Revision ‘A’ 16 Dec 2011

DHC-8 (DASH 8)

SERVICE BULLETIN 8-32-169

Landing Gear - Parking Brake System - Parking Brake Accumulator -

Installation of Restraint Device Around End Caps - ModSum 8Q101901

The Initial issue of this Service Bulletin was issued to one customer for a

“Release to Service” of verification aircraft Serial number 269.

This page transmits Revision ‘A’ of Service Bulletin 8-32-169, pages 1 thru

16 dated 16 Dec 2011.

NOTE: The Initial issue of this Service Bulletin is not posted on RACS and

was issue to one customer for “Release to Service” of verification

aircraft serial number 269.

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

- the Effectivity section is revised to remove Accumulator reference and

clarification note recommending accomplishing of Mods 8/1152 and 8/1982

prior to actioning of this SB

- the Description section revised to reflect part number commonalty with

AIPC manual listings, was P/N 0860162-001 now 08-60162-001

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

bulletin and engineering documentation

- the MATERIAL INFORMATION section, D. Existing Parts Accountability is

section is revised to show Parking Brake Accumulator P/N commonalty with

AIPC manual listings

- the ACCOMPLISHMENT INSTRUCTIONS section, B. Procedure

section is revised to:

- step (4) revised to reflect part number commonalty with AIPC manual

listings, was P/N 0860162-001 now 08-60162-001

- step 7 revised to show additional clarification statements

- step 8 deleted and then all following steps have been resequence

- Figure 1 is revised to reflect a nondescript vendor label locator and

introduce a min of 0.25 inch dimensional gap between bottom of

Parking Brake Accumulator and structure
The Compliance in the previous issues of this service bulletin is not affected

by this revision. No additional rework to the aircraft is introduced by this

revision.

Remove Service Bulletin 8-32-169 Initial issue and replace with attached.

Previous issues of Service Bulletin 8-32-169:

Initial issue (“Release to Service” of verification aircraft Serial number

269 only) - Pages 1 thru 16 dated 25 Nov 2011
D

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SERVICE BULLETIN

Customer

Support

ATA SYSTEM: 3244 NUMBER: 8-32-169

SUBJECT: Landing Gear - Parking Brake System - Parking Brake Accumulator -

Installation of Restraint Device Around End Caps - ModSum 8Q101901

1. PLANNING INFORMATION

A. Effectivity

Aircraft Affected:

In-Service: All DHC-8 Aircraft Models 102, 103, 106, 201, 202, 301, 311,

314 and 315 serial numbers 003 thru 672 with Mods 8/1152

and 8/1982.

NOTE: If Mods 8/1152 and 8/1982 have not already been incorporated on the

above listed aircraft serial numbers, incorporate it in conjunction with this

Service Bulletin.

Verification: ModSum 8Q101901 has been incorporated on DHC-8 Aircraft

Model 311 Serial Number 269 per Post Verification Service

Bulletin 8-32-169.

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.
SERVICE BULLETIN 8-32-169

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Spares Affected:

None

B. Reason

Problem: A fracture of one of the brake Accumulator end caps can result in loss of

the No. 2 hydraulic system, damage to adjacent systems and/or aircraft

structure.

Solution: This service bulletin introduces ModSum 8Q101901.

The ModSum installs a “containment device” around each end cap on the

brake Accumulator. Each containment device is designed to hold the end

cap in situ in the unlikely event that an end cap fails.

C. Description

The procedures in this service bulletin give the instructions to do the tasks that

follow:

- all aircraft electrical power is selected to OFF

- lock pins are installed thru each main gear and main gear door mechanism

- the nose gear ground lock is engaged

- a warning sign is installed on the external hydraulic connection

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

- an electrically grounded workstand or ladder is positioned under the right wing to

fuselage area (under the “wing root”)

