# Bombardier Service Bulletin 601R-57-052

## Copies (3)

Copies the FAA filed in AD dockets on regulations.gov, newest revision first. A newer revision may exist.

- Revision A ("Bombardier, Inc. - Service Bulletin"), 51 pages: PDF https://openairdocs.org/files/sha256/18/04/18049b3886969d47821377e42eaae46c503dabf4b21e76e71e5b067f092eb082; text https://openairdocs.org/service-documents/bombardier/601r-57-052/file/18049b388696.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2012-0592; AD 2012-21-14 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Revision A ("Comair, Inc - Service Bulletin - 601R-57-052A Inspection and Replacement of the MLG Side-Brace Shaft Fittings PN 601R10237-1 or PN 601R10237-3"), 51 pages: PDF https://openairdocs.org/files/sha256/21/d8/21d8bcb3bed9f8806f92bcb526e1731bf796a3a9c4b796250b7a1d4548086201; text https://openairdocs.org/service-documents/bombardier/601r-57-052/file/21d8bcb3bed9.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2012-0592; AD 2012-21-14 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Revision A ("U.S. DOT/FAA - Service Information"), 51 pages: PDF https://openairdocs.org/files/sha256/89/ee/89ee53c6ae97ff03fef1283c153b72337004500ea057f1ae710584047c434bf2; text https://openairdocs.org/service-documents/bombardier/601r-57-052/file/89ee53c6ae97.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2012-0592; AD 2012-21-14 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Bombardier](https://openairdocs.org/service-documents/bombardier.md)
- Type: Service bulletin (Service Bulletin)
- Number: 601R-57-052
- Latest revision known: 601R-57-052, Revision A, dated October 28, 2011 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/bombardier/601r-57-052

## ADs that cite it (1) (OpenAirDocs)

Newest first, with the revision each names, as OpenAirDocs read it from the AD's text.

- [AD 2012-21-14](https://openairdocs.org/ad/2012-21-14.md), effective Dec 5, 2012: Revision A

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/bombardier/601r-57-052/proposed.md).

## Text (51 pages)

Revision A, the newest copy. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2012-0592; AD 2012-21-14 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

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
S U B J E C T: W i n g S t r u c t u r e --- A u x i l i a r y --- I n s p e c t i o n a n d R e p l a c e m e n t o f t h e M a i n
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 2

Page 1 of 49
Jul 28/2011 SB 601R- - - 57- - - 052
Revision B, Oct 12/2012
SERVICE BULLETIN
T echnical
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
S U B J E C T: W i n g S t r u c t u r e --- A u x i l i a r y --- I n s p e c t i o n a n d R e p l a c e m e n t o f t h e M a i n
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
T wo instances were reported on in- - -service aircraft.
(3) Objective/Benefit
This service bulletin gives the procedure to do an inspection of the MLG
s i d e - - - b r a c es h a f tf i t t i n g sa n dt h eh a r d w a r ef o rc o r r o s i o n ,a n dt h ep r o c e d u r e
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.

### Page 3

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.

### Page 4

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
PA R T A ---
Inspection of the
Threads of the MLG
S i d e --- B r a c e S h a f t
Fitting (P/N
601R10237- - - 1 or P/N
601R10237- - - 3) on
the Left Side
F o ra i r c r a f tt h a to p e r -
ate more than 900
flight hours per year
and that have shaft
P/N 601R10237- - - 1 or
if you cannot identify
the part number with-
out removal of the
shaft.
T o be done no more
than 1000 flight hours
from the release date
of this service bulletin.
OR
Do PART C.
T o be repeated every
1000 flight hours from
the initial inspection
date of PART A until
PART C has been
done.
F o ra i r c r a f tt h a to p e r -
ate 900 flight hours or
l e s sp e ry e a ra n dt h a t
have shaft P/N
601R10237- - - 1 or if
you cannot identify
the part number with-
out removal of the
shaft.
T o be done no more
than 18 months from
the release date of
this service bulletin.
OR
Do PART C.
T o be repeated every
18 months from the
initial inspection date
of PART A until PART
C has been done.
F o ra i r c r a f tt h a to p e r -
ate more than 900
flight hours per year
and that have shaft
P/N 601R10237- - - 3.
T o be done no more
than 3 years from the
release date of this
service bulletin.
OR
Do PART C.
T o be repeated every
3 years from the initial
inspection date of
PART A until PART C
has been done.
F o ra i r c r a f tt h a to p e r -
ate 900 flight hours or
l e s sp e ry e a ra n dt h a t
have shaft P/N
601R10237- - - 3.
T o be done no more
than 5 years from the
release date of this
service bulletin.
OR
Do PART C.
T o be repeated every
5 years from the initial
inspection date of
PART A until PART C
has been done.

