SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 

REVISION No.: PAGE: 1 of 45 

Embraer Copyright © 2011. All rights reserved.

Copyright © 2011 by EMBRAER S.A. All rights reserved. 

STABILIZERS – IMPROVEMENT IN LIGHTNING PROTECTION OF THE TAIL BOOM 

1. PLANNING INFORMATION

A. SB EFFECTIVITY 

Aircraft affected: 

MODEL SN 

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

145540, 145549, 145555, 145586, 145625, 145637, 145642, 

145644, 145678, 145686, 145699, 145706, 145711, 145717, 

145730, 145770, 145775, 145780, 145789, 145796, 14500802, 

14500809, 14500818, 14500825, 14500832, 14500841, 14500851, 

14500854, 14500863, 14500867, 14500873, 14500880, 14500884, 

14500891, 14500901, 14500903, 14500910, 14500913, 14500916, 

14500919, 14500925, 14500933, 14500937, 14500939, 14500941, 

14500942, 14500944, 14500946, 14500948, 14500950, 14500952, 

14500954, 14500955, 14500957, 14500960, 14500961, 14500963, 

14500965 thru 14500967, 14500969 thru 14500976, 14500978 thru 

14500983, 14500985, 14500986, 14500988 thru 14500991, 

14500993 thru 14500995, 14500997 thru 14500999, 14501001 thru 

14501004, 14501006 thru 14501008, 14501010 thru 14501012, 

14501014 thru 14501018, 14501020, 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 14501091, 14501094 thru 14501096, 14501098 thru 

14501100, 14501102, 14501105 thru 14501107, 14501109 thru 

14501111, 14501113, 14501114, 14501117 thru 14501123, 

14501126 thru 14501128, 14501131 thru 14501134, and 14501136 

thru 14501145. 
SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 

PAGE: 2 REVISION No.: 

Embraer Copyright © 2011. All rights reserved.

In-production effectivity: 

EMB-135BJ model aircraft SN 14501092, 14501103, and 14501146 and on, have an 

equivalent modification factory-incorporated. 

The SB effectivity is divided into 02 GROUPS of aircraft, as follows: 

(1) GROUP 1 

MODEL SN 

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

145540, 145549, 145555, 145586, 145625, 145637, 145642, 

145644, 145678, 145686, 145699, 145706, 145711, 145717, 

145730, 145770, 145775, 145780, 145789, 145796, 14500802, 

14500809, 14500818, 14500825, 14500832, 14500841, 14500851, 

14500854, 14500863, 14500867, 14500873, 14500880, 14500884, 

14500891, 14500901, 14500903, 14500910, 14500913, 14500916, 

14500919, 14500925, 14500933, 14500937, 14500939, 14500941, 

14500942, 14500944, 14500946, 14500948, 14500950, 14500952, 

14500954, 14500955, 14500957, 14500960, 14500961, 14500963, 

14500965 thru 14500967, 14500969 thru 14500976, 14500978 thru 

14500983, 14500985, 14500986, 14500988 thru 14500991, 

14500993 thru 14500995, 14500997 thru 14500999, 14501001 thru 

14501004, 14501006 thru 14501008, 14501010 thru 14501012, 

14501014 thru 14501018, 14501020, 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 14501091, 14501094 thru 14501096, 14501098 thru 

14501100, 14501102, 14501105 thru 14501107, 14501109 thru 

14501111, 14501113, 14501114, 14501117 thru 14501123, 

14501126 thru 14501128, 14501131 thru 14501134, and 14501136 

thru 14501145 if equipped with Movable Tail Boom With Two 

Navigation Lights. 
SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 

REVISION No.: PAGE: 3 

Embraer Copyright © 2011. All rights reserved.

(2) GROUP 2 

MODEL SN 

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

145540, 145549, 145555, 145586, 145625, 145637, 145642, 

145644, 145678, 145686, 145699, 145706, 145711, 145717, 

145730, 145770, 145775, 145780, 145789, 145796, 14500802, 

14500809, 14500818, 14500825, 14500832, 14500841, 14500851, 

14500854, 14500863, 14500867, 14500873, 14500880, 14500884, 

14500891, 14500901, 14500903, 14500910, 14500913, 14500916, 

14500919, 14500925, 14500933, 14500937, 14500939, 14500941, 

14500942, 14500944, 14500946, 14500948, 14500950, 14500952, 

14500954, 14500955, 14500957, 14500960, 14500961, 14500963, 

14500965 thru 14500967, 14500969 thru 14500976, 14500978 thru 

14500983, 14500985, 14500986, 14500988 thru 14500991, 

14500993 thru 14500995, 14500997 thru 14500999, 14501001 thru 

14501004, 14501006 thru 14501008, 14501010 thru 14501012, 

14501014 thru 14501018, 14501020, 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 14501091, 14501094 thru 14501096, 14501098 thru 

14501100, 14501102, 14501105 thru 14501107, 14501109 thru 

14501111, 14501113, 14501114, 14501117 thru 14501123, 

14501126 thru 14501128, 14501131 thru 14501134, and 14501136 

thru 14501145 if equipped with Movable Tail Boom With Four 

Navigation Lights. 

B. CONCURRENT REQUIREMENTS 

The accomplishment of Service Bulletin SB145LEG-33-0004 in its original Issue or a 

subsequent approved revision is required prior to the accomplishment of this Service 

Bulletin. 
SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 

PAGE: 4 REVISION No.: 

Embraer Copyright © 2011. All rights reserved.

C. REASON 

(1) HISTORY 

During a troubleshooting following a reported of elevator control restriction the 

maintenance personnel found a frame loosed from the tail boom jamming a 

bellcrank. Further investigation revealed that this damage was caused by a 

lightning-strike that hit the tail boom area. 

(2) OBJECTIVE 

To install lightning diverters in the tail boom, replace the hood assembly with a 

new improved one and reroute the electrical harness. 

(3) EXPECTED BENEFITS 

To improve the electrical path for the lightning current, thereby minimizing 

lightning direct effects on the aircraft. 

(4) REVISION HISTORY 

None. 

D. DESCRIPTION 

The modification described of this bulletin consists of the installation of metallic 

diverters, aluminum sheets and improvements on lights assembly on the tail boom 

rear movable fairing, and also to replace the hood assembly with new one and reroute the applicable electrical harness to minimize lightning direct effects. 

To do this, it is necessary to remove the rear movable fairing of the tail boom. 

E. COMPLIANCE 

Embraer recommends that this bulletin be accomplished during the scheduled 

maintenance check of 48 months. 
SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 

REVISION No.: PAGE: 5 

Embraer Copyright © 2011. All rights reserved.

F. APPROVAL 

The technical aspects of this Service Bulletin are approved by: ANAC – Agência 

Nacional de Aviação Civil. 

G. ESTIMATED MANPOWER 

This estimate is for direct labor only, performed by experienced personnel, and does 

not include the time to plan, prepare, or inspect the work. 

It is assumed that all the tools, parts, and other means are promptly available when 

necessary. 

This estimate does not include the sealant, paint, or adhesive curing time. 

- Access opening: 1.5 man-hours. 

