1. DESCRIPTION This sheet transmits Revision 01 to Service Bulletin 170-53-0093. This is a complete reissue of the Bulletin. This revision incorporates the information presented in the Information Notice related to the previous issues of this Service Bulletin, as listed below: None. 2. ADDITIONAL ACTION Aircraft that have complied with the entire previous issue of this bulletin do not need any additional action. 3. RECORD OF REVISION Basic issue: 28/Feb/2011. Revision 01: 16/Mar/2012. 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 1.A. SB EFFECTIVITY /01 and 02 Updated Reason and added reason of revision 01. 1.D. DESCRIPTION /02 and 03 Splited Description into two parts. 1.E. COMPLIANCE /03 and 04 Splited Compliance into two parts. 1.G. ESTIMATED MANPOWER /04 and 05 Splited Estimated Manpower into two parts. 1.H. WEIGHT AND BALANCE /05 Splited Weight and Balance into two parts. 1.J. REFERENCES /05 and 06 Updated References. 2. MATERIAL INFORMATION /07 thru 10 Updated Material Information. 3. ACCOMPLISHMENT INSTRUCTIONS /11 thru 13 Updated Accomplishment Intructions into two parts. Figure 1 /15 thru 18 Updated Figure 1. Figure 2 /19 thru 23 Updated Figure 2. Figure 3 /24 and 25 included Figure 3. 

# TRANSMITTAL LETTER

SB No.: 170-53-0093 PAGE: 1 of 1 Copyright © 2012 by Embraer S.A. All rights reserved.FUSELAGE - INSPECTION AND PROTECTION FOR HARNESS W205 1. PLANNING INFORMATION A. SB EFFECTIVITY Aircraft affected: MODEL SN Embraer 170( ) and 175( ) 17000002, 17000004 thru 17000013, and 17000015 thru 17000324. Affected component: None. In-production effectivity: Embraer 170( ) and 175( ) model aircraft SN 17000001, 17000014, and 17000325 and on have an equivalent modification factory-incorporated. B. CONCURRENT REQUIREMENTS None. C. REASON (1) HISTORY Instances have been reported concerning chafing between the APU ESC (Electronic Starter Controller) power cables (Harness W205) and the tail cone firewall. This chafing occurs because the existing grommet installed in the tail cone firewall, intended to avoid contact between the APU ESC power cables and the tail cone firewall, moves out of place. This may cause damage to the APU ESC power cables. 

# SERVICE BULLETIN

DATE: 28/Feb/2011 REVISION No.:01 - 16/Mar/2012 SB No.: 170-53-0093 PAGE: 1 of 25 Copyright © 2012 by Embraer S.A. All rights reserved.(2) OBJECTIVE To provide the instructions to inspect the APU ESC power cables (Harness W205) and to install a new support in the tail cone firewall. (3) EXPECTED BENEFITS This modification is aimed at keeping the grommet in the correct position to prevent damage to the APU ESC power cables. Thus, the protection of the APU ESC power cables will be improved as a consequence. (4) REVISION HISTORY REVISION 01: This revision has been issued to include new conditions related to the inspection mentioned in this Service Bulletin. D. DESCRIPTION This Bulletin is divided into 2 PARTS, as follows: PART I INSPECTION AND PROTECTION FOR HARNESS W205 Applicable to: Refer to 1.A. SB EFFECTIVITY

. PART I of this bulletin consists in performing a detailed visual inspection for damage on the APU ESC power cables (Harness W205) and installing a support in the tail cone firewall. During the inspection, the criteria below should be followed : 