### Page 5

SERVICE BULLETIN 601R- - -57- - -052
Page 4 of 49
Jul 28/2011 SB 601R- - - 57- - - 052
Revision B, Oct 12/2012
PA R T B ---
Inspection of the
Threads of the MLG
S i d e --- B r a c e S h a f t
Fitting (P/N
601R10237- - - 1 or P/N
601R10237- - - 3) on
the Right Side
F o ra i r c r a f tt h a to p e r -
ate more than 900
flight hours per year
and that have shaft
P/N 601R10237- - - 1 or
if you cannot identify
the part number with-
out removal of the
shaft.
T o be done no more
than 1000 flight hours
from the release date
of this service bulletin.
OR
Do PART D.
T o be repeated every
1000 flight hours from
the initial inspection
date of PART B until
PART D has been
done.
F o ra i r c r a f tt h a to p e r -
ate 900 flight hours or
l e s sp e ry e a ra n dt h a t
have shaft P/N
601R10237- - - 1 or if
you cannot identify
the part number with-
out removal of the
shaft.
T o be done no more
than 18 months from
the release date of
this service bulletin.
OR
Do PART D.
T o be repeated every
18 months from the
initial inspection date
of PART B until PART
D has been done.
F o ra i r c r a f tt h a to p e r -
ate more than 900
flight hours per year
and that have shaft
P/N 601R10237- - - 3.
T o be done no more
than 3 years from the
release date of this
service bulletin.
OR
Do PART D.
T o be repeated every
3 years from the initial
inspection date of
PART B until PART D
has been done.
F o ra i r c r a f tt h a to p e r -
ate 900 flight hours or
l e s sp e ry e a ra n dt h a t
have shaft P/N
601R10237- - - 3.
T o be done no more
than 5 years from the
release date of this
service bulletin.
OR
Do PART D.
T o be repeated every
5 years from the initial
inspection date of
PART B until PART D
has been done.
PA R T C ---
Replacement of the
M L G S i d e --- B r a c e
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 with-
out removal of the
shaft.
T o be done no later
than Dec 01/2013.
Not applicable.
For aircraft with shaft
P/N 601R10237- - - 3.
T o be done no later
than June 2021.
Not applicable.

### Page 6

SERVICE BULLETIN 601R- - -57- - -052
Page 5 of 49
Jul 28/2011 SB 601R- - - 57- - - 052
Revision B, Oct 12/2012
PA R T D ---
Replacement of the
M L G S i d e --- B r a c e
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 with-
out removal of the
shaft.
T o be done no later
than Dec 01/2013.
Not applicable.
For aircraft with shaft
P/N 601R10237- - - 3.
T o be done no later
than June 2021.
Not applicable.
This service bulletin affects Airworthiness Limitations (AWLs) and/or Damage
T olerance 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. M a n p o w e r
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 speci fied 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.

### Page 7

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) T est 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) T est 1.0
(4) Job Close-Out 1.0

### Page 8

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 T eam
123 Garratt Blvd, N42- - - 24
T oronto, Ontario
Canada M3K 1Y5
Fax: 416-375-3060
Phone: 416-375-3920
Email: sbkits@aero.bombardier.com
Please contact the Service Bulletin Kit Support T eam 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 K i t --- M L G S i d e B r a c e S h a f t
Replacement
NOTE: Kit 601R57- - - 052K1 is for one side only. Order two kits to do PART C and
PART D.

### Page 9

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 T eam
123 Garratt Blvd, N42- - - 24
T oronto, Ontario
Canada M3K 1Y5
Fax: 416-375-3060
Phone: 416-375-3920
Email: sbkits@aero.bombardier.com
Please contact the Service Bulletin Kit Support T eam 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).
T o place an order for parts or kits, please call Bombardier Parts Logistics at
514-855-2999 or 1-866-538-1247.
H. T ooling - - - 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.

### Page 10

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.

