Pneumatic − Bleed Air System − Installation of Protective Shields on the Rudder Quadrant Support − Beam
This page transmits: Revision A of Service Bulletin 670BA−36−014, pages 1 thru 25, dated Oct 11/2011. The changes in this revision have no effect on aircraft that have incorporated a previous issue of this service bulletin.
Reason:

Revised Planning Information: Revised the effectivity table. Revised Accomplishment Instructions: Add new steps and new illustrations.
Document Instructions: Discard the copy of Service Bulletin 670BA−36−014, dated April 7/2011. Replace with the copy attached. Service Bulletin History: Initial issue, dated April 7/2011. 

### SERVICE BULLETIN 670BA−36−014

S.B. 670BA−36−014 Page 1 of 1 Oct 11/2011 

# SERVICE BULLETIN REVISION TRANSMITTAL SHEET

SUBJECT:Pneumatic − Bleed Air System − Installation of Protective Shields on the Rudder Quadrant Support−Beam

1. PLANNING INFORMATION A. Effectivity (1) Aircraft Affected:

Aircraft Model Service Bulletin Aircraft Serial Numbers Production Aircraft Serial Numbers

CL−600−2C10 10003 thru 10326 10327 and subsequent serial numbers [1] CL−600−2D15 and CL−600−2D24 15001 thru 15267 15268 and subsequent serial numbers [1] [1] This change will be incorporated before delivery on this range of aircraft. 

# SERVICE BULLETIN

ATA SYSTEM: 36−21 NUMBER: 670BA−36−014

S.B. 670BA−36−014 Page 1 of 25 Apr 07/2011 Revision A, Oct 11/2011 Technical Publications

THIS SERVICE BULLETIN IS SENT TO EACH OPERATOR. IF THE OPERATOR HAS LEASED AIRCRAFT, THIS SERVICE BULLETIN MUST BE SENT TO THE LESSEE. IF THE OPERATOR HAS SOLD AIRCRAFT OR TRANSFERRED SPARES IN THE LAST SIX MONTHS, THIS SERVICE BULLETIN MUST BE SENT TO THE NEW OWNER, UNLESS CONFIRMATION WAS RECEIVED THAT BOMBARDIER COMMERCIAL AIRCRAFT DIVISION HAS INCLUDED THE NEW OPERATOR ON THE DISTRIBUTION LIST.

SUBJECT:NOTE : The instructions in this service bulletin are only applicable to the systems and parts installed at the time of delivery of the aircraft or as changed by Bombardier service bulletin(s). Before you do this bulletin, examine all STC, STA or equivalent action changes to make sure this bulletin can be completed. NOTE : The procedure in this service bulletin was validated on aircraft with serial number 15001.

B. Reason (1) Condition In the bleed leak detection system, if there is a hot air leak after the rupture of a high pressure duct, the duct insulation shroud will not transmit the air correctly through the vent holes of the insulation. If a bleed air leak is not sensed by the bleed leak detection system and the hot air goes in the direction of the adjacent structure and/or system components, it can have an unwanted effect on structure and system components. (2) Evidence Reports have shown that some components and structural areas must be protected from the flow of direct bleed air leak. (3) Objective/Benefit This service bulletin gives the procedure to install protective shields on the rudder quadrant support−beam in the aft equipment compartment. This will prevent damage to the rudder quadrant if a bleed air leak occurs. C. Description Some circuit breakers are opened. The APU battery, the APU bleed−air duct, and some components of the drip tray installation are removed. If necessary, the air−cycle machine−ducts are removed. Shielding plates are installed on the rudder quadrant support−beam. The APU bleed−air duct and, if removed, the air−cycle machine−ducts are installed. The APU battery is installed. Components of the drip tray installation are installed. The circuit breakers are closed. The leak test of the bleed−air distribution system is done. Operational tests of the APU battery and of the APU battery charger are done. D. Compliance Recommended Service Bulletin. 

