# SERVICE BULLETIN

DATE: 03/Jul/2014 S B No.: 190LIN-54-0006 REVISION No.: PAGE: 1 of 2 3 Copyright © 2014 by Embraer S.A. All rights reserved. N A CELLES/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 a n d expressly disclaims any warranty of merchantability or fitness for a particular purpose.

TH IS BULLETIN SUPERSEDES ALERT SB190LIN-54-A006.

1. PLANNING INFORMATION
A. SB EFFECTIVITY

Aircraft affected: The SB effectivity is divided into GROUPS of aircraft, as follows: (1) GROUP 1

MODEL SN EMBRAER 190 ECJ 19000109, 19000140, 19000159, 19000177, 19000203,

1 9000225, 19000236, 19000243, 19000261, 19000278, 19000296, 19000307, 19000317, 19000362, 19000438,19000453, 19000534, 19000559, and 19000571, if POSTMOD SB 190LIN-54-0004.

(2) GROUP 2

MODEL SN EMBRAER 190 ECJ 19000611, 19000632, and 19000641.

(3) GROUP 3

MODEL SN EMBRAER 190 ECJ 19000109, 19000140, 19000159, 19000177, 19000203,

1 9000225, 19000236, 19000243, 19000261, 19000278, 19000296, 19000307, 19000317, 19000362, 19000438, 19000453, 19000534, 19000559, and 19000571, if PRE-MOD SB 190LIN-54-0004

# SERVICE BULLETIN

SB No.: 190LIN-54-0006 DATE: 03/Jul/2014 PAGE: 2 REVISION No.: Copyright © 2014 by Embraer S.A. All rights reserve d. In-production effectivity:
EMBRAER 190 Embraer Corporate Jet (ECJ) model aircr aft SN 19000656 and on have an equivalent modification factory-incorporate d.

B. CONCURRENT REQUIREMENTS

None.

C. REASON (1) HISTORY Embraer received reports about loose pylon lower li nk fitting assembly which can cause failure to one of the fittings and consequent ly, the separation of the engine from the wing.

(2) OBJECTIVE To replace the lower link fitting inboard and outbo ard attaching parts of the LH and RH pylon. Also, to apply the necessary re-torqu e to the inboard and outboard lower link fittings assy.

(3) EXPECTED BENEFITS This modification is aimed at preventing the loss o f the shear pins of the pylon outboard and inboard lower link fittings.

(4) REVISION HISTORY None.

# SERVICE BULLETIN

DATE: 03/Jul/2014 SB No.: 190LIN-54-0006 REVISION No.: PAGE: 3 Copyright © 2014 by Embraer S.A. All rights reserve d. 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 bullet in consists of replacing the LH lower link fitting inboard and outboard attaching p arts. 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 bulle tin consists of replacing the RH lower link fitting inboard and outboard attaching p arts. 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 bull etin 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.

# SERVICE BULLETIN

SB No.: 190LIN-54-0006 DATE: 03/Jul/2014 PAGE: 4 REVISION No.: Copyright © 2014 by Embraer S.A. All rights reserve d. 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 bulle tin 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 60 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 60 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) Applicable to GROUPS 1 and 2

Embraer recommends that PART III of this bulletin b e accomplished in the next 6000 Flight Cycle(s) or 7500 Flight Hour(s), whiche ver occurs first, after the accomplishment of PART I of this bulletin, and repe ated at each 2000 Flight Cycle(s) or 7500 Flight Hour(s), whichever occurs f irst.

(b) Applicable to GROUP 3

# SERVICE BULLETIN

DATE: 03/Jul/2014 SB No.: 190LIN-54-0006 REVISION No.: PAGE: 5 Copyright © 2014 by Embraer S.A. All rights reserve d. Embraer recommends that PART III of this bulletin b e accomplished in the next 6000 Flight Cycle(s) or 7500 Flight Hour(s), whiche ver occurs first, from the first issue date of this bulletin, and repeated at each 2 000 Flight Cycle(s) or 7500 Flight Hour(s), whichever occurs first.