### Page 11

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 T esting 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-SBPART NUMBER NAME
601R10237- - - 1 or
601R10237- - - 3
S h a f t --- M L G
Side Brace
601R10247- - - 3 S h a f t --- M L G
Side Brace

### Page 12

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
A M M 0 7 --- 1 1 --- 0 1 --- 5 8 2 --- 8 0 1 Put the Aircraft on Jacks
A M M 0 7 --- 1 1 --- 0 1 --- 5 8 2 --- 8 0 4 Removal of the Aircraft from Jacks
A M M 1 0 --- 1 1 --- 0 0 --- 0 0 0 --- 8 0 1Removal of the Nose Landing Gear Lockpin
A M M 1 0 --- 1 1 --- 0 0 --- 4 0 0 --- 8 0 1Installation of the Nose Landing Gear Lockpin
A M M 1 0 --- 1 1 --- 0 0 --- 0 0 0 --- 8 0 2Removal of the Main Landing Gear Lockpins
A M M 1 0 --- 1 1 --- 0 0 --- 4 0 0 --- 8 0 2Installation of the Main Landing Gear Lockpins
A M M 1 2 --- 0 0 --- 0 6 --- 8 6 3 --- 8 0 3 Pressurize Hydraulic System No. 3
A M M 1 2 --- 0 0 --- 0 6 --- 8 6 3 --- 8 0 4Release Hydraulic Pressure - - - System No. 3
A M M 1 2 --- 0 0 --- 0 7 --- 8 6 1 --- 8 0 1 Connect External AC Power
A M M 1 2 --- 0 0 --- 0 7 --- 8 6 1 --- 8 0 2 Remove External AC Power
A M M 2 0 --- 2 1 --- 0 0 --- 9 1 0 --- 8 0 1T orque Procedures for Threaded Fasteners
A M M 2 0 --- 2 4 --- 0 0 --- 9 1 0 --- 8 0 1 Cotter Pins - - - Maintenance Practices
A M M 2 4 --- 0 0 --- 0 0 --- 9 1 0 --- 8 0 1 Electrical/Electronic Safety Precautions
A M M 2 6 --- 1 4 --- 0 0 --- 7 1 0 --- 8 0 1Operational T est of the MLG Overheat Detection
and Warning System
A M M 5 3 --- 8 3 --- 0 1 --- 0 0 0 --- 8 0 1 R e m o v a lo ft h eM L GW h e e lB i n
A M M 5 3 --- 8 3 --- 0 1 --- 4 0 0 --- 8 0 1 Installation of the MLG Wheel Bin
N D T M 5 1 --- 2 0 --- 0 9 Visual- - -Inspection Procedures
S R M 5 1 --- 2 1 --- 1 1 Corrosion Prevention Procedures
S R M 5 1 --- 2 3 --- 0 0 Pressure, Environmental, Fuel T ank and Firewall
Sealing
S R M 5 1 --- 2 5 --- 0 6 Fluid- - -Resistant (FR) Epoxy Primer
S R M 5 1 --- 2 5 --- 1 6 Fluid- - -Resistant (FR) Polyurethane T opcoat
S R M 5 1 --- 2 6 --- 0 0 Cleaning

### Page 13

SERVICE BULLETIN 601R- - -57- - -052
Page 12 of 49
Jul 28/2011 SB 601R- - - 57- - - 052
Revision B, Oct 12/2012
T olerance Information
Linear T olerances Angular T olerance
X.XX in. (X.X mm) X.X in. (X mm)
+ / --- 0˚ 30”+/- - - 0.03 in. +/--- 0.1 in.
+ / --- 0 . 8 m m + / --- 3 m m
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
C B P --- 1 A2 HYD PUMP 3B 221
C B P --- 1 G11 H Y DS Y S TA CP U M PC O N T3 B 221
C B P --- 1 F6 PROX SENS LGC/D1 221
C B P --- 1 F7 PROX SENS WOW 1 221
C B P --- 2 A2 HYD PUMP 3A 222
C B P --- 2 F9 PROX SENS WOW 2 222
C B P --- 2 G15 H Y DS Y S TA CP U M PC O N T3 A 222
C B P --- 2 N9 MLG BAY OVHT DET 222
C B P --- 2 P2 PROX SENS LGC/D1 222
C B P --- 2 P3 PROX SENS LGC/D2 WOW 1 + 2 222
C B P --- 4 B13 PROX SENS LGC/D2 222

### Page 14

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 ACCIDENTALL Y 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).

