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 COMPONENTS

UNTIL 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

B

EM170SB531057A.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.)

1

EM170SB531058C.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

1

EM170SB531093B.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

1

6 5

5

6

3 4

B

7

4

EM170SB531051B.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.)

D

EM170SB531055A.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.