# Bombardier Service Bulletin 670BA-32-058

Copy: Revision A ("670BA-32-058 A"), 32 pages: PDF https://openairdocs.org/files/sha256/97/74/9774f67850f51eeee49784b61b88b9dc0e2b9d76695f84ed6ab029491e374ab5; text https://openairdocs.org/service-documents/bombardier/670ba-32-058/file/9774f67850f5.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2018-0634; AD 2019-05-12 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: 670BA-32-058
- Latest revision known: 670BA-32-058, Revision A, dated November 7, 2018 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/bombardier/670ba-32-058

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

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

- [AD 2019-05-12](https://openairdocs.org/ad/2019-05-12.md), effective May 3, 2019: Revision A

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/bombardier/670ba-32-058/proposed.md).

## Text (32 pages)

Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2018-0634; AD 2019-05-12 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

the evolution of mobility
SB 670BA−32−058
Page 1 of 1
Nov 07/2018
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
SERVICE BULLETIN 670BA−32−058
SUBJECT:  Landing Gear − Main Landing Gear − Installation of a New Orifice
Support Tube (OST) in the Main Landing Gear Shock Strut Assembly
This Page transmits:
Revision A of Service Bulletin 670BA−32−058, dated Nov 07/2018
The changes in this revision have no effect on aircraft that have had
this service bulletin incorporated.
Reason:
Revised Planning Information, paragraph 1., to:
Clarify the effectivities.
Add the part numbers of the new orifice support tubes in the Reason section.
Add information for new PART C and PART D (on-wing procedure)
Revise the revision of a Reference documents
Revised Accomplishment Instructions, paragraph 2., to:
Add new PART C and PART D to provide an on-wing procedure
This revision also includes small editorial changes that do not have an effect on the technical
content.
Instructions:  
Discard the copy of Service Bulletin 670BA−32−058, dated Sep 26/2016. Replace with
the copy attached.
Refer Goodrich Service Bulletins 49200−32−92, Revision 1 and/or 55200−32−04, Revision 1.
Service Bulletin History:  
Initial issue, dated Sep 26/ 2016
1

### Page 2

the evolution of mobility
SB 670BA−32−058
Page 1 of 31
Sep 26/2016
Revision A, Nov 07/2018
SERVICE BULLETIN
Technical
Publications
THIS SERVICE BULLETIN IS SENT TO EACH OPERATOR. IF THE OPERATOR HAS LEASED AIRCRAFT ,
TRANSFERRED SPARES IN THE LAST SIX MONTHS, SEND THIS SERVICE BULLETIN TO THE NEW
OWNER, UNLESS CONFIRMATION WAS RECEIVED THAT BOMBARDIER HAS INCLUDED THE NEW
OPERATOR ON THE DISTRIBUTION LIST .
SEND THIS SERVICE BULLETIN TO THE LESSEE. IF THE OPERATOR HAS SOLD AIRCRAFT OR
ATA SYSTEM: 32−11 NUMBER: 670BA−32−058
SUBJECT:  Landing Gear − Main Landing Gear − Installation of a New Orifice
Support Tube (OST) in the Main Landing Gear Shock Strut Assembly
1. PLANNING INFORMATION
A. Effectivity
(1) If OST P/N 49212−3 or 49212−5 is installed on aircraft listed below as part of
a P/N 49200−( ) sub−assembly, then replace the OST P/N 49212−3 or
49212−5 with a new OST P/N 49212−7 or 49212−9 per Goodrich service
bulletin 49200−32−92.
PART NUMBER: 49200−9, 49200−13, 49200−17, 49200−21,49200−25, and 49200−29
PART SERIAL
NUMBERS:
SPP0001 thru SPP0145 and
SPP010001 thru SPP010286
INSTALLED AT THE
TIME OF DELIVERY
ON CL−600−2C10
AIRCRAFT SERIAL
NUMBERS:
10002 thru 10263 [1]
SPARES:
Examine all spare parts. If a part with a serial
number listed above is found, it is necessary
to incorporate Goodrich Service Bulletin
49200−32−92.

### Page 3

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 2 of 31
Sep 26/2016
Revision A, Nov 07/2018
PART NUMBER: 49200−9, 49200−13, 49200−17, 49200−21,49200−25, and 49200−29
ALL CL−600−2C10
AIRCRAFT
If parts with the serial numbers listed above
are installed on aircraft, but were not identified
at the time of delivery, on the same aircraft
model, it is necessary to incorporate Goodrich
Service Bulletin 49200−32−92.
PRODUCTION:
[1] Aircraft 10346 and subsequent serial
numbers will have an equivalent modification
incorporated before delivery.
(2) If OST P/N 49212−3 or 49212−5 is installed on aircraft listed below as part of
a P/N 49200−( ) sub−assembly, then replace the OST P/N 49212−3 or
49212−5 with a new OST P/N 49212−7 or 49212−9 per Goodrich service
bulletin 49200−32−92.
PART NUMBER: 49200−10, 49200−14, 49200−18, 49200−22,49200−26, and 49200−30
PART SERIAL
NUMBERS:
SPP0001 thru SPP0141 and SPP015001 thru
SPP015281
INSTALLED AT THE
TIME OF DELIVERY
ON CL−600−2C10
AIRCRAFT SERIAL
NUMBERS:
10002 thru 10263 [1]
SPARES:
Examine all spare parts. If a part with a serial
number listed above is found, it is necessary
to incorporate Goodrich Service Bulletin
49200−32−92.
ALL CL−600−2C10
AIRCRAFT
If parts with the serial numbers listed above
are installed on aircraft, but were not identified
at the time of delivery, on the same aircraft
model, it is necessary to incorporate Goodrich
Service Bulletin 49200−32−92.

