SERVICE BULLETIN

DATE: 03/Jul/2014 SB No.: 190LIN-54-0006 

REVISION No.: PAGE: 1 of 23

Copyright © 2014 by Embraer S.A. All rights reserved. 

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 SB190LIN-54-A006.

1. PLANNING INFORMATION

A. SB EFFECTIVITY 

Aircraft affected: 

The SB effectivity is divided into GROUPS of aircraft, as follows: 

(1) GROUP 1 

MODEL SN 

EMBRAER 190 ECJ 19000109, 19000140, 19000159, 19000177, 19000203, 

19000225, 19000236, 19000243, 19000261, 19000278, 

19000296, 19000307, 19000317, 19000362, 19000438, 

19000453, 19000534, 19000559, and 19000571, if POSTMOD SB 190LIN-54-0004. 

(2) GROUP 2 

MODEL SN 

EMBRAER 190 ECJ 19000611, 19000632, and 19000641. 

(3) GROUP 3 

MODEL SN 

EMBRAER 190 ECJ 19000109, 19000140, 19000159, 19000177, 19000203, 

19000225, 19000236, 19000243, 19000261, 19000278, 

19000296, 19000307, 19000317, 19000362, 19000438, 

19000453, 19000534, 19000559, and 19000571, if PRE-MOD 

SB 190LIN-54-0004 
SERVICE BULLETIN

SB No.: 190LIN-54-0006 DATE: 03/Jul/2014 

PAGE: 2 REVISION No.: 

Copyright © 2014 by Embraer S.A. All rights reserved. 

In-production effectivity: 

EMBRAER 190 Embraer Corporate Jet (ECJ) model aircraft SN 19000656 and on 

have an equivalent modification factory-incorporated. 

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. 

(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. 
SERVICE BULLETIN

DATE: 03/Jul/2014 SB No.: 190LIN-54-0006 

REVISION No.: PAGE: 3 

Copyright © 2014 by Embraer S.A. All rights reserved. 

D. DESCRIPTION 

This Bulletin is divided into 4 PARTS, as follows: 

PART I REPLACEMENT OF THE LH LOWER INBOARD AND OUTBOARD 

LINK FITTING 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 

LINK FITTING 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 

LINK FITTING 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. 

To do this, it is necessary to get access to the LH pylon at zone 419 and remove skin 

fairing. 
SERVICE BULLETIN

SB No.: 190LIN-54-0006 DATE: 03/Jul/2014 

PAGE: 4 REVISION No.: 

Copyright © 2014 by Embraer S.A. All rights reserved. 

PART IV RE-TORQUE OF THE RH LOWER INBOARD AND OUTBOARD 

LINK FITTING 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 

60 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 

60 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) Applicable 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 2000 Flight 

Cycle(s) or 7500 Flight Hour(s), whichever occurs first. 

(b) Applicable to GROUP 3 
SERVICE BULLETIN

DATE: 03/Jul/2014 SB No.: 190LIN-54-0006 

REVISION No.: PAGE: 5 

Copyright © 2014 by Embraer S.A. All rights reserved. 

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 2000 Flight Cycle(s) or 7500 

Flight Hour(s), whichever occurs first. 

(4) APPLICABLE TO PART IV 

(a) Applicable 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 2000 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, after the 

accomplishment of PART II of this bulletin, and repeated at each 2000 Flight 

Cycle(s) or 7500 Flight Hour(s), whichever occurs first. 

F. APPROVAL 

The technical aspects of this Service Bulletin are approved by: ANAC – Agência 

Nacional de Aviação Civil. 

NOTE: If any aircraft listed in the SB effectivity has an incorporated modification 

or repair ithat 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 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 promptly available when 

necessary. 

This estimate does not include the sealant, paint, or adhesive curing time. 
SERVICE BULLETIN

SB No.: 190LIN-54-0006 DATE: 03/Jul/2014 

PAGE: 6 REVISION No.: 

Copyright © 2014 by Embraer S.A. All rights reserved. 

(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. 

