Revision ‘B’ 14 Feb 2011

DHC ---8 (DASH 8)

SERVICE BULLETIN 84 ---28 ---09

Fuel System --- Center Wing --- Engine Fuel Feed --- Introduction of New

Tube Assemblies To Eliminate Fouling Conditions ---

ModSum 4 ---113643

This page transmits Revision ‘B’ of Service Bulletin 84 ---28 ---09, pages 1 thru

18 dated 14 Feb 2011.

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

--- the References section is revised to convey the latest revision of the service

bulletin and engineering documentation

--- the ACCOMPLISHMENT INSTRUCTIONS section is revised to remove all

references of DHMS C4 ---11 (Coating ---Epoxy Polyamide Enamel, Fluid

Resistant) and replace with DHMS C4.06 Type 1, Class A, Grade A or Grade

B (Coating, Corrosion Preventative for Aircraft Integral Fuel Tanks)

The Compliance in the previous issues of this service bulletin is not affected

by this revision. No additional rework to the aircraft is introduced by this

revision.

Remove Service Bulletin 84 ---28 ---09 Revision ‘A’ dated 01 Sep 2010 and

replace with attached.

Previous issues of Service Bulletin 84 ---28 ---09:

Initial issue --- Pages 1 thru 18 dated 22 Jun 2010

Revision ‘A’ --- Pages 1 thru 18 dated 01 Sep 2010

D

S.B. 84 ---28 ---09

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SERVICE BULLETIN

Customer

Support

ATA SYSTEM: 2812 NUMBER: 84 ---28 ---09

SUBJECT: Fuel System --- Center Wing --- Engine Fuel Feed --- Introduction of

New Tube Assemblies To Eliminate Fouling Conditions ---

ModSum 4 ---113643

1. PLANNING INFORMATION

A. Effectivity

Aircraft Affected:

In ---Service: DHC ---8 Aircraft Model 402 Serial Number 4001 thru 4331.

Verification: ModSum 4 ---113643 has been installed on DHC ---8 Aircraft

Model 402 Serial Number 4106.

Production: ModSum 4 ---113643 will be installed before delivery on

applicable DHC ---8 Aircraft Models 401 and 402 at Serial

Number 4332 and subsequent.

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
SERVICE BULLETIN 84 ---28 ---09

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B. Reason

Problem: Operators of the Q400 aircraft have reported existence of a fouling

condition between engine fuel feed line (p/n 82822143) and the

feed ---through hole in wing rib (p/n 85713381 ---109) at station Y ---157.825

(right side fuel tank).

Other locations have been reported with inadequate clearance between

the fuel pipe and structure. In the event of a lightning strike a spark could

be produced at the fouling interface between pipe and structure.

Solution: This service bulletin introduces ModSum 4 ---113643.

The ModSum replaces five existing fuel lines (two in the left wing and three

in the right wing and supporting brackets) with new fuel lines and

supporting brackets.

The new fuel lines and brackets are designed to include different

geometric angles to ensure that when installed correctly contact with a

feed ---through hole in a rib is eliminated and adequate clearance is

maintained. In addition, Teflon tubing is wrapped around one motive flow

line and scavenge lines in each fuel tank (left and right side) at specific

locations as part of the modification.

C. Description

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

follow:

--- the aircraft is put into a maintenance configuration, all aircraft electrical power is

selected to OFF, MLG lock pins are installed, NG ground lock is engaged, hydraulic

systems pressure is depleted and work stands are set in position

--- the fuel tanks are drained

--- the engines are supported then specific fuel tank access panels (center and outer

wing) are removed

--- residual fuel is mopped up and the tank is vented

--- five existing fuel feed tube assemblies, four existing brackets, cushion clamps and

related hardware are removed

--- new brackets, fuel feed lines are installed and secured using kept hardware

--- the reworked ribs in each wing are re ---identified with a new part number
SERVICE BULLETIN 84 ---28 ---09

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--- Teflon sleeves are installed around a motive fuel line in each outer wing tank

--- the new lines are pressure tested

--- all access panels that were opened to do the job are re ---installed

--- all tools and equipment are removed

--- log book entries are made

D. Compliance

Bombardier Inc. recommends incorporation of ModSum 4 ---113643 at the earliest

opportunity unless otherwise directed by the operator’s airworthiness authority.