### Page 4

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 3 of 31
Sep 26/2016
Revision A, Nov 07/2018
PART NUMBER: 49200−10, 49200−14, 49200−18, 49200−22,49200−26, and 49200−30
PRODUCTION:
[1] Aircraft 10346 and subsequent serial
numbers will have an equivalent modification
incorporated before delivery.
(3) If OST P/N 49212−3 or 49212−5 is installed on CL−600−2C10 aircraft listed
below as part of a P/N 49200−( ) sub−assembly, then replace the OST P/N
49212−3 or 49212−5 with a new OST P/N 49212−7 or 49212−9 per
Goodrich service bulletin 49200−32−92.
If OST P/N 49212−5 is installed on CL−600−2D15 or CL−600−2D24 aircraft
listed below as part of a P/N 49200−( ) sub−assembly, then replace the OST
P/N 49212−5 with a new OST P/N 49212−9 per Goodrich service bulletin
49200−32−92.
PART NUMBER: 49200−11, 49200−15, 49200−19, 49200−23,49200−27, and 49200−31
PART SERIAL
NUMBERS:
SPP0001 thru SPP1011,
SPP510001 thru SPP510403 and
SPC512001 thru SPC512500
INSTALLED AT THE
TIME OF DELIVERY
ON CL−600−2C10
AIRCRAFT SERIAL
NUMBERS:
10264 thru 10345 [1]
INSTALLED AT THE
TIME OF DELIVERY
ON CL−600−2D24
and CL−600−2D15
AIRCRAFT SERIAL
NUMBERS:
15001 thru 15429 [1]
SPARES:
Examine all spare parts. If a part with a serial
number listed above is found, it is necessary
to incorporate Goodrich Service Bulletin
49200−32−92.

### Page 5

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 4 of 31
Sep 26/2016
Revision A, Nov 07/2018
PART NUMBER: 49200−11, 49200−15, 49200−19, 49200−23,49200−27, and 49200−31
ALL CL−600−2C10,
CL−600−2D15, and
CL−600−2D24,
AIRCRAFT
If parts with the serial numbers listed above
are installed on aircraft, but were not identified
at the time of delivery, on the same or on a
different aircraft model, it is necessary to
incorporate Goodrich Service Bulletin
49200−32−92.
PRODUCTION:
[1] Aircraft 10346 and subsequent serial
numbers and 15430 and subsequent serial will
have an equivalent modification incorporated
before delivery.
(4) If OST P/N 49212−3 or 49212−5 is installed on CL−600−2C10 aircraft listed
below as part of a P/N 49200−( ) sub−assembly, then replace the OST P/N
49212−3 or 49212−5 with a new OST P/N 49212−7 or 49212−9 per
Goodrich service bulletin 49200−32−92.
If OST P/N 49212−5 is installed on CL−600−2D15 or CL−600−2D24 aircraft
listed below as part of a P/N 49200−( ) sub−assembly, then replace the OST
P/N 49212−5 with a new OST P/N 49212−9 per Goodrich service bulletin
49200−32−92.
PART NUMBER: 49200−12, 49200−16, 49200−20, 49200−24,49200−28, and 49200−32
PART SERIAL
NUMBERS:
SPP0001 thru SPP1011,
SPP515001 thru SPP515406 and
SPC517001 thru SPC517500
INSTALLED AT THE
TIME OF DELIVERY
ON CL−600−2C10
AIRCRAFT SERIAL
NUMBERS:
10264 thru 10345 [1]

### Page 6

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 5 of 31
Sep 26/2016
Revision A, Nov 07/2018
PART NUMBER: 49200−12, 49200−16, 49200−20, 49200−24,49200−28, and 49200−32
INSTALLED AT THE
TIME OF DELIVERY
ON CL−600−2D24
and CL−600−2D15
AIRCRAFT SERIAL
NUMBERS:
15001 thru 15429 [1]
SPARES:
Examine all spare parts. If a part with a serial
number listed above is found, it is necessary
to incorporate Goodrich Service Bulletin
49200−32−92.
ALL CL−600−2C10,
CL−600−2D15, and
CL−600−2D24,
AIRCRAFT
If parts with the serial numbers listed above
are installed on aircraft, but were not identified
at the time of delivery, on the same or on a
different aircraft model, it is necessary to
incorporate Goodrich Service Bulletin
49200−32−92.
PRODUCTION:
[1] Aircraft 10346 and subsequent serial
numbers and 15430 and subsequent serial will
have an equivalent modification incorporated
before delivery.
(5) If OST P/N 55212−1 is installed on aircraft listed below as part of the P/N
55200−1 sub−assembly, then replace the OST P/N 55212−1 with a new OST
P/N 55212−3 per Goodrich service bulletin 55200−32−04.
PART NUMBER: 55200−1
PART SERIAL
NUMBERS:
SPP010001 thru SPP010041 and
SPC012001 thru SPC012500
INSTALLED AT THE
TIME OF DELIVERY
ON CL−600−2E25
AIRCRAFT SERIAL
NUMBERS:
19001 thru 19052 [1]

### Page 7

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 6 of 31
Sep 26/2016
Revision A, Nov 07/2018
PART NUMBER: 55200−1
SPARES:
Examine all spare parts. If a part with a serial
number listed above is found, it is necessary
to incorporate Goodrich Service Bulletin
55200−32−04.
ALL CL−600−2E25,
AIRCRAFT
If parts with the serial numbers listed above
are installed on aircraft, but were not identified
at the time of delivery, on the same aircraft
model, it is necessary to incorporate Goodrich
Service Bulletin 55200−32−04.
PRODUCTION:
[1] Aircraft 19053 and subsequent serial
numbers, will have an equivalent modification
incorporated before delivery.
(6) If OST P/N 55212−1 is installed on aircraft listed below as part of the P/N
55200−2 sub−assembly, then replace the OST P/N 55212−1 with a new OST
P/N 55212−3 per Goodrich service bulletin 55200−32−04.
PART NUMBER: 55200−2
PART SERIAL
NUMBERS:
SPP015001 thru SPP015041 and
SPC017001 thru SPC017500
INSTALLED AT THE
TIME OF DELIVERY
ON CL−600−2E25
AIRCRAFT SERIAL
NUMBERS:
19001 thru 19052 [1]
SPARES:
Examine all spare parts. If a part with a serial
number listed above is found, it is necessary
to incorporate Goodrich Service Bulletin
55200−32−04.

