# Embraer Service Bulletin 190-57-0036

Copy: Revision 02 ("SB190-57-0036R2"), 48 pages: PDF https://openairdocs.org/files/sha256/ae/0f/ae0f0d304f9cfccb6d9e0443a436ced580d02b835d076ccc5c93d8f1cef05998; text https://openairdocs.org/service-documents/embraer/sb-190-57-0036/file/ae0f0d304f9c.md. Rights: © Embraer S.A. Filed by the FAA in regulations.gov docket FAA-2012-1227; AD 2013-11-07 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Embraer](https://openairdocs.org/service-documents/embraer.md)
- Type: Service bulletin (Service Bulletin)
- Number: 190-57-0036
- Latest revision known: 190-57-0036, Revision 02, dated August 12, 2011 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/embraer/sb-190-57-0036

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

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

- [AD 2013-11-07](https://openairdocs.org/ad/2013-11-07.md), effective Jul 9, 2013: Revisions 01 and 02

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/embraer/sb-190-57-0036/proposed.md).

## Text (48 pages)

Rights: © Embraer S.A. Filed by the FAA in regulations.gov docket FAA-2012-1227; AD 2013-11-07 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

1. DESCRIPTION
This sheet transmits Revision 02 to Service Bulletin 190-57-0036.
This is a complete reissue of the Bulletin.
This revision incorporates the information presented in the Information Notice related to the
previous issues of this Service Bulletin, as listed below:
SB190-57-0036R01-IN01
2. ADDITIONAL ACTION
Aircraft that have complied with the previous issue of this bulletin do not need any additional
action.
3. RECORD OF REVISION
Basic issue: 20/Sep/2010.
Revision 01: 28/Feb/2011.
Revision 02: 12/Aug/2011.
4. HIGHLIGHTS
The topics, affected pages, and a brief description of the content-related changes introduced
by this revision are presented below.
Revision bars are put in the left margin of each page to show the location of the significant
changes. Text displacement and text format changes are not indicated.
TOPIC/PAGE DESCRIPTION OF REVISION
1. PLANNING INFORMATION
1.B. CONCURRENT REQUIREMENTS
/02 Updated information.
1.C. REASON
/03 Added reason of Revision 02.
1.E. COMPLIANCE
/05 Included flowchart reference.
2. MATERIAL INFORMATION
2.C. MATERIAL NECESSARY FOR EACH AIR-
CRAFT
/13 and 14 Updated the material to be procured information.
2.F. TOOLING - PRICE AND AVAILABILITY
/15 Updated information.
3. ACCOMPLISHMENT INSTRUCTIONS
/18 thru 20 Updated information.
Figure 6
/41 Updated figure information.
4. APPENDIX 1
/ 43 and 44 Included the Flowchart.
TRANSMITTAL LETTER
SB No.: 190-57-0036
PAGE:1of1
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 2

(No text on this page.)

### Page 3

WINGS - MAIN LANDING GEAR SIDE STAY BUSHING - REPLACEMENT
1. PLANNING INFORMATION
A. SB EFFECTIVITY
Aircraft affected:
(1) GROUP 1
MODEL SN
Embraer 190( ) and 195( ) 19000002, 19000004, 19000006 thru 19000108,
19000110 thru 19000139, 19000141 thru 19000158,
19000160 thru 19000176, 19000178 thru 19000196,
19000198 thru 19000202, 19000204 thru 19000212,
19000214 thru 19000219, 19000221 thru 19000224,
19000226 thru 19000235, 19000237 thru 19000242,
19000244 thru 19000250, 19000252 thru 19000260,
19000262 thru 19000266, 19000268 thru 19000277,
19000279 thru 19000295, 19000297 thru 19000306,
19000308 thru 19000316, 19000318 thru 19000343,
19000345 thru 19000360, 19000363 thru 19000376,
and 19000378 thru 19000381.
(2) GROUP 2
MODEL SN
Embraer 190( ) and 195( ) 19000197, 19000213, 19000220, 19000251,
19000267, 19000344, 19000361, and 19000377.
SERVICE BULLETIN
DATE: 20/Sep/2010
REVISION No.:02 - 12/Aug/2011
SB No.: 190-57-0036
PAGE: 1 of 44
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 4

(3) GROUP 3
MODEL SN
Embraer 190( ) and 195( ) 19000002, 19000004, 19000006 thru 19000108,
19000110 thru 19000139, 19000141 thru 19000158,
19000160 thru 19000176, 19000178 thru 19000202,
19000204 thru 19000210, 19000212 thru 19000224,
19000226 thru 19000235, 19000237 thru 19000242,
19000244 thru 19000260, 19000262 thru 19000277,
19000279 thru 19000295, 19000297 thru 19000306,
19000308 thru 19000316, 19000318 thru 19000339,
19000341, 19000343, 19000344, 19000346 thru
19000361, and 19000363 thru 19000381.
(4) GROUP 4
MODEL SN
Embraer 190( ) and 195( ) 19000211, 19000340, 19000342, and 19000345.
In-production effectivity:
Embraer 190( ) and 195( ) model aircraft SN 19000382 and on have an equivalent
modification factory-incorporated.
B. CONCURRENT REQUIREMENTS
The accomplishment of SB190-32-0043 original issue, or a subsequent approved
revision is recommended in conjunction with the accomplishment of PART II and PART III
of this Service Bulletin.
SERVICE BULLETIN
SB No.: 190-57-0036
PAGE: 2
DATE: 20/Sep/2010
REVISION No.: 02 - 12/Aug/2011
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 5

C. REASON
(1) HISTORY
Instances have been reported concerning the migration of the bushing of the side
stay support fitting on the left-hand and right-hand Main Landing Gear (MLG). The
migration of the bushing may cause inefficient lubrication of the support fitting. In
extreme cases of bushing migration, cracks on the Main Landing Gear (MLG) Side
Stay Support Assembly may occur.
(2) OBJECTIVE
To provide instructions to replace the current bushing of the Main Landing Gear
(MLG) side stay support fitting with new flanged ones plus support spacers.
(3) EXPECTED BENEFITS
This modification is aimed at ensuring proper lubrication of the Main Landing Gear
(MLG) side stay support fitting.
(4) REVISION HISTORY
REVISION 01: This revision has been issued to include the bushing housing
inspection with the installation of an alternative bushing, in case of
bushing housing enlargement. Also, the Main Landing Gear Side
Stay inspection according to SB190-32-0043 has been included.
REVISION 02: This revision has been issued to include an alternative bushing
installation for GROUP 1 and GROUP 3 aircraft and to include the
flowchart in the section 4. APPENDIX 1, to clarify the applicability of
this service bulletin.
D. DESCRIPTION
This Bulletin is divided into 03 PARTS, as follows:
PART I INSPECTION FOR MIGRATION OF THE BUSHING OF THE SIDE STAYSUPPORT FITTING OF THE LH AND RH MAIN LANDING GEAR
Applicable to: Refer to 1.A. SB EFFECTIVITY / GROUPS 1, 2, 3, and 4
SERVICE BULLETIN
DATE: 20/Sep/2010
REVISION No.:02 - 12/Aug/2011
SB No.: 190-57-0036
PAGE: 3
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 6

