# Embraer Service Bulletin 170-32-A094: Revision 1

- Rights: © Embraer S.A. Filed by the FAA in regulations.gov docket FAA-2024-1688, the docket of AD 2024-12-08. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Embraer Service Bulletin 170-32-A094](https://openairdocs.org/service-documents/embraer/170-32a094.md)
- Title as filed: SB170-32-A094_R01
- Pages: 20
- PDF: https://openairdocs.org/files/sha256/fe/b9/feb96bc69015bfc36226b956ec771a10dd531548af2c9f92b51da59412c12182
- Page: https://openairdocs.org/service-documents/embraer/170-32a094/file/feb96bc69015

## Text

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1. DESCRIPTION 
  This sheet informs about Revision 01 to the Service Bulletin SB170-32-A094.
  This is a complete reissue of this Service Bulletin.
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: May 18, 2024.
  Revision 01: May 28, 2024.
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 shown in the left margin of each page to show where significant changes were made. Text
displacement and text format changes are not indicated.
TOPIC/PAGE DESCRIPTION OF REVISION
1. PLANNING INFORMATION
1.A. SB EFFECTIVITY/01 Updated the effectivity.
1.C. REASON/02 Updated history and added reason for Revision01.
1.E. COMPLIANCE/03 and 04 Updated compliance information and included theRequired for Compliance (RC) note.
1.G. ESTIMATED MANPOWER/04 and 05. Included estimated manpower.
1.I. REFERENCES/05 Added new information.
2. MATERIAL INFORMATION
2.A. MATERIAL - PRICE AND AVAILABILITY/06
and 07
Updated the quantity of the components and
included alternative sealants.
3. ACCOMPLISHMENT INSTRUCTIONS
3. ACCOMPLISHMENT INSTRUCTIONS/08 thru
13
Updated instructions to include the Required for
Compliance (RC) tag and related notes, included
alternative sealants and updated text to improve
the procedure.
Figure 1 Revised a typo.
Figure 2 Included alternative sealants.
Figure 3 Included alternative sealants.
TRANSMITTAL LETTER
Date:  May 18, 2024
Revision No.:  01 - May 28, 2024 ALERT
SB170-32-A094
Page 1 of  1
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LANDING GEAR - INSPECTION/REPLACEMENT OF THE MAIN LANDING GEAR (MLG) LOCKING-STAY
BRACKET ASSEMBLY NUT
In connection with the use of this document, Embraer does not provide any express or implied warranties and expressly disclaims any
warranty of merchantability or fitness for a particular purpose.
This document contains trade secrets, confidential, proprietary information of Embraer and technical data subject to U.S. Export
Administration Regulation ("EAR") and other countries export control laws and regulations. Diversion contrary to the EAR and other laws
and regulations is strictly forbidden. The above restrictions may apply to data on all pages of this document.
1. PLANNING INFORMATION 
A. SB EFFECTIVITY 
  Aircraft affected:
  (1) GROUP 1
MODEL SN
Embraer 170( ) and 175( )
17000002, 17000004 thru 17000013, 17000015 thru
17000359, 17000361 thru 17000379, 17000381 thru
17000580, 17000582 thru 17000586, 17000588 thru
17000592, 17000594, 17000595, 17000597 thru 17000601,
17000603, 17000604, and 17000606 thru 17000768, POST-
MOD SB170-32-0089 and/or equipped with affected
components.
  (2) GROUP 2
MODEL SN
Embraer 170( ) and 175( ) 17000769 thru 17000945, and 17000947 thru 17000964,equipped with affected components.
  Affected component:
  MLG shock strut PNs 2801A0000-02/-03/-04/-05/-06 and 2802A0000-02/-03/-04/-05/-06, all serial
numbers restored through Liebherr CMM 32-11-01 (PN 49-CC0000505-00 - LIEBHERR) - MLG Shock
Strut (LH/RH) Rev 06 thru 15.
NOTE: This bulletin is not applicable for aircraft that did not have the MLG restored during an
overhaul maintenance and accomplished Liebherr CMM 32-11-01 (PN 49-CC0000505-00 -
LIEBHERR) - MLG Shock Strut (LH/RH) Rev 06 thru 15 and/or PRE-MOD SB170-32-0089.
  In-production effectivity:
The subject presented in this bulletin does not affect any in-production aircraft.
B. CONCURRENT REQUIREMENTS 
  None.
C. REASON 
  (1) HISTORY
  Embraer received a report that after the pilot gives the command to extend for landing, there was
no LH MLG Shock Strut downlocking indication to the pilot. After aircraft landing, it was found that
the LH MLG Locking Stay bracket became loose from the shock strut.
ALERT
SERVICE BULLETIN
Date:  May 18, 2024
Revision No.:  01 - May 28, 2024 ALERT
SB170-32-A094
Page 1 of  18
Copyright © by Embraer S.A. All rights reserved - See title page for details.
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It was identified that an incorrect nut can be installed in the MLG during the accomplishment of
SB170-32-0089 (original and revision 1 issues), or if the MLG was restored by an overhaul
maintenance and accomplished Liebherr CMM 32-11-01 (PN 49-CC0000505-00 - LIEBHERR) -
MLG Shock Strut (LH/RH) Rev 06 thru 15.
  (2) OBJECTIVE
  To inspect the LH and RH MLG Locking Stay bracket assembly and respective attachment
hardwares. Verify if the self-locking nuts installed on the lower screws of the brackets are the PN
MS14145-5 or MS17826-5.
  (3) EXPECTED BENEFITS
  To prevent the loss of the MLG locking stay bracket attachment hardwares and possible failure of
the MLG Downlocking Mechanism and respective position indication.
  (4) REVISION HISTORY
REVISION 01: This revision was issued to update the effectivity, the compliance information,
to improve the procedure, and to include the Required for Compliance (RC)
tag and related notes.
D. DESCRIPTION 
  This Bulletin is divided into 6 PARTS, as follows:
PART I LH MLG LOCKING-STAY BRACKET ASSEMBLY AND LOWER NUTINSPECTION
Applicable to: Refer to: 1.A. SB EFFECTIVITY
  The PART I of this bulletin consists of:
– The inspection of the attachment parts of LH MLG locking-stay bracket assembly to verify if they
are correctly installed. If not, do the PART V of the bulletin.
– The inspection of the LH MLG locking-stay bracket assembly lower nuts to check if the nuts PN
MS17826-5 are installed. If the nuts PN MS17826-5 are installed, do the PART III of the bulletin.
PART II RH MLG LOCKING-STAY BRACKET ASSEMBLY AND LOWER NUTINSPECTION
Applicable to: Refer to: 1.A. SB EFFECTIVITY
  The PART II of this bulletin consists of:
– The inspection of the attachment parts of RH MLG locking-stay bracket assembly to verify if they
are correctly installed. If not, do the PART VI of the bulletin.
– The inspection of the RH MLG locking-stay bracket assembly lower nuts to check if the nuts PN
MS17826-5 are installed. If the nuts PN MS17826-5 are installed, do the PART IV of the bulletin.
PART III LH AFFECTED MLG LOCKING-STAY BRACKET ASSEMBLY LOWERNUT REPLACEMENT
Applicable to: Refer to: 1.A. SB EFFECTIVITY
  The PART III of this bulletin consists of:
ALERT
SERVICE BULLETIN
SB170-32-A094
Page 2 of  18 ALERT
Date:  May 18, 2024
Revision No.:  01 - May 28, 2024
Copyright © by Embraer S.A. All rights reserved - See title page for details.
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– The removal of the lower nuts PN MS17826-5 from the LH MLG locking-stay bracket assembly
and install the nuts PN MS14145-5.
PART IV RH AFFECTED MLG LOCKING-STAY BRACKET ASSEMBLY LOWERNUT REPLACEMENT
Applicable to: Refer to: 1.A. SB EFFECTIVITY
  The PART IV of this bulletin consists of:
– The removal of the lower nuts PN MS17826-5 from the RH MLG locking-stay bracket assembly
and install the nuts PN MS14145-5.
PART V LH AFFECTED MLG LOCKING-STAY BRACKET ASSEMBLYREPLACEMENT
Applicable to: Refer to: 1.A. SB EFFECTIVITY
  The PART V of this bulletin consists of:
– The removal of the all attachment parts and bracket assembly from the LH MLG and install new
ones.
PART VI RH AFFECTED MLG LOCKING-STAY BRACKET ASSEMBLYREPLACEMENT
Applicable to: Refer to: 1.A. SB EFFECTIVITY
  The PART VI of this bulletin consists of:
– The removal of the all attachment parts and bracket assembly from the RH MLG and install new
ones.
E. COMPLIANCE 
1) SB CATEGORY
 
