Revision ‘A’ 02 Oct 2012 DHC-8 (DASH 8) SERVICE BULLETIN 84-32-99 Landing Gear, RH Nacelle, Parking Brake Hand Pump Lever Relocation from Nacelle to Nose Compartment - ModSum 4-113723 This page transmits Revision ‘A’ of Service Bulletin 84-32-99, pages 1 thru 20, dated 02 Oct 2012. This service bulletin is re-issued in its entirety for the reasons that follow:

- theReferencessection is revised to convey the latest revision of the service bulletin and engineering documentation

- theParts Required Per Aircraftsection is revised to delete material Part Number 05-01 and to add material Part Number 05-27

- Step (6)(c) in Proceduresection ofACCOMPLISHMENT INSTRUCTIONS part is revised as follows:

- changed adhesive, was EC 1300 now EC 1300L - changed manual reference, was AMM, PSM 1-84-3, Chapter 51-22-10 now SRM, PSM 1-84-3, Chapter 51-22-15. The Compliance in the previous issue of this service bulletin is not affected by this revision. No additional rework to the aircraft is introduced by this revision. Remove initial issue of Service Bulletin 84-32-99 and replace with attached. Previous issues of Service Bulletin 84-32-99: Initial issue - Pages 1 thru 20 dated 26 Jan 2012

# D

S.B. 84-32-99

Page 1 of 20 26 Jan 2012 NB Revision ‘A’ 02 Oct 2012 

# SERVICE BULLETIN Customer Support
ATA SYSTEM: 3200 NUMBER: 84-32-99 

### BOMBARDIER AEROSPACE REGIONAL AIRCRAFT CONSIDER THIS SERVICE BULLETIN TO BE PARTICULARLY SIGNIFICANT AND URGES OPERATORS TO PROMPTLY EVALUATE THE CONTENTS

SUBJECT: Landing Gear, RH Nacelle, Parking Brake Hand Pump Lever Relocation from Nacelle to Nose Compartment - ModSum 4-113723

1. PLANNING INFORMATION A. Effectivity Aircraft Affected: In-Service: DHC-8 Aircraft Models 401 and 402 Serial Numbers 4001, 4003 thru 4419 Production: ModSum 4-113723 will be installed before delivery on applicable DHC-8 Aircraft at Serial Number 4420 and subsequent. NOTE: The instructions in this service bulletin are only applicable to the systems and parts installed at the time of delivery on the aircraft or as changed by Bombardier Aerospace Service Bulletin(s). Before you do this bulletin, examine all STC or equivalent action changes to make sure this bulletin can be completed.

### SERVICE BULLETIN 84-32-99

S.B. 84-32-99 Page 2 of 20 26 Jan 2012 NB Revision ‘A’ 02 Oct 2012 Spares Affected: None B. Reason Problem: An operator had reported an incident which involved the migration of the main landing gear parking brake hand pump lever resulting in the damage of the nacelle side panels. During the incident, the parking brake pump lever located in the RH nacelle had dislodged from its mounting bracket and migrated down from the upper retaining collar and fell over inside the nacelle. Due to the unpredictable nature of an object migrating from its mounting position, the possibility exists that the pump lever could lodge itself into a position that would prevent the extension of the MLG or prevent the nacelle doors from opening or become runway F.O.D. Cause: The quick release pin used to secure the pump lever installation may not have been correctly installed, compromising the installation. If the quick release pin is not fully engaged, the potential exists for the pin to migrate out, disengaging, and allowing the pump lever to become dislodged from its installation position. Solution: ModSum 4-113723 relocates existing parking brake hand pump lever from RH nacelle to the flight deck web in the RH nose compartment. C. Description The procedures in this service bulletin give the instructions to do the tasks that follow: - aircraft is put into standard configuration for maintenance - aircraft electrical power is removed - the nose landing gear lock is engaged - the main landing gear lock pins are installed through each main gear and main gear door mechanism

