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:

- the SUBJECT section is revised to add ModSum 4-113731

- the Effectivity section is revised to include a Verification statement for serial

number 4033 and a new “In-Service” statement to cover additional aircraft

- the Description section is revised to include additional information

- the Compliance section is revised to add ModSum 4-113731

- the Manpower section 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

- the Material - Price and Availability section is revised to add Modkits

8MK4457-003 and -051

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

bulletin and related engineering documentation

- the MATERIAL INFORMATION section is revised to add Modkits

8MK4457-003 and -051 (ModSum 4-113731) and related details

- the ACCOMPLISHMENT INSTRUCTIONS section is revised to include new

instruction for installation of new Modkits 8MK4457-003 and -051

- the Close Out section is revised to include additional steps and reference to

ModSum 4-113731
The 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. MATERIAL INFORMATION

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

Description Qty. IC DC Number

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. ACCOMPLISHMENT INSTRUCTIONS

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

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