" é
`
`7’.
`
`L Ah. N\cf%¢'I:IAI=fA‘Cj7EiRiI#siTj:C»is;
`
`,-
`
`;
`
`_
`" ‘L/.
`*2‘
`~.
`.,_
`4
`I
`7
`____;';
`.
`‘
`«
`\ /I;
`A / pususngnz» *_EcEMB_ER~30, 1994
`_
`‘I
`J ,
`, V.7_\
`I
`-—.
`—V
`N5
`'
`
`3
`
`;__/
`
`,
`
`'-
`
`'
`
`,.
`
`, Au"Al2,I/_l,§lG'r'_£:oou_g_:ENT
`,.Pi:pared1:y,
`,
`'
`V
`-‘,
`V I
`/T" AIRLINES EIJECTRGINIC ENGINEERING c\gJMl',r1|'I'l'EE
`Pub/llshgd Igy r
`_
`=3 ,
`'
`-2
`u
`«
`'AERQNAUTICAL R_Ap1o. Lac. »
`@551 RIVA ROAD. AJSINAFPUS. MRRYMND 2140.1,
`
`'
`
`11
`
`BOEING
`Ex. 1040, p. 1
`
`

`
`submitted by various
`is based on material
`This document
`participants during the drafting; process. Neither AEEC nor
`ARINC has made any determination whether these materials could
`be subject to claims of patent or other proprietary rights by third
`parties, and no representation or warranty, express or implied, is
`made in this regard. Any use of or reliance on this document shall
`constitute an acceptance hereof ‘as is“ and be subject
`to this
`
`disclaimer.
`
`BOHNG
`BOEING
`Ex. 1040, p. 2
`Ex.1040,p.2
`
`

`
`Copyright” 1992. by
`AERONAUTICAL RADIO, INC.
`2551 Riva Road
`Annapolis, Maryland 21401
`
`ARINC CI-IARACTERISTIC 753”
`
`HF DATA LINK SYSTEM
`
`Published: December 30, 1994
`
`-Prepared by the Airlines Electronic Engineering Committee
`
`Chamcteristic 753
`
`Adopted by the Airlines Electronic Engineering Committee: October 20, 1994
`
`Adopted by the Industry: December 9, 1994
`
`BOEING
`BOEING
`Ex. 1040, p. 3
`EX. 1040, p. 3
`
`

`
`EQEEEKHD
`
`Activities of AERONAUTICAL RADIO, INC. (ARINC)
`
`and the
`
`Purpose of ARINC Characteristics
`
`Aeronautical Radio, Inc. is a corporation in which the United States scheduled airlines
`are the principal stockholders. Other stockholders include a variety of other air transport
`companies, aircraft manufacturers and non-U.S. airlines.
`
`Activities of ARINC include the operation of an extensive system of domestic and
`overseas aeronautical land radio stations, the fulfillment of systems requirements to accomplish
`ground and airborne compatibility, the allocation and assignment of frequencies to meet those
`needs, the coordination incident to standard airborne communications and electronics systems
`and the exchange of technical information. ARINC sponsors the Airlines Electronic Engineering
`Committee (AEEC), composed of airline techni.cal personnel. The AEEC formulates standards
`for electronic equipment and systems for the airlines.
`The establishment of Equipment
`Characteristics is a principal function of this Committee.
`
`An ARINC Equipment Characteristic is finalized after investigation and coordination with
`the airlines who have a requirement or anticipate a requirement, with other aircraft operators,
`with the Military services having similar requirements, and with the equipment manufacturers.
`It is released as an ARINC Equipment Characteristic only when the interested airline companies
`are in general agreement. Such a release does not commit any airline or ARINC to purchase
`equipment so described nor does it establish or indicate recognition of the existence of an
`operational
`requirement for such equipment, nor does it constitute endorsement of any
`manufacturer’s product designed or built to meet the Characteristic. An ARINC Characteristic
`has a twofold purpose, which is:
`
`(1)
`
`(2)
`
`To indicate to the prospective manufacturers of airline electronic equipment the
`considered opinion of the airline technical people, coordinated on an industry
`basis, concerning requisites of new equipment, and
`
`in the
`To channel new equipment designs in a direction which can result
`maximum possible standardization of those physical and electrical characteristics
`which influence interchangeability of equipment without seriously hampering
`engineering initiative.
`
`BOHNG
`BOEING
`Ex. 1040, p. 4
`Ex.1040,p.4
`
`

`
`ARJNC CHARACTERISTIC 753
`TABLE OF CONTENTS
`
`E
`
`SUBJECT
`
`
`
`_9AuMHommpppmmHoUI.hLi)[~.)i—ntor-—I
`
`
`
`2.
`
`2 2
`
`.
`2.
`2.
`2.
`2.
`2.
`2.
