Revision ‘C’ 02 Apr 2015 Tx Ltr SB 84 ---32 ---112

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DHC ---8 (DASH 8)

SERVICE BULLETIN 84 ---32 ---112

Main Landing Gear --- Stabilizer Brace Assembly --- Introduction of

Revised Stop Bracket --- ModSum 4 ---902416

This page transmits Revision ‘C’ of Service Bulletin 84 ---32 ---112, pages 1

thru 12 dated: 02 Apr 2015

This service bulletin is re ---issued in its entirety for the reasons that follow:

--- the Compliance section is revised to convey the TCCA AD number

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

bulletin, engineering documentation and the TCCA AD number

--- enclosed Goodrich Service Bulletin (VSB) 46400 ---32 ---102 R2 has been

revised

The Compliance 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 previous issue of Service Bulletin 84 ---32 ---112 along with its

attached VSB and replace with this issue.

Previous issues of Service Bulletin 84 ---32 ---112:

Initial issue --- Pages 1 thru 10 dated 20 Dec 2012

Revision ‘A’ --- Pages 1 thru 12 dated 16 Apr 2014

Revision ‘B’ --- Pages 1 thru 12 dated 12 Sep 2014
Revision ‘C’ 02 Apr 2015 Tx Ltr SB 84 ---32 ---112

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D

S.B. 84 ---32 ---112

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SERVICE BULLETIN

Customer

Support

ATA SYSTEM: 3211 NUMBER: 84 ---32 ---112

BOMBARDIER AEROSPACE REGIONAL AIRCRAFT CONSIDER THIS

SERVICE BULLETIN TO BE PARTICULARLY SIGNIFICANT AND

URGE OPERATORS TO PROMPTLY EVALUATE THE CONTENTS

SUBJECT: Main Landing Gear --- Stabilizer Brace Assembly --- Introduction of

Revised Stop Bracket --- ModSum 4 ---902416

1. PLANNING INFORMATION

A. Effectivity

Aircraft Affected:

In ---Service: DHC ---8 Aircraft Models 401 and 402 Serial Numbers 4001

and 4003 thru 4431 with Main Landing gear (MLG) Stabilizer

Brace Assembly 46400 ---27 installed.

For aircraft serial numbers 4003 --- 4055 pre --- requisite

ModSum 4 ---113774 (SB 84 ---54 ---21) or equivalent ModSum

IS4Q5450002 is required.

For aircraft serial numbers 4056 --- 4426 ModSum 4 ---113776

(SB 84 ---54 ---20) or equivalent ModSum IS4Q5450003 is

highly recommended.

Production: ModSum 4 ---902416 will be installed before delivery on

applicable DHC ---8 Aircraft at Serial Number 4432 and

subsequent.
SERVICE BULLETIN 84 ---32 ---112

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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:

The following is a list of spares affected by this change. Review spares and

procurement systems to determine the existence of any listed parts. See

Paragraph 2.D., Existing Parts Accountability, for disposition.

Part Number Description

46400 ---27 Brace Assembly, Stabilizer

B. Reason

Problem: Investigation has revealed a low clearance condition at installation of

the MLG stabilizer brace assembly and aircraft structure.

Solution: This service bulletin introduces ModSum 4 ---902416.

The ModSum introduces new stop brackets 46581 ---3/ ---4 and new stop

shim 46422 ---5 for all MLG stabilizer brace assemblies 46400 ---27.

Incorporation of this service bulletin will improve the position indication

of the downlock and provide improved protection from fretting damage

through application of dry film lubricant on new design stop bracket.

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 and the

nose gear ground lock is engaged

--- the hydraulic pressure in the No. 2 system is depleted

--- all aircraft electrical power is selected OFF

--- the landing gear doors are opened and locked

--- aircraft is lifted on jacks
SERVICE BULLETIN 84 ---32 ---112

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--- work platforms or ladders are positioned as required to gain access to the stabilizer

brace in the No.1 and / or No.2 wheel well

--- stabilizer brace is disassembled

--- rework is done on each stabilizer brace to install new stop bracket 46581 ---3/ ---4 ,

new design shim 46422 ---5 with reduced thickness and related hardware as

described in attached Goodrich Service Bulletin 46400 ---32 ---102

--- stabilizer brace is assembled

--- retraction and extension of landing gear is done

--- aircraft is lowered from jacks

--- landing gear doors are unlock and closed

--- Close ---Out.