- two access panel are removed

- the parking brake Accumulator is located

- depending on aircraft configuration existing tube assemblies 82920010-335,

82920010-361, 82920010-371 or 8Z5564-101 are removed and discarded

- the existing parking brake Accumulator is removed. Accumulators with p/n

2730489M1 or 08-60162-001 are discarded. Accumulators with p/n 08-60162-002

which are serviceable in accordance with SB 8-32-170 or 8-32-172 are kept for later

installation

- support plate p/n 82970084-101, top bracket assy 82970090-003 and bottom

bracket assy 82970091-003 are installed

- for aircraft that are Pre Mod 8/2463 bracket 85351008-001 is installed
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- containment assemblies 82970085-001 are installed to each end cap and secured

with fasteners

- label 81195108-101 “GAS” is applied to the top containment assy 82970085-001

and label 81195109-101 “FLUID” is applied to the bottom containment assy

- Tactair Accumulator p/n 08-60162-002 is installed and adjusted as required to

maintain no less than 0.250 inch clearance between adjacent structure and the top

and bottom containment devices

- new tube assy p/n 82920010-389, 82920010-391 and clamps p/n MS21919WDE3

and MS21919WDE4 are installed

- the parking brake Accumulator is serviced with nitrogen

- the parking brake system is bled, followed by a system functional test

- a visual check for any signs of leakage is accomplished at the rework site

- access panels are closed

- Close Out.

D. Compliance

Bombardier Inc. recommends incorporation of ModSum 8Q101901 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).
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F. Manpower

It will take an estimated 15 man-hours to complete this service bulletin if

replacement of the parking brake Accumulator is required. The breakdown of the

man-hours is shown in the table that follows:

TASK MAN-HOURS

Job Set-Up 1.00

Procedure 12.00

Test / RTS 1.50

Close-Out 0.50

For any on-site labor assistance, please speak with a Fleet Services representative

for a quote. The Fleet Services group can be contacted via the

Q Series Technical Help Desk by telephone at 416-375-4000 or

email at : thd.qseries@aero.bombardier.com

G. Material - Price and Availability

The Modkit listed in the table below is 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 Price (US$) Delivery

8MK4440-007 Brake Accumulator Kit Quoted at

time of order

Will be given at

time of order
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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 102 3.50 442.17 1.55

DHC-8 Model 103 3.50 442.17 1.55

DHC-8 Model 106 3.50 442.17 1.55

DHC-8 Model 201 3.50 442.17 1.55

DHC-8 Model 202 3.50 442.17 1.55

DHC-8 Model 301 3.50 442.17 1.55

DHC-8 Model 311 3.50 442.17 1.55

DHC-8 Model 314 3.50 442.17 1.55

DHC-8 Model 315 3.50 442.17 1.55

J. Electrical Load Data

Not affected

K. Publications Affected

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

PSM 1-82-4 and

PSM 1-83-4

Maintenance Manual PSM 1-8-2 and ................................

PSM 1-82-2 and

PSM 1-83-2

Modifications Manual PSM 1-813-12 ...............................
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L. References

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

DRAWING SHEET REV

8MK4440 1 E

8Z6855 1 F

8Z6855 2 E

ModSum 8Q101901 Rev. ‘K’

PCA 05765 Revision 8 (for internal reference only)

2. MATERIAL INFORMATION

A. Parts Required Per Aircraft

(1) Modification Kit 8MK4440-007 detail parts list:

Quantity Per Kit

-007

Part Number Description Remarks

1 MS21919WDE4 Clamp

1 MS21919WDE3 Clamp

1 NAS1801-3-8 Screw

2 81195109-101 Label, Fluid

2 81195108-101 Label, Gas

4 B0205016AD4-4S Rivet

8 B0207005M4-02 Rivet Equivalent -

NAS9307M4-02

2 B0207005M4-03 Rivet Equivalent -

NAS9307M4-03

9 MS21042-3 Nut

17 NAS1149D0316J Flat Washer

8 NAS6603-5 Bolt

1 CSP469C-200-075 Laminated Shim

1 85351008-001 Bracket Assy
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Quantity Per Kit

-007

Part Number Description Remarks

1 82970091-003 Bracket AssyBTM

1 82970090-003 Bracket AssyTop

4 82970085-003 Containment

Assy

1 82970084-101 Support Plate

1 82920010-391 Tube Assy

1 82920010-389 Tube Assy

1 8Z6855 Accum Retrofit Drawing Only

REF 8Z6855-103 Support Assy (Make from

85350994)

REF 8Z6855-101 Mounting Panel (Make from

85350969) See

NOTE 1 below

NOTE 1: For aircraft with post modification 8/2463 only.

B. Parts Required to Modify Spares

None

C. Special Tools and Equipment Required

None
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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

82920010-335 Tube Assy 1 DIS 82920010-389 S

82920010-361 or Tube Assy 1 A DIS 82920010-391 S

82920010-371 or Tube Assy 1 A DIS 82920010-391 S

8Z5564-101 Tube Assy 1 A DIS 82920010-391 S

82970039-001 Clamp 2 DIS

2730489M1 or Parking Brake

Accumulator

1 A DIS 08-60162-002 S

08-60162-001 Parking Brake

Accumulator

1 A DIS 08-60162-002 S

IC Interchangeability Code

A Not interchangeable.