`
`INTRODUCTION
`Purpose of this Document
`Relationship to Other Documents
`System Overview
`Airborne HFDL System Configuration
`Ground System Configuration
`Terms
`
`Interchangeability
`Regulatory Approvals
`
`INTERCHANGEABILITY STANDARDS
`Introduction
`
`Form Factor, Connector, and Index Pin Coding
`Standard Interwiring
`Power Circuitry
`Primary Power Input
`Power Control Circuitry
`Common Ground
`Internal Circuit Protection
`Abnormal Power
`
`System Functions and Signal Characteristics
`Environmental Conditions
`Cooling
`Grounding and Bonding
`Standardized Signalling
`ARINC 429 DITS Data Bus
`Standard "Open"
`Standard "Ground"
`
`Standard "Applied Voltage" Output
`Standard Discrete Input
`Standard Discrete Output
`Standard Program Pin Input
`
`SYSTEM DESIGN
`Introduction
`
`System Design
`AOC and ATS
`Other Services
`
`HFDL Avionics Components
`HF Data Radio
`HF Data Unit
`HF Data Link Control Functions
`Optional Additional Components
`Central Maintenance System
`Analog Data Operation
`Interlocks on Dual HFDR Systems
`HFDR and HFDU Modes of Operation
`HFDR Mode Select
`HFDU/I-IF Transceiver Combination Mode Select
`ARINC 719 HP Transceiver Controlled by
`Discretes
`
`ARINC 719 HF Transceiver Controlled by
`ARINC 429 Words
`ARINC 559A HF Transceiver
`
`HF DATA RADIO DESIGN
`Introduction
`Transceiver
`
`Tuning
`Frequency Switching Time
`Transmitter - Receiver Interaction
`Transmit to Receive Turnaround Time
`
`tQt~Jk~JhArdr—i—i--IL-
`
`
`
`i—3§i)i|i|—3}--\|—|I-II-H-31-||d|d|—'|—'CVOC\D\O\DOOOOO0OOOOO0--I‘--J‘--J‘--I‘--I‘-~l'--IIO\G\UI§hUIU|UIUI'J\-I5-I8-b-B-P-H-D-3-I>~b)U)LrJLD
`
`BOEING
`BOEING
`Ex. 1040, p. 5
`EX. 1040, p. 5
`
`'--30\U'I-hLr)l\H—-
`
`
`
`L):--Italks)!--I{Jr-I
`IQEQD-‘t—‘IONlxlldldLL0bL
`
`22
`
`.
`2.
`2.
`2.
`2.
`2.
`2.
`2.
`2.
`2.
`2.
`2.
`
`
`
`3.
`3.
`3.
`3.
`
`3 3 3
`
`.
`3.
`
`3 3
`
`.
`3.
`3.
`
`3 3 3 3
`
`.
`3.
`
`sssssss99.......PwNN-o99ooommssswwwwvwwwoPPPPPPPW““°“PPP*
`
`

`
`Ii
`
`3*’ M
`
`
`
`eseeesees+++s+++++s++++++++++++++9sassesessseesssesesssssseses@9999asasaaesewwwwmsesss9ssseesees+999ssewwwwwwwwwwwwwwwwwwwwv
`
`4999bG%%¥s¥b“F%%rr-LflI~Jr-L0t~Jb---FhLa-‘lt-.Ib--U1-Fhla3I~JI-~\
`
`
`
`
`flHHH*““*WPP““ew~—w~999ewn99wwamewwww~—
`
`
`
`-fl-{.oJl--3*-'I‘~JI-t.~7ItdI---.'lO\UI~h-l.oJt\J=--
`
`ARINC CHARACTERISTIC 753
`
`TABLE OF CONTENTS
`
`SUBTECT
`
`Receive to Transmit Turnaround Time
`Transmitter
`
`Power Output
`SSE Suppressed Cartier
`SSB Full Carrier (AME)
`Tune Power
`VSWR Tolerance
`
`Transmit Duty Cycle
`Frequency Stability
`Phase Stability
`Audio Input
`Input Level
`Audio Processing and Modulation limiting
`Frequency Response
`Transmit Audio Distortion
`Transmitter Keying
`Occupied Spectrum
`Interrnodulation Distortion
`Harmonics
`Non-Harmonics
`
`Tone Tuning Signal
`Receiver
`Sensitivity
`Selectivity
`SSB Suppressed Carrier
`Amplitude Modulated Equivalent (AME)
`Group Delay
`Frequency Stability
`Spurious Responses
`Audio Output
`Source Impedance
`Gain
`
`Frequency Response
`Distortion
`I-Ium Level
`Phase Shift
`Phase Stability
`Automatic Gain Control
`Voice Mode
`Data Mode
`
`Settling Time
`RF Sensitivity Control andlor Squelch Control
`SSB Mode Linearity
`SELCAL Output
`Frequency Response