PART I of this bulletin consists in measuring the axial migration of the bushing from its
housing on the side stay support fitting of the left-hand and right-hand Main Landing Gear
(MLG) .
To do this, it is necessary to gain access to the side stay support fitting of the left-hand
and right-hand Main Landing Gear (MLG).
PART II REPLACEMENT OF THE BUSHING OF THE SIDE STAY SUPPORTFITTING OF THE LH MAIN LANDING GEAR
Applicable to: Refer to 1.A. SB EFFECTIVITY / GROUPS 1 and 2
The modification presented in PART II of this bulletin consists in replacing the current
bushing of the LH Main Landing Gear (MLG) side stay support fitting with a new flanged
one made from beryllium-copper and support spacers installation.
To do this, it is necessary to remove the support assembly of the left-hand Main Landing
Gear (MLG) side stay support fitting.
PART III REPLACEMENT OF THE BUSHING OF THE SIDE STAY SUPPORTFITTING OF THE RH MAIN LANDING GEAR
Applicable to: Refer to 1.A. SB EFFECTIVITY / GROUPS 3 and 4
The modification presented in PART III of this bulletin consists in replacing the current
bushing of the right-hand Main Landing Gear (MLG) side stay support fitting with a new
flanged one made from beryllium-copper and support spacers installation.
To do this, it is necessary to remove the support assembly of the right-hand Main Landing
Gear (MLG) side stay support fitting.
NOTE: The modification presented in this bulletin does not affect Fatigue Critical
Structure (FCS).
E. COMPLIANCE
(1) Applicable to PART I
Embraer recommends that PART I of this bulletin be accomplished from the
impossibility to lubricate the side stay attachment point on the structure. The
lubrication of the side stay attachment point is required by a scheduled maintenance
task.
SERVICE BULLETIN
SB No.: 190-57-0036
PAGE: 4
DATE: 20/Sep/2010
REVISION No.: 02 - 12/Aug/2011
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 7

– If the distance of the bushing migration is less than 5 mm, the inspection of Part
I must be repetitive every 100 Flight Cycle(s) until the accomplishment of Part II
and/or PART III of this bulletin, no later than 1,200 Flight Cycle(s) after lubrication
became impossible.
– If the distance of the bushing migration is equal to or greater than 5 mm,
immediate accomplishment of Part II and/or PART III of this bulletin is necessary.
(2) Applicable to PART II
Embraer recommends that PART II of this bulletin be accomplished as follows:
– If the distance of the bushing migration is less than 5 mm, according to the
inspection presented in PART I, this PART II must be accomplished by the time
that the aircraft logs 1,200 Flight Cycle(s) from the impossibility to lubricate the
side stay attachment point on structure.
– If the distance of the bushing migration is equal to or greater than 5 mm,
according to the inspection presented in PART I, this PART II must be
accomplished immediately.
(3) Applicable to PART III
Embraer recommends that PART III of this bulletin be accomplished as follows:
– If the distance of the bushing migration is less than 5 mm, according to the
inspection presented in PART I, this PART III must be accomplished by the time
that the aircraft logs 1,200 Flight Cycle(s) from the impossibility to lubricate the
side stay attachment point on structure.
– If the distance of the bushing migration is equal to or greater than 5 mm,
according to the inspection presented in PART I, this PART III must be
accomplished immediately.
NOTE: Refer to the Flowchart attached in section 4. APPENDIX 1 of this service
bulletin.
SERVICE BULLETIN
DATE: 20/Sep/2010
REVISION No.:02 - 12/Aug/2011
SB No.: 190-57-0036
PAGE: 5
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 8

F. APPROVAL
The technical aspects of this Service Bulletin are approved by: Agência Nacional de
Aviação Civil (ANAC).
G. ESTIMATED MANPOWER
This estimate is for direct labor only, performed by experienced personnel, and does not
include the time to plan, prepare, or inspect the work.
It is assumed that all the tools, parts, and other means are readily available when
necessary.
This estimate does not include the sealant, paint, or adhesive curing time.
(1) Applicable to PART I
– Access opening: None.
– Inspection: 0.5 man-hours.
– Modification: None.
– Access closure: None.
– Test: None.
(2) Applicable to PART II
– Access opening: 4.5 man-hours.
– Inspection: None.
– Modification: 1.0 man-hour.
– Access closure: 5.0 man-hours.
– Test: 1.0 man-hour.
SERVICE BULLETIN
SB No.: 190-57-0036
PAGE: 6
DATE: 20/Sep/2010
REVISION No.: 02 - 12/Aug/2011
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 9

NOTE: These estimates do not include the time necessary to accomplish
SB190-32-0043.
(3) Applicable to PART III
– Access opening: 4.5 man-hours.
– Inspection: None.
– Modification: 1.0 man-hour.
– Access closure: 5.0 man-hours.
– Test: 1.0 man-hour.
NOTE: These estimates do not include the time necessary to accomplish
SB190-32-0043.
H. WEIGHT AND BALANCE
(1) Applicable to PART I
None.
(2) Applicable to PART II and PART III
(a) Applicable to Embraer 190
– Change in basic weight: + 3.538 lb (+ 1.605 kg).
– Change in basic moment: + 2,481.047 lb.in (+ 28.585 kg.m).
(b) Applicable to Embraer 195
– Change in basic weight: + 3.538 lb (+ 1.605 kg).
– Change in basic moment: + 2,593.605 lb.in (+ 29.885 kg.m).
SERVICE BULLETIN
DATE: 20/Sep/2010
REVISION No.:02 - 12/Aug/2011
SB No.: 190-57-0036
PAGE: 7
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 10

I. SOFTWARE ACCOMPLISHMENT SUMMARY
None.
J. REFERENCES
AMM 190/( ) Aircraft Maintenance Manual PART II - 07-10-01 - LIFTING &
SHORING.
AMM 190/( ) Aircraft Maintenance Manual PART II - 20-00-00 - STANDARD
PRACTICES-AIRFRAME.
AMM 190/( ) Aircraft Maintenance Manual PART II - 29-10-00 - HYDRAULIC
POWER.
AMM 190/( ) Aircraft Maintenance Manual PART II - 32-00-00, 32-00-03,
32-11-05, and 32-11-09 - LANDING GEAR.
SB190-32-0043 LANDING GEAR - MAIN LANDING GEAR SIDE STAY
INSPECTION AND REPAIR.
SRM 190/( ) Structural Repair Manual Part II - 51-21-01, 51-21-02, and
51-21-05 - STANDARD PRACTICES AND STRUCTURES.
K. OTHER PUBLICATIONS AFFECTED
AIPC 190/( ) Aircraft Illustrated Parts Catalog - 32-11-05 - LANDING GEAR.
AMM 190/( ) Aircraft Maintenance Manual PART II - 32-11-05 - LANDING
GEAR.
SRMI 190/( ) Structural Repair Manual Par t I - 57-50-00 - WINGS.
SERVICE BULLETIN
SB No.: 190-57-0036
PAGE: 8
DATE: 20/Sep/2010
REVISION No.: 02 - 12/Aug/2011
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 11

