# Bombardier Service Bulletin 215-4457

Copy: Revision 3 ("FAA-2017-0333_SB 215-4457 Rev 3"), 39 pages: PDF https://openairdocs.org/files/sha256/0a/93/0a93ea3512185517dfe6bab1a488c5c6bb8954c648116f1d7c3f0d4efe6bc6d3; text https://openairdocs.org/service-documents/bombardier/sb-215-4457/file/0a93ea351218.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2017-0333; AD 2017-15-14 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: 215-4457
- Latest revision known: 215-4457, Revision 3, dated May 8, 2013 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/bombardier/sb-215-4457

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

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

- [AD 2017-15-14](https://openairdocs.org/ad/2017-15-14.md), effective Sep 5, 2017: Revisions 1, 2 and 3

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/bombardier/sb-215-4457/proposed.md).

## Text (39 pages)

Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2017-0333; AD 2017-15-14 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

Service Bulletin 215-4457May 8/13
ATA Ref: 35−10Page 1 of 1
MODEL CL-215-6B11 (415)
REVISION TRANSMITTAL SHEET
OXYGEN
MODIFICATION OF THE PILOT AND COPILOT PORTABLE OXYGEN SYSTEM
(POST INSTALLATION OF SERVICE BULLETIN 215 −4051)
Service Bulletin No.: 215 −4457 Date of Original Issue: April 4/12
Revision No.: 3 Date of Issue: May 8/13
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. Change the revision of Modification Summaries 415 −79519 from Revision B to B −1 in Section
1.K. References.
2. Add aircraft serial nos. 2005, 2012, 2016, 2017, 2019, 2022, 2023, and 2026 (content of
Information Sheet No. 1) to sections 1.C, 1.K, 2.C, and 3.C.
3. Add NOTE 10 to Section 2.
4. Make other miscellaneous, non −technical changes.

### Page 2

Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 1 of 37
Rev. 3 May 8/13
MODEL CL-215-6B11 (415)
SERVICE BULLETIN
OXYGEN
MODIFICATION OF THE PILOT AND COPILOT PORTABLE OXYGEN SYSTEM
(POST INSTALLATION OF SERVICE BULLETIN 215−4051)
1. Planning Information
A. Compliance
Installation of this Service Bulletin is recommended.  Service Bulletin 215−4051 must be
incorporated prior to the installation of this Service Bulletin.
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. 
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
CL-215-6B11 (415) turboprop aircraft Serial Nos. 2001, 2002, 2005 to 2007, 2010, 2012 to
2017, 2019, 2022 to 2024, 2026, 2057, 2063, 2065, 2076, 2077, and 2081.
D. Reason
1) Post installation of Service Bulletin 215 −4051, it has been determined that the oxygen 
bottle is loose when the clamp strap is in the locked position
2) It has also been determined that the previous installation does not meet the strength 
required.
E. Description
This Service Bulletin gives instructions to modify the clamp strap and to install additional shims
to add strength to the attaching structure.

### Page 3

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 2 of 37
Rev. 3 May 8/13
F. Manpower
We estimate that it will take 1 technician approximately 16 hours to complete this Service
Bulletin.
G. Material Availability
Kit No. 215K4457 is necessary to do this Service Bulletin.  Information on price and delivery is
available from your Amphibious Aircraft Customer Service Representative (CSR).
H. Tool Availability
A force gauge 0−100 lbs.
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 Modification Summary: 415 −79495, Revision A
415−79519, Revision B−1
415−79564, Revision B.
Bombardier Aerospace Kit Drawing: K215T40028,
SNIEO S05 for aircraft Serial No. 2077.
SNIEO S06 for aircraft Serial No. 2076.
SNIEO S07 
SNIEO S10 has superceeded SNIEO S07 for aircraft 
Serial Nos. 2001, 2002, 2005 to 2007, 2010, 2012 to 
2017, 2019, 2022 to 2024, 2026, 2057, 2063 and 2065.
SNIEO S08 for aircraft Serial No. 2081.
L. Publications Affected
PSP 492, Maintenance Manual, Chapter 35−10−00.
PSP 494, Illustrated Parts Catalogue, Chapter 35−10−00.
M. Related Service Bulletin
215−4051 MODIFICATION OF THE PILOT AND COPILOT PORTABLE OXYGEN SYSTEM

### Page 4

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 3 of 37
Rev. 3 May 8/13
2. Accomplishment Instructions
NOTES: 1. For this modification, 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.
3. When drilling new fastener holes, maintain a minimum of a 2.0 fastener diameter
edge distance and an interpitch distance of 4 to 6 fastener head diameter unless
otherwise specified.
4. Bare metal areas must be treated with anodizing solution, MIL-C-5541 Class 1A, and
two coats of fluid resistant epoxy primer, BAMS 565-01.  Apply finishing topcoat, CMS
565-02, as required.  Refer to PSP 497, Chapter 51-71-02, CORROSION
PREVENTIVE TREATMENT − GENERAL PROCEDURES.
5. Review the associated Kit Drawing to get a good overview of the complete
installation.
6. This Service Bulletin describes the sequence that the structures are fitted on the
aircraft.  First, all the structures are fitted and secured with cleco pins.  Second, all the
structures are removed and subsequently riveted in place.
7. The instructions in this Service Bulletin do not call rivets or fasteners to be used.
Upon final installation of a part, refer to the detailed views on the Kit Drawings for
fastener callouts.
8. During structure fitting, use a #40 drill bit (3/32 or 0.098 inch) to drill all pilot holes.
For final installation, refer to the Kit Drawing for fastener size and drill full size
accordingly.
9. If any deviation exists, contact your Amphibious Aircraft Technical Representative for
further instructions.
10.Modification to Aircraft are seperated by Section Nos.
A/C 2076, Refer to Section 2.A.
A/C 2077, Refer to Section 2.B.
A/C 2001, 2002, 2005 to 2007, 2010, 2012 to 2017, 2019, 2022 to 2024, 2026, 2057,
2063, 2065, Refer to Section 2.C.
A/C 2081, Refer to Section 2.B.

### Page 5

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 4 of 37
Rev. 3 May 8/13
A. Modification for Aircraft Serial No. 2076.
Refer to the Illustration Figure 1 of this Service Bulletin
 
(1) Modify the pilot side oxygen bottle retaining structure as follows:
(a) Remove and retain the pilot oxygen bottle 804464-01 and smoke mask.
(b) Remove and retain the the latch assembly 215T40078 −2 and the attaching
hardware.
(c) Remove and retain the pilot cockpit trim panel 215T40531 −11 that covers the
structure on FS 227.36.
(d) Remove the 10 rivets that secure bracket assembly 215T40077 −10 (item 7 REF) to
the cockpit structure.  Remove and retain the bracket assembly.
(e) Rework bracket assembly 215T40077 −10 (item 7 REF) as follows:
1 Use the bracket as a template and backdrill the four shims (10 holes) as shown.
2 Open up all 10 holes full size to suit rivets MS20426AD5.
3 Bond the two shims S0602 in place on the channel assembly 215T51425−126 as
shown in accordance with PSP 497, Structural repair Manual, Chapter 51−21−01,
METAL TO METAL COLD BONDING − GENERAL PROCEDURES.
4 Bond shim S0604 and shim S0606 in place on the panel assembly
215T51425−116 as shown in accordance with PSP 497, Structural repair Manual,
Chapter 51−21−01, METAL TO METAL COLD BONDING − GENERAL
PROCEDURES.
(f) Secure the bracket 215T40077 −10 (item 7 REF) with rivets MS20426AD5−( )A to
the panel and channel assemblies in the 10 existing rivet locations.
NOTE: Rivet grip length is to be determined upon installation.
(g) Reinstall the pilot cockpit trim panel 215T40531 −11.
(h) Reinstall the pilot oxygen bottle 804464-01 and smoke mask.
(2) Make sure that the pilot oxygen bottle is tightly secured in the latch assembly
215T40078−2.

