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 SB190-54-A015.

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,

19000633 thru 19000640, 19000642 thru 19000655, and

19000657 thru 19000673.

SERVICE BULLETIN

DATE: 03/Jul/2014

REVISION No.:

SB No.: 190-54-0015

PAGE: 1 of 23

Copyright © 2014 by Embraer S.A. All rights reserved.
(3) GROUP 3

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 PRE-MOD SB190-54-0013.

In-production effectivity:

Embraer 190( ) and 195( ) model aircraft SN 19000674 and on have an equivalent

factory-included modification.

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.

SERVICE BULLETIN

SB No.: 190-54-0015

PAGE: 2

DATE: 03/Jul/2014

REVISION No.:

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

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.

SERVICE BULLETIN

DATE: 03/Jul/2014

REVISION No.:

SB No.: 190-54-0015

PAGE: 3

Copyright © 2014 by Embraer S.A. All rights reserved.
To do this, it is necessary to get access to the LH pylon at zone 419 and remove skin

fairing.

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 150

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 150

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) Aplicable 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 6000 Flight

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

(b) Applicable to GROUP 3

SERVICE BULLETIN

SB No.: 190-54-0015

PAGE: 4

DATE: 03/Jul/2014

REVISION No.:

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 6000 Flight Cycle(s) or 7500

Flight Hour(s), whichever occurs first.

(4) Applicable to PART IV

(a) Aplicable 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 6000 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, from the first

issue date of this bulletin, and repeated at each 6000 Flight Cycle(s) or 7500

Flight Hour(s), whichever occurs first.

F. APPROVAL

The technical aspects of this Service Bulletin are approved by: Agência Nacional de

Aviação Civil (ANAC).

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

repair that 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 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.

SERVICE BULLETIN

DATE: 03/Jul/2014

REVISION No.:

SB No.: 190-54-0015

PAGE: 5

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

– 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.

SERVICE BULLETIN

SB No.: 190-54-0015

PAGE: 6

DATE: 03/Jul/2014

REVISION No.:

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

H. WEIGHT AND BALANCE

None.

I. SOFTWARE ACCOMPLISHMENT SUMMARY

None.

J. REFERENCES

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

STANDARD PRACTICES-AIRFRAME.

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

NACELLES/PYLONS.

K. OTHER PUBLICATIONS AFFECTED

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

NACELLES/PYLONS.

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

NACELLES/PYLONS.

SERVICE BULLETIN

DATE: 03/Jul/2014

REVISION No.:

SB No.: 190-54-0015

PAGE: 7

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 acquired from the operator’s inventories or

manufacturer or locally purchased, or ordered as spares from Embraer at no

charge to the operator during a period of 36 months after the original release

date of this service bulletin.

SERVICE BULLETIN

SB No.: 190-54-0015

PAGE: 8

DATE: 03/Jul/2014

REVISION No.:

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

MS24665-374 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.

(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.

Applicable to all PARTS

NEW PN DESCRIPTION OLD PN QTY DISP/

Notes

ARDROX AV-15 Corrosion Inhibiting

Compound

- AR 6/ [1]

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

DISPOSITION: 2 = Incorporate part bearing NEW PN

SERVICE BULLETIN

DATE: 03/Jul/2014

REVISION No.:

SB No.: 190-54-0015

PAGE: 9

Copyright © 2014 by Embraer S.A. All rights reserved.
3 = Replace part bearing OLD PN with 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.

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

SB No.: 190-54-0015

PAGE: 10

DATE: 03/Jul/2014

REVISION No.:

Copyright © 2014 by Embraer S.A. All rights reserved.
3. ACCOMPLISHMENT INSTRUCTIONS

NOTE: 1) Obey all of the WARNINGS and CAUTIONS included in the mentioned manuals

and procedures.

2) The Manuals and other documents are mentioned as acronyms or with a

simplified form. Refer to section 1.J. REFERENCES for a more complete

definition.