  Category 01: MANDATORY
 
2) SB ACCOMPLISHMENT
 
– APPLICABLE TO GROUP 1
 
  This bulletin must be accomplished within the next 50 Flight Cycle(s) from the original issue
date of this Alert Service Bulletin for aircraft equipped with MLG restored during an overhaul
maintenance and that accomplished Liebherr CMM 32-11-01 (PN 49-CC0000505-00 -
LIEBHERR) - MLG Shock Strut (LH/RH) Rev 06 thru 15, or that was modified according to
SB170-32-0089 original or revision 01 version instructions.
 
– APPLICABLE TO GROUP 2
 
  This bulletin must be accomplished within the next 50 Flight Cycle(s) from the revision 01
issue date of this Alert Service Bulletin for aircraft equipped with MLG restored by an
ALERT
SERVICE BULLETIN
Date:  May 18, 2024
Revision No.:  01 - May 28, 2024 ALERT
SB170-32-A094
Page 3 of  18
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overhaul maintenance, and that accomplished Liebherr CMM 32-11-01 (PN 49-
CC0000505-00 - LIEBHERR) - MLG Shock Strut (LH/RH) Rev 06 thru 15.
NOTE: The indication RC (Required for Compliance) is presented in the accomplishment instructions
and/or figures. If this Service Bulletin is mandated by an Airworthiness Directive (AD) that
refers to any step identified as RC, it must be done to comply with the AD. If a step is
indicated as "RC Exempt", then the RC requirement is removed from that step. Steps not
identified with RC are recommended and may be deviated from, done as a part of other
actions, or done with accepted methods different from those given in the Service Bulletin,
provided that any RC step can still be done and the aircraft can be put back to a serviceable
condition. An Alternative Method of Compliance (AMOC) is not necessary in case of
deviations of the steps that are not identified as RC. If the applicable AD does not make any
reference to the RC (Required for Compliance) and/or RC Exempt, then the RC and RC
Exempt concept is not valid for this Service Bulletin, and an AMOC is necessary in case of
any deviation from the Service Bulletin steps.
F. APPROVAL 
  The changes to the type design specified in this Service Bulletin have been approved by Agência
Nacional de Aviação Civil (ANAC).
G. ESTIMATED MANPOWER 
  This is an estimate of the manpower necessary to accomplish this Service Bulletin on a single aircraft.
  It is intended for direct labor only, performed by experienced personnel and does not include the time
to plan, prepare or inspect the work. Sealant, paint or adhesive curing times are not included either.
  It is assumed that all the tools, parts and other means are readily available when necessary.
  An adjustment to these values may be necessary to meet particular circumstances.
  (1) APPLICABLE TO PART I and II
– Access opening: None.
– Inspection: 0.5 man-hours.
– Modification: None.
– Access closure: None.
– Test: None.
  (2) APPLICABLE TO PART III and IV
– Access opening: None.
– Inspection: None.
– Modification: 0.5 man-hours.
– Access closure: None.
– Test: None.
NOTE: This estimates do not include the time necessary for MLG middle door removal/
installation. If it is necessary the MLG middle door removal/installation, the manpower
will be increased by 3.0 man-hours, approximately.
  (3) APPLICABLE TO PART V and VI
ALERT
SERVICE BULLETIN
SB170-32-A094
Page 4 of  18 ALERT
Date:  May 18, 2024
Revision No.:  01 - May 28, 2024
Copyright © by Embraer S.A. All rights reserved - See title page for details.
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– Access opening: None.
– Inspection: None.
– Modification: 1.0 man-hour.
– Access closure: None.
– Test: None.
NOTE: This estimates do not include the time necessary for MLG middle door removal/
installation. If it is necessary the MLG middle door removal/installation, the manpower
will be increased by 3.0 man-hours, approximately.
H. COMMUNICATIONS TO EMBRAER 
  EMBRAER requests that any results found during these inspections be informed to your local
EMBRAER representatives or offices.
I. REFERENCES 
AMM 170/( ) Aircraft Maintenance Manual PART II - 20-00-00 - STANDARDPRACTICES-AIRFRAME.
AMM 170/( ) Aircraft Maintenance Manual PART II - 32-00-00, 32-11-07, 32-12-04,32-31-05, and 32-33-00 - LANDING GEAR.
SB170-32-0089 LANDING GEAR - MLG LOCKING-STAY BRACKET ASSEMBLYREPLACEMENT.
SRM 170/( ) Structural Repair Manual Part II - 51-21-00 - STANDARD PRACTICES ANDSTRUCTURES.
CMM 32-11-01 - 49-
CC0000505-00 Vendor Component Maintenance Manual - MLG Shock Strut (LH/RH).
J. OTHER PUBLICATIONS AFFECTED 
  None.
ALERT
SERVICE BULLETIN
Date:  May 18, 2024
Revision No.:  01 - May 28, 2024 ALERT
SB170-32-A094
Page 5 of  18
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2. MATERIAL INFORMATION 
A. MATERIAL - PRICE AND AVAILABILITY 
  When applicable, the use of alternative or similar parts is allowed, once it is 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 mentioned in this bulletin
can be acquired from the operator's inventories or ordered as spares.
  When necessary, additional information is presented as Notes in the respective Table.
  (1) TOP KITS AND KITS
  None.
  (2) MATERIAL TO BE PROCURED
  (a) Parts
