Feb 2/12 Service Bulletin 215-A4436

Page 1 of 2 ATA Ref: 53-20

MODEL CL-215-6B11 (415)

REVISION TRANSMITTAL SHEET

FUSELAGE

REPLACEMENT OF MDC RACK PANEL AND 

INSTALLATION OF ADDITIONAL HARNESS SUPPORT

Service Bulletin No.: 215-A4436 Date of Original Issue: Sept 19/11

Revision No.: 1 Date of Issue: Feb 2/12

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 date that the kit parts will be available from our SPS department.

2. Change the date that the Service Bulletin must be completed by in Section 1.A. Compliance.

3. Change the revision of Kit Drawing K215T52127 from revision A to Revision B in Section 1.K.

References.

4. Change the revision of Modification Summary 415−79299 from Revision C to Revision D Section

1.K. References.

5. Add Modification Summary 415−79544 Revision B to Section 1.K. References.

6. Add SNIEOs S02 to Section 1.K. References.

7. Add note 10 in Section 2, Accomplishment Instructions to advise that the MDC panel assembly is

re−identified as 215T52126−S0201 in accordance with 215T52126 SNIEO 02.
MODEL CL-215-6B11 (415)

SERVICE BULLETIN

Bombardier 415

Feb 2/12 Service Bulletin 215-A4436

Page 2 of 2 ATA Ref: 53-20

8. Add note 11 in Section 2, Accomplishment Instructions to locally manufacture a tool to help with

the removal/installation of certain hardware.

9. Revise the MDC Modification instructions in Section 2.A. to advise of additional components to be

removed to gain access.

10. Add reference to Note 21 from the Kit Drawing in Section 2.A.(17) with regards to the usage of an

alternate edge protector.

11. Add alternative P/N 215T52126−S0201 to 215T52126−2 (item 2) in the Accomplishment

Instructions and the Material Information.
Sept 19/11 Service Bulletin 215-A4436

Page 1 of 17 ATA Ref: 53-20

Rev. 1 Feb. 2/12

MODEL CL-215-6B11 (415)

ALERT

SERVICE BULLETIN

FUSELAGE

REPLACEMENT OF MDC RACK PANEL AND 

INSTALLATION OF ADDITIONAL HARNESS SUPPORT

1. Planning Information

A. Compliance

Installation of this Service Bulletin is mandatory and must be completed no later than June

30th, 2013.

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 to 2076.

D. Reason

A Bombardier 415 operator noticed and reported a fouling condition between the bottom of the

MDC rack and some wiring harnesses routed just below the rack.

After an investigation, it was determined that during aircraft operations, the MDC rack is

subject to flexing due to the weight of the two DC Generator Control Units and the Trim

Comparator Unit installed on the rack.

E. Description

This Service Bulletin gives instructions to replace a panel assembly in the existing MDC rack

assembly with a new panel assembly that incorporates additional stiffening support structure to

prevent flexing of the rack. Also, additional clamping is added and relocated to reduce the

possibility of the harness chaffing when contacting adjacent structure.
MODEL CL-215-6B11 (415)

ALERT

SERVICE BULLETIN

Bombardier 415

Sept 19/11 Service Bulletin 215-A4436

Page 2 of 17 ATA Ref: 53-20

Rev. 1 Feb. 2/12

F. Manpower

We estimate that it will take 1 technician approximately 8 hours to complete this Service

Bulletin.

G. Material Availability

Kit No. 215K4436 is necessary to do this Service Bulletin. All parts contained in the kit are free

of charge to operators of the Bombardier 415 aircraft and will be available approximately mid

January, 2012. Please contact your Amphibious Aircraft Customer Service Representative

(CSR) to place a “No Charge” Purchase Order (PO).

H. Tool Availability

No special tools or equipment are necessary.

I. Weight and Balance

As a result of this modification, the aircraft basic weight will increase by 1.56 pounds, and the

out-of-balance moment change will be + 385.423 pound-inches.

J. Electrical Load Data

Not affected.

K. References

For Bombardier Aerospace Reference only:

(Not Supplied with Kit)

Bombardier Aerospace Modification Summary: 415-79299, Revision D

415-79544, Revision B

Bombardier Aerospace Restriction and/or Special Instruction (RSI) C-3880, Revision A.

