Landing Gear − Landing−Gear Hydraulic Extension/Retraction − Inspection of the Main Landing Gear (MLG) Retraction−Actuator and Installation of a New Jam nut These pages transmit: Revision C of Service Bulletin 670BA−32−031, pages 1 thru 18, dated Apr 17/2012. For aircraft that have incorporated a previous issue of this service bulletin, it is necessary to make sure that the time compliance is applied to the actuators. Refer to the Compliance section paragraph 1.D. for other changes.
Reason:

Revised the title of this service bulletin. Revised Planning Information, paragraph 1., to: Add aircraft serial number 10002 to the service bulletin effectivity. Add PART B for the accomplishment of Goodrich Service Bulletin 49600−32−64 and change the time compliance in the Compliance section. Revised Accomplishment Instructions, paragraph 2., to: Add PART B. This revision also includes small editorial changes that do not have an effect on the technical content. 

### SERVICE BULLETIN 670BA−32−031

S.B. 670BA−32−031 Page 1 of 2 Apr 17/2012 

# SERVICE BULLETIN REVISION TRANSMITTAL SHEET

SUBJECT:Document Instructions: Discard the copy of Service Bulletin 670BA−32−031, Revision B, dated Jul 29/2011. Replace with the copy attached.

KEEP GOODRICH SERVICE BULLETIN 49600−32−63, REVISION 1. DISCARD THE COPY OF GOODRICH SERVICE BULLETIN 49600−32−64, REVISION 2, AND REPLACE WITH 49600−32−64, REVISON 3. Service Bulletin History: Initial issue, dated Mar 14/2011. Revision A, dated Jun 09/2011. Revision B, dated Jul 29/2011. 

### SERVICE BULLETIN 670BA−32−031

S.B. 670BA−32−031 Page 2 of 2 Apr 17/2012Landing Gear − Landing−Gear Hydraulic Extension/Retraction − Inspection of the Main Landing Gear (MLG) Retraction−Actuator and Installation of a New Jam nut
1. PLANNING INFORMATION A. Effectivity (1) Aircraft with the following components installed: Part number: P/N 49600−5, 49600−7, and 49600−11 Serial number: SPP0001 thru SPP0388, SPP020389 thru SPP021300, SPP011301 thru SPP011318, SPP011355, and SPP011356. Installed at the time of delivery on CL−600−2C10 aircraft with serial numbers: 10002 thru 10320 [1]

Installed at the time of delivery on CL−600−2D15 and CL−600−2D24 aircraft with serial numbers: 15001 thru 15262 [1] 

# SERVICE BULLETIN

ATA SYSTEM: 32−32 NUMBER: 670BA−32−031

S.B. 670BA−32−031 Page 1 of 18 Mar 14/2011 Revision C, Apr 17/2012 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:Spares: Examine all spare parts. If a part with a serial number listed above is found, it is necessary to incorporate Goodrich service bulletin 49600−32−63 and 49600−32−64. 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 49600−32−63 and 49600−32−64. 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 Possible corrosion on the interface of the rod end and the piston of the MLG retraction actuator can cause the jam nut of the MLG retraction actuator to become loose. This can cause the rod end and the piston of the MLG retraction actuator to disconnect. (2) Evidence Corrosion was found on some retraction actuators during environmental qualification testing. (3) Objective/Benefit This service bulletin gives the procedure to do Goodrich Service Bulletin 49600−32−63 and 49600−32−64. This will make sure that the MLG retraction actuator is not corroded, the jam nut of the MLG retraction actuator is correctly torqued, and prevent the rod end and the piston of the MLG retraction actuator from being disconnected. C. Description This service bulletin is divided into 2 parts: PART A and PART B. PART A − Torque Inspection of the Jam Nut of the MLG Retraction Actuator Circuit breakers are opened. The access panels for the MLG retraction actuators 

