# Bombardier Service Bulletin 215-4477

Copy: Revision 2 ("SB 215-4477 Rev 2"), 22 pages: PDF https://openairdocs.org/files/sha256/ec/ac/ecac1e956287e7fc673fedcbf6723a51dcc23150ef4ba34b6f7e02cc71643001; text https://openairdocs.org/service-documents/bombardier/sb-215-4477/file/ecac1e956287.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2018-1070; AD 2019-08-12 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: 215-4477
- Latest revision known: 215-4477, Revision 2, dated September 29, 2015 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/bombardier/sb-215-4477

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

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

- [AD 2019-08-12](https://openairdocs.org/ad/2019-08-12.md), effective Jun 13, 2019: Revisions 1 and 2

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/bombardier/sb-215-4477/proposed.md).

## Text (22 pages)

Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2018-1070; AD 2019-08-12 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

the evolution of mobility
Service Bulletin 215-4477Sept. 29/15
ATA Ref: 27−10Page 1 of 1
MODEL CL-215-6B11 (415)
REVISION TRANSMITTAL SHEET
SERVICE BULLETIN
215−4477
FLIGHT CONTROLS
REPLACEMENT OF POWERED AILERON SYSTEM TEFLON /C0084 PARTS DUE TO EXCESS CHARGE
OF FIBERGLASS
Service Bulletin No.: 215 −4477 Date of Original Issue: Sept. 30/13
Revision No.: 2 Date of Issue: Sept. 29/15
NOTES: 1. NO RETROACTIVE ACTION IS REQUIRED ON AIRCRAFT
MODIFIED TO THE PREVIOUS ISSUE OF THIS SERVICE
BULLETIN.
2. This revision supersedes the previous issue of this Service Bulletin.
3. Black bars in the left margin of this Service Bulletin and the details on
this Revision Transmittal Sheet refer to changes made since the
previous issue.
This Revision is issued to:
1. Revise Paragraph 1.A. Planning Information to change the compliance date in Part B from
April 30, 2015 to April 30, 2016.
2. Revise Paragraph 1.K. References to change the revision level of Bombardier Aerospace
Restriction and/or Special Instruction (RSI) C −3934 from Issue B−1 to Issue C.
3. Make other miscellaneous non −technical changes.

### Page 2

the evolution of mobility
Service Bulletin 215-4477Rev. NC  Sept. 30/13
Rev. 2  Sept. 29/15
ATA Ref: 27−10Page 1 of 20
Refer to applicable governmental agency regulations and requirements and make sure that the work described in this Service Bulletin is performed in compliance with manufacturer’s recommendations
and/or acceptable industry standards.  This document is proprietary to Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or by any means without the prior 
written consent of Bombardier Inc. or its affiliates.  This disclaimer applies to this, and all Service Bulletins listed in the 215−4000 Index, and those posted on the Bombardier Amphibious Aircraft 
web site:  www.support.amphibious.bombardier.com.
MODEL CL-215-6B11 (415)
SERVICE BULLETIN
215−4477
FLIGHT CONTROLS
REPLACEMENT OF POWERED AILERON SYSTEM TEFLON/C0084 PARTS DUE TO EXCESS CHARGE
OF FIBERGLASS
1. Planning Information
A. Compliance
SPECIAL NOTICE OF COMPLIANCE
THE MODIFICATION DESCRIBED IN THIS SERVICE BULLETIN IS KNOWN TO BE OF
SPECIAL INTEREST TO TRANSPORT CANADA.  IT IS EXPECTED THAT TRANSPORT
CANADA WILL ISSUE AN AIRWORTHINESS DIRECTIVE CONCERNING THIS
SERVICE BULLETIN IN THE FUTURE.  OTHER REGULATORY AUTHORITIES MAY
APPLY SIMILAR REQUIREMENTS.
This Service Bulletin is recommended.  The parts replacement should be completed as
follows:
− For PART A of this Service Bulletin, the Teflon/C0116 parts listed must be replaced before
April 30, 2014.
− For PART B of this Service Bulletin, the Teflon/C0116 parts listed must be replaced before
April 30, 2016.
− For PART C of this Service Bulletin, the Teflon/C0116 parts listed must be replaced not later than
the next scheduled 72 Month inspection.
NOTE: This Service Bulletin is applicable only to aircraft in the condition as originally
delivered by Canadair and/or Bombardier Aerospace or as subsequently modified by
Canadair and/or Bombardier Aerospace Service Bulletin(s).  Prior to incorporation of
this Service Bulletin, the status of any related systems or structural modification(s)
introduced by Supplementary Type Approval (STA) or equivalent action must be
examined for compatibility with the modifications and test procedures (if applicable)
detailed in this Service Bulletin.