### Page 15

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
t o S R M 5 1 --- 2 6 --- 0 0 ) .
(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).

### Page 16

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 T orque 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).

### Page 17

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
( R e f e r t o S R M 5 1 --- 2 3 --- 0 0 ) .

### Page 18

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
C B P --- 1 A2 HYD PUMP 3B 221
C B P --- 1 G11 H Y DS Y S TA CP U M PC O N T3 B 221
C B P --- 1 F6 PROX SENS LGC/D1 221
C B P --- 1 F7 PROX SENS WOW 1 221
C B P --- 2 A2 HYD PUMP 3A 222
C B P --- 2 F9 PROX SENS WOW 2 222
C B P --- 2 G15 H Y DS Y S TA CP U M PC O N T3 A 222
C B P --- 2 N9 MLG BAY OVHT DET 222
C B P --- 2 P2 PROX SENS LGC/D1 222
C B P --- 2 P3 PROX SENS LGC/D2 WOW 1 +
2
222
C B P --- 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.”

### Page 19

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
A M M 0 7 --- 1 1 --- 0 1 --- 5 8 2 --- 8 0 1 Put the Aircraft on Jacks
A M M 0 7 --- 1 1 --- 0 1 --- 5 8 2 --- 8 0 4 Removal of the Aircraft from Jacks
A M M 1 0 --- 1 1 --- 0 0 --- 0 0 0 --- 8 0 1Removal of the Nose Landing Gear Lockpin
A M M 1 0 --- 1 1 --- 0 0 --- 4 0 0 --- 8 0 1Installation of the Nose Landing Gear Lockpin
A M M 1 0 --- 1 1 --- 0 0 --- 0 0 0 --- 8 0 2Removal of the Main Landing Gear Lockpins
A M M 1 0 --- 1 1 --- 0 0 --- 4 0 0 --- 8 0 2Installation of the Main Landing Gear Lockpins
A M M 1 2 --- 0 0 --- 0 6 --- 8 6 3 --- 8 0 3 Pressurize Hydraulic System No. 3
A M M 1 2 --- 0 0 --- 0 6 --- 8 6 3 --- 8 0 4Release Hydraulic Pressure - - - System No. 3
A M M 1 2 --- 0 0 --- 0 7 --- 8 6 1 --- 8 0 1 Connect External AC Power
A M M 1 2 --- 0 0 --- 0 7 --- 8 6 1 --- 8 0 2 Remove External AC Power
A M M 2 0 --- 2 1 --- 0 0 --- 9 1 0 --- 8 0 1T orque Procedures for Threaded Fasteners
A M M 2 0 --- 2 4 --- 0 0 --- 9 1 0 --- 8 0 1 Cotter Pins - - - Maintenance Practices
A M M 2 4 --- 0 0 --- 0 0 --- 9 1 0 --- 8 0 1 Electrical/Electronic Safety Precautions
A M M 2 6 --- 1 4 --- 0 0 --- 7 1 0 --- 8 0 1Operational T est of the MLG Overheat Detection
and Warning System
A M M 5 3 --- 8 3 --- 0 1 --- 0 0 0 --- 8 0 1 R e m o v a lo ft h eM L GW h e e lB i n
A M M 5 3 --- 8 3 --- 0 1 --- 4 0 0 --- 8 0 1 Installation of the MLG Wheel Bin
N D T M 5 1 --- 2 0 --- 0 9 Visual- - -Inspection Procedures
S R M 5 1 --- 2 1 --- 1 1 Corrosion Prevention Procedures
S R M 5 1 --- 2 3 --- 0 0 Pressure, Environmental, Fuel T ank and Firewall
Sealing
S R M 5 1 --- 2 5 --- 0 6 Fluid- - -Resistant (FR) Epoxy Primer
S R M 5 1 --- 2 5 --- 1 6 Fluid- - -Resistant (FR) Polyurethane T opcoat
S R M 5 1 --- 2 6 --- 0 0 Cleaning