### SERVICE BULLETIN 84-32-99

S.B. 84-32-99 Page 3 of 20 26 Jan 2012 NB Revision ‘A’ 02 Oct 2012 - quick release pin is depressed and parking brake hand pump lever is removed from existing RH nacelle location, retained for rework and re-installation in new location - existing nacelle cushion clamp assembly is cut off and sharp edges are deburred (mounting hardware is left in place) - a new metal label is installed to the RH nacelle wall - quick release pin assembly is removed and retained for re-installation in new location - existing rivet hole exposed surface is treated with alodine, primed with an epoxy chromate primer and existing rivet hole is then plugged as required - neoprene pad from existing bracket assembly is removed and discarded - quick release pin hole in the existing bracket 82974258 is opened from 0.253 to 0.263 inch diameter, the existing hole exposed surface is treated with alodine, primed with an epoxy chromate primer and existing hole is then plugged as required - new holes are drilled through the flight deck web for the installation of anchor nuts and for the installation of cushioned clamp assembly - new holes are treated with alodine and primed with an epoxy chromate primer - new bracket assembly and cushioned clamp assembly is installed to the flight deck web in the RH nose compartment - the retained quick release pin is installed to the new bracket assembly - a new hole is drilled through the pump lever at a new position, oriented 90 degree from existing hole - new holes in the pump lever are treated with alodine and primed with an epoxy chromate primer - a new bumper pad is glued with adhesive to the radome bulkhead - the reworked pump lever is installed to its new location and secured with quick release pin assembly - close out.

### SERVICE BULLETIN 84-32-99

S.B. 84-32-99 Page 4 of 20 26 Jan 2012 NB Revision ‘A’ 02 Oct 2012 D. Compliance Bombardier Inc. highly recommend that ModSum 4-113723 be incorporated at the earliest opportunity unless otherwise directed by the operator’s airworthiness authority. A Transport Canada Airworthiness Directive is Pending. 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 4.0 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 1.00 Procedure 2.00 Test / RTS 0.00 Close-Out 1.00 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.

### SERVICE BULLETIN 84-32-99

S.B. 84-32-99 Page 5 of 20 26 Jan 2012 NB Revision ‘A’ 02 Oct 2012 G. Material - Price and Availability ModKit 8MK4479-001 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 8MK4479-001 RH Nacelle MLG Parking Brake Pump Lever Relocation
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 401 +0.26 -2521 -0.66 DHC-8 Model 402 +0.26 -2521 -0.66

### SERVICE BULLETIN 84-32-99

S.B. 84-32-99 Page 6 of 20 26 Jan 2012 NB Revision ‘A’ 02 Oct 2012 J. Electrical Load Data Not affected K. Publications Affected Aircraft Operating Data Manual PSM 1-84-1

....................... Maintenance Manual PSM 1-84-2

................................ Dash 8 Illustrated Parts Catalogue PSM 1-84-4

.................... ModSums Manual PSM 1-84-12

.................................. Weight and Balance Manual (Imperial) PSM 1-84-8

................ Weight and Balance Manual (Metric) PSM 1-84-8M

.................. L. References Revision ‘A’ of this service bulletin was prepared to the engineering drawings and related data that follows: DRAWING SHEET REV 8MK4479 1 ‘C’

8Z9300 1 ‘C’ 8Z9300 2 ‘B’ ModSum 4-113723 Rev. ‘F’ ModSum 4Q113723 Rev. ‘F’ PCA 43323 Revision 2 (for internal reference only) Transport Canada Airworthiness Directive Pending

### SERVICE BULLETIN 84-32-99

S.B. 84-32-99 Page 7 of 20 26 Jan 2012 NB Revision ‘A’ 02 Oct 2012 2. MATERIALINFORMATION
A. Parts Required Per Aircraft (1) Modification Kit 8MK4479-001 (2) Detailed Kit Content:

Quantity Per Kit -001 Part Number Description Remarks
5 MS20605S3W2 Rivet, Blind 3 MS21042-3 Nut 1 M85449/2-18 Clamp, Cushioned 2 MS21059L3 Anchor Nut 2 NAS43DD3-56FC Spacer 5 NAS1149C0332R Washer 3 NAS1149C0363R Washer 2 NAS6203-17 Bolt 2 NAS6203-3 Bolt 2 MS20470A8-5S Rivet 2 B0205016AD4-5S Rivet 2 B0205016AD4-4S Rivet 1 85314940-001 Bracket Assembly 1 85314939-101 Bumper Pad 1 81175053-101 Label (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.