### Page 8

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 7 of 31
Sep 26/2016
Revision A, Nov 07/2018
PART NUMBER: 55200−2
ALL CL−600−2E25,
AIRCRAFT
If parts with the serial numbers listed above
are installed on aircraft, but were not identified
at the time of delivery, on the same aircraft
model, it is necessary to incorporate Goodrich
Service Bulletin 55200−32−04.
PRODUCTION:
[1] Aircraft 19053 and subsequent serial
numbers, will have an equivalent modification
incorporated before delivery.
NOTE: The instructions in this service bulletin are only applicable to the
systems and parts installed at the time of delivery of the aircraft or as
changed by Bombardier service bulletins. Before you do this service
bulletin, examine all Supplemental Type Certificates (STCs) and
Supplemental Type Approvals (STAs) or equivalent action changes
to make sure you can complete this service bulletin.
B. Reason
(1) Condition
It is possible for the orifice support tube (OST) of the Main Landing Gear
(MLG) to break. If the OST breaks, it is possible that the shock absorber will
not operate correctly. This can cause damage to the aircraft structure and/or
the MLG to collapse.
(2) Evidence
Five broken MLG OSTs have been reported on in-service aircraft.
(3) Objective/Benefit
This service bulletin gives the instructions to do the Goodrich service bulletins
49200−32−92 or 55200−32−04. These Goodrich service bulletins will install
a new improved designed OST in the MLG. The new OST P/N 49212−7 or
49212−9 is for the CL−600−2C10 (CRJ 700), P/N  49212−9 is for the
CL−600−2D15 (CRJ 705) or CL−600−2D24 (CRJ 900), and the P/N
55212−3 is for the CL−600−2E25 (CRJ 1000).

### Page 9

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 8 of 31
Sep 26/2016
Revision A, Nov 07/2018
C. Description
This service bulletin is divided into four parts: PART A, PART B, PART C,
and PART D
Replacement of the LH MLG OST (PART A or PART C) and the RH MLG OST
(PART B or PART D) can be done independently within time limitation as described
in the compliance section.
PART A − Installation of a New OST in the Left MLG Shock Strut Assembly
The aircraft is put on jacks and the left MLG shock strut assembly is removed.
Goodrich Service Bulletin 49200−32−92 or 55200−32−04 is done. The left MLG
shock strut assembly is installed and the aircraft is removed from jacks.
PART B − Installation of a New OST in the Right MLG Shock Strut Assembly
The aircraft is put on jacks and the right MLG shock strut assembly is removed.
Goodrich Service Bulletin 49200−32−92 or 55200−32−04 is done. The right MLG
shock strut assembly is installed and the aircraft is removed from jacks.
PART C − Installation of a New OST in the Left MLG Shock Strut Assembly
(On-Wing Procedure)
The aircraft is put on jacks and the left MLG piston/axle is removed. Section 3.A,
3.B, and 3.D of Goodrich Service Bulletin 49200−32−92 or 55200−32−04 is done.
The left MLG piston/axle is installed. Return to service tests are done on MLG
shock strut. The aircraft is removed from jacks.
PART D − Installation of a New OST in the Right MLG Shock Strut Assembly
(On-Wing Procedure)
The aircraft is put on jacks and the right MLG piston/axle is removed. Section 3.A,
3.B, and 3.D of Goodrich Service Bulletin 49200−32−92 or 55200−32−04 is done.
The right MLG piston/axle is installed. Return to service tests are done on MLG
shock strut. The aircraft is removed from jacks.

### Page 10

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 9 of 31
Sep 26/2016
Revision A, Nov 07/2018
D. Compliance
Recommended service bulletin.
For the OST in the left MLG shock strut assembly, it is necessary to do PART A or
PART C of this service bulletin
For the OST in the right MLG shock strut assembly, it is necessary to do PART B or
PART D of this service bulletin
For CL−600−2C10 aircraft
Bombardier recommends that this service bulletin be done at no more than 21000
flight cycles from the release date on this service bulletin, or before the OST(s)
has/have 40000 flight cycles, whichever comes first, unless otherwise directed by
the airworthiness authority of the operator.
For CL−600−2D15 and CL−600−2D24 aircraft that have OST(s) with less than
23100 flight cycles at the release date on this service bulletin
Bombardier recommends that this service bulletin be done at no more than 20000
flight cycles from the release date on this service bulletin, or before the OST(s)
has/have 29100 flight cycles, whichever comes first, unless otherwise directed by
the airworthiness authority of the operator.
For CL−600−2D15 and CL−600−2D24 aircraft that have OST(s) with 23100 flight
cycles or more at the release date on this service bulletin
Bombardier recommends that this service bulletin be done at no more than 6000
flight cycles from the release date on this service bulletin, unless otherwise directed
by the airworthiness authority of the operator.
For CL−600−2E25 aircraft
Bombardier recommends that this service bulletin be done before the OST(s)
has/have 20000 flight cycles, unless otherwise directed by the airworthiness
authority of the operator.
For all aircraft
NOTE: If it is not possible to complete all the instructions in this service bulletin
because of the configuration of the aircraft, speak with a representative
of Bombardier in the CRC at 1−844−272−2720 (1−844−CRC−CRC0)
or 1−514−855−8500 or e-mail at thd.crj@aero.bombardier.com for
analysis and to get an approved disposition to complete this service
bulletin.
This service bulletin affects Airworthiness Limitations (AWLs) and/or Damage
Tolerance Inspections (DTIs). Reference applicable Pre/Post-Modsum 670T92265
and/or Service Bulletin 670BA−32−058 in the Maintenance Requirements Manual
(MRM).

