# Embraer Service Bulletin 190-54-0015

## Copies (2)

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

- No revision named ("SB190-54-0015"), 26 pages: PDF https://openairdocs.org/files/sha256/87/88/87889af63a7901874641cb2881eaaba43bbf9a840e867819986f68b8bf54fff4; text https://openairdocs.org/service-documents/embraer/sb-190-54-0015/file/87889af63a79.md. Rights: © Embraer S.A. Filed by the FAA in regulations.gov docket FAA-2014-0531; AD 2014-16-16 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- No revision named ("SB190-54-0015 Rev03"), 54 pages: PDF https://openairdocs.org/files/sha256/a6/17/a617784bffcf4457d3984dd196942c8fc47199cfbbb7bb1a7000de5905e674e5; text https://openairdocs.org/service-documents/embraer/sb-190-54-0015/file/a617784bffcf.md. Rights: © Embraer S.A. Filed by the FAA in regulations.gov docket FAA-2021-0692, the docket of AD 2021-25-02. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Embraer](https://openairdocs.org/service-documents/embraer.md)
- Type: Service bulletin (Service Bulletin)
- Number: 190-54-0015
- Page: https://openairdocs.org/service-documents/embraer/sb-190-54-0015

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

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

- [AD 2014-16-16](https://openairdocs.org/ad/2014-16-16.md), effective Sep 2, 2014: No revision named

## Text (26 pages)

No revision named, the newest copy. Rights: © Embraer S.A. Filed by the FAA in regulations.gov docket FAA-2014-0531; AD 2014-16-16 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

NACELLES/PYLONS - REPLACEMENT OF THE LOWER LINK FITTING INBOARD AND
OUTBOARD ATTACHING PARTS
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 BULLETIN SUPERSEDES ALERT SB190-54-A015.
1. PLANNING INFORMATION
A. SB EFFECTIVITY
Aircraft affected:
(1) GROUP 1
MODEL SN
Embraer 190( ) and 195( ) 19000002, 19000004 thru 19000108, 19000110 thru 19000139,
19000141 thru 19000158, 19000160 thru 19000176, 19000178
thru 19000202, 19000204 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
19000361, 19000363 thru 19000437, 19000439 thru 19000452,
19000454 thru 19000466, 19000468 thru 19000484, 19000486
thru 19000525, 19000527 thru 19000533, 19000535 thru
19000558, 19000560 thru 19000570, and 19000572 thru
19000585, if POST-MOD SB190-54-0013.
(2) GROUP 2
MODEL SN
Embraer 190( ) and 195( ) 19000485, 19000586 thru 19000610, 19000612 thru 19000631,
19000633 thru 19000640, 19000642 thru 19000655, and
19000657 thru 19000673.
SERVICE BULLETIN
DATE: 03/Jul/2014
REVISION No.:
SB No.: 190-54-0015
PAGE: 1 of 23
Copyright © 2014 by Embraer S.A. All rights reserved.

### Page 2

(3) GROUP 3
MODEL SN
Embraer 190( ) and 195( ) 19000002, 19000004 thru 19000108, 19000110 thru 19000139,
19000141 thru 19000158, 19000160 thru 19000176, 19000178
thru 19000202, 19000204 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
19000361, 19000363 thru 19000437, 19000439 thru 19000452,
19000454 thru 19000466, 19000468 thru 19000484, 19000486
thru 19000525, 19000527 thru 19000533, 19000535 thru
19000558, 19000560 thru 19000570, and 19000572 thru
19000585, if PRE-MOD SB190-54-0013.
In-production effectivity:
Embraer 190( ) and 195( ) model aircraft SN 19000674 and on have an equivalent
factory-included modification.
B. CONCURRENT REQUIREMENTS
None.
C. REASON
(1) HISTORY
Embraer received reports about loose pylon lower link fitting assembly which can
cause failure to one of the fittings and consequently, the separation of the engine
from the wing.
(2) OBJECTIVE
To replace the lower link fitting inboard and outboard attaching parts of the LH and
RH pylon. Also, to apply the necessary re-torque to the inboard and outboard lower
link fittings assy.
SERVICE BULLETIN
SB No.: 190-54-0015
PAGE: 2
DATE: 03/Jul/2014
REVISION No.:
Copyright © 2014 by Embraer S.A. All rights reserved.

