Revision ‘A’ 15 Jan 2014

DHC-8 (DASH 8)

SERVICE BULLETIN 84-26-15

Fire Protection - Extinguishing System - Forward Baggage

Compartment - Center Fuse - ModSum 4-190360

This page transmits Revision ‘A’ of Service Bulletin 84-26-15, pages 1 thru

18 dated 15 Jan 2014.

This service bulletin is re-issued in its entirety for the reasons that follow:

- the Description section is revised to add a new paragraphs

- the References section is revised to update the status of the engineering

documentation and service bulletin

- the ACCOMPLISHMENT INSTRUCTIONS section is revised to add

additional steps in Part A and to delete step 20 in Part B (no electrical

bonding check required)

The Compliance recommendation in the previous issue of this service

bulletin is not affected by this revision. No additional rework to the aircraft is

introduced by this revision.

Remove the previous issue of Service Bulletin 84-26-15 and replace with

attached.

Previous issues of Service Bulletin 84-26-15:

Initial issue - Pages 1 thru 16 dated 07 Jun 2013

D

S.B. 84-26-15

Page 1 of 18

07 Jun 2013

Revision ‘A’ 15 Jan 2014

JR

SERVICE BULLETIN

Customer

Support

ATA SYSTEM: 2622 NUMBER: 84-26-15

BOMBARDIER AEROSPACE REGIONAL AIRCRAFT CONSIDER THIS

SERVICE BULLETIN TO BE PARTICULARLY SIGNIFICANT AND

URGES OPERATORS TO PROMPTLY EVALUATE THE CONTENTS

SUBJECT: Fire Protection - Extinguishing System - Forward Baggage

Compartment - Center Fuse - ModSum 4-190360

1. PLANNING INFORMATION

NOTE: This service bulletin supercedes Service Bulletin 84-26-13.

A. Effectivity

Aircraft Affected:

In-Service: DHC-8 Aircraft Models 401 and 402 Serial Numbers 4001,

4003 thru 4424.

Production: ModSum 4Y123816 will be installed before delivery on

applicable DHC-8 Aircraft at Serial Number 4425 thru 4449.

Production: ModSum 4Y123869 will be installed before delivery on

applicable DHC-8 Aircraft at Serial Number 4450 thru 4799.

Production: ModSum 4-113741 will be installed before delivery on

applicable DHC-8 Aircraft at Serial Number 4800 and

subsequent.
SERVICE BULLETIN 84-26-15

S.B. 84-26-15

Page 2 of 18

07 Jun 2013

Revision ‘A’ 15 Jan 2014

JR

NOTE: The instructions in this service bulletin are only applicable to the systems

and parts installed at the time of delivery on the aircraft or as changed by

Bombardier Aerospace Service Bulletin(s). Before you do this bulletin,

examine all STC or equivalent action changes to make sure this bulletin

can be completed.

Spares Affected:

None

B. Reason

Problem: There have been reports of severe corrosion on the firex distribution lines

to the forward baggage compartment which has resulted in perforations

of some of the tubes. This could result in insufficient extinguishing agent

reaching the forward baggage compartment in the event of a fire situation.

Solution: This service bulletin provides instructions to inspect the tubes for leaks and

instructions to replace the alumunum tubes with stainless steel tubes.

C. Description

The procedures in this service bulletin give the instructions to do the tasks that

follow:

- aircraft is put into standard configuration for maintenance

- aircraft electrical power is removed

- the nose landing gear lock is engaged

- the main landing gear lock pins are installed thru each main gear and main gear

door mechanism

- the discharge head tube in the forward baggage compartment is plugged with a

plug

- dry nitrogen is connected to the aft pressure bulkhead connection

- the tubing is pressurized to check for leaks

- if no leaks are found, system is put back to normal and the leak test is repeated after

a specific period until all tubes are replaced with stainless steel

- If leak test fails, all aluminum tubing is replaced before next flight

- or the forward baggage compartment is placarded to inhibit use of forward

baggage compartment until the aluminum tubing is replaced with stainless steel

tubing within 10 days

- a leak check is done on the new tubes

- close out.
SERVICE BULLETIN 84-26-15

S.B. 84-26-15

Page 3 of 18

07 Jun 2013

Revision ‘A’ 15 Jan 2014

JR

D. Compliance

Bombardier Inc. recommends incorporation of ModSum 4-190360 as follows,

unless otherwise directed by the operator’s airworthiness authority:

For aircraft more than 12,000 FH or 6 years:

- Inspection: initially within 2,000 FH or 1 year and subsequently at intervals

not to exceed 2,000 FH or 1 year

- Replace tubes within 6,000 FH or 3 years with CRES tubing

For aircraft less than 12,000 FH or 6 years:

- Inspection: initially prior to reaching 12,000 FH or 6 years and

subsequently at intervals not to exceed 2,000 FH or 1 year

- Replace: prior to accumulating 18,000 FH or 9 years with CRES tubing

Transport Canada Airworthiness Directive Pending

E. Approval

The technical content of this service bulletin has been approved under the

authority of the Transport Canada Civil Aviation (TCCA) Design Approval

Organization No: DAO #93-Q-02.

This service bulletin does not affect Airworthiness Limitations (AWLs) or Damage

Tolerance Inspections (DTIs).

F. Manpower

PART A - Integrity Check of Firex Distribution Lines

It will take an estimated 1.00 man-hours to complete PART A of the

ACCOMPLISHMENT instructions in this service bulletin. The breakdown of man

-hours is shown in the table that follows:

TASK MAN-HOURS

Job Set-Up 0.25

Procedure in Part A 0.25

Test / RTS 0.25

Close-Out 0.25
SERVICE BULLETIN 84-26-15

S.B. 84-26-15

Page 4 of 18

07 Jun 2013

Revision ‘A’ 15 Jan 2014

JR

PART B - Tube Replacement

It will take an estimated 41.00 man-hours to complete PART B of the

ACCOMPLISHMENT instructions in this service bulletin. The breakdown of man

-hours is shown in the table that follows:

TASK MAN-HOURS

Job Set-Up 0.25

Procedure in Part

B

40.00

Test / RTS 0.50

Close-Out 0.25

For any on-site labor assistance, please speak with a Fleet Services representative

for a quote. The Fleet Services group can be contacted via the Q Series Technical

Help Desk by telephone at 416-375-4000 or email at:

thd.qseries@aero.bombardier.com

G. Material - Price and Availability

The ModKit(s) required to do this service bulletin are listed in the table below:

Operators should submit a purchase order through the Customer Accounts Service

Team (CAST) at Bombardier Aerospace Regional Aircraft division specifying aircraft

serial number(s) to:

Bombardier Aerospace

Customer Accounts Services Team (Mail Stop N11-32)

123 Garratt Blvd.

Toronto

Ontario

Canada M3K-1Y5

Facsimile: (416) 375-3060

Telephone: (416) 375-3920

Facsimile:

International: (416) 375-3334

European: (416) 373-5966

Americas East: (416) 373-5964

Americas West: (416) 373-5965
SERVICE BULLETIN 84-26-15

S.B. 84-26-15

Page 5 of 18

07 Jun 2013

Revision ‘A’ 15 Jan 2014

JR

Telephone:

International: (416) 375-3706

European: (416) 373-3704

Americas East: (416) 375-3700

Americas West: (416) 373-5888

E-mail addresses:

International: cast.international@aero.bombardier.com

European: cast.europe@aero.bombardier.com

Americas East: cast.americaseast@aero.bombardier.com

Americas West: cast.americaswest@aero.bombardier.com

Kit Number Description

8MK4652-001/-003/-051 Kit -Tube Installation Fire Protection

System Forward Baggage C/Fuse

NOTE: Kit 8MK4652-051 required only if Kit 8MK4598 was ordered from previous

S.B. 84-26-13.

H. Tooling - Price and Availability

None

I. Weight and Balance

A/C Type and

Model

Weight (Lb) Arm (Inches)

Moment

(Inches x Lb)

x 0.001

DHC-8 Model 401 +9.5 418.2 4.0

DHC-8 Model 402 +9.5 418.2 4.0

J. Electrical Load Data

Not affected
SERVICE BULLETIN 84-26-15

S.B. 84-26-15

Page 6 of 18

07 Jun 2013

Revision ‘A’ 15 Jan 2014

JR

K. Publications Affected

Dash 8 Illustrated Parts Catalogue PSM 1-84-4 ....................