B Removed Part. No direct replacement.

C Conditionally Interchangeable. Installation of superseded part negates the

intent of this service bulletin.

DC Disposition

DIS Discard Part.

MUI Multiple Usage Item: Return to stock if serviceable.

RWK If affected, rework existing part in accordance with this service bulletin and

SB 8-32-170 or 8-32-172.

RWI Rework existing part per .....

SAL Salvage. Return to operator’s stores for salvage consideration.
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PNC Part Number Code

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

part that this service bulletin has been accomplished.

R Part number after rework.

S Superseding part number.

X Reworked part and superseding part are functionally and physically

equivalent but not identical.

3. ACCOMPLISHMENT INSTRUCTIONS

A. Job Set-Up

(1) Placard and select all aircraft electrical power to OFF.

(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 and lock pin is through nose

gear door mechanism.

(4) Install wheel chocks at the nose landing gear and the main landing gear.

(5) Depressurize hydraulic systems by applying aileron and rudder flight control

inputs.

(6) Deplete parking brake Accumulator hydraulic pressure by applying and

releasing the EMERG. brake handle approximately 10 times.

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

(8) Position an electrically grounded workstand or ladder as required to gain access

to the parking brake Accumulator (wing to fuselage ‘wing root’ right side)

(9) Remove the access panels 264DR and 262LT (refer to AMM 06-40-10).

B. Procedure

WARNING: YOU MUST INSTALL THE LOCKPINS IN THE DOOR MECHANISMS OF

THE MLG AND NLG. THE DOOR MECHANISMS CAN ACCIDENTALLY

CLOSE THE LANDING GEAR DOORS. THIS CAN CAUSE INJURIES TO

PERSONS AND DAMAGE TO THE EQUIPMENT.
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WARNING: HYDRAULIC FLUID MAY CAUSE SKIN IRRITATION. AVOID

PROLONGED OR REPEATED CONTACT WITH SKIN. IN CASE OF EYE

CONTACT, FLUSH EYES THOROUGHLY WITH WATER AND SEEK

PROMPT MEDICAL ATTENTION. IN CASE OF INGESTION, SEEK

PROMPT MEDICAL ATTENTION.

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

General Notes: The procedures that follow are applicable to aircraft with Tactair

Parking Brake Accumulator p/n 08-60162-002 and prerequisite Mods

8/1152, 8/1982 installed.

If the part number of the existing Accumulator is other than 08-60162-002

it must be replaced prior to accomplishment of this service bulletin. Refer

to related Illustrated Parts Catalog (IPC) for interchangeability and

Aircraft Maintenance Manual (AMM) for removal / installations

instructions.

If prerequisite mods are not incorporated refer to latest issue of Service

bulletins 8-32-128 and 8-29-24 and complete the rework.

Do not attempt to do any rework conveyed below if the prereq conditions

described in the para’s above are not incorporated.

(1) Gain access to the parking brake Accumulator and related tube assemblies

(wing root right side, see Figure 1).

NOTE: Make sure to put a cap on all fluid lines and components whenever the

system is disconnected.

(2) Remove existing tube assemblies as as follows:

(a) Locate tube assy 82920010-335 (refer to dwg 8Z6855 sht 1 VIEW A-A and Flag

Note ). Remove and discard the tube assy 82920010-335.
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(b) For aircraft with Post Mods 8/1152 and 8/1982 but Pre-Mod 8/2463

(charging valve attached to web p/n 85350994) locate, disconnect and

discard tube assy 82920010-361 (refer to dwg 8Z6855 sht 1 VIEW A-A and

Flag Note ). Remove and keep charge valve p/n 8SC0137/G4304 and

related washers and bolts.

(c) For aircraft with Post Mod 8/2463 installed (charging valve attached to

bracket p/n 85351008) locate, disconnect and discard tube assy

82920010-371 or 8Z5564-101. Do not remove the charging valve p/n

8SC0137/G4304.

(3) Remove the existing parking brake Accumulator from the aircraft (for 100 or 300

series refer to applicable instructions in AMM 32-44-12 PARKING BRAKE

ACCUMULATOR - MAINTENANCE PRACTICES. For 200 series refer to

applicable instructions in AMM TASK 32-44-12-000-809). Discard band clamps

p/n 82970039-001 (qty 2), keep the bolts NAS1304-2 and washers AN960-416L.