# SERVICE BULLETIN

SB No.: 170-53-0093 PAGE: 2 DATE: 28/Feb/2011 REVISION No.: 01 - 16/Mar/2012 Copyright © 2012 by Embraer S.A. All rights reserved.(1) If no damage is detected to the APU ESC power cables, only a support installation in the tail cone firewall is required; (2) If there is any sign of damage to the APU ESC power cables, and if the damage only affects the harness insulation, it is necessary to repair the harness insulation and to install a support in the tail cone firewall. (3) If there is any sign of damage to the APU ESC power cables, and if the damage affects the harness insulation and the wire strands (inner conductors), it is necessary to install a support in the tail cone firewall and then, replace the harness W205 as described in PART II of this Service Bulletin. To do this, it is necessary to gain access to the work area by removing the tail cone access panel 351GL, and the air inlet silencer, located at zone 351. PART II HARNESS W205 REPLACEMENT Applicable to: Refer to 1.A. SB EFFECTIVITY

. PART II of this bulletin consists of the replacement of the APU ESC power cables (harness W205). To do this, it is necessary to gain access to the work area by removing the access panel 351GL, 314BR, 252AZ, the air inlet silencer, and replacing the APU power cable feedthrough, located at zones 311 and 351. NOTE: The modification presented in this bulletin does not affect the Fatigue Critical Structure (FCS). E. COMPLIANCE (1) APPLICABLE TO PART I Embraer recommends that PART I of this bulletin be accomplished within the next 3000 Flight Hour(s) after the original issue of this Service Bulletin. (2) APPLICABLE TO PART II – If during the accomplishment of the inspection described in PART I, the damage affects the harness insulation and the wire strands (inner conductors), EMBRAER recommends that the APU Auxiliary Power Unit (APU) be considered 

# SERVICE BULLETIN

DATE: 28/Feb/2011 REVISION No.:01 - 16/Mar/2012 SB No.: 170-53-0093 PAGE: 3 Copyright © 2012 by Embraer S.A. All rights reserved.1. Cut the tube PN RNF-100-3/4-9 2 inches larger than the damage. 2. Sand harness W205 carefully with a #150 to #180 sand paper. 3. Clean harness W205 with alcohol Isopropyl Alcohol (TT-I-735) TT-I-735 . 4. Pass Heat Shrinkable tubing PN RNF-100-3/4-9 through the damaged cable (Harness W205). 5. With a heat gun or equivalent, apply heat only to the middle of heat shrinkable tubing. 6. With the aid of a spatula, apply adhesive Epoxy Adhesive (A-A-56031) S1006 to the cable. 7. With a heat gun or equivalent, apply heat only to the ends of heat shrinkable tubing. 

# SERVICE BULLETIN

SB No.: 170-53-0093 PAGE: 24 DATE: 28/Feb/2011 REVISION No.: 01 - 16/Mar/2012 FIGURE 3 - HARNESS W205 REPAIR (SHEET 01 OF 02)

Copyright © 2012 by Embraer S.A. All rights reserved.inoperative until the replacement of harness W205. F. APPROVAL The technical aspects of this Service Bulletin are approved by: Agência Nacional de Aviação Civil (ANAC). 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 readily available when necessary. This estimate does not include the sealant, paint, or adhesive curing time. (1) APPLICABLE TO PART I – Access opening: 0.5 man-hours. – Inspection: 1.0 man-hour. – Modification: 3.0 man-hours. – Access closure: 0.5 man-hours. – Test: 1.0 man-hour. (2) APPLICABLE TO PART II – Access opening: 1.5 man-hours. – Inspection: None. – Modification: 10.0 man-hours. – Access closure: 1.5 man-hours. 

