Landing Gear − Landing−Gear Hydraulic Extension/Retraction − Inspection of

the Main Landing Gear (MLG) Retraction−Actuator Bracket and the Related

Pins

These pages transmit:

Revision B of Service Bulletin 670BA−32−033,

pages 1 thru 13, dated Jun 26/2012.

The changes in this revision have no effect on aircraft that have incorporated a

previous issue of this service bulletin.

Reason:

Revised Planning Information, paragraph 1., to:

Add aircraft 10002, and remove aircraft serial numbers 10265 and 15118 thru

15154 from the effectivity table.

Change the MLG dressed shock−struts’ part numbers/serial numbers.

Revised Accomplishment Instructions, paragraph 2., to:

Change some steps.

This revision also includes small editorial changes that do not have an effect on the

technical content.

Document Instructions:

Discard the copy of Service Bulletin 670BA−32−033 Revision A, dated Jul 29/2011.

Replace with the copy attached.

SERVICE BULLETIN 670BA−32−033

S.B. 670BA−32−033

Page 1 of 2

Jun 26/2012

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

SUBJECT:
Discard GOODRICH SERVICE BULLETIN 49000−32−46, REVISION 1 dated Jan

10/08. Replace with GOODRICH SERVICE BULLETIN 49000−32−46, REVISION 2

dated Nov 11/11.

Service Bulletin History:

Initial issue, dated Mar 14/2011.

Revision A, dated Jul 29/2011

SERVICE BULLETIN 670BA−32−033

S.B. 670BA−32−033

Page 2 of 2

Jun 26/2012
Landing Gear − Landing−Gear Hydraulic Extension/Retraction − Inspection of

the Main Landing Gear (MLG) Retraction−Actuator Bracket and the Related

Pins

1. PLANNING INFORMATION

A. Effectivity

(1) Aircraft with the following components installed:

MLG−Dressed Shock

Strut (LH) part number:

P/N: 49000−5 through P/N

49000−27

P/N: 49050−5 through P/N

49050−11

MLG−Dressed Shock

Strut (LH) serial number:

MA0007 thru MA0431 MA0039 thru MA1231

MLG−Dressed Shock

Strut (RH) part number:

P/N: 49000−6 through P/N

49000−28

P/N: 49050−6 through P/N

49050−12

MLG−Dressed Shock

Strut (RH) serial

number:

MA0007 thru MA0432 MA0039 thru MA1234

Installed at the time of

delivery on

CL−600−2C10 aircraft

with serial numbers:

10002 thru 10264 [1]

SERVICE BULLETIN

ATA SYSTEM: 32−32 NUMBER: 670BA−32−033

S.B. 670BA−32−033

Page 1 of 14

Mar 14/2011

Revision B, Jun 26/2012

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:
Installed at the time of

delivery on

CL−600−2D15 and

CL−600−2D24 aircraft

with serial numbers:

15001 thru 15117 [1]

Spares: Examine all spare parts. If a part with a serial number listed

above is found, it is necessary to incorporate Goodrich

service bulletin 49000−32−46.

All CL−600−2C10,

CL−600−2D15, and

CL−600−2D24 aircraft:

If parts with the serial numbers listed above are installed on

aircraft, but were not identified at the time of delivery, on the

same or on a different aircraft model, it is necessary to

incorporate Goodrich service bulletin 49000−32−46.

Production: [1] There is no production effectivity.

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.

B. Reason

(1) Condition

Corrosion on the MLG retraction−actuator bracket and the related pins can

cause the MLG to incorrectly extend.

(2) Evidence

Corrosion was found on some retraction−actuator brackets on in−service

aircraft.

(3) Objective/Benefit

This service bulletin gives the procedure to do Goodrich Service Bulletin

49000−32−46. This will make sure that the MLG retraction−actuator bracket

and the related pins are not corroded, that corrosion protection is enhanced,

and the MLG retraction actuators operate correctly.

C. Description

Circuit breakers are opened. The aircraft is put on jacks.

SERVICE BULLETIN 670BA−32−033

S.B. 670BA−32−033

Page 2 of 14

Mar 14/2011

Revision B, Jun 26/2012
The MLG retraction actuators and the auxiliary actuators are disconnected from

the brackets or if necessary removed from the aircraft. Goodrich Service Bulletin

49000−32−46 is done. The MLG retraction actuators and the auxiliary actuators

are connected to the brackets or installed.