### Page 3

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4477Rev. NC  Sept. 30/13
Rev. 2  Sept. 29/15
ATA Ref: 27−10Page 2 of 20
Refer to applicable governmental agency regulations and requirements and make sure that the work described in this Service Bulletin is performed in compliance with manufacturer’s recommendations
and/or acceptable industry standards.  This document is proprietary to Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or by any means without the prior 
written consent of Bombardier Inc. or its affiliates.  This disclaimer applies to this, and all Service Bulletins listed in the 215−4000 Index, and those posted on the Bombardier Amphibious Aircraft 
web site:  www.support.amphibious.bombardier.com.
B. Approval
The technical content of this Service Bulletin has been approved under the authority of the
Design Approval Organization No: DAO #93-Q-02.
C. Effectivity
Aircraft Validity: This Service Bulletin is valid for CL-215-6B11 (415) turboprop Aircraft Serial
Nos. 2076 to 2090.
Service Effectivity: CL-215-6B11 (415) turboprop aircraft Serial Nos. 2076 to 2090.
D. Reason
The supplier has fabricated Teflon/C0116 parts with a charge of 15% fiberglass content in lieu of 5%
which is the engineering drawing requirement.  Parts manufactured with this higher percentage
of fiberglass may cause deterioration of control cables and adjacent parts due to greater
friction should they come into contact.
E. Description
This Service Bulletin provides instructions to:
− Identify the parts to be replaced.
− Identify the part locations and how to gain access to the parts.
− Replace the parts, and when necessary, to test the assembly or installation.
F. Manpower
For the work described in Part A of this Service Bulletin, we estimate that it will take 1
technician approximately 6 hours to complete.
For the work described in Part B of this Service Bulletin, we estimate that it will take 1
technician approximately 12 hours to complete.
For the work described in Part C of this Service Bulletin, we estimate that it will take 1
technician approximately 46 hours to complete.
G. Material Availability
Contact you Customer Spare Parts Representative for parts availability and prices.
For the parts required for Part A of this Service Bulletin, the parts will be available by
mid September, 2013.
For the parts required for Part B of this Service Bulletin, the parts will be available by
mid September, 2013.
For the parts required for Part C of this Service Bulletin, the parts will be available by the end
of November, 2013.

### Page 4

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4477Rev. NC  Sept. 30/13
Rev. 2  Sept. 29/15
ATA Ref: 27−10Page 3 of 20
Refer to applicable governmental agency regulations and requirements and make sure that the work described in this Service Bulletin is performed in compliance with manufacturer’s recommendations
and/or acceptable industry standards.  This document is proprietary to Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or by any means without the prior 
written consent of Bombardier Inc. or its affiliates.  This disclaimer applies to this, and all Service Bulletins listed in the 215−4000 Index, and those posted on the Bombardier Amphibious Aircraft 
web site:  www.support.amphibious.bombardier.com.
H. Tool Availability
No special tools or equipment are necessary.
I. Weight and Balance
Not affected.
J. Electrical Load Data
Not affected.
K. References
For Bombardier Aerospace Reference only:
(Not Supplied with Kit)
Bombardier Aerospace Restriction and/or Special Instruction (RSI) C-3934 Issue C
L. Publications Affected
PSP 492, Aircraft Maintenance Manual
− 6−44−00
− 27−10−00
− 27−11−07
PSP 494, Illustrated Parts Catalogue, Chapter
− 27−11−00 Figure 3
− 27−11−00 Figure 5
− 27−25−00 Figure 1
− 27−71−00 Figure 2
PSP 497, Structural Repair Manual, Chapter:
− 51−42−01
− 51−45−01
− 51−46−01
PSP 498, Component Maintenance Manual, Chapter:
− 27−11−07
M. Related Service Bulletin
215−4476  Inspection of the Aileron Control System Cables.

### Page 5

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4477Rev. NC  Sept. 30/13
Rev. 2  Sept. 29/15
ATA Ref: 27−10Page 4 of 20
Refer to applicable governmental agency regulations and requirements and make sure that the work described in this Service Bulletin is performed in compliance with manufacturer’s recommendations
and/or acceptable industry standards.  This document is proprietary to Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or by any means without the prior 
written consent of Bombardier Inc. or its affiliates.  This disclaimer applies to this, and all Service Bulletins listed in the 215−4000 Index, and those posted on the Bombardier Amphibious Aircraft 
web site:  www.support.amphibious.bombardier.com.
2. Accomplishment Instructions
NOTES: 1. For this Service Bulletin, it is assumed that standard maintenance and repair
practices will be applied in accordance with applicable Product Support Publications
(PSP).
2. For parts location, refer to the illustrations in this Service Bulletin and the PSP
references given in the Accomplishment Instructions.
3. If any deviation exists, contact your Specialized and  Amphibious Aircraft Technical
Representative for further instructions.
4. Upon final installation of a part, refer to the illustrations in this Service Bulletin for
fastener callouts.
5. To see the locations of the affected aircraft access panels of the upper wing, refer to
the Aircraft Maintenance Manual, PSP 492, Chapter 6−44−00 WING, PYLON AND
FLOATS ACCESS PANELS − DESCRIPTION AND OPERATION.
6. For information how to set the aileron flight control system to NORMAL or MANUAL
modes, refer to the Aircraft Maintenance Manual, PSP 492, Chapter 27−10−00
CONTROL SYSTEM − DESCRIPTION AND OPERATION.
7. For information how to set the rudder flight control system to NORMAL or MANUAL
modes, refer to the Aircraft Maintenance Manual, PSP 492, Chapter 27−20−00
CONTROL SYSTEM − DESCRIPTION AND OPERATION.
8. For information on how to set the flight control surface gust lock system to either the
LOCK or UNLOCK setting, refer to the Aircraft Maintenance Manual, PSP 492,
Chapter 27−70−00, GUSTLOCK SYSTEM − DESCRIPTION AND OPERATION.
9. For information on how to release the flight control system hydraulic pressure, refer to
the Aircraft Maintenance Manual, PSP 492, Chapter 29−00−00, AILERONS,
RUDDER, OR ELEVATOR − RELEASE.
10.For information on how to remove or install the aileron artificial feel spring pot
assembly from the aileron power control unit assembly, refer to the Aircraft
Maintenance Manual, PSP 492, Chapter 27−11−07 ARTIFICIAL FEEL SPRING POT
ASSEMBLY − REMOVAL/INSTALLATION.
11. For information on how to disassemble, check, inspect, and assemble the aileron
artificial feel spring pot assembly, refer to the following in the Component
Maintenance Manual, PSP 498, 27−11−07:
− Page 301, ARTIFICIAL FEEL SPRING POT ASSEMBLY − DISASSEMBLY
− Page 501, ARTIFICIAL FEEL SPRING POT ASSEMBLY − CHECK
− Page 701, ARTIFICIAL FEEL SPRING POT ASSEMBLY − ASSEMBLY
− Page 801, ARTIFICIAL FEEL SPRING POT ASSEMBLY − FITS AND
CLEARANCES

