1. DESCRIPTION

This sheet transmits Revision 02 to Service Bulletin 190-21-0041.

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 original issue of this bulletin do not need any additional

action.

3. RECORD OF REVISION

Basic issue: 27/Sep/2012.

Revision 01: 20/Dec/2012.

Revision 02: 30/Jul/2013.

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.C. REASON / 02 AND 04 Updated reason text and added reason for revision

02

1.D. DESCRIPTION / 04 AND 05 Updated Hamilton Sundstrand bulletin and updated

links to Hamilton Sundstrand bulletin

1.G. ESTIMATED MANPOWER / 06 Updated text information

3. ACCOMPLISHMENT INSTRUCTIONS / 10 THRU

12

Included new AMS Controller Board PNS and updated text information

4. APPENDIX 1 / 13 THRU 43 Updated Hamilton Sundstrand bulletin

TRANSMITTAL LETTER

SB No.: 190-21-0041

PAGE: 1 of 1

Copyright © 2013 by Embraer S.A. All rights reserved.

AIR CONDITIONING - AIR MANAGEMENT SYSTEM CONTROLLER PROCESSOR

BOARD - INCORPORATION OF NEW OPS SOFTWARE (BLACK LABEL 13.0)

In connection with the use of this document, Embraer does not provide any express or implied

warranties and expressly disclaims any warranty of merchantability or fitness for a particular purpose.

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,

19000363 thru 19000437, 19000439 thru 19000452, 19000454 thru

19000466, 19000468 thru 19000525, 19000527 thru 19000533,

19000535 thru 19000558, 19000560 thru 19000570, 19000572 thru

19000586, 19000588, and 19000590 thru 19000592, equipped with

affected component.

Affected component:

AMS controller processor boards PN prefix 1001050, with any previously released Black

Label version, installed on the aircraft and in stock as spare.

NOTE: This effectivity list includes the aircraft originally equipped with the affected

component. Since this component is a Line Replaceable Unit (LRU), it may

be necessary to refer to the fleet maintenance control record and verify

whether the unit has been replaced with another one, during the routine

maintenance.

In-production effectivity:

SERVICE BULLETIN

DATE: 27/Sep/2012

REVISION No.:02 - 30/Jul/2013

SB No.: 190-21-0041

PAGE: 1 of 44

Copyright © 2013 by Embraer S.A. All rights reserved.
Embraer 190 ( ) and 195 ( ) model aircraft SN 19000587, SN 19000589, and 19000593

and on, have an equivalent modification factory-incorporated.

B. CONCURRENT REQUIREMENTS

None.

C. REASON

(1) HISTORY

After the introduction of the Nacelle Pressure Regulating Shutoff Valve (NAPRSOV)

PN 1013952-1 in the fleet, some bleed oscillations events during take-off/climb

phases at high engine power thrust have been observed.

Embraer engineering analysis revealed that this NAPRSOV PN 1013952-1 in

conjunction with some other degraded components make the system more susceptible to this kind of oscillations.

Therefore, Embraer and Hamilton Sundstrand developed a new Black Label

software version 13.0 in order to prevent new occurrences of these events.

In addition, this new software version also addresses two Air Cycle Machine (ACM)

failure modes: rotor speed excursions on ground and heat exchanger blockage

during single bleed operation. Both are key contributors of ACM fan and bearing

failures.

(2) OBJECTIVE

This bulletin gives instructions for the Air Management System (AMS) controller

operational program software upgrade, from any of the previous versions to BL-13.0.

(3) EXPECTED BENEFITS

The modification presented in this Service Bulletin is aimed at preventing events of

bleed oscillations in the fleet during take-off/climb phases at high engine power

thrust, as well as to improve Air Cycle Machine (ACM) reliability.

SERVICE BULLETIN

SB No.: 190-21-0041

PAGE: 2

DATE: 27/Sep/2012

REVISION No.: 02 - 30/Jul/2013

Copyright © 2013 by Embraer S.A. All rights reserved.
(4) REVISION HISTORY

REVISION 01: This revision has been issued to include aircraft SN 19000002,

19000004, 19000012, 19000016, 19000027, 19000029, 19000034,

19000038, 19000050, 19000051, 19000053, 19000056 thru

19000063, 19000066, 19000067, 19000069, 19000072, 19000074,

19000076, 19000078 thru 19000081, 19000084, 19000086 thru

19000089, 19000091, 19000093, 19000095, 19000098 thru

19000100, 19000102, 19000104, 19000106, 19000107, 19000110,

19000112 thru 19000114, 19000117, 19000119 thru 19000123,

19000126 thru 19000131, 19000133, 19000135, 19000137 thru

19000139, 19000141, 19000143, 19000145, 19000148, 19000152

thru 19000158, 19000160 thru 19000176, 19000178, 19000180 thru

19000184, 19000186 thru 19000202, 19000204 thru 19000218,

19000220 thru 19000223, 19000226 thru 19000234, 19000238,

19000244 thru 19000246, 19000248, 19000251 thru 19000256,

19000258, 19000259, 19000262 thru 19000270, 19000273 thru

19000277, 19000280, 19000281, 19000283 thru 19000285,

19000287, 19000290, 19000291, 19000293, 19000294, 19000297

thru 19000303, 19000305, 19000306, 19000308 thru 19000314,

19000316, 19000318, 19000320, 19000321, 19000323 thru

19000325, 19000327, 19000328, 19000331 thru 19000333,

19000335, 19000337, 19000340, 19000341, 19000344, 19000348

thru 19000350, 19000352, 19000354, 19000355, 19000357 thru

19000360, 19000365, 19000367 thru 19000369, 19000371 thru

19000373, 19000376, 19000377, 19000379, 19000381, 19000383,

19000385, 19000387, 19000389, 19000390, 19000393 thru

19000395, 19000397 thru 19000406, 19000408 thru 19000412,

19000414 thru 19000418, 19000420, 19000421, 19000423 thru

19000428, 19000431, 19000432, 19000435 thru 19000437,

19000439 thru 19000442, 19000444, 19000445, 19000447,

19000448, 19000450 thru 19000452, 19000454 thru 19000457,

19000459 thru 19000466, 19000468 thru 19000470, (Continued),

SERVICE BULLETIN

DATE: 27/Sep/2012

REVISION No.:02 - 30/Jul/2013

SB No.: 190-21-0041

PAGE: 3

Copyright © 2013 by Embraer S.A. All rights reserved.
REVISION 01

(Continued):

19000472, 19000474, 19000476 thru 19000483, 19000485 thru

19000489, 19000492 thru 19000497, 19000499 thru 19000503,

19000505 thru 19000509, 19000512, 19000513, 19000515 thru

19000518, 19000520, 19000523 thru 19000525, 19000527,

19000529, 19000531, 19000532, 19000535 thru 19000539,

19000541 thru 19000544, 19000546 thru 19000548, 19000550 thru

19000558, 19000560 thru 19000562, 19000564 thru 19000570,

19000572 thru 19000586, 19000588, 19000590 thru 19000592 in

the SB effectivity, and to include In-production effectivity.

REVISION 02: To update Hamilton Sundstrand bulletin 1001050-21-13 and updated

bulletin text accordingly.

D. DESCRIPTION

This Service Bulletin presents Hamilton Sundstrand SB 1001050-21-13, dated July,

01/2013, which provides instructions for replacing the Hamilton Sundstrand AMS

Controller Operational Program of the AMS controller processor boards with a new

improved one.

To do the modification described above, the operator has three alternatives, as follows:

SERVICE BULLETIN

SB No.: 190-21-0041

PAGE: 4

DATE: 27/Sep/2012

REVISION No.: 02 - 30/Jul/2013

Copyright © 2013 by Embraer S.A. All rights reserved.
(1) The AMS controller processor boards can be programmed on-wing as a line

maintenance activity by referring to the Aircraft Maintenance Manual procedures or

to the paragraph 3.C.(2).(c) Accomplishment Instructions of Hamilton Sundstrand

SB 1001050-21-13, attached to Section 4. APPENDIX 1 of this bulletin. For this,

operators may optionally call for Hamilton Sundstrand (HS) trained personnel to

assist the on-wing modification. For this, contact a local Hamilton Sundstrand

technical representative, or

(2) The AMS controller processor boards can be programmed off-wing, referring to the

Aircraft Maintenance Manual procedures or to the paragraph 3.C.(2).(a)

Accomplishment Instructions of Hamilton Sundstrand SB 1001050-21-13, attached

to Section 4. APPENDIX 1 of this bulletin. For this, operators may optionally call for

Hamilton Sundstrand (HS) trained personnel to assist the off-wing modification. For

this, contact a local Hamilton Sundstrand technical representative, or

(3) The AMS processor boards can be removed from the Secondary Power Distribution

Assembly (SPDA) 2 and returned to a Hamilton Sundstrand approved component

repair station and programmed by referring to the Component Maintenance Manual

procedures.

For all the above-mentioned alternatives, it is necessary to gain access to the middle

avionics compartment by opening access doors 195BL and 147AL.