(4) APPLICABLE TO PART IV (a) Applicable 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), whiche ver occurs first, after the accomplishment of PART II of this bulletin, and rep eated at each 2000 Flight Cycle(s) or 7500 Flight Hour(s), whichever occurs f irst. (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), whiche ver occurs first, after the accomplishment of PART II of this bulletin, and rep eated at each 2000 Flight Cycle(s) or 7500 Flight Hour(s), whichever occurs f irst.

F. APPROVAL The technical aspects of this Service Bulletin are approved by: ANAC – Agência Nacional de Aviação Civil.

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

or repair ithat is not from EMBRAER and which affec ts 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 estimate is for direct labor only, performed b y experienced personnel, and does not include the time to plan, prepare, or inspect t he 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.

# SERVICE BULLETIN

SB No.: 190LIN-54-0006 DATE: 03/Jul/2014 PAGE: 6 REVISION No.: Copyright © 2014 by Embraer S.A. All rights reserve d. (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.

(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.

# SERVICE BULLETIN

DATE: 03/Jul/2014 SB No.: 190LIN-54-0006 REVISION No.: PAGE: 7 Copyright © 2014 by Embraer S.A. All rights reserve d. H. WEIGHT AND BALANCE

None.

I. ELECTRICAL LOAD DATA

None.

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

STANDARD PRACTICES-AIRFRAME. AMM 190LIN/( ) Aircraft Maintenance Manual PART II - 54-50-22 -

NACELLES/PYLONS.
SB190LIN-54-0004 - NACELLES/PYLONS - INSTALLATION O F LOCK ASSEMBLY

AT INBOARD AND OUTBOARD LOWER LINK FITTING

K. OTHER PUBLICATIONS AFFECTED AIPC 190LIN/( ) Aircraft Illustrated Parts Catalog - 54-50-00 and 54-50-02 -

NACELLES/PYLONS. AMM 190LIN/( ) Aircraft Maintenance Manual PART II - 54-50-00 -

NACELLES/PYLONS.
SB190LIN-54-A006 - NACELLES/PYLONS - RETORQUE OF TH E LH/RH INBOARD

AND OUTBOARD LOWER LINK FITTINGS

# SERVICE BULLETIN

SB No.: 190LIN-54-0006 DATE: 03/Jul/2014 PAGE: 8 REVISION No.: Copyright © 2014 by Embraer S.A. All rights reserve d. 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 (1) WARRANTY COVERAGE (a) Parts The SB Material will be provided at no charge.

(b) Labor 1. APPLICABLE TO PART I THRU IV Embraer will compensate 1.5 hours for the SB incorp oration if it is performed in an Embraer authorized service center.

(c) Expiration The terms expressed in the warranty coverage will b e valued for 36 months after the SB issue date.

# SERVICE BULLETIN

DATE: 03/Jul/2014 SB No.: 190LIN-54-0006 REVISION No.: PAGE: 9 Copyright © 2014 by Embraer S.A. All rights reserve d. 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 altern ative or similar parts are approved by Embraer. Refer to IPC Optional PN Cross-Reference L ist. The expendable or consumable parts presented in the AMM Tasks referred to in this bulletin, which are necessary for its accomplishmen t, should be procured from the operator's inventories or ordered as spares. The complementary information, when necessary, is p resented 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 operato r’s inventories or manufacturer or locally purchased, or ordered as sp ares from Embraer
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

S24665-374 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 d uring the accomplishment of PART III and PART IV of this bull etin.

# SERVICE BULLETIN

SB No.: 190LIN-54-0006 DATE: 03/Jul/2014 PAGE: 10 REVISION No.: Copyright © 2014 by Embraer S.A. All rights reserve d. (b) Consumables The material below or equivalent, required for the accomplishment of this bulletin, should be procured from the operator’s in ventories or from a local supplier.

ITEM PN DESCRIPTION QTY DISP/ Notes ARDROX AV-15 Corrosion Inhibiting Compound AR 6/ (a) (a) Corrosion Inhibiting Compound, Type III (MEP 10-063 ) ARDROX AV-15

QUANTITY : AR = As Required.

