Revision ‘B’ 21 Oct 2009 DHC ---8 (DASH 8) SERVICE BULLETIN 84 ---28 ---04 Fuel --- Fuel Tank System and Fuel Indication --- Wiring Identification, Segregation and Installation (High Level Sensor and Fuel Quantity Indication) --- Retrofit --- ModSum 4 ---126366 This page transmits Revision ‘B’ of Service Bulletin 84 ---28 ---04, pages 1 thru 32 dated 21 Oct 2009. This service bulletin is re ---issued to introduce new ModKits 8MK4331 ---003 and 8MK4331 ---051. It has been reported that in some instances, installation of a solder sleeve used to terminate the shields of cable assembly 8Z6619 ---011 could be “challenging”. An in ---house review to determine the root cause was negative and the event could not be duplicated. The affected solder sleeve was successfully install during a factory test. Going forward operators should install new ModKit 8MK4331 ---003. The ---003 kit replaces the ---001 kit and includes a slightly larger solder sleeve and cable assembly 8Z6619 ---021 in lieu of cable assembly 8Z6619 ---011. All other related parts are unchanged. If an operator has already procured ModKit 8MK4331 ---001 and has not installed the kit, it may be necessary to procure new ModKit 8MK4331 ---051 for successful installation. The new kit (a delta kit) replaces the existing 8Z6619 ---011 cable assembly (p/o the ---001 kit) with cable assemble 8Z6619 ---021 and supplies a slightly larger solder sleeve. No action is required for operators who have successfully installed ModKit 8MK4332 ---001. This service bulletin is revised as follows: --- theDescription,theMaterial --- Price and Availabilityand theMA TERIAL INFORMATIONsections are revised accordingly to convey the above information --- theReferencessection is revised to convey the latest issue of the service bulletin and related engineering documentation--- theACCOMPLISHMENT INSTRUCTIONSare revised to add cable assembly 8Z6619 ---021 as required throughout the procedure.
The Compliance recommendation in the previous issue of this service bulletin is not affected by this revision. No additional rework to the aircraft is introduced by this revision. Remove Service Bulletin 84 ---28 ---04 revision ‘A’ dated 15 Nov 2006 and replace with attached. Previous issues of Service Bulletin 84 ---28 ---04: Initial issue --- Pages 1 thru 28 dated 29 Jun 2006 Revision ‘A’ --- Pages 1 thru 28 dated 15 Nov 2006

# D

S.B. 84 ---28 ---04 Page 1 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 

# SERVICE BULLETIN
Customer Support

ATA SYSTEM: 2840 NUMBER: 84 ---28 ---04 

### 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 and Fuel Indication --- Wiring Identification, Segregation and Installation (High Level Sensor and Fuel Quantity Indication) --- Retrofit --- ModSum 4 ---126366

1. PLANNING INFORMA TION
A. Effectivity Aircraft Affected: In ---Service: DHC ---8 Aircraft Models 401 and 402 Serial Numbers 4003, 4004, 4006 and 4008 thru 4118. Verification: ModSum 4 ---126366 has been installed on DHC ---8 Aircraft Model 402 Serial Number 4006. Production: Equivalent production ModSum 4 ---126333 will be installed before delivery on applicable DHC ---8 Aircraft at Serial Number 4119 and subsequent.

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 2 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 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 ---126366) 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 of the existing high level sensor wiring installation along the rear spar and inside the fuselage, the FQI wiring inside the fuselage and wiring connected to the vent valve position switch has determined that it may not comply with SFAR 88 certification requirements. Solution: This service bulletin conveys ModSum 4 ---126366. The ModSum adds new wiring with protective sleeving, reworks existing wiring, labels and segregates the FQI wiring and hi level sensor wiring from other wiring, enhances the EMI shielding of the wiring connected to the vent valve position switch and installs additional provision for wiring clipping in the center fuselage to improve the mechanical protection of some existing wiring. ModSum 4 ---126366 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 --- flaps are lowered to the 35 degrees position --- all aircraft electrical power is selected to the OFF position

