Revision ‘B’ 22 Nov 2011 DHC-8 (DASH 8) SERVICE BULLETIN 84-32-87 Landing Gear - Parking Brake Accumulator Retrofit - ModSum 4-113650 & 4-113731 This page transmits Revision ‘B’ of Service Bulletin 84-32-87, pages 1 thru 22 dated 22 Nov 2011. This service bulletin is re-issued in its entirety for the reasons that follow: - theSUBJECTsection is revised to add ModSum 4-113731 - theEffectivitysection is revised to include a Verification statement for serial number 4033 and a new “In-Service” statement to cover additional aircraft - theDescriptionsection is revised to include additional information - theCompliancesection is revised to add ModSum 4-113731 - theManpowersection is revised with a note that recommends incorporation of ModSum 4-113706 (Bombardier SB 84-29-30) to help reduce down time when incorporating this SB 84-32-87B - theMaterial - Price and Availabilitysection is revised to add Modkits 8MK4457-003 and -051 - theReferencessection is revised to convey the latest revision of this service bulletin and related engineering documentation - theMATERIAL INFORMATIONsection is revised to add Modkits 8MK4457-003 and -051 (ModSum 4-113731) and related details - theACCOMPLISHMENT INSTRUCTIONSsection is revised to include new instruction for installation of new Modkits 8MK4457-003 and -051 - theClose Outsection is revised to include additional steps and reference to ModSum 4-113731The Compliance in the previous issue of this service bulletin is not affected by this revision. Operators that have incorporated a previous issue of this service bulletin are unaffected by this revision. Remove previous issue of Service Bulletin 84-32-87 and replace with attached. Previous issues of Service Bulletin 84-32-87: Initial issue - Pages 1 thru 18 dated 09 Feb 2011 Revision ‘A’ - Pages 1 thru 16 dated 07 Apr 2011

# D

S.B. 84-32-87

Page 1 of 22 09 Feb 2011 LS/rl Revision ‘B’ 22 Nov 2011 

# SERVICE BULLETIN Customer Support

ATA SYSTEM: 3240 NUMBER: 84-32-87

SUBJECT: Landing Gear - Parking Brake Accumulator Retrofit - ModSums 4-113650 & 4-113731

1. PLANNING INFORMATION A. Effectivity Aircraft Affected: In-Service: DHC-8 Aircraft Model 401 or 402 Serial Number 4001, 4003, 4004, 4006, 4008 thru 4068, 4070 thru 4214, 4216, 4219 thru 4261, 4263 thru 4346 with prerequisite ModSum 4Q113706 (SB 84-29-30).
NOTE: If ModSum 4Q113706 (SB 84-29-30) has not already been incorporated on the above listed aircraft Serial Number, incorporate it in conjunction with this service bulletin.
In-Service: DHC-8 Aircraft Model 401 or 402 Serial numbers 4069, 4215, 4217, 4218 and 4262 modified in accordance with ModSum 4-113650 (SB 84-32-87A) and prerequisite ModSum 4Q113706 (SB 84-29-30).
NOTE: Aircraft which have already incorporated ModSum 4-113650 per SB 84-32-87 Revision A, plus instructions equivalent to 3.B. Part B herein, meet the intent of SB 84-32-87 at Revision B (this document).

### SERVICE BULLETIN 84-32-87

S.B. 84-32-87 Page 2 of 22 09 Feb 2011 LS/rl Revision ‘B’ 22 Nov 2011 Verification: ModSum 4-113731and prerequisite ModSum 4Q113706 (SB 84-29-30) has been installed on DHC-8 Aircraft Model 402 Serial Number 4033 at revision ‘B’ of this SB using Modkits 8MK4457-001 and 8MK4457-051.
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: A fractured end cap from the parking brake accumulator could cause partial loss of the No. 2 Hydraulic System, damage to adjacent components and/or damage to aircraft structure. Solution: This service bulletin gives instructions to relocate the parking brake to a new area where damage to adjacent components and/or damage to aircraft structure is minimized. C. Description The procedures in this service bulletin give the instructions to do the tasks that follow: - aircraft electrical power is removed - the nose landing gear lock is engaged - the main landing gear lock pins are installed thru each main gear and main gear door mechanism - all hydraulic pressure is removed - access is gained to the parking brake accumulator located in the left hand side wing root - the accumulator is removed and kept. A tube assembly is kept for future rework - new structural provisions are installed at a new location