DISPOSITION : 2 = Incorporate part bearing NEW PN 3 = Replace part bearing OLD PN with part bearing N EW PN 6 = Apply as required 7 = Replace with part bearing same PN

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

DATE: 03/Jul/2014 SB No.: 190LIN-54-0006 REVISION No.: PAGE: 11 Copyright © 2014 by Embraer S.A. All rights reserve d. 3. ACCOMPLISHMENT INSTRUCTIONS
NOTES : 1) Obey all of the WARNINGS and CAUTIONS included i n the referenced

manuals and procedures. 2) The Manuals and other documents are referred to by means of acronyms or using a simplified form. Refer to section “1. I. REFERENCES” for a more complete definition. 3) This Service Bulletin effectivity is divided int o 4 aircraft GROUPS according to the relevant configuration and the SB itself is divided into 4 PARTS. The SB PARTS are featured to allow their ind ependent 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 maintena nce. Refer to AMM TASK 20-00-00- 910 -801-A/200 - Aircraft Maintenance Safety Proced ures - 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 AM M TASK 54-50-22-400-801-A/400 - Pylon Side Fairings - Installation.

# SERVICE BULLETIN

SB No.: 190LIN-54-0006 DATE: 03/Jul/2014 PAGE: 12 REVISION No.: Copyright © 2014 by Embraer S.A. All rights reserve d. 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 A ND 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 AM M 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 Lin k Fitting. Refer to Figure 2. (3) Install the LH pylon side fairings. Refer to AM M 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

DATE: 03/Jul/2014 SB No.: 190LIN-54-0006 REVISION No.: PAGE: 13 Copyright © 2014 by Embraer S.A. All rights reserve d. (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 Lin k Fitting. Refer to Figure 2.

(3) Install the RH pylon side fairings. Refer to AM M 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. Restore the aircraft to the normal condition. G. Enter the accomplishment of PART I and/or PART I I and/or PART III and/or PART IV of this bulletin in the applicable documents. H. Fill out the attached “Service Bulletin Implemen tation and Evaluation” form and return it to:

EMBRAER S.A.

Customer Support Contact Center Embraer Executive Jets lineage.reliability@embraer.com

24/7 Toll Free Numbers 1 888 362-2648 USA & Canada 0800 704 1099 Brazil

24/7 International Numbers 1 703 621-7350 North America, including Mexico, & C aribbean +33 1 7048-0510 Europe, Middle East & Africa +65 6307-7647 Asia Pacific +55 12 3927-7000 Latin America

NOTE : To formally inform that the SB has been incorporat ed in the aircraft or that the

SB will not be incorporated, so that Embraer can up date the affected technical publications, use the “Service Bulletin Full-Fleet Incorporation Report” form, which is available on the Flyembraer portal (http:/ /www.flyembraer.com ).

# SERVICE BULLETIN

SB No.: 190LIN-54-0006 DATE: 03/Jul/2014 PAGE: 14 REVISION No.: Copyright © 2014 by Embraer S.A. All rights reserve d. 1. Remove the attachment parts of the LH/RH lower l ink 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 2U2 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 p osition). Refer to Detail B (PreMod). (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 D etail B (Pre-Mod). 2. Install the new attachment parts of the LH/RH lo wer link fitting outboard as follows: (a) Install the washer PN NAS1149C1432R. Refer to D etail B (Post-Mod). NOTE: Install a minimum of one washer PN NAS1149C1432R a nd a maximum of three washers PN NAS1149C1432R for each assembly. (b) Install castle nut PN PE22072L14 (1 position) a s shown in Detail B (Post-Mod) and apply torque as follows: NOTE: Make sure that the fuse pin does not turn when you apply the torque. If necessary, safety the other side of the fuse pin wi th 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 - 6 7.79 N.m (70 - 600 lb.in). NOTE: If the castle nut PN PE22072L14 is not in the corr ect range, replace it with new one with the same part number. 3. Add the drag torque value measured in 2.(b)1 Figur e 1 to the standard torque of 112.98 - 225.97 N.m (1000 - 2000 lb.in) to get t he final torque. 4. Apply the final torque to the castle nut PN PE2207 2L14 with a torque wrench. Refer to AMM TASK 20-10-01-910-801-A/200 - Bolt Tor que Data - Maintenance Practices.