2. MATERIAL INFORMATION
A. MATERIAL - PRICE AND AVAILABILITY
(1) MATERIAL AVAILABLE FROM EMBRAER
The kit(s) below and the parts to be procured mentioned in paragraph Item 2.C.(2)
required for the accomplishment of this bulletin will be available from Embraer at no
charge to the operator during a period of 36 months after the original release date
of this service bulletin.
The estimated delivery date will be provided by Embraer upon request.
When ordering, specify SB 190-57-0036 and Top Kit PN presented in Table below,
as applicable.
REF TOP KIT PN
Unit
Price
(US$)
TOP KIT EFFECTIVITY
01 BS1905700360001 3,034.85 PART II / GROUP 1 aircraft.
02 BS1905700360002 3,034.85 PART II / GROUP 2 aircraft.
03 BS1905700360003 3,034.85 PART III / GROUP 3 aircraft.
04 BS1905700360004 3,034.85 PART III / GROUP 4 aircraft.
(2) MATERIAL AVAILABLE FROM OTHER VENDORS
None.
B. INDUSTRY SUPPORT INFORMATION
None.
SERVICE BULLETIN
DATE: 20/Sep/2010
REVISION No.:02 - 12/Aug/2011
SB No.: 190-57-0036
PAGE: 9
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 12

C. MATERIAL NECESSARY FOR EACH AIRCRAFT
When applicable, the use of alternative or similar parts in place of the one specified in the
kits is allowable, provided that these alternative or similar parts are approved by Embraer
as indicated in the related Embraer Technical Publications or through a formal Embraer
communication channel.
The necessary expendable or consumable parts presented in the AMM Tasks referred to
in this bulletin should be procured from the operator’s inventories or ordered as spares.
The complementary information, when necessary, is presented as Notes in the respective
Table.
For ordering information and Top Kit effectivity refer to section 2.A. MATERIAL - PRICE
AND AVAILABILITY of this Bulletin.
(1) TOP KITS AND KITS
Kit Summary: Top Kit Composition (Kit PN / Quantity)
Top Kit PN 191-20095-601 191-20093-601 191-20096-601 191-20094-601
BS1905700360001 01 - - -
BS1905700360002 - 01 - -
BS1905700360003 - - 01 -
BS1905700360004 - - - 01
(a)
SERVICE BULLETIN
SB No.: 190-57-0036
PAGE: 10
DATE: 20/Sep/2010
REVISION No.: 02 - 12/Aug/2011
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 13

Kit PN 191-20095-601
NEW PN DESCRIPTION OLD PN QTYSUP QTYRQD DISP/NOTES
191-19356-003 Bushing
190-32805-003 or
190-32805-021 or
190-32805-023
01 01 3
191-19359-001 Washer - 01 01 2
191-19357-001 Spacer - 01 01 2
191-19358-401 Spacer - 01 01 2
MS51838-220 Pin MS51838-220 01 01 7
NAS6303-7 Bolt - 04 04 2
NAS1149C0363R Washer - 04 04 2
MS24665-134 Cotter pin MS24665-134 01 01 7
(b)
Kit PN 191-20093-601
NEW PN DESCRIPTION OLD PN QTYSUP QTYRQD DISP/NOTES
191-19356-005 Bushing
190-32805-003 or
190-32805-021 or
190-32805-023
01 01 3
191-19359-001 Washer - 01 01 2
191-19357-001 Spacer - 01 01 2
191-19358-401 Spacer - 01 01 2
MS51838-220 Pin MS51838-220 01 01 7
NAS6303-7 Bolt - 04 04 2
NAS1149C0363R Washer - 04 04 2
SERVICE BULLETIN
DATE: 20/Sep/2010
REVISION No.:02 - 12/Aug/2011
SB No.: 190-57-0036
PAGE: 11
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 14

Kit PN 191-20093-601
NEW PN DESCRIPTION OLD PN QTYSUP QTYRQD DISP/NOTES
MS24665-134 Cotter pin MS24665-134 01 01 7
(c)
Kit PN 191-20096-601
NEW PN DESCRIPTION OLD PN QTYSUP QTYRQD DISP/NOTES
191-19356-003 Bushing
190-32805-003 or
190-32805-021 or
190-32805-023
01 01 3
191-19359-001 Washer - 01 01 2
191-19357-001 Spacer - 01 01 2
191-19358-401 Spacer - 01 01 2
MS51838-220 Pin MS51838-220 01 01 7
NAS6303-7 Bolt - 04 04 2
NAS1149C0363R Washer - 04 04 2
MS24665-134 Cotter pin MS24665-134 01 01 7
(d)
SERVICE BULLETIN
SB No.: 190-57-0036
PAGE: 12
DATE: 20/Sep/2010
REVISION No.: 02 - 12/Aug/2011
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 15

Kit PN 191-20094-601
NEW PN DESCRIPTION OLD PN QTYSUP QTYRQD DISP/NOTES
191-19356-005 Bushing
190-32805-003 or
190-32805-021 or
190-32805-023
01 01 3
191-19359-001 Washer - 01 01 2
191-19357-001 Spacer - 01 01 2
191-19358-401 Spacer - 01 01 2
MS51838-220 Pin MS51838-220 01 01 7
NAS6303-7 Bolt - 04 04 2
NAS1149C0363R Washer - 04 04 2
MS24665-134 Cotter pin MS24665-134 01 01 7
(2) MATERIAL TO BE PROCURED
(a) Parts
The parts below, if required for the accomplishment of this bulletin, should be
ordered as spares from Embraer.
Applicable to all Top Kit
NEW PN DESCRIPTION OLD PN QTY DISP/Notes
191-19356-007 Bushing
190-32805-003 or
190-32805-021 or
190-32805-023
AR 6 [1]
1. Applicable to all GROUPS.
SERVICE BULLETIN
DATE: 20/Sep/2010
REVISION No.:02 - 12/Aug/2011
SB No.: 190-57-0036
PAGE: 13
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 16

Applicable to all Top Kit
NEW PN DESCRIPTION OLD PN QTY DISP/Notes
191-19356-005 Bushing
190-32805-003 or
190-32805-021 or
190-32805-023
AR 6 [1]
1. Applicable to GROUP 1 and GROUP 3.
(b) Consumable Materials
The material below or equivalent, required for the accomplishment of this
bulletin, should be procured from the operator’s inventories or from a local
supplier.
Applicable to all Top Kit
NEW PN DESCRIPTION OLD PN QTY DISP/Notes
RHODIASOLVE E-23 Solvent - AR 6/ [1]
PR1776M B-2 Sealant - AR 6/ [2]
COR-BAN 27L Corrosion-inhibiting
compound -A R 6 / [3]
AEROSHELL 33 Synthetic grease - AR 6/ [4]
ARDROX AV-15
Corrosion-inhibiting
compound
-A R 6 / [5]
70307-12
Lubricant Medium
Paste (BOELUB)
-A R 6/ [6]
1. Solvent for Manual Cleaning (MEP 13-073) RHODIASOLVE E-23
2. Class B2 Low-Density Polysulfide Sealant (AMS3281) PR1776M B-2
3. Corrosion Inhibiting Compound (MEP_09-075) COR-BAN 27L
4. Synthetic Grease (MIL-PRF-23827) AEROSHELL 33
5. Corrosion Inhibiting Compound (MEP_10-063) ARDROX AV-15
6. Class V-D(2) Lubricant Paste (-) 70307-12 (Spec BAC 5008)
SERVICE BULLETIN
SB No.: 190-57-0036
PAGE: 14
DATE: 20/Sep/2010
REVISION No.: 02 - 12/Aug/2011
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 17