### SERVICE BULLETIN 84-32-87

S.B. 84-32-87 Page 3 of 22 09 Feb 2011 LS/rl Revision ‘B’ 22 Nov 2011 - the accumulator is installed with kept fittings, a reworked tube assembly and two new tube assemblies. - the parking brake accumulator is serviced with nitrogen - a functional test of the parking brake system is done - the No. 1 & 2 Hydraulic System are bled - an operational test of the No. 1 & 2 Hydraulic System is done - close out. D. Compliance Bombardier Inc. recommends incorporation of ModSum 4-113650 or 4-113731 (as applicable) at the earliest opportunity unless otherwise directed by the operator’s airworthiness authority. 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). F. Manpower It will take an estimated 15.00 man-hours to complete this service bulletin. The breakdown of the man-hours is shown in the table that follows:

NOTE: To reduce aircraft down time, it is in the Operators best interest to do ModSum 4-113706 (Bombardier Service Bulletin 84-29-30) at the same time as this service bulletin (Bombardier Service Bulletin 84-32-87). TASK MAN-HOURS Job Set-Up 1.50 Procedure 10.00 Test / RTS 2.00 Close-Out 1.50 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

### SERVICE BULLETIN 84-32-87

S.B. 84-32-87 Page 4 of 22 09 Feb 2011 LS/rl Revision ‘B’ 22 Nov 2011 G. Material - Price and Availability ModKit 8MK4457-001/-003/-051 are available through the Customer Accounts Service Team at Bombardier Aerospace Regional Aircraft division. Operators should submit a purchase order specifying aircraft serial number(s) to: Bombardier Aerospace Customer Accounts Services Team (Mail Stop N11-32) 123 Garratt Blvd. Toronto Ontario Canada M3K-1Y5 Facsimile: (416) 375-3060 Telephone :(416) 375-3920

Kit Number Description 8MK4457-001 and -051 or 8MK4457-003 Retrofit Kit - Parking Brake Accumulator Rework

The part(s) detailed in Paragraph(s) 2.A. may be obtained from any Bombardier Aerospace Regional Aircraft authorized parts source. The price and availability will be quoted at the time of order. H. Tooling - Price and Availability None I. Weight and Balance

A/C Type and Model Weight (Lb) Arm (Inches) Moment (Inches x Lb) x 0.001 DHC-8 Model 401 / 402 0.83 465.5 0.38

### SERVICE BULLETIN 84-32-87

S.B. 84-32-87 Page 5 of 22 09 Feb 2011 LS/rl Revision ‘B’ 22 Nov 2011 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

.................................. L. References Revision ‘B’ of this service bulletin was prepared to the engineering drawings and related data that follows: DRAWING SHEET REV 8MK4457 1 F

8Z9222 1 F 2 C 3 C 4 C 5 D 6 D 7 B ModSum 4Q113650 Rev. ‘J’ ModSum 4-113650 Rev. ‘J’ ModSum 4Q113731 Rev. ‘D’ ModSum 4-113731 Rev. ‘D’ ModSum 4-113706 Rev. ‘C’ IS ModSum IS4Q2950004 Rev. ‘A’ PCA 43045 Revision 11 (for internal reference only) RD 84-53-3860 (for s/n 4069 only).

### SERVICE BULLETIN 84-32-87

S.B. 84-32-87 Page 6 of 22 09 Feb 2011 LS/rl Revision ‘B’ 22 Nov 2011 2. MATERIALINFORMATION
A. Parts Required Per Aircraft (1) Detailed Kit Content for ModKit 8MK4457-001, Retrofit Kit - Parking Brake Accumulator Rework (for serial numbers 4069, 4215, 4217, 4218 and 4262 ONLY).
Quantity Per Kit -001 Part Number Description Remarks

1 8Z6962-001 Bracket Assembly 1 8Z6963-001 Bracket Assembly 1 85306947-101 Support Angle 1 85306942-101 Support Angle 1 82920398-001 Tube Assembly 1 82920399-001 Tube Assembly 1 8Z9222-101 Tube Assembly See Note 1 1 M85052/2-4 Clamp 1 NAS1801-3-8 Bolt 21 B0205016AD5-6S Rivet See Note 2

1 NAS1149D0316J Washer 6 B0205016AD4-4S Rivet See Note 2 1 B0301010-04 Union 1 B0302126-04 Elbow 1 8Z9222-103 Tube Assembly See Note 1 1 8Z9222-105 Tube Assembly See Note 1 1 B0301010-06 Union

NOTE 1: This item is not to be included in this kit. item reworked from existing part on aircraft.

