EMS Technologies Canada A781-MK2 A350 Satellite Data Unit User Manual

EMS Technologies Canada, Ltd. A350 Satellite Data Unit

Users Manual

Honeywell International Inc.400 Maple Grove DriveOttawa, Ontario K2V 1B8CanadaCAGE: 38473Telephone: (800) 601-3099 (Toll Free U.S.A./Canada)Telephone: (602) 365-3099 (International Direct)Website: www.myaerospace.comAbbreviated Component Maintenance ManualA350 SDU and SCMPart Number CAGE1458-A-1101 384731458-A-1300 38473This document contains technical data and is subject to U.S. export regulations. These commodities, technology, orsoftware were exported from the United States in accordance with the export administration regulations. Diversion contraryto U.S. law is prohibited.ECCN: 7E994, NLR Eligible.23-15-30Page1of70Publication Number D201207000045, Revision 0 Initial 5 Oct 2012©Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Honeywell - ConfidentialTHIS COPYRIGHTED WORK AND ALL INFORMATION ARE THE PROPERTY OF HONEYWELLINTERNATIONAL INC., CONTAIN TRADE SECRETS AND MAY NOT, IN WHOLE OR IN PART, BE USED,DUPLICATED, OR DISCLOSED FOR ANY PURPOSE WITHOUT PRIOR WRITTEN PERMISSION OFHONEYWELL INTERNATIONAL INC. ALL RIGHTS RESERVED.Honeywell Materials License AgreementThe documents and information contained herein ("the Materials") are the proprietary data of HoneywellInternational Inc. and Honeywell Intellectual Properties Inc. (collectively "Honeywell"). These Materialsare provided for the exclusive use of Honeywell Service Centers; Honeywell-authorized repair facilities;operators of Honeywell aerospace products subject to an applicable product support agreement, theirwholly owned-subsidiaries or a formally designated third party service provider; and direct recipients ofMaterials from Honeywell’s Aerospace Technical Publication Distribution. The terms and conditions ofthis License Agreement govern your use of these Materials, except to the extent that any terms andconditions of another applicable agreement with Honeywell regarding the operation, maintenance, orrepair of Honeywell aerospace products conflict with the terms and conditions of this License Agreement,in which case the terms and conditions of the other agreement will govern. However, this LicenseAgreement will govern in the event of a conflict between its terms and conditions and those of a purchaseorder or acknowledgement.1. License Grant - If you are a party to an applicable product support agreement, a Honeywell ServiceCenter agreement, or an authorized repair facility agreement, Honeywell hereby grants you a limited,non-exclusive license to use these Materials to operate, maintain, or repair Honeywell aerospace productsonly in accordance with that agreement.If you are a direct recipient of these Materials from Honeywell’s Aerospace Technical PublicationDistribution and are not a party to an agreement related to the operation, maintenance or repair ofHoneywell aerospace products, Honeywell hereby grants you a limited, non-exclusive license to usethese Materials to maintain or repair the subject Honeywell aerospace products only at the facility towhich these Materials have been shipped ("the Licensed Facility"). Transfer of the Materials to anotherfacility owned by you is permitted only if the original Licensed Facility retains no copies of the Materialsand you provide prior written notice to Honeywell.2. Rights In Materials - Honeywell retains all rights in these Materials and in any copies thereof that are notexpressly granted to you, including all rights in patents, copyrights, trademarks, and trade secrets. Nolicense to use any Honeywell trademarks or patents is granted under this License Agreement.3. Confidentiality - You acknowledge that these Materials contain information that is confidential andproprietary to Honeywell. You agree to take all reasonable efforts to maintain the confidentiality of theseMaterials.4. Assignment And Transfer - This License Agreement may be assigned to a formally designated servicedesignee or transferred to a subsequent owner or operator of an aircraft containing the subject Honeywellaerospace products. However, the recipient of any such assignment or transfer must assume all ofyour obligations under this License Agreement. No assignment or transfer shall relieve any party ofany obligation that such party then has hereunder.5. Copies of Materials - Unless you have the express written permission of Honeywell, you may notmake or permit making of copies of the Materials. Notwithstanding the foregoing, you may make copiesof only portions of the Material for your internal use. You agree to return the Materials and any copiesthereof to Honeywell upon the request of Honeywell.6. Term - This License Agreement is effective until terminated as set forth herein. This License Agreementwill terminate immediately, without notice from Honeywell, if you fail to comply with any provision of this23-15-30 Page2of705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300License Agreement or will terminate simultaneously with the termination or expiration of your applicableproduct support agreement, authorized repair facility agreement, or your formal designation as a third partyservice provider. Upon termination of this License Agreement, you will return these Materials to Honeywellwithout retaining any copies and will have one of your authorized officers certify that all Materials havebeen returned with no copies retained.7. Remedies - Honeywell reserves the right to pursue all available remedies and damages resulting froma breach of this License Agreement.8. Limitation of Liability - Honeywell does not make any representation regarding the use or sufficiency ofthe Materials. THERE ARE NO OTHER WARRANTIES, WHETHER WRITTEN OR ORAL, EXPRESS,IMPLIED OR STATUTORY, INCLUDING, BUT NOT LIMITED TO, (i) WARRANTIES ARISING FROMCOURSE OF PERFORMANCE, DEALING, USAGE, OR TRADE, WHICH ARE HEREBY EXPRESSLYDISCLAIMED, OR (ii) WARRANTIES AGAINST INFRINGEMENT OF INTELLECTUAL PROPERTYRIGHTS OF THIRD PARTIES, EVEN IF HONEYWELL HAS BEEN ADVISED OF ANY SUCHINFRINGEMENT. IN NO EVENT WILL HONEYWELL BE LIABLE FOR ANY INCIDENTAL DAMAGES,CONSEQUENTIAL DAMAGES, SPECIAL DAMAGES, INDIRECT DAMAGES, LOSS OF PROFITS, LOSSOF REVENUES, OR LOSS OF USE, EVEN IF INFORMED OF THE POSSIBILITY OF SUCH DAMAGES.TO THE EXTENT PERMITTED BY APPLICABLE LAW, THESE LIMITATIONS AND EXCLUSIONS WILLAPPLY REGARDLESS OF WHETHER LIABILITY ARISES FROM BREACH OF CONTRACT, WARRANTY,TORT (INCLUDING BUT NOT LIMITED TO NEGLIGENCE), BY OPERATION OF LAW, OR OTHERWISE.9. Controlling Law - This License shall be governed and construed in accordance with the laws of theState of New York without regard to the conflicts of laws provisions thereof. This license sets forth theentire agreement between you and Honeywell and may only be modified by a writing duly executed bythe duly authorized representatives of the parties.Safety AdvisoryWARNING: BEFORE THE MATERIALS CALLED OUT IN THIS PUBLICATION ARE USED, KNOW THEHANDLING, STORAGE AND DISPOSAL PRECAUTIONS RECOMMENDED BY THE MANUFACTUREROR SUPPLIER. FAILURE TO OBEY THE MANUFACTURERS’ OR SUPPLIERS’ RECOMMENDATIONSCAN RESULT IN PERSONAL INJURY OR DISEASE.This publication describes physical and chemical processes which can make it necessary to use chemicals,solvents, paints, and other commercially available materials. The user of this publication must get theMaterial Safety Data Sheets (OSHA Form 174 or equivalent) from the manufacturers or suppliers of thematerials to be used. The user must know the manufacturer/ supplier data and obey the procedures,recommendations, warnings and cautions set forth for the safe use, handling, storage, and disposalof the materials.Warranty/Liability AdvisoryWARNING: HONEYWELL ASSUMES NO RESPONSIBILITY FOR ANY HONEYWELL EQUIPMENTWHICH IS NOT MAINTAINED AND/OR REPAIRED IN ACCORDANCE WITH HONEYWELL’SPUBLISHED INSTRUCTIONS AND/OR HONEYWELL’S FAA/SFAR 36 REPAIR AUTHORIZATION.NEITHER DOES HONEYWELL ASSUME RESPONSIBILITY FOR SPECIAL TOOLS AND TESTEQUIPMENT FABRICATED BY COMPANIES OTHER THAN HONEYWELL.WARNING: INCORRECTLY REPAIRED COMPONENTS CAN AFFECT AIRWORTHINESS ORDECREASE THE LIFE OF THE COMPONENTS. INCORRECTLY FABRICATED SPECIAL TOOLINGOR TEST EQUIPMENT CAN RESULT IN DAMAGE TO THE PRODUCT COMPONENTS OR GIVEUNSATISFACTORY RESULTS.23-15-30 Page3of705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Copyright - NoticeCopyright 2012 Honeywell International Inc. All rights reserved.Honeywell is a registered trademark of Honeywell International Inc.All other marks are owned by their respective companies.THIS IS THE CMM FOSI - DATE: CMM FOSI - 20080523, VERSION 0019 (GBB)23-15-30 Page4of705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300TRANSMITTAL INFORMATIONTHIS IS AN INITIAL RELEASE OF A350 SDU AND SCM ACMM ATA NO. 23-15-30 AND IS ISSUED FORUSEINSUPPORTOFTHEFOLLOWING:Table 1 shows the applicable components.Table 1. Applicable ComponentsComponent PN Nomenclature1458-A-1101 A350 SDU1458-A-1300 A350 SCMRevision HistoryTable 2 shows the revision history of this ACMM.Table 2. Revision HistoryRevision Number Revision Date05 Oct 2012EFFECTIVITYALL 23-15-30 Page5of705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Blank PageEFFECTIVITYALL 23-15-30 Page 6 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300INTRODUCTION1. How to Use This Manual (TASK 23-15-30-99F-801-A01)A. General (Subtask 23-15-30-99F-001-A01)(1) This publication gives maintenance instructions for the equipment shown on the Title page.(2) Standard maintenance procedures that technicians must know are not given in this manual.(3) This publication is written in agreement with the ATA Specification.(4) Refer to the Special Tools, Fixtures, and Equipment and Consumables tables in each sectionbefore the start of maintenance procedures.(5) Honeywell recommends that you do the tests in TESTING AND FAULT ISOLATION (PGBLK23-15-30-1000) to test the operational status of the unit. These tests can show the conditionof the unit or most possible cause of a malfunction. If a malfunction occurs, the unit mustbe returned to the manufacturer for fault isolation and repair, refer to APPENDIX A (RMA)(PGBLK 23-15-30-1700).(6) Maintenance for the A350 SDU and SCM system is limited to replacement on verified failure.After consultation with a Honeywell product support specialist and if replacement of the unitis deemed necessary, refer to APPENDIX A (RMA) (PGBLK 23-15-30-1700) for equipmentreturn procedures.(7) All repairs must be performed at Honeywell or a Honeywell approved repair facility.(8) Warnings, cautions, and notes in this manual give the data that follows:• A WARNING gives a condition or tells personnel what part of an operation or maintenanceprocedure, which if not obeyed, can cause injury or death• A CAUTION gives a condition or tells personnel what part of an operation or maintenanceprocedure, which if not obeyed, can cause damage to the equipment• A NOTE gives data, not commands. The NOTE helps personnel when they do the relatedinstruction.