ModSums Manual PSM 1-84-12 ..................................

Weight and Balance Manual (Imperial) PSM 1-84-8 ................

Weight and Balance Manual (Metric) PSM 1-84-8M ..................

L. References

Revision ‘A’ of this service bulletin was prepared to the engineering drawings and

related data that follows:

DRAWING SHEET REV

8MK4652 1 --

8Z9546 1 A

8Z9546 2 --

8Z9546 3 --

8Z9546 4 --

8Z9546 5 --

ModSum 4Q190360 Rev. ‘A’

ModSum 4-190360 Rev. ‘A’

PCA 43731 Revision 2 (for internal reference only)

Transport Canada Airworthiness Directive Pending

ADR SGUT-13-22137760, ABOE-13-21740728, MFU-13-28731247

(for internal reference only)

2. MATERIAL INFORMATION

A. Parts Required Per Aircraft

(1) Modification Kit 8MK4652-001 for aircraft serial numbers 4001, 4003 thru

4016.
SERVICE BULLETIN 84-26-15

S.B. 84-26-15

Page 7 of 18

07 Jun 2013

Revision ‘A’ 15 Jan 2014

JR

(2) Modification Kit 8MK4652-003 for aircraft serial numbers 4017 thru 4424.

(3) Detailed Kit Content:

Quantity Per Kit

-003 -001

Part Number Description Remarks

40 40 NAS1149C0316R WASHER

11 11 NAS1149C0363R WASHER

1 1 AN924-8J NUT

1 1 AN901-8C GASKET

1 1 B0313006J8 ELBOW

21 21 NAS1802-3-10 SCREW

9 9 MS35338-138 SPRING, WASHER

10 10 MS25083-2BB6 JUMPER

11 11 MS21043-3 NUT

18 18 B0313001J8 UNION

11 11 AN735C8 CLAMP

1 1 82620158-003 TUBE ASSEMBLY

1 1 82620157-007 TUBE ASSEMBLY

1 1 82620156-003 TUBE ASSEMBLY

1 1 82620155-007 TUBE ASSEMBLY

1 1 82620154-005 TUBE ASSEMBLY

1 1 82620149-003 TUBE ASSEMBLY

1 1 82620148-005 TUBE ASSEMBLY

1 1 82620147-003 TUBE ASSEMBLY

1 1 82620146-007 TUBE ASSEMBLY

1 1 82620145-009 TUBE ASSEMBLY

1 1 82620144-007 TUBE ASSEMBLY

1 1 82620143-007 TUBE ASSEMBLY

1 1 82620142-005 TUBE ASSEMBLY

1 1 82620141-005 TUBE ASSEMBLY

1 1 82620140-003 TUBE ASSEMBLY

1 1 82620139-005 TUBE ASSEMBLY

1 1 82620138-005 TUBE ASSEMBLY

1 1 82620137-003 TUBE ASSEMBLY

1 82620136-009 TUBE ASSEMBLY
SERVICE BULLETIN 84-26-15

S.B. 84-26-15

Page 8 of 18

07 Jun 2013

Revision ‘A’ 15 Jan 2014

JR

Quantity Per Kit

-003 -001

Part Number Description Remarks

1 82620136-007 TUBE ASSEMBLY

(4) Modification Kit 8MK4652-051 for operators who have kit 8MK4598-001

and/or -003 from S.B. 84-26-13.

(5) Detailed Kit Content:

Quantity Per Kit

-051

Part Number Description Remarks

1 82620145-009 Tube Assembly see NOTE below

NOTE: Operators that have kit 8MK4598-001 and/or 8MK4598-003 in stock only

need to order delta kit 8MK4652-051.

Tube assembly 82620145-009 is two way interchangeable with tube

assembly 82620145-007 (part of 8MK4598-001/-003). Operators can use

either tube assembly pending ease of installation.