- Inspection: None. 

- Modification: 5.5 man-hours. 

- Access closure: 1.5 man-hours. 

- Test: 1.0 man-hour. 

H. WEIGHT AND BALANCE 

- Change in basic weight: None 

- Change in basic moment: None 
SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 

PAGE: 6 REVISION No.: 

Embraer Copyright © 2011. All rights reserved.

I. ELECTRICAL LOAD DATA 

Not affected. 

J. REFERENCES 

AMM 145/( ) – Aircraft Maintenance Manual – Chapter 20-13-21 – Standard 

Practices - Airframe. 

AMM 145/( ) – Aircraft Maintenance Manual – Chapter 55-36-05 – Stabilizers. 

SRM 145/( ) – Structural Repair Manual – Chapter 51-20-01 and 51-40-04 – 

Standard Practices and Structures. 

K. OTHER PUBLICATIONS AFFECTED 

IPC 145/( ) – Illustrated Parts Catalog – Chapter 55-36-00 – Stabilizers. 

AMM 145/( ) – Aircraft Maintenance Manual – Chapter 55-36-00 – Stabilizers. 
SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 

REVISION No.: PAGE: 7 

Embraer Copyright © 2011. All rights reserved.

2. MATERIAL INFORMATION

A. MATERIAL – PRICE AND AVAILABILITY 

(1) MATERIAL AVAILABLE FROM EMBRAER 

The material below required for the accomplishment of this bulletin will be 

available from Embraer. 

Lead Times for delivery are conservative and are estimated from the date 

Embraer gets the purchase order. 

The prices are for reference only, subject to confirmation upon receipt of orders. 

When ordering, specify SB 145LEG-55-0013 and Top Kit PN presented in Table 

below, as applicable. 

REF TOP KIT PN Lead Time

(weeks) 

Unit Price 

(US$) TOP KIT EFFECTIVITY 

01 BSLEG5500130001 08 1.251,36 GROUP 1. 

02 BSLEG5500130002 08 1.227,84 GROUP 2. 

(2) MATERIAL AVAILABLE FROM OTHER VENDORS 

None. 

B. INDUSTRY SUPPORT INFORMATION 

(1) WARRANTY COVERAGE 

(a) Parts 

The SB kit will be provided at no charge. 

(b) Labor 

Embraer will compensate 9,5 hours for the SB incorporation if it is performed 

in an Embraer authorized service center. 
SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 

PAGE: 8 REVISION No.: 

Embraer Copyright © 2011. All rights reserved.

(c) Expiration 

The terms expressed in the warranty coverage will be valued for 48 months 

after the SB issue date. 

C. MATERIAL NECESSARY FOR EACH AIRCRAFT 

When applicable, the use of alternative or similar parts in place of the ones specified 

in the kit is allowable, provided that these alternative or similar parts are approved by 

Embraer. Refer to IPC Optional PN Cross-Reference List. 

The expendable or consumable parts presented in the AMM Tasks referred to in this 

bulletin, which are necessary for its accomplishment, should be procured from the 

operator's inventories or ordered as spares. 

The complementary information, when necessary, is presented as Notes in the 

respective Table. 

(1) TOP KITS AND KITS 

Kit Summary: Top Kit Composition (Kit PN / Quantity) 

Top Kit PN 145-03536-611 145-54608-607 145-03535-621 

BSLEG5500130001 01 01 -

BSLEG5500130002 - 01 01
SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 

REVISION No.: PAGE: 9 

Embraer Copyright © 2011. All rights reserved.

(a) Kit PN 145-03536-611 - Electrical kit for Tail Boom With two Navigation Lights 

NEW PN DESCRIPTION OLD PN QTY 

SUP 

QTY

RQD 

DISP/

Notes 

145-23046-403 Hood assy 145-23046-401 01 01 3 

H14-04 Nut H14-04 02 02 7 

H14-08 Nut - 02 02 2 

MS24693-C6 Screw - 02 02 2 

MS24694-C6 Screw - 02 02 2 

MS35206-214 Screw MS35206-214 02 02 7 

MS35338-40 Lock washer MS35338-40 04 04 7 

MS35489-8 Grommet MS35489−8 01 01 7 

NAS1149CN832R Washer - 01 01 2 

NAS1149FN416P Washer NAS1149FN416P 04 04 7 

NAS1149FN832P Washer - 02 02 2 

NAS1197-4L Washer NAS1197-4L 04 04 7 

NAS1801-08-8 Screw - 01 01 2 

PE21101-3-1CP Screw PE21101−3−2CP 07 07 3 

PE21101-3-2CP Screw - 06 06 2 

PE27019RI5 Clamp, chushion - 03 03 2 

PE88001-5AA8 Jumper assy PE88001−5AA6 02 02 3 

(b) Kit PN 145-54608-607 – Rework kit for rear movable fairing 

NEW PN DESCRIPTION OLD PN QTY 

SUP 

QTY 

RQD 

DISP/ 

Notes 

145-54611-004 Lightning sheet - 01 01 2

145-54611-005 Lightning sheet - 01 01 2 

145-54614-003 Lightning diverter - 01 01 2 

145-54614-007 Lightning diverter - 02 02 2 

145-54614-009 Lightning diverter - 01 01 2 

CCR244CS-3-2 Blind rivet csk 100 deg - 75 62 2 

MS20426AD3-4 Solid rivet csk 100 deg - 11 08 2 

MS20426AD3-5 Solid rivet csk 100 deg - 11 08 2 

MS20426AD4-7 Solid rivet csk 100 deg - 04 02 2 

MS21060L3 Nut plate - 30 27 2 

MS21062L3 Nut plate - 05 04 2 
SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 

PAGE: 10 REVISION No.: 

Embraer Copyright © 2011. All rights reserved.

NEW PN DESCRIPTION OLD PN QTY

SUP 

QTY 

RQD 

DISP/

Notes 

NAS620A5L Washer - 26 20 2 

NAS9301B-4-05 Blind rivet - 02 01 2 

NAS9302B-4-02 Blind rivet csk 100 deg - 02 01 2 

NAS9302B-4-03 Blind rivet csk 100 deg - 24 18 2 

PE21101-3-2CP Screw - 34 31 2 

PE29051Z-3CH Support assy - 01 01 2 

- Support TW2S6 01 01 5 

- Support MS3340-1-9 01 01 5 

(c) Kit PN 145-03535-621 – Electrical kit for Tail Boom With four Navigation Lights 

NEW PN DESCRIPTION OLD PN QTY

SUP 

QTY 

RQD 

DISP/

Notes 

145-23046-403 Hood assy 145-23046-401 01 01 3 

H14-04 Nut H14-04 02 02 7 

H14-08 Nut - 02 02 2 

MS24693-C6 Screw - 02 02 2 

MS24694-C6 Screw - 02 02 2 

MS35338-40 Lock washer MS35338-40 02 02 7 

MS35489-8 Grommet MS35489-8 01 01 7 

NAS1149CN832R Washer - 01 01 2 

NAS1149FN416P Washer NAS1149FN416P 02 02 7 

NAS1149FN832P Washer - 02 02 7 

NAS1197-4L Washer NAS1197-4L 02 02 7 

NAS1801-08-8 Screw - 01 01 2 

PE21101-3-1CP Screw PE21101−3−2CP 07 07 3 

PE21101-3-2CP Screw - 06 06 2 

PE27019RI5 Clamp, cushion - 03 03 2 

(2) MATERIAL TO BE PROCURED 

(a) Parts 

None. 
SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 

REVISION No.: PAGE: 11 

Embraer Copyright © 2011. All rights reserved.