### SERVICE BULLETIN 84-32-99

S.B. 84-32-99 Page 8 of 20 26 Jan 2012 NB Revision ‘A’ 02 Oct 2012 Part Number Qty. Per Aircraft Description Remarks
05-03 As Required Adhesive DHMS A6.12 Type 1 (EC 2216B/A) 05-27 As Required Adhesive DHMS A6.11 Type 1 Class 2 (EC 1300L) 06-01A 1/4 Pint Sealant DSMS S3.01 Type 2 Class B 07-02 1/4 Pint Epoxy Primer DHMS C4.01 Type 2 07-08 1/4 Pint Polyurethane Enamel DHMS C4.04 07-21 1/2 Ounce Alodine MIL-C-5541 08-12 1/4 Pint Solvent DS108F Dynamold 14-01 1 Sheet Abrasive Paper 120 - 180 Grit
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 72900011-001 Pump Lever 1 C RWK 8Z9300-201 R

### SERVICE BULLETIN 84-32-99

S.B. 84-32-99 Page 9 of 20 26 Jan 2012 NB Revision ‘A’ 02 Oct 2012 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. 3. ACCOMPLISHMENTINSTRUCTIONS A. Job Set-Up (1) Placard and select all aircraft electrical power to OFF. Obey all relevant WARNINGS and CAUTIONS (refer to AMM TASK’S 24-00-00-861-802 and 24-00-00-910-801). (2) Make sure that lock pins are installed thru each main gear and main gear door mechanism. (3) Make sure the nose gear ground lock is engaged.

### SERVICE BULLETIN 84-32-99

S.B. 84-32-99 Page 10 of 20 26 Jan 2012 NB Revision ‘A’ 02 Oct 2012 (4) Set up the work platforms or ladders as required to gain access to the right hand nacelle. Make sure the work platforms or ladders are electrically grounded.
B. Procedure (1) Remove existing parking brake pump lever 72900011 as follows: (a) Depress existing quick release pin assembly and remove and retain parking brake pump lever 72900011 from existing bracket 82974258. Refer to Figure 2. (b) Carefully remove existing rivet attaching quick release pin assembly 55440-4R15DL7C-4 from M/C frame aft uplock 85414452. Remove and retain quick release pin assembly for installation in RH upper nose compartment. (c) Deburr existing rivet hole, treat exposed surfaces with Alodine 1200S, prime treated areas with epoxy chromate primer and plug hole with rivet B0205016AD4-4S. (d) Remove and discard neoprene pad installed to area around hole in flange on existing bracket 82974258. (e) Drill existing quick release pin hole on flange to 0.253/ 0.263 inch diameter. Deburr existing quick release pin hole, treat exposed surfaces with Alodine 1200S, prime treated areas with epoxy chromate primer. Plug 0.253/ 0.263 inch diameter hole with rivet MS20470A8-5S. (2) Carefully cut off existing nacelle cushion clamp assembly M85449/2-18 and deburr sharp edges of remnant pieces of cushion clamp assembly (leave the original mounting hardware in place). Make sure the edge of the stiffener of M/C frame 85414452 is protected during the cutting operation. Refer to Figure 2, View on Arrow F. (3) Install new metal label 81175053-101 to RH nacelle structure as follows: (a) Before installing new label lightly scuff the affected area on the nacelle panel with 120 to 180 grit abrasive paper then solvent clean with a clean cotton cloth moistened with solvent DS108F. Refer to AMM, PSM 1-84-2, TASK 20-00-11-400-801.

### SERVICE BULLETIN 84-32-99

S.B. 84-32-99 Page 11 of 20 26 Jan 2012 NB Revision ‘A’ 02 Oct 2012 NOTE: Do not install the metal labels if the surface temperature is less than 15 degrees C (60 degrees F). (b) Apply a layer of EC 2216B/A adhesive to the new metal label and on the nacelle panel mating surface. Carefully apply new metal label 81175053-101 to area adjacent to pump lever previous installation location. Refer to Figure 3, View on Arrow G and Detail H. (c) Sparingly apply a small quantity of sealant DHMS S3.01 type 2 class B along the outside edges of the installed metal label 81175053-101. (4) Install retained quick release pin assembly to new bracket assembly as follows: (a) Install retained quick release pin assembly 55440-4R15DL7C-4 to new bracket assembly 85314940-001 using new rivet B0205016AD4-5S. Refer to Figure 6 , VIEW ON ARROW D and SECTION E-E. (5) Relocate parking brake pump lever to the RH nose compartment bay as follows: CAUTION THE OXYGEN BOTTLE IS LOCATED BELOW THE FLIGHT DECK FLOOR. COVER OXYGEN BOTTLE TO PREVENT INADVERTENT DAMAGE DURING DRILLING OPERATIONS. (a) Carefully mark and drill holes into the flight deck web as required. For new anchor nut installation locations and cushioned clamp location refer to Figure 4. (b) Drill new anchor nut holes to 0.250/ 0.254 inch diameter as required. Deburr existing anchor nut holes, treat exposed surfaces with Alodine 1200S, prime treated areas with epoxy chromate primer. (c) Install new anchor nuts MS21059L3 with blind rivets MS20605S3W2. (d) Install new bracket assembly 85314940-001 with bolts NAS6203-3 and washers NAS1149C0363R. Torque bolts to 25 inch pounds. (e) Drill bolt holes to 0.195/ 0.201 inch diameter for cushion clamp installation as required. Deburr bolt holes, treat exposed surfaces with Alodine 1200S, prime treated areas with epoxy chromate primer. (f) Install new cushion clamp M85449/2-18 to flight deck web with bolts NAS6203-17, spacers NAS43DD3-56FC, washers NAS1149C0332R and nuts MS21042-3. Torque bolts to 25 inch pounds.

