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

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Users Manual

Honeywell International Inc.

400 Maple Grove Drive

Ottawa, Ontario K2V 1B8

Canada

CAGE: 38473

Telephone: (800) 601-3099 (Toll Free U.S.A./Canada)

Telephone: (602) 365-3099 (International Direct)

Website: www.myaerospace.com

Abbreviated Component Maintenance Manual

A350 SDU and SCM

Part Number CAGE

1458-A-1101 38473

1458-A-1300 38473

This document contains technical data and is subject to U.S. export regulations. These commodities, technology, or

software were exported from the United States in accordance with the export administration regulations. Diversion contrary

to U.S. law is prohibited.

ECCN: 7E994, NLR Eligible.

23-15-30

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Publication Number D201207000045, Revision 0 Initial 5 Oct 2012

©Honeywell International Inc. Do not copy without express permission of Honeywell.

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ABBREVIATED COMPONENT MAINTENANCE MANUAL

1458-A-1101 / 1458-A-1300

Honeywell - Confidential

THIS COPYRIGHTED WORK AND ALL INFORMATION ARE THE PROPERTY OF HONEYWELL

INTERNATIONAL INC., CONTAIN TRADE SECRETS AND MAY NOT, IN WHOLE OR IN PART, BE USED,

DUPLICATED, OR DISCLOSED FOR ANY PURPOSE WITHOUT PRIOR WRITTEN PERMISSION OF

Honeywell Materials License Agreement

The documents and information contained herein ("the Materials") are the proprietary data of Honeywell

International Inc. and Honeywell Intellectual Properties Inc. (collectively "Honeywell"). These Materials

are 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, their

wholly owned-subsidiaries or a formally designated third party service provider; and direct recipients of

Materials from Honeywell’s Aerospace Technical Publication Distribution. The terms and conditions of

this License Agreement govern your use of these Materials, except to the extent that any terms and

conditions of another applicable agreement with Honeywell regarding the operation, maintenance, or

repair 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 License

Agreement will govern in the event of a conflict between its terms and conditions and those of a purchase

order or acknowledgement.

1. License Grant - If you are a party to an applicable product support agreement, a Honeywell Service

Center 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 products

only in accordance with that agreement.

If you are a direct recipient of these Materials from Honeywell’s Aerospace Technical Publication

Distribution and are not a party to an agreement related to the operation, maintenance or repair of

Honeywell aerospace products, Honeywell hereby grants you a limited, non-exclusive license to use

these Materials to maintain or repair the subject Honeywell aerospace products only at the facility to

which these Materials have been shipped ("the Licensed Facility"). Transfer of the Materials to another

facility owned by you is permitted only if the original Licensed Facility retains no copies of the Materials

and 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 not

expressly granted to you, including all rights in patents, copyrights, trademarks, and trade secrets. No

license 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 and

proprietary to Honeywell. You agree to take all reasonable efforts to maintain the confidentiality of these

Materials.

4. Assignment And Transfer - This License Agreement may be assigned to a formally designated service

designee or transferred to a subsequent owner or operator of an aircraft containing the subject Honeywell

aerospace products. However, the recipient of any such assignment or transfer must assume all of

your obligations under this License Agreement. No assignment or transfer shall relieve any party of

any obligation that such party then has hereunder.

5. Copies of Materials - Unless you have the express written permission of Honeywell, you may not

make or permit making of copies of the Materials. Notwithstanding the foregoing, you may make copies

of only portions of the Material for your internal use. You agree to return the Materials and any copies

thereof to Honeywell upon the request of Honeywell.

6. Term - This License Agreement is effective until terminated as set forth herein. This License Agreement

will terminate immediately, without notice from Honeywell, if you fail to comply with any provision of this

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License Agreement or will terminate simultaneously with the termination or expiration of your applicable

product support agreement, authorized repair facility agreement, or your formal designation as a third party

service provider. Upon termination of this License Agreement, you will return these Materials to Honeywell

without retaining any copies and will have one of your authorized officers certify that all Materials have

been returned with no copies retained.

7. Remedies - Honeywell reserves the right to pursue all available remedies and damages resulting from

a breach of this License Agreement.

8. Limitation of Liability - Honeywell does not make any representation regarding the use or sufficiency of

the Materials. THERE ARE NO OTHER WARRANTIES, WHETHER WRITTEN OR ORAL, EXPRESS,

IMPLIED OR STATUTORY, INCLUDING, BUT NOT LIMITED TO, (i) WARRANTIES ARISING FROM

COURSE OF PERFORMANCE, DEALING, USAGE, OR TRADE, WHICH ARE HEREBY EXPRESSLY

DISCLAIMED, OR (ii) WARRANTIES AGAINST INFRINGEMENT OF INTELLECTUAL PROPERTY

RIGHTS OF THIRD PARTIES, EVEN IF HONEYWELL HAS BEEN ADVISED OF ANY SUCH

INFRINGEMENT. IN NO EVENT WILL HONEYWELL BE LIABLE FOR ANY INCIDENTAL DAMAGES,

CONSEQUENTIAL DAMAGES, SPECIAL DAMAGES, INDIRECT DAMAGES, LOSS OF PROFITS, LOSS

OF 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 WILL

APPLY 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 the

State of New York without regard to the conflicts of laws provisions thereof. This license sets forth the

entire agreement between you and Honeywell and may only be modified by a writing duly executed by

the duly authorized representatives of the parties.

Safety Advisory

WARNING: BEFORE THE MATERIALS CALLED OUT IN THIS PUBLICATION ARE USED, KNOW THE

HANDLING, STORAGE AND DISPOSAL PRECAUTIONS RECOMMENDED BY THE MANUFACTURER

OR SUPPLIER. FAILURE TO OBEY THE MANUFACTURERS’ OR SUPPLIERS’ RECOMMENDATIONS

CAN 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 the

Material Safety Data Sheets (OSHA Form 174 or equivalent) from the manufacturers or suppliers of the

materials 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 disposal

of the materials.

Warranty/Liability Advisory

WARNING: HONEYWELL ASSUMES NO RESPONSIBILITY FOR ANY HONEYWELL EQUIPMENT

WHICH IS NOT MAINTAINED AND/OR REPAIRED IN ACCORDANCE WITH HONEYWELL’S

PUBLISHED INSTRUCTIONS AND/OR HONEYWELL’S FAA/SFAR 36 REPAIR AUTHORIZATION.

NEITHER DOES HONEYWELL ASSUME RESPONSIBILITY FOR SPECIAL TOOLS AND TEST

EQUIPMENT FABRICATED BY COMPANIES OTHER THAN HONEYWELL.