### SERVICE BULLETIN 670BA−32−031

S.B. 670BA−32−031 Page 2 of 18 Mar 14/2011 Revision C, Apr 17/2012are removed. Goodrich Service Bulletin 49600−32−63 is done. If necessary, the MLG retraction actuators are disconnected or removed and installed. The circuit breakers are closed. The access panels for the MLG retraction actuators are installed. If the MLG retraction actuators were disconnected or removed, the operational tests of the landing−gear extension/retraction system and the landing−gear alternate extension system are done. PART B − Installation of the New Jam Nut on the MLG Retraction Actuator Circuit breakers are opened. The access panels for the MLG retraction actuators are removed. The MLG retraction actuators are removed. Goodrich Service Bulletin 49600−32−64 is done. The MLG retraction actuators are installed. The circuit breakers are closed. The access panels for the MLG retraction actuators are installed. The operational tests of the landing−gear extension/retraction system and the landing−gear alternate extension system are done. D. Compliance For Aircraft Pre−Goodrich SB 49600−32−64 Recommended Service Bulletin. Bombardier Aerospace recommends that PART A of this service bulletin be done as shown in the table that follows, unless otherwise directed by the airworthiness authority of the operator:

APPLICABLE TIME COMPLIANCE REPETITIVE ACTION
For actuators that have more than 8000 flight hours or more than four years from the entry−into−service/restoration date, whichever comes first. To be done before 1200 flight hours from the release date on this service bulletin. This service bulletin is to be repeated every 1200 flight hours from the initial incorporation date until PART B is done. For actuators that have 8000 flight hours or less and four years or less from the entry−into−service/restoration date. To be done before the actuators have 9200 flight hours or five years, whichever comes first.

Bombardier recommends that PART B of this service bulletin be done no more than 20 000 flight hours from the release date of this service bulletin, unless otherwise directed by the airworthiness authority of the operator. 

### SERVICE BULLETIN 670BA−32−031

S.B. 670BA−32−031 Page 3 of 18 Mar 14/2011 Revision C, Apr 17/2012For Aircraft Post−Goodrich SB 49600−32−64 It is not necessary to do this service bulletin. For all Aircraft 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. These estimates do 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. PART A − Torque Inspection of the Jam Nut of the MLG Retraction Actuator It will take an estimated 1.5 man−hours to complete PART A of this service bulletin. The man−hours are divided as shown in the table that follows: 

### SERVICE BULLETIN 670BA−32−031

S.B. 670BA−32−031 Page 4 of 18 Mar 14/2011 Revision C, Apr 17/2012TASK MAN−HOURS (1) Job Set−Up 0.50 (2) Procedure 0.25 (3) Test 0.00 (4) Job Close−Out 0.75 NOTE : This estimate does not include the man−hours necessary to do Goodrich Service Bulletin 49600−32−63. NOTE : This estimate does not include the man−hours necessary to remove or disconnect and install the MLG retraction actuators. PART B − Installation of the New Jam Nut on the MLG Retraction Actuator It will take an estimated 9.5 man−hours to complete PART B of 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 4.0 (3) Test 1.0 (4) Job Close−Out 2.5 NOTE : This estimate does not include the man−hours necessary to do Goodrich Service Bulletin 49600−32−64.
G. Material − Price and Availability (1) Refer to Goodrich Service Bulletins 49600−32−63 and 49600−32−64. (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 670BA−32−031

S.B. 670BA−32−031 Page 5 of 18 Mar 14/2011 Revision C, Apr 17/2012service bulletin. I. Weight and Balance Not changed. J. Electrical Load Data Not changed. K. References − Restriction and/or Special Instruction (RSI), C−32−1356−00, Revision B. − Goodrich Service Bulletin 49600−32−63, Revision 1, dated May 17/11. − Goodrich Service Bulletin 49600−32−64, Revision 3, dated Dec 15/11. − 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 PART A − Torque Inspection of the Jam Nut of the MLG Retraction Actuator Not applicable. PART B − Installation of the New Jam Nut on the MLG Retraction Actuator
PRE−SB

PART NUMBER NAME POST−SB PART NUMBER NAME

49600−11 Retraction Actuator 49600−13 Retraction Actuator 

### SERVICE BULLETIN 670BA−32−031

S.B. 670BA−32−031 Page 6 of 18 Mar 14/2011 Revision C, Apr 17/20122. ACCOMPLISHMENT INSTRUCTIONS PART A − Torque Inspection of the Jam Nut of the MLG Retraction Actuator 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 

### SERVICE BULLETIN 670BA−32−031

S.B. 670BA−32−031 Page 7 of 18 Mar 14/2011 Revision C, Apr 17/2012REFERENCE DESIGNATION 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 AMM 57−20−32−000−801 Removal of the Access Panel for the Main Landing Gear (MLG) Retraction Actuator (542AT/642AT) AMM 57−20−32−400−801 Installation of the Access Panel for the Main Landing Gear (MLG) Retraction Actuator (542AT/642AT) (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) Remove the access panels that follow:

