1. DESCRIPTION This sheet informs about Revision 02 to the Service Bulletin 190LIN-54-A006. 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 actions. 3. RECORD OF REVISION Basic issue: 23/Jun/2014. Revision 01: 26/Jun/2014. Revision 02: 27/Jun/2014. 4. HIGHLIGHTS The topics, affected pages and a brief description of the content-related changes from 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 Corrected the text. Item 1.C.(4) / 02 Added reason of Revision 02. 1.D. DESCRIPTION / 02 and 03 Restructured and corrected the text. 1.E. COMPLIANCE / 03 and 04 Updated compliance information. 2. MATERIAL INFORMATION / 07 thru 09 Updated material information. 3. ACCOMPLISHMENT INSTRUCTIONS / 10 and 11 Restructured and corrected the text. Figure 1 / 12 and 14 Updated the information related to nut assembly and inspection. 

# TRANSMITTAL LETTER

SB No.: 190LIN-54-A006 PAGE: 1 of 1 Copyright © 2014 by Embraer S.A. All rights reserved.NACELLES/PYLONS - RETORQUE OF THE LH/RH INBOARD AND OUTBOARD LOWER LINK FITTINGS 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. 1. PLANNING INFORMATION A. SB EFFECTIVITY Aircraft affected: (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 POST-MOD SB 190LIN-54-0004. (2) GROUP 2
MODEL SN EMBRAER 190 ECJ 19000611, and 19000632. In-production effectivity: The subject presented in this bulletin does not affect any in-production aircraft. B. CONCURRENT REQUIREMENTS None. 

# SERVICE BULLETIN ALERT

ALERT DATE: 23/Jun/2014 REVISION No.:02 - 27/Jun/2014 SB No.: 190LIN-54-A006 PAGE: 1 of 15 Copyright © 2014 by Embraer S.A. All rights reserved.C. REASON (1) HISTORY During routine maintenance, the pylon lower link fitting assy was found loose even though the lock washer, lock nut and lock wire were installed. Since this can make the shear pins installed on the LH/RH pylon outboard and inboard fittings to get loose, Embraer proposes a retorque of the fitting assy. (2) OBJECTIVE To retorque the inboard and outboard lower link fitting assy on the two nacelles. (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 REVISION 01: This revision has been issued to update the information of the Compliance and Accomplishment Instructions. REVISION 02: This revision has been issued to update the Compliance information and the information related to the nut assembly and inspection. D. DESCRIPTION This Bulletin is divided into 2 PARTS, as follows:
PART I RETORQUE OF THE LH INBOARD AND OUTBOARD LOWER LINK FITTINGS Applicable to: GROUPS 1 and 2. The modification described in the PART I of this bulletin consists of the retorque of the LH lower Inboard and Outboard Link Fittings. To do this, it is necessary to get access to the LH pylon in zone 419 and remove the skin fairing. 

# SERVICE BULLETIN ALERT

ALERT SB No.: 190LIN-54-A006 PAGE: 2 DATE: 23/Jun/2014 REVISION No.: 02 - 27/Jun/2014 Copyright © 2014 by Embraer S.A. All rights reserved.PART II RETORQUE OF THE LH INBOARD AND OUTBOARD LOWER LINK FITTINGS Applicable to: GROUPS 1 and 2. The modification described in the PART II of this bulletin consists of the retorque of the RH lower Inboard and Outboard Link Fittings. To do this, it is necessary to get access to the RH pylon in zone 429 and remove the skin fairing. E. COMPLIANCE (1) APPLICABLE TO PART I (a) Applicable to GROUP 1 For aircraft that have reached less than 200 Flight Cycles (FC) and less than 750 Flight Hours (FH) after the SB190LIN-54-0004 incorporation, PART I of this bulletin must be accomplished within the next 50 Flight Hours (FH) after the first issuance of this bulletin, and repeated at each 200 Flight Cycles (FC) or 750 Flight Hours (FH), whichever occurs first. For aircraft that have reached more than 200 Flight Cycles (FC) or more than 750 Flight Hours (FH) after the SB190LIN-54-0004 incorporation, whichever occurs first, PART I of this bulletin must be accomplished within the next 10 Flight Hours (FH) from the Revision 01 issuance date of this bulletin, and repeated at each 200 Flight Cycles (FC) or 750 Flight Hours (FH), whichever occurs first. (b) Applicable to GROUP 2 For aircraft that have reached less than 200 Flight Cycles (FC) and less than 750 Flight Hours (FH), PART I of this bulletin must be accomplished within the next 50 Flight Hours (FH) after the first issuance of this bulletin, and repeated at each 200 Flight Cycles (FC) or 750 Flight Hours (FH), whichever occurs first. For aircraft that have reached more than 200 Flight Cycles (FC) or more than 750 Flight Hours (FH) , whichever occurs first, PART I of this bulletin must be accomplished within the next 10 Flight Hours (FH) from the Revision 01 issuance date of this bulletin, and repeated at each 200 Flight Cycles (FC) or 750 Flight Hours (FH), whichever occurs first. 