Bombardier Aerospace Kit Drawing: K215T52127, Revision B.

215T52126 SNIEO S02

L. Publications Affected

PSP 494, Illustrated Parts Catalogue, Chapter 53-20-00

M. Related Service Bulletin

None.
MODEL CL-215-6B11 (415)

ALERT

SERVICE BULLETIN

Bombardier 415

Sept 19/11 Service Bulletin 215-A4436

Page 3 of 17 ATA Ref: 53-20

Rev. 1 Feb. 2/12

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, FIGURE 1 and FIGURE 2 in this Service

Bulletin.

3. When drilling new fastener holes, maintain a 1.5 to 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. Unless otherwise

specified where bonding is required.

5. Review the associated Kit Drawing to get a good overview of the complete removals

and installations.

6. For specific and other general installation instructions, refer to the FLAG NOTES

(numbers in triangles) and the GENERAL NOTES on sheet 2 of the Kit Drawing Parts

List.

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 Drawing for

fastener callout.

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.During manufacturing of the MDC panel assembly 215T52126−2, a rework to the

panel was done in accordance with SNIEO 02 against drawing 215T52126. As a

result of this rework the MDC panel assembly 215T52126−2 is re−identified as

215T52126−S0201.

11. Refer to FIGURE 3 in this Service Bulletin for a visual idea to locally manufacture a

tool to help with the removal/Installation of three of the bolts along FS 236.00 that

secure the existing panel assembly 215T52118-182/-208.
MODEL CL-215-6B11 (415)

ALERT

SERVICE BULLETIN

Bombardier 415

Sept 19/11 Service Bulletin 215-A4436

Page 4 of 17 ATA Ref: 53-20

Rev. 1 Feb. 2/12

A. MDC Modification

(1) Remove the batteries. Refer to PSP 492, Maintenance Manual, Chapter 24.

NOTE: The above step will help to gain access to the forward corner of the MDC rack for

fasteners removal. During re-installation of the LH MDC rack harnesses, it is

necessary to loosen the harness clamps under the MDC shelf bottom (above the

battery location) to ensure proper routing.

(2) Remove and retain the Relay Box “A” 215T52125-2/-4/-6/-8/-10/-12/-26 and the attaching

hardware. DO NOT disconnect the electrical connectors from the box.

(3) Remove and retain the protective Lexan cover 215T52210-32 (2001 to 2036) or

215T52210-96 (2037 to 2990) from the Essential Bus Panel.

Refer to Kit Drawing K215T52127, Sheet 1 and FIGURE 1

(4) Remove the panel assembly 215T52118-182/-208 as follows:

(a) DO NOT disconnect the electrical connectors from the components. Use best shop

practice to suspend the components to allow the removal of the panel assembly

215T52118-182/-208.

NOTE: The use of long tye wraps was found to be useful in suspending the

components.

(b) Remove and retain the hardware that secures the four components (two DC

Generator Control Units 215T50946-2/-4, the Trim Comparator Unit 215T50942-4/

-6/ -10/ or -12 and the Relay Panel “E” 215T52189-2/-6) to the panel assembly

215T52118-182/-208.

(c) Remove and retain panel assembly 215T52118-160 from the MDC. Retain all

hardware.

(d) Remove and discard the ten screws that secure the panel assembly

215T52118-182/-208 to the MDC structure. Retain the ten washers.

NOTE: It may be necessary to locally manufacture a tool to remove the three most

Forward/Inboard screws at FS 236.00 that secure panel assembly

215T52118-182/-208. Refer to the illustration in FIGURE 3

1 Remove and retain all the existing clamps and attaching hardware from the panel

assembly that secure the wiring harnesses.

2 Remove and discard the panel assembly 215T52118-182/-208 from the MDC

rack.
MODEL CL-215-6B11 (415)

ALERT

SERVICE BULLETIN

Bombardier 415

Sept 19/11 Service Bulletin 215-A4436

Page 5 of 17 ATA Ref: 53-20

Rev. 1 Feb. 2/12

Refer to Kit Drawing K215T52127, Sheet 2, View H-H and FIGURE 2.

NOTES: 1. Refer to the various views for installation of screws, clamps, clamp spacers, and

lacing tape to secure the wiring harnesses in place.

2. Refer to FLAG NOTE 22 on the Kit Drawing, Sheet 3 for special instructions on

installation of standoffs and clamps.