### Page 11

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 10 of 31
Sep 26/2016
Revision A, Nov 07/2018
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 labor done by an experienced
crew on an aircraft prepared for maintenance.
These estimates do not include the time necessary for:
−Administrative functions such as planning, 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 labor assistance, please speak with a Fleet Services
representative for an estimate. Call the Fleet Services Team through the
CRC at 1−844−272−2720 (1−844−CRC−CRC0) or 1−514−855−8500 or
e-mail at thd.crj@aero.bombardier.com.
FOR PART A
It will take an estimated 12.0 man-hours to complete PART A of this service bulletin.
The man-hours are divided in the table that follows:
TASK MAN-HOURS
(1)  Job Set-Up 4.0
(2)  Procedure N/A
(3)  Test 4.0
(4)  Job Close-Out 4.0
NOTE: These estimates do not include the man-hours necessary to do Goodrich
Service Bulletin 49200−32−92 or 55200−32−04.

### Page 12

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 11 of 31
Sep 26/2016
Revision A, Nov 07/2018
FOR PART B
It will take an estimated 12.0 man-hours to complete PART B of this service bulletin.
The man-hours are divided in the table that follows:
TASK MAN-HOURS
(1)  Job Set-Up 4.0
(2)  Procedure N/A
(3)  Test 4.0
(4)  Job Close-Out 4.0
NOTE: These estimates do not include the man-hours necessary to do Goodrich
Service Bulletin 49200−32−92 or 55200−32−04.
FOR PART C
It will take an estimated 9.0 man-hours to complete PART C of this service bulletin.
The man-hours are divided in the table that follows:
TASK MAN-HOURS
(1)  Job Set-Up 3.0
(2)  Procedure N/A
(3)  Test 3.0
(4)  Job Close-Out 3.0
NOTE: These estimates do not include the man-hours necessary to do Goodrich
Service Bulletin 49200−32−92 or 55200−32−04.

### Page 13

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 12 of 31
Sep 26/2016
Revision A, Nov 07/2018
FOR PART D
It will take an estimated 9.0 man-hours to complete PART D of this service bulletin.
The man-hours are divided in the table that follows:
TASK MAN-HOURS
(1)  Job Set-Up 3.0
(2)  Procedure N/A
(3)  Test 3.0
(4)  Job Close-Out 3.0
NOTE: These estimates do not include the man-hours necessary to do Goodrich
Service Bulletin 49200−32−92 or 55200−32−04.
G. Material − Price and Availability
Refer to paragraph 3.B. and to Goodrich Service Bulletin 49200−32−92 or
55200−32−04 for a list of consumables for this service bulletin.
H. Tooling − Price and Availability
Refer paragraph 3.C and to Goodrich Service Bulletin 49200−32−92 or
55200−32−04 for a list of special tools and equipment for this service bulletin.
I. Weight and Balance
For PART A or PART C
For CL−600−2C10 aircraft
WEIGHT ARM MOMENT /C0001
+0.626 lb +813.5 in. +0.509 (1000 lb-in.)
+0.284 kg +20.66 m +0.0059 (1000 kg-m)
/C0001 The value in the Moment column is divided by 1000.
Refer to Weight and Balance Manual.

### Page 14

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 13 of 31
Sep 26/2016
Revision A, Nov 07/2018
For CL−600−2D15 and CL−600−2D24
WEIGHT ARM MOMENT /C0001
+0.626 lb +903.5 in. +0.566 (1000 lb-in.)
+0.284 kg +22.95 m +0.0065 (1000 kg-m)
/C0001 The value in the Moment column is divided by 1000.
Refer to Weight and Balance Manual.
For CL−600−2E25 aircraft
WEIGHT ARM MOMENT /C0001
+0.518 lb +963.5 in. +0.499 (1000 lb-in.)
+0.235 kg +24.47 m +0.0058 (1000 kg-m)
/C0001 The value in the Moment column is divided by 1000.
Refer to Weight and Balance Manual.
For PART B or PART D
For CL−600−2C10 aircraft
WEIGHT ARM MOMENT /C0001
+0.626 lb +813.5 in. +0.509 (1000 lb-in.)
+0.284 kg +20.66 m +0.0059 (1000 kg-m)
/C0001 The value in the Moment column is divided by 1000.
Refer to Weight and Balance Manual.
For CL−600−2D15 and CL−600−2D24
WEIGHT ARM MOMENT /C0001
+0.626 lb +903.5 in. +0.566 (1000 lb-in.)
+0.284 kg +22.95 m +0.0065 (1000 kg-m)
/C0001 The value in the Moment column is divided by 1000.
Refer to Weight and Balance Manual.

### Page 15

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 14 of 31
Sep 26/2016
Revision A, Nov 07/2018
For CL−600−2E25 aircraft
WEIGHT ARM MOMENT /C0001
+0.518 lb +963.5 in. +0.499 (1000 lb-in.)
+0.235 kg +24.47 m +0.0058 (1000 kg-m)
/C0001 The value in the Moment column is divided by 1000.
Refer to Weight and Balance Manual.
J. Electrical Load Data
Not changed.
K. References
Refer to the SB Introduction document for definition or explanation of service
bulletin content.
Restriction and/or Special Instruction (RSI) C−32−1735−00, Revision D
Goodrich Service Bulletin 49200−32−92, Revision 1, Apr 6/18
Goodrich Service Bulletin 55200−32−04, Revision 1, Jul 3/18
Aircraft Maintenance Manual (AMM)
For Bombardier reference only: PCA 75959
L. Other Publications Affected
Aircraft Maintenance Manual (AMM)
Aircraft Illustrated Parts Catalogue (AIPC)
Maintenance Requirement Manual (MRM)
M. Relationship Chart
Refer to Goodrich Service Bulletin 49200−32−92 or 55200−32−04.

