601R---57---052 Page 1 of 1 Oct 12/2012 

## SERVICE BULLETIN REVISION TRANSMITTAL SHEET CL ---600 ---2B19 Canadair Regional Jet (CRJ) Aircraft SERVICE BULLETIN 601R ---57 ---052

SUBJECT: Wing Structure --- Auxiliary --- Inspection and Replacement of the Main Landing Gear (MLG) Side ---Brace Shaft Fittings (P/N 601R10237 ---1 or P/N 601R10237 ---3) This page transmits: Revision B of Service Bulletin 601R --- 57 --- 052, pages 1 thru 49, dated Oct 12/2012 The changes in this revision have no effect on aircraft that have incorporated a previous issue of this service bulletin.

Reason: Revised Accomplishment Instructions, paragraph 2., to: Change a torque in PART D. Revised Material Information, paragraph 3., to: Change a part number in kit 601R57---052K1. This revision also includes small editorial changes that do not have an effect on the technical content.

Instructions: Discard the copy of Service Bulletin 601R --- 57 --- 052, Revision A, dated Oct 28/2011. Replace with the copy attached. Service Bulletin History: Initial issue, dated Jul 28/ 2011. Revision A, dated Oct 28/2011. 1Page 1 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 

# SERVICE BULLETIN

Technical Publications

THIS SERVICE BULLETIN IS SENT TO EACH OPERATOR. IF THE OPERATOR HAS LEASED 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 HAS INCLUDED THE NEW OPERATOR AIRCRAFT, THIS SERVICE BULLETIN MUST BE SENT TO THE LESSEE. IF THE OPERATOR

ON THE DISTRIBUTION LIST.

ATA SYSTEM: 57 ---21 NUMBER: 601R ---57 ---052 SUBJECT: Wing Structure --- Auxiliary --- Inspection and Replacement of the Main Landing Gear (MLG) Side ---Brace Shaft Fittings (P/N 601R10237 ---1 or P/N 601R10237 ---3)
1. PLANNING INFORMATION A. Effectivity (1) Aircraft Affected: Service Bulletin: CL ---600---2B19 aircraft with serial numbers 7003 thru 7067, 7069 thru 7990, 8000 thru 8999. Production: There is no production effectivity at this time. B. Reason (1) Condition It is possible for the MLG side---brace shaft fittings to crack because of stress corrosion. Cracks can cause the MLG side---brace shaft fittings to break, preventing the MLG from staying down and locked. (2) Evidence Two instances were reported on in---service aircraft. (3) Objective/Benefit This service bulletin gives the procedure to do an inspection of the MLG side---brace shaft fittings and the hardware for corrosion, and the procedure to replace the MLG side---brace shaft fittings and their hardware. This replacement increases the corrosion resistance of the MLG and keeps the MLG down and locked.

### SERVICE BULLETIN 601R---57 ---052

Page 2 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 C. Description This service bulletin is divided into four parts: PART A, PART B, PART C, and PART D. PART A --- Inspection of the Threads of the MLG Side ---Brace Shaft Fitting (P/N 601R10237 ---1 or P/N 601R10237 ---3) on the Left Side The external AC power is removed from the aircraft. Some circuit breakers are opened. The MLG and the NLG lockpins are installed. The aircraft is lifted on jacks and the wheel bin is removed. An inspection is done on the shaft of the MLG side---brace shaft fitting (written as “shaft” in this service bulletin) and on the forward nut and the washer. If corrosion or damage is found, PART C is done. If no corrosion or damage is found, the wheel bin is installed and the aircraft is removed from the jacks. The MLG and the NLG lockpins are removed. The external AC power is connected to the aircraft. PART B --- Inspection of the Threads of the MLG Side ---Brace Shaft Fitting (P/N 601R10237 ---1 or P/N 601R10237 ---3) on the Right Side The external AC power is removed from the aircraft. Some circuit breakers are opened. The MLG and the NLG lockpins are installed. The aircraft is lifted on jacks and the wheel bin is removed. An inspection is done on the shaft of the MLG side---brace shaft fitting and on the forward nut and the washer. If corrosion or damage is found, PART D is done. If no corrosion or damage is found, the wheel bin is installed and the aircraft is removed from the jacks. The MLG and the NLG lockpins are removed. The external AC power is connected to the aircraft. PART C --- Replacement of the MLG Side ---Brace Shaft Fitting (P/N 601R10237 ---1 or P/N 601R10237 ---3) on the Left Side The external AC power is removed from the aircraft. Some circuit breakers are opened. The MLG and the NLG lockpins are installed. The aircraft is lifted on jacks and the wheel bin is removed. The MLG side---brace shaft fitting is removed and discarded. An inspection of the bushings and the area between the bushings is done. If corrosion is found, it is removed. A new MLG side---brace shaft fitting is installed. The external AC power is connected to the aircraft and return---to ---service tests are done. The wheel bin is installed and the aircraft is removed from the jacks. PART D --- Replacement of the MLG Side ---Brace Shaft Fitting (P/N 601R10237 ---1 or P/N 601R10237 ---3) on the Right Side The external AC power is removed from the aircraft. Some circuit breakers are opened. The MLG and the NLG lockpins are installed. The aircraft is lifted on jacks and the wheel bin is removed.

### SERVICE BULLETIN 601R---57 ---052

Page 3 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 The MLG side---brace shaft fitting is removed and discarded. An inspection of the bushings and the area between the bushings is done. If corrosion is found, it is removed. A new MLG side---brace shaft fitting is installed. The external AC power is connected to the aircraft and return---to ---service tests are done. The wheel bin is installed and the aircraft is removed from the jacks. D. Compliance

Recommended Service Bulletin.

PART APPLICABILITY TIME COMPLIANCE REPETITIVE ACTION PART A --- Inspection of the Threads of the MLG Side---Brace Shaft Fitting (P/N 601R10237---1 or P/N 601R10237---3) on the Left Side For aircraft that operate more than 900 flight hours per year and that have shaft P/N 601R10237---1 or if you cannot identifythe part number without removal of the shaft. To be done no more than 1000 flight hours from the release date of this service bulletin. OR Do PART C. To be repeated every 1000 flight hours from the initial inspection date of PART A until PART C has been done.

For aircraft that operate 900 flight hours or less per year and that have shaft P/N 601R10237---1 or if you cannot identifythe part number without removal of the shaft. To be done no more than 18 months from the release date of this service bulletin. OR Do PART C. To be repeated every 18 months from the initial inspection date of PART A until PART C has been done.

For aircraft that operate more than 900 flight hours per year and that have shaft P/N 601R10237---3. To be done no more than 3 years from the release date of this service bulletin. OR Do PART C. To be repeated every 3 years from the initial inspection date of PART A until PART C has been done.For aircraft that operate 900 flight hours or less per year and that have shaft P/N 601R10237---3. To be done no more than 5 years from the release date of this service bulletin. OR Do PART C. To be repeated every 5 years from the initial inspection date of PART A until PART C has been done.

### SERVICE BULLETIN 601R---57 ---052

Page 4 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 PART B --- Inspection of the Threads of the MLG Side---Brace Shaft Fitting (P/N 601R10237---1 or P/N 601R10237---3) on the Right Side For aircraft that operate more than 900 flight hours per year and that have shaft P/N 601R10237---1 or if you cannot identifythe part number without removal of the shaft. To be done no more than 1000 flight hours from the release date of this service bulletin. OR Do PART D. To be repeated every 1000 flight hours from the initial inspection date of PART B until PART D has been done.

For aircraft that operate 900 flight hours or less per year and that have shaft P/N 601R10237---1 or if you cannot identifythe part number without removal of the shaft. To be done no more than 18 months from the release date of this service bulletin. OR Do PART D. To be repeated every 18 months from the initial inspection date of PART B until PART D has been done.

For aircraft that operate more than 900 flight hours per year and that have shaft P/N 601R10237---3. To be done no more than 3 years from the release date of this service bulletin. OR Do PART D. To be repeated every 3 years from the initial inspection date of PART B until PART D has been done.For aircraft that operate 900 flight hours or less per year and that have shaft P/N 601R10237---3. To be done no more than 5 years from the release date of this service bulletin. OR Do PART D. To be repeated every 5 years from the initial inspection date of PART B until PART D has been done.
PART C --- Replacement of the MLG Side---Brace Shaft Fitting (P/N 601R10237---1 or P/N 601R10237---3) on the Left Side For aircraft with shaft P/N 601R10237---1 or if you cannot identifythe part number without removal of the shaft. To be done no later than Dec 01/2013. Not applicable.

