Revision ‘C’ 15 May 2009

DHC ---8 (DASH 8)

SERVICE BULLETIN 84 ---28 ---03

Fuel --- Fuel Tank System --- Enhance Protective Covering for Electrical

Cable Assembly --- ModSum 4 ---126370

This page transmits Revision ‘C’ of Service Bulletin 84 ---28 ---03 pages 1 thru

28, dated 15 May 2009.

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

--- to clarify the Compliance statement of the pervious (Rev B) issue Transmittal

Letter, refer to NOTE below

--- to update the MATERIAL INFORMATION and ACCOMPLISHMENT

INSTRUCTIONS sections to include “O Ring” AS3578 ---026 and sealants

--- to update the References section to convey the latest issue of this Service

Bulletin and related engineering.

NOTE: The previous issue of this Transmittal Letter (Rev B) states that the

compliance is not affected by Revision B. The statement is

misleading and clarification is warranted.

Rework is introduced at Rev B and compliance is affected if a

previous issue of this service bulletin (Initial Issue or Rev ‘A’) was

incorporated.

The Compliance in the Initial Issue or Rev ‘A’ issue of this Service Bulletin is

affected by this revision. Operators should evaluate the content of this

Service Bulletin to determine if rework is required.

Remove Service Bulletin 84 ---28 ---03 Revision ’B’ dated 18 Oct 2006 and

replace with attached.

Previous issues of Service Bulletin 84 ---28 ---03:

Initial issue --- Pages 1 thru 28 dated 29 Jun 2006

Revision ‘A’ --- Pages 1 thru 28 dated 15 Aug 2006

Revision ‘B’ --- Pages 1 thru 28 dated 18 Oct 2006
D

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SERVICE BULLETIN

Customer

Support

ATA SYSTEM: 2800 NUMBER: 84 ---28 ---03

BOMBARDIER AEROSPACE REGIONAL AIRCRAFT CONSIDER THIS

SERVICE BULLETIN TO BE PARTICULARLY SIGNIFICANT AND

URGES OPERATORS TO PROMPTLY EVALUATE THE CONTENTS

SUBJECT: Fuel --- Fuel Tank System --- Enhance Protective Covering for

Electrical Cable Assembly --- ModSum 4 ---126370

1. PLANNING INFORMATION

A. Effectivity

Aircraft Affected:

In ---Service: DHC ---8 Aircraft Models 401 and 402 Serial Numbers 4003,

4004, 4006, 4008 thru 4118.

Verification: ModSum 4 ---126370 has been installed on DHC ---8 Aircraft

Model 402 Serial Number 4006.

Production: ModSum 4 ---126336 will be installed before delivery on

applicable DHC ---8 Aircraft at Serial Number 4119 and

subsequent.
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Revision ‘C’ 15 May 2009

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: This service bulletin (ModSum 4 ---126370) is issued as a result of FAA

certification requirements conveyed by Special Federal Aviation

Regulation 88 (SFAR 88). The regulations are set to enhance fuel tank

system safety.

A fuel system safety review has determined that the electrical cable

assembly connected to the fuel probes and in each wing may not

comply with SFAR 88 certification requirements.

Solution: This service bulletin conveys ModSum 4 ---126370.

The ModSum reworks bonding of electrical connectors 2800 ---J4 and

---J5 to structure, installs new grommets, cushion clamps and winds

additional spiral wrap around the harness (left and right wing) to provide

additional protection from abrasion and chafing.

ModSum 4 ---126370 is designed to enhance fuel tank system safety and

meet FAA SFAR 88 certification requirements.

C. Description

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

follow:

--- lock pins are installed thru each main gear and main gear door mechanism

--- the nose gear ground lock is engaged

--- the fuel tanks are pressure defueled

--- all aircraft electrical power is selected to OFF

--- work platforms or ladders are set up around the wings

--- certain left and/or right wing panels are removed

--- fuel tanks are vented
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--- electrical plugs 2800 ---J4 and 2800 ---J5 are removed from the rib at Yw 42.000.