### Page 6

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 5 of 37
Rev. 3 May 8/13
(3) Modify the copilot side oxygen bottle retaining structure as follows:
(a) Remove and retain the copilot oxygen bottle 804464-02 and smoke mask.
(b) Remove and retain the the latch assembly 215T40078 −2 and the attaching
hardware.
(c) Remove and retain the copilot cockpit trim panel 215T40531 −10 that covers the
structure on FS 227.36.
(d) Remove the 6 rivets that secure bracket assembly 215T40077 −18 (item 7 REF) to
the cockpit structure.  Remove and retain the bracket assembly.
(e) Rework bracket assembly 215T40077 −10 (item 8 REF) as follows:
1 Use the bracket assembly as a template and backdrill the three shims (6 holes)
as shown.
2 Open up all 6 holes full size to suit rivets MS20426AD5.
3 Bond shim S0602 in place on the channel assembly 215T51425−127 as shown in
accordance with PSP 497, Structural repair Manual, Chapter 51−21−01, METAL
TO METAL COLD BONDING − GENERAL PROCEDURES.
4 Bond shim S0610 in place on the panel assembly 215T51425−117 as shown in
accordance with PSP 497, Structural repair Manual, Chapter 51−21−01, METAL
TO METAL COLD BONDING − GENERAL PROCEDURES.
5 Bond shim S0608 in place on the channel assembly 215T51425−60 as shown in
accordance with PSP 497, Structural repair Manual, Chapter 51−21−01, METAL
TO METAL COLD BONDING − GENERAL PROCEDURES.
(f) Secure the bracket assembly 215T40077 −18 (item 8 REF) with rivets
MS20426AD5−( )A to the panel and channel assemblies in the 6 existing rivet
locations.
NOTE: Rivet grip length is to be determined upon installation.
(g) Reinstall the copilot cockpit trim panel 215T40531 −10.
(h) Reinstall the copilot oxygen bottle 804464-02 and smoke mask.
(4) Make sure that the copilot oxygen bottle is tightly secured in the latch assembly
215T40078−2.

### Page 7

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 6 of 37
Rev. 3 May 8/13
STRUCTURAL MODIFICATION OF PILOT AND COPILOT OXYGEN SYSTEM FOR A/C 2076
FIGURE 1
REMOVE 4 EXISTING
NAS1097AD4−( )A RIVETS
REMOVE 6 EXISTING
MS20426AD4−( )A RIVETS
215T51425−116 (REF)
(PANEL ASSY)
215T51425−126 (REF)
(CHANNEL ASSY)
215T40077−10 (REF)
(BRACKET ASSY)
BEFORE REPAIR AT FS 227.36
(OXYGEN BOTTLE AND LATCH ASSEMBLY
NOT SHOWN FOR CLARITY)
BEFORE REPAIR AT FS 227.36
(OXYGEN BOTTLE AND LATCH ASSEMBLY
NOT SHOWN FOR CLARITY)
215T51425−127 (REF)
(CHANNEL ASSY)
215T51425−60 (REF)
(CHANNEL ASSY)
215T40077−8 (REF)
(BRACKET ASSY)
REMOVE 2 EXISTING
NAS1097AD4−( )A RIVETS
REMOVE 3 EXISTING
MS20426AD4−( )A RIVETS
REMOVE EXISTING
NAS1097AD4−( )A RIVET
215T51425−117 (REF)
(PANEL ASSY)

### Page 8

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 7 of 37
Rev. 3 May 8/13
STRUCTURAL MODIFICATION OF PILOT AND COPILOT OXYGEN SYSTEM FOR A/C 2076
FIGURE 1
215T51425−116 (REF)
(PANEL ASSY) 215T51425−126 (REF)
(CHANNEL ASSY)
AFTER REPAIR AT FS 227.36
(OXYGEN BOTTLE AND LATCH ASSEMBLY
NOT SHOWN FOR CLARITY)
PICK−UP HOLES
AND INSTALL 6
MS20426AD5−( )A RIVETS
PICK−UP HOLES
AND INSTALL 4
MS20426AD5−( )A RIVETSK215T40028−S0602
(SHIM)
K215T40028−S0602
(SHIM)
K215T40028−S0604
(SHIM)
K215T40028−S0606
(SHIM)
215T40077−10 (REF)
(BRACKET ASSY)

### Page 9

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 8 of 37
Rev. 3 May 8/13
STRUCTURAL MODIFICATION OF PILOT AND COPILOT OXYGEN SYSTEM FOR A/C 2076
FIGURE 1
AFTER REPAIR AT FS 227.36
(OXYGEN BOTTLE AND LATCH ASSEMBLY
NOT SHOWN FOR CLARITY)
215T51425−127 (REF)
(CHANNEL ASSY)
215T51425−60 (REF)
(CHANNEL ASSY)
PICK−UP HOLES
AND INSTALL 2
MS20426AD5−( )A RIVETS
PICK−UP HOLES
AND INSTALL 3
MS20426AD5−( )A RIVETS
PICK−UP HOLE
AND INSTALL
MS20426AD5−( )A RIVET
K215T40028−S0602
(SHIM)
K215T40028−S0610
(SHIM)
K215T40028−S0608
(SHIM)
215T51425−117 (REF)
(PANEL ASSY)
215T40077−8 (REF)
(BRACKET ASSY)

### Page 10

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 9 of 37
Rev. 3 May 8/13
STRUCTURAL MODIFICATION OF PILOT AND COPILOT OXYGEN SYSTEM FOR A/C 2076
FIGURE 1
MS20426AD5−( )A RIVET
K215T40028−S0602
(SHIM)
0.01 in. MIN.
(0,25 mm)
215T40077−10 (REF) LH
215T40077−8 (REF) RH
(BRACKET ASSY)
215T51425−126 (REF) LH
215T51425−127 (REF) RH
(CHANNEL ASSY)
0.01 in. MIN.
(0,25 mm)
MS20426AD5−( )A RIVET
215T51425−116 (REF)
(PANEL ASSY)
K215T40028−S0604
K215T40028−S0606
(SHIM)
0.01 in. MIN.
(0,25 mm)
MS20426AD5−( )A RIVET
K215T40028−S0608
(SHIM)
215T51425−60 (REF)
(CHANNEL ASSY)
0.01 in. MIN.
(0,25 mm)
215T51425−117 (REF)
(PANEL ASSY)
MS20426AD5−( )A RIVET
K215T40028−S0610
(SHIM)
215T40077−10 (REF)
(BRACKET ASSY)
215T40077−8 (REF)
(BRACKET ASSY)
215T40077−8 (REF)
(BRACKET ASSY)