(4) On the parking brake Accumulator locate and record the part number of the

Accumulator and compare with the two steps below:

- If the p/n is 2730489M1 or 08-60162-001 discard the Accumulator

- if the p/n is 08-60162-002 and non suspect as identified in SB 8-32-170 or

8-32-172 keep for later installation.

NOTE: If installation of a new parking brake Accumulator p/n 08-60162-002 is

required transfer the end fittings AN919-2D and AN893-1D (gas port) and

AN919-10D (oil port) from “old Accumulator” to “new Accumulator”.

NOTE: Make sure to put a cap on all open tube assemblies, ports and fittings.

(5) Carefully remove two rivets used to attach angle p/n 85350970 to mounting

panel p/n 85350969 / 8Z3689 (refer to dwg 8Z6855 “VIEW LOOKING AFT ON

RHS AT X=445.500” flagnote 6E .

(a) Deburr open rivet holes. Treat bared metal using alodine 1200, 1200S or 1201

and prime using epoxy chromate primer.

(6) Do the structural rework that follows:

(a) Install support plate p/n 82970084-101 to panel 85350969-101 using kept

bolts NAS1304-2 (qty. 4) and washers AN960-416L.
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(b) Transfer 2 rivet centers (match-marks) from new plate onto panel 85350969.

Using the match-marks as a guide make two new holes thru panel 85350969

using a #30 drill bit (0.132 Inch dia).

(c) Deburr open rivet holes. Treat bared metal using alodine 1200, 1200S or 1201

and prime using epoxy chromate primer.

(d) Install support plate 82970084-101 to panels 85350969 and 85350647 using

rivets B0207005M4-03 (Equivalent - NAS9307M-4-02) (qty 2) and

B0207005M4-02 (Equivalent - NAS9307M-4-03) (qty 8).

(e) Install top bracket assy 82970090-003 to mounting panel 85350969 using

bolts NAS1304-2 and washers AN960-416L (do not tighten the bolts), refer to

dwg 8Z6855 SECTION C-C.

(f) Install bottom bracket assy 82970091-003 to mounting panel 85350969 using

bolts NAS1304-2 and washers AN960-416L. Torque tighten bolts to 40 to 50

inch pounds.

(g) Re-identify mounting panel 85350969 as 8Z6855-101. For 100 or 300 series

refer to applicable instructions in AMM 20-15-04 MARKING - AIRCRAFT

PARTS, MATERIALS AND ASSEMBLIES. For 200 series, refer to applicable

instructions in AMM TASK 20-15-04-910-801).

(h) For aircraft that are Pre Mod 8/2463 do step 1 and 2 below. For all other

aircraft continue with step (7).

1 Install bracket 85351008-001 to support assy 85350994 using rivets

B0205016AD4-4S, refer to dwg 8Z6855 sht 2 on “VIEW LOOKING

INBOARD with flagnote 7H ”.

2 Re-identify support assy 85350994 as 8Z6855-103. For 100 or 300

series refer to applicable instructions in AMM 20-15-04 MARKING -

AIRCRAFT PARTS, MATERIALS AND ASSEMBLIES. For 200 series

refer to applicable instructions in AMM TASK 20-15-04-910-801.

(7) Install containment assy and labels as follows:

(a) Install containment assy 82970085-003 on both Accumulator end caps

(nonsuspect Accumulator in accordance with Service Bulletins 8-32-170 and

8-32-172) and secure with bolts NAS6603-5, washers NAS1149D0316J and

nuts MS21042-3, refer to dwg 8Z6855 sht 2 Sec. E-E. Make sure that each

retainer is angled at approx. 45 deg +/- 10 deg with respect to the

Accumulator label to prevent contact with adjacent structure. Refer to dwg

8Z6855 sht 2 on “VIEW LOOKING INBOARD ON RHS AT X=445.500, Zone

F3.
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(b) Apply label 81195108-101 “GAS” to the top containment assy (top

containment assembly corresponds to the gas end of the Accumulator)

82970085-003 and 81195109-101 “FLUID” to the bottom containment assy

(for 100 or 300 series refer to applicable instructions in AMM 20-22-09. For 200

series refer to applicable instructions in AMM TASK 20-22-09-400-801).