# SERVICE BULLETIN ALERT

ALERT DATE: 23/Jun/2014 REVISION No.:02 - 27/Jun/2014 SB No.: 190LIN-54-A006 PAGE: 3 Copyright © 2014 by Embraer S.A. All rights reserved.(2) APPLICABLE TO PART II (a) Applicable to GROUP 1 For aircraft that have reached less than 200 Flight Cycles (FC) and less than 750 Flight Hours (FH) after the SB190LIN-54-0004 incorporation, PART II of this bulletin must be accomplished within the next 50 Flight Hours (FH) after the first issuance of this bulletin, and repeated at each 200 Flight Cycles (FC) or 750 Flight Hours (FH), whichever occurs first. For aircraft that have reached more than 200 Flight Cycles (FC) or more than 750 Flight Hours (FH) after the SB190LIN-54-0004 incorporation, whichever occurs first, PART II of this bulletin must be accomplished within the next 10 Flight Hours (FH) from the Revision 01 issuance date of this bulletin, and repeated at each 200 Flight Cycles (FC) or 750 Flight Hours (FH), whichever occurs first. (b) Applicable to GROUP 2 For aircraft that have reached less than 200 Flight Cycles (FC) and less than 750 Flight Hours (FH), PART II of this bulletin must be accomplished within the next 50 Flight Hours (FH) after the first issuance of this bulletin, and repeated at each 200 Flight Cycles (FC) or 750 Flight Hours (FH), whichever occurs first. For aircraft that have reached more than 200 Flight Cycles (FC) or more than 750 Flight Hours (FH), whichever occurs first, PART II of this bulletin must be accomplished within the next 10 Flight Hours (FH) from the Revision 01 issuance date of this bulletin, and repeated at each 200 Flight Cycles (FC) or 750 Flight Hours (FH), whichever occurs first. F. APPROVAL The technical aspects of this Service Bulletin are approved by: Embraer - Engineering Board. G. COMMUNICATIONS TO EMBRAER EMBRAER requests that any results found during these inspections be informed to your local EMBRAER representatives or offices. 

# SERVICE BULLETIN ALERT

ALERT SB No.: 190LIN-54-A006 PAGE: 4 DATE: 23/Jun/2014 REVISION No.: 02 - 27/Jun/2014 Copyright © 2014 by Embraer S.A. All rights reserved.H. 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. (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. I. REFERENCES AMM 190LIN/( ) Aircraft Maintenance Manual PART II - 20-00-00 - STANDARD PRACTICES-AIRFRAME. 

# SERVICE BULLETIN ALERT

ALERT DATE: 23/Jun/2014 REVISION No.:02 - 27/Jun/2014 SB No.: 190LIN-54-A006 PAGE: 5 Copyright © 2014 by Embraer S.A. All rights reserved.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. J. OTHER PUBLICATIONS AFFECTED None. 

# SERVICE BULLETIN ALERT

ALERT SB No.: 190LIN-54-A006 PAGE: 6 DATE: 23/Jun/2014 REVISION No.: 02 - 27/Jun/2014 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 None. 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 procured from the operator’s inventories or from a local supplier, or ordered as spares from Embraer. 

# SERVICE BULLETIN ALERT

ALERT DATE: 23/Jun/2014 REVISION No.:02 - 27/Jun/2014 SB No.: 190LIN-54-A006 PAGE: 7 Copyright © 2014 by Embraer S.A. All rights reserved.NEW PN DESCRIPTION OLD PN QTY DISP/ Notes NAS1149C1432R Washer - 01 2/ [1] 1. This part should be used If the operator do not get the correct adjustment of the lock nut in the assembly during the accomplishment 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.

NEW PN DESCRIPTION OLD PN QTY DISP/ Notes MS20995C32 Lock wire MS20995C32 A.R. 6 F-925-YELLOW TORQUE SEAL Sealant - A.R. 7/ [1]
ARDROX AV-15 Corrosion Inhibiting Compound - A.R. 7/ [2]
1. Yellow Torque Seal (MEP 09-068) F-925 2. Corrosion Inhibiting Compound, Type III (MEP 10-063) ARDROX AV-15 DISPOSITION: 2 = Incorporate part bearing NEW PN 6 = Apply as required QUANTITY: AR = As Required D. MATERIAL NECESSARY FOR EACH SPARE None. 