B. Parts Required to Modify Spares

None

C. Special Tools and Equipment Required

Reference Designation Remarks

AN806-D8 Plug

Regulated Nitrogen Supply 300 PSI capability

D. Existing Parts Accountability

The following parts may be affected by this service bulletin. Indented parts are

components of the next higher assembly. The quantity (Qty.) column lists the

quantity that may be affected per aircraft for non-indented parts and the quantity

per next higher assembly for indented parts.
SERVICE BULLETIN 84-26-15

S.B. 84-26-15

Page 9 of 18

07 Jun 2013

Revision ‘A’ 15 Jan 2014

JR

Existing

Part Number Description Qty. IC DC

New Part

Number PNC

82620136

82620137

82620138

82620139

82620140

82620141

82620142

82620143

82620144

82620145

82620146

82620147

82620148

82620149

82620154

82620155

82620156

82620157

82620158

Tube Assembly

Tube Assembly

Tube Assembly

Tube Assembly

Tube Assembly

Tube Assembly

Tube Assembly

Tube Assembly

Tube Assembly

Tube Assembly

Tube Assembly

Tube Assembly

Tube Assembly

Tube Assembly

Tube Assembly

Tube Assembly

Tube Assembly

Tube Assembly

Tube Assembly

1

1

1

1

1

1

1

1

1

1

1

1

1

1

1

1

1

1

1

B

B

B

B

B

B

B

B

B

B

B

B

B

B

B

B

B

B

B

DIS

DIS

DIS

DIS

DIS

DIS

DIS

DIS

DIS

DIS

DIS

DIS

DIS

DIS

DIS

DIS

DIS

DIS

DIS

82620136-007 or -009

82620137-003

82620138-005

82620139-005

82620140-003

82620141-005

82620142-005

82620143-007

82620144-007

82620145-007 or -009

82620146-007

82620147-003

82620148-005

82620149-003

82620154-005

82620155-007

82620156-003

82620157-007

82620158-003

S

S

S

S

S

S

S

S

S

S

S

S

S

S

S

S

S

S

S

IC Interchangeability Code

A Not interchangeable.

B Removed Part. No direct replacement.

C Conditionally Interchangeable. Installation of superseded part negates the

intent of this service bulletin.

DC Disposition

DIS Discard Part.

MUI Multiple Usage Item: Return to stock if serviceable.

RWK Rework existing part in accordance with this service bulletin.

RWI Rework existing part per .....

SAL Salvage. Return to operator’s stores for salvage consideration.
SERVICE BULLETIN 84-26-15

S.B. 84-26-15

Page 10 of 18

07 Jun 2013

Revision ‘A’ 15 Jan 2014

JR

PNC Part Number Code

N No equivalent Bombardier Inc. part number for reworked part. Indicate on

part that this service bulletin has been accomplished.

R Part number after rework.

S Superseding or equivalent part number.

X Reworked part and superseding part are functionally and physically

equivalent but not identical.

3. ACCOMPLISHMENT INSTRUCTIONS

Part A - INSPECTION (Integrity Check of Firex Distribution Lines)

A. Job Set-Up

WARNING: MAKE SURE YOU INSTALL THE LOCKPINS ON THE MAIN LANDING

GEAR. MAKE SURE YOU ENGAGE THE NOSE GEAR LOCK. IF YOU

DO NOT DO THIS, THE LANDING GEAR CAN ACCIDENTALLY

RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND DAMAGE

TO THE EQUIPMENT.

WARNING: MAKE SURE YOU INSTALL THE LOCKPINS IN THE DOOR

MECHANISMS OF THE MLG AND NLG. THE DOOR MECHANISMS

CAN ACCIDENTALLY CLOSE THE LANDING GEAR DOORS. THIS CAN

CAUSE INJURIES TO PERSONS AND DAMAGE TO THE EQUIPMENT.

(1) Placard and select all aircraft electrical power to OFF. Obey all relevant

WARNINGS and CAUTIONS (refer to AMM TASK’S 24-00-00-861-802 and

24-00-00-910-801).

(2) Make sure that lock pins are installed through each main gear and main gear

door mechanism.

(3) Make sure the nose gear ground lock is engaged.
SERVICE BULLETIN 84-26-15

S.B. 84-26-15

Page 11 of 18

07 Jun 2013

Revision ‘A’ 15 Jan 2014

JR

B. Procedure

(1) Perform blockage test of distribution tubes per AMM Task 26-22-21-790-801

Section 4.A. steps (1) through (5), but substitute the high pressure nitrogen

supply rig. Connect the rig at location shown in Figure 1.