### SERVICE BULLETIN 670BA−36−014

S.B. 670BA−36−014 Page 2 of 25 Apr 07/2011 Revision A, Oct 11/2011Bombardier recommends that this service bulletin be done before December 31, 2013 or no more than 6600 flight hours from the release date on this service bulletin, whichever comes first, unless otherwise directed by the airworthiness authority of the operator. NOTE : This Service Bulletin does not affect Airworthiness Limitations (AWLs) or Damage Tolerance Inspections (DTIs). E. Approval The technical content of this service bulletin has been approved under the authority of the TCCA Design Approval Organization No: DAO #93−Q−02. F. Manpower The man−hours given below are an estimate for direct labor done by an experienced crew on an aircraft prepared for maintenance. This estimate does not include the time necessary for: − Administrative functions such as planning, liaison, familiarization, and report writing. − Non productive elapsed time such as rest time, having meals, and crew shift changes. − Elapsed time such as for paint to dry, sealant to cure, and fuel tank venting. − Preparation for modification (unless specified in the accomplishment instructions) such as cleaning and getting parts, tools, consumables, and ground equipment. − Quality assurance inspections, troubleshooting and/or correction of discrepancies found when a task is done. − All other activities that are not considered by Bombardier as directly related to the accomplishment of this procedure. NOTE : For on−site labor assistance, please speak with a Fleet Services representative for a quote. The Fleet Services team can be contacted via the CRC at 514

– 855

– 8500 or email at thd.crj@aero.bombardier.com. It will take an estimated 8.0 man−hours to complete this service bulletin. The man−hours are divided as shown in the table that follows: 

### SERVICE BULLETIN 670BA−36−014

S.B. 670BA−36−014 Page 3 of 25 Apr 07/2011 Revision A, Oct 11/2011TASK MAN−HOURS (1) Job Set−Up 2.5 (2) Procedure 3.0 (3) Test 1.0 (4) Job Close−Out 1.5 G. Material − Price and Availability (1) The kit in the table that follows is available from Bombardier commercial aircraft. Refer to the paragraphs below for the terms and conditions. NOTE : For a list of the kit contents, refer to paragraph 3.A.

KIT NUMBER NAME 670BA36014K1 Kit−Rudder Quadrant Shielding (2) Please send a purchase order to the address below to schedule the kit: Bombardier Service Bulletin Kit Support Team 123 Garratt Blvd, N42

– 24 Toronto, Ontario Canada M3K 1Y5 Fax: 416−375−3060 Phone: 416−375−3920 email: sbkits@aero.bombardier.com Please contact your Service Bulletin Kit Support Team at the address above for terms and conditions. (3) Refer to paragraph 3.B. for a list of consumables for this service bulletin. H. Tooling − Price and Availability There are no tool kits for this service bulletin. (1) Refer to paragraph 3.C. for a list of special tools and equipment for this service bulletin. 

### SERVICE BULLETIN 670BA−36−014

S.B. 670BA−36−014 Page 4 of 25 Apr 07/2011 Revision A, Oct 11/2011I. Weight and Balance For CL−600−2C10 aircraft

WEIGHT ARM MOMENT [1] 1.5 (lbs) 1219.5 (in.) 1.829 (1000 lb·in) 0.7 (kg) 30.98 (m) 0.021 (1000 kg·m) [1] The value in the Moment column is divided by 1000. Refer to the Weight & Balance Manual CSP B−041.
For CL−600−2D15 aircraft For CL−600−2D24 aircraft

WEIGHT ARM MOMENT [1] 1.5 (lbs) 1371.5 (in.) 2.057 (1000 lb·in) 0.7 (kg) 34.84 (m) 0.024 (1000 kg·m) [1] The value in the Moment column is divided by 1000. Refer to the Weight & Balance Manual CSP C−041.
J. Electrical Load Data Not changed. K. References − Restriction and/or Special Instruction (RSI), C−36−1019−00, Revision A. − Modification Summary 670T31879, Revision A−2. − Aircraft Maintenance Manual (AMM). − Structural Repair Manual (SRM). − For Bombardier reference only: PCA 73660 & 71971, and DCP BA670−10705. L. Other Publications Affected − Aircraft Illustrated Parts Catalog (IPC). − Aircraft Maintenance Manual (AMM). 

