TRANSMITTAL LETTER

SB No.: 145-53-0062 

PAGE: 1 of 1 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

1. DESCRIPTION 

This sheet transmits Revision 07 to Service Bulletin 145-53-0062. 

This is a complete reissue of the Bulletin. 

2. ADDITIONAL ACTION 

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

additional action. 

3. RECORD OF REVISION 

Original issue: 29/Jul/2005. 

Revision 01: 28/Oct/2005. 

Revision 02: 25/Jan/2006. 

Revision 03: 21/Sep/2007. 

Revision 04: 23/Nov/2007. 

Revision 05: 20/May/2008. 

Revision 06: 11/Aug/2010. 

Revision 07: 27/May/2011. 

4. HIGHLIGHTS 

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

introduced by this revision are presented below. 

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

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

TOPIC/ PAGE DESCRIPTION OF REVISION 

1. PLANNING INFORMATION 

A. SB EFFECTIVITY / 01 and 02 Included aircraft in the SB effectivity.

C. REASON / 03 Added reason for revision 07. 

D. DESCRIPTION/ 03 Added information concerning the 

Fatigue Critical Structure (FCS). 

2. MATERIAL INFORMATION 

A. MATERIAL - PRICE AND 

AVAILABILITY / 06 and 08 

Updated and corrected information. 

C. TOOLING - PRICE AND AVAILABILITY 

/ 08 

Added notes. 

3. ACCOMPLISHMENT INSTRUCTIONS /09 

and 11 

Added and updated notes. 

SERVICE BULLETIN

DATE: 29/Jul/2005 SB No.: 145-53-0062 

REVISION No.: 07 – 27/May/2011 PAGE: 1 of 31 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

Copyright © 2011 by EMBRAER - Empresa Brasileira de Aeronautica S.A. All rights reserved. The information, technical data, designs 

and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to 

any third party without permission of Embraer. 

FUSELAGE – APU FIREWALL REPLACEMENT 

1. PLANNING INFORMATION 

A. SB EFFECTIVITY 

Aircraft affected: 

MODEL SN 

EMB-145( ) and EMB-135( ) 145003 thru 145103, 145105 thru 145121, 145123 

thru 145139, 145141 thru 145153, 145155 thru 

145189, 145191 thru 145256, 145258 thru 145262, 

145264 thru 145362, 145364, 145366 thru 145373, 

145375 thru 145391, 145393 thru 145411, 145413 

thru 145446, 145448 thru 145450, 145452 thru 

145461, 145463 thru 145483, 145485 thru 145494, 

145496 thru 145504, 145506 thru 145508, 145510 

thru 145515, 145517 thru 145523, 145525 thru 

145527, 145529 thru 145539, 145541 thru 145548, 

145550, 145552 thru 145554, 145556 thru 145585, 

145587 thru 145590, 145592 thru 145598, 145600, 

145602 thru 145613, 145615 thru 145619, 145621 

thru 145624, 145627 thru 145636, 145638 thru 

145641, 145643, 145645 thru 145660, 145662, 

145664 thru 145670, 145672 thru 145675, 145677, 

145680 thru 145685, 145688 thru 145690, 145692, 

145693, 145695, 145697, 145707, 145709, 145710, 

145716, 145722, 145726, 145728, 145734, 145736, 

145738, 145740, 145742 thru 145744, 145747, 

145748, 145750, 145752, 145754, 145760, 145762, 

145764, 145766, 145771, 145777 thru 145779, 

145783 thru 145785, 145788, 145790, 145793 thru 

145795, 145797, 145798, 14500801, 14500803, 

14500806, 14500807, 14500810, 14500813, 

14500814, 14500820, 14500822, 14500824, 

14500826, 14500829, 14500830, 14500833, 

14500835, 14500836, 14500838, 14500842, 

14500843, 14500846, 14500849, 14500852, 

14500853, 14500855, 14500857, 14500858, 
SERVICE BULLETIN

SB No.: 145-53-0062 DATE: 29/Jul/2005 

PAGE: 2 REVISION No.: 07 – 27/May/2011 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

MODEL SN 

14500860, 14500861, 14500866, 14500868 thru 

14500870, 14500874, 14500875, 14500877, 

14500883, 14500885 thru 14500887, 14500890, 

14500892 thru 14500895, 14500897, 14500899, 

14500902, 14500906 thru 14500908, 14500911, 

14500912, 14500915, 14501077, 14501084, 

14501124, and 14501125, if equipped with the 

affected component .

