# Bombardier Service Bulletin 601R-27-162

Copy: No revision named ("U.S. DOT/FAA - Service Bulletin - 601R-27-162"), 31 pages: PDF https://openairdocs.org/files/sha256/84/da/84da3e1d3928f2c5cece094a35a42f6a5b7d73f69267f59aa1ecc82936b0fe2c; text https://openairdocs.org/service-documents/bombardier/601r-27-162/file/84da3e1d3928.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2013-0700; AD 2013-24-02 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Bombardier](https://openairdocs.org/service-documents/bombardier.md)
- Type: Service bulletin (Service Bulletin)
- Number: 601R-27-162
- Page: https://openairdocs.org/service-documents/bombardier/601r-27-162

## ADs that cite it (1) (OpenAirDocs)

Newest first, with the revision each names, as OpenAirDocs read it from the AD's text.

- [AD 2013-24-02](https://openairdocs.org/ad/2013-24-02.md), effective Jan 6, 2014: No revision named

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/bombardier/601r-27-162/proposed.md).

## Text (31 pages)

Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2013-0700; AD 2013-24-02 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

SB 601R- - - 27- - - 162
Page 1 of 20
April 05/2013
SERVICE BULLETIN
T echnical
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.

### Page 2

SERVICE BULLETIN 601R- - -27- - -162
SB 601R- - - 27- - - 162
Page 2 of 20
April 05/2013
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.

### Page 3

SERVICE BULLETIN 601R- - -27- - -162
SB 601R- - - 27- - - 162
Page 3 of 20
April 05/2013
D. Compliance
Recommended Service Bulletin. Bombardier recommends that PART A of this
s e r v i c eb u l l e t i nb ed o n ea ss h o w ni nt h et a b l eb e l o w ,u n l e s so t h e r w i s ed i r e c t e db y
the airworthiness authority of the operator.
NOTE: It is not necessary to do PART A of this service bulletin if PART B of this
s e r v i c eb u l l e t i ni sd o n eb e f o r e .
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 orbefore 26,300 flight cycles
25,000± to <30,000 In 1,300 flight cycles or less orbefore 30,800 flight cycles
30,000± to <33,000 In 800 flight cycles or less orbefore 33,500 flight cycles
33,000± to <37,000 In 500 flight cycles or less orbefore 37,300 flight cycles
>37,000 In 300 flight cycles or less
B o m b a r d i e rr e c o m m e n d st h a tP A R TBo ft h i ss e r v i c eb u l l e t i nb ed o n ea tt h ee a r l i e s t
convenience of the operator, unless otherwise directed by the airworthiness
authority of the operator.
This service bulletin affects Airworthiness Limitations (AWLs) and/or Damage
T olerance 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.

### Page 4

SERVICE BULLETIN 601R- - -27- - -162
SB 601R- - - 27- - - 162
Page 4 of 20
April 05/2013
F. M a n p o w e r
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) T est 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.

### Page 5

SERVICE BULLETIN 601R- - -27- - -162
SB 601R- - - 27- - - 162
Page 5 of 20
April 05/2013
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) T est 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
A N 3 8 6 --- 2 --- 1 4 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

### Page 6

SERVICE BULLETIN 601R- - -27- - -162
SB 601R- - - 27- - - 162
Page 6 of 20
April 05/2013
(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. T ooling - - - 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

### Page 7

SERVICE BULLETIN 601R- - -27- - -162
SB 601R- - - 27- - - 162
Page 7 of 20
April 05/2013
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-SBPART 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