The contact area on the rib is cleaned and reworked for electrical bonding

--- electrical plugs 2800 ---J4 and 2800 ---J5 are installed in original position on the

rib at location Yw ---42.000, the jamb nut is torque tightened to the required

specification and new lockwire is installed

--- an electrical bonding test is done between connector 2800 ---J4 and 2800 ---J5 to

aircraft structure

--- the remaining length of electrical c/a 82440209 and 82440210 is examined to

determine extent of existing spiral wrap. If required, existing spiral wrap is

unwound and new longer pieces of spiral wrap (extending 4 inches past the

existing tie mounts) are installed and secured to tie mounts with new cable ties

--- the low level float switch cable assembly is examined. New spiral wrap is

installed if spiral wrap was not previously installed

--- the high level float switch cable assembly is examined. New spiral wrap is

installed if spiral wrap was not previously installed

--- the three threaded studs on the fuel high level sensor are dome sealed

--- new fuel grommets are installed

--- new fuel grommets (pre ---cut split) are installed over the installed cable

assemblies and inserted to the existing holes throughout the fuel tanks

--- new grommets are inserted through the fuel quantity probe cable assembly and

then installed to the the existing cutouts located on the fuel partition located

between stations Yw ---60.900 and Yw ---79.700

--- a functional test of the fuel quantity probes is done

--- all access panels are closed

--- the fuel tanks are refueled.

D. Compliance

Bombardier Inc. highly recommends that ModSum 4 ---126370 be incorporated at

the earliest opportunity unless otherwise directed by the operator’s airworthiness

authority.

An Airworthiness Directive from Transport Canada is pending.
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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 104 man ---hours to complete this Service Bulletin. The

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

TASK MAN ---HOURS

Job Set ---Up 35.00

Procedure 40.00

Test / RTS 6.00

Close ---Out 23.00

Many man ---hours would be saved if this ModSum 4 ---126370 is accomplished

concurrently with service bulletin 84 ---57 ---09 (ModSum 4 ---126330).

G. Material --- Price and Availability

ModKit 8MK4317 ---003 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.

Downsview

Ontario

Canada M3K ---1Y5

Facsimile: (416) 375 ---3060

Telephone: (416) 375 ---3920

Kit Number Description Price (US$) Delivery

8MK4317 ---003 Wing Tank Cable

Assy Protection

Quoted at

time of order

Will be given

at time of

order
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H. Tooling --- Price and Availability

None

I. Weight and Balance

None

J. Electrical Load Data

Not affected

K. Publications Affected

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

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

L. References

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

related data that follows:

DRAWING SHEET REV

8MK4317 1 F

8Z6521 1 G

ModSum 4 ---126370 Rev. ‘E’

ModSum 4Q126370 Rev. ‘E’

PCA 40933 issue 2 (for internal reference only)

2. MATERIAL INFORMATION

A. Parts Required Per Aircraft

(1) Modification 8MK4317 ---003

(2) Detailed Kit Content:
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Quantity Per Kit

---003

Part Number Description Remarks

2 DSC530 ---7 Fuel Grommet

2 NAS1149DO316H Washer

2 NAS43DD3 ---72FC Spacer

2 NAS1801 ---3 ---24 Screw

2 MS21919WDF10 Cushioned

Clamp

2 MS35489 ---1 Grommet

50 Ft. DSC230 ---6HT Spiral Wrap

2 DSC530 ---2 Fuel Grommet

8 DSC530 ---3 Fuel Grommet

4 DSC530 ---4 Fuel Grommet

4 DSC530 ---6 Fuel Grommet

76 B0816019 ---003 Cable Ties

1 8Z6521 Retrofit Drawing

1 8MK4317 Retrofit Kit DWG

(3) In addition to the above parts, the following materials are required for the

completion of this service bulletin and may be procured as single items from

Bombardier Aerospace Regional Aircraft or purchased directly from industry

sources.

Addresses of manufacturers and suppliers not shown below are listed in

Structural Repair Manual Chapter 51 or, for 400 Series Aircraft, in

Consumable Products Manual PSM 1 ---84 ---18.

Part Number Qty. Per Aircraft Description Remarks

DHMS S3.01 As required Sealant, Class B,

Type I or Type II

PR 1422 B1/2

PR 1422 B2

or

PR 1776M B1/2

PR 1776M B2

DS 108F 1/4 Pint Solvent, De ---

greaser

Dynamold
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Part Number Remarks Qty. Per Aircraft Description

1200S As required Alodine

As required Abrasive Paper 180 --- 240 Grit

As required Cotton, Lint free

Cloth

236049 1 Tube Alodine 1132 Touch ---N Prep Pen

DHMS A6.09 As required Epoxy Required to secure

C/A Tie Mount to

structure (as required)

DS 108F (or

equivalent)

Solvent

AS3578 ---026 2 O Ring (if required for connector 2800 J4/J5).

Alodine 1132 (Touch ---N Prep Pen) is available from:

Henkel Surface Technologies

32100 Stephenson Highway

Madison Heights, MI 48071

Telephone: 248 ---583 ---9300

Facsimile: 248 ---583 ---2976

B. Parts Required to Modify Spares

None

C. Special Tools and Equipment Required

None

D. Existing Parts Accountability

None
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3. ACCOMPLISHMENT INSTRUCTIONS

A. Job Set ---Up

(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.