(5) Install two standoffs B0204040AL-12W (item 3) to the dimensions shown. Secure the

existing wiring harness in place with three clamps B0305090A9S16 (item 6),

B0305090A9S10 (item 7), and B0305090A9S07 (item 9), a screw NAS1801-3-18

(item 12), and a spacer NAS43DD3-46FC (item 17).

Refer to Kit Drawing K215T52127, Sheet 2, View E−E and FIGURE 2.

(6) Install four additional clamps, two B0305090A9S09 (item 8) and two B0305090A9S06

(item 10) on the existing standoff. Secure all the clamps with a screw NAS1801-3-8

(item 14).

Refer to Kit Drawing K215T52127, Sheet 2, View J-J and FIGURE 2.

(7) Install two standoffs B0204040AL-6W (item 4) to the dimensions shown. Secure the

existing wiring harness in place with a clamp B0305090A9S16 (item 6), a screw

NAS1801-3-4 (item 16).

Refer to Kit Drawing K215T52127, Sheet 2, View K-K and FIGURE 2.

(8) Install two standoffs B0204037AL-10W (item 5) to the dimensions shown. Secure the

existing wiring harness in place with a clamp B0305090A9S16 (item 6), a screw

NAS1801-3-7 (item 15).

Refer to Kit Drawing K215T52127, Sheet 2, View D-D and FIGURE 2.

(9) Position the new MDC rack panel assembly 215T52126-S0201 (item 2) in the MDC

structure. Secure the MDC rack panel assembly with ten screws NAS1801-3-9 (item 13)

and 10 retained washers AN960-10L.

(10) Secure the two DC Generator Control Units 215T50946-2/-4, the Trim Comparator Unit

215T50942-4/-6/-10/ or -12 and the Relay Panel “E” 215T52189-2/-6 in place with the

retained hardware.

(11) Re-install the Relay Box “A” 215T52125-2/-4/-6/-8/-10/-12/-26 and the Cover Assembly

215T52211-8 on the MDC rack structure with the retained hardware.

(a) Reinstall all the retained clamps with attaching hardware on the standoffs on the

MDC rack panel assembly 215T52126-S0201 (item 2) to secure the wiring

harnesses in place.
MODEL CL-215-6B11 (415)

ALERT

SERVICE BULLETIN

Bombardier 415

Sept 19/11 Service Bulletin 215-A4436

Page 6 of 17 ATA Ref: 53-20

Rev. 1 Feb. 2/12

(12) Reinstall the batteries. Refer to PSP 492, Maintenance Manual, Chapter 24.

(13) Reinstall the retained panel assembly 215T52118-160 in the MDC.

(14) Connect the wiring harnesses on the forward side of the MDC rack panel assembly

215T52126-S0201 (item 2) with the mounting plate B0816029-004 (item 11) with cable

ties.

NOTE: Make sure to install the wiring harnesses on the mounting plate B0816029-004

(item 11) with maximum clearance between the wiring harnesses and the

adjacent structure to prevent a fouling condition. Refer to FLAG NOTE 22.

(15) Make sure to remove all drilling debris from the MDC rack and surrounding area to avoid

damage to the electrical components and harnesses.

(16) Re-install the panel assembly 215T52118-160 in the MDC with ten new screws

NAS1801-3-9 (item 13) and the ten retained washers AN960-10L.

Refer to Kit Drawing K215T52127, Sheet 3, Views F-F and G-G and FIGURE 2.

(17) Install the four Rayrim Edge Protectors RK-6182 Type 7 and 8 (items 20, 21, and 22) at

the locations shown. Refer to PSP 492, Maintenance Manual, Chapter 20-11-01,

RAYRIM EDGE PROTECTIVE MATERIAL − DESCRIPTION AND OPERATION.

(a) Refer to FLAG NOTE 21 on the Kit Drawing, Sheet 3 for special instructions on

installation of edge grommets MS21266 in lieu of the Rayrim Edge Protectors.

(18) Reinstall the protective Lexan cover 215T52210-32/ -96 on the Essential Bus Panel.