For aircraft with shaft P/N 601R10237---3. To be done no later than June 2021. Not applicable.

### SERVICE BULLETIN 601R---57 ---052

Page 5 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 PART D --- Replacement of the MLG Side---Brace Shaft Fitting (P/N 601R10237---1 or P/N 601R10237---3) on the Right Side For aircraft with shaft P/N 601R10237---1 or if you cannot identifythe part number without removal of the shaft. To be done no later than Dec 01/2013. Not applicable.

For aircraft with shaft P/N 601R10237---3. To be done no later than June 2021. Not applicable.
This service bulletin affects Airworthiness Limitations (AWLs) and/or Damage Tolerance Inspections (DTIs). Reference applicable Pre/Post Modsum TC601R18053 and/or service bulletin 601R---57---052 in the Maintenance Requirements Manual (MRM). NOTE: This service bulletin supercedes service bulletin 601R---57---036. If service bulletin 601R---57---036 has been incorporated, Bombardier recommends that you do this service bulletin. 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 estimates for direct labour 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, liaising, 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 labour assistance, please speak with a Fleet Services representative for a quote. The Fleet Services Team can be contacted through the CRC at 514-855-8500 or email at thd.crj@aero.bombardier.com.

### SERVICE BULLETIN 601R---57 ---052

Page 6 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 PART A --- Inspection of the Threads of the MLG Side ---Brace Shaft Fitting (P/N 601R10237 ---1 or P/N 601R10237 ---3) on the Left Side OR PART B --- Inspection of the Threads of the MLG Side ---Brace Shaft Fitting (P/N 601R10237 ---1 or P/N 601R10237 ---3) on the Right Side It will take an estimated 5.0 man-hours to complete PART A or PART B of this service bulletin. The man-hours are divided in the table that follows:
TASK MAN-HOURS (1) Job Set-Up 2.0 (2) Procedure 2.0 (3) Test 0.0 (4) Job Close-Out 1.0
PART C --- Replacement of the MLG Side ---Brace Shaft Fitting (P/N 601R10237 ---1 or P/N 601R10237 ---3) on the Left Side OR PART D --- Replacement of the MLG Side ---Brace Shaft Fitting (P/N 601R10237 ---1 or P/N 601R10237 ---3) on the Right Side It will take an estimated 7.0 man-hours to complete PART C or PART D of this service bulletin. The man-hours are divided in the table that follows:
TASK MAN-HOURS (1) Job Set-Up 2.0 (2) Procedure 3.0 (3) Test 1.0 (4) Job Close-Out 1.0

### SERVICE BULLETIN 601R---57 ---052

Page 7 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 G. Material --- Price and Availability (1) The parts in the table that follows can be necessary to do PART A and PART B of this service bulletin and are available from Bombardier Commercial Aircraft.

PART NUMBER NAME QUANTITY NAS1149C1690B Washer 2 B0202013S6556---80 Washer 2 B0203053---16 Nut 2 MS24665---360 Cotter pin 2
(2) Please send a purchase order to the address below to schedule part delivery: 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 the Service Bulletin Kit Support Team at the address above for terms and conditions. (3) The kit in the table that follows is available from Bombardier Commercial Aircraft. NOTE: For a list of kit contents, refer to paragraph 3.A.

KIT NUMBER NAME 601R57---052K1 Kit --- MLG Side Brace Shaft Replacement

NOTE: Kit 601R57---052K1 is for one side only. Order two kits to do PART C and PART D.

### SERVICE BULLETIN 601R---57 ---052

Page 8 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 (4) Please send a purchase order to the address below to schedule kit delivery: 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 the Service Bulletin Kit Support Team at the address above for terms and conditions. (5) Refer to paragraph 3.B. for a list of consumables for this service bulletin. For Business/Corporate Operators All Business/Corporate operators (i.e. operators who do not have a commercial airline operation) refer to SB 800-00-004 for commercial policy coverage and logistics/planning arrangements (refer to www.cic.bombardier.com/technical library/service bulletins/challenger/850/SB 800-00-004). To place an order for parts or kits, please call Bombardier Parts Logistics at 514-855-2999 or 1-866-538-1247. H. Tooling --- Price and Availability There are no tool kits for this service bulletin. Refer to paragraph 3.C. for a list of special tools and equipment for this service bulletin.

### SERVICE BULLETIN 601R---57 ---052

Page 9 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 I. Weight and Balance PART A --- Inspection of the Threads of the MLG Side ---Brace Shaft Fitting (P/N 601R10237 ---1 or P/N 601R10237 ---3) on the Left Side Not changed. PART B --- Inspection of the Threads of the MLG Side ---Brace Shaft Fitting (P/N 601R10237 ---1 or P/N 601R10237 ---3) on the Right Side Not changed. PART C --- Replacement of the MLG Side ---Brace Shaft Fitting (P/N 601R10237 ---1 or P/N 601R10237 ---3) on the Left Side

WEIGHT ARM MOMENT ¡ +0.5 lb +512.5 in. +0.256 (1000 lb-in.) +0.23 kg +13.02 m +0.0030 (1000 kg-m) ¡ The value in the Moment column is divided by 1000. Refer to Weight and Balance Manual CSP A ---041. PART D --- Replacement of the MLG Side ---Brace Shaft Fitting (P/N 601R10237 ---1 or P/N 601R10237 ---3) on the Right Side

WEIGHT ARM MOMENT ¡ +0.5 lb +512.5 in. +0.256 (1000 lb-in.) +0.23 kg +13.02 m +0.0030 (1000 kg-m) ¡ The value in the Moment column is divided by 1000. Refer to Weight and Balance Manual CSP A ---041.

### SERVICE BULLETIN 601R---57 ---052

Page 10 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 J. References Restriction and/or Special Instruction (RSI) C ---A289, Revision B. Modification Summary TC601R18053, Revision E. Aircraft Maintenance Manual Structural Repair Manual Non---destructive Testing Manual For Bombardier reference only: PCA 6396. K. Other Publications Affected Aircraft Maintenance Manual (AMM) Illustrated Parts Catalogue (IPC) L. Relationship Chart Not applicable.

PRE-SB PART NUMBER NAME POST-SB PART NUMBER NAME
601R10237---1 or

601R10237---3 Shaft --- MLG Side Brace 601R10247---3 Shaft --- MLG Side Brace

### SERVICE BULLETIN 601R---57 ---052

Page 11 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 2. ACCOMPLISHMENT INSTRUCTIONS PART A --- Inspection of the Threads of the MLG Side ---Brace Shaft Fitting (P/N 601R10237 ---1 or P/N 601R10237 ---3) on the Left Side Reference Information
REFERENCE DESIGNATION AMM 07---11---01---582---801 Put the Aircraft on Jacks AMM 07---11---01---582---804 Removal of the Aircraft from Jacks AMM 10---11---00---000---801 Removal of the Nose Landing Gear Lockpin AMM 10---11---00---400---801 Installation of the Nose Landing Gear Lockpin AMM 10---11---00---000---802 Removal of the Main Landing Gear Lockpins AMM 10---11---00---400---802 Installation of the Main Landing Gear Lockpins AMM 12---00---06---863---803 Pressurize Hydraulic System No. 3 AMM 12---00---06---863---804 Release Hydraulic Pressure --- System No. 3 AMM 12---00---07---861---801 Connect External AC Power AMM 12---00---07---861---802 Remove External AC Power AMM 20---21---00---910---801 Torque Procedures for Threaded Fasteners AMM 20---24---00---910---801 Cotter Pins --- Maintenance Practices AMM 24---00---00---910---801 Electrical/Electronic Safety Precautions AMM 26---14---00---710---801 Operational Test of the MLG Overheat Detection and Warning System AMM 53---83---01---000---801 Removal of the MLG Wheel Bin AMM 53---83---01---400---801 Installation of the MLG Wheel Bin NDTM 51---20---09 Visual---Inspection Procedures SRM 51---21---11 Corrosion Prevention Procedures SRM 51---23---00 Pressure, Environmental, Fuel Tank and Firewall Sealing SRM 51---25---06 Fluid ---Resistant (FR) Epoxy Primer SRM 51---25---16 Fluid ---Resistant (FR) Polyurethane Topcoat SRM 51---26---00 Cleaning