### Page 11

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 10 of 37
Rev. 3 May 8/13
K215T40028−S0608
(SHIM)
K215T40028−S0602
(SHIM)
K215T40028−S0606
(SHIM)
K215T40028−S0604
(SHIM)
K215T40028−S0610
(SHIM)
R 0.25 in.
(6,35 mm)
2.06 in.
(5,23 cm)
R 0.25 in.
(6,35 mm)
1.82 in.
(4,62 cm)
DIA 0.50 in.
(12,70 mm)
0.69 in.
(17,52 mm)
R 0.25 in.
(6,35 mm)
0.025 in.
(0,63 mm)
0.025 in.
(0,63 mm)
0.016 in.
(0,41 mm)
0.016 in.
(0,41 mm)
R 0.25 in.
(6,35 mm)
0.025 in.
(0,63 mm)
0.75 in.
(19,05 mm)
STRUCTURAL MODIFICATION OF PILOT AND COPILOT OXYGEN SYSTEM FOR A/C 2076
FIGURE 1
NOTE
All shims are fabricated from,
AL ALY 2024−T3 PER SPEC AMS−QQ−A−250/5.

### Page 12

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 11 of 37
Rev. 3 May 8/13
B. Modification for Aircraft Serial No. 2077.
NOTE: Aircraft serial No. 2077 was previously modified by K215T40028 SNIEO S02 and S04.
Refer to the Illustration Figure 2 of this Service Bulletin
 
(1) Modify the pilot side oxygen bottle retaining structure as follows:
(a) Remove and retain the pilot oxygen bottle 804464-01 and smoke mask
(b) Remove and retain the the latch assembly 215T40078 −2 and the attaching
hardware.
(c) Remove and retain the pilot cockpit trim panel 215T40531 −11 that covers the
structure on FS 227.36.
(d) Remove the 12 rivets that secure bracket assembly 215T40077 −10 (Bracket assy.
reworked per SNIEO S04) to the cockpit structure.  Remove and retain the bracket
assembly.
(e) Rework bracket assembly 215T40077 −S0410 as follows:
1 Use the bracket as a template and backdrill the four shims (12 holes) as shown.
2 Open up all 12 holes full size to suit rivets MS20426AD5.
3 Bond the two shims S0502 in place on the channel assembly 215T51425−126 as
shown in accordance with PSP 497, Structural repair Manual, Chapter 51−21−01,
METAL TO METAL COLD BONDING − GENERAL PROCEDURES.
4 Bond shim S0504 and shim S0506 in place on the panel assembly
215T51425−116 as shown in accordance with PSP 497, Structural repair Manual,
Chapter 51−21−01, METAL TO METAL COLD BONDING − GENERAL
PROCEDURES.
(f) Secure the bracket 215T40077 −S0410  with rivets MS20426AD5−( )A to the panel
and channel assemblies in the 12 existing rivet locations.
NOTE: Rivet grip length is to be determined upon installation.
(g) Reinstall the pilot cockpit trim panel 215T40531 −11.
(h) Reinstall the pilot oxygen bottle 804464-01 and smoke mask.
(2) Make sure that the pilot oxygen bottle is tightly secured in the latch assembly
215T40078−2.

### Page 13

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 12 of 37
Rev. 3 May 8/13
(3) Modify the copilot side oxygen bottle retaining structure as follows:
(a) Remove and retain the copilot oxygen bottle 804464-02 and smoke mask.
(b) Remove and retain the the latch assembly 215T40078 −2 and the attaching
hardware.
(c) Remove and retain the copilot cockpit trim panel 215T40531 −10 that covers the
structure on FS 227.36.
(d) Remove the 7 rivets that secure bracket assembly 215T40077 −S0408 (Bracket
assy. reworked per SNIEO S04) to the cockpit structure.  Remove and retain the
bracket assembly.
(e) Rework bracket assembly 215T40077 −S0408 as follows:
1 Use the bracket assembly as a template and backdrill the three shims (7 holes)
as shown.
2 Open up all 7 holes full size to suit rivets MS20426AD5.
3 Bond shim S0502 in place on the channel assembly 215T51425−127 as shown in
accordance with PSP 497, Structural repair Manual, Chapter 51−21−01, METAL
TO METAL COLD BONDING − GENERAL PROCEDURES.
4 Bond shim S0510 in place on panel assembly 215T51425−117 as shown in
accordance with PSP 497, Structural repair Manual, Chapter 51−21−01, METAL
TO METAL COLD BONDING − GENERAL PROCEDURES.
5 Bond shim S0508 in place on the channel assembly 215T51425−60 as shown in
accordance with PSP 497, Structural repair Manual, Chapter 51−21−01, METAL
TO METAL COLD BONDING − GENERAL PROCEDURES.
(f) Secure the bracket assembly 215T40077 −S0408 with rivets MS20426AD5−( )A to
the panel and channel assemblies in the 7 existing rivet locations.
NOTE: Rivet grip length is to be determined upon installation.
(g) Reinstall the copilot cockpit trim panel 215T40531 −10.
(h) Reinstall the copilot oxygen bottle 804464-02 and smoke mask.
(4) Make sure that the pilot oxygen bottle is tightly secured in the latch assembly
215T40078−2.

### Page 14

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 13 of 37
Rev. 3 May 8/13
STRUCTURAL MODIFICATION OF PILOT AND COPILOT OXYGEN SYSTEM FOR A/C 2077
FIGURE 2
REMOVE 6 EXISTING
NAS1097AD4−( )A RIVETS
REMOVE 6 EXISTING
MS20426AD4−( )A RIVETS
215T51425−116 (REF)
(PANEL ASSY)
215T51425−126 (REF)
(CHANNEL ASSY)
BEFORE REPAIR AT FS 227.36
(OXYGEN BOTTLE AND LATCH ASSEMBLY
NOT SHOWN FOR CLARITY)
BEFORE REPAIR AT FS 227.36
(OXYGEN BOTTLE AND LATCH ASSEMBLY
NOT SHOWN FOR CLARITY)
215T51425−127 (REF)
(CHANNEL ASSY)
215T51425−60 (REF)
(CHANNEL ASSY)
REMOVE 3 EXISTING
NAS1097AD4−( )A RIVETS
REMOVE 3 EXISTING
MS20426AD4−( )A RIVETS
REMOVE EXISTING
NAS1097AD4−( )A RIVET
215T51425−117 (REF)
(PANEL ASSY)
NOTE
Existing plugged holes for reference.
215T40028−S0410 (REF)
(BRACKET ASSY)
(SNIEO S04 REF)
215T40028−S0408 (REF)
(BRACKET ASSY)
(SNIEO S04 REF)

