SERVICE BULLETIN

DATE: 18/Oct/2013 SB No.: 145-53-0082 

REVISION No.: PAGE: 1 of 22 

Embraer Copyright © 2013. All rights reserved. 

FUSELAGE – INSPECTION AND REPLACEMENT OF THE ATTACHMENTS PARTS FROM 

THE LOWER EYELET FITTING OF THE COCKPIT-WINDSHIELD CENTER POST 

THIS SERVICE BULLETIN SUPERSEDES ALERT SERVICE BULLETIN 145-53-A082 

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: 

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

(1) GROUP 1 

MODEL SN 

EMB-145( ) and EMB-135( ) 145002, 145003, 14500885 thru 14500890, 

14500892 thru 14500900, 14500902, 14500904 

thru 14500909, 14500911, 14500912, 14500914, 

14500915, 14500917, 14500918, 14500920 thru 

14500924, 14500926 thru 14500932, 14500934 

thru 14500936, 14500938, 14500940, 14500943, 

14500945, 14500947, 14500949, 14500951, 

14500953, 14500956, 14500958, 14500959, 

14500962, 14500964, 14500968, 14500977, 

14500984, 14500987, 14500992, 14500996, 

14501000, 14501005, 14501009, 14501013, 

14501019, 14501022, 14501024, 14501027, 

14501030, 14501033, 14501036, 14501040, 

14501043, 14501047, 14501050, 14501053, 

14501056, 14501059, 14501063, 14501065, 
SERVICE BULLETIN

SB No.: 145-53-0082 DATE: 18/Oct/2013 

PAGE: 2 REVISION No.: 

Embraer Copyright © 2013. All rights reserved. 

MODEL SN 

14501068, 14501070, 14501073, 14501077, 

14501084, 14501124, 14501125, 14501129, 

14501130, 14501135, 14501136, 14501153, 

14501159, 14501177, 14501178, 14501185, and 

14501186. 

(2) GROUP 2 

MODEL SN 

EMB-145( ) and EMB-135( ) 145004 thru 145362, 145364 thru 145411, 145413 

thru 145461, 145463 thru 145483, 145485 thru 

145494, 145496 thru 145504, 145506 thru 145515, 

145517 thru 145527, 145529 thru 145539, 145541 

thru 145548, 145550 thru 145554, 145556 thru 

145585, 145587 thru 145590, 145592 thru 145624, 

145626 thru 145636, 145638 thru 145641, 145643, 

145645 thru 145677, 145679 thru 145685, 145687 

thru 145698, 145700 thru 145705, 145707 thru 

145710, 145712 thru 145716, 145718 thru 145729, 

145731 thru 145769, 145771 thru 145774, 145776 

thru 145779, 145781 thru 145788, 145790 thru 

145795, 145797 thru 14500801, 14500803 thru 

14500808, 14500810 thru 14500817, 14500819 

thru 14500824, 14500826 thru 14500831, 

14500833 thru 14500840, 14500842 thru 

14500850, 14500852, 14500853, 14500855 thru 

14500862, 14500864 thru 14500866, 14500868 

thru 14500872, 14500874 thru 14500879, and 

14500881 thru 14500883 which have incorporated 

first issue or Revision 01 of SB145-53-0058. 
SERVICE BULLETIN

DATE: 18/Oct/2013 SB No.: 145-53-0082 

REVISION No.: PAGE: 3 

Embraer Copyright © 2013. All rights reserved. 

Affected component: 

None. 

In-production effectivity: 

The subject presented in this bulletin does not affect any in-production aircraft. 

B. CONCURRENT REQUIREMENTS 

None. 

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 fitting 

(between windshields). Investigation indicates that this failure may be related 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 eyelet fitting of the 

forward fuselage center-post. 

(3) EXPECTED BENEFITS 

To provide bolts with higher mechanical properties and a longer fatigue life of the 

component. 

(4) REVISION HISTORY 

None. 
SERVICE BULLETIN

SB No.: 145-53-0082 DATE: 18/Oct/2013 

PAGE: 4 REVISION No.: 

Embraer Copyright © 2013. All rights reserved. 

D. DESCRIPTION 

NOTES: 1) The modification presented in this bulletin affects Fatigue Critical 

Structure (FCS); however, no change to the related Damage Tolerance 

Inspection (DTI) instructions is required. 