Affected component: 

Titanium APU firewall PN 145-47494-401 or PN 145-26850-401 or PN 145-26850-

601 or PN 145-47494-403. 

In-production effectivity: 

None. 

B. CONCURRENT REQUIREMENTS 

None. 

C. REASON 

1. History 

A new firewall of steel has shown better reliability than the titanium one. 

2. Objective 

Replacement of APU firewall to improve the reliability. 

3. Expected Benefits 

To prevent cracks on the APU firewall. 
SERVICE BULLETIN

DATE: 29/Jul/2005 SB No.: 145-53-0062 

REVISION No.: 07 – 27/May/2011 PAGE: 3 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

4. Revision History 

(a) Revision 01 – To change effectivity. 

(b) Revision 02 – After field’s accomplishment, it was detected that the removal 

of the electrical cables according to figure 05 of the last revision 

was not necessary. 

(c) Revision 03 – To include aircraft SN 145726, SN 145728 and SN 14500890 

to the Service Bulletin effectivity, add old firewalls PN’s, correct 

Service Bulletin kit PN at the material information and improve 

some tasks of accomplishment instructions. 

This revision incorporates the Information Notices:

SB145-53-0062R02-IN01 

(d) Revision 04 – To include aircraft SN 145361, 145364, 145450, 145466, 

145467, 145499, 145550, and 145648 to the Service Bulletin 

effectivity. 

(e) Revision 05 – To include aircraft SN 145020, 145023, 145027, 145028, and 

145076 to the Service Bulletin effectivity. 

(f) Revision 06 – To include the affected component and to correct the APU 

firewall Part Numbers affected by this SB. 

(g) Revision 07 – To include aircraft in the Service Bulletin effectivity. 

D. DESCRIPTION 

NOTE: The modification presented in this bulletin does not affect Fatigue 

Critical Structure (FCS).

This modification consists of replacing the existing APU firewall. 

To do this, it is necessary to remove the APU cowling, APU, APU fire extinguisher 

bottle, APU suspension structure, and the electrical, bleed, and fuel system 

components. 
SERVICE BULLETIN

SB No.: 145-53-0062 DATE: 29/Jul/2005 

PAGE: 4 REVISION No.: 07 – 27/May/2011 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

E. COMPLIANCE 

This bulletin may be accomplished at any time, at the operator’s discretion. 

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. 

- Disassembly: 12.0 man-hours. 

- Modification: 40.0 man-hours. 

- Assemblage: 15.0 man-hours. 

- Test: Not applicable. 

H. WEIGHT AND BALANCE 

1. For aircraft EMB-135( ): 

- Change in basic weight: + 13.809 lb (+ 6.264 kg).

- Change in basic moment: + 12,382.2 lb.in (+ 142.7 kg.m). 

2. For aircraft EMB-140( ): 
SERVICE BULLETIN

DATE: 29/Jul/2005 SB No.: 145-53-0062 

REVISION No.: 07 – 27/May/2011 PAGE: 5 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

- Change in basic weight: +13.809 lb (+ 6.264 kg). 

- Change in basic moment: + 13,537.5 lb.in (+ 156.0 kg.m). 

3. For aircraft EMB-145( ): 

- Change in basic weight: + 13.809 lb (+ 6.264 kg).

- Change in basic moment: + 14,306.8 lb.in (+ 164.8 kg.m). 

I. REFERENCES 

AMM 145 – Aircraft Maintenance Manual – Chapter 06-41-01 – Dimensions and 

Areas. 

AMM 145 – Aircraft Maintenance Manual – Chapter 26-22-01 – Fire Protection. 

AMM 145 – Aircraft Maintenance Manual – Chapter 28-21-11 – Fuel. 

AMM 145 – Aircraft Maintenance Manual – Chapter 36-11-09 – Pneumatic. 

AMM 145 – Aircraft Maintenance Manual – Chapters 49-12-01, 49-12-03,49-12-04, 

49-14-01, and 49-15-00 – Airborne Auxiliary Power. 

SRM 145 – Structural Repair Manual – Chapters 51-20-01 and 51-20-03 - Structure. 