### SERVICE BULLETIN 84-32-99

S.B. 84-32-99 Page 12 of 20 26 Jan 2012 NB Revision ‘A’ 02 Oct 2012 (6) Prepare the forward radome bulkhead area for bumper pad installation as follows: (a) Degrease the designated installation area with a clean, cotton cloth dampened with solvent DS108F. (b) Temporarily install pump lever to new bracket assembly and new cushion assembly to verify installation position of new bumper pad. (c) Apply adhesive EC 1300L, position and install bumper pad 85314939-101 with edges adjacent to radome bulkhead angles. Refer to Figure 5 and SRM, PSM 1-84-3, Chapter 51-22-15. (7) Rework existing pump lever as follows: (a) Carefully measure to new position and drill a new 0.256/0.263 inch diameter hole at 90 degree orientation from the existing hole in pump lever. Refer to Figure 4 and Figure 6. (b) Deburr new hole on pump lever, treat exposed surfaces with Alodine 1200S, prime treated areas with epoxy chromate primer. (c) Log reworked part as 8Z9300-201. (d) Install reworked pump lever 8Z9300-201 to its new location in the nose compartment. Depress lock pin and insert the quick release pin assembly 55440-4R15DL7C-4 to secure the pump lever to the bracket assembly 85314940-001. NOTE: Pump lever 72900011-001 and 82900002-001 are equivalent and can be reworked by adding hole as shown in VIEW ON ARROW B in Figure 4.

### SERVICE BULLETIN 84-32-99

S.B. 84-32-99 Page 13 of 20 26 Jan 2012 NB Revision ‘A’ 02 Oct 2012 C. Close Out (1) Remove all tools and equipment from the work area. (2) On incorporation of this ModSum/Modification, add the weight and balance data shown in Section I of this service bulletin to the Weight and Balance Manual PSM 1-84-8. Under ‘Description of Change’ enter “ModSum 4-113723 incorporated.” (3) On incorporation of this ModSum, make an entry that conforms to local regulatory requirements in the applicable logbook(s). 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 84-32-99

S.B. 84-32-99 Page 14 of 20 26 Jan 2012 NB Revision ‘A’ 02 Oct 2012 RH Nacelle MLG Parking Brake Pump Lever Relocation Installation Figure 1 WAS

NOW LEVER REMOVAL FROM RH NACELLE

LEVER INSTALLATION INTO NOSE COMPARTMENT

RH Nacelle MLG Parking Brake Pump Lever Relocation Installation Figure 1 NOTE: ALL DIMENSIONS ARE GIVEN IN INCHES

### SERVICE BULLETIN 84-32-99

S.B. 84-32-99 Page 15 of 20 26 Jan 2012 NB Revision ‘A’ 02 Oct 2012 Existing Parking Brake Pump Lever Removal in RH Nacelle Figure 2 LEVER PUMP 72900011 CLAMP M85449/2-18

BRACKET 82974258

PARKING BRAKE HAND PUMP M/C FRAME AFT UPLOCK 85414452 QUICK RELEASE PIN ASSEMBLY 55440-4R15DL7C-4 EXISTING LOCATION B0205016AD4-4S RIVET (PLUG)
RIVET (PLUG) MS20470A8-5S OPEN HOLE TO 0.253/0.263 INCH DIAMETER RIVET

VIEW ON ARROW LOOKING FORWARD IN RH NACELLE REMOVE EXISTING NEOPRENE PAD ON BRACKET 82974258 (Retain for Relocation) (Retain for Rework and Relocation) remains in place) (mounting CUSHIONED

hardware Clamp is cut off and sharp edges are deburred F M/C FRAME 85414452

VIEW ON ARROW CUT LINE AT RADIUS 2 PL
PUMP CUT AWAY CLAMP AND DISCARD MAKE SURE THE EDGE OF STIFFENER IS PROTECTED DURING CUTTING OPERATION