(3) Pressure defuel the applicable fuel tank (refer to TASK 12 ---10 ---28 ---650 ---802).

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

WARNINGS and CAUTIONS detailed in Maintenance Manual PSM 1 ---84 ---2

Chapter 24.

(5) Set up work platforms or ladders around and/or under the left (and/or right) wing

to permit access to the fuel tanks. Make sure that the work platforms or ladders

are electrically grounded.

(6) Make sure to obey the fuel system safety precautions (refer to Aircraft

Maintenance Manual PSM 1 ---84 ---2, TASK 28 ---00 ---00 ---910 ---80.

(7) Obey the electrical/electronic safety precautions (refer to TASK

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

(8) Obey the electrostatic discharge safety precautions (refer to TASK

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

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

THE FUEL SYSTEM OR A FUEL SYSTEM COMPONENT. IF YOU DO

NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND

DAMAGE TO THE EQUIPMENT.

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.

WARNING: DRAIN THE FUEL TANKS. REMOVE THE FUMES BEFORE YOU

REMOVE THE FUEL SYSTEM COMPONENT. FUEL FUMES ARE

DANGEROUS AND CAN BE FLAMMABLE.

WARNING: YOU MUST GROUND THE FUEL TENDER, THE AIRCRAFT, AND THE

FUEL NOZZLE BEFORE YOU DEFUEL OR REFUEL THE AIRCRAFT. IF

YOU DO NOT DO THIS, AN ELECTROSTATIC SPARK CAN OCCUR. IT

CAN CAUSE AN EXPLOSION OR A FIRE.
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WARNING: GROUND THE AIRCRAFT AND THE WORKSTAND BEFORE YOU DO

FUEL SYSTEM MAINTENANCE. AN ELECTROSTATIC SPARK CAN

CAUSE AN EXPLOSION OR A FIRE.

CAUTION: DRAIN THE FUEL TANK BEFORE YOU REMOVE THE ACCESS

PANELS. IF YOU DO NOT DO THIS YOU CAN CAUSE DAMAGE TO

THE WING STRUCTURE.

(9) Remove the left and/or right wing panels that follow:

ACCESS DESIGNATION

521BT (and/or 621BT right wing) Dry Bay Fuel Access Panels

522AT (and/or 622AT 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

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

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

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

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

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

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

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

(a) For removal of the dry bay fuel access panel 521BT (and/or 621BT right

wing) refer to PSM 1 ---84 ---2 TASK 57 ---11 ---06 ---000 ---802.

CAUTION: DRAIN THE FUEL TANK BEFORE YOU REMOVE THE ACCESS

PANELS. IF YOU DO NOT DO THIS, YOU CAN CAUSE DAMAGE TO

THE WING STRUCTURE.

(b) For removal of the wet bay fuel access panel refer to PSM 1 ---84 ---2 TASK

57 ---11 ---01 ---000 ---801.

(c) For remove the outer wing fuel access panels refer to PSM 1 ---84 ---2 TASK

57 ---21 ---01 ---000 ---801.

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

before working on aircraft. Refer to Aircraft Maintenance Manual PSM 1 ---84 ---2,

TASK 28 ---10 ---00 ---840 ---801.
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B. Procedure

Part A --- Rib Rework at Yw ---42.000

The procedure that follows gives the instructions to remove electrical connectors

2800 ---J4 (RHS) and 2800 ---J5 (LHS), rework the rib at Yw ---42.000, apply a layer of

alodine, do a bonding check and re ---install the connectors in original location.

(1) Rework rib Yw 42.000 as follows:

(at 2800 ---J4 (RHS) and 2800 ---J5 (LHS))

(a) Remove screw NAS1801 ---3 ---24, washer NAS1149D0316J, spacer

NAS43DD3 ---72FC and cushioned clamp MS21919WDF10 from existing

cable harness 82440209 and 82440210 from bracket at location

Yw ---42.000 (both LHS and RHS), refer to Figure 4, View C.

(b) Cut and discard lockwire MS20995C32 on fuel tank #1 disconnect plug

2800 ---J4 (RHS) and 2800 ---J5 (LHS). Remove and retain jam nut and

sealant ring from connector plug. Put a cap on plug and electrical

connector.

(c) Carefully remove sealant from around fuel tank disconnect plug 2800 ---J4

and 2800 ---J5 with a plastic scraper. Remove plug from rib structure at

station Yw ---42.000.

NOTE: Before re ---installation make sure that the O --- ring (AS3578 ---026) between

the rib at Yw 42.000 (left and right side) and each connector ( ---J4 / ---J5)

are in good condition, replace O --- ring if necessary.