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 a Detailed Inspection (DI) for the integrity of the 

attaching parts of the lower eyelet fitting of the cockpit windshield center-post. This 

part also includes a required check of the bolts tightness. 

To get access to the work area, it is necessary to remove the pilot and copilot seats, 

glareshield coverage, and the windshield center fairing. Also, the removal of the 

display unit 3 (DU-3) may be necessary as an alternative access to check the bolts 

tightness. 

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 lower eyelet 

fitting of the cockpit windshield center-post. 

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

pilot and copilot seats, glareshield coverage, and the windshield center fairing. Also, 

the removal of the display unit 3 (DU-3) may be necessary as an alternative access 

to replace the attachment parts of the lower eyelet fitting. 
SERVICE BULLETIN

DATE: 18/Oct/2013 SB No.: 145-53-0082 

REVISION No.: PAGE: 5 

Embraer Copyright © 2013. All rights reserved. 

E. COMPLIANCE 

(1) Applicable to PART I 

(a) Applicable to GROUP 1 

For aircraft that have reached more than 11,000 flight cycles, the 

incorporation of PART I of this Service Bulletin is recommended within the 

next 50 flight cycles after the first issuance of SB145-53-A082. Thereafter, 

PART I of this service bulletin must be repeated every 500 flight cycles until 

the accomplishment of PART II. 

For aircraft that have reached between 10,000 and 11,000 flight cycles, the 

incorporation of PART I of this Service Bulletin is recommended within the 

next 150 flight cycles after the first issuance of SB145-53-A082 or before the 

aircraft reaches 11,050 flight cycles, whichever occurs first and must be 

repeated every 500 flight cycles until the accomplishment of PART II. 

For aircraft that have reached between 7,500 and 10,000 flight cycles, the 

incorporation of PART I of this Service Bulletin is recommended within the 

next 500 flight cycles after the first issuance of SB145-53-A082 or before the 

aircraft reaches 10,150 flight cycles, whichever occurs first and must be 

repeated every 1,000 flight cycles until the accomplishment of PART II. After 

the aircraft reaches 11,050 flight cycles, PART I of this service bulletin must 

be repeated every 500 flight cycles until the accomplishment of PART II. 

For aircraft that have reached less than 7,500 flight cycles, the incorporation 

of PART I of this Service Bulletin is recommended within the next 5,000 flight 

cycles after the first issuance of SB145-53-A082 or before the aircraft 

reaches 8,000 flight cycles, whichever occurs first and must be repeated 

every 1,000 flight cycles until the accomplishment of PART II. After the 

aircraft reaches 11,050 flight cycles, PART I of this service bulletin must be 

repeated every 500 flight cycles until the accomplishment of PART II. 

NOTE: The implementation of MRB Task Reference Number 53-12-00-

220-803-A00 or MRB Task Reference Number 53-12-00-220-814-

A00 is valid as the first inspection incorporation of PART I of this 

bulletin. 
SERVICE BULLETIN

SB No.: 145-53-0082 DATE: 18/Oct/2013 

PAGE: 6 REVISION No.: 

Embraer Copyright © 2013. All rights reserved. 

(b) Applicable to GROUP 2 

For aircraft that have reached more than 11,000 flight cycles after the SB 

145-53-0058 incorporation, the incorporation of PART I of this Service 

Bulletin is recommended within the next 50 flight cycles after the first 

issuance of SB145-53-A082. Thereafter, PART I of this service bulletin must 

be repeated every 500 flight cycles until the accomplishment of PART II. 

For aircraft that have reached between 10,000 and 11,000 flight cycles after 

the SB 145-53-0058 incorporation, the incorporation of PART I of this 

Service Bulletin is recommended within the next 150 flight cycles after the 

first issuance of SB145-53-A082 or before the aircraft reaches 11,050 flight 

cycles after the SB 145-53-0058 incorporation, whichever occurs first and 

must be repeated every 500 flight cycles until the accomplishment of PART 

II. 

For aircraft that have reached between 7,500 and 10,000 flight cycles after 

the SB 145-53-0058 incorporation, the incorporation of PART I of this 

Service Bulletin is recommended within the next 500 flight cycles after the 

first issuance of SB145-53-A082 or before the aircraft reaches 10,150 flight 

cycles after the SB 145-53-0058 incorporation, whichever occurs first and 

must be repeated every 1,000 flight cycles until the accomplishment of PART 

II. After the aircraft reaches 11,050 flight cycles, PART I of this service 

bulletin must be repeated every 500 flight cycles until the accomplishment of 

PART II. 

