SB190-21-0041-REV.02 - AIR CONDITIONING - Regulations ...

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 theprevious 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 additionalaction.

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 introducedby this revision are presented below.

Revision bars are put in the left margin of each page to show the location of the significantchanges. Text displacement and text format changes are not indicated.

TOPIC/PAGE DESCRIPTION OF REVISION1. PLANNING INFORMATION

1.C. REASON / 02 AND 04Updated reason text and added reason for revision02

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

1.G. ESTIMATED MANPOWER / 06 Updated text information3. ACCOMPLISHMENT INSTRUCTIONS / 10 THRU12

Included new AMS Controller Board PNS and up-dated text information

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

TRANSMITTAL LETTER

SB No.: 190-21-0041PAGE: 1 of 1

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

AIR CONDITIONING - AIR MANAGEMENT SYSTEM CONTROLLER PROCESSORBOARD - INCORPORATION OF NEW OPS SOFTWARE (BLACK LABEL 13.0)

In connection with the use of this document, Embraer does not provide any express or impliedwarranties 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 BlackLabel version, installed on the aircraft and in stock as spare.

NOTE: This effectivity list includes the aircraft originally equipped with the affectedcomponent. Since this component is a Line Replaceable Unit (LRU), it maybe necessary to refer to the fleet maintenance control record and verifywhether the unit has been replaced with another one, during the routinemaintenance.

In-production effectivity:

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SB No.: 190-21-0041PAGE: 1 of 44


Embraer 190 ( ) and 195 ( ) model aircraft SN 19000587, SN 19000589, and 19000593and 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/climbphases at high engine power thrust have been observed.

Embraer engineering analysis revealed that this NAPRSOV PN 1013952-1 inconjunction with some other degraded components make the system more suscep-tible to this kind of oscillations.

Therefore, Embraer and Hamilton Sundstrand developed a new Black Labelsoftware 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 blockageduring single bleed operation. Both are key contributors of ACM fan and bearingfailures.

(2) OBJECTIVE

This bulletin gives instructions for the Air Management System (AMS) controlleroperational 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 ofbleed oscillations in the fleet during take-off/climb phases at high engine powerthrust, as well as to improve Air Cycle Machine (ACM) reliability.

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DATE: 27/Sep/2012REVISION No.: 02 - 30/Jul/2013


(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 thru19000063, 19000066, 19000067, 19000069, 19000072, 19000074,19000076, 19000078 thru 19000081, 19000084, 19000086 thru19000089, 19000091, 19000093, 19000095, 19000098 thru19000100, 19000102, 19000104, 19000106, 19000107, 19000110,19000112 thru 19000114, 19000117, 19000119 thru 19000123,19000126 thru 19000131, 19000133, 19000135, 19000137 thru19000139, 19000141, 19000143, 19000145, 19000148, 19000152thru 19000158, 19000160 thru 19000176, 19000178, 19000180 thru19000184, 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 thru19000277, 19000280, 19000281, 19000283 thru 19000285,19000287, 19000290, 19000291, 19000293, 19000294, 19000297thru 19000303, 19000305, 19000306, 19000308 thru 19000314,19000316, 19000318, 19000320, 19000321, 19000323 thru19000325, 19000327, 19000328, 19000331 thru 19000333,19000335, 19000337, 19000340, 19000341, 19000344, 19000348thru 19000350, 19000352, 19000354, 19000355, 19000357 thru19000360, 19000365, 19000367 thru 19000369, 19000371 thru19000373, 19000376, 19000377, 19000379, 19000381, 19000383,19000385, 19000387, 19000389, 19000390, 19000393 thru19000395, 19000397 thru 19000406, 19000408 thru 19000412,19000414 thru 19000418, 19000420, 19000421, 19000423 thru19000428, 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),

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REVISION 01(Continued):

19000472, 19000474, 19000476 thru 19000483, 19000485 thru19000489, 19000492 thru 19000497, 19000499 thru 19000503,19000505 thru 19000509, 19000512, 19000513, 19000515 thru19000518, 19000520, 19000523 thru 19000525, 19000527,19000529, 19000531, 19000532, 19000535 thru 19000539,19000541 thru 19000544, 19000546 thru 19000548, 19000550 thru19000558, 19000560 thru 19000562, 19000564 thru 19000570,19000572 thru 19000586, 19000588, 19000590 thru 19000592 inthe SB effectivity, and to include In-production effectivity.

REVISION 02: To update Hamilton Sundstrand bulletin 1001050-21-13 and updatedbulletin 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 AMSController Operational Program of the AMS controller processor boards with a newimproved one.