### Page 15

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 14 of 37
Rev. 3 May 8/13
215T51425−116 (REF)
(PANEL ASSY)
215T51425−126 (REF)
(CHANNEL ASSY)
AFTER REPAIR AT FS 227.36
(OXYGEN BOTTLE AND LATCH ASSEMBLY
NOT SHOWN FOR CLARITY)
PICK−UP HOLES
AND INSTALL 6
MS20426AD5−( )A RIVETS
PICK−UP HOLES
AND INSTALL 6
MS20426AD5−( )A RIVETSK215T40028−S0502
(SHIM)
K215T40028−S0502
(SHIM)
K215T40028−S0504
(SHIM)
K215T40028−S0506
(SHIM)
NOTE
Existing plugged holes for reference.
STRUCTURAL MODIFICATION OF PILOT AND COPILOT OXYGEN SYSTEM FOR A/C 2077
FIGURE 2
215T40028−S0410 (REF)
(BRACKET ASSY)
(SNIEO S04 REF)

### Page 16

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 15 of 37
Rev. 3 May 8/13
AFTER REPAIR AT FS 227.36
(OXYGEN BOTTLE AND LATCH ASSEMBLY
NOT SHOWN FOR CLARITY)
215T51425−127 (REF)
(CHANNEL ASSY)
215T51425−60 (REF)
(CHANNEL ASSY)
PICK−UP HOLES
AND INSTALL 3
MS20426AD5−( )A RIVETS
PICK−UP HOLES
AND INSTALL 3
MS20426AD5−( )A RIVETS
PICK−UP HOLE
AND INSTALL
MS20426AD5−( )A RIVET
K215T40028−S0502
(SHIM)
K215T40028−S0510
(SHIM)
K215T40028−S0508
(SHIM)
215T51425−117 (REF)
(PANEL ASSY)
NOTE
Existing plugged holes for reference.
STRUCTURAL MODIFICATION OF PILOT AND COPILOT OXYGEN SYSTEM FOR A/C 2077
FIGURE 2
215T40028−S0408 (REF)
(BRACKET ASSY)
(SNIEO S04 REF)

### Page 17

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 16 of 37
Rev. 3 May 8/13
MS20426AD5−( )A RIVET
K215T40028−S0502
(SHIM)
0.01 in. MIN.
(0,25 mm)
215T40028−S0410 (REF) LH
215T40028−S0408 (REF) RH
(BRACKET ASSY) (SNIEO S04 REF)
215T51425−126 (REF) LH
215T51425−127 (REF) RH
(CHANNEL ASSY)
0.01 in. MIN.
(0,25 mm)
MS20426AD5−( )A RIVET
215T51425−116 (REF)
(PANEL ASSY)
K215T40028−S0504
K215T40028−S0506
(SHIM)
0.01 in. MIN.
(0,25 mm)
MS20426AD5−( )A RIVET
K215T40028−S0508
(SHIM)
215T51425−60 (REF)
(CHANNEL ASSY)
0.01 in. MIN.
(0,25 mm)
215T51425−117 (REF)
(PANEL ASSY)
MS20426AD5−( )A RIVET
K215T40028−S0510
(SHIM)
STRUCTURAL MODIFICATION OF PILOT AND COPILOT OXYGEN SYSTEM FOR A/C 2077
FIGURE 2
215T40028−S0408 (REF)
(BRACKET ASSY)
(SNIEO S04 REF)
215T40028−S0408 (REF)
(BRACKET ASSY)
(SNIEO S04 REF)
215T40028−S0410 (REF)
(BRACKET ASSY)
(SNIEO S04 REF)

### Page 18

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 17 of 37
Rev. 3 May 8/13
K215T40028−S0508
(SHIM)
K215T40028−S0502
(SHIM)
K215T40028−S0506
(SHIM)
K215T40028−S0504
(SHIM)
K215T40028−S0510
(SHIM)
1.36 in.
(3,45 cm) R 0.25 in.(6,35 mm)
R 0.25 in.
(6,35 mm)
2.06 in.
(5,23 cm)
R 0.25 in.
(6,35 mm)
1.82 in.
(4,62 cm)
DIA 0.50 in.
(12,70 mm)
0.69 in.
(17,52 mm)
R 0.25 in.
(6,35 mm)
0.025 in.
(0,63 mm)
0.025 in.
(0,63 mm)
0.025 in.
(0,63 mm)
0.016 in.
(0,41 mm)
0.016 in.
(0,41 mm)
STRUCTURAL MODIFICATION OF PILOT AND COPILOT OXYGEN SYSTEM FOR A/C 2077
FIGURE 2
NOTE
All shims are fabricated from,
AL ALY 2024−T3 PER SPEC AMS−QQ−A−250/5.

### Page 19

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 18 of 37
Rev. 3 May 8/13
C. Modification for Aircraft Serial No. 2001, 2002, 2005 to 2007, 2010, 2012 to 2017, 2019,
2022 to 2024, 2026, 2057, 2063, 2065.
Refer to the Illustration Figure 3 of this Service Bulletin
 
(1) Modify the pilot side oxygen bottle retaining structure as follows:
(a) Remove and retain the pilot oxygen bottle 804464-01 and smoke mask
(b) Remove and retain the the latch assembly 215T40078 −2 and the attaching
hardware.
NOTE: The latch assembly will require rework prior to reinstallation.
(c) Remove and retain the pilot cockpit trim panel 215T40531 −11 that covers the
structure on FS 227.36.
(d) Remove the 10 rivets that secure bracket assembly 215T40077 −10 (item 7 ref) to
the cockpit structure.  Remove and retain the bracket assembly.
(e) Rework bracket assembly 215T40077 −10 as follows:
1 Use the bracket as a template and backdrill the four shims (10 holes) as shown.
2 Open up all 10 holes full size to suit rivets MS20426AD5.
3 Bond the two shims S1002 in place on the channel assembly 215T51425−126 as
shown in accordance with PSP 497, Structural repair Manual, Chapter 51−21−01,
METAL TO METAL COLD BONDING − GENERAL PROCEDURES.
4 Bond shim S1004 and shim S1006 in place on the panel assembly
215T51425−116 as shown in accordance with PSP 497, Structural repair Manual,
Chapter 51−21−01, METAL TO METAL COLD BONDING − GENERAL
PROCEDURES.
(f) Secure the bracket 215T40077 −10 with rivets MS20426AD5−( )A to the panel and
channel assemblies in the 10 existing rivet locations.
NOTE: Rivet grip length is to be determined upon installation.
(g) Reinstall the pilot cockpit trim panel 215T40531 −11.