### SERVICE BULLETIN 670BA−36−014

S.B. 670BA−36−014 Page 5 of 25 Apr 07/2011 Revision A, Oct 11/2011M. Relationship Chart Not applicable. 

### SERVICE BULLETIN 670BA−36−014

S.B. 670BA−36−014 Page 6 of 25 Apr 07/2011 Revision A, Oct 11/20112. ACCOMPLISHMENT INSTRUCTIONS A. Job Set−Up (1) Reference Information
REFERENCE DESIGNATION AMM 12−00−00−867−801 Standard Aircraft Configuration for Maintenance AMM 20−21−00−910−801 Torquing of Threaded Fasteners AMM 21−00−00−910−801 Air−Conditioning/Pressurization Safety Precautions AMM 21−53−00−790−801 Leak Test of the Filtering and Flow Control System AMM 21−53−16−000−801 Removal of the Pack Supply Duct AMM 21−53−16−400−801 Installation of the Pack Supply Duct AMM 23−71−00−710−802 Operational Test of the Cockpit Voice Recorder (CVR) System AMM 23−71−01−000−801 Removal of the Cockpit Voice Recorder (CVR) AMM 23−71−01−400−801 Installation of the Cockpit Voice Recorder (CVR) AMM 24−00−00−910−801 Electrical/Electronic Safety Precautions AMM 24−32−03−000−801 Removal of the APU Battery AMM 24−32−03−400−801 Installation of the APU Battery AMM 24−32−03−710−801 Operational Test of the APU Battery AMM 24−32−07−710−801 Operational Test of the APU Battery Charger AMM 31−31−01−710−801 Operational Test of the Flight Data Recorder (FDR) AMM 31−31−01−000−801 Removal of the Flight Data Recorder (FDR) 

### SERVICE BULLETIN 670BA−36−014

S.B. 670BA−36−014 Page 7 of 25 Apr 07/2011 Revision A, Oct 11/2011REFERENCE DESIGNATION AMM 31−31−01−400−801 Installation of the Flight Data Recorder (FDR) AMM 36−10−00−790−801 Leak Test of the Bleed−Air Distribution System AMM 36−19−03−000−801 Removal of the APU Bleed−Air Duct AMM 36−19−03−400−801 Installation of the APU Bleed−Air Duct AMM 36−21−00−910−801 Bleed−Air Leak−Detection−Elements and Components Maintenance Practices AMM 51−23−00−390−804 Faying Surface Sealing AMM 51−23−00−390−810 Wet Installation of Fasteners SRM 51−21−11−001−001 Corrosion Prevention Procedures SRM 51−25−06−001−001 Fluid−Resistant (FR) Epoxy Primer SRM 51−25−16−001−001 Fluid−Resistant (FR) Polyurethane Topcoat SRM 51−26−00−001−001 Cleaning SRM 51−41−02−001−001 Bolts, Screws and Related Items SRM 51−42−21−001−001 Hi−lite Fasteners (2) Tolerance Information

Linear Tolerances Angular Tolerance X.XX in. (X.X mm) X.X in. (X mm) +/−0°30 ” +/−0.03 in. +/−0.1 in. +/−0.8 mm +/−3 mm NOTE : The tolerances above apply to the dimensions given in this service bulletin except if specified differently. 

