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 Effectivitysection is revised to include all DHC-8 aircraft s/n’s (003 thru 672). Was limited to only s/n 342. - theReasonsection 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” - theCompliancesection is revised to include a new “NOTE” - theReferencessection is revised to convey the latest revision of this service bulletin - theJob Set-Upsection is revised to make an editorial change. Was “sht”, now “sheet”- theProceduresection 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

S.B. 8-32-176

Page 1 of 16 11 Feb 2013 LS Revision ‘A’ 22 Feb 2013 

# 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

S.B. 8-32-176 Page 2 of 16 11 Feb 2013 LS Revision ‘A’ 22 Feb 2013 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 andAuxiliary 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

### SERVICE BULLETIN 8-32-176

S.B. 8-32-176 Page 3 of 16 11 Feb 2013 LS Revision ‘A’ 22 Feb 2013 - 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

S.B. 8-32-176 Page 4 of 16 11 Feb 2013 LS Revision ‘A’ 22 Feb 2013 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

### SERVICE BULLETIN 8-32-176

S.B. 8-32-176 Page 5 of 16 11 Feb 2013 LS Revision ‘A’ 22 Feb 2013 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

S.B. 8-32-176 Page 6 of 16 11 Feb 2013 LS Revision ‘A’ 22 Feb 2013 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

S.B. 8-32-176 Page 7 of 16 11 Feb 2013 LS Revision ‘A’ 22 Feb 2013 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

S.B. 8-32-176 Page 8 of 16 11 Feb 2013 LS Revision ‘A’ 22 Feb 2013 2. MATERIALINFORMATION
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

### SERVICE BULLETIN 8-32-176

S.B. 8-32-176 Page 9 of 16 11 Feb 2013 LS Revision ‘A’ 22 Feb 2013 Quantity Per Kit -001 Remarks Description Part Number

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)

### SERVICE BULLETIN 8-32-176

S.B. 8-32-176 Page 10 of 16 11 Feb 2013 LS Revision ‘A’ 22 Feb 2013 Part Number Remarks Description Qty. Per Aircraft 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.

### SERVICE BULLETIN 8-32-176

S.B. 8-32-176 Page 11 of 16 11 Feb 2013 LS Revision ‘A’ 22 Feb 2013 3. ACCOMPLISHMENTINSTRUCTIONS 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 connectorfrom 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.

### SERVICE BULLETIN 8-32-176

S.B. 8-32-176 Page 12 of 16 11 Feb 2013 LS Revision ‘A’ 22 Feb 2013 (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

### SERVICE BULLETIN 8-32-176

S.B. 8-32-176 Page 13 of 16 11 Feb 2013 LS Revision ‘A’ 22 Feb 2013 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

### SERVICE BULLETIN 8-32-176

S.B. 8-32-176 Page 14 of 16 11 Feb 2013 LS Revision ‘A’ 22 Feb 2013 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.

### SERVICE BULLETIN 8-32-176

S.B. 8-32-176 Page 15 of 16 11 Feb 2013 LS Revision ‘A’ 22 Feb 2013 (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 connectorto 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.

### SERVICE BULLETIN 8-32-176

S.B. 8-32-176 Page 16 of 16 11 Feb 2013 LS Revision ‘A’ 22 Feb 2013 (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. 1Jan 2009 SERVICE BULLETIN (SB) --- RECORD OF INCORPORATION --- Q SERIES DASH 8 AIRCRAFT To: CMDB Focal Facsimile: (1) 416 375 4538 E --mail: cmdb.requests@aero.bombardier.com
From: Company: Phone: Extn: Facsimile: Date:

E --mail: The data that you provide below will help us record the incorporation of this ModSum and the aircraft effectivity in the maintenance manual. Operator: Service Bulletin:

__________________Revision:

_________ Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: 

## Fax this sheet to (1) 416 375 4538 or Email PDF to: 

# cmdb.requests@aero.bombardier.comFeb 2009 SERVICE BULLETIN (SB) --- COMMENT SHEET --- Q SERIES DASH 8 AIRCRAFT

To: SB Focal (Toronto), Bombardier Aerospace Commercial Aircraft Phone: (1) 416 375 4078 Facsimile: (1) 416 375 4538 E --mail: syed.rizvi@aero.bombardier.com
From: Company: Phone: Extn: Facsimile: Date:

E --mail: Select appropriate box(es) and add comments or suggestions you would like us to know that may enhance the quality of our service bulletins. Service Bulletin: Revision: ModSum: 1. PLANNING INFORMATION V Effectivity V Reason V Description VCompliance VApproval V Manpower V Material VWeight and Balance V Electrical Load VTooling V References V Publications Affected
2. MATERIAL INFORMATION V Kit Content VSpecial Tools/Equipment V Parts to Modify Spares V Consumables V Disposition of Existing Parts VOther
3. ACCOMPLISHMENT INSTRUCTIONS VJob Set ---Up V Procedure V Close---Out VTest V Illustration(s) V Other 4. COMMENTS, REMARKS, SUGGESTIONS



## Fax this sheet to (1) 416 375 4538 or Email PDF to: syed.rizvi@aero.bombardier.com