### TRANSMITTAL LETTER

.

TRANSMITTAL LETTER SB No.: 145LEG-53-A032 PAGE: 1 of 1 Copyright © 2013 by EMBRAER S.A. All rights reserve d. 1. DESCRIPTION
This sheet transmits Revision 01 to Service Bulleti n 145LEG-53-A032. This is a complete reissue of the Bulletin. This revision incorporates the information presente d 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 pa ge to show the location of the significant changes. Text displacement and text for mat 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.

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# 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 reserve d. FUSELAGE – INSPECTION AND REPLACEMENT OF ATTACHMENT S PARTS FROM THE COCKPIT WINDSHIELD CENTER POST LOWER EYELET FIT TING

In connection with the use of this document, Embrae r does not provide any express or implied warrantie s and expressly disclaims any warranty of merchantabi lity or fitness for a particular purpose.

1. PLANNING INFORMATION

A. SB EFFECTIVITY

Aircraft affected:

MODEL SN

EMB-135BJ 145412, 145462, 145484, 145495, 145505, 1 45516,

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 reserve d. 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, 145 01170, 14501175, 14501179, 14501180, 14501182, 14501183, 14501188 th ru 14501210, 14501212 thru 14501227, and 14501229 thru 14501249 and on ha ve 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 reserve d. The SB effectivity is divided into GROUPS of aircra ft, as follows:
(1) GROUP 1

MODEL SN

EMB-135BJ 145412, 145462, 145484, 145495, 145505, 145516, 145 528,

145540, 145549, 145555, 145586, 145591, 145625, 145 637, 145642, 145644, 145678, 145686, 145699, 145706, 145 711, 145717, 145730, 145770, 145775, 145780, 145789, 145 796, 14500802, 14500809, 14500818, 14500825, 14500832, 1 4500841, 14500851, and 14500854 which have accomplished with SB145LEG-53-0021.

(2) GROUP 2

MODEL SN

EMB-135BJ 14500863, 14500867, 14500873, 14500880, 14500884, 1 4500891,

14500901, 14500903, 14500910, 14500913, 14500916, 1 4500919, 14500925, 14500933, 14500937, 14500939, 14500941, 1 4500942, 14500944, 14500946, 14500948, 14500950, 14500952, 1 4500954, 14500955, 14500957, 14500960, 14500961, 14500963, 1 4500965 thru 14500967, 14500969 thru 14500976, 14500978 thr u 14500983, 14500985, 14500986, 14500988 thru 1450099 1, 14500993 thru 14500995, 14500997 thru 14500999, 145 01001 thru 14501004, 14501006 thru 14501008, 14501010 thru 145 01012, 14501014 thru 14501018, 14501020, 14501021, 1450102 3, 14501025, 14501026, 14501029, 14501031, 14501032, 1 4501034, 14501035, 14501037 thru 14501039, 14501041, 1450104 2, 14501044 thru 14501046, 14501048, 14501049, 1450105 1, 14501052, 14501054, 14501055, 14501057, 14501058, 1 4501060 thru 14501062, 14501064, 14501066, 14501067, 145010 69,

### 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 reserve d. MODEL SN

EMB-135BJ 14501071, 14501072, 14501074, 14501075, 14501078 th ru

14501080, 14501082, 14501083, 14501086, 14501087, 1 4501089 thru 14501092, 14501094 thru 14501096, 14501098 thr u 14501100, 14501102, 14501105 thru 14501107, 1450110 9 thru 14501111, 14501113, 14501114, 14501117 thru 1450112 3, 14501126 thru 14501128, 14501131 thru 14501134, 145 01136 thru 14501152, 14501154 thru 14501158, 14501160 thru 145 01169, 14501171 thru 14501174, 14501176, 14501181, 1450118 4, and 14501187.

B. CONCURRENT REQUIREMENTS

None.

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# 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 reserve d. 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 fai lure may have relation to the bolts fatigue strength, and therefore a dedicated a ction to ensure the structures’ integrity is required.