### Page 3

(3) EXPECTED BENEFITS
This modification is aimed at preventing the loss of the shear pins of the pylon
outboard and inboard lower link fittings.
(4) REVISION HISTORY
None.
D. DESCRIPTION
This Bulletin is divided into 4 PARTS, as follows:
PART I REPLACEMENT OF THE LH LOWER INBOARD AND OUTBOARD LINKFITTING ATTACHING PARTS
Applicable to: GROUPS 1 and 2 aircraft.
The modification presented in PART I of this bulletin consists of replacing the LH lower
link fitting inboard and outboard attaching parts.
To do this, it is necessary to get access to the LH pylon at zone 419 and remove skin
fairing.
PART II REPLACEMENT OF THE RH LOWER INBOARD AND OUTBOARD LINKFITTING ATTACHING PARTS
Applicable to: GROUPS 1 and 2 aircraft.
The modification presented in PART II of this bulletin consists of replacing the RH lower
link fitting inboard and outboard attaching parts.
To do this, it is necessary to get access to the RH pylon at zone 429 and remove skin
fairing.
PART III RE-TORQUE OF THE LH LOWER INBOARD AND OUTBOARD LINKFITTING ATTACHING PARTS
Applicable to: GROUPS 1, 2 and 3 aircraft.
The modification described in PART III of this bulletin consists of re-torque of the LH lower
Inboard and Outboard Link Fitting.
SERVICE BULLETIN
DATE: 03/Jul/2014
REVISION No.:
SB No.: 190-54-0015
PAGE: 3
Copyright © 2014 by Embraer S.A. All rights reserved.

### Page 4

To do this, it is necessary to get access to the LH pylon at zone 419 and remove skin
fairing.
PART IV RE-TORQUE OF THE RH LOWER INBOARD AND OUTBOARD LINKFITTING ATTACHING PARTS
Applicable to: GROUPS 1, 2 and 3 aircraft.
The modification described in PART IV of this bulletin consists of re-torque of the RH
lower Inboard and Outboard Link Fitting.
To do this, it is necessary to get access to the RH pylon at zone 429 and remove skin
fairing.
NOTE: The modification presented in this bulletin affects Fatigue Critical Structure
(FCS); however, no change to the related Damage Tolerance Inspection
(DTI) instructions is required.
E. COMPLIANCE
(1) Applicable to PART I
Embraer recommends the accomplishment of PART I of this bulletin in the next 150
Flight Cycle(s) or 200 Flight Hour(s), whichever occurs first, from the first issue date
of this bulletin.
(2) Applicable to PART II
Embraer recommends the accomplishment of PART II of this bulletin in the next 150
Flight Cycle(s) or 200 Flight Hour(s), whichever occurs first, from the first issue date
of this bulletin.
(3) Applicable to PART III
(a) Aplicable to GROUPS 1 and 2
Embraer recommends that PART III of this bulletin be accomplished in the next
6000 Flight Cycle(s) or 7500 Flight Hour(s), whichever occurs first, after the
accomplishment of PART I of this bulletin, and repeated at each 6000 Flight
Cycle(s) or 7500 Flight Hour(s), whichever occurs first.
(b) Applicable to GROUP 3
SERVICE BULLETIN
SB No.: 190-54-0015
PAGE: 4
DATE: 03/Jul/2014
REVISION No.:
Copyright © 2014 by Embraer S.A. All rights reserved.

### Page 5

Embraer recommends that PART III of this bulletin be accomplished in the next
6000 Flight Cycle(s) or 7500 Flight Hour(s), whichever occurs first, from the first
issue date of this bulletin, and repeated at each 6000 Flight Cycle(s) or 7500
Flight Hour(s), whichever occurs first.
(4) Applicable to PART IV
(a) Aplicable to GROUPS 1 and 2
Embraer recommends that PART IV of this bulletin be accomplished in the next
6000 Flight Cycle(s) or 7500 Flight Hour(s), whichever occurs first, after the
accomplishment of PART II of this bulletin, and repeated at each 6000 Flight
Cycle(s) or 7500 Flight Hour(s), whichever occurs first.
(b) Applicable to GROUP 3
Embraer recommends that PART IV of this bulletin be accomplished in the next
6000 Flight Cycle(s) or 7500 Flight Hour(s), whichever occurs first, from the first
issue date of this bulletin, and repeated at each 6000 Flight Cycle(s) or 7500
Flight Hour(s), whichever occurs first.
F. APPROVAL
The technical aspects of this Service Bulletin are approved by: Agência Nacional de
Aviação Civil (ANAC).
NOTE: If any aircraft listed in the SB effectivity has an incorporated modification or
repair that is not from EMBRAER and which affects the content of this
Service Bulletin, the operator will take full responsibility for obtaining
approval by a regulatory agency for any adaptation necessary before the
incorporation of this Service Bulletin.
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.
SERVICE BULLETIN
DATE: 03/Jul/2014
REVISION No.:
SB No.: 190-54-0015
PAGE: 5
Copyright © 2014 by Embraer S.A. All rights reserved.

