Service Bulletin Flight Controls - General - Primary

BD500-270013

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Service BulletinFlight Controls - General - Primary FlightControl Computers (PFCCs) and RemoteElectronic Units (REUs) Software Update

BD500-270013Issue No. 003

Copyright © 2020 Airbus Canada Limited Partnership

All rights reserved. No part of this work may be reproduced or copied in any form or by any means without written permission of AirbusCanada Limited Partnership.

The Airbus and A220 logos are registered trademarks of Airbus Canada Limited Partnership.

The information, technical data and the designs disclosed herein are the exclusive property of Airbus Canada Limited Partnership orcontain proprietary rights of others and are not to be used or disclosed to others without the written consent of Airbus Canada LimitedPartnership. The recipient of this document, by its retention and use, agrees to hold in confidence the technical data and designs containedherein. The foregoing shall not apply to persons having proprietary rights to such information, technical data or such designs to the extentthat such rights exist.

Manufacturer:Airbus Canada Limited PartnershipCustomer Services13100 Henri-Fabre Blvd., Mirabel, QuebecCanada J7N 3C6

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Table of contentsThe listed documents are included in Issue 003, dated 2020-10-22, of this publication.

Document title Data module code Issue date Applicableto

Flight Controls - General - Primary FlightControl Computers (PFCCs) and RemoteElectronic Units (REUs) Software Update- Service Bulletin

BD500-A-J27-00-13-00AAA-930A-A 2020-10-22 50010-50018,50020-50055,55003-55016,55018-55068,55070-55084,55086-55087

Primary Flight Control Computers(PFCCs) and Remote Electronic Units(REUs) Software Update - Materialinformation

BD500-A-J27-00-13-01AAA-934A-A 2020-10-22 50010-50018,50020-50055,55003-55016,55018-55068,55070-55084,55086-55087

PART A - Primary Flight ControlComputers (PFCCs) and RemoteElectronic Units (REUs) Software UpdateWith VSB - Accomplishment instruction

BD500-A-J27-00-13-01AAA-933A-A 2020-10-22 50010-50018,50020-50055,55003-55016,55018-55068,55070-55084,55086-55087

PART B - Primary Flight ControlComputers (PFCCs) and RemoteElectronic Units (REUs) Software Updateon Aircraft - Accomplishment instruction

BD500-A-J27-00-13-02AAA-933A-A 2020-10-22 50010-50018,50020-50055,55003-55016,55018-55068,55070-55084,55086-55087

491100-27-003 - Parker Service Bulletin BD500-A-J27-00-13-01AAA-910B-A 2020-10-22 50010-50018,50020-50055,55003-55016,55018-55068,55070-55084,55086-55087

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See applicability on thefirst page of the DMBD500-A-J27-00-13-00AAA-930A-A

BD500-A-J27-00-13-00AAA-930A-A

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Flight Controls - General - Primary Flight Control Computers (PFCCs)and Remote Electronic Units (REUs) Software Update - Service Bulletin

Applicability: 50010-50018, 50020-50055, 55003-55016, 55018-55068, 55070-55084, 55086-55087

Table of contents Page

Flight Controls - General - Primary Flight Control Computers (PFCCs) and RemoteElectronic Units (REUs) Software Update - Service Bulletin.................................................... 1References................................................................................................................................ 1Service Bulletin.......................................................................................................................... 1Common information................................................................................................................. 11 Maintenance Publications........................................................................................... 82 Operational Publications............................................................................................. 8

List of tables Page

1 References.................................................................................................................. 1

ReferencesTable 1 References

Data Module/Technical Publication Title

BD500-A-J27-00-13-01AAA-934A-A Primary Flight Control Computers (PFCCs) and RemoteElectronic Units (REUs) Software Update - Materialinformation

BD500-A-J27-00-13-01AAA-933A-A PART A - Primary Flight Control Computers (PFCCs)and Remote Electronic Units (REUs) Software UpdateWith VSB - Accomplishment instruction

BD500-A-J27-00-13-02AAA-933A-A PART B - Primary Flight Control Computers (PFCCs)and Remote Electronic Units (REUs) Software Updateon Aircraft - Accomplishment instruction

Service Bulletin

Common informationTHIS SERVICE BULLETIN IS SENT TO EACH OPERATOR. IF THE OPERATOR HASLEASED AIRCRAFT, SEND THE SERVICE BULLETIN TO THE LESSEE. IF THE OPERATORHAS SOLD AIRCRAFT OR TRANSFERRED SPARES IN THE LAST SIX MONTHS, SENDTHIS SERVICE BULLETIN TO THE NEW OWNER, UNLESS CONFIRMATION WASRECEIVED THAT AIRBUS HAS INCLUDED THE NEW OPERATOR ON THE DISTRIBUTIONLIST.

Management informationCompliance category: Recommended (Service bulletin recommended to be accomplished toprevent significant operational disruptions)

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Task category: Software update

Original issue date: 2020-07-17

Impact listImpact (Maintenance publications):Refer to the Documentation affected section of the Planning Information section.

Accomplishment limitsNone

Replacement service bulletinNone

Revision informationRevision informationThe revision information letter transmits:

Issue 003 of Service Bulletin BD500-270013, dated 2020-10-22

Additional work

The changes in this revision have no effect on aircraft that have incorporated a previousissue of this service bulletin.

Revision reasonRevised the Summary Section:

To change the Concurrent requirement.

Revised the Planning information:

To change the Concurrent requirement.

Revised the Service Bulletin Referenced Documentation:

To update RSI C-500-000-27-0026 to Revision B

To update Modsum 500T100581 to Revision E

Revised the Accomplishment Instructions:

To change the upload instructions for IMS-6000 and IMS-6010.

This revision also includes small editorial changes that do not have an effect on the technicalcontent.

Revision historyIssue 001, dated 2020-07-17

Issue 002, dated 2020-09-01

Revision sequenceDiscard the copy of Service Bulletin BD500-270013, Issue 002, dated 2020-09-01. Replace withthe copy attached.

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SummaryApplicabilityBD-500-1A10, Aircraft 50010 thru 50018 and 50020 thru 50055

BD-500-1A11, Aircraft 55003 thru 55016, 55018 thru 55068, 55070 thru 55084, 55086 and55087

ReasonThe software of the Remote Electronic Units (REU) and Primary Flight Control Computers(PFCC) is updated to introduce new maintenance functionalities, and to address continuingairworthiness and system robustness issues.

DescriptionThis service bulletin is divided into two parts: PART A and PART B.

PART AThe aircraft is put in standard configuration for maintenance. The 10 REUs are removed fromthe aircraft. The REUs are returned to Parker and updated with the Parker Service Bulletin491100-27-003 section 3.A. The 10 REUs are installed in the aircraft. The software of the threePFCCs is updated with a procedure in this service bulletin. The rigging and return to servicetests are done.

PART BThe aircraft is put in standard configuration for maintenance. The software of the 10 REUs isupdated by the owner/operator on the aircraft with the procedures in this service bulletin andParker service bulletin 491100-27-003 section 3.B. The REUs are identified with a new partnumber. The software of the three PFCCs is updated with a procedure in this service bulletin.The rigging and return to service tests are done.

Concurrent requirementsFor PART A and PART B

On aircraft pre Service Bulletin BD500-314004, Indicating/Recording System - GeneralComputers - Integrated Modular Avionic Application (IMAA) Avionics Software V5.6

- The OMS Equation Table (OMSEQT) database, part number OMSEQT_2B0003_V008 orlater version, is a pre-requisite to this service bulletin.

- The OMS Test and Rigging (OMSTAR) database, part number OMSTAR_2B0003_V008 orlater version, is a pre-requisite to this service bulletin.

- For Aircraft 50010 thru 50017, 55003 thru 55016, 55018 thru 55036, and 55038 thru55043Service Bulletin BD500-314002, Indicating/Recording System - General Computers - Inte-grated Modular Avionic Application (IMAA) Software Change (Build 8.0A) is a pre-requisiteto this service bulletin.

On aircraft post Service Bulletin BD500-314004, Indicating/Recording System - GeneralComputers - Integrated Modular Avionic Application (IMAA) Avionics Software V5.6


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For PART B

- For Aircraft 50010 thru 50017, and 55003 thru 55042Service Bulletin BD500-270010, Flight Controls - General - Replacement of the RemoteElectronic Unit (REU) is a pre-requisite to PART B of this service bulletin.

ManpowerIt will take an estimated 18.0 h to complete PART A of this service bulletin.

It will take an estimated 18.0 h to complete PART B of this service bulletin.

Material informationRefer to BD500-A-J27-00-13-01AAA-934A-A.

Planning informationApplicabilityAircraft affected:

AIRCRAFT MODEL SERVICE AIRCRAFT SERIALNUMBER

PRODUCTION AIRCRAFTSERIAL NUMBERS

BD-500-1A10 50010 thru 50018 and 50020 thru50055

50001 thru 50009, 50019, and50056 and subsequent serialnumbers 1

BD-500-1A11 55003 thru 55016, 55018 thru55068, 55070 thru 55084, 55086and 55087

55001, 55002, 55017, 55069,55085, and 55088 and subse-quent serial numbers 1.

1 Aircraft will have an equivalent modification incorporated before delivery.

NoteThe instructions in this service bulletin are only applicable to the systems and partsinstalled at the time of delivery of the aircraft or as changed by Airbus Service Bulletins.Before you do this service bulletin, examine all Supplemental Type Certificates (STCs),Supplemental Type Approvals (STAs), or equivalent action changes to make sure that youcan complete this service bulletin.

ReasonProblem and effect

The software of the REUs and PFCCs is updated to introduce new maintenance functionalities,and to address continuing airworthiness and system robustness issues.

Objective/Solution

This service bulletin gives the instruction to replace or update the REU software, and update thePFCC software to add new maintenance functions, and address the issues that follow:

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- Quick rigging- Auto rigging- Initiated built-in test- Update to basic rigging- OMS reporting- ABIT/PBIT update and fixes- Monitoring updates- NVM download/storage/clear updates- Fault/Config reporting fixes- ISM updates- AFCU monitoring- Normal mode control laws

The modification will improve the continuing airworthiness and system robustness.

DescriptionThis service bulletin is divided into two parts: PART A and PART B.

PART AThe aircraft is put in standard configuration for maintenance. The 10 REUs are removed fromthe aircraft. The REUs are returned to Parker and updated with the Parker Service Bulletin491100-27-003 section 3.A. The 10 REUs are installed in the aircraft. The software of the threePFCCs is updated with a procedure in this service bulletin. The rigging and return to servicetests are done.

