TRANSMITTAL LETTER

. 

TRANSMITTAL LETTER SB No.: 145LEG-53-A032 

PAGE: 1 of 1 

Copyright © 2013 by EMBRAER S.A. All rights reserved. 

1. DESCRIPTION 

This sheet transmits Revision 01 to Service Bulletin 145LEG-53-A032. 

This is a complete reissue of the Bulletin. 

This revision incorporates the information presented in the Information Notice related 

to the previous issues of this Service Bulletin, as listed below: 

None. 

2. ADDITIONAL ACTION 

Aircraft that have complied with the previous issue of this bulletin do not need any 

additional action. 

3. RECORD OF REVISION 

Original issue: 20/Sep/2013. 

Revision 01: 24/Sep/2013. 

4. HIGHLIGHTS 

The topics, affected pages, and a brief description of the content-related changes 

introduced by this revision are presented below. 

Revision bars are put in the left margin of each page to show the location of the 

significant changes. Text displacement and text format changes are not indicated. 

TOPIC/ PAGE DESCRIPTION OF REVISION 

1. PLANNING INFORMATION 

C. REASON/ 7 Included reason for Revision 01 

3. ACCOMPLISHMENT INSTRUCTIONS 

FIGURE 2/ 25 and 26. Updated illustration. 

A L E R T

SERVICE BULLETIN

DATE: 20/Sep/2013 SB No.: 145LEG-53-A032 

REVISION No.: 01 - 24/Sep/2013 PAGE: 1 of 24 

Copyright © 2013 by EMBRAER S.A. All rights reserved. 

FUSELAGE – INSPECTION AND REPLACEMENT OF ATTACHMENTS PARTS FROM 

THE COCKPIT WINDSHIELD CENTER POST LOWER EYELET FITTING 

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: 

MODEL SN 

EMB-135BJ 145412, 145462, 145484, 145495, 145505, 145516, 

145528, 145540, 145549, 145555, 145586, 145625, 

145637, 145642, 145644, 145678, 145686, 145699, 

145706, 145711, 145717, 145730, 145770, 145775, 

145780, 145789, 145796, 14500802, 14500809, 

14500818, 14500825, 14500832, 14500841, 

14500851, 14500854, 14500863, 14500867, 

14500873, 14500880, 14500884, 14500891, 

14500901, 14500903, 14500910, 14500913, 

14500916, 14500919, 14500925, 14500933, 

14500937, 14500939, 14500941, 14500942, 

14500944, 14500946, 14500948, 14500950, 

14500952, 14500954, 14500955, 

14500957, 14500960, 14500961, 14500963, 

14500965 thru 14500967, 14500969 thru 14500976, 

14500978 thru 14500983, 14500985, 14500986, 

14500988 thru 14500991, 14500993 thru 14500995, 

14500997 thru 14500999, 14501001 thru 

14501004, 14501006 thru 14501008, 14501010 thru 

14501012,14501014 thru 14501018, 14501020, 
A L E R T

SERVICE BULLETIN

SB No.: 145LEG-53-A032 DATE: 20/Sep/2013 

PAGE: 2 REVISION No.: 01 - 24/Sep/2013 

Copyright © 2013 by EMBRAER S.A. All rights reserved. 

MODEL SN 

EMB-135BJ 14501021, 14501023, 14501025, 14501026, 

14501029, 14501031, 14501032, 14501034, 

14501035, 14501037 thru 14501039, 14501041, 

14501042, 14501044 thru 14501046, 14501048, 

14501049, 14501051, 14501052, 14501054, 

14501055, 14501057, 14501058, 14501060 thru 

14501062, 14501064, 14501066, 14501067, 

14501069, 14501071, 14501072, 14501074, 

14501075, 14501078 thru 14501080, 14501082, 

14501083, 14501086, 14501087, 14501089 thru 

14501092, 14501094 thru 14501096, 14501098 

thru 14501100, 14501102, 14501105 thru 

14501107, 14501109 thru 14501111, 14501113, 

14501114, 14501117 thru 14501123, 14501126 

thru 14501128, 14501131 thru 14501134, 

14501136 thru 14501152, 14501154 thru 

14501158, 14501160 thru 14501169, 14501171 

thru 14501174, 14501176, 14501181, 14501184, 

and 14501187. 

Affected component: 

None. 

In-production effectivity: 

EMB-135BJ model aircraft SN 14501103, 14501115, 14501170, 14501175, 

14501179, 14501180, 14501182, 14501183, 14501188 thru 14501210, 14501212 

thru 14501227, and 14501229 thru 14501249 and on have an equivalent modification 

factory-incorporated. 
A L E R T

SERVICE BULLETIN

DATE: 20/Sep/2013 SB No.: 145LEG-53-A032 

REVISION No.: 01 - 24/Sep/2013 PAGE: 3 

Copyright © 2013 by EMBRAER S.A. All rights reserved. 