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 3 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 --- electrically grounded work platforms or ladders are set ---up around and/or under the left (and/or right) wing --- center fuselage overwing access panels are opened --- left and right side rear spar access panels are opened --- right side nacelle cowls and fairings are opened --- the refuel/defuel control panel is removed --- right side aft engine exhaust pipe is removed --- sidewall panels, dado panels, overhead baggage bins, seats and floor boards between stations X321.00 and X509.50 are removed (as required) --- new bulkhead brackets B0816026 ---001 are installed to frame at station X469.50 and X509.50 --- wiring identified as ‘EMC2, EMC4 and EMC5’ in the center fuselage is rerouted and clipped to redundant tie mounts as required --- some fuel system wires are removed or taped and stowed (at both ends) or reterminated (one end only) --- five new cable assemblies (c/a’s) are installed and are covered with ident sleeving ModKit 8MK4331 ---001 installs c/a’s p/n 8Z6619 ---011, 8Z6619 ---013, 8Z6619 ---015, 8Z6619 ---017 and 8Z6619 ---019 or ModKit 8MK4331 ---003 installs c/a’s p/n 8Z6619 ---021, 8Z6619 ---013, 8Z6619 ---015, 8Z6619 ---017 and 8Z6619 ---019 --- affected wiring is tested for continuity using an Ohmmeter --- the refuel/defuel control panel is re ---installed --- return to service checks are done --- center fuselage overwing access panels, rear spar access panels, aft nacelle cowls, the engine exhaust (RHS), dado panels, side wall panels, overhead bins, passenger seats, carpets and floor boards are re ---installed D. Compliance Bombardier Inc. highly recommends that ModSum 4 ---126366 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 ---04

S.B. 84 ---28 ---04 Page 4 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 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 All costs to incorporate this modification are the responsibility of the Operator It will take an estimated 263 man ---hours to complete of this Service Bulletin. The breakdown of man ---hours is shown in the table that follows: TASK MAN ---HOURS Job Set ---Up 44.00 Procedure 170.00 Test / RTS 5.00 Close ---Out 44.00 Many man ---hours would be saved if this ModSum 4 ---126366 is accomplished concurrently with service bulletin 84 ---57 ---09 (ModSum 4 ---126330). G. Material --- Price and Availability ModKits 8MK4331 ---001 and 8MK4331 ---051 or 8MK4331 ---003 are 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

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 5 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 Kit Number Description 8MK4331 ---001 Retrofit Kit --- Fuel System --- SFAR 88 --- Wiring Segregation
8MK4331 ---051 Delta Kit for 8MK4331 ---001 (see NOTE 1 below) 8MK4331 ---003 Retrofit Kit --- Fuel System --- SFAR 88 --- Wiring Segregation

NOTE 1: MAY BE HAVE

H. Tooling --- Price and Availability None I. Weight and Balance

A/C Type and Model Weight (Lb) Arm (Inches) Moment (Inches x Lb) x 0.001 DHC ---8 Model 401 +11.46 408.95 +4.69 DHC ---8 Model 402 +11.46 408.95 +4.69

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 6 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 J. Electrical Load Data Not affected K. Publications Affected Maintenance Manual PSM 1 ---84 ---2

................................ Wiring Diagrams Manual PSM 1 ---84 ---2W

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

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

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

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

..................