(c) Install Accumulator p/n 08-60162-002 with containment assembly on new

mounting brackets. Tighten clamp bolts to run-down torque from 15 to 25

in/lbs make sure the Accumulator serial number and the two labels “GAS” and

“FLUID” face FORWARD.

(d) Make sure that no less than 0.250 inch clearance is maintained between

adjacent structure and the top and bottom containment devices. Adjust if

required. Refer to dwg 8Z6855 sht 2 “VIEW LOOKING AFT ON RHS AT

X=445.500”, Zone G10 and Figure 1.

(e) Torque tighten each band clamp screw to 40 to 50 inch pounds.

NOTE: If required laminated shims p/n CSP469C-200-075 can be installed

between containment assy and top bracket 82970090-003 to provide

more support to the Accumulator (refer to dwg 8Z6855 sht 2 VIEW K-K as

shown).

(8) Install new tube assy as follows:

(a) Remove blanking caps then install tube assy p/n 82920010-389 to reducer

AN919-10D located at the fluid port of the Accumulator (bottom) and to fitting

82970032, refer to DWG 8Z6855 sht 2 “VIEW LOOKING AFT ON RHS AT

X=445.500” with flagnote 9 .

(b) For aircraft that are PreMod 8/2463 (charging valve sitting on bracket p/n

85350994) re-install charging valve onto bracket 85351008 using existing

bolts NAS 5903-8 (qty 4) and washers AN960D10L (qty 4), refer to dwg

8Z6855 sht 2 SECTION H-H.

(c) Remove blanking caps then install tube assy p/n 82920010-391 to the gas

side of the Accumulator and to the charging valve 8SC0137/G4304.

(d) Install clamps MS21919WDE3 and MS21919WDE4 to new tube assembles

and secure using screw NAS1801-3-8 and related hardware, refer to dwg

8Z6855 sht 2 SECTION H-H and “VIEW LOOKING AFT ON RHS AT

X=445.500” with flagnote 9 .

NOTE: Make sure prior to tightening clamps MS21919WDE3 and MS21919WDE4

with screw NAS1801-3-8 that you have edge distance clearance of pipes

to structure. If required, move clamps up or down to make sure you
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achieve required edge distance.

(9) Make sure that:

- all connections are secure and are torque tightened

- clamps are installed, secure and have no fouling conditions

- the Accumulator is facing in correct direction (labels and serial number facing

forward)

- a 0.250 inch clearance is maintained between adjacent structure and the top and

bottom containment devices. Adjust if required.

(10) Service the parking brake Accumulator with nitrogen. For 100 or 300 series

aircraft refer to applicable instructions in AMM chapter 12-10-32 part 9. For 200

series aircraft refer to applicable instructions in AMM TASK 12-14-00-614-801).

(11) Bleed the parking brake system. For 100 or 300 series aircraft refer to applicable

instructions in AMM 32-44-00. For 200 series aircraft refer to applicable

instructions in AMM TASK 32-44-00-870-801).

(12) Do a functional test of the parking brake system (for 100 or 300 series aircraft

refer to applicable instructions in AMM Chapter 32-44-00 para 3.

Adjustment/Test. For 200 series aircraft refer to applicable instructions in AMM

TASK 32-44-00-720-801).

(13) Do a systems leakage test. For 100 or 300 series aircraft refer to applicable

instructions in AMM Chapter 32-44-00 para 3B. Adjustment/Test. For 200 series

aircraft refer to applicable instructions in AMM TASK 32-44-00-790-801).

(14) Do a visual check for any signs of leakage at the rework site. Rectify as required.

C. Close Out

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

(2) Close the access panels 264DR and 262LT (refer to AMM 06-40-10).

(3) On incorporation of this Service Bulletin, make an entry that conforms to local

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

numbers if applicable. Enter numbers only after complete and functional

incorporation of all work defined in this service bulletin.
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Parking Brake Accumulator - Locator View

Figure 1

PARKING BRAKE

ACCUMULATOR

END CAP

END CAP

PARKING BRAKE

PRE MOD

(NO RETENTION DEVICE INSTALLED)

POST MOD

ACCUMULATOR

(RETENTION DEVICE INSTALLED)

RETENTION

DEVICE

(CONTAINMENT

ASSY)

RETENTION

(CONTAINMENT

ASSY)

DEVICE

VENDOR

LABEL

0.25 inch min
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This Page Intentionally Blank

3
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

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Company:

Phone: Extn:

Facsimile: Date:

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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