DISPOSITION: 2 = Incorporate part bearing NEW PN
3 = Replace part bearing OLD PN with part bearing NEW
PN
6 = Apply as required
7 = Replace with part bearing same PN
QUANTITY: AR = As Required
D. MATERIAL NECESSARY FOR EACH SPARE
None.
E. REIDENTIFIED PARTS
None.
F. TOOLING - PRICE AND AVAILABILITY
(1) The tooling presented below, required for the accomplishment of this bulletin, will be
available from Embraer as one kit per operator at no charge.
DESCRIPTION PN SUPPLIER
Side Stay Bushing Tool SAC-2010-HELICOIDAL(E1456715) EMBRAER
(2) The tooling presented below, if required for the accomplishment of this bulletin,
should be procured directly from the manufacturer or should be ordered at loan basis
from Embraer.
DESCRIPTION PN SUPPLIER
Roller burnishing tool - 68 mm
in diameter - Commercially available [1]
1. When ordering from Embraer, specify Ecode 1456716.
SERVICE BULLETIN
DATE: 20/Sep/2010
REVISION No.:02 - 12/Aug/2011
SB No.: 190-57-0036
PAGE: 15
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 18

(3) The tooling presented below, if required for the accomplishment of this bulletin, will
be available from Embraer at loan basis.
DESCRIPTION PN SUPPLIER
Reamer 70301493 Embraer
(4) Whenever required, the necessary tooling presented in the AMM Tasks referred to in
this bulletin, should be procured from the operator’s inventories or ordered as
spares.
SERVICE BULLETIN
SB No.: 190-57-0036
PAGE: 16
DATE: 20/Sep/2010
REVISION No.: 02 - 12/Aug/2011
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 19

3. ACCOMPLISHMENT INSTRUCTIONS
NOTE: 1) For the purpose of this Service Bulletin, a Detailed Inspection (DI) is: “An
intensive examination of a specific item, installation or assembly to detect
damage, failure or irregularity. Available lighting is normally supplemented with
a direct source of good lighting at an intensity deemed appropriate. Inspection
aids such as mirrors, magnifying lenses, etc. may be necessary. Surface
cleaning and elaborate access procedures may be required.”
2) Obey all of the WARNINGS and CAUTIONS included in the referenced manuals
and procedures.
3) The Manuals and other documents are referred to by acronyms or using a
simplified form. Refer to section 1.J. REFERENCES for a more complete
definition.
4) This Service Bulletin effectivity is divided into 04 aircraft GROUPS according to
the relevant configuration and the SB itself is divided into 03 PARTS. The SB
PARTS are featured to allow their independent accomplishment.
The steps below outline the general accomplishment instructions.
The detailed sequence is included in the respective figure, when necessary.
A. Make sure that the aircraft is safe for maintenance. Refer to AMM TASK 20-00-00-910-
801-A/200 - Aircraft Maintenance Safety Procedures - Standard Procedures.
B. PART I - LH AND RH MAIN LANDING GEAR SIDE STAY BUSHING MIGRATION -
MEASUREMENT
(1) Do the procedure to make the aircraft safe for maintenance of the landing gear.
Refer to AMM TASK 32-00-00-860-801-A/200 - Landing Gear - Prepare for
Maintenance.
(2) Measure the bushing axial migration from the bushing housing on the left-hand and
right-hand Main Landing Gear (MLG) side stay. Refer to Figure 1.
– If the distance of the bushing migration is less than 5 mm, the inspection of this
Part I must be repetitive every 100 Flight Cycle(s) until the accomplishment of
Part II and/or PART III of this bulletin, no later than 1,200 Flight Cycle(s).
SERVICE BULLETIN
DATE: 20/Sep/2010
REVISION No.:02 - 12/Aug/2011
SB No.: 190-57-0036
PAGE: 17
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 20

– If the distance of the bushing migration is equal to or greater than 5 mm, it is
necessary to accomplish Part II and/or PART III of this bulletin immediately.
(3) Restore the aircraft to normal.
(4) Enter the accomplishment of PART I of this bulletin in the applicable documents.
C. PART II - LH MAIN LANDING GEAR SIDE STAY BUSHING - REPLACEMENT
(1) Do the procedure to make the aircraft safe for maintenance of the landing gear.
Refer to AMM TASK 32-00-00-860-801-A/200 - Landing Gear - Prepare for
Maintenance.
(2) Release the pressure from the No. 2 hydraulic system. Refer to AMM TASK
29-10-00-860-804-A/200 - Hydraulic System - Depressurization.
(3) Lift the aircraft on jacks. Refer to AMM TASK 07-10-01-500-801-A/200 - Complete
Aircraft Jacking - Maintenance Practices.
(4) Remove the two left-hand MLG downlock springs. Refer to AMM TASK 32-11-09-
000-801-A/400 - Main-Landing-Gear Downlock Spring - Removal.
(5) Remove the left-hand downlock sensor harness from the lever and side stay upper
assembly. Refer to AMM TASK 32-11-05-000-801-A/400 - Main-Landing-Gear Side
Stay - Removal.
(6) Disconnect the union nuts of the left-hand hydraulic hoses from the unions. Refer to
AMM TASK 32-11-05-000-801-A/400 - Main-Landing-Gear Side Stay - Removal.
(7) Remove the left-hand side stay support assembly from the trunnion. Refer to Figure
2.
(8) Replace the bushing of the left-hand main landing gear side stay. Refer to Figure 3.
(9) Reinstall the left-hand side-stay support assembly to the trunnion. Refer to Figure 4.
(10) Reconnect the left-hand hydraulic hoses on the unions. Refer to AMM TASK
32-11-05-400-801-A/400 - Main-Landing-Gear Side Stay - Installation.
SERVICE BULLETIN
SB No.: 190-57-0036
PAGE: 18
DATE: 20/Sep/2010
REVISION No.: 02 - 12/Aug/2011
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 21

(11) Reinstall the left-hand downlock sensor harnesses to the locking stay. Refer to AMM
TASK 32-11-05-400-801-A/400 - Main-Landing-Gear Side Stay - Installation.
(12) Reinstall the left-hand MLG downlock springs. Refer to AMM TASK 32-11-09-400-
801-A/400 - Main-Landing-Gear Downlock Spring - Installation.
(13) Lubricate the left-hand upper side stay attachment point on the aircraft structure.
Refer to AMM TASK 32-00-03-600-801-A/300 - Main-Landing-Gear Mechanical
System - Lubrication.
(14) Restore the aircraft to normal.
(15) Enter the accomplishment of PART II of this bulletin in the applicable documents.
D. PART III - RH MAIN LANDING GEAR SIDE STAY BUSHING - REPLACEMENT
(1) Do the procedure to make the aircraft safe for maintenance of the landing gear.
Refer to AMM TASK 32-00-00-860-801-A/200 - Landing Gear - Prepare for
Maintenance.
(2) Release the pressure from the No. 2 hydraulic system. Refer to AMM TASK
29-10-00-860-804-A/200 - Hydraulic System - Depressurization.
(3) Lift the aircraft on jacks. Refer to AMM TASK 07-10-01-500-801-A/200 - Complete
Aircraft Jacking - Maintenance Practices.
(4) Remove the two right-hand MLG downlock springs. Refer to AMM TASK 32-11-09-
000-801-A/400 - Main-Landing-Gear Downlock Spring - Removal.
(5) Remove the right-hand downlock sensor harness from the lever and side stay upper
assembly. Refer to AMM TASK 32-11-05-000-801-A/400 - Main-Landing-Gear Side
Stay - Removal.
(6) Disconnect the union nuts of the right-hand hydraulic hoses from the unions. Refer
to AMM TASK 32-11-05-000-801-A/400 - Main-Landing-Gear Side Stay - Removal.
(7) Remove the right-hand side-stay support assembly from the trunnion. Refer to
Figure 2.
SERVICE BULLETIN
DATE: 20/Sep/2010
REVISION No.:02 - 12/Aug/2011
SB No.: 190-57-0036
PAGE: 19
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 22