2. OBJECTIVE To ensure the integrity of the four bolts that conn ect 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 reserve d. D. DESCRIPTION
This Bulletin is divided into 2 PARTS, as follows:

PART I INSPECTION OF THE CENTER POST FITTING ATTACHMENT PA RTS. 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 fit ting.
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.

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# 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 reserve d. E. COMPLIANCE
(a) Applicable to GROUP 1 aircraft: For aircraft with more than 3000 flight cycles sinc e the SB 145LEG-53-0021 incorporation:
- “PART I” of this bulletin is to be accomplished w ithin the next 50 flight cycles from the date this bulletin was issued. - Thereafter, “PART I” of this bulletin is to be r epeated 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 sinc e the SB 145LEG-53-0021 incorporation:
PART II of this bulletin must be accomplished befor e the aircraft logs 3000 flight cycles or the next 96 months check (or multi ples), whichever occurs first.

(b) Applicable to GROUP 2 aircraft: For aircraft with more than 3000 total flight cycle s:
- “PART I” of this bulletin is to be accomplished w ithin the next 50 flight cycles from the date this bulletin was issued. - Thereafter, “PART I” of this bulletin is to be r epeated 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 cycle s:
PART II of this bulletin must be accomplished befor e the aircraft logs 3000 flight cycles or the next 96 months check (or multi ples), whichever occurs first.

F. APPROVAL
The technical aspects of this Alert Service Bulleti n are approved by: Embraer – Engineering Board.

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# 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 reserve d. G. COMMUNICATIONS TO EMBRAER
EMBRAER requests that any results found during thes e inspections be informed to your local EMBRAER representatives or offices.

H. 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.

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 reserve d. 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.

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# 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 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

None.

C. MATERIAL NECESSARY FOR EACH AIRCRAFT

None.

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# 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 reserve d. (2) MATERIAL TO BE PROCURED
(a) Parts The parts below should be procured from the manufac turer or locally purchase, as indicated in the associated Note, or o rdered 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 in ventories 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

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# 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 reserve d. QUANTITY : AR = As Required.

DISPOSITION: 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

None.

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# 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 reserve d. 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 e xterior 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 th e inspection area. This level of inspection is made under normal ly available lighting conditions such as daylight, hangar lighti ng, flashlight or drop-light and may require removal or opening of ac cess 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 i n 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 secti on “1. I. REFERENCES” for a more complete definition. 4) This Service Bulletin effectivity is divided int o 02 aircraft GROUPS according to the relevant configuration and the SB itself is divided into 02 PARTS. The SB PARTS are featured to allow t heir 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 maintena nce.

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# 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 reserve d. 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 t he applicable “Aircraft Maintenance Manual” – Chapter 32-00-01 (TASK 32-00-01-910-801-A ) – Landing Gear.
(2) Remove and retain the glareshield coverage (223 AZ) from the instrument panel. Refer to the applicable AMM 25-12-07 (TASK 2 5-12-07-000-801-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, wa shers PN MS21299C5K, MS21299-5K and nuts NAS1805-5 that attaches the coc kpit windshield center post eyelet fitting to the structure as follows:
(a) If there is any sign of discrepancy on the bolt s, washers and nuts replace the bolts washers and nuts of the cockpit windshield ce nter post eyelet fitting immediately, according to PART II of this bulletin.
(b) If there is no discrepancy on bolts, washers an d 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 bo lts washers and nuts of the cockpit windshield center post eyelet fitting immed iately, according to PART II of this bulletin.
(5) Reinstall the retained glareshield coverage ( 2 23AZ) on its respective place on the instrument panel. Refer to the applicable AMM 2 5-12-07 (TASK 25-12-07- 400-801-A) - Glareshild Coverage.
(6) Reinstall the retained windshield center fairin g. 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 bull etin in the applicable documents.

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# 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 reserve d. (9) Fill out the attached “Service Bulletin Impleme ntation 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, & 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 ).