The circuit breakers are closed. The operational tests of the landing−gear

extension/retraction system and the landing−gear alternate extension system are

done. The aircraft is removed from jacks.

D. Compliance

Recommended Service Bulletin.

Bombardier recommends that this service bulletin be done no more than 4400

flight hours or no later than 2 years from the release date on this service bulletin,

whichever comes first, unless otherwise directed by the airworthiness authority of

the operator.

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.

SERVICE BULLETIN 670BA−32−033

S.B. 670BA−32−033

Page 3 of 14

Mar 14/2011

Revision B, Jun 26/2012
− 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 7.0 man−hours to complete this service bulletin. The

man−hours are divided as shown in the table that follows:

TASK MAN−HOURS

(1) Job Set−Up 2.0

(2) Procedure 1.0

(3) Test 2.0

(4) Job Close−Out 2.0

NOTE: This estimate does not include the man−hours necessary to do

Goodrich Service Bulletin 49000−32−46.

G. Material − Price and Availability

(1) Refer to Goodrich Service Bulletin 49000−32−46.

(2) 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.

I. Weight and Balance

Not changed.

J. Electrical Load Data

Not changed.

K. References

− Restriction and/or Special Instruction (RSI), C−32−1357−00, Revision B.

SERVICE BULLETIN 670BA−32−033

S.B. 670BA−32−033

Page 4 of 14

Mar 14/2011

Revision B, Jun 26/2012
− Goodrich Service Bulletin 49000−32−46, Revision 2, dated Nov 11/11.

− Aircraft Maintenance Manual (AMM).

− Electrical/Electronic Components − Standard Practices Manual (ESPM).

− For Bombardier reference only: PCA 73949 and 74323.

L. Other Publications Affected

None.

M. Relationship Chart

Not applicable.

SERVICE BULLETIN 670BA−32−033

S.B. 670BA−32−033

Page 5 of 14

Mar 14/2011

Revision B, Jun 26/2012
2. ACCOMPLISHMENT INSTRUCTIONS

A. Job Set−Up

(1) Reference Information

REFERENCE DESIGNATION

AMM 07−11−01−582−801 Jacking of the Aircraft

AMM 07−11−01−586−801 Lowering of the Aircraft

AMM 12−00−00−867−801 Standard Aircraft Configuration for

Maintenance

AMM 12−00−06−862−801 Pressurize Hydraulic System No. 1

and No. 2

AMM 12−00−06−862−802 Release Hydraulic Pressure of

System No. 1 and No. 2

AMM 12−00−06−862−803 Pressurize Hydraulic System No. 3

AMM 12−00−06−862−804 Release Hydraulic Pressure of

System No. 3

AMM 20−21−00−910−801 Torquing of Threaded Fasteners

AMM 20−51−00−000−801 Removal of Cotter Pins

AMM 20−51−00−400−801 Installation of Cotter Pins

AMM 24−00−00−910−801 Electrical/Electronic Safety

Precautions

AMM 29−00−00−910−802 Hydraulic Technical Precautions

AMM 29−10−00−870−801 Bleed Hydraulic Systems No. 1 and

No. 2

AMM 29−10−00−870−802 Bleed Hydraulic System No. 3

AMM 32−30−00−710−801 Operational Test of the

Landing−Gear Extension/Retraction

System

AMM 32−32−03−000−801 Removal of the MLG Auxiliary

Actuator

SERVICE BULLETIN 670BA−32−033

S.B. 670BA−32−033

Page 6 of 14

Mar 14/2011

Revision B, Jun 26/2012
REFERENCE DESIGNATION

AMM 32−32−03−400−801 Installation of the MLG Auxiliary

Actuator

AMM 32−32−05−000−801 Removal of the MLG

Retraction−Actuator

AMM 32−32−05−400−801 Installation of the MLG

Retraction−Actuator

AMM 32−34−00−710−801 Operational Check of the

Landing−Gear Alternate−Extension

System

(2) Make sure that the aircraft is in standard configuration for maintenance

(AMM 12−00−00−867−801).

(3) Obey all the electrical/electronic safety precautions (AMM

24−00−00−910−801).

(4) Open, safety, and tag the circuit breakers that follow:

CB−PANEL CB NO. NAME

CBP−1 F11 HYD SYST AC PUMP CONT 3B

CBP−1 F14 HYD SYST AC PUMP CONT 2

CBP−2 F14 HYD SYST AC PUMP CONT 3A

ACPC ACPC HYD PUMP 2B

(5) Obey all the hydraulic technical precautions (AMM 29−00−00−910−802).