SRM 145 – Structural Repair Manual – Chapter 53-32-13 – Fuselage. 

J. AFFECTED PUBLICATIONS 

SRM 145 – Structural Repair Manual – Chapter 53-32-13 – Fuselage. 
SERVICE BULLETIN

SB No.: 145-53-0062 DATE: 29/Jul/2005 

PAGE: 6 REVISION No.: 07 – 27/May/2011 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

2. MATERIAL INFORMATION 

A. MATERIAL – PRICE AND AVAILABILITY 

The material required for the accomplishment of this bulletin will be available from 

Embraer 13 weeks after receipt of orders, at the reference price of US$ 11,450.00,

subject to confirmation upon receipt of orders. 

When ordering, specify SB 145-53-0062, KIT PN BS145-53-0062/0200, which 

comprises PN 145-54140-603, 145-42382-601, and 145-34585-681. 

(a) PN 145-54140-603: 

NEW PN DESCRIPTION OLD PN QTY

SUP

QTY

RQD DISP

145-47494-607 Firewall 145-47494-401 or 

145-26850-401 or 

145-26850-601 or 

145-47494-403 

01 01 3 

M7885/4-4-02 Rivet M7885/4-4-02 125 111 7 

MS20615-4M4 Solid Rivet - 84 77 2 

145-38229-001 Clip - 01 01 2 

145-38230-001 Clip - 01 01 2 

145-54143-003 Clip - 01 01 2 

145-54144-005 Clip - 01 01 2 

145-54145-003 Clip - 01 01 2 

145-54146-005 Clip - 01 01 2 

145-54148-005 Clip - 01 01 2 

145-54149-003 Clip - 01 01 2 

145-54149-004 Clip - 01 01 2 

145-54150-003 Clip - 01 01 2 

145-54150-004 Clip - 01 01 2 

145-54151-005 Clip - 01 01 2 

145-54151-006 Clip - 01 01 2 

145-54153-003 Clip - 01 01 2 
SERVICE BULLETIN

DATE: 29/Jul/2005 SB No.: 145-53-0062 

REVISION No.: 07 – 27/May/2011 PAGE: 7 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

NEW PN DESCRIPTION OLD PN QTY

SUP

QTY

RQD DISP

145-54154-005 Clip - 01 01 2 

145-54155-003 Clip - 01 01 2 

145-54156-005 Clip - 01 01 2 

PS700 

(Spec. MIL-S-38249) Sealant, Type I - - AR 6/9 

PR1440B2 

(Spec. MIL-S-8802) Sealant, Type II - - AR 6/9 

P/S870C-12 

(Spec. MIL-S-81733) Sealant, Type IV - - AR 6/9 

MEK 

(Spec. ASTM-D740) Methyl Ethyl Ketone - - AR 6/9 

(b) PN 145-42382-601: 

NEW PN DESCRIPTION OLD PN QTY

SUP

QTY

RQD DISP

NAS1291C4M Self-locking nut NAS1291C4M 01 01 7 

NAS1291C3M Self-locking nut NAS1291C3M 28 28 7 

(c) PN 145-34585-681: 

NEW PN DESCRIPTION OLD PN QTY

SUP

QTY

RQD DISP

S2U2-230 O-Ring, 2.5” S2U2-230 02 02 7 

PLT4S-C76 Tiedown strap PLT4S-C76 02 02 7 

600-052 Metallic Band 600-052 02 02 7 

NAS1291C3M Self-locking nut NAS1291C3M 04 04 7 

145-22415-009 Seal, bleed 145-22415-009 01 01 7 
SERVICE BULLETIN

SB No.: 145-53-0062 DATE: 29/Jul/2005 

PAGE: 8 REVISION No.: 07 – 27/May/2011 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

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. 

9 = Contact manufacturer directly. 

QUANTITY: AR = As Required. 

NOTES: 1) 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. 

2) The expendable or consumable parts presented in the tasks referred to in 

this bulletin, which are necessary for its accomplishment, should be 

procured from the operator's inventories or ordered as spares. 

3) Sealant PS700 (Spec. MIL-S-38249 - Type I), Sealant PR1440B2 (Spec. 

