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 theCompliancestatement of the pervious (Rev B) issue Transmittal Letter, refer to NOTE below --- to update the MATERIAL INFORMATION and ACCOMPLISHMENT INSTRUCTIONSsections 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

S.B. 84 ---28 ---03 Page 1 of 28 29 Jun 2006 L.S Revision ‘C’ 15 May 2009 

# 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 INFORMA TION 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.

### SERVICE BULLETIN 84 ---28 ---03

S.B. 84 ---28 ---03 Page 2 of 28 29 Jun 2006 L.S 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

### SERVICE BULLETIN 84 ---28 ---03

S.B. 84 ---28 ---03 Page 3 of 28 29 Jun 2006 L.S Revision ‘C’ 15 May 2009 --- 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.

### SERVICE BULLETIN 84 ---28 ---03

S.B. 84 ---28 ---03 Page 4 of 28 29 Jun 2006 L.S Revision ‘C’ 15 May 2009 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

### SERVICE BULLETIN 84 ---28 ---03

S.B. 84 ---28 ---03 Page 5 of 28 29 Jun 2006 L.S Revision ‘C’ 15 May 2009 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 INFORMA TION
A. Parts Required Per Aircraft (1) Modification 8MK4317 ---003 (2) Detailed Kit Content:

### SERVICE BULLETIN 84 ---28 ---03

S.B. 84 ---28 ---03 Page 6 of 28 29 Jun 2006 L.S Revision ‘C’ 15 May 2009 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

### SERVICE BULLETIN 84 ---28 ---03

S.B. 84 ---28 ---03 Page 7 of 28 29 Jun 2006 L.S Revision ‘C’ 15 May 2009 Part Number Remarks Description Qty. Per Aircraft 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 tostructure (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

### SERVICE BULLETIN 84 ---28 ---03

S.B. 84 ---28 ---03 Page 8 of 28 29 Jun 2006 L.S Revision ‘C’ 15 May 2009 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.

### SERVICE BULLETIN 84 ---28 ---03

S.B. 84 ---28 ---03 Page 9 of 28 29 Jun 2006 L.S Revision ‘C’ 15 May 2009 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.

### SERVICE BULLETIN 84 ---28 ---03

S.B. 84 ---28 ---03 Page 10 of 28 29 Jun 2006 L.S Revision ‘C’ 15 May 2009 B. Procedure
Part A --- Rib Rework atYw ---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).

### SERVICE BULLETIN 84 ---28 ---03

S.B. 84 ---28 ---03 Page 11 of 28 29 Jun 2006 L.S Revision ‘C’ 15 May 2009 (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 Cand 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.

### SERVICE BULLETIN 84 ---28 ---03

S.B. 84 ---28 ---03 Page 12 of 28 29 Jun 2006 L.S Revision ‘C’ 15 May 2009 (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.

### SERVICE BULLETIN 84 ---28 ---03

S.B. 84 ---28 ---03 Page 13 of 28 29 Jun 2006 L.S Revision ‘C’ 15 May 2009 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.

### SERVICE BULLETIN 84 ---28 ---03

S.B. 84 ---28 ---03 Page 14 of 28 29 Jun 2006 L.S Revision ‘C’ 15 May 2009 (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.

### SERVICE BULLETIN 84 ---28 ---03

S.B. 84 ---28 ---03 Page 15 of 28 29 Jun 2006 L.S Revision ‘C’ 15 May 2009 (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 Y

W--42.000bray31a01.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) Y

W--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--2bray31a02.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 2009Spiral 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 B0816019--003 Extend spiral wrap DSC--6HT approximately 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 --209.019bray31a05.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 KA 82822001 (LH ONLY) 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 1DSC530 ---6FUEL GROMMETDSC530 ---7FUEL GROMMETLL---

### 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--6bray31a07.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 8SC0741bray31a08.dg, gv, 21/01/05 P

P

Q Q 2800--J7 (LHS) EXISTING TIE MOUNTS

1Jan 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.comFeb 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 VApproval 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