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.

F. Manpower

It will take an estimated 35 man ---hours to complete this service bulletin. The

breakdown of the man ---hours is shown in the table that follows:

TASK MAN ---HOURS MAN ---HOURS TO

RWK LEFT WING

MAN ---HOURS TO

RWK RIGHT

WING

Job Set ---Up *2.00 n/a n/a

Procedure /Test/

RTS

n/a 14.00 15.00

Close ---Out **4.00 n/a n/a

* time required to defuel and vent fuel tank not included

** cure time for sealant not included.

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
SERVICE BULLETIN 84 ---28 ---09

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G. Material --- Price and Availability

ModKit 8MK4429 ---001 is available through the Customer Accounts Service Team

at Bombardier Aerospace Regional Aircraft division. Operators should submit a

purchase order 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

Kit Number Description

8MK4429 ---001 Engine Fuel Feed Line --- Retrofit Kit

H. Tooling --- Price and Availability

None

I. Weight and Balance

None

J. Electrical Load Data

Not affected

K. Publications Affected

Maintenance Manual PSM 1 ---84 ---2 ................................

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

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

L. References

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

related data that follows:
SERVICE BULLETIN 84 ---28 ---09

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Revision ‘B’ 14 Feb 2011

DRAWING SHEET REV

8MK4429 1 ---A

8Z6836 1 ---

8Z9209 1 ---A

8Z9214 1 ---

ModSum 4Q113643 Rev. ‘C’

ModSum 4 ---113643 Rev. ‘C’

PCA 42939 Revision 4 (for internal reference only)

An Airworthiness Directive to be issued by Transport Canada is pending.

2. MATERIAL INFORMATION

A. Parts Required Per Aircraft

(1) Modification Kit 8MK4429 ---001

(2) Detailed Kit Content:

Quantity Per Kit

---001

Part Number Description Remarks

4 B0305078 ---04 Clamp

4 B0305078 ---10 Clamp

2 DSC411 ---6 ---0026 Teflon Hose

4 DSC411 ---12 ---032 Teflon Hose

4 B0205016AD5 ---8S Rivet, Solid

4 B0205016AD5 ---7S Rivet, Solid

1 85714430 ---003 Bracket Assy

1 85714428 ---003 Bracket Assy

1 85714527 ---001 Bracket Assy

1 85714426 ---003 Bracket Assy

14 MS29513 ---214 O ---Ring
SERVICE BULLETIN 84 ---28 ---09

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Quantity Per Kit

---001

Part Number Description Remarks

1 82822144 ---003 Tube Assy

1 82822143 ---003 Tube Assy

1 82822142 ---005 Tube Assy

1 82822140 ---003 Tube Assy

1 82822139 ---005 Tube Assy

1 8Z6836 Structural Provision

Drawing

Drawing

1 8Z9209 Retrofit Drawing Drawing

1 8Z9214 Retrofit Drawing Drawing

B. Parts Required to Modify Spares

None

C. Special Tools and Equipment Required

None

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.

Existing

Part Number Description Qty. IC DC

New Part

Number PNC

82822139 ---003 Tube Assy Eng

Feed (LH side)

1 A SAL 82822139 ---005 S

82822140 ---001 Tube Assy Eng

Fee (LH side)

1 A SAL 82822140 ---003 S

82822142 ---003 Tube Assy Eng

Feed (RH side)

1 A SAL 82822142 ---005 S
SERVICE BULLETIN 84 ---28 ---09

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Existing

Part Number PNC

New Part

Description Qty. IC DC Number

82822143 ---001 Tube Assy Eng

Feed (RH side)

1 A SAL 82822143 ---003 S

82822144 ---001 Tube Assy Eng

Feed (RH side)

1 A SAL 82822144 ---003 S

IC Interchangeability Code

A One way 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.

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 part number.