(9) Warnings and cautions go before the applicable paragraph or step. Notes follow the applicableparagraph or step.B. Observance of Manual Instructions (Subtask 23-15-30-99F-002-A01)(1) Make sure that you carefully obey all safety, quality, operation, and shop procedures for the unit.(2) All personnel who operate equipment and do maintenance specified in this manual must knowand obey the safety precautions.C. Symbols (Subtask 23-15-30-99F-003-A01)(1) The symbols and special characters are in agreement with IEEE Publication 260 and IECPublication 27. Special characters in text are spelled out.(2) The signal mnemonics, unit control designators, and test designators are shown in capitalletters.(3) The signal names followed by an “*” show an active low signal.(4) The symbols in Figure 1 (GRAPHIC 23-15-30-99B-801-A01) show ESDS and moisturesensitive devices.EFFECTIVITYALL 23-15-30 Page7of705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Figure 1. (Sheet 1 of 1) Symbols (GRAPHIC 23-15-30-99B-801-A01)D. Units of Measure (Subtask 23-15-30-99F-004-A01)(1) Measurements, weights, temperatures, dimensions, and other values are expressed in theUSMS followed by the appropriate SI metric units in parentheses. Some standard tools orparts such as drills, taps, bolts, nuts, etc. do not have an equivalent.E. Illustration (Subtask 23-15-30-99F-005-A01)(1) Supplemental illustrations use a suffix number to the basic figure number. For example, ifFigure 501-5 is used, it signifies that it is an illustration of the item identified by index number 5in Figure 501.(2) Illustrations with no specific designation are applicable to all units.F. Application of Maintenance Task Oriented Support System (MTOSS) (Subtask 23-15-30-99F-006-A01)(1) In accordance with the ATA Specification 2200, this publication uses a Maintenance TaskNumbering System which make the maintenance procedures in this manual compatible withan automated shop environment.(2) The system uses standard and unique number combinations to identify maintenance tasksand subtasks.(3) The MTOSS structure is the logical approach to organizing maintenance tasks and subtasks.The MTOSS numbering system includes the ATA Chapter-Section-Subject number as well as afunction code and unique identifiers. The purpose of incorporating the MTOSS numberingsystem is to provide a means for the automated sorting, retrieval, and management ofdigitized data.(4) Section and Sub-section Numbering System(a) All procedures in this publication have TASK and SUBTASK numbers at key data retrievalpoints. The numbers provide the following:• Identification of the hardware (part or parts) primary to the TASK• Identification of the maintenance function applied to the part or parts• A unique identifier for a set of instructions (known as TASK or SUBTASK)• Identification of alternate methods and configuration differences that change theprocedure applied to the TASK• Identification of airline changes to a TASK or SUBTASK.(5) Components of Task and Subtask Number(a) The numbering system is an expansion of the ATA three-element numbering system. Thenumber has seven elements. The first five elements are necessary for each TASK orSUBTASK. The sixth and seventh elements are applied only when necessary. Refer toFigure 2 (GRAPHIC 23-15-30-99B-802-A01).EFFECTIVITYALL 23-15-30 Page 8 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300(b) Elements 1, 2, and 3 identify the ATA Chapter-Section-Subject number of the page block.(c) Element 4 defines the maintenance function being performed. This element is a threeposition element. The third position is zero filled when further definition is not required. Ifrequired, the manufacturer will use the numbers 1 thru 9 or letters A thru Z, excluding theletters I and O. Refer to Table 3.(d) Element 5 provides a unique identification for each TASK or SUBTASK number which issimilarly numbered through the first four elements.• TASKS are numbered from 801 thru 999• SUBTASKS are numbered from 001 thru 800.(e) Element 6 is a three position alphanumeric element used for identification of differencesin configurations, methods or techniques, variations of standard practice applications, etc.(f) Element 7 provides coding of those tasks or subtasks that have been changed by thecustomer (e.g., those tasks or subtasks accomplished by an outside repair source).Figure 2. (Sheet 1 of 1) MTOSS Code Positions (GRAPHIC 23-15-30-99B-802-A01)Table 3. MTOSS Function Code DefinitionsCode Function Definition000 REMOVAL AND DISASSEMBLY010 Removal Removal of the engine/component from aworkstand, transport dolly, test stand, etc., oraircraft.020 Remove Modular Sections This is the first echelon of disassembly whichconsists of sectionalization of the unit/engineinto primary modular sections. Modularsections are identified by the third elementof the ATA number when removed from theunit/engine.EFFECTIVITYALL 23-15-30 Page9of705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Code Function Definition030 Disassemble Modular Sections This is the second echelon of disassemblywhich consists of disassembly of the modularsections into subassemblies after removal fromthe unit/engine. Modular section designationsappear in the second element of the ATAnumber for this echelon of disassembly.040 Disassemble Subassemblies This is the third echelon of enginedisassembly which consists of disassemblyof subassemblies to the piece part level.The subassemblies are identified by the thirdelement of the ATA number.050 Remove Accessory/Power Plant Components This consists of removing individualaccessory/power plant components from eitherinstalled or uninstalled engines.060 Disassemble Accessory This involves disassembly of accessories/components into subassemblies.070 Disassemble Accessory Subassembly This involves disassembly of accessories/components subassemblies into piece parts.080 Remove Test Equipment This consists of removing equipment andinstrumentation after accessory/componenttest.090 Disassemble Support Equipment This consists of disassembly of supportequipment required to maintain said supportequipment.100 CLEANING110 Chemical Removal of surface deposits from a part byuse of a chemical cleaning agent. After beingdissolved, the deposit is washed or rinsed awayafter a soaking period. Also includes chemicalpower flushing.120 Abrasive Removal of surface deposits from a part by wetor dry particle impingement.130 Ultrasonic Removal of surface deposits and entrappedmaterial by use of high frequency sound wavesto produce cavitation at the surface of thepart. Cleaning is performed in a liquid baththat transmits the sound energy and keeps theremoved material in suspension.140 Mechanical Removal of surface deposits from a part by useof a brush, felt bob, sandpaper, or other handor mechanical action.EFFECTIVITYALL 23-15-30 Page 10 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Code Function Definition150 Unassigned160 MiscellaneousRemoval of deposits from parts withcompressed air, miscellaneous hand cleaning,and various combinations of cleaningprocedures.170 Foam/Water Wash Removal or post emulsified fluorescentpenetrant via an agitated water wash,automatic spray rinse, or an aqueous removeraeratedtoproduceafoam.180 Testing of Solutions Test used to assist in identifying certainmaterials by electro-mechanically determiningthe presence or absence of known constituents.190 Unassigned200 INSPECTION210 Check Athoroughvisual examination of components,accessories, subsystems, and piece partsto detect structural failure, deterioration ordamage: and to determine the need forcorrective action. For example: exteriorsurfaces, electronic circuit cards, gears, controlsystems, linkages, accessories, components,tubing, wiring and connections, safety wiring,fasteners, clamps, etc., are inspected to verifyproper condition and acceptability for continuedservice.220 Visual/Dimensional A comparison of the dimensions and materialconditions of parts, subassemblies, andassemblies with the specifications containedin technical manuals and/or blueprints, todetect deviations from established standardand limits and determine the acceptability forcontinued service, repair, or need to discardthe item. A visual/dimensional function codeis also required to verify that proper correctivemaintenance has been accomplished.Although some of these tasks may not requiremeasurements, a complete spectrum oftasks/sub tasks requires a variety of measuringequipment to determine runout, concentricity,flatness, parallelism, hardness, thickness,clarity, dimensions, etc.230 Penetrant Fluorescent penetrant inspection to detectsurface cracks.EFFECTIVITYALL 23-15-30 Page 11 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Code Function Definition240 Magnetic Magnetic particle inspection to detect surfacecracks in magnetic materials.250 Eddy Current Inspection for subsurface cracks, porosity,inclusions, or other nonhomogeneousmaterial structure by use of high frequencyelectromagnetic wave equipment. Parts arescanned and compared to similar parts or testspecimens having known material defects.260 X-Ray Inspection for subsurface cracks, porosity,inclusions, or other nonhomogeneous materialstructure by use of x-ray techniques.270 Ultrasonic Inspection for subsurface cracks, porosity,inclusions, or other nonhomogeneous materialstructure by use of contact pulse echoultrasonic techniques.280 Special Any special inspection to determine theintegrity of a part for continued operationIn-Service or qualitative analysis.290 Unassigned300 REPAIR310 Welding and Brazing The joining of pieces by welding (fusion,resistance, spot, electron beam, plasma arc),brazing (furnace, torch, induction), or soldering.This category includes hard facing.320 Machining The process of obtaining a desired shape orfinish by grinding, turning, boring, reaming,broaching, milling, drilling, lapping, honing,sizing, polishing, buffing, cutting, forming,stamping, blanking, etc.330 Stripping and Plating Removing or applying a metallic coating on asurface by mechanical, chemical, or electricalmeans. Plating of chromium, cadmium, tin,etc., to build up the size of a part or providesurface protection. Includes masking or waxingprior to the process.340 Plasma and Flame Spraying The application of a protective coating to apart by feeding a powder into an ionized gasstream. Flame spraying uses a fuel oxygenflame to melt and propel metal onto parts tobuild up the size or provide surface protection.EFFECTIVITYALL 23-15-30 Page 12 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Code Function Definition350 Miscellaneous Repairs Repairing parts by hand (cutting, drilling,polishing, grinding, lapping, riveting, blending,routing, fitting, burring, planishing, sanding,sawing, recambering, drilling, tapping,heating, chilling) and including miscellaneousdisassembly and assembly required.360 Bonding and Molding/Sealing Joining and curing of parts with