# Bombardier Service Bulletin 84-27-55 Copy: Revision A ("U.S. DOT/FAA - SB 84-27-55 RA"), 19 pages: PDF https://openairdocs.org/files/sha256/84/98/8498c3263203d3dcaba860a4b41970d9572b911d4e0c7fb39e4ddccfa362d3a3; text https://openairdocs.org/service-documents/bombardier/sb-84-27-55/file/8498c3263203.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2012-1311; AD 2013-22-04 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. ## Details - Manufacturer: [Bombardier](https://openairdocs.org/service-documents/bombardier.md) - Type: Service bulletin (Service Bulletin) - Number: 84-27-55 - Latest revision known: 84-27-55, Revision A, dated February 22, 2012 (OpenAirDocs) - Page: https://openairdocs.org/service-documents/bombardier/sb-84-27-55 ## ADs that cite it (1) (OpenAirDocs) Newest first, with the revision each names, as OpenAirDocs read it from the AD's text. - [AD 2013-22-04](https://openairdocs.org/ad/2013-22-04.md), effective Dec 5, 2013: Revision A ## Text (19 pages) Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2012-1311; AD 2013-22-04 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. This text is OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 (OCR) DHC-8 (DASH 8) SERVICE BULLETIN 84-27-55 Flight Controls - Addition of Bushing in Brake Pedal Bell Crank - Rudder Control - ModSum 4-110372 This page transmits Revision 'A' of Service Bulletin 84-27-55, pages 1 thru 16 dated 22 Feb 2012. This service bulletin is re-issued in its entirety for the reasons that follow: - the References section is revised to convey the latest revision of the service bulletin and engineering documentation - in the ACCOMPLISHMENT INSTRUCTIONS section added an alternate Task and an additional paragraph to Part B The Compliance in the previous issues of this service bulletin is not affected by this revision. No additional rework to the aircraft is introduced by this revision. Remove previous issue of Service Bulletin 84-27-55 and replace with attached. Previous issues of Service Bulletin 84-27-55: Initial issue - Pages 1 thru 16 dated 15 Jun 2011 Revision 'A' 22 Feb 2012 ### Page 2 (OCR) de HAVILLAND BOMBARDIER DASH8 Customer Support ATA SYSTEM: 2730 NUMBER: 84-27-55 BOMBARDIER AEROSPACE REGIONAL AIRCRAFT CONSIDER THIS SERVICE BULLETIN TO BE PARTICULARLY SIGNIFICANT AND URGES OPERATORS TO PROMPTLY EVALUATE THE CONTENTS SUBJECT: Flight Controls - Addition of Bushing in Brake Pedal Bell Crank - Rudder Control - ModSum 4-110372 1. PLANNING INFORMATION A. Effectivity Aircraft Affected: In-Service: DHC-8 Aircraft Models 401 and 402 Serial Numbers 4003 thru 4372. Aircraft with ModSum 4-903003 installed are already compliant with this Service Bulletin. Production: ModSum 4-110372 will be installed before delivery on applicable DHC-8 Aircraft at Serial Number 4373 and subsequent. Verification: ModSum 4-110372 has been installed on DHC-8 Aircraft Model 402 Serial Number 4265. 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. 15 Jun 2011 S.B. 84-27-55 Revision 'A' 22 Feb 2012 Page 1 of 16 JR ### Page 3 (OCR) SERVICE BULLETIN 84-27-55 Spares Affected: None B. Reason Problem: During maintenance, an operator found that the LH & RH pilot brake pedal bellcrank had exhibited excessive wear in the tie rod attachment clevis hole. Solution: This service bulletin provides instructions to add a steel bushing to the rod attachment clevis hole, or replace with new bellcrank containing steel bushing. 