### Page 16

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 15 of 31
Sep 26/2016
Revision A, Nov 07/2018
2. ACCOMPLISHMENT INSTRUCTIONS
PART A − Installation of a New OST in the Left MLG Shock Strut Assembly
Reference Information
REFERENCE DESIGNATION
AMM 07−11−01−582−801 Jacking of the Aircraft
AMM 12−00−00−867−801 Standard Aircraft Configuration for Maintenance
AMM 24−00−00−910−801 Electrical/Electronic Safety Precautions
AMM 29−00−00−910−801 Hydraulic Safety Precautions
AMM 29−00−00−910−802 Hydraulic Technical Precautions
AMM 32−11−05−000−801 Removal of the MLG Shock−Strut Assembly
AMM 32−11−05−400−801 Installation of the MLG Shock−Strut Assembly
A. Job Set-Up
NOTE: The steps in the Job Set-Up section of this service bulletin are
recommended steps. The steps give a recommendation to get access
to the work area. This recommendation is to give a safe work area and
to minimize possible damage to surrounding aircraft parts. Alternative
steps can be used at the operator discretion.
(1) Make sure that the aircraft is in standard configuration for maintenance
(refer to AMM 12−00−00−867−801).
(2) Obey all the electrical/electronic safety precautions (refer to AMM
24−00−00−910−801).
(3) Obey all the hydraulic technical precautions (refer to AMM
29−00−00−910−802).
(4) Obey all the hydraulic safety precautions (refer to AMM
29−00−00−910−801).
(5) Make sure there is a warning tag on the landing gear control lever.
(6) Lift the aircraft on jacks (refer to AMM 07−11−01−582−801).
(7) Remove the left MLG shock strut assembly (refer to AMM
32−11−05−000−801).

### Page 17

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 16 of 31
Sep 26/2016
Revision A, Nov 07/2018
B. Procedure
(1) If it is not possible to complete all the instructions in this service bulletin
because of the configuration of the aircraft, speak with a representative of
Bombardier in the CRC at 1−844−272−2720 (1−844−CRC−CRC0) or
1−514−855−8500 or e-mail at thd.crj@aero.bombardier.com for analysis
and to get an approved disposition to complete this service bulletin.
Refer to Figure 1.
For CL−600−2C10, CL−600−2D15 and CL−600−2D24 aircraft
(2) Do Goodrich Service Bulletin 49200−32−92.
For CL−600−2E25 aircraft
(3) Do Goodrich Service Bulletin 55200−32−04.
C. Job Close-Out
NOTE: The steps in the Job Close-Out section of this service bulletin, except for
the return-to-service tests, are recommended steps. The steps give a
recommendation to install components removed during the Job Set-Up.
This recommendation is to make sure that the aircraft is safe and ready
to return to service. Alternative steps can be used at the operator
discretion.
(1) Install the left MLG shock strut assembly (refer to AMM
32−11−05−400−801).
(2) Remove all tools, equipment, and unwanted materials from the work area.
(3) When PART A 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 /quoteblleftService Bulletin
670BA−32−058, Revision A, PART A, incorporated."
(4) When PART A of this service bulletin is completed, make this entry in the
applicable logbooks: /quoteblleftService Bulletin 670BA−32−058, Revision A, Landing
Gear − Main Landing Gear − Installation of a New Orifice Support Tube in the
Main Landing Gear Shock Strut Assembly, PART A, incorporated."

### Page 18

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 17 of 31
Sep 26/2016
Revision A, Nov 07/2018
PART B − Installation of a New OST in the Right MLG Shock Strut Assembly
Reference Information
REFERENCE DESIGNATION
AMM 07−11−01−582−801 Jacking of the Aircraft
AMM 12−00−00−867−801 Standard Aircraft Configuration for Maintenance
AMM 24−00−00−910−801 Electrical/Electronic Safety Precautions
AMM 29−00−00−910−801 Hydraulic Safety Precautions
AMM 29−00−00−910−802 Hydraulic Technical Precautions
AMM 32−11−05−000−801 Removal of the MLG Shock−Strut Assembly
AMM 32−11−05−400−801 Installation of the MLG Shock−Strut Assembly
D. Job Set-Up
NOTE: The steps in the Job Set-Up section of this service bulletin are
recommended steps. The steps give a recommendation to get access
to the work area. This recommendation is to give a safe work area and
to minimize possible damage to surrounding aircraft parts. Alternative
steps can be used at the operator discretion.
(1) Make sure that the aircraft is in standard configuration for maintenance
(refer to AMM 12−00−00−867−801).
(2) Obey all the electrical/electronic safety precautions (refer to AMM
24−00−00−910−801).
(3) Obey all the hydraulic technical precautions (refer to AMM
29−00−00−910−802).
(4) Obey all the hydraulic safety precautions (refer to AMM
29−00−00−910−801).
(5) Make sure there is a warning tag on the landing gear control lever.
(6) Lift the aircraft on jacks (refer to AMM 07−11−01−582−801).
(7) Remove the right MLG shock strut assembly (refer to AMM
32−11−05−000−801).