### Page 20

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 19 of 37
Rev. 3 May 8/13
(2) Rework the latch assembly 215T40078 −2 as follows:
(a) Remove and discard the two straps 215T40079 −10 and 215T40079−12 from the
latch assembly.
(b) Refer to the illustration that shows the installation of the reworked straps
K215T40028−S1012 and −S1014.
1 Cut the new one piece strap 896697 in half and trim each half to length per
dimensions shown in FIGURE 3.
2 Trim and bond the cork (cushion) pads to the strap as shown.  Identify the cork
(cushion) pads as K215T40028−S1016 and −S1018.
(c) Install the base bracket in place on the aircraft structure and secure with the
retained hardware.
(d) Clamp the two reworked straps in place on the base bracket and fit the oxygen
bottle in place to make sure a tight fit is obtained.
(e) Use the base bracket as a template and backdrill the two straps
K215T40028−S1012 and −S1014.
1 Secure the two straps to the base bracket with four rivets MS20470AD5−()A.
NOTE: Rivet grip length is to be determined upon installation.
(f) Reinstall the pilot oxygen bottle 804464-01 and smoke mask.
(3) Make sure that the pilot oxygen bottle is tightly secured in the latch assembly
215T40078−2.
(4) Modify the copilot side oxygen bottle retaining structure as follows:
(a) Remove and retain the copilot oxygen bottle 804464-02 and smoke mask.
(b) Remove and retain the the latch assembly 215T40078 −2 and the attaching
hardware.
NOTE: The latch assembly will require rework prior to reinstallation.
(c) Remove and retain the copilot cockpit trim panel 215T40531 −10 that covers the
structure on FS 227.36.
(d) Remove the 6 rivets that secure bracket assembly 215T40077 −18 (item 8 ref) to the
cockpit structure.  Remove and retain the bracket assembly.

### Page 21

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 20 of 37
Rev. 3 May 8/13
(e) Rework bracket assembly 215T40077 −18 as follows:
1 Use the bracket assembly as a template and backdrill the three shims (6 holes)
as shown.
2 Open up all 6 holes full size to suit rivets MS20426AD5.
3 Bond shim S1002 in place on the channel assembly 215T51425−127 as shown in
accordance with PSP 497, Structural repair Manual, Chapter 51−21−01, METAL
TO METAL COLD BONDING − GENERAL PROCEDURES.
4 Bond shim S1010 in place on panel assembly 215T51425−117 as shown in
accordance with PSP 497, Structural repair Manual, Chapter 51−21−01, METAL
TO METAL COLD BONDING − GENERAL PROCEDURES.
5 Bond shim S1008 in place on the channel assembly 215T51425−60 as shown in
accordance with PSP 497, Structural repair Manual, Chapter 51−21−01, METAL
TO METAL COLD BONDING − GENERAL PROCEDURES.
(f) Secure the bracket assembly 215T40077 −18 with rivets MS20426AD5−( )A to the
panel and channel assemblies in the 6 existing rivet locations.
NOTE: Rivet grip length is to be determined upon installation.
(g) Reinstall the copilot cockpit trim panel 215T40531 −10.
(5) Rework the latch assembly 215T40078 −2 as follows:
(a) Remove and discard the two straps 215T40079 −10 and 215T40079−12 from the
latch assembly.
(b) Refer to the illustration that shows the installation of the reworked straps
K215T40028−S1012 and −S1014.
1 Cut the new one piece strap 896697 in half and trim each half to length per
dimensions shown in FIGURE 3.
2 Trim and bond the cork (cushion) pads to the strap as shown.  Identify the cork
(cushion) pads as K215T40028−S1016 and −S1018.
(c) Install the base bracket in place on the aircraft structure and secure with the
retained hardware.
(d) Clamp the two reworked straps in place on the base bracket and fit the oxygen
bottle in place to make sure a tight fit is obtained.

### Page 22

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 21 of 37
Rev. 3 May 8/13
(e) Use the base bracket as a template and backdrill the two straps
K215T40028−S1012 and −S1014.
1 Secure the two straps to the base bracket with four rivets MS20470AD5−( )A.
NOTE: Rivet grip length is to be determined upon installation.
(f) Reinstall the copilot oxygen bottle 804464-02 and smoke mask.
(6) Make sure that the copilot oxygen bottle is tightly secured in the latch assembly
215T40078−2.

### Page 23

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 22 of 37
Rev. 3 May 8/13
REMOVE 4 EXISTING
MS20426AD4−( )A RIVETS
REMOVE 6 EXISTING
MS20426AD4−( )A RIVETS
215T51425−116 (REF)
(PANEL ASSY)
215T51425−126 (REF)
(CHANNEL ASSY)
215T40077−10 (REF)
(BRACKET ASSY)
BEFORE REPAIR AT FS 227.36
(OXYGEN BOTTLE
NOT SHOWN FOR CLARITY)
BEFORE REPAIR AT FS 227.36
(OXYGEN BOTTLE
NOT SHOWN FOR CLARITY)
215T51425−127 (REF)
(CHANNEL ASSY)
215T51425−60 (REF)
(CHANNEL ASSY))
215T40077−18 (REF)
(BRACKET ASSY)
REMOVE 2 EXISTING
MS20426AD4−( )A RIVETS
REMOVE 3 EXISTING
MS20426AD4−( )A RIVETS
REMOVE EXISTING
MS20426AD4−( )A RIVET
215T51425−117 (REF)
(PANEL ASSY)
STRUCTURAL MODIFICATION OF PILOT AND COPILOT OXYGEN SYSTEM FOR
A/C 2001, 2002, 2006, 2007, 2010, 2013 TO 2015, 2024, 2057, 2063, AND 2065
FIGURE 3
DISCARD STRAP
215T40079−12
DISCARD STRAP
215T40079−10
REMOVE 4 EXISTING
RIVETS
BEFORE REPAIR

### Page 24

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 23 of 37
Rev. 3 May 8/13
215T51425−116 (REF)
(PANEL ASSY)
215T51425−126 (REF)
(CHANNEL ASSY)
AFTER REPAIR AT FS 227.36
(OXYGEN BOTTLE
NOT SHOWN FOR CLARITY)
PICK−UP HOLES
AND INSTALL 6
MS20426AD5−( )A RIVETS
PICK−UP HOLES
AND INSTALL 4
MS20426AD5−( )A RIVETSK215T40028−S1002
(SHIM)
K215T40028−S1002
(SHIM)
SHIM
K215T40028−S1006
(SHIM)
215T40077−10 (REF)
(BRACKET ASSY)
STRUCTURAL MODIFICATION OF PILOT AND COPILOT OXYGEN SYSTEM FOR
A/C 2001, 2002, 2006, 2007, 2010, 2013 TO 2015, 2024, 2057, 2063, AND 2065
FIGURE 3
K215T40028−S1004

### Page 25

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 24 of 37
Rev. 3 May 8/13
AFTER REPAIR AT FS 227.36
(OXYGEN BOTTLE
NOT SHOWN FOR CLARITY)
215T51425−127 (REF)
(CHANNEL ASSY)
215T51425−60 (REF)
(CHANNEL ASSY)
PICK−UP HOLES
AND INSTALL 2
MS20426AD5−( )A RIVETS
PICK−UP HOLES
AND INSTALL 3
MS20426AD5−( )A RIVETS
PICK−UP HOLE
AND INSTALL
MS20426AD5−( )A RIVET
K215T40028−S1002
(SHIM)
K215T40028−S1010
(SHIM)K215T40028−S1008
(SHIM)
215T51425−117 (REF)
(PANEL ASSY)
215T40077−8 (REF)
(BRACKET ASSY)
STRUCTURAL MODIFICATION OF PILOT AND COPILOT OXYGEN SYSTEM FOR
A/C 2001, 2002, 2006, 2007, 2010, 2013 TO 2015, 2024, 2057, 2063, AND 2065
FIGURE 3
INSTALL NEW STRAP
K215T40028−S1014
INSTALL NEW STRAP
K215T40028−S1012PICK−UP HOLES
AND INSTALL 4
MS20470AD5−( )A RIVETS
AFTER REPAIR