For aircraft that have reached less than 7,500 flight cycles after the SB 145-

53-0058 incorporation, the incorporation of PART I of this Service Bulletin is 

recommended within the next 5,000 flight cycles after the first issuance of 

SB145-53-A082 or before the aircraft reaches 8,000 flight cycles after the SB 

145-53-0058 incorporation, whichever occurs first and must be repeated 

every 1,000 flight cycles until the accomplishment of PART II. After the 

aircraft reaches 11,050 flight cycles, PART I of this service bulletin must be 

repeated every 500 flight cycles until the accomplishment of PART II. 

NOTE: The implementation of MRB Task Reference Number 53-12-00-

220-803-A00 or MRB Task Reference Number 53-12-00-220-814-

A00 is valid as the first inspection incorporation of PART I of this 

bulletin. 
SERVICE BULLETIN

DATE: 18/Oct/2013 SB No.: 145-53-0082 

REVISION No.: PAGE: 7 

Embraer Copyright © 2013. All rights reserved. 

(2) Applicable to PART II 

(a) Applicable to GROUP 1 and GROUP 2 

Incorporation of PART II of this service bulletin is recommended immediately 

after the accomplishment of PART I, if any discrepancy is detected during 

the inspection provided in PART I of this service bulletin. 

Incorporation of PART II of this service bulletin is recommended in the next 

Heavy Maintenance Check after the accomplishment of PART I, if no 

discrepancy is detected during the inspection provided in PART I of this 

service bulletin. 

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 a modification or repair 

incorporated that is not of EMBRAER origin, and which affects the content 

of this Service Bulletin, the operator will take full responsibility for obtaining 

approval by a regulatory agency for any adaptation necessary before the 

incorporation of this Service Bulletin. 

G. 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. 
SERVICE BULLETIN

SB No.: 145-53-0082 DATE: 18/Oct/2013 

PAGE: 8 REVISION No.: 

Embraer Copyright © 2013. All rights reserved. 

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. 

I. WEIGHT AND BALANCE 

- Change in basic weight: None 

- Change in basic moment: None 

J. ELECTRICAL LOAD DATA 

None. 
SERVICE BULLETIN

DATE: 18/Oct/2013 SB No.: 145-53-0082 

REVISION No.: PAGE: 9 

Embraer Copyright © 2013. All rights reserved. 

K. REFERENCES 

AMM-( ) – Aircraft Maintenance Manual – Chapter 20-10-01 – Standard 

Practices - Airframe. 

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

AMM-( ) – Aircraft Maintenance Manual – Chapter 34-22-01 – Navigation. 

AMM-( ) – Aircraft Maintenance Manual – Chapter 25-11-01, 25-12-01, 25-12-07 

– Equipment and Furnishings. 

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

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

MRB-145/1150 – Maintenance Review Board Report. 

SB145-53-0058 – REPLACEMENT OF THE COCKPIT WINDSHIELD CENTER 

POST LOWER EYELET FITTING. 

SB145-53-A082 – INSPECTION AND REPLACEMENT OF THE ATTACHMENTS 

PARTS FROM THE LOWER EYELET FITTING OF THE 

COCKPIT-WINDSHIELD CENTER POST. 

L. OTHER PUBLICATIONS AFFECTED 

IPC-( ) – Illustrated Parts Catalog - Chapter 53-12-00 - Fuselage. 

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

SB No.: 145-53-0082 DATE: 18/Oct/2013 

PAGE: 10 REVISION No.: 

Embraer Copyright © 2013. 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. 

(2) MATERIAL TO BE PROCURED 

(a) Parts 

The parts below should be acquired from the manufacturer or locally 

purchased, or ordered as spares from Embraer at no charge to the operator 

during a period of 36 months after the original release date of this service 

bulletin. 
SERVICE BULLETIN

DATE: 18/Oct/2013 SB No.: 145-53-0082 

REVISION No.: PAGE: 11 

Embraer Copyright © 2013. All rights reserved. 