(8) Replace the bushing of the right-hand main landing gear side stay. Refer to Figure
3.
(9) Reinstall the right-hand side stay support assembly to the trunnion. Refer to Figure
4.
(10) Reconnect the right-hand hydraulic hoses on the unions. Refer to AMM TASK
32-11-05-400-801-A/400 - Main-Landing-Gear Side Stay - Installation.
(11) Reinstall the right-hand downlock sensor harnesses to the locking stay. Refer to
AMM TASK 32-11-05-400-801-A/400 - Main-Landing-Gear Side Stay - Installation.
(12) Reinstall the right-hand MLG downlock springs. Refer to AMM TASK 32-11-09-400-
801-A/400 - Main-Landing-Gear Downlock Spring - Installation.
(13) Lubricate the right-hand upper side stay attachment point on the aircraft structure.
Refer to AMM TASK 32-00-03-600-801-A/300 - Main-Landing-Gear Mechanical
System - Lubrication.
(14) Restore the aircraft to normal.
(15) Enter the accomplishment of PART III of this bulletin in the applicable documents.
NOTE: 1) Please inform us by e-mail fleet.reliability@embraer.com.br of the aircraft
manufacturer serial number and the SB incorporation date, specifying the SB
Part(s) incorporated or whether the whole SB has been incorporated. This will
enable Embraer to consider your aircraft configuration when providing future
modifications.
2) To formally inform that the SB has been incorporated fleet-wide or that the SB
will not be incorporated, so that Embraer can update the affected technical
publications, use the “Service Bulletin Full-Fleet Incorporation Report” form,
which is available on the Flyembraer portal (http://www.flyembraer.com).
3) Use the attached “Service Bulletin Evaluation” form to send us your comments
regarding this SB. Your feedback will be much appreciated as an aid for us to
improve the quality of the SBs.
SERVICE BULLETIN
SB No.: 190-57-0036
PAGE: 20
DATE: 20/Sep/2010
REVISION No.: 02 - 12/Aug/2011
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 23

1. Use a vernier caliper to measure the distance between the bushing housing limit edge
and the bushing edge.
SERVICE BULLETIN
DATE: 20/Sep/2010
REVISION No.:02 - 12/Aug/2011
SB No.: 190-57-0036
PAGE: 21
FIGURE 1 - MAIN LANDING GEAR SIDE STAY BUSHING MIGRATION - INSPECTION
(SHEET 01 OF 02)
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 24

ZONE
740ZONE730
A
BA A
B
DIMENSION
(MEASURE)
BUSHING
(REF.)
BUSHING HOUSING
(REF.)
EM170SB570894A.DGN
1
SERVICE BULLETIN
SB No.: 190-57-0036
PAGE: 22
DATE: 20/Sep/2010
REVISION No.: 02 - 12/Aug/2011
FIGURE 1 - MAIN LANDING GEAR SIDE STAY BUSHING MIGRATION - INSPECTION
(SHEET 02 OF 02)
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 25

1. Disconnect the side stay upper assembly from the support assembly, following the steps
below:
(a) Remove and discard cotter pin PN MS24665-134. Then remove nut PN
MS17825-5, flat washer PN NAS1149F0563P and washer PN 190-70157-001 from
the bolt PN NAS6605D54.
(b) Hold the MLG side stay. Then remove bolt PN NAS6605D54 and washer PN
190-70157-001 from the side-stay upper assembly.
(c) Remove sleeve PN 190-70156-001 or PN 190-70156-003.
(d) Disconnect the side stay upper assembly from the support assembly.
2. Remove support assembly PN 190-70165-403 or PN 190-70165-405 from the trunnion,
following the steps below:
(a) Remove retaining ring PN M27426-1147D, locking nut PN 2821-0059, and spring
ring PN 2000A0764K01 from the support assembly.
(b) Remove nut PN 2821-0058. Then remove locking ring PN 2821-0056 and pin PN
MS51838-220 from the support assembly.
(c) Remove support assembly PN 190-70165-403 or PN 190-70165-405 from the
trunnion. Retain the support assembly.
(d) Use a polyethylene spatula, lint-free wiper cloth and Solvent for Manual Cleaning
(MEP 13-073) RHODIASOLVE E-23 to remove the fillet sealant from the bushing.
SERVICE BULLETIN
DATE: 20/Sep/2010
REVISION No.:02 - 12/Aug/2011
SB No.: 190-57-0036
PAGE: 23
FIGURE 2 - SIDE STAY SUPPORT ASSEMBLY - REMOVAL
(SHEET 01 OF 04)
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 26

ZONE
740ZONE730
A A
A
TYPICAL
B
B
D
C
EM170SB570895A.DGN
SERVICE BULLETIN
SB No.: 190-57-0036
PAGE: 24
DATE: 20/Sep/2010
REVISION No.: 02 - 12/Aug/2011
FIGURE 2 - SIDE STAY SUPPORT ASSEMBLY - REMOVAL
(SHEET 02 OF 04)
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 27

C
SLEEVE
PN 190−70156−001 OR
PN 190−70156−003
(REMOVE AND RETAIN)
1
1
BOLT
PN NAS6605D54
(REMOVE AND RETAIN)
1
WASHER
PN 190−70157−001
(REMOVE AND RETAIN)
1
1
WASHER
PN 190−70157−001
(REMOVE AND RETAIN)
1
1
NUT
PN MS17825−5
(REMOVE AND RETAIN)
1
EM170SB570896A.DGN
FLAT WASHER
PN NAS1149F0563P
(REMOVE AND RETAIN)
COTTER PIN
PN MS24665−134
(REMOVE AND DISCARD)
SIDE−STAY UPPER ASSEMBLY
(DISCONNECT)
SERVICE BULLETIN
DATE: 20/Sep/2010
REVISION No.:02 - 12/Aug/2011
SB No.: 190-57-0036
PAGE: 25
FIGURE 2 - SIDE STAY SUPPORT ASSEMBLY - REMOVAL
(SHEET 03 OF 04)
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 28

2
SUPPORT ASSEMBLY
PN 190−70165−403 OR
PN 190−70165−405
(REMOVE AND RETAIN)
2 NUT
PN 2821−0058
(REMOVE AND RETAIN)
2
TRUNNION
(REF.)
2
LOCKING RING
PN 2821−0056
(REMOVE AND RETAIN)
2
SPRING RING
PN 2000A0764K01
(REMOVE AND RETAIN)
LOCKING NUT
PN 2821−0059
(REMOVE AND RETAIN)
2
2
RETAINING RING
PN M27426−1147D
(REMOVE AND RETAIN)
D
EM170SB570897A.DGN
PIN
PN MS51838−220
(REMOVE AND DISCARD)
BUSHING
(REF.)
1 REMOVE THE FILLET SEALANT FROM THE BUSHING.
1
SERVICE BULLETIN
SB No.: 190-57-0036
PAGE: 26
DATE: 20/Sep/2010
REVISION No.: 02 - 12/Aug/2011
FIGURE 2 - SIDE STAY SUPPORT ASSEMBLY - REMOVAL
(SHEET 04 OF 04)
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 29

