1. DESCRIPTION This sheet informs about Revision 03 to the Service Bulletin 190-54-A015. 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: 23/Jun/2014. Revision 01: 26/Jun/2014. Revision 02: 27/Jun/2014. Revision 03: 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 Added aircraft SN 19000485 on the SB effectivity. 1.C. REASON /02 Added reason of Revision 03. 2. MATERIAL INFORMATION2.C. MATERIAL NECESSARY FOR EACH AIRCRAFT /07 and 08 Updated information. Figure 1 /12 and 14 Updated the information related to nut assembly and inspection. 

# TRANSMITTAL LETTER

SB No.: 190-54-A015 PAGE: 1 of 1 Copyright © 2014 by Embraer S.A. All rights reserved.NACELLES/PYLONS - RE-TORQUE OF THE LOWER LINK FITTING INBOARD AND OUTBOARD 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( ) 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, and 19000633 thru 19000636. In-production effectivity: The subject presented in this bulletin does not affect any in-production aircraft. 

# SERVICE BULLETIN ALERT

ALERT DATE: 23/Jun/2014 REVISION No.: 03 -27/Jun /2014 SB No.: 190-54-A015 PAGE: 1 of 15 Copyright © 2014 by Embraer S.A. All rights reserved.B. CONCURRENT REQUIREMENTS None. 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. REVISION 03: This revision has been issued to include aircraft SN 19000485 on the SB effectivity. Also this revision has been issued to update the information related to the nut assembly and inspection. D. DESCRIPTION This Bulletin is divided into 2 PARTS, as follows:
PART I RE-TORQUE OF THE LH LOWER INBOARD AND OUTBOARD LINK FITTING Applicable to: Groups 1 and 2 

# SERVICE BULLETIN ALERT

ALERT SB No.: 190-54-A015 PAGE: 2 DATE: 23/Jun/2014 REVISION No.: 03 -27/Jun/2014 Copyright © 2014 by Embraer S.A. All rights reserved.The modification described in PART I 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.
PART II RE-TORQUE OF THE RH LOWER INBOARD AND OUTBOARD LINK FITTING Applicable to: Groups 1 and 2 The modification described in PART II 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 (a) Applicable to Group 1 For aircraft that have reached less than 600 flight cycles and less than 750 flight hours after the SB 190-54-0013 incorporation, PART I of this bulletin must be accomplished within the next 50 flight hours after the first issuance of this bulletin, and repeated at each 600 flight cycles or 750 flight hours, whichever occurs first. For aircraft that have reached more than 600 flight cycles or more than 750 flight hours after the SB 190-54-0013 incorporation, whichever occurs first, PART I of this bulletin must be accomplished within the next 10 flight hours from the Revision 01 issuance date of this bulletin, and repeated at each 600 flight cycles or 750 flight hours, whichever occurs first. (b) Applicable to Group 2 

# SERVICE BULLETIN ALERT

ALERT DATE: 23/Jun/2014 REVISION No.: 03 -27/Jun/2014 SB No.: 190-54-A015 PAGE: 3 Copyright © 2014 by Embraer S.A. All rights reserved.For aircraft that have reached less than 600 flight cycles and less than 750 flight hours, PART I of this bulletin must be accomplished within the next 50 flight hours after the first issuance of this bulletin, and repeated at each 600 flight cycles or 750 flight hours, whichever occurs first. For aircraft that have reached more than 600 flight cycles or more than 750 flight hours, whichever occurs first, PART I of this bulletin must be accomplished within the next 10 flight hours from the Revision 01 issuance date of this bulletin, and repeated at each 600 flight cycles or 750 flight hours, whichever occurs first. (2) Applicable to PART II (a) Applicable to Group 1 For aircraft that have reached less than 600 flight cycles and less than 750 flight hours after the SB 190-54-0013 incorporation, PART II of this bulletin must be accomplished within the next 50 flight hours after the first issuance of this bulletin, and repeated at each 600 flight cycles or 750 flight hours, whichever occurs first. For aircraft that have reached more than 600 flight cycles or more than 750 flight hours after the SB 190-54-0013 incorporation, whichever occurs first, PART II of this bulletin must be accomplished within the next 10 flight hours from the Revision 01 issuance date of this bulletin, and repeated at each 600 flight cycles or 750 flight hours, whichever occurs first. (b) Applicable to Group 2 For aircraft that have reached less than 600 flight cycles and less than 750 flight hours, PART II of this bulletin must be accomplished within the next 50 flight hours after the first issuance of this bulletin, and repeated at each 600 flight cycles or 750 flight hours, whichever occurs first. For aircraft that have reached more than 600 flight cycles or more than 750 flight hours, whichever occurs first. PART II of this bulletin must be accomplished within the next 10 flight hours from the Revision 01 issuance date of this bulletin, and repeated at each 600 flight cycles or 750 flight hours, whichever occurs first. 