The SB effectivity is divided into GROUPS of aircraft, as follows: 

(1) GROUP 1 

MODEL SN 

EMB-135BJ 145412, 145462, 145484, 145495, 145505, 145516, 145528, 

145540, 145549, 145555, 145586, 145591, 145625, 145637, 

145642, 145644, 145678, 145686, 145699, 145706, 145711, 

145717, 145730, 145770, 145775, 145780, 145789, 145796, 

14500802, 14500809, 14500818, 14500825, 14500832, 14500841, 

14500851, and 14500854 which have accomplished with

SB145LEG-53-0021. 

(2) GROUP 2 

MODEL SN 

EMB-135BJ 14500863, 14500867, 14500873, 14500880, 14500884, 14500891, 

14500901, 14500903, 14500910, 14500913, 14500916, 14500919, 

14500925, 14500933, 14500937, 14500939, 14500941, 14500942, 

14500944, 14500946, 14500948, 14500950, 14500952, 14500954, 

14500955, 14500957, 14500960, 14500961, 14500963, 14500965 

thru 14500967, 14500969 thru 14500976, 14500978 thru 

14500983, 14500985, 14500986, 14500988 thru 14500991, 

14500993 thru 14500995, 14500997 thru 14500999, 14501001 thru 

14501004, 14501006 thru 14501008, 14501010 thru 14501012, 

14501014 thru 14501018, 14501020, 14501021, 14501023, 

14501025, 14501026, 14501029, 14501031, 14501032, 14501034, 

14501035, 14501037 thru 14501039, 14501041, 14501042, 

14501044 thru 14501046, 14501048, 14501049, 14501051, 

14501052, 14501054, 14501055, 14501057, 14501058, 14501060 

thru 14501062, 14501064, 14501066, 14501067, 14501069, 
A L E R T

SERVICE BULLETIN

SB No.: 145LEG-53-A032 DATE: 20/Sep/2013 

PAGE: 4 REVISION No.: 01 - 24/Sep/2013 

Copyright © 2013 by EMBRAER S.A. All rights reserved. 

MODEL SN 

EMB-135BJ 14501071, 14501072, 14501074, 14501075, 14501078 thru 

14501080, 14501082, 14501083, 14501086, 14501087, 14501089 

thru 14501092, 14501094 thru 14501096, 14501098 thru 

14501100, 14501102, 14501105 thru 14501107, 14501109 thru 

14501111, 14501113, 14501114, 14501117 thru 14501123, 

14501126 thru 14501128, 14501131 thru 14501134, 14501136 thru 

14501152, 14501154 thru 14501158, 14501160 thru 14501169, 

14501171 thru 14501174, 14501176, 14501181, 14501184, and 

14501187. 

B. CONCURRENT REQUIREMENTS 

None. 
A L E R T

SERVICE BULLETIN

DATE: 20/Sep/2013 SB No.: 145LEG-53-A032 

REVISION No.: 01 - 24/Sep/2013 PAGE: 5 

Copyright © 2013 by EMBRAER S.A. All rights reserved. 

C. REASON 

1. HISTORY 

During planned inspections of ERJ145 aircraft lower beam it was detected a 

failure of bolts that connect the forward fuselage center post eyelet (between 

windshields). Investigation indicates that this failure may have relation to the 

bolts fatigue strength, and therefore a dedicated action to ensure the structures’ 

integrity is required. 

2. OBJECTIVE 

To ensure the integrity of the four bolts that connect the forward fuselage center 

post eylet. 

3. EXPECTED BENEFITS 

The new bolts present higher mechanical properties and also better fatigue life, 

preventing eyelet fitting dettaching. 

4. REVISION HISTORY 

(a) Revision 01: Updated illustration. 
A L E R T

SERVICE BULLETIN

SB No.: 145LEG-53-A032 DATE: 20/Sep/2013 

PAGE: 6 REVISION No.: 01 - 24/Sep/2013 

Copyright © 2013 by EMBRAER S.A. All rights reserved. 

D. DESCRIPTION 

This Bulletin is divided into 2 PARTS, as follows: 

PART I INSPECTION OF THE CENTER POST FITTING ATTACHMENT PARTS.

Applicable to: GROUPS 1 and 2 aircraft. 

PART I of this bulletin presents an inspection for the integrity of the attaching parts of 

the cockpit windshield center post lower eyelet fitting. 

To gain access to the work area, it is necessary to remove the glareshield coverage, 

and the windshield center fairing. 

PART II REPLACEMENT OF THE CENTER POST FITTING ATTACHMENT 

PARTS.

Applicable to: GROUPS 1 and 2 aircraft. 