WARNING: INCORRECTLY REPAIRED COMPONENTS CAN AFFECT AIRWORTHINESS OR

DECREASE THE LIFE OF THE COMPONENTS. INCORRECTLY FABRICATED SPECIAL TOOLING

OR TEST EQUIPMENT CAN RESULT IN DAMAGE TO THE PRODUCT COMPONENTS OR GIVE

UNSATISFACTORY RESULTS.

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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)

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TRANSMITTAL INFORMATION

THIS IS AN INITIAL RELEASE OF A350 SDU AND SCM ACMM ATA NO. 23-15-30 AND IS ISSUED FOR

USEINSUPPORTOFTHEFOLLOWING:

Table 1 shows the applicable components.

Table 1. Applicable Components

Component PN Nomenclature

1458-A-1101 A350 SDU

1458-A-1300 A350 SCM

Revision History

Table 2 shows the revision history of this ACMM.

Table 2. Revision History

Revision Number Revision Date

05 Oct 2012

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Blank Page

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INTRODUCTION

1. 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 section

before the start of maintenance procedures.

(5) Honeywell recommends that you do the tests in TESTING AND FAULT ISOLATION (PGBLK

23-15-30-1000) to test the operational status of the unit. These tests can show the condition

of the unit or most possible cause of a malfunction. If a malfunction occurs, the unit must

be 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 unit

is deemed necessary, refer to APPENDIX A (RMA) (PGBLK 23-15-30-1700) for equipment

return 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 maintenance

procedure, which if not obeyed, can cause injury or death

• A CAUTION gives a condition or tells personnel what part of an operation or maintenance

procedure, which if not obeyed, can cause damage to the equipment

• A NOTE gives data, not commands. The NOTE helps personnel when they do the related

instruction.

(9) Warnings and cautions go before the applicable paragraph or step. Notes follow the applicable

paragraph 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 know

and 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 IEC

Publication 27. Special characters in text are spelled out.

(2) The signal mnemonics, unit control designators, and test designators are shown in capital

letters.

(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 moisture

sensitive devices.

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Figure 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 the

USMS followed by the appropriate SI metric units in parentheses. Some standard tools or

parts 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, if

Figure 501-5 is used, it signifies that it is an illustration of the item identified by index number 5

in 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 Task

Numbering System which make the maintenance procedures in this manual compatible with

an automated shop environment.

(2) The system uses standard and unique number combinations to identify maintenance tasks

and 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 a

function code and unique identifiers. The purpose of incorporating the MTOSS numbering

system is to provide a means for the automated sorting, retrieval, and management of

digitized data.

(4) Section and Sub-section Numbering System

(a) All procedures in this publication have TASK and SUBTASK numbers at key data retrieval

points. 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 the

procedure 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. The

number has seven elements. The first five elements are necessary for each TASK or

SUBTASK. The sixth and seventh elements are applied only when necessary. Refer to

Figure 2 (GRAPHIC 23-15-30-99B-802-A01).

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(b) Elements 1, 2, and 3 identify the ATA Chapter-Section-Subject number of the page block.

position element. The third position is zero filled when further definition is not required. If

required, the manufacturer will use the numbers 1 thru 9 or letters A thru Z, excluding the

letters I and O. Refer to Table 3.

(d) Element 5 provides a unique identification for each TASK or SUBTASK number which is

similarly 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 differences

in 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 the

customer (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 Definitions

Code Function Definition

000 REMOVAL AND DISASSEMBLY

010 Removal Removal of the engine/component from a

workstand, transport dolly, test stand, etc., or

aircraft.

020 Remove Modular Sections This is the first echelon of disassembly which

consists of sectionalization of the unit/engine

into primary modular sections. Modular

sections are identified by the third element

of the ATA number when removed from the

unit/engine.

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Code Function Definition

030 Disassemble Modular Sections This is the second echelon of disassembly

which consists of disassembly of the modular

sections into subassemblies after removal from

the unit/engine. Modular section designations

appear in the second element of the ATA

number for this echelon of disassembly.

040 Disassemble Subassemblies This is the third echelon of engine

disassembly which consists of disassembly

of subassemblies to the piece part level.

The subassemblies are identified by the third

element of the ATA number.

050 Remove Accessory/Power Plant Components This consists of removing individual

accessory/power plant components from either

installed 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 and

instrumentation after accessory/component

test.

090 Disassemble Support Equipment This consists of disassembly of support

equipment required to maintain said support

equipment.

100 CLEANING

110 Chemical Removal of surface deposits from a part by

use of a chemical cleaning agent. After being

dissolved, the deposit is washed or rinsed away

after a soaking period. Also includes chemical

power flushing.

120 Abrasive Removal of surface deposits from a part by wet

or dry particle impingement.

130 Ultrasonic Removal of surface deposits and entrapped

material by use of high frequency sound waves

to produce cavitation at the surface of the

part. Cleaning is performed in a liquid bath

that transmits the sound energy and keeps the

removed material in suspension.

140 Mechanical Removal of surface deposits from a part by use

of a brush, felt bob, sandpaper, or other hand

or mechanical action.

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Code Function Definition

150 Unassigned

160 MiscellaneousRemoval of deposits from parts with

compressed air, miscellaneous hand cleaning,

and various combinations of cleaning

procedures.

170 Foam/Water Wash Removal or post emulsified fluorescent

penetrant via an agitated water wash,

automatic spray rinse, or an aqueous remover

aeratedtoproduceafoam.

180 Testing of Solutions Test used to assist in identifying certain

materials by electro-mechanically determining

the presence or absence of known constituents.

190 Unassigned

200 INSPECTION

210 Check Athoroughvisual examination of components,

accessories, subsystems, and piece parts

to detect structural failure, deterioration or

damage: and to determine the need for

corrective action. For example: exterior

surfaces, electronic circuit cards, gears, control

systems, linkages, accessories, components,

tubing, wiring and connections, safety wiring,

fasteners, clamps, etc., are inspected to verify

proper condition and acceptability for continued

service.

220 Visual/Dimensional A comparison of the dimensions and material

conditions of parts, subassemblies, and

assemblies with the specifications contained

in technical manuals and/or blueprints, to

detect deviations from established standard

and limits and determine the acceptability for

continued service, repair, or need to discard

the item. A visual/dimensional function code

is also required to verify that proper corrective

maintenance has been accomplished.

Although some of these tasks may not require

measurements, a complete spectrum of

tasks/sub tasks requires a variety of measuring

equipment to determine runout, concentricity,

flatness, parallelism, hardness, thickness,

clarity, dimensions, etc.