MIL-S-8802 - Type II CLASS B2), Sealant P/S870C-12 (Spec. MIL-S-81733 

- Type IV -12), Methyl Ethyl Ketone (Spec. ASTM-D740), Lockwire PN 

MS20995-C20 or equivalent, and commercially available torque-paint, 

required for the accomplishment of this bulletin, should be procured from 

the operator’s inventories or from a local supplier. 

B. REIDENTIFIED PARTS 

None. 

C. 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: 29/Jul/2005 SB No.: 145-53-0062 

REVISION No.: 07 – 27/May/2011 PAGE: 9 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

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. H. REFERENCES” for a 

more complete definition. 

The steps below outline the general accomplishment instructions. 

The detailed sequence is given as notes in the figures. 

A. Make sure that the aircraft is safe for maintenance. 

B. Make sure that the GPU pushbutton, on the overhead panel, is set at OFF and 

attach a DO-NOT-SET-TO-ON tag to it. 

C. Make sure that the BATT1 and BATT2 switches, on the overhead panel, are set at 

OFF and attach a DO-NOT-SET-TO-AUTO tag to them.

D. Set the BACKUP pushbutton, on the overhead panel, to OFF and attach a DONOT-SET-TO-AUTO tag to it. 

E. On the circuit breaker panel, open the circuit breakers below and attach a DO-NOTCLOSE tag to them:

- APU CONTROL. 

- APU FUEL SOV. 

- APU BLEED. 

- APU FIRE EXTG. 

- APU FIRE DET. 

WARNING: BEFORE YOU DO THE MODIFICATION, OBEY THE SAFETY 

PRECAUTIONS GIVEN IN AMM 49-00-00 TO PREVENT 

INJURY TO YOU AND DAMAGE TO MATERIAL.

F. Remove and save the APU cowling according to the applicable Aircraft 

Maintenance Manual – Chapter 49-15-00 (TASK 49-15-00-000-801-A) – Airborne 

Auxiliary Power. 

G. Remove and save the APU. Refer to the applicable Aircraft Maintenance Manual – 

Chapter 49-14-01 (TASK 49-14-01-000-801-A) – Airborne Auxiliary Power. 
SERVICE BULLETIN

SB No.: 145-53-0062 DATE: 29/Jul/2005 

PAGE: 10 REVISION No.: 07 – 27/May/2011 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

H. Remove and save the APU fire extinguisher bottle. Refer to the applicable Aircraft 

Maintenance Manual – Chapter 26-22-01 (TASK 26-22-01-000-801-A) – Fire 

Protection. 

I. Remove and save the APU mounting support assy. Refer to the applicable Aircraft 

Maintenance Manual – Chapter 49-12-04 (TASK 49-12-04-000-801-A) – Airborne 

Auxiliary Power. 

J. Remove and save the APU side mounts. Refer to the applicable Aircraft 

Maintenance Manual – Chapter 49-12-03 (TASK 49-12-03-000-801-A) – Airborne 

Auxiliary Power. 

K. Open access panel 312AR. Refer to the applicable Aircraft Maintenance Manual – 

Chapter 06-41-01 – Dimensions and Areas. 

L. Remove the fire-extinguishing tubes from the firewall as well as the components of 

the electrical, bleed, and fuel systems. Refer to the instructions in Figures 1, 2, 3, 4, 

and 5. 

NOTE: Cover the remaining equipment and harness in the cone compartment to 

protect them from the ingress of chips. 

M. Carefully unrivet APU firewall PN 145-47494-401 or 145-26850-401 or 145-26850-

601 or 145-47494-403, as applicable, from the structure and discard it. 

N. Remove the sealant residues from the frame structure. Refer to Structural Repair 

Manual – Chapter 51-20-01 – Structures. 

O. Install new APU firewall PN 145-47494-607. Refer to the instruction in Figure 6. 

NOTE: Wipe the cone compartment to remove residues or filings left after the APU 

firewall replacement. 

P. Reinstall the fire-extinguishing tubes to the firewall as well as the components of the 

electrical, bleed, and fuel systems. Refer to the instructions in Figures 1, 2, 3, 4, 

and 5. 

Q. Close access panel 312AR. Refer to the applicable Aircraft Maintenance Manual – 

Chapter 06-41-01 – Dimensions and Areas. 