PART BThe aircraft is put in standard configuration for maintenance. The software of the 10 REUs isupdated by the owner/operator on the aircraft with the procedures in this service bulletin andParker service bulletin 491100-27-003 section 3.B. The REUs are identified with a new partnumber. The software of the three PFCCs is updated with a procedure in this service bulletin.The rigging and return to service tests are done.

ComplianceRecommended Service Bulletin

Airbus recommends that PART A or PART B of this service bulletin be done before the aircrafthas 12000 flight hours or at no more than 9350 flight hours or 56 months, whichever comes first,from the initial release date of the service bulletin unless otherwise directed by the airworthinessauthority of the operator.

NoteIf it is not possible to complete all the instructions in this service bulletin because ofthe configuration of the aircraft, speak with a CRC representative at 1-866-A220-CRC(1-866-222-0272) or 1-450-476-7676 or e-mail at [email protected] for analysis and toget an approved disposition to complete this service bulletin.

Concurrent requirementsFor PART A and PART B

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On aircraft pre Service Bulletin BD500-314004, Indicating/Recording System - GeneralComputers - Integrated Modular Avionic Application (IMAA) Avionics Software V5.6



- For Aircraft 50010 thru 50017, 55003 thru 55016, 55018 thru 55036, and 55038 thru55043Service Bulletin BD500-314002, Indicating/Recording System - General Computers - Inte-grated Modular Avionic Application (IMAA) Software Change (Build 8.0A) is a pre-requisiteto this service bulletin.

On aircraft post Service Bulletin BD500-314004, Indicating/Recording System - GeneralComputers - Integrated Modular Avionic Application (IMAA) Avionics Software V5.6



For PART B

- For Aircraft 50010 thru 50017, and 55003 thru 55042Service Bulletin BD500-270010, Flight Controls - General - Replacement of the RemoteElectronic Unit (REU) is a pre-requisite to PART B of this service bulletin.

ApprovalThe technical content of this service bulletin has been approved under the authority of the TC-CA Design Approval Organization No: DAO #19-Q-02.

ManpowerThe man-hours given below are estimates for direct labor done by an experienced crew on anaircraft prepared for maintenance.

These estimates do not include the time necessary for:

- Administrative functions such as planning, liaising, familiarization, and report writing.- Non-productive elapsed time such as rest time, having meals, and crew shift changes.- Elapsed time such as for paint to dry, sealant to cure, and fuel tank venting.- Preparation for modification (unless specified in the Accomplishment Instructions) such as

cleaning and getting parts, tools, consumables, and ground equipment.- Quality assurance inspections, troubleshooting and/or correction of discrepancies found

when a task is done.- All other activities that are not considered by Airbus as directly related to the accomplish-

ment of this procedure.

It will take an estimated 18.0 h to complete PART A of this service bulletin. The man-hours aredivided as shown in the table that follows:

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TASK MAN-HOURS

Job Set-Up 1.0 h

Procedure 8.0 h

Test 8.0 h

Job Close-Up 1.0 h

NoteThese estimates do not include the man-hours necessary to do Parker Service Bulletin491100-27-003.

It will take an estimated 18.0 h to complete PART B of this service bulletin. The man-hours aredivided as shown in the table that follows:

TASK MAN-HOURS

Job Set-Up 1.0 h

Procedure 8.0 h

Test 8.0 h

Job Close-Up 1.0 h

NoteThe estimated time for PART B can be reduced to 12.0 man-hours if the service bulletin isperformed as follows:- Use two Close Box Programmer (CBP) tools and two REU software CDs.- REU identification plate modification is performed in parallel with REU software

upload.- All three PFCCs are uploaded simultaneously on aircraft with IMS-6010 and above.- PFCCs are uploaded in parallel of REU upgrade.

Weight and balanceNot changed

Electrical load dataNot changed

Referenced documentationRefer to the SB Introduction document BD500-000000 for definition or explanation of servicebulletin content.

For Airbus reference only: Restriction and/or Special Instruction RSI C-500-000-27-0026,Revision B

Modification Summary 500T100581, Revision E

Parker Service Bulletin 491100-27-003 Dated Jul 10, 2020

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For Airbus reference only: PCR 42008

Documentation affected1 Maintenance PublicationsAircraft Maintenance Procedure (AMP)

Illustrated Parts Data Publication (IPDP)

Airworthiness Limitation (AWL)

2 Operational PublicationsAirplane Flight Manual (AFM)

Industry support informationFor on-site labor assistance, please speak with a CRC representative at 1-866-A220-CRC(1-866-222-0272) or 1-450-476-7676 or e-mail at [email protected].

Material informationBD500-A-J27-00-13-01AAA-934A-A.

Accomplishment instructionsFor PART A refer to BD500-A-J27-00-13-01AAA-933A-A.

For PART B refer to BD500-A-J27-00-13-02AAA-933A-A.

Additional informationNone

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Primary Flight Control Computers (PFCCs) and RemoteElectronic Units (REUs) Software Update - Material information

Applicability: 50010-50018, 50020-50055, 55003-55016, 55018-55068, 55070-55084, 55086-55087


Primary Flight Control Computers (PFCCs) and Remote Electronic Units (REUs) SoftwareUpdate - Material information................................................................................................... 1References................................................................................................................................ 1Service Bulletin.......................................................................................................................... 1

List of tables Page

1 References.................................................................................................................. 1



None

Service Bulletin

Material set listNo information

Support equipment listThe support equipment in the table that follows is necessary to complete this service bulletin;

For PART A or PART B

Individual support equipment:

Part number[Mfg. code]

Name Quantity Remarks

Commercially available USB memory stick 1 USB 2.0, FAT32, 8GB(minimum)

For PART BThe support equipment in the table that follows is available from Satair:

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Individual support equipment:



491100TF50-1001 Close Box Programmer (CBP) A/R To minimize groundtime multiple REUC05500026-007can be uploaded atthe same time. Foreach additional REUuploaded in parallel anew kit is required. (I.E.to upload four REUs atthe same time, four CBPtools and four REU CDsare required).

Procurement information:Procurement address:

Name: For customers based in the AmericasBusiness unit:Business unit name: Satair USA, Inc525 Westpark Drive, Suite 400Peachtree City, GA 30269United States of AmericaFor tool lease and repair: [email protected] tool purchase, please contact your Customer Order Specialisthttps:/www.satair.com/market/search

Name: For customers based in Europe, Middle East, AfricaBusiness unit:Business unit name: Satair A/SAmager Landevej 147A2770 KastrupDenmarkFor tool lease and repair: [email protected] tool purchase, please contact your Customer Order Specialisthttps:/www.satair.com/market/search

Name: For customers based in the Asia Pacific (excluding mainland China)Business unit:Business unit name: Satair Pte Ltd12 Seletar Aerospace LinkSingapore 797553The Republic of SingaporeFor tool lease and repair: [email protected] tool purchase, please contact your Customer Order Specialisthttps:/www.satair.com/market/search

Name: For customers based in mainland ChinaBusiness unit:Business unit name: Satair (Beijing) Co. LtdTian Zhu Lu 8, Tianzhu Airport Industrial ZoneBeijing 101312

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People’s Republic of ChinaFor tool lease and repair: [email protected] tool purchase, please contact your Customer Order Specialisthttps:/www.satair.com/market/search

Supplies listThere are no supplies for this service bulletin.

Spares listFor PART A or PART BWhen ordered the below listed software file is found on the A220World.airbus.com portal→ FlightLink → My LSAP → Field Loadable Software.

NoteLoad the PFCC software on USB key.

NoteLocate the folder “1“ and copy only the path “...\DLUR\load“ on the USB key.

Individual spare:



810-0337-007[0EFD0]

Software, PFCC Application 3

Procurement information:Procurement address:

Name: For customers based in the AmericasBusiness unit:Business unit name: Satair USA, Inc525 Westpark Drive, Suite 400Peachtree City, GA 30269United States of AmericaPh.: 1 404 675 6333Please contact your Customer Order Specialisthttps:/www.satair.com/market/searchCPHSB7X

Name: For customers based in Europe, Middle East, AfricaBusiness unit:Business unit name: Satair A/SAmager Landevej 147A2770 KastrupDenmarkPh.: 45 3247 0100Please contact your Customer Order Specialisthttps:/www.satair.com/market/searchCPHSB7X

Name: For customers based in the Asia Pacific (excluding mainland China)Business unit:

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Business unit name: Satair Pte Ltd12 Seletar Aerospace LinkSingapore 797553The Republic of SingaporePh.: 65 6543 0977Please contact your Customer Order Specialisthttps:/www.satair.com/market/searchCPHSB7X

Name: For customers based in mainland ChinaBusiness unit:Business unit name: Satair (Beijing) Co. LtdTian Zhu Lu 8, Tianzhu Airport Industrial ZoneBeijing 101312People’s Republic of ChinaPh.: 86 10 8048 6161Please contact your Customer Order Specialisthttps:/www.satair.com/market/searchCPHSB7XFor PART BRefer to Parker Service Bulletin 491100-27-003.

Removed spares listFor PART A or PART B

Individual removed spare:

Pre-SBPart number[Mfg. code]

Name Qty Usage Post-SBPart number[Mfg. code]

Description(Repl. condition)[Repl. code]

810-0337-002 or810-0337-003 or810-0337-004 or810-0337-005[0EFD0]

Software, PFCCApplication

3 Discarded 810-0337-007[0EFD0]

[Refer to IPDP]

NoteFor PART A, the REU are updated by Parker with Service Bulletin 491100-27-003,Section 3.A, to modify the REU part number from C05500026-003 (VPN 491100-1007),or C05500026-005 (VPN 491100-1009) or C05500026-007 (VPN 491100-1011) toC05500026-009 (VPN 491100-1013).

For PART A

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C05500026-003(VPN 491100-1007)or C05500026-005(VPN 491100-1009)or C05500026-007(VPN 491100-1011)[82106]

REU 10 Modified.Refer toVendorServiceBulletin

C05500026-009(VPN 491100-1013)[82106]

NoteFor PART B, the REU are updated on aircraft by the customer with Parker Service Bulletin491100-27-003, Section 3.B, to modify the REU part number from C05500026-007 (VPN491100-1011) to C05500026-009 (VPN 491100-1013).

