# Embraer Service Bulletin 190-53-0054

Copy: Revision 01 ("Service Bulletin - 190-53-0054"), 30 pages: PDF https://openairdocs.org/files/sha256/96/02/9602ce753856052868c822863c60c54536e27d4b7afc0505c73c9d84dda72a61; text https://openairdocs.org/service-documents/embraer/sb-190-53-0054/file/9602ce753856.md. Rights: © Embraer S.A. Filed by the FAA in regulations.gov docket FAA-2013-0092; AD 2013-16-22 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Embraer](https://openairdocs.org/service-documents/embraer.md)
- Type: Service bulletin (Service Bulletin)
- Number: 190-53-0054
- Latest revision known: 190-53-0054, Revision 01, dated March 16, 2012 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/embraer/sb-190-53-0054

## ADs that cite it (1) (OpenAirDocs)

Newest first, with the revision each names, as OpenAirDocs read it from the AD's text.

- [AD 2013-16-22](https://openairdocs.org/ad/2013-16-22.md), effective Sep 27, 2013: Revision 01

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/embraer/sb-190-53-0054/proposed.md).

## Text (30 pages)

Rights: © Embraer S.A. Filed by the FAA in regulations.gov docket FAA-2013-0092; AD 2013-16-22 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

1. DESCRIPTION
This sheet transmits Revision 01 to Service Bulletin 190-53-0054.
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.: 190-53-0054
PAGE: 1 of 1
Copyright © 2012 by Embraer S.A. All rights reserved.

### Page 2

(No text on this page.)

### Page 3

FUSELAGE - INSPECTION AND PROTECTION FOR HARNESS W205
1. PLANNING INFORMATION
A. SB EFFECTIVITY
Aircraft affected:
MODEL SN
Embraer 190( ) and 195( ) 19000002, 19000004, 19000006 thru 19000108,
19000110 thru 19000139, 19000141 thru 19000158,
19000160 thru 19000176, 19000178 thru 19000202,
19000204 thru 19000224, 19000226 thru 19000235,
19000237 thru 19000242, 19000244 thru 19000260,
19000262 thru 19000277, 19000279 thru 19000295,
19000297 thru 19000306, 19000308 thru 19000316,
19000318 thru 19000361, and 19000363 thru 19000434.
Affected component:
None.
In-production effectivity:
Embraer 190( ) and 195( ) model aircraft SN 19000003, SN 19000005, and 19000435
and on, have an equivalent modification factory-incorporated.
B. CONCURRENT REQUIREMENTS
None.
SERVICE BULLETIN
DATE: 28/Feb/2011
REVISION No.:01 - 16/Mar/2012
SB No.: 190-53-0054
PAGE: 1 of 25
Copyright © 2012 by Embraer S.A. All rights reserved.

### Page 4

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.
(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.: 190-53-0054
PAGE: 2
DATE: 28/Feb/2011
REVISION No.: 01 - 16/Mar/2012
Copyright © 2012 by Embraer S.A. All rights reserved.

### Page 5

(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.: 190-53-0054
PAGE: 3
Copyright © 2012 by Embraer S.A. All rights reserved.

### Page 6

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.: 190-53-0054
PAGE: 4
DATE: 28/Feb/2011
REVISION No.: 01 - 16/Mar/2012
Copyright © 2012 by Embraer S.A. All rights reserved.

### Page 7

– 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 190/( ) Aircraft Illustrated Parts Catalog - 49-42-11 - AIRBORNE
AUXILIARY POWER.
AMM 190/( ) Aircraft Maintenance Manual PART I - 34-61-00 - NAVIGATION.
AMM 190/( ) 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.: 190-53-0054
PAGE: 5
Copyright © 2012 by Embraer S.A. All rights reserved.