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 7 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 L. References Revision ‘B’ of this service bulletin was prepared to the engineering drawings and related data that follows: DRAWING SHEET REV 8MK4331 1 B

8Z6624 1

--- 8Z6624 2

--- 8Z6624 3

--- 8Z6619 1 F 8Z6619 2 E 8Z6619 3 B 8Z6619 4 B 8Z6619 5 B 8Z6619 6 B 8Z6619 7 B 8Z6619 8 A 8Z6619 9 B 8Z6619 10 B ModSum 4Q126366 Rev. ‘H’ ModSum 4 ---126366 Rev. ‘H’ ModSum 4Q126452 Rev. ‘A’ ModSum 4 ---126452 Rev. ‘A’ PCA 40933 Revision 1 (for internal reference only)

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 8 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 2. MATERIAL INFORMA TION
A. Parts Required Per Aircraft (1) Modification Kit 8MK4331 ---001 and 8MK4331 ---051 or 8MK4331 ---003 (a) Detailed kit content for 8MK4331 ---001:
Quantity per Kit ---001 Part Number Description Remarks
4 MS35207 ---261 Screws Pan Head 4 M85052/2 ---4 Cushioned Clamp 6 MS21919WDG4 Cushioned Clamp 1 8Z6624 Provisions Fuel Systems DWG 1 8Z6619 Fuel System Wiring DWG 6 B0205016AD4 ---7S Rivet 25 B0205016AD4 ---6S Rivet 30 B0816026 ---001 Bulkhead Bracket

1 8Z6619 ---019 C/A Rear Spar O/B Right Side 1 8Z6619 ---017 C/A Rear Spar O/B Left Side 1 8Z6619 ---015 C/A Rear Spar I/B Left Side 1 8Z6619 ---013 C/A Refuel/Defuel 1 8Z6619 ---011 C/A Center Fuse 1 CSP255 ---2800 ---GS26 Label 1 CSP255 ---2800 ---GS25 Label 2 NAS43DD3 ---52FC Spacer 2 NAS43DD3 ---16FC Spacer 1 NAS1801 ---3 ---22 Screw 2 NAS1801 ---3 ---21 Screw 2 NAS1801 ---3 ---20 Screw 2 NAS1801 ---3 ---10 Screw 1 NAS1801 ---3 ---8 Screw 3 NAS1149F0316P Plain Washer

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 9 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 Quantity per Kit ---001 Remarks Description Part Number
3 NAS1149D0363J Plain Washer 8 NAS1149D0316J Plain Washer 3 MS35650 ---302 Plain Nut 3 MS35338 ---43 Lock Washer 4 MS21919WDG3 Cushion Clamp 8 MS21042L3 Self Locking Nut 20 CSCS ---M Cross Spacer 50 CR4H Connector Ring 150 B0816019 ---003 Strap Tie Down (b) Detailed kit content for 8MK4331 ---051: (The ---051 kit that follows is a delta kit for 8MK4431 ---001. Ref to NOTE 1 in theMaterial --- Price and Availabilitysection for explanation).
Quantity per Kit ---051 Part Number Description Remarks
1 8Z6619 ---021 C/A Center Fuse 1 8Z6619 Fuel System Wiring DWG (c) Detailed kit content for 8MK4331 ---003:
Quantity per Kit ---003 Part Number Description Remarks
4 MS35207 ---261 Screws Pan Head 4 M85052/2 ---4 Cushioned Clamp 6 MS21919WDG4 Cushioned Clamp 1 8Z6624 Provisions Fuel Systems DWG 1 8Z6619 Fuel System Wiring DWG 6 B0205016AD4 ---7S Rivet 25 B0205016AD4 ---6S Rivet 30 B0816026 ---001 Bulkhead Bracket