B. Recording

When this Service Bulletin is completed, make the entry in the aircraft technical log book and

send back the attached Incorporation Notice to Amphibious Aircraft Technical Publications.
MODEL CL-215-6B11 (415)

ALERT

SERVICE BULLETIN

Bombardier 415

Sept 19/11 Service Bulletin 215-A4436

Page 7 of 17 ATA Ref: 53-20

Rev. 1 Feb. 2/12

MDC RACK PANEL REPLACEMENT − REMOVAL

FIGURE 1

215T52118−182/−208

(PANEL ASSY)

215T52118−160

(COVER) LEGEND

REMOVE AND DISCARD

215T52104

(COVER)

REMOVE TO GET ACCESS 215T52105−2

(DOOR ASSY)
MODEL CL-215-6B11 (415)

ALERT

SERVICE BULLETIN

Bombardier 415

Sept 19/11 Service Bulletin 215-A4436

Page 8 of 17 ATA Ref: 53-20

Rev. 1 Feb. 2/12

MDC RACK PANEL REPLACEMENT − REMOVAL

FIGURE 1

215T52189−2/−6

(RELAY PANEL ”E”)

215T50942−2/−6/−10/−12

(TRIM COMPARATOR UNIT)

215T50946−2/−4

(DC GENERATOR

CONTROL UNIT)

215T50946−2/−4

(DC GENERATOR

CONTROL UNIT) LEGEND

REMOVE AND RE−INSTALL

(DO NOT DISCONNECT)

REMOVE TO GET ACCESS

31560−001

(BATTERY)

31560−001

(BATTERY)
MODEL CL-215-6B11 (415)

ALERT

SERVICE BULLETIN

Bombardier 415

Sept 19/11 Service Bulletin 215-A4436

Page 9 of 17 ATA Ref: 53-20

Rev. 1 Feb. 2/12

MDC RACK PANEL REPLACEMENT − REMOVAL

FIGURE 1

LEGEND

REMOVE TO GET ACCESS

215T52125−2/−4/−6/−8/−10/−12/−26

(RELAY BOX ”A”)
MODEL CL-215-6B11 (415)

ALERT

SERVICE BULLETIN

Bombardier 415

Sept 19/11 Service Bulletin 215-A4436

Page 10 of 17 ATA Ref: 53-20

Rev. 1 Feb. 2/12

MDC RACK PANEL REPLACEMENT − INSTALLATION

FIGURE 2

215T52118−160

LEGEND (COVER)

RE−INSTALL

215T52104

(COVER)

215T52105−2

(DOOR ASSY)
MODEL CL-215-6B11 (415)

ALERT

SERVICE BULLETIN

Bombardier 415

Sept 19/11 Service Bulletin 215-A4436

Page 11 of 17 ATA Ref: 53-20

Rev. 1 Feb. 2/12

MDC RACK PANEL REPLACEMENT − INSTALLATION

FIGURE 2

215T50946−2/−4

(DC GENERATOR

CONTROL UNIT)

215T50942−4/−6/−10/−12

(TRIM COMPARATOR UNIT)

215T50946−2/−4

(DC GENERATOR

CONTROL UNIT)

215T52189−2/−6

(RELAY PANEL ”E”)

215T52127−2

(PANEL ASSY)

LEGEND

INSTALL NEW

RE−INSTALL

NAS1801−3−9

(SCREW)

B0816029−004

(PLATE MOUNTING)

31560−001

(BATTERY)
MODEL CL-215-6B11 (415)

ALERT

SERVICE BULLETIN

Bombardier 415

Sept 19/11 Service Bulletin 215-A4436

Page 12 of 17 ATA Ref: 53-20

Rev. 1 Feb. 2/12

MDC RACK PANEL REPLACEMENT − INSTALLATION

FIGURE 2

B0204040AL−12W

(STANDOFF)

NAS43DD3−46FC

(STANDOFF)

B0204040AL−6W

(STANDOFF)

B0204037AL−10W

(STANDOFF)

B0305090A9S16

(CLAMP)

B0305090A9S10

(CLAMP)

B0305090A9S07

(CLAMP)

B0305090A9S09

(CLAMP)

B0305090A9S06

(CLAMP)

B0305090A9S16

(CLAMP)

B0305090A9S16

(CLAMP)

NAS1801−3−18

(SCREW)

NAS1801−3−4

(SCREW)

NAS1801−3−7

(SCREW)

NAS1801−3−8

(SCREW)

LEGEND

INSTALL NEW

EXISTING

STANDOFF
MODEL CL-215-6B11 (415)