NOTE 2: It is permitted to use NAS1097AD*-* rivets in lieu of B0205018AD*-*S, and MS20470AD*-*S rivets in lieu of B0205016AD*-*S.

### SERVICE BULLETIN 84-32-87

S.B. 84-32-87 Page 7 of 22 09 Feb 2011 LS/rl Revision ‘B’ 22 Nov 2011 (2) Detailed Kit Content for ModKit 8MK4457-003, Retrofit Kit - Parking Brake Accumulator Rework (for serial numbers 4001, 4003, 4004, 4006, 4008 thru 4068, 4070 thru 4214, 4216 and 4219 thru 4261, 4263 thru 4346 only) Quantity Per Kit -003 Part Number Description Remarks
1 82920398-001 Tube Assembly 1 82920399-001 Tube Assembly 1 8Z9222-101 Tube Assembly See Note 1 1 M85052/2-4 Clamp 1 NAS1801-3-8 Bolt 15 B0205016AD5-6S Rivet See Note 2 1 NAS1149D0316J Washer 6 B0205016AD4-4S Rivet See Note 2 1 B0301010-04 Union 1 B0302126-04 Elbow 1 8Z9222-103 Tube Assembly See Note 1 1 8Z9222-105 Tube Assembly See Note 1 1 B0301010-06 Union 1 8Z6962-003 Bracket Assembly 1 8Z6963-003 Bracket Assembly 2 CSP469B-350-200 Laminated Shim 7075-T7351 AMS QQ-250/12 1 8Z9417-101 Support Angle 1 8Z9418-101 Support Angle 2 B0205018AD5-6S Rivet See Note 2 1 CSP468-063-350-175 Shim 14 B0205016AD5-8S Rivet See Note 2 8 B0205016AD5-9S Rivet See Note 2
NOTE 1: This item is not to be included in this kit. item reworked from existing part on aircraft.

NOTE 2: It is permitted to use NAS1097AD*-* rivets in lieu of B0205018AD*-*S, and MS20470AD*-*S rivets in lieu of B0205016AD*-*S.

### SERVICE BULLETIN 84-32-87

S.B. 84-32-87 Page 8 of 22 09 Feb 2011 LS/rl Revision ‘B’ 22 Nov 2011 (3) Modification Kit 8MK4457-051, Retrofit Kit - Parking Brake Accumulator Rework (for serial numbers 4001, 4003, 4004, 4006, 4008 thru 4068, 4070 thru 4214, 4216 and 4219 thru 4261, 4263 thru 4346 only).
NOTE: Modification kit 8MK4457-051 is a delta kit intended for operators that have already acquired kit 8MK4457-001 only. When merging these two kits, part numbers 8Z6962-001, 8Z6963-001, 85306947-101 and 85306942-101 from the 8MK4457-001 kit must be discarded.
(4) Detailed Kit Content:
Quantity Per Kit -051 Part Number Description Remarks

8 B0205016AD5-9S Rivet See Note 1 14 B0205016AD5-8S Rivet See Note 1 1 CSP468-063-350-175 Shim 2 B0205018AD5-6S Rivet See Note 1
1 8Z9417-101 Support Angle 1 8Z9418-101 Support Angle 2 CSP469B-350-200 Laminated Shim 7075-T7351 AMS QQ-250/12 1 8Z6963-003 Bracket Assembly 1 8Z6962-003 Bracket Assembly 6 B0205016AD4-4S Rivet See Note 1 15 B0205016AD5-6S Rivet See Note 1 8Z9222 Drawing 8MK4457 Drawing
NOTE 1: It is permitted to use NAS1097AD*-* rivets in lieu of B0205018AD*-*S, and MS20470AD*-*S rivets in lieu of B0205016AD*-*S.