### SERVICE BULLETIN 670BA−36−014

S.B. 670BA−36−014 Page 8 of 25 Apr 07/2011 Revision A, Oct 11/2011(3) Make sure that the aircraft is in standard configuration for maintenance (AMM 12−00−00−867−801). (4) Obey all the electrical/electronic safety precautions (AMM 24−00−00−910−801). (5) Obey all the air−conditioning pressurization safety precautions (AMM 21−00−00−910−801). (6) Obey all the bleed−air leak−detection−elements and components maintenance practices (AMM 36−21−00−910−801). (7) Open, safety, and tag the circuit breakers that follow:

CB−PANEL CB NO. NAME CBP−1 K6 ACS CONT 2 CH A CBP−1 L1 ACS CONT 1 CH A CBP−1 LOWER R9 FUEL SOV APU CBP−2 E5 APU CHARGER CBP−2 J4 ACS CONT 1 CH B CBP−2 K6 ACS R MAN CBP−2 LOWER T7 ACS CONT 2 CH B CBP−2 LOWER T8 ACS L MAN CBP−5 A3 APU BATT CONT (8) Open the aft equipment compartment door. (9) Remove the APU battery (AMM 24−32−03−000−801). (10) Remove the left pack supply ducts if necessary (AMM 21−53−16−000−801). (11) Remove the APU duct if necessary (AMM 36−19−03−000−801). Refer to Figure 1. 

### SERVICE BULLETIN 670BA−36−014

S.B. 670BA−36−014 Page 9 of 25 Apr 07/2011 Revision A, Oct 11/2011(12) Remove the drip tray (12) as follows: (a) Remove the screws (10) and the washers (11). (b) Remove the drip tray (12) from the main drip tray (9). (13) Remove the main drip tray (9) as follows: (a) Remove the screws (13) and the washers (14). (b) Remove the screws (15) and the washers (16). (c) Remove the main drip tray (9). (14) Remove the drain tube (1) as follows: (a) Cut the cable ties (2). (b) Remove the screw (3), the washer (4), and the clamp (5) from the standoff. (c) Disconnect and remove the drain tube (1). (15) Remove the CVR (AMM 23−71−01−000−801). (16) Remove the CVR mounting tray (17) as follows: (a) Remove the screws (18) and the washers (19). (b) Remove the screws (20). (c) Move the CVR mounting tray (17) aft of the support structure. (17) Remove the FDR (AMM 31−31−01−000−801). (18) Remove the FDR mounting tray (21) as follows: (a) Remove the screws (22) and the washers (23). (b) Remove the screws (24). (c) Move the CVR mounting tray (21) aft of the support structure. 

### SERVICE BULLETIN 670BA−36−014

S.B. 670BA−36−014 Page 10 of 25 Apr 07/2011 Revision A, Oct 11/2011B. Procedure Refer to Figure 2. (1) Drill two 0.098 in. (2.49 mm) diameter holes through the intercostal as follows: (a) Use a clean lint−free cloth, moist with isopropyl alcohol or the equivalent, and clean the outboard surface of the intercostal in the area of the quadrant support. (b) Make a vertical line with a marker on the outboard surface of the intercostal, at 0.87 in. (22.1 mm) from the aft vertical row of rivets that attach the quadrant support to the intercostal. (c) At the location of the vertical line, make a horizontal line with a marker at 1.64 in. (41.7 mm) from the lower flange of the intercostal. (d) Make sure that the distance between the intersection of the two lines and the edges of the quadrant support is 0.275 in. (7.00 mm) minimum. (e) Make a vertical line with a marker on the outboard surface of the intercostal, at 2.99 in. (76.0 mm) from the forward vertical row of rivets that attach the quadrant support to the intercostal. (f) At the location of the vertical line, make a horizontal line with a marker at 2.00 in. (50.8 mm) from the lower flange of the intercostal. (g) Make sure that the distance between the intersection of the two lines and the edges of the quadrant support is 0.275 in. (7.00 mm) minimum. (h) At the marked locations, drill two holes to a diameter of 0.098 in. (2.49 mm). (2) Assemble the top plate (3) on the brackets (1) and (2) with the bolts (4) and the washers (5) as shown in view (C). (3) Tighten the bolts (4) with your hand. (4) Drill the brackets (1) and (2) as follows: (a) Align the upper hole in the bracket (1) with the forward 0.098 in. (2.49 mm) diameter hole in the intercostal. 