### Page 6

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4477Rev. NC  Sept. 30/13
Rev. 2  Sept. 29/15
ATA Ref: 27−10Page 5 of 20
Refer to applicable governmental agency regulations and requirements and make sure that the work described in this Service Bulletin is performed in compliance with manufacturer’s recommendations
and/or acceptable industry standards.  This document is proprietary to Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or by any means without the prior 
written consent of Bombardier Inc. or its affiliates.  This disclaimer applies to this, and all Service Bulletins listed in the 215−4000 Index, and those posted on the Bombardier Amphibious Aircraft 
web site:  www.support.amphibious.bombardier.com.
12.For information on how to do a functional test of the aileron frictional forces, refer to
the Aircraft Maintenance Manual, PSP 492, Chapter 27−10−00 AILERON CONTROL
SYSTEM − ADJUSTMENT/TEST, Paragraph E.
13.For information on how to apply torque to threaded fasteners, refer to the Aircraft
Maintenance Manual, PSP 492, Chapter 20−21−00 TORQUING OF THREADED
FASTENERS − MAINTENANCE PRACTICES.
14.For information on how to remove and install blind rivets, refer to the Structural Repair
Manual, PSP 497 Chapter 51−46−01, BLIND RIVETS − GENERAL PROCEDURES.
15.For information on how to use rig pins and rig the gust lock system, refer to the
Aircraft Maintenance Manual, PSP 492, Chapter 27−70−00 GUST LOCK SYSTEM −
ADJUSTMENT/TEST.
16.For information on how to disassemble the aileron gust lock quadrant, refer to the
Aircraft Maintenance Manual, PSP 492, Chapter 27−71−03 AILERON GUST LOCK
QUADRANT − REMOVAL/INSTALLATION.
17.For information on how to install cotter pins, refer to Aircraft Maintenance Manual,
PSP 492, Chapter 20−71−00, SAFETYING DEVICES − MAINTENANCE
PRACTICES.
18.For information on how to remove and install the aileron power control unit, refer to
Aircraft Maintenance Manual, PSP 492, Chapter 27−11−03 POWER CONTROL UNIT
− REMOVAL/INSTALLATION.
PART A
A. Replacement of Teflon /C0116 Parts in Aileron Control Systems
WARNING: IN THE STEPS THAT FOLLOW, VERIFY THAT NO FOREIGN OBJECT DEBRIS
(FOD) REMAINS AFTER THE TEFLON/C0084 PARTS ARE REPLACED.  FOD LEFT
AFTER THE PARTS REPLACEMENT CAN INTERFERE OR JAM THE CONTROL
MECHANISMS.  FAILURE TO ENSURE THAT THE CONTROL SYSTEMS ARE
FREE OF FOD COULD LEAD TO DAMAGE TO THE EQUIPMENT OR CREATE A
FLIGHT SAFETY HAZARD.
Refer to PSP 492 Chapters 6, 27, and 29.
(1) Ensure the surface gust lock lever is set to the UNLOCKED position.  Refer to PSP 492,
Chapter 27.
(2) Release the flight control hydraulic system pressure.  Refer to PSP 492, Chapter 29.
(3) Ensure that the aileron and rudder flight control systems are set to MANUAL mode.
Refer to PSP 492, Chapter 27.
(4) Open the access panels 541 −1, and 641−1.  Refer to PSP 492, Chapter 6.

### Page 7

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4477Rev. NC  Sept. 30/13
Rev. 2  Sept. 29/15
ATA Ref: 27−10Page 6 of 20
Refer to applicable governmental agency regulations and requirements and make sure that the work described in this Service Bulletin is performed in compliance with manufacturer’s recommendations
and/or acceptable industry standards.  This document is proprietary to Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or by any means without the prior 
written consent of Bombardier Inc. or its affiliates.  This disclaimer applies to this, and all Service Bulletins listed in the 215−4000 Index, and those posted on the Bombardier Amphibious Aircraft 
web site:  www.support.amphibious.bombardier.com.
Refer to Figure 1 Detail F and PSP 494 Chapter 27−11−00 Figure 3.
(5) Replace the four rubbing strips S215 −513−20 as follows:
(a) At the left trailing edge rib structure at WS 60.80 and at approximately FS 441.00,
drill out and remove the existing MS20600AD4W4 rivets and the two rubbing strips
S215−513−20.  Discard the rubbing strips.
NOTE: Ensure that the discarded rubbing strips do not get mistaken for the
replacement rubbing strips.
(b) Install the two new rubbing strips S215 −513−20 using two new MS20600AD4W4
rivets.  Refer to PSP 497 Chapter 51.
(c) Replace the two rubbing strips S215 −513−20 at the right side trailing edge rib
structure at WS 60.80 and at approximately FS 441.00, as described in the above
mentioned steps.
(6) Install 541-1 and 641-1.  Refer to PSP 492, Chapter 6.
PART B
B. Replacement of Teflon /C0116 Parts in Aileron/Rudder Interconnect
WARNING: IN THE STEPS THAT FOLLOW, VERIFY THAT NO FOREIGN OBJECT DEBRIS
(FOD) REMAINS AFTER THE TEFLON/C0084 PARTS ARE REPLACED.  FOD LEFT
AFTER THE PARTS REPLACEMENT CAN INTERFERE OR JAM THE CONTROL
MECHANISMS.  FAILURE TO ENSURE THAT THE CONTROL SYSTEMS ARE
FREE OF FOD COULD LEAD TO DAMAGE TO THE EQUIPMENT OR CREATE A
FLIGHT SAFETY HAZARD.
Refer to PSP 492 Chapters 6, 27, and 29.
(1) Ensure the surface gust lock lever is set to the UNLOCKED position.  Refer to PSP 492,
Chapter 27.
(2) Release the flight control hydraulic system pressure.  Refer to PSP 492, Chapter 29.
(3) Ensure that the aileron and rudder flight control systems are set to MANUAL mode.
Refer to PSP 492, Chapter 27.
(4) Open the access panels 255 −1, 255−2, 255−3, 255−4, 414−3, 414−4, 424−3, 424−4 and
remove the protective, transparent covers from the aileron power control unit.  Refer to
PSP 492, Chapter 6.