### Page 8

SERVICE BULLETIN 601R- - -27- - -162
SB 601R- - - 27- - - 162
Page 8 of 20
April 05/2013
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
A M M 0 6 --- 4 1 --- 0 0 --- 0 0 Fuselage Access - - - Description and Operation
A M M 1 2 --- 0 0 --- 0 7 --- 8 6 1 --- 8 0 1 Connect External AC Power
A M M 1 2 --- 0 0 --- 0 7 --- 8 6 1 --- 8 0 2 Remove External AC Power
A M M 2 0 --- 2 4 --- 0 0 --- 9 1 0 --- 8 0 1 Cotter Pins - - - Maintenance Practices
A M M 2 0 --- 2 4 --- 0 0 --- 9 1 0 --- 8 0 2 Lockwire - - - Maintenance Practices
A M M 2 7 --- 2 1 --- 0 0 --- 7 1 0 --- 8 0 1Operational T est of the Rudder Control
System
A M M 5 1 --- 2 6 --- 0 0 --- 1 1 0 --- 8 0 1 Solvent Cleaning
A M M 5 3 --- 1 0 --- 3 4 --- 0 0 0 --- 8 0 1Removal of the Forward Fuselage Access Pan-
els
A M M 5 3 --- 1 0 --- 3 4 --- 4 0 0 --- 8 0 1Installation of the Forward-Fuselage Access
Panels
S R M 5 1 --- 2 6 --- 0 0 Fluid-Resistant (FR) Epoxy Primer
S R M 5 1 --- 4 1 --- 0 4 T orque Procedures - - - Bolts and Screws
S R M 5 1 --- 4 3 --- 0 0 Ta p e r P i n s
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:
--- F L I G H T C O N T R O L S
- - -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 .

### Page 9

SERVICE BULLETIN 601R- - -27- - -162
SB 601R- - - 27- - - 162
Page 9 of 20
April 05/2013
(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
o nt h el e f ts i d e( r e f e rt oV i e wA ) .
(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).

### Page 10

SERVICE BULLETIN 601R- - -27- - -162
SB 601R- - - 27- - - 162
Page 10 of 20
April 05/2013
(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) T orque 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
a s s e m b l yo nt h el e f ts i d e( r e f e rt oV i e wA ) .
(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 T echnical Help Desk, before next
flight, at phone number 514-855-8500 for an approved disposition.

### Page 11

SERVICE BULLETIN 601R- - -27- - -162
SB 601R- - - 27- - - 162
Page 11 of 20
April 05/2013
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.”

### Page 12

SERVICE BULLETIN 601R- - -27- - -162
SB 601R- - - 27- - - 162
Page 12 of 20
April 05/2013
Rudder Pedal Tubes T apered Holes - - - Locator
F i g u r e1( S h e e t1o f1 )
rsb601r27162_003.cgm, sc/cr, 5- -mar- -2013
A
A
B
B
1
23
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)

### Page 13

SERVICE BULLETIN 601R- - -27- - -162
SB 601R- - - 27- - - 162
Page 13 of 20
April 05/2013
PART B - - - Replacement of the Rudder Bar Assemblies on the Pilot’s Rudder Pedal
Assembly
REFERENCE DESIGNATION
A M M 2 0 --- 2 4 --- 0 0 --- 9 1 0 --- 8 0 1 Cotter Pins - - - Maintenance Practices
A M M 2 7 --- 2 1 --- 0 1 --- 0 0 0 --- 8 0 1Removal of the Rudder Pedal Assembly
A M M 2 7 --- 2 1 --- 0 1 --- 4 0 0 --- 8 0 1Installation of the Rudder Pedal Assembly
A M M 3 2 --- 4 3 --- 1 4 --- 8 2 0 --- 8 0 1 Adjustment of the Brake Pedal Rod
S R M 5 1 --- 4 1 --- 0 4 T orque Procedures - - - Bolts and Screws
S R M 5 1 --- 2 1 --- 1 6 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 ) .T h ep r o c e d u r ef o rt h eo t h e rr u d d e rb a ra s s e m b l y( 1 )i st h es a m e .
(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)

### Page 14

SERVICE BULLETIN 601R- - -27- - -162
SB 601R- - - 27- - - 162
Page 14 of 20
April 05/2013
(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 ) .T h ep r o c e d u r ef o rt h eo t h e rr u d d e rb a ra s s e m b l y( 1 )i st h es a m e .
(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),
a n dt h et h r e ea t t a c h m e n tl u g so nt h et o r q u et u b ea s s e m b l y .
(d) Assemble the rudder bar assembly (1) together with the pivot bolt (16)
wet with CA1000 corrosion inhibiting compound or Mastinox compound
( r e f e r t o S R M 5 1 --- 2 1 --- 1 6 ) .
(e) Install the washer (15) and the new nut (14) on the bolt (16).
(f) T orque 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).