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

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(1) The AMS controller processor boards can be programmed on-wing as a linemaintenance activity by referring to the Aircraft Maintenance Manual procedures orto the paragraph 3.C.(2).(c) Accomplishment Instructions of Hamilton SundstrandSB 1001050-21-13, attached to Section 4. APPENDIX 1 of this bulletin. For this,operators may optionally call for Hamilton Sundstrand (HS) trained personnel toassist the on-wing modification. For this, contact a local Hamilton Sundstrandtechnical representative, or

(2) The AMS controller processor boards can be programmed off-wing, referring to theAircraft Maintenance Manual procedures or to the paragraph 3.C.(2).(a)Accomplishment Instructions of Hamilton Sundstrand SB 1001050-21-13, attachedto Section 4. APPENDIX 1 of this bulletin. For this, operators may optionally call forHamilton Sundstrand (HS) trained personnel to assist the off-wing modification. Forthis, contact a local Hamilton Sundstrand technical representative, or

(3) The AMS processor boards can be removed from the Secondary Power DistributionAssembly (SPDA) 2 and returned to a Hamilton Sundstrand approved componentrepair station and programmed by referring to the Component Maintenance Manualprocedures.

For all the above-mentioned alternatives, it is necessary to gain access to the middleavionics compartment by opening access doors 195BL and 147AL.

NOTE: The modification presented in this bulletin does not affect Fatigue CriticalStructure (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 deAviação Civil (ANAC).

NOTE: If any aircraft listed in the SB effectivity has a modification or repairincorporated that is not of EMBRAER origin, and which affects the contentof this Service Bulletin, the operator will take full responsibility for obtainingapproval by a regulatory agency for any adaptation necessary beforeincorporation of this Service Bulletin.

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G. ESTIMATED MANPOWER

This is an estimate of the manpower necessary to accomplish this Service Bulletin on asingle aircraft.

It is intended for direct labor only, performed by experienced personnel, and does notinclude the time to plan, prepare, or inspect the work. Sealant, paint, or adhesive curingtimes are not included.

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

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.






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(3) Applicable to AMS controller processor boards replacement.






H. WEIGHT AND BALANCE

None.

I. SOFTWARE ACCOMPLISHMENT SUMMARY

Refer to paragraph 1.J. Software Accomplishment Summary of Hamilton Sundstrand SB1001050-21-13, 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.

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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 SundstrandSB 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 SB1001050-21-13, 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 thekits is allowable, provided that these alternative or similar parts are approved by Embraeras indicated in the related Embraer Technical Publications or through a formal Embraercommunication channel.

The necessary expendable or consumable parts presented in the AMM Tasks referred toin 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 respectiveTable.

(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 Unit of Hamilton Sundstrand SB1001050-21-13, 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 SB1001050-21-13, attached to Section 4. APPENDIX 1 of this bulletin.

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3. ACCOMPLISHMENT INSTRUCTIONS

NOTE: 1) Obey all of the WARNINGS and CAUTIONS included in the referenced manualsand procedures.

2) The Manuals and other documents are referred to by acronyms or using asimplified form. Refer to section 1.J. REFERENCES for a more completedefinition.

The steps below outline the general accomplishment instructions.

WARNING : MAKE SURE THAT THE AIRCRAFT IS IN A SAFE CONDITION BEFOREYOU DO THE MAINTENANCE PROCEDURES. THIS IS TO PREVENTINJURY TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT.

A. Make sure that the aircraft is safe for maintenance. Refer to AMM TASK20-00-00-910-801-A/200 - Aircraft Maintenance Safety Procedures - StandardProcedures.

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

(1) Upload new BL-13.0 software PN Y1001399-013, available on compact disk PN1002256-130, to both of the AMS processor boards installed on the aircraft. Refer toAMM TASK 21-00-00-470-801-A/200 - AMS-Controller - Field-Loadable SoftwareUpload (On Wing) or refer to paragraph 3.C.(2).(c) Accomplishment Instructions ofHamilton Sundstrand SB 1001050-21-13, attached to Section 4. APPENDIX 1 of thisbulletin.

(2) Reidentify the boards with a new tag bearing appropriate PNs 1001050-1-015 or1001050-2-015 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 ofHamilton Sundstrand SB 1001050-21-13, herein attached to Section 4. APPENDIX1.

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

(1) Upload new BL-13.0 software PN Y1001399-013, available on compact disk PN1002256-130, to both of the AMS processor boards installed on the aircraft. Refer toAMM TASK 21-00-00-470-802-A/200 - AMS-Controller - Field-Loadable Software

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Upload (Off Wing) or refer to paragraph 3.C.(2).(a) Accomplishment Instructions ofHamilton Sundstrand SB 1001050-21-13, attached to Section 4. APPENDIX 1 of thisbulletin.

(2) Reidentify the boards with a new tag bearing appropriate PNs 1001050-1-015 or1001050-2-015 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 ofHamilton Sundstrand SB 1001050-21-13, herein attached to Section 4. APPENDIX1.

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

(1) Replace both existing AMS controller processor boards PNs 1001050-1-YYY, or1001050-2-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 or1001050-6-015 or 1001050-7-015, with BL-13.0 already uploaded. Refer to AMMTASK 21-00-01-000-801-A/400 - AMS Controller Processor Modules - Removal andAMM TASK 21-00-01-400-801-A/400 - AMS Controller Processor Modules - Instal-lation.