### SERVICE BULLETIN 84-32-87

S.B. 84-32-87 Page 9 of 22 09 Feb 2011 LS/rl Revision ‘B’ 22 Nov 2011 (5) In addition to the above part(s), the following material(s) are required for the completion of this service bulletin and may be procured as single items from Bombardier Aerospace Regional Aircraft or purchased directly from industry sources. Addresses of manufacturers and suppliers not shown below are listed in either Maintenance Manual Chapter 20 or in Structural Repair Manual Chapter 51 or, for 400 Series Aircraft, in Consumable Products Manual PSM 1-84-18.

Part Number Qty. Per Aircraft Description Remarks C1 1/4 pint Alodine 1200 DHMS C4.01 1/4 Pint Epoxy Primer Type 2 B. Parts Required to Modify Spares None 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 85307502-007 Bracket Assembly 1 B DIS 8Z6962-001 OR 8Z6962-003 N

85307502-009 Bracket Assembly 1 B DIS 8Z6963-001 OR 8Z6963-003 N

82920587-003 Tube Assembly 1 B RWK 8Z9222-103 R

### SERVICE BULLETIN 84-32-87

S.B. 84-32-87 Page 10 of 22 09 Feb 2011 LS/rl Revision ‘B’ 22 Nov 2011 Existing Part Number PNC New Part Number DC IC Qty. Description 82920399-001 Tube Assembly 1 B RWK 8Z9222-105 R 82920581-001 Tube Assembly 1 A RWK 8Z9222-101 R 82920398-001 Tube Assembly 1 A RWK NOTE: Tube assembly 82920581-001 and 82920398-001 are reworked to make new tube assembly 8Z9222-101

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. PNC Part Number Code N New part. R Part number after rework. S Superseding or equivalent part number. X Reworked part and superseding part are functionally and physically equivalent but not identical.

### SERVICE BULLETIN 84-32-87

S.B. 84-32-87 Page 11 of 22 09 Feb 2011 LS/rl Revision ‘B’ 22 Nov 2011 3. ACCOMPLISHMENTINSTRUCTIONS A. Job Set-Up (1) Refer to AMM TASK 24-00-00-861-802 and TASK 24-00-00-910-801 and placard and select all aircraft electrical power to OFF. Obey all relevant WARNINGS and CAUTIONS. WARNING: YOU MUST INSTALL THE LOCKPINS ON THE MAIN LANDING GEAR. MAKE SURE YOU ENGAGE THE NOSE GEAR LOCK. IF YOU DO NOT DO THIS, THE LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO THE EQUIPMENT. (2) Make sure that lock pins are installed thru each main gear and main gear door mechanism. (3) Make sure the nose gear ground lock is engaged. (4) Open and lock the landing gear doors (refer to AMM TASK 32-00-00-840-801). WARNING: OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
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. (5) Remove the hydraulic pressure from systems 1, 2 and 3 per AMM TASK 29-00-00-863-802 and AMM TASK 29-00-00-863-804 including all accumulator pre charges and make sure all hydraulic power is off. (6) Put the landing gear chocks in position. (7) Operate the EMERG BRAKE lever in the flight compartment (minimum of ten times) until there is no parking brake system pressure. Deplete the precharge pressure.

### SERVICE BULLETIN 84-32-87

S.B. 84-32-87 Page 12 of 22 09 Feb 2011 LS/rl Revision ‘B’ 22 Nov 2011 (8) Set the EMERG BRAKE lever to OFF. (9) Set up the work platforms or ladders as required to gain access to the parking brake accumulator located in the left hand side wing root. Make sure the work platforms or ladders are electrically grounded. (10) Refer to AMM TASK 53-31-00-992-801 and remove access panels 262JT, 262KT, 264CR and 264DR to gain access to the parking brake accumulator. (11) Disconnect connectors 2800-J724, 9811-J739, 9811-J750, 9811-J723 and 9811-J724 to allow removal of the existing brackets and installation of the fill rivets. (12) Remove all necessary interior equipment, interior panels and insulation blankets to gain access to fuselage internal structure at stringer 4 and stringer 6 between station X449 and X469. B. Procedure Part A - Removal of Parking Brake Accumulator 08-60197-001 (pre-mod 4Q113653) or 48904-1 (post-mod 4Q113653) Drawing 8Z9222 sheets 2 & 3 (for all serial numbers)
NOTE: Make sure caps are installed on all fluid lines and system components when the system is disconnected. (1) Refer VIEW LOOKING DOWN and AMM TASK 32-44-11-000-801 and remove existing parking brake accumulator. (2) Remove and keep two accumulator clamps MS21920-20. (3) Refer to drawing 8Z9222 sheet 2 for pre-mod 4Q113653 or sheet 3 for post mod 4Q113653, remove and retain the label 81194007-101. (4) Remove and keep tube assembly 82920581-001 for later rework. Keep end fitting attached to tube assembly. (5) Remove and keep bolt NAS1801-3-8, clamp M85052/2-4 and washer AN960D10L. (6) Refer to AMM TASK 29-11-61-000-801 and remove and keep hydraulic power transfer unit (PTU).