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 10 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 Quantity per Kit ---003 Remarks Description Part Number
1 8Z6619 ---019 C/A Rear Spar O/B Right Side 1 8Z6619 ---017 C/A Rear Spar O/B Left Side 1 8Z6619 ---015 C/A Rear Spar I/B Left Side 1 8Z6619 ---013 C/A Refuel/Defuel 1 8Z6619 ---021 C/A Center Fuse 1 CSP255 ---2800 ---GS26 Label 1 CSP255 ---2800 ---GS25 Label 2 NAS43DD3 ---52FC Spacer 2 NAS43DD3 ---16FC Spacer 1 NAS1801 ---3 ---22 Screw 2 NAS1801 ---3 ---21 Screw 2 NAS1801 ---3 ---20 Screw 2 NAS1801 ---3 ---10 Screw 1 NAS1801 ---3 ---8 Screw 3 NAS1149F0316P Plain Washer 3 NAS1149D0363J Plain Washer 8 NAS1149D0316J Plain Washer 3 MS35650 ---302 Plain Nut 3 MS35338 ---43 Lock Washer 4 MS21919WDG3 Cushion Clamp 8 MS21042L3 Self Locking Nut 20 CSCS ---M Cross Spacer 50 CR4H Connector Ring 150 B0816019 ---003 Strap Tie Down (2) In addition to the above part(s), the following material(s) 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 either Maintenance Manual Chapter 20 or in Structural Repair Manual Chapter 51 or, for 400 Series Aircraft, in Consumable Products Manual PSM 1 ---84 ---18.

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 11 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 Part Number Qty. Per Aircraft Description Remarks CS7707 As Required 07 ---58 --- Coating, Nylon Epoxy B0207017C4 ---3 6 Rivet Alternate p/n CCR244CS ---4 ---3 B. Parts Required to Modify Spares None C. Special Tools and Equipment Required None D. Existing Parts Accountability None

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 12 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 3. ACCOMPLISHMENTINSTRUCTIONS 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) Lower the wing flaps to the 35 degrees position as follows: WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE MOVEMENT OF FLIGHT CONTROL SURFACES. MOVEMENT OF THE FLIGHT CONTROL SURFACES CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO THE EQUIPMENT. (a) Pressurize the No. 1 hydraulic system (Refer to PSM 1 ---84 ---2 TASK 29 ---00 ---00 ---863 ---801). (b) Have a person give you visual clearance to extend the flaps. (c) Set the flap selector to 35 degrees to lower the wing flaps. (d) Remove the pressure from the No. 1 hydraulic system (Refer to AMM 29 ---00 ---00 ---863 ---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. (5) Set up the work platforms and/or ladders to permit access to the rear spar (left and right side). Make sure that the work platforms or ladders are electrically grounded. (6) Gain access to the wiring located along the left and right wing rear spar, the overcenter fuselage and right side nacelle as follows: (a) Remove the center fuselage overwing access panels that follow (refer to PSM 1 ---84 ---2 TASK 06 ---41 ---00 ---992 ---803): ACCESS DESIGNATION

262AT Access Panel Center Wing 262BT Access Panel Center Wing 262HT Access Panel Center Wing 262JT Access Panel Center Wing 262CT Access Panel Center Wing 262KT Access Panel Center Wing

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 13 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 (b) Remove the L/H and R/H rear spar access panels that follow. Refer to PSM 1 ---84 ---2 TASK’s 06 ---41 ---00 ---992 ---808 and 06 ---41 ---00 ---992 ---809 for component location. Refer to TASK’s 57 ---51 ---01 ---000 ---801 and 57 ---51 ---06 ---000 ---801 for removal instructions. ACCESS DESIGNATION

531AB Closure Panel 631AB Closure Panel 532AB Closure Panel 532BB Closure Panel 532DB Closure Panel 532FB Closure Panel 632AB Closure Panel 632BB Closure Panel 632DB Closure Panel 632FB Closure Panel (c) Remove the cowls and fairing from the R/H nacelle that follow (refer to PSM 1 ---84 ---2 TASK 54 ---32 ---00 ---992 ---801): ACCESS DESIGNATION 424AL, 424AR Aft Upper Cowl 424BB Boat ---tail Fairing 424AT Upper Mid Aft ---Cowl (d) Remove the refuel/defuel control panel (refer to PSM 1 ---84 ---2 TASK 28 ---24 ---01 ---000 ---801). (e) Remove R/H aft engine exhaust (refer to PSM 1 ---84 ---2 TASK 78 ---10 ---01 ---000 ---801). (7) Gain access to the center fuselage rework areas as follows: (a) Remove overhead bins (both sides) located between stations X361.50 and X529.50 (refer to applicable instructions in PSM 1 ---84 ---2 TASK 25 ---23 ---01 ---000 ---801). (b) Remove passenger seats (both sides), carpets and floor boards located between stations X321.00 and X509.50 (refer to the applicable instructions in PSM 1 ---84 ---2 TASK 53 ---33 ---01 ---000 ---801).

