D

S.B. 8-32-177

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SERVICE BULLETIN

Customer

Support

ATA SYSTEM: 3261 NUMBER: 8-32-177

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 8Q101969

1. PLANNING INFORMATION

A. Effectivity

Aircraft Affected:

In-Service: DHC-8 Aircraft Models 102, 103 and 106 Serial Numbers 003

thru 099 that are Pre Mod 8/0534.

NOTE: Mod 8/0235 (SB 8-39-3) must be incorporated in aircraft serial numbers

003 thru 099 before incorporation of this service bulletin.

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 8-32-177

S.B. 8-32-177

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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 8Q101969.

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 in 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 (co-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

- the forward panel of the wardrobe is opened

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

- cable assemblies 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 8Q101969 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 8-32-177.

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.
SERVICE BULLETIN 8-32-177

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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(s) required to do this service bulletin are listed in the table below:

Operators should submit a purchase order through the Customer Accounts Service

Team (CAST) at Bombardier Aerospace Regional Aircraft division 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

Facsimile:

International: (416) 375-3334

European: (416) 373-5966

Americas East: (416) 373-5964

Americas West: (416) 373-5965
SERVICE BULLETIN 8-32-177

S.B. 8-32-177

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Telephone:

International: (416) 375-3706

European: (416) 373-3704

Americas East: (416) 375-3700

Americas West: (416) 373-5888

E-mail addresses:

International: cast.international@aero.bombardier.com

European: cast.europe@aero.bombardier.com

Americas East: cast.americaseast@aero.bombardier.com

Americas West: cast.americaswest@aero.bombardier.com

Kit Number Description

8MK4657-001/-003 Kit - Redesign of EDIS to Eliminate

Possibility of False Indication

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

Kit - 8MK4657-001

(Pre Mods 8/0461 & 8/1485)

+2.37 183.19 +0.43

DHC-8 Model 102, 103 & 106

Kit - 8MK4657-001

(Pre Mod 8/0461 & Post Mod 8/1485)

+2.51 184.05 +0.46

DHC-8 Model 102, 103 & 106

Kit - 8MK4657-003

(Post Mod 8/0461 & Pre Mod 8/1485)

+2.32 183.19 +0.43

DHC-8 Model 102, 103 & 106

Kit - 8MK4657-003

(Post Mods 8/0461 & 8/1485)

+2.45 184.08 +0.45
SERVICE BULLETIN 8-32-177

S.B. 8-32-177

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J. Electrical Load Data

1. Direct Current (DC) Load Change

Item Equipment Bus Bus Code Load Operating

Condition

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

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 .......................

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

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

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

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

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

Modifications Manual PSM 1-813-12 ...............................
SERVICE BULLETIN 8-32-177

S.B. 8-32-177

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L. References

Initial issue of this service bulletin was prepared to the engineering drawings and

related data that follows:

DRAWING SHEET REV

8MK4657 1 --

8Z9479 1 A

8Z8602 1 A

8Z6007 1 A

8Z6007 2 A

8Z6007 3 --

8Z6007 4 --

8Z6007 5 --

8Z6007 6 --

8Z6007 7 --

8Z6007 8 A

8Z6007 9 --

8Z6007 10 --

ModSum 8Q101969 Rev. ‘B’

PCA 07276 Revision 0 (for internal reference only)

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 8-32-177

S.B. 8-32-177

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2. MATERIAL INFORMATION

A. Parts Required Per Aircraft

(1) Modification Kit 8MK4657-001 for aircraft Pre Mod 8/0461,

(2) Modification Kit 8MK4657-003 for aircraft Post Mod 8/0461

(3) Detailed Kit Content:

Quantity Per Kit

-003 -001

Part Number Description Remarks

1 CSP255-3262-P4B LABEL

1 CSP255-3262-P4 LABEL

1 CSP255-3262-J4A LABEL

1 82411123-101 BRACKET

2 2 NAS1801-3-16 SCREW

2 2 CSP192-6-00 WASHER

2 2 M7885/6-4-2 RIVET

2 2 B0816031-002 TIE MOUNT

3 3 B0205016AD4-4S RIVET

1 82411127-101 BRACKET

1 1 B0816035AA3N TIE MOUNT

2 2 NAS1149D0363J WASHER

4 4 NAS1149D0316J WASHER

2 2 MS35650-302 NUT

2 2 MS35338-43 LOCK WASHER

500 500 MS3367-1-9 TIE WRAP

2 2 MS21042L2 NUT SELF LOCK

2 2 NAS1801-3-10 SCREW

1 1 25-1195-122 FILTER

1 1 CSP255-3262-K10 LABEL see Note 1

1 CSP255-3262-P3B LABEL

1 CSP255-3262-P3 LABEL

1 CSP255-3262-J3A LABEL

1 1 CSP255-3262-GS1 LABEL

1 1 CSP255-3262-GS2 LABEL
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Quantity Per Kit