`Distortion
`Phase Shift
`
`Differential Phase Delay
`I-{FDR — System Interface
`HF Voicel'Data Mode Switching
`HFDR Voice Transceiver Tuning
`ARINC 719 Style I-IF Transceiver Tuning
`ARINC 559A Style: HF Transceiver 'l\1ning
`I-IF Voice Transceiver Keying
`I-IF Antenna Coupler Tuning Initiation
`ACARS MUICMU Interface Functions
`Voi-::efData Mode Switching Functions
`Other Interfaces
`Aircraft Position Data
`Universal Coordinated Time (UTC) Data
`ICAO Address Data
`Maintenance Data
`
`iv
`
`PAGE
`
`11
`12
`
`12
`
`n----u-ap—-y--:-Ib-a—nv—-:-r—n>-In-r--I-IIb—>—II-I-AI-I--Inb—Irur—-r-—an—-:-»un—In—nr—una>-b-ar-huu—Ip—ar-n-ahdhavuwat--to--r-I--I-o-an--I--u—n—->-up--II-n--I
`
`BOEING
`BOEING
`Ex. 1040, p. 6
`EX. 1040, p. 6
`
`

`
`
`
`
`
`tQ|—-bJ|—IU)kQI--A
`
`ARINC CI-IARACTERISTIC 753
`TABLE OF CONTENTS
`
`SUBJECT
`
`Maintenance System Identification
`Data Loader
`Status Indication Discretes
`HFDL DATA LINK LOST Indication Discrete
`HFDR FAULT Indication Discrete
`Built-In Tests
`
`Air;’Ground Discrete Input
`Transmit Inhibit Discrete Input
`Key Event Output
`SDI Input Pin Definition
`HF Test Enable Discrete Definition
`Chopper Control
`Strap Even Parity
`ICAO Strap Even Parity
`
`I-IF DATA UNIT DESIGN
`Introduction
`
`I-IF Voice/Data Mode Enable Switching
`Air/Ground Data Transmission Functions
`HF Transceiver Audio Interface
`Transmit Audio Waveform
`HF Transceiver Keying
`Air/Ground Data Receive Functions
`HF Transceiver Audio Interface
`Receive Audio Waveform
`HF Transceiver Tuning
`ARINC 719 HF Transceiver Tuning
`ARINC 559A I-IF Transceiver Tuning
`HF Antenna Coupler Tuning Initiation
`Air/Ground Data Transfer Protocol
`ACARS MUICMU Interface Functions
`Other Interfaces
`Aircraft Position Data
`
`Universal Coordinated Time (UTC) Data
`ICAO Address Data
`Maintenance Data
`
`Maintenance System Identification
`Data Loader
`
`AirfGround Discrete Input
`MU/CMU Interface Speed Select
`Transmit Inhibit Discrete Input
`SDI Inputs
`Strap Even Parity
`Status Indications
`HF DATA LINK LOST Indication Discrete
`HFDU FAULT Indication Discrete
`Built-In Tests
`
`DATALINK CONTROL FUNCTIONS
`Introduction
`HFDCF Functions
`HF Voice/Data Select
`Programmable Functions
`I-IF Datalink ON/OFF Switch
`I-IF Datalink DATA LINK LOST Indication
`I-IFDUII-IFDR FAULT Indication
`HF Datalink Status Display
`HFDU Mode Select
`
`HF Frequency Port Select
`RF Sensitivity or Squelch Control
`
`BOEING
`BOEING
`Ex. 1040, p. 7
`EX. 1040, p. 7
`
`IE
`
`D—|
`
`4 4 4
`
`.
`4.
`4.
`
`....:"*:'*:'-‘-:‘-“-.‘*.4‘.~°*:F*:“
`
`:5'5'5‘.‘°)°.“°.‘°§°§°}°§°§°§°§°‘°°°“‘°‘E"$“°‘:‘°*:"*"‘P’P’!'°‘*”""‘°F"P‘?‘.°“F".°‘.°‘.°‘?‘P‘?‘.°‘.°‘9‘"naaaoozswnnmee
`
`
`
`5.
`5.
`5.
`5.
`5.
`
`5 5 5
`
`.
`5.
`5.
`5.
`5.
`5.
`5.
`5.
`5.
`5.
`5.
`5.
`5.
`5.
`5.
`5.
`5.
`5.
`5.
`5.
`5.
`5.
`5.
`5.
`5.
`
`
`
`D—|\DOO'--.iD'\Ul.-P-F~UJbJI—\0;.
`
`I\J)--4
`
`6.0
`6.1
`6.2
`6.2.1
`6.2.2
`6.2.3
`6.2.4
`6.2.5
`6.2.6
`6.2.7
`6.2.8
`6.2.9
`
`

`
`ARINC CHARACTERISTIC 753
`
`TABLE OE CONTENTS
`
`IE
`
`El
`
`PAGE
`
`iiLLL L
`
`i.n1t:'mi~.nI—-i..oioi—-
`
`hhwmm
`b-db-|l—lI-fil-II-I
`
`qqqqqqqqqqqqqqqq
`
`HfiflqfiflflfiflqflomnwppnypuwemacmnbhhnnahbhAnnhhhhbhbbbhhhbLn:zi.mo.—-PPPPPPPPPPPPPP?