X Reworked part and superseding part are functionally and physically

equivalent but not identical.
SERVICE BULLETIN 84 ---28 ---09

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3. ACCOMPLISHMENT INSTRUCTIONS

A. Job Set ---Up

WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK

ON THE FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF

YOU DO NOT YOU CAN CAUSE INJURIES TO PERSONS AND/OR

DAMAGE TO EQUIPMENT.

(1) Make sure that lock pins are installed thru each main gear and main gear door

mechanism.

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

WARNING: YOU MUST REMOVE THE FUEL FROM THE FUEL TANK IN AN OPEN

AREA. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO

PERSONS AND DAMAGE TO THE EQUIPMENT.

(3) Prepare fuel tank for access. Make sure no fuel or fuel vapors are present

before working on aircraft or in the fuel tanks (refer to AMM TASK

28 ---10 ---00 ---840 ---801).

(4) Set up work platforms and/or ladders to permit access to the fuel tank access

panels between wing stations Y ---42.000 and Y ---317.019 left and right side wing.

Make sure that the work platforms or ladders are electrically grounded.

(5) Make sure to obey the fuel system safety precautions (refer to AMM TASK

28 ---00 ---00 ---910 ---801).

(6) Make sure to obey the electrical/electronic safety precautions (refer to AMM

TASK 24 ---00 ---00 ---910 ---801).

(7) Obey the electrostatic discharge safety precautions (refer to AMM TASK

24 ---00 ---00 ---910 ---802).

CAUTION: MAKE SURE THAT THE FUEL TANKS ARE DRAINED BEFORE YOU

REMOVE THE ACCESS PANELS. IF YOU DO NOT DO THIS, YOU CAN

CAUSE DAMAGE TO THE WING STRUCTURE.
SERVICE BULLETIN 84 ---28 ---09

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CAUTION: MAKE SURE THAT YOU DO NOT MOVE THE AIRCRAFT BEFORE YOU

INSTALL THE FUEL ACCESS PANELS. THIS IS NECESSARY TO

PREVENT DAMAGE TO THE WING AND THE WING BOX STRUCTURE.

(8) Remove the left and/or right wing wet bay fuel tank access panels that follow,

refer to Figure 1 and applicable instructions in AMM TASK

57 ---11 ---01 ---000 ---801:

ACCESS DESIGNATION

523AT (and/or 623AT right wing) Wet Bay Fuel Access Panels

522BT (and/or 622BT right wing) Wet Bay Fuel Access Panels

522CT (and/or 622CT right wing) Wet Bay Fuel Access Panels

(9) Remove the outer wing fuel tank access panels that follow, refer to Figure 1 and

applicable instructions in AMM TASK 57 ---21 ---01 ---000 ---801.

ACCESS DESIGNATION

524AT (and/or 624AT right wing) Outer Wing Fuel Access Panels

524CT (and/or 624CT right wing) Outer Wing Fuel Access Panels

(10) Use cotton cloths or a natural sponge to soak up the remaining fuel.

(11) Remove fuel fumes from tank(s) using applicable instructions in AMM TASK

28 ---10 ---00 ---840 ---802.

NOTE: KEEP A CONTINUOUS FLOW OF VENTILATING AIR THROUGH A

FUEL TANK WHEN WORK IS BEING DONE INSIDE THE TANK.
SERVICE BULLETIN 84 ---28 ---09

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B. Procedure

The Procedure section is divided into two parts. PART 1 gives the instructions to

rework the left side fuel tanks. PART 2 gives the instructions to rework the right side

fuel tanks.

PART 1 --- REWORK THE LEFT SIDE FUEL TANK

(1) Locate and remove the engine fuel feed lines that follow: (including related

cushion clamps and hardware) (refer to applicable instructions in AMM TASK

28 ---21 ---06 ---000 ---801 and Figure 2). Keep related cushion clamps and related

hardware.

--- 82822139 ---003 fuel feed line

--- 82822140 ---001 fuel feed line

(2) Make sure to remove and discard the preformed O --- rings from the fuel line

couplings.

(3) Make sure to put a cap on all open fuel lines. Route the removed fuel lines to

stores to determine disposition.