### Page 20

SERVICE BULLETIN 601R- - -57- - -052
Page 19 of 49
Jul 28/2011 SB 601R- - - 57- - - 052
Revision B, Oct 12/2012
T olerance Information
Linear T olerances Angular T olerance
X.XX in. (X.X mm) X.X in. (X mm)
+ / --- 0˚ 30”+/- - - 0.03 in. +/--- 0.1 in.
+ / --- 0 . 8 m m + / --- 3 m m
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
C B P --- 1 A2 HYD PUMP 3B 221
C B P --- 1 G11 H Y DS Y S TA CP U M PC O N T3 B 221
C B P --- 1 F6 PROX SENS LGC/D1 221
C B P --- 1 F7 PROX SENS WOW 1 221
C B P --- 2 A2 HYD PUMP 3A 222
C B P --- 2 F9 PROX SENS WOW 2 222
C B P --- 2 G15 H Y DS Y S TA CP U M PC O N T3 A 222
C B P --- 2 N9 MLG BAY OVHT DET 222
C B P --- 2 P2 PROX SENS LGC/D1 222
C B P --- 2 P3 PROX SENS LGC/D2 WOW 1 + 2 222
C B P --- 4 B13 PROX SENS LGC/D2 222

### Page 21

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 ACCIDENTALL Y 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).

### Page 22

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
S R M 5 1 --- 2 6 --- 0 0 ) .
(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).

### Page 23

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 T orque 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).

### Page 24

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
( R e f e r t o S R M 5 1 --- 2 3 --- 0 0 ) .

### Page 25

SERVICE BULLETIN 601R- - -57- - -052
Page 24 of 49
Jul 28/2011 SB 601R- - - 57- - - 052
Revision B, Oct 12/2012
F. J o b C l o s e - O u t
(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
C B P --- 1 A2 HYD PUMP 3B 221
C B P --- 1 G11 H Y DS Y S TA CP U M PC O N T3 B 221
C B P --- 1 F6 PROX SENS LGC/D1 221
C B P --- 1 F7 PROX SENS WOW 1 221
C B P --- 2 A2 HYD PUMP 3A 222
C B P --- 2 F9 PROX SENS WOW 2 222
C B P --- 2 G15 H Y DS Y S TA CP U M PC O N T3 A 222
C B P --- 2 N9 MLG BAY OVHT DET 222
C B P --- 2 P2 PROX SENS LGC/D1 222
C B P --- 2 P3 PROX SENS LGC/D2 WOW 1 +
2
222
C B P --- 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.”

### Page 26

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

### Page 27

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)
43
2
1
BUSHING
(REF)
(REF)
FITTING
AN960XC1616 or

### Page 28

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
A M M 0 7 --- 1 1 --- 0 1 --- 5 8 2 --- 8 0 1 Put the Aircraft on Jacks
A M M 0 7 --- 1 1 --- 0 1 --- 5 8 2 --- 8 0 4 Removal of the Aircraft from Jacks
A M M 1 0 --- 1 1 --- 0 0 --- 0 0 0 --- 8 0 1Removal of the Nose Landing Gear Lockpin
A M M 1 0 --- 1 1 --- 0 0 --- 4 0 0 --- 8 0 1Installation of the Nose Landing Gear Lockpin
A M M 1 0 --- 1 1 --- 0 0 --- 0 0 0 --- 8 0 2Removal of the Main Landing Gear Lockpins
A M M 1 0 --- 1 1 --- 0 0 --- 4 0 0 --- 8 0 2Installation of the Main Landing Gear Lockpins
A M M 1 2 --- 0 0 --- 0 6 --- 8 6 3 --- 8 0 3 Pressurize Hydraulic System No. 3
A M M 1 2 --- 0 0 --- 0 6 --- 8 6 3 --- 8 0 4Release Hydraulic Pressure - - - System No. 3
A M M 1 2 --- 0 0 --- 0 7 --- 8 6 1 --- 8 0 1 Connect External AC Power
A M M 1 2 --- 0 0 --- 0 7 --- 8 6 1 --- 8 0 2 Remove External AC Power
A M M 2 0 --- 2 1 --- 0 0 --- 9 1 0 --- 8 0 1T orque Procedures for Threaded Fasteners
A M M 2 0 --- 2 4 --- 0 0 --- 9 1 0 --- 8 0 1 Cotter Pins - - - Maintenance Practices
A M M 2 4 --- 0 0 --- 0 0 --- 9 1 0 --- 8 0 1 Electrical/Electronic Safety Precautions
A M M 2 6 --- 1 4 --- 0 0 --- 7 1 0 --- 8 0 1Operational T est of the MLG Overheat Detection
and Warning System
A M M 3 2 --- 3 0 --- 0 0 --- 7 1 0 --- 8 0 2Landing Gear Extension and Retraction - - -
Maintenance Practices
A M M 3 2 --- 3 4 --- 0 0 --- 7 1 0 --- 8 0 1Operational T est of the Landing Gear Manual- - -
R e l e a s e --- S y s t e m
A M M 5 3 --- 8 3 --- 0 1 --- 0 0 0 --- 8 0 1 R e m o v a lo ft h eM L GW h e e lB i n
A M M 5 3 --- 8 3 --- 0 1 --- 4 0 0 --- 8 0 1 Installation of the MLG Wheel Bin
A M M 5 7 --- 2 1 --- 2 8 --- 0 0 0 --- 8 0 1R e m o v a l o f t h e M L G S i d e --- B r a c e S h a f t --- F i t t i n g
A M M 5 7 --- 2 1 --- 2 8 --- 4 0 0 --- 8 0 1I n s t a l l a t i o n o f t h e M L G S i d e --- B r a c e S h a f t ---
Fitting
N D T M 5 1 --- 2 0 --- 0 9 Visual- - -Inspection Procedures
S R M 5 1 --- 2 1 --- 1 1 Corrosion Prevention Procedures
S R M 5 1 --- 2 3 --- 0 0 Pressure, Environmental, Fuel T ank and Firewall
Sealing
S R M 5 1 --- 2 5 --- 0 6 Fluid- - -Resistant (FR) Epoxy Primer
S R M 5 1 --- 2 5 --- 1 6 Fluid- - -Resistant (FR) Polyurethane T opcoat