PART II of this bulletin consists in replacing the attachment parts of the cockpit 

windshield center post lower eyelet fitting. 

To gain access to the work area, it is necessary to remove the cockpit windshields, 

pilot and copilot seats, glareshield coverage, and the windshield center fairing. 
A L E R T

SERVICE BULLETIN

DATE: 20/Sep/2013 SB No.: 145LEG-53-A032 

REVISION No.: 01 - 24/Sep/2013 PAGE: 7 

Copyright © 2013 by EMBRAER S.A. All rights reserved. 

E. COMPLIANCE 

 (a) Applicable to GROUP 1 aircraft: 

For aircraft with more than 3000 flight cycles since the SB 145LEG-53-0021 

incorporation: 

- “PART I” of this bulletin is to be accomplished within the next 50 flight 

cycles from the date this bulletin was issued. 

- Thereafter, “PART I” of this bulletin is to be repeated every 50 flight cycles 

limited to maximum of 6 inspections, until “PART II” of this bulletin has 

been accomplished. 

For aircraft with less than 3000 flight cycles since the SB 145LEG-53-0021 

incorporation: 

PART II of this bulletin must be accomplished before the aircraft logs 3000 

flight cycles or the next 96 months check (or multiples), whichever occurs 

first. 

(b) Applicable to GROUP 2 aircraft: 

For aircraft with more than 3000 total flight cycles: 

- “PART I” of this bulletin is to be accomplished within the next 50 flight 

cycles from the date this bulletin was issued. 

- Thereafter, “PART I” of this bulletin is to be repeated every 50 flight cycles 

limited to maximum of 6 inspections, until “PART II” of this bulletin has 

been accomplished. 

For aircraft with less than 3000 total flight cycles: 

PART II of this bulletin must be accomplished before the aircraft logs 3000 

flight cycles or the next 96 months check (or multiples), whichever occurs 

first. 

F. APPROVAL 

The technical aspects of this Alert Service Bulletin are approved by: Embraer – 

Engineering Board. 
A L E R T

SERVICE BULLETIN

SB No.: 145LEG-53-A032 DATE: 20/Sep/2013 

PAGE: 8 REVISION No.: 01 - 24/Sep/2013 

Copyright © 2013 by EMBRAER S.A. All rights reserved. 

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 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: 1.0 man-hour. 

- Inspection: 0.5 man-hours. 

- Modification: None. 

- Access closure: 1.0 man-hour. 

- Test: none. 

2. APPLICABLE TO PART II 

- Access opening: 10.0 man-hours. 

- Inspection: 0.5 man-hours. 

- Modification: 1.5 man-hours. 

- Access closure: 22.0 man-hours. 

- Test: none. 
A L E R T

SERVICE BULLETIN

DATE: 20/Sep/2013 SB No.: 145LEG-53-A032 

REVISION No.: 01 - 24/Sep/2013 PAGE: 9 

Copyright © 2013 by EMBRAER S.A. All rights reserved. 

I. WEIGHT AND BALANCE 

- Change in basic weight: None 

- Change in basic moment: None 

J. ELECTRICAL LOAD DATA 

None. 

K. REFERENCES 

AMM-( ) – Aircraft Maintenance Manual – Chapter 32-00-01 – Landing Gear. 

AMM-( ) – Aircraft Maintenance Manual – Chapter 25-12-07 – Equipment and 

Furnishings. 

AMM-( ) – Aircraft Maintenance Manual – Chapter 25-12-01 – Equipment and 

Furnishings. 

AMM-( ) – Aircraft Maintenance Manual – Chapter 25-11-01 – Equipment and 

Furnishings. 

AMM-( ) – Aircraft Maintenance Manual – Chapter 25-12-15 – Equipment and 

Furnishings. 

AMM-( ) – Aircraft Maintenance Manual – Chapter 53-12-02 – Fuselage. 

AMM-( ) – Aircraft Maintenance Manual – Chapter 56-10-01 – Windows. 

L. OTHER PUBLICATIONS AFFECTED 

IPC-( ) – Illustrated Parts Catalog - Chapter 53-12-00 - Fuselage. 
A L E R T

SERVICE BULLETIN

SB No.: 145LEG-53-A032 DATE: 20/Sep/2013 

PAGE: 10 REVISION No.: 01 - 24/Sep/2013 

Copyright © 2013 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 

None. 
A L E R T

SERVICE BULLETIN

DATE: 20/Sep/2013 SB No.: 145LEG-53-A032 

REVISION No.: 01 - 24/Sep/2013 PAGE: 11 

Copyright © 2013 by EMBRAER S.A. All rights reserved. 

(2) MATERIAL TO BE PROCURED 

(a) Parts 

The parts below should be procured from the manufacturer or locally 

purchase, as indicated in the associated Note, or ordered as spares from 

Embraer. 