`
`
`v'...ai.»aL»>L>i.»i.s:i~JiaixJi~J'''°''
`
`
`ATTACHMENTS
`
`ANTENNA SYSTEMS
`Introduction
`Antenna
`
`HF Antenna Coupler
`Matching
`Frequency Coverage
`Power Handling Capability
`Tune Mode
`
`Interwiring
`Multiwire Serial Interface (MSI)
`Physical Layer
`Physical Medium
`Serial vs Parallel Interface Selection
`Detection Scheme
`Parallel Interface (ARINC 719) Definition
`Multiwire Serial Interface (ARINC 753
`or MSI) Definition
`Link Layer Protocol
`Link Protocol Sequencing
`Link Protocol Message Description
`Link Protocol Timings
`Control Protocol
`Sequencing
`Aborting Commands
`RF Operations
`Control Protocol Command and Request Messages
`Example Communication Sequence
`Tuning Time
`
`PROVISIONS FOR AUTOMATIC TEST EQUIPMENT
`General
`
`ATE Testing
`
`PROVISIONS EOR BUILT—l.N TEST EQUIPMENT {§I’I‘E)
`Introduction
`BITE Interfaces
`OMS Interfaces
`Character-Oriented CFDS Interfaces
`Bit-Oriented CFDS Interfaces
`MUICMU BITE Interfaces
`I-IFDRXI-IFDU Equipment Identification Word
`Bite Presentation
`Fault Monitor
`Self-Test Initiation
`Monitor Memory Output
`
`Airborne Subsystem Block Diagram
`HFDR Avionics Configuration A
`I-[FDR System Block Diagram
`I-[FDR Standard Interwiring
`HFDR Top Connector Layout
`I-{FDR Middle Connector Layout
`I-IFDR Bottom Connector Layout
`ARINC 600 Size 2 Connector - I-IFDR Rear View
`
`I-IFDU Avionics Configuration B
`(Using ARINC 719 HF XCVR With Discrete
`Voicea'Data Control}
`HFDU Avionics Configuration B
`(Using ARINC 719 HP XCVR With ARINC 429
`Voicel'Data Control)
`
`26
`26
`26
`26
`26
`26
`26
`26
`26
`27
`2'.’
`27
`27
`27
`28
`
`28
`29
`29
`29
`30
`30
`30
`30
`31
`31
`45
`49
`
`S0
`
`S0
`
`5 1
`
`51
`52
`S2
`52
`S2
`S2
`52
`52
`S3
`
`S4
`55
`56
`57-61
`62
`63
`64
`65
`
`66
`
`6')‘
`
`vi
`
`BOHNG
`BOEING
`Ex. 1040, p. 8
`Ex.1040,p.8
`
`

`
`ITEM
`
`ATTACHMENTS
`
`3- 1 C
`
`3-1D
`3-2
`3-3A
`3-3B
`3-3C
`3-3D
`4-1A
`
`APPENDICES
`
`ARINC CI-IARACTERISTIC 753
`
`TABLE OF CONTENTS
`
`SUBJECT
`
`HFDU Avionics Configuration B (Using HF XCVR
`ARINC 559A Type)
`HFDU System Block Diagram
`HFDU Standard Interwiring
`HFDU Top Connector Layout
`HFDU Middle Connector Layout
`HFDU Bottom Connector layout
`ARINC 600 Size 2 Connector - HFDU Rear View
`HF Data Control Panel Standard Interwiring
`HF Data Control Panel Connector Layout
`Coupler Standard Interwiring
`Coupler Connector Layout
`Notes Applicable to Standard Interwiring
`Environmental Test Categories Per DO-160C
`Maintenance System Codes
`USB Selectivity
`Typical Test Procedures
`Typical Message Transfer Diagram
`Coupler CMC Flight Data
`
`HF Transmission Requirements
`ACARS MU-HFDU MSK Interface
`ARINC 429 Control Word Formats for the HFDR
`Documents List
`Acronym List
`
`BOHNG
`BOEING
`Ex. 1040, p. 9
`Ex.1040,p.9
`
`

`
`BOEING
`BOEING
`Ex. 1040, p. 10
`EX. 1040, p. 10
`
`

`
`ARINC CI-IARACTERISTIC 753 7 Page 1
`
`1.0 INTRODUCTION
`
`1.1 Pugpose of This Document
`
`The HFDL system should have two main modes:
`
`form and fit
`the physical
`This document contains
`interface definition and a
`dimensions,
`the electrical
`description of the functional operation of the airborne
`components of the High Frequency Data Link (HFDL)
`communications system. An overview of the associated
`ground system is also provided. The protocols used in
`the HFDL system are defined in ARINC Specification 635
`"I-IF Data Link Protocols".
`
`The intent of this document is to provide general and
`specific design guidance for
`the development
`and
`installation of the airborne equipment. As such,
`this
`guidance covers. the desired operational capability of the
`HFDL system and the standards necessary to achieve
`interchangeability of the airborne hardware. The HP Data
`Link system has various modes of operation which are
`described more fully in Chapters 3, 4 and 5.