NEW PN DESCRIPTION OLD PN QTY 

RQD 

DISP/

Notes 

MS14182L05 Nut NAS1805-5 04 3 

MS14181-05018L or 

MS14181-05020L 

Bolt 

NAS6405A17 or 

NAS6405A18 or 

NAS6405A19 or 

NAS6405A20 

04 3 (a) (b)

MS24665-302 Cotter Pin MS24665-302 01 7 

MS21299-C5 Washer MS21299C5K AR 3 

MS21299-5 Washer MS21299-5K AR 3 

(a) The new bolts should be installed based on the grip length requirements. 

(b) If applicable, bolts PN MS14181-05017L or PN MS14181-05019L can be 

installed based on the grip length requirements. 

(b) Consumables 

The material below or equivalent required for the accomplishment of this 

bulletin should be acquired from the operator’s inventories or from a local 

supplier. 

ITEM PN DESCRIPTION QTY DISP/ 

Notes 

COR-BAN 27L Corrosion Inhibitive Compound. 

(MEP 09-075) AR AR 

QUANTITY: 

AR = As Required. 

DISPOSITION: 

3 = Replace part bearing OLD PN with part bearing NEW PN 

7 = Replace with part bearing same PN 

D. MATERIAL NECESSARY FOR EACH SPARE 

None. 
SERVICE BULLETIN

SB No.: 145-53-0082 DATE: 18/Oct/2013 

PAGE: 12 REVISION No.: 

Embraer Copyright © 2013. All rights reserved. 

E. REIDENTIFIED PARTS 

None. 

F. TOOLING – PRICE AND AVAILABILITY 

None. 
SERVICE BULLETIN

DATE: 18/Oct/2013 SB No.: 145-53-0082 

REVISION No.: PAGE: 13 

Embraer Copyright © 2013. All rights reserved. 

3. ACCOMPLISHMENT INSTRUCTIONS

NOTES: 1) For the purpose of this Service Bulletin, a Detailed Inspection (DET) is: “An 

intensive examination of a specific item, installation or assembly to detect 

damage, failure or irregularity. Available lighting is normally supplemented 

with a direct source of good lighting at an intensity deemed appropriate. 

Inspection aids such as mirrors, magnifying lenses, etc. may be 

necessary. Surface cleaning and elaborate access procedures may be 

required.” 

 2) 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." 

 3) Obey all of the WARNINGS and CAUTIONS included in the referenced 

manuals and procedures. 

 4) The Manuals and other documents are referred to by means of acronyms 

or using a simplified form. Refer to section “1. K. REFERENCES” for a 

more complete definition. 

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. 

B. PART I - INSPECTION OF THE CENTER POST FITTING ATTACHMENT PARTS 

(1) Install the landing gear safety pin. Refer to the applicable AMM 32-00-01 

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

(2) If necessary, 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) – Equipment/Furnishings. 
SERVICE BULLETIN

SB No.: 145-53-0082 DATE: 18/Oct/2013 

PAGE: 14 REVISION No.: 

Embraer Copyright © 2013. All rights reserved. 

(3) If necessary, remove and retain the windshield center fairing. Refer to the 

applicable AMM 25-12-01 (TASK 25-12-01-000-801-A) –

Equipment/Furnishings. 

(4) If necessary, remove and retain the pilot and copilot seats. Refer to the 

applicable AMM 25-11-01 (TASK 25-11-01-000-801-A) –

Equipment/Furnishings. 

(5) If necessary, move the LH and RH pedal assembly (backward or forward) to 

get access to the lower part of the work area. 

(6) If necessary, remove Display Unit 3 (DU-3) to get access to eyelet fitting 

securing nut. Refer to AMM 34-22-01 (TASK 34-22-01-000-801-A) - Navigation. 

(7) Do the inspection for general conditions and obvious damage of the bolts PN 

NAS6405A17 or PN NAS6405A18 or PN NAS6405A19 or PN NAS6405A20, 

washers PN MS21299C5K and PN MS21299-5K, and nuts PN NAS1805-5 that 

attach the eyelet fitting of the cockpit windshield center-post. Refer to Figure 1. 

(a) If there is any sign of discrepancy to the requirements of this inspection on 

the bolts, washers and nuts, replace the attachment parts of the cockpit 

windshield center post eyelet fitting immediately, according to PART II of 

this bulletin. 

(b) If there is no discrepancy to the requirements of this inspection on bolts, 

washers and nuts, with a proper wrench do a check to make sure that the 

bolts are tight, to ensure the bolts and nuts do not move freely. 