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

Structure (FCS).

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: Agência Nacional de

Aviação Civil (ANAC).

NOTE: If any aircraft listed in the SB effectivity has a modification or repair

incorporated that is not of EMBRAER origin, and which affects the content

of this Service Bulletin, the operator will take full responsibility for obtaining

approval by a regulatory agency for any adaptation necessary before

incorporation of this Service Bulletin.

SERVICE BULLETIN

DATE: 27/Sep/2012

REVISION No.:02 - 30/Jul/2013

SB No.: 190-21-0041

PAGE: 5

Copyright © 2013 by Embraer S.A. All rights reserved.
G. ESTIMATED MANPOWER

This is an estimate of the manpower necessary to accomplish this Service Bulletin on a

single aircraft.

It is intended for direct labor only, performed by experienced personnel, and does not

include the time to plan, prepare, or inspect the work. Sealant, paint, or adhesive curing

times are not included.

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

necessary.

An adjustment to these values may be necessary to meet particular circumstances.

(1) Applicable to On-wing upgrade.

– Access opening: 0.15 man-hours.

– Inspection: None.

– Modification: 0.5 man-hours.

– Access closure: 0.15 man-hours.

– Test: 0.3 man-hours.

(2) Applicable to Off-wing upgrade.

– Access opening: 0.15 man-hours.

– Inspection: None.

– Modification: 0.7 man-hours.

– Access closure: 0.15 man-hours.

– Test: 0.3 man-hours.

SERVICE BULLETIN

SB No.: 190-21-0041

PAGE: 6

DATE: 27/Sep/2012

REVISION No.: 02 - 30/Jul/2013

Copyright © 2013 by Embraer S.A. All rights reserved.
(3) Applicable to AMS controller processor boards replacement.

– Access opening: 0.15 man-hours.

– Inspection: None.

– Modification: 0.3 man-hours.

– Access closure: 0.15 man-hours.

– Test: 0.3 man-hours.

H. WEIGHT AND BALANCE

None.

I. SOFTWARE ACCOMPLISHMENT SUMMARY

Refer to paragraph 1.J. Software Accomplishment Summary of Hamilton Sundstrand SB

1001050-21-13, attached to Section 4. APPENDIX 1 of this bulletin.

J. REFERENCES

AMM 190/( ) Aircraft Maintenance Manual PART II - 20-00-00 - STANDARD

PRACTICES-AIRFRAME.

AMM 190/( ) Aircraft Maintenance Manual PART II - 21-00-00 and 21-00-01 -

AIR CONDITIONING.

Hamilton

Sundstrand

SB 1001050-21-13 - AIR CONDITIONING – AIR MANAGEMENT

SYSTEMS CONTROLLER PROCESSOR BOARD -

INCORPORATION OF NEW OPS SOFTWARE (BLACK LABEL

13.0).

K. OTHER PUBLICATIONS AFFECTED

AIPC 190/( ) Aircraft Illustrated Parts Catalog - 21-00-01 - AIR CONDITIONING.

SERVICE BULLETIN

DATE: 27/Sep/2012

REVISION No.:02 - 30/Jul/2013

SB No.: 190-21-0041

PAGE: 7

Copyright © 2013 by Embraer S.A. All rights reserved.
2. MATERIAL INFORMATION

A. MATERIAL - PRICE AND AVAILABILITY

(1) MATERIAL AVAILABLE FROM EMBRAER

None.

(2) MATERIAL AVAILABLE FROM OTHER VENDORS

Refer to paragraph 2.C. Material Necessary For Each Unit of Hamilton Sundstrand

SB 1001050-21-13, attached to Section 4. APPENDIX 1 of this bulletin.

B. INDUSTRY SUPPORT INFORMATION

Refer to paragraph 2.B Industry Support Information of Hamilton Sundstrand SB

1001050-21-13, attached to Section 4. APPENDIX 1 of this bulletin.

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.

(1) TOP KITS AND KITS

None.

(2) MATERIAL TO BE PROCURED

(a) Parts

SERVICE BULLETIN

SB No.: 190-21-0041

PAGE: 8

DATE: 27/Sep/2012

REVISION No.: 02 - 30/Jul/2013

Copyright © 2013 by Embraer S.A. All rights reserved.
None.

(b) Consumable Materials

None.

D. MATERIAL NECESSARY FOR EACH SPARE

Refer to paragraph 2.C. Material Necessary For Each Unit of Hamilton Sundstrand SB

1001050-21-13, attached to Section 4. APPENDIX 1 of this bulletin.

E. REIDENTIFIED PARTS

Refer to paragraph 2.E. Reidentified Parts of Hamilton Sundstrand SB 1001050-21-13,

attached to Section 4. APPENDIX 1 of this bulletin.

F. TOOLING - PRICE AND AVAILABILITY

Refer to paragraph 2.F. Tooling - Price and Availability of Hamilton Sundstrand SB

1001050-21-13, attached to Section 4. APPENDIX 1 of this bulletin.

SERVICE BULLETIN

DATE: 27/Sep/2012

REVISION No.:02 - 30/Jul/2013

SB No.: 190-21-0041

PAGE: 9

Copyright © 2013 by Embraer S.A. All rights reserved.
3. ACCOMPLISHMENT INSTRUCTIONS

NOTE: 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 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.

WARNING : MAKE SURE THAT THE AIRCRAFT IS IN A SAFE CONDITION BEFORE

YOU DO THE MAINTENANCE PROCEDURES. THIS IS TO PREVENT

INJURY TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT.

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. Applicable to on-wing AMS controller processor board upgrade:

(1) Upload new BL-13.0 software PN Y1001399-013, available on compact disk PN

1002256-130, to both of the AMS processor boards installed on the aircraft. Refer to

AMM TASK 21-00-00-470-801-A/200 - AMS-Controller - Field-Loadable Software

Upload (On Wing) or refer to paragraph 3.C.(2).(c) Accomplishment Instructions of

Hamilton Sundstrand SB 1001050-21-13, attached to Section 4. APPENDIX 1 of this

bulletin.

(2) Reidentify the boards with a new tag bearing appropriate PNs 1001050-1-015 or

1001050-2-015 or 1001050-3-015 or 1001050-4-015 or 1001050-5-015 or 1001050

-6-015 or 1001050-7-015. Refer to Figure 6 and paragraph 2.E. Reidentified Parts of

Hamilton Sundstrand SB 1001050-21-13, herein attached to Section 4. APPENDIX

1.

C. Applicable to off-wing AMS controller processor board upgrade.

(1) Upload new BL-13.0 software PN Y1001399-013, available on compact disk PN

1002256-130, to both of the AMS processor boards installed on the aircraft. Refer to

AMM TASK 21-00-00-470-802-A/200 - AMS-Controller - Field-Loadable Software

SERVICE BULLETIN

SB No.: 190-21-0041

PAGE: 10

DATE: 27/Sep/2012

REVISION No.: 02 - 30/Jul/2013

Copyright © 2013 by Embraer S.A. All rights reserved.
Upload (Off Wing) or refer to paragraph 3.C.(2).(a) Accomplishment Instructions of

Hamilton Sundstrand SB 1001050-21-13, attached to Section 4. APPENDIX 1 of this

bulletin.

(2) Reidentify the boards with a new tag bearing appropriate PNs 1001050-1-015 or

1001050-2-015 or 1001050-3-015 or 1001050-4-015 or 1001050-5-015 or 1001050

-6-015 or 1001050-7-015. Refer to Figure 6 and paragraph 2.E. Reidentified Parts of

Hamilton Sundstrand SB 1001050-21-13, herein attached to Section 4. APPENDIX

1.

D. Applicable to AMS controller processor board upgrade at a repair station:

(1) Replace both existing AMS controller processor boards PNs 1001050-1-YYY, or

1001050-2-YYY, or 1001050-3-YYY, or 1001050-4-YYY with new PN 1001050-1

-015 or 1001050-2-015 or 1001050-3-015 or 1001050-4-015 or 1001050-5-015 or

1001050-6-015 or 1001050-7-015, with BL-13.0 already uploaded. Refer to AMM

TASK 21-00-01-000-801-A/400 - AMS Controller Processor Modules - Removal and

AMM TASK 21-00-01-400-801-A/400 - AMS Controller Processor Modules - Installation.

NOTE: Send the removed AMS controller processor boards to an authorized

Hamilton Sundstrand repair facility to be upgraded. For this, refer to

paragraph 2.B. Industry Support Information of this bulletin.

E. Perform the Air Management System (AMS) controller power-up BIT, if it has not been

done yet, during the AMM job close-up tasks. Refer to AMM TASK 21-00-00-740-801

-A/500 - AMS Controller - Power-up BIT.

F. Restore the aircraft to the normal condition.

G. Enter the accomplishment 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: 27/Sep/2012

REVISION No.:02 - 30/Jul/2013

SB No.: 190-21-0041

PAGE: 11

Copyright © 2013 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 to help us improve the quality of the SBs.