`
`COMMENTARY
`
`this
`should note that
`Equipment manufacturers
`document aims
`to encourage them to produce
`maintenance-free,
`high performance
`equipment.
`They are at liberty to accomplish this by the use of
`design techniques they consider
`to be the most
`appropriate.
`Their airline customers are more
`interested in the end result
`than in the means to
`achieve it.
`
`1.2 Relationship to Other Documents
`
`functionality into the
`This Characteristic introduces
`components of the HFDL by way of reference. Many of
`these
`references
`are
`to other Airline Electronic
`Engineering Committee
`(AEEC) documents.
`The
`designer should use the most current version of the
`referenced document unless a specific version is given.
`A list of referenced documents is provided in Appendix D
`for the readers convenience.
`
`1.3 System Overview
`
`The HFDL System consists of the Airborne HFDL
`System Configuration described in Section 1.3.1 and the
`Ground System Configuration described in Section 1.3.2.
`
`1.3.1 Airborne HFDL System Configgration
`
`The HFDL avionics system hardware consists of an I-IF
`Data Unit (HFDU) or an integrated voice/data I-IF Data
`Radio (HFDR). The I-IFDR provides either voice or data
`communications services in a simplex mode on demand.
`The HFDU interfaces with a conventional analog Single
`Side Band (SSB) HF transceiver already installed in the
`aircraft to provide voice or data communications services
`in a simplex mode on demand also.
`This document
`assumes that the airborne components implementing HF
`Data Link are arranged as shown in Attachments 2
`through 4 and that
`they function within the system
`operating rules specified in ARINC Specification 635,
`ARINC Specification 637, and ARINC Specification 638.
`
`— the Data Mode for digital data transmission as
`described throughout
`this document and ARINC
`Specification 635 ,
`
`- the Voice Mode, which is identical in function and
`control as the existing HF Voice Radios, according
`to ARINC Characteristic 719.
`
`As an HF Packet Communications (I-IFPAC) bridge, the
`High Frequency Data Link (HFDL) system is an integral
`part of the I-IFPAC/Aeronautical Telecommunication
`Network (ATN) communications protocol suite. Detailed
`background of HFPAC/ATN can be found in ARINC
`Specifications 635, 637 and 638.
`
`COMMENTARY
`
`The use of the HFDL system (Attachments 2
`through 4),
`for sole means of ATN operation
`depends on the integrity and availability requirements
`set forth by world wide agencies. Aeronautical
`operators planning to implement ATN capability may
`need to install additional equipment.
`
`the HFDL avionics
`Depending on the selected mode,
`system operates with a Communications Management Unit
`(CMU) (see ARINC Characteristic 748), a Management
`Unit (MU) (see ARINC Characteristics 597, 724 and
`7248, and ARINC Specification 618), a Centralized Fault
`Display Interface Unit (CFDIU) (see ARINC Report 604)
`or Onboard Maintenance System (OMS) (see ARINC
`Report 624).
`
`The Aircraft Communications Addressing and Reporting
`System (ACARS) Management Unit
`(MU)
`or
`Communications Management Unit (CMU) is the onboard
`router for the Aeronautical Telecommunications Network
`(ATN). As such, all application messages intended for
`transmission to the ground are sent onboard to the MU or
`CMU, which in—turn has the responsibility to determine
`the most efficient subnetwork over which to transmit the
`packet, and to route the packet accordingly. The MU or
`CMU also implements
`any management protocols
`required to ensure the continued and correct operation of
`the various bridges located onboard the aircraft.
`
`1.3.2 Ground System Configpration
`
`The aeronautical I-IF subnetwork provides air}ground data
`and voice communications capability. Ground service is
`provided by a network of HF ground stations strategically
`located to cover major oceanic air routes as well as
`continental areas.
`
`The HFDL air/ground subnetwork provides primarily
`Airline Operational Control
`(AOC) and Air Traffic
`Control (ATC) data and voice communications services.
`Optional services, FAX and voice patch, may also be
`available at some ground stations.
`
`BOEING
`BOEING
`Ex. 1040, p. 11
`EX. 1040, p. 11
`
`

`
`ARINC CHARACTERISTIC 753 - Page 2
`
`1.0 INTRODUCTION [cont’d1
`
`1.4 Terms
`
`Antenna: Built-In Antenna; not considered as part of the
`I-IFDR
`
`CFDS:
`
`Central Fault Display System
`
`Coupler: Antenna tuning device to match the antenna
`impedance to the 50 ohm coaxial transmission
`line.
`
`I-IF DataNoice
`HFDL: High Frequency Data Link;
`Communication Subnetwork AirfGround.
`
`I-IFDR: High Frequency Data Radio; used for
`airborne HF Transceiver.
`
`the
`
`The HFDU
`I-IFDU: High Frequency Data Unit.
`contains the Modem for the system when the
`Modem is a separate LRU.