(6) Release the hydraulic pressure of system No. 2 (AMM 12−00−06−862−802).

(7) Release the hydraulic pressure of system No. 3 (AMM 12−00−06−862−804).

(8) Put the aircraft on jacks (AMM 07−11−01−582−801).

B. Procedure

Refer to Figure 1.

NOTE: This procedure is applicable to the left and right sides. The procedure that

follows is written for the left side. The differences are given.

SERVICE BULLETIN 670BA−32−033

S.B. 670BA−32−033

Page 7 of 14

Mar 14/2011

Revision B, Jun 26/2012
(1) On the MLG, disconnect the retraction actuator (1) from the bracket (2) as

follows:

(a) Remove and discard the cotter pin (3) from the nut (4).

(b) Remove the nut (4), the washers (5), and the pin (6) that attach the rod

end of the retraction actuator (1) to the bracket (2).

(c) Move the rod end of the retraction actuator (1) away from the bracket

(2).

(2) On the MLG, disconnect the auxiliary actuator (7) from the bracket (2) as

follows:

(a) Remove and discard the cotter pin (8) from the nut (9).

(b) Remove the nut (9), the washer (10), the pin (12), and the sleeve

bearing (11) that attach the rod end of the auxiliary actuator (7) to the

bracket (2).

(c) Move the rod end of the auxiliary actuator (7) away from the bracket (2).

(3) If necessary, remove the auxiliary actuator (7) (AMM 32−32−03−000−801).

(4) If necessary, remove the retraction actuator (1) (AMM 32−32−05−000−801).

Refer to Figure 1.

(5) Do Goodrich service bulletin 49000−32−46 on the MLG dressed−shock

struts.

(6) If the auxiliary actuator (7) was removed, install the auxiliary actuator (7)

(AMM 32−32−03−400−801).

(7) If the auxiliary actuator (7) was not removed, install the rod end of the

auxiliary actuator (7) on the bracket (2) as follows:

(a) Lubricate the sleeve bearing (11) and the bushings on the bracket (2)

with grease.

(b) Extend the piston of the auxiliary actuator (7) as necessary to align the

holes of the rod end and the bracket (2).

(c) Apply a thin layer of corrosion inhibitor (Mastinox) to the thread, thread

and grind relief areas of the pin (12).

SERVICE BULLETIN 670BA−32−033

S.B. 670BA−32−033

Page 8 of 14

Mar 14/2011

Revision B, Jun 26/2012
(d) Remove the unwanted corrosion inhibitor from the pin (12).

(e) Install the sleeve bearing (11) and the pin (12) through the bracket (2)

and the rod end of the auxiliary actuator (7).

(f) Install the washer (10) and the nut (9) on the pin (12).

(g) Torque the nut (9) from 90 to 105 lbf·in (10.17 to 11.87 N·m).

(h) Safety the nut (9) with a new cotter pin (8).

(i) Apply a yellow anti−sabotage strip across the nut (9).

(8) If the retraction actuator (1) was removed, install the retraction actuator (1)

(AMM 32−32−05−400−801).

(9) If the retraction actuator (1) was not removed, install the rod end of the

retraction actuator (1) on the bracket (2) as follows:

(a) Lubricate the bushings on the bracket (2) with grease.

(b) Extend the piston of the retraction actuator (1) as necessary to align the

holes of the rod end and the bracket (2).

(c) Apply a thin layer of corrosion inhibitor (Mastinox) to the thread, thread

and grind relief areas of the pin (6).

(d) Remove the unwanted corrosion inhibitor from the pin (6).

(e) Install the pin (6) through the bracket (2) and the rod end of the

retraction actuator (1).

(f) Install the washers (5) and the nut (4) on the pin (6).

NOTE: It is permitted to install one or two washers to align the locking

mechanism of the pin (6) and the nut (4).

(g) Torque the nut (4) from 150 to 200 lbf·in (16.94 to 22.59 N·m) plus

running torque.

(h) Measure the gap between the washer (5) and the bracket (2).

(i) Make sure that the gap is between 0.005 and 0.034 in. (0.127 and 0.864

mm).

(j) Safety the nut (4) with a new cotter pin (3).

SERVICE BULLETIN 670BA−32−033

S.B. 670BA−32−033

Page 9 of 14

Mar 14/2011

Revision B, Jun 26/2012
(k) Apply a yellow anti−sabotage strip across the nut (4).

