# 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 ATTACH MENTS PARTS FROM THE LOWER EYELET FITTING OF THE COCKPIT-WINDSHIELD CENTER POST

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

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:

The SB effectivity is divided into GROUPS of aircra ft, 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 aff ect 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 dedicat ed action to ensure the structures' integrity is required.

(2) OBJECTIVE To ensure the integrity of the four bolts that conn ect 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 aff ects 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 PA RTS Applicable to: GROUPS 1 and 2 aircraft.

PART I of this bulletin presents a Detailed Inspect ion (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 ti ghtness.
To get access to the work area, it is necessary to remove the pilot and copilot seats, glareshield coverage, and the windshield center fai ring. Also, the removal of the display unit 3 (DU-3) may be necessary as an altern ative 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 nec essary 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 fli ght cycles, the incorporation of PART I of this Service Bulletin is recommended within the next 50 flight cycles after the first issuance of S B145-53-A082. Thereafter, PART I of this service bulletin must be repeated ev ery 500 flight cycles until the accomplishment of PART II.

For aircraft that have reached between 10,000 and 1 1,000 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 oc curs first and must be repeated every 500 flight cycles until the accompli shment 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 oc curs first and must be repeated every 1,000 flight cycles until the accomp lishment of PART II. After the aircraft reaches 11,050 flight cycles, PART I o f this service bulletin must be repeated every 500 flight cycles until the accom plishment of PART II.
For aircraft that have reached less than 7,500 flig ht cycles, the incorporation of PART I of this Service Bulletin is recommended w ithin 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 th is service bulletin must be repeated every 500 flight cycles until the accompli shment of PART II.

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

220-803-A00 or MRB Task Reference Number 53-12-00-2 20-814- 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 fli ght cycles after the SB 145-53-0058 incorporation, the incorporation of PAR T I of this Service Bulletin is recommended within the next 50 flight c ycles after the first issuance of SB145-53-A082. Thereafter, PART I of th is service bulletin must be repeated every 500 flight cycles until the accom plishment of PART II.

For aircraft that have reached between 10,000 and 1 1,000 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 aircr aft reaches 11,050 flight cycles after the SB 145-53-0058 incorporation, whic hever 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 aircr aft reaches 10,150 flight cycles after the SB 145-53-0058 incorporation, whic hever occurs first and must be repeated every 1,000 flight cycles until th e 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 u ntil the accomplishment of PART II.
For aircraft that have reached less than 7,500 flig ht 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 aft er 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 a nd 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 th is service bulletin must be repeated every 500 flight cycles until the accompli shment of PART II.

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

220-803-A00 or MRB Task Reference Number 53-12-00-2 20-814- 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 i s recommended immediately after the accomplishment of PART I, if any discrepa ncy is detected during the inspection provided in PART I of this service b ulletin.
Incorporation of PART II of this service bulletin i s recommended in the next Heavy Maintenance Check after the accomplishment of PART I, if no discrepancy is detected during the inspection provi ded 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 whi ch affects the content of this Service Bulletin, the operator will take fu ll 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 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.

# 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 WINDSHIE LD CENTER

POST LOWER EYELET FITTING.

SB145-53-A082 – INSPECTION AND REPLACEMENT OF THE A TTACHMENTS

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 manufac turer or locally purchased, or ordered as spares from Embraer at no charge to the operator during a period of 36 months after the original rel ease 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 MS1418 1-05019L can be installed based on the grip length requirements.

(b) Consumables The material below or equivalent required for the a ccomplishment of this bulletin should be acquired from the operator’s inv entories 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 N EW 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 Detaile d Inspection (DET) is: “An

intensive examination of a specific item, installat ion or assembly to detect damage, failure or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensi ty deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be necessary. Surface cleaning and elaborate access pr ocedures may be required.” 2) For the purpose of this Service Bulletin, a General Visual Inspection (GVI)

is: "A visual examination of an interior or exterio r area, installation or assembly to detect obvious damage, failure or irreg ularity. This level of inspection is made from within touching distance, u nless otherwise specified. A mirror may be necessary to enhance vis ual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such a s daylight, hangar lighting, flashlight or drop-light and may require removal or opening of access panels or doors. Stands, ladders or platform s 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 maintena nce.

B. PART I - INSPECTION OF THE CENTER POST FITTING A TTACHMENT PARTS
(1) Install the landing gear safety pin. Refer to t he 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 c opilot 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 g et 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 ob vious damage of the bolts PN NAS6405A17 or PN NAS6405A18 or PN NAS6405A19 or PN NAS6405A20, washers PN MS21299C5K and PN MS21299-5K, and nuts P N 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 requ irements 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 t o make sure that the bolts are tight, to ensure the bolts and nuts do no t move freely.