(2) On the forward baggage compartment, disconnect tube 82620149 from

discharge nozzle and plug end of tube using plug AN806-D8. See Figure 2.

(3) Pressure test the whole suppression line system to 300 psig, turn off the

nitrogen supply and hold for 5 minutes.

(4) If within 5 minutes the pressure is less than 270 psi (10% or 30 psi) do as

follows:

(a) Reduce the pressure to 0 psi, remove nitrogen supply rig, connect tube

back to the discharge head, remove plug AN806-D8 and connect tube

82620149 to discharge nozzle.

(b) replace all aluminum tubing with stainless steel tubing before next flight,

per PART B - RECTIFICATION, or

(c) Inhibit use of forward baggage compartment by placarding forward

baggage compartment and flight compartment.

(d) Replace the aluminum firex tubes with (CRES) stainless steel tubes within

10 days per Part B - Rectification.

(e) Make appropriate entry in the aircraft journey log.

(5) If the pressure is greater than 270 psi during the 5 minutes, do as follows:

(a) Reduce the pressure to 0 psi, remove nitrogen supply rig, connect tube

back to the discharge head, remove plug AN806-D8 and connect tube

82620149 to discharge nozzle.

(b) Repeat the integrity check as per the Compliance section of this service

bulletin.

C. Close Out

(1) Remove all tools and equipment from the work area.
SERVICE BULLETIN 84-26-15

S.B. 84-26-15

Page 12 of 18

07 Jun 2013

Revision ‘A’ 15 Jan 2014

JR

(2) On completion of this service bulletin, make the following entry in the

appropriate logbook(s): “Service Bulletin 84-26-15 - Fire Protection -

Extinguishing System - Forward Baggage Compartment - Center Fuse - Part A -

INSPECTION incorporated’’.

Part B - RECTIFICATION (Tube Replacement)

A. Job Set-Up

WARNING: MAKE SURE YOU INSTALL THE LOCKPINS ON THE MAIN LANDING

GEAR. MAKE SURE YOU ENGAGE THE NOSE GEAR LOCK. IF YOU

DO NOT DO THIS, THE LANDING GEAR CAN ACCIDENTALLY

RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND DAMAGE

TO THE EQUIPMENT.

WARNING: MAKE SURE YOU INSTALL THE LOCKPINS IN THE DOOR

MECHANISMS OF THE MLG AND NLG. THE DOOR MECHANISMS

CAN ACCIDENTALLY CLOSE THE LANDING GEAR DOORS. THIS CAN

CAUSE INJURIES TO PERSONS AND DAMAGE TO THE EQUIPMENT.

(1) Placard and select all aircraft electrical power to OFF. Obey all relevant

WARNINGS and CAUTIONS (refer to AMM TASK’S 24-00-00-861-802 and

24-00-00-910-801).

(2) Make sure that lock pins are installed through each main gear and main gear

door mechanism.

(3) Make sure the nose gear ground lock is engaged.

B. Procedure

(1) Remove the squibs (cartridges) from the bottles. Refer to AMM Tasks

26-22-06-000-801, 26-22-08-000-801 and 26-22-16-000-801.

(2) Remove HRD bottle. Refer to AMM Task 26-22-03-000-801.

(3) Remove the base panel of the halon box in the forward baggage compartment.

Refer to AMM Task 25-51-15-000-801.

(4) Remove ceiling panels 235AZ, 235BZ and 235CZ. Refer to AMM Task

25-27-01-000-801 (25-27-01-000-802 Next Generation).

(5) Remove overhead bin 234AZ. Refer to AMM Task 25-23-01-000-801

(25-23-01-000-802 Next Generation).
SERVICE BULLETIN 84-26-15

S.B. 84-26-15

Page 13 of 18

07 Jun 2013

Revision ‘A’ 15 Jan 2014

JR

(6) Remove sidewall panels 232CZ and 232DZ. Refer to AMM Task

25-26-01-000-801 (25-26-01-000-802 Next Generation).

(7) Remove the following floor panels: Refer to AMM Tasks 53-23-01-000-801,

53-33-01-000-801 and 53-41-01-000-801.

132DZ, 132EZ, 132FZ, 132GZ, 132HZ, 142AZ, 142BZ, 142CZ, 142DZ, 142EZ,

142FZ, 144CZ, 144EZ, 145AZ, 145BZ and 145CZ.