`
`OMS:
`
`On-Board Maintenance System
`
`1.5 Interchange-abiligg
`
`System interchangeability, as defined in Section 2.0 of
`ARINC Report 607, "Guidance for Designers of Airborne
`Electronic Equipment“,
`is desired for the I-[FDR and
`HFDU. The standards necessary to ensure this level of
`interchangeability are set
`forth in Chapter 2 of this
`document.
`
`1.6 Regglatogg Aggrovals
`
`all applicable regulatory
`The equipment must meet
`requirements. Manufacturers are urged to obtain all
`necessary information for such regulatory approval. This
`information is not contained in this characteristic, nor is
`it available from ARINC.
`
`BOEING
`BOEING
`Ex. 1040, p. 12
`EX. 1040, p. 12
`
`

`
`2.0 INTERCHANGEABILITY STANDARDS
`
`ARINC CHARACTERISTIC 753 - Page 3
`
`2.1 Introduction
`
`This chapter sets forth the specific form factor, mounting
`provisions, interwiring, input and output interfaces and
`power supply characteristics desired for the HF Data
`Radio and HF Data Unit. These standards will permit the
`parallel, but independent design of compatible equipment
`and airframe installations.
`
`Unit interchangeability is required for the HF Data Radio,
`HF Data Unit, and. Antenna Coupler,
`regardless of
`manufacturing source.
`
`COMMENTARY
`
`In order to achieve the full benefit of the economics
`
`the industry desires that
`offered by these changes,
`any provisions for backwards compatibility with
`earlier generations of HF Communications equipment
`described by ARINC ‘719 be provided as basic
`provisions.
`
`The ARINC 753 transceiver (HFDR) is pin- and function-
`compatible with the ARINC 719 transceiver. When an
`HF Data Radio is installed in an ARINC 719 slot,
`(replacing an ARINC 719 transceiver) it should operate
`with ARINC 719 radio functionality. An HF Data Unit
`attached to this array would be required to obtain I-IF
`Data. Link functionality.
`
`2.2 Form Factor, Connector, and Index Pin Coding
`
`The HFDR and HFDU should comply with the
`dimensional standards in ARINC Specification 600, "Air
`Transport Avionics Equipment Interfaces (NIC Phase 1)“,
`for the 6 MCU and 4 MCU form factors respectively.
`The HFDR and HFDU should also comply with ARINC
`Specification 600 standards with respect
`to weight,
`racking attachments,
`front and rear projections and
`cooling.
`
`COMMENTARY
`
`The only form factor defined in this Characteristic is
`the Modular Concept Unit (MCU) defined in ARINC
`Specification 600.
`Packaging of the HFDR in
`accordance with ARINC Specification 404A was not
`considered desirable.
`However,
`some retrofit
`installations into aircraft racking for ARINC 404A
`equipment are expected.
`
`The HFDR and HFDU should each be provided with a
`low insertion force, Size 2 Shell ARINC Specification 600
`service
`connector.
`This connector, which should
`accommodate service interconnections in its middle plug
`(MP)
`and
`top
`plug
`(TP)
`inserts
`and
`power
`interconnections in its bottom plug (BP) insert, should be
`located on the center grid of the HFDR and HFDU rear
`panel.
`Index pin code 10 should be used for the HFDR.
`Index pin code 20 should be used for the HFDU. The pin
`coding for
`the HFDR and HFDU are depicted in
`Attachments 2-3D and 3—3D respectively.
`
`If bench testing of the HFDR and HFDU with Automatic
`Test Equipment
`(ATE)
`necessitates
`interconnect
`capabilities that are not covered by the pin assignments on
`the service connector set forth in Attachments 2-3A
`through 2-3C and 3—3A through 3~3C (including pins
`TP4-A through TP4D which are designated for unspecified
`ATE function use) an auxiliary connector should be
`provided whose type and location are selected by the
`equipment manufacturer. As this auxiliary connector will
`not be used while the HFDR or HFDU is installed in the
`aircraft,
`it should be provided with a cover to ensure
`protection from damage, contamination, ete., during that
`time. The manufacturer should observe the standards of
`ARINC Specification 600 when choosing the location for
`the connector. Also, other than accommodating the needs
`for equipment identification by the ATE described in
`Section 8 of this document, the manufacturer is free to
`make whatever use of both the service connector ATE
`pins and the auxiliary connector pins he wishes.
`
`COMMENTARY
`
`is specified to permit
`The auxiliary connector
`completion of the interface without recourse to the
`use of individual "test leads" from the ATE, each of
`which has to be clipped, or otherwise secured, to a
`test point on the equipment.
`
`2.3 Standard Interwiring
`
`The standard interwiring to be installed for the HFDR and
`HFDU are set
`forth in Attachments 2-2 and 3-2
`
`respectively. This interwiring is designed to provide the
`degree of interchangeability specified in Section 1.5 of
`this Characteristic.
`
`COMMENTARY
`
`The standardized
`Why Standardize Interwiring?