For PART B





C05500026-007(VPN 491100-1011)[82106]

REU 10 Modified.Refer toVendorServiceBulletin

C05500026-009(VPN 491100-1013)[82106]

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PART A - Primary Flight Control Computers (PFCCs)and Remote Electronic Units (REUs) Software

Update With VSB - Accomplishment instruction Applicability: 50010-50018, 50020-50055, 55003-55016, 55018-55068, 55070-55084, 55086-55087


PART A - Primary Flight Control Computers (PFCCs) and Remote Electronic Units (REUs)Software Update With VSB - Accomplishment instruction....................................................... 1References................................................................................................................................ 1Preliminary requirements.......................................................................................................... 4Procedure.................................................................................................................................. 41 Job set-up................................................................................................................... 42 Procedure.................................................................................................................... 63 Job close-up................................................................................................................ 304 Administrative.............................................................................................................. 30Requirements after job completion........................................................................................... 31

List of tables Page

1 References.................................................................................................................. 12 Required conditions.................................................................................................... 43 Support equipment...................................................................................................... 44 Consumables, materials, and expendables................................................................ 45 Spares......................................................................................................................... 46 Required conditions.................................................................................................... 31

List of figures Page

1 Inboard Aileron REU................................................................................................... 102 Outboard aileron REU................................................................................................ 113 AFT REU No. 1 and No. 4......................................................................................... 124 AFT REU No. 2 and No. 3......................................................................................... 135 MFS REU No. 1, No. 3 and No. 4............................................................................. 146 MFS REU No. 2......................................................................................................... 16



BD500-A-J12-00-00-01AAA-398A-A Standard configuration for maintenance - Aircraftsystem configuration

BD500-A-J24-00-00-01AAA-913G-A Electrical/Electronic safety precautions - Generalmaintenance safety procedure

BD500-A-J24-00-00-04AAA-398D-A Thermal circuit breaker opening - Circuit breakeroperation

BD500-A-J24-00-00-07AAA-398D-A Circuit Protection Device (CPD) opening - Circuitbreaker operation

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BD500-A-J24-00-00-05AAA-398D-A Electronic circuit breaker opening from IN to OUT -Circuit breaker operation

BD500-A-J52-43-00-01AAA-540A-A Mid avionics compartment door - Open for accessprocedure

BD500-A-J52-47-03-01AAA-540A-A Wing To Body Fairing (WTBF) servicing doors - Openfor access procedure

BD500-A-J52-44-00-01AAA-540A-A Aft equipment compartment door - Open for accessprocedure

BD500-A-J27-04-33-01AAA-520A-A Aileron Remote Electronics Unit (REU) - Removeprocedure

BD500-A-J27-04-33-01AAA-720A-A Aileron Remote Electronics Unit (REU) - Installprocedure

BD500-A-J27-04-35-01AAA-520A-A Aft Remote Electronics Unit (REU) - Remove procedure

BD500-A-J27-04-35-01AAA-720A-A Aft Remote Electronics Unit (REU) - Install procedure

BD500-A-J27-04-31-01AAA-520A-A Multi-function spoiler Remote Electronics Unit (REU) -Remove procedure

BD500-A-J27-04-31-01AAA-720A-A Multi-function spoiler Remote Electronics Unit (REU) -Install procedure

BD500-A-J46-15-00-01AAA-C21A-A Software configuration verification - System monitoring

BD500-A-J24-00-00-08AAA-398D-A Thermal circuit breaker closing - Circuit breakeroperation

BD500-A-J24-00-00-11AAA-398D-A Circuit Protection Device (CPD) closing - Circuitbreaker operation

BD500-A-J46-15-01-02AAA-752A-A Transfer the Universal Serial Bus (USB) memory stickdata to the Information Management System (IMS) unit- Data loading

BD500-A-J45-45-00-03AAA-C21A-A Access to perform Line Replaceable Unit (LRU)/systemoperation - System monitoring

BD500-A-J24-00-00-10AAA-398D-A Electronic circuit breaker closing from OUT to IN -Circuit breaker operation

BD500-A-J27-41-01-01AAA-275B-A Horizontal Stabilizer Trim Actuator (HSTA) - Electricalrigging

BD500-A-J27-64-01-01AAA-275B-A Left multi-Function Spoiler (MFS) No. 1 surface rigging- Electrical rigging

BD500-A-J27-64-00-00AAA-396A-A Multi-Function Spoiler (MFS) Travel Check - Flightcontrol surface movement

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BD500-A-J27-64-01-02AAA-275B-A Right multi-Function Spoiler (MFS) No. 1 surfacerigging - Electrical rigging



BD500-A-J27-64-01-05AAA-275B-A Left Multi-Function Spoiler (MFS) No. 3 surface rigging- Electrical rigging

BD500-A-J27-64-01-06AAA-275B-A Right Multi-Function Spoiler (MFS) No. 3 surfacerigging - Electrical rigging



BD500-A-J27-04-31-01AAA-275B-A OMS rigging - Remote Electronics Unit (REU) quickrigging - Electrical rigging

BD500-A-J27-04-00-01AAA-343A-A Electronic Flight Control System (FCS) - BIT

BD500-A-J27-04-00-02AAA-343A-A Actuation Flight Control System (FCS) - BIT

BD500-A-J27-04-35-01AAA-552A-A Aft Remote Electronics Unit (REU) Non-VolatileMemory (NVM) - Data erasing

BD500-A-J27-04-33-01AAA-552A-A Aileron Remote Electronics Unit (REU) Non-VolatileMemory (NVM) - Data erasing

BD500-A-J27-04-31-01AAA-552A-A Multi-function spoiler Remote Electronics Unit (REU)Non-Volatile Memory (NVM) - Data erasing

BD500-A-J27-41-03-01AAA-552A-A Horizontal Stabilizer Motor Control Electronics (MCE)unit Non-Volatile Memory (NVM) - Data erasing

BD500-A-J27-04-05-01AAA-552A-A Primary Flight Control Computer (PFCC) Non-VolatileMemory (NVM) - Data erasing

BD500-A-J52-47-03-01AAA-740A-A Wing To Body Fairing (WTBF) servicing doors - Closeafter access procedure

BD500-A-J52-43-00-01AAA-740A-A Mid avionics compartment door - Close after accessprocedure

BD500-A-J52-44-00-01AAA-740A-A Aft equipment compartment door - Close after accessprocedure

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Preliminary requirements

Required conditions

Table 2 Required conditions

Action/Condition Data Module/Technical publication

None

Support equipment

Table 3 Support equipment

Name Identification/Reference Quantity Remark

None

Consumables, materials, and expendables

Table 4 Consumables, materials, and expendables


None

Spares

Table 5 Spares


None

Safety conditionsNone

Procedure1 Job set-up

NoteThe steps in the Job set-up section of this service bulletin are recommendedsteps. The steps give a recommendation to get access to the work area. This

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recommendation is to give a safe work area and to minimize possible damage tosurrounding aircraft parts. Alternative steps can be used at the discretion of theoperator.

1.1 From the web site address A220World.airbus.com portal → FlightLink → MyLSAPs → Field Loadable Software do as follows:1.1.1 Download the PFCC software P/N 810-0337-007 and unzip the file.

1.1.2 Expand the folder and copy only the folder 1 located in path "...\DLUR\load\", on a formatted Universal Serial Bus (USB) memory stick.

1.2 Make sure that the aircraft is in standard configuration for maintenance (refer toAMP BD500-A-J12-00-00-01AAA-398A-A).

1.3 Obey all the electrical/electronic safety precautions (refer to AMP BD500-A-J24-00-00-01AAA-913G-A).

1.4 Make sure that the thermal circuit breakers that follow are open (refer to AMPBD500-A-J24-00-00-04AAA-398D-A):

NAME CB NUMBER/LOCATION

REU INBD AIL PRI L-CBP-A3

REU INBD AIL SEC L-CBP-A4

REU AFT 2 PRI L-CBP-B1

REU AFT 2 SEC L-CBP-B2



REU MFS 2 PRI L-CBP-A1

REU MFS 2 SEC L-CBP-A2

1.5 Make sure that the toggle switch is set to the DISABLE position for theCircuit Protection Devices (CPD) that follow (refer to AMP BD500-A-J24-00-00-07AAA-398D-A):


REU OUTBD AIL R-FBWPC-3

REU AFT 1 PRI L-FBWPC-4

REU AFT 4 R-FBWPC-4

REU MFS 1 L-FBWPC-2

REU MFS 3 L-FBWPC-3

REU MFS 4 R-FBWPC-2

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1.6 Make sure that the electronic circuit breaker that follows is OUT on the CBsynoptic page (refer to AMP BD500-A-J24-00-00-05AAA-398D-A):


REU AFT 1 SEC CDC1-8-3

1.7 Open the mid avionics compartment door 812 (refer to AMP BD500-A-J52-43-00-01AAA-540A-A).

1.8 Open the mid avionics compartment access door (195AB) (refer to AMPBD500-A-J52-47-03-01AAA-540A-A).

1.9 Open the Landing Gear Control Valve (LGCV) door (195BB) (refer to AMPBD500-A-J52-47-03-01AAA-540A-A).

1.10 Open the Wing To Body Fairing (WTBF) hydraulic servicing door (196CB) (referto AMP BD500-A-J52-47-03-01AAA-540A-A).

1.11 Open the aft equipment compartment door (refer to AMP BD500-A-J52-44-00-01AAA-540A-A).

2 Procedure2.1 If it is not possible to complete all the instructions in this service bulletin

because of the configuration of the aircraft, speak with a CRC representativeat 1 866 A220 CRC (1-866-222-0272) or 1-450-476-7676 or e-mail [email protected] for analysis and to get an approved disposition tocomplete this service bulletin.

2.2 Update the 10 Remote Electronic Units (REUs) as follows:

NoteParker Service Bulletin 491100-27-002 does the upgrade of the REUsfrom P/N C05500026-003 or C05500026-005 to P/N C05500026-007.

NoteParker Service Bulletin 491100-27-003 does the upgrade of the REUsfrom P/N C05500026-007 to P/N C05500026-009.

NoteIt is possible that Flight Control System (FCS) related EICAS, INFOand OMS messages will be posted during the update of the REUs. Donot do the troubleshooting of these message at this time.

NoteIt is possible to do the PFCC software upload from Step 2.3 to Step 2.6in parallel with the upgrade of the REUs, if all the REU circuit breakersare de-energized before the PFCC software is loaded.

2.2.1 For the inboard aileron REU, do as follows:Refer to Fig. 12.2.1.1 Remove the inboard aileron REU P/N C05500026-003

or C05500026-005 or C05500026-007 (refer to AMPBD500-A-J27-04-33-01AAA-520A-A).

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2.2.1.2 Install the inboard aileron REU P/N C05500026-009(refer to AMP BD500-A-J27-04-33-01AAA-720A-A).

NoteThe rigging and Return to Service (RTS) test is notnecessary at this time.