# SERVICE BULLETIN

SB No.: 170-53-0093 PAGE: 4 DATE: 28/Feb/2011 REVISION No.: 01 - 16/Mar/2012 Copyright © 2012 by Embraer S.A. All rights reserved.– Test: 1.0 man-hour. H. WEIGHT AND BALANCE (1) APPLICABLE TO PART I (a) Applicable to EMBRAER 170 – Change in basic weight: + 0,1728 lb (+ 0,0784 kg). – Change in basic moment: + 185,2249 lb.in (+ 2,1340 kg.m). (b) Applicable to EMBRAER 175 – Change in basic weight: + 0,1728 lb (+ 0,0784 kg). – Change in basic moment: + 197,3237 lb.in (+ 2,2734 kg.m). (2) APPLICABLE TO PART II (a) Applicable to EMBRAER 170 and EMBRAER 175 None. I. SOFTWARE ACCOMPLISHMENT SUMMARY None. J. REFERENCES AIPC 170/( ) Aircraft Illustrated Parts Catalog - 49-42-11 - AIRBORNE AUXILIARY POWER. AMM 170/( ) Aircraft Maintenance Manual PART I - 34-61-00 - NAVIGATION. AMM 170/( ) Aircraft Maintenance Manual PART II - 20-00-00 - STANDARD PRACTICES-AIRFRAME. 

# SERVICE BULLETIN

DATE: 28/Feb/2011 REVISION No.:01 - 16/Mar/2012 SB No.: 170-53-0093 PAGE: 5 Copyright © 2012 by Embraer S.A. All rights reserved.AMM 170/( ) Aircraft Maintenance Manual PART II - 49-00-00, 49-10-00, 49-16-01, and 49-42-11 - AIRBORNE AUXILIARY POWER. AMM 170/( ) Aircraft Maintenance Manual PART II - 53-03-64 - FUSELAGE. K. OTHER PUBLICATIONS AFFECTED AIPC 170/( ) Aircraft Illustrated Parts Catalog - 53-31-00 - FUSELAGE. 

# SERVICE BULLETIN

SB No.: 170-53-0093 PAGE: 6 DATE: 28/Feb/2011 REVISION No.: 01 - 16/Mar/2012 Copyright © 2012 by Embraer S.A. All rights reserved.2. MATERIAL INFORMATION A. MATERIAL - PRICE AND AVAILABILITY (1) MATERIAL AVAILABLE FROM EMBRAER (a) APPLICABLE TO PART I The kit below required for the accomplishment of PART I of this bulletin will be available from Embraer at no charge to the operator. Embraer will receive the ′′no charge′′ orders during a period of 12 months after the latest release date of this service bulletin. The estimated delivery date will be provided by Embraer upon request. When ordering, specify SB 170-53-0093 and Top Kit PN presented in Table below, as applicable.

REF TOP KIT PN Unit Price (US$) TOP KIT EFFECTIVITY
01 BS1705300930001 523.85 Refer to 1.A. SB EFFECTIVITY / PART I. (b) APPLICABLE TO PART II The material below, required for the accomplishment of PART II of this bulletin will be available from Embraer.
NEW PN DESCRIPTION OLD PN QTY DISP/ Notes 171-06728-401 Harness W205 170-25066-401 or 171-06728-401 01 7/ [1]
1. Refer to AIPC 49-42-11 - ELECTRONIC STARTER CONTROLLER / AICC INTERFACE HARNESS (W205). 

# SERVICE BULLETIN

DATE: 28/Feb/2011 REVISION No.:01 - 16/Mar/2012 SB No.: 170-53-0093 PAGE: 7 Copyright © 2012 by Embraer S.A. All rights reserved.NEW PN DESCRIPTION OLD PN QTY DISP/ Notes 207W245-3-01/42 or 207W245-3-01/42-0 Freedthrough 207W245-3-01/42 01 7/ [1]
1. Refer to AIPC 49-42-11 - ELECTRONIC STARTER CONTROLLER / AICC INTERFACE HARNESS (W205). DISPOSITION: 7 = Replace with part bearing same PN (2) MATERIAL AVAILABLE FROM OTHER VENDORS None. B. INDUSTRY SUPPORT INFORMATION None. C. MATERIAL NECESSARY FOR EACH AIRCRAFT When applicable, the use of alternative or similar parts in place of the one specified in the kits is allowable, provided that these alternative or similar parts are approved by Embraer as indicated in the related Embraer Technical Publications or through a formal Embraer communication channel. The necessary expendable or consumable parts presented in the AMM Tasks referred to in this bulletin 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. For ordering information and Top Kit effectivity refer to section 2.A. MATERIAL - PRICE AND AVAILABILITY of this Bulletin. 