  The parts below should be ordered as indicated in the associated Note.
Applicable to PART III and IV
NEW PN DESCRIPTION OLD PN QTY DISP/Notes
MS14145-5 Nut Self Locking MS17826-5 04 3/[1]
MS24665-153 Cotter Pin MS24665-153 04 7/[1]
[1] This part should be procured from the operator’s inventories or from a local supplier.
Applicable to PART V and VI
NEW PN DESCRIPTION OLD PN QTY DISP/Notes
1840A0700-04 Bracket Assembly 1840A0700-03 or1840A0700-04 02 3/[1]
MS14145-4 Nut Self Locking MS14145-4 04 7/[1]
MS14145-5 Nut Self Locking MS17826-5 04 3/[1]
NAS1149C0463R Washer NAS1149C0463R 04 7/[1]
NAS1149C0532R Washer NAS1149C0532R 04 7/[1]
MS24665-153 Cotter Pin MS24665-153 08 7/[1]
NAS6605D10 Screw NAS6605D10 04 7/[1]
NAS6604D9 Screw NAS6604D9 04 7/[1]
[1] This part should be procured from the operator’s inventories or from local supplier.
  (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.
ALERT
SERVICE BULLETIN
SB170-32-A094
Page 6 of  18 ALERT
Date:  May 18, 2024
Revision No.:  01 - May 28, 2024
Copyright © by Embraer S.A. All rights reserved - See title page for details.
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Applicable to PART III, IV, V and VI
NEW PN DESCRIPTION OLD PN QTY DISP/Notes
MEK Methyl Ethyl Ketone - AR 6/[1]
PR1826B2ALO or
PR1826B2 or
PR1826B1/2 or
PR1826B1/4
Polythioether Sealant - AR 6/[2]
[1] Methyl Ethyl Ketone (ASTM-D-740) MEK
[2] Fuel Tank Sealant (AMS_3277) PR1826B2 654 SEMKIT
DISPOSITION: 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
B. TOOLING - PRICE AND AVAILABILITY 
  Whenever required, the necessary tooling presented in the AMM Tasks mentioned in this bulletin
should be procured from the operator’s inventories or ordered as spares.
ALERT
SERVICE BULLETIN
Date:  May 18, 2024
Revision No.:  01 - May 28, 2024 ALERT
SB170-32-A094
Page 7 of  18
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3. ACCOMPLISHMENT INSTRUCTIONS 
NOTE:
1) The definition of a General Visual Inspection (GVI) for this Service Bulletin is: “A visual
examination of an interior or exterior area, installation or assembly to detect obvious damage,
failure or irregularity. This level of inspection is made from within touching distance, unless
otherwise specified. A mirror may be necessary to enhance visual access to all exposed
surfaces in the inspection area. This level of inspection is made under normally available
lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may require
removal or opening of access panels or doors. Stands, ladders or platforms may be required
to gain proximity to the area being checked.”
2) The indication RC (Required for Compliance) is presented in the accomplishment instructions
and/or figures. If this Service Bulletin is mandated by an Airworthiness Directive (AD) that
refers to any step identified as RC, it must be done to comply with the AD. If a step is
indicated as "RC Exempt", then the RC requirement is removed from that step. Steps not
identified with RC are recommended and may be deviated from, done as a part of other
actions, or done with accepted methods different from those given in the Service Bulletin,
provided that any RC step can still be done and the aircraft can be put back to a serviceable
condition. An Alternative Method of Compliance (AMOC) is not necessary in case of
deviations of the steps that are not identified as RC. If the applicable AD does not make any
reference to the RC (Required for Compliance) and/or RC Exempt, then the RC and RC
Exempt concept is not valid for this Service Bulletin, and an AMOC is necessary in case of
any deviation from the Service Bulletin steps.
3) Obey all of the WARNINGS and CAUTIONS included in the referenced manuals and
procedures.
4) The Manuals and other documents are referred to by acronyms or using a simplified form.
Refer to section 1.I. REFERENCES for a more complete definition.
5) This Service Bulletin is divided into 06 PARTS. The SB PARTS division allows their
independent accomplishment.
6) This Service Bulletin effectivity is divided into 02 aircraft GROUPS and all the steps bellow are
applicable for both groups.
  The steps below outline the general accomplishment instructions.
  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. 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.
  C. PART I – LH MLG LOCKING-STAY BRACKET ASSEMBLY LOWER NUT INSPECTION
  (1) On the lower side of the bracket assembly, use a polyethylene spatula, lint-free wiper cloth and
MEK to remove the sealant from the screws PN NAS6605D10, washers PN NAS1149C0532R,
nuts PN MS17826-5 or PN MS14145-5, and cotter pins PN MS24665-153.
  (2) [RC] Do a General Visual Inspection (GVI) of the bracket assembly, screws, washers, nuts, and
cotter pins for looseness, missing parts, bents, cracks, and other types of damage.
  (a) If the screws PN NAS6605D10, washers PN NAS1149C0532R, nuts PN MS17826-5 or PN
MS14145-5, and cotter pins PN MS24665-153 are correctly installed on the bracket
assembly PN 1840A0700-03 or 04, go to Step 3.C.(3).
ALERT
SERVICE BULLETIN
SB170-32-A094
Page 8 of  18 ALERT
Date:  May 18, 2024
Revision No.:  01 - May 28, 2024
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### Page 11