(4) Install new replacement bracket 85714430 ---003 to rib at station Y ---136.300 in

the left fuel tank as follows:

At station Y ---136.300 locate and carefully remove and discard one existing

bracket from rib (p/n 85713370 ---001) (refer to Figure 2 Flag Note 1).

Deburr the vacated rivet holes and treat with a layer of alodine and touch up

with a layer of DHMS C4.06 Type 1, Class A, Grade A or Grade B, (Coating,

Corrosion Preventative for Aircraft Integral Fuel Tanks).

Install new replacement bracket 85714430 ---003 to rib at station Y ---136.300

using two solid rivets B0205016AD5 ---7S (refer to drawing 8Z6836, VIEW

LOOKING RIB ASSY INBD AT Y ---136.30 LH and detail VIEW A).

In a suitable area next to new bracket 85714430 ---003 re ---identify rib

85713370 ---001 as 8Z6836 ---1 using an indelible marker.

(5) Install new replacement bracket 85714527 ---001 to rib at station Y ---157.825 in

the left fuel tank as follows:

At station Y ---157.825 locate and carefully remove and discard one existing

bracket from rib (p/n 85713380 ---001) (refer to Figure 2 Flag Note 2).
SERVICE BULLETIN 84 ---28 ---09

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Deburr the vacated rivet holes and treat with a layer of alodine and touch up

with a layer of DHMS C4.06 Type 1, Class A, Grade A or Grade B, (Coating,

Corrosion Preventative for Aircraft Integral Fuel Tanks).

Install new replacement bracket 85714527 ---001 to rib at station Y ---157.825

using two solid rivets B0205016AD5 ---8S (refer to drawing 8Z6836, VIEW

LOOKING RIB ASSY INBD AT Y157.825 LH and detail VIEW C).

In a suitable area next to new bracket 85714527 ---001 re ---identify rib

85713380 ---001 as 8Z6836 ---3 using an indelible marker.

(6) Install / route the new fuel feed lines listed below to agree with all of the NOTES

and detail views given on drawing 8Z9209 ASSY VIEW ---001. Secure the fuel

feed lines using previously removed clamps, screws and washers. Make sure to

install new preformed O ---Rings MS29513 ---214 at each coupling B030508A16

during assembly.

--- 82822139 ---005 fuel feed line

--- 82822140 ---003 fuel feed line.

(7) Make sure that the fuel lines installed in the above steps have a minimum

clearance of no less that 0.125 inch from adjacent structure.

NOTE: If any discrepancy exists record the condition then contact the ‘‘Toronto

Help Desk at telephone number (416) 375 ---4000 or facsimile (416)

375 ---4539’’ or E ---mail: thd.qseries@aero.bombardier.com for a

corrective action

NOTE: Fuel lines designed with a protective Teflon sleeve installed around the

tube adjacent to wing structure are not required to achieve the minimum

clearance requirement given in the step above.

(8) Install and secure one Teflon hose DSC411 ---6 ---0026 and two clamps

B0305078 ---04 around tube assembly 82822065 (motive flow) at approx. station

Y ---117.500 to agree with detail views given on drawing 8Z9209 ASSY ---001,

detail VIEW A and NOTES 7, 8 and 9.
SERVICE BULLETIN 84 ---28 ---09

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(9) Install and secure one Teflon hose DSC411 ---12 ---0032 and one clamp

B0305078 ---10 around scavenge fuel line adjacent rib 85713802 at approx.

station Y ---245.019 (refer to drawing 8Z9214, VIEW LOOKING DOWN, DETAIL A.

and NOTES 1 and 2).

(10) Install and secure one Teflon hose DSC411 ---12 ---0032 and one clamp

B0305078 ---10 around scavenge fuel line adjacent rib 85713806 at approx.

station Y ---317.019 (refer to drawing 8Z9214, VIEW LOOKING DOWN, DETAIL A.

and NOTES 1 and 2).

(11) Do a pressure test of the fuel feed lines (left side) to agree with applicable

instructions in AMM TASK 28 ---21 ---00 ---780 ---801.

(12) Refer to the Close Out section of this SB upon successful completion of the

pressure test (left side).

(13) Refer to PART 2 and rework the right side fuel tanks.