### Page 6

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
– Access opening: 0.5 man-hours.
– Inspection: None.
– Modification: 0.5 man-hours.
– Access closure: 0.5 man-hours.
– Test: None.
(2) Applicable to PART II
– Access opening: 0.5 man-hours.
– Inspection: None.
– Modification: 0.5 man-hours.
– Access closure: 0.5 man-hours.
– Test: None.
(3) Applicable to PART III
– Access opening: 0.5 man-hours.
– Inspection: None.
– Modification: 0.5 man-hours.
– Access closure: 0.5 man-hours.
– Test: None.
SERVICE BULLETIN
SB No.: 190-54-0015
PAGE: 6
DATE: 03/Jul/2014
REVISION No.:
Copyright © 2014 by Embraer S.A. All rights reserved.

### Page 7

(4) Applicable to PART IV
– Access opening: 0.5 man-hours.
– Inspection: None.
– Modification: 0.5 man-hours.
– Access closure: 0.5 man-hours.
– Test: None.
H. WEIGHT AND BALANCE
None.
I. SOFTWARE ACCOMPLISHMENT SUMMARY
None.
J. REFERENCES
AMM 190/( ) Aircraft Maintenance Manual PART II - 20-00-00 and 20-10-01 -
STANDARD PRACTICES-AIRFRAME.
AMM 190/( ) Aircraft Maintenance Manual PART II - 54-50-22 -
NACELLES/PYLONS.
K. OTHER PUBLICATIONS AFFECTED
AIPC 190/( ) Aircraft Illustrated Parts Catalog - 54-50-00 and 54-50-02 -
NACELLES/PYLONS.
AMM 190/( ) Aircraft Maintenance Manual PART II - 54-50-00 -
NACELLES/PYLONS.
SERVICE BULLETIN
DATE: 03/Jul/2014
REVISION No.:
SB No.: 190-54-0015
PAGE: 7
Copyright © 2014 by Embraer S.A. All rights reserved.

### Page 8

2. MATERIAL INFORMATION
A. MATERIAL - PRICE AND AVAILABILITY
(1) MATERIAL AVAILABLE FROM EMBRAER
None.
(2) MATERIAL AVAILABLE FROM OTHER VENDORS
None.
B. INDUSTRY SUPPORT INFORMATION
None.
C. MATERIAL NECESSARY FOR EACH AIRCRAFT
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 acquired from the operator’s inventories or
manufacturer or locally purchased, or ordered as spares from Embraer at no
charge to the operator during a period of 36 months after the original release
date of this service bulletin.
SERVICE BULLETIN
SB No.: 190-54-0015
PAGE: 8
DATE: 03/Jul/2014
REVISION No.:
Copyright © 2014 by Embraer S.A. All rights reserved.

### Page 9

Applicable to PART I and PART II
NEW PN DESCRIPTION OLD PN QTY DISP/Notes
PE22072L14 Castle Nut NAS509 −14C 02 3
NAS1149C1432R Washer
191-28248-001
191-28248-002
191-28249-001
06 3
MS24665-374 Cotter Pin - 02 2
Applicable to PART III and PART IV
NEW PN DESCRIPTION OLD PN QTY DISP/Notes
MS24665-374 Cotter Pin MS24665-374 02 7
PE22072L14 Castle Nut PE22072L14 AR 7/ [1]
1. Replace the castle nut PN PE22072L14 if necessary during the accomplishment of PART
III and PART IV of this bulletin.
(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 PARTS
NEW PN DESCRIPTION OLD PN QTY DISP/Notes
ARDROX AV-15
Corrosion Inhibiting
Compound
-A R 6/ [1]
1. Corrosion Inhibiting Compound, Type III (MEP 10-063) ARDROX AV-15
DISPOSITION: 2 = Incorporate part bearing NEW PN
SERVICE BULLETIN
DATE: 03/Jul/2014
REVISION No.:
SB No.: 190-54-0015
PAGE: 9
Copyright © 2014 by Embraer S.A. All rights reserved.