-003 -001

Part Number Description Remarks

1 1 Y-D4N RELAY see Note 1

1 1 MS24523-33 SWITCH

1 1 8Z6007-015 CABLE ASSEMBLY see Note 1

1 1 8Z6007-013 CABLE ASSEMBLY

1 8Z6007-051 RELAY ASSEMBLY

1 8Z6007-053 RELAY ASSEMBLY

REF 8Z8602 DRAWING

REF 8Z9479 DRAWING

REF REF 8Z6007 DRAWING

NOTE 1: For aircraft Post Mod 8/1485

Listed drawings that are required to complete the kits above can be requested by

writing to the following e-mail address:

qseriesdwgrequest@aero.bombardier.com

(4) 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)

DHMS C4.04

(F24)

As Required Enamel, Polyurethane
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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 8Z9479-001

(Pre-Mod 8/0461)

R

85311889 Web, RH Upper

Bulkhead

1 C RWK 8Z8602-001

(Post-Mod 8/0461)

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.
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S.B. 8-32-177

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S Superseding or equivalent part number.

X Reworked part and superseding part are functionally and physically

equivalent but not identical.

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 8-32-177.

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,

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) Remove panel from wardrobe for access to Relay Panel No. 1.

(11) 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 AMM Chapter 25-40-01).

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 drawing 8Z8602.

(2) For aircraft post mod 8/0461, install bracket 82411123-101 to bulkhead using 3

rivets B0205016AD4-4S and prepare two existing tooling holes (for ground

studs), refer to drawing 8Z8602.

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

(4) For aircraft pre mod 8/0461, install bracket 82411127-101 to bulkhead using 3

rivets B0205016AD4-4S and prepare two existing tooling holes (for ground

studs), refer to drawing 8Z9479.

(5) Make sure to re-identify web 85311889 as 8Z9479-001.

(6) 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, refer to drawing 8Z6007 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.

(7) Install cable assembly 8Z6007-013 as follows: (refer to drawing 8Z6007 sheets 3

and 10)

(a) Open the Landing Gear Alternate Extension Door.

(b) Loosen and remove locknuts securing emergency gear downlock indicator

light control toggle switch assembly, refer to drawing 8Z6007 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 8Z6007-013 and reterminate existing wires, refer

to drawing 8Z6007 sheet 3.

(8) For aircraft with post mod 8/1485 install new cable assembly 8Z6007-015, refer

to drawing 8Z6007 sheets 3 and 10.

(9) For aircraft with pre mod 8/0461, install relay assembly 8Z6007-051 as follows:

(a) Install relay assembly 8Z6007-051 to the terminal block panel, refer to drawing

8Z6007 sheet 7.
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(b) Gain access to the rework area on the upper right hand corner of bulkhead at

Station X182.00, refer to drawing 8Z6007 sheet 7.

(c) Remove hardware and clamps used to secure existing cable assembly to the

terminal block panel, refer to 8Z6007 sheet 7.

(d) Set relay bracket 82411122-101 on the terminal block as shown on 8Z6007

sheet 7. Rotate clamps and move the cable assembly as described in flagnote

7.

(e) 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.

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

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

(g) Assemble and install new cable assembly 8Z6007-011, refer to drawing

8Z6007 sheet 2 & 7.

(h) Secure all electrical connections.

(i) Apply the identification labels where applicable, refer to drawing 8Z6007

sheet 7.

(j) Secure ground wires the two ground studs, refer to drawing 8Z6007 sheet 7.

(k) Install tie mount B081635AA3N in the noted area on drawing 8Z6007 sheet 7.

(10) For aircraft with post mod 8/0461, install relay assembly 8Z6007-053 as follows:

(a) Install relay assembly 8Z6007-053 to the terminal block panel, refer to drawing

8Z6007 sheet 9.

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

Station X182.00, refer to drawing 8Z6007 sheet 9.

(c) Remove hardware and clamps used to secure existing cable assembly to the

terminal block panel, refer to 8Z6007 sheet 9.

(d) Set relay bracket 82411122-101 on the terminal block as shown on 8Z6007

sheet 9. Rotate clamps and move the cable assembly as described in flagnote

7.

(e) 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.

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

relay bracket 82411122-101 and clamps to the terminal block panel.
SERVICE BULLETIN 8-32-177

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(g) Assemble and install new cable assembly 8Z6007-017, refer to drawing

8Z6007 sheet 8 & 9.

(h) Secure all electrical connections.

(i) Apply the identification labels where applicable, refer to drawing 8Z6007

sheet 9.

(j) Secure ground wires the two ground studs, refer to drawing 8Z6007 sheet 9.

(k) Install tie mount B081635AA3N in the noted area on drawing 8Z6007 sheet 9.

(11) Re-install relay panel No. 1.

(12) Do a continuity check with an Ohmmeter to verify compliance with the

schematic wiring view shown on drawing 8Z6007 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
SERVICE BULLETIN 8-32-177

S.B. 8-32-177

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

bent pins and corrosion. Correct the deficiency.

(13) 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.

(14) Do the Functional Test Procedure of the Alternate Gear Indication Fault

Monitoring system, refer to drawing 8Z6007 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 Chapter

25-40-01.

(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

Under ‘Description of Change’ enter “ModSum 8Q101969 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.
SERVICE BULLETIN 8-32-177

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This Page Intentionally Blank

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:

syed.rizvi@aero.bombardier.com