D. Compliance

Bombardier Inc. highly recommends that ModSum ModSum 4 ---902416 be

incorporated at the earliest opportunity unless otherwise directed by the operator’s

airworthiness authority.

Transport Canada Airworthiness Directive CF ---2014 ---45.

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 ---112

S.B. 84 ---32 ---112

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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 1.00

Procedure 10.00

Close ---Out 1.00

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

Refer to SECTION I step 8. MATERIAL COST AND AVAILABILITY in attached

Goodrich Service Bulletin (VSB) 46400 ---32 ---102.

H. Tooling --- Price and Availability

None

I. Weight and Balance

None

J. Electrical Load Data

Not affected

K. Publications Affected

Maintenance Manual PSM 1 ---84 ---2 ................................

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

ModSums Manual PSM 1 ---84 ---12 ..................................
SERVICE BULLETIN 84 ---32 ---112

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L. References

Revision ‘C’ of this service bulletin was prepared to the related data that follows:

ModSum 4 ---902416 Rev ‘H’

ModSum 4N902416 Rev ‘E’

ModSum 4Q902416 Rev ‘D’

ModSum IS4Q5450002 Rev ‘B’

ModSum IS4Q5450003 Rev ‘C’

ModSums 4 ---113774 Rev ‘C’ and 4Q113774 Rev ‘C’

ModSums 4 ---113776 Rev ‘D’ and 4Q113776 Rev ‘D’

PCA 43892 Revision 0 (for internal reference only)

Goodrich Landing Gear Component Maintenance Manual 32 ---11 ---04

Goodrich Service Concession Request 026 ---09

Goodrich Reference Modification Summary Package (MODSUM) 4N902416

Goodrich Landing Gear Service Information Letter (SIL) 02121 ---32 ---53

Goodrich Service Bulletin (VSB) 46400 ---32 ---102 R2 dated: Feb 17/15

Transport Canada Airworthiness Directive CF ---2014 ---45.

MCR 53796 (for internal reference only)

2. MATERIAL INFORMATION

A. Parts Required Per Aircraft

Refer to SECTION III --- MATERIAL INFORMATION in Goodrich VSB

46400 ---32 ---102.

B. Parts Required to Modify Spares

None
SERVICE BULLETIN 84 ---32 ---112

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C. Special Tools and Equipment Required

None

D. Existing Parts Accountability

The following parts may be affected by this service bulletin. Indented parts are

components of the next higher assembly. The quantity (Qty.) column lists the

quantity that may be affected per aircraft for non ---indented parts and the quantity

per next higher assembly for indented parts.

Existing

Part Number Description Qty. IC DC

New Part

Number PNC

46400 ---27 Stabilizer Brace

Assembly

1 A RWK 46400 ---29 R

46401 ---9 FWD Stabilizer

Brace Assembly

1 A RWK 46401 ---15 R

46401 ---13 FWD Stabilizer

Brace Assembly

1 A RWK 46401 ---17 R

46422 ---3 Stop Shim 1 A DIS 46422 ---5 S

46581 ---1 Bracket 1 A DIS 46581 ---3 S

46581 ---2 Bracket 1 A DIS 46581 ---4 S

IC Interchangeability Code

A Not interchangeable.

B Removed Part. No direct replacement.

C Conditionally Interchangeable. Installation of superseded part negates the

intent of this service bulletin.

DC Disposition

DIS Discard Part.

MUI Multiple Usage Item: Return to stock if serviceable.

RWK Rework existing part in accordance with this service bulletin.

RWI Rework existing part per .....