### Page 26

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 25 of 37
Rev. 3 May 8/13
MS20426AD5−( )A RIVET
K215T40028−S1002
(SHIM)
0.01 in. MIN.
(0,25 mm)
215T40077−8 (REF) LH
215T40077−10 (REF) LH
(BRACKET ASSY)
215T51425−126 (REF) LH
215T51425−127 (REF) RH
(CHANNEL ASSY)
0.01 in. MIN.
(0,25 mm)
MS20426AD5−( )A RIVET
215T51425−116 (REF)
(PANEL ASSY)
K215T40028−S1004
K215T40028−S1006
(SHIM)
0.01 in. MIN.
(0,25 mm)
MS20426AD5−( )A RIVET
K215T40028−S1008
(SHIM)
215T51425−60 (REF)
(CHANNEL ASSY)
3.15 in.
(8,00 cm)
215T51425−117 (REF)
(PANEL ASSY)
MS20426AD5−( )A RIVET
K215T40028−S1010
(SHIM)
215T40077−10 (REF)
(BRACKET ASSY)
215T40077−8 (REF)
(BRACKET ASSY)
215T40077−8 (REF)
(BRACKET ASSY)
STRUCTURAL MODIFICATION OF PILOT AND COPILOT OXYGEN SYSTEM FOR
A/C 2001, 2002, 2006, 2007, 2010, 2013 TO 2015, 2024, 2057, 2063, AND 2065
FIGURE 3
K215T40028−S1014
(STRAP)K215T40028−S1012(STRAP)
BOND CORK K215T40028−S1016
WITH THE STRAP
BOND CORK K215T40028−S1018
WITH THE STRAP
STRAP FABRICATION
1.57 in.
(3,98 cm)
R 0.13 in.
(3,30 mm)
(4 PLACES)
NOTES
1 Make straps −S1012 and −S1014
from Kidde Aerospace strap 896697.
Cork material: MIL−C−6183, Type 11,
Class 1, Grade B, 0.032 inch thick.
2
2 2
11
0.01 in. MIN.
(0,25 mm)

### Page 27

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 26 of 37
Rev. 3 May 8/13
STRUCTURAL MODIFICATION OF PILOT AND COPILOT OXYGEN SYSTEM FOR
A/C 2001, 2002, 2006, 2007, 2010, 2013 TO 2015, 2024, 2057, 2063, AND 2065
FIGURE 3
K215T40028−S1008
(SHIM)
K215T40028−S1002
(SHIM)
K215T40028−S1006
(SHIM)
K215T40028−S1004
(SHIM)
K215T40028−S1010
(SHIM)
R 0.25 in.
(6,35 mm)
2.06 in.
(5,23 cm)
R 0.25 in.
(6,35 mm)
1.82 in.
(4,62 cm)
DIA 0.50 in.
(12,70 mm)
0.69 in.
(17,52 mm)
R 0.25 in.
(6,35 mm)
0.025 in.
(0,63 mm)
0.025 in.
(0,63 mm)
0.016 in.
(0,41 mm)
0.016 in.
(0,41 mm)
R 0.25 in.
(6,35 mm)
0.025 in.
(0,63 mm)
0.75 in.
(19,05 mm)
NOTE
All shims are fabricated from,
AL ALY 2024−T3 PER SPEC AMS−QQ−A−250/5.

### Page 28

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 27 of 37
Rev. 3 May 8/13
D. Modification for Aircraft Serial No. 2081.
Refer to the Illustration Figure 4 of this Service Bulletin
(1) Locally fabricate the shims as shown in the table below:
Shim
P/N
Qty Material Thickness For dimensions 
refer to:
S0810 3 AL ALY 2024−T3 (AMS−QQ−A−250/5) 0.025 inch Figure 4
S0812 1 AL ALY 2024−T3 (AMS−QQ−A−250/5) 0.016 inch Figure 4
S0814 1 AL ALY 2024−T3 (AMS−QQ−A−250/5) 0.016 inch Figure 4
S0816 1 AL ALY 2024−T3 (AMS−QQ−A−250/5) 0.025 inch Figure 4
S0818 1 AL ALY 2024−T3 (AMS−QQ−A−250/5) 0.016 inch Figure 4
(2) Modify the pilot side oxygen bottle retaining structure as follows:
(a) Remove and retain the pilot oxygen bottle 804464-01 and smoke mask.
(b) Remove and retain the the latch assembly 215T40078 −2 and the attaching
hardware.
NOTE: The latch assembly will require rework prior to reinstallation.
(c) Remove and retain the pilot cockpit trim panel 215T40531 −11 that covers the
structure on FS 227.36.
(d) Remove the 10 rivets that secure bracket assembly 215T40077 −10 (item 7 ref) to
the cockpit structure.  Remove and retain the bracket assembly.
(e) Rework bracket assembly 215T40077 −10 as follows:
1 Use the bracket as a template and backdrill the four shims (10 holes) as shown.
2 Open up all 10 holes full size to suit rivets MS20426AD5.
3 Bond the two shims S0810 in place on the channel assembly 215T51425−126 as
shown in accordance with PSP 497, Structural repair Manual, Chapter 51−21−01,
METAL TO METAL COLD BONDING − GENERAL PROCEDURES.
4 Bond shim S0812 and shim S0814 in place on the panel assembly
215T51425−116 as shown in accordance with PSP 497, Structural repair Manual,
Chapter 51−21−01, METAL TO METAL COLD BONDING − GENERAL
PROCEDURES.

### Page 29

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 28 of 37
Rev. 3 May 8/13
(f) Secure the bracket 215T40077 −10 with rivets MS20426AD5−( )A to the panel and
channel assemblies in the 10 existing rivet locations.
NOTE: Rivet grip length is to be determined upon installation.
(g) Reinstall the pilot cockpit trim panel 215T40531 −11.
(3) Rework the latch assembly 215T40078 −2 as follows:
(a) Remove and discard the two straps 215T40079 −10 and 215T40079−12 from the
latch assembly.
(b) Refer to the illustration that shows the installation of the reworked straps
K215T40028−S0802 and −S0804.
1 Cut the new one piece strap 896697 in half and trim each half to length per
dimensions shown in Figure 3.
2 Trim and bond the cork (cushion) pads to the strap as shown.  Identify the cork
(cushion) pads as K215T40028−S0806 and −S0808.
(c) Install the base bracket in place on the aircraft structure and secure with the
retained hardware.
(d) Clamp the two reworked straps in place on the base bracket and fit the oxygen
bottle in place to make sure a tight fit is obtained.
(e) Use the base bracket as a template and backdrill the two straps
K215T40028−S0802 and −S0804.
1 Secure the two straps to the base bracket with four rivets MS20470AD5−()A.
NOTE: Rivet grip length is to be determined upon installation.
(f) Reinstall the pilot oxygen bottle 804464-01 and smoke mask.
(4) Make sure that the pilot oxygen bottle is tightly secured in the latch assembly
215T40078−2.
(5) Modify the copilot side oxygen bottle retaining structure as follows:
(a) Remove and retain the copilot oxygen bottle 804464-02 and smoke mask.
(b) Remove and retain the the latch assembly 215T40078 −2 and the attaching
hardware.
NOTE: The latch assembly will require rework prior to reinstallation.
(c) Remove and retain the copilot cockpit trim panel 215T40531 −10 that covers the
structure on FS 227.36.
(d) Remove and discard the existing nutplate MS21069L3 from channel 215T51425 −60
(REF).