an adhesive orfusible material (including silicone, fiberglass,glues).370 Heat Treating Controlled heating and cooling of a material toobtain the desired physical property (includesannealing, tempering, quenching, stressrelieving, solution heat treat, etc.).380 Surface Treating Treating the surface of a part by painting,varnishing, aluminizing, Teflon coating, zincchromate priming, tumble finishing, shotpeening, etc. Baking and masking processesare included.390 Machine Riveting and Flaring Joining of parts by riveting and flaring the rivet.400 INSTALLATION AND ASSEMBLY410 Install Installation of the unit/engine onto a workstand,transportdolly,teststand,oraircraft.420 Install Modular Sections The third echelon of assembly consisting ofassembly of the modular assemblies into acomplete unit/engine assembly. The modularsections are identified by the third element ofthe ATA number.430 Assemble Modular Sections The second echelon of assembly consistingof assembling subassemblies into modularsections. The modular section is identified bythe second element of the ATA number.440 Assemble Subassemblies The first echelon of assembly consisting ofassembling piece parts into subassemblies.The subassemblies are identified by the thirdelement of the ATA number.450 Install/Close Items Removed/Opened forAccessInstallation or closing of access plates, closingof ports, installation of components, tubingor any item which was removed or opened inorder to provide access to perform the task.EFFECTIVITYALL 23-15-30 Page 13 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Code Function Definition460 Assemble Accessory Assemble accessory components.470 Assemble Accessory Subassembly Assembly of accessory subassemblycomponents.480 Install Test Equipment Install equipment and instrumentation requiredfor accessory component test.490 Assemble Support Equipment Any assembly required to maintain supportequipment.500 MATERIAL HANDLING510 Shipping Themovementofanypart,subassembly,assembly, or component from the time it ispackaged until it reaches its destination.520 ReceivingThe receipt activity for any incoming part,subassembly, assembly, or component.530 Packing Installing parts, subassemblies, assemblies, orcomponents into shipping containers.540 Unpacking Removing parts, subassemblies, assemblies,or components from shipping containers.550 Storage Safekeeping of parts, subassemblies,assemblies, or components until required foruse.560 Marshaling/Positioning Marshaling is collection of parts,subassemblies, and accessories prior torelease for assembly. Positioning is movementfrom one fixed state to another.570 Engine Ferry/Pod Maintenance Necessary preparations before and aftertransporting an engine by aircraft ferry method.580 Unassigned590 Unassigned600 SERVICING/PRESERVING/LUBRICATING610 Servicing Action required to sustain a unit or system inproper operating status including priming withapplicable fluids prior to use.EFFECTIVITYALL 23-15-30 Page 14 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Code Function Definition620 Preserving Preparation of a unit, part, assembly, etc.,for safekeeping from decomposition ordeterioration. Includes preparation for storage(applying a preservative layer, desiccants, etc.).630 DepreservingRemoving preservatives, desiccants, etc., froma unit, part, assembly, etc., prior to installationor operation.640 Lubricating Applying oil, grease, dry film, or siliconlubricants on moving parts to reduce frictionor cool the item.650 Unassigned660 Unassigned670 Unassigned680 Unassigned690 Unassigned700 TESTING/CHECKING710 Oil Flow Measuring the flow of oil through componentsor compartments under specific conditions.720 Air Flow Measuring the flow of air through componentsor compartments under specific conditions.730 Fuel Flow Function checks and flow measurementsthrough the part or system being tested.740 Water Flow Function checks and flow measurementsthrough the part or system being tested.750 Electrical/Return to Service Functional tests (manual or ATE) of the systemor component as well as measurement ofelectrical or electronic parameters designed todetermine whether the item can be returned toservice. May include fault isolation proceduresfor components that require close correlationbetween test results and fault indications.760 Engine Operation of an engine to establish systemsfunction or operation under specific conditionsto measure performance.770 Accessory/Bite Te s t ing of an accessory to ensure properoperation or function.780 Pressure Check Testing to establish the ability of a normallypressurized component or system to operateproperly.EFFECTIVITYALL 23-15-30 Page 15 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Code Function Definition790 Leak Check Determine the ability of a component or systemto operate without leaking.800 MISCELLANEOUS810 Fault Isolation Operation of an engine at constant thrust levelor identical Engine Pressure Ratio (EPR) tolocate the prime suspect deficient system:operating an improperly functioning system orcomponent to locate the cause; or performinga series of checks to isolate a failed part orcomponent.820 Adjusting/Aligning/Calibrating Makingaphysical correction to ensureproper placement or operation of a system orcomponent.830 Rigging Hooking-up, arranging, or adjusting acomponent or accessory linkage for properoperation.840 Service Bulletin Incorporation Performing the work specified in theservice bulletin. Provides for identificationof modification tasks at the task level withsubtasks recognizing any functional changes(chemical, visual/dimensional, cleaning,machining, etc.) necessary to incorporate theservice bulletin.850 PN Change/Re-identification Change of PN, application of PN by transfer,engrave repair number, etc.860 Unassigned870 Description and Operation Electrical and mechanical description of theunit or component. Includes leading particulars,descriptions, limitations, specifications, andtheory of operation.880 Approved Vendor Processes Includes processes that may be proprietaryand controlled by a particular manufacturer, orby nonproprietary and approved for applicationby conforming vendors.890 Airline Maintenance Program (Customer Use)900 Unassigned910 Special Equipment Maintenance Identification of tasks to maintain specialsupport equipment.920 Standard Equipment Maintenance Identification of tasks to maintain standardsupport equipment.EFFECTIVITYALL 23-15-30 Page 16 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Code Function Definition930 Tool Fabrication Includes fabricating any tool for whichprocedures to use are included in the manual.940 Special Tools, Equip, and Consumables Listing Listing of all special tools, standard equipment,special equipment, and consumables requiredto perform maintenance on the unit orcomponent.94A Consumables94B Special Tools/Non Std Tools94C Fixtures/Test Equipment94D Standard Tools950 Illustrated Parts List (Detailed Parts List) Section of IPL/IPC that contains partsdescription and identification in top-down breakdown sequence.960 Illustrated Parts List (Equipment DesignationIndex)Section of IPL/IPC that contains equipmentdesignators cross-referenced to detailed partslist.970 Illustrated Parts List (Numerical Index) Section of IPL/IPC that contains analphanumeric listing of all parts in the unitcross-referenced to the detailed parts list.980 Illustrated Parts List (Alternate Vendor Index) Optional section of IPL/IPC that contains analphanumeric listing of all parts in the unit thathave more than one vendor source.990 Illustrations, Tables, Front Matter, Etc.99A Ta b l e s99B Illustrations99C Front Matter Pageblock (TASK Level MTOSS)Front Matter Task (Collection of SubtaskMTOSS)99D Access99E References99F General/Introduction2. Customer Support (TASK 23-15-30-99F-802-A01)A. Honeywell Aerospace Online Technical Publications Website (Subtask 23-15-30-99F-007-A01)(1) Go to the Honeywell Online Technical Publications Website at http://www.myaerospace.com• To download or see publications online• To order a publication• To tell Honeywell of a possible data error in a publication.EFFECTIVITYALL 23-15-30 Page 17 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300B. Global Customer Care Center (Subtask 23-15-30-99F-008-A01)(1) If you do not have access to the Honeywell Technical Publications Website, or if you need tospeak to personnel about non-Technical Publication matters, the Honeywell Aerospace GlobalCustomer Care Center gives 24/7 customer service to Air Transport & Regional, Business &General Aviation, and Defense & Space customers around the globe.• Telephone: 800-601-3099 (Toll Free U.S.A./Canada)• Telephone: 602-365-3099 (International)• Telephone: 00-800-601-30999 (EMEA Toll Free)• Telephone: 420-234-625-500 (EMEA Direct).3. References (TASK 23-15-30-99F-803-A01)A. Honeywell/Vendor Publications (Subtask 23-15-30-99F-009-A01)(1) Not applicable.B. Other Publications (Subtask 23-15-30-99F-010-A01)(1) These publications are standard references:• The United States GPO Style Manual 2000 (available at http://www.gpoaccess.gov/stylemanual/browse.html)• IEEE Std 260, Standard Letter Symbols for Units of Measurement (available from theAmerican National Standards Institute, New York, NY)• ASME Y14.38, Abbreviations for Use on Drawings and in Text (available from the AmericanNational Standards Institute, New York, NY)• H4/H8 CAGE Codes (available at http://www.logisticsinformationservice.dla.mil)• IEEE 315/ANSI Y32.2, Graphic Symbols for Electrical and Electronics Diagrams (availablefrom the American National Standards Institute, New York, NY)• TSO-C132 Geosynchronous Aeronautical Mobile Satellite Services Earth Station Equipment• ARINC 781 Mark 3 Aviation Satellite Communications System• ARINC 758 Communications Management Unit Mark 2• DO-160E Environmental Conditions and Test Procedures for Airborne Equipment• DO-178B Software Considerations in Airborne Systems and Equipment Certification• DO-254 Design Assurance Guidance for Airborne Electronic Hardware.C. Certification and Approvals (Subtask 23-15-30-99F-011-A01)(1) Installation of the A350 SDU and SCM system on an aircraft typically requires the approvalof the appropriate government air/radio authority (such as Transport Canada, the FAA, theJAA, etc.). Honeywell highly recommends contacting the appropriate authorities early in thesystem-planning phase to minimize approval/certification issues that could delay releaseof the aircraft.(2) The conditions and tests for TSO approval of this article are minimum performance standards.Those installing this article, on or within a specific type or class of aircraft, must determinethat the aircraft installation conditions are within the TSO standards. TSO articles must havedifferent approval for installation in an aircraft. The article can be installed only according to 14CFR part 43, or the applicable airworthiness requirements.