230 Penetrant Fluorescent penetrant inspection to detect

surface cracks.

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Code Function Definition

240 Magnetic Magnetic particle inspection to detect surface

cracks in magnetic materials.

250 Eddy Current Inspection for subsurface cracks, porosity,

inclusions, or other nonhomogeneous

material structure by use of high frequency

electromagnetic wave equipment. Parts are

scanned and compared to similar parts or test

specimens having known material defects.

260 X-Ray Inspection for subsurface cracks, porosity,

inclusions, or other nonhomogeneous material

structure by use of x-ray techniques.

270 Ultrasonic Inspection for subsurface cracks, porosity,

inclusions, or other nonhomogeneous material

structure by use of contact pulse echo

ultrasonic techniques.

280 Special Any special inspection to determine the

integrity of a part for continued operation

In-Service or qualitative analysis.

290 Unassigned

300 REPAIR

310 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 or

finish 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 a

surface by mechanical, chemical, or electrical

means. Plating of chromium, cadmium, tin,

etc., to build up the size of a part or provide

surface protection. Includes masking or waxing

prior to the process.

340 Plasma and Flame Spraying The application of a protective coating to a

part by feeding a powder into an ionized gas

stream. Flame spraying uses a fuel oxygen

flame to melt and propel metal onto parts to

build up the size or provide surface protection.

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Code Function Definition

350 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 miscellaneous

disassembly and assembly required.

360 Bonding and Molding/Sealing Joining and curing of parts with an adhesive or

fusible material (including silicone, fiberglass,

glues).

370 Heat Treating Controlled heating and cooling of a material to

obtain the desired physical property (includes

annealing, tempering, quenching, stress

relieving, solution heat treat, etc.).

380 Surface Treating Treating the surface of a part by painting,

varnishing, aluminizing, Teflon coating, zinc

chromate priming, tumble finishing, shot

peening, etc. Baking and masking processes

are included.

390 Machine Riveting and Flaring Joining of parts by riveting and flaring the rivet.

400 INSTALLATION AND ASSEMBLY

410 Install Installation of the unit/engine onto a workstand,

transportdolly,teststand,oraircraft.

420 Install Modular Sections The third echelon of assembly consisting of

assembly of the modular assemblies into a

complete unit/engine assembly. The modular

sections are identified by the third element of

the ATA number.

430 Assemble Modular Sections The second echelon of assembly consisting

of assembling subassemblies into modular

sections. The modular section is identified by

the second element of the ATA number.

440 Assemble Subassemblies The first echelon of assembly consisting of

assembling piece parts into subassemblies.

The subassemblies are identified by the third

element of the ATA number.

450 Install/Close Items Removed/Opened for

Access

Installation or closing of access plates, closing

of ports, installation of components, tubing

or any item which was removed or opened in

order to provide access to perform the task.

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Code Function Definition

460 Assemble Accessory Assemble accessory components.

470 Assemble Accessory Subassembly Assembly of accessory subassembly

components.

480 Install Test Equipment Install equipment and instrumentation required

for accessory component test.

490 Assemble Support Equipment Any assembly required to maintain support

equipment.

500 MATERIAL HANDLING

510 Shipping Themovementofanypart,subassembly,

assembly, or component from the time it is

packaged until it reaches its destination.

520 ReceivingThe receipt activity for any incoming part,

subassembly, assembly, or component.

530 Packing Installing parts, subassemblies, assemblies, or

components 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 for

use.

560 Marshaling/Positioning Marshaling is collection of parts,

subassemblies, and accessories prior to

release for assembly. Positioning is movement

from one fixed state to another.

570 Engine Ferry/Pod Maintenance Necessary preparations before and after

transporting an engine by aircraft ferry method.

580 Unassigned

590 Unassigned

600 SERVICING/PRESERVING/LUBRICATING

610 Servicing Action required to sustain a unit or system in

proper operating status including priming with

applicable fluids prior to use.

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Code Function Definition

620 Preserving Preparation of a unit, part, assembly, etc.,

for safekeeping from decomposition or

deterioration. Includes preparation for storage

(applying a preservative layer, desiccants, etc.).

630 DepreservingRemoving preservatives, desiccants, etc., from

a unit, part, assembly, etc., prior to installation

or operation.

640 Lubricating Applying oil, grease, dry film, or silicon

lubricants on moving parts to reduce friction

or cool the item.

650 Unassigned

660 Unassigned

670 Unassigned

680 Unassigned

690 Unassigned

700 TESTING/CHECKING

710 Oil Flow Measuring the flow of oil through components

or compartments under specific conditions.

720 Air Flow Measuring the flow of air through components

or compartments under specific conditions.

730 Fuel Flow Function checks and flow measurements

through the part or system being tested.

740 Water Flow Function checks and flow measurements

through the part or system being tested.

750 Electrical/Return to Service Functional tests (manual or ATE) of the system

or component as well as measurement of

electrical or electronic parameters designed to

determine whether the item can be returned to

service. May include fault isolation procedures

for components that require close correlation

between test results and fault indications.

760 Engine Operation of an engine to establish systems

function or operation under specific conditions

to measure performance.

770 Accessory/Bite Te s t ing of an accessory to ensure proper

operation or function.

780 Pressure Check Testing to establish the ability of a normally

pressurized component or system to operate

properly.

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Code Function Definition

790 Leak Check Determine the ability of a component or system

to operate without leaking.

800 MISCELLANEOUS

810 Fault Isolation Operation of an engine at constant thrust level

or identical Engine Pressure Ratio (EPR) to

locate the prime suspect deficient system:

operating an improperly functioning system or

component to locate the cause; or performing

a series of checks to isolate a failed part or

component.

820 Adjusting/Aligning/Calibrating Makingaphy

sical correction to ensure

proper placement or operation of a system or

component.

830 Rigging Hooking-up, arranging, or adjusting a

component or accessory linkage for proper

operation.

840 Service Bulletin Incorporation Performing the work specified in the

service bulletin. Provides for identification

of modification tasks at the task level with

subtasks recognizing any functional changes

(chemical, visual/dimensional, cleaning,

machining, etc.) necessary to incorporate the

service bulletin.

850 PN Change/Re-identification Change of PN, application of PN by transfer,

engrave repair number, etc.

860 Unassigned

870 Description and Operation Electrical and mechanical description of the

unit or component. Includes leading particulars,

descriptions, limitations, specifications, and

theory of operation.

880 Approved Vendor Processes Includes processes that may be proprietary

and controlled by a particular manufacturer, or

by nonproprietary and approved for application

by conforming vendors.