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

the related configuration and the SB itself is divided into 4 PARTS. The SB

PARTS division allows 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

DATE: 03/Jul/2014

REVISION No.:

SB No.: 190-54-0015

PAGE: 11

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

SB No.: 190-54-0015

PAGE: 12

DATE: 03/Jul/2014

REVISION No.:

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. Put the aircraft back to a serviceable condition.

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

DATE: 03/Jul/2014

REVISION No.:

SB No.: 190-54-0015

PAGE: 13

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 ′′U′′ 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

(Pre-Mod).

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

necessary, safety the other side of the shear 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.

SERVICE BULLETIN

SB No.: 190-54-0015

PAGE: 14

DATE: 03/Jul/2014

REVISION No.:

FIGURE 1 - LH/RH LOWER LINK FITTING INBOARD AND OUTBOARD ATTACHMENT PARTS - REPLACEMENT

(SHEET 01 OF 06)

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

(Pre-Mod).

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

necessary, safety the other side of the shear 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).

SERVICE BULLETIN

DATE: 03/Jul/2014

REVISION No.:

SB No.: 190-54-0015

PAGE: 15

FIGURE 1 - LH/RH LOWER LINK FITTING INBOARD AND OUTBOARD ATTACHMENT PARTS - REPLACEMENT

(SHEET 02 OF 06)

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).

SERVICE BULLETIN

SB No.: 190-54-0015

PAGE: 16

DATE: 03/Jul/2014

REVISION No.:

FIGURE 1 - LH/RH LOWER LINK FITTING INBOARD AND OUTBOARD ATTACHMENT PARTS - REPLACEMENT

(SHEET 03 OF 06)

Copyright © 2014 by Embraer S.A. All rights reserved.
EM170SB540301A.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

SERVICE BULLETIN

DATE: 03/Jul/2014

REVISION No.:

SB No.: 190-54-0015

PAGE: 17

FIGURE 1 - LH/RH LOWER LINK FITTING INBOARD AND OUTBOARD ATTACHMENT PARTS - REPLACEMENT

(SHEET 04 OF 06)

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)

2 124

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.

EM170SB540302A.DGN

APPLICABLE TO GROUPS 1 AND 2.

SERVICE BULLETIN

SB No.: 190-54-0015

PAGE: 18

DATE: 03/Jul/2014

REVISION No.:

FIGURE 1 - LH/RH LOWER LINK FITTING INBOARD AND OUTBOARD ATTACHMENT PARTS - REPLACEMENT

(SHEET 05 OF 06)

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)

EM170SB540303A.DGN

POST − MOD

LOCK WIRE

PN MS20995C32

(REMOVE AND DISCARD)

APPLICABLE TO GROUPS 1 AND 2.

SERVICE BULLETIN

DATE: 03/Jul/2014

REVISION No.:

SB No.: 190-54-0015

PAGE: 19

FIGURE 1 - LH/RH LOWER LINK FITTING INBOARD AND OUTBOARD ATTACHMENT PARTS - REPLACEMENT

(SHEET 06 OF 06)

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

necessary, safety the other side of the shear 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.

SERVICE BULLETIN

SB No.: 190-54-0015

PAGE: 20

DATE: 03/Jul/2014

REVISION No.:

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

(SHEET 01 OF 04)

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

necessary, safety the other side of the shear 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.

SERVICE BULLETIN

DATE: 03/Jul/2014

REVISION No.:

SB No.: 190-54-0015

PAGE: 21

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

(SHEET 02 OF 04)

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

EM170SB540304A.DGN

SERVICE BULLETIN

SB No.: 190-54-0015

PAGE: 22

DATE: 03/Jul/2014

REVISION No.:

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

(SHEET 03 OF 04)

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

PYLON FITTINGS

(REF.)

123

1 1

WASHER

(REF.)

CASTLE NUT

(REF.)

COTTER PIN

PN MS24665−374

(REMOVE AND DISCARD)

(INSTALL)

PYLON FITTINGS

(REF.)

C

2 1

123

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).

EM170SB540305A.DGN

SERVICE BULLETIN

DATE: 03/Jul/2014

REVISION No.:

SB No.: 190-54-0015

PAGE: 23

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

(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.