SAL Salvage. Return to operator’s stores for salvage consideration.
SERVICE BULLETIN 84 ---32 ---112

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PNC Part Number Code

N No equivalent Bombardier Inc. part number for reworked part. Indicate

on part that this service bulletin has been accomplished.

R Part number after rework.

S Superseding part number.

X Reworked part and superseding part are functionally and physically

equivalent but not identical.

3. ACCOMPLISHMENT INSTRUCTIONS

A. Job Set ---Up

(1) Open and lock the landing gear doors (refer to AMM TASK

32 ---00 ---00 ---840 ---801 ).

(2) Install the lock pins on the main landing gear (refer to AMM TASK

10 ---11 ---00 ---400 ---802).

(3) Engage the nose gear ground lock (refer to AMM TASK 10 ---11 ---00 ---400 ---801 ).

(4) Lift the aircraft on jacks (refer to AMM TASK 07 ---10 ---00 ---582 ---801).

(5) Deplete hydraulic pressure in the No. 2 system (refer to AMM TASK

29 ---00 ---00 ---863 ---802).

(6) Install a warning sign on the external hydraulic connection.

(7) Placard and select all aircraft electrical power to OFF. Obey all relevant

WARNINGS and CAUTIONS (refer to AMM TASK 24 ---00 ---00 ---910 ---801).

(8) 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 (For On ---Wing Rework)

WARNING: BE SURE THAT THE HYDRAULIC PRESSURE IS OFF AND THAT

THERE IS NO PRESSURE IN THE HYDRAULIC SYSTEM. IF YOU DO

NOT DO THIS YOU CAN CAUSE INJURIES TO PERSONS AND

DAMAGE TO THE EQUIPMENT.

NOTE: For aircraft 4003 --- 4055 pre --- requisite ModSum 4 ---113774 (SB

84 ---54 ---21) or equivalent ModSum IS4Q5450002 is required.
SERVICE BULLETIN 84 ---32 ---112

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NOTE: For aircraft serial numbers 4056 --- 4426 ModSum 4 ---113776 (SB

84 ---54 ---20) or equivalent ModSum IS4Q5450003 is highly

recommended.

(1) With aircraft on jacks, remove ground lock in and apply an upward load on the

lock links to break the over center. Slowly fold the stab brace towards the

retracted position to gain clearance to remove the apex pins.

NOTE: Full retraction is not required.

(2) Support the landing gear from beneath the wheels to keep it in this position for

the procedure.

(3) Carefully disconnect both stabilizer lock springs per AMM Task

32 ---11 ---16 ---000 ---804.

NOTE: Stabilizer Springs can remain attached to the AFT Stab Brace.

(4) With the FWD and AFT braces supported, refer to Accomplishment Instructions

in Goodrich VSB 46400 ---32 ---102 Section II, 1.A. --- , for disassembly of the Stab

Brace lock link assembly and apex joint pins.

(5) Carefully position AFT Stab Brace assembly P/N 46403 on Yoke assembly.

Protect the grease nipples on the AFT Stab Brace at the Yoke attachment points.

Make sure that the Down Lock springs are stowed.

NOTE: Prior to the next step, protect the area of the drag strut that will contact

the FWD Stab Brace using a foam pad or equivalent.

(6) To gain access to the apex lug stop bracket assembly, carefully position FWD

Stab brace P/N 46401 against drag strut making sure there is no damage to the

brake lines.

(7) Remove and replace FWD stab brace apex lug stop bracket, refer to

Accomplishment Instructions in Goodrich VSB 46400 ---32 ---102 Section II, 2. ---

for rework of the FWD stab brace assembly.

(8) Carefully move the FWD stab brace and AFT stab braces upward and assemble

apex pin and lock link assembly, refer to Accomplishment Instructions in

Goodrich VSB 46400 ---32 ---102 Section II, 2. --- for assembly.

(9) Replace the stop shim, refer to Accomplishment Instructions in Goodrich VSB
SERVICE BULLETIN 84 ---32 ---112

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46400 ---32 ---102 Section II, 3. --- Replacement of Stop Shim (2 ---1050A).