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 14 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 (c) Remove L/H and R/H side wall panels between stations X321.00 and X509.50 (refer to the applicable instructions in PSM 1 ---84 ---2 TASK 25 ---26 ---01 ---000 ---801). (d) Remove L/H and R/H dado panels between stations X321.00 and X509.50 (refer to the applicable instructions in PSM 1 ---84 ---2 TASK 25 ---26 ---06 ---000 ---801). B. Procedure (1) Install new bulkhead brackets B0816026 ---001 to frame at station X469.50 and X509.50 as follows: NOTE: Installation of bulkhead brackets B0816026 ---001 will provide clipping provisions for a new SFAR 88 harness in the center fuselage. NOTE: The steps that follow give the instructions to install a typical bulkhead bracket B0816026 ---001 to the related frame. (a) Refer to locator view on drawing 8Z6624 sheet 1 and detail views on sheets 2 and 3 to determine the position of each new bulkhead bracket on affected frame at station X469.50 and X509.50. (b) In the center fuselage remove or detach insulation as required to gain access to affected frame at station X469.50 and X509.50. (c) Temporally hold new bulkhead bracket in position against the frame. Using the pilot hole in the bracket as a guide make a match mark onto the frame. (d) Remove bulkhead bracket then makea hole thru the match mark on frame to final size using a #30 drill (0.128 inch). (e) Deburr the new holes thru frames. (f) Treat bared metal using alodine 1200, 1200S or 1201 and prime using epoxy chromate primer. NOTE: If additional access is required loosen or remove adjacent sidewall rail and/or dado panel rail as required to install any bulkhead bracket to stringer. (g) Attach each new bulkhead bracket to affected frame using rivets B0205016AD ---6S or B0205016AD ---7S (as required per installation) to agree with all of the notes and detail views given on drawing 8Z6624 sheets 1, 2 and 3. (h) Clean up all unwanted materials from the rework area.

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 15 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 (i) Install or reattach the insulation, sidewall and/or dado panel rail that were removed to do the above procedure. (2) Refer to drawing 8Z6619 sheet 3 and identify the location/routing of the wiring bundles (wiring) identified as ‘EMC2, EMC4 and EMC5’. (3) In the center fuselage reroute the wiring identified as ‘EMC2, EMC4 and EMC5’ as follows: (a) In the left side wiring trough locate existing EMC5 wiring. (b) Open any clips (keep all hardware) and/or cut away tie wraps that are used to secure EMC5 wiring. (c) Reroute EMC5 wiring in the wiring trough to accommodate the new W22 (c/a ---011 or ---021) run to agree with the detail views and notes given on drawing 8Z6619 sheet 3 and Section views H ---H and L ---L. (d) Starting at the forward leftwing root electrical disconnect, reroute existing EMC2 wiring with EMC4 wiring to agree with the detail views and notes given on drawing 8Z6619 sheet 3. Open any clips (keep all hardware) and/or cut away tie wraps as required. Use redundant tie mounts as required. (e) Starting at the forward rightwing root electrical disconnect, reroute existing EMC4 wiring with EMC2 wiring to agree with the detail views and notes given on drawing 8Z6619 sheet 3. Open any clips (keep all hardware) and/or cut away tie wraps as required. Use redundant tie mounts as required. (f) Secure EMC2, EMC4 and EMC5 wiring using tie wraps as required. (4) Remove and discard the wires that follow (refer to Table 1 and the views and notes given on drawing 8Z6619 sheets 2, 3, 4, 5, 6 7, and Figures 1 and 4). If required it is also acceptable to tape and stow both ends of the affected wires.