(1) Applicable to GROUPS 1 and 2 aircraft: 

NEW PN DESCRIPTION OLD PN QTY DISP/ 

Notes

MS14181-05018L Bolt NAS6405A17 04 3

MS21299-5 Washer MS21299-5K 08 3

MS21299-C5 Washer MS21299C5K 08 3

MS14182L05 Nut NAS1805-5 04 3

MS24665-302 Cotter pin MS24665-302 01 7

 (b) Consumables 

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. 

ITEM PN DESCRIPTION QTY DISP/ 

Notes

PR1776M B2 654 SEM 

KIT Interface sealant (AMS3281 CLASS B) AR 6 

COR-BAN 27L Corrosion Inhibitive Compound. 

(MEP 09-075) AR 6 
A L E R T

SERVICE BULLETIN

SB No.: 145LEG-53-A032 DATE: 20/Sep/2013 

PAGE: 12 REVISION No.: 01 - 24/Sep/2013 

Copyright © 2013 by EMBRAER S.A. All rights reserved. 

QUANTITY: 

AR = As Required. 

DISPOSITION:

3 = Replace part bearing OLD PN with part bearing NEW 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 

None. 
A L E R T

SERVICE BULLETIN

DATE: 20/Sep/2013 SB No.: 145LEG-53-A032 

REVISION No.: 01 - 24/Sep/2013 PAGE: 13 

Copyright © 2013 by EMBRAER S.A. All rights reserved. 

3. ACCOMPLISHMENT INSTRUCTIONS

NOTES: 1) For the purpose of this Service Bulletin, a General Visual Inspection 

(GVI) is: “A visual examination of an interior or exterior area, 

installation or assembly to detect obvious damage, failure or 

irregularity. This level of inspection is made from within touching 

distance, unless otherwise specified. A mirror may be necessary to 

enhance visual access to all exposed surfaces in the inspection 

area. This level of inspection is made under normally available 

lighting conditions such as daylight, hangar lighting, flashlight or 

drop-light and may require removal or opening of access panels or 

doors. Stands, ladders or platforms may be required to gain 

proximity to the area being checked.” 

2) Obey all of the WARNINGS and CAUTIONS included in the 

referenced manuals and procedures. 

3) 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. 

4) This Service Bulletin effectivity is divided into 02 aircraft GROUPS 

according to the relevant configuration and the SB itself is divided 

into 02 PARTS. The SB PARTS are featured to allow their 

independent accomplishment. 

REFERENCE APPLICATION TABLE 

Aircraft GROUPS SB PART APPLICABLE FIGURES 

1 and 2 I 1 

1 and 2 II 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. 
A L E R T

SERVICE BULLETIN

SB No.: 145LEG-53-A032 DATE: 20/Sep/2013 

PAGE: 14 REVISION No.: 01 - 24/Sep/2013 

Copyright © 2013 by EMBRAER S.A. All rights reserved. 

B. PART I - INSPECTION OF THE BOLTS OF THE COCKPIT WINDSHIELD 

CENTER POST LOWER EYELET FITTING. 

(1) Install the landing gear safety pin. Refer to the applicable “Aircraft Maintenance 

Manual” – Chapter 32-00-01 (TASK 32-00-01-910-801-A) – Landing Gear. 

(2) Remove and retain the glareshield coverage (223AZ) from the instrument 

panel. Refer to the applicable AMM 25-12-07 (TASK 25-12-07-000-801-A) - 

Glareshild Coverage. 

(3) Remove and retain the windshield center fairing. Refer to the applicable AMM 

25-12-01 (TASK 25-12-01-000-801-A) - Ceiling Lining. 

(4) Do the inpection on the bolts PN NAS6405A17, washers PN MS21299C5K, 

MS21299-5K and nuts NAS1805-5 that attaches the cockpit windshield center 

post eyelet fitting to the structure as follows: 

(a) If there is any sign of discrepancy on the bolts, washers and nuts replace the 

bolts washers and nuts of the cockpit windshield center post eyelet fitting 

immediately, according to PART II of this bulletin.

(b) If there is no discrepancy on bolts, washers and nuts, with the proper 

wrench, check if the bolts are tightened. 

(1) If the bolts are tightened, perform actions of inspection or replacement 

according limits defined in section E. COMPLIANCE. 

(2) If the bolt(s) are not tightened replace the bolts washers and nuts of the 

cockpit windshield center post eyelet fitting immediately, according to 

PART II of this bulletin. 

(5) Reinstall the retained glareshield coverage ( 223AZ) on its respective place on 

the instrument panel. Refer to the applicable AMM 25-12-07 (TASK 25-12-07-

400-801-A) - Glareshild Coverage. 