### SERVICE BULLETIN 670BA−36−014

S.B. 670BA−36−014 Page 11 of 25 Apr 07/2011 Revision A, Oct 11/2011(b) Align the lower hole in the bracket (2) with the aft 0.098 in. (2.49 mm) diameter hole in the intercostal. (c) Install, temporarily, the assembled brackets (1) and (2) on the outboard face of the intercostal. (d) Adjust the position of the top plate (3) to get a minimum clearance of 0.25 in. (6.4 mm) between the inboard face of the top plate (3), and the rudder quadrant (refer to view D). (e) Backdrill three holes to a diameter of 0.1590 to 0.1620 in. (4.038 to 4.115 mm) from the bracket (1) to the intercostal. (f) Backdrill three holes to a diameter of 0.1590 to 0.1620 in. (4.038 to 4.115 mm) from the bracket (2) to the intercostal. NOTE : The minimum edge distance is 2 times the diameter of the holes. NOTE : The minimum distance between the center of the holes and the adjacent row of rivets is 4.5 times the diameter of the holes. (5) Remove the assembled brackets (1) and (2) from the intercostal. (6) Remove the brackets (1) and (2) from the top plate (3). (7) Remove the burrs and sharp edges from the brackets (1) and (2) and the adjacent structure. (8) Apply chemical conversion coating to the bare metal areas. (9) Apply faying surface sealant on the mating surfaces of the brackets (1) and (2) and the intercostal. (10) Install the brackets (1) and (2) on the intercostal as follows: (a) Wet−install three Hi−lites (6) and the collars (7) to the bracket (1) and the intercostal. (b) Wet−install three Hi−lites (6) and the collars (7) to the bracket (2) and the intercostal. (c) Apply fluid−resistant primer on the Hi−lites (6) and the collars (7). (d) Apply polyurethane topcoat on the Hi−lites (6) and the collars (7). (11) Install the pack supply ducts if removed (AMM 21−53−16−400−801). 

### SERVICE BULLETIN 670BA−36−014

S.B. 670BA−36−014 Page 12 of 25 Apr 07/2011 Revision A, Oct 11/2011(12) If removed, install the APU duct (AMM 36−19−03−400−801). (13) Install the top plate (3) on the brackets (1) and (2) as follows: (a) Install the top plate (3) on the brackets (1) and (2) with the bolts (4) and the washers (5). (b) Do not apply the final torque at this step. (c) Adjust the position of the top plate (3) to get the conditions that follow, (refer to view D): − A minimum clearance of 0.50 in. (12.7 mm) between the outboard edge of the top plate (3) and the bleed leak elements. − A minimum clearance of 0.25 in. (6.4 mm) between the inboard face of the top plate (3) and the rudder quadrant. − A minimum clearance of 0.20 in. (5.1 mm) between the top plate (3) and the p−clamp on the APU duct. (d) If you cannot get a clearance of 0.20 in. (5.1 mm) between the top plate (3) and the p−clamp on the APU duct, move the p−clamp until you can get it. NOTE : The p−clamp must not touch the vent hole washer on the duct. (14) Tighten the four bolts (4). 

### SERVICE BULLETIN 670BA−36−014

S.B. 670BA−36−014 Page 13 of 25 Apr 07/2011 Revision A, Oct 11/2011ba7034a01.cgm, eg/cr , 28/0911 EXHAUST DUCT (REF) V. STAB55%

1 DRIP TRAY (REF)

A

B

C A

0.20 in. (5.08 mm) MINIMUM

1

2 B C

2

1 C FWD

D

4 3 5 STGR17

D SUPPORT (REF) SUPPORT (REF) 1 LEGEND 1. Tube. 2. Cable tie. 3. Screw. 4. Washer. 5. Clamp. 6. Cable loom. 7. Standoff. 8. Exhaust port, ram air.