### Page 19

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 18 of 31
Sep 26/2016
Revision A, Nov 07/2018
E. Procedure
(1) If it is not possible to complete all the instructions in this service bulletin
because of the configuration of the aircraft, speak with a representative of
Bombardier in the CRC at 1−844−272−2720 (1−844−CRC−CRC0) or
1−514−855−8500 or e-mail at thd.crj@aero.bombardier.com for analysis
and to get an approved disposition to complete this service bulletin.
Refer to Figure 1.
For CL−600−2C10, CL−600−2D15 and CL−600−2D24 aircraft
(2) Do Goodrich Service Bulletin 49200−32−92.
For CL−600−2E25 aircraft
(3) Do Goodrich Service Bulletin 55200−32−04.
F . Job Close-Out
NOTE: The steps in the Job Close-Out section of this service bulletin, except for
the return-to-service tests, are recommended steps. The steps give a
recommendation to install components removed during the Job Set-Up.
This recommendation is to make sure that the aircraft is safe and ready
to return to service. Alternative steps can be used at the operator
discretion.
(1) Install the right MLG shock strut assembly (refer to AMM
32−11−05−400−801).
(2) Remove all tools, equipment, and unwanted materials from the work area.
(3) When PART B 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 /quoteblleftService Bulletin
670BA−32−058, Revision A, PART B, incorporated."
(4) When PART B of this service bulletin is completed, make this entry in the
applicable logbooks: /quoteblleftService Bulletin 670BA−32−058, Revision A, Landing
Gear − Main Landing Gear − Installation of a New Orifice Support Tube in the
Main Landing Gear Shock Strut Assembly, PART B, incorporated."

### Page 20

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 19 of 31
Sep 26/2016
Revision A, Nov 07/2018
PART C − Installation of a New OST in the Left MLG Shock Strut Assembly (On-Wing
Procedure)
Reference Information
REFERENCE DESIGNATION
AMM 07−11−01−582−801 Jacking of the Aircraft
AMM 12−00−00−867−801 Standard Aircraft Configuration for Maintenance
AMM 24−00−00−910−801 Electrical/Electronic Safety Precautions
AMM 29−00−00−910−801 Hydraulic Safety Precautions
AMM 29−00−00−910−802 Hydraulic Technical Precautions
AMM 32−11−00−840−802 Restore the Main-Landing-Gear (MLG) Shock Strut
to Normal Configuration After Maintenance
AMM 32−11−09−000−801 Removal of the MLG Piston/Axle Assembly
AMM 32−11−09−400−801 Installation of the MLG Piston/Axle Assembly
AMM 32−11−25−000−801 Removal of the MLG Swivel Coupling
AMM 32−11−25−400−801 Installation of the MLG Swivel Coupling
AMM 32−32−05−000−806 Removal of the MLG Retraction-Actuator Bracket
AMM 32−32−05−400−806 Installation of the MLG Retraction-Actuator Bracket
G. Job Set-Up
NOTE: The steps in the Job Set-Up section of this service bulletin are
recommended steps. The steps give a recommendation to get access
to the work area. This recommendation is to give a safe work area and
to minimize possible damage to surrounding aircraft parts. Alternative
steps can be used at the operator discretion.
(1) Make sure that the aircraft is in standard configuration for maintenance
(refer to AMM 12−00−00−867−801).
(2) Obey all the electrical/electronic safety precautions (refer to AMM
24−00−00−910−801).
(3) Obey all the hydraulic technical precautions (refer to AMM
29−00−00−910−802).

### Page 21

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 20 of 31
Sep 26/2016
Revision A, Nov 07/2018
(4) Obey all the hydraulic safety precautions (refer to AMM
29−00−00−910−801).
(5) Make sure there is a warning tag on the landing gear control lever.
(6) Lift the aircraft on jacks (refer to AMM 07−11−01−582−801).
(7) Remove the left MLG piston/axle assembly (refer to AMM
32−11−09−000−801).
(8) If necessary, remove the left MLG Aft hydraulic swivel (refer to AMM
32−11−25−000−801).
(9) If necessary, remove the left MLG retract-actuator bracket (refer to AMM
32−32−05−000−806).
H. Procedure
(1) If it is not possible to complete all the instructions in this service bulletin
because of the configuration of the aircraft, speak with a representative of
Bombardier in the CRC at 1−844−272−2720 (1−844−CRC−CRC0) or
1−514−855−8500 or e-mail at thd.crj@aero.bombardier.com for analysis
and to get an approved disposition to complete this service bulletin.
Refer to Figure 1.
For CL−600−2C10, CL−600−2D15 and CL−600−2D24 aircraft
(2) Do Section 3.A., steps (2) through (6) inclusively of Goodrich Service Bulletin
49200−32−92.
(3) Do Section 3.B., steps (1) through (14) inclusively of Goodrich Service Bulletin
49200−32−92 with the exceptions that follow:
(a) Do not apply fillet seal after assembly of the OST , the tab washer and the
nut at the two locations shown on the illustration in Figure 1, Note 6 until
the servicing and a leak check is completed per the close out section of
this service bulletin.
For CL−600−2E25 aircraft
(4) Do Section 3.A., steps (2) through (6) inclusively of Goodrich Service Bulletin
55200−32−04.
(5) Do Section 3.B., steps (1) through (14) inclusively of Goodrich Service Bulletin
55200−32−04 with the exceptions that follow:
(a) Do not apply fillet seal after assembly of the OST , the tab washer and the
nut at the two locations shown on the illustration in Figure 1, Note 6 until
the servicing and a leak check is completed per the close out section of
this service bulletin.

### Page 22

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 21 of 31
Sep 26/2016
Revision A, Nov 07/2018
I. Job Close-Out
NOTE: The steps in the Job Close-Out section of this service bulletin, except for
the return-to-service tests, are recommended steps. The steps give a
recommendation to install components removed during the Job Set-Up.
This recommendation is to make sure that the aircraft is safe and ready
to return to service. Alternative steps can be used at the operator
discretion.
(1) If removed, install the left MLG retraction-actuator bracket (refer to AMM
32−32−05−400−806).
(2) If removed, install the left MLG swivel coupling (refer to AMM
32−11−25−400−801).
(3) Install the left MLG piston/axle assembly (refer to AMM
32−11−09−400−801).
(4) Restore the left MLG shock strut to normal configuration after maintenance
(refer to AMM 32−11−00−840−802) and as follows:
Refer to Figure 2.
(a) When the shock strut is fully extended, make sure the Dimension /quoteblleftX" is
between 14.00 to 14.17 in. (35.6 to 36.0 cm).
(b) When the shock strut is fully compressed, make sure the external stop
tabs on the cylinder touch the external stop blocks on the piston axle.
(5) Do a leak check of the nitrogen charge valve to the OST and the OST to the
outer cylinder interface areas with the aircraft on jacks as follows:
(a) Make sure there are no oil leaks from the nitrogen charge valve area at
the top of the left shock strut.
(b) Apply a soapy solution to the nitrogen charge valve to the OST and the
OST to the outer cylinder interface surfaces.
(c) Make sure there are no nitrogen leaks from the nitrogen charge valve
area at the top of the left shock strut.