SERVICE BULLETIN

SB No.: 190-21-0041

PAGE: 12

DATE: 27/Sep/2012

REVISION No.: 02 - 30/Jul/2013

Copyright © 2013 by Embraer S.A. All rights reserved.
4. APPENDIX 1

HAMILTON SUNDSTRAND SB 1001050-21-13 - AIR MANAGEMENT SYSTEMS CONTROLLER PROCESSOR BOARD - INCORPORATION OF NEW OPS SOFTWARE (BLACK

LABEL 13.0)

SERVICE BULLETIN

DATE: 27/Sep/2012

REVISION No.:02 - 30/Jul/2013

SB No.: 190-21-0041

PAGE: 13

Copyright © 2013 by Embraer S.A. All rights reserved.
Original Issue Date: Aug 31/12

Revision 1: Jul 1/13

1001050-21-13

Page 1 of 31

SERVICE BULLETIN

Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

AIR CONDITIONING - AIR MANAGEMENT SYSTEMS CONTROLLER PROCESSOR BOARD - 

INCORPORATION OF NEW OPS SOFTWARE (BLACK LABEL 13.0)

© 2013 Hamilton Sundstrand Corporation

PROPRIETARY

THIS DOCUMENT IS THE PROPERTY OF UTC AEROSPACE SYSTEMS. YOU MAY NOT POSSESS, USE, COPY OR DISCLOSE THIS 

DOCUMENT OR ANY INFORMATION IN IT, FOR ANY PURPOSE, INCLUDING WITHOUT LIMITATION, TO DESIGN, MANUFACTURE 

OR REPAIR PARTS, OR OBTAIN ANY GOVERNMENT APPROVAL TO DO SO, WITHOUT UTC AEROSPACE SYSTEM’S EXPRESS 

WRITTEN PERMISSION. NEITHER RECEIPT NOR POSSESSION OF THIS DOCUMENT ALONE, FROM ANY SOURCE, 

CONSTITUTES SUCH PERMISSION. POSSESSION, USE, COPYING OR DISCLOSURE BY ANYONE WITHOUT UTC AEROSPACE 

SYSTEM’S EXPRESS WRITTEN PERMISSION IS NOT AUTHORIZED AND MAY RESULT IN CRIMINAL AND/OR CIVIL LIABILITY. 

INFORMATION SUBJECT TO EXPORT CONTROL LAWS

Subject to the EAR, ECCN 9E991

This information is subject to the export control laws of the United States, specifically including the Export Administration Regulations (EAR), 

15 C.F.R. Part 730 et. seq. Transfer, retransfer, or disclosure of this data by any means to a non-U.S. person (individual or company), 

whether in the United States or abroad, without any required export license or other approval from the U.S Government is prohibited, 

including without limitation any diversion to a military end user or use in a military end use application. 

THE DATA IN THIS DOCUMENT WERE DEVELOPED ONLY TO MAINTAIN SYSTEMS AND/OR PARTS MANUFACTURED BY OR FOR 

HAMILTON SUNDSTRAND OR APPROVED BY HAMILTON SUNDSTRAND. THE DATA MAY NOT BE APPLICABLE TO ANY OTHER 

SYSTEMS AND/OR PARTS, REGARDLESS OF THEIR APPARENT SIMILARITY TO SYSTEMS AND/OR PARTS MANUFACTURED BY 

OR FOR HAMILTON SUNDSTRAND OR APPROVED BY HAMILTON SUNDSTRAND. DO NOT RELY IN ANY WAY ON DATA IN THIS 

DOCUMENT TO MAINTAIN OR OTHERWISE SUPPORT SYSTEMS AND/OR PARTS THAT WERE NOT MANUFACTURED BY OR FOR 

HAMILTON SUNDSTRAND OR APPROVED BY HAMILTON SUNDSTRAND WITHOUT EVIDENCE THAT THE FEDERAL AVIATION 

ADMINISTRATION OR OTHER REGULATORY AGENCY HAS DETERMINED THAT THE DATA IN THIS DOCUMENT IS VALID FOR 

SUCH USE.

HAMILTON SUNDSTRAND ASSUMES NO LIABILITY WHATSOEVER, WHETHER CONTRACTUAL, WARRANTY, TORT OR 

OTHERWISE, FOR UNAUTHORIZED ALTERATION OR ALTERATIONS NOT PERFORMED IN ACCORDANCE WITH HAMILTON 

SUNDSTRAND APPROVED PROCEDURES.

REVISIONS

Revision 1

This revision updated the Service Bulletin to the latest template standards, expands the part number 

effectivity and adds the additional parts to Table 2.

Units previously modified according to this bulletin do not require remodification according to this 

bulletin revision.

This bulletin has been reproduced in its entirety. Discard the bulletin you now have and replace it with 

this copy. The tabulation below is provided for record keeping and traceability of bulletin issues. 

Issue Date

Basic Aug 31/12

Revision 1 Jul 1/13

SERVICE BULLETIN

SB No.: 190-21-0041

PAGE: 14

DATE: 27/Sep/2012

REVISION No.: 02 - 30/Jul/2013

Copyright © 2013 by Embraer S.A. All rights reserved.
Original Issue Date: Aug 31/12

Revision 1: Jul 1/13

1001050-21-13

Page 2

SERVICE BULLETIN

Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

1. PLANNING INFORMATION

A. Effectivity

(1) For the upgrade of AMS software installed on EMB170/190 aircraft to black label 13.0

All AMS controller processor boards Identified as Hamilton Sundstrand Part Numbers 

1001050-1-YYY, 1001050-2-YYY, 1001050-3-YYY, 1001050-4-YYY, 1001050-5-YYY, 

1001050-6-YYY, 1001050-7-YYY. Where YYY identifies any prior software 

configuration

NOTE: The AMS controller black label 13.0 software version introduced by this 

service bulletin contains all software improvements contained in the previous 

AMS controller software versions.

B. Concurrent Requirements

(1) None

C. Reason

(1) The software configuration introduced by this Service Bulletin was generated to 

incorporate AMS controller software improvements. The following software 

improvements will be incorporated when upgrading to AMS software change black 

label 13.0

(a) Pneumatic bleed system control and built in test improvements:

1 Revised engine bleed system control logic to quickly detect manifold 

pressure oscillations and respond by implementing an override command to 

the bleed valve (open loop logic) to stabilize manifold pressure. (Applicable 

to EMB190/195 only).

2 Revised engine bleed system control logic to de-activate the engine bleed 

system and open the cross bleed valve if the corresponding air conditioning 

pack is on MEL (de-activated). This change will reduce manifold pressure 

oscillations on the side where no bleed flow is being utilized.

3 Revised BLEED OFF EICAS setting logic so the message is only displayed 

during failure / abnormal operating conditions or when the system is 

shutdown by the pilot.

4 Revised HPSOV failed closed fault logic to require a higher pressure drop 

across the HPSOV before the fault is set. This improvement will help to 

eliminate spurious HPSOV failed closed faults.

(b) Air conditioning system control and built in test improvements:

1 Revised ventilation control logic to reduce the pack flow reference on the 

ground during engine idle conditions. These changes are implemented to 

prevent an ACM over-speed condition which can result from the flow control 

valves being commanded full open during taxi/takeoff. 

SERVICE BULLETIN

DATE: 27/Sep/2012

REVISION No.:02 - 30/Jul/2013

SB No.: 190-21-0041

PAGE: 15

Copyright © 2013 by Embraer S.A. All rights reserved.
Original Issue Date: Aug 31/12

Revision 1: Jul 1/13

1001050-21-13

Page 3

SERVICE BULLETIN

Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

2 Revised ventilation control logic to reduce the pack flow reference after pack 

startup in icing conditions. This change is implemented to reduce ACM 

speed while melting possible ice buildup on the ram heat exchanger surface 

which could lead to ACM failure.

3 Revised ACM fault logic to prevent the ACM fault from setting when the AddHeat valve is failed

D. Description

(1) This Service Bulletin provides procedures to change Hamilton Sundstrand AMS 

Controller Operational Program Software to part number Y1001399-013 configuration.

E. Compliance

(1) It is recommended that this Service Bulletin be accomplished at the earliest opportunity 

or as directed by the associated Embraer Service Bulletin and/or applicable 

airworthiness directives.

F. Approval

(1) Embraer engineering board has reviewed and agreed with the contents of this Service 

Bulletin. 

G. Manpower

(1) Approximately 0.5 hour is required to install the new software in each AMS controller 

processor board. Each airplane has two AMS controller processor boards.