(b) Consumables 

The material below or equivalent, required for the accomplishment of this 

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

supplier. 

ITEM PN DESCRIPTION QTY DISP/ 

Notes 

P/S870C-12 Sealant (Spec. MIL-PRF-81733) AR 6 

PR1440B2 Sealant (Spec. SAE AMS-S-8802) AR 6 

PR1776M B2 654 SEMKIT Sealant (Spec. AMS3281) AR 6 

PR1776M B1/2 654 SEMKIT Sealant (Spec. AMS3281) AR 6 

SB496 Cyanoacrylate adhesive (Spec. MEP 

09-033) AR 6 

P/S870-B1/2 Sealant (Spec. MIL-PRF-81733) AR 6 

ALODINE 1200S Chemical Conversion Compound 

(Spec. MIL-DTL-81706) AR 6 

QUANTITY: 

AR = As Required. 

DISPOSITION: 

2 = Incorporate part bearing NEW PN 

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

6 = Apply as required 

7 = Replace with part bearing same PN 

D. MATERIAL NECESSARY FOR EACH SPARE 

None. 
SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 

PAGE: 12 REVISION No.: 

Embraer Copyright © 2011. All rights reserved.

E. REIDENTIFIED PARTS 

The information necessary to modify and/or reidentify the parts, when necessary, is 

presented in the referenced Notes. 

DESCRIPTION OLD PN NEW PN 

145-53615-403 

Movable Tail Boom fairing assy 145-21648-433 

145-03536-401 

145-03536-603 

Movable Tail Boom fairing assy 145-03535-401 145-03535-603 

Movable Tail Boom fairing assy 145-03535-409 145-03535-617 

145-38445-403 Movable Tail Boom fairing assy 145-38445-407 145-03535-413 

Movable Tail Boom fairing 145-21649-417 

Movable Tail Boom fairing 145-21649-419 140-13327-601 

F. TOOLING – PRICE AND AVAILABILITY 

Whenever required, the tooling presented in the AMM Tasks referred to in this 

bulletin, should be procured from the operator’s inventories or ordered as spares. 
SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 

REVISION No.: PAGE: 13 

Embraer Copyright © 2011. All rights reserved.

3. ACCOMPLISHMENT INSTRUCTIONS

NOTES: 1) Obey all of the WARNINGS and CAUTIONS included in the referenced 

manuals and procedures. 

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

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

more complete definition. 

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. Remove the rear movable fairing of the tail boom. Refer to the applicable Aircraft 

Maintenance Manual – Chapter 55-36-00 – Stabilizers. 

C. Rework the movable fairing of the tail boom according Figure 1. 

D. Carry out the electrical modification to the rear movable fairing according Figure 2 

(GROUP 1) or Figure 3 (GROUP 2), as applicable. 

E. Reinstall the rear movable fairing of the tail boom according to the applicable Aircraft 

Maintenance Manual – Chapter 55-36-00 – Stabilizers, and perform the following 

electrical bonding test: 

a Do the electrical bonding test according to the applicable Aircraft Maintenance 

Manual – Chapter 20 (TASK 20-13-21-700-801-A) – Standard Practices – 

Airframe. 

NOTE: Measure the electrical resistance value between the electrical 

connector P0834 and the primary structure. The maximum allowed 

resistance value is 15 miliohms. 

F. Paint the reworked area with customer’s color scheme. Refer to Corrosion 

Prevention Manual, Chapter 51-21-06. 
SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 

PAGE: 14 REVISION No.: 

Embraer Copyright © 2011. All rights reserved.

G. Restore the aircraft to normal. 

H. Enter the accomplishment of this bulletin in the applicable documents. 

I. Fill out the attached “Service Bulletin Implementation and Evaluation” form and return 

it to: 

EMBRAER S.A. 

Customer Support Contact Center 

Embraer Executive Jets 

contact.center@embraer.com

24/7 Toll Free Numbers 

1 888 362-2648 USA & Canada 

0800 704 1099 Brazil 

24/7 International Numbers 

1 703 621-7350 North America, including Mexico, & Caribbean 

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

+65 6307-7647 Asia Pacific 

+55 12 3927-7000 Latin America 

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

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

publications, use the “Service Bulletin Full-Fleet Incorporation Report” form, 

which is available on the Flyembraer portal (http://www.flyembraer.com). 
SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 

REVISION No.: PAGE: 15 

Embraer Copyright © 2011. All rights reserved.

1. Position sheets PN 145-54611-004 (RH) and PN 145-54611-005 (LH) on the rear 

movable fairing and transfer the existing holes from fairing to sheet and from sheet 

to fairing, using the dimension shown in view B and G as a guide. 

2. Drill the holes marked in step 1. 

3. Countersink sheets PN 145-54611-004 (RH) and PN 145-54611-005 (LH) to install 

screws and rivets according to the dimensions shown in detail D. 

4. Install nut plate PN MS21062L3 (4 positions) by using rivet PN CCR244CS-3-2 

(2 positions). Refer to details D and H. 

5. Install sheets PN 145-54611-004 (RH) and PN 145-54611-005 (LH) to the rear 

movable fairing by using rivet PN NAS9302B-4-03 (18 positions) and washer PN 

NAS620A5L (18 positions). Refer to details C and D. 

NOTE: Before installation, apply interface sealant PN P/S870C-12 (Spec. MILPRF-81733 Type IV Class 12) and fillet sealant PN PR1440B2 (Spec. SAE 

AMS-S-8802 Type II Class B2). Refer to the applicable Structural Repair 

Manual – Chapter 51-20-01 – Standard Practices and Structures. 

6. Install support PN PE29051Z-3CH to the rear movable fairing according to sections 

J-J and K-K, and details L and L1 and the following instructions: 

(a) Remove and discard existing support PN MS3340-1-9. 

(b) Plug the hole with rivet PN NAS9301B-4-05. 

(c) Position new support PN PE29051Z-3CH on the rear movable fairing. 

(d) Transfer, drill and countersink the hole. 

(e) Install the support using rivet PN MS20426AD4-7 (2 positions). 

7. Position diverters PN 145-54614-003 (1 position), PN 145-54614-009 (1 position), 

and PN 145-54614-007 (2 positions) on the rear movable fairing, mark and drill 

holes in the fairing using the existing holes of the diverters and the dimensions 

shown in details C, D, E and F as a guide. 

8. Remove the diverters and install nut plate PN MS21060L3 (27 positions) from the 

rear movable fairing using rivet PN CCR244CS-3-2 (54 positions). Refer to detail D. 