PANEL NAME REFERENCE 542AT Access Panel AMM 57−20−32−000−801 642AT Access Panel AMM 57−20−32−000−801 

### SERVICE BULLETIN 670BA−32−031

S.B. 670BA−32−031 Page 8 of 18 Mar 14/2011 Revision C, Apr 17/2012(6) Obey all the hydraulic technical precautions (AMM 29−00−00−910−802). 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. (1) Do Goodrich Service Bulletin 49600−32−63. (a) If it is necessary to torque the jam nut during the incorporation of the Goodrich service bulletin, and it is too difficult to torque while installed, disconnect or remove the retraction actuator (1) as follows: 1 Release the hydraulic pressure of system No. 2 (AMM 12−00−06−862−802). 2 Release the hydraulic pressure of system No. 3 (AMM 12−00−06−862−804). 3 Put the aircraft on jacks (AMM 07−11−01−582−801). 4 On the MLG, remove and discard the cotter pin (3) from the nut (4). 5 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). 6 Move the rod end of the retraction actuator (1) away from the bracket (2). 7 If necessary, remove the retraction actuator (1) (AMM 32−32−05−000−801). (b) If the retraction actuator was disconnected, do as follows: 1 Lubricate the bushings on the bracket (2) with grease. 2 Extend the piston of the retraction actuator (1) as necessary to align the holes of the rod end and the bracket (2). 3 Apply a thin layer of corrosion inhibitor on the pin (6). 4 Remove the unwanted corrosion inhibitor from the pin (6). 5 Install the pin (6) through the bracket (2) and the rod end of the retraction actuator (1). 

### SERVICE BULLETIN 670BA−32−031

S.B. 670BA−32−031 Page 9 of 18 Mar 14/2011 Revision C, Apr 17/20126 Install the washers (5) and the nut (4) on the pin (6). NOTE : It is permitted to install one or two washers (5) to align the locking mechanism of the pin (6) and the nut (4). 7 Torque the nut (4) from 150 to 200 lbf·in (16.94 to 22.59 N·m) plus running torque. 8 Measure the gap between the washer (5) and the bracket (2). 9 Make sure that the gap is between 0.005 and 0.034 in. (0.127 and 0.864 mm). 10 Safety the nut (4) with a new cotter pin (3). 11 Apply a yellow anti−sabotage strip across the nut (4). (c) If the retraction actuator was removed, install the retraction actuator (1) (AMM 32−32−05−400−801). 

### SERVICE BULLETIN 670BA−32−031

S.B. 670BA−32−031 Page 10 of 18 Mar 14/2011 Revision C, Apr 17/2012ba6852a01.cgm, sc, 14Jan 11 B A

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 LEGEND 1. Retraction actuator. 2. Bracket. 3. Cotter pin MS24665−376. 4. Nut. 5. Washer. 6. Pin. 

### SERVICE BULLETIN 670BA−32−031

MLG Retraction−Actuator Figure 1

S.B. 670BA−32−031 Page 11 of 18 Mar 14/2011 Revision C, Apr 17/2012C. 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) Install the access panels that follow:

PANEL NAME REFERENCE 542AT Access Panel AMM 57−20−32−400−801 642AT Access Panel AMM 57−20−32−400−801 (4) If the retraction actuator was removed or disconnected, do as follows: (a) Pressurize hydraulic system No. 2 (AMM 12−00−06−862−801). (b) Pressurize hydraulic system No. 3 (AMM 12−00−06−862−803). (c) Bleed hydraulic systems No. 2 (AMM 29−10−00−870−801). (d) Bleed hydraulic systems No. 3 (AMM 29−10−00−870−802). (e) Do an operational test of the landing−gear extension/retraction system (AMM 32−30−00−710−801). (f) Do an operational test of the landing−gear alternate−extension system (AMM 32−34−00−710−801). (g) Remove the aircraft from jacks (AMM 07−11−01−586−801). 