### Page 30

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 29 of 37
Rev. 3 May 8/13
(e) Remove the 6 rivets that secure bracket assembly 215T40077 −18 (item 8 ref) to the
cockpit structure.  Remove and retain the bracket assembly.
(f) Rework bracket assembly 215T40077 −18 as follows:
1 Use the bracket assembly as a template and backdrill the three shims (6 holes)
as shown.
2 Open up all 6 holes full size to suit rivets MS20426AD5.
3 Bond shim S0810 in place on the channel assembly 215T51425−127 as shown in
accordance with PSP 497, Structural repair Manual, Chapter 51−21−01, METAL
TO METAL COLD BONDING − GENERAL PROCEDURES.
4 Bond shim S0818 in place on panel assembly 215T51425−117 as shown in
accordance with PSP 497, Structural repair Manual, Chapter 51−21−01, METAL
TO METAL COLD BONDING − GENERAL PROCEDURES.
5 Bond shim S0816 in place on the channel assembly 215T51425−60 as shown in
accordance with PSP 497, Structural repair Manual, Chapter 51−21−01, METAL
TO METAL COLD BONDING − GENERAL PROCEDURES.
Refer to SNIEO S08 NOTE 13 and PSP 497 Structural Repair Manual, Filling
Redundant Dimples or Countersinks
(g) Remove and reinstall the existing nutplate from bracket assembly 215T40077 −18
(item 8 REF), as follows:
1 Remove and retain the nutplate.
2 Bond a rivet head MS20426AD3−( )A into the existing countersunk holes with
retaining compound MIL−R−46082 (type 3).
3 Let cure for 24 hours at room temperature.
4 Shave rivet flush, both sides.
5 Drill diameter for 3/32 rivet through bonded rivets.
(h) Secure the bracket assembly 215T40077 −18 with rivets MS20426AD5−( )A to the
panel and channel assemblies in the 6 existing rivet locations.
NOTE: Rivet grip length is to be determined upon installation.
1 Re−install nutplate and rivet through bracket assembly 215T40077−18 and
channel 215T51425−60.
(i) Reinstall the copilot cockpit trim panel 215T40531 −10.

### Page 31

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 30 of 37
Rev. 3 May 8/13
(6) Rework the latch assembly 215T40078 −2 as follows:
(a) Remove and discard the two straps 215T40079 −10 and 215T40079−12 from the
latch assembly.
(b) Refer to the illustration that shows the installation of the reworked straps
K215T40028−S0802 and −S0804.
1 Cut the new one piece strap 896697 in half and trim each half to length per
dimensions shown in Figure 3.
2 Trim and bond the cork (cushion) pads to the strap as shown.  Identify the cork
(cushion) pads as K215T40028−S0806 and −S0808.
(c) Install the base bracket in place on the aircraft structure and secure with the
retained hardware.
(d) Clamp the two reworked straps in place on the base bracket and fit the oxygen
bottle in place to make sure a tight fit is obtained.
(e) Use the base bracket as a template and backdrill the two straps
K215T40028−S0802 and −S0804.
1 Secure the two straps to the base bracket with four rivets MS20470AD5−( )A.
NOTE: Rivet grip length is to be determined upon installation.
(f) Reinstall the copilot oxygen bottle 804464-02 and smoke mask.
(7) Make sure that the copilot oxygen bottle is tightly secured in the latch assembly
215T40078−2.

### Page 32

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 31 of 37
Rev. 3 May 8/13
REMOVE 4 EXISTING
MS20426AD4−( )A RIVETS
REMOVE 6 EXISTING
MS20426AD4−( )A RIVETS
215T51425−116 (REF)
(PANEL ASSY)
215T51425−126 (REF)
(CHANNEL ASSY)
215T40077−10 (REF)
(BRACKET ASSY)
BEFORE REPAIR AT FS 227.36
(OXYGEN BOTTLE
NOT SHOWN FOR CLARITY)
BEFORE REPAIR AT FS 227.36
(OXYGEN BOTTLE
NOT SHOWN FOR CLARITY)
215T51425−127 (REF)
(CHANNEL ASSY)
215T51425−60 (REF)
(CHANNEL ASSY)
215T40077−18 (REF)
(BRACKET ASSY)
REMOVE 2 EXISTING
MS20426AD4−( )A RIVETS
REMOVE 3 EXISTING
MS20426AD4−( )A RIVETS
REMOVE EXISTING
MS20426AD4−( )A RIVET
215T51425−117 (REF)
(PANEL ASSY)
STRUCTURAL MODIFICATION OF PILOT AND COPILOT OXYGEN SYSTEM FOR A/C 2081
FIGURE 4
DISCARD STRAP
215T40079−12
DISCARD STRAP
215T40079−10
REMOVE 4 EXISTING
RIVETS
BEFORE REPAIR
REMOVE AND DISCARD
EXISTING NUTPLATE MS21069L3

### Page 33

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 32 of 37
Rev. 3 May 8/13
215T51425−116 (REF)
(PANEL ASSY)
215T51425−126 (REF)
(CHANNEL ASSY)
AFTER REPAIR AT FS 227.36
(OXYGEN BOTTLE
NOT SHOWN FOR CLARITY)
PICK−UP HOLES
AND INSTALL 6
MS20426AD5−( )A RIVETS
PICK−UP HOLES
AND INSTALL 4
MS20426AD5−( )A RIVETSK215T40028−S0810
(SHIM)
K215T40028−S0810
(SHIM)
SHIM
K215T40028−S0814
(SHIM)
215T40077−10 (REF)
(BRACKET ASSY)
STRUCTURAL MODIFICATION OF PILOT AND COPILOT OXYGEN SYSTEM FOR A/C 2081
FIGURE 4
K215T40028−S0812

### Page 34

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 33 of 37
Rev. 3 May 8/13
AFTER REPAIR AT FS 227.36
(OXYGEN BOTTLE
NOT SHOWN FOR CLARITY)
215T51425−127 (REF)
(CHANNEL ASSY)
215T51425−60 (REF)
(CHANNEL ASSY)
PICK−UP HOLES
AND INSTALL 2
MS20426AD5−( )A RIVETS
PICK−UP HOLES
AND INSTALL 3
MS20426AD5−( )A RIVETS
PICK−UP HOLE
AND INSTALL
MS20426AD5−( )A RIVET
K215T40028−S0810
(SHIM)
K215T40028−S0818
(SHIM)K215T40028−S0816
(SHIM)
215T51425−117 (REF)
(PANEL ASSY)
215T40077−18 (REF)
(BRACKET ASSY)
STRUCTURAL MODIFICATION OF PILOT AND COPILOT OXYGEN SYSTEM FOR A/C 2081
FIGURE 4
INSTALL NEW STRAP
K215T40028−S0804
INSTALL NEW STRAP
K215T40028−S0802PICK−UP HOLES
AND INSTALL 4
MS20470AD5−( )A RIVETS
AFTER REPAIR
1
1
NOTE
1 Bond MS20426AD3−( )A rivet head into existing countersunk holes,
using retaining compound MIL−R−46082 (TYPE III) and cure for 24 hours.
Shave rivet flush on both side and drill holes for 3/32 rivet through bonded rivets.
Reinstall bracket assembly and intercoastal using 3/32 rivets.