7
6 

### SERVICE BULLETIN 670BA−36−014

Drain Tube − Removal/Installation Figure 1 (Sheet 1 of 4)

S.B. 670BA−36−014 Page 14 of 25 Apr 07/2011 Revision A, Oct 11/2011ba7034a02.cgm, eg/cr, 22/09/2011 E STGR14 V. STAB 55%

12 9 22 F E

F STGR14 11 10

10 11 ANGLE (REF)

SUPPORT (REF) LEGEND 9. Main drip tray. 10. Screw. 11. Washer. 12. Drip tray. 

### SERVICE BULLETIN 670BA−36−014

Drain Tube − Removal/Installation Figure 1 (Sheet 2 of 4)

S.B. 670BA−36−014 Page 15 of 25 Apr 07/2011 Revision A, Oct 11/2011ba7034a03.cgm, eg/cr, 23/09/11 V. STAB 55%

9 13

14

E G

CVR (REF) RADIO ALTIMETER (REF)

RADIO ALTIMETER CONVECTOR (REF) 15 16

ANGLE (REF) ANGLE (REF)

G LEGEND 9. Main drip tray. 13. Screw. 14. Washer. 15. Screw. 16. Washer. 

### SERVICE BULLETIN 670BA−36−014

Drain Tube − Removal/Installation Figure 1 (Sheet 3 of 4)

S.B. 670BA−36−014 Page 16 of 25 Apr 07/2011 Revision A, Oct 11/201122 23 21 CONNECTOR A65AP1(REF)

24

CONNECTOR A59P1(REF)

18 19

20

17

CVR MOUNTING TRAY FDR MOUNTING TRAY H Hba7034a04.cgm, eg/cr, 23/09/11 LEGEND 17. CVR Mounting tray. 18. Screw. 19. Washer. 20. Screw. 21. FDR Mounting tray. 22. Screw. 23. Washer. 24. Screw. J

J SUPPORT STRUCTURE (REF) SUPPORT STRUCTURE (REF)

3 

### SERVICE BULLETIN 670BA−36−014

Drain Tube − Removal/Installation Figure 1 (Sheet 4 of 4)

S.B. 670BA−36−014 Page 17 of 25 Apr 07/2011 Revision A, Oct 11/2011ba6450a01.cgm
B A A

2.99 in. (76.0 mm)

2.00 in. (50.8 mm) 0.87 in. (22.1 mm)

1.64 in. (41.7 mm) B

QUADRANT SUPPORT (REF.)

INTERCOSTAL (REF.) V STAB 67.5% REAR SPAR (REF.)

NOTE THE DISTANCE BETWEEN THE CENTER OF THE HOLE AND THE ADJACENT QUADRANT SUPPORT MUST BE 0.275 IN. (7.0 mm) MINIMUM. 1 1 1 

### SERVICE BULLETIN 670BA−36−014

Rudder Quadrant Shields Installation Figure 2 (Sheet 1 of 3)

S.B. 670BA−36−014 Page 18 of 25 Apr 07/2011 Revision A, Oct 11/2011A LEGEND 1. Bracket BA670−35541−1SB. 2. Bracket BA670−35542−1SB. 3. Top plate BA670−35543−1. 4. Bolt NAS6703U2. 5. Washer NAS1149C0316R. 6. Hi−lite B0206003AG5−3. 7. Collar B0206017TP5.
1 2

3 4 5 6

7 6

C Cba6450a02.cgm INTERCOSTAL (REF.) 

### SERVICE BULLETIN 670BA−36−014

Rudder Quadrant Shields Installation Figure 2 (Sheet 2 of 3)

S.B. 670BA−36−014 Page 19 of 25 Apr 07/2011 Revision A, Oct 11/2011P−CLAMP (REF.)ba6450a03.cgm D

A

D 3 1

ANTI−ICE DUCT (REF.) VENT HOLE WASHER (REF.)