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 16 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 Table 1

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 17 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 Table 1 Continued

(5) Tape and stow the wires that follow (one end only) --- Post ModSum 4 ---126285 (refer to Table 2 and the views and notes given on drawing 8Z6619 sheet 2, 3, 5, 6, 7 and Figures 1 and 3). Table 2

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 18 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 (6) Tape and stow the wires that follow (one end only) --- Pre ModSum 4 ---126285 (refer to Table 3 and the views and notes given on drawing 8Z6619 sheet 2 and Figures 1 and 3). Table 3

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 19 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 (7) Reterminate the wires that follow (one end only) (refer to Table 4 and the views and notes given on drawing 8Z6619 sheet 2 and Figure 2 and Figures 1 and 3). Table 4

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 20 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 (8) Install cable assembly 8Z6619 ---011 (if installing ---001 kit) or 8Z6619 ---021 (if installing ---003 kit) using the instruction that follow: (a) Add the new wires that follow, refer to Table 5 and the views and notes given on drawing 8Z6619 sheets 2 thru 7 and Figures 1 and 4 (refer to PSM 1 ---84 ---2W TASK 20 ---15 ---10 ---401). NOTE 1: MAY BE HAVE

(b) Wrap fuel indent sleeving over cable assembly on all waycode W22 and W23 wires, (refer to views and notes given on drawing 8Z6619 sheet 2 and Figures 1 and 4). (c) Secure each end of the fuel indent sleeving under the backshell clamps.

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 21 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 Table 5

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 22 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 Table 5 Continued

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 23 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 (9) Install cable assembly 8Z6619 ---013 using the instructions that follow: (a) In the forward section of the refuel defuel panel locate electrical connector 2811 ---J1 and related mounting bracket (refer to 8Z6619 sheet 10 VIEW ON ARROW T). (b) Detach the electrical connector from the mounting bracket. If the electrical connector is difficult to detach or additional work space is required remove the six rivets that secure the mounting bracket to structure and remove the connector and bracket as an assembly. (c) Add the new wires that follow, refer to Table 6 and the views and notes given on drawing 8Z6619 sheets 2, 9, 10 and Figures 1 and 2 (refer to PSM 1 ---84 ---2W TASK 20 ---15 ---10 ---401). (d) Install fuel indent sleeving on all waycode W22 and W23 wires, refer to views and notes given on drawing 8Z6619 sheet 2 and Figures 1 and 2. (e) Make sure that fuel indent sleeving extends under the connector backshell clamps. (f) Reinstall mounting bracket and attached connector 2811 ---J1 to original position using six rivets B0207017C4 ---3 (alternate p/n CCR244CS ---4 ---3). Table 6

(10) Install cable assembly 8Z6619 ---015 using the instructions that follow: (a) Add the new wires that follow, refer to Table 7 and the views and notes given on drawing 8Z6619 sheets 2, 8, 10 and Figures 1 and 2 (Refer to PSM 1 ---84 ---2W TASK 20 ---15 ---10 ---401). (b) Install fuel indent sleeving on all waycode W22 and W23 wires, refer to views and notes given on drawing 8Z6619 sheet 2 and Figures 1 and 2. (c) Secure each end of the fuel indent sleeving under the backshell clamps.

