Revision ‘A’ 22 Feb 2013

DHC-8 (DASH 8)

SERVICE BULLETIN 8-32-176

Landing Gear - Alternate Downlock Indication System - Introduction of

Fault Monitoring Circuit to Eliminate Possibility of False Indication -

ModSum 8Q101955

NOTE: The initial issue of this service bulletin is not posted on RACS and was

issued to one customer for “release to service” of verification aircraft

serial number 342.

This page transmits Revision ‘A’ of Service Bulletin 8-32-176, pages 1 thru

16 dated 22 Feb 2013.

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

- the In-Service part of the Effectivity section is revised to include all DHC-8

aircraft s/n’s (003 thru 672). Was limited to only s/n 342.

- the Reason section is revised to make an editorial change in the Cause section.

Was “EDI”, now “EDIS” and provided additional information in the Solution

section.

- the Description section is revised to make spelling correction. Was “fight”,

now “flight”

- the Compliance section is revised to include a new “NOTE”

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

bulletin

- the Job Set-Up section is revised to make an editorial change.

Was “sht”, now “sheet”
- the Procedure section is revised to make a few editorial changes that follow

in various steps:

Was “Connect / terminate”, now “Connect and/or terminate”

Was “sht”, now “sheet”

Was “a” now “an”

Was “turn”, now “rotate”

step (5) is deleted

step (6) is revised to provide details on how to do a continuity check and

provide a maximum resistance limit.

The Compliance in the previous issue(s) of this service bulletin is not affected by

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

Remove the initial issue of Service Bulletin 8-32-176 and replace with attached.

Previous issue(s) of Service Bulletin 8-32-176:

Initial issue - Pages 1 thru 16 dated 11 Feb 2013
D

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SERVICE BULLETIN

Customer

Support

ATA SYSTEM: 3261 NUMBER: 8-32-176

BOMBARDIER AEROSPACE REGIONAL AIRCRAFT CONSIDER THIS

SERVICE BULLETIN TO BE PARTICULARLY SIGNIFICANT AND

URGES OPERATORS TO PROMPTLY EVALUATE THE CONTENTS

SUBJECT: Landing Gear - Alternate Downlock Indication System - Introduction

of Fault Monitoring Circuit to Eliminate Possibility of False Indication

- ModSum 8Q101955

1. PLANNING INFORMATION

A. Effectivity

Aircraft Affected:

In-Service: DHC-8 Aircraft Models 102, 103, 106, 201, 202, 301, 311, 314

and 315 Serial Numbers 003 thru 672 with Mod 8/0235,

8/0461 and 8/0534 installed.

Verification: ModSum 8Q101955 has been installed on DHC-8 Aircraft

Model 311 Serial Number 342.

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
SERVICE BULLETIN 8-32-176

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B. Reason

Problem: One operator has recently experienced an incident and reported that the

emergency downlock indication system (EDIS) had given a false “down

and locked” indication when the landing gear was not downlocked.

Cause: Analysis of the EDIS indicates that a false indiction, regardless of the

condition of the landing gear, can be caused by a failure of the

photo-transistors or wiring, or the presence of scattered ambient light.

Solution: This service bulletin introduces ModSum 8Q101955.

The ModSum introduces a fault monitoring circuit to the EDIS. When the

EDIS is in the normally off position and the aircraft is in the air, relays

monitor each channel. When a ground signal that would provide a false

locked down indication is detected by the relay, after a few seconds

another relay is latched to turn on a new caution light and inhibit the

affected EDIS channel from illuminating.

A WOW signal and time delay relay is used to enable the fault monitoring

circuit only when the aircraft is the air, such that landing gear transition

conditions and scattered light from ground mounted light sources are not

falsely annunciated as faults.

An intermediate relay/diode/resistor panel assembly is introduced to be

put in between the EDIS and the aircraft wiring. The existing EDIS switch

is replaced with p/n MS24523-33. A new connection to the caution and

warning panel is added for indication, and another connection is made to

the relay panel for the WOW signal.