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 thru each main gear and main gear door mechanism - pilot & co-pilot brake pedal bellcranks are inspected - pilot & co-pilots bellcranks are either re-worked to install steel bushing or replaced - close out. D. Compliance Bombardier Inc. highly recommend that ModSum 4-110372 be incorporated at the earliest opportunity unless otherwise directed by the operator's airworthiness authority. Transport Canada Airworthiness Directive CF-2011-32 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 (DTS). 15 Jun 2011 S.B. 84-27-55 Revision 'A' 22 Feb 2012 Page 2 of 16 JR ### Page 4 (OCR) SERVICE BULLETIN 84-27-55 F. Manpower The following is the man-hours required to complete the ACCOMPLISHMENT INSTRUCTIONS in this service bulletin. The breakdown of man -hours is shown in the table that follows: TASK MAN-HOURS Job Set-Up 0.50 Procedure (Inspection) 1.00 Procedure (Bushing Installation) 4.00 Procedure (Bellcrank Replacement) 16.00 Test / RTS 2.00 Close-Out 0.50 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 ModKit 8MK4453-001 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 8MK4453-001 Retrofit Kit -Bellcrank Assembly - Pedal Assembly Rudder Controls 15 Jun 2011 S.B. 84-27-55 Revision 'A' 22 Feb 2012 Page 3 of 16 JR ### Page 5 (OCR) SERVICE BULLETIN 84-27-55 H. Tooling - Price and Availability None I. Weight and Balance None J. Electrical Load Data Not affected K. Publications Affected Dash 8 Illustrated Parts Catalogue .... PSM 1-84-4 ModSums Manual .... PSM 1-84-12 References Revision 'A' of this service bulletin was prepared to the engineering drawings and related data that follows: DRAWING SHEET REV 8MK4453 1 8Z6930 1 D ModSum 4Q110372 Rev. 'D' ModSum 4-110372 Rev. 'D' PCA 43253 Revision 2 (for internal reference only) Transport Canada Airworthiness Directive CF-2011-32 2. MATERIAL INFORMATION A. Parts Required Per Aircraft (1) Modification Kit 8MK4453-001 (2) Detailed Kit Content: 15 Jun 2011 S.B. 84-27-55 Revision 'A' 22 Feb 2012 Page 4 of 16 JR ### Page 6 (OCR) SERVICE BULLETIN 84-27-55 Quantity Per Kit Part Number Description Remarks -001 4 MS24665-163 Cotter Pin 4 NAS6603CD13 Bolt 8 82710297-101 Bushing 1 8Z6930 Retrofit Bellcrank Assembly Drawing 1 8MK4453 Retrofit Kit Drawing (3) In addition to the above parts, the following material is 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 MS20995C32 as required Lockwire F19 as required Primer - Type II MIL-PRF-23377 Parts Required to Modify Spares None C. Special Tools and Equipment Required None D. Existing Parts Accountability None 3. ACCOMPLISHMENT INSTRUCTIONS 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. 15 Jun 2011 S.B. 84-27-55 Revision 'A' 22 Feb 2012 Page 5 of 16 JR ### Page 7 (OCR) SERVICE BULLETIN 84-27-55 (3) Make sure the nose gear ground lock is engaged. (4) Remove access panels 121AL and 122AR from the nose fuselage. Refer to Maintenance Manual Task 06-41-00-992-801. B. Procedure (1) Insert rig pins RP1, RP2, RP3 and RP4 in the LH and RH rudder output levers rudder forward quadrants. refer to Maintenance Manual Task 27-21-05-400-801. (2) Disconnect control rod assembly 82710795-001 (four places). Retain hardware, discard cotter pin. Refer to Figure 1. Part A - Inspection (1) Determine length of clevis holes on each bellcrank. If length is less than or equal to 0.218 inches from edge to edge (see