## AIR CONDITIONING - AIR MANAGEMENT SYSTEM CONTROLLER PROCESSOR BOARD – INCORPORATION OF NEW OPS SOFTWARE (BLACK LABEL 11.0)
1. PLANNING INFORMATION
A. SB EFFECTIVITY
Aircraft affected:
MODEL SN Embraer 170( ) and 175( ) 17000002, 17000004 thru 17000013, and 17000015 thru 17000321, 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: Embraer 170( ) and 175( ) model aircraft SN 17000322 and on, have an equivalent modification factory-incorporated.
B. CONCURRENT REQUIREMENTS For aircraft SN 17000002, 17000005 thru 17000013, 17000015, 17000016, and 17000018 thru 17000114, if PART II of SB 170-21-0016 has not been accomplished, it must be accomplished either in conjunction with or after the accomplishment of this bulletin. 

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DATE: 29/Nov/2010 REVISION No.: SB No.: 170-21-0049 PAGE: 1 of 37 Embraer Copyright © 2010. All rights reserved.

## C. REASON (1) HISTORY The Air Management System (AMS) processor board manufacturer has released a new operational program software version to eliminate the possibility of right hand (RH) engine compressor stall after the Auxiliary Power Unit (APU) becomes the active bleed source for the left side. In addition, the new software includes improvements and corrections for AMS system control logic and built-in test functions. The Air Management System (AMS) controller operational program software is also known as the Black Label - BL. (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-11.0. (3) EXPECTED BENEFITS The purpose of this software change is to correct the issues presented in the Air Management System control logic, its built-in test, and the fault monitoring functions at the field operation. The occurrence of spurious fault messages will also be reduced, so that the maintenance actions will be facilitated. (4) REVISION HISTORY None.
D. DESCRIPTION This Service Bulletin presents Hamilton Sundstrand SB 1001050-21-10, dated Nov 23/2010, 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: 

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SB No.: 170-21-0049 PAGE: 2 DATE: 29/Nov/2010 REVISION No.: Embraer Copyright © 2010. 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.(3) Accomplishment Instructions of Hamilton Sundstrand SB 1001050-21-10, 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.(1) Accomplishment Instructions of Hamilton Sundstrand SB 1001050-21-10, 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. To do all the above-mentioned alternatives, it is necessary to gain access to the middle avionics compartment by opening access doors 199BL, 147AL, and 123BL. NOTE: The modification presented in this bulletin does not affect Fatigue Critical Structure (FCS).
E. COMPLIANCE Embraer recommends that this bulletin be accomplished within the next 3300 Flight Hour(s).
F. APPROVAL The technical aspects of this Service Bulletin are approved by: Agência Nacional de Aviação Civil (ANAC). 

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DATE: 29/Nov/2010 REVISION No.: SB No.: 170-21-0049 PAGE: 3 Embraer Copyright © 2010. All rights reserved.

## 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 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. (3) Applicable to AMS controller processor boards replacement. – Access opening: 0.15 man-hours. – Inspection: None. 

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## – 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
None.
J. REFERENCES AMM 170/( ) Aircraft Maintenance Manual PART II - 20-00-00 - STANDARD PRACTICES-AIRFRAME. AMM 170/( ) Aircraft Maintenance Manual PART II - 21-00-00 and 21-00-01 - AIR CONDITIONING.
SB170-21-0016 AIR CONDITIONING - UPGRADE OF AIR MANAGEMENT SYSTEM CONTROLLER PROCESSOR BOARD TO BLACK LABEL 6.0.
Hamilton Sundstrand SB 1001050-21-10 AIR CONDITIONING – AIR MANAGEMENT SYSTEMS CONTROLLER PROCESSOR BOARD - INCORPORATION OF NEW OPS SOFTWARE (BLACK LABEL 11.0). K. OTHER PUBLICATIONS AFFECTED AIPC 170/( ) Aircraft Illustrated Parts Catalog - 21-00-01 - AIR CONDITIONING. 