C. Description

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

follow:

- the aircraft electrical system is de-energized

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

- the nose gear ground lock is engaged

- the terminal connector from the Main and Auxiliary batteries are disconnected

- flight compartment ceiling panels (pilots side) and overhead console instruments

are removed for access to the annunciator (caution and warning) panel cable

assemblies

- front lower access panel 122BR is removed
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- the forward panel of the wardrobe is opened

- access is gained to the relay panel No. 1, 2 and 3 as applicable

- relay panels are released (as required) to provide access to the wiring and relay

base plates

- the lavatory is removed to gain access to aft side of co-pilot bulkhead

- a connector bracket p/n 82411123-101 is installed to bulkhead

- two existing tooling holes are prepared for ground stud installation

- the flight compartment center floor panel is removed

- the existing filter at position 55 on the Annunciator Panel is replace with filter p/n

25-1195-122

- cable assemblies 8Z9678-011, -013 and -015 (post mod 8/1485 100 series only) are

installed

- existing wiring is reterminated as required

- relay panel No. 1 is re-attached

- continuity check of the wiring is done

- the battery terminal connector is re-connected to the Main and Auxiliary battery

- functional test procedure is completed

- the lavatory is installed

- all access panels, floor panels, overhead console and ceiling panels are re-installed

and closed

- close out.

D. Compliance

Bombardier Inc. highly recommend that ModSum 8Q101955 be incorporated at

the earliest opportunity unless otherwise directed by the operator’s airworthiness

authority.

A Transport Canada Airworthiness Directive is Pending.

NOTE: Do Service Bulletin 8-32-173 (Landing Gear - Special Inspection and

Rectification - Alternate Downlock Indication System) before

commencing this modification to ensure there are no dormant faults

with ALT IND SYS which otherwise delay the incorporation of this

Service Bulletin 8-32-176.
SERVICE BULLETIN 8-32-176

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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 40 man-hours to complete this service bulletin. The

breakdown of the man-hours is shown in the table that follows:

TASK MAN-HOURS

Job Set-Up 18.00

Procedure 10.00

Test/RTS 2.00

Close-Out 10.00

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

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

Help Desk by telephone at 416-375-4000 or email at:

thd.qseries@aero.bombardier.com

G. Material - Price and Availability

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

8MK4456-001 Kit - Redesign of EDIS to Eliminate

Possibility of False Indication
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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, 103 &

106

(Pre Mod 8/1485)

+2.10 182.40 +0.38

DHC-8 Model 102, 103 &

106

(Post Mod 8/1485)

+2.23 183.98 +0.41

DHC-8 Model 201 & 202 +2.10 182.40 +0.38

DHC-8 Model 301, 311,

314 & 315

+2.10 109.40 +0.23

J. Electrical Load Data

1. Direct Current (DC) Load Change

Item Equipment Bus Bus Code Load Operating

Condition

32D1 NLG ADI

FLR MNT

RLY (0.16)

28 V DC Right

Essential Bus

H2 +0.00 Amps N/A

32D2 LMLG ADI

FLR MNT

RLY (0.16)

28 V DC Right

Essential Bus

H2 +0.00 Amps N/A

32D3 RMLG ADI

FLR MNT

RLY (0.16)

28 V DC Right

Essential Bus

H2 +0.00 Amps N/A
SERVICE BULLETIN 8-32-176

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2. Alternating Current (AC) Load Change

Item Equipment Bus Bus

Code

Phase VA PF Load Operating

Conditions

N/A N/A N/A N/A N/A N/A N/A N/A N/A

K. Publications Affected

Aircraft Operating Data Manual PSM 1-81-1 and .......................

PSM 1-82-1 and

PSM 1-83-1

Flight Manual PSM 1-81-1A and ......................................

PSM 1-82-1A and

PSM 1-83-1A

PSM 1-82-1B and

PSM 1-83-1B

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

PSM 1-82-2 and

PSM 1-83-2

Wiring Diagrams Manual PSM 1-8-2W and ............................

PSM 1-82-2W and

PSM 1-83-2W

Weight and Balance Manuals PSM 1-8-8 and ........................