(10) Re ---install both stabilizer lock springs per AMM Task 32 ---11 ---16 ---400 ---804.

(11) Repeat all steps for opposite side stabilizer brace assembly.

NOTE: Both LH and RH Stabilizer Brace assemblies may be accomplished in

parallel.

(12) Do the retraction and extension of the landing gear, refer to AMM TASK

32 ---31 ---00 ---867 ---801.

(13) Do a visual check to see that the main landing gear is fully retracted. Make sure

that nothing hangs loose, binds or touches the other components. Make sure

that there is sufficient clearance around all the components especially between

the A ---Frame and Stabilizer Brace and the doors are fully closed.

(14) Make sure to re ---identify the stabilizer brace assembly nameplate as described

on attached VSB 46400 ---32 ---102 using the vibropeen method.

C. Procedure (For On ---Bench Rework)

WARNING: BE SURE THAT THE HYDRAULIC PRESSURE IS OFF AND THAT

THERE IS NO PRESSURE IN THE HYDRAULIC SYSTEM. IF YOU DO

NOT DO THIS YOU CAN CAUSE INJURIES TO PERSONS AND

DAMAGE TO THE EQUIPMENT.

NOTE: For aircraft 4003 --- 4055 pre --- requisite ModSum 4 ---113774 (SB

84 ---54 ---21) or equivalent ModSum IS4Q5450002 is required.

NOTE: For aircraft serial numbers 4056 --- 4426 ModSum 4 ---113776 (SB

84 ---54 ---20) or equivalent ModSum IS4Q5450003 is highly

recommended.

(1) Remove or disassemble the Stabilizer brace, as necessary, refer to AMM Task

32 ---11 ---16 ---000 ---801.

(2) Do the rework on stabilizer brace in accordance with the instructions given in

Section II --- Accomplishment Instructions of Goodrich VSB 46400 ---32 ---102.
SERVICE BULLETIN 84 ---32 ---112

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(3) Install the stabilizer brace, refer to AMM Task 32 ---11 ---16 ---400 ---801.

(4) Do the retraction and extension of the landing gear, refer to AMM TASK

32 ---31 ---00 ---867 ---801.

(5) Do a visual check to see that the main landing gear is fully retracted. Make sure

that nothing hangs loose, binds or touches the other components. Make sure

that there is sufficient clearance around all the components especially between

the A ---Frame and Stabilizer Brace and the doors are fully closed.

(6) Make sure to re ---identify the stabilizer brace assembly nameplate as described

on attached VSB 46400 ---32 ---102 using the vibropeen method.

(7) Repeat all steps for opposite side stabilizer brace assembly.

D. Close Out

(1) Remove all tools and equipment from the work area.

(2) Lower the aircraft from the jacks, refer to AMM TASK 07 ---10 ---00 ---582 ---801.

(3) Unlock and close the landing gear doors, refer to AMM TASK

32 ---00 ---00 ---840 ---802.

(4) On incorporation of this ModSum, make an entry that conforms to local

regulatory requirements in the applicable logbook(s). Enter component serial

numbers if applicable. Enter this ModSum number only after complete and

functional incorporation of all work defined in this service bulletin.
SERVICE BULLETIN 84 ---32 ---112

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Location of Rework --- Stabilizer Brace

Figure 1 FORWARD STABILIZER BRACE ASSEMBLY
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1
46400-32-102 R2

SERVICE BULLETIN 

 HIGHLIGHTS 

Feb 17/15 

 Page 1 of 1

DASH 8 Q400 - MLG 

STABILIZER BRACE ASSEMBLY – FWD STABILIZER BRACE AND STOP PADS 

AND NEW LOCK LINK RIGGING - 

INTRODUCTION OF NEW CONFIGURATION (PN 46400-29) 

REVISION NO.2 – February 17, 2015 

Service Bulletin 46400-32-102 R2 supersedes Service Bulletin 46400-32-102 R1 dated Jun 24/13 

and is re-issued in its entirety to reflect the changes listed below. 