### SERVICE BULLETIN 84-32-99

S.B. 84-32-99 Page 16 of 20 26 Jan 2012 NB Revision ‘A’ 02 Oct 2012 Label Installation on RH Nacelle Composite Sidewall Panel Figure 3 85414429 SIDEWALL PANEL

LABEL EDGE X201D 210.0

LOOKING OUTBOARD ON RH AFT M/C FRAME AFT UPLOCK

81175053-101

COMPOSITE SIDEWALL PANEL 85414429 SIDEWALL PANEL COMPOSITE CONSTRUCTION

1.00

OF CORE 0.10

DETAIL SEAL OUTSIDE EDGE OF METAL LABEL WITH DHMS S3.01 TYPE 2 CLASS B SEALANT VIEW ON ARROW DETAIL

TO LABEL AND PANEL APPLY EC 2216B/A ADHESIVE BEFORE LABEL INSTALLATION

### SERVICE BULLETIN 84-32-99

S.B. 84-32-99 Page 17 of 20 26 Jan 2012 NB Revision ‘A’ 02 Oct 2012 Installation of new Bracket Assembly and Cushion Clamp for Lever Relocation Figure 4 CUSHIONED CLAMP M85449/2-18 BOLT NAS6203-17 WASHER NAS1149C0332R SPACER

VIEW ON ARROW NUT MS21042-3

LOOKING DOWN ON FLIGHT DECK FLOOR IN NOSE COMPARTMENT AT Z112.00 B BRACKET ASSEMBLY

55440-4R15DL7C-4 BOLT NAS6203-3 WASHER NAS1149C0363R ANCHOR NUT MS21059L3 D DRILL NEW 0.256/0.263 INCH DIAMETER HOLE IN PUMP LEVER AT RIVET, BLIND MS20605S3W2 FLIGHT DECK FLOOR 85314922 8Z7886 OR RADOME BULKHEAD 85310146

0.40 0.45

NAS43DD3-56FC

EXISTING HOLE IN PUMP LEVER 0.76 2.08

1.50

0.55 FITTING BASE PARALLEL WITH STIFFENER
Y22.00 Y17.00 Y12.50 -131.090 x -141.320 -149.000 -155.000 x x x

PUMP LEVER 72900011 RADOME BULKHEAD DATUM

STIFFENER 85313612 STIFFENER 85314015

STIFFENER 85314072 STIFFENER 85314016

3.50 85314940-001

QUICK RELEASE PIN ASSEMBLY RIVET B0205016AD4-5S DIMENSION SHOWN 90 DEGREES TO THE EXISTING HOLE

### SERVICE BULLETIN 84-32-99

S.B. 84-32-99 Page 18 of 20 26 Jan 2012 NB Revision ‘A’ 02 Oct 2012 Rubber Pad Installation to Radome Bulkhead Figure 5 RADOME BULKHEAD 85310146

ANGLE 85310148 RADOME TO FLIGHT DECK ATTACHMENT

85314939-101 BUMPER PAD POSITION BUMPER PAD AS SHOWN WITH EDGES ADJACENT TO BULKHEAD ANGLES

LOOKING FWD ON RADOME BULKHEAD ANGLE 85311886 

## UPA

### SERVICE BULLETIN 84-32-99

S.B. 84-32-99 Page 19 of 20 26 Jan 2012 NB Revision ‘A’ 02 Oct 2012 Quick Release Pin Assembly Installation to new Location on Flight Deck Floor Figure 6 BRACKET 85314940-001 ASSEMBLY CUSHIONED CLAMP M85449/2-18

FLIGHT DECK FLOOR VIEW ON ARROW (ROTATED CCW 30 DEGREES) LOOKING ON PUMP LEVER

SECTION QUICK RELEASE PIN ASSEMBLY 55440-4R15DL7C-4
(LANYARD DEPICTION

-REFERENCE ONLY) RIVET B0205016AD4-5S QUICK RELEASE PIN ASSEMBLY 55440-4R15DL7C-4

SPACER NAS43DD3-56FC (Retained from RH. Nacelle)

### SERVICE BULLETIN 84-32-99

S.B. 84-32-99 Page 20 of 20 26 Jan 2012 NB Revision ‘A’ 02 Oct 2012 

### This Page Intentionally Blank 3Jan 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 V Compliance VApproval V Manpower V Material VWeight and Balance V Electrical Load VTooling 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 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