2.2.2 For the outboard aileron REU, do as follows:Refer to Fig. 22.2.2.1 Remove the outboard aileron REU P/N C05500026-003


2.2.2.2 Install the outboard aileron REU P/N C05500026-009(refer to AMP BD500-A-J27-04-33-01AAA-720A-A).


2.2.3 For the AFT REU No. 1, do as follows:Refer to Fig. 32.2.3.1 Remove the AFT REU No. 1, P/N C05500026-003


2.2.3.2 Install the AFT REU No. 1, P/N C05500026-009 (refer toAMP BD500-A-J27-04-35-01AAA-720A-A).








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2.2.7 For the Multi-Function Spoiler (MFS) No. 1 REU, do as follows:Refer to Fig. 52.2.7.1 Remove the MFS No. 1 REU, P/N C05500026-003


2.2.7.2 Install the MFS No. 1 REU, P/N C05500026-009 (refer toAMP BD500-A-J27-04-31-01AAA-720A-A).


2.2.8 For the MFS No. 2 REU, do as follows:Refer to Fig. 62.2.8.1 Remove the MFS No. 2 REU, P/N C05500026-003






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1 INBOARD AILERON REU

NOTES

On aircraft 50010-50017, 55003-55016 and 55018-55042 Pre-SB BD500-270010.1

2

LEGEND

1. Remote Electronic UnitC05500026-003 or C05500026-005 (Pre-mod)C05500026-007 (Pre-Mod)C05500026-009 (Post-Mod)

1

2 On aircraft 50010-50017, 55003-55016 and 55018-55042 Post-SB BD500-270010 and aircraft 50018,50020-50055, 55043-55068, 55070-55084, and 55086-55087.

ICN-BD500-A-J270013-F-3AB48-60324-A-001-01Figure 1 Inboard Aileron REU

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1

OUTBOARD AILERON REU

NOTES


2

LEGEND


1


ICN-BD500-A-J270013-F-3AB48-60325-A-001-01Figure 2 Outboard aileron REU

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1

1

AFT REU NO. 1

AFT REU NO. 4

NOTES


2

LEGEND


1


ICN-BD500-A-J270013-F-3AB48-60326-A-001-01Figure 3 AFT REU No. 1 and No. 4

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1

1AFT REU NO. 3

AFT REU NO. 2

NOTES


2

LEGEND


1



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1

MFS REU NO.1

MFS REU NO.1

1

3

2

LEGEND


1

4

MFS REU NO.1

1

NOTES


On aircraft 50010-50018.3On aircraft 50020-50055, 55043-55068, 55070-55084, and 55086-55087.4


ICN-BD500-A-J270013-F-3AB48-60322-A-001-01Figure 5 MFS REU No. 1, No. 3 and No. 4 - (Sheet 1 of 2)

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1

1

MFS REU NO.3

MFS REU NO.4

2

LEGEND


1

MFS REU NO.31

MFS REU NO.4

1

NOTES

On aircraft 50010-50017, 55003-55016 and 55018-55042 Pre-SB BD500-270010.12 On aircraft 50010-50017, 55003-55016 and 55018-55042 Post-SB BD500-270010 and aircraft 50018,

50020-50055, 55043-55068, 55070-55084, and 55086-55087.

ICN-BD500-A-J270013-F-3AB48-61439-A-001-01Figure 5 MFS REU No. 1, No. 3 and No. 4 - (Sheet 2 of 2)

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1

MFS REU NO.2

NOTES


2

LEGEND


1


ICN-BD500-A-J270013-F-3AB48-60323-A-001-01Figure 6 MFS REU No. 2

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2.3 Do the software configuration verification system monitoring to confirm the IMSversion (refer to AMP BD500-A-J46-15-00-01AAA-C21A-A).

NoteThe procedure for the upgrade of the PFCC is dependent on theInformation Management System (IMS) version installed on the aircraft.

2.4 For aircraft with IMS-6010 and aboveDo the PFCC update as follows:

NoteThe PFCC software upgrade can be done simultaneously by making surethat all PFCCs are selected ON. The time necessary to upload all threePFCCs simultaneously is approximately 45 minutes.

2.4.1 Make sure that the thermal circuit breaker that follows is closed (referto AMP BD500-A-J24-00-00-08AAA-398D-A):


PFCC 3 L-CBP-B5

2.4.2 Make sure that the toggle switch is set to the ENABLE position forthe electronic circuit breakers that follow (refer to AMP BD500-A-J24-00-00-11AAA-398D-A):


PFCC 1 L-FBWPC-5

PFCC 2 R-FBWPC-5

2.4.3 Make sure that the PFCC 1, PFCC 2 and PFCC 3 Push ButtonAnnunciator (PBA) lights are off.

2.4.4 Transfer the Universal Serial Bus (USB) memory stick data to theInformation Management System (IMS) unit (refer to AMP BD500-A-J46-15-01-02AAA-752A-A).

NoteTransfer only folder “1“ located in path “...\DLUR\load\“.

2.4.5 Load the PFCC software per the IMS version installed on the aircraftas follows:2.4.5.1 On the cockpit maintenance panel (pilot-side bulkhead),

set the AIRCRAFT switch to the UPLOAD position andthe CHAN switch to the A position.

2.4.5.2 On the Cursor Control Panel (CCP), push the MENUpushbutton.2.4.5.2.1 Make sure that the main menu is shown

on the Adaptive Flight Display (AFD).

2.4.5.3 From the main menu, select DATA.

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2.4.5.3.1 Make sure that the dataload submenu isshown.

2.4.5.4 From the dataload submenu, select DATALOAD.2.4.5.4.1 Make sure that the Load New Databases

page is shown.

2.4.5.5 From the Load New Databases page, selectMAINTENANCE DATA LOAD.2.4.5.5.1 Make sure that the Maintenance Data

Load Password page is shown.

2.4.5.6 Move the cursor into the password box and then pushselect button.2.4.5.6.1 Make sure that the password box is

active (cyan).

2.4.5.7 Use the Multifunction Keyboard Panel (MKP) to enter thepassword MAINT in the Enter Password box, and thenpush ENTER.2.4.5.7.1 Make sure that the Maintenance Data

Load Menu page is shown.

2.4.5.8 With the CCP, select Load New Documents & Tablesfrom the Maintenance Data Load Menu page.2.4.5.8.1 Make sure that the Load New Documents

& Tables page is shown.

NoteA check mark is automatically shownin front of all documents, tables, andsoftware.

2.4.5.9 Remove the selection from all documents, tables, andsoftware that are not necessary.2.4.5.9.1 Make sure that a check mark (cyan) is

shown in front of the document, table, orsoftware that you will load.

2.4.6 Select Start Load.

NoteFor aircraft with IMS-6010, an automatic electronic FCS testwill be initiated after two of the three PFCCs have finished thesoftware installation. Wait until the FLT CTRL advisory CASmessage has cleared before you do the next step. It is possibleat this point that the electronic FCS test will fail and FCS relatedEICAS, info and OMS messages will be posted. Do not do thetroubleshooting of these messages at this time.

2.4.7 For aircraft with IMS-6010 and above, after the upgrade of the PFCCsis completed, do the software configuration check in Step 2.6.

2.5 For aircraft with IMS-6000

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Do the PFCC updates as follows:

NoteFor aircraft with IMS-6000, the PFCC software upgrade must be done onePFCC at a time by making sure that the PFCC to upgrade is selected ONand the other PFCCs are selected OFF. The time required to upload eachPFCC is approximately 45 minutes.


NoteTransfer only folder 1 located in path ...\DLUR\load\.

2.5.2 Load PFCC 1 software as follows:2.5.2.1 Make sure that the toggle switch is set to the ENABLE

position for the electronic circuit breaker that follows(refer to AMP BD500-A-J24-00-00-11AAA-398D-A):


PFCC 1 L-FBWPC-5

2.5.2.2 Make sure that the toggle switch is set to the DISABLEposition for the electronic circuit breaker that follows(refer to AMP BD500-A-J24-00-00-07AAA-398D-A):


PFCC 2 R-FBWPC-5

2.5.2.3 Make sure that the thermal circuit breaker that follows isopen (refer to AMP BD500-A-J24-00-00-04AAA-398D-A):


PFCC 3 L-CBP-B5

2.5.2.4 Make sure that the PFCC 1 is selected ON, and the PBAlight is off.

2.5.2.5 On the cockpit maintenance panel (pilot-side bulkhead),set the AIRCRAFT switch to the UPLOAD position andthe CHAN switch to the A position.


on the AFD.

2.5.2.7 From the main menu, select DATA.2.5.2.7.1 Make sure that the dataload submenu is

shown.

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page is shown.



2.5.2.10 Move the cursor into the password box and then push theselect button.2.5.2.10.1 Make sure that the password box is

active (cyan).

2.5.2.11 Use the Multifunction Keyboard Panel (MKP) to enter thepassword MAINT in the Enter Password data field, andthen push ENTER.2.5.2.11.1 Make sure that the Maintenance Data







2.5.2.14 Select Start Load.

NoteFor aircraft with IMS-6000, when PFCC 1 completesthe upload, the message “LOAD COMPLETE WITHERRORS“ will be displayed. When you click onView Errors, the status of all three PFCCs will bedisplayed (PFCC 1 will indicate LOAD COMPLETEand PFCC 2 and PFCC 3 will indicate FAILED).

2.5.3 Load PFCC 2 software as follows:2.5.3.1 Make sure that the toggle switch is set to the DISABLE


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PFCC 1 L-FBWPC-5

2.5.3.2 Make sure that the toggle switch is set to the ENABLEposition for the electronic circuit breaker that follows(refer to AMP BD500-A-J24-00-00-11AAA-398D-A):


PFCC 2 R-FBWPC-5



PFCC 3 L-CBP-B5


2.5.3.5 On the Cursor Control Panel (CCP), select View Errors.2.5.3.5.1 Make sure that the Load Error Summary

page is shown.

2.5.3.6 On the Load Error Summary page, select “RETRYFAILED LOADS“ to start the loading of the PFCC 2.

NoteFor aircraft with IMS-6000, when PFCC 2 completesthe upload, the message “LOAD COMPLETE WITHERRORS“ will be displayed. When you click onView Errors, the status of all three PFCCs will bedisplayed (PFCC 1 and PFCC 2 will indicate LOADCOMPLETE and PFCC 3 will indicate FAILED).


position for the electronic circuit breakers that follow(refer to AMP BD500-A-J24-00-00-07AAA-398D-A):


PFCC 1 L-FBWPC-5

PFCC 2 R-FBWPC-5

2.5.4.2 Make sure that the thermal circuit breaker that follows isclosed (refer to AMP BD500-A-J24-00-00-08AAA-398D-A):

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PFCC 3 L-CBP-B5

2.5.4.3 Make sure that the PFCC 3 is selected ON, the PBA lightis off.


page is shown.