(b) If the screws PN NAS6605D10, washers PN NAS1149C0532R, nuts PN MS17826-5 or PN
MS14145-5, and cotter pins PN MS24665-153 are not correctly installed on the bracket
assembly PN 1840A0700-03 or 04, do the PART V of this bulletin immediately after the
accomplishment of PART I.
  (3) [RC] Do a General Visual Inspection (GVI) to verify which nuts are installed. Refer to Figure 1.
  (a) If nuts PN MS17826-5 are installed, do the PART III of this bulletin immediately after the
accomplishment of PART I. Refer to Figure 1.
  (b) If nuts PN MS14145-5 are installed, do as follows:
  1 With a soft bristle brush, apply a continuous bead of the PR1826B2ALO or PR1826B2
or PR1826B1/2 or PR1826B1/4 on the head of the screws PN NAS6605D10, washers
PN NAS1149C0532R, nuts PN MS14145-5, and cotter pins PN MS24665-153 ( SRM
PART II 51-21-00 - SEALANTS, PROPERTIES AND ALTERNATIVES).
  D. PART II – RH MLG LOCKING-STAY BRACKET ASSEMBLY LOWER NUT INSPECTION
  (1) On the lower side of the bracket assembly, use a polyethylene spatula, lint-free wiper cloth and
MEK to remove the sealant from the screws PN NAS6605D10, washers PN NAS1149C0532R,
nuts PN MS17826-5 or PN MS14145-5, and cotter pins PN MS24665-153.
  (2) [RC] Do a General Visual Inspection (GVI) of the bracket assembly, screws, washers, nuts, and
cotter pins for looseness, missing parts, bents, cracks and other types of damage.
  (a) If the screws PN NAS6605D10, washers PN NAS1149C0532R, nuts PN MS17826-5 or PN
MS14145-5, and cotter pins PN MS24665-153 are correctly installed on the bracket PN
1840A0700-03 or 04, go to Step 3.D.(3).
  (b) If the screws PN NAS6605D10, washers PN NAS1149C0532R, nuts PN MS17826-5 or PN
MS14145-5, and cotter pins PN MS24665-153 are not correctly installed on the bracket PN
1840A0700-03 or 04, do the PART VI of this bulletin immediately after the accomplishment
of PART II.
  (3) [RC] Do a General Visual Inspection (GVI) to verify which nuts are installed. Refer to Figure 1.
  (a) If nuts PN MS17826-5 are installed, do the PART IV of this bulletin immediately after the
accomplishment of PART II. Refer to Figure 1.
  (b) If nuts PN MS14145-5 are installed, do as follows:
  1 With a soft bristle brush, apply a continuous bead of the PR1826B2ALO or PR1826B2
or PR1826B1/2 or PR1826B1/4 on the head of the screws PN NAS6605D10, washers
PN NAS1149C0532R, nuts PN MS14145-5, and cotter pins PN MS24665-153 ( SRM
PART II 51-21-00 - SEALANTS, PROPERTIES AND ALTERNATIVES).
  E. PART III – LH AFFECTED MLG LOCKING-STAY BRACKET ASSEMBLY LOWER NUT
REPLACEMENT
NOTE: You must not remove the two nuts at the same time. You must remove one nut at a time and
do the installation of the new nut before removing the second nut.
  (1) If necessary to get a better access, remove the MLG middle door (AMM TASK
32-12-04-000-801-A/400 - Main-Landing-Gear Middle Door - Removal).
  (2) Remove the cotter pin PN MS24665-153 from the first nut PN MS17826-5 and discard the cotter
pin PN MS24665-153. Refer to Figure 2.
  (3) [RC] Remove the first nut PN MS17826-5 from the screw PN NAS6605D10 and discard nut PN
MS17826-5. Refer to Figure 2.
ALERT
SERVICE BULLETIN
Date:  May 18, 2024
Revision No.:  01 - May 28, 2024 ALERT
SB170-32-A094
Page 9 of  18
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### Page 12