NOTE: An alternate means to check for the bolts tightness is to torque 

check them through Display Unit 3 (DU-3) access. 

(1) If the bolts are tight, replace the bolts washers and nuts of the eyelet 

fitting of the cockpit windshield center-post in the next heavy 

maintenance check, according to PART II of this bulletin. 

(2) If the bolt(s) and nut(s) move freely, disassemble and assemble the 

nut(s) and washer(s) of the bottom part of the assembly, to make sure 

the correct grip and torque of the installation. Do a check again to 

make sure that the bolts are tight. 

1. If the bolts are tight, replace the bolts washers and nuts of the 

eyelet fitting of the cockpit windshield center-post in the next heavy 

maintenance check, according to PART II of this bulletin. 
SERVICE BULLETIN

DATE: 18/Oct/2013 SB No.: 145-53-0082 

REVISION No.: PAGE: 15 

Embraer Copyright © 2013. All rights reserved. 

2. If the bolt(s) are not tight, replace the bolts washers and nuts of the 

eyelet fitting of the cockpit windshield center-post immediately, 

according to PART II of this bulletin. 

(8) If removed, install again Display Unit 3 (DU-3). Refer to AMM 34-22-01 (TASK 

34-22-01-400-801-A) – Navigation. 

(9) If removed, install again the 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) - Equipment/Furnishings. 

(10) If removed, install again the windshield center fairing. Refer to the applicable 

AMM 25-12-01 (TASK 25-12-01-400-801-A) - Equipment/Furnishings. 

(11) If removed, install again the pilot and copilot seats. Refer to the applicable 

AMM 25-11-01 (TASK 25-11-01-400-801-A) – Equipment/Furnishings. 

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

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

documents. 

C. PART II - REPLACEMENT OF THE CENTER-POST-FITTING ATTACHMENT 

PARTS. 

(1) Install the landing gear safety pin. Refer to the applicable AMM 32-00-01 

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

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

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

802-A, as applicable) – Windows. 

(3) If necessary, remove and retain the pilot and copilot seats. Refer to the 

applicable AMM 25-11-01 (TASK 25-11-01-000-801-A) – Pilot Seats. 

(4) If necessary, move the LH and RH pedal assembly (backward or forward) to 

get access to the bottom part of the work area. 

(5) If necessary, remove Display Unit 3 (DU-3) to get access to eyelet fitting 

securing nut. Refer to AMM 34-22-01 (TASK 34-22-01-000-801-A) - Navigation. 
SERVICE BULLETIN

SB No.: 145-53-0082 DATE: 18/Oct/2013 

PAGE: 16 REVISION No.: 

Embraer Copyright © 2013. All rights reserved. 

(6) Replace the bolts PN NAS6405A17 or PN NAS6405A18 or PN NAS6405A19

or PN NAS6405A20, washers PN MS21299C5K, MS21299-5K and nuts 

NAS1805-5 of the eyelet fitting of the cockpit windshield center-post according 

to Figure 2. 

(7) If removed, install again Display Unit 3 (DU-3). Refer to AMM 34-22-01 (TASK 

34-22-01-400-801-A) – Navigation. 

(8) Install again the cockpit windshields (LH and RH sides). Refer to the applicable 

AMM 56-10-01 (TASK 56-10-01-400-801-A or TASK 56-10-01-400-802-A, as 

applicable) – Windows. 

(9) If removed, install again the pilot and copilot seats. Refer to the applicable 

AMM 25-11-01 (TASK 25-11-01-400-801-A) – Pilot Seats. 

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

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

documents. 

NOTES: 1) Please inform us by e-mail fleet.reliability@embraer.com.br of the aircraft 

manufacturer serial number and the SB incorporation date, specifying the 

SB Part(s) incorporated or whether the whole SB has been incorporated. 

This will enable Embraer to consider your aircraft configuration when 

providing future modifications. 

2) To formally inform that the SB has been incorporated fleetwide or that the 

SB will not be incorporated, so that Embraer can update the affected 

technical publications, use the “Service Bulletin Full-Fleet Incorporation 

Report” form, which is available on the Flyembraer portal 

(http://www.flyembraer.com). 

3) Use the attached “Service Bulletin Evaluation” form to send us your 

comments regarding this SB. Your feedback will be much appreciated as 

an aid for us to improve the quality of the SBs. 
SERVICE BULLETIN

DATE: 18/Oct/2013 SB No.: 145-53-0082 

REVISION No.: PAGE: 17 

Embraer Copyright © 2013. All rights reserved. 