- APPLICABLE TO GROUP 1 AND GROUP 2 

FIGURE 1: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE TAIL BOOM 

(SHEET 01 OF 13)
SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 

PAGE: 16 REVISION No.: 

Embraer Copyright © 2011. All rights reserved.

9. Install diverters PN 145-54614-003 (1 position), PN 145-54614-009 (1 position), 

and PN 145-54614-007 (2 positions) to the rear movable fairing using screw PN 

PE21101-3-2CP (31 positions). Refer to details C, E and F. 

NOTES: (1) Carry out the electrical bonding according to the applicable Aircraft 

Maintenance Manual – Chapter 20 (TASK 20-13-21-910-801-A) – 

Standard Practices - Airframe. 

(2) Apply fillet sealant PN PR1440B2 (Spec. SAE AMS-S-8802 Type II 

Class B2) and interface sealant PN P/S870C-12 (Spec. MIL-PRF81733 Type IV Class 12) except in the surface prepared for 

electrical bonding shown in the figure. Refer to the applicable 

Structural Repair Manual – Chapter 51-20-01 – Standard Practices 

and Structures. 

10. Remove the existing rivet and enlarge the hole to 25.4 mm, as shown in section PP. 

11. Remove and discard the existing electrical support PN TM2S6 by removing its 

attached rivet. Plug the hole with rivet PN NAS9302B-4-02 and washer PN 

NAS620A5L. Refer to detail Q. 

12. At the stabilizer structure, remove and retain nut plate PN MS21062L3 (6 positions) 

and PN MS21060L3 (2 positions) and discard the attaching rivets. Refer to detail T 

(PRE MOD) and Structural Repair Manual – Chapter 51-40-02 – Standard 

Procedures. 

13. Reinstall the removed nut plates PN MS21062L3 (6 positions) and PN MS21060L3 

(2 positions) using rivets PN MS20426AD3-5 (8 positions) and PN MS20426AD3-4 

(8 positions) according to detail T (POST MOD). Refer to Structural Repair Manual 

– Chapter 51-40-02 and 51-40-03 – Standard Procedures. 

14. Apply a fillet of sealant PN PR1776M B2 654 SEMKIT to the contour of the part. 

Refer to detail U. 

- APPLICABLE TO GROUP 1 AND GROUP 2 

FIGURE 1: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE TAIL BOOM 

(SHEET 02 OF 13)
SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 

REVISION No.: PAGE: 17 

Embraer Copyright © 2011. All rights reserved.

15. With a permanent marker pen or a rubber stamp, re-identify the movable Tail Boom 

fairing according to the Table, below: 

REIDENTIFICATION TABLE

FROM TO 

145-21649-417 140-13327-601 

145-21649-419 140-13327-601 

- APPLICABLE TO GROUP 1 AND GROUP 2 

FIGURE 1: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE TAIL BOOM 

(SHEET 03 OF 13) 
SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 

PAGE: 18 REVISION No.: 

Embraer Copyright © 2011. All rights reserved.

A

ZONE

321

C

D

E

DET. A

F

REAR FIXED

FAIRING

DET. B

B

T

EM145SB550346A.DGN

- APPLICABLE TO GROUP 1 AND GROUP 2 

FIGURE 1: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE TAIL BOOM 

(SHEET 04 OF 13) 
SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 

REVISION No.: PAGE: 19 

Embraer Copyright © 2011. All rights reserved.

SHEET

PN 145−54611−004 (RH)

(INSTALL)

2

1

1

1

1

APPLY INTERFACE SEALANT PN P/S870C−12 AND FILLET SEALANT PN PR1440B2.

REAR MOVABLE

FAIRING

(REF.)

1 5

7

7

5

DIVERTER

PN 145−54614−007

(INSTALL)

7

DIVERTER

PN 145−54614−003

(INSTALL)

DET. C

1

1

DIVERTER

PN 145−54614−007

(INSTALL)

1 7

DIVERTER

PN 145−54614−009

(INSTALL)

SHEET

PN 145−54611−005 (LH)

(INSTALL)

EM145SB550347A.DGN

- APPLICABLE TO GROUP 1 AND GROUP 2 

FIGURE 1: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE TAIL BOOM 

(SHEET 05 OF 13)
SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 

PAGE: 20 REVISION No.: 

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Y

0.0

SCREW

PN PE21101−3−4CP

(4 POSITIONS)

(INSTALL)

SCREW

PN PE21101−3−4CP

(4 POSITIONS)

(INSTALL)

10.0

RIVET

PN NAS9302B−4−03

(9 POSITIONS)

WASHER

PN NAS620A5L

(9 POSITIONS)

(INSTALL)

RIVET

PN NAS9302B−4−03

(9 POSITIONS)

WASHER

PN NAS620A5L

(9 POSITIONS)

(INSTALL)

4

2 5

4

2 5

2 3 5

2 3 5

H

DIMENSION IN mm

DET. G

Ø5.1

Ø5.3

1.3

RIVET

PN CCR244CS−3−2

(2 POSITIONS)

(INSTALL)

8 8

9

DET. H

TYPICAL

DET. D

G

G

NUT PLATE

PN MS21060L3

(14 POSITIONS)

RIVET

PN CCR244CS−3−2

(2 POSITIONS PER NUT PLATE)

(INSTALL)

EM145SB550348A.DGN

8

8

NUT PLATE

PN MS21062L3

(2 POSITIONS)

(INSTALL)

NUT PLATE

PN MS21060L3

(13 POSITIONS)

RIVET

PN CCR244CS−3−2

(2 POSITIONS PER NUT PLATE)

(INSTALL)

NUT PLATE

PN MS21062L3

(2 POSITIONS)

(INSTALL)

NUT PLATE

PN MS21060L3

(INSTALL)

SCREW

PN PE21101−3−2CP

(INSTALL) 130°

- APPLICABLE TO GROUP 1 AND GROUP 2 

FIGURE 1: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE TAIL BOOM 

(SHEET 06 OF 13) 
SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 

REVISION No.: PAGE: 21 

Embraer Copyright © 2011. All rights reserved.

ZV

3755.0

ZV

3604.5

X

28135.9

SPAR III

X

28644.9

X

29075.0

VT

100%

X

29786.4

K K

P P

N N

S S

DET. E

9

R R

Q

EM145SB550349A.DGN

X

29075.0

VT

100%

X

29786.4

33.0 100.0

DET. E1

E1

DO NOT APPLY SEALANT IN THIS AREA. 6

6

SCREW

PN PE21101−3−2CP

(13 POSITIONS)

(INSTALL)

SCREW

PN PE21101−3−2−CP

(2 POSITIONS)

(INSTALL TOGETHER 

WITH THE HOOD ASSY)

9

- APPLICABLE TO GROUP 1 AND GROUP 2 

FIGURE 1: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE TAIL BOOM 

(SHEET 07 OF 13) 
SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 

PAGE: 22 REVISION No.: 

Embraer Copyright © 2011. All rights reserved.