### SERVICE BULLETIN 601R---57 ---052

Page 12 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 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 when specified differently. A. Job Set-Up WARNING: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU DO MAINTENANCE ON OR NEAR ELECTRICAL/ELECTRONIC EQUIPMENT. IF YOU DO NOT OBEY THE SAFETY PRECAUTIONS, INJURIES TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT CAN OCCUR. (1) Obey all the electrical/electronic safety precautions (Refer to AMM 24---00---00---910---801). (2) Remove the external AC power from the aircraft (Refer to AMM 12---00---07---861---802). (3) Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE

CBP ---1 A2 HYD PUMP 3B 221 CBP ---1 G11 HYD SYST AC PUMP CONT 3B 221 CBP --- 1 F6 PROX SENS LGC/D1 221 CBP --- 1 F7 PROX SENS WOW 1 221 CBP --- 2 A2 HYD PUMP 3A 222 CBP --- 2 F9 PROX SENS WOW 2 222 CBP --- 2 G15 HYD SYST AC PUMP CONT 3A 222 CBP --- 2 N9 MLG BAY OVHT DET 222 CBP --- 2 P2 PROX SENS LGC/D1 222 CBP --- 2 P3 PROX SENS LGC/D2 WOW 1 + 2 222 CBP --- 4 B13 PROX SENS LGC/D2 222

### SERVICE BULLETIN 601R---57 ---052

Page 13 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 WARNING: MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. (4) Install the nose landing gear (NLG) lockpin (Refer to AMM 10---11---00---400---801). (5) Install the main landing gear (MLG) lockpins (Refer to AMM 10---11---00---400---802). (6) Lift the aircraft on jacks (Refer to AMM 07---11---01---582---801). WARNING: OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON ANY HYDRAULIC SYSTEM OR ON A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT OBEY THE SAFETY PRECAUTIONS, YOU CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. (7) Release hydraulic pressure from system No. 3 (Refer to AMM 12---00---06---863---804). (8) Remove the MLG wheel bin (Refer to AMM 53---83---01---000---801).

### SERVICE BULLETIN 601R---57 ---052

Page 14 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 B. Procedure Refer to Figure 1. (1) Identify the part number of the MLG side---brace shaft fitting (1). NOTE: It is possible to see the part number on the aft end of the shaft. NOTE: The part number can also be identified with maintenance records. NOTE: If the part number can only be identified by the removal of the shaft, do the instructions applicable for part number 601R10237---1. Refer to Figure 2. CAUTION: DO NOT TURN THE MLG SIDE ---BRACE SHAFT FITTING (1) DURING THE INSPECTION PROCEDURE. IF YOU DO THE SURFACE FINISH WILL BE DAMAGED. (2) Do the inspection of the forward end of the MLG side---brace shaft fitting (1) and the hardware as follows: (a) Remove the sealant from the area (Refer to SRM 51---23---00). (b) Remove and discard the cotter pin (2). (c) Remove the nut (3) and the washer (4). (d) Clean the threaded area on the MLG side---brace shaft fitting (1) (Refer to SRM 51---26---00). (e) Do a detailed visual inspection of the full---threaded area of the MLG side---brace shaft fitting (1) to make sure there is no corrosion or damage (Refer to NDTM 51---20---09). (f) If corrosion or damage is found, do PART C of this service bulletin. (g) If no corrosion or damage is found, do as follows:
1 Clean the nut (3) and the washer (4) (Refer to SRM 51---26---00).
2 Do a visual inspection of the nut (3) and the washer (4) to make sure there is no corrosion or damage (Refer to NDTM 51---20---09).
3 If corrosion or damage is found, replace the nut (3) and the washer (4).

### SERVICE BULLETIN 601R---57 ---052

Page 15 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 4 If the part number of the removed washer (4) is B0202013S6556---80, you must install a washer with the same part number. NOTE: The washer B0202013S6556---80 is 0.080 in. (2.03 mm) thick. 5 If the part number of the removed washer (4) is AN960XC1616, you must install washer AN960XC1616 or NAS1149C1690B. NOTE: The washer AN960XC1616 is 0.090 in. (2.29 mm) thick. CAUTION: DO NOT TURN THE MLG SIDE ---BRACE SHAFT FITTING (1) DURING INSTALLATION OF THE NUT (3). IF YOU DO THE SURFACE FINISH WILL BE DAMAGED. 6 Install the washer (4), the nut (3), and the cotter pin (2) on the MLG side---brace shaft fitting (1) as follows:

a Make sure the fitting, the MLG side---brace shaft fitting (1), the nut (3), and the washer (4) are free of dirt, grease, and moisture.
b Apply Mastinox to the threads of the MLG side---brace shaft fitting (1).

c Install the washer (4) and the nut (3) on the MLG side---brace shaft fitting (1) with Mastinox.
d Torque the nut (3) from 74.2 lbfft to 90.8 lbf ft (100.6 to 123.1 N.m) (Refer to AMM 20---21---00---910---801). NOTE: The running torque has been added to the torque value.

e Safety the nut (3) with the cotter pin (2) (Refer to AMM 20---24---00---910---801).
f It is permitted to loosen and reinstall the nut (3) to correctly install the cotter pin (2) if the nut (3) was not over ---torqued and if the minimum breakaway torque is at least 7.5 lbf ft (10.2 N.m).

### SERVICE BULLETIN 601R---57 ---052

Page 16 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 g If the nut (3) was over ---torqued or if the minimum breakaway torque does not meet the requirement, discard and replace the nut (3).
h Apply sealant on the end of the MLG side---brace shaft fitting (1), the nut (3), the washer (4), the bushing, and the fitting (Refer to SRM 51---23---00).

### SERVICE BULLETIN 601R---57 ---052

Page 17 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 C. Job Close-Out (1) Remove all tools, equipment, and unwanted materials from the work area. (2) Connect external AC power to the aircraft (Refer to AMM 12---00---07---861---801). (3) Remove the tags and close the circuit breakers that follow: CB PANEL CB NO. NAME ZONE

CBP ---1 A2 HYD PUMP 3B 221 CBP ---1 G11 HYD SYST AC PUMP CONT 3B 221 CBP --- 1 F6 PROX SENS LGC/D1 221 CBP --- 1 F7 PROX SENS WOW 1 221 CBP --- 2 A2 HYD PUMP 3A 222 CBP --- 2 F9 PROX SENS WOW 2 222 CBP --- 2 G15 HYD SYST AC PUMP CONT 3A 222 CBP --- 2 N9 MLG BAY OVHT DET 222 CBP --- 2 P2 PROX SENS LGC/D1 222 CBP --- 2 P3 PROX SENS LGC/D2 WOW 1 + 2 222

CBP --- 4 B13 PROX SENS LGC/D2 222 (4) Pressurize hydraulic system No. 3 (Refer to AMM 12---00---06---863---803). (5) Install the MLG wheel bin (Refer to AMM 53---83---01---400---801). (6) Do an operational test of the MLG overheat detection and warning system (Refer to AMM 26---14---00---710---801). (7) Lower the aircraft and remove the jacks (Refer to AMM 07---11---01---582---804). (8) Remove the NLG lockpin (Refer to AMM 10---11---00---000---801). (9) Remove the MLG lockpins (Refer to AMM 10---11---00---000---802). (10) When PART A of this service bulletin is completed, make this entry in the applicable logbooks: “Service Bulletin 601R---57---052, Revision B, Wing Structure --- Auxiliary --- Inspection and Replacement of the Main Landing Gear (MLG) Side---Brace Shaft Fitting (P/N 601R10237---1 or P/N 601R10237---3), Part A, incorporated.”