# SERVICE BULLETIN ALERT

ALERT SB No.: 190LIN-54-A006 PAGE: 8 DATE: 23/Jun/2014 REVISION No.: 02 - 27/Jun/2014 Copyright © 2014 by Embraer S.A. All rights reserved.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 ALERT

ALERT DATE: 23/Jun/2014 REVISION No.:02 - 27/Jun/2014 SB No.: 190LIN-54-A006 PAGE: 9 Copyright © 2014 by Embraer S.A. All rights reserved.3. ACCOMPLISHMENT INSTRUCTIONS NOTE: 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 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 02 PARTS. The SB PARTS are featured to allow their independent accomplishment. REFERENCE APPLICATION TABLE SB PART APPLICABLE FIGURES I 1 II 1 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 - RETORQUE OF THE LH LOWER INBOARD AND OUTBOARD LINK FITTINGS (1) Remove the pylon side fairing by loosening the screws. Refer to Figure 1 and AMM TASK 54-50-22-000-801-A/400 - Pylon Side Fairings - Removal. NOTE: Skin 5 assembly is applicable to the outboard side. Skin 6 assembly is applicable to the inboard side. (2) Retorque the LH lower Inboard and Outboard Link Fittings according to Figure 1

. (3) Reinstall pylon side fairings. Refer to Figure 1 and AMM TASK 54-50-22-400-801 -A/400 - Pylon Side Fairings - Installation. NOTE: It is acceptable install the side fairings without the installation of the aerodynamic sealant until EMBRAER issue a permanent solution for this case. 

# SERVICE BULLETIN ALERT

ALERT SB No.: 190LIN-54-A006 PAGE: 10 DATE: 23/Jun/2014 REVISION No.: 02 - 27/Jun/2014 Copyright © 2014 by Embraer S.A. All rights reserved.C. PART II - RETORQUE OF THE RH LOWER INBOARD AND OUTBOARD LINK FITTINGS (1) Remove the pylon side fairing by loosening the screws. Refer to Figure 1 and AMM TASK 54-50-22-000-801-A/400 - Pylon Side Fairings - Removal. NOTE: Skin 5 assembly is applicable to the outboard side. Skin 6 assembly is applicable to the inboard side. (2) Retorque the RH lower Inboard and Outboard Link Fittings according to Figure 1

. (3) Reinstall pylon side fairings. Refer to Figure 1 and AMM TASK 54-50-22-400-801 -A/400 - Pylon Side Fairings - Installation. NOTE: It is acceptable install the side fairings without the installation of the aerodynamic sealant until EMBRAER issue a permanent solution for this case. D. Restore the aircraft to normal. E. Enter the accomplishment of PART I and/or PART II of this bulletin in the applicable documents. NOTE: 1) Please inform us by e-mail lineage.reliability@embraer.com.br of the aircraft manufacturer serial number and the SB incorporation date, specifying the SB Part(s) incorporated or whether the whole SB has been incorporated. This will enable Embraer to consider your aircraft configuration when providing future modifications. 2) To formally inform that the SB has been incorporated fleet-wide or that the SB will not be incorporated, so that Embraer can update the affected technical publications, use the “Service Bulletin Full-Fleet Incorporation Report” form, which is available on the Flyembraer portal (http://www.flyembraer.com). 3) Use the attached “Service Bulletin Evaluation” form to send us your comments regarding this SB. Your feedback will be much appreciated as an aid for us to improve the quality of the SBs. 

# SERVICE BULLETIN ALERT

ALERT DATE: 23/Jun/2014 REVISION No.:02 - 27/Jun/2014 SB No.: 190LIN-54-A006 PAGE: 11 Copyright © 2014 by Embraer S.A. All rights reserved.1. Remove the lock wire PN MS20995C32 from the lock nut. Refer to Details B and C

. 2. Remove and save the profile ′′U′′ PN 191-28250-401 (01 position) with the screw PN NAS1802-04-5 (02 positions). Refer to Details B and C

. 3. Keep the lock washer in place and apply a toque of 1,500 lb.in to the lock nut. After that, adjust the lock nut position as indicated in Details B

. C, D . and E

. NOTE: 1) The final torque must not exceed 2,000 lb.in. 2) With a pressure plier, fix the lock washer at the pylon structure to avoid rotation, and consequential damages, while torque is applied. 3) Ensure that at least one full thread extend beyond the nut. 4) If you do not get the correct adjustment of the lock nut in the assembly, the installation of washer PN NAS1149C1432R (01 position) between the lock washer and lock nut can be done, provided at least one of the full threads extends beyond the nut. 4. Reinstall profile ′′U′′ PN 191-28250-401 (01 position) by positioning and tightening the screw PN NAS1802-04-5 (02 positions). Refer to Details B and C

. 5. Install lock wire PN MS20995C32. Refer to Details B and C

. 6. Apply Yellow Torque Seal (MEP 09-068) F-925 and Corrosion Inhibiting Compound, Type III (MEP 10-063) ARDROX AV-15 . 