(d) Make sure that the mounting surface around fuel tank disconnect plug

2800 ---J4 and 2800 ---J5 are free from paint, primer, stains, dyes and

anodic/phosphatic coatings, if not, clean as required (refer to applicable

procedure(s) in PSM 1 ---84 ---2 TASK 51 ---80 ---00 ---120 ---801).

(e) Apply alodine 1200S (or 1132 Touch ---N Prep Pen) to all exposed surfaces.

Remove excess alodine 1200S with a clean, cotton cloth moistened with

water. Do not wipe if alodine 1132 was used.

(f) Install fuel tank #1 disconnect plug, 2800 ---J5 (LHS) and 2800 ---J4 (RHS)

to rib at station Yw ---42.000 with retained jamb nut and sealant ring.

Torque jamb nut to 55 to 60 inch pounds and install new lockwire

MS20995C32 (refer to Figure 2).

(g) Do an electrical bonding test between connectors 2800 ---J4 (RHS) and

2800 ---J5 (LHS) to aircraft structure. Reading to be less than 5 milliohms

(refer to Aircraft Maintenance Manual, PSM 1 ---84 ---2, TASK

51 ---80 ---00 ---760 ---801).
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(h) Apply sealant DHMS S3.01, Class B, Type I or Type II to the perimeter of

installed plug 2800 ---J5 and 2800 ---J4 on rib station Yw ---42.000 (fuel side

only).

(i) Secure cable harness 82440209 and 82440210 to bracket at rib location

Yw ---42.000 (on both wings) using cushioned clamp MS21919WDF10,

screw NAS1801 ---3 ---24, washer NAS1149D0316J and spacer

NAS43DD3 ---72FC (refer to Figure 4, View C).

(j) Wind spiral wrap on cable harness 82440209 and 82440210 from bracket

at location Yw ---42.000 (both LHS and RHS), refer to Figure 4 Sheet 1, View

C. Make sure to to extend the spiral wrap up to next tie mount and secure

with cable ties B0816019 ---003. For spiral wrap installation details refer to

PSM 1 ---84 ---2W Chapter 20 ---12 ---10 ---201.

Part B --- Spiral Wrap Installation

NOTE: The procedure that follows gives the instructions to install spiral

wrap DSC230 ---6HT around various cable assemblies. If an alternate

size of spiral wrap is required refer to PSM 1 ---84 ---2W Chapter

20 ---12 ---10 ---201.

(1) Inspect the existing spiral wrap DSC230 ---6HT installations on cable assembly

82440209 and 82440210 (eighteen locations in left and right hand wing tanks)

and do one of the two procedures that follow: (refer to Figure 5, View F)

(a) If the spiral wrap extends at least four inches past the tie mounts refer to

Part C and subsequent.

or

(b) If the existing spiral wrap does not extend four inches past the tie mounts

continue with the next step.

(2) Install new spiral wrap (eighteen locations in left and right hand wing tanks) to

existing cable assemblies 82440209 and 82440210 as follows (only if existing

spiral wrap does not extend four inches past the tie mounts):

NOTE: If any cable tie mount become detached or loosens you must re ---attach

them in original location using DHMS A6.09 epoxy.

(a) Carefully clip the cable ties at each tie mount, loosen clamps as required to

allow the cable assembly to hang. Remove and discard the spiral wrap.
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(b) Measure and cut the new spiral wrap DSC230 ---6HT to extend four inches

past the existing tie mounts (refer to Figure 5, View F).

(c) Install the new spiral wrap to cable assembly 82440209 and 82440210 and

secure the installed spiral wrap ends with cable ties B0816019 ---003.

(d) Install and secure the cable assembly with cable ties B0816019 ---003 to the

existing tie mounts.

(e) Reinstall clamp(s) (if previously removed) to cable assembly (in original

position) and secure to structure using kept hardware.

(3) Install new spiral wrap DSC230 ---6HT throughout the entire length of the low

level float switch cable assembly (If spiral wrap was not previously installed) as

follows:

NOTE: If combination of heat shrink sleeve and spiral wrap already exist on total

length of harness, no additional spiral wrap is required.

(a) Inspect the existing low level float switch cable assembly for heat shrink

tubing installation. Do not remove the heat shrink tubing if installed (refer

to Figure 4, View D).

(b) Loosen or detach clamp(s) as required, keep all hardware. Wind spiral

wrap DSC230 ---6HT along the entire length of the low level float switch

cable assembly. Secure the installed spiral wrap ends with cable ties

B0816019 ---003.