### Page 8

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4477Rev. NC  Sept. 30/13
Rev. 2  Sept. 29/15
ATA Ref: 27−10Page 7 of 20
Refer to applicable governmental agency regulations and requirements and make sure that the work described in this Service Bulletin is performed in compliance with manufacturer’s recommendations
and/or acceptable industry standards.  This document is proprietary to Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or by any means without the prior 
written consent of Bombardier Inc. or its affiliates.  This disclaimer applies to this, and all Service Bulletins listed in the 215−4000 Index, and those posted on the Bombardier Amphibious Aircraft 
web site:  www.support.amphibious.bombardier.com.
Refer to Figure 2 Detail B, and PSP 494 Chapter 27−11−00 Figure 3.
(5) Replace the cable guide S215 −475−21 as follows:
(a) Disconnect the flap interconnect cables at the turnbuckle locations.  Refer to
PSP 492, Chapter 27−50−00 Flap System − Interconnect Cable Rigging Adjustment.
(b) On the aileron power control unit, drill out and discard the four attaching solid rivets
and the existing cable guide S215−475−21.  Retain the four AN960PD6L washers.
NOTE: Ensure that the discarded strip S215 −475−21 does not get mistaken for the
replacement part.
(c) Install a new cable guide S215 −475−21 with new MS20470AD4−3A rivets and the
retained AN960PD6L washers under the rivet heads.  Refer to PSP 497,
Chapter 51.
(d) Connect the flap interconnect cables at the turnbuckle locations.  Refer to PSP 492,
Chapter 27−50−00 Flap System − Interconnect Cable Rigging Adjustment.
(e) Perform a rigging of the flap system interconnect system.  Refer to PSP 492,
Chapter 27−50−00 Flap System − Interconnect Cable Rigging Adjustment.
(6) Install the protective, transparent covers on the aileron power control unit and close the
access panels 255-1, 255-2, 255-3, 255-4, 414-3, 414-4, 424-3, 424-4.  Refer to PSP
492, Chapter 6.
PART C
C. Replacement of Teflon /C0116 Parts on the Aileron Power Unit Beam
WARNING: IN THE STEPS THAT FOLLOW, VERIFY THAT NO FOREIGN OBJECT DEBRIS
(FOD) REMAINS AFTER THE TEFLON/C0084 PARTS ARE REPLACED.  FOD LEFT
AFTER THE PARTS REPLACEMENT CAN INTERFERE OR JAM THE CONTROL
MECHANISMS.  FAILURE TO ENSURE THAT THE CONTROL SYSTEMS ARE
FREE OF FOD COULD LEAD TO DAMAGE TO THE EQUIPMENT OR CREATE A
FLIGHT SAFETY HAZARD.
Refer to PSP 492 Chapters 6, 27, and 29.
(1) Ensure the the surface gust lock lever is set to the UNLOCKED position.  Refer to
PSP 492, Chapter 27.
(2) Release the flight control hydraulic system pressure.  Refer to PSP 492, Chapter 29.
(3) Verify that the aileron and rudder flight control systems are set to MANUAL mode.  Refer
to PSP 492, Chapter 27.
(4) Open the access panels 255-1, 255-2, 255-6, 255-7, 541-3, 542-3, 641-3, 642-3 and
remove the protective, transparent covers from the aileron power control unit.  Refer to
PSP 492, Chapter 6.

### Page 9

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4477Rev. NC  Sept. 30/13
Rev. 2  Sept. 29/15
ATA Ref: 27−10Page 8 of 20
Refer to applicable governmental agency regulations and requirements and make sure that the work described in this Service Bulletin is performed in compliance with manufacturer’s recommendations
and/or acceptable industry standards.  This document is proprietary to Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or by any means without the prior 
written consent of Bombardier Inc. or its affiliates.  This disclaimer applies to this, and all Service Bulletins listed in the 215−4000 Index, and those posted on the Bombardier Amphibious Aircraft 
web site:  www.support.amphibious.bombardier.com.
(5) Remove the aileron artificial feel spring pot assembly.  Refer to PSP 492, Chapter 27.
Refer to PSP 498, Chapter 27.
(6) Replace the three S215 −696−20 packings and the two S215−695−20 rings as follows:
(a) Disassemble the artificial feel spring pot assembly and discard the three
S215−696−20 packings and the two S215−695−20 Teflon/C0116 rings.
NOTE: Ensure that the discarded packings and rings do not get mistaken for the
replacement packing and rings.
(b) Inspect the components of the artificial feel spring pot assembly for evidence of
excessive wear.  Replace any damaged or worn parts.
(c) Check the fit and clearance of all suspect components and proceed to do a
dimensional check of the parts.
(d) Assemble the artificial feel spring pot assembly with the new three S215 −696−20
packings and the new two S215−695−20 Teflon/C0116 rings.  Ensure that the correct
lubrication and corrosion preventive materials are used.
(7) Install the aileron artificial feel spring pot assembly.  Refer to PSP 492, Chapter 27.
Ensure that the correct lubrication and corrosion preventive materials are used.
Refer to Figure 1 Details C and D and PSP 494, Chapter 27−25−00 Figure 1.
(8) Replace the two cable guides S215 −145−20 and S215−145−21 as follows:
(a) Locate the two cable guides S215 −145−20 and S215−145−21 attached to the
support, forward of the load limiter assembly.  Remove and discard the existing
cable guides and nuts.  Retain the bolts and washers.
NOTE: Ensure that the discarded cable guides do not get mistaken for the
replacement cable guides.
(b) Install two new cable guides S215 −145−20 and S215−145−21 using the retained
bolts, washers, and new MS21042−L3  nuts.
Torque the nuts to a value of 20 to 25 pound-inches (2,3 to 2,8 Newton Metres).
Refer to PSP 492, Chapter 20.
Refer to Figure 1 Details G and H and PSP 494, Chapter 27−11−00 Figure 3.
(9) Replace the cable guide S215 −512−20 as follows:
(a) On the former at left WS 27.0 and FS 441.74, remove and discard the existing cable
guide S215−512−20 and the nuts.  Retain the bolts and washers.
NOTE: Ensure that the discarded cable guide does not get mistaken for the
replacement cable guide.

