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 11/2011
Bombardier 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 11/2011
TASK 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 11/2011
I. 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

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Apr 07/2011

Revision A, Oct 11/2011
M. Relationship Chart

Not applicable.

SERVICE BULLETIN 670BA−36−014

S.B. 670BA−36−014

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Apr 07/2011

Revision A, Oct 11/2011
2. 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

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Revision A, Oct 11/2011
REFERENCE 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)

+/−0.03 in. +/−0.1 in. +/−0°30”

+/−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

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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

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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

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Revision A, Oct 11/2011
B. 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

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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

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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

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Revision A, Oct 11/2011
ba7034a01.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)

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Revision A, Oct 11/2011
ba7034a02.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

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Revision A, Oct 11/2011
ba7034a03.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)

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Revision A, Oct 11/2011
22

23

21

CONNECTOR

A65AP1(REF)

24

CONNECTOR

A59P1(REF)

18

19

20

17

CVR MOUNTING TRAY

H FDR MOUNTING TRAY

H

ba7034a04.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)

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Revision A, Oct 11/2011
ba6450a01.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)

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Revision A, Oct 11/2011
A

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

C

ba6450a02.cgm

INTERCOSTAL (REF.)

SERVICE BULLETIN 670BA−36−014

Rudder Quadrant Shields Installation

Figure 2 (Sheet 2 of 3)

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Revision A, Oct 11/2011
P−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)

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Revision A, Oct 11/2011
C. 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

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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 11/2011
3. 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 11/2011
CONSUMABLES

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 11/2011
THANK YOU FOR ANSWERING THIS EVALUATION FORM 

UPON COMPLETION OF THIS EVALUATION FORM/COMPLIANCE SHEET, FAX TO 

450-476-7300 

SERVICE BULLETIN EVALUATION 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:

    

• Illustration(s), figure(s), picture(s) and/or 

kit drawing(s) were helpful to carry out 

instructions. 

Comments:

    

• If a parts kit was required, did the kit 

contents received agree with the 

contents listed in the bulletin? 

Comments: 

    

• Aircraft hands-on work was 

accomplished in estimated time. 

 Comments:

    

• Overall, I was satisfied with this Service 

Bulletin. 

 Comments: 

    

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