R. Install the APU side mounts. Refer to the applicable Aircraft Maintenance Manual – 

Chapter 49-12-03 (TASK 49-12-03-400-801-A) – Airborne Auxiliary Power. 
SERVICE BULLETIN

DATE: 29/Jul/2005 SB No.: 145-53-0062 

REVISION No.: 07 – 27/May/2011 PAGE: 11 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

S. Install the APU suspension structure. Refer to the applicable Aircraft Maintenance 

Manual – Chapter 49-12-01 (TASK 49-12-01-400-801-A) – Airborne Auxiliary 

Power. 

T. Install the APU fire extinguisher bottle. Refer to the applicable Aircraft Maintenance 

Manual – Chapter 26-22-01 (TASK 26-22-01-000-801-A) – Fire protection. 

U. Install the APU. Refer to the applicable Aircraft Maintenance Manual – Chapter 

49-14-01 (TASK 49-14-01-400-801-A) – Airborne Auxiliary Power. 

V. Carry out an operational test. Refer to the applicable Aircraft Maintenance Manual – 

Chapter 28-21-11 – Fuel. 

W. Install the APU cowling according to the applicable Aircraft Maintenance Manual – 

Chapter 49-15-00 (TASK 49-15-00-400-801-A) – Airborne Auxiliary Power. 

X. On the circuit breaker panel, close the circuit breakers below and remove a DONOT-CLOSE tag to them: 

- APU CONTROL. 

- APU FUEL SOV. 

- APU BLEED. 

- APU FIRE EXTG. 

- APU FIRE DET. 

Y. Set the BACKUP pushbutton, on the overhead panel, to AUTO, and remove the 

DO-NOT-SET-AUTO tag from it. 

Z. Set the BATT1 and BATT2 switches, on the overhead panel, to AUTO and remove 

the DO-NOT-SET-AUTO tag from them. 

AA. Restore the aircraft to normal. 

BB. Enter the accomplishment 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). 
SERVICE BULLETIN

SB No.: 145-53-0062 DATE: 29/Jul/2005 

PAGE: 12 REVISION No.: 07 – 27/May/2011 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

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: 29/Jul/2005 SB No.: 145-53-0062 

REVISION No.: 07 – 27/May/2011 PAGE: 13 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

FIGURE 1: REMOVAL / INSTALLATION OF THE COMPONENTS AT THE FIREWALL 

(SHEET 01 OF 01) 
SERVICE BULLETIN

SB No.: 145-53-0062 DATE: 29/Jul/2005 

PAGE: 14 REVISION No.: 07 – 27/May/2011 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

1. DETACHMENT OF THE FUEL HOSE FROM THE FIREWALL 

(1.a) Remove and retain the fuel support and its attachment parts. 

(1.b) Remove the old sealing compound from the fuel support and fuel hose. Refer to 

Structural Repair Manual – Chapter 51-20-01 – Structure. 

(1.c) Carefully stow the fuel hose in the cone compartment. 

2. REINSTALLATION OF THE FUEL HOSE AT THE FIREWALL 

(2.a) Reposition the fuel hose at the new firewall.

(2.b) Reinstall the fuel support at the new firewall. 

(2.c) Apply Fire-Proof Sealant PS700 (Spec. MIL-S-38249- Type I) along all the 

contour of the support. Refer to Structural Repair Manual – Chapter 51-20-01 – 

Structures. 

FIGURE 2: DISPLACEMENT / INSTALLATION OF THE FUEL HOSE AT THE FIREWALL 

(SHEET 01 OF 02) 
SERVICE BULLETIN

DATE: 29/Jul/2005 SB No.: 145-53-0062 

REVISION No.: 07 – 27/May/2011 PAGE: 15 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

FIGURE 2: DISPLACEMENT / INSTALLATION OF THE FUEL HOSE AT THE FIREWALL 

(SHEET 02 OF 02) 
SERVICE BULLETIN

SB No.: 145-53-0062 DATE: 29/Jul/2005 

PAGE: 16 REVISION No.: 07 – 27/May/2011 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

WARNING: DO NOT TOUCH THE BLEED-AIR SYSTEM DUCTS OR COMPONENTS 

IMMEDIATELY AFTER THE ENGINE OR APU STOPS BECAUSE OF THE 

HIGH BLEED-AIR TEMPERATURE. 