### Page 10

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4477Rev. NC  Sept. 30/13
Rev. 2  Sept. 29/15
ATA Ref: 27−10Page 9 of 20
Refer to applicable governmental agency regulations and requirements and make sure that the work described in this Service Bulletin is performed in compliance with manufacturer’s recommendations
and/or acceptable industry standards.  This document is proprietary to Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or by any means without the prior 
written consent of Bombardier Inc. or its affiliates.  This disclaimer applies to this, and all Service Bulletins listed in the 215−4000 Index, and those posted on the Bombardier Amphibious Aircraft 
web site:  www.support.amphibious.bombardier.com.
(b) Install a new cable guide S215 −512−20 and retained bolts, washers, and new
MS21042−3 nuts.
Torque the nuts to a value of 20 to 25 pound-inches (2,3 to 2,8 Newton Metres).
Refer to PSP 492, Chapter 20.
(10) Replace the cable guide S215 −512−21 and the rubbing strip S215−512−22 as follows:
(a) On the former at right WS 27.0 and FS 441.74, remove and discard the existing
cable guide S215−512−21 and the nuts.  Retain the bolts and the washers.
NOTE: Ensure that the discarded cable guide does not get mistaken for the
replacement cable guide.
(b) On the former at right WS 27.0 and FS 441.74, drill out and discard the rivets
MS20600AD4W4 and the existing rubbing strip S215−512−22.  Refer to PSP 497
Chapter 51.
NOTE: Ensure that the discarded rubbing strip does not get mistaken for the
replacement rubbing strip.
(c) Install a new rubbing strip S215 −512−22 using two new MS20600AD4W4 rivets.
Refer to PSP 497 Chapter 51.
(d) Install a new cable guide S215 −512−21 and retained bolts, washers, and
new MS21042−3 nuts.
Torque the nuts to a value of 20 to 25 pound-inches (2,3 to 2,8 Newton Metres).
Refer to PSP 492, Chapter 20.
Refer to Figure 1 Detail E and PSP 494, Chapter 27−11−00 Figure 3.
(11) Replace the cable guide S215 −501−20 as follows:
(a) On the former near WS 0.00 and at approximately FS 441.5, drill out the two
MS20600AD4W3 rivets and remove the cable guide S215−501−20.  Retain the two
washers AN960KD6L and discard the cable guide.
NOTE: Ensure that the discarded cable guide does not get mistaken for the
replacement cable guide.
(b) Install new cable guide S215 −501−20 using two new MS20600AD4W3 rivets with
one washers AN960KD6L under the rivet head.  Refer to PSP 497 Chapter 51.

### Page 11

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4477Rev. NC  Sept. 30/13
Rev. 2  Sept. 29/15
ATA Ref: 27−10Page 10 of 20
Refer to applicable governmental agency regulations and requirements and make sure that the work described in this Service Bulletin is performed in compliance with manufacturer’s recommendations
and/or acceptable industry standards.  This document is proprietary to Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or by any means without the prior 
written consent of Bombardier Inc. or its affiliates.  This disclaimer applies to this, and all Service Bulletins listed in the 215−4000 Index, and those posted on the Bombardier Amphibious Aircraft 
web site:  www.support.amphibious.bombardier.com.
Refer to Figure 1 Detail J and PSP 494, Chapter 27−71−00 Figure 2.
(12) Replace the backing plate S215 −643−21 as follows:
(a) Install rig pin RP7 into the P7 hole in the aileron gust lock quadrant assembly.  Refer
to PSP 492 Chapter 27.
(b) Remove the cabin roof liner panels in the area of the aileron power control unit.
(c) Remove the locking clips from the turnbuckles TB5 and TB6.  Relax the tension on
the G2 cable.
(d) Disassemble the aileron gust lock quadrant to free the G2 cable from the quadrant.
Refer to PSP 492, Chapter 27.
NOTE: Perform only those steps necessary to free the G2 cable to minimize the
work necessary to reconnect the cables, and rig the aileron gust lock
system.
(e) At the pulley bracket mounted on the top of the fuselage frame, remove the cotter
pins MS24665-134, the nuts MS17826−3, the washers AN960−10L, the
spacers S215−645−20, and the bolts NAS6603D7 and free the pulley bracket.  
Discard the cotter pins and retain the bolts, the spacers, the washers, and the nuts.
(f) Remove and discard the backing plate S215 −643−21.
NOTE: Ensure that the discarded backing plate does not get mistaken for the
replacement backing plate.
(g) Install the pulley bracket with a new backing plate S215 −643−21, and the retained
bolts, spacers, washers, and nuts.
Torque the nuts to a value of 10 to 12 pound-inches (1,1 to 1,4 Newton-Meters) and
safety using new cotter pins MS24665-134.  Refer to PSP 492, Chapter 20.
(h) Assemble the aileron gust lock quadrant to connect the G2 cable to the quadrant.
Refer to PSP 492, Chapter 27.
NOTE: Perform only those steps necessary to connect the G2 cable.
(i) Tighten the turnbuckles TB5 and TB6 to restore the tension on the G2 cable and
remove the rig pin RP 7 from the P7 hole in the aileron gust lock quadrant..  Refer to
PSP 492, Chapter 27−70−00 GUST LOCK SYSTEM − ADJUSTMENT/TEST.
(j) Do a rigging adjustment of the gust lock system.  Refer to PSP 492,
Chapter 27−70−00 GUST LOCK SYSTEM − ADJUSTMENT/TEST.
(k) Install the cabin roof liner panels.