### Page 8

AMM 190/( ) Aircraft Maintenance Manual PART II - 49-00-00, 49-10-00,
49-16-01, and 49-42-11 - AIRBORNE AUXILIARY POWER.
AMM 190/( ) Aircraft Maintenance Manual PART II - 53-03-64 - FUSELAGE.
K. OTHER PUBLICATIONS AFFECTED
AIPC 190/( ) Aircraft Illustrated Parts Catalog - 53-31-00 - FUSELAGE.
SERVICE BULLETIN
SB No.: 190-53-0054
PAGE: 6
DATE: 28/Feb/2011
REVISION No.: 01 - 16/Mar/2012
Copyright © 2012 by Embraer S.A. All rights reserved.

### Page 9

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 190-53-0054 and Top Kit PN presented in Table
below, as applicable.
REF TOP KIT PN Unit Price(US$) TOP KITEFFECTIVITY
01 BS1905300540001 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
190-19047-401 Harness W205
190-19047-401 or
190-03784-401
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.: 190-53-0054
PAGE: 7
Copyright © 2012 by Embraer S.A. All rights reserved.

### Page 10

NEW PN DESCRIPTION OLD PN QTY DISP/Notes
207W245-3-01/42or
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.: 190-53-0054
PAGE: 8
DATE: 28/Feb/2011
REVISION No.: 01 - 16/Mar/2012
Copyright © 2012 by Embraer S.A. All rights reserved.

### Page 11

(1) TOP KITS AND KITS
Kit Summary: Top Kit Composition (Kit PN / Quantity)
Top Kit PN 171-11709-603
BS1905300540001 01
Kit PN 171-11709-603
NEW PN DESCRIPTION OLD PN QTYSUP QTYRQD 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
-0 1 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.: 190-53-0054
PAGE: 9
Copyright © 2012 by Embraer S.A. All rights reserved.

### Page 12

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.: 190-53-0054
PAGE: 10
DATE: 28/Feb/2011
REVISION No.: 01 - 16/Mar/2012
Copyright © 2012 by Embraer S.A. All rights reserved.

### Page 13

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 (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 AF-
TER 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.
(4) On the MCDU (AMM SDS 34-61-00/1), use the sequence in parentheses to make
sure that these SSPCs are open:
SERVICE BULLETIN
DATE: 28/Feb/2011
REVISION No.:01 - 16/Mar/2012
SB No.: 190-53-0054
PAGE: 11
Copyright © 2012 by Embraer S.A. All rights reserved.

### Page 14

– 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.Refer 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:
– ASC CMD PWR-SPDA2 (CBMENU/CB BY SYS/APU)
– APU FADEC-SPDA2 (CBMENU/CB BY SYS/APU)
SERVICE BULLETIN
SB No.: 190-53-0054
PAGE: 12
DATE: 28/Feb/2011
REVISION No.: 01 - 16/Mar/2012
Copyright © 2012 by Embraer S.A. All rights reserved.

### Page 15

– 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
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: 28/Feb/2011
REVISION No.:01 - 16/Mar/2012
SB No.: 190-53-0054
PAGE: 13
Copyright © 2012 by Embraer S.A. All rights reserved.

### Page 16

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.: 190-53-0054
PAGE: 14
DATE: 28/Feb/2011
REVISION No.: 01 - 16/Mar/2012
Copyright © 2012 by Embraer S.A. All rights reserved.

### Page 17

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. Refer 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 inDetail 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 toFigure 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.: 190-53-0054
PAGE: 15
FIGURE 1 - INSPECTION OF HARNESS W205
(SHEET 01 OF 04)
Copyright © 2012 by Embraer S.A. All rights reserved.

### Page 18

TAILCONE 
(REF.)
A
ZONE
351
A
FWD ACCESS
PANEL 351 GL
B
EM170SB531059A.DGN
SERVICE BULLETIN
SB No.: 190-53-0054
PAGE: 16
DATE: 28/Feb/2011
REVISION No.: 01 - 16/Mar/2012
FIGURE 1 - INSPECTION OF HARNESS W205
(SHEET 02 OF 04)
Copyright © 2012 by Embraer S.A. All rights reserved.