(6) Reinstall the retained windshield center fairing. Refer to the applicable AMM 

25-12-01 (TASK 25-12-01-400-801-A) - Ceiling Lining. 

(7) Put the aircraft back to its initial condition.

(8) Write the accomplishment of PART I of this bulletin in the applicable 

documents. 
A L E R T

SERVICE BULLETIN

DATE: 20/Sep/2013 SB No.: 145LEG-53-A032 

REVISION No.: 01 - 24/Sep/2013 PAGE: 15 

Copyright © 2013 by EMBRAER S.A. All rights reserved. 

(9) Fill out the attached “Service Bulletin Implementation and Evaluation” form and 

return it to: 

EMBRAER S.A. 

Customer Support Contact Center 

Embraer Executive Jets 

contact.center@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, & Caribbean 

+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 incorporated in the aircraft 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). 
A L E R T

SERVICE BULLETIN

SB No.: 145LEG-53-A032 DATE: 20/Sep/2013 

PAGE: 16 REVISION No.: 01 - 24/Sep/2013 

Copyright © 2013 by EMBRAER S.A. All rights reserved. 

C. PART II - BOLTS, WASHERS AND NUTS OF THE COCKPIT WINDSHIELD 

CENTER POST LOWER EYELET FITTING REPLACEMENT. 

(1) Install the landing gear safety pin. Refer to the applicable “Aircraft 

Maintenance Manual” – Chapter 32-00-01 (TASK 32-00-01-910-801-A) – 

Landing Gear. 

(2) Remove and retain the glareshield coverage ( 223AZ) from the instrument 

panel. Refer to the applicable AMM 25-12-07 (TASK 25-12-07-000-801-A) - 

Glareshild Coverage. 

(3) Remove and retain the windshield center fairing. Refer to the applicable AMM 

25-12-01 (TASK 25-12-01-000-801-A) - Ceiling Lining. 

(4) Remove and retain the cockpit windshields (LH and RH sides). Refer to the 

applicable AMM – Chapter 56-10-01 (TASK 56-10-01-000-801-A or TASK 56-

10-01-000-802-A, as applicable) – Windows. 

(5) Remove and retain the pilot and copilot seats. Refer to the applicable “Aircraft 

Maintenance Manual” – Chapter 25-11-01 (TASK 25-11-01-000-801-A) – Pilot 

Seats. 

(6) Move the LH and RH pedal assembly (backward or forward) to get access to 

the botton part of the work area. Refer to the applicable AOM - Section 2-02 

(TASK 2-02-05) - Pedal Adjustment. 

(7) Remove and retain the cockpit pedal covers. Refer to the applicable 

“Aircraft Maintenance Manual” – Chapter 25-12-15 (TASK 25-12-15-000-801-

A) – Cockpit Pedal Covers. 

(8) Replace the attachment parts of the cockpit windshield center post eyelet 

fitting according to Figure 2. 

(9) Reinstall the cockpit pedal covers. Refer to the applicable 

“Aircraft Maintenance Manual” – Chapter 25-12-15 (TASK 25-12-15-400-801-

A) – Cockpit Pedal Covers. 

(10) Reinstall the retained glareshield coverage ( 223AZ) on its respective place on 

the instrument panel. Refer to the applicable AMM 25-12-07 

(TASK 25-12-07-400-801-A) - Glareshild Coverage. 

(11) Reinstall the retained windshield center fairing. Refer to the applicable AMM 

25-12-01 (TASK 25-12-01-400-801-A) - Ceiling Lining. 
A L E R T

SERVICE BULLETIN

DATE: 20/Sep/2013 SB No.: 145LEG-53-A032 

REVISION No.: 01 - 24/Sep/2013 PAGE: 17 

Copyright © 2013 by EMBRAER S.A. All rights reserved. 

(12) Reinstall the retained cockpit windshields (LH and RH sides). Refer to the 

applicable AMM – Chapter 56-10-01 (TASK 56-10-01-400-801-A or TASK 

56-10-01-400-802-A, as applicable) – Windows. 

(13) Reinstall the retained pilot and copilot seats. Refer to the applicable “Aircraft 

Maintenance Manual” – Chapter 25-11-01 (TASK 25-11-01-400-801-A) – 

Pilot Seats. 

(14) Put the aircraft back to its initial condition. 

(15) Write the accomplishment of PART II of this bulletin in the applicable 

documents. 

(16) Fill out the attached “Service Bulletin Implementation and Evaluation” form 

and return it to: 

EMBRAER S.A. 

Customer Support Contact Center 

Embraer Executive Jets 

contact.center@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, & Caribbean 

+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 incorporated in the aircraft 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). 
A L E R T

SERVICE BULLETIN

SB No.: 145LEG-53-A032 DATE: 20/Sep/2013 

PAGE: 18 REVISION No.: 01 - 24/Sep/2013 

Copyright © 2013 by EMBRAER S.A. All rights reserved. 