### SERVICE BULLETIN 84-32-87

S.B. 84-32-87 Page 13 of 22 09 Feb 2011 LS/rl Revision ‘B’ 22 Nov 2011 NOTE: PTU pressure output line must be disconnected from T fitting and should stay with the PTU. (7) Refer to VIEW LOOKING DOWN and remove and discard bracket assembly 85307502-007. (8) Refer to AMM TASK 51-25-16-390-801 and TASK 51-25-26-370-801 and apply alodine 1200 and epoxy polymide primer (F19) to three open holes. (9) Refer to SRM PSM 1-84-3 TASK 51-42-05-02-01 and install three rivets B0205016AD4-4S to open holes. (10) Refer to VIEW LOOKING DOWN and remove and discard bracket assembly 85307502-009. (11) Refer to AMM TASK 51-25-16-390-801 and TASK 51-25-26-370-801 and apply alodine 1200 and epoxy polymide primer (F19) to three open holes. (12) Refer to SRM PSM 1-84-3 TASK 51-42-05-02-01 and install three rivets B0205016AD4-4S to open holes. (13) Deleted Part B -001 Installation of New Provisions For Parking Brake Accumulator Drawing 8Z9222, sheet 4 (for aircraft serial numbers 4069, 4215, 4217, 4218 and 4262 only). (1) Refer to VIEW LOOKING DOWN and drill out three rivets on stringer 4 (P/N 85360211-136 and 4 rivets on stringer 6 (P/N 85360211-140). (2) Position bracket assembly 8Z6963-001 to stringer 6 and skin 85360111 using pilot hole as a guide. Pick up four existing fastener holes from top skin panel and stringer 6. Second row of four rivet centers in bracket assembly to be located using second pilot hole as a guide. (3) Transfer four rivet centers from bracket assembly 8Z6963-001 to skin 85360111 and skin flange of support angle 85306942-101. (4) Install support angle 85306942-101 to stringer 6 using four rivets B0205016AD5-6S.

### SERVICE BULLETIN 84-32-87

S.B. 84-32-87 Page 14 of 22 09 Feb 2011 LS/rl Revision ‘B’ 22 Nov 2011 (5) Install bracket assembly 8Z6963-001 by securing it in position on skin panel and stringer 6 using four rivets B0205016AD5-8S.
NOTE: If doubler 85363659-103 is installed, install shim CSP468-063-350-175 under bracket assembly 8Z6963-001, trimming around doubler and touching up shim with C1 & F19. If shim is used, bracket assembly 8Z6963-001 must be installed using four rivets B0205016AD5-9S. Make sure a minimum edge distance of 1.75D is maintained. (6) Install bracket assembly 8Z6963-001 to skin panel and support angle 85306942-101 using three rivets B0205016AD5-8S.
NOTE: If doubler 85363659-103 is installed, install shim CSP468-063-350-175 under bracket assembly 8Z6963-001, trimming around doubler and touching up shim with C1 & F19. If shim is used, bracket assembly 8Z6963-001 must be installed using four rivets B0205016AD5-9S. Make sure a minimum edge distance of 1.75D is maintained. (7) Shim if required (maximum 0.030 inches) using shim CSP469B-350-200 and five rivets B0205016AD5-8S. (8) Position bracket assembly 8Z6962-001 to stringer 4 and skin 85360111 using pilot hole as a guide. Pick up three existing fastener holes from top skin panel and stringer 4. Second row of three rivet centers in bracket assembly to be located using second pilot hole as a guide. (9) Transfer three rivet centers from bracket assembly 8Z6962-001 to skin 85360111 and skin flange of support angle 85306942-101. (10) Install support angle 85306947-101 to stringer 4 using three rivets B0205016AD5-6S. (11) Install bracket assembly 8Z6962-001 by securing it in position on skin panel and stringer 4 using three rivets B0205016AD5-8S. (12) Install bracket assembly 8Z6962-001 to skin panel and support angle 85306947-101 using three rivets B0205016AD5-8S. (13) Shim as required (maximum 0.030 inches) using shim CSP469B-350-200 and three rivets B0205016AD5-6S.