(8) Remove the aft baggage compartment ceiling liner. Refer to AMM Task

25-52-19-000-801.

(9) Remove aft baggage compartment sidewall panel 251QZ.

(10) Remove the canted bulkhead. Refer to AMM Task 25-52-01-000-801.

(11) Remove and discard the following tubes and all aluminum bonding hardware,

from X1.0 to X136.0. Retain all other hardware. Refer to AMM Task

26-22-21-000-803.

Tube assembly 82620149

Tube assembly 82620148

Tube assembly 82620147

Tube assembly 82620146

Tube assembly 82620145

(12) Remove the following tubes and all aluminum bonding hardware, from X136.0 to

X728.1. Retain all other hardware. Refer to AMM Task 26-22-21-000-802.

Tube assembly 82620157

Tube assembly 82620156

Tube assembly 82620144

Tube assembly 82620143

Tube assembly 82620142

Tube assembly 82620155

Tube assembly 82620154

Tube assembly 82620141

Tube assembly 82620140

Tube assembly 82620139

(13) Remove the following tubes and all aluminum bonding hardware, from X728.1 to

X882.7. Retain all other hardware. Refer to AMM Task 26-22-21-000-801.

Tube assembly 82620138

Tube assembly 82620137

Tube assembly 82620158

Tube assembly 82620136
SERVICE BULLETIN 84-26-15

S.B. 84-26-15

Page 14 of 18

07 Jun 2013

Revision ‘A’ 15 Jan 2014

JR

(14) Install the following new tube assemblies using kept and new electrical bonding

hardware, from X1.0 to X136.0. Refer to AMM Task 26-22-21-400-803.

Tube assembly 82620149-003

Tube assembly 82620148-005

Tube assembly 82620147-003

Tube assembly 82620146-007

Tube assembly 82620145-009 or -007

(15) Install the following new tube assemblies using kept and new electrical bonding

hardware, from X136.0 to X728.1. Refer to AMM Task 26-22-21-400-802.

Tube assembly 82620157-007

Tube assembly 82620156-003

Tube assembly 82620144-007

Tube assembly 82620143-007

Tube assembly 82620142-005

Tube assembly 82620155-007

Tube assembly 82620154-005

Tube assembly 82620141-005

Tube assembly 82620140-003

Tube assembly 82620139-005

(16) Install the following new tube assemblies using kept and new electrical bonding

hardware, from X728.1 to X882.7. Refer to AMM Task 26-22-21-400-801.

Tube assembly 82620138-005

Tube assembly 82620137-003

Tube assembly 82620158-003

Tube assembly 82620136-007 (for aircraft s/n 4001, 4003 thru 4016 only)

or

Tube assembly 82620136-009 (for aircraft s/n 4017 thru 4424 only)

(17) Check the newly installed tubes for leaks per AMM Task 26-22-21-790-801 using

a pressure of 75 psi +- 5 psi.

(18) Rectify any noted leaks and recheck as necessary.

(19) Install HRD bottle. Refer to AMM Task 26-22-03-400-801.

(20) DELETED

(21) Install the squibs (cartridges) to the bottles. Refer to AMM Tasks

26-22-06-400-801, 26-22-08-400-801 and 26-22-16-400-801.
SERVICE BULLETIN 84-26-15

S.B. 84-26-15

Page 15 of 18

07 Jun 2013

Revision ‘A’ 15 Jan 2014

JR

C. Close Out

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

(2) Install the canted bulkhead. Refer to AMM Task 25-52-01-400-801.

(3) Install aft baggage compartment sidewall panel 251QZ.

(4) Install the aft baggage compartment ceiling liner. Refer to AMM Task

25-52-19-400-801.

(5) Install the following floor panels: Refer to AMM Tasks 53-23-01-400-801,

53-33-01-400-801 and 53-41-01-400-801.

132DZ, 132EZ, 132FZ, 132GZ, 132HZ, 142AZ, 142BZ, 142CZ, 142DZ, 142EZ,

142FZ, 144CZ, 144EZ, 145AZ, 145BZ and 145CZ.

(6) Install sidewall panels 232CZ and 232DZ. Refer to AMM Task 25-26-01-400-801

(25-26-01-400-802 Next Generation).