1. Inspection for the integrity of the attaching parts of the cockpit windshield center post 

lower eyelet fitting. 

APPLICABLE TO GROUPS 1 AND 2 AIRCRAFT 

FIGURE 1: INSPECTION OF THE CENTER POST FITTING ATTACHMENT PARTS. 

(SHEET 01 OF 02)
A L E R T

SERVICE BULLETIN

DATE: 20/Sep/2013 SB No.: 145LEG-53-A032 

REVISION No.: 01 - 24/Sep/2013 PAGE: 19 

Copyright © 2013 by EMBRAER S.A. All rights reserved. 

EM145SB531356A.DGN

A

ZONES

223

224

DET. A

VIEW B

INSPECT THE ATTACHING

PARTS FOR INTEGRITY

B

1

APPLICABLE TO GROUPS 1 AND 2 AIRCRAFT 

FIGURE 1: INSPECTION OF THE CENTER POST FITTING ATTACHMENT PARTS. 

(SHEET 02 OF 02)
A L E R T

SERVICE BULLETIN

SB No.: 145LEG-53-A032 DATE: 20/Sep/2013 

PAGE: 20 REVISION No.: 01 - 24/Sep/2013 

Copyright © 2013 by EMBRAER S.A. All rights reserved. 

1. Remove and discard the bolts, washers and nuts of the lower eyelet fitting of the 

cockpit windshield center post following the steps below: 

(a) Remove and discard cotter pin PN MS24665-302 (1 position) and remove and 

retain nut PN PE22072L7 (1 position), washers PN NAS1149C0763R (2 

positions), and bolt PN NAS6407A20D (1 position) that attach the lower eyelet 

fitting to the cockpit windshield center post. Refer to the applicable AMM 53-12-02 

(TASK 53-12-02-000-801-A) - Fuselage. 

(b) Remove and retain lower eyelet fitting PN 120-44541-003 (1 position) from the 

fuselage structure by removing and discarding nuts PN NAS1805-5 (4 position), 

washers PN MS21299-5K (4 positions) and PN MS21299C5K (4 positions), and 

bolts PN NAS6405A17 (4 positions). Refer to the applicable AMM 53-12-02 

(TASK 53-12-02-000-801-A) - Fuselage. 

NOTE: More than one washer (PN MS21299-5K and PN MS21299C5K) can 

be found in each position, limited in the maximum of two for position. 

(c) Remove and retain shim PN 120-04462-001 (2 positions). Refer to the applicable 

AMM 53-12-02 (TASK 53-12-02-000-801-A) - Fuselage. 

CAUTION: THE SHIMS ARE VERY IMPORTANT IN THE ADJUSTMENT OF 

THE WINDSHIELD. BE CAREFUL NOT TO LOSE THEM OR 

CHANGE THEIR POSITIONS. 

WARNING: BE CAREFUL WHEN YOU USE RHODIASOLVE. PUT ON SAFETY

GOGGLES AND PROTECTIVE CLOTHING. DO NOT BREATHE THE

GAS OR DUST. DO THE WORK IN AN AREA THAT HAS A GOOD

FLOW OF AIR. THE RHODIASOLVE IS POISONOUS AND HIGHLY 

FLAMMABLE.

(d) With the aid of a spatula and using RHODIASOLVE E-23 (MEP 13-073), clean up 

the sealant from the removed eyelet fitting and the fuselage faying area. 

APPLICABLE TO GROUPS 1 AND 2 AIRCRAFT 

FIGURE 2: REPLACEMENT ATTACHMENTS PARTS 

(SHEET 01 OF 05)
A L E R T

SERVICE BULLETIN

DATE: 20/Sep/2013 SB No.: 145LEG-53-A032 

REVISION No.: 01 - 24/Sep/2013 PAGE: 21 

Copyright © 2013 by EMBRAER S.A. All rights reserved. 

2. Perform a general visual inspection of lower eyelet fitting PN 120-44541-003 (1 

position) to detect obvious damage, failure or irregularity. 

(a) if any damage (cracks, dents, scratches), failure or irregularity is found, contact 

EMBRAER according to address below. 

Customer Support Contact Center 

Embraer Executive Jets 

contact.center@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, & Caribbean 

+33 1 7048-0510 Europe, Middle East & Africa 

+65 6307-7647 Asia Pacific 

+55 12 3927-7000 Latin America 

(b) if no damage (cracks, dents, scratches), failure or irregularity is found,, no action 

is required. Perform steps (3) and on. 