EM145SB531366A.DGN

A

DET. A

B

WINDSHIELD

CENTER POST

(REF.)

FUSELAGE

STRUCTURE

(REF.)

1

2

1 2 EYELET FITTING

PN 120−45541−003

(REF.)

DET. B

C

 DO A VISUAL INSPECTION ON THE BOLTS, WASHERS AND NUTS FOR INTEGRITY.

D

3

3 TORQUE: 13.5 − 16.4 N.m (119 − 145 lb.in) PLUS DRAG TORQUE

MAKE SURE THAT THE BOLTS ARE TIGHT WITH A PROPER WRENCH.

BOLT

PN NAS6405A17 OR

PN NAS6405A18 OR

PN NAS6405A19 OR

PN NAS6405A20

(4 POSITIONS)

WASHERS

PN MS21299C5K AND

MS21299−5K 

(AS APPLICABLE)

NUTS

PN NAS1805−5

(4 POSITIONS)

(REF.)

FIGURE 1: INSPECTION OF THE BOLTS, NUTS AND WASHERS OF THE LOWER 

EYELET FITTING 

(SHEET 01 OF 02) 
SERVICE BULLETIN

SB No.: 145-53-0082 DATE: 18/Oct/2013 

PAGE: 18 REVISION No.: 

Embraer Copyright © 2013. All rights reserved. 

EM145SB531367A.DGN

VIEW D

VIEW C

1 2

1 2

1

2

 DO A VISUAL INSPECTION ON THE BOLTS, WASHERS AND NUTS FOR INTEGRITY.

LH SHOWN, RH OPPOSITE

3 TORQUE: 13.5 − 16.4 N.m (119 − 145 lb.in) PLUS DRAG TORQUE

3

MAKE SURE THAT THE BOLTS ARE TIGHT WITH A PROPER WRENCH.

BOLT

PN NAS6405A17OR

PN NAS6405A18 OR

PN NAS6405A19 OR

PN NAS6405A20

(4 POSITIONS)

WASHERS

PN MS21299C5K AND

MS21299−5K 

(AS APPLICABLE)

NUTS

PN NAS1805−5

(4 POSITIONS)

(REF.)

BOLT

PN NAS6405A17 OR

PN NAS6405A18 OR

PN NAS6405A19 OR

PN NAS6405A20

(4 POSITIONS)

WASHERS

PN MS21299C5K AND

MS21299−5K 

(AS APPLICABLE)

NUTS

PN NAS1805−5

(4 POSITIONS)

(REF.)

FIGURE 1: INSPECTION OF THE BOLTS, NUTS AND WASHERS OF THE LOWER 

EYELET FITTING 

(SHEET 02 OF 02) 
SERVICE BULLETIN

DATE: 18/Oct/2013 SB No.: 145-53-0082 

REVISION No.: PAGE: 19 

Embraer Copyright © 2013. All rights reserved. 

1. Follow the steps below to remove and discard the bolts, washers and nuts of the lower 

eyelet fitting of the cockpit windshield center-post: 

(a) If necessary, 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 to facilitate access. Refer to the 

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

CAUTION: THE SHIMS ARE VERY IMPORTANT FOR THE ADJUSTMENT OF THE 

WINDSHIELD. BE CAREFUL NOT TO LOSE THEM OR CHANGE 

THEIR POSITIONS. 

(b) Remove and discard nuts PN NAS1805-5 (4 positions), washers PN MS21299-5K 

(as applicable) and PN MS21299C5K (as applicable), and applicable bolts 

PN NAS6405A17 (4 positions) or PN NAS6405A18 (4 positions) or PN 

NAS6405A19 (4 positions) or PN NAS6405A20 (4 positions). If necessary, 

remove lower eyelet fitting PN 120-44541-003 (1 position) and shim PN 120-

04462-001 (as applicable) from the fuselage structure to facilitate access. Refer to 

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

a. If any discrepancy to the requirements is found in the bolts, do a visual 

inspection (GVI) for damage on the eyelet fitting PN 120-44541-003. 

i. If there are signs of damage, contact the Embraer Technical Support 

Department. 

(c) Clean the sealant from the removed eyelet fitting and the fuselage faying area. 