ZV

3755.0

ZV

3604.5

X

28135.9

SPAR III

X

28644.9

X

29075.0

VT

100%

X

29786.4

9

X

29075.0

VT

100%

X

29786.4

100.0

DET. F1

F1

DO NOT APPLY SEALANT IN THIS AREA. 6

6

EM145SB550355A.DGN

DET. F

SCREW

PN PE21101−3−2CP

(14 POSITIONS)

(INSTALL)

SCREW

PN PE21101−3−2−CP

(2 POSITIONS)

(INSTALL TOGETHER 

WITH THE HOOD ASSY)

9

S S

DIMENSIONS IN MM

- APPLICABLE TO GROUP 1 AND GROUP 2 

FIGURE 1: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE TAIL BOOM 

(SHEET 08 OF 13) 
SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 

REVISION No.: PAGE: 23 

Embraer Copyright © 2011. All rights reserved.

Y

0.0

ZV

3755.0

Y

0.0

ZV

3755.0

HARNESS SUPPORT

PN MS3340−1−9

EXISTING RIVET

(REMOVE AND DISCARD)

6

6

4

NUT PLATE

PN MS21062L3

(4 POSITIONS)

(INSTALL)

RIVET

PN NAS9301B−4−05

WASHER

PN NAS620A5L

(INSTALL)

EM145SB550350A.DGN

SECTION J−J

(POST MOD)

SECTION J−J

(PRE MOD)

M K

- APPLICABLE TO GROUP 1 AND GROUP 2 

FIGURE 1: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE TAIL BOOM 

(SHEET 09 OF 13) 
SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 

PAGE: 24 REVISION No.: 

Embraer Copyright © 2011. All rights reserved.

DIVERTER

(REF.)

SHEET

(REF.)

REAR MOVABLE

FAIRING 

(REF.)

NUT PLATE

(REF.)

DET. M

TYPICAL

SECTION N−N

1

Ø6.3

Ø6.1

DIMENSIONS IN MM

SHEET

(REF.)

REAR MOVABLE

FAIRING 

(REF.)

Ø3.4

Ø3.2

1.2

SUPPORT

PN PE29051Z−3CH

(1 POSITION)

RIVET

PN MS20426AD4−7

(2 POSITIONS)

(INSTALL)

6

SHEET

(REF.)

SUPPORT

PN PE29051Z−3CH

(1 POSITION)

RIVET

PN MS20426AD4−7

(2 POSITIONS)

(INSTALL)

RIVET

PN CCR244CS−3−2

(2 POSITIONS)

(INSTALL)

EM145SB550351A.DGN

6

141°

86°

DET. K

L

DET. L

100°

90°

- APPLICABLE TO GROUP 1 AND GROUP 2 

FIGURE 1: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE TAIL BOOM 

(SHEET 10 OF 13) 
SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 

REVISION No.: PAGE: 25 

Embraer Copyright © 2011. All rights reserved.

PRE − MOD

HARNESS SUPPORT

PN TM2S6

EXISTING RIVET

(REMOVE AND DISCARD)

RIVET

PN NAS9302B−4−02

WASHER

PN NAS620A5L

(INSTALL)

REMOVE THE EXISTING RIVET AND ENLARGE THE HOLE TO DIAMETER 25.4 MM

3

3

Y

0.0

ZV

3755.0

POST − MOD

10

11

11

DET. Q DET. Q

SECTION P−P

EXISTING RIVET

(REMOVE AND DISCARD

ENLARGE THE HOLE)

EM145SB550352A.DGN

- APPLICABLE TO GROUP 1 AND GROUP 2 

FIGURE 1: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE TAIL BOOM 

(SHEET 11 OF 13) 
SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 

PAGE: 26 REVISION No.: 

Embraer Copyright © 2011. All rights reserved.

2

2

100°

Ø 8.5

2

100°

Ø 8.5

SECTION R−R

DIMENSION IN mm

SECTION S−S

TYPICAL

APPLY ALODYNE ON THE COUNTERSINK AREA FOR BONDING.

(LH SIDE SHOWN,

RH SIDE OPPOSITE)

EM145SB550353A.DGN

4.0 ± 0.1

4.6 ± 0.1

- APPLICABLE TO GROUP 1 AND GROUP 2 

FIGURE 1: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE TAIL BOOM 

(SHEET 12 OF 13) 
SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 

REVISION No.: PAGE: 27 

Embraer Copyright © 2011. All rights reserved.

(PRE−MOD)

1 APPLY A FILLET OF SEALANT PN PR1776M B2 654 SEMKIT TO THE CONTOUR OF THE PART.

(POST−MOD)

U

DET. U

1

DET. T

DET. T

EM145SB550354A.DGN

SUPPORT

(APPLY SEALANT)

14

Y

0.0

YH

30.0

YH

−30.0

1

1

1

1

NUT PLATE

PN MS21060L3

(RETAIN)

NUT PLATE

PN MS21060L3

(RETAIN)

NUT PLATE

PN MS21062L3

(3 POSITIONS)

(RETAIN)

NUT PLATE

PN MS21062L3

(3 POSITIONS)

(RETAIN)

13

13

13

13

NUT PLATE 13

PN MS21062L3

(2 POSITIONS)

(REINSTALL)

RIVET

PN MS20426AD3−4

(4 POSITIONS)

(INSTALL)

NUT PLATE

PN MS21062L3

(REINSTALL)

RIVET

PN MS20426AD3−5

(2 POSITIONS)

(INSTALL)

NUT PLATE

PN MS21060L3

(REINSTALL)

RIVET

PN MS20426AD3−5

(2 POSITIONS)

(INSTALL)

13

NUT PLATE

PN MS21060L3

(REINSTALL)

RIVET

PN MS20426AD3−5

(2 POSITIONS)

(INSTALL)

NUT PLATE

PN MS21062L3

(REINSTALL)

RIVET

PN MS20426AD3−5

(2 POSITIONS)

(INSTALL)

NUT PLATE

PN MS21062L3

(2 POSITIONS)

(REINSTALL)

RIVET

PN MS20426AD3−4

(4 POSITIONS)

(INSTALL)

- APPLICABLE TO GROUP 1 AND GROUP 2 

FIGURE 1: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE TAIL BOOM 

(SHEET 13 OF 13) 
SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 

PAGE: 28 REVISION No.: 

Embraer Copyright © 2011. All rights reserved.

1. Remove and discard hood assembly PN 145-23046-401 by removing screw PN 

PE21101-3-2CP (9 positions). Refer to detail B. 

2. Disconnect electrical connectors P0707, P0708, and P0715. Refer to detail B (PRE 

MOD). 

3. Remove and discard grommet PN MS35489-8. Refer to detail A (PRE MOD). 

4. Remove and discard bonding jumper PN PE88001-5AA6 (2 positions) by removing 

screw PN MS35206-216 and PN MS35206-214, washer PN NAS1149FN416P 

(2 positions per bonding jumper), PN MS35338-40 (2 positions per bonding jumper), 

and PN NAS1197-4L (3 positions per bonding jumper), and nut PN H14-04. Refer to 

detail B (PRE MOD) and section C-C (PRE MOD). 

5. Reroute electrical harness W308 and install clamp PN PE27019RI5 with screw PN 

NAS1801-08-8, washer PN NAS1149CN832R, and clamp PN PE27019RI5 with 

screw PN MS24694-C6, washer PN NAS1149FN832P, and nut PN H14-08. Refer to 

Detail A (Post-Mod). 

