Revision ‘B’ 03 Feb 2015 DHC ---8 (DASH 8) SERVICE BULLETIN 84 ---32 ---114 Landing Gear --- Retrofit --- Redress Gear Harness Routing to Address Interference with Stabilizer Brace --- ModSum 4 ---126562 This page transmits Revision ‘B’ of Service Bulletin 84 ---32 ---114, pages 1 thru 22 dated 03 Feb 2015. This service bulletin is re ---issued in its entirety for the reasons that follow: --- theDescriptionsection is revised to add additional information --- theCompliancesection is revised to add Airworthiness Directive number --- the Material Price and Availability section is revised to add kits 8MK4615 ---006/ ---007/ ---009/ ---051 and a Note --- theReferencessection is revised to convey the latest revision of this service bulletin and related engineering documentation --- theParts Required Per Aircraftsection is revised to add additional parts to kit 8MK4615 ---001, add kits 8MK4615 ---006/ ---007/ ---009/ ---051 --- theACCOMPLISHMENT INSTRUCTIONSsection is revised to add additional steps and Notes --- steps (1) (f) & (g) in theProceduresection are revised to show correct Views --- step (2) (g) in theProceduresection is revised to show the correct flagnote The Compliance in the previous issue of this service bulletin is not affected by this revision. Additional rework to the aircraft is introduced by this revision.Remove the previous issue of Service Bulletin 84 ---32 ---114 and replace with attached. Previous issue(s) of Service Bulletin 84 ---32 ---114: Initial issue --- Pages 1 thru 22 dated 06 Jun 2013 Revision ‘A’ --- Pages 1 thru 22 dated 18 Sep 2013

# D

S.B. 84 ---32 ---114 Page 1 of 22 06 Jun 2013 JR Revision ‘B’ 03 Feb 2015 

# SERVICE BULLETIN Customer Support
ATA SYSTEM: 3211 NUMBER: 84 ---32 ---114 

### BOMBARDIER AEROSPACE REGIONAL AIRCRAFT CONSIDER THIS SERVICE BULLETIN TO BE PARTICULARLY SIGNIFICANT AND URGE OPERATORS TO PROMPTLY EVALUATE THE CONTENTS

SUBJECT: Landing Gear --- Retrofit --- Redress Gear Harness Routing to Address Interference with Stabilizer Brace --- ModSum 4 ---126562

1. PLANNING INFORMA TION A. Effectivity Aircraft Affected: In ---Service: DHC ---8 Aircraft Models 401 and 402 Serial Numbers 4001, 4003 thru 4411. NOTE: If ModSum IS4Q2400028 was previously accomplished on aircraft Serial Numbers 4001 and 4003 thru 4089, no further action is required. NOTE: If ModSum IS4Q2400029 was previously accomplished on aircraft Serial Numbers 4090 thru 4411, no further action is required. Production: ModSum 4 ---123798 will be installed before delivery on applicable DHC ---8 Aircraft at Serial Numbers 4412 thru 4452. ModSum 4 ---126562 will be installed before delivery on applicable DHC ---8 Aircraft at Serial Numbers 4453 and subsequent.

### SERVICE BULLETIN 84 ---32 ---114

S.B. 84 ---32 ---114 Page 2 of 22 06 Jun 2013 JR Revision ‘B’ 03 Feb 2015 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: The clearance between the MLG stabilizer brace and the nacelle A ---Frame can be insufficient for some harness routings. With the insufficient clearance, there is a potential interference between the MLG stabilizer brace, electrical harness and nacelle A ---Frame possibly causing damage to all three components. Solution: This service bulletin introduces ModSum 4 ---126562. The ModSum redresses the MLG electrical harness to improve the clearance between the MLG electrical harness, stabilizer brace and nacelle A ---Frame. C. Description The procedures in this service bulletin give the instructions to do the tasks that follow: --- nose landing gear lock is engaged --- main landing gear lock pins are installed thru each main gear and main gear door mechanism --- pressure in the No. 1, 2 & 3 hydraulic systems are depleted --- all aircraft electrical power systems are selected to OFF --- aircraft is lifted on jacks --- LH and RH MLG stabilizer struts are removed as required for access --- LH and RH MLG forward doors are removed --- work platforms or ladders are set up and properly grounded --- LH and RH MLG electrical harness are reworked per drawings 8Z9552 and 8Z9553