2.5.5 To proceed to the software configuration check, make sure that PFCC1, PFCC 2, and PFCC 3 are powered as follows:2.5.5.1 Make sure that the thermal circuit breaker that follows is

closed (refer to AMP BD500-A-J24-00-00-08AAA-398D-A):


PFCC 3 L-CBP-B5

2.5.5.2 Make sure that the toggle switch is set to the ENABLEposition for the electronic circuit breakers that follow(refer to AMP BD500-A-J24-00-00-11AAA-398D-A):


PFCC 1 L-FBWPC-5

PFCC 2 R-FBWPC-5

NoteFor aircraft with IMS-6000, because this will be thefirst time that two or more PFCCs are powered at thesame time since the software upload, an automaticelectronic FCS test will be initiated. Wait until theFLT CTRL IN TEST advisory CAS message hascleared before you do the next step. It is possible atthis point that the electronic FCS TEST will fail andFCS related EICAS, info, and OMS messages will beposted. Troubleshooting of these messages shouldnot be done at this time.

2.6 Do a software configuration check of PFCC 1, PFCC 2, and PFCC 3 as follows:2.6.1 Get the access to the OMS LRU/System Operations page (refer to

AMP BD500-A-J45-45-00-03AAA-C21A-A).

2.6.2 From the MAINT MENU, select LRU System Operations:- View ALL ATAs

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- Select ATA 27 - FLIGHT CONTROLS- Select LRU/System PFCC1

2.6.3 Select the Config/Status.

2.6.4 Make sure that the PFCC1 software P/N is 810-0337-007.

2.6.5 From the MAINT MENU, select LRU System Operations:- View ALL ATAs- Select ATA 27 - FLIGHT CONTROLS- Select LRU/System PFCC2






2.7 Make sure that the thermal circuit breakers that follow are closed (refer to AMPBD500-A-J24-00-00-08AAA-398D-A):










2.8 Make sure that the toggle switch is set to the ENABLE position for the electroniccircuit breakers that follow (refer to AMP BD500-A-J24-00-00-11AAA-398D-A):




REU AFT 4 R-FBWPC-4

REU MFS 1 L-FBWPC-2

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REU MFS 3 L-FBWPC-3

REU MFS 4 R-FBWPC-2

2.9 Make sure that the electronic circuit breaker that follows is IN on the CBsynoptic page (refer to AMP BD500-A-J24-00-00-10AAA-398D-A):



NoteIt is possible to have rigging faults at this time. Do not do thetroubleshooting at this time.

2.10 Get access to the Onboard Maintenance System (OMS) LRU/SystemOperations page to do the system monitoring of each of the 10 REUs as follows(refer to AMP BD500-A-J45-45-00-03AAA-C21A-A):2.10.1 From the Select ATA drop-down list, select ATA 27.

2.10.2 From the Select LRU/System drop-down list, select the REU thatfollows:

- AFT 1 REU

2.10.3 From the LRU/System Operations page, select the CONFIG tag.

2.10.4 Make sure that the selected REU part number and serial number areas shown in the table that follows:

REU PART AND SERIAL NUMBERS

BA PART NUMBER C05500026-009

PH PART NUMBER 491100-1013

SERIAL NUMBER VERIFY MATCHING REU NAMEPLATE


- AFT 2 REU






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- AFT 3 REU








- AFT 4 REU








- INBOARD AILERON REU






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- OUTBOARD AILERON REU








- MFS 1 REU








- MFS 2 REU






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- MFS 3 REU








- MFS 4 REU







NoteFrom this point forward, consider the aircraft as post SB BD500-270013when performing the AMP procedures in the steps that follow.

2.11 Do the post SB BD500-270013 modification test that follows:2.11.1 Do the Horizontal Stabilizer Trim Actuator (HSTA) rigging (refer to

AMP BD500-A-J27-41-01-01AAA-275B-A).

2.11.2 Do the left Multi-Function Spoiler (MFS) No. 1 rigging (refer to AMPBD500-A-J27-64-01-01AAA-275B-A).

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NoteThe MFS travel check is not required at this time, the left and rightMFS No. 1 must be rigged before you do the MFS travel checkper AMP BD500-A-J27-64-00-00AAA-396A-A.

2.11.3 Do the right Multi-Function Spoiler (MFS) No. 1 rigging (refer to AMPBD500-A-J27-64-01-02AAA-275B-A).

NoteIt is required to do the check on the left MFS No. 1 and onthe right MFS No. 1 surface with the flight spoiler control leveronly, when you do the MFS travel check per AMP BD500-A-J27-64-00-00AAA-396A-A.










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2.11.10 Do the AFT REU No. 1 Onboard Maintenance System (OMS) quickrigging (refer to AMP BD500-A-J27-04-31-01AAA-275B-A).

2.11.11 Do the AFT REU No. 2 OMS quick rigging (refer to AMP BD500-A-J27-04-31-01AAA-275B-A).



2.11.14 Do the inboard aileron REU OMS quick rigging (refer to AMP BD500-A-J27-04-31-01AAA-275B-A).

2.11.15 Do the outboard aileron REU OMS quick rigging (refer to AMP BD500-A-J27-04-31-01AAA-275B-A).

2.11.16 Do the electronic Flight Control System (FCS) test (refer to AMPBD500-A-J27-04-00-01AAA-343A-A).

2.11.17 Do the actuation FCS test (refer to AMP BD500-A-J27-04-00-02AAA-343A-A).

2.11.18 Do the electronic FCS test (refer to AMP BD500-A-J27-04-00-01AAA-343A-A).

NoteThe electronic FCS test is repeated to reset the latched riggingfaults after the actuation FCS test is done in Step 2.11.17.

2.11.19 Make sure that there are no FCS EICAS, INFO, or OMS messages.

NoteIf any message is displayed, do troubleshooting.

2.11.20 Clear the Non-Volatile Memory (NVM) of the AFT REU No. 1 (refer toAMP BD500-A-J27-04-35-01AAA-552A-A).

2.11.21 Clear the NVM of the AFT REU No. 2 (refer to AMP BD500-A-J27-04-35-01AAA-552A-A).


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2.11.24 Clear the NVM of the inboard aileron REU (refer to AMP BD500-A-J27-04-33-01AAA-552A-A).

2.11.25 Clear the NVM of the outboard aileron REU (refer to AMP BD500-A-J27-04-33-01AAA-552A-A).

2.11.26 Clear the NVM of the MFS REU No. 1 (refer to AMP BD500-A-J27-04-31-01AAA-552A-A).




2.11.30 Clear the NVM of the horizontal stabilizer Motor Control Electronics(MCE) unit (refer to AMP BD500-A-J27-41-03-01AAA-552A-A).

2.11.31 Clear the NVM of the PFCC No. 1 (refer to AMP BD500-A-J27-04-05-01AAA-552A-A).



3 Job close-up

NoteThe steps in the Job close-up section of this service bulletin, except for the return-to-service tests, are recommended steps. The steps give a recommendation toinstall components removed during the Job set-up. This recommendation is tomake sure that the aircraft is safe and ready to return to service. Alternative stepscan be used at the discretion of the operator.

3.1 Remove all tools, equipment, and unwanted materials from the work area.

3.2 Close the LGCV door (195BB) (refer to AMP BD500-A-J52-47-03-01AAA-740A-A).

3.3 Close the mid avionics compartment access door (195AB) (refer to AMPBD500-A-J52-47-03-01AAA-740A-A).

3.4 Close the mid avionics compartment door 812 (refer to AMP BD500-A-J52-43-00-01AAA-740A-A).

3.5 Close the WTBF hydraulic servicing door (196CB) (refer to AMP BD500-A-J52-47-03-01AAA-740A-A).

3.6 Close the aft equipment compartment door (refer to AMP BD500-A-J52-44-00-01AAA-740A-A).

4 AdministrativeWhen Part A of this service bulletin is completed, record in the applicable aircraftrecords that you have completed Part A of this service bulletin.

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Requirements after job completionRequired conditions



None

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PART B - Primary Flight Control Computers (PFCCs)and Remote Electronic Units (REUs) Software

Update on Aircraft - Accomplishment instruction Applicability: 50010-50018, 50020-50055, 55003-55016, 55018-55068, 55070-55084, 55086-55087


PART B - Primary Flight Control Computers (PFCCs) and Remote Electronic Units (REUs)Software Update on Aircraft - Accomplishment instruction...................................................... 1References................................................................................................................................ 1Preliminary requirements.......................................................................................................... 3Procedure.................................................................................................................................. 41 Job set-up................................................................................................................... 42 Procedure.................................................................................................................... 63 Job close-up................................................................................................................ 284 Administrative.............................................................................................................. 28Requirements after job completion........................................................................................... 28

List of tables Page

1 References.................................................................................................................. 12 Required conditions.................................................................................................... 33 Support equipment...................................................................................................... 44 Consumables, materials, and expendables................................................................ 45 Spares......................................................................................................................... 46 Required conditions.................................................................................................... 28


1 Inboard aileron REU................................................................................................... 82 MFS REU No. 2......................................................................................................... 93 MFS REU No. 3 and No. 4........................................................................................ 104 Outboard aileron REU................................................................................................ 115 MFS REU No. 1......................................................................................................... 126 AFT REU No. 2 and No. 3......................................................................................... 137 AFT REU No. 1 and No. 4......................................................................................... 14



BD500-A-J12-00-00-01AAA-398A-A Standard configuration for maintenance - Aircraftsystem configuration

BD500-A-J24-00-00-01AAA-913G-A Electrical/Electronic safety precautions - Generalmaintenance safety procedure

BD500-A-J24-00-00-04AAA-398D-A Thermal circuit breaker opening - Circuit breakeroperation

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BD500-A-J24-00-00-07AAA-398D-A Circuit Protection Device (CPD) opening - Circuitbreaker operation

BD500-A-J24-00-00-05AAA-398D-A Electronic circuit breaker opening from IN to OUT -Circuit breaker operation

BD500-A-J52-43-00-01AAA-540A-A Mid avionics compartment door - Open for accessprocedure

BD500-A-J52-47-03-01AAA-540A-A Wing To Body Fairing (WTBF) servicing doors - Openfor access procedure

BD500-A-J52-44-00-01AAA-540A-A Aft equipment compartment door - Open for accessprocedure