NOTE: Send the removed AMS controller processor boards to an authorizedHamilton Sundstrand repair facility to be upgraded. For this, refer toparagraph 2.B. Industry Support Information of this bulletin.

E. Perform the Air Management System (AMS) controller power-up BIT, if it has not beendone 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 [email protected] of the aircraftmanufacturer serial number and the SB incorporation date, specifying the SBPart(s) incorporated or whether the whole SB has been incorporated. Thiswill enable Embraer to consider your aircraft configuration when providingfuture modifications.

2) To formally inform that the SB has been incorporated fleet-wide or that theSB will not be incorporated, so that Embraer can update the affected

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technical publications, use the “Service Bulletin Full-Fleet IncorporationReport” form, which is available on the Flyembraer portal(http://www.flyembraer.com).

3) Use the attached “Service Bulletin Evaluation” form to send us yourcomments regarding this SB. Your feedback will be much appreciated as anaid to help us improve the quality of the SBs.

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4. APPENDIX 1

HAMILTON SUNDSTRAND SB 1001050-21-13 - AIR MANAGEMENT SYSTEMS CON-TROLLER PROCESSOR BOARD - INCORPORATION OF NEW OPS SOFTWARE (BLACKLABEL 13.0)

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Original Issue Date: Aug 31/12Revision 1: Jul 1/13

1001050-21-13Page 1 of 31

SERVICE BULLETINHamilton 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

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1001050-21-13Page 2




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.

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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 Add-Heat 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

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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 CorporationA United Technologies CompanyAttention: Manager Commercial Spares AdministrationMail Stop: 236-6P.O. Box 70024747 Harrison AvenueRockford, IL 61125-7002USA

Table 1AMS 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

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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 StationOne Hamilton RoadDock WWindsor Locks, CT 06096USA

or

Hamilton SundstrandCustomer Support Center - MaastrichtHorsterweg 76199 AC Maastricht AirportThe 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.

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(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 CorporationA United Technologies CompanyAttention: Manager Commercial Spares AdministrationMail Stop: 236-6P.O. Box 70024747 Harrison AvenueRockford, IL 61125-7002USA

Facsimile: (815) 226-2624

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

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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 2Parts Information

New Part Number Keyword

Old Part Number Qty

Unit PriceSpecial

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


1006401-2-014 1 $5.00 Note 3


1006401-3-014 1 $5.00 Note 4


1006401-4-014 1 $5.00 Note 5


1006401-5-014 1 $5.00 Note 6


1006401-6-014 1 $5.00 Note 7


1006401-7-014 1 $5.00 Note 8

1002123-1 Identification Plate

1002123-1 1 $5.00 Note 9

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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 3Reidentified 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

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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 4GSE 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)

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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:

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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).

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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.

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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).


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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:


• 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).


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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 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.



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.

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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.


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


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.


• FLIGHT SOFTWARE PART NUMBER • FLIGHT SOFTWARE CRC• SYSTEM DATE AND TIME

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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.

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Figure 1

Figure 1Off-Wing Loading Equipment Setup

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Figure 2

Figure 2Software Upload Main Screen

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Figure 3

Figure 3Configuration Port Selection Screen

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Figure 4

Figure 4Flight 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).

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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:


• 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).


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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 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.



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.

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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.


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


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.


• FLIGHT SOFTWARE PART NUMBER• FLIGHT SOFTWARE CRC• SYSTEM DATE AND TIME

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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:


• 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).


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.


Result:(1) The CONFIGURE PORT SELECTION SCREEN, Figure 3, comes into view on the laptop.

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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.


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.


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

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

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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).


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).

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(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 inch-pounds (2.8 - 3.4 N•m).

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Figure 5

Figure 5Loading 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.

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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 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.C.(1) above or the alternate loading instructions referenced in paragraph 3.C.(2). Identification plate location is shown in Figure 6.

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Figure 6

Figure 6Processor Board Identification Plate Location

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SERVICE BULLETIN EVALUATION

THE PURPOSE OF THIS FORM IS TO COLLECT DATA THAT WILL BE USED TO IMPROVE THE QUALITY OF OURSERVICE BULLETINS. PLEASE FILL IN FORM AND RETURN IT TO:

EMBRAER - EMPRESA BRASILEIRA DE AERONÁUTICA S.A.EFTC - SERVICE BULLETIN ENGINEERINGAV. BRIGADEIRO FARIA LIMA, 2170SÃO JOSÉ DOS CAMPOS - SP - 12227-901BRASILFax: + 55 12 3927-6600 (ext. 1624)e-mail: [email protected]

S.B. Title: S.B.: (Number / Rev.)

Operator:

SB Implementation ReportAircraft 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:


SB190-21-0041-REV.02 - AIR CONDITIONING - Regulations ...

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