SERVICE BULLETIN 670BA−32−033

S.B. 670BA−32−033

Page 10 of 14

Mar 14/2011

Revision B, Jun 26/2012
B

A

LEGEND

1. Retraction actuator.

2. Bracket.

3. Cotter pin MS24665−376.

4. Nut.

5. Washer.

6. Pin.

A

B

C

C

6

5

3

4

2

ROD END

(REF)

BUSHING

(REF)

1

6

2 5

4

ROD END

(REF)

0.005 TO 0.034 in.

(0.127 TO 0.864 mm)

C − C

ba6863a01.cgm, mt,sc, 14Jan 11

SERVICE BULLETIN 670BA−32−033

Disconnection of the MLG Retraction and Auxiliary Actuator

Figure 1 (Sheet 1 of 2)

S.B. 670BA−32−033

Page 11 of 14

Mar 14/2011

Revision B, Jun 26/2012
LEGEND

2. Bracket.

7. Auxiliary actuator.

8. Cotter pin MS24665−304.

9. Nut.

10. Washer.

11. Sleeve bearing.

A

2

ROD END

(REF)

BUSHING

(REF)

9

8 10

11

12

7

12. Pin.

D

D

ba6863a02.cgm, mt/sc, 14 Jan 11

SERVICE BULLETIN 670BA−32−033

Disconnection of the MLG Retraction and Auxiliary Actuator

Figure 1 (Sheet 2 of 2)

S.B. 670BA−32−033

Page 12 of 14

Mar 14/2011

Revision B, Jun 26/2012
C. Job Close−Out

(1) Remove all tools, equipment, and unwanted materials from the work area.

(2) Remove the tags and close the circuit breakers that follow:

CB−PANEL CB NO. NAME

CBP−1 F11 HYD SYST AC PUMP CONT 3B

CBP−1 F14 HYD SYST AC PUMP CONT 2

CBP−2 F14 HYD SYST AC PUMP CONT 3A

ACPC ACPC HYD PUMP 2B

(3) Pressurize hydraulic system No. 2 (AMM 12−00−06−862−801).

(4) Pressurize hydraulic system No. 3 (AMM 12−00−06−862−803).

(5) If the retraction actuator (1) and/or the auxiliary actuator (7) were removed,

do as follows:

(a) Bleed Hydraulic Systems No. 2 (AMM 29−10−00−870−801).

(b) Bleed Hydraulic Systems No. 3 (AMM 29−10−00−870−802).

(6) Do an operational test of the landing−gear extension/retraction system

(AMM 32−30−00−710−801).

(7) Do an operational test of the landing−gear alternate extension system (AMM

32−34−00−710−801).

(8) Remove the aircraft from jacks (AMM 07−11−01−586−801).

(9) When this service bulletin is completed, make this entry in the applicable

logbook(s): "Service Bulletin 670BA−32−033, Revision B, Landing Gear −

Landing−Gear Hydraulic Extension/Retraction − Inspection of the Main

Landing Gear (MLG) Retraction−Actuator Bracket and the Related Pins,

incorporated."

SERVICE BULLETIN 670BA−32−033

S.B. 670BA−32−033

Page 13 of 14

Mar 14/2011

Revision B, Jun 26/2012
3. MATERIAL INFORMATION

A. Kit Information

None.

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

MS24665−376 2 Cotter pin

MS24665−304 2 Cotter pin

Not specified As

necessary

Grease,

Aeroshell #33 or

equivalent

04−010 [1]

F925 As

necessary

Seal, yellow

torque

09−033 [1]

6856K As

necessary

Corrosion

inhibitor

Mastinox

13−001 [1]

[1] Refer to AMM 51−31−00−992−801.

NOTE: To complete this list of consumables, refer to the different tasks, the

Goodrich service bulletin and appendix 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 and the Goodrich

service bulletin given as references in this service bulletin.

D. Disposition of Parts

Not applicable.

SERVICE BULLETIN 670BA−32−033

S.B. 670BA−32−033

Page 14 of 14

Mar 14/2011

Revision B, Jun 26/2012
THANK YOU FOR ANSWERING THIS EVALUATION FORM 

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

450-476-7300 or email to CRJ_SB_Evaluation_Form@aero.bombardier.com

SERVICE BULLETIN EVALUATION FORM/COMPLIANCE SHEET 

(YOUR IDEAS WILL HELP US PROVIDE BETTER BULLETINS) 

SERVICE BULLETIN : 670BA-32-033 ISSUE: B

 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