0.25 in. (6.4 mm) MINIMUM RUDDER QUADRANT ASSEMBLY (REF.) 2 LEGEND 1. Bracket BA670−35541−1SB. 3. Top plate BA670−35543−1.

INTERCOSTAL (REF.)

ELEMENT (REF.) NOTE THE DISTANCE BETWEEN THE P−CLAMP AND THE TOP PLATE (3) MUST BE 0.20 IN. (5.1 mm) MINIMUM. 2 

### SERVICE BULLETIN 670BA−36−014

Rudder Quadrant Shields Installation Figure 2 (Sheet 3 of 3)

S.B. 670BA−36−014 Page 20 of 25 Apr 07/2011 Revision A, Oct 11/2011C. Job Close−Out Refer to Figure 1. (1) Install the FDR mounting tray (21) as follows: (a) Put the FDR mounting tray (21) in position on the support structure. (b) Install the screws (18) and the washers (19). (c) Install the screws (20). (2) Install the FDR (AMM 31−31−01−400−801). (3) Install the CVR mounting tray (17) as follows: (a) Put the CVR mounting tray (17) in position on the support structure. (b) Install the screws (22) and the washers (23). (c) Install the screws (24). (4) Install the CVR (AMM 23−71−01−400−801). (5) Install the drain tube (1) as follows: (a) Install the drain tube (1) on the cable looms (6) with the cable ties (2). (b) Install the cable ties (2) manually. Make sure that the drain tube (1) stays in position and has no deformation. (c) Make sure you have the correct length to attach the drain tube (1) to the ram−air exhaust−port (8). (d) Attach the clamp (5) to the standoff (7) with the screw (3) and the washer (4). (e) Connect the drain tube (1) to the ram−air exhaust−port (8) as follows: 1 Install the drain tube (1) on the ram−air exhaust−port (8). 2 Install the cable tie (2) on the drain tube (1) above the bead of the ram−air exhaust−port (8). Make sure the tube (1) is at least 0.20 in. (5.08 mm) above the cable tie (2). (6) Install the main drip tray (9) with the screws (13) and (15) and the washers (14) and (16). 

### SERVICE BULLETIN 670BA−36−014

S.B. 670BA−36−014 Page 21 of 25 Apr 07/2011 Revision A, Oct 11/2011(7) Install the drip tray (12) with the screws (10) and the washers (11). (8) Remove all tools, equipment, and unwanted materials from the work area. (9) Install the APU battery (AMM 24−32−03−400−801). (10) Remove the tags and close the circuit breakers that follow:

CB−PANEL CB NO. NAME CBP−1 K6 ACS CONT 2 CH A CBP−1 L1 ACS CONT 1 CH A CBP−1 LOWER R9 FUEL SOV APU CBP−2 E5 APU CHARGER CBP−2 J4 ACS CONT 1 CH B CBP−2 K6 ACS R MAN CBP−2 LOWER T7 ACS CONT 2 CH B CBP−2 LOWER T8 ACS L MAN CBP−5 A3 APU BATT CONT (11) Do a leak test of the bleed−air distribution system (AMM 36−10−00−790−801). (12) Do a leak test of the filtering and flow control system (AMM 21−53−00−790−801). (13) Do an operational test of the CVR (AMM 23−71−00−710−802). (14) Do an operational test of the APU battery (AMM 24−32−03−710−801). (15) Do an operational test of the APU battery charger (AMM 24−32−07−710−801). (16) Do an operational test of the FDR (AMM 31−31−01−710−801). (17) Close the aft equipment compartment door. 

### SERVICE BULLETIN 670BA−36−014

S.B. 670BA−36−014 Page 22 of 25 Apr 07/2011 Revision A, Oct 11/2011(18) When this service bulletin is completed, add the weight and balance data shown in paragraph 1.I. of this service bulletin to the Weight and Balance Manual. Under ‘Description of Change’ enter "Service Bulletin 670BA−36−014 Revision A , incorporated." (19) When this service bulletin is completed, make this entry in the applicable logbook(s): "Service Bulletin 670BA−36−014 Revision A , Pneumatic − Bleed Air System − Installation of Protective Shields on the Rudder Quadrant Support−Beam, incorporated." 