H. Weight and Balance

(1) Not affected

I. Electrical Load Data

(1) Not Applicable

SERVICE BULLETIN

SB No.: 190-21-0041

PAGE: 16

DATE: 27/Sep/2012

REVISION No.: 02 - 30/Jul/2013

Copyright © 2013 by Embraer S.A. All rights reserved.
Original Issue Date: Aug 31/12

Revision 1: Jul 1/13

1001050-21-13

Page 4

SERVICE BULLETIN

Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

J. Software Accomplishment Summary

(1) The AMS Controller Software Configuration Matrix in Table 1 provides information that 

can be used to verify that the AMS controller software and loading media are the 

correct configuration as defined by this Service Bulletin Table 1

K. References

(1) Hamilton Sundstrand Component Maintenance Manual (CMM) 21-00-05

(2) Hamilton Sundstrand Engineering Change Number 11E659

L. Other Publications Affected

(1) Hamilton Sundstrand CMM 21-00-05 will be revised to incorporate this bulletin.

M. Interchangeability or Intermixability of Parts

(1) Not applicable

2. MATERIAL INFORMATION

A. Material - Price and Availability

(1) The parts that are necessary to do this Service Bulletin procedure are shown in Table 

2, Parts Information.

(2) Hamilton Sundstrand will provide the parts required for the accomplishment of this 

Service Bulletin at no charge. To obtain such material, the operator should direct a “no 

charge” purchase order for the total quantity of parts to:

Hamilton Sundstrand Corporation

A United Technologies Company

Attention: Manager Commercial Spares Administration

Mail Stop: 236-6

P.O. Box 7002

4747 Harrison Avenue

Rockford, IL 61125-7002

USA

Table 1

AMS Controller Software Configuration Matrix

Software Block 

Number

OPS Software PN OPS Software 

CRC Number

Compact Disk

Black Label 13.0

Hamilton Sundstrand PN Flight Executable 

Program CRC 

Number

Hamilton 

Sundstrand PN

Y1001399-013 3941 6245 1002256-130

SERVICE BULLETIN

DATE: 27/Sep/2012

REVISION No.:02 - 30/Jul/2013

SB No.: 190-21-0041

PAGE: 17

Copyright © 2013 by Embraer S.A. All rights reserved.
Original Issue Date: Aug 31/12

Revision 1: Jul 1/13

1001050-21-13

Page 5

SERVICE BULLETIN

Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

B. Industry Support Information

(1) Hamilton Sundstrand will modify spare processor boards, as defined in this Service 

Bulletin, at no charge to the operator. Spare processor boards must be sent to one of 

the following Hamilton Sundstrand approved repair facilities for this modification.

Hamilton Sundstrand 

Windsor Locks Repair Station

One Hamilton Road

Dock W

Windsor Locks, CT 06096

USA

or 

Hamilton Sundstrand

Customer Support Center - Maastricht

Horsterweg 7

6199 AC Maastricht Airport

The Netherlands

C. Material Necessary For Each Unit

(1) Refer to Hamilton Sundstrand CMM 21-00-05 for expendable parts information.

(2) Material to be Purchased

(a) This Service Bulletin change will use parts in the list for each AMS Controller 

Processor Board that is changed.

(b) Any parts that usually are discarded when you disassemble the AMS Controller 

Processor Board are not in the list. 

(c) In the list of parts for this change, the “Keyword” is the name of the part.

(d) In the list of parts for this change, the “instruction codes” tell you what to do with 

the parts. A short list under the list of parts tells you about the instruction codes 

that are used in the list.

SERVICE BULLETIN

SB No.: 190-21-0041

PAGE: 18

DATE: 27/Sep/2012

REVISION No.: 02 - 30/Jul/2013

Copyright © 2013 by Embraer S.A. All rights reserved.
Original Issue Date: Aug 31/12

Revision 1: Jul 1/13

1001050-21-13

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SERVICE BULLETIN

Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

(e) The prices that are shown are estimates for one part. When you buy the parts, the 

prices may be different. Send requests for parts to:

Hamilton Sundstrand Corporation

A United Technologies Company

Attention: Manager Commercial Spares Administration

Mail Stop: 236-6

P.O. Box 7002

4747 Harrison Avenue

Rockford, IL 61125-7002

USA

Facsimile: (815) 226-2624

(f) Refer to Table 2 for parts to be purchased.

SERVICE BULLETIN

DATE: 27/Sep/2012

REVISION No.:02 - 30/Jul/2013

SB No.: 190-21-0041

PAGE: 19

Copyright © 2013 by Embraer S.A. All rights reserved.
Original Issue Date: Aug 31/12

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1001050-21-13

Page 7

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Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

Table 2

Table 2 Note 1: Compact Disk PN 1002256-130 is used to reprogram the Air Management 

System controller processor board while it is installed in the aircraft. The AMS 

controller processor board can also be programmed as a shop maintenance 

procedure in accordance with the applicable component maintenance manual 

instructions.

Table 2 Note 2: Identification label 1006401-1-015 is used to re-identify AMS controller processor 

boards PN 1001050-1-YYY that were modified on wing. 

Table 2 Note 3: Identification label 1006401-2-015 is used to re-identify AMS controller processor 

boards PN 1001050-2-YYY that were modified on wing. 

Table 2 Note 4: Identification label 1006401-3-015 is used to re-identify AMS controller processor 

boards PN 1001050-3-YYY that were modified on wing. 

Table 2 Note 5: Identification label 1006401-4-015 is used to re-identify AMS controller processor 

boards PN 1001050-4-YYY that were modified on wing. 

Table 2

Parts Information

New Part 

Number Keyword

Old Part 

Number Qty

Unit Price

Special 

Instructions/

Disposition

1002256-130 Compact Disk 1002256-120 1 $30.00 Note 1

1006401-1-015 Identification 

Label

1006401-1-014 1 $5.00 Note 2

1006401-2-015 Identification 

Label

1006401-2-014 1 $5.00 Note 3

1006401-3-015 Identification 

Label

1006401-3-014 1 $5.00 Note 4

1006401-4-015 Identification 

Label

1006401-4-014 1 $5.00 Note 5

1006401-5-015 Identification 

Label

1006401-5-014 1 $5.00 Note 6

1006401-6-015 Identification 

Label

1006401-6-014 1 $5.00 Note 7

1006401-7-015 Identification 

Label

1006401-7-014 1 $5.00 Note 8

1002123-1 Identification 

Plate

1002123-1 1 $5.00 Note 9

SERVICE BULLETIN

SB No.: 190-21-0041

PAGE: 20

DATE: 27/Sep/2012

REVISION No.: 02 - 30/Jul/2013

Copyright © 2013 by Embraer S.A. All rights reserved.
Original Issue Date: Aug 31/12

Revision 1: Jul 1/13

1001050-21-13

Page 8

SERVICE BULLETIN

Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

Table 2 Note 6: Identification label 1006401-5-015 is used to re-identify AMS controller processor 

boards PN 1001050-5-YYY that were modified on wing. 

Table 2 Note 7: Identification label 1006401-6-015 is used to re-identify AMS controller processor 

boards PN 1001050-6-YYY that were modified on wing.

Table 2 Note 8: Identification label 1006401-7-015 is used to re-identify AMS controller processor 

boards PN 1001050-7-YYY that were modified on wing.

Table 2 Note 9: Identification plate 1002123-1 is used to re-identify AMS controller processor 

boards that were modified as a shop maintenance activity.

(3) Material Supplied by the Operator

(a) None

D. Material Necessary For Each Spare

(1) The same as the material necessary for each unit.

E. Reidentified Parts

(1) AMS controller processor boards that incorporate the modification described in this 

Service Bulletin must be re-identified in accordance with Table 3 shown below. Table 3

(2) Refer to paragraph 3.F. for re-identification instructions.

Table 3

Reidentified Parts 

Old Processor Board 

Part Number

New Processor Board 

Part Number

1001050-1-YYY 1001050-1-015

1001050-2-YYY 1001050-2-015

1001050-3-YYY 1001050-3-015

1001050-4-YYY 1001050-4-015

1001050-5-YYY 1001050-5-015

1001050-6-YYY 1001050-6-015

1001050-7-YYY 1001050-7-015

SERVICE BULLETIN

DATE: 27/Sep/2012

REVISION No.:02 - 30/Jul/2013

SB No.: 190-21-0041

PAGE: 21

Copyright © 2013 by Embraer S.A. All rights reserved.
Original Issue Date: Aug 31/12

Revision 1: Jul 1/13

1001050-21-13

Page 9

SERVICE BULLETIN

Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

F. Tooling - Price and Availability

(1) Tools shown in Table 4 are used when performing the alternate software loading 

procedures defined in paragraph 3.C. Operators should contact their local Hamilton 

Sundstrand field service representative for tooling availability. Table 4

Table 4 Note 1: CD-ROM AGE16738 is used to program the loading software for the laptop 

AGE16732. This is considered GSE Equipment and is not flight software.

3. ACCOMPLISHMENT INSTRUCTIONS

A. General

(1) The facility performing the work (user) should obtain the material safety data sheets 

[Occupational Safety and Health Act (OSHA) Form 20 or equivalent] from the 

manufacturers or suppliers of materials to be used. The user must become completely 

familiar with the manufacturer/supplier information and adhere to the procedures, 

recommendations, warnings, and cautions of the manufacturer/supplier for the safe 

use, handling, storage, and disposal of these materials. The user should also read the 

long version of the warnings contained in this bulletin. The long version warnings are 

contained in Hamilton Sundstrand Warnings Registry 341-006 available free of charge 

to all organizations that are on distribution for this bulletin. The Warnings Registry 341-

006 is also available at myhs.hamiltonsundstrand.com.