PSM 1-82-8 and

PSM 1-83-8

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

PSM 1-82-4 and

PSM 1-83-4

Modifications Manual PSM 1-813-12 ...............................
SERVICE BULLETIN 8-32-176

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L. References

Revision ‘A’ of this service bulletin was prepared to the engineering drawings and

related data that follows:

DRAWING SHEET REV

8MK4456 1 B

8Z8602 1 --

8Z9678 1 F

8Z9678 2 A

8Z9678 3 A

8Z9678 4 --

8Z9678 5 B

8Z9678 6 --

8Z9678 7 B

82411123 1 --

82411122 1 --

ModSum 8Q101955 Rev. ‘H’

PCA 06824 Revision 1 (for internal reference only)

Transport Canada Airworthiness Directive Pending

Bombardier Inc. Modification 8/0235 (Service Bulletin 8-39-03)

Bombardier Inc. Modification 8/0534 (Service Bulletin 8-32-41 Rev. A)

Bombardier Inc. Modification 8/0461 and 8/0820 (Service Bulletin 8-32-42 Rev. A)

Bombardier Inc. Service Bulletin 8-32-173

A Transport Canada Airworthiness Directive is Pending.
SERVICE BULLETIN 8-32-176

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2. MATERIAL INFORMATION

A. Parts Required Per Aircraft

(1) Modification Kit 8MK4456-001

(2) Detailed Kit Content:

Quantity Per Kit

-001

Part Number Description Remarks

2 NAS1801-3-16 Screw

2 CSP192-6-00 Washer

2 M7885/6-4-2 Rivet

2 B0816031-002 Tie Mount or Click Bond

CB3019AA3N

3 B0205016AD4-4S Rivet

1 8Z8602 Drawing-EDIS

Bracket Instln

Drawing Only

1 82411123 Drawing-EDIS

Conn Bracket

Drawing Only

1 82411123-101 Bracket

1 82411122 Drawing-EDIS

Relay Bracket

Drawing Only

1 B0816035AA3N Tie Mount or Click Bond

CB3019AA3N

2 NAS1149D0363J Washer

4 NAS1149D0316J Washer

2 MS35650-302 Nut

2 MS35338-43 Lock Washer

500 MS3367-1-9 Tie Wrap Quantity may

be surplus to

account for

losses

2 MS21042L3 Nut, Self Locking

2 NAS1801-3-10 Screw

1 25-1195-122 Filter
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Quantity Per Kit

-001

Part Number Description Remarks

1 CSP255-3261-K10 Label For A/C Post

Mod 8/1485

1 CSP255-3262-P4B Label

1 CSP255-3262-P4 Label

1 CSP255-3262-J4A Label

1 CSP255-3262-GS1 Label

1 CSP255-3262-GS2 Label

1 SO-1066-001 Relay Base For A/C Post

Mod 8/1485

1 Y-D4N Relay For A/C Post

Mod 8/1485

1 MS24523-33 Switch

1 8Z9678-015 Cable Assembly For A/C Post

Mod 8/1485

1 8Z9678-013 Cable Assembly

1 8Z9678-051 Relay Assembly

1 8Z9678 Drawing-EDIS

Wiring

Drawing Only

(3) 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

MIL-C-5541 1/2 Quart Alodine 1200 C1 - Chemical Conversion Coating

DHMS C4.01 As Required Epoxy Primer Type 2

(F19)
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Part Number Remarks Qty. Per Aircraft Description

DHMS C4.04

(F24)

As Required Enamel, Polyurethane

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

85311889 Web, RH Upper

Bulkhead

1 C RWK 8Z8602-001 R

MS24523-24 Switch 1 B DIS MS24523-33 N

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 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 or equivalent part number.

X Reworked part and superseding part are functionally and physically

equivalent but not identical.
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3. ACCOMPLISHMENT INSTRUCTIONS

NOTE: Do Service Bulletin 8-32-173 (Landing Gear - Special Inspection and

Rectification - Alternate Downlock Indication System) before

commencing this modification to ensure there are no dormant faults

with ALT IND SYS which otherwise delay the incorporation of this

Service Bulletin 8-32-176.

A. Job Set-Up

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

WARNINGS and CAUTIONS detailed in Maintenance Manual PSM 1-8-2, 1-82-2

or 1-83-2 Chapters 12 and 24.