(3) Contact Honeywell for more information on certification and approval issues.EFFECTIVITYALL 23-15-30 Page 18 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-13004. Acronyms and Abbreviations (TASK 23-15-30-99F-804-A01)A. General (Subtask 23-15-30-99F-012-A01)(1) The abbreviations are used in agreement with ASME Y14.38.(2) Acronyms and non-standard abbreviations used in this publication are as follows:List of Acronyms and AbbreviationsTerm Full TermAC alternating currentACMM abbreviated component maintenance manualADIRU air data inertial reference unitAFDX avionics full duplex switched ethernetAMM aircraft maintenance manualAMSS aeronautical mobile satellite servicesAMU audio management unitANSI American National Standards InstituteAORE Atlantic Ocean Region-EastAORW Atlantic Ocean Region-WestARINC Aeronautical Radio, IncorporatedASME American Society of Mechanical EngineersATA Air Transport AssociationATE automated test equipmentBITE built-in test equipmentBP bottom plugbps bits per secondC CelsiusCAGE commercial and government entityCFR code of federal regulationCMS central maintenance systemCRES corrosion resistant steelDC direct currentDLCS data loading and configuration systemDLNA diplexer/low noise amplifierEMEA Europe, the Middle East, and AfricaESDS electrostatic discharge sensitiveEST Eastern Standard TimeF FahrenheitFAA Federal Aviation AdministrationEFFECTIVITYALL 23-15-30 Page 19 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300FWS flight warning systemGES ground earth stationGPO Government Printing OfficeHGA high gain antennaHMI human machine interfaceHPA high power amplifierhr hourHz HertzI/O input/outputICA Instructions for Continued AirworthinessICAO International Civil Aviation OrganizationIEC International Electrotechnical CommissionIEEE Institute of Electrical and Electronics EngineersIM interactive modein-lb inch-poundIOR Indian Ocean RegionIPC iIlustrated parts catalogIPL illustrated parts listISDN integrated services digital networkJAA Joint Aviation Authoritykbps kilobits per secondkg kilogramLED light emitting diodeLES land earth stationLGERS landing gear extension/retraction systemmA milliampereMAX maximumMCU modular concept unitMEL minimum equipment listMES mobile earth stationMHz megahertzmm millimeterMP middle plugMPDS mobile packet data serviceMTOSS maintenance task oriented support systemNm newton meterNo. numberEFFECTIVITYALL 23-15-30 Page 20 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300ORT owner requirements tablePA power amplifierPN part numberPOR Pacific Ocean RegionRF radio frequencyRMA return material authorizationRMP radio management panelRMU radio management unitRTCA Radio Technical Commission for AeronauticsSATCOM satellite communicationsSBB swift broadbandSCM satellite data unit configuration moduleSDIMM system description, installation, and maintenance manualSDU satellite data unitSI International System of UnitsSIS standalone identification systemSRU shop replaceable unitSTC supplemental type certificateTP top plugTSO technical standing orderU.S.A. United States of AmericaUSIM universal subscriber identity moduleUSMS United States Measurement SystemVAC volt, alternating currentVDC volt, direct current5. Process Verification (TASK 23-15-30-99F-805-A01)A. Verification Data (Subtask 23-15-30-99F-013-A01)(1) Honeywell does a verification of these technical instructions by demonstration or by simulationof the necessary procedures. Demonstration shows that the procedures were checked by theuse of the manual. Simulation shows that the applicable personnel looked at the procedurein the manual and that the procedure is technically correct. The dates of verification forthis manual are given in Table 4.EFFECTIVITYALL 23-15-30 Page 21 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Table 4. Verification DataSection Method DateTesting and Fault Isolation 1Demonstration 14 Nov 2012NOTE:1Only the TESTING portion of the TESTING AND FAULT ISOLATION section was done by demonstration.DESCRIPTION AND OPERATION1. Description (TASK 23-15-30-870-801-A01)A. General (Subtask 23-15-30-870-001-A01)(1) This section contains a description of the A350 SDU and SCM.(2) The A350 SATCOM avionics products developed under this program complement HoneywellSATCOMs existing range of SATCOM products. The Honeywell furnished A350 SATCOMavionics, in concert with the amplifier and antenna subsystem, achieves all of the requirementsfor providing AMSS by facilitating airborne satellite communications. These servicescomprise Classic Aero-H+, Swift64 and SBB as described above provided by Inmarsat andits designated service provider agencies.(3) The A350 SATCOM avionics is an integral part of the complete L-band Inmarsat SATCOMsystem and comprises of the following components:• SDU PN 1458-A-1100• SCM PN 1458-A-1300.(4) Refer to Table 5 for the SDU leading particulars.(5) Refer to Table 6 for the SCM leading particulars.Table 5. SDU Leading ParticularsCharacteristic SpecificationLength 14.58 inches (370.3 mm)Width 7.52 inches (191.0 mm)Height 7.85 inches (199.4 mm)Weight 18.08 pounds (8.2 kg)Heating and cooling:• Cooling air ARINC 600•Flowrate 110.2 lb/hr (50 kg/hr), 104 F(40C) (MAX) air• Pressure drop 0.2 ±0.12 inH2O(5±3mmH2O)Mounting information 6 MCU tray as per ARINC 600Electrical interfaces:• Power/Control interface ARINC 781Power requirements:EFFECTIVITYALL 23-15-30 Page 22 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Characteristic Specification• Input voltage (AC) 96 to 122 VAC, 300 to 900 Hz• Input voltage (DC) 18 to 32.3 VDCPower consumption 300 mA if operated with an external FMPA400 mA if operated as standaloneTable 6. SCM Leading ParticularsCharacteristic SpecificationLength 4.75 inches (120.7 mm)Width 4.00 inches (101.6 mm)Height 1.00 inch (25.4 mm)Weight 0.66 pound (0.30 kg)Mounting information 4 x 0.125 inch (3.18 mm) holes on 3.3 x 3.50 inches(88.9 mm) spacing, per attachment 1-6 of ARINC781Electrical interfaces:•Power/Control interface ARINC 781Power requirements +12 volts ±5% (derived from SDU)(6) Refer to Figure 3 (GRAPHIC 23-15-30-99B-803-A01) for the SDU and Figure 4 (GRAPHIC23-15-30-99B-804-A01) for detailed information on the physical characteristics of the SDU.EFFECTIVITYALL 23-15-30 Page 23 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Figure 3. (Sheet 1 of 1) SDU (GRAPHIC 23-15-30-99B-803-A01)EFFECTIVITYALL 23-15-30 Page 24 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Figure 4. (Sheet 1 of 2) SDU Outline and Installation Drawing (GRAPHIC 23-15-30-99B-804-A01)EFFECTIVITYALL 23-15-30 Pages 25/26 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
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ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Figure 4. (Sheet 2 of 2) SDU Outline and Installation Drawing (GRAPHIC 23-15-30-99B-804-A01)EFFECTIVITYALL 23-15-30 Pages 27/28 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
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ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300(7) Refer to Figure 5 (GRAPHIC 23-15-30-99B-805-A01) for the SCM and Figure 6 (GRAPHIC23-15-30-99B-806-A01) for a detailed information on the physical characteristics of the SCM.Figure 5. (Sheet 1 of 1) SCM (GRAPHIC 23-15-30-99B-805-A01)EFFECTIVITYALL 23-15-30 Page 29 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Blank PageEFFECTIVITYALL 23-15-30 Page 30 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Figure 6. (Sheet 1 of 2) SCM Outline and Installation Drawing (GRAPHIC 23-15-30-99B-806-A01)EFFECTIVITYALL 23-15-30 Pages 31/32 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
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ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Figure 6. (Sheet 2 of 2) SCM Outline and Installation Drawing (GRAPHIC 23-15-30-99B-806-A01)EFFECTIVITYALL 23-15-30 Pages 33/34 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
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ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300(8) Table 7 lists the equipment covered by this manual.Table 7. Equipment DescriptionEquipment PN Description/NotesSDU 1458-A-1101 The central communications processing and control unit.SCM 1458-A-1300 Stores installation configuration, ORT, ICAO, and USIM information.B. Job Setup Data (Subtask 23-15-30-99C-001-A01)(1) The list that follows identifies Honeywell publications that are related to this section:• Not applicable.C. A350 SDU and SCM (Subtask 23-15-30-870-002-A01)(1) SDU(a) The SDU is the central communications processing and control unit, largely determiningthe functionality of the complete SATCOM system. The signal-in-space parameters aredetermined by the SDU in relation to modulation/demodulation, error correction, coding,interleaving and data rates associated with the communication channel(s). The SDUcontains circuits for conversion of digital and/or analog inputs/outputs to/from RF, andtypically contains a PA module. The SDU interfaces at L-band with the HPA and DLNAand also controls the antenna.(b)The SDU is capable of sending and receiving various data rates. The rate is dynamicallyselected by the individual applications and by pragmatic assessment of current operatingconditions.(2) SCM(a) The SCM is an external peripheral of the SDU and provides a dedicated interface to theSDU. It stores aircraft specific installation configuration, ORT configuration, and ICAOidentities. The SCM also contains four USIM that store subscriber information for theSBB network.(b) By storing configuration information independent of the SDU, the SCM facilitatesefficient SDU replacement. A new SDU that replaces a faulty SDU does not require anyconfiguration. All configuration information is obtained from the SCM.(3) Refer to Figure 7 (GRAPHIC 23-15-30-99B-807-A01) for the A350 SATCOM Avionics System.EFFECTIVITYALL 23-15-30 Page 35 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Figure 7. (Sheet 1 of 1) A350 SATCOM Avionics System (GRAPHIC 23-15-30-99B-807-A01)D. Purpose of the Equipment (Subtask 23-15-30-870-003-A01)(1) The A350 SATCOM Avionics System enables airborne satellite communications, including thefollowing services:• AERO or “Classic” AERO - This service provides packet data services at 600, 1200, or10500 bps over the PRT channel combination and half-rate circuit switched voice or dataservice over the C channel.• Swift64 - This service provides circuit switched 64 kbps, and 56 kbps mobile ISDN. Inaddition, it provides packet switched MPDS up to 64 kbps.• SBB - This service will give broadband circuit and packet switched services with datarates of 128 kbps and higher per channel.(2) The following interfaces are provided for the above defined services:(a) AMU (x2) - Provides voice and voice control discretes:• 4 wire port (x2) - 4 wire voice communication system used for AERO voice servicefrom the cockpit• Call and Mic ON discretes.