### Revision ‘C’ 02 Apr 2015 Tx Ltr SB 84 ---32 ---112 Page 1 of 2 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 Page 2 of 2 

## This Page Intentionally Blank 1

# D

S.B. 84 ---32 ---112 Page 1 of 12 20 Dec 2012 JR Revision ‘C’ 02 Apr 2015 

# 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 INFORMA TION 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

S.B. 84 ---32 ---112 Page 2 of 12 20 Dec 2012 JR Revision ‘C’ 02 Apr 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: 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

S.B. 84 ---32 ---112 Page 3 of 12 20 Dec 2012 JR Revision ‘C’ 02 Apr 2015 --- 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 Page 4 of 12 20 Dec 2012 JR Revision ‘C’ 02 Apr 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 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

S.B. 84 ---32 ---112 Page 5 of 12 20 Dec 2012 JR Revision ‘C’ 02 Apr 2015 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 INFORMA TION 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

S.B. 84 ---32 ---112 Page 6 of 12 20 Dec 2012 JR Revision ‘C’ 02 Apr 2015 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. Inst allation of superseded part negates the intent of this service bulletin. DC Disposition DIS Discard Part. MUI Multiple Usage Item: Return to stock if serviceable. RWK Rework existing part in accordance with this service bulletin. RWI Rework existing part per ..... SAL Salvage. Return to operator’s stores for salvage consideration.

## SERVICE BULLETIN 84 ---32 ---112

S.B. 84 ---32 ---112 Page 7 of 12 20 Dec 2012 JR Revision ‘C’ 02 Apr 2015 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

S.B. 84 ---32 ---112 Page 8 of 12 20 Dec 2012 JR Revision ‘C’ 02 Apr 2015 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

S.B. 84 ---32 ---112 Page 9 of 12 20 Dec 2012 JR Revision ‘C’ 02 Apr 2015 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 aro und all the components especially between the A ---Frame and Stabilizer Brace and the doors are fully closed. (14) Make sure to re ---identify the stabili zer 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 Stabilize r 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

S.B. 84 ---32 ---112 Page 10 of 12 20 Dec 2012 JR Revision ‘C’ 02 Apr 2015 (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 aro und 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

S.B. 84 ---32 ---112 Page 11 of 12 20 Dec 2012 JR Revision ‘C’ 02 Apr 2015 Location of Rework --- Stabilizer Brace Figure 1FORWARD STABILIZERBRACE ASSEMBLY

## SERVICE BULLETIN 84 ---32 ---112

S.B. 84 ---32 ---112 Page 12 of 12 20 Dec 2012 JR Revision ‘C’ 02 Apr 2015 

## This Page Intentionally Blank 1

# 4640 0 - 32 - 102 R 2



# SERVICE BULLETIN

HIGHLIGHTS Feb 17 /1 5 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
- 2 7

. 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 concur rence 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 N one 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 p arenthesis refer to CMM 32
- 11
- 04 , IPL Figure
- Item numbe r. 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 S tabilizer B race A ssembly 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- 1050 A, 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 F WD Stabilizer Brace Assembly PN 4640 1
- 17 vibropeen 32
- 102 A 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
- 102 B 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 2Jan 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 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