(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. 
SERVICE BULLETIN

DATE: 03/Jul/2014 SB No.: 190LIN-54-0006 

REVISION No.: PAGE: 7 

Copyright © 2014 by Embraer S.A. All rights reserved. 

H. WEIGHT AND BALANCE 

None. 

I. ELECTRICAL LOAD DATA 

None. 

J. REFERENCES 

AMM 190LIN/( ) Aircraft Maintenance Manual PART II - 20-00-00 and 20-10-01 - 

STANDARD PRACTICES-AIRFRAME. 

AMM 190LIN/( ) Aircraft Maintenance Manual PART II - 54-50-22 - 

NACELLES/PYLONS. 

SB190LIN-54-0004 - NACELLES/PYLONS - INSTALLATION OF LOCK ASSEMBLY 

AT INBOARD AND OUTBOARD LOWER LINK FITTING 

K. OTHER PUBLICATIONS AFFECTED 

AIPC 190LIN/( ) Aircraft Illustrated Parts Catalog - 54-50-00 and 54-50-02 -

NACELLES/PYLONS. 

AMM 190LIN/( ) Aircraft Maintenance Manual PART II - 54-50-00 - 

NACELLES/PYLONS. 

SB190LIN-54-A006 - NACELLES/PYLONS - RETORQUE OF THE LH/RH INBOARD 

AND OUTBOARD LOWER LINK FITTINGS 
SERVICE BULLETIN

SB No.: 190LIN-54-0006 DATE: 03/Jul/2014 

PAGE: 8 REVISION No.: 

Copyright © 2014 by Embraer S.A. All rights reserved. 

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 

(1) WARRANTY COVERAGE 

(a) Parts 

The SB Material will be provided at no charge. 

(b) Labor 

1. APPLICABLE TO PART I THRU IV 

Embraer will compensate 1.5 hours for the SB incorporation if it is 

performed in an Embraer authorized service center. 

(c) Expiration 

The terms expressed in the warranty coverage will be valued for 36 months 

after the SB issue date. 
SERVICE BULLETIN

DATE: 03/Jul/2014 SB No.: 190LIN-54-0006 

REVISION No.: PAGE: 9 

Copyright © 2014 by Embraer S.A. All rights reserved. 

C. MATERIAL NECESSARY FOR EACH AIRCRAFT 

When applicable, the use of alternative or similar parts in place of the ones specified 

in the kit is allowable, provided that these alternative or similar parts are approved by 

Embraer. Refer to IPC Optional PN Cross-Reference List. 

The expendable or consumable parts presented in the AMM Tasks referred to in this 

bulletin, which are necessary for its accomplishment, 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. 

(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 

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

S24665-374 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. 
SERVICE BULLETIN

SB No.: 190LIN-54-0006 DATE: 03/Jul/2014 

PAGE: 10 REVISION No.: 

Copyright © 2014 by Embraer S.A. All rights reserved. 

(b) Consumables 

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. 

ITEM PN DESCRIPTION QTY DISP/ 

Notes 

ARDROX AV-15 Corrosion Inhibiting Compound AR 6/ (a)

(a) Corrosion Inhibiting Compound, Type III (MEP 10-063) ARDROX AV-15

QUANTITY: 

AR = As Required. 

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 

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

DATE: 03/Jul/2014 SB No.: 190LIN-54-0006 

REVISION No.: PAGE: 11 

Copyright © 2014 by Embraer S.A. All rights reserved. 

3. ACCOMPLISHMENT INSTRUCTIONS

NOTES: 1) Obey all of the WARNINGS and CAUTIONS included in the referenced 

manuals and procedures. 

2) The Manuals and other documents are referred to by means of acronyms 

or using a simplified form. Refer to section “1. I. REFERENCES” for a 

more complete definition. 

3) This Service Bulletin effectivity is divided into 4 aircraft GROUPS 

according to the relevant configuration and the SB itself is divided into 4 

PARTS. The SB PARTS are featured to allow 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

SB No.: 190LIN-54-0006 DATE: 03/Jul/2014 

PAGE: 12 REVISION No.: 

Copyright © 2014 by Embraer S.A. All rights reserved. 