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DATE: 29/Nov/2010 REVISION No.: SB No.: 170-21-0049 PAGE: 5 Embraer Copyright © 2010. 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.A Material - Price and Availability of Hamilton Sundstrand SB 1001050-21-10, 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 1001050-21-10, 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 

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## None. (b) Consumable Materials None.
D. MATERIAL NECESSARY FOR EACH SPARE Refer to paragraph 2.C Material Necessary for Each Component of Hamilton Sundstrand SB 1001050-21-10, attached to Section 4. APPENDIX 1 of this bulletin.
E. REIDENTIFIED PARTS Refer to paragraph 2.F Reidentified Parts of Hamilton Sundstrand SB 1001050-21-10, attached to Section 4. APPENDIX 1 of this bulletin.
F. TOOLING - PRICE AND AVAILABILITY Refer to paragraph 2.G Tooling of Hamilton Sundstrand SB 1001050-21-10, attached to Section 4. APPENDIX 1 of this bulletin. 

# SERVICE BULLETIN

DATE: 29/Nov/2010 REVISION No.: SB No.: 170-21-0049 PAGE: 7 Embraer Copyright © 2010. 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-11.0 software PN Y1001399-011, available on compact disk PN 1002256-110, 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.(3) Accomplishment Instructions of Hamilton Sundstrand SB 1001050-21-10, attached to Section 4. APPENDIX 1 of this bulletin. (2) Reidentify the boards with a new tag bearing appropriate PNs 1001050-1-013 or 1001050-2-013 or 1001050-3-013 or 1001050-4-013. Refer to Figure 6 and paragraph 2.F. Reidentified Parts of Hamilton Sundstrand SB 1001050-21-10, herein attached to Section 4. APPENDIX 1

. C. Applicable to off-wing AMS controller processor board upgrade. (1) Upload new BL-11.0 software PN Y1001399-011, available on compact disk PN 1002256-110, to both of the Air Management System (AMS) processor boards installed on the aircraft. Refer to AMM TASK 21-00-00-470-802-A/200 - AMS-Controller - Field-Loadable Software Upload (Off Wing) or refer to paragraph 

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## 3.C.(1) Accomplishment Instructions of Hamilton Sundstrand SB 1001050-21-10, attached to Section 4. APPENDIX 1 of this bulletin. (2) Reidentify the boards with a new tag bearing appropriate PNs 1001050-1-013 or 1001050-2-013 or 1001050-3-013 or 1001050-4-013. Refer to Figure 6 and paragraph 2.F. Reidentified Parts of Hamilton Sundstrand SB 1001050-21-10, 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 1001050-1-013 or 1001050-2-013 or 1001050-3-013 or 1001050-4-013, with BL-11.0 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. 

# SERVICE BULLETIN

DATE: 29/Nov/2010 REVISION No.: SB No.: 170-21-0049 PAGE: 9 Embraer Copyright © 2010. All rights reserved.

## 4. APPENDIX 1 HAMILTON SUNDSTRAND SB 1001050-21-10 - AIR MANAGEMENT SYSTEMS CONTROLLER PROCESSOR BOARD - INCORPORATION OF NEW OPS SOFTWARE (BLACK LABEL 11.0) 

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© 2010 Hamilton Sundstrand Corporation PROPRIETARY
THIS DOCUMENT AND THE INFORMATION CONTAINED HEREIN ARE THE PROPERTY OF HAMILTON SUNDSTRAND CORPORATION (HSC). RECIPIENT AGREES TO HOLD ALL SUCH INFORMATION IN CONFIDENCE AND AGREES IT SHALL BE USED ONLY FOR RECIPIENT’S INTERNAL PURPOSES TO MAINTAIN RECIPIENT’S EQUIPMENT OR AS MAY OTHERWISE BE PERMITTED IN AN APPLICABLE AGREEMENT BETWEEN RECIPIENT AND HSC. THIS DOCUMENT AND THE INFORMATION CONTAINED HEREIN SHALL NOT BE USED FOR ANY OTHER PURPOSE, INCLUDING THE CREATION, MANUFACTURE, DEVELOPMENT, OR DERIVATION OF ANY REPAIRS, MODIFICATIONS, SPARE PARTS, DESIGN, OR CONFIGURATION CHANGES, OR TO OBTAIN FAA OR ANY OTHER GOVERNMENT OR REGULATORY APPROVAL FOR SAME. RECIPIENT AGREES NOT TO DISCLOSE SUCH INFORMATION TO ANY THIRD PARTY, EXCEPT AS MAY OTHERWISE BE PROVIDED FOR IN AN APPLICABLE AGREEMENT BETWEEN RECIPIENT AND HSC. COPYING OR DISCLOSURE OF THIS DOCUMENT AND THE INFORMATION CONTAINED HEREIN BY ANYONE WITHOUT HSC’S PRIOR WRITTEN PERMISSION IS NOT AUTHORIZED AND MAY RESULT IN CRIMINAL AND/OR CIVIL LIABILITY.
INFORMATION SUBJECT TO EXPORT CONTROL LAWS THE TECHNICAL DATA IN THIS DOCUMENT (OR FILE) IS CONTROLLED FOR EXPORT UNDER THE EXPORT ADMINISTRATION REGULATIONS (EAR), 15 CFR PARTS 730-774. VIOLATIONS OF THESE LAWS MAY BE SUBJECT TO FINES AND PENALTIES UNDER THE EXPORT ADMINISTRATION ACT. EAR EXPORT CLASSIFICATION: ECCN 9E991 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.