`interwiring is perhaps the heart of all ARINC
`Characteristics. It is this feature which allows the
`airline customer to complete his negotiation with the
`airframe manufacturer so that the latter can proceed
`with engineering and initial
`fabrication prior to
`airline
`commitment on a
`specific
`source of
`equipment.
`This
`provides
`the
`equipment
`manufacturer with many valuable months in which to
`put
`the
`final
`"polish"
`on his
`equipment
`in
`development.
`
`COMMENTARY
`
`The reader is cautioned to give due consideration to
`the specific notes in Attachment 5 as they apply to
`the
`standard interwiring.
`Manufacturers
`are
`cautioned not to rely on special wires, cabling or
`shielding for use with particular units because they
`will
`not
`exist
`in
`a
`standard
`installation.
`Furthermore, manufactures are encouraged to utilize,
`for ATE purposes, only those pins designated for
`ATE, and not make use of pins not currently defined
`or left for customer definition.
`
`BOEING
`BOEING
`Ex. 1040, p. 13
`EX. 1040, p. 13
`
`

`
`ARINC CHARACTERISTIC 753 - Page 4
`
`2.0 INTERCHANGEABILITY SI ANDARDS §cont’d[
`
`2.4 Power Circuitfl
`
`2.4.1 Primggg Power Input
`
`The HFDR should he designed to accept 115 Vac, 400
`Hz, three phase power. The I-{FDR should be protected
`by a 5 ampere circuit breaker in each phase. The HFDU,
`if installed, should be designed to accept 115 Vac, 400
`Hz, single phase power. The HFDU should be protected
`by a single 2 ampere circuit breaker.
`See ARINC
`Characteristic 413A, "Guidance for Aircraft Electrical
`Power Utilization and Transient Protection".
`
`2.4.2 Power Cogtrol Circuitg/_
`
`The primary power to the HF transceiver should not
`normally be controlled by a master onfoff switch.
`It
`should be noted that no onfoff switches will be needed in
`
`installations. A master on/off power switching
`most
`capability should be provided as an option. When this
`option is selected, power input to the transceiver should
`be accomplished using the pins reserved for switched
`power.
`
`2.4.3 Common Ground
`
`The wires designated as “Common Ground" (or as chassis
`ground) are used for the DC ground return to the aircraft
`structure and may be grounded to the chassis of the
`equipment if the manufacturer so desires. In any event,
`they will be grounded to the aircraft structure. They
`should not be used as common returns for any circuits
`carrying AC currents.
`
`2.4.4 Internal Circuit Protection
`
`the equipment should automatically resume
`conditions,
`normal operation when the frequency andfor voltage
`returns within limits. Set manufacturers should provide
`their own protection. wholly within the equipment against
`the possibility of one of the three AC line circuits being
`interrupted by an aircraft electrical system power phase
`failure in the aircraft. The equipment should not be
`damaged in any way if one phase lead is opened and it is
`desirable the equipment:
`
`(a) continue to operate at reduced power, or,
`
`(la) cease operating entirely, or,
`
`(c) malfunction in such a manner as to make it evident
`to the crew that such a failure has occurred, in order
`to guard against attempted continued operation which
`is not providing satisfactory communications.
`
`5 stem Functions
`
`d Si
`
`Characteristics
`
`A list of the system functions and signal characteristics
`required to ensure the desired level of interchangeability
`for the l-IFDR and HFDU are set forth in Chapters 4, 5
`and 6 of this document and ARINC Specification 635.
`
`2.6 Environmental Conditions
`
`The HFDL Line Replaceable Units (LRUs) should be
`specified environmentally in terms of the requirements of
`RTCA Document DO-160C, "Environmental Conditions
`and Test Procedures
`for Airborne Electronic
`and
`Electrical Equipment and instruments". Attachment 6 to
`this document
`tabulates
`the relevant
`environmental
`categories.
`
`The basic master power protection means for the HFDR
`will be external to the unit and utilize a standard circuit
`
`2.? Cooling
`
`breaker rating. Within the equipment, no master power
`protection means
`is
`to
`be
`provided,
`although
`subdistribution circuit protection is acceptable where the
`set manufacturer feels this would improve the overall
`reliability of the equipment.
`
`these fuses
`If internal protection by fuses is employed,
`should not be accessible when the set is installed in the
`aircraft radio rack, but should be replaceable only when
`the gquipment goes through the service shop.
`
`If such subdistribution circuit protection is by means of
`circuit bfiers, the majority of airlines prefer that these
`be accessible on the front panel of the equipment so that
`they can be reset in service.
`
`2.4.5 Abnormal Power
`
`The I-IFDL equipment should accept power variations
`without adverse effects upon equipment performance.
`Refer to ARINC Report 413A, "Guidance for Aircraft
`Electrical Power Utilization and Transient Protection" or
`ARINC Report 609,
`"Design Guidance for Aircraft
`Electrical Power Systems". The equipment should be of
`such design that it will not be damaged by power supply
`frequencies andior voltages below the minimum or
`exceeding the maximum specified operating voltage and
`frequency, and if operation is interrupted under these
`
`The I-IFDR and HFDU should be designed to accept, and
`airframe manufacturers should configure the installation
`to provide forced air cooling as defined in ARINC
`Specification 600.