### Page 23

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 22 of 31
Sep 26/2016
Revision A, Nov 07/2018
(6) Do a leak check of the nitrogen charge valve to the OST and the OST to the
outer cylinder interface areas with the aircraft on on ground as follows:
(a) Make sure there are no oil leaks from the nitrogen charge valve area at
the top of the left shock strut.
(b) Apply a soapy solution to the nitrogen charge valve to the OST and the
OST to the outer cylinder interface surfaces.
(c) Make sure there are no nitrogen leaks from the nitrogen charge valve
area at the top of the left shock strut.
For CL−600−2C10, CL−600−2D15 and CL−600−2D24 aircraft
(7) Apply a fillet seal of the OST , the tab washer and the nut at the two locations
shown on the illustration in Figure 1, Note 6 of Goodrich Service Bulletin
49200−32−92.
For CL−600−2E25 aircraft
(8) Apply a fillet seal of the OST , the tab washer and the nut at the two locations
shown on the illustration in Figure 1, Note 6 of Goodrich Service Bulletin
55200−32−04.
For CL−600−2C10, CL−600−2D15 and CL−600−2D24 aircraft
(9) Do Section 3.D. of Goodrich Service Bulletin 49200−32−92.
For CL−600−2E25 aircraft
(10) Do Section 3.D. of Goodrich Service Bulletin 55200−32−04.

### Page 24

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 23 of 31
Sep 26/2016
Revision A, Nov 07/2018
For all aircraft
(11) Remove all tools, equipment, and unwanted materials from the work area.
(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 /quoteblleftService Bulletin
670BA−32−058, Revision A, PART C, incorporated."
(13) When PART C of this service bulletin is completed, make this entry in the
applicable logbooks: /quoteblleftService Bulletin 670BA−32−058, Revision A, Landing
Gear − Main Landing Gear − Installation of a New Orifice Support Tube in the
Main Landing Gear Shock Strut Assembly, PART C, incorporated."

### Page 25

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 24 of 31
Sep 26/2016
Revision A, Nov 07/2018
PART D − Installation of a New OST in the Right MLG Shock Strut Assembly (On-Wing
Procedure)
Reference Information
REFERENCE DESIGNATION
AMM 07−11−01−582−801 Jacking of the Aircraft
AMM 12−00−00−867−801 Standard Aircraft Configuration for Maintenance
AMM 24−00−00−910−801 Electrical/Electronic Safety Precautions
AMM 29−00−00−910−801 Hydraulic Safety Precautions
AMM 29−00−00−910−802 Hydraulic Technical Precautions
AMM 32−11−00−840−802 Restore the Main-Landing-Gear (MLG) Shock Strut
to Normal Configuration After Maintenance
AMM 32−11−09−000−801 Removal of the MLG Piston/Axle Assembly
AMM 32−11−09−400−801 Installation of the MLG Piston/Axle Assembly
AMM 32−11−25−000−801 Removal of the MLG Swivel Coupling
AMM 32−11−25−400−801 Installation of the MLG Swivel Coupling
AMM 32−32−05−000−806 Removal of the MLG Retraction-Actuator Bracket
AMM 32−32−05−400−806 Installation of the MLG Retraction-Actuator Bracket
J. Job Set-Up
NOTE: The steps in the Job Set-Up section of this service bulletin are
recommended steps. The steps give a recommendation to get access
to the work area. This recommendation is to give a safe work area and
to minimize possible damage to surrounding aircraft parts. Alternative
steps can be used at the operator discretion.
(1) Make sure that the aircraft is in standard configuration for maintenance
(refer to AMM 12−00−00−867−801).
(2) Obey all the electrical/electronic safety precautions (refer to AMM
24−00−00−910−801).
(3) Obey all the hydraulic technical precautions (refer to AMM
29−00−00−910−802).

### Page 26

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 25 of 31
Sep 26/2016
Revision A, Nov 07/2018
(4) Obey all the hydraulic safety precautions (refer to AMM
29−00−00−910−801).
(5) Make sure there is a warning tag on the landing gear control lever.
(6) Lift the aircraft on jacks (refer to AMM 07−11−01−582−801).
(7) Remove the right MLG piston/axle assembly (refer to AMM
32−11−09−000−801).
(8) If necessary, remove the right MLG swivel coupling (refer to AMM
32−11−25−000−801).
(9) If necessary, remove the right MLG retraction-actuator bracket (refer to AMM
32−32−05−000−806).
K. Procedure
(1) If it is not possible to complete all the instructions in this service bulletin
because of the configuration of the aircraft, speak with a representative of
Bombardier in the CRC at 1−844−272−2720 (1−844−CRC−CRC0) or
1−514−855−8500 or e-mail at thd.crj@aero.bombardier.com for analysis
and to get an approved disposition to complete this service bulletin.
Refer to Figure 1.
For CL−600−2C10, CL−600−2D15 and CL−600−2D24 aircraft
(2) Do Section 3.A. steps (2) through (6) inclusively of Goodrich Service Bulletin
49200−32−92.
(3) Do Section 3.B. steps (1) through (14) inclusively of Goodrich Service Bulletin
49200−32−92 with the exceptions that follow:
(a) Do not apply fillet seal after assembly of the OST , the tab washer and the
nut at the two locations shown on the illustration in Figure 1, Note 6 until
the servicing and a leak check is completed per the close out section of
this service bulletin.
For CL−600−2E25 aircraft
(4) Do Section 3.A. steps (2) through (6) inclusively of Goodrich Service Bulletin
55200−32−04.
(5) Do Section 3.B. steps (1) through (14) inclusively of Goodrich Service Bulletin
55200−32−04 with the exceptions that follow:
(a) Do not apply fillet seal after assembly of the OST , the tab washer and the
nut at the two locations shown on the illustration in Figure 1, Note 6 until
the servicing and a leak check is completed per the close out section of
this service bulletin.