Nov 23/10 1001050-21-10 Page 1 of 24 

### AIR CONDITIONING - AIR MANAGEMENT SYSTEMS CONTROLLER PROCESSOR BOARD - INCORPORATION OF NEW OPS SOFTWARE (BLACK LABEL 11.0) 1. Planning Information A. Effectivity 

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# SERVICE BULLETIN

Use or disclosure of this data is subject to restrictions on the front page of this document. (1) For the upgrade of AMS software installed on EMB170/190 aircraft to black label 11.0 All AMS controller processor boards Identified as Hamilton Sundstrand Part Numbers 1001050-1-YYY, 1001050-2-YYY, 1001050-3-YYY and, 1001050-4-YYY. YYY identifies any prior software configuration. NOTE: Part numbers 1001050-3-YYY and 1001050-4-YYY Identify processor cards which incorporate the modification defined in Hamilton Sundstrand Service Bulletin 1001050-21-06. NOTE: The AMS controller black label 11.0 software version introduced by this service bulletin contains all software improvements contained in the previous AMS controller software versions. B. Concurrent Requirements (1) Not applicable C. Reason (1) The software configuration introduced by this Service Bulletin was generated to incorporate AMS controller software improvements. The new software includes improvements and corrections for AMS system control logic and built in test functions. (a) The following software improvements will be incorporated when upgrading to AMS software change black label 11.0: 1 Revised APU bleed request logic to prevent the APU shutoff valve from

opening before the cross bleed valve has closed. This change is implemented to prevent the possibility of a right engine shutdown caused by the APU bleed flow back pressuring the right engine during bleed source transitions when the right engine is supplying bleed air. As part of this change the LH (left hand) NAPRSOV control logic was modified to further protect against uncommanded left engine shutdown. 2 Remove indication that SAIV IBIT is not active and remove its use in logic to close both NaPRSOVs. Although the SAIV IBIT is no longer automatically commanded on ground after landing, this monitor is already considered in the logic that commands both NaPRSOVs to close (BLK 10.1 and previous versions), delaying the bleed source transition. 3 Revised HPSOV built in test logic to eliminate spurious HPSOV faults occurring during single bleed - dual pack operating conditions on aircraft with AMS software BLK 9.0. 4 Revised Initiated built in test logic for the Add Heat Valve (AHV) to prevent spurious faults occurring on aircraft with AMS software BLK 9.0. As part of this change the existing AHV Failed Open and Failed Closed CMC messages were replaced with a single AHV Failed CMC Message. The AHV failed open fault was also removed from the PACK 1 (2) FAIL CAS message setting logic. In Black Label 10.1 the AHV maintenance messages were inhibited as an interim solution. 

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Nov 23/10 1001050-21-10 Page 3 Use or disclosure of this data is subject to restrictions on the front page of this document. 5 Revised built in test logic for the Low Limit Valve for improved fault detection capability. Improved logic will help to prevent spurious faults occurring during transient pack operating conditions. 6 Revised the RH Pack Bypass Valve Failed Open fault logic to prevent spurious faults occurring on aircraft with AMS software BLK 9.0 and above. 7 Revised SPDA / AMS Controller ARINC communication built in test logic to prevent spurious ARINC faults occurring during power up transients. As part of this change the RECIRC SMOKE DET FAIL CAS message logic was revised to prevent spurious CAS messages triggered by the ARINC built in test monitor. D. Description (1) This Service Bulletin provides procedures to change Hamilton Sundstrand AMS Controller Operational Program Software to part number Y1001399-011 configuration

. E. Compliance (1) It is recommended that this Service Bulletin is 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 

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Use or disclosure of this data is subject to restrictions on the front page of this document. J. 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.

