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 Page 1 of 18 22 Jun 2010 VB Revision ‘B’ 14 Feb 2011 

# 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 INFORMA TION 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

S.B. 84 ---28 ---09 Page 2 of 18 22 Jun 2010 VB Revision ‘B’ 14 Feb 2011 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, f our 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

S.B. 84 ---28 ---09 Page 3 of 18 22 Jun 2010 VB Revision ‘B’ 14 Feb 2011 --- 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 incorpora tion 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

S.B. 84 ---28 ---09 Page 4 of 18 22 Jun 2010 VB Revision ‘B’ 14 Feb 2011 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

S.B. 84 ---28 ---09 Page 5 of 18 22 Jun 2010 VB 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 INFORMA TION 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

S.B. 84 ---28 ---09 Page 6 of 18 22 Jun 2010 VB Revision ‘B’ 14 Feb 2011 Quantity Per Kit ---001 Remarks Description Part Number
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

S.B. 84 ---28 ---09 Page 7 of 18 22 Jun 2010 VB Revision ‘B’ 14 Feb 2011 Existing Part Number PNC New Part Number DC IC Qty. Description 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. Inst allation 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

S.B. 84 ---28 ---09 Page 8 of 18 22 Jun 2010 VB Revision ‘B’ 14 Feb 2011 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

S.B. 84 ---28 ---09 Page 9 of 18 22 Jun 2010 VB Revision ‘B’ 14 Feb 2011 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

S.B. 84 ---28 ---09 Page 10 of 18 22 Jun 2010 VB Revision ‘B’ 14 Feb 2011 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 T ANK (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

S.B. 84 ---28 ---09 Page 11 of 18 22 Jun 2010 VB Revision ‘B’ 14 Feb 2011 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

S.B. 84 ---28 ---09 Page 12 of 18 22 Jun 2010 VB Revision ‘B’ 14 Feb 2011 (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 T ANK (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

S.B. 84 ---28 ---09 Page 13 of 18 22 Jun 2010 VB Revision ‘B’ 14 Feb 2011 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

S.B. 84 ---28 ---09 Page 14 of 18 22 Jun 2010 VB Revision ‘B’ 14 Feb 2011 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 wit h 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

### SERVICE BULLETIN 84 ---28 ---09

S.B. 84 ---28 ---09 Page 15 of 18 22 Jun 2010 VB Revision ‘B’ 14 Feb 2011 (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 applic able 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

S.B. 84 ---28 ---09 Page 16 of 18 22 Jun 2010 VB Revision ‘B’ 14 Feb 2011 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)
Y

W --42.000 522BT (LHS) 622BT (RHS)

### SERVICE BULLETIN 84 ---28 ---09

S.B. 84 ---28 ---09 Page 17 of 18 22 Jun 2010 VB Revision ‘B’ 14 Feb 2011 Existing Clipping & Fuel feed Lines --- Removal Left Side Fuel Tanks Figure 2ACCL82822139 ---003ENG FUEL FEED LINEREMOVE EXISTING82822140 ---001ENG FUEL FEED LINEREMOVE EXISTINGREMOVE EXISTING BRACKET.INSTALL NEW BRACKETS AT SAME LOCATION1NOTES:RIB85713370 ---00121285713380 ---001RIB Y--42.00

Y--117.500

Y--136.300

Y--157.820

Y--191.200LEFT WING TOP VIEW SHOWN.REAR SPAR

### SERVICE BULLETIN 84 ---28 ---09

S.B. 84 ---28 ---09 Page 18 of 18 22 Jun 2010 VB Revision ‘B’ 14 Feb 2011 Existing Clipping & Fuel feed Lines --- Removal Right Side Fuel Tanks Figure 3 Y ---173.200

Y ---157.825

Y ---136.300

Y ---25.258ENG FUEL FEED LINEREMOVE EXISTING82822143 ---001ENG FUEL FEED LINEREMOVE EXISTING82822144 ---001ENG FUEL FEED LINEREMOVE EXISTING82822142 ---003 Y ---117.50012NOTES:12REMOVE EXISTING BRACKET.INSTALL NEW BRACKETS AT SAME LOCATIONRIB85713370 ---001RIB85713380 ---002EXISTING CLIPPINGEXISTING FUEL FEED LINEEXISTING SCAVENGE LINERIGHT WING TOP VIEW SHOWN.REMOVE AND DISCARD

3Jan 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 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