### Page 29

SERVICE BULLETIN 601R- - -57- - -052
Page 28 of 49
Jul 28/2011 SB 601R- - - 57- - - 052
Revision B, Oct 12/2012
REFERENCE DESIGNATION
S R M 5 1 --- 2 6 --- 0 0 Cleaning
T olerance Information
Linear T olerances Angular T olerance
X.XX in. (X.X mm) X.X in. (X mm)
+ / --- 0˚ 30”+/- - - 0.03 in. +/--- 0.1 in.
+ / --- 0 . 8 m m + / --- 3 m m
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
C B P --- 1 A2 HYD PUMP 3B 221
C B P --- 1 G11 H Y DS Y S TA CP U M PC O N T3 B 221
C B P --- 1 F6 PROX SENS LGC/D1 221
C B P --- 1 F7 PROX SENS WOW 1 221
C B P --- 2 A2 HYD PUMP 3A 222
C B P --- 2 F9 PROX SENS WOW 2 222
C B P --- 2 G15 H Y DS Y S TA CP U M PC O N T3 A 222

### Page 30

SERVICE BULLETIN 601R- - -57- - -052
Page 29 of 49
Jul 28/2011 SB 601R- - - 57- - - 052
Revision B, Oct 12/2012
CB PANEL ZONE NAMECB NO.
C B P --- 2 N9 MLG BAY OVHT DET 222
C B P --- 2 P2 PROX SENS LGC/D1 222
C B P --- 2 P3 PROX SENS LGC/D2 WOW 1 + 2 222
C B P --- 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 ACCIDENTALL Y 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).

### Page 31

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
T echnical 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 ASSEMBL Y WILL GET DAMAGED AND REQUIRE
REPLACEMENT .
CAUTION: DO NOT TURN THE SHAFT FITTING DURING INSTALLATION. IF
YOU DO THE SURFACE FINISH WILL BE DAMAGED.

### Page 32

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) T orque 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).

### Page 33

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)
( R e f e r t o S R M 5 1 --- 2 6 --- 0 0 ) .
(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) T orque 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).

### Page 34

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
M L G s i d e --- b r a c e f i t t i n g ( 6 ) ( R e f e r t o S R M 5 1 --- 2 6 --- 0 0 ) .
(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).

### Page 35

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
C B P --- 1 A2 HYD PUMP 3B 221
C B P --- 1 G11 H Y DS Y S TA CP U M PC O N T3 B 221
C B P --- 1 F6 PROX SENS LGC/D1 221
C B P --- 1 F7 PROX SENS WOW 1 221
C B P --- 2 A2 HYD PUMP 3A 222
C B P --- 2 F9 PROX SENS WOW 2 222
C B P --- 2 G15 H Y DS Y S TA CP U M PC O N T3 A 222
C B P --- 2 N9 MLG BAY OVHT DET 222
C B P --- 2 P2 PROX SENS LGC/D1 222
C B P --- 2 P3 PROX SENS LGC/D2 WOW 1 +
2
222
C B P --- 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).