K. References (1) Hamilton Sundstrand Component Maintenance Manual (CMM) 21-00-05 L. Other Publications Affected (1) Hamilton Sundstrand Component Maintenance Manual (CMM) 21-00-05. 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

Hamilton Sundstrand PN Flight Executable Program CRC Number Hamilton Sundstrand PN
Black Label 11.0 Y1001399-011 041F AABA 1002256-110 

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Nov 23/10 1001050-21-10 Page 5 Use or disclosure of this data is subject to restrictions on the front page of this document. 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 Component (1) Material to be Purchased (a) This Service Bulletin change will use parts in the list for each AMS Controller Board that is changed. (b) Any parts that usually are discarded when you disassemble the AMS Controller Board are not in the list. (c) In the list of parts for this change, the “Key Word” 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. (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 

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Use or disclosure of this data is subject to restrictions on the front page of this document. (f) Refer to Table 2 for part to be purchased.

• Instruction Code A: Compact Disk PN 1002256-110 is used to reprogram the Air

Management System processor board while it is installed in the aircraft. The AMS processor board can also be programmed as a shop maintenance procedure in accordance with the applicable component maintenance manual instructions. • Instruction Code B: Identification label 1006401-1-013 is used to re-identify

AMS controller processor boards PN 1001050-1-YYY that were modified on wing. • Instruction Code C: Identification label 1006401-2-013 is used to re-identify

AMS controller processor boards PN 1001050-2-YYY that were modified on wing. • Instruction Code D: Identification label 1006401-3-013 is used to re-identify

AMS controller processor boards PN 1001050-3-YYY that were modified on wing. • Instruction Code E: Identification label 1006401-4-013 is used to re-identify

AMS controller processor boards PN 1001050-4-YYY that were modified on wing. • Instruction Code F: Identification label 1002123-1 is used to re-identify

processor boards that were modified as a shop maintenance activity. D. Material Supplied by the Operator (1) None Table 2. Parts Information

New PN Keyword Old PN Qty Estimated Unit Price Instruction Code 1002256-110 Compact Disk 1002256-101 1 $30.00 A 1006401-1-013 Identification Label 1006401-1-012 1 $5.00 B
1006401-2-013 Identification Label 1006401-2-012 1 $5.00 C

1002123-1 Identification Label Same as previous 1 $5.00 F

1006401-3-013 Identification Label 1006401-3-012 1 $5.00 D

1006401-4-013 Identification Label 1006401-4-012 1 $5.00 E 

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Nov 23/10 1001050-21-10 Page 7 Use or disclosure of this data is subject to restrictions on the front page of this document. E. Material Necessary for Spare (1) Material to be Purchased (a) Refer to paragraph 2.C. (2) Material Supplied by the Operator (a) None F. 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.

(2) Refer to paragraph 3. for re-identification instructions. G. 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. GSE Equipment

NOTE: CD-ROM AGE 16738 is used to program the loading software for the laptop AGE 16732. This is considered GSE Equipment and is not flight software. Table 3. Re-Identified Parts Old Processor Board Part Number New Processor Board Part Number 1001050-1-YYY 1001050-1-013 1001050-2-YYY 1001050-2-013 1001050-3-YYY 1001050-3-013 1001050-4-YYY 1001050-4-013

Part Number Description AGE 14573 Off Wing Load Chassis and Power Supply AGE 16695 Switch Box and Connector Cable AGE 16732 Laptop with Extension and USB cables AGE16738 CD-ROM - Loading Program (See Note 1 below) 

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# SERVICE BULLETIN

Use or disclosure of this data is subject to restrictions on the front page of this document. 3. Accomplishment Instructions A. The user of this publication 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. B. To perform this modification while the AMS 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 Y1001399-011. C. 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: (1) Procedure for OFF-WING loading of AMS processor card 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. (a) Do the procedure to make the aircraft safe for maintenance (AMM TASK 20-00- 00-910-801-A/200). (b) Select the applicable cables, interface devices, power supply, and laptop ofAGE16695, AGE14573 and AGE16732 related to the AMS-controller softwareloading application. (c) 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 ORASSEMBLIES. DAMAGE CAN OCCUR FROM ELECTROSTATIC DISCHARGE. (d) Obey all the electrostatic discharge safety precautions (AMM TASK 20-40-00- 910-801-A/200). (e) Connect the DC power supply (12) to the card chassis AGE14573 (1) and install its ground strap. Refer to Figure 1