### Page 12

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4477Rev. NC  Sept. 30/13
Rev. 2  Sept. 29/15
ATA Ref: 27−10Page 11 of 20
Refer to applicable governmental agency regulations and requirements and make sure that the work described in this Service Bulletin is performed in compliance with manufacturer’s recommendations
and/or acceptable industry standards.  This document is proprietary to Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or by any means without the prior 
written consent of Bombardier Inc. or its affiliates.  This disclaimer applies to this, and all Service Bulletins listed in the 215−4000 Index, and those posted on the Bombardier Amphibious Aircraft 
web site:  www.support.amphibious.bombardier.com.
Refer to Figure 2 Detail A, and PSP 492 Chapter 27
NOTE: The replacement of the Teflon /C0116 parts associated with the Powered Aileron Control
Unit may involve the disassembly of some components in order to improve access.
(13) Remove the aileron power control unit.  Refer to PSP 492 Chapter 27.
(14) Replace the strip S215 −479−20 as follows:
(a) Drill out and discard the four attaching solid rivets and the existing strip
S215−479−20.  Refer to PSP 497, Chapter 51.
Retain the two shims S215−476−21.
NOTE: Ensure that the discarded strip S215 −479−20 does not get mistaken for the
replacement part.
(b) Install a new strip S215 −479−20 with the two retained shims S215−476−21 using
four solid rivets MS20426E−4.  Refer to PSP 497, Chapter 51.
(15) Replace the strip S215 −477−20 as follows:
(a) Drill out and discard the two attaching solid rivets and the existing strip
S215−477−20.  Refer to PSP 497, Chapter 51.
Retain the shim S215−476−20.
NOTE: Ensure that the discarded strip S215 −477−20 does not get mistaken for the
replacement part.
(b) Install a new strip S215 −477−20 with the retained shim S215−476−20 using two new
solid rivets MS20426E−4.  Refer to PSP 497, Chapter 51.
(16) Replace the strip S215 −478−20 as follows:
(a) Drill out and discard the four attaching solid rivets and the existing strip
S215−478−20.  Note the location of the two longer grip length rivets.  Refer to
PSP 497, Chapter 51.
Retain the shim S215−476−20.
NOTE: Ensure that the discarded strip S215 −478−20 does not get mistaken for the
replacement part.
(b) Install a new strip S215 −478−20 with the retained shim S215−476−20 using two new
solid rivets MS20426E−4 and two new MS20426E−6 (longer grip length) rivets.
Refer to PSP 497, Chapter 51.

### Page 13

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4477Rev. NC  Sept. 30/13
Rev. 2  Sept. 29/15
ATA Ref: 27−10Page 12 of 20
Refer to applicable governmental agency regulations and requirements and make sure that the work described in this Service Bulletin is performed in compliance with manufacturer’s recommendations
and/or acceptable industry standards.  This document is proprietary to Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or by any means without the prior 
written consent of Bombardier Inc. or its affiliates.  This disclaimer applies to this, and all Service Bulletins listed in the 215−4000 Index, and those posted on the Bombardier Amphibious Aircraft 
web site:  www.support.amphibious.bombardier.com.
Refer to PSP 492 Chapter 27.
(17) Install the aileron power control unit.  Refer to PSP 492 Chapter 27.
(18) Do a rigging adjustment of the aileron power control unit.  Refer to PSP 492,
Chapter 27−11−03 POWER CONTROL UNIT − ADJUSTMENT/TEST.
(19) Perform the following adjustment/test procedures in PSP 492, AILERON CONTROL
SYSTEM − ADJUSTMENT/TEST:
− Paragraph A., Aileron Control System − Cable Rigging Adjustment
− Paragraph B., Aileron Control System − Functional Test
− Paragraph C., Aileron Travel Stops − Adjustment
− Paragraph D., Aileron Backlash − Adjustment
− Paragraph E., Aileron Frictional Forces − Functional Test
(20) Install the protective, transparent covers from the aileron power control unit and close the
access panels 255−1, 255−2, 255−3, 255−6, 255−7, 541−3, 542−3, 641−3, and 642−3.
Refer to PSP 492, Chapter 6.
D. Recording
When this Service Bulletin is completed, make the entry in the aircraft log book and send back
the attached Incorporation Notice to Amphibious Aircraft Technical Publications.
3. Material Information
A. Kit No. 215K4477 A − Parts List
Kit No. 215K4477 A is necessary to do Part A of this Service Bulletin and consists of the parts
that are listed as follows:
PART NO. QUANTITY DESCRIPTION DRW ITEM
S215−513−20 4 Strip −
MS20600AD4W4 8 Rivet −
B. Kit No. 215K4477 B − Parts List
Kit No. 215K4477 B is necessary to do Part B of this Service Bulletin and consists of the parts
that are listed as follows:
PART NO. QUANTITY DESCRIPTION DRW ITEM
S215−475−21 1 Cable Guide −
MS20470AD4−3A 4 Rivet −