### SERVICE BULLETIN 84-32-87

S.B. 84-32-87 Page 15 of 22 09 Feb 2011 LS/rl Revision ‘B’ 22 Nov 2011 Part C -007 Installation of New Provisions For Parking Brake Accumulator Drawing 8Z9222, sheet 7 (for aircraft serial numbers 4001 thru 4046 only). (1) Refer to VIEW LOOKING DOWN and drill out four rivets on stringer 4 (P/N 85360211-136 and 4 rivets on stringer 6 (P/N 85360211-140). (2) At two locations on stringer 4, countersink skin and install two rivets B0205018AD5-6S. Re-identify skin assembly as 8Z9222-013. (3) Position bracket assembly 8Z6963-003 to stringer 6 and skin 85360111 using pilot hole as a guide. Pick up four existing fastener holes from top skin panel and stringer 6. Second row of four rivet centers in bracket assembly to be located using second pilot hole as a guide. (4) Transfer four rivet centers from bracket assembly 8Z6963-003 to skin 85360111 and skin flange of support angle 8Z9417-101. (5) Install support angle 8Z9417-101 to stringer 6 using four rivets B0205016AD5-6S. Make sure to maintain 2D edge distance and 4D center to center distance. (6) Install bracket assembly 8Z6963-003 by securing it in position on skin panel and stringer 6 using four rivets B0205016AD5-8S. NOTE: If doubler 85363659-103 is installed, install shim CSP468-063-350-175 under bracket assembly 8Z6963-003, trimming around doubler and touching up shim with C1 & F19. If shim is used, bracket assembly 8Z6963-003 must be installed using four rivets B0205016AD5-9S. Make sure a minimum edge distance of 1.75D is maintained. (7) Install bracket assembly 8Z6963-003 to skin panel and support angle 8Z9417-101 using four rivets B0205016AD5-8S. NOTE: If doubler 85363659-103 is installed, install shim CSP468-063-350-175 under bracket assembly 8Z6963-001, trimming around doubler and touching up shim with C1 & F19. If shim is used, bracket assembly 8Z6963-003 must be installed using four rivets B0205016AD5-9S. Make sure a minimum edge distance of 1.75D is maintained. (8) Shim if required (maximum 0.030 inches) using shim CSP469B-350-200 and five rivets B0205016AD5-6S.

### SERVICE BULLETIN 84-32-87

S.B. 84-32-87 Page 16 of 22 09 Feb 2011 LS/rl Revision ‘B’ 22 Nov 2011 (9) Position bracket assembly 8Z6962-003 to stringer 4 and skin 85360111 using accumulator to align. Pick up two existing fastener holes from top skin panel and stringer 4. Second row of three rivet centers in bracket assembly to be located as shown in View R-R. (10) Transfer three rivet centers from bracket assembly 8Z6962-003 to skin 85360111 and skin flange of support angle 8Z9418-101. (11) Install support angle 8Z9418-101 to stringer 4 using three rivets B0205016AD5-6S. Make sure to maintain 2D edge distance and 4D center to center distance. (12) Install bracket assembly 8Z6962-003 by securing it in position on skin panel and stringer 4 using two rivets B0205016AD5-8S. (13) Install bracket assembly 8Z6962-003 to skin panel and support angle 8Z9418-101 using three rivets B0205016AD5-8S. (14) Re-indentify bracket 8Z6962-003 as 8Z9222-011. (15) Shim as required (maximum 0.030 inches) using shim CSP469B-350-200 and three rivets B0205016AD5-6S.