(4) [RC] Install the nut PN MS14145-5 on the screw PN NAS6605D10. Refer to Figure 2.
  (5) [RC] Use a torque wrench to torque the nut PN MS14145-5 to 22 - 25 N.m (195 - 220 lb.in). Refer
to Figure 2.
  (6) [RC] Torque the nut PN MS14145-5 with the minimum final torque value and continue to torque
as necessary to align its slot with the cotter pin PN MS24665-153 hole in the screw PN
NAS6605D10. Refer to Figure 2.
NOTE: Be careful not to apply more than the maximum final torque value.
  (7) Safety the nut PN MS14145-5 with a cotter pin PN MS24665-153. Refer to Figure 2.
  (8) Remove the cotter pin PN MS24665-153 from the second nut PN MS17826-5 and discard the
cotter pin PN MS24665-153. Refer to Figure 2.
  (9) [RC] Remove the second nut PN MS17826-5 from the screw PN NAS6605D10 and discard nut
PN MS17826-5. Refer to Figure 2.
  (10) [RC] Install the nut PN MS14145-5 on the screw PN NAS6605D10. Refer to Figure 2.
  (11) [RC] Use a torque wrench to torque the nut PN MS14145-5 to 22 - 25 N.m (195 - 220 lb.in). Refer
to Figure 2.
  (12) [RC] Torque the nut PN MS14145-5 with the minimum final torque value and continue to torque
as necessary to align its slot with the cotter pin PN MS24665-153 hole in the screw PN
NAS6605D10. Refer to Figure 2.
NOTE: Be careful not to apply more than the maximum final torque value.
  (13) Safety the nut PN MS14145-5 with a cotter pin PN MS24665-153. Refer to Figure 2.
  (14) With a soft bristle brush, apply a continuous bead of the PR1826B2ALO or PR1826B2 or
PR1826B1/2 or PR1826B1/4 on the head of the screws PN NAS6605D10, washers PN
NAS1149C0532R, nuts PN MS14145-5, and cotter pins PN MS24665-153 (SRM PART II
51-21-00 - SEALANTS, PROPERTIES AND ALTERNATIVES).
  (15) If removed, install the MLG middle door (AMM TASK 32-12-04-400-801-A/400  - Main-Landing-
Gear Middle Door - Installation).
  F. PART IV – RH AFFECTED MLG LOCKING-STAY BRACKET ASSEMBLY LOWER NUT
REPLACEMENT
NOTE: You must not remove the two nuts at the same time. You must remove one nut at a time and
do the installation of the new nut before removing the second nut.
  (1) If necessary to get a better access, remove the MLG middle door (AMM TASK
32-12-04-000-801-A/400 - Main-Landing-Gear Middle Door - Removal).
  (2) Remove the cotter pin PN MS24665-153 from the first nut PN MS17826-5 and discard the cotter
pin PN MS24665-153. Refer to Figure 2.
  (3) [RC] Remove the first nut PN MS17826-5 from the screw PN NAS6605D10 and discard nut PN
MS17826-5. Refer to Figure 2.
  (4) [RC] Install the nut PN MS14145-5 on the screw PN NAS6605D10. Refer to Figure 2.
  (5) [RC] Use a torque wrench to torque the nut PN MS14145-5 to 22 - 25 N.m (195 - 220 lb.in). Refer
to Figure 2.
ALERT
SERVICE BULLETIN
SB170-32-A094
Page 10 of  18 ALERT
Date:  May 18, 2024
Revision No.:  01 - May 28, 2024
Copyright © by Embraer S.A. All rights reserved - See title page for details.
User: kgreer - Printed By myTechCare - May 30/24 - 22:33:15