### Page 14

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4477Rev. NC  Sept. 30/13
Rev. 2  Sept. 29/15
ATA Ref: 27−10Page 13 of 20
Refer to applicable governmental agency regulations and requirements and make sure that the work described in this Service Bulletin is performed in compliance with manufacturer’s recommendations
and/or acceptable industry standards.  This document is proprietary to Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or by any means without the prior 
written consent of Bombardier Inc. or its affiliates.  This disclaimer applies to this, and all Service Bulletins listed in the 215−4000 Index, and those posted on the Bombardier Amphibious Aircraft 
web site:  www.support.amphibious.bombardier.com.
C. Kit No. 215K4477 C − Parts List
Kit No. 215K4477 C is necessary to do Part C of this Service Bulletin and consists of the parts
that are listed as follows:
PART NO. QUANTITY DESCRIPTION DRW ITEM
S215−501−20 1 Cable Guide −
S215−643−21 1 Backing Plate −
S215−477−20 1 Strip −
S215−478−20 1 Strip −
S215−479−20 1 Strip
S215−512−20 1 Cable Guide −
S215−512−21 1 Cable Guide −
S215−512−22 1 Strip −
S215−145−20 1 Cable Guide −
S215−145−21 1 Cable Guide −
S215−696−20 3 Packing −
S215−695−20 2 Rings −
S1401S3 1 Tab Washer −
L23550−060−000
OR
23350CA060
4 Tab Washer −
MS24665−134 8 Cotter Pin −
MS24665−351 2 Cotter Pin −
AN996−20 1 Lock Ring −
S215−663−20 1 Lock Ring −
MS21256−1 4 Locking Clip −
MS21256−2 12 Locking Clip −
MS24665−67
OR 
MS24665−69
4 Cotter Pin −
MS24665−133
OR 
MS24665−134
6 Cotter Pin −
MS24665−136
OR 
MS24665−155
6 Cotter Pin −

### Page 15

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4477Rev. NC  Sept. 30/13
Rev. 2  Sept. 29/15
ATA Ref: 27−10Page 14 of 20
Refer to applicable governmental agency regulations and requirements and make sure that the work described in this Service Bulletin is performed in compliance with manufacturer’s recommendations
and/or acceptable industry standards.  This document is proprietary to Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or by any means without the prior 
written consent of Bombardier Inc. or its affiliates.  This disclaimer applies to this, and all Service Bulletins listed in the 215−4000 Index, and those posted on the Bombardier Amphibious Aircraft 
web site:  www.support.amphibious.bombardier.com.
PART NO. QUANTITY DESCRIPTION DRW ITEM
MS24665−154
OR 
MS24665−155
4 Cotter Pin −
MS24665−210
OR 
MS24665−229
2 Cotter Pin −
S215−619−20 2 Tab Washer −
S1401R6 3 Tab Washer −
MS20600AD4W3 2 Rivet −
MS20600AD4W4 2 Rivet −
MS21042−3 4 Nut −
MS21042−L3 2 Nut −
D. The following materials, or equivalent, are necessary to do this Service Bulletin. You can buy
them locally:
DESCRIPTION PART NO./NAME SPECIFICATION QUANTITY
Aliphatic naphtha Commercial TT−N−95 Type II A/R
Sealing Compound Mastinox 6856
H/K or 
equivalent
− A/R
Corrosion Preventive
Compound
Commercial MIL−C−16173 Grade 1
or equivalent
A/R
Grease, aircraft and
instrument
Commercial MIL-PRF-23827 A/R
Solid Rivet MS20426E4 Determine Grip upon
Installation
8
Solid Rivet MS20426E6 Determine Grip upon
Installation
2

### Page 16

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4477Rev. NC  Sept. 30/13
Rev. 2  Sept. 29/15
ATA Ref: 27−10Page 15 of 20
Refer to applicable governmental agency regulations and requirements and make sure that the work described in this Service Bulletin is performed in compliance with manufacturer’s recommendations
and/or acceptable industry standards.  This document is proprietary to Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or by any means without the prior 
written consent of Bombardier Inc. or its affiliates.  This disclaimer applies to this, and all Service Bulletins listed in the 215−4000 Index, and those posted on the Bombardier Amphibious Aircraft 
web site:  www.support.amphibious.bombardier.com.
FIGURE 1
POWERED CONTROL AILERON − REPLACEMENT OF TEFLON PARTS
S215−696−20
(PACKING)
S215−695−20
(TEFLON RING)
S215−696−20
(PACKING)
S215−696−20
(PACKING)
S215−695−20
(TEFLON RING)
LEGEND
DISCARD EXISTING AND INSTALL NEW

### Page 17

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4477Rev. NC  Sept. 30/13
Rev. 2  Sept. 29/15
ATA Ref: 27−10Page 16 of 20
Refer to applicable governmental agency regulations and requirements and make sure that the work described in this Service Bulletin is performed in compliance with manufacturer’s recommendations
and/or acceptable industry standards.  This document is proprietary to Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or by any means without the prior 
written consent of Bombardier Inc. or its affiliates.  This disclaimer applies to this, and all Service Bulletins listed in the 215−4000 Index, and those posted on the Bombardier Amphibious Aircraft 
web site:  www.support.amphibious.bombardier.com.
S215−145−20
(CABLE GUIDE)
S215−145−21
(CABLE GUIDE)
NOTE
FIGURE 1
POWERED CONTROL AILERON − REPLACEMENT OF TEFLON PARTS
LEGEND
DISCARD EXISTING AND INSTALL NEW
Remove and retain hardware fixing both cable guides
except the nuts which are to be discarded.