. (f) Install the AMS controller processor modules (slots 18 and 25) on the card chassis AGE14573 (1) as follows: 

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Nov 23/10 1001050-21-10 Page 9 Use or disclosure of this data is subject to restrictions on the front page of this document. 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. 1 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

. 2 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. (g) Turn on the DC power supply (12)

. Refer to Figure 1

. (h) On the card chassis AGE14573, set the +5, -15 and +15 switches to the ON position. Refer to Figure 1

. Result: (1) On the card chassis (1) the correspondent LEDs will come on. (2) On the Switch Box (8) both LEDs, DS1 (Channel A) and DS11 (Channel B) comes ON. (i) 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 that HSCLoad and FlightPN shortcuts are on the desktop or executables are in “ C:\Windows\Program Files\HSCLoad ” directory. If the files are not found in the directories specified, they can be installed from CD-ROM AGE16738. NOTE: Operators should contact Hamilton Sundstrand’s local field service representative for all GSE equipment setup or software upload inquiries. (j) Setup the connections to the AMS Controller Modules by: 1 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). 2 Attach connector P1 (7) of the cable (6) to connector P1 on the switch box (8). 3 Connect connector P18 (5) of cable (6) to the AMS Controller module 18 - channel A (channel 1) (2) in AGE14573 (1). 4 Connect connector P25 (4) of cable (6) to the AMS Controller module 25 - channel B (channel 2) (3) in AGE14573 (1). (k) To load the software to the AMS Controller Channel A (Channel 1) do as follows: 1 On the Switch Box (8), do the following: 

# SERVICE BULLETIN

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# SERVICE BULLETIN

Use or disclosure of this data is subject to restrictions on the front page of this document. • 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. 2 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. 3 Click on the CONFIGURE PORT button. Result: (1) The CONFIGURE PORT SELECTION SCREEN Figure 3 comes into view on the laptop. 4 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. 5 Click on the OPEN FILE button. Result: (1) The OPEN FILE screen comes into view on the laptop. 6 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. 7 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. 8 Click on the SEND button to start the loading process. Result: (1) On 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 4 selecting COM2 (or COM3 or 

# SERVICE BULLETIN

SB No.: 170-21-0049 PAGE: 20 DATE: 29/Nov/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.

# SERVICE BULLETIN

Nov 23/10 1001050-21-10 Page 11 Use or disclosure of this data is subject to restrictions on the front page of this document. 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 screen the Status screen after a short time. 9 On the SOFTWARE UPLOAD MAIN SCREEN Figure 2 , click on the EXIT button. Result: (1) SOFTWARE UPLOAD MAIN SCREEN closes. 10 On the Switch Box (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. 11 On the laptop, start the FlightPN application either from the link on the desktop or from the “ C:\Windows\ProgramFiles\HSCLoad directory ”. Result: The FLIGHT SOFTWARE INFORMATION SCREEN comes in to view. 12 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 13 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. 14 On the FLIGHT SOFTWARE INFORMATION SCREEN Figure 4 , click on the “Exit” button. Result: (1) FLIGHT SOFTWARE INFORMATION SCREEN closes. (2) The AMS Controller Channel A (Channel 1) software load is complete. (l) Setup the connections to the AMS Controller Modules by: 

# SERVICE BULLETIN

DATE: 29/Nov/2010 REVISION No.: SB No.: 170-21-0049 PAGE: 21 Embraer Copyright © 2010. All rights reserved.Nov 23/10 1001050-21-10 Page 12 

# SERVICE BULLETIN

Use or disclosure of this data is subject to restrictions on the front page of this document. 1 Disconnect the USB cable (13) from Channel A (9) on the switch Box (8) and

connect the cable to Channel B (10) on the Switch Box (8). (m) To load the software to the AMS Controller Channel B (Channel 2), do as follows: 1 On the Switch Box (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. 2 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. 3 Click on the CONFIGURE PORT button. Result: (1) The CONFIGURE PORT SELECTION SCREEN Figure 3 comes into view on the laptop. 4 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. 5 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. 6 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.: 170-21-0049 PAGE: 22 DATE: 29/Nov/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.