### Page 13

(6) [RC] Torque the nut PN MS14145-5 with the minimum final torque value and continue to torque
as necessary to align its slot with the cotter pin PN MS24665-153 hole in the screw PN
NAS6605D10. Refer to Figure 2.
NOTE: Be careful not to apply more than the maximum final torque value.
  (7) Safety the nut PN MS14145-5 with a cotter pin PN MS24665-153. Refer to Figure 2.
  (8) Remove the cotter pin PN MS24665-153 from the second nut PN MS17826-5 and discard the
cotter pin PN MS24665-153. Refer to Figure 2.
  (9) [RC] Remove the second nut PN MS17826-5 from the screw PN NAS6605D10 and discard nut
PN MS17826-5. Refer to Figure 2.
  (10) [RC] Install the nut PN MS14145-5 on the screw PN NAS6605D10. Refer to Figure 2.
  (11) [RC] Use a torque wrench to torque the nut PN MS14145-5 to 22 - 25 N.m (195 - 220 lb.in). Refer
to Figure 2.
  (12) [RC] Torque the nut PN MS14145-5 with the minimum final torque value and continue to torque
as necessary to align its slot with the cotter pin PN MS24665-153 hole in the screw PN
NAS6605D10. Refer to Figure 2.
NOTE: Be careful not to apply more than the maximum final torque value.
  (13) Safety the nut PN MS14145-5 with a cotter pin PN MS24665-153. Refer to Figure 2.
  (14) With a soft bristle brush, apply a continuous bead of the PR1826B2ALO or PR1826B2 or
PR1826B1/2 or PR1826B1/4 on the head of the screws PN NAS6605D10, washers PN
NAS1149C0532R, nuts PN MS14145-5, and cotter pins PN MS24665-153 (SRM PART II
51-21-00 - SEALANTS, PROPERTIES AND ALTERNATIVES).
  (15) If removed, install the MLG middle door (AMM TASK 32-12-04-400-801-A/400  - Main-Landing-
Gear Middle Door - Installation).
  G. PART V – LH AFFECTED MLG LOCKING-STAY BRACKET ASSEMBLY REPLACEMENT
  (1) Disconnect the locking stay from the shock strut. Refer to AMM TASK 32-11-07-000-801-A/400 -
Main-Landing-Gear Locking Stay - Removal. It is not necessary to fully remove the locking stay.
  (2) Disconnect the downlock release actuator from the shock strut. Refer to AMM TASK
32-31-05-000-801-A/400 - Main-Landing-Gear Downlock-Release Actuator - Removal. It is not
necessary to fully remove the downlock release actuator.
  (3) If necessary to get a better access, remove the MLG middle door (AMM TASK
32-12-04-000-801-A/400 - Main-Landing-Gear Middle Door - Removal).
  (4) [RC] Replace the bracket assembly PN 1840A0700-03 or -04 as follows (Figure 3):
  (a) On the upper side of the bracket assembly, use a polyethylene spatula, lint-free wiper cloth
and MEK to remove the sealant from the screws PN NAS6604D9, washers PN
NAS1149C0463R, nuts PN MS14145-4, and cotter pins PN MS24665-153.
  (b) Remove screws PN NAS6604D9, washers PN NAS1149C0463R, nuts PN MS14145-4, and
cotter pins PN MS24665-153 from the bracket assembly PN 1840A0700-03 or -04 and
discard all of them.
  (c) Remove the screws PN NAS6605D10, washers PN NAS1149C0532R, nuts PN
MS17826-5, and cotter pins PN MS24665-153 from the bracket assembly PN
1840A0700-03 or -04 and discard all of them.
ALERT
SERVICE BULLETIN
Date:  May 18, 2024
Revision No.:  01 - May 28, 2024 ALERT
SB170-32-A094
Page 11 of  18
Copyright © by Embraer S.A. All rights reserved - See title page for details.
User: kgreer - Printed By myTechCare - May 30/24 - 22:33:15

### Page 14

(d) Remove the bracket assembly PN 1840A0700-03 or -04 from the MLG shock strut and
discard it.
  (e) Put a new bracket assembly PN 1840A0700-04 on the installation position on the MLG
shock strut.
  (f) On the lower side, install the new screws PN NAS6605D10, washers PN NAS1149C0532R,
and nuts PN MS14145-5 on the bracket assembly PN 1840A0700-04.
  (g) Use a torque wrench to torque the nuts PN MS14145-5 to 22 - 25 N.m (195 - 220 lb.in).
  (h) Torque the nut PN MS14145-5 with the minimum final torque value and continue to torque
as necessary to align its slot with the cotter pin PN MS24665-153 hole in the screw PN
NAS6605D10.
NOTE: Be careful not to apply more than the maximum final torque value.
  (i) Safety the nut PN MS14145-5 with a cotter pin PN MS24665-153.
  (j) On the upper side, install the new screws PN NAS6604D9, washers PN NAS1149C0463R,
and nuts PN MS14145-4 on the bracket assembly PN 1840A0700-04.
  (k) Use a torque wrench to torque the nuts PN MS14145-4 to 8 - 10 N.m (70.8 - 88.5 lb.in).
  (l) Torque the nut PN MS14145-4 with the minimum final torque value and continue to torque
as necessary to align its slot with the cotter pin PN MS24665-153 hole in the screw PN
NAS6604D9.
NOTE: Be careful not to apply more than the maximum final torque value.
  (m) Safety the nut PN MS14145-4 with a cotter pin PN MS24665-153.
  (n) With a soft bristle brush, apply a continuous bead of the PR1826B2ALO or PR1826B2 or
PR1826B1/2 or PR1826B1/4 on the head of the screws PN NAS6605D10 and PN
NAS6604D9, washers PN NAS1149C0532R and PN NAS1149C0463R, nuts PN
MS14145-5 and PN MS14145-4, and cotter pins PN MS24665-153 (SRM PART II 51-21-00
- SEALANTS, PROPERTIES AND ALTERNATIVES).
  (5) If removed, install the MLG middle door (AMM TASK 32-12-04-400-801-A/400  - Main-Landing-
Gear Middle Door - Installation).
  (6) Connect the downlock release actuator to the shock strut. Refer to AMM TASK
32-31-05-400-801-A/400 - Main-Landing-Gear Downlock-Release Actuator - Installation.
  (7) Connect the locking stay to the shock strut. Refer to AMM TASK 32-11-07-400-801-A/400 - Main-
Landing-Gear Locking Stay - Installation.
  (8) Do the operational test of the landing gear. Refer to AMM TASK 32-33-00-710-801-A/500  -
Landing-Gear Extension-and-Retraction System (On Jacks) - Operational Test.
  H. PART VI – RH AFFECTED MLG LOCKING-STAY BRACKET ASSEMBLY REPLACEMENT
  (1) Disconnect the locking stay from the shock strut. Refer to AMM TASK 32-11-07-000-801-A/400 -
Main-Landing-Gear Locking Stay - Removal. It is not necessary to fully remove the locking stay.
  (2) Disconnect the downlock release actuator from the shock strut. Refer to AMM TASK
32-31-05-000-801-A/400 - Main-Landing-Gear Downlock-Release Actuator - Removal. It is not
necessary to fully remove the downlock release actuator.
  (3) If necessary to get a better access, remove the MLG middle door (AMM TASK
32-12-04-000-801-A/400 - Main-Landing-Gear Middle Door - Removal).
ALERT
SERVICE BULLETIN
SB170-32-A094
Page 12 of  18 ALERT
Date:  May 18, 2024
Revision No.:  01 - May 28, 2024
Copyright © by Embraer S.A. All rights reserved - See title page for details.
User: kgreer - Printed By myTechCare - May 30/24 - 22:33:15