2. Follow the step below to replace the bolts, washers and nuts of the lower eyelet of the 

cockpit windshield center-post: 

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.

FIGURE 2: BOLTS, WASHERS AND NUTS REPLACEMENT OF THE LOWER EYELET 

FITTING 

(SHEET 01 OF 04) 
SERVICE BULLETIN

SB No.: 145-53-0082 DATE: 18/Oct/2013 

PAGE: 20 REVISION No.: 

Embraer Copyright © 2013. All rights reserved. 

CAUTION: THE SHIMS ARE VERY IMPORTANT FOR THE ADJUSTMENT OF

THE WINDSHIELD. BE CAREFUL NOT TO LOSE THEM OR CHANGE 

THEIR POSITIONS. 

(a) Install lower eyelet fitting PN 120-44541-003 (1 position) and shim PN 120-04462-

001 (as required) to the fuselage structure, applying sealant PN COR-BAN 27L 

(MEP 09-075) and using bolts PN MS14181-05018L (4 positions) or PN 

MS14181-05020L (4 positions), as applicable, wet in sealant PN COR-BAN 27L 

(MEP 09-075), washers PN MS21299-C5 (as required) and PN MS21299-5 (as 

required), and nuts PN MS14182L05 (4 positions). Refer to the applicable AMM 

20-10-01 – Standard Practices and 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 to a minimum of one and maximum 

of two for position. 

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

so 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. 

(b) If removed, install windshield center post to lower eyelet fitting PN 120-44541-003 

using 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 with +/- 0.8mm of tolerance. 

FIGURE 2: BOLTS, WASHERS AND NUTS REPLACEMENT OF THE LOWER EYELET 

FITTING 

 (SHEET 02 OF 04) 
SERVICE BULLETIN

DATE: 18/Oct/2013 SB No.: 145-53-0082 

REVISION No.: PAGE: 21 

Embraer Copyright © 2013. All rights reserved. 

EM145SB531368A.DGN

2

A

WINDSHIELD

CENTER POST

(REF.)

1

1

2

1

1

DET. A

3

1

1

B

NUT 

PN NAS1805−5

(04 POSITIONS)

(REMOVE AND DISCARD)

NUT 

PN MS14182L05

(04 POSITIONS)

(INSTALL)

THICKNESS OF SHIM

(REF.)

4

FUSELAGE

STRUCTURE

(REF.)

4

2

4

2

2

1 2

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)

2

1 2

BOLT

PN NAS6407A20D

(REMOVE AND RETAIN)

(REINSTALL)

WASHER

PN NAS1149C0763R

(REMOVE AND RETAIN)

(REINSTALL)

2 EYELET FITTING

PN 120−44541−003

(REMOVE AND RETAIN)

(INSPECT)

(REINSTALL)

4

3

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

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

ENSURE THAT AT LEAST TWO FULL THREADS EXTEND

BEYOUND THE NUT.

INSTALL THE NEW BOLTS BASED ON THE GRIP LENGTH

REQUIREMENTS.

BOLT

PN NAS6405A17 OR

PN NAS6405A18 OR

PN NAS6405A19 OR 

PN NAS6405A20

(04 POSITIONS)

(REMOVE AND DISCARD)

BOLT

PN MS14181−05018L OR

PN MS14181−05020L

(04 POSITIONS)

(INSTALL)

WASHER

PN MS21299C5K

(AS APPLICABLE)

(REMOVE AND DISCARD)

WASHER

PN MS21299−C5

(04 POSITIONS)

(USE A MAXIMUM OF 2 

WASHERS FOR POSITION)

(INSTALL)

WASHER

PN MS21299−5K

(AS APPLICABLE)

(REMOVE AND DISCARD)

WASHER

PN MS21299−5

(04 POSITIONS)

(USE MAXIMUM 2 

WASHERS FOR POSITION)

(INSTALL)

FIGURE 2: BOLTS, WASHERS AND NUTS REPLACEMENT OF THE LOWER EYELET 

FITTING 

 (SHEET 03 OF 04) 
SERVICE BULLETIN

SB No.: 145-53-0082 DATE: 18/Oct/2013 

PAGE: 22 REVISION No.: 

Embraer Copyright © 2013. All rights reserved. 

1

VIEW B

BOLT

PN NAS6407A20D

WASHER

PN NAS1149C0763R

(02 POSITIONS)

NUT

PN PE22072L7

COTTER PIN

PN MS24665−302

(REINSTALL)

WINDSHIELD

CENTER POST

(REF.)