(2) A unit modified according to this service bulletin might be returned to the shop for 

maintenance or repair before the new or modified part numbers or procedures in this 

bulletin are incorporated into the applicable CMM.

Until this service bulletin is incorporated into the CMM, operators are allowed to 

disassemble, clean, check, repair, assemble, and test the unit according to the 

applicable CMM, using the new or modified part numbers or procedures in this bulletin.

After this service bulletin is incorporated into the CMM, the CMM procedures will 

supersede this bulletin.

Table 4

GSE Equipment 

Old Part Number Keyword

AGE14573 Off Wing Load Chassis and Power Supply

AGE16695 Switch Box and Connector Cable

AGE16732 Laptop with Extension and USB cables

AGE16738 CD-ROM - Loading Program (See Note 1 

below)

SERVICE BULLETIN

SB No.: 190-21-0041

PAGE: 22

DATE: 27/Sep/2012

REVISION No.: 02 - 30/Jul/2013

Copyright © 2013 by Embraer S.A. All rights reserved.
Original Issue Date: Aug 31/12

Revision 1: Jul 1/13

1001050-21-13

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Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

B. Disassembly 

(1) Not applicable

C. Modification

(1) To perform this modification while the AMS controller processor boards are installed on 

the aircraft, refer to the Embraer Service Bulletin, which provides instructions for 

standard on-wing loading of the AMS controller operational program software identified 

by Hamilton Sundstrand part number Y1001399-013.

(2) The modification procedures in this Service Bulletin may also be performed using 

alternate software loading procedures, which are defined in this Service Bulletin. The 

alternate loading procedures in this service bulletin include procedures for loading the 

AMS Processor cards “off wing” (using a GSE holding fixture) and loading the AMS 

processor cards “on wing”. Instructions for performing these loading procedures are as 

follows:

(a) Procedure for off-wing loading of AMS Controller Processor board software. 

Refer to Figure 1.

WARNING: MAKE SURE THAT THE AIRCRAFT IS IN A SAFE CONDITION BEFORE 

YOU DO THE MAINTENANCE PROCEDURES. THIS IS TO PREVENT 

INJURY TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT.

1 Do the procedure to make the aircraft safe for maintenance (AMM TASK 20-

00-00-910-801-A/200). 

2 Select the applicable cables, interface devices, power supply, and laptop of 

AGE16695, AGE14573 and AGE16732 related to the AMS controller 

software-loading application.

3 Remove the AMS Controller Processor Modules (slots 18 and 25) from the 

aircraft (AMM TASK 21- 00-01-000-801-A/400), as applicable.

CAUTION: THE MODULE OR UNIT CONTAINS ELECTROSTATIC 

DISCHARGE SENSITIVE (ESDS) ITEMS. OBEY THE APPROVED 

INDUSTRY PRECAUTIONS WHEN YOU TOUCH, REMOVE, OR 

INSERT PARTS OR ASSEMBLIES. DAMAGE CAN OCCUR FROM 

ELECTROSTATIC DISCHARGE. 

4 Obey all the electrostatic discharge safety precautions (AMM TASK 20-40-

00-910-801-A/200).

5 Connect the DC power supply (12) to the card chassis AGE14573 (1) and 

install its ground strap. Refer to .

6 Install the AMS Controller Processor Modules (slots 18 and 25) on the card 

chassis AGE14573 (1) as follows:

SERVICE BULLETIN

DATE: 27/Sep/2012

REVISION No.:02 - 30/Jul/2013

SB No.: 190-21-0041

PAGE: 23

Copyright © 2013 by Embraer S.A. All rights reserved.
Original Issue Date: Aug 31/12

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Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

CAUTION: DO NOT TOUCH THE ELECTRICAL PINS OF THE 

CONNECTORS. DAMAGE CAN OCCUR TO THE INTERNAL ESDS 

COMPONENTS.

CAUTION: DO NOT USE TOO MUCH FORCE WHEN YOU INSTALL THE 

MODULE OR UNIT. TOO MUCH FORCE CAN CAUSE DAMAGE 

TO THE CONNECTOR PINS.

a Align the top and bottom edges of the AMS Controller Processor 

Module between the pairs of edge guides in the applicable slot of the 

card chassis AGE14573 (1). Refer to Figure 1. 

b Push in the top and bottom part of the module front plate with a light, 

equally distributed force, parallel to the edge guides. Stop when the rear 

electrical connectors engage and the wedge locks are locked into 

position on the card chassis AGE14573 (1). Refer to Figure 1. 

NOTE: The edge guides can cause some friction during the module 

installation.

7 Turn on the DC power supply (12). Refer to Figure 1.

8 On the card chassis AGE14573 (1), set the +5, -15 and +15 switches to the 

ON position. Refer to Figure 1. 

Result:

(1) On the card chassis AGE14573 (1), the correspondent LEDs will come 

on.

(2) On the Switch Box AGE16711 (8), both LEDs, DS1 (Channel A) and 

DS11 (Channel B) will come ON. 

9 To start and run the AMS controller software-loading application, do as 

follows: 

Verify the required AMS controller software-loading application by starting 

the laptop (14) and selecting OPERATOR. Verify that HSC Load and Flight 

PN shortcuts are on the desktop or executables are in the 

“C:\Windows\Program Files\HSCLoad” directory. If the files are not found in 

the directory specified, they can be installed from the CD-ROM AGE16738. 

NOTE: Operators should contact Hamilton Sundstrand’s local field service 

representative for all GSE equipment setup or software upload 

inquiries.

10 Set up the connections to the AMS Controller Modules as follows:

a Use a standard USB cable (13) from any open USB port on the laptop 

(14) and the opposite end to Channel A (9) with extension cable (11). 

b Attach connector P1 (7) of the cable AGE16712 (6) to connector P1 on 

the Switch Box AGE16711 (8).

SERVICE BULLETIN

SB No.: 190-21-0041

PAGE: 24

DATE: 27/Sep/2012

REVISION No.: 02 - 30/Jul/2013

Copyright © 2013 by Embraer S.A. All rights reserved.
Original Issue Date: Aug 31/12

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Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

c Connect connector P18 (5) of cable AGE16712 (6) to the AMS 

Controller Module 18 - channel A (channel 1) (2) in card chassis 

AGE14573 (1).

d Connect connector P25 (4) of cable AGE16712 (6) to the AMS 

Controller Module 25 - channel B (channel 2) (3) in card chassis 

AGE14573 (1).

11 To load the software to the AMS Controller Channel A (Channel 1), do as 

follows:

a On the Switch Box AGE16711 (8), do the following: 

• Set S1 switch (CHANNEL A - BITE) to the GND position.

• Set S2 switch (CHANNEL A - BOOT) to the GND position.

• Set S3 switch (CHANNEL A) to the GND position and release it (while 

the S3 switch is set to GND, the LED SD1 momentarily goes OFF). 

Result: 

(1) S3 switch moves back to the previous position. 

b On the laptop, start the HSCLoad.exe application either from the 

shortcut link on the desktop or in the “C:\Windows\Program 

Files\HSCLoad directory”.

Result: 

(1) The SOFTWARE UPLOAD MAIN SCREEN, Figure 2, comes into 

view on the laptop. 

(2) The Property of Hamilton Sundstrand screen comes into view. 

Select OK. 

c Click on the CONFIGURE PORT button. 

Result: 

(1) The CONFIGURE PORT SELECTION SCREEN, Figure 3, comes 

into view on the laptop. 

d On the CONFIGURE PORT SELECTION SCREEN, Figure 3, select 

COM PORT 1. Also select 38400 BPS. Then click on the DONE button. 

Result: 

(1) The SOFTWARE UPLOAD MAIN-SCREEN, Figure 2, comes back 

into view on the laptop. 

e Click on the OPEN FILE button. 

Result: 

(1) The OPEN FILE screen comes into view on the laptop.

SERVICE BULLETIN

DATE: 27/Sep/2012

REVISION No.:02 - 30/Jul/2013

SB No.: 190-21-0041

PAGE: 25

Copyright © 2013 by Embraer S.A. All rights reserved.
Original Issue Date: Aug 31/12

Revision 1: Jul 1/13

1001050-21-13

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SERVICE BULLETIN

Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

f Insert current flight software CD as defined by the AMS service bulletin 

you are currently loading (see Table 1).

NOTE: If the OPEN FILE screen does not point to the CD-ROM 

DRIVE, you must select it in the LOOK IN box on the OPEN 

FILE screen.

g The target software part number will show in the FILE NAME window. 

Select the file with the “HSC” extension. Then, click on the OPEN button 

to open the software file. 

Result:

(1) The FILE SEND screen comes into view on the laptop. 

h Click on the SEND button to start the loading process. 