Figure 6 for reference) then crack check using Liquid Penetrant Inspection (LPI). Refer to ASTM E1417. NOTE: As an alternate to the LPI, an Eddy current inspection may be pertormed per NDT Manual PSM 1-84-7A, Part 6, Chapter 51-00-05 Task 51-00-05-250-801. (2) If crack is found, replace with new bellcrank (refer to Part C - Bellcrank Replacement). (3) If no crack is found, rework bellcrank per instructions in Part B within 600 flight hours or replace with new, within 6000 flight hours (refer to Part C - Bellcrank Replacement). (4) If length is less than or equal to 0.248 inches, but greater than 0.218 inches then replace with a new bellcrank within 6000 flight hours (refer to Part C - Bellcrank Replacement). (5) If length is greater than 0.248 inches, but less than or equal to 0.278 inches then replace with new bellcrank within 1200 flight hours, if greater than 0.278 inches replace with new bellcrank before next flight (refer to Part C - Bellcrank Replacement). Part B - Bushing Installation (In-Situ) (1) Disconnect rod assembly 82710274-001 (two places) from bellcranks on pilots side. Retain hardware, discard cotter pin. Refer to Figure 1. (2) Disconnect cable assembly 82700570-001/-003 from bellcranks on co-pilots side. Retain hardware, discard cotter pin. Refer to Figure 2. NOTE: In order to remove the clevis pins from the co-pilots bellcranks the cable tension must be released by temporarily moving the brake control assembly levers on the pilots side forward. 15 Jun 2011 S.B. 84-27-55 Revision 'A' 22 Feb 2012 Page 6 of 16 JR ### Page 8 (OCR) SERVICE BULLETIN 84-27-55 (3) Open the hole on original center in bellcrank assembly as shown in section A-A/B-B of Figures 4 & 5 using a reamer 0.250 inches diameter with a 0.187 inches pilot. NOTE: Reamer should not be longer than 2 inches and to be used with an angle NOTE: Alternatively, bushing installation may be conducted outside the aircraft. Follow the applicable instructions in Part C to remove the bellcrank from the aircraft and to install the reworked bellcrank into aircraft. NOTE: If original hole is damaged, bellcrank may be re-used only if hole enlargement (to the size shown in section A-A/B-B) is sufficient to repair the damage and edge distance as shown in Figure 4 can be maintained. Otherwise bellcrank requires replacement. Replace 82710813-003/-004 and 82710814-003/-004. For aircraft without ModSum 4-126182 installed also use 82710813-003/-004 and 82710814-003/-004. (4) Deburr holes. Make sure edge distance 0.310‡ 0.030 inches. Refer to Figures 4 & 5. (5) Refer to Figures 4 & 5 wet install bushings 82710297-101 into bellcrank assembly using F19 primer. Refer to Structural Repair Manual Task 51-27-20-02-01. (6) Re-identify bellcrank assembly 82710813-001/-002 as 8Z6930-051/-053 and 82710814-001/-002 as 826930-055/-057. Refer to Maintenance Manual Task 20-00-01-910-801. (7) Re-identify bellcrank assembly 82710022-001/-002 as 8Z6930-059/-061 and 82710029-001/-002 as 8Z6930-063/-065 for aircraft without ModSum 4-126182 installed. Refer to Maintenance Manual Task 20-00-01-910-801. (8) Connect control rod assembly 82710795-001 (four places) to reworked bellcranks using kept hardware and new bolt NAS6603CD13 and new cotter pin MS24665-163. Refer to Figure 1. If bolt doesn't fit, ream bushing to 0.190/0.192 inches diameter. (9) Connect rod assembly 82710274-001 (two places) to reworked bellcranks on pilots side using kept hardware and new cotter pin MS24665-163. Refer to Figure 1. (10) Connect cable assembly 82700570-001/-003 to reworked bellcranks on co-pilots side using kept hardware and new cotter pin MS24665-163. Refer to Figure 2. 