(2) Make sure that lock pins are installed through each main gear and main gear

door mechanism.

(3) Make sure the nose gear ground lock is engaged.

(4) Remove access panel 122BR from the front lower fuselage - right side.

(5) Disconnect the terminal connector from the Main and Auxiliary battery.

(6) Remove the flight compartment Co-Pilot’s ceiling panel.

(7) Remove flight compartment overhead console instruments as required to gain

access to annunciator (caution and warning) panel cable assemblies.

(8) Remove the flight compartment center floor panel.

(9) Open Landing Gear Alternate Extension Door.

(10) For Dash 8 Series 100 and 200, remove panel from wardrobe for access to

Relay Panel No. 1. For Dash 8 Series 300, remove panels from the wardrobe to

gain access to relay panels No. 3 (refer to drawing 8Z9678 sheet 6 for applicable

relay panel location).

(11) For Dash 8 Series 100 and 200, remove and keep fasteners securing relay panel

No. 1. Pull panel out far enough to gain access to the wiring and relay base

plates. Support and hang the relay panel temporarily with a tie wrap or

equivalent.
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(12) Remove the lavatory (refer to applicable instructions in PSM 1-8-2 or 1-83-2

Chapter 25-40-01 or PSM 1-82-2 TASK 25-41-05-000-801 or TASK

25-41-07-000-801).

B. Procedure

(1) Gain access to the aft side upper right hand corner of the co-pilots bulkhead

web at Station X182.00 (refer to dwg 8Z8602).

(2) Install bracket 82411123-101 to bulkhead using 3 rivets B0205016AD4-4S and

prepare two existing tooling holes (for ground studs) to agree with all of the

Notes and detail views given on drawing 8Z8602. Make sure to treat newly

opened hole edges with alodine and apply a layer of epoxy primer or

polyurethane enamel as directed per flagnotes 4 & 5 .

(3) Make sure to re-identify the web 85311889 as 8Z8602-001.

(4) Gain access to the Annunciator Panel. Remove the existing filter at position 55

of the panel and replace with filter P/N 25-1195-122 to agree with all of the Notes

and detail views given on the drawing 8Z9678 sheet 1 view labeled VIEW ON

ANNUNCIATOR PANEL.

NOTE: To change the filter in the module, pop out filter in position 55 from the

back. Apply a small drop of Loctite 430 to the back of each corner of the

new filter and secure in space position 55.

(5) Deleted

(6) Install Cable Assembly 8Z9678-011 as follows:

(a) Gain access to the rework area on the upper right hand corner of bulkhead at

Station X182.00 (refer to drawing 8Z9678 sheets 5 & 7 for location).

(b) Remove hardware and clamps (qty 3) used to secure existing cable assembly
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to the terminal block panel (refer to 8Z9678 sheet 5 view A and flagnote 7

for location).

(c) Set relay bracket 82411122-101 on the terminal block as shown on 8Z9678

sheet 5 view A. Rotate clamps and move the cable assembly as described in

flagnote 7 and 8 .

(d) Align mounting holes in relay bracket 82411122-101 and clamps with the

mounting holes in the terminal block panel. Make sure the wire looms are

facing outboard to the aircraft and the clamps and cable assembly are

positioned per step above.

(e) Using kept hardware and a washers CSP192-6-00 under each clamp secure

relay bracket 82411122-101 and clamps to the terminal block panel.

(f) Install the relay assembly 8Z9678-051 to the terminal block panel (refer to

drawing 8Z9678 sheet 7 DETAIL EB).

(g) Assemble and install new cable assembly 8Z9678-011 to agree with all the

notes and views on drawing 8Z9678 sheet 2, 5 & 7.

(h) Secure all electrical connections.

(i) Apply the identification labels where applicable (refer to applicable NOTES

and detail view on drawing 8Z9678 sheet 1 (flagnotes 4 and 5 ), sheet

2 & 7).

(j) Secure ground wires the two ground studs (refer to drawing 8Z9678 sheet 7

DETAIL VIEW EA).

(k) Install tie mount (click bond fastener) B081635AA3N in the noted area on

drawing 8Z9678 sheet 7 FN 66.