### Page 10

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
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.
SERVICE BULLETIN
SB No.: 190-54-0015
PAGE: 10
DATE: 03/Jul/2014
REVISION No.:
Copyright © 2014 by Embraer S.A. All rights reserved.

### Page 11

3. ACCOMPLISHMENT INSTRUCTIONS
NOTE: 1) Obey all of the WARNINGS and CAUTIONS included in the mentioned manuals
and procedures.
2) The Manuals and other documents are mentioned as acronyms or with a
simplified form. Refer to section 1.J. REFERENCES for a more complete
definition.
3) This Service Bulletin effectivity is divided into 4 aircraft GROUPS according to
the related configuration and the SB itself is divided into 4 PARTS. The SB
PARTS division allows their independent accomplishment.
REFERENCE APPLICATION TABLE
Aircraft GROUP SB PART APPLICABLE FIGURES
1 and 2 I and II 1
1, 2, and 3 III and IV 2
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 - REPLACEMENT OF THE LH LOWER INBOARD AND OUTBOARD LINK
FITTING ATTACHING PARTS
(1) Remove the LH pylon side fairings. Refer to AMM TASK 54-50-22-000-801-A/400 -
Pylon Side Fairings - Removal.
NOTE: Skin 5 assy is applicable to outboard side.
Skin 6 assy is applicable to inboard side.
(2) Replace the LH lower Inboard and Outboard Link Fitting attaching parts. Refer to
Figure 1.
(3) Install the LH pylon side fairings. Refer to AMM TASK 54-50-22-400-801-A/400 -
Pylon Side Fairings - Installation.
SERVICE BULLETIN
DATE: 03/Jul/2014
REVISION No.:
SB No.: 190-54-0015
PAGE: 11
Copyright © 2014 by Embraer S.A. All rights reserved.

### Page 12

NOTE: It is permitted to apply the aerodynamic sealant on the side fairings at the
next suitable maintenance opportunity.
C. PART II - REPLACEMENT OF THE RH LOWER INBOARD AND OUTBOARD LINK
FITTING ATTACHING PARTS
(1) Remove the RH pylon side fairings. Refer to AMM TASK 54-50-22-000-801-A/400 -
Pylon Side Fairings - Removal.
NOTE: Skin 5 assy is applicable to outboard side.
Skin 6 assy is applicable to inboard side.
(2) Replace the RH lower Inboard and Outboard Link Fitting attaching parts. Refer to
Figure 1.
(3) Install the RH pylon side fairings. Refer to AMM TASK 54-50-22-400-801-A/400 -
Pylon Side Fairings - Installation.
NOTE: It is permitted to apply the aerodynamic sealant on the side fairings at the
next suitable maintenance opportunity.
D. PART III - RE-TORQUE OF THE LH LOWER INBOARD AND OUTBOARD LINK
FITTING ATTACHING PARTS
(1) Remove the LH pylon side fairings. Refer to AMM TASK 54-50-22-000-801-A/400 -
Pylon Side Fairings - Removal.
NOTE: Skin 5 assy is applicable to outboard side.
Skin 6 assy is applicable to inboard side.
(2) Re-torque the LH lower Inboard and Outboard Link Fitting. Refer to Figure 2.
(3) Install the LH pylon side fairings. Refer to AMM TASK 54-50-22-400-801-A/400 -
Pylon Side Fairings - Installation.
NOTE: It is permitted to apply the aerodynamic sealant on the side fairings at the
next suitable maintenance opportunity.
E. PART IV - RE-TORQUE OF THE RH LOWER INBOARD AND OUTBOARD LINK
FITTING ATTACHING PARTS
SERVICE BULLETIN
SB No.: 190-54-0015
PAGE: 12
DATE: 03/Jul/2014
REVISION No.:
Copyright © 2014 by Embraer S.A. All rights reserved.