15 Jun 2011 S.B. 84-27-55 Revision 'A' 22 Feb 2012 Page 7 of 16 JR ### Page 9 (OCR) SERVICE BULLETIN 84-27-55 (11) Identify the installation as 8Z6930-001 & 8Z6930-002 or 8Z6930-003 & 826930-004 for aircraft without ModSum 4-126182 installed. Refer to Maintenance Manual Task 20-00-01-910-801. Part C - Bellcrank Replacement (1) On the flight compartment floor, remove and retain all the screws securing the rudder pedal cover to the floor. Leave cover in place. (2) Disconnect rod assembly 82710274-001 (two places) from bellcranks on pilots side. Retain hardware, discard cotter pin. Refer to Figure 1. (3) Disconnect cable assembly 82700570-001/-003 from bellcranks on co-pilots side. Retain hardware, discard cotter pin. Refer to Figure 2. (4) Disconnect rudder force sensor 9000925-1 or rod assembly 82710028-003 (four places) from the rudder control pedal assembly. Retain hardware, discard cotter pin. Refer to Figure 1. (5) Remove microswitch support bracket 82710812. Retain hardware and shim if present. Be careful not to damage microswitches. Refer to Figure 3. (6) Remove aileron trim actuator (pilot side only). Refer to Maintenance Manual Task 27-13-01-000-801. Remove bracket assembly 85314893-001 (pilot side only). Refer to Figure 1. (8) Index mark rudder control pivot assembly mounting flange and fitting on both sides. (9) Remove pivot assembly fitting 82710021-101. Retain hardware. Refer to Figure 2. (10) Remove and retain hardware from the pivot assembly mounting flange. Refer to Figure 2. (11) While holding the pivot tube assembly gently twist the assembly and slightly move it aft until it clears the rudder pedal assembly mounting brackets. (12) Rotate the pivot tube mounting flange in a clockwise and anti-clockwise direction while moving towards the inboard until tube as moved enough to remove the belcrank. NOTE: As you move the pivot tube inboard be sure to support the teflon spacers and bushings. (13) Remove affected bellcrank and replace with a new bellcrank containing steel bushing. (14) Rotate the pivot tube mounting flange in a clockwise and anti-clockwise direction while moving towards the outboard until its fully through. 15 Jun 2011 S.B. 84-27-55 Revision 'A' 22 Feb 2012 Page 8 of 16 JR ### Page 10 (OCR) SERVICE BULLETIN 84-27-55 (15) While holding the pivot tube assembly gently twist the assembly and slightly move it forward until it positions itself on the rudder pedal assembly mounting brackets. (16) Install pivot assembly fitting 82710021-101 using kept hardware. Refer to Figure 2. (17) Secure pivot assembly mounting flange to the rudder pedal assembly mounting brackets using kept hardware. (18) Install bracket assembly 85314893-001 (pilot side only) using rivets B0205015AD4-5. Refer to Figure 1. (19) Install aileron trim actuator (pilot side only). Refer to Maintenance Manual Task 27-13-01-400-801. (20) Install microswitch support bracket 82710812 and shim 82710602-953, if originally present, using kept hardware. Refer to Figure 3. (21) Connect rudder force sensor 9000925-1 or rod assembly 82710028-003 (four places) to the rudder control pedal assembly using kept hardware and new cotter pin MS24665-153. Refer to