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# 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 reserve d. 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 t he applicable “Aircraft Maintenance Manual” – Chapter 32-00-01 (TASK 32-00- 01-910-801-A) – Landing Gear.
(2) Remove and retain the glareshield coverage ( 22 3AZ) from the instrument panel. Refer to the applicable AMM 25-12-07 (TASK 2 5-12-07-000-801-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 a nd RH sides). Refer to the applicable AMM – Chapter 56-10-01 (TASK 56-10-01-00 0-801-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 appl icable AOM - Section 2-02 (TASK 2-02-05) - Pedal Adjustment.
(7) Remove and retain the cockpit pedal covers. Ref er to the applicable “Aircraft Maintenance Manual” – Chapter 25-12-15 (T ASK 25-12-15-000-801- A) – 

### Cockpit Pedal Covers

. (8) Replace the attachment parts of the cockpit win dshield center post eyelet fitting according to Figure 2.
(9) Reinstall the cockpit pedal covers. Refer to th e applicable “Aircraft Maintenance Manual” – Chapter 25-12-15 (T ASK 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 2 5-12-07 (TASK 25-12-07-400-801-A) - Glareshild Coverage.
(11) Reinstall the retained windshield center fairi ng. 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 reserve d. (12) Reinstall the retained cockpit windshields (LH and RH sides). Refer to the applicable AMM – Chapter 56-10-01 (TASK 56-10-01-40 0-801-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 bu lletin in the applicable documents.
(16) Fill out the attached “Service Bulletin Implem entation 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, & 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 ).

### 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 reserve d. 1. Inspection for the integrity of the attaching pa rts of the cockpit windshield center post lower eyelet fitting.

APPLICABLE TO GROUPS 1 AND 2 AIRCRAFT

FIGURE 1: INSPECTION OF THE CENTER POST FITTING ATT ACHMENT 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 reserve d. 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 ATT ACHMENT 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 reserve d. 1. Remove and discard the bolts, washers and nuts o f 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 NA S1149C0763R (2 positions), and bolt PN NAS6407A20D (1 position) th at attach the lower eyelet fitting to the cockpit windshield center post. Refe r to the applicable AMM 53-12-02 (TASK 53-12-02-000-801-A) - Fuselage.
(b) Remove and retain lower eyelet fitting PN 120-4 4541-003 (1 position) from the fuselage structure by removing and discarding nuts PN NAS1805-5 (4 position), washers PN MS21299-5K (4 positions) and PN MS21299C 5K (4 positions), and bolts PN NAS6405A17 (4 positions). Refer to the app licable AMM 53-12-02 (TASK 53-12-02-000-801-A) - Fuselage.

NOTE : More than one washer (PN MS21299-5K and PN MS21299C 5K) can

be found in each position, limited in the maximum o f two for position.
(c) Remove and retain shim PN 120-04462-001 (2 posi tions). 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 HIGHL Y 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 reserve d. 2. Perform a general visual inspection of lower eye let fitting PN 120-44541-003 (1 position) to detect obvious damage, failure or irre gularity.

(a) if any damage (cracks, dents, scratches), failu re 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, & C aribbean +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), failur e or irregularity is found,, no action

is required. Perform steps (3) and on.
3. Replace the bolts, washers and nuts of the cockp it 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 THA T HAS A GOOD FLOW OF AIR. THE RHODIASOLVE IS POISONOU S 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 tha t they were installed before the disassembly, and apply COR-BAN 27L (MEP 09-075). Re fer 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 reserve d. (b) Install lower eyelet fitting PN 120-44541-003 ( 1 position) to the fuselage structure, applying interface sealant PN PR1776M B2 654 SEM KI T (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 insta lled 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 s tandard torque

together to get the final torque. Refer to AMM 20- 10-01 – Standard Practices. Apply a torque threaded fastener 190LBF.IN to 230LB F.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 NAS 1149C0763R, nut PN PE22072L7 and a new cotter pin PN MS24665-30 2.

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 reserve d. 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

3 2

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 reserve d. 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 7

3

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 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 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, & 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:

SB145LEG-53-A032R01 REPLACEMENT ATTACHMENTS PARTS OF THE COCKPIT WINDSH IELD CENTER POST LOWER EYELET FITTING

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:

ENS-003393