### Page 36

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.”

### Page 37

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
A M M 0 7 --- 1 1 --- 0 1 --- 5 8 2 --- 8 0 1 Put the Aircraft on Jacks
A M M 0 7 --- 1 1 --- 0 1 --- 5 8 2 --- 8 0 4 Removal of the Aircraft from Jacks
A M M 1 0 --- 1 1 --- 0 0 --- 0 0 0 --- 8 0 1Removal of the Nose Landing Gear Lockpin
A M M 1 0 --- 1 1 --- 0 0 --- 4 0 0 --- 8 0 1Installation of the Nose Landing Gear Lockpin
A M M 1 0 --- 1 1 --- 0 0 --- 0 0 0 --- 8 0 2Removal of the Main Landing Gear Lockpins
A M M 1 0 --- 1 1 --- 0 0 --- 4 0 0 --- 8 0 2Installation of the Main Landing Gear Lockpins
A M M 1 2 --- 0 0 --- 0 6 --- 8 6 3 --- 8 0 3 Pressurize Hydraulic System No. 3
A M M 1 2 --- 0 0 --- 0 6 --- 8 6 3 --- 8 0 4Release Hydraulic Pressure - - - System No. 3
A M M 1 2 --- 0 0 --- 0 7 --- 8 6 1 --- 8 0 1 Connect External AC Power
A M M 1 2 --- 0 0 --- 0 7 --- 8 6 1 --- 8 0 2 Remove External AC Power
A M M 2 0 --- 2 1 --- 0 0 --- 9 1 0 --- 8 0 1T orque Procedures for Threaded Fasteners
A M M 2 0 --- 2 4 --- 0 0 --- 9 1 0 --- 8 0 1 Cotter Pins - - - Maintenance Practices
A M M 2 4 --- 0 0 --- 0 0 --- 9 1 0 --- 8 0 1 Electrical/Electronic Safety Precautions
A M M 2 6 --- 1 4 --- 0 0 --- 7 1 0 --- 8 0 1Operational T est of the MLG Overheat Detection
and Warning System
A M M 3 2 --- 3 0 --- 0 0 --- 7 1 0 --- 8 0 2Landing Gear Extension and Retraction - - -
Maintenance Practices
A M M 3 2 --- 3 4 --- 0 0 --- 7 1 0 --- 8 0 1Operational T est of the Landing Gear Manual- - -
R e l e a s e --- S y s t e m
A M M 5 3 --- 8 3 --- 0 1 --- 0 0 0 --- 8 0 1 R e m o v a lo ft h eM L GW h e e lB i n
A M M 5 3 --- 8 3 --- 0 1 --- 4 0 0 --- 8 0 1 Installation of the MLG Wheel Bin
A M M 5 7 --- 2 1 --- 2 8 --- 0 0 0 --- 8 0 1R e m o v a l o f t h e M L G S i d e --- B r a c e S h a f t --- F i t t i n g
A M M 5 7 --- 2 1 --- 2 8 --- 4 0 0 --- 8 0 1I n s t a l l a t i o n o f t h e M L G S i d e --- B r a c e S h a f t ---
Fitting
N D T M 5 1 --- 2 0 --- 0 9 Visual- - -Inspection Procedures
S R M 5 1 --- 2 1 --- 1 1 Corrosion Prevention Procedures
S R M 5 1 --- 2 3 --- 0 0 Pressure, Environmental, Fuel T ank and Firewall
Sealing
S R M 5 1 --- 2 5 --- 0 6 Fluid- - -Resistant (FR) Epoxy Primer
S R M 5 1 --- 2 5 --- 1 6 Fluid- - -Resistant (FR) Polyurethane T opcoat