890 Airline Maintenance Program (Customer Use)

900 Unassigned

910 Special Equipment Maintenance Identification of tasks to maintain special

support equipment.

920 Standard Equipment Maintenance Identification of tasks to maintain standard

support equipment.

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ABBREVIATED COMPONENT MAINTENANCE MANUAL

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Code Function Definition

930 Tool Fabrication Includes fabricating any tool for which

procedures 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 required

to perform maintenance on the unit or

component.

94A Consumables

94B Special Tools/Non Std Tools

94C Fixtures/Test Equipment

94D Standard Tools

950 Illustrated Parts List (Detailed Parts List) Section of IPL/IPC that contains parts

description and identification in top-down break

down sequence.

960 Illustrated Parts List (Equipment Designation

Index)

Section of IPL/IPC that contains equipment

designators cross-referenced to detailed parts

list.

970 Illustrated Parts List (Numerical Index) Section of IPL/IPC that contains an

alphanumeric listing of all parts in the unit

cross-referenced to the detailed parts list.

980 Illustrated Parts List (Alternate Vendor Index) Optional section of IPL/IPC that contains an

alphanumeric listing of all parts in the unit that

have more than one vendor source.

990 Illustrations, Tables, Front Matter, Etc.

99A Ta b l e s

99B Illustrations

99C Front Matter Pageblock (TASK Level MTOSS)

Front Matter Task (Collection of Subtask

MTOSS)

99D Access

99E References

99F General/Introduction

2. 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.

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ABBREVIATED COMPONENT MAINTENANCE MANUAL

1458-A-1101 / 1458-A-1300

B. 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 to

speak to personnel about non-Technical Publication matters, the Honeywell Aerospace Global

Customer 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 the

American National Standards Institute, New York, NY)

• ASME Y14.38, Abbreviations for Use on Drawings and in Text (available from the American

National 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 (available

from 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 approval

of the appropriate government air/radio authority (such as Transport Canada, the FAA, the

JAA, etc.). Honeywell highly recommends contacting the appropriate authorities early in the

system-planning phase to minimize approval/certification issues that could delay release

of 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 determine

that the aircraft installation conditions are within the TSO standards. TSO articles must have

different approval for installation in an aircraft. The article can be installed only according to 14

CFR part 43, or the applicable airworthiness requirements.

(3) Contact Honeywell for more information on certification and approval issues.

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ABBREVIATED COMPONENT MAINTENANCE MANUAL

1458-A-1101 / 1458-A-1300

4. 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 Abbreviations

Term Full Term

AC alternating current

ACMM abbreviated component maintenance manual

ADIRU air data inertial reference unit

AFDX avionics full duplex switched ethernet

AMM aircraft maintenance manual

AMSS aeronautical mobile satellite services

AMU audio management unit

ANSI American National Standards Institute

AORE Atlantic Ocean Region-East

AORW Atlantic Ocean Region-West

ARINC Aeronautical Radio, Incorporated

ASME American Society of Mechanical Engineers

ATA Air Transport Association

ATE automated test equipment

BITE built-in test equipment

BP bottom plug

bps bits per second

C Celsius

CAGE commercial and government entity

CFR code of federal regulation

CMS central maintenance system

CRES corrosion resistant steel

DC direct current

DLCS data loading and configuration system

DLNA diplexer/low noise amplifier

EMEA Europe, the Middle East, and Africa

ESDS electrostatic discharge sensitive

EST Eastern Standard Time

F Fahrenheit

FAA Federal Aviation Administration

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FWS flight warning system

GES ground earth station

GPO Government Printing Office

HGA high gain antenna

HMI human machine interface

HPA high power amplifier

hr hour

Hz Hertz

I/O input/output

ICA Instructions for Continued Airworthiness

ICAO International Civil Aviation Organization

IEC International Electrotechnical Commission

IEEE Institute of Electrical and Electronics Engineers

IM interactive mode

in-lb inch-pound

IOR Indian Ocean Region

IPC iIlustrated parts catalog

IPL illustrated parts list

ISDN integrated services digital network

JAA Joint Aviation Authority

kbps kilobits per second

kg kilogram

LED light emitting diode

LES land earth station

LGERS landing gear extension/retraction system

mA milliampere

MAX maximum

MCU modular concept unit

MEL minimum equipment list

MES mobile earth station

MHz megahertz

mm millimeter

MP middle plug

MPDS mobile packet data service

MTOSS maintenance task oriented support system

Nm newton meter

No. number

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ORT owner requirements table

PA power amplifier

PN part number

POR Pacific Ocean Region

RF radio frequency

RMA return material authorization

RMP radio management panel

RMU radio management unit

RTCA Radio Technical Commission for Aeronautics

SATCOM satellite communications

SBB swift broadband

SCM satellite data unit configuration module

SDIMM system description, installation, and maintenance manual

SDU satellite data unit

SI International System of Units

SIS standalone identification system

SRU shop replaceable unit

STC supplemental type certificate

TP top plug

TSO technical standing order

U.S.A. United States of America

USIM universal subscriber identity module

USMS United States Measurement System

VAC volt, alternating current

VDC volt, direct current

5. 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 simulation

of the necessary procedures. Demonstration shows that the procedures were checked by the

use of the manual. Simulation shows that the applicable personnel looked at the procedure

in the manual and that the procedure is technically correct. The dates of verification for

this manual are given in Table 4.

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Table 4. Verification Data

Section Method Date

Testing and Fault Isolation 1Demonstration 14 Nov 2012

NOTE:

1Only the TESTING portion of the TESTING AND FAULT ISOLATION section was done by demonstration.

DESCRIPTION AND OPERATION

1. 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 Honeywell

SATCOMs existing range of SATCOM products. The Honeywell furnished A350 SATCOM

avionics, in concert with the amplifier and antenna subsystem, achieves all of the requirements

for providing AMSS by facilitating airborne satellite communications. These services

comprise Classic Aero-H+, Swift64 and SBB as described above provided by Inmarsat and

its designated service provider agencies.

(3) The A350 SATCOM avionics is an integral part of the complete L-band Inmarsat SATCOM

system 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 Particulars

Characteristic Specification

Length 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±3mmH

2O)

Mounting information 6 MCU tray as per ARINC 600

Electrical interfaces:

• Power/Control interface ARINC 781

Power requirements:

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Characteristic Specification

• Input voltage (AC) 96 to 122 VAC, 300 to 900 Hz

• Input voltage (DC) 18 to 32.3 VDC

Power consumption 300 mA if operated with an external FMPA

400 mA if operated as standalone

Table 6. SCM Leading Particulars

Characteristic Specification

Length 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 ARINC

781

Electrical interfaces:

•P

ower/Control interface ARINC 781

Power 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 (GRAPHIC

23-15-30-99B-804-A01) for detailed information on the physical characteristics of the SDU.

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Figure 3. (Sheet 1 of 1) SDU (GRAPHIC 23-15-30-99B-803-A01)

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Figure 4. (Sheet 1 of 2) SDU Outline and Installation Drawing (GRAPHIC 23-15-30-99B-804-A01)

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Figure 4. (Sheet 2 of 2) SDU Outline and Installation Drawing (GRAPHIC 23-15-30-99B-804-A01)

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ABBREVIATED COMPONENT MAINTENANCE MANUAL

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(7) Refer to Figure 5 (GRAPHIC 23-15-30-99B-805-A01) for the SCM and Figure 6 (GRAPHIC

23-15-30-99B-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)

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Blank Page

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Figure 6. (Sheet 1 of 2) SCM Outline and Installation Drawing (GRAPHIC 23-15-30-99B-806-A01)

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Figure 6. (Sheet 2 of 2) SCM Outline and Installation Drawing (GRAPHIC 23-15-30-99B-806-A01)

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ABBREVIATED COMPONENT MAINTENANCE MANUAL

1458-A-1101 / 1458-A-1300

(8) Table 7 lists the equipment covered by this manual.

Table 7. Equipment Description

Equipment PN Description/Notes

SDU 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 determining

the functionality of the complete SATCOM system. The signal-in-space parameters are

determined by the SDU in relation to modulation/demodulation, error correction, coding,

interleaving and data rates associated with the communication channel(s). The SDU

contains circuits for conversion of digital and/or analog inputs/outputs to/from RF, and

typically contains a PA module. The SDU interfaces at L-band with the HPA and DLNA

and also controls the antenna.

(b)The SDU is capable of sending and receiving various data rates. The rate is dynamically

selected by the individual applications and by pragmatic assessment of current operating

conditions.

(2) SCM

(a) The SCM is an external peripheral of the SDU and provides a dedicated interface to the

SDU. It stores aircraft specific installation configuration, ORT configuration, and ICAO

identities. The SCM also contains four USIM that store subscriber information for the

SBB network.

(b) By storing configuration information independent of the SDU, the SCM facilitates

efficient SDU replacement. A new SDU that replaces a faulty SDU does not require any

configuration. 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.

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Figure 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 the

following services:

• AERO or “Classic” AERO - This service provides packet data services at 600, 1200, or

10500 bps over the PRT channel combination and half-rate circuit switched voice or data

service over the C channel.

• Swift64 - This service provides circuit switched 64 kbps, and 56 kbps mobile ISDN. In

addition, it provides packet switched MPDS up to 64 kbps.

• SBB - This service will give broadband circuit and packet switched services with data

rates 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 service

from the cockpit

• Call and Mic ON discretes.

(b) Ethernet Port (x2) - one used at any one time (under ORT control) for packet data

services access

over a standard ARINC 429 interface. The RMP implements the HMI necessary to control

radio and satellite communication equipment. The RMP enables user to:

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• 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 System

block diagram.

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Figure 8. (Sheet 1 of 1) A350 SATCOM Avionics System Block Diagram (GRAPHIC 23-15-30-99B-808-A01)

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2. 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 HGA

subsystem, it achieves all of the requirements for providing AMSS by facilitating airborne

satellite communication services over the Inmarsat network. These services comprise Classic

Aero-H+, Swift64, and SBB.

(2) The SCM is a dedicated peripheral of the SDU and stores aircraft specific installation

configuration 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 by

accessing global satellite and ground communications networks.

(4) Inmarsat is an international organization that operates and maintains the satellites and satellite

networks. Inmarsat operates multiple geostationary satellites. Each satellite is

•AORE

•AORW

•IOR

•POR.

(5) All I-3 satellites give worldwide telecommunication services for aviation, shipping, and

land-mobile terminal users. The satellites connect to ground telecommunication systems

through a network of GESs.

(6) In addition to the services offered by I-3 satellites, the I-4 satellites also give worldwide

broadband 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 SBB

service and I-4 satellites support broadband applications such as videoconferencing and

video-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 an

antenna subsystem, act as an AES/MES. The combined system provides users with a data

and voice communications link to the satellite network and global telecommunications system.

(9) A simplified satellite communications system is shown in Figure 9 (GRAPHIC

23-15-30-99B-809-A01).

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Figure 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 the

backplane. Various SRUs are also connected with the RF cables.

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mounting arrangement conform to ARINC 781-2. The interconnecting cable between the

SDU and the SCM must not be longer than 393.7 inches (10 meters).

1Weight

aThe 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 Factor

aThe A350 SDU and SCM form factors are compliant with ARINC 781.

3Connectors

aThe SDU uses two external interface connectors:

• Rear Connector - accommodates coaxial and signal interconnections in

the TP insert, quadrax and signal interconnections in the MP insert, and

coaxial, and power interconnections in the BP insert. The top insert pin

assignment are in accordance with ARINC 781 with the following deviations

as shown in the Table 8.

• Front Connector - an RJ45 and 9S DSUB connector providing 10bT

Ethernet and an RS-232 maintenance interface to the control processor.

Table 8. SDU Rear Connector Pin Deviations

Description Pin Deviation

CP maintenance TXD TP01A ATE p i n 1

CP maintenance RXD TP01B ATE p in 2

CP/DP maintenance GND TP01C ATE p i n 3

Data I/O processor maintenance TXD TP01D ATE p i n 4

Data I/O processor maintenance RXD TP01E ATE p i n 5

CC1 processors #1 and #2 maintenance GND TP01F ATE p i n 6

CC1 processor #1 maintenance TXD TP01G ATE p i n 7

CC1 processor #1 maintenance RXD TP01H ATE p i n 8

CC1 processor #2 maintenance TXD TP01J ATE p i n 9

CC1 processor #2 maintenance RXD TP01K ATE p i n 1 0

Download security TP02A ATE p i n 1 1

No connect TP02B ATE p i n 1 2

Voice processor maintenance GND TP02C ATE p i n 1 3

Voice processor maintenance TXD TP02D ATE p i n 1 4

Voice processor maintenance RXD TP02E ATE p i n 1 5

CC2 and CC3 maintenance GND TP02F ATE p i n 1 6

CC2 processor maintenance TXD TP02G ATE p i n 1 7

CC2 processor maintenance RXD TP02H ATE p i n 1 8

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Description Pin Deviation

CC3 processor maintenance TXD TP02J AT E p i n 1 9

CC3 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 are

consistent with ARINC 781 as shown in Table 9.

Table 9. SCM D-Type Connector Pin Assignment

Pin Number Description

1Data 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)

6Spare

7Chassis GND

8Power input (+8 to +15 volts)

9Reserved - Enable RS232 (used for shop loading)

10 Reserved - 0 volt strap output (used for shop loading)

11 Spare

12 Reserved - RS232 Tx (used for shop loading)

13 Reserved - RS232 Rx (used for shop loading)

14 Spare

15 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.

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(b) The major interfaces of the SDU are shown in Table 10.

Table 10. SDU Functional Interfaces

Interface Description Type

HGA (x1) HGA/DLNA A429 bus

HPA (x1) HPA A429 bus

RMP (x3) RMU (for Control and Display) A429 bus

AFDX (x2) AFDX AFDX bus

ADIRU virtual links AFDX VL

LGERS virtual links AFDX VL

CMS virtual links AFDX VL

DLCS virtual links AFDX VL

FWS virtual links AFDX VL

DFDRS virtual links AFDX VL

SPP virtual links AFDX VL

SCM (x1) SCM RS422

SCM 12V power SCM power Power

SIS (x1) SIS I2C

Servicing Front panel accessible service port for data log retrieval Ethernet

Miscellaneous ARINC discrete input, outputs and configuration straps Discretes

• 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.

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Blank Page

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Figure 10. (Sheet 1 of 3) System Interconnection Drawing (GRAPHIC 23-15-30-99B-810-A01)

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Figure 10. (Sheet 2 of 3) System Interconnection Drawing (GRAPHIC 23-15-30-99B-810-A01)

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Figure 10. (Sheet 3 of 3) System Interconnection Drawing (GRAPHIC 23-15-30-99B-810-A01)

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TESTING AND FAULT ISOLATION

1. 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 consumable

materials. 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) for

manufacturer’s address.

Table 11. Special Tools, Fixtures, and Equipment

Number Description Source

Not applicable Not applicable Not applicable

WARNING: BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS’ MATERIAL

SAFETY DATA SHEETS. SOME MATERIALS CAN BE DANGEROUS.

CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO HONEYWELL

SPECIFIED MATERIALS. MATERIALS THAT ARE NOT EQUIVALENT CAN

CAUSE DAMAGE TO THE EQUIPMENT AND CAN MAKE THE WARRANTY NOT

APPLICABLE.

(4) Refer to Table 12 for the specified consumable materials in this section.

Table 12. Consumables

Number Description Source

Not applicable Not applicable Not applicable

(5) The list that follows identifies Honeywell publications that are related to this section:

• Not applicable.

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2. 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’ MATERIAL

SAFETY DATA SHEETS. SOME MATERIALS CAN BE DANGEROUS.

CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO HONEYWELL

SPECIFIED MATERIALS. MATERIALS THAT ARE NOT EQUIVALENT CAN

CAUSE DAMAGE TO THE EQUIPMENT AND CAN MAKE THE WARRANTY NOT

APPLICABLE.

CAUTION: DO NOT DROP OR HIT THE SDU DURING THESE PROCEDURES. THE SDU

CONTAINS AN ASSEMBLY THAT CAN BE DAMAGED FROM INCORRECT USE.

CAUTION: DO THESE PROCEDURES IN A CLEAN ENVIRONMENT TO PREVENT DAMAGE

TO 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 during

normal SDU system operation.

(2) The failure of some of these tests will cause the equipment to go into fail safe mode and

prevent RF transmission. Once entered, safe mode cannot be exited except by fixing the

underlying condition and rebooting.

(3) The SDU implements security segregation whereby the control domain (responsible for classic

aero cockpit functionality) is separated from the data domain (responsible for Ethernet and

swift cabin functionality).

(4) The SDU will respond to a segregation failure by closing-down the user data (Ethernet and

swift RF) interfaces and reporting the condition to both the CMS and security event log

interfaces. If the SDU cannot verify that the user data (Ethernet and swift RF) interfaces are

closed 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 accomplished

by the manufacturer.

(2) Field-loading of ORT software is supported through 615A-2 through Ethernet 3.

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F. Fault Isolation (Subtask 23-15-30-810-006-A01)

(1) Testing

(a) Power-Up Test

1The power-up test verifies basic SDU functions and uses the front-panel LEDs

to communicate the results.

2The fault LED indicates several possible internal SDU system problems, not specific

problems, refer to Table 13.

Table 13. LED Status Indicators Table

Power LED State Fault LED State Indicates Action

ON for 60 seconds during

boot-up, then OFF

ON Normal operation during

boot-up

OFF OFF Normal operation -

OFF ON LRU fault Use Interactive Mode

BITE via CMS to confirm

fault, remove the LRU

and return it to the factory

OFF Flashing System fault, not

necessarily with the

A350 LRU

Use Interactive Mode

BITE via CMS to isolate

fault, use confirmation

method of suspect LRU

to confirm fault

Flashing 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 BITE

pages. Some examples of possible SDU system faults indicated by the flashing

fault LED includes:

• Strapped configuration does not match the capabilities of the A350 SDU system

or the configuration in the ORT - check the wiring and strapping

• Code images in the SDU do not match the expected configuration - check the

software version and your configuration

• RF path from the SDU to D/LNA failed - check wiring and cable loss settings

• USIM not detected.

(b) Troubleshooting Guidelines

1If the front-panel LEDs signal that the SDU is operating normally and some services

are still not available:

• Verify your SATCOM system - view to satellite, SCM installed

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• Verify your account information - proper login, Inmarsat registration

• Check the SATCOM system using CMS interactive mode maintenance

commands.

1Before you can make any Aero-H+ voice or data calls, make sure:

• The Inmarsat registration paperwork is filled out and submitted to the service

provider 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 BITE

through the CMS interface

• A valid ICAO address is present on the SPP interface - check via IM BITE

through the CMS interface

• All ARINC 429 interfaces configured as present are present - check via IM BITE

through the CMS interface. If any are not present, spurious faults are raised.

(d) Swift 64 or SBB Calls

1Before 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 the

CMS interface

• The USIM modules are installed and activated with the service provider (for

SBB 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 fail

the operational test procedure provided in this document to the manufacturer for fault

isolation and repair. Refer to APPENDIX A (RMA) (PGBLK 23-15-30-1700) for the

return procedure.

(3) Schematic Change Pages

(a) No schematic change pages are required. Return any SDU or SCM units that fail the

operational test procedure provided in this document to the manufacturer for fault

isolation and repair. Refer to APPENDIX A (RMA) (PGBLK 23-15-30-1700) for the

return 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 DIAGRAMS

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1. Not Applicable

DISASSEMBLY

1. Not Applicable

CLEANING

1. 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 to

cause 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 consumable

materials. 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) for

manufacturer’s address.

Table 14. Special Tools, Fixtures, and Equipment

Number Description Source

Not applicable Not applicable Not applicable

WARNING: BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS’ MATERIAL

SAFETY DATA SHEETS. SOME MATERIALS CAN BE DANGEROUS.

CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO HONEYWELL

SPECIFIED MATERIALS. MATERIALS THAT ARE NOT EQUIVALENT CAN

CAUSE DAMAGE TO THE EQUIPMENT AND CAN MAKE THE WARRANTY NOT

APPLICABLE.

(4) Refer to Table 15 for the specified consumable materials in this section.

Table 15. Consumables

Number Description Source

Not applicable Not applicable Not applicable

(5) The list that follows identifies Honeywell publications that are related to this section:

• Not applicable.

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2. 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’ MATERIAL

SAFETY DATA SHEETS. SOME MATERIALS CAN BE DANGEROUS.

CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO HONEYWELL

SPECIFIED MATERIALS. MATERIALS THAT ARE NOT EQUIVALENT CAN

CAUSE DAMAGE TO THE EQUIPMENT AND CAN MAKE THE WARRANTY NOT

APPLICABLE.

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 DAMAGED

FROM INCORRECT USE.

CAUTION: DO THESE PROCEDURES IN A CLEAN ENVIRONMENT TO PREVENT DAMAGE

TO 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 pressure

than is necessary.

(4) After you clean the assemblies and parts, supply protection from moisture, dust, and other

contamination 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/CHECK

1. 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 consumable

materials. 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) for

manufacturer’s address.

Table 16. Special Tools, Fixtures, and Equipment

Number Description Source

Not applicable Not applicable Not applicable

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WARNING: BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS’ MATERIAL

SAFETY DATA SHEETS. SOME MATERIALS CAN BE DANGEROUS.

CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO HONEYWELL

SPECIFIED MATERIALS. MATERIALS THAT ARE NOT EQUIVALENT CAN

CAUSE DAMAGE TO THE EQUIPMENT AND CAN MAKE THE WARRANTY NOT

APPLICABLE.

(4) Refer to Table 17 for the specified consumable materials in this section.

Table 17. Consumables

Number Description Source

Not 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’ MATERIAL

SAFETY DATA SHEETS. SOME MATERIALS CAN BE DANGEROUS.

CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO HONEYWELL

SPECIFIED MATERIALS. MATERIALS THAT ARE NOT EQUIVALENT CAN

CAUSE DAMAGE TO THE EQUIPMENT AND CAN MAKE THE WARRANTY NOT

APPLICABLE.

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 DAMAGED

FROM INCORRECT USE.

CAUTION: DO THESE PROCEDURES IN A CLEAN ENVIRONMENT TO PREVENT DAMAGE

TO 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 SCM

components to the aircraft must be completed as defined by the governing airworthiness

body’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 aircraft

operator to include the maintenance information supplied by this manual in the operator’s

aircraft 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 system

components to the aircraft should be completed as defined by the governing airworthiness

body’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 aircraft

operator to include the maintenance information supplied by the A350 SATCOM avionics

SDIMM in the operator’s AMM and the operator’s aircraft scheduled maintenance program.

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D. 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 minimum

each 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 the

standard 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 record

the 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.

REPAIR

1. 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 or

repair 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 consumable

materials. 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) for

manufacturer’s address.

Table 18. Special Tools, Fixtures, and Equipment

Number Description Source

Not applicable Not applicable Not applicable

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WARNING: BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS’ MATERIAL

SAFETY DATA SHEETS. SOME MATERIALS CAN BE DANGEROUS.

CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO HONEYWELL

SPECIFIED MATERIALS. MATERIALS THAT ARE NOT EQUIVALENT CAN

CAUSE DAMAGE TO THE EQUIPMENT AND CAN MAKE THE WARRANTY NOT

APPLICABLE.

(4) Refer to Table 19 for the specified consumable materials in this section.

Table 19. Consumables

Number Description Source

Not 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’ MATERIAL

SAFETY DATA SHEETS. SOME MATERIALS CAN BE DANGEROUS.

CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO HONEYWELL

SPECIFIED MATERIALS. MATERIALS THAT ARE NOT EQUIVALENT CAN

CAUSE DAMAGE TO THE EQUIPMENT AND CAN MAKE THE WARRANTY NOT

APPLICABLE.

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 DAMAGED

FROM INCORRECT USE.

CAUTION: DO THESE PROCEDURES IN A CLEAN ENVIRONMENT TO PREVENT DAMAGE

TO 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 Bite

through the CMS interface.

(2) As per continued airworthiness instructions, if an SDU or SCM is inoperative, use the standard

practices chapter of the AMM to remove the unit, secure 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 record

the 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.

ASSEMBLY

1. Not Applicable

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FITS AND CLEARANCES

1. 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 Clearances

Nomenclature/Description

Figure - Item Requirement/Dimension

Minimum clearance between the SDU and any other

equipment installed above it

0.50 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, for

standard 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 between

the parts. Monitor the rundown torque necessary just before the fastener becomes tight. Then

tighten to the final torque (refer to Table 21 for the correct thread size) and add the rundown

torque. 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 or

similar elastomeric gasket) equally to get a pressure tight seal.

Table 21. Thread Size and Torque Data

Torque in-lb (Nm)

Thread Size Aluminum Fastener CRES Fastener

6-32 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)

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Torque in-lb (Nm)

Thread Size Aluminum Fastener CRES Fastener

5/16-18 80 (9.04) 160 (18.08)

3/8-24 140 (15.82) 275 (31.075)

Table 22. Final Torque Data

Thread Size Approximate Turn After Run-Down

6-32 45 degrees

8-32 60 degrees

10-24 40 degrees

1/4-20 40 degrees

5/16-18 40 degrees

3/8-24 60 degrees

D. 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 CONSUMABLES

1. 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 the

only equipment required.

SPECIAL PROCEDURES

1. Not Applicable

REMOVAL

1. 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 consumable

materials. 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) for

manufacturer’s address.

EFFECTIVITY

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Table 23. Special Tools, Fixtures, and Equipment

Number Description Source

Not applicable Not applicable Not applicable

WARNING: BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS’ MATERIAL

SAFETY DATA SHEETS. SOME MATERIALS CAN BE DANGEROUS.

CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO HONEYWELL

SPECIFIED MATERIALS. MATERIALS THAT ARE NOT EQUIVALENT CAN

CAUSE DAMAGE TO THE EQUIPMENT AND CAN MAKE THE WARRANTY NOT

APPLICABLE.

(4) Refer to Table 24 for the specified consumable materials in this section.

Table 24. Consumable Materials

Number Description Source

Not 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’ MATERIAL

SAFETY DATA SHEETS. SOME MATERIALS CAN BE DANGEROUS.

CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO HONEYWELL

SPECIFIED MATERIALS. MATERIALS THAT ARE NOT EQUIVALENT CAN

CAUSE DAMAGE TO THE EQUIPMENT AND CAN MAKE THE WARRANTY NOT

APPLICABLE.

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 DAMAGED

FROM INCORRECT USE.

CAUTION: DO THESE PROCEDURES IN A CLEAN ENVIRONMENT TO PREVENT DAMAGE

TO 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 a

basic 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 all

equipment 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 all

equipment from the SCM and then remove the four mounting screws.

D. Job Close-up (Subtask 23-15-30-000-004-A01)

(1) Not applicable.

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INSTALLATION

1. 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 consumable

materials. 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) for

manufacturer’s address.

Table 25. Special Tools, Fixtures, and Equipment

Number Description Source

Not applicable Not applicable Not applicable

WARNING: BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS’ MATERIAL

SAFETY DATA SHEETS. SOME MATERIALS CAN BE DANGEROUS.

CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO HONEYWELL

SPECIFIED MATERIALS. MATERIALS THAT ARE NOT EQUIVALENT CAN

CAUSE DAMAGE TO THE EQUIPMENT AND CAN MAKE THE WARRANTY NOT

APPLICABLE.

(4) Refer to Table 26 for the specified consumable materials in this section.

Table 26. Consumable Materials

Number Description Source

Not applicable Not applicable Not applicable

(5) The list that follows identifies Honeywell publications that are related to this section:

• Not applicable.

EFFECTIVITY

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2. 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’ MATERIAL

SAFETY DATA SHEETS. SOME MATERIALS CAN BE DANGEROUS.

CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO HONEYWELL

SPECIFIED MATERIALS. MATERIALS THAT ARE NOT EQUIVALENT CAN

CAUSE DAMAGE TO THE EQUIPMENT AND CAN MAKE THE WARRANTY NOT

APPLICABLE.

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 DAMAGED

FROM INCORRECT USE.

CAUTION: DO THESE PROCEDURES IN A CLEAN ENVIRONMENT TO PREVENT DAMAGE

TO 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 for

any 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 and

visually 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 by

performing the test procedures described in TESTING AND FAULT ISOLATION (PGBLK

23-15-30-1000).

E. Installation Procedure (Subtask 23-15-30-400-005-A01)

(1) General

(a) Only authorized technical personnel, trained in general aviation workmanship, that have a

basic 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 unit

and requires an ARINC 600 6 MCU tray for installation.

require. The interconnection and pinout drawings are also provided for information

purposes.

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Figure 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.

milliohms 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 the

SCM and SDU interconnection diagrams.

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Figure 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 (PGBLK

23-15-30-1000).

G. Job Close-up (Subtask 23-15-30-400-007-A01)

(1) Not applicable.

SERVICING

1. Not Applicable

STORAGE (INCLUDING TRANSPORTATION)

EFFECTIVITY

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1. 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. The

function of these procedures is to make sure that the A350 SDU and SCM has protection from

dust, 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 consumable

materials. 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) for

manufacturer’s address.

Table 27. Special Tools, Fixtures, and Equipment

Number Description Source

Not applicable Not applicable Not applicable

WARNING: BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS’ MATERIAL

SAFETY DATA SHEETS. SOME MATERIALS CAN BE DANGEROUS.

CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO HONEYWELL

SPECIFIED MATERIALS. MATERIALS THAT ARE NOT EQUIVALENT CAN

CAUSE DAMAGE TO THE EQUIPMENT AND CAN MAKE THE WARRANTY NOT

APPLICABLE.

(4)Refer to Table 28 for the specified consumable materials in this section.

Table 28. Consumables

Number Description Source

Not applicable Not applicable Not applicable

(5) The list that follows identifies Honeywell publications that are related to this section:

• Not applicable.

EFFECTIVITY

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2. 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’ MATERIAL

SAFETY DATA SHEETS. SOME MATERIALS CAN BE DANGEROUS.

CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO HONEYWELL

SPECIFIED MATERIALS. MATERIALS THAT ARE NOT EQUIVALENT CAN

CAUSE DAMAGE TO THE EQUIPMENT AND CAN MAKE THE WARRANTY NOT

APPLICABLE.

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 DAMAGED

FROM INCORRECT USE.

CAUTION: DO THESE PROCEDURES IN A CLEAN ENVIRONMENT TO PREVENT DAMAGE

TO 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 temperature

range 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.

REWORK

1. 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 procedures

provided in this document to the manufacturer for fault isolation and repair. Refer to APPENDIX

A (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. Failure

to comply with this procedure can result in shipping delays and additional charges.

EFFECTIVITY

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B. Warranty Returns (Subtask 23-15-30-99C-020-A01)

(1) Equipment that qualifies for warranty repair can be returned to Honeywell for repair or

replacement at our discretion. The customer must pay the shipping costs to Honeywell and

Honeywell 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, shipping

damage, or any other condition can still be returned to Honeywell for repair or replacement

at our discretion. The customer will be notified of the cost to repair or replace the unit

before invoicing for the repair or replacement. The customer must pay for the shipping costs

to 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 shipping

containers. Failure to do so can invalidate the warranty.

(2) If SDU or SCM shipping containers are unavailable, they can be ordered from Honeywell

customer 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, please

follow 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. If

equipment must be returned to Honeywell, the product support specialist will authorize the

Repair & 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 Road

Ottawa, Ontario,

CANADA K2V 1B8

RMA #: ___________

ATTN: Repair & Overhaul

Tel: 613 591-6040 extension 1214

Fax: 613 591-8951

EFFECTIVITY

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Email: rmareturns@emsaviation.com

(7) Fax or email the details of the shipment to the Repair & Overhaul coordinator, including the

following 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 5:00

pm EST. For general inquires and status requests, please contact the Repair & Overhaul

department directly:

Phone: 613-591-9064, extension 1214 (Repair & Overhaul group)

Fax: 613-591-8951

Email: rmareturns@emsaviation.com

ILLUSTRATED PARTS LIST

1. Not Applicable

EFFECTIVITY

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

EMS Technologies Canada, Ltd. A350 Satellite Data Unit

Users Manual

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