BD500-A-J46-15-00-01AAA-C21A-A Software configuration verification - System monitoring

BD500-A-J24-00-00-08AAA-398D-A Thermal circuit breaker closing - Circuit breakeroperation

BD500-A-J24-00-00-11AAA-398D-A Circuit Protection Device (CPD) closing - Circuitbreaker operation

BD500-A-J46-15-01-02AAA-752A-A Transfer the Universal Serial Bus (USB) memory stickdata to the Information Management System (IMS) unit- Data loading

BD500-A-J45-45-00-03AAA-C21A-A Access to perform Line Replaceable Unit (LRU)/systemoperation - System monitoring

BD500-A-J24-00-00-10AAA-398D-A Electronic circuit breaker closing from OUT to IN -Circuit breaker operation

BD500-A-J27-41-01-01AAA-275B-A Horizontal Stabilizer Trim Actuator (HSTA) - Electricalrigging


BD500-A-J27-64-00-00AAA-396A-A Multi-Function Spoiler (MFS) Travel Check - Flightcontrol surface movement





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BD500-A-J27-04-31-01AAA-275B-A OMS rigging - Remote Electronics Unit (REU) quickrigging - Electrical rigging

BD500-A-J27-04-00-01AAA-343A-A Electronic Flight Control System (FCS) - BIT

BD500-A-J27-04-00-02AAA-343A-A Actuation Flight Control System (FCS) - BIT

BD500-A-J27-04-35-01AAA-552A-A Aft Remote Electronics Unit (REU) Non-VolatileMemory (NVM) - Data erasing

BD500-A-J27-04-33-01AAA-552A-A Aileron Remote Electronics Unit (REU) Non-VolatileMemory (NVM) - Data erasing

BD500-A-J27-04-31-01AAA-552A-A Multi-function spoiler Remote Electronics Unit (REU)Non-Volatile Memory (NVM) - Data erasing

BD500-A-J27-41-03-01AAA-552A-A Horizontal Stabilizer Motor Control Electronics (MCE)unit Non-Volatile Memory (NVM) - Data erasing

BD500-A-J27-04-05-01AAA-552A-A Primary Flight Control Computer (PFCC) Non-VolatileMemory (NVM) - Data erasing

BD500-A-J52-47-03-01AAA-740A-A Wing To Body Fairing (WTBF) servicing doors - Closeafter access procedure

BD500-A-J52-43-00-01AAA-740A-A Mid avionics compartment door - Close after accessprocedure

BD500-A-J52-44-00-01AAA-740A-A Aft equipment compartment door - Close after accessprocedure

Preliminary requirements

Required conditions



None

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Support equipment

Table 3 Support equipment


None

Consumables, materials, and expendables

Table 4 Consumables, materials, and expendables


None

Spares

Table 5 Spares


None

Safety conditionsNone

Procedure1 Job set-up

NoteThe steps in the Job set-up section of this service bulletin are recommendedsteps. The steps give a recommendation to get access to the work area. Thisrecommendation is to give a safe work area and to minimize possible damage tosurrounding aircraft parts. Alternative steps can be used at the discretion of theoperator.

1.1 From the web site address A220World.airbus.com portal → FlightLink → MyLSAPs → Field Loadable Software do as follows:1.1.1 Download the PFCC software P/N 810-0337-007 and unzip the file.

1.1.2 Expand the folder and copy only the folder 1 located in path "...\DLUR\load\", on a formatted Universal Serial Bus (USB) memory stick.

1.2 Make sure that the aircraft is in standard configuration for maintenance (refer toAMP BD500-A-J12-00-00-01AAA-398A-A).

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1.3 Obey all the electrical/electronic safety precautions (refer to AMP BD500-A-J24-00-00-01AAA-913G-A).

1.4 Make sure that the thermal circuit breakers that follow are open (refer to AMPBD500-A-J24-00-00-04AAA-398D-A):










1.5 Make sure that the toggle switch is set to the DISABLE position for theCircuit Protection Devices (CPD) that follow (refer to AMP BD500-A-J24-00-00-07AAA-398D-A):




REU AFT 4 R-FBWPC-4

REU MFS 1 L-FBWPC-2

REU MFS 3 L-FBWPC-3

REU MFS 4 R-FBWPC-2

1.6 Make sure that the electronic circuit breaker that follows is OUT on the CBsynoptic page (refer to AMP BD500-A-J24-00-00-05AAA-398D-A):



1.7 Open the mid avionics compartment door 812 (refer to AMP BD500-A-J52-43-00-01AAA-540A-A).

1.8 Open the mid avionics compartment access door (195AB) (refer to AMPBD500-A-J52-47-03-01AAA-540A-A).

1.9 Open the Landing Gear Control Valve (LGCV) door (195BB) (refer to AMPBD500-A-J52-47-03-01AAA-540A-A).

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1.10 Open the Wing To Body Fairing (WTBF) hydraulic servicing door (196CB) (referto AMP BD500-A-J52-47-03-01AAA-540A-A).

1.11 Open the AFT equipment compartment door (refer to AMP BD500-A-J52-44-00-01AAA-540A-A).

2 Procedure2.1 If it is not possible to complete all the instructions in this service bulletin

because of the configuration of the aircraft, speak with a CRC representativeat 1 866 A220 CRC (1-866-222-0272) or 1-450-476-7676 or e-mail [email protected] for analysis and to get an approved disposition tocomplete this service bulletin.

2.2 Update the 10 Remote Electronic Units (REUs) as follows:

NoteTo minimize ground time, multiple REU P/N C05500026-007 can beuploaded at the same time. For each additional REU uploaded inparallel, a new kit is necessary (i.e. to upload four REUs at the sametime, four Close Box Programmer (CBP) tools and four REU softwareCDs are necessary).

NoteIt is possible to do the PFCC software upload from Step 2.3 to Step 2.6in parallel with the upgrade of the REUs, if all the REU circuit breakersare de-energized before the PFCC software is loaded.

NoteRefer to Parker Service Bulletin 491100-27-003 section 2.C for the softwareCD part number and the REU identification plate necessary to update theREUs.

2.2.1 For the inboard aileron REU, do as follows:Refer to Fig. 12.2.1.1 Do the REU software update with the Parker SB

491100-27-003 Section 3.B.

2.2.2 For the MFS No. 2 REU, do as follows:Refer to Fig. 22.2.2.1 Do the REU software update with the Parker SB

491100-27-003 Section 3.B.


491100-27-003 Section 3.B.

2.2.4 For the outboard aileron REU, do as follows:Refer to Fig. 42.2.4.1 Do the REU software update with the Parker SB

491100-27-003 Section 3.B.

2.2.5 For the Multi-Function Spoiler (MFS) No. 1 REU, do as follows:

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Refer to Fig. 52.2.5.1 Do the REU software update with the Parker SB

491100-27-003 Section 3.B.


491100-27-003 Section 3.B.

2.2.7 For the AFT REU No. 2, do as follows:Refer to Fig. 62.2.7.1 Do the REU software update with the Parker SB

491100-27-003 Section 3.B.


491100-27-003 Section 3.B.


491100-27-003 Section 3.B.


491100-27-003 Section 3.B.

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INBOARD AILERON REU

NOTE

1

LEGEND

1. Remote Electronic UnitC05500026-007 (Pre-Mod)C05500026-009 (Post-Mod)

1

On aircraft 50010-50017, 55003-55016 and 55018-55042 Post-SB BD500-270010 and aircraft 50018,50020-50055, 55043-55068, 55070-55084, 55086-55087.

1

ICN-BD500-A-J270013-F-3AB48-61404-A-001-01Figure 1 Inboard aileron REU

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MFS REU NO.2

NOTE

1

LEGEND


1

1

On aircraft 50010-50017, 55003-55016 and 55018-55042 Post-SB BD500-270010 and aircraft 50018,50020-50055, 55043-55068, 55070-55084, and 55086-55087.


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1

MFS REU NO.4

LEGEND


1

NOTE

1

1

MFS REU NO.3


ICN-BD500-A-J270013-F-3AB48-61410-A-001-01Figure 3 MFS REU No. 3 and No. 4

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OUTBOARD AILERON REU

NOTE

1

LEGEND


1

On aircraft 50010-50017, 55003-55016 and 55018-55042 Post-SB BD500-270010 and aircraft 50018,50020-50055, 55043-55068, 55070-55084, 55086-55087.

1

ICN-BD500-A-J270013-F-3AB48-61405-A-001-01Figure 4 Outboard aileron REU

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1

MFS REU NO.1

MFS REU NO.1

1

NOTE

1

On aircraft 50010-50018.

3 On aircraft 50020-50055, 55003-55068, 55070-55084, and 55086-55087.

LEGEND

1. Remote Electronic UnitC05500026-007 (Pre-Mod)C05500026-009 (Post-Mod) 1

2

2

3



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1

1

AFT REU NO. 3

AFT REU NO. 2

NOTE

1

LEGEND


1



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AFT REU NO. 1

AFT REU NO. 4

NOTE

1

LEGEND


1

1

1



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2.3 Do the software configuration verification system monitoring to confirm the IMSversion (refer to AMP BD500-A-J46-15-00-01AAA-C21A-A).

NoteThe procedure for the upgrade of the PFCC is dependent on theInformation Management System (IMS) version installed on the aircraft.

2.4 For aircraft with IMS-6010 and aboveDo the PFCCs update as follows:

NoteThe PFCC software upgrade can be done simultaneously by making surethat all PFCCs are selected ON. The time necessary to upload all threePFCCs simultaneously is approximately 45 minutes.

2.4.1 Make sure that the thermal circuit breaker that follows is closed (referto AMP BD500-A-J24-00-00-08AAA-398D-A):


PFCC 3 L-CBP-B5

2.4.2 Make sure that the toggle switch is set to the ENABLE position forthe electronic circuit breakers that follow (refer to AMP BD500-A-J24-00-00-11AAA-398D-A):


PFCC 1 L-FBWPC-5

PFCC 2 R-FBWPC-5

2.4.3 Make sure that the PFCC 1, PFCC 2 and PFCC 3 Push ButtonAnnunciator (PBA) lights are off.



2.4.5 Load the PFCC software per the IMS version installed on the aircraftas follows:2.4.5.1 On the cockpit maintenance panel (pilot-side bulkhead),

set the AIRCRAFT switch to the UPLOAD position andthe CHAN switch to the A position.


on the Adaptive Flight Display (AFD).

2.4.5.3 From the main menu, select DATA.

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2.4.5.3.1 Make sure that the dataload submenu isshown.


page is shown.




active (cyan).