### Page 27

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 26 of 31
Sep 26/2016
Revision A, Nov 07/2018
L. Job Close-Out
NOTE: The steps in the Job Close-Out section of this service bulletin, except for
the return-to-service tests, are recommended steps. The steps give a
recommendation to install components removed during the Job Set-Up.
This recommendation is to make sure that the aircraft is safe and ready
to return to service. Alternative steps can be used at the operator
discretion.
(1) If removed, install the right MLG retraction-actuator bracket (refer to AMM
32−32−05−400−806).
(2) If removed, install the right MLG swivel coupling (refer to AMM
32−11−25−400−801).
(3) Install the right MLG piston/axle assembly (refer to AMM
32−11−09−400−801).
(4) Restore the right MLG shock strut to normal configuration after maintenance
(refer to AMM 32−11−00−840−802) and as follows:
Refer to Figure 2.
(a) When the shock strut is fully extended, make sure the Dimension /quoteblleftX" is
between 14.00 to 14.17 in. (35.6 to 36.0 cm).
(b) When the shock strut is fully compressed, make sure the external stop
tabs on the cylinder touch the external stop blocks on the piston axle.
(5) Do a leak check of the nitrogen charge valve to the OST and the OST to the
outer cylinder interface areas with the aircraft on jacks as follows:
(a) Make sure there are no oil leaks from the nitrogen charge valve area at
the top of the right shock strut.
(b) Apply a soapy solution to the nitrogen charge valve to the OST and the
OST to the outer cylinder interface surfaces.
(c) Make sure there are no nitrogen leaks from the nitrogen charge valve
area at the top of the right shock strut.

### Page 28

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 27 of 31
Sep 26/2016
Revision A, Nov 07/2018
(6) Do a leak check of the nitrogen charge valve to the OST and the OST to the
outer cylinder interface areas with the aircraft on on ground as follows:
(a) Make sure there are no oil leaks from the nitrogen charge valve area at
the top of the right shock strut.
(b) Apply a soapy solution to the nitrogen charge valve to the OST and the
OST to the outer cylinder interface surfaces.
(c) Make sure there are no nitrogen leaks from the nitrogen charge valve
area at the top of the right shock strut.
For CL−600−2C10, CL−600−2D15 and CL−600−2D24 aircraft
(7) Apply a fillet seal of the OST , the tab washer and the nut at the two locations
shown on the illustration in Figure 1, Note 6 of Goodrich Service Bulletin
49200−32−92.
For CL−600−2E25 aircraft
(8) Apply a fillet seal of the OST , the tab washer and the nut at the two locations
shown on the illustration in Figure 1, Note 6 of Goodrich Service Bulletin
55200−32−04.
For CL−600−2C10, CL−600−2D15 and CL−600−2D24 aircraft
(9) Do Section 3.D. of Goodrich Service Bulletin 49200−32−92.
For CL−600−2E25 aircraft
(10) Do Section 3.D. of Goodrich Service Bulletin 55200−32−04.

### Page 29

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 28 of 31
Sep 26/2016
Revision A, Nov 07/2018
For all aircraft
(11) Remove all tools, equipment, and unwanted materials from the work area.
(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 /quoteblleftService Bulletin
670BA−32−058, Revision A, PART D, incorporated."
(13) When PART D of this service bulletin is completed, make this entry in the
applicable logbooks: /quoteblleftService Bulletin 670BA−32−058, Revision A, Landing
Gear − Main Landing Gear − Installation of a New Orifice Support Tube in the
Main Landing Gear Shock Strut Assembly, PART D, incorporated."

### Page 30

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 29 of 31
Sep 26/2016
Revision A, Nov 07/2018
MLG Orifice Support Tube − Locator
Figure 1 (Sheet 1 of 1)
A
B
ORIFICE
SUPPORT
TUBE (REF)
PISTON/AXLE
ASSEMBLY (REF)
ba8778a01, kp, Aug. 16, 2016
OUTER
CYLINDER
(REF)
NOTES
1. Left side shown, right side opposite.
A
B
2. The orifice support tube is in the outer cylinder.

### Page 31

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 30 of 31
Sep 26/2016
Revision A, Nov 07/2018
MLG Shock Strut − Dimension /quoteblleftX" and Leak Check Area
Figure 2 (Sheet 1 of 1)
bc8424a01.cgm, md, jan16/2018
C
B
A
B
C
NITROGEN CHARGE
VALVE (REF)
DIMENSION X
(REF)
CYLINDER
EXTERNAL
TAB (REF)
PISTON AXLE
STOP BLOCK
(REF)
A

### Page 32

SERVICE BULLETIN  670BA−32−058
SB 670BA−32−058
Page 31 of 31
Sep 26/2016
Revision A, Nov 07/2018
3. MATERIAL INFORMATION
A. Kit Information
Refer to Goodrich Service Bulletin 49200−32−92 or 55200−32−04.
B. Consumable Information
For a list of consumables, refer to the different tasks and the Goodrich service
bulletin that are given as references in this service bulletin.
C. Special Tools and Equipment
For a list of special tools and equipment, refer to the different tasks and the
Goodrich service bulletin that are given as references in this service bulletin.
D. Disposition of Parts
Refer to Goodrich Service Bulletin 49200−32−92 or 55200−32−04.
1

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