1. REMOVAL OF THE APU BLEED TUBE FROM THE FIREWALL 

(1.a) Remove and retain the APU bleed tube as per instructions in Aircraft 

Maintenance Manual – Chapter 36 (TASK 36-11-09-000-801-A). 

2. INSTALLATION OF THE APU BLEED TUBE AT THE FIREWALL 

(2.a) Reinstall the APU bleed tube as per instructions in Aircraft Maintenance Manual 

– Chapter 36 (TASK 36-11-09-400-801-A and TASK 36-11-10-400-801-A). 

FIGURE 3: REMOVAL / INSTALLATION OF THE APU BLEED TUBE 

(SHEET 01 OF 02)
SERVICE BULLETIN

DATE: 29/Jul/2005 SB No.: 145-53-0062 

REVISION No.: 07 – 27/May/2011 PAGE: 17 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

FIGURE 3: REMOVAL / INSTALLATION OF THE APU BLEED TUBE 

(SHEET 02 OF 02) 
SERVICE BULLETIN

SB No.: 145-53-0062 DATE: 29/Jul/2005 

PAGE: 18 REVISION No.: 07 – 27/May/2011 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

FIGURE 4: REMOVAL / INSTALLATION OF THE FIRE EXTINGUISHING TUBE 

(SHEET 01 OF 01) 
SERVICE BULLETIN

DATE: 29/Jul/2005 SB No.: 145-53-0062 

REVISION No.: 07 – 27/May/2011 PAGE: 19 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

1. DISCONNECTION OF THE APU HARNESS AND HARNESS W317 FROM THE APU 

FIREWALL. 

(1.a) Disconnect electrical connector P4 of the APU harness from electrical connector 

J0274, and retain the APU harness. 

(1.b) Disconnect electrical connector P0832 of harness W317 from electrical 

connector J0832, and retain harness W317. 

(1.c) Remove the bolt, washer, and nut that attach electrical connectors J0832 and 

J0274 to the firewall. 

(1.d) Release electrical connectors J0832 and J0274 and stow harness W315 in the 

cone compartment. 

(1.e) Protect electrical connectors J0832 and J0274 during the rework. 

2. REINSTALLLATION OF THE APU HARNESS AND HARNESS W317 TO THE APU 

FIREWALL. 

(2.a) Reinstall electrical connectors J0832 and J0274 to the new firewall by using the 

bolt, washer, and nut. 

(2.b) Connect electrical connector P4 of the APU harness to electrical connector 

J0274. 

(2.c) Connect electrical connector P0832 of harness W317 to electrical connector 

J0832. 

(2.d) Post the identification of electrical connectors J0832 and J0274 on the new 

firewall. 

FIGURE 5: REMOVAL / INSTALLATION OF THE HARNESS 

(SHEET 01 0F 02) 
SERVICE BULLETIN

SB No.: 145-53-0062 DATE: 29/Jul/2005 

PAGE: 20 REVISION No.: 07 – 27/May/2011 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

FIGURE 5: REMOVAL / INSTALLATION OF THE HARNESS 

(SHEET 02 0F 02) 
SERVICE BULLETIN

DATE: 29/Jul/2005 SB No.: 145-53-0062 

REVISION No.: 07 – 27/May/2011 PAGE: 21 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

1. On a bench, mark and draw rivet centerlines at the edge of the APU firewall 

reinforcements, where the clips will be installed. 

2. On a bench, mark and draw rivet centerlines at the clips that will be installed at the 

APU firewall. 

3. Position new APU firewall PN 145-47494-607 at the frame, and transfer the holes to 

the APU firewall using the frame as a template. Refer to the Structural Repair Manual – 

Chapter 51-20-01 – Structures. 

4. If necessary, rework the APU firewall to clear the APU cowling attachment points, 

observing the correct distance from the edge and making sure that there is no sharp 

edge. 

5. Maintain the APU firewall at the frame using cleco fasteners. 

6. In the rear electronic compartment, position and adjust the clip angles. 

7. Mark 8mm-edge distance on the APU firewall and clips, and transfer the holes. 

REMARK: For details E, G, and K, transfer holes from frame to the clips. 

8. Remove the firewall and clips and, on a bench, drill the remaining holes, maintaining an 

equal distance between them. 