### Page 15

(4) [RC] Replace the bracket assembly PN 1840A0700-03 or -04 as follows (Figure 3):
  (a) On the upper side of the bracket assembly, use a polyethylene spatula, lint-free wiper cloth
and MEK to remove the sealant from the screws PN NAS6604D9, washers PN
NAS1149C0463R, nuts PN MS14145-4, and cotter pins PN MS24665-153.
  (b) Remove screws PN NAS6604D9, washers PN NAS1149C0463R, nuts PN MS14145-4, and
cotter pins PN MS24665-153 from the bracket assembly PN 1840A0700-03 or -04 and
discard all of them.
  (c) Remove the screws PN NAS6605D10, washers PN NAS1149C0532R, nuts PN
MS17826-5, and cotter pins PN MS24665-153 from the bracket assembly PN
1840A0700-03 or -04 and discard all of them.
  (d) Remove the bracket assembly PN 1840A0700-03 or -04 from the MLG shock strut and
discard it.
  (e) Put a new bracket assembly PN 1840A0700-04 on the installation position on the MLG
shock strut.
  (f) On the lower side, install the new screws PN NAS6605D10, washers PN NAS1149C0532R,
and nuts PN MS14145-5 on the bracket assembly PN 1840A0700-04.
  (g) Use a torque wrench to torque the nuts PN MS14145-5 to 22 - 25 N.m (195 - 220 lb.in).
  (h) Torque the nut PN MS14145-5 with the minimum final torque value and continue to torque
as necessary to align its slot with the cotter pin PN MS24665-153 hole in the screw PN
NAS6605D10.
NOTE: Be careful not to apply more than the maximum final torque value.
  (i) Safety the nut PN MS14145-5 with a cotter pin PN MS24665-153.
  (j) On the upper side, install the new screws PN NAS6604D9, washers PN NAS1149C0463R,
and nuts PN MS14145-4 on the bracket assembly PN 1840A0700-04.
  (k) Use a torque wrench to torque the nuts PN MS14145-4 to 8 - 10 N.m (70.8 - 88.5 lb.in).
  (l) Torque the nut PN MS14145-4 with the minimum final torque value and continue to torque
as necessary to align its slot with the cotter pin PN MS24665-153 hole in the screw PN
NAS6604D9.
NOTE: Be careful not to apply more than the maximum final torque value.
  (m) Safety the nut PN MS14145-4 with a cotter pin PN MS24665-153.
  (n) With a soft bristle brush, apply a continuous bead of the PR1826B2ALO or PR1826B2 or
PR1826B1/2 or PR1826B1/4 on the head of the screws PN NAS6605D10 and PN
NAS6604D9, washers PN NAS1149C0532R and PN NAS1149C0463R, nuts PN
MS14145-5 and PN MS14145-4, and cotter pins PN MS24665-153 (SRM PART II 51-21-00
- SEALANTS, PROPERTIES AND ALTERNATIVES).
  (5) If removed, install the MLG middle door (AMM TASK 32-12-04-400-801-A/400  - Main-Landing-
Gear Middle Door - Installation).
  (6) Connect the downlock release actuator to the shock strut. Refer to AMM TASK
32-31-05-400-801-A/400 - Main-Landing-Gear Downlock-Release Actuator - Installation.
  (7) Connect the locking stay to the shock strut. Refer to AMM TASK 32-11-07-400-801-A/400 - Main-
Landing-Gear Locking Stay - Installation.
ALERT
SERVICE BULLETIN
Date:  May 18, 2024
Revision No.:  01 - May 28, 2024 ALERT
SB170-32-A094
Page 13 of  18
Copyright © by Embraer S.A. All rights reserved - See title page for details.
User: kgreer - Printed By myTechCare - May 30/24 - 22:33:15

### Page 16

(8) Do the operational test of the landing gear. Refer to AMM TASK 32-33-00-710-801-A/500  -
Landing-Gear Extension-and-Retraction System (On Jacks) - Operational Test.
  I. Restore the aircraft to normal.
  J. Enter the accomplishment of this bulletin in the applicable documents.
NOTE:
1) Please inform us by e-mail fleet.monitoring@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 have 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
AEROChain portal (http://www.aerochain.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 to help us improve the quality
of the SBs.
ALERT
SERVICE BULLETIN
SB170-32-A094
Page 14 of  18 ALERT
Date:  May 18, 2024
Revision No.:  01 - May 28, 2024
Copyright © by Embraer S.A. All rights reserved - See title page for details.
User: kgreer - Printed By myTechCare - May 30/24 - 22:33:15

### Page 17

FIGURE 1 - MLG LOCKING-STAY BRACKET ASSEMBLY LOWER NUT - INSPECTION
(Sheet 1 of 2)
EM170SB329006A.IDR
 ZONES
 731
 741
C
BRACKET
ASSEMBLY
D
C
B
A
B
LH SIDE SHOWN
RH SIDE OPPOSITE
A
ALERT
SERVICE BULLETIN
Date:  May 18, 2024
Revision No.:  01 - May 28, 2024 ALERT
SB170-32-A094
Page 15 of  18
Copyright © by Embraer S.A. All rights reserved - See title page for details.
User: kgreer - Printed By myTechCare - May 30/24 - 22:33:15

### Page 18

FIGURE 1 - MLG LOCKING-STAY BRACKET ASSEMBLY LOWER NUT - INSPECTION
(Sheet 2 of 2)
EM170SB329007B.IDR
NUT
PN MS17826-5 OR PN MS14145-5
(INSPECT)
E
E
D
NUT 
PN MS14145-5
NUT 
PN MS17826-5
ALERT
SERVICE BULLETIN
SB170-32-A094
Page 16 of  18 ALERT
Date:  May 18, 2024
Revision No.:  01 - May 28, 2024
Copyright © by Embraer S.A. All rights reserved - See title page for details.
User: kgreer - Printed By myTechCare - May 30/24 - 22:33:15

### Page 19

FIGURE 2 - MLG LOCKING-STAY BRACKET ASSEMBLY LOWER NUT - REPLACEMENT
(Sheet 1 of 1)
EM170SB329008B.IDR
COTTER PIN
PN MS24665-153
(REMOVE AND DISCARD)
COTTER PIN
PN MS24665-153
(INSTALL)
WASHER
PN NAS1149C0532R
(REMOVE AND KEEP)
WASHER
PN NAS1149C0532R
(INSTALL)
A
SCREW
PN NAS6605D10
(REMOVE AND KEEP)
SCREW
PN NAS6605D10
(INSTALL)
NUT
PN MS17826-5
(REMOVE AND DISCARD)
NUT
PN MS14145-5
(INSTALL)
A
TORQUE 22 - 25 N.m (195 - 220 lb.in)1
1 2
2
2
2
SEALANT PR1826B2ALO OR PR1826B2 OR PR1826B1/2 OR PR1826B1/42
ALERT
SERVICE BULLETIN
Date:  May 18, 2024
Revision No.:  01 - May 28, 2024 ALERT
SB170-32-A094
Page 17 of  18
Copyright © by Embraer S.A. All rights reserved - See title page for details.
User: kgreer - Printed By myTechCare - May 30/24 - 22:33:15

### Page 20

FIGURE 3 - MLG LOCKING-STAY BRACKET ASSEMBLY BRACKET - REPLACEMENT
(Sheet 1 of 1)
EM170SB329009C.IDR
A
TORQUE 22 - 25 N.m (195 - 220 lb.in)1
TORQUE 8 - 10 N.m (70.8 - 88.5 lb.in)3
NUT
PN MS17826-5 OR PN MS14145-5
(REMOVE AND DISCARD)
NUT
PN MS14145-5
(INSTALL)
1 2
WASHER
PN NAS1149C0532R
(REMOVE AND DISCARD)
WASHER
PN NAS1149C0532R
(INSTALL)
2
A
COTTER PIN
PN MS24665-153
(REMOVE AND DISCARD)
COTTER PIN
PN MS24665-153
(INSTALL)
2
COTTER PIN
PN MS24665-153
(REMOVE AND DISCARD)
COTTER PIN
PN MS24665-153
(INSTALL)
2
NUT
PN MS14145-4
(REMOVE AND DISCARD)
NUT
PN MS14145-4
(INSTALL)
2 3
SCREW
PN NAS6605D10
(REMOVE AND DISCARD)
SCREW
PN NAS6605D10
(INSTALL)
2
SCREW
PN NAS6604D9
(REMOVE AND DISCARD)
SCREW
PN NAS6604D9
(INSTALL)
2
BRACKET
PN 1840A0700-03 OR 1840A0700-04
(REMOVE AND DISCARD)
BRACKET
PN 1840A0700-04
(INSTALL)
WASHER
PN NAS1149C0463R
(REMOVE AND DISCARD)
WASHER
PN NAS1149C0463R
(INSTALL)
2
SEALANT PR1826B2ALO OR PR1826B2 OR PR1826B1/2 OR  PR1826B1/42
ALERT
SERVICE BULLETIN
SB170-32-A094
Page 18 of  18 ALERT
Date:  May 18, 2024
Revision No.:  01 - May 28, 2024
Copyright © by Embraer S.A. All rights reserved - See title page for details.
User: kgreer - Printed By myTechCare - May 30/24 - 22:33:15

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