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.

1
Page 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 identify

the 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 identify

the 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 identify

the 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 identify

the 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 identify

the 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

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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 identify

the 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

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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

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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

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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

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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

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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

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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

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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

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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

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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 or

rsb601r57052_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 2

rsb601r57052_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 CB NO. NAME

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

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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 CB NO. NAME

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 QUANTITY NAME

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.

1
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 : ISSUE: 

 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