### Page 38

SERVICE BULLETIN 601R- - -57- - -052
Page 37 of 49
Jul 28/2011 SB 601R- - - 57- - - 052
Revision B, Oct 12/2012
REFERENCE DESIGNATION
S R M 5 1 --- 2 6 --- 0 0 Cleaning
T olerance Information
Linear T olerances Angular T olerance
X.XX in. (X.X mm) X.X in. (X mm)
+ / --- 0˚ 30”+/- - - 0.03 in. +/--- 0.1 in.
+ / --- 0 . 8 m m + / --- 3 m m
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
C B P --- 1 A2 HYD PUMP 3B 221
C B P --- 1 G11 H Y DS Y S TA CP U M PC O N T3 B 221
C B P --- 1 F6 PROX SENS LGC/D1 221
C B P --- 1 F7 PROX SENS WOW 1 221
C B P --- 2 A2 HYD PUMP 3A 222
C B P --- 2 F9 PROX SENS WOW 2 222
C B P --- 2 G15 H Y DS Y S TA CP U M PC O N T3 A 222

### Page 39

SERVICE BULLETIN 601R- - -57- - -052
Page 38 of 49
Jul 28/2011 SB 601R- - - 57- - - 052
Revision B, Oct 12/2012
CB PANEL ZONE NAMECB NO.
C B P --- 2 N9 MLG BAY OVHT DET 222
C B P --- 2 P2 PROX SENS LGC/D1 222
C B P --- 2 P3 PROX SENS LGC/D2 WOW 1 + 2 222
C B P --- 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 ACCIDENTALL Y 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).

### Page 40

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
T echnical 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 ASSEMBL Y 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:

### Page 41

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) T orque 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).

### Page 42

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)
( R e f e r t o S R M 5 1 --- 2 6 --- 0 0 ) .
(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) T orque 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).

### Page 43

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
M L G s i d e --- b r a c e f i t t i n g ( 6 ) ( R e f e r t o S R M 5 1 --- 2 6 --- 0 0 ) .
(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).

### Page 44

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
C B P --- 1 A2 HYD PUMP 3B 221
C B P --- 1 G11 H Y DS Y S TA CP U M PC O N T3 B 221
C B P --- 1 F6 PROX SENS LGC/D1 221
C B P --- 1 F7 PROX SENS WOW 1 221
C B P --- 2 A2 HYD PUMP 3A 222
C B P --- 2 F9 PROX SENS WOW 2 222
C B P --- 2 G15 H Y DS Y S TA CP U M PC O N T3 A 222
C B P --- 2 N9 MLG BAY OVHT DET 222
C B P --- 2 P2 PROX SENS LGC/D1 222
C B P --- 2 P3 PROX SENS LGC/D2 WOW 1 +
2
222
C B P --- 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).

### Page 45

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.”

### Page 46

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
45
6
MLG
SIDE- -STAY
ACTUATOR
(REF)
78
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)

### Page 47

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)

### Page 48

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 ALTERNATEPARTS 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 N u t , S e l f --- L o c k i n g
MS17826- - - 20 1 N u t , S e l f --- L o c k i n g
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
s h e l fl i f eo ft h em a t e r i a l .
CONSUMABLES
SPECIFICATION QUANTITY NAME REFERENCE
MIL- - - PRF- - - 23827
Typ e I & II
As
necessary
Grease, Aircraft and
Instrument, Gear and
Actuator Screw
04- - - 005£
No specification As
necessary
Abrasive Pad 05- - - 012¡

### Page 49

SERVICE BULLETIN 601R- - -57- - -052
Page 48 of 49
Jul 28/2011 SB 601R- - - 57- - - 052
Revision B, Oct 12/2012
SPECIFICATION REFERENCE NAMEQUANTITY
MIL- - - C - - - 81706,
Class 1A
As
necessary
Compound, Chemical
Conversion
05- - - 025¡
MIL- - - PRF- - - 23827C
Typ e I
As
necessary
Lubricant, Grease,
Aircraft and
Instrument, Gear and
Actuator Screw
06- - - 038£
MIL- - - PRF- - - 81733
T ype 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
P r i m e r ,E p o x y ,F l u i d
Resistant, Grade A
(Green)
13- - - 007B¡
BAMS 552- - - 010
(CA 1000)
As
necessary
Compound,
N o n --- C h r o m a t e d
Corrosion- - - Inhibiting
Compound
13- - - 012¡
BAMS 552- - - 002 As
necessary
Sealant, Fuel
Resistant PR 1776M
( B --- 1 / 2 o r 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 T ools and Equipment
There are no special tools and equipment for this service bulletin.

### Page 50

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
S h a f t --- M L G ,
Brace Fitting 2 DIS 601R10247- - - 3
Disposition code (DC):
DIS: Discard Part.
1

### Page 51

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

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