# SERVICE BULLETIN ALERT

ALERT SB No.: 190LIN-54-A006 PAGE: 12 DATE: 23/Jun/2014 REVISION No.: 02 - 27/Jun/2014 FIGURE 1 - RETORQUE OF THE LH/RH LOWER INBOARD AND OUTBOARD LINK FITTINGS (SHEET 01 OF 04)

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

### A ZONES

419 429



### B



### A LH PYLON SHOWN 

### 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.)EM170SB540298A.DGN 

# SERVICE BULLETIN ALERT

ALERT DATE: 23/Jun/2014 REVISION No.:02 - 27/Jun/2014 SB No.: 190LIN-54-A006 PAGE: 13 FIGURE 1 - RETORQUE OF THE LH/RH LOWER INBOARD AND OUTBOARD LINK FITTINGS (SHEET 02 OF 04)

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

### B

2 1

3 2

2

LOCK WIRE PN MS20995C32 (REPLACE) PYLON FITTINGS (REF.)



### D

PYLON FITTINGS (REF.)
4 

### C LOCK WIRE PN MS20995C32 (REPLACE) 

### EEM170SB540299E.DGN 3 6

4 2 1 5

3

2 4

4

3 6 1 5 3 LOCK WASHER PN 191−28248−001(LH) OR PN 191−28248−002 (RH) (KEEP IN PLACE) SCREW PN NAS1802−04−5 (02 POSITIONS) (REMOVE AND REINSTALL) PROFILE "U" PN 191−28250−401 (REMOVE AND REINSTALL)

LOCK NUT PN NAS509−14C (APPLY TORQUE)

LOCK NUT PN NAS509−14C (APPLY TORQUE)

PROFILE "U" PN 191−28250−401 (REMOVE AND REINSTALL)

LOCK WASHER PN 191−28249−001 (KEEP IN PLACE)

SCREW PN NAS1802−04−5 (02 POSITIONS) (REMOVE AND REINSTALL) APPLY YELLOW TORQUE SEAL (MEP 09−068) F−925. APPLY CORROSION INHIBITING COMPOUND (MEP_10−063) ANDROX AV−15. 4

4 TORQUE: 169.47 − 225.97 N.m (1500 − 2000 lb.in)

ENSURE THAT AT LEAST ONE FULL THREADS EXTEND BEYOND THE NUT. 1 2 5 4 1 2 3 5

3

5 IF YOU DO NOT GET THE CORRECT ADJUSTMENT OF THE LOCK NUT IN THE ASSEMBLY, WASHER PN NAS1149C1432R (01 POSITION) CAN BE INSTALLED BETWEEN LOCK WASHER AND LOCK NUT, PROVIDED AT LEAST ONE OF THE FULL THREADS EXTENDS BEYOND THE NUT. 

# SERVICE BULLETIN ALERT

ALERT SB No.: 190LIN-54-A006 PAGE: 14 DATE: 23/Jun/2014 REVISION No.: 02 - 27/Jun/2014 FIGURE 1 - RETORQUE OF THE LH/RH LOWER INBOARD AND OUTBOARD LINK FITTINGS (SHEET 03 OF 04)

Copyright © 2014 by Embraer S.A. All rights reserved.EM170SB540300A.DGN 

### D 30° (REF.) PARALLEL 22° (REF.)



### E E ACCEPTABLE CONDITION 30° (REF.) PARALLEL

22° (REF.) NOMINAL CONDITION

NOMINAL CONDITION 

### D ACCEPTABLE CONDITION 

# SERVICE BULLETIN ALERT

ALERT DATE: 23/Jun/2014 REVISION No.:02 - 27/Jun/2014 SB No.: 190LIN-54-A006 PAGE: 15 FIGURE 1 - RETORQUE OF THE LH/RH LOWER INBOARD AND OUTBOARD LINK FITTINGS (SHEET 04 OF 04)

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

### 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. LINEAGE CUSTOMER SUPPORT AV. BRIGADEIRO FARIA LIMA, 2170 SÃO JOSÉ DOS CAMPOS - SP - 12227-901 BRASIL Fax: + 55 12 3927-2619 e-mail: lineage.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.