6. Install grommet PN MS35489-8 with cyanoacrylate adhesive PN SB496. Fill gaps 

and free spaces with sealant PN PR1776M B1/2 654 SEMKIT (Spec AMS 3281, 

class B), or similar. Refer to detail D. 

7. Install new bonding jumper PN PE88001-5AA8 using screw PN MS35206-214 and 

PN MS24693-C6, washer PN MS35338-40 (2 positions per bonding jumper), PN 

NAS1149FN416P (2 positions per bonding jumper), and PN NAS1197-4L (2 

positions per bonding Jumper), and nut PN H14-04. Refer to detail B, and section DD (PRE MOD) and E-E. 

NOTE: Carry out the electrical bonding procedure, method 3. Refer to the 

applicable Aircraft Maintenance Manual - Chapter 20-13-21 - Standard 

Practices - Airframe.

- APPLICABLE TO GROUP 1 

FIGURE 2: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL 

SYSTEM 

(SHEET 01 OF 09) 
SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 

REVISION No.: PAGE: 29 

Embraer Copyright © 2011. All rights reserved.

8. Connect electrical connectors P0707, P0708, and P0715. Refer to detail B (POST 

MOD). 

9. Install hood assembly PN 145-23046-403 between diverters and fairing with screws 

PN PE21101-3-1CP (7 positions) and PN PE21101-3-2CP (6 positions). Refer to 

detail B (POST MOD) and section F-F. 

NOTES: (1) Carry out the electrical bonding procedure, method 3. Refer to the 

applicable Aircraft Maintenance Manual - Chapter 20-13-21 - 

Standard Practices - Airframe. 

(2) Apply aerodynamic sealant P/S870-B1/2 along the contour of the 

hood assy. Refer to the applicable Structural Repair Manual - Chapter 

51-20-01 – Standard Practices and Structures - General. 

10. Complete the application of fillet sealant PN PR1440B2 (Spec. SAE AMS-S-8802 

Type I Class B2) to the lightning diverter (4 positions). Refer to the applicable 

Structural Repair Manual – Chapter 51-20-01 – Standard Practices and Structures. 

Refer to detail A (POST MOD). 

11. Measure the electrical resistance value between the lightning diverters and the 

primary structure. The maximum allowed resistance value is 10 miliohms. Refer to 

the applicable Aircraft Maintenance Manual - Chapter 20-13-21 (TASK 20-13-21-

700-801- A) - Maintenance Practices. Refer detail A (POST MOD). 

12. Measure the electrical resistance value between the static discharger and the 

primary structure. The allowed resistance value is from 6 megaohms to 150 

megaohms. Refer to the applicable Aircraft Maintenance Manual - Chapter 20-13-

21 (TASK 20-13-21-700-801- A) - Maintenance Practices. Refer detail B (POST 

MOD). 

- APPLICABLE TO GROUP 1 

FIGURE 2: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL 

SYSTEM 

(SHEET 02 OF 09)
SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 

PAGE: 30 REVISION No.: 

Embraer Copyright © 2011. All rights reserved.

13. Measure the electrical resistance value between the hood belt and the primary 

structure. The maximum allowed resistance value is 10 miliohms. Refer to the 

applicable Aircraft Maintenance Manual - Chapter 20-13-21 (TASK 20-13-21-700-

801- A) - Maintenance Practices. Refer to detail B (POST MOD). 

14. With a permanent marker pen or a rubber stamp, reidentify the movable Tail Boom 

fairing according to the Table, as follows: 

REIDENTIFICATION TABLE 

FROM TO 

145-53615-403

145-21648-433

145-03536-401

145-03536-603

- APPLICABLE TO GROUP 1 

FIGURE 2: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL 

SYSTEM 

(SHEET 03 OF 09) 
SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 

REVISION No.: PAGE: 31 

Embraer Copyright © 2011. All rights reserved.

A

ZONES

223

224

PRE − MOD

DET. A

CONNECTOR

P0708

(DISCONNECT)

CONNECTOR

P0707

(DISCONNECT)

CONNECTOR

P0715

(DISCONNECT)

2

2

2

GROMMET

PN MS35489−8

(REMOVE AND DISCARD)

3 ELECTRICAL

HARNESS W308

(REF.)

DET. B

B

C

C

1

HOOD ASSY

PN 145−23046−401

(REMOVE AND DISCARD)

1

EM145SB550326A.DGN

SCREW

PN PE21101−3−2CP

(9 POSITIONS)

(REMOVE AND DISCARD)

CONNECTOR

P0834

(REF.)

PRE − MOD

- APPLICABLE TO GROUP 1 

FIGURE 2: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL 

SYSTEM 

(SHEET 04 OF 09) 
SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 

PAGE: 32 REVISION No.: 

Embraer Copyright © 2011. All rights reserved.

BONDING JUMPER

PN PE88001−5AA6

(REMOVE AND DISCARD)

4

WASHER

PN NAS1149FN416P

(REMOVE AND DISCARD)

WASHER

PN MS35338−40

(REMOVE AND DISCARD)

SCREW

PN MS35206−216

(REMOVE AND DISCARD)

SCREW

PN MS35206−214

(REMOVE AND DISCARD)

WASHER

PN MS35338−40

(REMOVE AND DISCARD)

WASHER

PN NAS1149FN416P

(REMOVE AND DISCARD)

WASHER

PN NAS1197−4L

(REMOVE AND DISCARD)

NUT

PN H14−04

(REMOVE AND DISCARD)

WASHER

PN NAS1197−4L

(REMOVE AND DISCARD)

C−C

TYPICAL

PRE − MOD

4

4

4

4

4

4

4

4

4

EM145SB550327A.DGN

- APPLICABLE TO GROUP 1 

FIGURE 2: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL 

SYSTEM 

(SHEET 05 OF 09) 
SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 

REVISION No.: PAGE: 33 

Embraer Copyright © 2011. All rights reserved.

A

ZONES

223

224

DET. A

1

2

APPLY CYANOACRYLATE ADHESIVE PN SB496, OR SIMILAR.

FILL GAPS AND FREE SPACES WITH SEALANT PN PR1776MB1/2, OR SIMILAR.

10 11

5

MOVABLE TAIL BOOM FAIRING

(REIDENTIFY)

W308

(REF.)

CUT LINE

GROMMET

PN MS35489−8

(INSTALL)

1 2

EM145SB550328A.DGN

LIGHTNING DIVERTER

(4 POSITIONS)

(APPLY FILLET SEALANT)

(MEASURE THE ELECTRICAL

RESISTANCE)

6

PRIMARY

STRUCTURE

(REF.)

H

G

D

B

DET. D

F

F

POST − MOD

ELECTRICAL HARNESS

W308

(REROUTE)

14

CONNECTOR

P0834

(REF.)

- APPLICABLE TO GROUP 1 

FIGURE 2: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL 

SYSTEM 

(SHEET 06 OF 09) 
SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 

PAGE: 34 REVISION No.: 

Embraer Copyright © 2011. All rights reserved.