The compliance in the previous issue of this Service Bulletin is not affected by this revision. 

No additional rework is introduced by this revision. 

Please destroy all copies of SB 46400-32-102 R1 dated Jun 24/13. 

Page/Para Change 

Page 3, Paras 2B, 2F Item numbers revised. 
46400-32-102 R2

SERVICE BULLETIN 

Feb 17/15 

Page 1 of 6 

WARNING – This information is subject to the export of which is restricted by the Export Administration Act and the Export Administration Regulations (EAR), 15 C.F.R. parts 730-774, diversion contrary to U.S. law is prohibited. The 

export, re-export, transfer or re-transfer of this technical data to any other company, entity, person, or destination, or for any use or purpose other than that for which the technical data was originally provided is prohibited without 

prior written approval and authorization under applicable export control laws. EAR Export Classification: ECCN 9E991 Warning – This document or file contains Technical Data the export of which is, or may be, restricted by the 

Export and Import Permits Act administered by the Trade Controls & Technical Barriers Bureau. Diversion contrary to Canada Law is prohibited. The export, re-export, transfer or re-transfer of this Technical Data to any other 

company, entity, person, or destination, or for any use of purpose other than that for which the Technical Data was originally provided by UTC Landing Systems , is prohibited without prior written approval from the UTC Landing 

Systems and authorization under applicable export control laws. EIPA Export Classification: NLR – No License Required 

DASH 8 Q400 - MLG 

STABILIZER BRACE ASSEMBLY – FWD STABILIZER BRACE AND STOP PADS 

AND NEW LOCK LINK RIGGING - 

INTRODUCTION OF NEW CONFIGURATION (PN 46400-29) 

------------------------------------------------------------------------------------------------------------------------------- 

SECTION I - PLANNING INFORMATION 

1. EFFECTIVITY

All Main Landing Gear Stabilizer Brace Assemblies PN 46400-27.

2. CONCURRENT REQUIREMENTS

None. 

3. REASON 

Investigation has revealed a low clearance condition at installation of the MLG Stabilizer 

Brace Assembly and aircraft structure. 

Incorporation of this service bulletin will improve the position indication of the downlock 

and provide improved protection from fretting damage through application of dry film 

lubricant on new design stop bracket. 

4. DESCRIPTION

MLG Stabilizer Brace Assembly PN 46400-27 is disassembled and the stop brackets are 

removed from the FWD Stabilizer Brace Assembly. 

Replacement stop brackets are coated with corrosion inhibiting compound and installed 

on the FWD Stabilizer Brace Assembly. 

A new design shim with reduced thickness is installed on the lock link stop pin. This 

reduced shim thickness increases the lock link over center position. 

FWD Stabilizer Brace Assembly is assembled to the MLG Stabilizer Brace Assembly. 

The MLG Stabilizer Brace Assembly is rigged with the new lock link over center position 

and re-identified as PN 46400-29. 

NOTE: For on-wing incorporation of this service bulletin, do disassembly/assembly of 

the stabilizer brace assembly in accordance with applicable instructions 

contained in Bombardier Aerospace Service Bulletin 84-32-112.

5. COMPLIANCE

Goodrich Landing Gear in concurrence with the aircraft manufacturer recommends 

incorporation of this bulletin at operators earliest opportunity.

6. APPROVAL

 The technical content of this Service Bulletin has been reviewed and accepted by 

Bombardier Aerospace. 
46400-32-102 R2

Goodrich Landing Gear Division 

Goodrich Aerospace Canada Ltd. 

Feb 17/15 

 Page 2 of 6 

This document contains technical data subject to the export controls / proprietary information noted on page one. 

7. MANPOWER 

10 man hours are required to incorporate this Service Bulletin off-wing (shop upgrade). 

NOTE: For on-wing manpower requirements, refer to Bombardier Aerospace Service 

Bulletin 84-32-112. 

8. MATERIAL COST AND AVAILABILITY 

Refer to Goodrich Landing Gear Service Information Letter (SIL 02121-32-53) for 

material cost and availability. 