### Page 15

SERVICE BULLETIN 601R- - -27- - -162
SB 601R- - - 27- - - 162
Page 15 of 20
April 05/2013
(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) T orque 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) T orque 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
s h o w ni nt h et a b l et h a tf o l l o w s :
NOTE: The new part number must be written below the serial number of the
rudder bar assemblies (1).
RUDDER BAR
ASSEMBL Y PART
NUMBER
PEDAL ASSEMBL Y
PART NUMBER
NEW PART NUMBER
OF THE RUDDER BAR
ASSEMBL Y
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.

### Page 16

SERVICE BULLETIN 601R- - -27- - -162
SB 601R- - - 27- - - 162
Page 16 of 20
April 05/2013
(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. J o b C l o s e - O u t
(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.”

### Page 17

SERVICE BULLETIN 601R- - -27- - -162
SB 601R- - - 27- - - 162
Page 17 of 20
April 05/2013
Rudder Bar Assemblies - - - Replacement
F i g u r e2( S h e e t1o f2 )
rsb601r27162_001.cgm, sc/cr, 13- -mar- -2013
5
6 7 8
A
A
1
16
3
109
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. T orque tube.
BA670- -93408- -1 or
6. Nut
MS17826- -9.
ATTACHMENT
LUG (REF)
11

### Page 18

SERVICE BULLETIN 601R- - -27- - -162
SB 601R- - - 27- - - 162
Page 18 of 20
April 05/2013
Rudder Bar Assemblies - - - Replacement
F i g u r e2( S h e e t2o f2 )
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.

### Page 19

SERVICE BULLETIN 601R- - -27- - -162
SB 601R- - - 27- - - 162
Page 19 of 20
April 05/2013
3. MATERIAL INFORMATION
A. Kit Information
Kit Contents:
KIT 601R27 - - -162K1
PART NUMBER QTY NAME ALTERNATEPARTS 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. Y ou 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¡
¡ R e f e r t o A M M 5 1 --- 3 1 --- 0 0 --- 9 9 0 --- 8 0 1
NOTE: T o complete this list of consumables, refer to the different tasks and the
appendix that are given as references in this service bulletin
C. Special T ools 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.

### Page 20

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

### Page 21

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.

### Page 22

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. T ools and Equipement
REFERENCE DESIGNATION
Hocking Phasec 2200 Eddy Current Instrument-Impedance - - - Plane T ype
T echna 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

### Page 23

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.
T o 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 T ube 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.

### Page 24

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 T ubes 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
s h o w ni nF i g u r e1 .
(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.

### Page 25

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
s u r f a c ei n c l u d i n gt h eE D Mn o t c h e s .
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
b a l a n c ep o i n to nt h eC R S ,r e m o v eas t r i po ft a p eo rs h i mu n t i l
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.

### Page 26

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
s h o w ni nF i g u r e3 .
(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.

### Page 27

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.

### Page 28

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)
F i g u r e1( S h e e t1o f1 )
rsb601r27162_004.cgm, sc, 15 feb 2013
CH 1 FREQ
CH 1 PHASE
CH 1
500 KHz
X- - 8d B
INSTRUMENT SETTINGS SCREEN DISPLA Y
ABS CH1
XY
342.0
44.5 dB
DC
200 Hz
47
40
-- 4 0
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.

### Page 29

APPENDIX A
SERVICE BULLETIN 601R- - -27- - -162
APPENDIX A
Page A9 of A10
Apr 05/2013
Bombardier Aerospace Calibration Reference Standard AL 29-32
F i g u r e2( S h e e t1o f1 )
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.

### Page 30

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
F i g u r e3( S h e e t1o f1 )
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

### Page 31

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

---
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