### Page 19

EM170SB531060B.DGN
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
SERVICE BULLETIN
DATE: 28/Feb/2011
REVISION No.:01 - 16/Mar/2012
SB No.: 190-53-0054
PAGE: 17
FIGURE 1 - INSPECTION OF HARNESS W205
(SHEET 03 OF 04)
Copyright © 2012 by Embraer S.A. All rights reserved.

### Page 20

1 INSPECT THE CABLES ACCORDING TO SECTION 3. ACCOMPLISHMENT INSTRUCTION OF THIS SERVICE BULLETIN.
EM170SB531094A.DGN
D
(CABLE CONSTRUCTION)
INSULATION
(INSPECT THE CABLES)
INSULATION
(INSPECT THE CABLES)
WIRE STRANDS
(INSPECT THE CABLES)
1
1
1
1
1
1
SERVICE BULLETIN
SB No.: 190-53-0054
PAGE: 18
DATE: 28/Feb/2011
REVISION No.: 01 - 16/Mar/2012
FIGURE 1 - INSPECTION OF HARNESS W205
(SHEET 04 OF 04)
Copyright © 2012 by Embraer S.A. All rights reserved.

### Page 21

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 the support PN 191-21716-003 through the power supply cables and then position
it over the grommet as indicated in Detail C (POST-MOD).
4. Install the 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 toView
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 toView
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.: 190-53-0054
PAGE: 19
FIGURE 2 - GROMMET SUPPORT INSTALLATION
(SHEET 01 OF 05)
Copyright © 2012 by Embraer S.A. All rights reserved.

### Page 22

TAILCONE 
(REF.)
A
ZONE
351
A
FWD ACCESS
PANEL 351 GL
B
EM170SB531052A.DGN
SERVICE BULLETIN
SB No.: 190-53-0054
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.

### Page 23

STARTER 
CONTROLLER
(REF.)
FIREWALL
(REF.)
C
PRE − MOD
APU COMPARTMENT
(REF.)
CBOLTWASHER
(03 POSITIONS)
(REMOVE AND RETAIN)
POWER SUPPLY CABLE
(DISCONNECT)
NUT
(02 POSITIONS)
(REMOVE AND RETAIN)
1
POWER SUPPLY CABLE
(DISCONNECT)
PRE − MOD
1
1
GROMMET
(REF.)
2
EM170SB531053A.DGN
B
SERVICE BULLETIN
DATE: 28/Feb/2011
REVISION No.:01 - 16/Mar/2012
SB No.: 190-53-0054
PAGE: 21
FIGURE 2 - GROMMET SUPPORT INSTALLATION
(SHEET 03 OF 05)
Copyright © 2012 by Embraer S.A. All rights reserved.

### Page 24

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)
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
65
5
6
43
7
B
D
4
EM170SB531054B.DGN
SERVICE BULLETIN
SB No.: 190-53-0054
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.

### Page 25

45°
(REF.)
  45°
(REF.)
D
STARTER
CONTROLLER
(REF.)
56
POWER SUPPLY CABLE
(CONNECT)
EM170SB531056A.DGN
SERVICE BULLETIN
DATE: 28/Feb/2011
REVISION No.:01 - 16/Mar/2012
SB No.: 190-53-0054
PAGE: 23
FIGURE 2 - GROMMET SUPPORT INSTALLATION
(SHEET 05 OF 05)
Copyright © 2012 by Embraer S.A. All rights reserved.

### Page 26

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.: 190-53-0054
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.

### Page 27

EM170SB531095A.DGN
45
67
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
12
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.: 190-53-0054
PAGE: 25
FIGURE 3 - HARNESS W205 REPAIR
(SHEET 02 OF 02)
Copyright © 2012 by Embraer S.A. All rights reserved.

### Page 28

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### Page 29

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.

### Page 30

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