(c) Install the fuel level low switch cable assembly to the existing tie mounts

and secure with cable ties B0816019 ---003. Reinstall clamp(s) to cable

assembly and secure to structure using kept hardware

(4) Install new spiral wrap to the high level float switch cable assembly (If spiral

wrap was not previously installed) as follows:

(a) Measure and cut the new spiral wrap to extend four inches past the

existing tie mounts (refer to Figure 10 View P).

(b) Carefully clip the existing cable ties at each tie mount.

(c) Wind spiral wrap where wires rest against upper structure and through

existing tie mounts. Secure the spiral wrap ends with cable ties

B0816019 ---003.

(d) Install and secure the cable assembly with cable ties B0816019 ---003 to the

existing tie mounts.
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Part C --- Dome Seal High Level Sensor

(1) Dome seal thread openings on the inside of the high level sensor located

between rib stations Yw ---389.019 and Yw ---407.019 as follows:

(a) Clean and degrease thread openings on the high level sensor 8SC0741

with solvent DS 108F (or equivalent) (refer to Figure 10, View P and Figure

5, View F).

(b) Dome seal thread openings on the high level sensor 8SC0741 with sealant

DHMS S3.01 Class B, Type I or Type II. Make sure the thread openings are

completely covered to reduce the possibility of wire contact.

Part D --- New Grommet Installation

(1) Install new fuel grommets DSC530 ---4 to existing holes located on the rib at

stations Yw ---157.825 and Yw ---173.200 as follows:

(a) Trim fuel grommet DSC530 ---4 flange to provide clearance between

electrical bracket assembly and grommet flange on the outboard side of

rib. Refer to Figure 7, Section J ---J, Detail KA.

(b) Clean and degrease the trimmed fuel grommets DSC530 ---4 and areas

surrounding the existing holes on the ribs with a clean, lint ---free, cotton

cloth moistened with solvent DS108 ---F.

(c) Hold open the new trimmed fuel grommet DSC530 ---4 (along pre ---cut slit)

and install grommet over the existing cable assembly 82440209 and cable

assembly 82440210.

(d) Insert the new trimmed fuel grommet DSC530 ---4 into the existing holes

located on the rib at stations Yw ---157.825 and Yw ---173.200. (four

locations per aircraft). Refer to Figure 7, Section J ---J, View K and Detail

KA and Figure 6, View H.

(e) Fillet seal around perimeter of the trimmed fuel grommet DSC530 ---4 on

the inboard side of rib with sealant DHMS S3.01 Class B, Type I or Type II

to retain grommet at stations Yw ---157.825 and Yw ---173.200. Refer to

Aircraft Maintenance Manual PSM 1 ---84 ---2, TASK 51 ---23 ---00 ---800 ---801.

(2) Install new fuel grommets DSC530 ---3 to existing holes located on the rib at

stations Yw ---60.900 , Yw ---98.600, Yw ---117.500 and Yw ---136.300 as follows:

(a) Trim fuel grommet DSC530 ---3 flange to provide clearance between

electrical bracket assembly and grommet flange on the outboard side of

rib. Refer to Figure 7, Section J ---J, Detail KA.

(b) Clean and degrease the trimmed fuel grommets DSC530 ---3 and areas

surrounding the existing holes on the ribs with a clean, lint ---free, cotton

cloth moistened with solvent DS108 ---F.
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(c) Hold open the new fuel grommet DSC530 ---3 (along pre ---cut slit) and

install grommet over the existing cable assembly 82440209 and cable

assembly 82440210.

(d) Insert the new fuel grommet DSC530 ---3 into the existing hole located on

the rib at stations Yw ---60.900, Yw ---98.600, Yw ---117.500 and Yw ---136.300

(8 locations per aircraft). Refer to VIEW M on Figure 8 Sheet 2, Figure 3

and Figure 6.

(e) Fillet seal around perimeter of the trimmed fuel grommet DSC530 ---3 on

the inboard side of rib with sealant DHMS S3.01 Class B, Type I or Type II

to retain grommet at stations stations Yw ---60.900 , Yw ---98.600,

Yw ---117.500 and Yw ---136.300. Refer to Aircraft Maintenance Manual PSM

1 ---84 ---2, TASK 51 ---23 ---00 ---800 ---801.

(3) Install new fuel grommets DSC530 ---2 to existing holes located on the rib at

station Yw ---79.700 as follows:

(a) Hold open the new fuel grommet DSC530 ---2 (along pre ---cut slit) and

install grommet over the existing cable assembly 82440209 (LHS) and

cable assembly 82440210 (RHS). Refer to Figure 5, Section G ---G and

Figure 3, View B.

(b) Insert new fuel grommet DSC530 ---2 into existing hole located on the rib at

station Yw ---79.700 (two locations per aircraft).