### SERVICE BULLETIN 84 ---32 ---114

S.B. 84 ---32 ---114 Page 3 of 22 06 Jun 2013 JR Revision ‘B’ 03 Feb 2015 --- clearance between the stabilizer brace and electrical harnesses on both LH and RH nacelles is measured --- LH and RH nacelle A ---Frames and MLG stabilizer braces are checked for signs of chafing --- LH and RH MLG forward doors are installed --- operational test of the landing gear primary extension and retraction system is done --- close out. D. Compliance Bombardier Inc. highly recommends that ModSum 4 ---126562 be incorporated at the earliest opportunity unless otherwise directed by the operator’s airworthiness authority. Transport Canada Airworthiness Directive CF ---2014 ---45. ModSum IS4Q2400028 or IS4Q2400029 is equivalent to ModSum 4 ---126562. There is no need to incorporate ModSum 4 ---126562 if ModSums IS4Q2400028 or IS4Q2400029 has already been incorporated. 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. This service bulletin does not affect Airworthiness Limitations (AWLs) or Damage Tolerance Inspections (DTIs).

### SERVICE BULLETIN 84 ---32 ---114

S.B. 84 ---32 ---114 Page 4 of 22 06 Jun 2013 JR Revision ‘B’ 03 Feb 2015 F. Manpower It will take an estimated 12 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 0.50 Procedure 10.00 Test / RTS 1.00 Close ---Out 0.50 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. G. Material --- Price and Availability The ModKits required to do this service bulletin are listed in the table below: Operators should submit a purchase order through the Customer Accounts Service Team (CAST) at Bombardier Aerospace Regional Aircraft division 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 Facsimile: International: (416) 375 ---3334 European: (416) 373 ---5966 Americas East: (416) 373 ---5964 Americas West: (416) 373 ---5965 Telephone:

### SERVICE BULLETIN 84 ---32 ---114

S.B. 84 ---32 ---114 Page 5 of 22 06 Jun 2013 JR Revision ‘B’ 03 Feb 2015 International: (416) 375 ---3706 European: (416) 373 ---3704 Americas East: (416) 375 ---3700 Americas West: (416) 373 ---5888 E ---mail addresses: International: cast.international@aero.bombardier.com European: cast.europe@aero.bombardier.com Americas East: cast.americaseast@aero.bombardier.com Americas West: cast.americaswest@aero.bombardier.com

Kit Number Description 8MK4615 ---001 Kit --- Rework --- Elec Conduit Assembly, L/G Harness, LH Nacelle --- See NOTE 1 8MK4615 ---002 Kit --- Rework --- Elec Conduit Assembly, L/G Harness, RH Nacelle --- See NOTE 2 8MK4615 ---003 Kit --- Rework --- Elec Conduit Assembly, L/G Harness, LH Nacelle --- See NOTE 3 8MK4615 ---004 Kit --- Rework --- Elec Conduit Assembly, L/G Harness, RH Nacelle --- See NOTE 4 8MK4615 ---005 Kit --- Rework --- Elec Conduit Assembly, L/G Harness, LH Nacelle --- See NOTE 4 8MK4615 ---006 Kit --- Rework --- Elec Conduit Assembly, L/G Harness, RH Nacelle --- See NOTE 4 8MK4615 ---007 Kit --- Rework --- Elec Conduit Assembly, L/G Harness, LH Nacelle --- See NOTE 4 8MK4615 ---009 Kit --- Rework --- Elec Conduit Assembly, L/G Harness, LH Nacelle --- See NOTE 3 8MK4615 ---051 Delta Kit --- See NOTE 5 NOTE 1: Applicable to aircraft serial numbers 4001 thru 4027. NOTE 2: Applicable to aircraft serial numbers 4001 thru 4089. NOTE 3: Applicable to aircraft serial numbers 4028 thru 4089.

### SERVICE BULLETIN 84 ---32 ---114

S.B. 84 ---32 ---114 Page 6 of 22 06 Jun 2013 JR Revision ‘B’ 03 Feb 2015 NOTE 4: Applicable to aircraft serial numbers 4090 thru 4411. NOTE 5: For any unconsumed 8MK4615 ---003/ ---004/ ---005 kits, operators only need to order delta kit 8MK4615 ---051. H. Tooling --- Price and Availability None I. Weight and Balance Not affected J. Electrical Load Data Not affected K. Publications Affected Dash 8 Illustrated Parts Catalogue PSM 1 ---84 ---4

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

............................ 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:
DRAWING SHEET REV 8MK4615 1 E

8Z9552 1 E 8Z9552 2 D 8Z9552 3 C 8Z9553 1 E 8Z9553 2 D 8Z9553 3 B 8Z9553 4 B ModSum 4Q126562 Rev. ‘F’