Figures 1 & 2. (22) Connect cable assembly 82700570-001/-003 to the bellcranks on co-pilots side using kept hardware and new cotter pin MS24665-163. Refer to Figure 2. (23) Connect rod assembly 82710274-001 (two places) to the bellcranks on pilots side using kept hardware and new cotter pin MS24665-163. Refer to Figure 1. (24) On the flight compartment floor secure the rudder pedal cover to the floor using kept hardware. (25) Connect control rod assembly 82710795-001 (four places) to bellcranks using kept hardware and new bolt NAS6603CD13 and new cotter pin MS24665-163. Refer to Figure 1. (26) Identify the installation as 826930-001 & 826930-002 or 826930-003 & 8Z6930-004 for aircraft without ModSum 4-126182 installed. Refer to Maintenance Manual Task 20-00-01-910-801. C. Close Out (1) Do the Return to Service Procedure as follows: (a) Remove rig pins RP1, RP2, RP3 and RP4. Move the pedal adjustment mechanism fully forward and operate the rudder pedals forward and aft. Check for full and free movement of the rudder pedals. For aircraft equipped with force sensors 9000925-1, check for clearance between the sensor harness and the adjacent components. Inspect for clearance as follows: 15 Jun 2011 S.B. 84-27-55 Revision 'A' 22 Feb 2012 Page 9 of 16 JR ### Page 11 (OCR) SERVICE BULLETIN 84-27-55 (c) Minimum clearance of 0.12 inches (3.05 mm) between the harness and surrounding components. (d) Minimum clearance of 0.375 inches (9.53 mm) between the force sensor and surrounding components except the fitting assembly and the aft rod end bearing of the force sensor. (e) Move the pedal adjustment mechanism fully aft and operate the rudder pedals forward and aft. Check for full and free movement of the rudder pedals. For aircraft equipped with force sensors 9000925-1, check for clearance between the sensor harness and the adjacent components. Inspect for clearance as follows: 1 Minimum clearance of 0.12 inches (3.05 mm) between the harness and surrounding components. Minimum clearance of 0.375 inches (9.53 mm) between the torce sensor and surrounding components except the fitting assembly and the aft rod end bearing of the force sensor. Apply full pilot brake travel to each pedal for a minimum of 25 cycles. Make sure the system has full and free movement. (g) Apply full co-pilot brake travel to each pedal for a minimum of 25 cycles. Make sure the system has full and free movement. NOTE: Make sure the brake linkages go back to their initial position after each brake application. The co-pilot brake lever will touch the structural stop. Refer to Maintenance Manual Task 32-42-00-830-801 Figure 502. (h) Check and if necessary, adjust the brake position switch. Refer to Maintenance Manual Task 27-21-01-400-802. (2) Remove all tools and equipment from the work area. (3) Install access panels 121AL and 122AR to the nose fuselage. Refer to Maintenance Manual Task 06-41-00-992-801. (4) On incorporation of this ModSum, make an entry that conforms to local regulatory requirements in the applicable logbooks). Enter component serial numbers if applicable. Enter this ModSum number only after complete and functional incorporation of all work defined in this service bulletin. 