Result: 

(1) The SOFTWARE UPLOAD MAIN SCREEN, Figure 2 comes into 

view on the laptop. The STATUS box shows the load status information. 

If an error occurs during the software upload, repeat step 3.C.(2)(a)11d

selecting COM2 (or COM3 or COM4) instead of COM1. 

(2) When the loading completes, the STATUS BOX in the SOFTWARE 

UPLOAD MAIN SCREEN, Figure 2 shows the LOAD COMPLETE 

message. 

NOTE: The “Open File” button will also enable when complete. The 

LOAD COMPLETE message may scroll off the Status screen 

after a short time. 

i On the SOFTWARE UPLOAD MAIN SCREEN, Figure 2, click on the 

EXIT button. 

Result: 

(1) SOFTWARE UPLOAD MAIN SCREEN, Figure 2, closes. 

j On the Switch Box AGE16711 (8), do as follows: 

• Set S1 switch (CHANNEL A - BITE) to the OFF position. 

• Set S2 switch (CHANNEL A - BOOT) to the OFF position. 

• Set S3 switch (CHANNEL A) to the GND position and release it (while 

the S3 switch is set to GND, the LED SD1 momentarily goes OFF). 

Result: 

(1) S3 switch moves back to the previous position. 

SERVICE BULLETIN

SB No.: 190-21-0041

PAGE: 26

DATE: 27/Sep/2012

REVISION No.: 02 - 30/Jul/2013

Copyright © 2013 by Embraer S.A. All rights reserved.
Original Issue Date: Aug 31/12

Revision 1: Jul 1/13

1001050-21-13

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SERVICE BULLETIN

Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

k On the laptop, start the FlightPN application either from the link on the 

desktop or from the “C:\Windows\ProgramFiles\HSCLoad directory”. 

Result: 

(1) The FLIGHT SOFTWARE INFORMATION SCREEN, Figure 4, 

comes into view. 

l On the FLIGHT SOFTWARE INFORMATION SCREEN, Figure 4, click 

on the “Get Software Information” button. 

Result: 

(1) After a short delay, the FLIGHT SOFTWARE INFORMATION 

SCREEN, Figure 4, comes back into view with this information:

• FLIGHT SOFTWARE PART NUMBER

• FLIGHT SOFTWARE CRC 

• SYSTEM DATE AND TIME 

m Verify that the part number and the CRC information are correct. Refer 

to Table 1 in this Service Bulletin for the correct CRC and part number 

information. 

n On the FLIGHT SOFTWARE INFORMATION SCREEN, Figure 4, click 

on the “Exit” button. 

Result:

(1) FLIGHT SOFTWARE INFORMATION SCREEN, Figure 4, closes. 

(2) The AMS Controller Channel A (Channel 1) software load is 

complete. 

12 Set up the connections to the AMS Controller Modules as follows: 

a Disconnect the USB cable (13) from Channel A (9) on the Switch Box 

AGE16711 (8) and connect the USB cable (13) to Channel B (10) on the 

Switch Box AGE16711 (8).

13 To load the software to the AMS Controller Channel B (Channel 2), do as 

follows: 

a On the Switch Box AGE16711 (8), do the following: 

• Set S11 switch (CHANNEL B - BITE) to the GND position. 

• Set S12 switch (CHANNEL B - BOOT) to the GND position. 

• Set S13 switch (CHANNEL B) to the GND position and release it 

(while the S13 switch is set to GND, the LED SD11 momentarily goes 

OFF). 

Result: 

(1) S13 switch moves back to the previous position.

SERVICE BULLETIN

DATE: 27/Sep/2012

REVISION No.:02 - 30/Jul/2013

SB No.: 190-21-0041

PAGE: 27

Copyright © 2013 by Embraer S.A. All rights reserved.
Original Issue Date: Aug 31/12

Revision 1: Jul 1/13

1001050-21-13

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SERVICE BULLETIN

Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

b On the laptop, start the HSCLoad.exe application either from the 

shortcut link on the desktop or in the “C:\Windows\Program 

Files\HSCLoad directory”.

Result: 

(1) The SOFTWARE UPLOAD MAIN SCREEN, Figure 2, comes into 

view on the laptop. 

(2) The Property of Hamilton Sundstrand screen comes into view. 

Select OK.

c Click on the CONFIGURE PORT button.

Result:

(1) The CONFIGURE PORT SELECTION SCREEN, Figure 3, comes 

into view on the laptop.

d On the CONFIGURE PORT SELECTION SCREEN, Figure 3, select 

the same COM PORT used during channel A software upload. Also 

select 38400 BPS. Then click on the DONE button.

Result:

(1) The SOFTWARE UPLOAD MAIN-SCREEN, Figure 2 comes back 

into view on the laptop.

e Click on the OPEN FILE button.

Result: 

(1) The OPEN FILE screen comes into view on the laptop. 

NOTE: If the OPEN FILE screen does not point to the CD-ROM 

DRIVE, you must select it in the LOOK IN box on the OPEN 

FILE screen.

f The target software part number will show in the FILE NAME window. 

Select the file with the “HSC” extension. Then, click on the OPEN button 

to open the software file. 

Result: 

(1) The FILE SEND screen comes into view on the laptop. 

SERVICE BULLETIN

SB No.: 190-21-0041

PAGE: 28

DATE: 27/Sep/2012

REVISION No.: 02 - 30/Jul/2013

Copyright © 2013 by Embraer S.A. All rights reserved.
Original Issue Date: Aug 31/12

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1001050-21-13

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SERVICE BULLETIN

Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

g Click on the SEND button to start the loading process. 

Result: 

(1) On the SOFTWARE UPLOAD MAIN SCREEN, Figure 2, the 

STATUS box shows the load status information. 

(2) When the loading completes, the STATUS box on the SOFTWARE 

UPLOAD MAIN SCREEN, Figure 2, shows the LOAD COMPLETE 

message. 

NOTE: The “Open File” button will also enable when complete. The 

LOAD COMPLETE message may scroll off the Status screen 

after a short time. 

h On the SOFTWARE UPLOAD MAIN SCREEN, Figure 2, click on the 

EXIT button. 

Result: 

(1) SOFTWARE UPLOAD MAIN SCREEN, Figure 2, closes. 

i On the Switch Box AGE16711 (8), do as follows: 

• Set S11 switch (CHANNEL B - BITE) to the OFF position.

• Set S12 switch (CHANNEL B - BOOT) to the OFF position.

• Set S13 switch (CHANNEL B) to the GND position and release it 

(while the S13 switch is set to GND, the LED SD11 momentarily goes 

OFF). 

Result:

(1) S13 switch moves back to the previous position.

j On the laptop, start the FlightPN application either from the link on the 

desktop or from the “C:\Windows\ProgramFiles\HSCLoad directory”. 

Result: 

(1) The FLIGHT SOFTWARE INFORMATION SCREEN, Figure 4,

comes into view. 

k On the FLIGHT SOFTWARE INFORMATION SCREEN, Figure 4, click 

on the “Get Software Information” button. 

Result: 

(1) After a short delay, the FLIGHT SOFTWARE INFORMATION 

SCREEN, Figure 4, comes back into view with this information: 

• FLIGHT SOFTWARE PART NUMBER 

• FLIGHT SOFTWARE CRC

• SYSTEM DATE AND TIME

SERVICE BULLETIN

DATE: 27/Sep/2012

REVISION No.:02 - 30/Jul/2013

SB No.: 190-21-0041

PAGE: 29

Copyright © 2013 by Embraer S.A. All rights reserved.
Original Issue Date: Aug 31/12

Revision 1: Jul 1/13

1001050-21-13

Page 17

SERVICE BULLETIN

Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

l Verify that the part number and the CRC information are correct. Refer 

to Table 1 in this Service Bulletin for the correct CRC and part number 

information.

m On the FLIGHT SOFTWARE INFORMATION SCREEN, Figure 4, click 

on the “Exit” button. 

Result: 

(1) FLIGHT SOFTWARE INFORMATION SCREEN, Figure 4, closes. 

(2) The AMS Controller Channel B (Channel 2) software load is 

complete. 

14 Set the +5, -15 and +15 switches of card chassis AGE14573 (1) to the OFF 

position. Refer to Table 1.

Result:

(1) The correspondent LEDs goes off.

15 Turn off the DC power supply (12). Refer to Figure 1. 

16 Disconnect the DC power supply (12) from the card chassis AGE14573 (1). 

Refer to Figure 1.

17 Turn off the laptop (14). Refer to Figure 1.

18 Disconnect the USB cable (13), cable (11) and cable AGE16712 (6) from the 

laptop (14) and AMS Controller Modules (2) and (3).

19 Obey all the electrostatic discharge safety precautions (AMM TASK 20-40-

910-801-A/200).

20 Release the wedge locks and move them out to disconnect the modules from 

the connectors of card chassis AGE14573 (1). Refer to Figure 1.

(b) To replace the part number identification label of the AMS Controller Processor 

Modules, do as follows:

1 Remove the AMS Controller Processor Modules from the GSE Card Chassis 

AGE14573 (1).