PART 2 --- REWORK THE RIGHT SIDE FUEL TANK

(1) Remove and discard cushion clamps and related hardware that secures existing

fuel feed line (p/n 82822143 ---001) to adjacent scavenge line at approx.

Y ---150.00 (refer to detail A on Figure 3).

(2) Locate and remove the engine fuel feed lines that follow: (including related

cushion clamps and hardware) (refer to applicable instructions in AMM TASK

28 ---21 ---06 ---000 ---801 and locations shown on Figure 3). Keep related cushion

clamps and hardware.

--- 82822142 ---003

--- 82822143 ---001

--- 82822144 ---001

(3) Make sure to put a cap on all open fuel lines. Route the removed fuel lines to

stores to determine disposition.

(4) Install new replacement bracket 85714428 ---003 to rib at station Y ---136.300 in

the right side fuel tank as follows:

Locate and carefully remove and discard one existing bracket from rib p/n

85713370 ---002 at station Y ---136.300 (refer to Figure 3 Flag Note 1).
SERVICE BULLETIN 84 ---28 ---09

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Deburr the vacated rivet holes and treat with a layer of alodine and touch up

with a layer of DHMS C4.06 Type 1, Class A, Grade A or Grade B (Coating,

Corrosion Preventative for Aircraft Integral Fuel Tanks).

Install new bracket 85714428 ---003 to rib p/n 85713370 ---002 at station

Y ---136.300 using solid rivets B0205016AD5 ---7S (refer to drawing 8Z6836,

VIEW LOOKING RIB ASSY INBD AT Y ---136.30 and detail VIEW B).

In a suitable area next to new bracket 85714428 ---003 re ---identify rib

85713370 ---002 as 8Z6836 ---2 using an indelible marker.

(5) Install new replacement bracket 85714426 ---003 to rib at station Y ---157.825 in

the right side fuel tank as follows:

At station Y ---157.825 locate and carefully remove and discard one existing

bracket from rib (p/n 85713380 ---002) (refer to Figure 3 Flag Note 2).

Deburr the vacated rivet holes and treat with a layer of alodine and touch up

with a layer of DHMS C4.06 Type 1, Class A, Grade A or Grade B (Coating,

Corrosion Preventative for Aircraft Integral Fuel Tanks).

Install new bracket 85714426 ---003 to rib at station Y ---157.825 using two solid

rivets B0205016AD5 ---8S (refer to drawing 8Z6836 VIEW LOOKING RIB ASSY

INBD AT Y157.825 and detail VIEW D).

In a suitable area next to new bracket 85714526 ---003 re ---identify rib

85713380 ---002 as 8Z6836 ---4 using an indelible marker.

(6) Install / route the new fuel feed lines listed below to agree with all of the Notes

and detail views given on drawing 8Z9209, ASSY VIEW ---002. Secure the fuel

feed lines using previously removed clamps, screws and washers. Make sure to

use new O ---Rings MS29513 ---214 at each coupling B030508A16 during

assembly.

--- 82822142 ---005 fuel feed line

--- 82822143 ---003 fuel feed line

--- 82822144 ---003 fuel feed line

(7) Make sure that fuel lines installed in the above steps have a minimum clearance

of no less that 0.125 inch from adjacent structure.
SERVICE BULLETIN 84 ---28 ---09

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NOTE: Fuel lines designed with a protective Teflon sleeve installed around the

tube adjacent to wing structure are not required to achieve the minimum

clearance requirement given in the step above.

NOTE: If any discrepancy exists record the condition then contact the ‘‘Toronto

Help Desk at telephone number (416) 375 ---4000 or facsimile (416)

375 ---4539’’ or E ---mail: thd.qseries@aero.bombardier.com for a

corrective action

(8) Install and secure one Teflon hose DSC411 ---6 ---0026 and two clamps

B0305078 ---04 around tube assembly 82822065 (motive flow) at approx. station

Y ---117.500 to agree with detail views given on drawing 8Z9209 ASSY ---002,

detail VIEW A and NOTES 7, 8 and 9.