# SERVICE BULLETIN ALERT

ALERT SB No.: 190-54-A015 PAGE: 4 DATE: 23/Jun/2014 REVISION No.: 03 -27/Jun/2014 Copyright © 2014 by Embraer S.A. All rights reserved.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. H. 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 – 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. 

# SERVICE BULLETIN ALERT

ALERT DATE: 23/Jun/2014 REVISION No.: 03 -27/Jun/2014 SB No.: 190-54-A015 PAGE: 5 Copyright © 2014 by Embraer S.A. All rights reserved.– Inspection: None. – Modification: 0.5 man-hours. – Access closure: 0.5 man-hours. – Test: None. I. REFERENCES AMM 190/( ) Aircraft Maintenance Manual PART II - 20-00-00 - STANDARD PRACTICES-AIRFRAME. AMM 190/( ) Aircraft Maintenance Manual PART II - 54-50-22 - NACELLES/PYLONS. J. OTHER PUBLICATIONS AFFECTED None. 

# SERVICE BULLETIN ALERT

ALERT SB No.: 190-54-A015 PAGE: 6 DATE: 23/Jun/2014 REVISION No.: 03 -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 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 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.: 03 -27/Jun/2014 SB No.: 190-54-A015 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 could 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 AR 7 F-925-YELLOW TORQUE SEAL Torque Seal F-925-YELLOW TORQUE SEAL AR 6/ [1]
ARDROX AV-15 Corrosion Inhibiting Compound ARDROX AV-15 AR 6/ [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 7 = Replace with part bearing same PN QUANTITY: AR = As Required D. MATERIAL NECESSARY FOR EACH SPARE None. 

# SERVICE BULLETIN ALERT

ALERT SB No.: 190-54-A015 PAGE: 8 DATE: 23/Jun/2014 REVISION No.: 03 -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.: 03 -27/Jun/2014 SB No.: 190-54-A015 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 - RE-TORQUE OF THE LH LOWER INBOARD AND OUTBOARD LINK FITTING (1) Remove the LH pylon side fairings. Refer to Figure 1 and 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 1

. (3) Install the LH 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 to install the side fairings without the installation of the aerodynamic sealant until EMBRAER issues a permanent solution for this case. 

# SERVICE BULLETIN ALERT

ALERT SB No.: 190-54-A015 PAGE: 10 DATE: 23/Jun/2014 REVISION No.: 03 -27/Jun/2014 Copyright © 2014 by Embraer S.A. All rights reserved.C. PART II - RE-TORQUE OF THE RH LOWER INBOARD AND OUTBOARD LINK FITTING (1) Remove the RH pylon side fairings. Refer to Figure 1 and 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 1

. (3) Install the RH 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 to install the side fairings without the installation of the aerodynamic sealant until EMBRAER issues a permanent solution for this case. D. Put the aircraft back to a serviceable condition. E. Write the accomplishment of PART I and/or PART II 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 technical 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 ALERT

ALERT DATE: 23/Jun/2014 REVISION No.: 03 -27/Jun/2014 SB No.: 190-54-A015 PAGE: 11 Copyright © 2014 by Embraer S.A. All rights reserved.1. Remove the lock wire PN MS20995C32 from lock nut. Refer to Details B and C

. 2. Remove and keep 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 torque of 169.47 N.m (1,500 lb.in) at lock nut. After that, adjust the lock nut position as indicated at Details B , C , D , and E

. NOTE: 1) The final torque must not exceed 225.97 N.m (2,000 lb.in). 2) With pressure plier fix the lock washer at pylon structure to avoid rotation, and consequential damages, while torque is applied. 3) Ensure that at least one full threads 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. Install 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.: 190-54-A015 PAGE: 12 DATE: 23/Jun/2014 REVISION No.: 03 -27/Jun/2014 FIGUR E 1 - FIGURE TITLE (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.)EM170SB540295A.DGN 

# SERVICE BULLETIN ALERT

ALERT DATE: 23/Jun/2014 REVISION No.: 03 -27/Jun/2014 SB No.: 190-54-A015 PAGE: 13 FIGUR E 1 - FIGURE TITLE (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.: 190-54-A015 PAGE: 14 DATE: 23/Jun/2014 REVISION No.: 03 -27/Jun/2014 FIGUR E 1 - FIGURE TITLE (SHEET 03 OF 04)

Copyright © 2014 by Embraer S.A. All rights reserved.EM170SB540297A.DGN 

### D D ACCEPTABLE CONDITION 30° (REF.) PARALLEL 22° (REF.)



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

22° (REF.) NOMINAL CONDITION

NOMINAL CONDITION 

# SERVICE BULLETIN ALERT

ALERT DATE: 23/Jun/2014 REVISION No.: 03 -27/Jun/2014 SB No.: 190-54-A015 PAGE: 15 FIGUR E 1 - FIGURE TITLE (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. 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.