FORWARD

FUSELAGE

(REF.)

NUT

PN NAS1805−5

(04 POSITIONS)

(REMOVE AND DISCARD)

NUT 

PN MS14182L05

(04 POSITIONS)

(INSTALL)

2

1 2

1

1

1

1

4

2

2

2

2

1 2

7

SHIM 

PN 120−04462−001

(REMOVE AND RETAIN)

(REINSTALL)

4 5

4

INSTALL BOLT BY SLIDING IT INTO PLACE.

APPLY SEALANT PN COR−BAN 27L (MEP 09−075). 4

5 REINSTALL THE SHIM IN THE SAME POSITION.

3

6

7

3

6

THE WINDSHIELD CENTER POST MUST BE ALIGNED WITH FORWARD FUSELAGE.

EYELET FITTING

PN 120−44541−003

(REINSTALL)

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

WASHER

PN MS21299−5K

(AS APPLICABLE)

(REMOVE AND DISCARD)

WASHER

PN MS21299−5

(04 POSITIONS)

(USE MAXIMUM 2 

WASHERS FOR POSITION)

(INSTALL)

BOLT

PN NAS6405A17 OR

PN NAS6405A18 OR

PN NAS6405A19 OR

PN NAS6405A20

(04 POSITIONS)

(REMOVE AND DISCARD)

BOLT

PN MS14181−05018L OR

PN MS14181−05020L

(04 POSITIONS)

(INSTALL) WASHER

PN MS21299C5K

(AS APPLICABLE)

(REMOVE AND DISCARD)

WASHER

PN MS21299−C5

(04 POSITIONS)

(USE MAXIMUM 2

WASHERS FOR POSITION)

(INSTALL)

ENSURE THAT AT LEAST

TWO FULL THREADS EXTEND BEYOND

THE NUT

EM145SB531369A.DGN

FIGURE 2: BOLTS, WASHERS AND NUTS REPLACEMENT OF THE LOWER EYELET 

FITTING 

 (SHEET 04 OF 04)
.

..

SERVICE BULLETIN EVALUATION 

THE PURPOSE OF THIS FORM IS TO COLLECT DATA THAT WILL BE USED TO IMPROVE THE QUALITY OF OUR 

SERVICE BULLETINS AND UPDATE THE TECHNICAL PUBLICATION. PLEASE FILL IN FORM AND RETURN IT TO: 

EMBRAER S.A. 

TECHNICAL PUBLICATIONS 

AV. BRIG. FARIA LIMA, 2170 

SÃO JOSÉ DOS CAMPOS - SP - 12227-901 

BRASIL 

Fax: ++ 55 12 3927-7546 

e-mail: fleet.reliability@embraer.com.br

SB Title: SB: (Number / Rev.) 

Operator: Aircraft serial number affected: (per SB effectivity list) 

 

PRE-ACCOMPLISHMENT EVALUATION: (check applicable squares below)

[ ] WILL BE ACCOMPLISHED ON FIRST A/C [ ] WILL BE ACCOMPLISHED AS REQUIRED 

[ ] WILL BE ACCOMPLISHED ON FLEET [ ] DECISION DEFERRED (Explain below) 

[ ] UNECONOMICAL 

[ ] SERVICE EXPERIENCE DOES NOT JUSTIFY 

[ ] OPERATIONAL ENVIRONMENT DOES NOT JUSTIFY [ ] WILL NOT BE ACCOMPLISHED: 

[ ] OTHER (Explain below) 

POST-ACCOMPLISHMENT EVALUATION: (Check applicable squares below)

ESTIMATED MANPOWER: [ ] OK [ ] NOT OK (Explain below) 

MATERIAL & KITS: [ ] OK [ ] NOT OK (Explain below) 

ACCOMPLISHMENT INSTRUCTIONS: [ ] OK [ ] NOT OK (Explain below) 

FIGURES: [ ] OK [ ] NOT OK (Explain below) 

SB GENERAL EVALUATION: [ ] OK [ ] NOT OK (Explain below) 

COMMENTS: (Bulletin quality/ Difficulties found at the time of incorporation/ Suggested improvements/ Other)

Organization: Fax: Phone: 

 

E-mail: 

Address: Prepared by: (Name/ Title) Date: 

 

ENS-003393