2.4.5.7 Use the Multifunction Keyboard Panel (MKP) to enter thepassword MAINT in the Enter Password box, and thenpush ENTER.2.4.5.7.1 Make sure that the Maintenance Data







2.4.6 Select Start Load.

NoteFor aircraft with IMS-6010, an automatic electronic FCS testwill be initiated after two of the three PFCCs have finished thesoftware installation. Wait until the FLT CTRL advisory CASmessage has cleared before you do the next step. It is possibleat this point that the electronic FCS test will fail and FCS relatedEICAS, info and OMS messages will be posted. Do not do thetroubleshooting of these messages at this time.

2.4.7 For aircraft with IMS-6010 and above, after the upgrade of the PFCCsis completed, do the software configuration check in Step 2.6.

2.5 For aircraft with IMS-6000

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Do the PFCCs update as follows:

NoteFor aircraft with IMS-6000, the PFCC software upgrade must be done onePFCC at a time by making sure that the PFCC to upgrade is selected ONand the other PFCCs are selected OFF. The time required to upload eachPFCC is approximately 45 minutes.



2.5.2 Load PFCC 1 software as follows:2.5.2.1 Make sure that the toggle switch is set to the ENABLE



PFCC 1 L-FBWPC-5

2.5.2.2 Make sure that the toggle switch is set to the DISABLEposition for the electronic circuit breaker that follows(refer to AMP BD500-A-J24-00-00-07AAA-398D-A):


PFCC 2 R-FBWPC-5



PFCC 3 L-CBP-B5


2.5.2.5 On the cockpit maintenance panel (pilot-side bulkhead),set the AIRCRAFT switch to the UPLOAD position andthe CHAN switch to the A position.


on the AFD.

2.5.2.7 From the main menu, select DATA.2.5.2.7.1 Make sure that the dataload submenu is

shown.

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page is shown.




active (cyan).

2.5.2.11 Use the Multifunction Keyboard Panel (MKP) to enter thepassword MAINT in the Enter Password data field, andthen push ENTER.2.5.2.11.1 Make sure that the Maintenance Data







2.5.2.14 Select Start Load.

NoteFor aircraft with IMS-6000, when PFCC 1 completesthe upload, the message “LOAD COMPLETE WITHERRORS“ will be displayed. When you click onView Errors, the status of all three PFCCs will bedisplayed (PFCC 1 will indicate LOAD COMPLETEand PFCC 2 and PFCC 3 will indicate FAILED).



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PFCC 1 L-FBWPC-5

2.5.3.2 Make sure that the toggle switch is set to the ENABLEposition for the electronic circuit breaker that follows(refer to AMP BD500-A-J24-00-00-11AAA-398D-A):


PFCC 2 R-FBWPC-5



PFCC 3 L-CBP-B5



page is shown.


NoteFor aircraft with IMS-6000, when PFCC 2 completesthe upload, the message “LOAD COMPLETE WITHERRORS“ will be displayed. When you click onView Errors, the status of all three PFCCs will bedisplayed (PFCC 1 and PFCC 2 will indicate LOADCOMPLETE and PFCC 3 will indicate FAILED).


position for the electronic circuit breakers that follow(refer to AMP BD500-A-J24-00-00-07AAA-398D-A):


PFCC 1 L-FBWPC-5

PFCC 2 R-FBWPC-5

2.5.4.2 Make sure that the thermal circuit breaker that follows isclosed (refer to AMP BD500-A-J24-00-00-08AAA-398D-A):

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PFCC 3 L-CBP-B5



page is shown.


2.5.5 To proceed to the software configuration check, make sure that PFCC1, PFCC 2, and PFCC 3 are powered as follows:2.5.5.1 Make sure that the thermal circuit breaker that follows is

closed (refer to AMP BD500-A-J24-00-00-08AAA-398D-A):


PFCC 3 L-CBP-B5

2.5.5.2 Make sure that the toggle switch is set to the ENABLEposition for the electronic circuit breakers that follow(refer to AMP BD500-A-J24-00-00-11AAA-398D-A):


PFCC 1 L-FBWPC-5

PFCC 2 R-FBWPC-5

NoteFor aircraft with IMS-6000, because this will be thefirst time that two or more PFCCs are powered at thesame time since the software upload, an automaticelectronic FCS test will be initiated. Wait until theFLT CTRL IN TEST advisory CAS message hascleared before you do the next step. It is possible atthis point that the electronic FCS TEST will fail andFCS related EICAS, info, and OMS messages will beposted. Troubleshooting of these messages shouldnot be done at this time.

2.6 Do a software configuration check of PFCC1, PFCC2 and PFCC3 as follows:2.6.1 Get the access to the OMS LRU/System Operations page (refer to

AMP BD500-A-J45-45-00-03AAA-C21A-A).

2.6.2 From the MAINT MENU, select LRU System Operations:- View ALL ATAs

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- Select ATA 27 - FLIGHT CONTROLS- Select LRU/System PFCC1









2.7 Make sure that the thermal circuit breakers that follow are closed (refer to AMPBD500-A-J24-00-00-08AAA-398D-A):










2.8 Make sure that the toggle switch is set to the ENABLE position for the electroniccircuit breakers that follow (refer to AMP BD500-A-J24-00-00-11AAA-398D-A):




REU AFT 4 R-FBWPC-4

REU MFS 1 L-FBWPC-2

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REU MFS 3 L-FBWPC-3

REU MFS 4 R-FBWPC-2

2.9 Make sure that the electronic circuit breaker that follows is IN on the CBsynoptic page (refer to AMP BD500-A-J24-00-00-10AAA-398D-A):



NoteIt is possible to have rigging faults at this time. Do not do thetroubleshooting at this time.

2.10 Get access to the Onboard Maintenance System (OMS) LRU/SystemOperations page to do the system monitoring of each of the 10 REUs as follows(refer to AMP BD500-A-J45-45-00-03AAA-C21A-A):2.10.1 From the Select ATA drop-down list, select the ATA 27.


- AFT 1 REU


2.10.4 Make sure that the part number and serial number of the selectedREU is as shown in the table that follows:





- AFT 2 REU






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- AFT 3 REU







- AFT 4 REU







- INBOARD AILERON REU







- OUTBOARD AILERON REU



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- MFS 1 REU







- MFS 2 REU







- MFS 3 REU






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- MFS 4 REU






NoteFrom this point forward, consider the aircraft as post SB BD500-270013when performing the AMP procedures in the steps that follow.

2.11 Do the post SB BD500-270013 modification test that follows:2.11.1 Do the Horizontal Stabilizer Trim Actuator (HSTA) rigging (refer to

AMP BD500-A-J27-41-01-01AAA-275B-A).








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2.11.10 Do the AFT REU No. 1 Onboard Maintenance System (OMS) quickrigging (refer to AMP BD500-A-J27-04-31-01AAA-275B-A).




2.11.14 Do the inboard aileron REU OMS quick rigging (refer to AMP BD500-A-J27-04-31-01AAA-275B-A).

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2.11.15 Do the outboard aileron REU OMS quick rigging (refer to AMP BD500-A-J27-04-31-01AAA-275B-A).

2.11.16 Do the Electronic Flight Control System (FCS) test (refer to AMPBD500-A-J27-04-00-01AAA-343A-A).

2.11.17 Do the Actuation FCS test (refer to AMP BD500-A-J27-04-00-02AAA-343A-A).

2.11.18 Do the electronic FCS test (refer to AMP BD500-A-J27-04-00-01AAA-343A-A).

NoteThe electronic FCS test is repeated to reset the latched riggingfaults after the actuation FCS test is done in Step 2.11.17.

2.11.19 Make sure that there are no FCS EICAS, INFO, or OMS messages.

NoteIf any messages is displayed, do troubleshooting.

2.11.20 Clear the Non-Volatile Memory (NVM) of the AFT REU No. 1 (refer toAMP BD500-A-J27-04-35-01AAA-552A-A).




2.11.24 Clear the NVM of the inboard aileron REU (refer to AMP BD500-A-J27-04-33-01AAA-552A-A).

2.11.25 Clear the NVM of the outboard aileron REU (refer to AMP BD500-A-J27-04-33-01AAA-552A-A).





2.11.30 Clear the NVM of the horizontal stabilizer Motor Control Electronics(MCE) unit (refer to AMP BD500-A-J27-41-03-01AAA-552A-A).



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3 Job close-up

NoteThe steps in the Job close-up section of this service bulletin, except for the return-to-service tests, are recommended steps. The steps give a recommendation toinstall components removed during the Job set-up. This recommendation is tomake sure that the aircraft is safe and ready to return to service. Alternative stepscan be used at the discretion of the operator.

3.1 Remove all tools, equipment, and unwanted materials from the work area.

3.2 Close the LGCV door (195BB) (refer to AMP BD500-A-J52-47-03-01AAA-740A-A).

3.3 Close the mid avionics compartment access door (195AB) (refer to AMPBD500-A-J52-47-03-01AAA-740A-A).

3.4 Close the mid avionics compartment door 812 (refer to AMP BD500-A-J52-43-00-01AAA-740A-A).

3.5 Close the WTBF hydraulic servicing door (196CB) (refer to AMP BD500-A-J52-47-03-01AAA-740A-A).

3.6 Close the AFT equipment compartment door (refer to AMP BD500-A-J52-44-00-01AAA-740A-A).

4 AdministrativeWhen PART B of this service bulletin is completed, record in the applicable aircraftrecords that you have completed PART B of this service bulletin.

Requirements after job completionRequired conditions



None

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491100-27-003 - Parker Service Bulletin.................................................................................. 1References................................................................................................................................ 1Description................................................................................................................................. 1

List of tables Page

1 References.................................................................................................................. 1


1 Parker SB 491100-27-003.......................................................................................... 2



None

Description

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SERVICE BULLETIN

Initial Issue Jul 10, 2020 491100-27-003Page 1 of 6

THIS DOCUMENT CONTAINS INFORMATION THAT IS CONFIDENTIAL AND PROPRIETARY TO PARKER-HANNIFIN CORPORATION. THIS DOCUMENT IS FURNISHED ON THEUNDERSTANDING THAT THE DOCUMENT AND THE INFORMATION IT CONTAINS WILL NOT BE COPIED OR DISCLOSED TO OTHERS EXCEPT WITH THE WRITTENCONSENT OF PARKER, WILL NOT BE USED FOR ANY PURPOSE OTHER THAN CONDUCTING BUSINESS WITH PARKER, AND WILL BE RETURNED AND ALL FURTHER USEDISCONTINUED UPON REQUEST BY PARKER. COPYRIGHT PARKER. YEAR OF COPYRIGHT IS FIRST YEAR INDICATED ON THIS DOCUMENT. ALL RIGHTS RESERVED.