15 Jun 2011 S.B. 84-27-55 Revision 'A' 22 Feb 2012 Page 10 of 16 JR ### Page 12 (OCR) SERVICE BULLETIN 84-27-55 ROD ASSEMBLY (TYP) 82710795-001 RUDDER FORCE SENSOR 9000925-1 (TYP) OR BOLT NAS1801-3D10 ROD ASSEMBLY WASHER AN960D10L - C/L OF A/C 82710028-003 (TYP) LOCK WIRE MS20995C32 RUDDER PEDAL ASSEMBLY (TYP) MOUNTING BRACKET BOLT NAS6203-3 NUT MS21042L3 WASHER AN960D10L BOLT NAS6203-3 NUT MS21042L3 WASHER AN960D10L 8Z6930-059 (Pre MS) 8Z6930-051 - 85314893-001 BRACKET ASSEMBLY CONTINUED ON FIGURE 2 RIVET IN THIS AREA. B0205016AD4-5 826930-061 (Pre MS) 8Z6930-053 ROD ASSEMBLY 82710274-001 BOLT NAS6603D7 NUT MS14144L3 WASHER AN960D10L COTTER PIN MS24665-163 -(Y=-20.05) Pilots Pedals Figure 1 15 Jun 2011 S.B. 84-27-55 Revision 'A' 22 Feb 2012 Page 11 of 16 JR ### Page 13 (OCR) SERVICE BULLETIN 84-27-55 BOLT NAS1801-3D10 WASHER AN960D10L LOCK WIRE MS20995C32 - C/L OF A/C BOLT NAS6203-3 NUT MS21042L3 BOLT NAS6203-3 WASHER AN960D10L - NUT MS21042L3 WASHER AN960D10L PIVOT ASSEMBLY FITTING (TYP) PIVOT ASSEMBLY 82710021-101 MOUNTING FLANGE (TYP) FROM FIGURE 1 826930-065 8Z6930-063 (Pre MS) (Pre MS) 8Z6930-055 8Z6930-057 (3133-J15) - PIN MS20392-2C11 CABLE ASSEMBLY 82700570-001 COTTER PIN MS24665-163 WASHER AN960D10L CABLE ASSEMBLY 82700570-003 _ (Y-18.97) Co-Pilots Pedals Figure 2 15 Jun 2011 S.B. 84-27-55 Revision 'A' 22 Feb 2012 Page 12 of 16 JR ### Page 14 (OCR) SERVICE BULLETIN 84-27-55 ROD ASSEMBLY 82710795-001 BOLT NAS6603CD13 NUT MS14144L3 WASHER AN960D10L COTTER PIN MS24665-163 NOTE: Tighten nut to ensure posi- tive clamp-up of bearing inner race. MICROSWITCH SUPPORT BRACKET 82710812 8Z6930-059 (Pre MS) 8Z6930-061 (Pre MS) 8Z6930-051 8Z6930-053 8Z6930-063 (Pre MS) 8Z6930-065 (Pre MS) 8Z6930-055 8Z6930-057 Detail C and D Figure 3 15 Jun 2011 S.B. 84-27-55 Revision 'A' 22 Feb 2012 Page 13 of 16 JR ### Page 15 (OCR) SERVICE BULLETIN 84-27-55 - (82710813-001/-002) (82710022-001/-002) (Pre MS) / BUSHING 82710297-101 (one on each lug) EDGE DISTANCE 0.310 + 0.030 2 PLCS • 2500 2 PLCS . 2506 -051 AS SHOWN - 053 OPP -059 AS SHOWN (Pre MS) -0b1 SECTION A-A BUSHINGS REMOVED FOR CLARITY Bushing Installation Figure 4 15 Jun 2011 S.B. 84-27-55 Revision 'A' 22 Feb 2012 Page 14 of 16 JR ### Page 16 (OCR) SERVICE BULLETIN 84-27-55 - (82/10814-001/-002) (82710029-001/-002) (Pre MS) BUSHING 82710297-101 (one on each lug) EDGE DISTANCE 0.310 + 0.030 2 PLCS 2500 2 PLCS 2506 -055 AS SHOWN -057 -063 AS SOWN -065 OPP (Pre MS) SECTION B-B BUSHINGS REMOVED FOR CLARITY Bushing Installation Figure 5 15 Jun 2011 S.B. 84-27-55 Revision 'A' 22 Feb 2012 Page 15 of 16 JR ### Page 17 (OCR) SERVICE BULLETIN 84-27-55 Edge to edge length reference Figure 6 15 Jun 2011 S.B. 84-27-55 Revision 'A' 22 Feb 2012 Page 16 of 16 JR ### Page 18 (OCR) BOMBARDIER 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 Jan 2009 ### Page 19 (OCR) BOMBARDIER SERVICE BULLETIN (SB) - COMMENT SHEET - Q SERIES DASH 8 AIRCRAFT 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 boxes) 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 • Effectivity • Reason • Description • Compliance • Approval • Manpower • Material • Weight and Balance • Electrical Load • Tooling • References • Publications Affected 2. MATERIAL INFORMATION • Kit Content • Special Tools/Equipment • Parts to Modify Spares • Consumables • Disposition of Existing Parts • Other 3. ACCOMPLISHMENT INSTRUCTIONS • Job Set-Up • Procedure • Close-Out D Test • Illustration (s) • Other 4. COMMENTS, REMARKS, SUGGESTIONS Fax this sheet to (1) 416 375 4538 or Email PDF to: syed.rizvi@aero.bombardier.com Feb 2009 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.