3. Replace the bolts, washers and nuts of the cockpit windshield center post lower eyelet 

fitting following the step below: 

WARNING: BE CAREFUL WHEN YOU USE COR-BAN 27L (MEP 09-075). PUT ON 

SAFETY GOGGLES AND PROTECTIVE CLOTHING. DO NOT 

BREATHE THE GAS OR DUST. DO THE WORK IN AN AREA THAT 

HAS A GOOD FLOW OF AIR. THE RHODIASOLVE IS POISONOUS 

AND HIGHLY FLAMMABLE.

(a) Install the shim PN 120-04462-001 (2 positions) between the lower eyelet fitting 

and the fuselage structure in the same position that they were installed before the 

disassembly, and apply COR-BAN 27L (MEP 09-075). Refer to the applicable 

AMM 53-12-02 (TASK 53-12-02-400-801-A) - Fuselage. 

CAUTION: THE SHIMS ARE VERY IMPORTANT IN THE ADJUSTMENT OF 

THE WINDSHIELD. BE CAREFUL NOT TO LOSE THEM OR 

CHANGE THEIR POSITIONS. 

FIGURE 2: REPLACEMENT ATTACHMENTS PARTS 

(SHEET 02 OF 05) 
A L E R T

SERVICE BULLETIN

SB No.: 145LEG-53-A032 DATE: 20/Sep/2013 

PAGE: 22 REVISION No.: 01 - 24/Sep/2013 

Copyright © 2013 by EMBRAER S.A. All rights reserved. 

(b) Install lower eyelet fitting PN 120-44541-003 (1 position) to the fuselage structure, 

applying interface sealant PN PR1776M B2 654 SEM KIT (AMS3281 CLASS B) 

and using bolts PN MS14181-05018L (4 positions) wet in sealant 

PN COR-BAN 27L (MEP 09-075), washers PN MS21299-C5 (4 positions) and 

PN MS21299-5 (4 positions), and nuts PN MS14182L05 (4 positions). Refer to the 

applicable AMM 53-12-02 (TASK 53-12-02-400-801-A) - Fuselage. 

NOTE: More than one washer (PN MS21299-C5 and PN MS21299-5) can be 

installed in each position, limited in the maximum of two for position. 

NOTE: The lower eyelet fitting and the windshield center post must be aligned 

in such a way that bolt PN NAS6407A20D can be installed by sliding. 

Refer to the applicable AMM 53-12-02 (TASK 53-12-02-400-801-A) - 

Fuselage. 

NOTE: Add the drag torque value measured before and the standard torque 

 together to get the final torque. Refer to AMM 20-10-01 – Standard 

Practices. 

Apply a torque threaded fastener 190LBF.IN to 230LBF.IN. Refer to 

AMM 20-10-01 – Standard Practices. 

(c) Install windshield center post to lower eyelet fitting PN 120-44541-003 reusing bolt 

PN NAS6407A20D, washers PN NAS1149C0763R and PN NAS1149C0763R, 

nut PN PE22072L7 and a new cotter pin PN MS24665-302. 

NOTE: The windshield center post must be aligned with the forward fuselage 

centerline. 

FIGURE 2: REPLACEMENT ATTACHMENTS PARTS 

(SHEET 03 OF 05) 
A L E R T

SERVICE BULLETIN

DATE: 20/Sep/2013 SB No.: 145LEG-53-A032 

REVISION No.: 01 - 24/Sep/2013 PAGE: 23 

Copyright © 2013 by EMBRAER S.A. All rights reserved. 

EM145SB531354A.DGN

A

ZONES

223

224

WINDSHIELD

CENTER POST

(REF.)

1

1

DET. A

1

1

B

NUT 

PN NAS1805−5

(04 POSITIONS)

(REMOVE AND DISCARD)

NUT 

PN MS14182L05

(04 POSITIONS)

(INSTALL)

WASHER

PN MS21299−5K

(04 POSITIONS)

(REMOVE AND DISCARD)

WASHER

PN MS21299−5

(04 POSITIONS)

(USE MAXIMUM 2 

WASHERS FOR POSITION)

(INSTALL)

WASHER

PN MS21299C5K

(04 POSITIONS)

(REMOVE AND DISCARD)

WASHER

PN MS21299−C5

(04 POSITIONS)

(USE MAXIMUM 2 

WASHERS FOR POSITION)

(INSTALL)

THICKNESS OF SHIM

(REF.)

FUSELAGE

STRUCTURE

(REF.)