### SERVICE BULLETIN 84 ---32 ---114

S.B. 84 ---32 ---114 Page 7 of 22 06 Jun 2013 JR Revision ‘B’ 03 Feb 2015 ModSum 4 ---126562 Rev. ‘F’ ModSum 4Y123798 Rev. ‘B’ ModSum 4 ---123798 Rev. ‘B’ ModSum IS4Q2400028 Rev. ‘B’ ModSum IS4Q2400029 Rev. ‘A’ PCA 44059 Revision 1 (for internal reference only) Transport Canada Airworthiness Directive CF ---2014 ---45 2. MATERIAL INFORMA TION
A. Parts Required Per Aircraft (1) Modification Kit 8MK4615 ---001, for aircraft serial numbers 4001 thru 4027. Modification Kit 8MK4615 ---002, for aircraft serial numbers 4001 thru 4089. (2) Detailed Kit Content: Quantity Per Kit ---002 ---001 Part Number Description Remarks

2 B0816035AA3N750 Tie Mount 5 B0816019 ---001 Strap Tie Down 1 8Z9553 Rework ---Ldg Gear Harness LH Nacelle Drawing Only 1 8Z9552 Rework ---Ldg Gear Harness RH Nacelle Drawing Only
4 4 TR04AI Tinel ---Lock Ring See NOTE 1 6 ft. 6 ft. MIL ---I ---19166 Fibreglass Tape 4 4 202A121 ---3/42 Boot HT Shrink See NOTE 1 1 1 B0204046CRA3 ---20 Clickbond Standoff See NOTE 2 1 CSP255 ---8Z9553 ---051 Label 1 CSP255 ---8Z9552 ---051 Label 1 1 MS21919WDE12 Clamp 6 ft 6 ft 3C ---CML ---1NSNJ ---0006 Conduit See NOTE 1 1 1 B0816035CR3TT Cable Tie Mount

### SERVICE BULLETIN 84 ---32 ---114

S.B. 84 ---32 ---114 Page 8 of 22 06 Jun 2013 JR Revision ‘B’ 03 Feb 2015 Quantity Per Kit ---002 ---001 Remarks Description Part Number
8 8 M39029/56 ---351 Pin, Contact 6 5 B0816035CR3T Cable Tie Mount See NOTE 3 6 ft. 6 ft. DSC230 ---7HT Spiral Wrap 1 ft. 1 ft. MS21266 ---2N Grommet Edging 1 1 MS21919WDE10 Clamp 1 1 NAS1801 ---3 ---10 Screw 1 1 NAS1801 ---3 ---16 Screw 6 1 B0816038 ---002 Connector Ring 13 12 B0816019 ---003 Tie Strap
NOTE 1: If required. Replace the conduit assembly with these parts. NOTE 2: Acceptable to use substitute part CB3001CRA3 ---20. NOTE 3: Acceptable to use substitute part CB3019CR3T, CSP458 ---1 or B0816033 ---002.

### SERVICE BULLETIN 84 ---32 ---114

S.B. 84 ---32 ---114 Page 9 of 22 06 Jun 2013 JR Revision ‘B’ 03 Feb 2015 (3) Modification Kit 8MK4615 ---003, for aircraft serial numbers 4028 thru 4089. Modification Kit 8MK4615 ---004, for aircraft serial numbers 4090 thru 4411. Modification Kit 8MK4615 ---005, for aircraft serial numbers 4090 thru 4411. (4) Detailed Kit Content: Quantity Per Kit ---005 ---004 ---003 Part Number Description Remarks

1 1 8Z9553 Rework ---Ldg Gear Harness LH Nacelle Drawing Only 1 8Z9552 Rework ---Ldg Gear Harness RH Nacelle Drawing Only
444 TR04AI Tinel ---Lock Ring See NOTE 1 6 ft. 6 ft 6 ft. MIL ---I ---19166 Fibreglass Tape 444 202A121 ---3/42 Boot HT Shrink See NOTE 1 1 B0204046CRA3 ---20 Clickbond Standoff See NOTE 2 1 1 CSP255 ---8Z9553 ---051 Label 1 CSP255 ---8Z9552 ---051 Label 6 ft. 6 ft. 6 ft. 3C ---CML ---1NSNJ ---0006 Conduit See NOTE 1 111 B0816035CR3TT Cable Tie Mount 888 M39029/56 ---351 Pin, Contact 4 1 B0816035CR3T Cable Tie Mount See NOTE 3 6 ft. 6 ft. 6 ft. DSC230 ---7HT Spiral Wrap 1 ft. 1 ft. 1 ft. MS21266 ---2N Grommet Edging 111 MS21919WDE10 Clamp 222 MS21919WDE7 Clamp 111 NAS1801 ---3 ---20 Screw 111 NAS43DD3 ---40FC Spacer 122 B0816038 ---002 Connector Ring 444 B0305091 ---5 Clamp 7 15 7 B0816019 ---003 Tie Strap 444 CSP458 ---1 Tie Mount NOTE 1: These parts are required if the conduit assembly is replaced. NOTE 2: Acceptable to use substitute part CB3001CRA3 ---20. NOTE 3: Acceptable to use substitute part CB3019CR3T, CSP458 ---1 or B0816033 ---002.