### SERVICE BULLETIN 84-32-87

S.B. 84-32-87 Page 17 of 22 09 Feb 2011 LS/rl Revision ‘B’ 22 Nov 2011 Part D -009 Installation of New Provisions For Parking Brake Accumulator Drawing 8Z9222, sheet 4 (for aircraft serial numbers 4047 thru 4337 excluding 4069, 4215, 4217, 4218 and 4262). (1) Refer to VIEW LOOKING DOWN and drill out three rivets on stringer 4 (P/N 85360211-136 and 4 rivets on stringer 6 (P/N 85360211-140). (2) Position bracket assembly 8Z6963-003 to stringer 6 and skin 85360111 using pilot hole as a guide. Pick up four existing fastener holes from top skin panel and stringer 6. Second row of four rivet centers in bracket assembly to be located using second pilot hole as a guide. (3) Transfer four rivet centers from bracket assembly 8Z6963-003 to skin 85360111 and skin flange of support angle 8Z9417-101. (4) Install support angle 8Z9417-101 to stringer 6 using four rivets B0205016AD5-6S. Make sure to maintain 2D edge distance and 4D center to center distance. (5) Install bracket assembly 8Z6963-003 by securing it in position on skin panel and stringer 6 using four rivets B0205016AD5-8S. NOTE: If doubler 85363659-103 is installed, install shim CSP468-063-350-175 under bracket assembly 8Z6963-003, trimming around doubler and touching up shim with C1 & F19. If shim is used, bracket assembly 8Z6963-003 must be installed using four rivets B0205016AD5-9S. Make sure a minimum edge distance of 1.75D is maintained. (6) Install bracket assembly 8Z6963-003 to skin panel and support angle 8Z9417-101 using four rivets B0205016AD5-8S. NOTE: If doubler 85363659-103 is installed, install shim CSP468-063-350-175 under bracket assembly 8Z6963-003, trimming around doubler and touching up shim with C1 & F19. If shim is used, bracket assembly 8Z6963-003 must be installed using four rivets B0205016AD5-9S. Make sure a minimum edge distance of 1.75D is maintained. (7) Shim if required (maximum 0.030 inches) using shim CSP469B-350-200 and five rivets B0205016AD5-6S. (8) Position bracket assembly 8Z6962-003 to stringer 4 and skin 85360111 using accumulator to align. Pick up three existing fastener holes from top skin panel and stringer 4. Second row of three rivet centers in bracket assembly to be located as shown in View G-G.

### SERVICE BULLETIN 84-32-87

S.B. 84-32-87 Page 18 of 22 09 Feb 2011 LS/rl Revision ‘B’ 22 Nov 2011 (9) Transfer three rivet centers from bracket assembly 8Z6962-003 to skin 85360111 and skin flange of support angle 8Z9418-101. (10) Install support angle 8Z9418-101 to stringer 4 using three rivets B0205016AD5-6S. (11) Install bracket assembly 8Z6962-003 by securing it in position on skin panel and stringer 4 using three rivets B0205016AD5-8S.
NOTE: If doubler 85363659-105 is installed, install shim CSP468-063-350-175 under bracket assembly 8Z6962-003, trimming around doubler and touching up shim with C1 & F19. If shim is used, bracket assembly 8Z6962-003 must be installed using four rivets B0205016AD5-9S. Make sure a minimum edge distance of 1.75D is maintained. (12) Install bracket assembly 8Z6962-003 to skin panel and support angle 8Z9418-101 using three rivets B0205016AD5-8S.
NOTE: If doubler 85363659-105 is installed, install shim CSP468-063-350-175 under bracket assembly 8Z6962-003, trimming around doubler and touching up shim with C1 & F19. If shim is used, bracket assembly 8Z6962-003 must be installed using four rivets B0205016AD5-9S. Make sure a minimum edge distance of 1.75D is maintained. (13) Shim as required (maximum 0.030 inches) using shim CSP469B-350-200 and three rivets B0205016AD5-6S.