# SERVICE BULLETIN

SB No.: 170-53-0093 PAGE: 8 DATE: 28/Feb/2011 REVISION No.: 01 - 16/Mar/2012 Copyright © 2012 by Embraer S.A. All rights reserved.(1) TOP KITS AND KITS Kit Summary: Top Kit Composition (Kit PN / Quantity) Top Kit PN 171-11709-603 BS1705300930001 01
Kit PN 171-11709-603 NEW PN DESCRIPTION OLD PN QTY SUP QTY RQD DISP/ Notes 191-21716-003 Grommet Support - 01 01 2 T50R-6TZ Cable Tie - 02 02 2 (2) MATERIAL TO BE PROCURED (a) Parts If applicable, the material below or equivalent, required to repair the cable, should be procured from the operator’s inventories, from a local supplier or ordered as spare from Embraer.
Refer to 1.A. SB EFFECTIVITY NEW PN DESCRIPTION OLD PN QTY DISP/ Notes

RNF-100-3/4-9 Heat Shrinkable Tubing or similar - 01 6 (b) Consumable Materials If during the inspection any sign of damage to the harness W205 was detected, the material below or equivalent, required to repair the cable, should be procured from the operator’s inventories or from a local supplier. 

# SERVICE BULLETIN

DATE: 28/Feb/2011 REVISION No.:01 - 16/Mar/2012 SB No.: 170-53-0093 PAGE: 9 Copyright © 2012 by Embraer S.A. All rights reserved.Refer to 1.A. SB EFFECTIVITY NEW PN DESCRIPTION OLD PN QTY DISP/ Notes
S1006 Adhesive - 01 6/ [1] 1. Epoxy Adhesive (A-A-56031) S1006. DISPOSITION: 2 = Incorporate part bearing NEW PN 6 = Apply as required D. MATERIAL NECESSARY FOR EACH SPARE None. E. REIDENTIFIED PARTS None. F. TOOLING - PRICE AND AVAILABILITY Whenever required, the necessary 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

SB No.: 170-53-0093 PAGE: 10 DATE: 28/Feb/2011 REVISION No.: 01 - 16/Mar/2012 Copyright © 2012 by Embraer S.A. All rights reserved.3. ACCOMPLISHMENT INSTRUCTIONS NOTE: 1) For the purpose of this Service Bulletin, a Detailed Inspection (DI) is: “An intensive examination of a specific item, installation or assembly to detect damage, failure or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be necessary. Surface cleaning and elaborate access procedures may be required.” 2) Obey all of the WARNINGS and CAUTIONS included in the referenced manuals and procedures. 3) The Manuals and other documents are referred to by acronyms or using a simplified form. Refer to section 1.J. 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. Refer to AMM TASK 20-00-00-910- 801-A/200 - Aircraft Maintenance Safety Procedures - Standard Procedures. B. PART I – INSPECTION AND PROTECTION FOR HARNESS W205 (1) Carry out the procedure to make the aircraft safe for maintenance of the APU (Refer to AMM TASK 49-00-00-910-801-A/200 - Airborne Auxiliary Power - Maintenance Practices). WARNING : DO NOT TOUCH THE EXHAUST DUCT AND APU COMPONENTSUNTIL THEY ARE COOL. THE TEMPERATURE STAYS HIGH AFTER THE APU STOPS. IF YOU TOUCH THEM, YOU CAN BURN YOURSELF. (2) Remove tail cone access panel 351GL. Refer to AMM TASK 53-03-64-000-801- A/400 - Tail-Cone External Access-Panels - Removal. (3) Remove the air inlet silencer. Refer to AMM TASK 49-16-01-000-801-A/400 - APU Air Inlet Silencer Assembly - Removal. 