(7) Install Cable Assembly 8Z9678-013 as follows:

(a) Open the Landing Gear Alternate Extension Door.

(b) Loosen and remove locknuts securing emergency gear downlock indicator
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light control toggle switch assembly (refer to drawing 8Z9678 sheet 4 detail

VIEW E for location)..

(c) Disconnect wires from existing switch for retermination. Remove and discard

the existing switch MS24523-24.

(d) Install the new switch MS24523-33 (3262-S1).

(e) Install new cable assembly 8Z9678-013 and reterminate existing wires to

agree with all of the Notes and detail views given on drawing 8Z9678 sheet 3 &

6.

(f) If additional workspace is required remove LRU’s from the upper section of

the wardrobe.

NOTE: Cable Assembly 8Z9678-015 is for aircraft with post Mod 8/1485

only.

(8) For aircraft with post Mod 8/1485, install new cable assembly 8Z9678-015 to

agree with all of the Notes and detail views given in drawing 8Z9678 sheet 3.

(9) Re-install the relay panel No. 1.
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(10) Do a continuity check of the new and the existing wires shown on drawing

8Z9678 sheet 2 & 3 as follows:

(a) Connect the negative (-) lead of an ohmmeter to one end of a wire to be tested

and the positive lead (+) of the ohmmeter to the opposite end of the same

wire.

(b) For long distance checking of a wire connect one end of a wire to be tested to

the positive lead (+) of an ohmmeter and the other end of the wire to a ground

point with a jumper wire. Connect the negative lead (-) of the ohmmeter to the

same ground point.

(c) A complete circuit (or closed circuit) from point to point must exist through

each wire. The maximum resistance permitted between the two points in a

closed circuit is 5 ohms.

NOTE: Continuity of a circuit is affected when a diode is part of a circuit. When

checking continuity across a diode the electrical polarity must be

observed.

Continuity of a circuit is affected when a resistor is part of a circuit. When

checking continuity across a resistor the value of the resistor must be

observed as follows:

R10, R20 & R30 are 510 ohms +/- 10% each

R11, R12 & R13 are 500K ohms +/- 10% each

R40 is 820K ohms +/- 10%.

Continuity of a circuit is also affected when a circuit contains computer

controllers, valves, relays, coils, circuit breakers, etc. Temporarily

disconnect or remove all the electrical components connected to the

wires to be tested. Reconnect components after testing.

(d) If the resistance exceeds 5 ohms from point to point (open circuit) recheck the

new and reworked wiring to make sure it is terminated to the correct

connection, check the wiring for mechanical damage, loose connector parts,

bent pins and corrosion. Correct the deficiency.

(11) Connect the battery terminal connector to the Main and Auxiliary battery. Make

sure to safety the battery terminal connector with copper lockwire.

CAUTION: DO NOT APPLY HYDRAULIC POWER DURING THIS FUNCTIONAL

TEST.
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(12) Do the Functional Test Procedure of the Alternate Gear Indication Fault

Monitoring system (refer to drawing 8Z9678 sheet 1).

C. Close Out

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

(2) Install the lavatory (refer to applicable instructions in PSM 1-8-2 or 1-83-2

Chapter 25-40-01 or PSM 1-82-2 TASK 25-41-05-400-801 or TASK

25-41-07-400-801).

(3) Re-install LRU’s that were previously removed from the upper wardrobe to agree

with applicable instructions in the AMM.

(4) Re-install flight compartment center floor panels and cockpit ceiling panel.

(5) Install all access panels and the overhead console that were previously removed

or opened to do the tasks.

(6) On incorporation of this ModSum add the weight and balance data shown in

Section 1 of this service bulletin to the Weight and Balance Manual PSM 1-8-8 or

PSM 1-82-8 or PSM 1-83-8 or PSM 1-84-8. Under ‘Description of Change’ enter

“ModSum 8Q101955 incorporated.”

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

regulatory requirements in the applicable logbook(s). If only part of this

ModSum is completed, use only this service bulletin number as reference and

detail exact limit of work completed. Enter component serial numbers if

applicable. Enter this ModSum number only after complete and functional

incorporation of all work defined in this service bulletin.

1
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:

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