### SERVICE BULLETIN 670BA−32−031

S.B. 670BA−32−031 Page 12 of 18 Mar 14/2011 Revision C, Apr 17/2012(5) When PART A of this service bulletin is completed, make this entry in the applicable logbook(s): "Service Bulletin 670BA−32−031, Revision C, Landing Gear − Landing−Gear Hydraulic Extension/Retraction − Inspection of the Main Landing Gear (MLG) Retraction−Actuator and Installation of a New Jam Nut, PART A, incorporated." PART B − Installation of the New Jam Nut on the MLG Retraction Actuator A. Job Set−Up (1) Reference Information
REFERENCE DESIGNATION 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 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 32−32−05−000−801 Removal of the MLG Retraction−Actuator AMM 32−32−05−400−801 Installation of the MLG Retraction−Actuator 

### SERVICE BULLETIN 670BA−32−031

S.B. 670BA−32−031 Page 13 of 18 Mar 14/2011 Revision C, Apr 17/2012REFERENCE DESIGNATION AMM 32−34−00−710−801 Operational Check of the Landing−Gear Alternate−Extension System AMM 57−20−32−000−801 Removal of the Access Panel for the Main Landing Gear (MLG) Retraction Actuator (542AT/642AT) AMM 57−20−32−400−801 Installation of the Access Panel for the Main Landing Gear (MLG) Retraction Actuator (542AT/642AT) (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) Remove the access panels that follow:

PANEL NAME REFERENCE 542AT Access Panel AMM 57−20−32−000−801 642AT Access Panel AMM 57−20−32−000−801 (6) Obey all the hydraulic technical precautions (AMM 29−00−00−910−802). 

### SERVICE BULLETIN 670BA−32−031

S.B. 670BA−32−031 Page 14 of 18 Mar 14/2011 Revision C, Apr 17/2012(7) Release the hydraulic pressure of system No. 2 (AMM 12−00−06−862−802). (8) Remove the MLG auxiliary actuator (AMM 32−32−03−000−801). (9) Release the hydraulic pressure of system No. 3 (AMM 12−00−06−862−804). (10) Remove the retraction actuator (1) (AMM 32−32−05−000−801). 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. (1) Do Goodrich Service Bulletin 49600−32−64. C. Job Close−Out (1) Install the retraction actuator (1) (AMM 32−32−05−400−801). (2) Install the MLG auxiliary actuator (AMM 32−32−03−400−801). (3) Remove all tools, equipment, and unwanted materials from the work area. (4) 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 (5) Pressurize hydraulic system No. 2 (AMM 12−00−06−862−801). (6) Pressurize hydraulic system No. 3 (AMM 12−00−06−862−803). (7) Bleed hydraulic systems No. 2 (AMM 29−10−00−870−801). (8) Bleed hydraulic systems No. 3 (AMM 29−10−00−870−802). 

### SERVICE BULLETIN 670BA−32−031

S.B. 670BA−32−031 Page 15 of 18 Mar 14/2011 Revision C, Apr 17/2012(9) Do an operational test of the landing−gear extension/retraction system (AMM 32−30−00−710−801). (10) Do an operational test of the landing−gear alternate−extension system (AMM 32−34−00−710−801). (11) Install the access panels that follow:

PANEL NAME REFERENCE 542AT Access Panel AMM 57−20−32−400−801 642AT Access Panel AMM 57−20−32−400−801 (12) When PART B of this service bulletin is completed, make this entry in the applicable logbook(s): "Service Bulletin 670BA−32−031, Revision C, Landing Gear − Landing−Gear Hydraulic Extension/Retraction − Inspection of the Main Landing Gear (MLG) Retraction−Actuator and Installation of a New Jam Nut, PART B, incorporated." 

### SERVICE BULLETIN 670BA−32−031

S.B. 670BA−32−031 Page 16 of 18 Mar 14/2011 Revision C, Apr 17/20123. 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 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 and the Goodrich service bulletins 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 bulletins given as references in this service bulletin. D. Disposition of Parts PART A − Torque Inspection of the Jam Nut of the MLG Retraction Actuator Not applicable. PART B − Installation of the New Jam Nut on the MLG Retraction Actuator 

### SERVICE BULLETIN 670BA−32−031

S.B. 670BA−32−031 Page 17 of 18 Mar 14/2011 Revision C, Apr 17/2012PRE−SB PART NUMBER NAME QUANTITY DC POST−SB PART NUMBER 49600−11 Retraction Actuator 2 RWI 49600−13
Disposition code (DC): RWI: Rework the part as shown in Goodrich Service Bulletin 49600−32−64. 

### SERVICE BULLETIN 670BA−32−031

S.B. 670BA−32−031 Page 18 of 18 Mar 14/2011 Revision C, Apr 17/2012THANK 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-32-031 ISSUE: C

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