### Page 13

(1) Remove the RH pylon side fairings. Refer to AMM TASK 54-50-22-000-801-A/400 -
Pylon Side Fairings - Removal.
NOTE: Skin 5 assy is applicable to outboard side.
Skin 6 assy is applicable to inboard side.
(2) Re-torque the RH lower Inboard and Outboard Link Fitting. Refer to Figure 2.
(3) Install the RH pylon side fairings. Refer to AMM TASK 54-50-22-400-801-A/400 -
Pylon Side Fairings - Installation.
NOTE: It is permitted to apply the aerodynamic sealant on the side fairings at the
next suitable maintenance opportunity.
F. Put the aircraft back to a serviceable condition.
G. Write the accomplishment of PART I and/or PART II and/or PART III and/or PART IV of
this bulletin in the applicable documents.
NOTE: 1) Please inform us by e-mail fleet.reliability@embraer.com.br the aircraft
manufacturer serial number and the SB incorporation date, specifying the SB
Part(s) incorporated or if the whole SB was incorporated. This will allow
Embraer to consider your aircraft configuration when providing future
modifications.
2) To formally inform that the SB was incorporated fleet-wide or that the SB will
not be incorporated, use the “Service Bulletin Full-Fleet Incorporation
Report” form, which is available on the Flyembraer portal
(http://www.flyembraer.com) so that Embraer can update the affected tech-
nical publications.
3) Use the “Service Bulletin Evaluation” form annexed to send us your
comments about this SB. Your feedback will be much appreciated since it will
be an aid for us to improve the SBs quality.
SERVICE BULLETIN
DATE: 03/Jul/2014
REVISION No.:
SB No.: 190-54-0015
PAGE: 13
Copyright © 2014 by Embraer S.A. All rights reserved.

### Page 14

1. Remove the attachment parts of the LH/RH lower link fitting outboard as follows:
(a) Remove and discard the lock wire PN MS20995C32. Refer to Detail B (Pre-Mod).
(b) Remove and discard the profile ″U″ PN 191-28250-401 (1 position) by removing
and discarding screw PN NAS1802-04-5 (2 positions). Refer to DetailB (Pre-Mod).
(c) Remove and discard lock nut PN NAS509-14C (01 position). Refer to Detail B
(Pre-Mod).
(d) Remove and discard lock washer PN 191-28248-001 (1 position LH) or PN
191-28248-002 (1 position RH) as applicable. Refer to Detail B (Pre-Mod).
2. Install the new attachment parts of the LH/RH lower link fitting outboard as follows:
(a) Install the washer PN NAS1149C1432R. Refer to Detail B (Post-Mod).
NOTE: Install a minimum of one washer PN NAS1149C1432R and a maximum of
three washers PN NAS1149C1432R for each assembly.
(b) Install castle nut PN PE22072L14 (1 position) as shown in Detail B (Post-Mod) and
apply torque as follows:
NOTE: Make sure that the shear pin does not turn when you apply the torque. If
necessary, safety the other side of the shear pin with a proper wrench to do
not permit it to turn.
1 Turn the castle nut PN PE22072L14 and measure the drag torque with a
torque wrench.
2 Make sure that the drag torque is between 7.91 - 67.79 N.m (70 - 600 lb.in).
NOTE: If the castle nut PN PE22072L14 is not in the correct range, replace it
with new one with the same part number.
3 Add the drag torque value measured in 2.(b)1 Figure 1 to the standard torque
of 112.98 - 225.97 N.m (1000 - 2000 lb.in) to get the final torque.
4 Apply the final torque to the castle nut PN PE22072L14 with a torque wrench.
SERVICE BULLETIN
SB No.: 190-54-0015
PAGE: 14
DATE: 03/Jul/2014
REVISION No.:
FIGURE 1 - LH/RH LOWER LINK FITTING INBOARD AND OUTBOARD ATTACHMENT PARTS - REPLACEMENT
(SHEET 01 OF 06)
Copyright © 2014 by Embraer S.A. All rights reserved.