# SERVICE BULLETIN

DATE: 28/Feb/2011 REVISION No.:01 - 16/Mar/2012 SB No.: 170-53-0093 PAGE: 11 Copyright © 2012 by Embraer S.A. All rights reserved.(4) On the MCDU (AMM SDS 34-61-00/1), use the sequence in parentheses to make sure that these SSPCs are open: – ASC CMD PWR-SPDA2 (CBMENU/CB BY SYS/APU) – APU FADEC-SPDA2 (CBMENU/CB BY SYS/APU) – APU FUEL SOV OPN-SPDA2 (CBMENU/CB BY SYS/APU) (5) Perform a detailed visual inspection for damage on the APU ESC power cables (harness W205). Refer to Figure 1

. NOTE: The damage may occur if the grommet, installed in the tail cone firewall, moves (moved) out of its place, allowing contact between the APU ESC power cables (harness W205 ) and the tail cone firewall. For this, if the grommet is not installed in the indicated position, reinstall it before the support installation as mentioned in Figure 2

. (6) If there is no damage to the APU ESC power cables, install the new support in the tail cone firewall. Refer to Figure 2 and go to Step 3.B.(8) and on. (7) If there is any sign of damage to the APU ESC power cables, do as follows: (a) If the damage only affects the harness insulation, repair the harness insulation by following the instructions given in Figure 3, install the new support in the tail cone firewall. Refer to Figure 2 , and go to Step 3.B.(8) and on. (b) If the damage affects the harness insulation and the inner conductors (wire strands), install the new support in the tail cone firewall as mentioned in Figure 2 and then, replace the harness W205 as described in PART II of this bulletin. Go to Step 3.B.(8) and on. (8) Reinstall the air inlet silencer. Refer to AMM TASK 49-16-01-400-801-A/400 - APU Air Inlet Silencer Assembly - Installation. (9) Reinstall the tail cone access panel 351GL, according to AMM TASK 53-03-64-400- 801-A/400 - Tail Cone External Access Panels - Installation. (10) On the MCDU (AMM SDS 34-61-00/1), use the sequence in parentheses to make sure that these SSPCs are closed: 

# SERVICE BULLETIN

SB No.: 170-53-0093 PAGE: 12 DATE: 28/Feb/2011 REVISION No.: 01 - 16/Mar/2012 Copyright © 2012 by Embraer S.A. All rights reserved.– ASC CMD PWR-SPDA2 (CBMENU/CB BY SYS/APU) – APU FADEC-SPDA2 (CBMENU/CB BY SYS/APU) – APU FUEL SOV OPN-SPDA2 (CBMENU/CB BY SYS/APU) (11) Perform the test of the APU system as described below: 1) START THE APU (AMM TASK 49-10-00-910-801-A/200 - AUXILIARY POWER UNIT (APU) - START); 2) OPERATE THE APU FOR TWO MINUTES; 3) MAKE SURE THE EICAS SHOW NO APU FAULT MESSAGE; 4) SHUTDOWN THE APU (AMM TASK 49-10-00-910-802-A/200 - AUXILIARY POWER UNIT (APU) - SHUTDOWN). (12) Restore the aircraft to normal. (13) Enter the accomplishment of PART I of this bulletin in the applicable documents. C. PART II – HARNESS W205 REPLACEMENT (1) Replace the damaged Harness W205 with a new one. Refer to AMM MPP 49-42-11/401 - ELECTRONIC STARTER CONTROLLER / AICC INTERFACE HARNESS (W205) - REMOVAL/INSTALLATION. (2) Restore the aircraft to normal. (3) Enter the accomplishment of PART II of this bulletin in the applicable documents. NOTE: 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 fleet-wide or that the SB will not be incorporated, so that Embraer can update the affected 

# SERVICE BULLETIN

DATE: 28/Feb/2011 REVISION No.:01 - 16/Mar/2012 SB No.: 170-53-0093 PAGE: 13 Copyright © 2012 by Embraer S.A. All rights reserved.technical publications, use the “Service Bulletin Full-Fleet Incorporation Report” form, which is available on the Flyembraer portal (http://www.flyembraer.com). 3) Use the attached “Service Bulletin Evaluation” form to send us your comments regarding this SB. Your feedback will be much appreciated as an aid for us to improve the quality of the SBs. 