1

EYELET FITTING

PN 120−44541−003

(REMOVE AND RETAIN)

(REINSTALL)

1

WASHER

PN NAS1149C0763R

(REMOVE AND RETAIN)

(REINSTALL)

NUT

PN PE22072L7

(REMOVE AND RETAIN)

(REINSTALL)

COTTER PIN

PN MS24665−302

(REMOVE AND DISCARD)

(INSTALL)

SHIM

PN 120−04462−001

(REMOVE AND RETAIN)

(REINSTALL)

1

BOLT

PN NAS6407A20D

(REMOVE AND RETAIN)

(REINSTALL)

WASHER

PN NAS1149C0763R

(REMOVE AND RETAIN)

(REINSTALL)

BOLT

PN NAS6405A17

(04 POSITIONS)

(REMOVE AND DISCARD)

BOLT

PN MS14181−05018L

(04 POSITIONS)

(INSTALL)

1

2

2

1

3

3

3

3

3

3

2 3

TORQUE: 33.9 − 45.2 N.m (300 − 400 lb.in) PLUS DRAG TORQUE.

3

APPLY SEALANT PN COR−BAN 27L (MEP 09−075).

3

2

APPLY INTERFACE SEALANT PN PR1776M B2 654 SEM KIT (AMS3281 CLASS B).

APPLICABLE TO GROUPS 1 AND 2 AIRCRAFT 

FIGURE 2: REPLACEMENT ATTACHMENTS PARTS 

(SHEET 04 OF 05)
A L E R T

SERVICE BULLETIN

SB No.: 145LEG-53-A032 DATE: 20/Sep/2013 

PAGE: 24 REVISION No.: 01 - 24/Sep/2013 

Copyright © 2013 by EMBRAER S.A. All rights reserved. 

EM145SB531355A.DGN

1

VIEW B

EYELET FITTING

PN 120−44541−003

(INSTALL)

WINDSHIELD

CENTER POST

(REF.)

FORWARD

FUSELAGE

(REF.)

NUT

PN NAS1805−5

(04 POSITIONS)

(REMOVE AND DISCARD)

NUT 

PN MS14182L05

(04 POSITIONS)

(INSTALL)

WASHER

PN MS21299−5K

(04 POSITIONS)

(REMOVE AND DISCARD)

WASHER

PN MS21299−5

(04 POSITIONS)

(USE MAXIMUM 2 

WASHERS FOR POSITION)

(INSTALL)

WASHER

PN MS21299C5K

(04 POSITIONS)

(REMOVE AND DISCARD)

WASHER

PN MS21299−C5

(04 POSITIONS)

(USE MAXIMUM 2 

WASHERS FOR POSITION)

(INSTALL)

1

1

1

1

1

1

SHIM 

PN 120−04462−001

(REMOVE AND RETAIN)

(REINSTALL)

INSTALL BOLT BY SLIDING IT INTO PLACE.

REINSTALL THE SHIM IN THE SAME POSITION.

THE WINDSHIELD CENTER POST MUST BE ALIGNED WITH FORWARD FUSELAGE.

2

BOLT

PN NAS6405A17

(04 POSITIONS)

(REMOVE AND DISCARD)

BOLT

PN MS14181−05018L

(04 POSITIONS)

(INSTALL)

BOLT

PN NAS6407A20D

WASHER

PN NAS1149C0763R

(02 POSITIONS)

NUT

PN PE22072L7

(REINSTALL)

COTTER PIN

PN MS24665−302

(INSTALL)

4

4

5

5

3

3

3

3

3

3

3

2

6 TORQUE: 21.47 − 25.99 N.m (190 − 230 lb.in) PLUS DRAG TORQUE.

2 6

7

3 7

APPLY SEALANT PN COR−BAN 27L (MEP 09−075). 2

3

APPLY INTERFACE SEALANT PN PR1776M B2 654 SEM KIT

(AMS3281 CLASS B).

MAKE SURE THAT AT LEAST 2.0

OF THE BOLT THREAD REMAIN

APPLICABLE TO GROUPS 1 AND 2 AIRCRAFT 

FIGURE 2: REPLACEMENT ATTACHMENTS PARTS 

(SHEET 05 OF 05) 
.

..

SERVICE BULLETIN IMPLEMENTATION AND EVALUATION FORM

The purpose of this form is to collect data that will be used to improve the quality of our Service Bulletins and 

Reliability Program. 

Please fill in this form and return it to: EMBRAER S.A. 

Customer Support Contact Center 

Embraer Executive Jets 

contact.center@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, & Caribbean 

+33 1 7048-0510 Europe, Middle East & Africa 

+65 6307-7647 Asia Pacific 

+55 12 3927-7000 Latin America

SB Number/Revision: SB Title: 

SB145LEG-53-A032R01 REPLACEMENT ATTACHMENTS PARTS OF THE COCKPIT WINDSHIELD 

CENTER POST LOWER EYELET FITTING

SB Implementation Report 

Aircraft Serial Number or Registration Number: Incorporation 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 of incorporation, suggested improvements,...)

Company/ Service Center: Fax: Phone: 

Address: 

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

 

ENS-003393