# SERVICE BULLETIN

Nov 23/10 1001050-21-10 Page 13 Use or disclosure of this data is subject to restrictions on the front page of this document. 7 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 screen the Status screen after a short time. 8 On the SOFTWARE UPLOAD MAIN SCREEN Figure 2 , click on the EXIT button. Result: (1) SOFTWARE UPLOAD MAIN SCREEN closes. 9 On the Switch Box (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. 10 On the laptop, start the FlightPN application either from the link on the desktop or from the “ C:\Windows\ProgramFiles\HSCLoad directory ”. Result: The FLIGHT SOFTWARE INFORMATION SCREEN comes in to view. 11 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 12 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. 13 On the FLIGHT SOFTWARE INFORMATION SCREEN, click on the “Exit” button. Result: (1) FLIGHT SOFTWARE INFORMATION SCREEN closes. (2) The AMS Controller Channel B (Channel 2) software load is complete. 

# SERVICE BULLETIN

DATE: 29/Nov/2010 REVISION No.: SB No.: 170-21-0049 PAGE: 23 Embraer Copyright © 2010. All rights reserved.Nov 23/10 1001050-21-10 Page 14 

# SERVICE BULLETIN

Use or disclosure of this data is subject to restrictions on the front page of this document. (n) Set the +5, -15 and +15 switches of card chassis (1) to the OFF position. Refer to Figure 1

. Result: (1) The correspondent LEDs goes off. (o) Turn off the DC power supply (12)

. Refer to Figure 1

. (p) Disconnect the DC power supply (12) from the card chassis (1). Refer to Figure 1

. (q) Turn of the laptop (14). Refer to Figure 1

. (r) Disconnect USB cable (13), cable (11) and cable (6) from the laptop (14) and AMS Controller Modules (2) and (3). (s) Obey all the electrostatic discharge safety precautions (AMM TASK 20-40-910- 801-A/200)

. (t) Release the wedge locks and move them out to disconnect the modules from the connectors of card chassis (1). Refer to Figure 1

. (2) To replace the part number identification label of the AMS Controller Processor modules, do as follows: (a) Remove the AMS Controller Processor modules from the GSE card Chassis (1). (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) 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. 

# SERVICE BULLETIN

SB No.: 170-21-0049 PAGE: 24 DATE: 29/Nov/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.

# SERVICE BULLETIN

Nov 23/10 1001050-21-10 Page 15 Use or disclosure of this data is subject to restrictions on the front page of this document. 1 Install the new part-number-identification label on the identification plate.

Figure 1. Off-Wing Loading Equipment Setup 

# SERVICE BULLETIN

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# SERVICE BULLETIN

Use or disclosure of this data is subject to restrictions on the front page of this document. Figure 2. Software Upload Main Screen 

# SERVICE BULLETIN

SB No.: 170-21-0049 PAGE: 26 DATE: 29/Nov/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.

# SERVICE BULLETIN

Nov 23/10 1001050-21-10 Page 17 Use or disclosure of this data is subject to restrictions on the front page of this document. Figure 3. Configuration Port Selection Screen

Figure 4. Flight Software Information Screen 

# SERVICE BULLETIN

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# SERVICE BULLETIN

Use or disclosure of this data is subject to restrictions on the front page of this document. (3) Procedure for On-Wing Loading of AMS 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. (a) Do the procedure to make the aircraft safe for maintenance (AMM TASK 20-00-00-910-801-A/200). (b) Disconnect the external AC power supply from the aircraft (AMM TASK 24-42-02-860-802-A/200). (c) 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 ORASSEMBLIES. DAMAGE CAN OCCUR FROM ELECTROSTATIC DISCHARGE. (d) Obey all the electrostatic discharge safety precautions (AMM TASK 20-40-00- 910-801-A/200). (e) Loosen the captive screws (16) and remove the front cover (15) from the SPDA 2 (1).E. (f) 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 ” . Ifthe files are not found in the directories specified, they can be installed from CDROM AGE16738. NOTE: Operators should contact Hamilton Sundstrand’s local field service representative for all GSE equipment setup or software upload inquiries. (g) Setup the connections to the AMS Controller Modules by: 1 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)

. 2 Attach connector P1 (7) of the cable (6) to connector P1 on the switch box (8). 3 Connect connector P18 (5) of cable (6) to the AMS Controller module 18 - channel A (channel 1) (2) in SPDA2 (1). 4 Connect connector P25 (4) of cable (6) to the AMS Controller module 25 - channel B (channel 2) (3) in SPDA 2 (1). 

# SERVICE BULLETIN

SB No.: 170-21-0049 PAGE: 28 DATE: 29/Nov/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.