### Page 18

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4477Rev. NC  Sept. 30/13
Rev. 2  Sept. 29/15
ATA Ref: 27−10Page 17 of 20
Refer to applicable governmental agency regulations and requirements and make sure that the work described in this Service Bulletin is performed in compliance with manufacturer’s recommendations
and/or acceptable industry standards.  This document is proprietary to Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or by any means without the prior 
written consent of Bombardier Inc. or its affiliates.  This disclaimer applies to this, and all Service Bulletins listed in the 215−4000 Index, and those posted on the Bombardier Amphibious Aircraft 
web site:  www.support.amphibious.bombardier.com.
S215−501−20
(CABLE GUIDE)
AN960KD6L
(WASHER) S215−513−20
(TEFLON STRIP)
FIGURE 1
POWERED CONTROL AILERON − REPLACEMENT OF TEFLON PARTS
(LH SHOWN RH OPPOSITE)
NOTES
1 Remove and discard MS20600AD4W3 (rivets),
install new MS20600AD4W3(rivets).
2 Remove and retain hardware fixing both cable guides.
LEGEND
DISCARD EXISTING AND INSTALL NEW
REMOVE AND REINSTALL

### Page 19

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4477Rev. NC  Sept. 30/13
Rev. 2  Sept. 29/15
ATA Ref: 27−10Page 18 of 20
Refer to applicable governmental agency regulations and requirements and make sure that the work described in this Service Bulletin is performed in compliance with manufacturer’s recommendations
and/or acceptable industry standards.  This document is proprietary to Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or by any means without the prior 
written consent of Bombardier Inc. or its affiliates.  This disclaimer applies to this, and all Service Bulletins listed in the 215−4000 Index, and those posted on the Bombardier Amphibious Aircraft 
web site:  www.support.amphibious.bombardier.com.
S215−512−20
(CABLE GUIDE)
S215−512−21
(CABLE GUIDE)
S215−512−22
(TEFLON STRIP)
FIGURE 1
POWERED CONTROL AILERON − REPLACEMENT OF TEFLON PARTS
NAS6203−3
(BOLT)
MS21042−3
(NUT)
AN960KD10L
(WASHER)
NAS6203−3
(BOLT)
AN960KD10L
(WASHER)
MS21042−3
(NUT)
NOTES
1 Remove and discard MS20600AD4W4 (rivets)
and replace by new ones.
2 Remove and retain hardware fixing both cable guides.
DISCARD EXISTING AND INSTALL NEW
LEGEND
REMOVE AND REINSTALL

### Page 20

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4477Rev. NC  Sept. 30/13
Rev. 2  Sept. 29/15
ATA Ref: 27−10Page 19 of 20
Refer to applicable governmental agency regulations and requirements and make sure that the work described in this Service Bulletin is performed in compliance with manufacturer’s recommendations
and/or acceptable industry standards.  This document is proprietary to Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or by any means without the prior 
written consent of Bombardier Inc. or its affiliates.  This disclaimer applies to this, and all Service Bulletins listed in the 215−4000 Index, and those posted on the Bombardier Amphibious Aircraft 
web site:  www.support.amphibious.bombardier.com.
S215−643−21
(TEFLON BACKING PLATE)
NAS6603D7
(BOLT)
S215−645−20
(SPACER)
AN960−lOL
(WASHER)
MS17826−3
(NUT)
MS24665−134
(COTTER PIN)
FIGURE 1
POWERED CONTROL AILERON − REPLACEMENT OF TEFLON PARTS
LEGEND
INSTALL NEW
REMOVE AND REINSTALL
DISCARD EXISTING AND INSTALL NEW

### Page 21

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4477Rev. NC  Sept. 30/13
Rev. 2  Sept. 29/15
ATA Ref: 27−10Page 20 of 20
Refer to applicable governmental agency regulations and requirements and make sure that the work described in this Service Bulletin is performed in compliance with manufacturer’s recommendations
and/or acceptable industry standards.  This document is proprietary to Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or by any means without the prior 
written consent of Bombardier Inc. or its affiliates.  This disclaimer applies to this, and all Service Bulletins listed in the 215−4000 Index, and those posted on the Bombardier Amphibious Aircraft 
web site:  www.support.amphibious.bombardier.com.
S215−477−20
(TEFLON PART)
S215−479−20
(TEFLON PART)
S215−478−20
(TEFLON PART)
FIGURE 2
AILERON POWERED CONTROL BEAM − REPLACEMENT OF TEFLON PARTS
LEGEND
DISCARD EXISTING AND INSTALL NEW
REMOVE AND REINSTALL
S215−476−20
(SHIM)
S215−476−21
(SHIM)
NOTE
Remove and discard MS20426DD−4(rivets),
install new MS20426E4(rivets).
S215−475−21
(TEFLON PART) AN960PD6L
(WASHER)
MS20470AD4−3
(RIVET)

### Page 22

Upon completion of Service Bulletin(s), please fill in and return by fax to:
Service Bulletin Number(s) Rev.
Aircraft Serial No.
Date of Incorporation
Aircraft Reg. No.
Technical Publication,
Dept. 649-DBF−(9)
Bombardier Aerospace
Specialized &
Amphibious Aircraft
St. Laurent, Quebec
Fax No.: (514) 855−7602
Airframe Hours
Remarks
Name
SERVICE BULLETIN
INCORPORATION NOTICE
REPLY FAX
Customer/Operation
(Please Print)
the evolution of mobility

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