1. Remove and discard bushing PN 190-32805-003 or PN 190-32805-021 or PN 190-
32805-023, following the steps below:
(a) Remove bushing using tool PN SAC-2010-HELICOIDAL as shown in pictures 1 and
2.
(b) Perform the bushing housing inspection according to Figure 6.
2. Install bushing PN 191-19356-003 or PN 191-19356-005 or PN 191-19356-007,
following the steps below:
WARNING : LIQUID NITROGEN IS DANGEROUS, OBEY MANUFACTURERS
INSTRUCTIONS.
(a) Assemble the bushing and tool as shown in picture 3 and put it in liquid nitrogen.
NOTE: The base of the tool (″L″) should be positioned on the structure to receive
the bushing and tool set.
(b) Let the bushing and tool set in liquid nitrogen for 20 minutes, as shown in picture
4. As a guide, the bushing soak will usually stop ″gassing off″ when the maximum
shrinkage has been obtained.
(c) Apply a thin layer of Corrosion Inhibiting Compound (MEP_09-075) COR-BAN
27L around the bushing housing. Refer to SRM PART II 51-21-01/1 - FAYING
SURFACE SEALING.
(d) Remove the bushing and tool set from the liquid nitrogen and install the bushing
into the housing immediately using tool PN SAC-2010-HELICOIDAL as shown in
pictures 5 and 6.
1 Make sure that the bushing and tool set are positioned on the base of the tool
(″L″) in the correct position, with the tool pins facing up, as shown in picture 3.
2 Make sure the flange of the bushing is in contact with the trunnion using tool
PN SAC-2010-HELICOIDAL, as shown in picture 7.
(e) Measure the internal diameter of the bushing, as shown in picture 8. The bushing
SERVICE BULLETIN
DATE: 20/Sep/2010
REVISION No.:02 - 12/Aug/2011
SB No.: 190-57-0036
PAGE: 27
FIGURE 3 - MAIN LANDING GEAR SIDE STAY BUSHING - REPLACEMENT
(SHEET 01 OF 05)
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 30

must have an internal diameter between 68.04 and 68.06 mm.
1 If the measure value is less than the allowed limit, burnish inside the installed
bushing using an appropriate roller burnishing tool.
(f) Apply Class B2 Low-Density Polysulfide Sealant (AMS3281) PR1776M B-2 to the
bushing (both lateral interfaces between the flanged bushing and the fitting), as
shown in pictures 9 and 10. Refer to SRM PART II 51-21-02/1 - FILLET SEALING.
SERVICE BULLETIN
SB No.: 190-57-0036
PAGE: 28
DATE: 20/Sep/2010
REVISION No.: 02 - 12/Aug/2011
FIGURE 3 - MAIN LANDING GEAR SIDE STAY BUSHING - REPLACEMENT
(SHEET 02 OF 05)
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 31

2
1
EM170SB570891A.DGN
TOOL
PN SAC−2010−HELICOIDAL
(REF.)
BUSHING
(REF.)
11
TOOL
PN SAC−2010−HELICOIDAL
(REF.)
1 REMOVE BUSHING USING TOOL PN SAC−2010−HELICOIDAL.
SERVICE BULLETIN
DATE: 20/Sep/2010
REVISION No.:02 - 12/Aug/2011
SB No.: 190-57-0036
PAGE: 29
FIGURE 3 - MAIN LANDING GEAR SIDE STAY BUSHING - REPLACEMENT
(SHEET 03 OF 05)
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 32

EM170SB570892A.DGN
TOOL
PN SAC−2010−HELICOIDAL
(REF.) BUSHING(REF.)
2
LIQUID
NITROGEN
2
BUSHING
(REF.)
TOOL
PN SAC−2010−HELICOIDAL
(REF.)
BUSHING
(REF.)
2
2
3
LET THE BUSHING IN LIQUID NITROGEN.
2
4
5
HOUSING BUSHING
(REF.)
3
UP
4
5 6
6
APPLY COR−BAN 27L
REMOVE THE BUSHING FROM LIQUID NITROGEN.
INSTALL THE BUSHING IMMEDIATELY.
6
3
5
4
TOOL
PN SAC−2010−HELICOIDAL
(REF.)
THE BASE "L" SHOULD BE POSITIONED ON THE STRUCTURE.
BUSHING
(REF.)
TOOL
PN SAC−2010−HELICOIDAL
(REF.)
SERVICE BULLETIN
SB No.: 190-57-0036
PAGE: 30
DATE: 20/Sep/2010
REVISION No.: 02 - 12/Aug/2011
FIGURE 3 - MAIN LANDING GEAR SIDE STAY BUSHING - REPLACEMENT
(SHEET 04 OF 05)
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 33

EM170SB570893A.DGN
MAKE SURE THAT THE FLANGE IS IN CONTACT WITH THE TRUNNION.
MEASURE THE INTERNAL DIAMETER OF THE BUSHING.
IF NECESSARY, USE ROLLER BURNISHER TOOL.
BUSHING
(REF.)
2
BURNISHER
(REF.)
TRUNNION
(REF.)
TOOL
PN SAC−2010−HELICOIDAL
(REF.)
BUSHING
(REF.)
2
SEALANT
(REF.)
APPLY FILLET SEALANT PN PR1776M B−2
A
SEALANT
(REF.)
A
7
7
8
9
10
10
10
8
9
7
8
9
10
SERVICE BULLETIN
DATE: 20/Sep/2010
REVISION No.:02 - 12/Aug/2011
SB No.: 190-57-0036
PAGE: 31
FIGURE 3 - MAIN LANDING GEAR SIDE STAY BUSHING - REPLACEMENT
(SHEET 05 OF 05)
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 34

1. Reinstall side stay support assembly PN 190-70165-403 or PN 190-70165-405 to the
trunnion. Refer to D and following the steps below:
(a) Apply a thin layer of Corrosion Inhibiting Compound (MEP_09-075) COR-BAN
27L to washer PN 191-19359-001. Refer to SRM PART II 51-21-01/1 - FAYING
SURFACE SEALING.
(b) Position washer PN 191-19359-001 and the support assembly into the trunnion.
(c) Install spacer PN 191-19357-001 and PN 191-19358-401 according to Figure
Figure 5.
(d) Apply a thin layer of Corrosion Inhibiting Compound (MEP_09-075) COR-BAN
27L to new pin PN MS51838-220, locking ring PN 2821-0056, and nut PN
2821-0058. Refer to SRM PART II 51-21-01/1 - FAYING SURFACE SEALING.
(e) Apply a thin layer of Synthetic Grease (MIL-PRF-23827) AEROSHELL 33 to
locking ring PN 2821-0056.
(f) Put new pin PN MS51838-220 on the support assembly. Then install the locking
ring PN 2821-0056.
(g) Install nut PN 2821-0058 to the support assembly.
(h) Use a torque wrench to apply the initial torque to the nut of 135 - 165 N.m (1195 -
1460 lb.in).
(i) Loosen the nut and use a torque wrench to apply the final torque to the nut of 18
- 22 N.m (160 - 195 lb.in).
NOTE: Loosen the nut to adjacent locking hole position (max. 8º).
(j) Install spring ring PN 2000A0764K01 on the nut, then put locking nut PN 2821-0059
and retaining ring PN M27426-1147D to lock the nut.
2. Connect the side stay upper assembly to the support assembly. Refer to C and following
the steps below:
SERVICE BULLETIN
SB No.: 190-57-0036
PAGE: 32
DATE: 20/Sep/2010
REVISION No.: 02 - 12/Aug/2011
FIGURE 4 - SIDE STAY SUPPORT ASSEMBLY - INSTALLATION
(SHEET 01 OF 06)
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 35