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 24 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 Table 7

(11) Install cable assembly 8Z6619 ---017 using the instructions that follow: (a) Add the new wires that follow, refer to Table 8 and the views and notes given on drawing 8Z6619 sheets 2, 10 and Figures 1 and 2 (refer to PSM 1 ---84 ---2W TASK 20 ---15 ---10 ---401). (b) Install fuel indent sleeving on all waycode W22 and W23 wires , refer to views and notes given on drawing 8Z6619 sheet 2 and Figures 1 and 2. (c) Secure each end the fuel indent sleeving under the backshell clamps. (d) Install label CSP255 ---2800 ---GS25 adjacent ground stud, refer to 8Z6619 sheet 10 SECTION V ---V. NOTE: Make sure cable assembly is grounded to GS25.
Table 8

(12) Install cable assembly 8Z6619 ---019 using the instructions that follow: (a) Add the new wires that follow, refer to Table 9 and the views and notes given on drawing 8Z6619 sheets 2, 10 and Figures 1 and 2 (Refer to PSM 1 ---84 ---2W TASK 20 ---15 ---10 ---401). (b) Install fuel indent sleeving on all waycode W22 and W23 wires, refer to views and notes given on drawing 8Z6619 sheet 2 and Figures 1 and 2. (c) Secure each end of the fuel indent sleeving under the backshell clamps. (d) Install label CSP255 ---2800 ---GS26 adjacent ground stud Refer to 8Z6619 sheet 10 SECTION V ---V.

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 25 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 NOTE: Make sure cable assembly is grounded to GS26.
Table 9

(13) Do a continuity check with a Ohmmeter to verify compliance with the wiring diagram shown on Tables 1 thru 9. (14) Install the refuel/defuel control panel (refer to PSM 1 ---84 ---2 TASK 28 ---24 ---01 ---400 ---801). (15) Do the return to service checks that follow (refer to PSM 1 ---84 ---2): (a) Operational test of the AC variable frequency generation system (refer to PSM 1 ---84 ---2 TASK 24 ---21 ---00 ---710 ---801). (b) Operational test of the external AC power system (refer to PSM 1 ---84 ---2 TASK 24 ---41 ---00 ---710 ---801). C. Close Out (1) Install the center fuselage overwing access panels that follow (refer to PSM 1 ---84 ---2 TASK 06 ---41 ---00 ---992 ---803): ACCESS DESIGNATION

262AT Access Panel Center Wing 262BT Access Panel Center Wing 262HT Access Panel Center Wing 262JT Access Panel Center Wing 262CT Access Panel Center Wing 262KT Access Panel Center Wing

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 26 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 (2) Install the L/H and R/H rear spar access panels that follow (refer to PSM 1 ---84 ---2 TASK’s 06 ---41 ---00 ---992 ---808 and 06 ---41 ---00 ---992 ---809): ACCESS DESIGNATION

531AB Closure Panel 532AB Closure Panel 532BB Closure Panel 532DB Closure Panel 532FB Closure Panel 631AB Closure Panel 632AB Closure Panel 632BB Closure Panel 632DB Closure Panel 632FB Closure Panel (3) Install the R/H aft nacelle cowl that follows (refer to PSM 1 ---84 ---2 TASK 06 ---41 ---00 ---992 ---807): ACCESS DESIGNATION 424AL, 424AR Aft Upper Cowl 424BB Boat ---tail Fairing 424AT Upper Mid Aft ---Cowl (4) Install R/H aft engine exhaust (refer to PSM 1 ---84 ---2 TASK 78 ---10 ---01 ---400 ---801). (5) Install L/H and R/H dado panels between stations X321.00 and X509.50 (refer to PSM 1 ---84 ---2 TASK 25 ---26 ---00 ---400 ---801). (6) Install L/H and R/H side wall panels between stations X321.00 and X529.50 (refer to PSM 1 ---84 ---2 TASK 25 ---26 ---01 ---400 ---801). (7) Install overhead bins (both sides) located between stations X361.50 and X509.50 (refer to applicable instructions in PSM 1 ---84 ---2 TASK 25 ---23 ---01 ---400 ---801). (8) Install passenger seats (both sides), carpets and floor boards located between stations X321.0 and X509.50 (refer to the applicable instructions in PSM 1 ---84 ---2 TASK 53 ---23 ---01 ---400 ---801). (9) Remove all tools and equipment from the work area.