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

DATE: 03/Jul/2014 SB No.: 190LIN-54-0006 

REVISION No.: PAGE: 13 

Copyright © 2014 by Embraer S.A. All rights reserved. 

(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. Restore the aircraft to the normal condition. 

G. Enter the accomplishment of PART I and/or PART II and/or PART III and/or PART IV 

of this bulletin in the applicable documents. 

H. Fill out the attached “Service Bulletin Implementation and Evaluation” form and 

return it to: 

EMBRAER S.A. 

Customer Support Contact Center 

Embraer Executive Jets 

lineage.reliability@embraer.com

24/7 Toll Free Numbers 

1 888 362-2648 USA & Canada 

0800 704 1099 Brazil 

24/7 International Numbers 

1 703 621-7350 North America, including Mexico, & Caribbean 

+33 1 7048-0510 Europe, Middle East & Africa 

+65 6307-7647 Asia Pacific 

+55 12 3927-7000 Latin America 

NOTE: To formally inform that the SB has been incorporated in the aircraft 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). 
SERVICE BULLETIN

SB No.: 190LIN-54-0006 DATE: 03/Jul/2014 

PAGE: 14 REVISION No.: 

Copyright © 2014 by Embraer S.A. All rights reserved. 

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 2U2 PN 191-28250-401 (1 position) by removing 

and discarding screw PN NAS1802-04-5 (2 positions). Refer to Detail B (Pre-Mod). 

(c) Remove and discard lock nut PN NAS509-14C (01 position). Refer to Detail B (PreMod). 

(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 fuse pin does not turn when you apply the torque. If 

necessary, safety the other side of the fuse 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. 

Refer to AMM TASK 20-10-01-910-801-A/200 - Bolt Torque Data - 

Maintenance Practices. 

FIGURE 1 - LH/RH LOWER LINK FITTING INBOARD AND OUTBOARDATTACHMENT 

PARTS - REPLACEMENT 

(SHEET 01 OF 06) 
SERVICE BULLETIN

DATE: 03/Jul/2014 SB No.: 190LIN-54-0006 

REVISION No.: PAGE: 15 

Copyright © 2014 by Embraer S.A. All rights reserved. 

(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 Detail C (Pre-Mod). 

(c) Remove and discard lock nut PN NAS509-14C (1 position). Refer to Detail C (PreMod). 

(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 fuse pin does not turn when you apply the torque. If 

necessary, safety the other side of the fuse 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). 

FIGURE 1 - LH/RH LOWER LINK FITTING INBOARD AND OUTBOARDATTACHMENT 

PARTS - REPLACEMENT 

(SHEET 02 OF 06) 
SERVICE BULLETIN

SB No.: 190LIN-54-0006 DATE: 03/Jul/2014 

PAGE: 16 REVISION No.: 

Copyright © 2014 by Embraer S.A. All rights reserved. 

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 - 

Maintenance 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). 

FIGURE 1 - LH/RH LOWER LINK FITTING INBOARD AND OUTBOARDATTACHMENT 

PARTS - REPLACEMENT 

(SHEET 03 OF 06) 
SERVICE BULLETIN

DATE: 03/Jul/2014 SB No.: 190LIN-54-0006 

REVISION No.: PAGE: 17 

Copyright © 2014 by Embraer S.A. All rights reserved. 

EM170SB540307A.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

FIGURE 1 - LH/RH LOWER LINK FITTING INBOARD AND OUTBOARDATTACHMENT 

PARTS - REPLACEMENT 

(SHEET 04 OF 06) 
SERVICE BULLETIN

SB No.: 190LIN-54-0006 DATE: 03/Jul/2014 

PAGE: 18 REVISION No.: 

Copyright © 2014 by Embraer S.A. All rights reserved. 

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)

1 1

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)

2 1 2 4

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.

EM170SB540308A.DGN

APPLICABLE TO GROUPS 1 AND 2.