9. Deburr all the holes. 

10. Clean the APU firewall surface, structure, and holes with a cloth moist with Methyl 

Ethyl Ketone (Spec. ASTM-D740), and then pass a clean dry cloth on it before the 

solvent evaporates. 

11. On a bench, install the clips to the APU firewall using rivets PN MS20615-4M4. Wet 

the rivets in sealant PS700 (Spec. MIL-S-38249 – Type I). Refer to the Structural 

Repair Manual – Chapter 51-20-03 – Structures. 

FIGURE 6: APU FIREWALL REPLACEMENT 

(SHEET 01 OF 11)
SERVICE BULLETIN

SB No.: 145-53-0062 DATE: 29/Jul/2005 

PAGE: 22 REVISION No.: 07 – 27/May/2011 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

12. Apply fillet sealant PS700 (Spec. MIL-S-38249 – Type I) along all the contour of the 

APU firewall. Refer to the Structural Repair Manual – Chapter 51-20-01 – Structures. 

13. Install APU firewall PN 145-47949-607 using rivet PN M7885/4-4-02 (111 positions). 

Wet the rivets in sealant PS700 (Spec. MIL-S-38249 – Type I). Refer to the Structural 

Repair Manual – Chapter 51-20-03 – Structures. 

14. In the rear electronic compartment, install all the clips using rivets PN MS20615-4M4. 

Wet the rivets in sealant PS700 (Spec. MIL-S-38249 – Type I). Refer to the Structural 

Repair Manual – Chapter 51-20-03 – Structures. 

FIGURE 6: APU FIREWALL REPLACEMENT 

(SHEET 02 OF 11) 
SERVICE BULLETIN

DATE: 29/Jul/2005 SB No.: 145-53-0062 

REVISION No.: 07 – 27/May/2011 PAGE: 23 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

FIGURE 6: APU FIREWALL REPLACEMENT 

(SHEET 03 OF 11) 
SERVICE BULLETIN

SB No.: 145-53-0062 DATE: 29/Jul/2005 

PAGE: 24 REVISION No.: 07 – 27/May/2011 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

FIGURE 6: APU FIREWALL REPLACEMENT 

(SHEET 04 OF 11) 
SERVICE BULLETIN

DATE: 29/Jul/2005 SB No.: 145-53-0062 

REVISION No.: 07 – 27/May/2011 PAGE: 25 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

FIGURE 6: APU FIREWALL REPLACEMENT 

(SHEET 05 OF 11) 
SERVICE BULLETIN

SB No.: 145-53-0062 DATE: 29/Jul/2005 

PAGE: 26 REVISION No.: 07 – 27/May/2011 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

FIGURE 6: APU FIREWALL REPLACEMENT 

(SHEET 06 OF 11) 
SERVICE BULLETIN

DATE: 29/Jul/2005 SB No.: 145-53-0062 

REVISION No.: 07 – 27/May/2011 PAGE: 27 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

FIGURE 6: APU FIREWALL REPLACEMENT 

(SHEET 07 OF 11) 
SERVICE BULLETIN

SB No.: 145-53-0062 DATE: 29/Jul/2005 

PAGE: 28 REVISION No.: 07 – 27/May/2011 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

FIGURE 6: APU FIREWALL REPLACEMENT 

(SHEET 08 OF 11) 
SERVICE BULLETIN

DATE: 29/Jul/2005 SB No.: 145-53-0062 

REVISION No.: 07 – 27/May/2011 PAGE: 29 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

FIGURE 6: APU FIREWALL REPLACEMENT 

(SHEET 09 OF 11) 
SERVICE BULLETIN

SB No.: 145-53-0062 DATE: 29/Jul/2005 

PAGE: 30 REVISION No.: 07 – 27/May/2011 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

FIGURE 6: APU FIREWALL REPLACEMENT 

(SHEET 10 OF 11) 
SERVICE BULLETIN

DATE: 29/Jul/2005 SB No.: 145-53-0062 

REVISION No.: 07 – 27/May/2011 PAGE: 31 

Copyright © by EMBRAER - All rights reserved - See page 1 for details. 

FIGURE 6: APU FIREWALL REPLACEMENT 

(SHEET 11 OF 11)

.

..

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 

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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: 

 

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

 

ENS-003393HR01