(4) Install new fuel grommet to existing holes located on the rib at stations

Yw ---191.200 and Yw ---281.019 as follows:

For aircraft serial number 4007 thru 4118 refer to step (a). For aircraft serial

number 4001 thru 4006 refer to step (b):

(a) For aircraft serial number 4007 thru 4118 install fuel grommet DSC350 ---6,

do the steps that follow:

1 Carefully trim the new fuel grommet DSC530 ---6 to allow the grommet

to fit securely into the undersized hole on the rib at Yw ---191.200

only. Refer to applicable view on Figure 8, Section L ---L and Figure 6,

View H.

2 Hold open the new trimmed fuel grommet DSC530 ---6 along pre ---cut

slit and install grommet over the existing cable assembly 82440209

(LHS) and cable assembly 82440210 (RHS).

3 Insert the new trimmed fuel grommet into the existing hole located on

the rib at station Yw ---191.200 (two locations per aircraft). Make sure

that there is no gap along slit on grommet after installation is

complete.
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(b) For aircraft serial number 4001 thru 4006 install fuel grommet DSC350 ---7

as follows:

1 Hold open the new fuel grommet DSC530 ---7 along pre ---cut slit and

install grommet over the existing cable assembly 82440209 (LHS)

and cable assembly 82440210 (RHS). Refer to applicable view on

Figure 8, Section L ---L.

2 Insert the new fuel grommet DSC530 ---7 into the existing hole located

on the rib at station Yw ---191.200 (two locations per aircraft).

(5) Install new fuel grommet DSC530 ---6 to existing hole located on the rib at

stations Yw ---281.019 as follows:

(a) Hold open the new fuel grommet DSC530 ---7 along pre ---cut slit and install

grommet over the existing cable assembly 82440209 (LHS) and cable

assembly 82440210 (RHS). Refer to Figure 9, Section L ---L.

(b) Insert the new fuel grommet DSC530 ---7 into the existing hole located on

the rib at station Yw ---281.019 (two locations per aircraft).

(6) Install new grommets MS35489 ---1 to existing cutouts located on fuel partition

85714460 as follows:

(a) Split grommet then hold open the new fuel grommet MS35489 ---1 (along

pre ---cut slit) and install grommet over the existing cable assembly (two

locations per aircraft). Refer to Figure 3, View B.

(b) Install new grommet MS35489 ---1 to the existing cutout lip on fuel partition

85714460. Apply sealant DHMS S3.01, Class B, Type I or Type II to the

perimeter of grommet. Refer to Figure 4, Section E ---E.
SERVICE BULLETIN 84 ---28 ---03

S.B. 84 ---28 ---03

Page 16 of 28

29 Jun 2006

L.S

Revision ‘C’ 15 May 2009

C. Close Out

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

(2) Do a function test the fuel quantity probes. Refer to Aircraft Maintenance

Manual PSM 1 ---84 ---2, TASK 28 ---40 ---31 ---720 ---801.

(3) Install the left and/or right wing panels that follow:

ACCESS DESIGNATION

521BT (and/or 621BT right wing) Dry Bay Fuel Access Panels

522AT (and/or 622AT 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

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

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

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

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

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

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

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

(a) For installation of the dry bay fuel access panel 521BT (and/or 621BT right

wing) refer to PSM 1 ---84 ---2 TASK 57 ---11 ---06 ---400 ---802.

(b) For installation of the wet bay fuel access panel refer to PSM 1 ---84 ---2

TASK 57 ---11 ---01 ---400 ---801.

(c) For installation the outer wing fuel access panels refer to PSM 1 ---84 ---2

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

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

regulatory requirements in the applicable logbook(s). 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 ---03

S.B. 84 ---28 ---03

Page 17 of 28

29 Jun 2006

L.S

Revision ‘C’ 15 May 2009

Removal and Installation of Fuel Access Panels

Figure 1

YW --42.000

bray31a01.dg, gv, 20/01/05

CABLE ASSEMBLY (LHS)

82440209

CABLE ASSEMBLY (RHS)

82440210

LH SIDE SHOWN, RH SIDE OPPOSITE

EXCEPT AS NOTED

522AT (LHS)

622AT (RHS)

522BT (LHS)

622BT (RHS)

523AT (LHS)

623AT (RHS)

522CT (LHS)

622CT (RHS)

524AT (LHS)

624AT (RHS)

524BT (LHS)

624BT (RHS)

524CT (LHS)

624CT (RHS)

524DT (LHS)

624DT (RHS)

524ET (LHS)

624ET (RHS)

524FT (LHS)

624FT (RHS)

YW --42.000

P
SERVICE BULLETIN 84 ---28 ---03

S.B. 84 ---28 ---03

Page 18 of 28

29 Jun 2006

L.S

Revision ‘C’ 15 May 2009

Connector 2800 ---J4 and ---J5 Installation.