### Page 15

Refer to AMM TASK 20-10-01-910-801-A/200 - Bolt Torque Data - Mainte-
nance Practices.
(c) Install the cotter pin PN MS24665-374 (1 position). Refer to Detail B (Post-Mod).
(d) Clean up the reworked area and apply Corrosion Inhibiting Compound, Type III
(MEP 10-063) ARDROX AV-15 . Refer to Detail B (Post-Mod).
3. Remove the attachment parts of the LH/RH lower link fitting inboard as follows:
(a) Remove and discard the lock wire PN MS20995C32. Refer to Detail C (Pre-Mod).
(b) Remove and discard the profile ″U″ PN 191-28250-401 (1 position) by removing
and discarding screw PN NAS1802-04-5 (2 positions). Refer to DetailC (Pre-Mod).
(c) Remove and discard lock nut PN NAS509-14C (1 position). Refer to Detail C
(Pre-Mod).
(d) Remove and discard lock washer PN 191-28249-001 (1 position LH and RH). Refer
to Detail C (Pre-Mod).
4. Install the new attachment parts of the LH/RH lower link fitting inboard as follows:
(a) Install the washer PN NAS1149C1432R. Refer to Detail C (Post-Mod).
NOTE: Install a minimum of one washer PN NAS1149C1432R and a maximum of
three washers PN NAS1149C1432R for each assembly.
(b) Install castle nut PN PE22072L14 (1 position) as shown in Detail C (Post-Mod) and
apply torque as follows:
NOTE: Make sure that the shear pin does not turn when you apply the torque. If
necessary, safety the other side of the shear pin with a proper wrench to do
not permit it to turn.
1 Turn the castle nut PN PE22072L14 and measure the drag torque with a
torque wrench.
2 Make sure that the drag torque is between 7.91 - 67.79 N.m (70 - 600 lb.in).
SERVICE BULLETIN
DATE: 03/Jul/2014
REVISION No.:
SB No.: 190-54-0015
PAGE: 15
FIGURE 1 - LH/RH LOWER LINK FITTING INBOARD AND OUTBOARD ATTACHMENT PARTS - REPLACEMENT
(SHEET 02 OF 06)
Copyright © 2014 by Embraer S.A. All rights reserved.

### Page 16

NOTE: If the castle nut PN PE22072L14 is not in the correct range, replace it
with new one with the same part number.
3 Add the drag torque value measured in 4.(b)1 Figure 1 to the standard torque
of 112.98 - 225.97 N.m (1000 - 2000 lb.in) to get the final torque.
4 Apply the final torque to the castle nut PN PE22072L14 with a torque wrench.
Refer to AMM TASK 20-10-01-910-801-A/200 - Bolt Torque Data - Mainte-
nance Practices.
(c) Install the cotter pin PN MS24665-374 (1 position). Refer to Detail C (Post-Mod).
(d) Clean up the reworked area and apply Corrosion Inhibiting Compound, Type III
(MEP 10-063) ARDROX AV-15 . Refer to Detail C (Post-Mod).
SERVICE BULLETIN
SB No.: 190-54-0015
PAGE: 16
DATE: 03/Jul/2014
REVISION No.:
FIGURE 1 - LH/RH LOWER LINK FITTING INBOARD AND OUTBOARD ATTACHMENT PARTS - REPLACEMENT
(SHEET 03 OF 06)
Copyright © 2014 by Embraer S.A. All rights reserved.

### Page 17

EM170SB540301A.DGN
A
ZONES
419
429
B
A
C
LH PYLON
(REF.)
PYLON FITTINGS
(REF.)
OUTBOARD PYLON FAIRING
419ACL (SKIN 5) − LH
429AER (SKIN 5) − RH
(REF.)
INBOARD PYLON FAIRING
419ADR (SKIN 6) − LH
429ADL (SKIN 6) − RH
(REF.)
TYPICAL
SERVICE BULLETIN
DATE: 03/Jul/2014
REVISION No.:
SB No.: 190-54-0015
PAGE: 17
FIGURE 1 - LH/RH LOWER LINK FITTING INBOARD AND OUTBOARD ATTACHMENT PARTS - REPLACEMENT
(SHEET 04 OF 06)
Copyright © 2014 by Embraer S.A. All rights reserved.

### Page 18

B
B
1
PYLON FITTINGS
(REF.)
PYLON FITTINGS
(REF.)
APPLY CORROSION INHIBITING COMPOUND (MEP_10−063) ANDROX AV−15
1
LOCK WASHER
PN 191−28248−001(LH) OR
PN 191−28248−002 (RH)
(REMOVE AND DISCARD)
1
LOCK WIRE
PN MS20995C32
(REMOVE AND DISCARD)
11
PRE − MOD
1
LOCK NUT
PN NAS509−14C
(REMOVE AND DISCARD)
PROFILE "U"
PN 191−28250−401
(REMOVE AND DISCARD)
1 1
1 1
SCREW
PN NAS1802−04−5
(02 POSITIONS)
(REMOVE AND DISCARD)
1
WASHER
PN NAS1149C1432R
(INSTALL)
2 3
CASTLE NUT
PN PE22072L14
(INSTALL)
1242
POST − MOD
2
COTTER PIN
PN MS24665−374
(INSTALL)
1
1
2
3
4
APPLY TORQUE OF 112.98 − 225.97 N.m (1000 − 2000 lb.in) PLUS DRAG TORQUE OF 7.91 − 67.79 N.m (70 − 600 lb.in).
INSTALL A MINIMUM OF ONE WASHER PN NAS1149C1432R AND MAXIMUM OF THREE FOR EACH ASSEMBLY.
EM170SB540302A.DGN
APPLICABLE TO GROUPS 1 AND 2.
SERVICE BULLETIN
SB No.: 190-54-0015
PAGE: 18
DATE: 03/Jul/2014
REVISION No.:
FIGURE 1 - LH/RH LOWER LINK FITTING INBOARD AND OUTBOARD ATTACHMENT PARTS - REPLACEMENT
(SHEET 05 OF 06)
Copyright © 2014 by Embraer S.A. All rights reserved.