### SERVICE BULLETIN 670BA−36−014

S.B. 670BA−36−014 Page 23 of 25 Apr 07/2011 Revision A, Oct 11/20113. MATERIAL INFORMATION A. Kit Information Kit Content:

670BA36014K1

PART NUMBER QUANTITY [1] NAME ALTERNATE PART(S) NOTES

B0206003AG5−3 7 Hi−Lite B0206017TP5 7 Collar BA670−35541−1SB 1 Forward Bracket BA670−35542−1SB 1 Aft Bracket BA670−35543−1 1 Top Plate NAS1149C0316R 5 Washers NAS6703U2 5 Bolt [1] The kit can contain more hardware and/or material than necessary. B. Consumable Information The materials that follow are necessary to do this service bulletin and can be ordered from Bombardier or purchased directly from industry sources. If the material is ordered from Bombardier, there can be some lead time because of shelf life of the material.

CONSUMABLES

SPECIFICATION QUANTITY NAME REFERENCE MIL−PRF−81733 Type IV As necessary Sealant, Pressure and Environmental 09−022 [1] 

### SERVICE BULLETIN 670BA−36−014

S.B. 670BA−36−014 Page 24 of 25 Apr 07/2011 Revision A, Oct 11/2011CONSUMABLES

SPECIFICATION QUANTITY NAME REFERENCE MIL

– C

– 81706 Class 1A As necessary Compound, chemical conversion, for coating aluminum and aluminum alloys Alodine 1200S or equivalent 05

– 025 [1]

None As necessary Cloths, cleaning, low−lint 05−046 [1]
TT−I−735 As necessary Alcohol isopropyl 11−004 [1]
CMS 565−01 As necessary Fluid−resistant epoxy primer 13−006 [1]
CMS 565−02 As necessary Polyurethane topcoat, fluid−resistant (for aircraft interiors). 07−001 [1] Color: White #17875, FED−STD−595 [1] Refer to AMM 51−31−00−992−801. NOTE : To complete this list of consumables, refer to the different tasks given as references in this service bulletin. C. Special Tools and Equipment For a list of special tools and equipment, refer to the different tasks given as references in this service bulletin. D. Disposition of Parts Not applicable. 

### SERVICE BULLETIN 670BA−36−014

S.B. 670BA−36−014 Page 25 of 25 Apr 07/2011 Revision A, Oct 11/2011THANK YOU FOR ANSWERING THIS EVALUATION FORM UPON COMPLETION OF THIS EVALUATION FORM/COMPLIANCE SHEET, FAX TO 450-476-7300 

### SERVICE BULLETIN EVALUATI ON FORM/COMPLIANCE SHEET (YOUR IDEAS WILL HELP US PROVIDE BETTER BULLETINS)
SERVICE BULLETIN : 670BA-36-014 ISSUE: A

STRONGLY DISAGREE NEUTRAL AGREE STRONGLY DISAGREE AGREE
• Instructions to do the Service Bulletin were accurate. Comments: 

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• Illustration(s), figure(s), picture(s) and/or kit drawing(s) were helpful to carry out instructions. Comments: 

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• If a parts kit was required, did the kit contents received agree with the contents listed in the bulletin? Comments: 

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• Aircraft hands-on work was accomplished in estimated time. Comments: 

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• Overall, I was satisfied with this Service Bulletin. Comments: 

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PLEASE SUPPLY US WITH THE FOLLOWING DATA AND FAX TO (450) 476-7300: OPERATOR: NAME (Please print) SERVICE CENTER: TELEPHONE: AIRCRAFT SERIAL NO.: FACSIMILE: DATE OF SB INCORPOARTION