ALERT

SERVICE BULLETIN

Bombardier 415

Sept 19/11 Service Bulletin 215-A4436

Page 13 of 17 ATA Ref: 53-20

Rev. 1 Feb. 2/12

MDC RACK PANEL REPLACEMENT − INSTALLATION

FIGURE 2

WARNING: EQUIPMENT LIVE

Turn off power before removing cover

RK−6182 TYPE 7

(RAYRIM − PROTECTIVE

MATERIAL)

2 PLACES

RK−6182 TYPE 7

(RAYRIM − PROTECTIVE

MATERIAL)

RK−6182 TYPE 8

(RAYRIM − PROTECTIVE

MATERIAL)

LEGEND

INSTALL NEW
MODEL CL-215-6B11 (415)

ALERT

SERVICE BULLETIN

Bombardier 415

Sept 19/11 Service Bulletin 215-A4436

Page 14 of 17 ATA Ref: 53-20

Rev. 1 Feb. 2/12

MDC RACK PANEL REPLACEMENT − INSTALLATION

FIGURE 2

215T52125−2/−4/−6/−8/−10/−12/−26

(RELAY BOX ”A”)

LEGEND

RE−INSTALL
MODEL CL-215-6B11 (415)

ALERT

SERVICE BULLETIN

Bombardier 415

Sept 19/11 Service Bulletin 215-A4436

Page 15 of 17 ATA Ref: 53-20

Rev. 1 Feb. 2/12

RATCHET WRENCH TOOL

FIGURE 3

NOTE

Shop made ratchet wrench,

used to remove some bolts with limited

access that secure panel assembly

215T52118−182/−208.

NOTE

Cut a 5/16 ratchet wrench in half

and attach a handle as shown.
MODEL CL-215-6B11 (415)

ALERT

SERVICE BULLETIN

Bombardier 415

Sept 19/11 Service Bulletin 215-A4436

Page 16 of 17 ATA Ref: 53-20

Rev. 1 Feb. 2/12

3. Material Information

A. Kit No. 215K4436 − Parts List

Kit No. 215K4436 is necessary to do this Service Bulletin and consists of the K215T52127-2

Installation Kit that includes the parts that follow:

An additional 10% of common hardware has been added to the quantities below.

PART NO. QUANTITY DESCRIPTION DRW ITEM

215T52126-2

RE−IDENTIFIED AS

215T52126−S0201

1 MDC Rack Panel 

Assembly

2

B0204040AL−12W 2 Standoff 3

B0204040AL−6W 2 Standoff 4

B0204037AL−10W 1 Standoff 5

B0305090A9S16 5 Clamp 6

B0305090A9S10 1 Clamp 7

B0305090A9S09 2 Clamp 8

B0305090A9S07 1 Clamp 9

B0305090A9S06 2 Clamp 10

B0816029−004 1 Mounting Plate 11

NAS1801−3−18 2 Screw 12

NAS1801−3−9 10 Screw 13

NAS1801−3−8 1 Screw 14

NAS1801−3−7 1 Screw 15

NAS1801−3−4 2 Screw 16

NAS43DD3−46FC 2 Spacer 17

MS20470AD4−5A 2 Rivet 18

MS20426AD4−5A 8 Rivet 19

RK−6182 TYPE 7 1 Rayrim − Protective 

Material (7.0 inch)

20

RK−6182 TYPE 7 2 Rayrim − Protective 

Material (7.0 inch)4

21

RK−6182 TYPE 8 1 Rayrim − Protective 

Material (3.5 inch)

22
MODEL CL-215-6B11 (415)

ALERT

SERVICE BULLETIN

Bombardier 415

Sept 19/11 Service Bulletin 215-A4436

Page 17 of 17 ATA Ref: 53-20

Rev. 1 Feb. 2/12

B. The following materials, or equivalent, are necessary to do this Service Bulletin. You can buy

them locally:

DESCRIPTION PART NO./NAME SPECIFICATION QUANTITY

Aerodynamic 

Sealant

Pro Seal 870

Class B−2

MIL-S-81733 

Type 2

A/R

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

Humiseal 1B15 A/R

Fluid Resistant Epoxy

Primer

BAMS 565-01 A/R

Lacing Tape A−A−52081−B−3 A/R
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)