### Page 35

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 34 of 37
Rev. 3 May 8/13
MS20426AD5−( )A RIVET
K215T40028−S0810
(SHIM)
0.01 in. MIN.
(0,25 mm)
215T40077−18 (REF) LH
215T40077−10 (REF) LH
(BRACKET ASSY)
215T51425−126 (REF) LH
215T51425−127 (REF) RH
(CHANNEL ASSY)
0.01 in. MIN.
(0,25 mm)
MS20426AD5−( )A RIVET
215T51425−116 (REF)
(PANEL ASSY)
K215T40028−S0812
K215T40028−S0814
(SHIM)
0.01 in. MIN.
(0,25 mm)
MS20426AD5−( )A RIVET
K215T40028−S0816
(SHIM)
215T51425−60 (REF)
(CHANNEL ASSY)
3.15 in.
(8,00 cm)
215T51425−117 (REF)
(PANEL ASSY)
MS20426AD5−( )A RIVET
K215T40028−S0818
(SHIM)
215T40077−10 (REF)
(BRACKET ASSY)
215T40077−18 (REF)
(BRACKET ASSY)
215T40077−18 (REF)
(BRACKET ASSY)
STRUCTURAL MODIFICATION OF PILOT AND COPILOT OXYGEN SYSTEM FOR A/C 2081
FIGURE 4
K215T40028−S0804
(STRAP)K215T40028−S0802(STRAP)
BOND CORK K215T40028−S0806
WITH THE STRAP
BOND CORK K215T40028−S0808
WITH THE STRAP
STRAP FABRICATION
1.57 in.
(3,98 cm)
R 0.13 in.
(3,30 mm)
(4 PLACES)
NOTES
1 Make straps −S0802 and −S0804
from Kidde Aerospace strap 896697.
Cork material: MIL−C−6183, Type 11,
Class 1, Grade B, 0.032 inch thick.
2
2 2
11
0.01 in. MIN.
(0,25 mm)

### Page 36

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 35 of 37
Rev. 3 May 8/13
STRUCTURAL MODIFICATION OF PILOT AND COPILOT OXYGEN SYSTEM FOR A/C 2081
FIGURE 4
K215T40028−S0816
(SHIM)
K215T40028−S0810
(SHIM)
K215T40028−S0814
(SHIM)
K215T40028−S0812
(SHIM)
K215T40028−S0818
(SHIM)
R 0.25 in.
(6,35 mm)
2.06 in.
(5,23 cm)
R 0.25 in.
(6,35 mm)
1.82 in.
(4,62 cm)
DIA 0.50 in.
(12,70 mm)
0.69 in.
(17,52 mm)
R 0.25 in.
(6,35 mm)
0.025 in.
(0,63 mm)
0.016 in.
(0,41 mm)
0.016 in.
(0,41 mm)
0.016 in.
(0,41 mm)
R 0.25 in.
(6,35 mm)
0.025 in.
(0,63 mm)
0.75 in.
(19,05 mm)
NOTE
All shims are fabricated from,
AL ALY 2024−T3 PER SPEC AMS−QQ−A−250/5.

### Page 37

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 36 of 37
Rev. 3 May 8/13
E. 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. Modification for Aircraft Serial No. 2076
Kit No. 215K4457 is necessary to do this Service Bulletin and consists of the the parts that
follow:
PART NO. QUANTITY DESCRIPTION DRW ITEM
K215T40028-S0602 6 Shim (.025” THK) −
K215T40028-S0604 2 Shim (.016” THK) −
K215T40028-S0606 2 Shim (.016” THK) −
K215T40028-S0608 2 Shim (.025” THK) −
K215T40028-S0610 2 Shim (.025” THK) −
896697 2 Strap −
N391−5477 4 Cork 
MIL−C−6183 type II,
Class 1, Grade B
(3.5 X 48.0 Inch)
−
B. Modification for Aircraft Serial No. 2077
Kit No. 215K4457A is necessary to do this Service Bulletin and consists of the the parts that
follow:
PART NO. QUANTITY DESCRIPTION DRW ITEM
K215T40028-S0502 6 Shim (.025” THK) −
K215T40028-S0504 2 Shim (.016” THK) −
K215T40028-S0506 2 Shim (.016” THK) −
K215T40028-S0508 2 Shim (.025” THK) −
K215T40028-S0510 2 Shim (.025” THK) −
896697 2 Strap −
N391−5477 4 Cork 
MIL−C−6183 type II,
Class 1, Grade B
(3.5 X 48.0 Inch)
−

### Page 38

MODEL CL-215-6B11 (415)
SERVICE BULLETIN
Bombardier 415
Service Bulletin 215-4457April 4/12
ATA Ref: 35−10Page 37 of 37
Rev. 3 May 8/13
C. Modification for Aircraft Serial Nos. 2001, 2002, 2005 to 2007, 2010, 2012 to 2017, 2019,
2022 to 2024, 2026, 2057, 2063, 2065.
Kit No. 215K4457B is necessary to do this Service Bulletin and consists of the the parts that
follow:
PART NO. QUANTITY DESCRIPTION DRW ITEM
K215T40028-S1002 6 Shim (.025” THK) −
K215T40028-S1004 2 Shim (.016” THK) −
K215T40028-S1006 2 Shim (.016” THK) −
K215T40028-S1008 2 Shim (.025” THK) −
K215T40028-S1010 2 Shim (.025” THK) −
896697 2 Strap −
N391−5477 4 Cork 
MIL−C−6183 type II,
Class 1, Grade B
(3.5 X 48.0 Inch)
−
D. Modification for Aircraft Serial No. 2081, no kit required, all parts to be manufactured
locally.
E. The following materials, or equivalent, are necessary to do this Service Bulletin. You can buy
them locally:
DESCRIPTION PART NO./NAME SPECIFICATION QUANTITY
Anodizing Solution Alodine 1200S MIL-C-5541 
Class 1A
A/R
Faying Surface
Sealant
Pro Seal 870
Class C
MIL-S-81733 
Type 4
A/R
Fluid Resistant Epoxy
Primer
CMS 565-01 A/R
Rivet  MS20426AD5−()A TBD on
Installation

### Page 39

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)

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