NOTE : An alternate means to check for the bolts tightne ss is to torque check them through Display Unit 3 (DU-3) access.
(1) If the bolts are tight, replace the bolts washe rs and nuts of the eyelet fitting of the cockpit windshield center-post in th e next heavy maintenance check, according to PART II of this bul letin.
(2) If the bolt(s) and nut(s) move freely, disassem ble and assemble the nut(s) and washer(s) of the bottom part of the asse mbly, 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 washer s and nuts of the eyelet fitting of the cockpit windshield center-pos t in the next heavy maintenance check, according to PART II of this bul letin.

# 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-pos t 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 cover age (223AZ) on its respective place on the instrument panel. Refer to the applica ble AMM 25-12-07 (TASK 25-12-07-400-801-A) - Equipment/Furnishings.
(10) If removed, install again the windshield cente r 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 copilo t 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 bul letin in the applicable documents.

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

PARTS.
(1) Install the landing gear safety pin. Refer to t he applicable AMM 32-00-01 (TASK 32-00-01-910-801-A) – Landing Gear.
(2) Remove and retain the cockpit windshields (LH a nd 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 c opilot 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 g et 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 NAS6405A1 8 or PN NAS6405A19 or PN NAS6405A20, washers PN MS21299C5K, MS21299-5K and nuts NAS1805-5 of the eyelet fitting of the cockpit wind shield 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 R H 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 Seat s. (10) Put the aircraft back to its initial condition

. (11) Write the accomplishment of PART II of this bu lletin 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 incorpor ated fleetwide or that the SB will not be incorporated, so that Embraer can up date the affected technical publications, use the “Service Bulletin F ull-Fleet Incorporation Report” form, which is available on the Flyembraer portal ( http://www.flyembraer.com ). 3) Use the attached “Service Bulletin Evaluation” f orm to send us your comments regarding this SB. Your feedback will be m uch 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-pos t:
(a) If necessary, remove and discard cotter pin PN MS24665-302 (1 position) and remove and retain nut PN PE22072L7 (1 position), wa shers PN NAS1149C0763R (2 positions), and bolt PN NAS6407A20D (1 position) that attach the lower eyelet fitting to the cockpit windshield center-post to fa cilitate 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 positio ns), washers PN MS21299-5K (as applicable) and PN MS21299C5K (as applicable), and applicable bolts PN NAS6405A17 (4 positions) or PN NAS6405A18 (4 pos itions) or PN NAS6405A19 (4 positions) or PN NAS6405A20 (4 positi ons). If necessary, remove lower eyelet fitting PN 120-44541-003 (1 pos ition) and shim PN 120- 04462-001 (as applicable) from the fuselage structu re 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 P N 120-44541-003.
i. If there are signs of damage, contact the Embra er Technical Support Department.
(c) Clean the sealant from the removed eyelet fitti ng and the fuselage faying area.

2. Follow the step below to replace the bolts, wash ers 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 THA T HAS A GOOD FLOW OF AIR. THE RHODIASOLVE IS POISONOU S AND HIGHLY FLAMMABLE.

FIGURE 2: BOLTS, WASHERS AND NUTS REPLACEMENT OF TH E 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 CHAN GE 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, applyi ng sealant PN COR-BAN 27L (MEP 09-075) and using bolts PN MS14181-05018L (4 p ositions) or PN MS14181-05020L (4 positions), as applicable, wet in sealant PN COR-BAN 27L (MEP 09-075), washers PN MS21299-C5 (as required) a nd PN MS21299-5 (as required), and nuts PN MS14182L05 (4 positions). Re fer to the applicable AMM 20-10-01 – Standard Practices and AMM 53-12-02 (TAS K 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 sli ding. Refer to the applicable AMM 53-12-02 (TASK 53-12-02-400-801-A) - Fuselage. (b) If removed, install windshield center post to l ower eyelet fitting PN 120-44541-003 using bolt PN NAS6407A20D, washers PN NAS1149C0763R and PN NAS1149C0763R, nut PN PE22072L7 and a new cotter pi n 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 TH E 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 TH E 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) 5

4 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 TH E LOWER EYELET FITTING (SHEET 04 OF 04). . .



### SERVICE BULLETIN EVALUATION

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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 o f incorporation/ Suggested improvements/ Other)

Organization: Fax: Phone:

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

ENS-003393