notches shall have a tolerance of +/--0.0001 in. (+/--0.025mm)

3.75 in.

(95.3 mm)

1.00 in.

(25.4 mm)

0.040 in.

(1.02 mm)

0.020 in.

(0.51 mm)

0.008 in.

(0.20 mm)

0.25 in.

(6.4 mm)

0.75 in.

(19.1 mm)

0.75 in.

(19.1 mm)

1.50 in.

(38.1 mm)

0.005 in. (0.13 mm)

WIDE

(TYPICAL)

4

4

4

4

rsb601r27162_005.cgm, sc, 15 feb 2013

for depth and +0.00/--0.002 in. (+0.000/--0.051mm) for width.
APPENDIX A

SERVICE BULLETIN 601R---27 ---162

APPENDIX A

Page A10 of A10

Apr 05/2013

Inspection Area and Typical Scan Path of Rudder Pedal Tubes at the Connecting

Rod Fittings

Figure 3 (Sheet 1 of 1)

INSPECT THE EDGES OF

THE 2 AFT TAPERED HOLES.

TUBE ROTATED FOR CLARITY. INSPECT AROUND THE 2 AFT

TAPERED HOLES.

rsb601r27162_006.cgm, sc, 15 feb 2013

TYPICAL SCAN PATH EXTENDING

0.250 IN. (6.35 mm)

FROM THE HOLE

A
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 : 601R-27-162 ISSUE: NC

 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