### SERVICE BULLETIN 84 ---32 ---114

S.B. 84 ---32 ---114 Page 10 of 22 06 Jun 2013 JR Revision ‘B’ 03 Feb 2015 (5) Modification Kit 8MK4615 ---006, for aircraft serial numbers 4090 thru 4411. Modification Kit 8MK4615 ---007, for aircraft serial numbers 4090 thru 4411. Modification Kit 8MK4615 ---009, for aircraft serial numbers 4028 thru 4089. (6) Detailed Kit Content:
Quantity Per Kit ---009 ---007 ---006 Part Number Description Remarks
2 B0816035AA3N750 Tie Mount 5 B0816019 ---001 Strap Tie Down 111 B0305091 ---9 Clamp 333 B0305091 ---6 Clamp 1 1 8Z9553 Rework ---Ldg Gear Harness LH Nacelle Drawing Only 1 8Z9552 Rework ---Ldg Gear Harness RH Nacelle Drawing Only
444 TR04AI Tinel ---Lock Ring See NOTE 1 6 ft. 6 ft 6 ft. MIL ---I ---19166 Fibreglass Tape 444 202A121 ---3/42 Boot HT Shrink See NOTE 1 1 B0204046CRA3 ---20 Clickbond Standoff See NOTE 2 1 1 CSP255 ---8Z9553 ---051 Label 1 CSP255 ---8Z9552 ---051 Label 6 ft. 6 ft. 3C ---CML ---1NSNJ ---0006 Conduit See NOTE 1 111 B0816035CR3TT Cable Tie Mount 888 M39029/56 ---351 Pin, Contact 4 1 B0816035CR3T Cable Tie Mount See NOTE 3 6 ft. DSC230 ---7HT Spiral Wrap 1 ft. MS21266 ---2N Grommet Edging 111 MS21919WDE10 Clamp 222 MS21919WDE7 Clamp 111 NAS1801 ---3 ---20 Screw 111 NAS43DD3 ---40FC Spacer 212 B0816038 ---002 Connector Ring 7 7 15 B0816019 ---003 Tie Strap 444 CSP458 ---1 Tie Mount

NOTE 1: These parts are required if the conduit assembly is replaced.

### SERVICE BULLETIN 84 ---32 ---114

S.B. 84 ---32 ---114 Page 11 of 22 06 Jun 2013 JR Revision ‘B’ 03 Feb 2015 NOTE 2: Acceptable to use substitute part CB3001CRA3 ---20. NOTE 3: Acceptable to use substitute part CB3019CR3T, CSP458 ---1 or B0816033 ---002. (7) Modification Kit 8MK4615 ---051, for any unconsumed 8MK4615 ---003/ ---004/ ---005 kits. (8) Detailed Kit Content: Quantity Per Kit ---051 Part Number Description Remarks

1 B0305091 ---9 Clamp 3 B0305091 ---6 Clamp (9) 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 (CPM) PSM 1 ---84 ---18.
Product ID No. Qty. Per Aircraft Description Specifications* 05 ---03 As Required Adhesive, Modified Epoxy DHMS A6.12 DOD ---A ---82720 06 ---01 As Required Sealant, Temperature Resistant DHMS S3.01 SAE AMS ---S8802A ASTMD412 BMS 3 ---11G MIL ---STD ---1916 *NOTE: Refer to CPM PSM 1 ---84 ---18 for the list of approved alternative consumable products under each Product Id No., any of which can be used unless a note states otherwise.

### SERVICE BULLETIN 84 ---32 ---114

S.B. 84 ---32 ---114 Page 12 of 22 06 Jun 2013 JR Revision ‘B’ 03 Feb 2015 B. Parts Required to Modify Spares None C. Special Tools and Equipment Required None D. Existing Parts Accountability None 3. ACCOMPLISHMENTINSTRUCTIONS A. Job Set ---Up (1) Make sure the nose gear ground lock is engaged. (2) Make sure that lock pins are installed through each main gear and main gear door mechanism. (3) Set wheel chocks in front and behind the landing gear tires. (4) Deplete hydraulic pressure in the No. 1, 2 & 3 systems (refer to AMM TASKs 29 ---00 ---00 ---863 ---802 and 29 ---00 ---00 ---863 ---804). (5) Install a warning sign on the external hydraulic connection. (6) Placard and select all aircraft electrical power to OFF. Obey all relevant WARNINGS and CAUTIONS (refer to AMM TASKs 24 ---00 ---00 ---861 ---802 and 24 ---00 ---00 ---910 ---801). (7) Lift the aircraft on jacks (refer to applicable instructions in AMM Task 07 ---10 ---00 ---582 ---801). (8) Remove the LH and RH MLG stabilizer struts as required for access (refer to applicable instructions in AMM TASK 32 ---11 ---16 ---000 ---801). (9) Remove the LH and RH MLG forward doors (refer to applicable instructions in AMM TASK 32 ---12 ---11 ---000 ---801). (10) Set up work platforms or ladders as required to gain access to the stabilizer brace in the No. 1 and/or No. 2 wheel well. Make sure that the work platforms or ladders are electrically grounded. B. Procedure NOTE: The rework is limited to the tasks that follow: --- The repair of the conduit assembly that may be damaged due to MLG stabilizer brace interference on harness. --- Rerouting the conduit assembly to eliminate fouling condition on the nacelle A ---Frame.

### SERVICE BULLETIN 84 ---32 ---114

S.B. 84 ---32 ---114 Page 13 of 22 06 Jun 2013 JR Revision ‘B’ 03 Feb 2015 NOTE: Existing cable routing may vary between aircraft due to modification configuration. (1) Rework the LH MLG electrical wiring harness as follows (refer to drawing 8Z9553): (a) Disconnect the conduit assembly 82440848 on ends 3261 ---J24 & 3261 ---J22 and conduit assembly 82440845 on ends 3261 ---J21 & 3261 ---J23 (refer to drawing 8Z9553 sheet 1 to 4). (b) Undo the clippings of the conduit assembly on area shown on drawing 8Z9553 sheet 2 VIEW B ---B and VIEW A. Keep hardware for re ---installation as the conduit will be rerouted (refer to drawing 8Z9553 sheet 2 VIEW W ---W). (c) Do an inspection of the conduit assembly for the conditions that follow and rectify as necessary per the Wiring Diagram Manual Chapters 20 ---12 ---10 ---201, 20 ---15 ---04 ---201 and 20 ---15 ---10 ---401. 1 Foreign object damage (FOD). 2 Damage due to sharp bends and kinking and deterioration. 3 Condition of overbraid for cracking. 4 Sign of damage to the overbraid due to fouling structures. 5 Chafing. (d) If the inspection is satisfactory, re ---install the electrical conduit assembly per drawing 8Z9553. NOTE: Make sure the cables are kept below the reference line as shown by flagnote 15 in dwg 8Z9553 sheet 2 VIEW B ---B or sheet 3 VIEW B ---B or sheet 4 VIEW B1 ---B1 or VIEW B2 ---B2 as applicable, then continue to section (f). (e) If conduit is damaged, replace the damaged conduit on conduit assembly as follows: 1 Disassemble conduit (refer to drawing 8Z9553 sheet 1 DETAIL G and applicable instructions in Wiring Diagram Manual Task 20 ---15 ---10 ---401). 2 Do an inspection of the two connectors, two 90_connector backshells, two straight adaptors and one Y ---transition for condition and keep them for re ---installation if they are in good condition (refer to drawing 8Z9552 sheet 1 flagnote 6).