# SERVICE BULLETIN

SB No.: 170-53-0093 PAGE: 14 DATE: 28/Feb/2011 REVISION No.: 01 - 16/Mar/2012 Copyright © 2012 by Embraer S.A. All rights reserved.1. Perform a detailed visual inspection for damage on the APU ESC power cables in the region shown in Detail C . If necessary, pull the cable slightly in the Starter Controller direction to help in the inspection. NOTE: The damage may occur if the grommet installed in the tail cone firewall moves (moved) out of its place, allowing contact between the APU ESC power cables and the tail cone firewall. (a) If there is no damage to the APU ESC power cables, install the new support in the tail cone firewall, according to Figure 2

. (b) If there is any sign of damage to the APU ESC power cables, do as follows: – If the damage only affects the harness insulation, repair the harness insulation according to Figure 3 and install the new support in the tail cone firewall according to Figure 2

. Verify if the grommet is installed in the position shown in Detail C . If the grommet is not installed in the indicated position, reinstall it. – If the damage affects the harness insulation and the wire strands (inner conductors), install the new support in the tail cone firewall, refer to Figure 2 and then, replace the harness W205 as described in PART II of this Service Bulletin. 

# SERVICE BULLETIN

DATE: 28/Feb/2011 REVISION No.:01 - 16/Mar/2012 SB No.: 170-53-0093 PAGE: 15 FIGURE 1 - DETAILED INSPECTION OF HARNESS W205 (SHEET 01 OF 04)

Copyright © 2012 by Embraer S.A. All rights reserved.TAILCONE (REF.) 

### A ZONE

351



### A

FWD ACCESS PANEL 351 GL 

### BEM170SB531057A.DGN 

# SERVICE BULLETIN

SB No.: 170-53-0093 PAGE: 16 DATE: 28/Feb/2011 REVISION No.: 01 - 16/Mar/2012 FIGURE 1 - DETAILED INSPECTION OF HARNESS W205 (SHEET 02 OF 04)

Copyright © 2012 by Embraer S.A. All rights reserved.STARTER CONTROLLER (REF.)

FIREWALL (REF.) 

### C

APU COMPARTMENT (REF.)



### C B POWER SUPPLY CABLE (REF.)

GROMMET (VERIFY) (REINSTALL, IF NECESSARY) 1 1

2

1 2 POWER SUPPLY CABLES (REF.) 

### D

VERIFY IF THE GROMMET IS INSTALLED AS INDICATED IN THE FIGURE. IF IT IS NOT INSTALLED AS INDICATED, REINSTALL IT. INSPECT THE CABLES ACCORDING TO SECTION 3. ACCOMPLISHMENT INSTRUCTION OF THIS SERVICE BULLETIN. INSPECT THE CABLES APU ESC POWER CABLES (REF.)

1EM170SB531058C.DGN 

# SERVICE BULLETIN

DATE: 28/Feb/2011 REVISION No.:01 - 16/Mar/2012 SB No.: 170-53-0093 PAGE: 17 FIGURE 1 - DETAILED INSPECTION OF HARNESS W205 (SHEET 03 OF 04)

Copyright © 2012 by Embraer S.A. All rights reserved.1 INSPECT THE CABLES ACCORDING TO SECTION 3. ACCOMPLISHMENT INSTRUCTION OF THIS SERVICE BULLETIN. 