(7) Install overhead bin 234AZ. Refer to AMM Task 25-23-01-400-801

(25-23-01-400-802 Next Generation).

(8) Install ceiling panels 235AZ, 235BZ and 235CZ. Refer to AMM Task

25-27-01-400-801 (25-27-01-400-802 Next Generation).

(9) Install the base panel of the halon box in the forward baggage compartment.

Refer to AMM Task 25-51-15-400-801.

(10) On completion of this service bulletin, make the following entry in the

appropriate logbook(s): “Service Bulletin 84-26-15 - Fire Protection -

Extinguishing System - Forward Baggage Compartment - Center Fuse - Part B -

RECTIFICATION incorporated’’.
SERVICE BULLETIN 84-26-15

S.B. 84-26-15

Page 16 of 18

07 Jun 2013

Revision ‘A’ 15 Jan 2014

JR

Location of LRD bottle

Figure 1

DISCONNECT HERE AND CONNECT NITROGEN LINE
SERVICE BULLETIN 84-26-15

S.B. 84-26-15

Page 17 of 18

07 Jun 2013

Revision ‘A’ 15 Jan 2014

JR

Forward Baggage Compartment

Figure 2

DISCONNECT FROM DISCHARGE NOZZLE AND PLUG

1
SERVICE BULLETIN 84-26-15

S.B. 84-26-15

Page 18 of 18

07 Jun 2013

Revision ‘A’ 15 Jan 2014

JR

This Page Intentionally Blank

1
Jan 2009

SERVICE BULLETIN (SB) --- RECORD OF INCORPORATION

--- Q SERIES DASH 8 AIRCRAFT

To: CMDB Focal

Facsimile: (1) 416 375 4538

E --mail: cmdb.requests@aero.bombardier.com

From:

Company:

Phone: Extn:

Facsimile: Date:

E --mail:

The data that you provide below will help us record the incorporation of this ModSum

and the aircraft effectivity in the maintenance manual.

Operator: Service Bulletin: __________________ Revision: _________

Aircraft Serial Number: Model Number: Date Bulletin Completed:

Aircraft Serial Number: Model Number: Date Bulletin Completed:

Aircraft Serial Number: Model Number: Date Bulletin Completed:

Aircraft Serial Number: Model Number: Date Bulletin Completed:

Aircraft Serial Number: Model Number: Date Bulletin Completed:

Aircraft Serial Number: Model Number: Date Bulletin Completed:

Aircraft Serial Number: Model Number: Date Bulletin Completed:

Aircraft Serial Number: Model Number: Date Bulletin Completed:

Aircraft Serial Number: Model Number: Date Bulletin Completed:

Aircraft Serial Number: Model Number: Date Bulletin Completed:

Aircraft Serial Number: Model Number: Date Bulletin Completed:

Aircraft Serial Number: Model Number: Date Bulletin Completed:

Fax this sheet to (1) 416 375 4538 or Email PDF to:

cmdb.requests@aero.bombardier.com
Feb 2009

SERVICE BULLETIN (SB) --- COMMENT SHEET --- Q SERIES DASH 8 AIRCRAFT

To: SB Focal (Toronto), Bombardier Aerospace Commercial Aircraft

Phone: (1) 416 375 4078 Facsimile: (1) 416 375 4538

E --mail: syed.rizvi@aero.bombardier.com

From:

Company:

Phone: Extn:

Facsimile: Date:

E --mail:

Select appropriate box(es) and add comments or suggestions you would like us to know

that may enhance the quality of our service bulletins.

Service Bulletin: Revision: ModSum:

1. PLANNING INFORMATION

V Effectivity V Reason V Description V Compliance

V Approval V Manpower V Material V Weight and Balance

V Electrical Load V Tooling V References V Publications Affected

2. MATERIAL INFORMATION

V Kit Content V Special Tools/Equipment V Parts to Modify Spares

V Consumables V Disposition of Existing Parts V Other

3. ACCOMPLISHMENT INSTRUCTIONS

V Job Set ---Up V Procedure V Close---Out V Test

V Illustration(s) V Other

4. COMMENTS, REMARKS, SUGGESTIONS

Fax this sheet to (1) 416 375 4538 or Email PDF to:

syed.rizvi@aero.bombardier.com