(a) Apply a thin layer of Corrosion Inhibiting Compound (MEP_09-075) COR-BAN
27L to bolt PN NAS6605D54, sleeve PN 190-70156-001 or PN 190-70156-003,
washer PN 190-70157-001, and mating faces of the side stay upper assembly with
the support assembly. Refer to SRM PART II 51-21-01/1 - FAYING SURFACE
SEALING.
(b) Connect the side stay upper assembly on the support assembly. Then install sleeve
PN 190-70156-001 or PN 190-70156-003, washer PN 190-70157-001, and bolt PN
NAS6605D54 through them.
(c) Apply a thin layer of Corrosion Inhibiting Compound (MEP_09-075) COR-BAN
27L to washer PN 190-70157-001, flat washer PN NAS1149F0563P, and nut PN
MS17825-5. Refer to SRM PART II 51-21-01/1 - FAYING SURFACE SEALING.
(d) Install the washer PN 190-70157-001, flat washer PN NAS1149F0563P, and nut PN
MS17825-5 on the bolt PN NAS6605D54.
NOTE: Make sure the threads of the nut and bolt fully engage. The base of the nut
must not touch the surface of the side-stay upper assembly.
(e) Turn the nut and measure the locking torque using a torque wrench.
(f) Make sure that the locking torque is between 0.75 - 6.75 N.m (6.5 - 60.0 lb.in).
NOTE: If you find that the nut is not in the correct range, replace it and do these
steps again.
(g) Use a torque wrench to add the locking torque value measured to the standard
torque of 11 - 16 N.m (100 - 140 lb.in) to get the final torque.
(h) Apply a final torque to the nut with a torque wrench as follows:
1 Tighten the nut to the bolt to remove clearance.
2 Torque the nut with the minimum final torque value and continue to torque as
necessary to align its slot with the cotter pin hole in the bolt.
NOTE: Be careful so as not to apply more than the maximum final torque
value.
SERVICE BULLETIN
DATE: 20/Sep/2010
REVISION No.:02 - 12/Aug/2011
SB No.: 190-57-0036
PAGE: 33
FIGURE 4 - SIDE STAY SUPPORT ASSEMBLY - INSTALLATION
(SHEET 02 OF 06)
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 36

(i) Safety the nut with new cotter pin PN MS24665-134.
(j) Apply Class B2 Low-Density Polysulfide Sealant (AMS3281) PR1776M B-2 to the
fasteners head. Refer to SRM PART II 51-21-05/1 - FASTENER SEALING.
(k) Apply Corrosion Inhibiting Compound (MEP_10-063) ARDROX AV-15 over the
whole area of the side-stay support assembly.
SERVICE BULLETIN
SB No.: 190-57-0036
PAGE: 34
DATE: 20/Sep/2010
REVISION No.: 02 - 12/Aug/2011
FIGURE 4 - SIDE STAY SUPPORT ASSEMBLY - INSTALLATION
(SHEET 03 OF 06)
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 37

ZONE
740ZONE730
A A
A
TYPICAL
B
B
D
C
EM170SB570898A.DGN
SERVICE BULLETIN
DATE: 20/Sep/2010
REVISION No.:02 - 12/Aug/2011
SB No.: 190-57-0036
PAGE: 35
FIGURE 4 - SIDE STAY SUPPORT ASSEMBLY - INSTALLATION
(SHEET 04 OF 06)
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 38

C
2
2
2
2
2
2
2
2
BOLT
PN NAS6605D54
(INSTALL)SLEEVE
PN 190−70156−001 OR
PN 190−70156−003
(INSTALL)
COTTER PIN
PN MS24665−134
(INSTALL)
NUT
PN MS17825−5
(INSTALL)
WASHER
PN 190−70157−001
(INSTALL)
WASHER
PN 190−70157−001
(INSTALL)
EM170SB570899A.DGN
1
13
1
1
1
123
1
2
3
APPLY COR−BAN 27L
APPLY SEALANT PN PR1776M B−2 TO THE FASTENERS HEAD.
SIDE−STAY UPPER ASSEMBLY
(CONNECT)
FLAT WASHER
PN NAS1149F0563P
(INSTALL)
TORQUE: 11 − 16 N.m (100 − 140 lb.in) PLUS LOCKING TORQUE
SERVICE BULLETIN
SB No.: 190-57-0036
PAGE: 36
DATE: 20/Sep/2010
REVISION No.: 02 - 12/Aug/2011
FIGURE 4 - SIDE STAY SUPPORT ASSEMBLY - INSTALLATION
(SHEET 05 OF 06)
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 39

1
1
1
TRUNNION
(REF.)
1
1
1
1
D
SUPPORT ASSEMBLY
PN 190−70165−403 OR
PN 190−70165−405
(INSTALL)
PIN
PN MS51838−220
(INSTALL)
LOCKING RING
PN 2821−0056
(INSTALL)
NUT
PN 2821−0058
(INSTALL)
SPRING RING
PN 2000A0764K01
(INSTALL)
LOCKING NUT
PN 2821−0059
(INSTALL)
RETAINING RING
PN M27426−1147D
(INSTALL)
1
1
SPACER
PN 191−19357−001
(INSTALL, SEE FIG.5)
APPLY GREASE AEROSHEEL 33
5
APPLY COR−BAN 27L4
54
4
47
1 4
WASHER
PN 191−19359−001
(INSTALL)
SPACER
PN 191−19358−401
(INSTALL, SEE FIG.5)
APPLY ARDROX AV−15
6
7
8
INITIAL TORQUE: 135−165 N.m (1195−1460 lb.in)
FINAL TORQUE: 18−22 N.m (160−195 lb.in)
8
6
EM170SB570900A.DGN
SERVICE BULLETIN
DATE: 20/Sep/2010
REVISION No.:02 - 12/Aug/2011
SB No.: 190-57-0036
PAGE: 37
FIGURE 4 - SIDE STAY SUPPORT ASSEMBLY - INSTALLATION
(SHEET 06 OF 06)
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 40

1. Install spacer PN 191-19358-401 or PN 191-19357-001, following the steps below:
(a) Position spacer PN 191-19358-401 over the side stay support assembly, as shown
in picture 2.
(b) Move up spacer PN 191-19358-40 1(±3 0 degrees) and position spacer PN
191-19357-001, as shown in picture 3.
(c) Position bolt PN NAS6303-7 (2 positions) and washer PN NAS1149C0363R to the
upper part of the spacers, as shown in picture 4.
(d) Move spacer PN 191-19358-401 and PN 191-19357-001 in order to position bolt
PN NAS6303-7 (2 positions) and washer PN NAS1149C0363R to the lower part of
the spacers, as shown in picture 5.
(e) Move the spacers to the final position, as shown in picture 6.
(f) Apply the final torque to the bolt, as shown in picture 6 and following the steps
below:
1 Turn the bolt (4 positions) and measure the drag torque with a torque wrench.
2 Make sure that the drag torque value is 0.23 to 2.03 N.m (2 to 18 lb.in).
3 Add the drag torque value measured to the standard torque of 4.52 to 5.65 N.m
(40 to 50 lb.in) to get the final torque.
4 Apply the final torque to the screws with a torque wrench.
NOTE: Due to some tolerances in parts, the rotation of the spacer assembly
may occur.
SERVICE BULLETIN
SB No.: 190-57-0036
PAGE: 38
DATE: 20/Sep/2010
REVISION No.: 02 - 12/Aug/2011
FIGURE 5 - SIDE STAY SUPPORT SPACERS - INSTALLATION
(SHEET 01 OF 03)
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 41