FLIGHTCONTROLS

REMOTE ELECTRONIC UNIT, PARTNUMBER 491100-1007, -1009, -1011

SOFTWARE UPDATE FBW PC1, UPDATEREU TO 491100-1013

1. PLANNING INFORMATION

A. Effectivity

This Service Bulletin is applicable to the A220-100 and -300 aircraft Remote Electronic Unit (REU), PartNumber (P/N) 491100-1007, 491100-1009 and 491100-1011, A220 P/N C05500026-003, C05500026-005 and C05500026-007.

B. Concurrent Requirements

For P/N 491100-1007 and -1009, Service Bulletin 491100-27-002 must be performed prior to thisService Bulletin to bring the REU up to the 491100-1011 configuration.

C. Reason

This service bulletin introduces new maintenance functionalities to the Fly-By-Wire (FBW) system withFBW PC1

includes fixes and improvements to the current FBW software.

D. Description

(1) The FBW system software FBW PC1 implements the following new functionalities: Quick Rigging,Auto Rigging and Initiated Built-In Test (IBIT) capability.

(2) FBW software FBW PC1 also includes fixes impacting OMS reporting, ABIT and PBIT, REU andAFCU monitors, Normal Mode Control Laws, Non-Volatile Memory (NVM) download/storage/clearing,Input Signal Management, Synoptics / Info Messages and PFCC Fault Reporting.

(3) The installation of FBW software FBW PC1 is recommended to be performed on aircraft by theoperator using a Closed-Box Programming (CBP) tool. Spares can be upgraded off-aircraft using thesame procedure.

(4) Accomplishment of this service bulletin will upgrade REU PN 491100-1011 to PN 491100-1013,A220 PN C05500026-009, and BAE Systems PN 115E5846G7.

E. Compliance

Refer to the applicable A220 Service Bulletin (Ref 2) for the compliance recommendation.

F. Approval

This Service Bulletin has been reviewed by the A220 Program and has been approved for application tothe A220-100 and A220-300 aircraft platforms.

G. Manpower

Refer to the applicable A220 Service Bulletin for additional REU upgrade and return-to-service manpowerrequirements.

ICN-BD500-A-J270013-F-3AB48-63904-A-002-01Figure 1 Parker SB 491100-27-003

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H. Weight and Balance

None.

I. Electrical Load Data

Not Applicable.

J. Software Accomplishment Summary

REU Software version 3.0.17 used in REU P/N 491100-1011, is replaced with REU software version 4.6.0 forREU P/N 491100-1013.

K. References

(1) Parker Service Bulletin 491100-27-002(2) Airbus Canada A220 Service Bulletin BD500-27-0013(3) BAE Systems Service Bulletin 115E5846-27-03(4) 491100TF50-1001 REU Closed Box Programmer (BAE Systems P/N 116E1573G1)(5) 116E1573_GETM REU Closed Box Programmer Ground Equipment Technical Manual (BAE

Systems)(6) Software Version 4.6.0(7) Software Configuration Index (SCI) 365A1249

L. Other Publications Affected

Component Maintenance Manual (CMM) 27-00-30 (BAE Systems).

M. Interchangeability and Intermixability of Parts

REU P/N 491100-1009 and 491100-1011 are one-way interchangeable with REU 491100-1013.Intermixing REU 491100-1013 with prior configurations is not permitted.

2. MATERIAL INFORMATION

A. Material - Price and Availability

(1) The software and materials required for the operator to modify REU P/N 491100-1011 to the P/N491100-1013 configuration is available at no charge from Parker Hannifin as described below.

(2) The programming tool for installing the software is available from Airbus Canada. See Toolingsection below for additional information.

(3) Parker Hannifin will perform the modification of REU P/Ns 491100-1007, 491100-1009 to P/N491100-1013 at no charge.

(4) Parker Hannifin will perform the modification of REU P/Ns 491100-1011 to P/N 491100-1013 at acost of $2110 USD per REU.

(5) Coordinate return of the REU(s), with your applicable Parker Customer Support RepairAdministrator or Parker CRC at the location and contact below.


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B. Industry Support Information

(1) The provisions contained in this Service Bulletin only apply to the work described herein and are validuntil all affected REUs have been updated with this Service Bulletin.

(2) The pricing in Section 2.A.(3) is valid until December 31, 2021. After that time, please contact yourParker Customer Support Repair Administrator or Parker CRC as described in 2.A.(4).

(3) Damage from mishandling and/or abnormal use, and parts or work required outside the scope of thisService Bulletin is subject to time and material charges.

C. Material Necessary for Each Component

The following parts are required for this Service Bulletin.

Table 1

NEW P/N KEYWORD OLD P/N QTY DISPOSITION

332B1678P6 Identification plate * Same or 332B1678P5 1 ScrapMS16995-10 Screw Same 1 Spare; Re-use originalsNAS620C4 Flat washer Same 1 Spare; Re-use originals365A1674P1 Compact Disc software ** N/A 2 N/A

* Parker to provide identification plates pre-marked with all but the Serial Number (S/N) and MFG Date for all

** REU software CD will run from the CBP tool to upload directly to the REU on aircraft. Only one software CDis required for each CBP programmer. To reduce aircraft downtime more than 1 CBP may be ordered fromAirbus Canada, therefore an additional CD is recommended.

D. Material Necessary for Each Spare

See Table 1, above.

E. Re-identified Parts

Upon completion of the modification per this Service Bulletin, the REU P/N 491100-1011 will change to P/N491100-1013, A220 PN C05500026-009, and BAE Systems PN 115E5846G7.

F. Tooling Price and Availability

A Closed-Box Programmer GSE will be required to install the new REU software, PN 491100TF50-1001(BAE Systems PN 116E1573G1). Refer to the applicable A220 service bulletin for information regarding thetooling price and availability. The Compact Disc containing the REU software is not included with the CBPand is to be ordered from Parker Hannifin Corporation as described in Section 2.

[email protected]

REPAIR STATION NO.:TECH INQUIRY:

(949) [email protected](949) 809-8646

CUSTOMER RESPONSECENTER:FAX (Repairs):

PARKER HANNIFIN CORPORATION

Customer Support Operations14300 Alton ParkwayIrvine, CA 92618-1898USA


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3. ACCOMPLISHMENT INSTRUCTIONS

A. Owner/operator instructions if the REU is to be updated per this service bulletin by Parker HannifinCorporation

NOTE: The rigging information that was stored in the REU at the time of removal from the aircraft will becleared when this option is used. Rigging of the affected PCUs will need to be performed when thereplacement REU is installed per Airbus service bulletin instructions (Ref 2).

(1) REU P/Ns 491100-1007, 491100-1009 or 491100-1011 may be returned to Parker HannifinCorporation at the address shown in paragraph 2.A for upgrade per this Service Bulletin.

(2) Parker will forward the REU to the BAE Systems repair station who will perform the modificationrequired to update to the new configuration, including airworthiness recertification.

(3) For P/Ns 491100-1007 or -1009, BAE Systems will modify or replace the REU Interface CCAP/N 115E6772G1 with P/N 115E6772G2 per Service Bulletin 491100-27-002 (BAE SB115E5846-27-02) and then install software load [4.6.0] (BAE SB 115E5846-27-03) prior torecertifying the unit.

(4) For P/N 491100-1011 units, software load 4.6.0 will be installed using the approved productionprogramming equipment and BAE SB 115E5846-27-03 to satisfy the intent of this servicebulletin.

(5) BAE Systems will recertify and re-identify the unit to Parker P/N 491100-1013, A220 PNC05500026-009, and BAE Systems PN 115E5846G7.

B. Instructions if the REU is to be updated per this service bulletin by the owner/operator

NOTE: For the Multi-Function Spoilers (MFS) and the Horizontal Stabilizer Trim Actuator (HSTA), OnboardMaintenance System (OMS) Surface Rigging will need to be performed at the time of incorporationof this service bulletin.

NOTE: For the aileron, elevator and rudder PCUs, the rigging information that was stored in the REUsbefore the new software is uploaded will be retained if the REU is left in, or returned to, its originalinstalled location on the aircraft. No surface rigging will be necessary.

NOTE: REU spares P/N 491100-1011 can be upgraded off-aircraft using the CBP tool and the sameinstructions provided below.

(1) Before attempting to upload software into the REU, review the publication 116E1573_GETMREU Closed Box Programmer Ground Equipment Technical Manual to familiarize yourself withthe equipment and its operation. See APPENDIX section of this service bulletin.

(2) For on-aircraft software installation, prepare the aircraft for the REU update as described in theapplicable A220 service bulletin.

(3) Refer to SECTION 2 OPERATION of the 116E1573 GETM paragraphs 1.A through C toprepare and connect the CBP to the REU for programming.

(4) Perform the programming as described in SECTION 2 OPERATION of the GETM subsectionsD and E.


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(5) In the GETM Section 2, step E.(5) make sure the CBP Image Verification tab is showing the sixCRC values exactly as in Figure 1, below. DO NOT use the CRC values from the User Manual.

NOTE: The CRC values showing in the CBP User Manual 116E1573_GETM figure 1-24 per latest CBP usermanual are for illustrative purpose and may not reflect the current values. DO NOT use the CRCvalues from the User Manual.

Figure 1Post-update completion screen (GETM Figure 1-24 per latest CBP user manual)

(6) Copy the S/N and MFG DATE found on the identification plate of the REU that is beingprogrammed with the new software.

(7) On a new nameplate provided by Parker that shows the P/N 491100-1013, use vibro-peen,laser-etch, engraving, impression-stamp, or indelible ink marker with clear topcoat to transfer theS/N and MFG DATE into the corresponding blank spaces, see Figure 2.


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(8) Remove the nameplate from the front panel of the REU and replace with the new one that ismarked with Parker P/N 491100-1013 and A220 P/N C05500026-009. Re-use the mountingscrews and washers. Torque to 8 in-lbs (0.904 N-m).

(9) If not done so already, remove the CBP cables and install protective covers on the connectors.

(10) For REUs upgraded on-aircraft, remove the protective coverings from the aircraft harness andreconnect P1 and P2 connectors to the J1 and J2 receptacles on the REU. Refer to thecorresponding A220 service bulletin for Return to Service (RTS) instructions.

Figure 2REU Nameplate Marking Location

4. APPENDIX

A. 116E1573_GETM REU Closed Box Programmer Ground Equipment Technical Manual (BAE Systems)

CBP User Manual116E1573_GETM - R3_reduced.pdf


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