Figure 2

LOCKWIRE

MS20995C32

INSTALL CONNECTOR AFTER REWORK .

TORQUE JAM NUT TO 55--60 INCH POUNDS.

NOTE:

MAKE SURE THAT

CONNECTOR MOUNT--

ING AREA IS FREE

FROM CONTAMINATION,

GREASE, PAINT, PRIMER,

ANODIC/PHOSPHATIC

APPLY ALODINE 1200S

TO EXPOSED SURFACES

DUST, SEALANT AND

COATINGS. APPLY

NOTE:

FILLET SEAL PERIMETER

OF CONNECTOR WITH

SEALANT DHMS S3.01

CLASS B TYPE I OR

TYPE II TO THE WET

AREA ONLY ON RIB

Y--42.00

ON 2800--J4 AND 2800--J5

ONLY.
SERVICE BULLETIN 84 ---28 ---03

S.B. 84 ---28 ---03

Page 19 of 28

29 Jun 2006

L.S

Revision ‘C’ 15 May 2009

Grommet and Spiral Wrap Installation Locations

Figure 3

Yw

--42.000

Yw

--60.900

Yw

--79.700

Yw

--98.600

Yw

--117.500

FUEL QUANTITY

PROBE

2800--TU2

FUEL QUANTITY

PROBE

2800--TU3

FUEL QUANTITY

PROBE

2800--TU1

8SC0766

FUEL PUMP DOUBLER

85713207

AUXILLIARY

FUEL PUMP

8SC0743

VIEW LOOKING AFT

VIEW LOOKING DOWN

LOW LEVEL

FLOAT SWITCH

GROMMET

MS35489--1

FUEL GROMMET

DSC--530--2

bray31a02.dg, gv, 21/01/05

M

FUEL

85714460

PARTITION

NOTE:

APPLY SPIRAL WRAP DSC230--6HT

TO ENTIRE LENGTH OF LOW LEVEL

FLOAT WIRING.

M
SERVICE BULLETIN 84 ---28 ---03

S.B. 84 ---28 ---03

Page 20 of 28

29 Jun 2006

L.S

Revision ‘C’ 15 May 2009

Heat Shrink, Spiral Wrap and Grommet Installation

Figure 4 Sheet 1

CABLE ASSEMBLY

82440209 (LHS)

CUSHIONED

CLAMP

HEX HEAD SCREW

WASHER (REF)

CABLE TIE

B0816019--003

SPIRAL WRAP

DSC 230--6HT

82440210 (RHS)

SPACER (REF)

CABLE TIE

B0816019--003

VIEW LOOKING AFT AT Y--60.900

SHOWING HARNESS CLIPPING TO TANK CAN ASSY

FUEL TANK No.1

DISCONNECT

2800--J5 (LHS)

CUSHIONED

CLAMP

MS21919WDF10

SCREW

NAS1801--3--24

WASHER

NAS1801--3--15

2800--J4 (RHS)

HEX HEAD

CABLE ASSEMBLY

82440209 (LHS)

82440210 (RHS)

bray31a03.dg, gv, 21/01/05

NAS1149D0316J

SPACER

NAS43DD3--72FC

SPIRAL WRAP

B0816019 ---003

WIRING TO LOW LEVEL FLOAT SWITCH
SERVICE BULLETIN 84 ---28 ---03

S.B. 84 ---28 ---03

Page 21 of 28

29 Jun 2006

L.S

Revision ‘C’ 15 May 2009

Figure 4 Sheet 2

FUEL PARTITION

85714460

GROMMET

MS35489--1

CABLE ASSEMBLY

82440209 (LHS)

82440210 (RHS)

LH SIDE SHOWN, RH SIDE OPPOSITE

VIEW LOOKING AFT AT FUEL DAM (Between Ribs Y--60.900 & Y--79.700)

DO NOT INSTALL SPIRAL WRAP THRU THE GROMMET
SERVICE BULLETIN 84 ---28 ---03

S.B. 84 ---28 ---03

Page 22 of 28

29 Jun 2006

L.S

Revision ‘C’ 15 May 2009

Spiral Wrap and Grommet Installation

Figure 5

TYPICAL 18 LOCATIONS

LH SIDE SHOWN, RH SIDE OPPOSITE

SPIRAL WRAP

DSC 230--6HT

EXISTING

TIE MOUNTS

CABLE TIE

B0816019--003

CABLE TIE

Extend spiral wrap DSC--6HT approximately B0816019--003

4 inches from existing tie mounts. Secure to

cable assembly with cable tie B0816019--003.