# SERVICE BULLETIN

Nov 23/10 1001050-21-10 Page 19 Use or disclosure of this data is subject to restrictions on the front page of this document. (h) Connect the external AC power supply to the aircraft (AMM TASK 24-42-02-860-801-A/200). Result: (1) On the Switch Box (8) both LEDs, DS1(Channel A) and DS11 (Channel B) come ON. (i) To load the software to the AMS Controller Channel A (Channel 1), do as follows: 1 On the Switch Box (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. 2 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. 3 Click on the CONFIGURE PORT button. Result: (1) The CONFIGURE PORT SELECTION SCREEN Figure 3 comes into view on the laptop. 4 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. 5 Click on the OPEN FILE button. Result: (1) The OPEN FILE screen comes into view on the laptop. 6 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 DRIVER, you must select it in the LOOK IN box of the OPEN FILE window. 

# SERVICE BULLETIN

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# SERVICE BULLETIN

Use or disclosure of this data is subject to restrictions on the front page of this document. 7 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. 8 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 4 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 screen the Status screen after a short time. 9 On the SOFTWARE UPLOAD MAIN SCREEN Figure 2 , click on the EXIT button. Result: (1) SOFTWARE UPLOAD MAIN SCREEN closes. 10 On the Switch Box (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 (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. 11 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 comes in to view. 12 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 

# SERVICE BULLETIN

SB No.: 170-21-0049 PAGE: 30 DATE: 29/Nov/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.

# SERVICE BULLETIN

Nov 23/10 1001050-21-10 Page 21 Use or disclosure of this data is subject to restrictions on the front page of this document. • FLIGHT SOFTWARE CRC • SYSTEM DATE AND TIME 13 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. 14 On the FLIGHT SOFTWARE INFORMATION SCREEN Figure 4 , click on the “Exit” button. Result (1) FLIGHT SOFTWARE INFORMATION SCREEN closes. (2) The AMS Controller Channel A (Channel 1), Slot 18 software load is complete. (j) Setup the connections to the AMS Controller Modules by: 1 Disconnect the USB cable (13) from Channel A (9) on the switch Box (8) and

connect the cable to Channel B (10) on the Switch Box (8). (k) To load the software to the AMS Controller Channel B (Channel 2), do as follows: 1 On the Switch Box (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. 2 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. 3 Click on the CONFIGURE PORT button. Result: (1) The CONFIGURE PORT SELECTION SCREEN Figure 3 comes into view on the laptop. 

# SERVICE BULLETIN

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# SERVICE BULLETIN

Use or disclosure of this data is subject to restrictions on the front page of this document. 4 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. 5 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. 6 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. 7 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 screen the Status screen after a short time. 8 On the SOFTWARE UPLOAD MAIN SCREEN Figure 2 , click on the EXIT button. Result: (1) SOFTWARE UPLOAD MAIN SCREEN closes. 9 On the Switch Box (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. 

# SERVICE BULLETIN

SB No.: 170-21-0049 PAGE: 32 DATE: 29/Nov/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.

# SERVICE BULLETIN

Nov 23/10 1001050-21-10 Page 23 Use or disclosure of this data is subject to restrictions on the front page of this document. 10 On the laptop, start the FlightPN application either from the link on the desktop or from the “ C:\Windows\Program Files\HSCLoad directory ”. Result: The FLIGHT SOFTWARE INFORMATION SCREEN comes in to view. 11 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 12 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. 13 On the FLIGHT SOFTWARE INFORMATION SCREEN, click on the “Exit” button. Result: (1) FLIGHT SOFTWARE INFORMATION SCREEN closes. (2) The AMS Controller Channel B (Channel 2), Slot 25 software load is complete. (l) Remove the external AC power supply to the aircraft (AMM Task 24-42-02-860- 802-A/200)

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

. (n) Disconnect USB cable (13), cable (17) and cable (6) from the laptop (14) and AMS Controller Modules (2) and (3). (4) To replace the part number identification label of the AMS Controller Processor modules, do as follows: (a) To replace the part number identification label of the AMS Controller Processor module 18 (2), do as follows: 1 Remove the AMS Controller Processor module 18 (AMM TASK 21-00-01-000-801- A/400). 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 Install the AMS Controller Processor module 18 (AMM TASK 21-00-01-400-801- A/400). (b) To replace the part-number-identification label of the AMS Controller Processor module 25 (3), do as follows: 