### D (CABLE CONSTRUCTION) INSULATION (INSPECT THE CABLES) INSULATION (INSPECT THE CABLES) WIRE STRANDS (INSPECT THE CABLES) 1

1 1 1

1EM170SB531093B.DGN 1 

# SERVICE BULLETIN

SB No.: 170-53-0093 PAGE: 18 DATE: 28/Feb/2011 REVISION No.: 01 - 16/Mar/2012 FIGURE 1 - DETAILED INSPECTION OF HARNESS W205 (SHEET 04 OF 04)

Copyright © 2012 by Embraer S.A. All rights reserved.1. Remove and retain the existing nuts and disconnect the power supply cables from the bottom of the starter controller. Refer to View B (PRE-MOD)

. 2. Remove and retain the existing bolts (03 positions) and the washers (03 positions). Refer to Detail C (PRE-MOD)

. NOTE: Make sure that the grommet is correctly installed in the APU firewall to prevent harness chafing. 3. Pass support PN 191-21716-003 through the power supply cables and then position it over the grommet as shown in Detail C (POST-MOD)

. 4. Install support PN 191-21716-003 over the grommet, using the retained washers and bolts removed in step 3 (above). Refer to Detail C (POST-MOD) and to View D to the correct power cables position. NOTE: Apply a torque of 3.38 - 3.95 N.m (30 - 35 lbf.in) to the bolts. 5. Connect the power supply cable and install the nut to the starter controller. Refer to View B (POST-MOD) and View D

. NOTE: Apply a torque of 3.5 - 4.1 N.m (31 - 36 lb.in) to the nut. 6. Connect the power supply cable and install the nut to the starter controller. Refer to View B (POST-MOD) and View D

. NOTE: Apply a torque of 7.0 - 8.1 N.m (62 - 72 lb.in) to the nut. 7. Install cable ties PN T50R-6TZ (02 positions) as shown in Detail C (POST-MOD)

. 

# SERVICE BULLETIN

DATE: 28/Feb/2011 REVISION No.:01 - 16/Mar/2012 SB No.: 170-53-0093 PAGE: 19 FIGURE 2 - GROMMET SUPPORT INSTALLATION (SHEET 01 OF 05)

Copyright © 2012 by Embraer S.A. All rights reserved.TAILCONE (REF.)EM170SB531049A.DGN 

### A ZONE

351



### A

FWD ACCESS PANEL 351 GL 

### B 

# SERVICE BULLETIN

SB No.: 170-53-0093 PAGE: 20 DATE: 28/Feb/2011 REVISION No.: 01 - 16/Mar/2012 FIGURE 2 - GROMMET SUPPORT INSTALLATION (SHEET 02 OF 05)

Copyright © 2012 by Embraer S.A. All rights reserved.STARTER CONTROLLER (REF.)

FIREWALL (REF.) 

### C

PRE − MOD APU COMPARTMENT (REF.)



### C BOLT WASHER (03 POSITIONS) (REMOVE AND RETAIN) POWER SUPPLY CABLE (DISCONNECT)EM170SB531050A.DGN NUT (02 POSITIONS) (REMOVE AND RETAIN)

1

POWER SUPPLY CABLE (DISCONNECT)

PRE − MOD 1

1

GROMMET (REF.)

2 

### B 

# SERVICE BULLETIN

DATE: 28/Feb/2011 REVISION No.:01 - 16/Mar/2012 SB No.: 170-53-0093 PAGE: 21 FIGURE 2 - GROMMET SUPPORT INSTALLATION (SHEET 03 OF 05)

Copyright © 2012 by Embraer S.A. All rights reserved.APU COMPARTMENT (REF.) FIREWALL (REF.) STARTER CONTROLLER (REF.)