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 27 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 (10) On incorporation of this ModSum/Modification, add the weight and balance data shown in Section I of this service bulletin to the Weight and Balance Manual PSM 1 ---84 ---8. Under ‘Description of Change’ enter “ModSum 4 ---126366 incorporated.” (11) On incorporation of this ModSum make an entry that conforms to local regulatory requirements in the applicable logbook(s). If only part of this ModSum is completed, use only this service bulletin number as reference and detail exact limit of work completed. Enter component serial numbers if applicable. Enter this ModSum number only after complete and functional incorporation of all work defined in this service bulletin.

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 28 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 1. UNLESS OTHERWISE SPECIFIED ALL WIRE CODES AND REF DESIGNATIONS ARE PREFIXED 2800 ---. 2. UNLESS OTHERWISE SPECIFIED ALL WAYCODES ARE W7. 3. CONNECTOR PIN IDENTS SUFFIXED BY ( --- ) DENOTE LOWER CASE LETTERS. 4. SHIELD TERMINATION TO BE WITHIN 2.0 INCHES E7/E8. 5 LENGTH 3 INCHES MAXIMUM. 6. TAPE AND STOW EXISTING WIRES. INSTALL NEW WIRES IN SEPARATED RUNS WRAPPED IN FUEL IDENT SLEEVING (S8021). 7. WRAP EXISTING WIRES WITH FUEL IDENT SLEEVING (S8021). 8. FOR AIRCRAFT PRE ---MODSUM 4Q109534, RE ---IDENTIFY SPLICES E3 / E4 AS E7 / E8 ACCORDINGLY. 17. DISENGAGE AND DE ---PIN CONNECTOR 2800 ---P/J715. REMOVE BACKSHELL 3CSR0AB4014S AND REPLACE WITH 3CGA00AB4014S. RE ---PIN CONNECTOR BACK TO ORIGINAL STATE AND RECONNECT ‘P’ AND ‘J’ SIDES. TERMINATE SHIELD PER PSM 1 ---84 ---2W TASK 20 ---15 ---10 ---401. 18. FOR INSTALLATION EASEMENT WHEN ADDING FUEL IDENT SLEEVING (P/N S8021) ON EXISTING WIRES, START AT EITHER END OF CABLE ASSEMBLY. FIND WIRE CODES TO BE SLEEVED PER WIRING DIAGRAM IN FIGURES 2 AND 3. ADD SLEEVE TOWARDS THE OTHER END OF CABLE ASSEMBLY REFER TO NOTE 6 FOR OTHER INSTRUCTIONS. NOTE THAT ‘W’ CODE IS PART OF THE WIRE IDENT.

Figure 1

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 29 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 Figure 2NOTE: Terminate shields to backshellrefer to PSM 1 ---814 ---2WTASK 20 ---15 ---10 ---401.88OR

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 30 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 Figure 3NOTE: Terminate shields to backshellrefer to PSM 1 ---814 ---2WTASK 20 ---15 ---10 ---401.

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 31 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 NOTE: Terminate shields to backshell refer to PSM 1 ---814 ---2W TASK 20 ---15 ---10 ---401.

Figure 4 OR

### SERVICE BULLETIN 84 ---28 ---04

S.B. 84 ---28 ---04 Page 32 of 32 29 Jun 2006 L.S Revision ‘B’ 21 Oct 2009 

### This Page Intentionally Blank 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 VCompliance VApproval V Manpower V Material VWeight and Balance V Electrical Load VTooling V References V Publications Affected 2. MATERIAL INFORMATION V Kit Content VSpecial Tools/Equipment V Parts to Modify Spares VConsumables V Disposition of Existing Parts VOther
3. ACCOMPLISHMENT INSTRUCTIONS VJob Set ---Up V Procedure VClose---Out VTest V Illustration(s) VOther 4. COMMENTS, REMARKS, SUGGESTIONS



## Fax this sheet to (1) 416 375 4538 or Email PDF to: syed.rizvi@aero.bombardier.com