### SERVICE BULLETIN 84-32-87

S.B. 84-32-87 Page 19 of 22 09 Feb 2011 LS/rl Revision ‘B’ 22 Nov 2011 Part E - Systems Rework Drawing 8Z9222, sheets 5 & 6 (for all serial numbers). (1) Cut tube assembly 82920587-003 to required length. Refer to Maintenance Manual Task 20-20-00-220-801. (2) Re-identify reworked tube assembly as 8Z9222-103. Refer to Maintenance Manual Task 20-00-01-910-801. (3) Cut tube assembly 82920399-001 to required length. Refer to Maintenance Manual Task 20-20-00-220-801. (4) Re-identify reworked tube assembly as 8Z9222-105. Refer to Maintenance Manual Task 20-00-01-910-801. (5) Install free end of tube assembly 8Z9222-103 to tube assembly 8Z9222-105 by swaging it with union B0301010-06.
NOTE: It is acceptable to cut the tube assemblies further to obtain required total length. (6) Cut tube assembly 82920581-001 to required length. Refer to Maintenance Manual Task 20-20-00-220-801. (7) Re-identify reworked tube assembly as 8Z9222-101. Refer to Maintenance Manual Task 20-00-01-910-801. (8) Swage new tube assembly 82920398-001 to reworked tube assembly 8Z9222-101 by using union B0301010-04.
NOTE: It is acceptable to cut the tube assemblies further to obtain required total length. (9) Re-install parking brake accumulator. Refer to Maintenance Manual Task 32-44-11-400-801. (10) Secure tube assembly 82920398-001 to bracket assembly 8Z6962-001 (for -001 / -003 installation) or bracket assembly 8Z6962-003 (for -009 installation) by attaching the tube to the stand-off on bracket using p-clamp M85052/2-4, washer NAS1149D0316J and bolt NAS1801-3-8.

### SERVICE BULLETIN 84-32-87

S.B. 84-32-87 Page 20 of 22 09 Feb 2011 LS/rl Revision ‘B’ 22 Nov 2011 (11) Install fluid lines and fittings. Refer to Maintenance Manual Task 20-20-11-400-801. (12) Install permaswage fittings. Refer to Maintenance Manual Task 20-20-21-350-801. C. Close Out (1) Refer to AMM TASK 29-11-61-400-801 and install Power Transfer Unit. (2) Connect connectors 2800-J724, 9811-J739, 9811-J750, 9811-J723 and 9811-J724. (3) Refer to AMM TASK 12-10-32-614-801 and service the parking brake accumulator with nitrogen. (4) Refer to AMM TASK 29-10-00-870-801 and bleed the No. 1 Hydraulic System. (5) Refer to AMM TASK 29-10-00-870-802 and bleed the No. 2 Hydraulic System. (6) Refer to AMM TASK 29-00-00-863-801 and pressurize the No. 1 and No. 2 hydraulic systems. (7) Inspect affected hydraulic connections and swaged joints for leaks. (8) Refer to AMM TASK 32-44-00-720-001 and do a functional test of the parking brake system. (9) Refer to AMM TASK 29-11-00-710-801 and do an operational test of the No. 1 & 2 Hydraulic System. (10) Re-inspect all hydraulic connections for leaks. (11) Remove all unwanted materials and cleanup any hydraulic fluid spillage from the rework area. (12) Install label (previously removed p/n 81194007-101) in a visible location on the skin next to the accumulator (refer to applicable instructions in AMM TASK 20-00-11-400-801). (13) Install all interior equipment, interior panels and insulation blankets that were removed to gain access to fuselage internal structure. (14) Refer to AMM TASK 53-31-00-992-801 and install access panels 262JT, 262KT, 264CR and 264DR.

### SERVICE BULLETIN 84-32-87

S.B. 84-32-87 Page 21 of 22 09 Feb 2011 LS/rl Revision ‘B’ 22 Nov 2011 (15) Remove all tools and equipment from the work area. (16) On incorporation of ModSum 4-113650 or 4-113731, add the weight and balance data shown in Section I of this service bulletin to the Weight and Balance Manual PSM 1-84-8. Under ‘Description of Change’ enter “ModSum 4-113650 or 4-113731 incorporated.” (17) On incorporation of ModSum 4-113650 or 4-113731, 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 84-32-87

S.B. 84-32-87 Page 22 of 22 09 Feb 2011 LS/rl Revision ‘B’ 22 Nov 2011 Location of Rework Figure 1 1 Location of Rework

1

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 VApproval V Manpower V Material VWeight and Balance V Electrical Load VTooling 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 VJob Set ---Up V Procedure V Close---Out VTest 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