# D

S.B. 8-32-177

Page 1 of 16 09 Oct 2013 JR 

# 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. PLANNINGINFORMATION 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 Page 2 of 16 09 Oct 2013 JR 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 groundsignal 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 andAuxiliary 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

### SERVICE BULLETIN 8-32-177

S.B. 8-32-177 Page 3 of 16 09 Oct 2013 JR - 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

S.B. 8-32-177 Page 4 of 16 09 Oct 2013 JR 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 Page 5 of 16 09 Oct 2013 JR 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 Page 6 of 16 09 Oct 2013 JR 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 Page 7 of 16 09 Oct 2013 JR 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 Page 8 of 16 09 Oct 2013 JR 2. MATERIALINFORMATION 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

### SERVICE BULLETIN 8-32-177

S.B. 8-32-177 Page 9 of 16 09 Oct 2013 JR Quantity Per Kit -003 -001 Remarks Description Part Number

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

### SERVICE BULLETIN 8-32-177

S.B. 8-32-177 Page 10 of 16 09 Oct 2013 JR 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.

### SERVICE BULLETIN 8-32-177

S.B. 8-32-177 Page 11 of 16 09 Oct 2013 JR S Superseding or equivalent part number. X Reworked part and superseding part are functionally and physically equivalent but not identical. 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 8-32-177.
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 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) 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.

### SERVICE BULLETIN 8-32-177

S.B. 8-32-177 Page 12 of 16 09 Oct 2013 JR (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 8Z6007-013and 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.

### SERVICE BULLETIN 8-32-177

S.B. 8-32-177 Page 13 of 16 09 Oct 2013 JR (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

S.B. 8-32-177 Page 14 of 16 09 Oct 2013 JR (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 Page 15 of 16 09 Oct 2013 JR connection, check the wiring for mechanical damage, loose connector parts, bent pins and corrosion. Correct the deficiency. (13) 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. (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

S.B. 8-32-177 Page 16 of 16 09 Oct 2013 JR 

### This Page Intentionally Blank 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 VReason V Description VCompliance VApproval VManpower VMaterial VWeight and Balance V Electrical Load VTooling VReferences VPublications Affected
2. MATERIAL INFORMATION V Kit Content VSpecial Tools/Equipment VParts to Modify Spares VConsumables VDisposition of Existing Parts VOther
3. ACCOMPLISHMENT INSTRUCTIONS VJob Set ---Up VProcedure VClose---Out VTest V Illustration(s) VOther 4. COMMENTS, REMARKS, SUGGESTIONS



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