3

4

ELECTRICAL BONDING (METHOD 3)

APPLY AERODYNAMIC SEALANT PN P/S870B−1/2

9 3 4

HOOD ASSY

PN 145−23046−403

(INSTALL)

9

9

STATIC DISCHARGER

(MEASURE THE ELECTRICAL

RESISTANCE)

CONNECTOR

P0708

(INSTALL)

CONNECTOR

P0707

(INSTALL)

CONNECTOR

P0715

(INSTALL)

8

8 8

EM145SB550329A.DGN

SCREW

PN PE21101−3−1CP

(7 POSITIONS)

(INSTALL)

SCREW

PN PE21101−3−2CP

(6 POSITIONS)

(INSTALL) HOOD BELT

(MEASURE THE ELECTRICAL

RESISTANCE)

C

C

DET. B

POST − MOD

12

13

- APPLICABLE TO GROUP 1 

FIGURE 2: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL 

SYSTEM 

(SHEET 07 OF 09) 
SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 

REVISION No.: PAGE: 35 

Embraer Copyright © 2011. All rights reserved.

TYPICAL

E

E

BONDING JUMPER

PN PE88001−5AA8

(INSTALL)

3

WASHER

PN NAS1197−4L

(INSTALL)

WASHER 7

PN NAS1149FN416P

(INSTALL)

7

WASHER

PN MS35338−40

INSTALL)

7

SCREW

PN MS35206−214

(INSTALL)

7

7

WASHER

PN NAS1149FN416P

(INSTALL)

WASHER

PN NAS1197−4L

(INSTALL)

7

SCREW

PN MS24693−C6

(INSTALL)

7

7

NUT

PN H14−04

(INSTALL)

7

WASHER

PN MS35338−40

(INSTALL)

E−E

7

ELECTRICAL BONDING (METHOD 3) 3

EM145SB550330A.DGN

POST − MOD

C−C

- APPLICABLE TO GROUP 1 

FIGURE 2: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL 

SYSTEM 

(SHEET 08 OF 09) 
SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 

PAGE: 36 REVISION No.: 

Embraer Copyright © 2011. All rights reserved.

EM145SB550357A.DGN

HOOD ASSY

REAR MOVABLE

FAIRING

(REF.)

DIVERTERS

(REF.)

CLAMP 

PN PE27019R15

SCREW

PN MS24694−C6

WASHER

PN NAS1149FN832P

NUT

PN H14−08

(02 POSITIONS)

(INSTALL)

5

5

CLAMP 

PN PE27019R15

SCREW

PN NAS1801−08−8

WASHER

PN NAS1149CN832R DET. H (INSTALL)

DET. G

(TYPICAL)

SECTION F−F

NUT PLATE

(REF.)

- APPLICABLE TO GROUP 1 

FIGURE 2: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL 

SYSTEM 

(SHEET 09 OF 09) 
SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 

REVISION No.: PAGE: 37 

Embraer Copyright © 2011. All rights reserved.

1. Remove and discard hood assy PN 145-23046-401 by removing screw PN 

PE21101-3-2CP (9 positions). Refer to detail B (PRE MOD). 

2. Disconnect electrical connector P0715 and splices SP7654, SP7655, and SP7656. 

Refer to detail B (PRE MOD). 

3. Remove and discard grommet PN MS35489-8. Refer to detail A (PRE MOD). 

4. Remove the bonding jumber (2 positions) attaching parts by removing screw 

PN MS35206-216, washer PN NAS1149FN416P, PN MS35338-40, and 

PN NAS1197-4L (2 positions per bonding jumper), and nut PN H14-04. Refer to 

SECTION C-C (PRE MOD). 

5. Reroute electrical harness W308 and install clamp PN PE27019RI5 with screw PN 

NAS1801-08-8, washer PN NAS1149CN832R ,and clamp PN PE27019RI5 with 

screw PN MS24694-C6, washer PN NAS1149FN832P, and nut PN H14-08. Refer to 

Details A (Post-Mod), G and H. 

6. Install grommet PN MS35489-8 with cyanoacrylate adhesive PN SB496. Fill gaps 

and free spaces with sealant PN PR1776M B1/2 654 SEMKIT (Spec AMS 3281, 

class B), or similar. Refer to detail D. 

7. Install the bonding jumber (2 positions) attaching parts using screw PN MS24693-

C6, washer PN MS35338-40, PN NAS1149FN416P, and PN NAS1197-4L, and nut 

PN H14-04. Refer to sections C-C and E-E. 

NOTE: Carry out the electrical bonding procedure, method 3. Refer to the 

applicable Aircraft Maintenance Manual - Chapter 20-13-21 - Standard 

Practices - Airframe.

- APPLICABLE TO GROUP 2 

FIGURE 3: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL 

SYSTEM 

(SHEET 01 OF 09)
SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 

PAGE: 38 REVISION No.: 

Embraer Copyright © 2011. All rights reserved.

8. Connect electrical connector P0715 and splices SP7654, SP7655, and SP7656. 

Refer to detail B (POST MOD). 

9. Install hood assy PN 145-23046-403 between diverters and fairing with screw PN 

PE21101-3-1CP (7 positions) and PN PE21101-3-2CP (6 positions). Refer to detail 

B (POST MOD) and section F-F. 

NOTES: (1) Carry out the electrical bonding procedure, method 3. Refer to the 

applicable Aircraft Maintenance Manual - Chapter 20-13-21 - 

Standard Practices - Airframe. 

 (2) Apply aerodynamic sealant P/S870-B1/2 along the contour of the 

hood assy. Refer to the applicable Structural Repair Manual - 

Chapter 51-20-01 – Standard Practices and Structures - General. 

10. Complete the application of fillet sealant PN PR1440B2 (Spec. SAE AMS-S-8802 

Type I Class B2) to the lightning diverter (4 positions). Refer to the applicable 

Structural Repair Manual – Chapter 51-20-01 – Standard Practices and Structures. 

Refer to detail A (POST MOD). 

11. Measure the electrical resistance value between the lightning diverters and the 

primary structure. The maximum allowed resistance value is 10 miliohms. Refer to 

the applicable Aircraft Maintenance Manual - Chapter 20-13-21 (TASK 20-13-21-

700-801- A) - Maintenance Practices and detail A (POST MOD). 

12. Measure the electrical resistance value between the static discharger and the 

primary structure. The allowed resistance value is from 6 mega ohms to 150 mega 

ohms. Refer to the applicable Aircraft Maintenance Manual - Chapter 20-13-21 

(TASK 20-13-21-700-801- A) - Maintenance Practices and detail A (POST MOD). 

- APPLICABLE TO GROUP 2 

FIGURE 3: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL 

SYSTEM 

(SHEET 02 OF 09) 
SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 

REVISION No.: PAGE: 39 

Embraer Copyright © 2011. All rights reserved.

13. Measure the electrical resistance value between the hood belt and the primary 

structure. The maximum allowed resistance value is 10 miliohms. Refer to the 

applicable Aircraft Maintenance Manual - Chapter 20-13-21 (TASK 20-13-21-700-

801- A) - Maintenance Practices and detail A (POST MOD). 