FIGURE 1 - LH/RH LOWER LINK FITTING INBOARD AND OUT BOARDATTACHMENT PARTS - REPLACEMENT (SHEET 01 OF 06)

# SERVICE BULLETIN

DATE: 03/Jul/2014 SB No.: 190LIN-54-0006 REVISION No.: PAGE: 15 Copyright © 2014 by Embraer S.A. All rights reserve d. (c) Install the cotter pin PN MS24665-374 (1 positi on). 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 l ink 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 po sition). Refer to Detail C (PreMod). (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 lo wer link fitting inboard as follows: (a) Install the washer PN NAS1149C1432R. Refer to D etail C (Post-Mod). NOTE: Install a minimum of one washer PN NAS1149C1432R an d a maximum of three washers PN NAS1149C1432R for each assembly. (b) Install castle nut PN PE22072L14 (1 position) a s shown in Detail C (Post-Mod) and apply torque as follows: NOTE: Make sure that the fuse pin does not turn when you apply the torque. If necessary, safety the other side of the fuse pin wi th 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 - 6 7.79 N.m (70 - 600 lb.in).

FIGURE 1 - LH/RH LOWER LINK FITTING INBOARD AND OUT BOARDATTACHMENT PARTS - REPLACEMENT (SHEET 02 OF 06)

# SERVICE BULLETIN

SB No.: 190LIN-54-0006 DATE: 03/Jul/2014 PAGE: 16 REVISION No.: Copyright © 2014 by Embraer S.A. All rights reserve d. NOTE: If the castle nut PN PE22072L14 is not in the corre ct range, replace it with new one with the same part number. 3. Add the drag torque value measured in 4.(b)1 Figur e 1 to the standard torque of 112.98 - 225.97 N.m (1000 - 2000 lb.in) t o get the final torque. 4. Apply the final torque to the castle nut PN PE2207 2L14 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 positi on). 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).

FIGURE 1 - LH/RH LOWER LINK FITTING INBOARD AND OUT BOARDATTACHMENT PARTS - REPLACEMENT (SHEET 03 OF 06)

# SERVICE BULLETIN

DATE: 03/Jul/2014 SB No.: 190LIN-54-0006 REVISION No.: PAGE: 17 Copyright © 2014 by Embraer S.A. All rights reserve d.EM170SB540307A.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

FIGURE 1 - LH/RH LOWER LINK FITTING INBOARD AND OUT BOARDATTACHMENT PARTS - REPLACEMENT (SHEET 04 OF 06)

# SERVICE BULLETIN

SB No.: 190LIN-54-0006 DATE: 03/Jul/2014 PAGE: 18 REVISION No.: Copyright © 2014 by Embraer S.A. All rights reserve d. 

### 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) 1 2 4 2

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.EM170SB540308A.DGN APPLICABLE TO GROUPS 1 AND 2.

FIGURE 1 - LH/RH LOWER LINK FITTING INBOARD AND OUT BOARDATTACHMENT PARTS - REPLACEMENT (SHEET 05 OF 06)

# SERVICE BULLETIN

DATE: 03/Jul/2014 SB No.: 190LIN-54-0006 REVISION No.: PAGE: 19 Copyright © 2014 by Embraer S.A. All rights reserve d. 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)EM170SB540309A.DGN POST − MOD LOCK WIRE PN MS20995C32 (REMOVE AND DISCARD)

APPLICABLE TO GROUPS 1 AND 2.

FIGURE 1 - LH/RH LOWER LINK FITTING INBOARD AND OUT BOARDATTACHMENT PARTS - REPLACEMENT (SHEET 06 OF 06)

# SERVICE BULLETIN

SB No.: 190LIN-54-0006 DATE: 03/Jul/2014 PAGE: 20 REVISION No.: Copyright © 2014 by Embraer S.A. All rights reserve d. 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 posit ion) as shown in Detail B and do the steps that follows: NOTE: Make sure that the fuse pin does not turn when you apply the torque. If necessary, safety the other side of the fuse pin wi th 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 - 6 7.79 N.m (70 - 600 lb.in). NOTE: If the castle nut PN PE22072L14 is not in the corre ct range, replace it with new one with the same part number. 4. Add the drag torque value measured in 1.(b)2 Figur e 2 to the standard torque of 112.98 - 225.97 N.m (1000 - 2000 lb.in) t o get the final torque. 5. Apply the final torque to the castle nut PN PE2207 2L14 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 positi on). 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.