### Page 19

PYLON FITTINGS
(REF.)
PYLON FITTINGS
(REF.)
1
C
C
1
2
3
4
APPLY TORQUE OF 112.98 − 225.97 N.m (1000 − 2000 lb.in) PLUS DRAG TORQUE OF 7.91 − 67.79 N.m (70 − 600 lb.in).
INSTALL A MINIMUM OF ONE WASHER PN NAS1149C1432R AND MAXIMUM OF THREE FOR EACH ASSEMBLY.
APPLY CORROSION INHIBITING COMPOUND (MEP_10−063) ANDROX AV−15.
3
LOCK NUT
PN NAS509−14C
(REMOVE AND DISCARD)
3
3
3
3
PRE − MOD
1
1
1
1
PROFILE "U"
PN 191−28250−401
(REMOVE AND DISCARD)
LOCK WASHER
PN 191−28249−001
(REMOVE AND DISCARD)
SCREW
PN NAS1802−04−5
(02 POSITIONS)
(REMOVE AND DISCARD)
4
COTTER PIN
PN MS24665−374
(INSTALL)
4
4 1
CASTLE NUT
PN PE22072L14
(INSTALL)
24
13
WASHER
PN NAS1149C1432R
(INSTALL)
EM170SB540303A.DGN
POST − MOD
LOCK WIRE
PN MS20995C32
(REMOVE AND DISCARD)
APPLICABLE TO GROUPS 1 AND 2.
SERVICE BULLETIN
DATE: 03/Jul/2014
REVISION No.:
SB No.: 190-54-0015
PAGE: 19
FIGURE 1 - LH/RH LOWER LINK FITTING INBOARD AND OUTBOARD ATTACHMENT PARTS - REPLACEMENT
(SHEET 06 OF 06)
Copyright © 2014 by Embraer S.A. All rights reserved.

### Page 20

1. Re-torque the castle nut PN PE22072L14 of the LH/RH lower link fitting outboard as
follows:
(a) Remove and discard cotter pin PN MS24665-374 (1 position). Refer to Detail B.
(b) Re-torque the castle nut PN PE22072L14 (1 position) as shown in Detail B and do
the steps that follows:
NOTE: Make sure that the shear pin does not turn when you apply the torque. If
necessary, safety the other side of the shear pin with a proper wrench to do
not permit it to turn.
1 Loosen the castle nut PN PE22072L14 (1 position).
2 Turn the castle nut PN PE22072L14 and measure the drag torque with a
torque wrench.
3 Make sure that the drag torque is between 7.91 - 67.79 N.m (70 - 600 lb.in).
NOTE: If the castle nut PN PE22072L14 is not in the correct range, replace it
with new one with the same part number.
4 Add the drag torque value measured in 1.(b)2 Figure 2 to the standard torque
of 112.98 - 225.97 N.m (1000 - 2000 lb.in) to get the final torque.
5 Apply the final torque to the castle nut PN PE22072L14 with a torque wrench.
Refer to AMM TASK 20-10-01-910-801-A/200 - Bolt Torque Data - Mainte-
nance Practices.
(c) Install the cotter pin PN MS24665-374 (1 position). Refer to Detail B.
(d) Clean up the reworked area and apply Corrosion Inhibiting Compound, Type III
(MEP 10-063) ARDROX AV-15 . Refer to Detail B.
2. Re-torque the castle nut PN PE22072L14 of the LH/RH lower link fitting inboard as
follows:
(a) Remove and discard cotter pin PN MS24665-374 (1 position). Refer to Detail C.
SERVICE BULLETIN
SB No.: 190-54-0015
PAGE: 20
DATE: 03/Jul/2014
REVISION No.:
FIGURE 2 - RE-TORQUE OF THE LH/RH LOWER INBOARD AND OUTBOARD LINK FITTING CASTLE NUT
(SHEET 01 OF 04)
Copyright © 2014 by Embraer S.A. All rights reserved.

### Page 21

(b) Re-torque the castle nut PN PE22072L14 (1 position) as shown in Detail C and do
the steps that follows:
NOTE: Make sure that the shear pin does not turn when you apply the torque. If
necessary, safety the other side of the shear pin with a proper wrench to do
not permit it to turn.
1 Loosen the castle nut PN PE22072L14 (1 position).
2 Turn the castle nut PN PE22072L14 and measure the drag torque with a
torque wrench.
3 Make sure that the drag torque is between 7.91 - 67.79 N.m (70 - 600 lb.in).
NOTE: If the castle nut PN PE22072L14 is not in the correct range, replace it
with new one with the same part number.
4 Add the drag torque value measured in 2.(b)2 Figure 2 to the standard torque
of 112.98 - 225.97 N.m (1000 - 2000 lb.in) to get the final torque.
5 Apply the final torque to the castle nut PN PE22072L14 with a torque wrench.
Refer to AMM TASK 20-10-01-910-801-A/200 - Bolt Torque Data - Mainte-
nance Practices.
(c) Install the cotter pin PN MS24665-374 (1 position). Refer to Detail C.
(d) Clean up the reworked area and apply Corrosion Inhibiting Compound, Type III
(MEP 10-063) ARDROX AV-15 . Refer to Detail C.
SERVICE BULLETIN
DATE: 03/Jul/2014
REVISION No.:
SB No.: 190-54-0015
PAGE: 21
FIGURE 2 - RE-TORQUE OF THE LH/RH LOWER INBOARD AND OUTBOARD LINK FITTING CASTLE NUT
(SHEET 02 OF 04)
Copyright © 2014 by Embraer S.A. All rights reserved.

### Page 22

A
ZONES
419
429
B
A
C
LH PYLON
(REF.)
PYLON FITTINGS
(REF.)
OUTBOARD PYLON FAIRING
419ACL (SKIN 5) − LH
429AER (SKIN 5) − RH
(REF.)
INBOARD PYLON FAIRING
419ADR (SKIN 6) − LH
429ADL (SKIN 6) − RH
(REF.)
TYPICAL
EM170SB540304A.DGN
SERVICE BULLETIN
SB No.: 190-54-0015
PAGE: 22
DATE: 03/Jul/2014
REVISION No.:
FIGURE 2 - RE-TORQUE OF THE LH/RH LOWER INBOARD AND OUTBOARD LINK FITTING CASTLE NUT
(SHEET 03 OF 04)
Copyright © 2014 by Embraer S.A. All rights reserved.

### Page 23

B
PYLON FITTINGS
(REF.)
123
1 1
WASHER
(REF.)
CASTLE NUT
(REF.)
COTTER PIN
PN MS24665−374
(REMOVE AND DISCARD)
(INSTALL)
PYLON FITTINGS
(REF.)
C
12
123
1
2
3 APPLY CORROSION INHIBITING COMPOUND (MEP_10−063) ANDROX AV−15.
COTTER PIN
PN MS24665−374
(REMOVE AND DISCARD)
(INSTALL)
WASHER
(REF.)
CASTLE NUT
(REF.)
APPLICABLE TO ALL GROUPS.
APPLY TORQUE OF 112.98 − 225.97 N.m (1000 − 2000 lb.in) PLUS DRAG TORQUE OF 7.91 − 67.79 N.m (70 − 600 lb.in).
EM170SB540305A.DGN
SERVICE BULLETIN
DATE: 03/Jul/2014
REVISION No.:
SB No.: 190-54-0015
PAGE: 23
FIGURE 2 - RE-TORQUE OF THE LH/RH LOWER INBOARD AND OUTBOARD LINK FITTING CASTLE NUT
(SHEET 04 OF 04)
Copyright © 2014 by Embraer S.A. All rights reserved.

### Page 24

(No text on this page.)

### Page 25

SERVICE BULLETIN EVALUATION
THE PURPOSE OF THIS FORM IS TO COLLECT DATA THAT WILL BE USED TO IMPROVE THE QUALITY OF OUR
SERVICE BULLETINS. 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 © 2014 by Embraer S.A. All rights reserved.

### Page 26

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