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 INFORMATION

2.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

FIGURE 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

FIGURE 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) E

EM170SB540299E.DGN

3 6

2 4

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

FIGURE 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

FIGURE 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.