(b) Ethernet Port (x2) - one used at any one time (under ORT control) for packet dataservices access(c) RMP (x3) - The RMP is installed in the cockpit and interfaces directly to the A350 SDUover a standard ARINC 429 interface. The RMP implements the HMI necessary to controlradio and satellite communication equipment. The RMP enables user to:EFFECTIVITYALL 23-15-30 Page 36 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300• Place calls manually or from a directory• Accept, reject, preempt incoming calls• View and change SATCOM settings and options• Select auto login or control logon with manual logon and logoff options• Control cabin communications (cabin calls enable/disable).(3) Refer to Figure 8 (GRAPHIC 23-15-30-99B-808-A01) for the A350 SATCOM Avionics Systemblock diagram.EFFECTIVITYALL 23-15-30 Page 37 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Figure 8. (Sheet 1 of 1) A350 SATCOM Avionics System Block Diagram (GRAPHIC 23-15-30-99B-808-A01)EFFECTIVITYALL 23-15-30 Page 38 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-13002. Operation (TASK 23-15-30-870-802-A01)A. General (Subtask 23-15-30-870-004-A01)(1) The SDU is an integral component in an AES. Together with the SCM, DLNA, and HGAsubsystem, it achieves all of the requirements for providing AMSS by facilitating airbornesatellite communication services over the Inmarsat network. These services comprise ClassicAero-H+, Swift64, and SBB.(2) The SCM is a dedicated peripheral of the SDU and stores aircraft specific installationconfiguration critical to the operation of the AES.B. Satellite Network Overview (Subtask 23-15-30-870-005-A01)(1) This section provides a brief overview of the Inmarsat I-3/I-4 satellite communication system.Satellite communication systems include global satellite networks, GES/LES, and AES/MES.(2) GES and AES are the terms associated with Aero-H+ services.(3) Satellite communication systems give users with long-range voice and data communication byaccessing global satellite and ground communications networks.(4) Inmarsat is an international organization that operates and maintains the satellites and satellitenetworks. Inmarsat operates multiple geostationary satellites. Each satellite is•AORE•AORW•IOR•POR.(5) All I-3 satellites give worldwide telecommunication services for aviation, shipping, andland-mobile terminal users. The satellites connect to ground telecommunication systemsthrough a network of GESs.(6) In addition to the services offered by I-3 satellites, the I-4 satellites also give worldwidebroadband service, SBB. Each I-4 satellite has 19 wide spot beams, 228 narrow spot beams,and is capable of accommodating many different, simultaneous SBB sessions. The SBBservice and I-4 satellites support broadband applications such as videoconferencing andvideo-streaming.(7) At the time of publishing, three I-4 satellites are operational:•Americas•EMEA• Asia-Pacific.(8) The satellite communication avionics (ARINC 781 systems), typically in conjunction with anantenna subsystem, act as an AES/MES. The combined system provides users with a dataand voice communications link to the satellite network and global telecommunications system.(9) A simplified satellite communications system is shown in Figure 9 (GRAPHIC23-15-30-99B-809-A01).EFFECTIVITYALL 23-15-30 Page 39 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Figure 9. (Sheet 1 of 1) Simplified Aeronautical Satellite Communications System(GRAPHIC 23-15-30-99B-809-A01)C. Software Specifications (Subtask 23-15-30-870-006-A01)(1) The A350 SDU and SCM operating software meets RTCA/DO-178B Level D requirements.D. Hardware Specifications (Subtask 23-15-30-870-007-A01)(1) The A350 SDU and SCM hardware meets RTCA/DO-254 Level D requirements.E. Equipment Description (Subtask 23-15-30-870-008-A01)(1) Mechanical(a) The A350 SATCOM Avionics System consists of the following LRUs:•SDU•SCM• FMPA (optional).(b) The SDU is divided into several SRUs that are electrically connected through thebackplane. Various SRUs are also connected with the RF cables.EFFECTIVITYALL 23-15-30 Page 40 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300(c) The SCM is a dedicated peripheral of the SDU. The SCM package envelope andmounting arrangement conform to ARINC 781-2. The interconnecting cable between theSDU and the SCM must not be longer than 393.7 inches (10 meters).1WeightaThe combined maximum weight of the A350 SDU and SCM is 18.72 pounds(8.5 kg), exclusive of mounting trays, fans, and interconnecting cable.2Form FactoraThe A350 SDU and SCM form factors are compliant with ARINC 781.3ConnectorsaThe SDU uses two external interface connectors:• Rear Connector - accommodates coaxial and signal interconnections inthe TP insert, quadrax and signal interconnections in the MP insert, andcoaxial, and power interconnections in the BP insert. The top insert pinassignment are in accordance with ARINC 781 with the following deviationsas shown in the Table 8.• Front Connector - an RJ45 and 9S DSUB connector providing 10bTEthernet and an RS-232 maintenance interface to the control processor.Table 8. SDU Rear Connector Pin DeviationsDescription Pin DeviationCP maintenance TXD TP01A ATE p i n 1CP maintenance RXD TP01B ATE p in 2CP/DP maintenance GND TP01C ATE p i n 3Data I/O processor maintenance TXD TP01D ATE p i n 4Data I/O processor maintenance RXD TP01E ATE p i n 5CC1 processors #1 and #2 maintenance GND TP01F ATE p i n 6CC1 processor #1 maintenance TXD TP01G ATE p i n 7CC1 processor #1 maintenance RXD TP01H ATE p i n 8CC1 processor #2 maintenance TXD TP01J ATE p i n 9CC1 processor #2 maintenance RXD TP01K ATE p i n 1 0Download security TP02A ATE p i n 1 1No connect TP02B ATE p i n 1 2Voice processor maintenance GND TP02C ATE p i n 1 3Voice processor maintenance TXD TP02D ATE p i n 1 4Voice processor maintenance RXD TP02E ATE p i n 1 5CC2 and CC3 maintenance GND TP02F ATE p i n 1 6CC2 processor maintenance TXD TP02G ATE p i n 1 7CC2 processor maintenance RXD TP02H ATE p i n 1 8EFFECTIVITYALL 23-15-30 Page 41 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Description Pin DeviationCC3 processor maintenance TXD TP02J AT E p i n 1 9CC3 processor maintenance RXD TP02K AT E p i n 2 0(d) The SCM uses a 15 pin D-type male connector and locking screws. Pin assignments areconsistent with ARINC 781 as shown in Table 9.Table 9. SCM D-Type Connector Pin AssignmentPin Number Description1Data to SDU A (RS422)2Data to SDU B (RS422)3Data from SDU A (RS422)4Data from SDU B (RS422)5Reserved - RS232 GND (used for shop loading)6Spare7Chassis GND8Power input (+8 to +15 volts)9Reserved - Enable RS232 (used for shop loading)10 Reserved - 0 volt strap output (used for shop loading)11 Spare12 Reserved - RS232 Tx (used for shop loading)13 Reserved - RS232 Rx (used for shop loading)14 Spare15 Power return (0 volt)(2) Electrical(a) The SDU is divided into the following SRUs:• Channel card (2)• Multi-channel card• SDU control processor and data I/O processor• AFDX mezzanine card• SDU voice processor• Combiner and splitter• Backplane• Oven controlled crystal oscillator• Power supply•SCM.EFFECTIVITYALL 23-15-30 Page 42 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300(b) The major interfaces of the SDU are shown in Table 10.Table 10. SDU Functional InterfacesInterface Description TypeHGA (x1) HGA/DLNA A429 busHPA (x1) HPA A429 busRMP (x3) RMU (for Control and Display) A429 busAFDX (x2) AFDX AFDX busADIRU virtual links AFDX VLLGERS virtual links AFDX VLCMS virtual links AFDX VLDLCS virtual links AFDX VLFWS virtual links AFDX VLDFDRS virtual links AFDX VLSPP virtual links AFDX VLSCM (x1) SCM RS422SCM 12V power SCM power PowerSIS (x1) SIS I2CServicing Front panel accessible service port for data log retrieval EthernetMiscellaneous ARINC discrete input, outputs and configuration straps Discretes(c) The frequency of operation is as follows:• Receive band - 1525.0 to 1559.0 MHz• Transmit band - 1626.5 to 1660.5 MHz.(3) Refer to Figure 10 (GRAPHIC 23-15-30-99B-810-A01) for the System Interconnection Drawing.EFFECTIVITYALL 23-15-30 Page 43 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Blank PageEFFECTIVITYALL 23-15-30 Page 44 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Figure 10. (Sheet 1 of 3) System Interconnection Drawing (GRAPHIC 23-15-30-99B-810-A01)EFFECTIVITYALL 23-15-30 Pages 45/46 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
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ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Figure 10. (Sheet 2 of 3) System Interconnection Drawing (GRAPHIC 23-15-30-99B-810-A01)EFFECTIVITYALL 23-15-30 Pages 47/48 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
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ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Figure 10. (Sheet 3 of 3) System Interconnection Drawing (GRAPHIC 23-15-30-99B-810-A01)EFFECTIVITYALL 23-15-30 Pages 49/50 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
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ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300TESTING AND FAULT ISOLATION1. Planning Data (TASK 23-15-30-99C-801-A01)A. Reason for the Job (Subtask 23-15-30-99C-002-A01)(1) Use the test procedures in this section to test and isolate faults.(2) The function of the test procedures is to find if there is a failure in the operation of the SDU.B. Job Setup Data (Subtask 23-15-30-99C-003-A01)(1) You can use equivalent alternatives for the special tools, fixtures, equipment, and consumablematerials. The user must find equivalent alternatives.(2) Refer to Table 11 for the specified special tools, fixtures, and equipment in this section.(3) Refer to H4/H8 CAGE Codes (available at http://www.logisticsinformationservice.dla.mil) formanufacturer’s address.Table 11. Special Tools, Fixtures, and EquipmentNumber Description SourceNot applicable Not applicable Not applicableWARNING: BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS’ MATERIALSAFETY DATA SHEETS. SOME MATERIALS CAN BE DANGEROUS.CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO HONEYWELLSPECIFIED MATERIALS. MATERIALS THAT ARE NOT EQUIVALENT CANCAUSE DAMAGE TO THE EQUIPMENT AND CAN MAKE THE WARRANTY NOTAPPLICABLE.(4) Refer to Table 12 for the specified consumable materials in this section.Table 12. ConsumablesNumber Description SourceNot applicable Not applicable Not applicable(5) The list that follows identifies Honeywell publications that are related to this section:• Not applicable.EFFECTIVITYALL 23-15-30 Page 51 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-13002. Procedure (TASK 23-15-30-700-801-A01)A. Job Setup (Subtask 23-15-30-810-001-A01)WARNING: BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS’ MATERIALSAFETY DATA SHEETS. SOME MATERIALS CAN BE DANGEROUS.CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO HONEYWELLSPECIFIED MATERIALS. MATERIALS THAT ARE NOT EQUIVALENT CANCAUSE DAMAGE TO THE EQUIPMENT AND CAN MAKE THE WARRANTY NOTAPPLICABLE.CAUTION: DO NOT DROP OR HIT THE SDU DURING THESE PROCEDURES. THE SDUCONTAINS AN ASSEMBLY THAT CAN BE DAMAGED FROM INCORRECT USE.CAUTION: DO THESE PROCEDURES IN A CLEAN ENVIRONMENT TO PREVENT DAMAGETO MECHANICAL COMPONENTS.(1) Obey the precautions.B. BITE (Subtask 23-15-30-810-002-A01)(1) On power up, the SDU performs a number of invasive BITE tests that are not possible duringnormal SDU system operation.(2) The failure of some of these tests will cause the equipment to go into fail safe mode andprevent RF transmission. Once entered, safe mode cannot be exited except by fixing theunderlying condition and rebooting.(3) The SDU implements security segregation whereby the control domain (responsible for classicaero cockpit functionality) is separated from the data domain (responsible for Ethernet andswift cabin functionality).(4) The SDU will respond to a segregation failure by closing-down the user data (Ethernet andswift RF) interfaces and reporting the condition to both the CMS and security event loginterfaces. If the SDU cannot verify that the user data (Ethernet and swift RF) interfaces areclosed then it will enter a safe mode whereby all interfaces are terminated.C. LEDs (Subtask 23-15-30-810-003-A01)(1) The front panel of the SDU has two LEDs to indicate unit status:• One green LED labelled “Power”• One red LED labelled “Fault”.D. Self-Test (Subtask 23-15-30-810-004-A01)(1) The front panel of the SDU has a recessed button labelled “Test”:• To reset the unit, press and hold the test button for 5 seconds.• To initiate self-test (when no LEDs are flashing), momentarily press the test button.E. Unit Software Load Procedure (Subtask 23-15-30-810-005-A01)(1) Field-loading of SDU software is not supported. All software upgrades must be accomplishedby the manufacturer.(2) Field-loading of ORT software is supported through 615A-2 through Ethernet 3.EFFECTIVITYALL 23-15-30 Page 52 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300F. Fault Isolation (Subtask 23-15-30-810-006-A01)(1) Testing(a) Power-Up Test1The power-up test verifies basic SDU functions and uses the front-panel LEDsto communicate the results.2The fault LED indicates several possible internal SDU system problems, not specificproblems, refer to Table 13.Table 13. LED Status Indicators TablePower LED State Fault LED State Indicates ActionON for 60 seconds duringboot-up, then OFFON Normal operation duringboot-up-OFF OFF Normal operation -OFF ON LRU fault Use Interactive ModeBITE via CMS to confirmfault, remove the LRUand return it to the factoryOFF Flashing System fault, notnecessarily with theA350 LRUUse Interactive ModeBITE via CMS to isolatefault, use confirmationmethod of suspect LRUto confirm faultFlashing Flashing Self-test -3Some of the possible LRU faults indicated by the lit fault LED include:• Software image incorrect or corrupted• Internal busses non-operational• Internal processors non-functional.4To fi n d t h e equipment or connection that failed, check the interactive mode BITEpages. Some examples of possible SDU system faults indicated by the flashingfault LED includes:• Strapped configuration does not match the capabilities of the A350 SDU systemor the configuration in the ORT - check the wiring and strapping• Code images in the SDU do not match the expected configuration - check thesoftware version and your configuration• RF path from the SDU to D/LNA failed - check wiring and cable loss settings• USIM not detected.(b) Troubleshooting Guidelines1If the front-panel LEDs signal that the SDU is operating normally and some servicesare still not available:• Verify your SATCOM system - view to satellite, SCM installedEFFECTIVITYALL 23-15-30 Page 53 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300• Verify your account information - proper login, Inmarsat registration• Check the SATCOM system using CMS interactive mode maintenancecommands.(c) Aero-H+ Voice or Data Calls1Before you can make any Aero-H+ voice or data calls, make sure:• The Inmarsat registration paperwork is filled out and submitted to the serviceprovider of choice• The aircraft has a clear view to the satellite• Proper power is applied to the SATCOM system• The INS is aligned - check via IM BITE through the CMS interface• AIC positional data is provided on the ADIRU interface - check via IM BITEthrough the CMS interface• A valid ICAO address is present on the SPP interface - check via IM BITEthrough the CMS interface• All ARINC 429 interfaces configured as present are present - check via IM BITEthrough the CMS interface. If any are not present, spurious faults are raised.(d) Swift 64 or SBB Calls1Before you can make any Swift 64 or SBB calls make sure:• All prerequisites for Aero-H+ calls are followed• The Aero-H+ service must be logged-on – check via RMP status in the cockpit• The LES access codes are programmed (Swift 64)• The forward IDs are present on the SPP bus – check via IM BITE through theCMS interface• The USIM modules are installed and activated with the service provider (forSBB service).(e) You can download fault logs from the SDU using the IM BITE.(2) Maintenance Aid Diagrams(a) No maintenance aid diagrams are required. Return any SDU or SCM units that failthe operational test procedure provided in this document to the manufacturer for faultisolation and repair. Refer to APPENDIX A (RMA) (PGBLK 23-15-30-1700) for thereturn procedure.(3) Schematic Change Pages(a) No schematic change pages are required. Return any SDU or SCM units that fail theoperational test procedure provided in this document to the manufacturer for faultisolation and repair. Refer to APPENDIX A (RMA) (PGBLK 23-15-30-1700) for thereturn procedure.(4) Modification History(a) There are currently no service bulletins for the SDU or SCM.G. Job Close-up (Subtask 23-15-30-810-007-A01)(1) Not applicable.SCHEMATIC AND WIRING DIAGRAMSEFFECTIVITYALL 23-15-30 Page 54 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-13001. Not ApplicableDISASSEMBLY1. Not ApplicableCLEANING1. Planning Data (TASK 23-15-30-99C-802-A01)A. Reason for the Job (Subtask 23-15-30-99C-004-A01)(1) Use these procedures to remove dust, dirt, and unwanted oil and grease. Be careful not tocause damage to the parts when you do these procedures.B. Job Setup Data (Subtask 23-15-30-99C-005-A01)(1) You can use equivalent alternatives for the special tools, fixtures, equipment, and consumablematerials. The user must find equivalent alternatives.(2) Refer to Table 14 for the specified special tools, fixtures, and equipment in this section.(3) Refer to H4/H8 CAGE Codes (available at http://www.logisticsinformationservice.dla.mil) formanufacturer’s address.Table 14. Special Tools, Fixtures, and EquipmentNumber Description SourceNot applicable Not applicable Not applicableWARNING: BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS’ MATERIALSAFETY DATA SHEETS. SOME MATERIALS CAN BE DANGEROUS.CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO HONEYWELLSPECIFIED MATERIALS. MATERIALS THAT ARE NOT EQUIVALENT CANCAUSE DAMAGE TO THE EQUIPMENT AND CAN MAKE THE WARRANTY NOTAPPLICABLE.(4) Refer to Table 15 for the specified consumable materials in this section.Table 15. ConsumablesNumber Description SourceNot applicable Not applicable Not applicable(5) The list that follows identifies Honeywell publications that are related to this section:• Not applicable.EFFECTIVITYALL 23-15-30 Page 55 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-13002. Procedure (TASK 23-15-30-100-801-A01)A. Job Setup (Subtask 23-15-30-100-001-A01)WARNING: BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS’ MATERIALSAFETY DATA SHEETS. SOME MATERIALS CAN BE DANGEROUS.CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO HONEYWELLSPECIFIED MATERIALS. MATERIALS THAT ARE NOT EQUIVALENT CANCAUSE DAMAGE TO THE EQUIPMENT AND CAN MAKE THE WARRANTY NOTAPPLICABLE.CAUTION: DO NOT DROP OR HIT THE A350 SDU AND SCM DURING THESE PROCEDURES.THE A350 SDU AND SCM CONTAINS AN ASSEMBLY THAT CAN BE DAMAGEDFROM INCORRECT USE.CAUTION: DO THESE PROCEDURES IN A CLEAN ENVIRONMENT TO PREVENT DAMAGETO MECHANICAL COMPONENTS.(1) Obey the precautions.(2) Do the procedures in a clean location.(3) When you use pressurized air to clean assemblies and parts, do not use more air pressurethan is necessary.(4) After you clean the assemblies and parts, supply protection from moisture, dust, and othercontamination until you do a visual check and assemble the component.B. Job Close-up (Subtask 23-15-30-100-002-A01)(1) Not applicable.INSPECTION/CHECK1. Planning Data (TASK 23-15-30-99C-803-A01)A. Reason for the Job (Subtask 23-15-30-99C-006-A01)(1) Use these procedures to find damage or worn parts and parts that show signs of near failure.B. Job Setup Data (Subtask 23-15-30-99C-007-A01)(1) You can use equivalent alternatives for the special tools, fixtures, equipment, and consumablematerials. The user must find equivalent alternatives.(2) Refer to Table 16 for the specified special tools, fixtures, and equipment in this section.(3) Refer to H4/H8 CAGE Codes (available at http://www.logisticsinformationservice.dla.mil) formanufacturer’s address.Table 16. Special Tools, Fixtures, and EquipmentNumber Description SourceNot applicable Not applicable Not applicableEFFECTIVITYALL 23-15-30 Page 56 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300WARNING: BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS’ MATERIALSAFETY DATA SHEETS. SOME MATERIALS CAN BE DANGEROUS.CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO HONEYWELLSPECIFIED MATERIALS. MATERIALS THAT ARE NOT EQUIVALENT CANCAUSE DAMAGE TO THE EQUIPMENT AND CAN MAKE THE WARRANTY NOTAPPLICABLE.(4) Refer to Table 17 for the specified consumable materials in this section.Table 17. ConsumablesNumber Description SourceNot applicable Not applicable Not applicable(5) The list that follows identifies Honeywell publications that are related to this section:(a) Not applicable.2. Procedure (TASK 23-15-30-210-801-A01)A. Job Setup (Subtask 23-15-30-210-001-A01)WARNING: BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS’ MATERIALSAFETY DATA SHEETS. SOME MATERIALS CAN BE DANGEROUS.CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO HONEYWELLSPECIFIED MATERIALS. MATERIALS THAT ARE NOT EQUIVALENT CANCAUSE DAMAGE TO THE EQUIPMENT AND CAN MAKE THE WARRANTY NOTAPPLICABLE.CAUTION: DO NOT DROP OR HIT THE A350 SDU AND SCM DURING THESE PROCEDURES.THE A350 SDU AND SCM CONTAINS AN ASSEMBLY THAT CAN BE DAMAGEDFROM INCORRECT USE.CAUTION: DO THESE PROCEDURES IN A CLEAN ENVIRONMENT TO PREVENT DAMAGETO MECHANICAL COMPONENTS.(1) Obey the precautions.B. General Inspection/Check Procedure of the A350 SDU and SCM (Subtask 23-15-30-210-002-A01)(1) Periodic inspections of the mechanical and electrical interfaces of the SDU and SCMcomponents to the aircraft must be completed as defined by the governing airworthinessbody’s ICA for the installation (Transport Canada, the FAA, the JAA). Refer to Paragraph 2.D.(Subtask 23-15-30-210-004-A01) for general guidelines.(2) Installation of the A350 SATCOM avionics system on an aircraft by STC obligates the aircraftoperator to include the maintenance information supplied by this manual in the operator’saircraft maintenance manual and the operator’s aircraft scheduled maintenance program.C. Instructions for Continued Airworthiness, FAR 25.1529 (Subtask 23-15-30-210-003-A01)(1) Periodic inspections of the mechanical and electrical interfaces of the A350 SDU systemcomponents to the aircraft should be completed as defined by the governing airworthinessbody’s ICA for the installation (Transport Canada, FAA, and EASA).(2) Installation of the A350 SATCOM avionics system on an aircraft by STC obligates the aircraftoperator to include the maintenance information supplied by the A350 SATCOM avionicsSDIMM in the operator’s AMM and the operator’s aircraft scheduled maintenance program.EFFECTIVITYALL 23-15-30 Page 57 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300D. Inspection/Check Schedule (Subtask 23-15-30-210-004-A01)(1) The SDU and SCM system does not require routine maintenance for continued airworthiness.(2) Follow the standard practices chapter of the AMM and do all required inspections at a minimumeach year or for every aircraft maintenance requirements and schedule.E. Unscheduled Maintenance (Subtask 23-15-30-210-005-A01)(1) Follow the standard practices chapter of the AMM and do all required inspections and repairs.F. Repair Requirements (Subtask 23-15-30-210-006-A01)(1) If functional problems occur, the SDU BITE identifies the faulty LRU.(2) For each continued airworthiness instructions, if an SDU or SCM is inoperative, use thestandard practices chapter of the AMM to:• Remove the unit.• Attach cables and wiring.• Collar applicable switches and circuit breakers, and placard them as “inoperative”.(3) Before flight, revise the equipment list and weight and balance data as applicable, and recordthe removal of the unit in the log book, refer to section 91.213 of the FAR or the aircraft MEL.(4) All repairs must be performed at Honeywell or a Honeywell approved repair facility.G. Job Close-up (Subtask 23-15-30-210-007-A01)(1) Not applicable.REPAIR1. Planning Data (TASK 23-15-30-99C-804-A01)A. Reason for the Job (Subtask 23-15-30-99C-008-A01)(1) Use these procedures for the A350 SDU and SCM to replace defective parts and replace orrepair defective subassemblies.B. Job Setup Data (Subtask 23-15-30-99C-009-A01)(1) You can use equivalent alternatives for the special tools, fixtures, equipment, and consumablematerials. The user must find equivalent alternatives.(2) Refer to Table 18 for the specified special tools, fixtures, and equipment in this section.(3) Refer to H4/H8 CAGE Codes (available at http://www.logisticsinformationservice.dla.mil) formanufacturer’s address.Table 18. Special Tools, Fixtures, and EquipmentNumber Description SourceNot applicable Not applicable Not applicableEFFECTIVITYALL 23-15-30 Page 58 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300WARNING: BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS’ MATERIALSAFETY DATA SHEETS. SOME MATERIALS CAN BE DANGEROUS.CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO HONEYWELLSPECIFIED MATERIALS. MATERIALS THAT ARE NOT EQUIVALENT CANCAUSE DAMAGE TO THE EQUIPMENT AND CAN MAKE THE WARRANTY NOTAPPLICABLE.(4) Refer to Table 19 for the specified consumable materials in this section.Table 19. ConsumablesNumber Description SourceNot applicable Not applicable Not applicable(5) The list that follows identifies Honeywell publications that are related to this section:(a) Not applicable.2. Procedure (TASK 23-15-30-300-801-A01)A. Job Setup (Subtask 23-15-30-300-001-A01)WARNING: BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS’ MATERIALSAFETY DATA SHEETS. SOME MATERIALS CAN BE DANGEROUS.CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO HONEYWELLSPECIFIED MATERIALS. MATERIALS THAT ARE NOT EQUIVALENT CANCAUSE DAMAGE TO THE EQUIPMENT AND CAN MAKE THE WARRANTY NOTAPPLICABLE.CAUTION: DO NOT DROP OR HIT THE A350 SDU AND SCM DURING THESE PROCEDURES.THE A350 SDU AND SCM CONTAINS AN ASSEMBLY THAT CAN BE DAMAGEDFROM INCORRECT USE.CAUTION: DO THESE PROCEDURES IN A CLEAN ENVIRONMENT TO PREVENT DAMAGETO MECHANICAL COMPONENTS.(1) Obey the precautions.B. General Repair Instructions (Subtask 23-15-30-300-002-A01)(1) If functional problems occur, the SDU BITE identifies the faulty LRU - check via IM Bitethrough the CMS interface.(2) As per continued airworthiness instructions, if an SDU or SCM is inoperative, use the standardpractices chapter of the AMM to remove the unit, secure cables and wiring, collar applicableswitches and circuit breakers, and placard them as “inoperative”.(3) Before flight, revise the equipment list and weight and balance data as applicable, and recordthe removal of the unit in the log book. Refer to Section 91.213 of the FAR or the aircraft’s MEL.(4) All repairs must be performed at the Honeywell factory.C. Job Close-up (Subtask 23-15-30-300-003-A01)(1) Not applicable.ASSEMBLY1. Not ApplicableEFFECTIVITYALL 23-15-30 Page 59 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300FITS AND CLEARANCES1. Planning Data (TASK 23-15-30-99C-805-A01)A. Reason for the Job (Subtask 23-15-30-99C-010-A01)(1) This section gives the fits and clearances used when the A350 SDU and SCM was made.(2) This section gives the torque data required for repair and assembly of the A350 SDU and SCM.B. Job Setup Data (Subtask 23-15-30-99C-011-A01)(1) Not applicable.2. Procedure (TASK 23-15-30-220-801-A01)A. Job Setup (Subtask 23-15-30-220-001-A01)(1) Not applicable.B. Fits and Clearances of the A350 SDU and SCM (Subtask 23-15-30-220-002-A01)(1) Refer to Table 20 when you do the procedures in INSTALLATION (PGBLK 23-15-30-13000).Table 20. Fits and ClearancesNomenclature/DescriptionFigure - Item Requirement/DimensionMinimum clearance between the SDU and any otherequipment installed above it0.50 inch (12.7 mm)C. Torque Values (Subtask 23-15-30-220-003-A01)(1) Tighten nuts, bolts, screws, and tube fittings to the standard torque unless specified differently.Refer to FAA Manual FAA-H-8083-30, Aviation Maintenance Technician Handbook, forstandard torque.(2) Tighten nuts, bolts, screws, and tube fittings to the standard torque unless specified differently.(3) Tighten fasteners installed through non-elastic boundaries to remove visible clearance betweenthe parts. Monitor the rundown torque necessary just before the fastener becomes tight. Thentighten to the final torque (refer to Table 21 for the correct thread size) and add the rundowntorque. This procedure is sufficient for all fasteners not shown under torque values below.Refer to Table 22 for final torque data after rundown torque.(4) Tighten fasteners installed through elastic boundaries (sealed by means of a diaphragm orsimilar elastomeric gasket) equally to get a pressure tight seal.Table 21. Thread Size and Torque DataTorque in-lb (Nm)Thread Size Aluminum Fastener CRES Fastener6-32 5 (0.565) 10 (1.13)8-32 10 (1.13) 20 (2.26)10-24 15 (1.695) 35 (3.955)1/4-20 45 (5.085) 75 (8.475)EFFECTIVITYALL 23-15-30 Page 60 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Torque in-lb (Nm)Thread Size Aluminum Fastener CRES Fastener5/16-18 80 (9.04) 160 (18.08)3/8-24 140 (15.82) 275 (31.075)Table 22. Final Torque DataThread Size Approximate Turn After Run-Down6-32 45 degrees8-32 60 degrees10-24 40 degrees1/4-20 40 degrees5/16-18 40 degrees3/8-24 60 degreesD. Specified Torque Values (Subtask 23-15-30-220-004-A01)(1) Not applicable.E. Job Close-up (Subtask 23-15-30-220-005-A01)(1) Not applicable.SPECIAL TOOLS, FIXTURES, EQUIPMENT, AND CONSUMABLES1. Planning Data (TASK 23-15-30-99C-806-A01)A. General (Subtask 23-15-30-99C-012-A01)(1) No special tools, fixtures, or equipment is required. Standard avionics shop tools are theonly equipment required.SPECIAL PROCEDURES1. Not ApplicableREMOVAL1. Planning Data (TASK 23-15-30-99C-807-A01)A. Reason for the Job (Subtask 23-15-30-99C-013-A01)(1) Use these procedures to remove the A350 SDU and SCM.B. Job Setup Data (Subtask 23-15-30-99C-014-A01)(1) You can use equivalent alternatives for the special tools, fixtures, equipment, and consumablematerials. The user must find equivalent alternatives.(2) Refer to Table 23 for the specified special tools, fixtures, and equipment in this section.(3) Refer to H4/H8 CAGE Codes (available at http://www.logisticsinformationservice.dla.mil) formanufacturer’s address.EFFECTIVITYALL 23-15-30 Page 61 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Table 23. Special Tools, Fixtures, and EquipmentNumber Description SourceNot applicable Not applicable Not applicableWARNING: BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS’ MATERIALSAFETY DATA SHEETS. SOME MATERIALS CAN BE DANGEROUS.CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO HONEYWELLSPECIFIED MATERIALS. MATERIALS THAT ARE NOT EQUIVALENT CANCAUSE DAMAGE TO THE EQUIPMENT AND CAN MAKE THE WARRANTY NOTAPPLICABLE.(4) Refer to Table 24 for the specified consumable materials in this section.Table 24. Consumable MaterialsNumber Description SourceNot applicable Not applicable Not applicable(5) The list that follows identifies Honeywell publications that are related to this section:• Not applicable.2. Procedure (TASK 23-15-30-000-801-A01)A. Job Setup (Subtask 23-15-30-000-001-A01)WARNING: BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS’ MATERIALSAFETY DATA SHEETS. SOME MATERIALS CAN BE DANGEROUS.CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO HONEYWELLSPECIFIED MATERIALS. MATERIALS THAT ARE NOT EQUIVALENT CANCAUSE DAMAGE TO THE EQUIPMENT AND CAN MAKE THE WARRANTY NOTAPPLICABLE.CAUTION: DO NOT DROP OR HIT THE A350 SDU AND SCM DURING THESE PROCEDURES.THE A350 SDU AND SCM CONTAINS AN ASSEMBLY THAT CAN BE DAMAGEDFROM INCORRECT USE.CAUTION: DO THESE PROCEDURES IN A CLEAN ENVIRONMENT TO PREVENT DAMAGETO MECHANICAL COMPONENTS.(1) Obey the precautions.B. General (Subtask 23-15-30-000-002-A01)(1) Only authorized technical personnel, trained in general aviation workmanship, that have abasic understanding of SATCOM systems must proceed with the following procedure.C. Removal (Subtask 23-15-30-000-003-A01)(1) If an SDU must be removed from service for repair, with power removed, disconnect allequipment from the SDU and then remove it from the ARINC tray.(2) If a SCM must be removed from service for repair, with power removed, disconnect allequipment from the SCM and then remove the four mounting screws.D. Job Close-up (Subtask 23-15-30-000-004-A01)(1) Not applicable.EFFECTIVITYALL 23-15-30 Page 62 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300INSTALLATION1. Planning Data (TASK 23-15-30-99C-808-A01)A. Reason for the Job (Subtask 23-15-30-99C-015-A01)(1) Use these procedures to install the A350 SDU and SCM.B. Job Setup Data (Subtask 23-15-30-99C-016-A01)(1) You can use equivalent alternatives for the special tools, fixtures, equipment, and consumablematerials. The user must find equivalent alternatives.(2) Refer to Table 25 for the specified special tools, fixtures, and equipment in this section.