POWER SUPPLY CABLE (CONNECT) POWER SUPPLY CABLE (CONNECT) NUT (REINSTALL) NUT (REINSTALL)

CABLE TIE PN T50R−6TZ (02 POSITIONS) (INSTALL)

BOLT WASHER (03 POSITIONS) (REINSTALL) GROMMET SUPPORT PN 191−21716−003 (POSITION) (INSTALL) 

### D C

TORQUE: 7.0 − 8.1 N.m (62 − 72 lb.in) TO THE NUT. 2 TORQUE: 3.5 − 4.1 N.m (31 − 36 lb.in) TO THE NUT. TORQUE: 3.38 − 3.95 N.m (30 − 35 lb.in) TO THE BOLTS. 

### C POST − MOD 2

POST − MOD 3

3 1 16 5

5

6
4 3 

### B

7

4EM170SB531051B.DGN 

# SERVICE BULLETIN

SB No.: 170-53-0093 PAGE: 22 DATE: 28/Feb/2011 REVISION No.: 01 - 16/Mar/2012 FIGURE 2 - GROMMET SUPPORT INSTALLATION (SHEET 04 OF 05)

Copyright © 2012 by Embraer S.A. All rights reserved.45° (REF.)

45° (REF.) 

### DEM170SB531055A.DGN STARTER CONTROLLER (REF.) 5 6 POWER SUPPLY CABLE (CONNECT) 

# SERVICE BULLETIN

DATE: 28/Feb/2011 REVISION No.:01 - 16/Mar/2012 SB No.: 170-53-0093 PAGE: 23 FIGURE 2 - GROMMET SUPPORT INSTALLATION (SHEET 05 OF 05)

Copyright © 2012 by Embraer S.A. All rights reserved.EM170SB531095A.DGN 

### 4 5

6 7 CLEAN THE CABLE ACCORDING TO SWPM 20−61−10 CLEAN

PASS THE TUBE THROUGH THE CABLE HEAT THE MIDDLE OF THE TUBE CAREFULLY HEAT GUN

APPLY GLUE AS INDICATED GLUE GLUE

HEAT THE ENDS OF THE TUBE HEAT GUN HEAT GUN 

### 1 2

3 CUT THE TUBE 2 INCHES LARGER THAN DAMAGE

DAMAGE

SAND CAREFULLY THE DAMAGED CABLE 

# SERVICE BULLETIN

DATE: 28/Feb/2011 REVISION No.:01 - 16/Mar/2012 SB No.: 170-53-0093 PAGE: 25 FIGURE 3 - HARNESS W205 REPAIR (SHEET 02 OF 02)

Copyright © 2012 by Embraer S.A. All rights reserved.

### 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 PUBLICATIONS. PLEASE FILL IN FORM AND RETURN IT TO: EMBRAER - EMPRESA BRASILEIRA DE AERONÁUTICA S.A. EFTC - SERVICE BULLETIN ENGINEERING AV. BRIGADEIRO FARIA LIMA, 2170 SÃO JOSÉ DOS CAMPOS - SP - 12227-901 BRASIL Fax: + 55 12 3927-6600 (ext. 1624) e-mail: fleet.reliability@embraer.com.br S.B. Title: S.B.: (Number / Rev.) Operator: SB Implementation Report Aircraft Serial Number or Registration Number: Incorporation Date: Aircraft Flight Hours: Aircraft Landings:
POST-ACCOMPLISHMENT EVALUATION: (Check applicable squares below) ESTIMATED MANPOWER: [ ] OK [ ] NOT OK (Explain Below) MATERIAL & KITS: [ ] OK [ ] NOT OK (Explain Below) ACCOMPLISHMENT INSTRUCTIONS: [ ] OK [ ] NOT OK (Explain Below) FIGURES: [ ] OK [ ] NOT OK (Explain Below) SB GENERAL EVALUATION: [ ] OK [ ] NOT OK (Explain Below) COMMENTS: (Bulletin quality/ Difficulties found at the time of incorporation/ Suggested improvements/ Other)

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

Copyright © 2012 by Embraer S.A. All rights reserved.