2 Remove the adhesive part number identification label from the identification 

plate.

3 Install the new part number identification label on the identification plate.

4 Re-install the AMS Controller Processor Modules (slots 18 and 25) (AMM 

Task 21-00-01-400-801-A/400) on the aircraft, as applicable.

a Install the new part number identification label on the identification 

plate. 

SERVICE BULLETIN

SB No.: 190-21-0041

PAGE: 30

DATE: 27/Sep/2012

REVISION No.: 02 - 30/Jul/2013

Copyright © 2013 by Embraer S.A. All rights reserved.
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SERVICE BULLETIN

Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

Figure 1

Figure 1

Off-Wing Loading Equipment Setup

SERVICE BULLETIN

DATE: 27/Sep/2012

REVISION No.:02 - 30/Jul/2013

SB No.: 190-21-0041

PAGE: 31

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SERVICE BULLETIN

Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

Figure 2

Figure 2

Software Upload Main Screen

SERVICE BULLETIN

SB No.: 190-21-0041

PAGE: 32

DATE: 27/Sep/2012

REVISION No.: 02 - 30/Jul/2013

Copyright © 2013 by Embraer S.A. All rights reserved.
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SERVICE BULLETIN

Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

Figure 3

Figure 3

Configuration Port Selection Screen

SERVICE BULLETIN

DATE: 27/Sep/2012

REVISION No.:02 - 30/Jul/2013

SB No.: 190-21-0041

PAGE: 33

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Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

Figure 4

Figure 4

Flight Software Information Screen

(c) Procedure for on-wing loading of AMS Controller Processor Card Software. Refer 

to Figure 5 for tooling and equipment setup.

WARNING: MAKE SURE THAT THE AIRCRAFT IS IN A SAFE CONDITION BEFORE 

YOU DO THE MAINTENANCE PROCEDURES. THIS IS TO PREVENT 

INJURY TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT.

1 Do the procedure to make the aircraft safe for maintenance 

(AMM TASK 20-00-00-910-801-A/200).

2 Disconnect the external AC power supply from the aircraft 

(AMM TASK 24-42-02-860-802-A/200).

3 Select the applicable cables, interface devices, and laptop of AGE16695 and 

AGE16732 related to the AMS-controller software-loading application.

CAUTION: THE MODULE OR UNIT CONTAINS ELECTROSTATIC 

DISCHARGE SENSITIVE (ESDS) ITEMS. OBEY THE APPROVED 

INDUSTRY PRECAUTIONS WHEN YOU TOUCH, REMOVE, OR 

INSERT PARTS OR ASSEMBLIES. DAMAGE CAN OCCUR FROM 

ELECTROSTATIC DISCHARGE. 

4 Obey all the electrostatic discharge safety precautions (AMM TASK 20-40-

00-910-801-A/200).

SERVICE BULLETIN

SB No.: 190-21-0041

PAGE: 34

DATE: 27/Sep/2012

REVISION No.: 02 - 30/Jul/2013

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Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

5 Loosen the captive screws (16) and remove the front cover (15) from the 

SPDA 2 (1).

6 To start and run the AMS-controller software-loading application, do as 

follows: Verify required AMS-controller software-loading application by 

starting the laptop (14) and select OPERATOR. Verify HSCLoad and 

FlightPN shortcuts on the desktop or executables in “C:\Windows\Program 

Files\HSCLoad directory”. If the files are not found in the directory specified, 

they can be installed from the CD-ROM AGE16738.

NOTE: Operators should contact Hamilton Sundstrand’s local field service 

representative for all GSE equipment setup or software upload 

inquiries.

7 Set up the connections to the AMS Controller Processor Modules as follows:

a Use a standard USB cable (13) from any open USB port on the laptop 

(14) and the opposite end to Channel A (9) with extension cable (17).

b Attach connector P1 (7) of the cable AGE16712 (6) to connector P1 on 

the Switch Box AGE16711 (8).

c Connect connector P18 (5) of cable AGE16712 (6) to the AMS 

Controller Module 18 - channel A (channel 1) (2) in SPDA 2 (1).

d Connect connector P25 (4) of cable AGE16712 (6) to the AMS 

Controller Processor Module 25 - channel B (channel 2) (3) in SPDA 2 

(1).

8 Connect the external AC power supply to the aircraft 

(AMM TASK 24-42-02-860-801-A/200).

Result:

(1) On the Switch Box AGE16711 (8), both LEDs, DS1 (Channel A) and 

DS11 (Channel B) come ON.

9 To load the software to the AMS Controller Channel A (Channel 1), do as 

follows:

a On the Switch Box AGE16711 (8), do the following: 

• Set S1 switch (CHANNEL A - BITE) to the GND position. 

• Set S2 switch (CHANNEL A - BOOT) to the GND position. 

• Set S3 switch (CHANNEL A) to the GND position and release it (while 

the S3 switch is set to GND, the LED SD1 momentarily goes OFF). 

Result: 

(1) S3 switch moves back to the previous position.

SERVICE BULLETIN

DATE: 27/Sep/2012

REVISION No.:02 - 30/Jul/2013

SB No.: 190-21-0041

PAGE: 35

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Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

b On the laptop, start the HSCLoad.exe application either from the 

shortcut link on the desktop or in the 

“C:\Windows\ProgramFiles\HSCLoad directory”. 

Result: 

(1) The SOFTWARE UPLOAD MAIN SCREEN, Figure 2, comes into 

view on the laptop. 

(2) The Property of Hamilton Sundstrand screen comes into view. 

Select OK.

c Click on the CONFIGURE PORT button. 

Result: 

(1) The CONFIGURE PORT SELECTION SCREEN, Figure 3, comes 

into view on the laptop.

d On the CONFIGURE PORT SELECTION SCREEN, Figure 3, select 

COM PORT 1. Also select 38400 BPS. Then click on the DONE button. 

Result: 

(1) The SOFTWARE UPLOAD MAIN-SCREEN, Figure 2, comes back 

into view on the laptop.

e Click on the OPEN FILE button.

Result: 

(1) The OPEN FILE screen comes into view on the laptop.

f Insert the current flight software CD as defined by the AMS service 

bulletin you are currently loading (See Table 1).

NOTE: If the OPEN FILE screen does not point to the CD-ROM 

DRIVER, you must select it in the LOOK IN box of the OPEN 

FILE window.

g The target software part number will show in the FILE NAME window. 

Select the file with the “HSC” extension. Then, click on the OPEN button 

to open the software file.

Result:

(1) The FILE SEND screen comes into view on the laptop.

SERVICE BULLETIN

SB No.: 190-21-0041

PAGE: 36

DATE: 27/Sep/2012

REVISION No.: 02 - 30/Jul/2013

Copyright © 2013 by Embraer S.A. All rights reserved.
Original Issue Date: Aug 31/12

Revision 1: Jul 1/13

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SERVICE BULLETIN

Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

h Click on the SEND button to start the loading process. 

Result: 

(1) On the SOFTWARE UPLOAD MAIN SCREEN, Figure 2, the 

STATUS box shows the load status information. If an error occurs 

during the software upload, repeat step 3.C.(2)(c)9d selecting COM2 

(or COM3 or COM4) instead of COM1.

(2) When the loading completes, the STATUS box on the SOFTWARE 

UPLOAD MAIN SCREEN, Figure 2, shows the LOAD COMPLETE 

message.

NOTE: The “Open File” button will also enable when complete. The 

LOAD COMPLETE message may scroll off the Status screen 

after a short time. 

i On the SOFTWARE UPLOAD MAIN SCREEN, Figure 2, click on the 

EXIT button. 

Result: 

(1) SOFTWARE UPLOAD MAIN SCREEN, Figure 2, closes.

j On the Switch Box AGE16711 (8), do as follows: 

• Set S1 switch (CHANNEL A - BITE) to the OFF position.

• Set S2 switch (CHANNEL A - BOOT) to the OFF position. Set S3 

switch.

• Set S3 switch (CHANNEL A) to the GND position and release it (while 

the S3 switch is set to GND, the LED SD1 momentarily goes OFF).

Result

(1) S3 switch moves back to the previous position.

k On the laptop, start the FlightPN application either from the link on the 

desktop or from the “C:\Windows\ProgramFiles\HSCLoad directory”. 

Result

(1) The FLIGHT SOFTWARE INFORMATION SCREEN, Figure 4, 

comes into view.

l On the FLIGHT SOFTWARE INFORMATION SCREEN, Figure 4, click 

on the “Get Software Information” button. 

Result: 

(1) After a short delay, the FLIGHT SOFTWARE INFORMATION 

SCREEN, Figure 4, comes back into view with this information: 

• FLIGHT SOFTWARE PART NUMBER

• FLIGHT SOFTWARE CRC

• SYSTEM DATE AND TIME

SERVICE BULLETIN

DATE: 27/Sep/2012

REVISION No.:02 - 30/Jul/2013

SB No.: 190-21-0041

PAGE: 37

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SERVICE BULLETIN

Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

m Verify that the part number and the CRC information are correct. Refer 

to Table 1 in this Service Bulletin for the correct CRC and part number 

information.

n On the FLIGHT SOFTWARE INFORMATION SCREEN, Figure 4, click 

on the “Exit” button. 