### SERVICE BULLETIN 601R---57 ---052

Page 18 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 PART B --- Inspection of the Threads of the MLG Side ---Brace Shaft Fitting (P/N 601R10237 ---1 or P/N 601R10237 ---3) on the Right Side Reference Information
REFERENCE DESIGNATION AMM 07---11---01---582---801 Put the Aircraft on Jacks AMM 07---11---01---582---804 Removal of the Aircraft from Jacks AMM 10---11---00---000---801 Removal of the Nose Landing Gear Lockpin AMM 10---11---00---400---801 Installation of the Nose Landing Gear Lockpin AMM 10---11---00---000---802 Removal of the Main Landing Gear Lockpins AMM 10---11---00---400---802 Installation of the Main Landing Gear Lockpins AMM 12---00---06---863---803 Pressurize Hydraulic System No. 3 AMM 12---00---06---863---804 Release Hydraulic Pressure --- System No. 3 AMM 12---00---07---861---801 Connect External AC Power AMM 12---00---07---861---802 Remove External AC Power AMM 20---21---00---910---801 Torque Procedures for Threaded Fasteners AMM 20---24---00---910---801 Cotter Pins --- Maintenance Practices AMM 24---00---00---910---801 Electrical/Electronic Safety Precautions AMM 26---14---00---710---801 Operational Test of the MLG Overheat Detection and Warning System AMM 53---83---01---000---801 Removal of the MLG Wheel Bin AMM 53---83---01---400---801 Installation of the MLG Wheel Bin NDTM 51---20---09 Visual---Inspection Procedures SRM 51---21---11 Corrosion Prevention Procedures SRM 51---23---00 Pressure, Environmental, Fuel Tank and Firewall Sealing SRM 51---25---06 Fluid ---Resistant (FR) Epoxy Primer SRM 51---25---16 Fluid ---Resistant (FR) Polyurethane Topcoat SRM 51---26---00 Cleaning

### SERVICE BULLETIN 601R---57 ---052

Page 19 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 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 when specified differently. D. Job Set-Up WARNING: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU DO MAINTENANCE ON OR NEAR ELECTRICAL/ELECTRONIC EQUIPMENT. IF YOU DO NOT OBEY THE SAFETY PRECAUTIONS, INJURIES TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT CAN OCCUR. (1) Obey all the electrical/electronic safety precautions (Refer to AMM 24---00---00---910---801). (2) Remove the external AC power from the aircraft (Refer to AMM 12---00---07---861---802). (3) Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE

CBP ---1 A2 HYD PUMP 3B 221 CBP ---1 G11 HYD SYST AC PUMP CONT 3B 221 CBP --- 1 F6 PROX SENS LGC/D1 221 CBP --- 1 F7 PROX SENS WOW 1 221 CBP --- 2 A2 HYD PUMP 3A 222 CBP --- 2 F9 PROX SENS WOW 2 222 CBP --- 2 G15 HYD SYST AC PUMP CONT 3A 222 CBP --- 2 N9 MLG BAY OVHT DET 222 CBP --- 2 P2 PROX SENS LGC/D1 222 CBP --- 2 P3 PROX SENS LGC/D2 WOW 1 + 2 222 CBP --- 4 B13 PROX SENS LGC/D2 222

### SERVICE BULLETIN 601R---57 ---052

Page 20 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 WARNING: MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. (4) Install the nose landing gear (NLG) lockpin (Refer to AMM 10---11---00---400---801). (5) Install the main landing gear (MLG) lockpins (Refer to AMM 10---11---00---400---802). (6) Lift the aircraft on jacks (Refer to AMM 07---11---01---582---801). WARNING: OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON ANY HYDRAULIC SYSTEM OR ON A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT OBEY THE SAFETY PRECAUTIONS, YOU CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. (7) Release hydraulic pressure from system No. 3 (Refer to AMM 12---00---06---863---804). (8) Remove the MLG wheel bin (Refer to AMM 53---83---01---000---801).

### SERVICE BULLETIN 601R---57 ---052

Page 21 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 E. Procedure Refer to Figure 1. (1) Identify the part number of the MLG side---brace shaft fitting (1). NOTE: It is possible to see the part number on the aft end of the shaft. NOTE: The part number can also be identified with maintenance records. NOTE: If the part number can only be identified by the removal of the shaft, do the instructions applicable for part number 601R10237---1. Refer to Figure 2. CAUTION: DO NOT TURN THE MLG SIDE ---BRACE SHAFT FITTING (1) DURING THE INSPECTION PROCEDURE. IF YOU DO THE SURFACE FINISH WILL BE DAMAGED. (2) Do the inspection of the forward end of the MLG side---brace shaft fitting (1) and the hardware as follows: (a) Remove the sealant from the area (Refer to SRM 51---23---00). (b) Remove and discard the cotter pin (2). (c) Remove the nut (3) and the washer (4). (d) Clean the threaded area of the MLG side---brace shaft fitting (1) (Refer to SRM 51---26---00). (e) Do a detailed visual inspection of the full---threaded area of the MLG side---brace shaft fitting (1) to make sure there is no corrosion or damage (Refer NDTM 51---20---09). (f) If corrosion or damage is found, do PART D of this service bulletin. (g) If no corrosion or damage is found, do as follows:
1 Clean the nut (3) and the washer (4) (Refer to SRM 51---26---00).
2 Do a visual inspection of the nut (3) and the washer (4) to make sure there is no corrosion or damage (Refer to NDTM 51---20---09).
3 If corrosion or damage is found, replace the nut (3) and the washer (4).

### SERVICE BULLETIN 601R---57 ---052

Page 22 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 4 If the part number of the removed washer (4) is B0202013S6556---80, you must install a washer with the same part number. NOTE: The washer B0202013S6556---80 is 0.080 in. (2.03 mm) thick. 5 If the part number of the removed washer (4) is AN960XC1616, you must install washer AN960XC1616 or NAS1149C1690B. NOTE: The washer AN960XC1616 is 0.090 in. (2.29 mm) thick. CAUTION: DO NOT TURN THE MLG SIDE ---BRACE SHAFT FITTING (1) DURING INSTALLATION OF THE NUT (3). IF YOU DO THE SURFACE FINISH WILL BE DAMAGED. 6 Install the washer (4), the nut (3), and the cotter pin (2) on the MLG side---brace shaft fitting (1) as follows:

a Make sure the fitting, the MLG side---brace shaft fitting (1), the nut (3), and the washer (4) are free of dirt, grease, and moisture.
b Apply Mastinox to the threads of the MLG side---brace shaft fitting (1).

c Install the washer (4) and the nut (3) on the MLG side---brace shaft fitting (1) with Mastinox.
d Torque the nut (3) from 74.2 lbfft to 90.8 lbf ft (100.6 to 123.1 N.m) (Refer to AMM 20---21---00---910---801). NOTE: The running torque has been added to the torque value.

e Safety the nut (3) with the cotter pin (2) (Refer to AMM 20---24---00---910---801).
f It is permitted to loosen and reinstall the nut (3) to correctly install the cotter pin (2) if the nut (3) was not over ---torqued and if the minimum breakaway torque is at least 7.5 lbf ft (10.2 N.m).

### SERVICE BULLETIN 601R---57 ---052

Page 23 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 g If the nut (3) was over ---torqued or if the minimum breakaway torque does not meet the requirement, discard and replace the nut (3).
h Apply sealant on the end of the MLG side---brace shaft fitting (1), the nut (3), the washer (4), the bushing, and the fitting (Refer to SRM 51---23---00).

### SERVICE BULLETIN 601R---57 ---052

Page 24 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 F. Job Close-Out (1) Remove all tools, equipment, and unwanted materials from the work area. (2) Connect external AC power to the aircraft (Refer to AMM 12---00---07---861---801). (3) Remove the tags and close the circuit breakers that follow: CB PANEL CB NO. NAME ZONE

CBP ---1 A2 HYD PUMP 3B 221 CBP ---1 G11 HYD SYST AC PUMP CONT 3B 221 CBP --- 1 F6 PROX SENS LGC/D1 221 CBP --- 1 F7 PROX SENS WOW 1 221 CBP --- 2 A2 HYD PUMP 3A 222 CBP --- 2 F9 PROX SENS WOW 2 222 CBP --- 2 G15 HYD SYST AC PUMP CONT 3A 222 CBP --- 2 N9 MLG BAY OVHT DET 222 CBP --- 2 P2 PROX SENS LGC/D1 222 CBP --- 2 P3 PROX SENS LGC/D2 WOW 1 + 2 222

CBP --- 4 B13 PROX SENS LGC/D2 222 (4) Pressurize hydraulic system No. 3 (Refer to AMM 12---00---06---863---803). (5) Install the MLG wheel bin (Refer to AMM 53---83---01---400---801). (6) Do an operational test of the MLG overheat detection and warning system (Refer to AMM 26---14---00---710---801). (7) Lower the aircraft and remove the jacks (Refer to AMM 07---11---01---582---804). (8) Remove the NLG lockpin (Refer to AMM 10---11---00---000---801). (9) Remove the MLG lockpins (Refer to AMM 10---11---00---000---802). (10) When PART B of this service bulletin is completed, make this entry in the applicable logbooks: “Service Bulletin 601R---57---052, Revision B, Wing Structure --- Auxiliary --- Inspection and Replacement of the Main Landing Gear (MLG) Side---Brace Shaft Fitting (P/N 601R10237---1 or P/N 601R10237---3), Part B, incorporated.”