### SERVICE BULLETIN 84 ---32 ---114

S.B. 84 ---32 ---114 Page 14 of 22 06 Jun 2013 JR Revision ‘B’ 03 Feb 2015 NOTE: The components are considered to be in good condition if they have minimal paint chaffing, level 1 corrosion or less and no impact damage. Refer to Q ---Series CPC Manual (PSM ---1GEN ---5).
NOTE: The connectors, 90_ connector backshells, straight adaptors and Y ---transition may show sign of deterioration but not due to MLG stabilizer brace interference on harness. These parts have to be procured by the customer if replacement parts are necessary for re ---installation (refer to drawing 8Z9552 sheet 1 flagnote 13). Contact the Bombardier Aerospace Technical Help Desk for part information if required. 3 Remove wires from connectors 3261 ---J24 and 3261 ---J22 (refer to drawing 8Z9553 sheet 1 flagnote 7 and applicable instructions in Wiring Diagram Manual Chapter 20 Wiring Standard Practices). 4 Rework conduit assembly 82440848 on connectors 3261 ---J24 and 3261 ---J22 (refer to drawing 8Z9553 sheet 1 flagnote 8 and applicable instructions in Wiring Diagram Manual Task 20 ---15 ---10 ---401), adaptors connectors that are used to terminate the overbraid and individual wireshield that protects the EMI and HIRF during removal and installation as follows:
a Replace damaged overbraid conduit. b Reterminate wiring (refer to drawing 8Z9553 sheet 1 flagnote 8 and WIRING DIAGRAM).
c Install adapters, tinel ring, conduit and heat shrink boots (refer to applicable instructions in WDM Task 20 ---15 ---10 ---401). d Complete assembly of the conduit assembly and re ---install (refer to drawing 8Z9553).
NOTE: Similar repair procedure can be done on conduit assembly 82440845 (3261 ---J21 & 3261 ---J23) if required. Contact the Bombardier Aerospace Technical Help Desk for part information if required.
NOTE: Make sure the cables are kept below the reference line as shown by flagnote 15 in dwg 8Z9553 sheet 2 VIEW B ---B or sheet 3 VIEW B ---B or sheet 4 VIEW B1 ---B1 or VIEW B2 ---B2 as applicable.
e Do a check of the inductance value of proximity sensors LGWOW2 (S02) and LGDLK2 (S08) (refer to applicable instructions in AMM 32 ---61 ---00 ---280 ---801).

### SERVICE BULLETIN 84 ---32 ---114

S.B. 84 ---32 ---114 Page 15 of 22 06 Jun 2013 JR Revision ‘B’ 03 Feb 2015 NOTE: This check can be done beforeClose Out

.

(f) Install edge grommet MS21266 ---2N (refer to flagnote 16 in dwg 8Z9553 sheet 2 VIEW B ---B, sheet 3 VIEW B ---B and sheet 4 View B1 ---B1 & B2 ---B2). (g) Cover electrical cables and hydraulic lines with spiral wrap DSC230 ---7HT as necessary (refer to flagnote 21 in dwg 8Z9553 sheet 2 VIEW S ---S, sheet 3 VIEW A and sheet 4 View A). (h) Do an electrical bonding through direct interface contact (refer to drawing 8Z9553 sheet 1 flagnote 9 and to applicable instructions in AMM Task 51 ---80 ---00 ---120 ---801 and SRM Task 51 ---80 ---00 ---02 ---01). (i) Bond with Epoxy adhesive (product ID No. 05 ---03). After cure, seal edge base with sealant (Product ID No. 06 ---01) (refer to CPM PSM 1 ---84 ---18 and to drawing 8Z9553 sheet 2 flagnote 10 and to applicable instructions in AMM 51 ---23 ---00 ---390 ---801). (j) Install label (refer to drawing 8Z9553 sheet 1 flagnote 11 and to applicable instructions in AMM 20 ---00 ---16 ---400 ---801). (k) Dress up routing to make sure harness is firmly secured and not fouling on the frame (refer to drawing 8Z9553 sheet 2 flagnote 12). (2) Rework the RH MLG electrical wiring harness as follows (refer to drawing 8Z9552): (a) Disconnect the conduit assembly 82440850 on ends 3261 ---J44 & 3261 ---J42 and conduit assembly 82440841 on ends 3261 ---J41 & 3261 ---J43 (refer to drawing 8Z9552 sheet 1 to 3). (b) Undo the clippings of the conduit assembly on area shown on drawing 8Z9552 sheet 2 VIEW B ---B and VIEW A. Keep hardware for re ---installation as the conduit will be rerouted (refer to drawing 8Z9552 sheet 2 VIEW BX ---BX). (c) Do an inspection of the conduit assembly for the conditions that follow and rectify as necessary per the Wiring Diagram Manual Chapters 20 ---12 ---10 ---201, 20 ---15 ---04 ---201 and 20 ---15 ---10 ---401. 1 Foreign object damage (FOD). 2 Damage due to sharp bends and kinking and deterioration. 3 Condition of overbraid for cracking. 4 Sign of damage to the overbraid due to fouling structures. 5 Chafing. (d) If the inspection is satisfactory, re ---install the electrical conduit assembly per drawing 8Z9552.