(9) Install and secure one Teflon hose DSC411 ---12 ---0032 and one clamp

B0305078 ---10 around scavenge tube assembly adjacent rib 85713802 at

approx. station Y ---245.019 to agree with detail views given on drawing 8Z9214

VIEW A. and NOTES 1 and 2.

(10) Install and secure one Teflon hose DSC411 ---12 ---0032 and one clamp

B0305078 ---10 around scavenge fuel line adjacent rib 85713806 at approx.

station Y ---317.019 (refer to drawing 8Z9214, VIEW LOOKING DOWN, DETAIL A.

and NOTES 1 and 2).

(11) Do a pressure test of the fuel feed lines (right side) to agree with applicable

instructions in AMM TASK 28 ---21 ---00 ---780 ---801.

C. Close Out

(1) Make sure to remove all debris and unwanted material(s) from the fuel tanks.

(2) Install the left and/or right wing wet bay fuel tank access panels that follow, refer

to AMM TASK 57 ---11 ---01 ---400 ---801:

ACCESS DESIGNATION

523AT (and/or 623AT right wing) Wet Bay Fuel Access Panels

522BT (and/or 622BT right wing) Wet Bay Fuel Access Panels

522CT (and/or 622CT right wing) Wet Bay Fuel Access Panels
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(3) Install the outer wing fuel access panels refer to AMM TASK

57 ---21 ---01 ---400 ---801.

ACCESS DESIGNATION

524CT (and/or 624CT right wing) Outer Wing Fuel Access Panels

524AT (and/or 624AT right wing) Outer Wing Fuel Access Panels

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

(5) On incorporation of this ModSum make an entry that conforms to local

regulatory requirements in the applicable logbook(s). If only part of this

ModSum is completed, use only this service bulletin number as reference and

detail exact limit of work completed. Enter component serial numbers if

applicable. Enter this ModSum number only after complete and functional

incorporation of all work defined in this service bulletin.
SERVICE BULLETIN 84 ---28 ---09

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Removal and Installation of Fuel Access Panels

Figure 1

LH SIDE SHOWN, RH SIDE OPPOSITE

EXCEPT AS NOTED

523AT (LHS)

623AT (RHS)

522CT (LHS)

622CT (RHS)

524AT (LHS)

624AT (RHS)

524CT (LHS)

624CT (RHS)

YW --42.000

522BT (LHS)

622BT (RHS)
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Existing Clipping & Fuel feed Lines --- Removal Left Side Fuel Tanks

Figure 2

AC

CL

REMOVE EXISTING

ENG FUEL FEED LINE

82822139 ---003

REMOVE EXISTING

ENG FUEL FEED LINE82822140 ---001

REMOVE EXISTING BRACKET.INSTALL NEW BRACKETS AT SAME LOCATION

1

NOTES:

RIB

85713370 ---001

2

1 2

RIB

85713380 ---001

Y--42.00

Y--117.500

Y--136.300

Y--157.820

Y--191.200

LEFT WING TOP VIEW SHOWN.

REAR SPAR
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Existing Clipping & Fuel feed Lines --- Removal Right Side Fuel Tanks

Figure 3

Y ---173.200

Y ---157.825

Y ---136.300

Y ---25.258

REMOVE EXISTING

ENG FUEL FEED LINE

82822143 ---001

REMOVE EXISTING

ENG FUEL FEED LINE

82822144 ---001

REMOVE EXISTING

ENG FUEL FEED LINE

82822142 ---003

Y ---117.500

1 2

NOTES:

1 2 REMOVE EXISTING BRACKET. INSTALL NEW BRACKETS AT SAME LOCATION

RIB

85713370 ---001 RIB 85713380 ---002 EXISTING CLIPPING

EXISTING FUEL FEED LINE

EXISTING SCAVENGE LINE

RIGHT WING TOP VIEW SHOWN.

REMOVE AND DISCARD

3
Jan 2009

SERVICE BULLETIN (SB) --- RECORD OF INCORPORATION

--- Q SERIES DASH 8 AIRCRAFT

To: Partner Data Co ---Ordinator (Toronto), Bombardier Aerospace Commercial Aircraft

Phone: (1) 416 375 3534 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

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Company:

Phone: Extn:

Facsimile: Date:

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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