14. With a permanent marker pen or a rubber stamp, reidentify the movable Tail Boom 

fairing according to Table, as follows: 

REIDENTIFICATION TABLE 

FROM TO 

145-03535-401 145-03535-603

145-03535-409 145-03535-617

145-38445-403

145-38445-407

145-03535-413

- APPLICABLE TO GROUP 2 

FIGURE 3: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL 

SYSTEM 

(SHEET 03 OF 09) 
SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 

PAGE: 40 REVISION No.: 

Embraer Copyright © 2011. All rights reserved.

EM145SB550331A.DGN

PRE − MOD

DET. A

2

2

3

DET. B

B

C

C

1

HOOD ASSY

PN 145−23046−401

(REMOVE AND DISCARD)

1

CONNECTOR

P0715

(DISCONNECT)

SPLICE

SP7656

(DISCONNECT)

2

SPLICE

SP7654

(DISCONNECT)

2

SPLICE

SP7655

(DISCONNECT)

ELECTRICAL

HARNESS W308

(REF.)

GROMMET

PN MS35489−8

(REMOVE AND DISCARD)

SCREW

PN PE21101−3−2CP

(9 POSITIONS)

(REMOVE AND DISCARD)

A

ZONES

223

224

CONNECTOR

P0834

(REF.)

PRE − MOD

- APPLICABLE TO GROUP 2 

FIGURE 3: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL 

SYSTEM 

(SHEET 04 OF 09) 
SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 

REVISION No.: PAGE: 41 

Embraer Copyright © 2011. All rights reserved.

NUT

PN H14−04

(REMOVE AND DISCARD)

C−C

TYPICAL

PRE − MOD

4

4

BONDING JUMPER

(REF.)

WASHER

PN NAS1197−4L

(REMOVE AND DISCARD)

SCREW

PN MS35206−216

(REMOVE AND DISCARD)

4

4

WASHER

PN MS35338−40

(REMOVE AND DISCARD)

4

WASHER

PN NAS1149FN416P

(REMOVE AND DISCARD)

EM145SB550332A.DGN

- APPLICABLE TO GROUP 2 

FIGURE 3: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL 

SYSTEM 

(SHEET 05 OF 09) 
SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 

PAGE: 42 REVISION No.: 

Embraer Copyright © 2011. All rights reserved.

A

ZONES

223

224

DET. A

1

2

APPLY CYANOACRYLATE ADHESIVE PN SB496, OR SIMILAR.

FILL GAPS AND FREE SPACES WITH SEALANT PN PR1776MB1/2, OR SIMILAR.

10 11

5

MOVABLE TAIL BOOM FAIRING

(REIDENTIFY)

W308

(REF.)

CUT LINE

GROMMET

PN MS35489−8

(INSTALL)

1 2

LIGHTNING DIVERTER

(4 POSITIONS)

(APPLY FILLET SEALANT)

(MEASURE THE ELECTRICAL

RESISTANCE)

6

EM145SB550333A.DGN

POST − MOD

PRIMARY

STRUCTURE

(REF.)

D

B

F

F

DET. D

H

G

ELECTRICAL HARNESS

W308

(REROUTE)

14

CONNECTOR

P0834

(REF.)

- APPLICABLE TO GROUP 2 

FIGURE 3: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL 

SYSTEM 

(SHEET 06 OF 09) 
SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 

REVISION No.: PAGE: 43 

Embraer Copyright © 2011. All rights reserved.

3

4

ELECTRICAL BONDING (METHOD 3)

APPLY AERODYNAMIC SEALANT PN P/S870B−1/2

9 3 4

HOOD ASSY

PN 145−23046−403

(INSTALL)

9

9

STATIC DISCHARGER

(MEASURE THE ELECTRICAL

RESISTANCE)

8

8

SPLICE

SP7655

(CONNECT)

8

SPLICE

SP7656

(CONNECT)

8

SPLICE

SP7654

(CONNECT)

CONNECTOR

P0715

(CONNECT)

EM145SB550344A.DGN

HOOD BELT

(MEASURE THE ELECTRICAL

RESISTANCE)

SCREW

PN PE21101−3−1CP

(7 POSITIONS)

(INSTALL)

SCREW

PN PE21101−3−2CP

(6 POSITIONS)

(INSTALL)

POST − MOD

C

C

DET. B

12

13

- APPLICABLE TO GROUP 2 

FIGURE 3: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL 

SYSTEM 

(SHEET 07 OF 09) 
SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 

PAGE: 44 REVISION No.: 

Embraer Copyright © 2011. All rights reserved.

EM145SB550345A.DGN

TYPICAL

E

E

3

7

WASHER

PN NAS1149FN416P

(INSTALL)

WASHER

PN NAS1197−4L

(INSTALL)

7

SCREW

PN MS24693−C6

(INSTALL)

7

7

NUT

PN H14−04

(INSTALL)

7

WASHER

PN MS35338−40

(INSTALL)

E−E

ELECTRICAL BONDING (METHOD 3) 3

BONDING JUMPER

(REF.)

POST − MOD

C−C

- APPLICABLE TO GROUP 2 

FIGURE 3: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL 

SYSTEM 

(SHEET 08 OF 09) 
SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 

REVISION No.: PAGE: 45 

Embraer Copyright © 2011. All rights reserved.

HOOD ASSY

REAR MOVABLE

FAIRING

(REF.)

DIVERTERS

(REF.)

CLAMP 

PN PE27019R15

SCREW

PN MS24694−C6

WASHER

PN NAS1149FN832P

NUT

PN H14−08

(02 POSITIONS)

(INSTALL)

5

5

CLAMP 

PN PE27019R15

SCREW

PN NAS1801−08−8

WASHER

PN NAS1149CN832R DET. H (INSTALL)

DET. G

(TYPICAL)

SECTION F−F

EM145SB550358A.DGN

NUT PLATE

(REF.)

- APPLICABLE TO GROUP 2 

FIGURE 3: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL 

SYSTEM 

(SHEET 09 OF 09) 

.

..

SERVICE BULLETIN IMPLEMENTATION AND EVALUATION FORM

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

Reliability Program. 

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

Customer Support Contact Center 

Embraer Executive Jets 

contact.center@embraer.com

24/7 Toll Free Numbers 

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+55 12 3927-7000 Latin America

SB Number/Revision: SB Title: 

SB145LEG-55-0013R00 IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE TAIL BOOM 

SB Implementation Report 

Aircraft Serial Number or Registration Number: Incorporation Date: 

 

Aircraft Flight Hours: Aircraft Landings:

SB Evaluation (Check applicable squares below)

Estimated Manpower: [ ] OK [ ] Not OK (Explain below) 

Material & Kits: [ ] OK [ ] Not OK (Explain below) 

Accomplishment Instructions: [ ] OK [ ] Not OK (Explain below) 

Figures: [ ] OK [ ] Not OK (Explain below) 

SB General Evaluation: [ ] OK [ ] Not OK (Explain below) 

Comments: (Bulletin quality, difficulties found at the time of incorporation, suggested improvements,...)

Company/ Service Center: Fax: Phone: 

 

Address: 

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

 

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