Result

(1) FLIGHT SOFTWARE INFORMATION SCREEN, Figure 4, closes.

(2) The AMS Controller Channel A (Channel 1), Slot 18 software load is 

complete.

10 Set up the connections to the AMS Controller Processor Modules as follows:

a Disconnect the USB cable (13) from Channel A (9) on the Switch Box 

AGE16711 (8) and connect the USB cable (13) to Channel B (10) on the 

Switch Box AGE16711 (8).

11 To load the software to the AMS Controller Channel B (Channel 2), do as 

follows:

a On the Switch Box AGE16711 (8), do the following: 

• Set S11 switch (CHANNEL B - BITE) to the GND position.

• Set S12 switch (CHANNEL B - BOOT) to the GND position.

• Set S13 switch (CHANNEL B) to the GND position and release it 

(while the S13 switch is set to GND, the LED SD11 momentarily goes 

OFF).

Result

(1) S13 switch moves back to the previous position.

b On the laptop, start the HSCLoad.exe application either from the 

shortcut link on the desktop or in the 

“C:\Windows\ProgramFiles\HSCLoad directory”. 

Result

(1) The SOFTWARE UPLOAD MAIN SCREEN, Figure 2, comes into 

view on the laptop. 

(2) The Property of Hamilton Sundstrand screen comes into view. 

Select OK. 

c Click on the CONFIGURE PORT button.

Result:

(1) The CONFIGURE PORT SELECTION SCREEN, Figure 3, comes 

into view on the laptop.

SERVICE BULLETIN

SB No.: 190-21-0041

PAGE: 38

DATE: 27/Sep/2012

REVISION No.: 02 - 30/Jul/2013

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SERVICE BULLETIN

Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

d On the CONFIGURE PORT SELECTION SCREEN, Figure 3, select 

the same COM PORT used during channel A software upload. Also 

select 38400 BPS. Then click on the DONE button.

Result:

(1) The SOFTWARE UPLOAD MAIN-SCREEN, Figure 2, comes back 

into view on the laptop.

e Click on the OPEN FILE button.

Result:

(1) The OPEN FILE screen comes into view on the laptop.

NOTE: If the OPEN FILE screen does not point to the CD-ROM 

DRIVE, you must select it in the LOOK IN box on the OPEN 

FILE window.

f The target software part number will show in the FILE NAME window. 

Select the file with the “HSC” extension. Then, click on the OPEN button 

to open the software file.

Result:

(1) the FILE SEND screen comes into view on the laptop.

g Click on the SEND button to start the loading process. 

Result

(1) On the SOFTWARE UPLOAD MAIN SCREEN, Figure 2, the 

STATUS box shows the load status information.

(2) When the loading completes, the STATUS box on the SOFTWARE 

UPLOAD MAIN SCREEN, Figure 2, shows the LOAD COMPLETE 

message.

NOTE: The “Open File” button will also enable when complete. The 

LOAD COMPLETE message may scroll off the Status screen 

after a short time.

h On the SOFTWARE UPLOAD MAIN SCREEN, Figure 2, click on the 

EXIT button. 

Result:

(1) SOFTWARE UPLOAD MAIN SCREEN, Figure 2, closes. 

SERVICE BULLETIN

DATE: 27/Sep/2012

REVISION No.:02 - 30/Jul/2013

SB No.: 190-21-0041

PAGE: 39

Copyright © 2013 by Embraer S.A. All rights reserved.
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SERVICE BULLETIN

Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

i On the Switch Box AGE16711 (8), do as follows: 

• Set S11 switch (CHANNEL B - BITE) to the OFF position.

• Set S12 switch (CHANNEL B - BOOT) to the OFF position. 

• Set S13 switch (CHANNEL B) to the GND position and release it 

(while the S13 switch is set to GND, the LED SD11 momentarily goes 

OFF). 

Result

(1) S13 switch moves back to the previous position.

j On the laptop, start the FlightPN application either from the link on the 

desktop or from the “C:\Windows\Program Files\HSCLoad directory”. 

Result:

(1) The FLIGHT SOFTWARE INFORMATION SCREEN, Figure 4, 

comes into view. 

k On the FLIGHT SOFTWARE INFORMATION SCREEN, Figure 4, click 

on the “Get Software Information” button.

Result:

(1) After a short delay, a FLIGHT SOFTWARE INFORMATION 

SCREEN, Figure 4, comes back into view with this information: 

• FLIGHT SOFTWARE PART NUMBER 

• FLIGHT SOFTWARE CRC

• SYSTEM DATE AND TIME

l Verify that the part number and the CRC information are correct. Refer 

to Table 1 in this Service Bulletin for the correct CRC and part number 

information.

m On the FLIGHT SOFTWARE INFORMATION SCREEN, Figure 4, click 

on the “Exit” button.

Result:

(1) FLIGHT SOFTWARE INFORMATION SCREEN, Figure 4, closes. 

(2) The AMS Controller Channel B (Channel 2), Slot 25 software load is 

complete. 

12 Remove the external AC power supply to the aircraft (AMM Task 24-42-02-

860-802-A/200).

13 Tun off the laptop (14). Refer to Figure 5.

14 Disconnect USB cable (13), extension cable (17) and cable AGE16712 (6) 

from the laptop (14) and AMS Controller Processor Modules (2) and (3).

SERVICE BULLETIN

SB No.: 190-21-0041

PAGE: 40

DATE: 27/Sep/2012

REVISION No.: 02 - 30/Jul/2013

Copyright © 2013 by Embraer S.A. All rights reserved.
Original Issue Date: Aug 31/12

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SERVICE BULLETIN

Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

(d) To replace the part number identification label of the AMS Controller Processor 

Modules, do as follows: 

1 To replace the part number identification label of the AMS Controller 

Processor Module 18 (2), do as follows:

a Remove the AMS Controller Processor Module 18 

(AMM TASK 21-00-01-000-801- A/400).

b Remove the adhesive part number identification label from the 

identification plate.

c Install the new part number identification label on the identification 

plate.

d Install the AMS Controller Processor Module 18 

(AMM TASK 21-00-01-400-801- A/400).

2 To replace the part number identification label of the AMS Controller 

Processor Module 25 (3), do as follows:

a Remove the AMS Controller Processor Module 25 

(AMM TASK 21-00-01-000-801- A/400).

b Remove the adhesive part number identification label from the 

identification plate.

c Install the new part number identification label on the identification 

plate.

d Install the AMS Controller Processor Module 25 

(AMM TASK 21-00-01-400-801- A/400).

e Install the front cover (15) on SPDA 2 (1) with the captive screws (16).

f Use a torque wrench to torque the captive screws (16) to 25 - 30 inchpounds (2.8 - 3.4 N•m).

SERVICE BULLETIN

DATE: 27/Sep/2012

REVISION No.:02 - 30/Jul/2013

SB No.: 190-21-0041

PAGE: 41

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Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

Figure 5

Figure 5

Loading Program on Wing

3 To perform this modification as a shop maintenance activity, refer to the 

programming procedures contained in Hamilton Sundstrand Component 

Maintenance Manual 21-00-05.

SERVICE BULLETIN

SB No.: 190-21-0041

PAGE: 42

DATE: 27/Sep/2012

REVISION No.: 02 - 30/Jul/2013

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Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

D. Assembly

(1) Not applicable

E. Test

(1) Not applicable

F. Identification

(1) To show that this Service Bulletin was done, re-identify the AMS Controller Processor 

Boards as follows:

(a) AMS Controller Processor Boards that are modified as a shop maintenance 

procedure must be re-identified to the new part number listed in Table 3. This will 

be accomplished by replacing the identification plate PN 1002123-1 in 

accordance with instructions contained in Hamilton Sundstrand Component 

Maintenance Manual 21-00-05.

(b) AMS Controller Processor Boards that are modified on-wing should be reidentified to the new part number listed in Table 3 in accordance with the 

instructions contained in the Embraer Service Bulletin referenced in paragraph 

3.C.(1) above or the alternate loading instructions referenced in paragraph 

3.C.(2). Identification plate location is shown in Figure 6.

SERVICE BULLETIN

DATE: 27/Sep/2012

REVISION No.:02 - 30/Jul/2013

SB No.: 190-21-0041

PAGE: 43

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Original Issue Date: Aug 31/12

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SERVICE BULLETIN

Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company

UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page.

Subject to the EAR - See the Title, First, or Cover Page for more information.

Figure 6

Figure 6

Processor Board Identification Plate Location

SERVICE BULLETIN

SB No.: 190-21-0041

PAGE: 44

DATE: 27/Sep/2012

REVISION No.: 02 - 30/Jul/2013

Copyright © 2013 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. 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 © 2013 by Embraer S.A. All rights reserved.