### SERVICE BULLETIN 84 ---32 ---114

S.B. 84 ---32 ---114 Page 16 of 22 06 Jun 2013 JR Revision ‘B’ 03 Feb 2015 NOTE: Make sure the cables are kept below the reference line as shown by flagnote 15 in dwg 8Z9552 sheet 2 VIEW B ---B or sheet 3 VIEW B ---B, VIEW B1 ---B1 and VIEW B2 ---B2 as applicable, then continue to section (f). (e) If conduit is damaged, replace the damaged conduit on conduit assembly as follows: 1 Disassemble conduit (refer to drawing 8Z9552 sheets 1 and 2 DETAIL G and applicable instructions in Wiring Diagram Manual Task 20 ---15 ---10 ---401). 2 Do an inspection of the two connectors, two 90_connector backshells, two straight adaptors and one Y ---transition for condition and keep them for re ---installation if they are in good condition (refer to drawing 8Z9552 sheet 1 flagnote 6). NOTE: The components are considered to be in good condition if they have minimal paint chaffing, level 1 corrosion or less and no impact damage. Refer to Q ---Series CPC Manual (PSM ---1GEN ---5).
NOTE: The connectors, 90_ connector backshells, straight adaptors and Y ---transition may show sign of deterioration but not due to MLG stabilizer brace interference on harness. These parts have to be procured by the customer if replacement parts are necessary for re ---installation (refer to drawing 8Z9552 sheet 1 flagnote 13). Contact the Bombardier Aerospace Technical Help Desk for part information if required. 3 Remove wires from connectors 3261 ---J44 and 3261 ---J42 (refer to drawing 8Z9552 sheet 1 flagnote 7 and applicable instructions Wiring Diagram Manual Chapter 20 Wiring Standard Practices). 4 Rework conduit assembly 82440850 on connectors 3261 ---J44 and 3261 ---J42 (refer to drawing 8Z9552 sheet 1 flagnote 8 and applicable instructions in Wiring Diagram Manual (WDM) Task 20 ---15 ---10 ---401), adaptors connectors that are used to terminate the overbraid and individual wireshield that protects the EMI and HIRF during removal and installation as follows:
a Replace damaged overbraid conduit. b Reterminate wiring (refer to drawing 8Z9553 sheet 1 flagnote 8 and WIRING DIAGRAM).
c Install adapters, tinel ring, conduit and heat shrink boots (refer to applicable instructions in WDM Task 20 ---15 ---10 ---401).

### SERVICE BULLETIN 84 ---32 ---114

S.B. 84 ---32 ---114 Page 17 of 22 06 Jun 2013 JR Revision ‘B’ 03 Feb 2015 d Complete assembly of the conduit assembly and re ---install (refer to drawing 8Z9552).
NOTE: Make sure the cables are kept below the reference line as shown by flagnote 15 in dwg 8Z9552 sheet 2 VIEW B ---B or sheet 3 VIEW B ---B, VIEW B1 ---B1 and VIEW B2 ---B2 as applicable.

e Do a check of the inductance value of proximity sensors RGWOW2 (S06) and RGDLK2 (S14) (refer to applicable instructions in AMM 32 ---61 ---00 ---280 ---801).
NOTE: Similar repair procedure can be done on conduit assembly 82440841 (3261 ---J41 & 3261 ---J43) if required. Contact the Bombardier Aerospace Technical Help Desk for part information if required.

NOTE: This check can be done beforeClose Out

.

(f) Install edge grommet MS21266 ---2N (refer to flagnote 16 in dwg 8Z9552 sheet 2 VIEW B ---B and sheet 3 View B ---B). (g) Cover electrical cables and hydraulic lines with spiral wrap DSC230 ---7HT as necessary (refer to flagnote 25 in dwg 8Z9552 sheet 2 VIEW A and sheet 3 View A). (h) Do an electrical bonding through direct interface contact (refer to drawing 8Z9552 sheet 1 flagnote 9 and to applicable instructions in AMM Task 51 ---80 ---00 ---120 ---801 and SRM Task 51 ---80 ---00 ---02 ---01). (i) Bond with Epoxy adhesive (product ID No. 05 ---03). After cure, seal edge base with sealant (Product ID No. 06 ---01) (refer to CPM PSM 1 ---84 ---18 and to drawing 8Z9552 sheet 2 flagnote 10 and to applicable instructions in AMM 51 ---23 ---00 ---390 ---801). (j) Install label (refer to drawing 8Z9552 sheet 1 flagnote 11 and to applicable instructions in AMM 20 ---00 ---16 ---400 ---801). (k) Dress up routing to make sure harness is firmly secured and not fouling on the frame (refer to drawing 8Z9552 sheet 2 flagnote 12). (3) Measure the clearance between the stabilizer brace and electrical harnesses on both LH and RH nacelles as follows: (a) Re ---install the LH and RH MLG stabilizer struts as required (refer to applicable instructions in AMM TASK 32 ---11 ---16 ---400 ---801).

### SERVICE BULLETIN 84 ---32 ---114

S.B. 84 ---32 ---114 Page 18 of 22 06 Jun 2013 JR Revision ‘B’ 03 Feb 2015 (b) With the LH and RH MLG forward doors still removed from aircraft, do the Operational Test of the Landing Gear Primary Extension and Retraction System (refer to applicable instructions in AMM TASK 32 ---31 ---00 ---710 ---801). (c) Retract the landing gear and leave in the up and locked position (refer to applicable instructions in AMM Task 32 ---31 ---00 ---867 ---801). (d) Inspect the reworked area in the LH and RH nacelles and do a clearance check between the MLG stabilizer brace and electrical harnesses (refer to Figure 1 Sheets 1 to 3 and Figure 2). Make sure there is 0.100 in. (2.54 mm) minimum clearance between the MLG stabilizer brace and electrical harnesses. (4) Check for signs of contact on LH and RH nacelle A ---Frames and MLG stabilizer braces (refer to Figure 1). If damage caused by contact was found, contact the Q Series Technical Help Desk by telephone at 416---375---4000 or email at: thd.qseries@aero.bombardier.com for approved disposition/action. (5) Extend the landing gear (refer to applicable instructions in AMM Task 32 ---31 ---00 ---867 ---801). (6) Install the LH and RH MLG forward doors (refer to applicable instructions in AMM TASK 32 ---12 ---11 ---400 ---801). (7) Do the operational test of the landing gear primary extension and retraction system (refer to applicable instructions in AMM 32 ---31 ---00 ---710 ---801). C. Close Out (1) Lower the aircraft on jacks and remove the jacks (refer to applicable instructions in AMM Task 07 ---10 ---00 ---582 ---801). (2) Remove all tools and equipment from the work area. (3) 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 ---32 ---114

S.B. 84 ---32 ---114 Page 19 of 22 06 Jun 2013 JR Revision ‘B’ 03 Feb 2015 Nacelle A ---Frame and MLG Stabilizer Brace Figure 1 (Sheet 1) STABILIZER BRACE A ---FRAME

APPLICABLE ON A/C 4056 AND SUBS (POST MS 4 ---113159)
AND FIGURE 2) FOR SIGNS OF CHAFING.

### SERVICE BULLETIN 84 ---32 ---114

S.B. 84 ---32 ---114 Page 20 of 22 06 Jun 2013 JR Revision ‘B’ 03 Feb 2015 A ---FRAME STABILIZER BRACE

Nacelle A ---Frame and MLG Stabilizer Brace Figure 1 (Sheet 2) DURING MLG SWING, CHECK FOR CLEARANCE IN THIS AREA.

APPLICABLE ON A/C 4003 THRU 4055 (POST MS 4 ---113305) F

F

AND FIGURE 2) FOR SIGNS OF CHAFING.

### SERVICE BULLETIN 84 ---32 ---114

S.B. 84 ---32 ---114 Page 21 of 22 06 Jun 2013 JR Revision ‘B’ 03 Feb 2015 Nacelle A ---Frame and MLG Stabilizer Brace Figure 1 (Sheet 3) x

0.100 IN. (2.54 MM) MINIMUM 0.100 IN. (2.54 MM) MINIMUM

0.100 IN. (2.54 MM) MINIMUM 0.100 IN. (2.54 MM) MINIMUM

AND FIGURE 2) FOR SIGNS OF CHAFING. (MLG STABILIZER BRACE P/N 46400 ---25 AND PREV) (MLG STABILIZER BRACE P/N 46400 ---27 AND SUBS)

(MLG STABILIZER BRACE P/N 46400 ---27 AND SUBS) (MLG STABILIZER BRACE P/N 46400 ---25 AND PREV) (AIRCRAFT SERIAL NUMBERS 4001 THRU 4055) (AIRCRAFT SERIAL NUMBERS 4056 THRU 4411)

(AIRCRAFT SERIAL NUMBERS 4056 THRU 4411) (AIRCRAFT SERIAL NUMBERS 4001 THRU 4055)

### SERVICE BULLETIN 84 ---32 ---114

S.B. 84 ---32 ---114 Page 22 of 22 06 Jun 2013 JR Revision ‘B’ 03 Feb 2015 Nacelle A ---Frame and MLG Stabilizer Brace --- Clearance Check Figure 2

1Jan 2009 SERVICE BULLETIN (SB) --- RECORD OF INCORPORATION --- Q SERIES DASH 8 AIRCRAFT To: CMDB Focal 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 V Consumables V Disposition of Existing Parts VOther
3. ACCOMPLISHMENT INSTRUCTIONS VJob Set ---Up V Procedure V Close---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