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) 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.: 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.