FIGURE 2 - RE-TORQUE OF THE LH/RH LOWER INBOARD AND OUTBOARD LINK FITTING CASTLE NUT (SHEET 01 OF 04)

# SERVICE BULLETIN

DATE: 03/Jul/2014 SB No.: 190LIN-54-0006 REVISION No.: PAGE: 21 Copyright © 2014 by Embraer S.A. All rights reserve d. (b) Re-torque the castle nut PN PE22072L14 (1 posit ion) as shown in Detail C and do the steps that follows: NOTE: Make sure that the fuse pin does not turn when you apply the torque. If necessary, safety the other side of the fuse pin wi th 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 - 6 7.79 N.m (70 - 600 lb.in). NOTE: If the castle nut PN PE22072L14 is not in the corre ct range, replace it with new one with the same part number. 4. Add the drag torque value measured in 2.(b)2 Figur e 2 to the standard torque of 112.98 - 225.97 N.m (1000 - 2000 lb.in) t o get the final torque. 5. Apply the final torque to the castle nut PN PE2207 2L14 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 positi on). 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.

FIGURE 2 - RE-TORQUE OF THE LH/RH LOWER INBOARD AND OUTBOARD LINK FITTING CASTLE NUT (SHEET 02 OF 04)

# SERVICE BULLETIN

SB No.: 190LIN-54-0006 DATE: 03/Jul/2014 PAGE: 22 REVISION No.: Copyright © 2014 by Embraer S.A. All rights reserve d. 

### 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.)

TYPICALEM170SB540310A.DGN

FIGURE 2 - RE-TORQUE OF THE LH/RH LOWER INBOARD AND OUTBOARD LINK FITTING CASTLE NUT (SHEET 03 OF 04)

# SERVICE BULLETIN

DATE: 03/Jul/2014 SB No.: 190LIN-54-0006 REVISION No.: PAGE: 23 Copyright © 2014 by Embraer S.A. All rights reserve d. 

### B PYLON FITTINGS (REF.)

1 2 3

1 1 WASHER (REF.)

CASTLE NUT (REF.)

COTTER PIN PN MS24665−374 (REMOVE AND DISCARD) (INSTALL)

PYLON FITTINGS (REF.) 

### C 1 2

1 2 3

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).EM170SB540311A.DGN

FIGURE 2 - RE-TORQUE OF THE LH/RH LOWER INBOARD AND OUTBOARD LINK FITTING CASTLE NUT (SHEET 04 OF 04). . .



### SERVICE BULLETIN IMPLEMENTATION AND EVALUATION FORM

The purpose of this form is to collect data that wi ll be used to improve the quality of our Service Bu lletins and Reliability Program. Please fill in this form and return it to: EMBRAER S.A. Customer Support Contact Center Embraer Executive Jets lineage.reliability@embraer.com

24/7 Toll Free Numbers 1 888 362-2648 USA & Canada 0800 704 1099 Brazil

24/7 International Numbers 1 703 621-7350 North America, including Mexico, & C aribbean +33 1 7048-0510 Europe, Middle East & Africa +65 6307-7647 Asia Pacific +55 12 3927-7000 Latin America
SB Number/Revision: SB Title:
SB190LIN-54-0006R00 REPLACEMENT OF THE LOWER LINK FITTING INBOARD AND OUTBOARD ATTACHING PARTS
SB Implementation Report Aircraft Serial Number or Registration Number: Inco rporation Date:

Aircraft Flight Hours: Aircraft Landings:

SB 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 o f incorporation, suggested improvements,...)

Company/ Service Center: Fax: Phone:

Address:

E-mail: Prepared by: (Name/Title) Date: