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:

--- the Description section is revised to add additional information

--- the Compliance section 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

--- the References section is revised to convey the latest revision of this service

bulletin and related engineering documentation

--- the Parts Required Per Aircraft section is revised to add additional parts to kit

8MK4615 ---001, add kits 8MK4615 ---006/ ---007/ ---009/ ---051

--- the ACCOMPLISHMENT INSTRUCTIONS section is revised to add additional

steps and Notes

--- steps (1) (f) & (g) in the Procedure section are revised to show correct Views

--- step (2) (g) in the Procedure section 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

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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 INFORMATION

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.
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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

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--- 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

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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

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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.
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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’
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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 INFORMATION

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
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Quantity Per Kit

---002 ---001

Part Number Description Remarks

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.
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(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.
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(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.
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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 ResistantDHMS 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

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B. Parts Required to Modify Spares

None

C. Special Tools and Equipment Required

None

D. Existing Parts Accountability

None

3. ACCOMPLISHMENT INSTRUCTIONS

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.
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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).
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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).
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NOTE: This check can be done before Close 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.
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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).
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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 before Close 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).
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(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

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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.
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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.
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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 4001 THRU 4055) (AIRCRAFT SERIAL NUMBERS 4056 THRU 4411)
SERVICE BULLETIN 84 ---32 ---114

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Nacelle A ---Frame and MLG Stabilizer Brace --- Clearance Check

Figure 2

1
Jan 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.com
Feb 2009

SERVICE BULLETIN (SB) --- COMMENT SHEET --- Q SERIES DASH 8 AIRCRAFT

To: SB Focal (Toronto), Bombardier Aerospace Commercial Aircraft

Phone: (1) 416 375 4078 Facsimile: (1) 416 375 4538

E --mail: syed.rizvi@aero.bombardier.com

From:

Company:

Phone: Extn:

Facsimile: Date:

E --mail:

Select appropriate box(es) and add comments or suggestions you would like us to know

that may enhance the quality of our service bulletins.

Service Bulletin: Revision: ModSum:

1. PLANNING INFORMATION

V Effectivity V Reason V Description V Compliance

V Approval V Manpower V Material V Weight and Balance

V Electrical Load V Tooling V References V Publications Affected

2. MATERIAL INFORMATION

V Kit Content V Special Tools/Equipment V Parts to Modify Spares

V Consumables V Disposition of Existing Parts V Other

3. ACCOMPLISHMENT INSTRUCTIONS

V Job Set ---Up V Procedure V Close---Out V Test

V Illustration(s) V Other

4. COMMENTS, REMARKS, SUGGESTIONS

Fax this sheet to (1) 416 375 4538 or Email PDF to:

syed.rizvi@aero.bombardier.com