### SERVICE BULLETIN 601R---57 ---052

Page 25 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 Identification of the MLG Side ---Brace Shaft Fitting Figure 1 LEGEND 1. MLG side--brace shaft fitting. 601R10237--1 orrsb601r57052_001.dg, rb, 14 juin 2011 C MLG SIDE--STAY ACTUATOR (REF) C

VIEW LOOKING FORWARD ON WING--BOX REAR SPAR LBL 13.10

WL 57.25 LBL 8.35

NOTES 1. Left side shown, right side opposite. 1

601R10237--3.

2 MLG side--brace shaft fitting identification. 2

### SERVICE BULLETIN 601R---57 ---052

Page 26 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 Inspection of the MLG Side ---Brace Shaft Fitting Figure 2rsb601r57052_002.dg, rb, 17 juin 2011 NOTES Area to be inspected. 2. Left side shown, right side opposite. LEGEND 1. MLG side--brace shaft fitting. 2. Cotter pin

MS24665--360. 3. Nut MS17826--16 or B0203053--16 (Pre--Mod)
4. Washer

NAS1149C1690B or B0202013S6556--80 (Post--Mod) B0203053--16 (Post--Mod).
AN960XC1616 or B0202013S6556--80 (Pre--Mod).

SECTION VIEW OF FITTING ASSEMBLY MLG SIDE--STAY ACTUATOR (REF) 4 3 2

1 BUSHING

(REF)

(REF) FITTING AN960XC1616 or

### SERVICE BULLETIN 601R---57 ---052

Page 27 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 PART C --- Replacement of the MLG Side ---Brace Shaft Fitting (P/N 601R10237 ---1 or P/N 601R10237 ---3) on the Left Side Reference Information
REFERENCE DESIGNATION AMM 07---11---01---582---801 Put the Aircraft on Jacks AMM 07---11---01---582---804 Removal of the Aircraft from Jacks AMM 10---11---00---000---801 Removal of the Nose Landing Gear Lockpin AMM 10---11---00---400---801 Installation of the Nose Landing Gear Lockpin AMM 10---11---00---000---802 Removal of the Main Landing Gear Lockpins AMM 10---11---00---400---802 Installation of the Main Landing Gear Lockpins AMM 12---00---06---863---803 Pressurize Hydraulic System No. 3 AMM 12---00---06---863---804 Release Hydraulic Pressure --- System No. 3 AMM 12---00---07---861---801 Connect External AC Power AMM 12---00---07---861---802 Remove External AC Power AMM 20---21---00---910---801 Torque Procedures for Threaded Fasteners AMM 20---24---00---910---801 Cotter Pins --- Maintenance Practices AMM 24---00---00---910---801 Electrical/Electronic Safety Precautions AMM 26---14---00---710---801 Operational Test of the MLG Overheat Detection and Warning System AMM 32---30---00---710---802 Landing Gear Extension and Retraction --- Maintenance Practices AMM 32---34---00---710---801 Operational Test of the Landing Gear Manual--- Release---System AMM 53---83---01---000---801 Removal of the MLG Wheel Bin AMM 53---83---01---400---801 Installation of the MLG Wheel Bin AMM 57---21---28---000---801 Removal of the MLG Side---Brace Shaft ---Fitting AMM 57---21---28---400---801 Installation of the MLG Side---Brace Shaft --- Fitting NDTM 51---20---09 Visual---Inspection Procedures SRM 51---21---11 Corrosion Prevention Procedures SRM 51---23---00 Pressure, Environmental, Fuel Tank and Firewall Sealing SRM 51---25---06 Fluid ---Resistant (FR) Epoxy Primer SRM 51---25---16 Fluid ---Resistant (FR) Polyurethane Topcoat

### SERVICE BULLETIN 601R---57 ---052

Page 28 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 REFERENCE DESIGNATION SRM 51---26---00 Cleaning
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 when specified differently. G. Job Set-Up WARNING: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU DO MAINTENANCE ON OR NEAR ELECTRICAL/ELECTRONIC EQUIPMENT. IF YOU DO NOT OBEY THE SAFETY PRECAUTIONS, INJURIES TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT CAN OCCUR. (1) Obey all the electrical/electronic safety precautions (Refer to AMM 24---00---00---910---801). (2) Remove the external AC power from the aircraft (Refer to AMM 12---00---07---861---802).
(3) Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE

CBP ---1 A2 HYD PUMP 3B 221 CBP ---1 G11 HYD SYST AC PUMP CONT 3B 221 CBP --- 1 F6 PROX SENS LGC/D1 221 CBP --- 1 F7 PROX SENS WOW 1 221 CBP --- 2 A2 HYD PUMP 3A 222 CBP --- 2 F9 PROX SENS WOW 2 222 CBP --- 2 G15 HYD SYST AC PUMP CONT 3A 222

### SERVICE BULLETIN 601R---57 ---052

Page 29 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 CB PANEL ZONE NAME CB NO. CBP --- 2 N9 MLG BAY OVHT DET 222 CBP --- 2 P2 PROX SENS LGC/D1 222 CBP --- 2 P3 PROX SENS LGC/D2 WOW 1 + 2 222 CBP --- 4 B13 PROX SENS LGC/D2 222
WARNING: MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. (4) Install the nose landing gear (NLG) lockpin (Refer to AMM 10---11---00---400---801). (5) Install the main landing gear (MLG) lockpins (Refer to AMM 10---11---00---400---802). (6) Lift the aircraft on jacks (Refer to AMM 07---11---01---582---801). WARNING: OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON ANY HYDRAULIC SYSTEM OR ON A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT OBEY THE SAFETY PRECAUTIONS, YOU CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. (7) Release hydraulic pressure from system No. 3 (Refer to AMM 12---00---06---863---804). (8) Remove the MLG wheel bin (Refer to AMM 53---83---01---000---801).

### SERVICE BULLETIN 601R---57 ---052

Page 30 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 H. Procedure Refer to Figure 3 (Sheets 1 and 2). (1) Remove and discard the MLG side---brace shaft fitting (Refer to AMM 57---21---28---000---801). Discard the nuts (2) and (8), the washer (7), and the cotter pins (1) and (9). (2) Do a detailed visual inspection of the forward and aft bushings for signs of corrosion, wear, scratches, nicks, gouges, scores, deformation, or other damage (Refer to NDTM 51---20---09). (3) If corrosion is found, do as follows: (a) Remove the corrosion (Refer to SRM 51---21---06 for parts made with martensitic corrosion--- resistant steel) with a fine---grit abrasive pad instead of aluminum ---oxide abrasive paper. (b) After the corrosion is removed, make sure that the forward bushing has a maximum diameter of 1.1887 in. (30.193 mm). (c) After the corrosion is removed, make sure that the aft bushing has a maximum diameter of 1.8021 in. (45.773 mm). (4) Inspect the area between the forward and the aft bushings for corrosion. (5) If there is more corrosion, damage to the bushings, or corrosion in the area between the bushings, speak with a representative of Bombardier at the Technical Help Desk at phone number 514-855-8500 for a disposition. CAUTION: MAKE SURE THAT YOU PROTECT THE FITTING AND THE BUSHINGS DURING THE SHAFT FITTING REMOVAL AND INSTALLATION. IF YOU DO NOT, THE FITTING ASSEMBLY WILL GET DAMAGED AND REQUIRE REPLACEMENT. CAUTION: DO NOT TURN THE SHAFT FITTING DURING INSTALLATION. IF YOU DO THE SURFACE FINISH WILL BE DAMAGED.