(3) Refer to H4/H8 CAGE Codes (available at http://www.logisticsinformationservice.dla.mil) formanufacturer’s address.Table 25. Special Tools, Fixtures, and EquipmentNumber Description SourceNot applicable Not applicable Not applicableWARNING: BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS’ MATERIALSAFETY DATA SHEETS. SOME MATERIALS CAN BE DANGEROUS.CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO HONEYWELLSPECIFIED MATERIALS. MATERIALS THAT ARE NOT EQUIVALENT CANCAUSE DAMAGE TO THE EQUIPMENT AND CAN MAKE THE WARRANTY NOTAPPLICABLE.(4) Refer to Table 26 for the specified consumable materials in this section.Table 26. Consumable MaterialsNumber Description SourceNot applicable Not applicable Not applicable(5) The list that follows identifies Honeywell publications that are related to this section:• Not applicable.EFFECTIVITYALL 23-15-30 Page 63 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-13002. Procedure (TASK 23-15-30-400-801-A01)A. Job Setup (Subtask 23-15-30-400-001-A01)WARNING: BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS’ MATERIALSAFETY DATA SHEETS. SOME MATERIALS CAN BE DANGEROUS.CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO HONEYWELLSPECIFIED MATERIALS. MATERIALS THAT ARE NOT EQUIVALENT CANCAUSE DAMAGE TO THE EQUIPMENT AND CAN MAKE THE WARRANTY NOTAPPLICABLE.CAUTION: DO NOT DROP OR HIT THE A350 SDU AND SCM DURING THESE PROCEDURES.THE A350 SDU AND SCM CONTAINS AN ASSEMBLY THAT CAN BE DAMAGEDFROM INCORRECT USE.CAUTION: DO THESE PROCEDURES IN A CLEAN ENVIRONMENT TO PREVENT DAMAGETO MECHANICAL COMPONENTS.(1) Obey the precautions.B. Installation Data (Subtask 23-15-30-400-002-A01)(1) Installation requirements are based on ARINC 781 specifications.C. Unpacking and Inspecting Equipment (Subtask 23-15-30-400-003-A01)(1) Unpack the equipment components from the shipping container. Visually inspect the units forany shipping damage. Make sure that both the SDU and SCM are available.• SDU PN 1394-A-1100• SCM PN 1394-A-1300.(2) If optional parts have been ordered, these items must be removed from the packaging andvisually inspected for any shipping damage.D. Customer Acceptance Procedure (Subtask 23-15-30-400-004-A01)(1) Make sure that the part number on the equipment received is correct as ordered.(2) Check for physical damage that can occurred during shipping.(3) Check the operational status of the SDU and SCM before installation on an aircraft byperforming the test procedures described in TESTING AND FAULT ISOLATION (PGBLK23-15-30-1000).E. Installation Procedure (Subtask 23-15-30-400-005-A01)(1) General(a) Only authorized technical personnel, trained in general aviation workmanship, that have abasic understanding of SATCOM systems must proceed with the following procedure.Before performing any installation procedures, read the safety advisories.(2) SDU Installation(a) Refer to Figure 11 (GRAPHIC 23-15-30-99B-811-A01).(b) The A350 SDU uses ARINC 600 size 2 shell receptacles located at the rear of the unitand requires an ARINC 600 6 MCU tray for installation.(c) Refer to the interconnection diagrams to install the correct wiring for the services yourequire. The interconnection and pinout drawings are also provided for informationpurposes.EFFECTIVITYALL 23-15-30 Page 64 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Figure 11. (Sheet 1 of 1) SDU Back View (GRAPHIC 23-15-30-99B-811-A01)(3) SCM Installation(a) Refer to Figure 12 (GRAPHIC 23-15-30-99B-812-A01).(b) The A350 SCM can be installed in any orientation, but must be mounted on a flat surface.(c) The A350 SCM must be provided with a low impedance bonding path (less than 2.5milliohms to airframe ground) to a point on its base.(d) After the SCM is mounted, connect it to the SDU using a connector cable as per theSCM and SDU interconnection diagrams.EFFECTIVITYALL 23-15-30 Page 65 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Figure 12. (Sheet 1 of 1) SCM Top View (GRAPHIC 23-15-30-99B-812-A01)F. Test (Subtask 23-15-30-400-006-A01)(1) Do the operational test procedures described in TESTING AND FAULT ISOLATION (PGBLK23-15-30-1000).G. Job Close-up (Subtask 23-15-30-400-007-A01)(1) Not applicable.SERVICING1. Not ApplicableSTORAGE (INCLUDING TRANSPORTATION)EFFECTIVITYALL 23-15-30 Page 66 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-13001. Planning Data (TASK 23-15-30-99C-809-A01)A. Reason for the Job (Subtask 23-15-30-99C-017-A01)(1) Use these procedures to prepare the A350 SDU and SCM for storage or transportation. Thefunction of these procedures is to make sure that the A350 SDU and SCM has protection fromdust, moisture, and other contamination.B. Job Setup Data (Subtask 23-15-30-99C-018-A01)(1) You can use equivalent alternatives for the special tools, fixtures, equipment, and consumablematerials. The user must find equivalent alternatives.(2) Refer to Table 27 for the specified special tools, fixtures, and equipment in this section.(3) Refer to H4/H8 CAGE Codes (available at http://www.logisticsinformationservice.dla.mil) formanufacturer’s address.Table 27. Special Tools, Fixtures, and EquipmentNumber Description SourceNot applicable Not applicable Not applicableWARNING: BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS’ MATERIALSAFETY DATA SHEETS. SOME MATERIALS CAN BE DANGEROUS.CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO HONEYWELLSPECIFIED MATERIALS. MATERIALS THAT ARE NOT EQUIVALENT CANCAUSE DAMAGE TO THE EQUIPMENT AND CAN MAKE THE WARRANTY NOTAPPLICABLE.(4)Refer to Table 28 for the specified consumable materials in this section.Table 28. ConsumablesNumber Description SourceNot applicable Not applicable Not applicable(5) The list that follows identifies Honeywell publications that are related to this section:• Not applicable.EFFECTIVITYALL 23-15-30 Page 67 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-13002. Procedure (TASK 23-15-30-550-801-A01)A. Job Setup (Subtask 23-15-30-550-001-A01)WARNING: BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS’ MATERIALSAFETY DATA SHEETS. SOME MATERIALS CAN BE DANGEROUS.CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO HONEYWELLSPECIFIED MATERIALS. MATERIALS THAT ARE NOT EQUIVALENT CANCAUSE DAMAGE TO THE EQUIPMENT AND CAN MAKE THE WARRANTY NOTAPPLICABLE.CAUTION: DO NOT DROP OR HIT THE A350 SDU AND SCM DURING THESE PROCEDURES.THE A350 SDU AND SCM CONTAINS AN ASSEMBLY THAT CAN BE DAMAGEDFROM INCORRECT USE.CAUTION: DO THESE PROCEDURES IN A CLEAN ENVIRONMENT TO PREVENT DAMAGETO MECHANICAL COMPONENTS.(1) Obey the precautions.B. Preservation (Subtask 23-15-30-550-002-A01)(1) Not applicable.C. Packing (Subtask 23-15-30-550-003-A01)(1) Not applicable.D. Storage (Subtask 23-15-30-550-004-A01)(1) Store the A350 SDU and SCM equipment in a cool, dry place [ground survival temperaturerange is 67 to 185 F( 55 to +85 C)] in its original shipping container.E. Transportation (Subtask 23-15-30-550-005-A01)(1) Not applicable.F. J o b C l o s e - up (Subtask 23-15-30-550-006-A01)(1) Not applicable.REWORK1. Planning Data (TASK 23-15-30-99F-806-A01)A. General (Subtask 23-15-30-99F-014-A01)(1) Rework is not supported in the field. Return any SDU or SCM units that fail the test proceduresprovided in this document to the manufacturer for fault isolation and repair. Refer to APPENDIXA (RMA) (PGBLK 23-15-30-1700) for the return procedure.APPENDIX A (RMA)1. Planning Data(TASK 23-15-30-99F-807-A01)A. General (Subtask 23-15-30-99C-019-A01)(1) To return the equipment to Honeywell for repair, this RMA procedure must be followed. Failureto comply with this procedure can result in shipping delays and additional charges.EFFECTIVITYALL 23-15-30 Page 68 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300B. Warranty Returns (Subtask 23-15-30-99C-020-A01)(1) Equipment that qualifies for warranty repair can be returned to Honeywell for repair orreplacement at our discretion. The customer must pay the shipping costs to Honeywell andHoneywell will pay the shipping costs to return the repaired/replaced unit to the customer.C. Non-Warranty Returns (Subtask 23-15-30-99C-021-A01)(1) Equipment that fails to work properly because of improper or negligent use, abuse, shippingdamage, or any other condition can still be returned to Honeywell for repair or replacementat our discretion. The customer will be notified of the cost to repair or replace the unitbefore invoicing for the repair or replacement. The customer must pay for the shipping coststo and from Honeywell.D. Repackaging Requirements (Subtask 23-15-30-99C-022-A01)(1) A350 SDU and SCM components must be returned to Honeywell in approved shippingcontainers. Failure to do so can invalidate the warranty.(2) If SDU or SCM shipping containers are unavailable, they can be ordered from Honeywellcustomer service when requesting the RMA number.2. Procedure (TASK 23-15-30-600-801-A01)A. RMA (Subtask 23-15-30-600-001-A01)(1) If it is determined that a unit must be returned to Honeywell for repair or overhaul, pleasefollow the RMA procedure below.(2) Have the following information ready before calling Honeywell customer support:• Model (e.g., A350 SDU or SCM)• Unit part number (e.g., 1458-A-1101 or 1458-A-1300)• Serial number• Description of failure• Aircraft tail number, serial number, and aircraft model number.(3) Call Honeywell customer support, refer to Paragraph 2 (TASK 23-15-30-99F-802-A01).(4) A Honeywell product support specialist will attempt to resolve the problem by telephone. Ifequipment must be returned to Honeywell, the product support specialist will authorize theRepair & Overhaul coordinator to issue an RMA number.(5) Pack the equipment in the original shipping container or a container approved by Honeywell.(6) Write the RMA number on the outside of the shipping container and on all shipping documents,enclose a copy in the box, and send your prepaid shipment to:Honeywell International Inc.400 Maple Grove RoadOttawa, Ontario,CANADA K2V 1B8RMA #: ___________ATTN: Repair & OverhaulTel: 613 591-6040 extension 1214Fax: 613 591-8951EFFECTIVITYALL 23-15-30 Page 69 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013
ABBREVIATED COMPONENT MAINTENANCE MANUAL1458-A-1101 / 1458-A-1300Email: rmareturns@emsaviation.com(7) Fax or email the details of the shipment to the Repair & Overhaul coordinator, including thefollowing information: Shipment date, carrier name, and the waybill number.(8) The processing of LRU returns is limited to standard business hours from 8:30 am to 5:00pm EST. For general inquires and status requests, please contact the Repair & Overhauldepartment directly:Phone: 613-591-9064, extension 1214 (Repair & Overhaul group)Fax: 613-591-8951Email: rmareturns@emsaviation.comILLUSTRATED PARTS LIST1. Not ApplicableEFFECTIVITYALL 23-15-30 Page 70 of 705 Oct 2012© Honeywell International Inc. Do not copy without express permission of Honeywell.Interim DRAFT for FCC Approval Purposes Do Not Use for Maintenance 10-Feb-2013

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