FIGURE 1 - LH/RH LOWER LINK FITTING INBOARD AND OUTBOARDATTACHMENT 

PARTS - REPLACEMENT 

(SHEET 05 OF 06) 
SERVICE BULLETIN

DATE: 03/Jul/2014 SB No.: 190LIN-54-0006 

REVISION No.: PAGE: 19 

Copyright © 2014 by Embraer S.A. All rights reserved. 

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)

2 4

1 3

WASHER

PN NAS1149C1432R

(INSTALL)

EM170SB540309A.DGN

POST − MOD

LOCK WIRE

PN MS20995C32

(REMOVE AND DISCARD)

APPLICABLE TO GROUPS 1 AND 2.

FIGURE 1 - LH/RH LOWER LINK FITTING INBOARD AND OUTBOARDATTACHMENT 

PARTS - REPLACEMENT 

(SHEET 06 OF 06) 
SERVICE BULLETIN

SB No.: 190LIN-54-0006 DATE: 03/Jul/2014 

PAGE: 20 REVISION No.: 

Copyright © 2014 by Embraer S.A. All rights reserved. 

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 fuse pin does not turn when you apply the torque. If 

necessary, safety the other side of the fuse 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 - Maintenance 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. 

FIGURE 2 - RE-TORQUE OF THE LH/RH LOWER INBOARD AND OUTBOARD LINK 

FITTING CASTLE NUT 

(SHEET 01 OF 04) 
SERVICE BULLETIN

DATE: 03/Jul/2014 SB No.: 190LIN-54-0006 

REVISION No.: PAGE: 21 

Copyright © 2014 by Embraer S.A. All rights reserved. 

(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 fuse pin does not turn when you apply the torque. If 

necessary, safety the other side of the fuse 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 - 

Maintenance 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. 

FIGURE 2 - RE-TORQUE OF THE LH/RH LOWER INBOARD AND OUTBOARD LINK 

FITTING CASTLE NUT 

(SHEET 02 OF 04) 
SERVICE BULLETIN

SB No.: 190LIN-54-0006 DATE: 03/Jul/2014 

PAGE: 22 REVISION No.: 

Copyright © 2014 by Embraer S.A. All rights reserved. 

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

EM170SB540310A.DGN

FIGURE 2 - RE-TORQUE OF THE LH/RH LOWER INBOARD AND OUTBOARD LINK 

FITTING CASTLE NUT 

(SHEET 03 OF 04) 
SERVICE BULLETIN

DATE: 03/Jul/2014 SB No.: 190LIN-54-0006 

REVISION No.: PAGE: 23 

Copyright © 2014 by Embraer S.A. All rights reserved. 

B

PYLON FITTINGS

(REF.)

1 2 3

1 1

WASHER

(REF.)

CASTLE NUT

(REF.)

COTTER PIN

PN MS24665−374

(REMOVE AND DISCARD)

(INSTALL)

PYLON FITTINGS

(REF.)

C

2 1

1 2 3

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).

EM170SB540311A.DGN

FIGURE 2 - RE-TORQUE OF THE LH/RH LOWER INBOARD AND OUTBOARD LINK 

FITTING CASTLE NUT 

(SHEET 04 OF 04) 

.

..

SERVICE BULLETIN IMPLEMENTATION AND EVALUATION FORM

The purpose of this form is to collect data that will be used to improve the quality of our Service Bulletins and 

Reliability Program. 

Please fill in this form and return it to: EMBRAER S.A. 

Customer Support Contact Center 

Embraer Executive Jets 

lineage.reliability@embraer.com

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+65 6307-7647 Asia Pacific 

+55 12 3927-7000 Latin America 

SB Number/Revision: SB Title: 

SB190LIN-54-0006R00 REPLACEMENT OF THE LOWER LINK FITTING INBOARD AND 

OUTBOARD ATTACHING PARTS 

SB Implementation Report 

Aircraft Serial Number or Registration Number: Incorporation Date: 

Aircraft Flight Hours: Aircraft Landings:

SB 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) 

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