### SERVICE BULLETIN 601R---57 ---052

Page 31 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 (6) Install the MLG side---brace shaft fitting (5) as follows: (a) Clean the mating surfaces of the MLG side---brace shaft fitting (5), the bushings (12) and (13), and the space between the bushings (12) and (13) (Refer to SRM 51---26---00). (b) Apply a layer of BAMS 552---010 compound to the mating surfaces of the MLG side---brace shaft fitting (5), the MLG side---brace fitting (6), and the bushings (12) and (13). (c) Make sure there is enough compound to fill the space between the bushings (12) and (13). (d) Make sure there is enough compound to have equal quantities of squeeze---out all around the bushings (12) and (13). (e) Align the straight edge of the flange of the MLG side---brace shaft fitting (5) with the locating flange on the MLG side---brace fitting (6). (f) Install the MLG side---brace shaft fitting (5) in the MLG side---brace fitting (6). (g) Clean the threads of the MLG side---brace shaft fitting (5) and the flange of the bushing (12) (Refer to SRM 51---26---00). (h) Install the washer (7), the laminated washer (10), and the nut (8) with fluid --- resistant primer (Refer to SRM 51---25---06). Make sure the laminated washer (10) is between the flange of the bushing (12) and the washer (7). (i) If necessary, peel the laminated washer (10) to correctly engage the cotter pin (9). (j) Torque the nut (8) from 74.2 lbf ft to 90.8 lbfft (100.6 to 123.1 N.m) (Refer to AMM 20---21---00---910---801). NOTE: The running torque has been added to the torque value. (k) It is permitted to loosen and reinstall the nut (8) to correctly install the cotter pin (9) if the nut (8) was not over ---torqued and if the minimum breakaway torque is at least 7.5 lbf ft (10.2 N.m). (l) Safety the nut (8) with the cotter pin (9) (Refer to AMM 20---24---00---910---801). (m) If the nut (8) was over ---torqued or if the minimum breakaway torque does not meet the requirement, discard and replace the nut (8).

### SERVICE BULLETIN 601R---57 ---052

Page 32 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 (7) Connect the MLG side---stay actuator to the MLG side---brace shaft fitting (5) as follows: CAUTION: MAKE SURE TO CONNECT THE MLG SIDE ---STAY ACTUATOR AND THE MLG SIDE ---BRACE SHAFT FITTING (5) DURING THE APPLICATION LIFE OF THE FILLET SEAL. IF NOT, THE SEALANT CAN BE DAMAGED BY TORQUING OF THE NUT (2). (a) Apply a fillet seal around the aft end of the flange of the MLG side---brace shaft fitting (5) (Refer to SRM 51---23---00). (b) Clean the mating surfaces of the MLG side---stay actuator and the MLG side---brace shaft fitting (5) (Refer to SRM 51---26---00). (c) Clean the threads of the MLG side---brace shaft fitting (5) and the nut (2) (Refer to SRM 51---26---00). (d) Apply a layer of BAMS 552---010 compound to the mating surfaces of the MLG side---stay actuator and the MLG side---brace shaft fitting (5). (e) Install the washer (4) on the MLG side---brace shaft fitting (5). (f) Install the cylinder end of the MLG side---stay actuator on the MLG side---brace shaft fitting (5). (g) Apply a layer of BAMS 552---010 compound to the threads of the MLG side---brace shaft fitting (5). (h) Install the washer (3) and the nut (2) on the MLG side---brace shaft fitting (5). (i) Torque the nut (2) from 41.9 to 95.3 lbfft (56.8 to 129.2 N  m) (Refer to AMM 20---21---00---910---801). NOTE: The running torque has been added to the torque value. (j) It is permitted to loosen and reinstall the nut (2) to correctly install the cotter pin (1) if the nut (2) was not over ---torqued and if the minimum breakaway torque is at least 11.9 lbfft (16.1 N.m). (k) Safety the nut (2) with the cotter pin (1) (Refer to AMM 20---24---00---910---801).

### SERVICE BULLETIN 601R---57 ---052

Page 33 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 (l) If the nut (2) was over ---torqued or if the minimum breakaway torque does not meet the requirement, discard and replace the nut (2). (m) Lubricate the two ends of the MLG side---stay actuator (Refer to AMM 12---20---32---640---802). (8) Install the sealant cap (11) as follows: (a) Clean the MLG side---brace shaft fitting (5), the nut (8), the washer (7), the laminated washer (10), the cotter pin (9), the bushing (12), and the MLG side---brace fitting (6) (Refer to SRM 51---26---00). (b) Fill the sealant cap (11) with sealing compound MIL ---PRF---81733. (c) Put the sealant cap against the MLG side---brace fitting (6) and over the MLG side---brace shaft fitting (5). NOTE: The sealant should come out continuously around the base of the sealant cap (11).

### SERVICE BULLETIN 601R---57 ---052

Page 34 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 I. Job Close-Out (1) Remove all tools, equipment, and unwanted materials from the work area. (2) Connect external AC power to the aircraft (Refer to AMM 12---00---07---861---801). (3) Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE

CBP ---1 A2 HYD PUMP 3B 221 CBP ---1 G11 HYD SYST AC PUMP CONT 3B 221 CBP --- 1 F6 PROX SENS LGC/D1 221 CBP --- 1 F7 PROX SENS WOW 1 221 CBP --- 2 A2 HYD PUMP 3A 222 CBP --- 2 F9 PROX SENS WOW 2 222 CBP --- 2 G15 HYD SYST AC PUMP CONT 3A 222 CBP --- 2 N9 MLG BAY OVHT DET 222 CBP --- 2 P2 PROX SENS LGC/D1 222 CBP --- 2 P3 PROX SENS LGC/D2 WOW 1 + 2 222

CBP --- 4 B13 PROX SENS LGC/D2 222
(4) Pressurize hydraulic system No. 3 (Refer to AMM 12---00---06---863---803). (5) Do the extension and retraction checks of the landing gear (Refer to AMM 32---30---00---710---802). (6) Do an operational test of the landing gear manual--- release system (Refer to AMM 32---34---00---710---801). (7) Install the MLG wheel bin (Refer to AMM 53---83---01---400---801). (8) Do an operational test of the MLG overheat detection and warning system (Refer to AMM 26---14---00---710---801).

### SERVICE BULLETIN 601R---57 ---052

Page 35 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 (9) Lower the aircraft and remove the jacks (Refer to AMM 07---11---01---582---804). (10) Remove the NLG lockpin (Refer to AMM 10---11---00---000---801). (11) Remove the MLG lockpins (Refer to AMM 10---11---00---000---802). (12) When PART C of 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 601R---57---052, Revision B, incorporated.” (13) When PART C of this service bulletin is completed, make this entry in the applicable logbooks: “Service Bulletin 601R---57---052, Revision B, Wing Structure --- Auxiliary --- Inspection and Replacement of the Main Landing Gear (MLG) Side---Brace Shaft Fitting (P/N 601R10237---1 or P/N 601R10237---3), Part C, incorporated.”

### SERVICE BULLETIN 601R---57 ---052

Page 36 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 PART D --- Replacement of the MLG Side ---Brace Shaft Fitting (P/N 601R10237 ---1 or P/N 601R10237 ---3) on the Right Side Reference Information
REFERENCE DESIGNATION AMM 07---11---01---582---801 Put the Aircraft on Jacks AMM 07---11---01---582---804 Removal of the Aircraft from Jacks AMM 10---11---00---000---801 Removal of the Nose Landing Gear Lockpin AMM 10---11---00---400---801 Installation of the Nose Landing Gear Lockpin AMM 10---11---00---000---802 Removal of the Main Landing Gear Lockpins AMM 10---11---00---400---802 Installation of the Main Landing Gear Lockpins AMM 12---00---06---863---803 Pressurize Hydraulic System No. 3 AMM 12---00---06---863---804 Release Hydraulic Pressure --- System No. 3 AMM 12---00---07---861---801 Connect External AC Power AMM 12---00---07---861---802 Remove External AC Power AMM 20---21---00---910---801 Torque Procedures for Threaded Fasteners AMM 20---24---00---910---801 Cotter Pins --- Maintenance Practices AMM 24---00---00---910---801 Electrical/Electronic Safety Precautions AMM 26---14---00---710---801 Operational Test of the MLG Overheat Detection and Warning System AMM 32---30---00---710---802 Landing Gear Extension and Retraction --- Maintenance Practices AMM 32---34---00---710---801 Operational Test of the Landing Gear Manual--- Release---System AMM 53---83---01---000---801 Removal of the MLG Wheel Bin AMM 53---83---01---400---801 Installation of the MLG Wheel Bin AMM 57---21---28---000---801 Removal of the MLG Side---Brace Shaft ---Fitting AMM 57---21---28---400---801 Installation of the MLG Side---Brace Shaft --- Fitting NDTM 51---20---09 Visual---Inspection Procedures SRM 51---21---11 Corrosion Prevention Procedures SRM 51---23---00 Pressure, Environmental, Fuel Tank and Firewall Sealing SRM 51---25---06 Fluid ---Resistant (FR) Epoxy Primer SRM 51---25---16 Fluid ---Resistant (FR) Polyurethane Topcoat