NOTE

4 in.

4 in.

bray31a04.dg, gv, 20/01/05

VIEW LOOKING INBOARD AT RIB Y--79.700

FUEL GROMMET

DSC--530--2

CABLE ASSEMBLY

82440209 (LHS)

82440210 (RHS)

BOTH LEFT AND RIGHT HAND WING TANKS

SLIT
SERVICE BULLETIN 84 ---28 ---03

S.B. 84 ---28 ---03

Page 23 of 28

29 Jun 2006

L.S

Revision ‘C’ 15 May 2009

Grommet Installation

Figure 6

Yw

--136.300

Yw

--157.825

Yw

--173.200

Yw

--191.200

Yw

--209.019

bray31a05.dg, gv, 20/01/05

FUEL QUANTITY

PROBE

2800--TU4

FUEL QUANTITY

PROBE

2800--TU5

FUEL QUANTITY

PROBE

2800--TU6

FUEL GROMMET

DSC530--6

VIEW LOOKING AFT

VIEW LOOKING DOWN

M K K
SERVICE BULLETIN 84 ---28 ---03

S.B. 84 ---28 ---03

Page 24 of 28

29 Jun 2006

L.S

Revision ‘C’ 15 May 2009

Grommet Installation

Figure 7

CABLE ASSEMBLY

82440209 (LHS)

82440210 (RHS)

FUEL GROMMET

DETAIL

82822001 (LH ONLY) KA

82822001

DETAIL KA

NOTE:

TRIM GROMMET

FLANGE TO

PROVIDE CLEAR--

ANCE BETWEEN

ELECT BRKT ASSY

AND GROMMET

FLANGE ON THE

OUTBD SIDE OF

RIB.

M

FUEL GROMMET

DSC530--4

FUEL GROMMET

DSC530--3

DSC530--4 / DSC530--3

VIEW LOOKING INBOARD AT RIB Y-- 60.900, 98.600, 117.500, 136.300, 157.825 AND 173.200

TYPICAL

BOTH LEFT AND RIGHT HAND WING TANKS
SERVICE BULLETIN 84 ---28 ---03

S.B. 84 ---28 ---03

Page 25 of 28

29 Jun 2006

L.S

Revision ‘C’ 15 May 2009

Figure 8 Sheet 1

DSC530 ---6

FUEL GROMMET DSC530 ---7

FUEL GROMMET

L

L ---
SERVICE BULLETIN 84 ---28 ---03

S.B. 84 ---28 ---03

Page 26 of 28

29 Jun 2006

L.S

Revision ‘C’ 15 May 2009

Figure 8 Sheet 2

FUEL GROMMET DSC--530--4

TYPICAL AT STATIONS

Y--60.900, Y--98.600, Y--117.50 AND Y--136.30

BOTH LEFT AND RIGHT HAND

WING TANKS

M

FUEL GROMMET DSC--530--3
SERVICE BULLETIN 84 ---28 ---03

S.B. 84 ---28 ---03

Page 27 of 28

29 Jun 2006

L.S

Revision ‘C’ 15 May 2009

Yw

--227.019

Yw

--245.019

Yw

--263.019

Yw

--281.019

Yw

--299.019

Yw

--317.019

FUEL QUANTITY

PROBE

2800--TU7

FUEL QUANTITY

PROBE

2800--TU8

FUEL GROMMET

DSC530--6

bray31a07.dg, gv, 20/01/05

VIEW LOOKING AFT

VIEW LOOKING DOWN

Grommet Installation

Figure 9

N

N
SERVICE BULLETIN 84 ---28 ---03

S.B. 84 ---28 ---03

Page 28 of 28

29 Jun 2006

L.S

Revision ‘C’ 15 May 2009

High Level Sensor Dome Seal Application

Figure 10

Yw

--317.019

Yw

--335.019

Yw

--353.019

Yw

--371.019

Yw

--389.019

Yw

--407.019

FUEL QUANTITY

PROBE

2800--TU9

STR 14

Dome seal thread openings on inside

of sensor to avoid wire contact.

NOTE

VIEW LOOKING OUTBOARD ON

HIGH LEVEL SENSOR FUEL TANK

2800--J7 (LHS)

2800--J8 (RHS)

VIEW LOOKING AFT

VIEW LOOKING DOWN

HIGH LEVEL

SENSOR

8SC0741

bray31a08.dg, gv, 21/01/05

P

P

Q

Q

2800--J7 (LHS) EXISTING TIE

MOUNTS

1
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

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