Parts are available from: 

Goodrich Landing Gear, Tele: 1-905-827-7777

1400 South Service Rd, Fax: 1-905-825-1583

Oakville, Ontario, 

Canada L6L 5Y7 ATT: Warranty Administrator

9. TOOLING

NA

10. WEIGHT AND BALANCE

None

11. ELECTRICAL LOAD DATA

 NA 

12. REFERENCES 

Goodrich Landing Gear Component Maintenance Manual 32-11-04

Goodrich Reference Modification Summary Package (MODSUM) 4N902416 

Goodrich Landing Gear Service Information Letter (SIL) 02121-32-53

Bombardier Aerospace Service Bulletin 84-32-112 

13. OTHER PUBLICATIONS AFFECTED 

Goodrich Landing Gear Component Maintenance Manual 32-11-04

------------------------------------------------------------------------------------------------------------------------------- 

SECTION II - ACCOMPLISHMENT INSTRUCTIONS 

NOTE: Numbers in parenthesis refer to CMM 32-11-04, IPL Figure-Item number.

1. Disassembly

CAUTION: SPRING ASSEMBLY (2-450A) IS IN TENSION ON STABILIZER BRACE 

ASSEMBLY. USE CARE WHEN WORKING IN THE LOCAL VICINITY. 

RELEASE SPRING TENSION BEFORE PERFORMING DISASSEMBLY.

A. Disassemble the MLG Stabilizer Brace Assembly (2-1E) to remove FWD Stabilizer 

Brace Assembly PN 46401-9/-13 (Ref. CMM 32-11-04 DISASSEMBLY).
46400-32-102 R2

Goodrich Landing Gear Division 

Goodrich Aerospace Canada Ltd. 

Feb 17/15 

 Page 3 of 6 

This document contains technical data subject to the export controls / proprietary information noted on page one. 

2. Rework of FWD Stabilizer Brace Assembly 

A. Remove sealant from stop bracket lugs on FWD Stabilizer Brace Assembly. 

B. Remove nut (2-1223) and washer (2-1225). Remove bolt (2-1227), washer (2-1226) 

and stop bracket (2-1230A), (2-1250A) from FWD Stabilizer Brace Assembly. 

Discard stop brackets (2-1230A), (2-1250A). 

C. Inspect lugs on FWD Stabilizer Brace Assembly for fretting damage. Restore 

missing coating as required (Ref CMM 32-11-04 REPAIR).

WARNING: USE PROTECTIVE EQUIPMENT WHEN WORKING WITH 

CORROSION INHIBITING COMPOUND SUCH AS MASTINOX 6856K. 

SKIN CONTACT CAN BE HAZARDOUS TO YOUR HEALTH.

D. Apply a liberal amount of corrosion inhibiting compound (CIC, Mastinox 6856K) to 

mating faces of FWD Stabilizer Brace Assembly, stop bracket PN 46581-3 and stop 

bracket PN 46581-4 (Refer to Figure 1). 

E. Coat shank of bolt (2-1227) with corrosion inhibiting compound (Mastinox). 

F. Align stop bracket PN 46581-3 and stop bracket PN 46581-4 to FWD Stabilizer 

Brace and install bolt (2-1227) and washer (2-1226) (under bolt head). Install 

washer (2-1225) and nut (2-1223) (Refer to Figure 1). 

NOTE: Make sure washer (2-1226) countersunk feature is facing bolt head.

G. Torque nut (2-1223) and install new cotter pin (2-1221) (Ref CMM 32-11-04 Table 

803). 

NOTE: A maximum of two washers can be used under nut to achieve cotter pin 

alignment.

H. Remove excess CIC using a clean lint free cloth. Fillet seal periphery of stop bracket 

with sealant per AMS-S-8802, type 2 (Ref CMM 32-11-04 ASSEMBLY). 

I. Reidentify FWD Stabilizer Brace Assembly PN 46401-9/-13 as PN 46401-15/-17 by 

ink stamp (Refer to Figure 1). 