### SERVICE BULLETIN 601R---57 ---052

Page 37 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 REFERENCE DESIGNATION SRM 51---26---00 Cleaning
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 when specified differently. J. Job Set-Up WARNING: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU DO MAINTENANCE ON OR NEAR ELECTRICAL/ELECTRONIC EQUIPMENT. IF YOU DO NOT OBEY THE SAFETY PRECAUTIONS, INJURIES TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT CAN OCCUR. (1) Obey all the electrical/electronic safety precautions (Refer to AMM 24---00---00---910---801). (2) Remove the external AC power from the aircraft (Refer to AMM 12---00---07---861---802).
(3) Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE

CBP ---1 A2 HYD PUMP 3B 221 CBP ---1 G11 HYD SYST AC PUMP CONT 3B 221 CBP --- 1 F6 PROX SENS LGC/D1 221 CBP --- 1 F7 PROX SENS WOW 1 221 CBP --- 2 A2 HYD PUMP 3A 222 CBP --- 2 F9 PROX SENS WOW 2 222 CBP --- 2 G15 HYD SYST AC PUMP CONT 3A 222

### SERVICE BULLETIN 601R---57 ---052

Page 38 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 CB PANEL ZONE NAME CB NO. CBP --- 2 N9 MLG BAY OVHT DET 222 CBP --- 2 P2 PROX SENS LGC/D1 222 CBP --- 2 P3 PROX SENS LGC/D2 WOW 1 + 2 222 CBP --- 4 B13 PROX SENS LGC/D2 222
WARNING: MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. (4) Install the nose landing gear (NLG) lockpin (Refer to AMM 10---11---00---400---801). (5) Install the main landing gear (MLG) lockpins (Refer to AMM 10---11---00---400---802). (6) Lift the aircraft on jacks (Refer to AMM 07---11---01---582---801). WARNING: OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON ANY HYDRAULIC SYSTEM OR ON A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT OBEY THE SAFETY PRECAUTIONS, YOU CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. (7) Release hydraulic pressure from system No. 3 (Refer to AMM 12---00---06---863---804). (8) Remove the MLG wheel bin (Refer to AMM 53---83---01---000---801).

### SERVICE BULLETIN 601R---57 ---052

Page 39 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 K. Procedure Refer to Figure 3 (Sheets 1 and 2). (1) Remove and discard the MLG side---brace shaft fitting (Refer to AMM 57---21---28---000---801). Discard the nuts (2) and (8), the washer (7), and the cotter pins (1) and (9). (2) Do a detailed visual inspection of the forward and aft bushings for signs of corrosion, wear, scratches, nicks, gouges, scores, deformation, or other damage (Refer to NDTM 51---20---09). (3) If corrosion is found, do as follows: (a) Remove the corrosion (Refer to SRM 51---21---06 for parts made with martensitic corrosion--- resistant steel) with a fine---grit abrasive pad instead of aluminum oxide abrasive paper. (b) After the corrosion is removed, make sure that the forward bushing has a maximum diameter of 1.1887 in. (30.193 mm). (c) After the corrosion is removed, make sure that the aft bushing has a maximum diameter of 1.8021 in. (45.773 mm). (4) Inspect the area between the forward and the aft bushings for corrosion. (5) If there is more corrosion, damage to the bushings, or corrosion in the area between the bushings, speak with a representative of Bombardier at the Technical Help Desk at phone number 514-855-8500 for a disposition. CAUTION: MAKE SURE THAT YOU PROTECT THE FITTING AND THE BUSHINGS DURING THE SHAFT FITTING REMOVAL AND INSTALLATION. IF YOU DO NOT, THE FITTING ASSEMBLY WILL GET DAMAGED AND REQUIRE REPLACEMENT. CAUTION: DO NOT TURN THE SHAFT FITTING DURING INSTALLATION. IF YOU DO THE SURFACE FINISH WILL BE DAMAGED. (6) Install the MLG side---brace shaft fitting (5) as follows:

### SERVICE BULLETIN 601R---57 ---052

Page 40 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 (a) Clean the mating surfaces of the MLG side---brace shaft fitting (5), the bushings (12) and (13), and the space between the bushings (12) and (13) (Refer to SRM 51---26---00). (b) Apply a layer of BAMS 552---010 compound to the mating surfaces of the MLG side---brace shaft fitting (5), the MLG side---brace fitting (6), and the bushings (12) and (13). (c) Make sure there is enough compound to fill the space between the bushings (12) and (13). (d) Make sure there is enough compound to have equal quantities of squeeze---out all around the bushings (12) and (13). (e) Align the straight edge of the flange of the MLG side---brace shaft fitting (5) with the locating flange on the MLG side---brace fitting (6). (f) Install the MLG side---brace shaft fitting (5) in the MLG side---brace fitting (6). (g) Clean the threads of the MLG side---brace shaft fitting (5) and the flange of the bushing (12) (Refer to SRM 51---26---00). (h) Install the washer (7), the laminated washer (10), and the nut (8) with fluid --- resistant primer (Refer to SRM 51---25---06). Make sure the laminated washer (10) is between the flange of the bushing (12) and the washer (7). (i) If necessary, peel the laminated washer (10) to correctly engage the cotter pin (9). (j) Torque the nut (8) from 74.2 lbf ft to 90.8 lbfft (100.6 to 123.1 N.m) (Refer to AMM 20---21---00---910---801). NOTE: The running torque has been added to the torque value. (k) It is permitted to loosen and reinstall the nut (8) to correctly install the cotter pin (9) if the nut (8) was not over ---torqued and if the minimum breakaway torque is at least 7.5 lbf ft (10.2 N.m). (l) Safety the nut (8) with the cotter pin (9) (Refer to AMM 20---24---00---910---801).

### SERVICE BULLETIN 601R---57 ---052

Page 41 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 (m) If the nut (8) was over ---torqued or if the minimum breakaway torque does not meet the requirement, discard and replace the nut (8). (7) Connect the MLG side---stay actuator to the MLG side---brace shaft fitting (5) as follows: CAUTION: MAKE SURE TO CONNECT THE MLG SIDE ---STAY ACTUATOR AND THE MLG SIDE ---BRACE SHAFT FITTING (5) DURING THE APPLICATION LIFE OF THE FILLET SEAL. IF NOT, THE SEALANT CAN BE DAMAGED BY TORQUING OF THE NUT (2) (a) Apply a fillet seal around the aft end of the flange of the MLG side---brace shaft fitting (5) (Refer to SRM 51---23---00). (b) Clean the mating surfaces of the MLG side---stay actuator and the MLG side---brace shaft fitting (5) (Refer to SRM 51---26---00). (c) Clean the threads of the MLG side---brace shaft fitting (5) and the nut (2) (Refer to SRM 51---26---00). (d) Apply a layer of BAMS 552---010 compound to the mating surfaces of the MLG side---stay actuator and the MLG side---brace shaft fitting (5). (e) Install the washer (4) on the MLG side---brace shaft fitting (5). (f) Install the cylinder end of the MLG side---stay actuator on the MLG side---brace shaft fitting (5). (g) Apply a layer of BAMS 552---010 compound to the threads of the MLG side---brace shaft fitting (5). (h) Install the washer (3) and the nut (2) on the MLG side---brace shaft fitting (5). (i) Torque the nut (2) from 41.9 lbfft to 95.3 lbfft (56.8 to 129.2 N.m) (Refer to AMM 20---21---00---910---801). NOTE: The running torque has been added to the torque value. (j) It is permitted to loosen and reinstall the nut (2) to correctly install the cotter pin (1) if the nut (2) was not over ---torqued and if the minimum breakaway torque is at least 11.9 lbfft (16.1 N.m).

### SERVICE BULLETIN 601R---57 ---052

Page 42 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 (k) Safety the nut (2) with the cotter pin (1) (Refer to AMM 20---24---00---910---801). (l) If the nut (2) was over ---torqued or if the minimum breakaway torque does not meet the requirement, discard and replace the nut (2). (m) Lubricate the two ends of the MLG side---stay actuator (Refer to AMM 12---20---32---640---802). (8) Install the sealant cap (11) as follows: (a) Clean the MLG side---brace shaft fitting (5), the nut (8), the washer (7), the laminated washer (10), the cotter pin (9), the bushing (12), and the MLG side---brace fitting (6) (Refer to SRM 51---26---00). (b) Fill the sealant cap (11) with sealing compound MIL ---PRF---81733. (c) Put the sealant cap against the MLG side---brace fitting (6) and over the MLG side---brace shaft fitting (5). NOTE: The sealant should come out continuously around the base of the sealant cap (11).