1
2
3
SIDE STAY
SUPPORT ASSY
(REF.)
SPACER
PN 191−19358−401
(POSITION)
EM170SB570901A.DGN
1
SPACER
PN 191−19357−001
(POSITION)
SPACER
PN 191−19358−401
(MOVE)
1
1
SERVICE BULLETIN
DATE: 20/Sep/2010
REVISION No.:02 - 12/Aug/2011
SB No.: 190-57-0036
PAGE: 39
FIGURE 5 - SIDE STAY SUPPORT SPACERS - INSTALLATION
(SHEET 02 OF 03)
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 42

1
1
4
5
6
1
1
1
EM170SB570902A.DGN
BOLT
PN NAS6303−7
WASHER
PN NAS1149C0363R
(02 POSITIONS)
(POSITION)
BOLT
PN NAS6303−7
WASHER
PN NAS1149C0363R
(02 POSITIONS)
(POSITION)
BOLT
PN NAS6303−7
(04 POSITIONS)
(APPLY TORQUE)
TORQUE: 4.52 − 5.65 N.m (40 − 50 lb.in) PLUS DRAG TORQUE: 0.23 − 2.03 N.m (2 − 18 lb.in)
SERVICE BULLETIN
SB No.: 190-57-0036
PAGE: 40
DATE: 20/Sep/2010
REVISION No.: 02 - 12/Aug/2011
FIGURE 5 - SIDE STAY SUPPORT SPACERS - INSTALLATION
(SHEET 03 OF 03)
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 43

1. Perform a detailed inspection on the bushing housing surface for signs of scratches,
marks or gouges.
(a) If any discrepancy is found, blend out the damaged area of the bushing housing
using an aluminum-oxyde grain sandpaper No.300/600 and/or a scotch brite pad.
2. Measure the internal diameter of the bushing housing at three different points and three
different depths using a bore micrometer. If applicable, measure the internal diameter of
the bushing housing at the blended out area.
(a) Applicable to GROUP 1 and GROUP 3
1 For bushing PN 191-19356-003 installation, the bushing housing must not
have an internal diameter greater than 82.035mm.
2 For bushing PN 191-19356-005 installation, the bushing housing must have an
internal diameter greater than 82.035 mm, but no greater than 82.075 mm.
NOTE: Bushing PN 191-19356-005, should be ordered as spares from
Embraer.
(b) Applicable to GROUP 2 and GROUP 4
1 For bushing PN 191-19356-005 installation, the bushing housing must not
have an internal diameter greater than 82.075mm.
3. If the damaged area of the bushing housing does not clean-up after the blend out and/or
if the internal diameter of the bushing housing is out of the limits according to step 2.
Figure 6, enlarge it using reamer PN 70301493 with Class V-D(2) Lubricant Paste (-)
70307-12 for bushing PN 191-19356-007 installation.
NOTE: Bushing PN 191-19356-007, should be ordered as spares from Embraer.
SERVICE BULLETIN
DATE: 20/Sep/2010
REVISION No.:02 - 12/Aug/2011
SB No.: 190-57-0036
PAGE: 41
FIGURE 6 - MAIN LANDING GEAR SIDE STAY BUSHING HOUSING - INSPECTION
(SHEET 01 OF 02)
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 44

1 1
3
1
3
BUSHING
HOUSING
(INSPECT)
BUSHING HOUSING
(ENLARGE, IF NECESSARY)
BORE MICROMETER
(REF.)
2
BUSHING
HOUSING
(MEASURE THE 
INTERNAL DIAMETER)
2
USE LUBRICANT PASTE (BOELUB) PN 70307−12
EM170SB570958A.DGN
REAMER
PN 70301493
(REF.)
RATCHET WRENCH
(REF.)
2
1 IF ANY DISCREPANCY IS FOUND, BLEND OUT THE DAMAGED AREA
2
SERVICE BULLETIN
SB No.: 190-57-0036
PAGE: 42
DATE: 20/Sep/2010
REVISION No.: 02 - 12/Aug/2011
FIGURE 6 - MAIN LANDING GEAR SIDE STAY BUSHING HOUSING - INSPECTION
(SHEET 02 OF 02)
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 45

4. APPENDIX 1
FLOWCHART - SB190-57-0036
SERVICE BULLETIN
DATE: 20/Sep/2010
REVISION No.:02 - 12/Aug/2011
SB No.: 190-57-0036
PAGE: 43
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 46

Could the 
bushing be
lubricated?
Schedule next inspection
within the next 100 FC.
1,200 FC
since first
 inspection?
 START SB
190−57−0036
END
inspect and
measure
bushing
migration.
Immediately
replace
bushing.
START
NO
YES
Migration
_ > 5.0 mm?
YES
NO
NO
YES
EM170SB571020A.DGN
Schedule next
regreasing
stop (600 FC).
SERVICE BULLETIN
SB No.: 190-57-0036
PAGE: 44
DATE: 20/Sep/2010
REVISION No.: 02 - 12/Aug/2011
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 47

SERVICE BULLETIN EVALUATION
THE PURPOSE OF THIS FORM IS TO COLLECT DATA THAT WILL BE USED TO IMPROVE THE QUALITY OF OUR
SERVICE BULLETINS AND UPDATE THE TECHNICAL PUBLICATIONS. PLEASE FILL IN FORM AND RETURN IT TO:
EMBRAER - EMPRESA BRASILEIRA DE AERONÁUTICA S.A.
EFTC - SERVICE BULLETIN ENGINEERING
AV. BRIGADEIRO FARIA LIMA, 2170
SÃO JOSÉ DOS CAMPOS - SP - 12227-901
BRASIL
Fax: + 55 12 3927-6600 (ext. 1624)
e-mail: fleet.reliability@embraer.com.br
S.B. Title: S.B.: (Number / Rev.)
Operator:
SB Implementation Report
Aircraft Serial Number or Registration Number: Incorporation Date:
Aircraft Flight Hours: Aircraft Landings:
POST-ACCOMPLISHMENT EVALUATION:(Check applicable squares below)
ESTIMATED MANPOWER: [ ] OK [ ] NOT OK (Explain Below)
MATERIAL & KITS: [ ] OK [ ] NOT OK (Explain Below)
ACCOMPLISHMENT INSTRUCTIONS: [ ] OK [ ] NOT OK (Explain Below)
FIGURES: [ ] OK [ ] NOT OK (Explain Below)
SB GENERAL EVALUATION: [ ] OK [ ] NOT OK (Explain Below)
COMMENTS: (Bulletin quality/ Difficulties found at the time of incorporation/ Suggested improvements/ Other)
Organization: Fax: Phone:
E-mail:
Address: Prepared by:(Name/Title) Date:
Copyright © 2011 by Embraer S.A. All rights reserved.

### Page 48

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