NOTE FWD Stabilizer Brace Assembly PN 46401-11 is not in-service.

J. Apply an overcoat of clear enamel to ink stamp per MIL-PRF-85285.

3. Replacement of Stop Shim (2-1050A) 

A. Remove cotter pin (2-1010), nut (2-1020) and washer (2-1030) Disassemble stop pin 

(2-1040) and stop shim (2-1050A). Discard cotter pin. 

B. Determine stop shim (2-1050A, PN 46422-3) thickness and calculate required 

thickness of new stop shim PN 46422-5 as follows: 

(1) Stop shim PN 46422-5 = stop shim PN 46422-3 thickness – 0.065 ± 0.005 inch. 

C. Remove peelable layers on new stop shim PN 46422-5, as required, to achieve the 

dimension calculated above. 

D. Install new stop shim PN 46422-5 and stop pin (2-1040) in FWD Stabilizer Brace 

Assembly and install washer (2-1030) and nut (2-1020) (Ref. CMM 32-11-04 

ASSEMBLY). 

E. Torque nut (2-1020) (Ref. CMM 32-11-04 FITS AND CLEARANCES).

F. Safety nut (2-1020) with cotter pin (2-1010). 
46400-32-102 R2

Goodrich Landing Gear Division 

Goodrich Aerospace Canada Ltd. 

Feb 17/15 

 Page 4 of 6 

This document contains technical data subject to the export controls / proprietary information noted on page one. 

4. Assembly 

A. Assemble the MLG Stabilizer Brace Assembly using FWD Stabilizer Brace Assembly 

PN 46401-15/-17(Ref. CMM 32-11-04).

NOTE: The lock link overcenter dimension with stop shim PN 46422-5 installed will 

be 0.135 – 0.155 inch (Refer to Figure 2). 

5. Re-identification 

CAUTION: DO NOT LETTER STAMP NAMEPLATE ON ASSEMBLY. THIS CAN DAMAGE 

ASSEMBLY. 

A. Re-identify FWD Stabilizer Brace Assembly (refer to Paragraph 2.I.). 

B. Re-identify Stabilizer Brace Assembly PN 46400-27 as PN 46400-29 on nameplate (2-

760). 

C. For assemblies with FWD Stabilizer Brace Assembly PN 46401-17 vibropeen 

32-102A and date accomplished in the MOD STATUS field of nameplate (2-760).

D. For assemblies with FWD Stabilizer Brace Assembly PN 46401-15 vibropeen 

32-102B and date accomplished in the MOD STATUS field of nameplate (2-760).

E. Record accomplishment of this bulletin in aircraft logbook.

--------------------------------------------------------------------------------------------------------------------------- 

SECTION III - MATERIAL INFORMATION 

New P/N Qty* Keyword Old P/N Qty Disposition 

46400-29 1 Stabilizer Brace 46400-27 1 Rework 

 Assembly 

46401-15 1 FWD Stabilizer 46401-9 1 Rework 

 Brace Assembly 

46401-17 1 FWD Stabilizer 46401-13 1 Rework 

 Brace Assembly 

46422-5 1 Stop Shim 46422-3 1 Discard 

46581-3 1 Bracket 46581-1 1 Discard 

46581-4 1 Bracket 46581-2 1 Discard 

* Qty per assembly 
46400-32-102 R2

Goodrich Landing Gear Division 

Goodrich Aerospace Canada Ltd. 

Feb 17/15 

 Page 5 of 6 

This document contains technical data subject to the export controls / proprietary information noted on page one. 

FWD Stabilizer Brace – Rework 

Figure 1 
46400-32-102 R2

Goodrich Landing Gear Division 

Goodrich Aerospace Canada Ltd. 

Feb 17/15 

 Page 6 of 6 

This document contains technical data subject to the export controls / proprietary information noted on page one. 

Lock Link Overcenter Dimension with Stop Shim PN 46422-5 (shown assembled) 

Figure 2 
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