### SERVICE BULLETIN 601R---57 ---052

Page 43 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 L. Job Close-Out (1) Remove all tools, equipment, and unwanted materials from the work area. (2) Connect external AC power to the aircraft (Refer to AMM 12---00---07---861---801). (3) Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE

CBP ---1 A2 HYD PUMP 3B 221 CBP ---1 G11 HYD SYST AC PUMP CONT 3B 221 CBP --- 1 F6 PROX SENS LGC/D1 221 CBP --- 1 F7 PROX SENS WOW 1 221 CBP --- 2 A2 HYD PUMP 3A 222 CBP --- 2 F9 PROX SENS WOW 2 222 CBP --- 2 G15 HYD SYST AC PUMP CONT 3A 222 CBP --- 2 N9 MLG BAY OVHT DET 222 CBP --- 2 P2 PROX SENS LGC/D1 222 CBP --- 2 P3 PROX SENS LGC/D2 WOW 1 + 2 222

CBP --- 4 B13 PROX SENS LGC/D2 222
(4) Pressurize hydraulic system No. 3 (Refer to AMM 12---00---06---863---803). (5) Do the extension and retraction checks of the landing gear (Refer to AMM 32---30---00---710---802). (6) Do an operational test of the landing gear manual--- release system (Refer to AMM 32---34---00---710---801). (7) Install the MLG wheel bin (Refer to AMM 53---83---01---400---801). (8) Do an operational test of the MLG overheat detection and warning system (Refer to AMM 26---14---00---710---801).

### SERVICE BULLETIN 601R---57 ---052

Page 44 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 (9) Lower the aircraft and remove the jacks (Refer to AMM 07---11---01---582---804). (10) Remove the NLG lockpin (Refer to AMM 10---11---00---000---801). (11) Remove the MLG lockpins (Refer to AMM 10---11---00---000---802). (12) When PART D of 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 601R---57---052, Revision B, incorporated.” (13) When PART D of this service bulletin is completed, make this entry in the applicable logbooks: “Service Bulletin 601R---57---052, Revision B, Wing Structure --- Auxiliary --- Inspection and Replacement of the Main Landing Gear (MLG) Side---Brace Shaft Fitting (P/N 601R10237---1 or P/N 601R10237---3), Part D, incorporated.”

### SERVICE BULLETIN 601R---57 ---052

Page 45 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 Replacement of MLG Side ---Brace Shaft Fitting Figure 3 (Sheet 1 of 2)rsb601r57052_004.dg, rb, 17 juin 2011

NOTES Inspection area. 2. Left side shown, right side opposite. 3 1 2 4 5 6 MLG SIDE--STAY ACTUATOR (REF) 7 8 9 10

SECTION VIEW OF FITTING ASSEMBLY 12

13 LEGEND

1. Cotter pin MS24665--361 (Pre--Mod). MS24665--378 (Post--Mod). 2. Nut MS17826--20. 3. Washer. 4. Washer. 5. MLG side--brace shaft fitting 601R10237--1 or 601R10237--3 (Pre--Mod). 601R10247--3 (Post Mod). 6. MLG side--brace fitting. 7. Washer AN960XC1616 or B0202013S6556--80 (Pre--Mod). 601R10248--1 (Post--Mod). 8. Nut MS17826--16 or B0203053--16 (Pre--Mod). B0203053--16 (Post--Mod). 9. Cotter pin MS24665--360 (Pre--Mod) MS24665--377 (Post--Mod). 10. Laminated Washer B0202013P6556--20 (Post--Mod only). 12. Bushing. 13. Bushing.

Max diameter 1.1887 in. (30.193 mm) Max diameter 1.8021 in. (45.773 mm)

### SERVICE BULLETIN 601R---57 ---052

Page 46 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 Replacement of the MLG Side ---Brace Shaft Fitting Figure 3 (Sheet 2 of 2)rsb601r57052_005.dg, gb, 22/07/11 MLG SIDE--STAY ACTUATOR (REF)

LEGEND

5. MLG side--brace shaft fitting 601R10237--1 or 601R10237--3 (Pre--Mod). 601R10247--3 (Post Mod). 6. MLG side--brace fitting. 2. Left side shown, right side opposite.

4 NOTES
Area to apply BAMS 552--010. to the mating surfaces. Fillet seal. SECTION VIEW OF FITTING ASSEMBLY FS515.04 (Post--Mod) (REF)

11
5 4 6

11. Sealant Cap 601R10249--1 (Post--Mod only). FS515.00 (Pre--Mod)

### SERVICE BULLETIN 601R---57 ---052

Page 47 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 3. MATERIAL INFORMATION
A. Kit Information Kit Contents:
KIT 601R57 ---052K1 ¡©
PART NUMBER QUANTITY NAME ALTERNATE PARTS NOTES
601R10247---3 1 Shaft --- MLG, Side Brace 601R10248---1 1 Washer, Steel 601R10249---1 1 Cap, Sealant B0202013P6556---20 1 Washer, Laminated B0203053---16 1 Nut, Self---Locking MS17826---20 1 Nut, Self---Locking MS24665---377 2 Pin, Cotter MS24665---378 2 Pin, Cotter ¡ The kit can contain more hardware and/or material than necessary. © The kit is for one side only. Order two kits to do PART C and PART D.

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 the shelf life of the material. CONSUMABLES SPECIFICATION QUANTITY NAME REFERENCE MIL ---PRF---23827 Type I & II As necessary Grease, Aircraft and Instrument, Gear and Actuator Screw 04---005 £

No specification As necessary Abrasive Pad 05---012 ¡

### SERVICE BULLETIN 601R---57 ---052

Page 48 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 SPECIFICATION REFERENCE NAME QUANTITY MIL ---C ---81706, Class 1A As necessary Compound, Chemical Conversion 05---025 ¡
MIL ---PRF---23827C Type I As necessary Lubricant, Grease, Aircraft and Instrument, Gear and Actuator Screw 06---038 £

MIL ---PRF---81733 Type II, Class 1, Grade A As necessary Compound, Sealing and Coating, Corrosion Inhibitive 09---031 ¡

MIL ---P ---8116 As necessary Primer, Putty, Corrosion Inhibitor, Fluid ---Resistant (Mastinox) 13---001 ¡

BAMS 565---001 As necessary Primer, Epoxy, Fluid Resistant, Grade A (Green) 13---007B ¡

BAMS 552---010 (CA 1000) As necessary Compound, Non---Chromated Corrosion---Inhibiting Compound 13---012 ¡

BAMS 552---002 As necessary Sealant, Fuel Resistant PR 1776M (B---1/2 or B---2) ©

BAMS 565---002 As necessary Polyurethane Paint, Fluid ---Resistant Enamel ¢

¡ Refer to AMM 51---31---00---990---801. © Refer to SRM 51---23---00. ¢ Refer to SRM 51---25---16. £ Refer to AMM 12---20---32---640---802.

C. Special Tools and Equipment There are no special tools and equipment for this service bulletin.

### SERVICE BULLETIN 601R---57 ---052

Page 49 of 49 Jul 28/2011 SB 601R---57---052 Revision B, Oct 12/2012 D. Disposition of Parts The table that follows shows the disposition of installed parts on the aircraft (or spares), and the relation of installed parts (or spares) to the new parts to be installed with this service bulletin.
PRE-SB PART NUMBER NAME QUANTITY DC POST-SB PART NUMBER 601R10237---1 or 601R10237---3 Shaft ---MLG, Brace Fitting 2 DIS 601R10247---3

Disposition code (DC): DIS: Discard Part.

1THANK YOU FOR ANSWERING THIS EVALUATION FORM UPON COMPLETION OF THIS EVALUATIONFORM/COMPLIANCE SHEET, FAX TO 450-476-7300 or email toCRJ_SB_Evaluation_Form@aero.bombardier.com 

### SERVICE BULLETIN EVALUATI ON FORM/COMPLIANCE SHEET (YOUR IDEAS WILL HELP US PROVIDE BETTER BULLETINS)
SERVICE BULLETIN : ISSUE:

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: 

##     

 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