# SERVICE BULLETIN

DATE: 29/Nov/2010 REVISION No.: SB No.: 170-21-0049 PAGE: 33 Embraer Copyright © 2010. All rights reserved.Nov 23/10 1001050-21-10 Page 24 

# SERVICE BULLETIN

Use or disclosure of this data is subject to restrictions on the front page of this document. 1 Remove the AMS Controller Processor module 25 (AMM TASK 21-00-01-000-801- A/400). 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 Install the AMS Controller Processor module 25 (AMM TASK 21-00-01-400-801- A/400). 5 Install the front cover (15) on SPDA2 (1) with the captive screws (16). 6 Use a torque wrench to torque the captive screws (16) to 25 - 30 inch-pounds (2.8 - 3.4 N • m). 

# SERVICE BULLETIN

SB No.: 170-21-0049 PAGE: 34 DATE: 29/Nov/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.

# SERVICE BULLETIN

Nov 23/10 1001050-21-10 Page 25 Use or disclosure of this data is subject to restrictions on the front page of this document. Figure 5. Loading Program on Wing D. To perform this modification as a shop maintenance activity refer to the programming procedures contained in Hamilton Sundstrand Component Maintenance Manual 21-00- 05. E. To show that this Service Bulletin was done re-identify the AMS Controller Processor Boards as follows: 

# SERVICE BULLETIN

DATE: 29/Nov/2010 REVISION No.: SB No.: 170-21-0049 PAGE: 35 Embraer Copyright © 2010. All rights reserved.Nov 23/10 1001050-21-10 Page 26 

# SERVICE BULLETIN

Use or disclosure of this data is subject to restrictions on the front page of this document.(1) Processor boards that are modified as a shop maintenance procedure must be reidentified to the new part number listed in Table 3 . This will be accomplished by replacing the nameplate PN 1002123-1 in accordance with instructions contained in Hamilton Sundstrand Component Maintenance Manual 21-00-05. (2) Processor boards that are modified On-Wing should be re-identified to the new part number listed in Table 3 in accordance with the instructions contained in the Embraer Service Bulletin referenced in paragraph 3.B. above or the alternate loading instructions referenced in paragraph 3.C. Identification plate location is shown in Figure 6

. 

# SERVICE BULLETIN

SB No.: 170-21-0049 PAGE: 36 DATE: 29/Nov/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.

# SERVICE BULLETIN

Nov 23/10 1001050-21-10 Page 27 Use or disclosure of this data is subject to restrictions on the front page of this document. Figure 6. Processor Board Identification Plate Location Hamilton Sundstrand Reference Number EC10B455 

# SERVICE BULLETIN

DATE: 29/Nov/2010 REVISION No.: SB No.: 170-21-0049 PAGE: 37 Embraer Copyright © 2010. All rights reserved.

# SERVICE BULLETIN EVALUATION

THE PURPOSE OF THIS FORM IS TO COLLECT DATA THAT WILL BE USED TO IMPROVE THE QUALITY OF OUR SERVICE BULLETINS AND UPDATE THE TECHNICAL PUBLICATIONS. PLEASE FILL IN FORM AND RETURN IT TO: EMBRAER - EMPRESA BRASILEIRA DE AERONÁUTICA S.A. EFTC - SERVICE BULLETIN ENGINEERING AV. BRIGADEIRO FARIA LIMA, 2170 SÃO JOSÉ DOS CAMPOS - SP - 12227-901 BRASIL Fax: + 55 12 3927-6600 (ext. 1624) e-mail: fleet.reliability@embraer.com.br 

### S.B. Title: S.B.: (Number / Rev.) Operator:
SB Implementation Report Aircraft Serial Number or Registration Number: Incorporation Date: Aircraft Flight Hours: Aircraft Landings:

POST-ACCOMPLISHMENT EVALUATION: (Check applicable squares below) 

### ESTIMATED MANPOWER: [ ] OK [ ] NOT OK (Explain Below) MATERIAL & KITS: [ ] OK [ ] NOT OK (Explain Below) ACCOMPLISHMENT INSTRUCTIONS: [ ] OK [ ] NOT OK (Explain Below) FIGURES: [ ] OK [ ] NOT OK (Explain Below) SB GENERAL EVALUATION: [ ] OK [ ] NOT OK (Explain Below) COMMENTS: (Bulletin quality/ Difficulties found at the time of incorporation/ Suggested improvements/ Other)

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