`The standard HFDR installation
`should provide an air flow rate of 57.2 kgfhr of 40 °C
`(max.) air and the unit should not dissipate more than an
`average of 260 watts of power. The standard I-IFDU
`installation should provide an air flow rate of 22 kgfhr of
`40 °C (max.) air and the unit should not dissipate more
`than an average of 100 watts of power. The coolant air
`pressure drop through the HFDR should be 25 i 5 mm
`of water and 5 1 5 mm of water through the HFDU at
`standard conditions. The HFDR and HFDU should be
`designed to expend this pressure drop to maximize the
`cooling effect. Adherence to the pressure drop standard
`is needed to allow interchangeability of the equipment.
`Continuous transmitter operation without ARINC cooling
`is permissible as long as the internal blower operates
`continuously and the ambient air temperature does not
`exceed 55°C.
`
`COMMENTARY
`
`Although the I-IFDR and HFDU are packaged in
`accordance with ARINC Specification 600, some
`retrofit installations will be made into aircraft racking
`designed in accordance with ARJNC Specification
`404A. The cooling provisions of these racking
`
`BOEING
`BOEING
`Ex. 1040, p. 14
`EX. 1040, p. 14
`
`

`
`2.0 INTERCHANGEABILITY STANDARDS !cont’d[
`
`ARINC CHARACTERISTIC 753 - Page 5
`
`standards were intentionally established such that
`ARINC 600 equipment would be compatible with
`ARINC 404A racking. Thus, the HFDR and HFDU
`cooling provisions are compatible with ARINC 404A
`aircraft racking.
`
`The HFDR and/or HFDU designer should consider
`that
`the HFDR and HFDU will be expected to
`operate without substantially lower reliability in an
`aircraft installation in which cooling is not available.
`A loss of cooling should not cause total loss of
`functionality, although a partial reduction in output
`power is acceptable.
`
`COMMENTARY
`
`The specified cooling air flow rate is based on an
`estimated average power dissipation. However, it
`should be noted that the power dissipation of the
`HFDR during transmission will be higher than the
`estimated average. Thus, the specified air flow rate
`will be less than the rate recommended in ARINC
`
`Specification
`dissipation.
`
`600
`
`(NIC)
`
`for
`
`the maximum
`
`failures in aircraft due to inadequate
`Equipment
`thermal management have plagued the airlines for
`many years.
`In Section 3.5 of ARINC Specification
`600 they have written down everything they believe
`airframe and equipment suppliers need to know to
`prevent such problems in the future. They regard
`this material as "required reading" for all potential
`suppliers of I-IFDR/HFDU and aircraft installation.
`
`2.9.2 Standard "(_)pen"
`
`is characterized by a
`signal
`The standard "open"
`resistance of 100,000 ohms or more with respect to signal
`common.
`
`COMMENTARY
`
`In many installations, a single switch is used to
`supply a logic input to several LRUs. One or more
`of these LRUs may utilize a pul1~up resistor in its
`input circuitry. The result is that an "open" may be
`accompanied by the presence of +27.5 Vdc nominal.
`The signal could range from 12 to 36 Vdc.
`
`2.9.3 Standard "Ground"
`
`A standard "ground" signal may be generated by either a
`solid state or mechanical type switch. For mechanical
`switch—type circuitry a resistance of 10 ohms or less to
`signal common would represent the "ground" condition.
`Semiconductor circuitry should exhibit a voltage of 3.5
`Vdc or less with respect
`to signal common in the
`"ground" condition.
`
`2.9.4 Standard "Applied Voltage" Output
`
`The standard "applied voltage" is defined as having a
`nominal value of +27.5 Vdc.
`‘This voltage should be
`considered to be "applied" when the actual voltage under
`the specified load conditions exceeds 18.5 volts (+36 Vdc
`maximum) and should be considered to be "not applied"
`when the equivalent
`impedance to the voltage source
`exceeds 100,000 ohms.
`
`2.8 Grounding and Bonding
`
`2.9.5 Standard Discrete Input
`
`The attention of equipment and airframe manufacturers is
`drawn to the guidance material
`in Section 3.2.4 of
`ARINC Specification 600 as well as Section 6 and
`Appendix 2 of ARINC Specification 404A on the subject
`of equipment and radio rack grounding and bonding.
`
`2.9 Standardized Si galling
`
`inputs and outputs from the
`The standard electrical
`systems should be in the form of a digital format or
`switch contact. Standards should be established exactly to
`assure the desired interchangeability of equipment.
`
`Certain basic standards established herein are applicable
`to all signals. Unless otherwise specified the signals
`should conform with the standards set
`forth in the
`subsections below.
`
`2.9.1 ARINC 429 DITS Data Bus
`
`ARINC Specification 429 "Mark 33 Digital Information
`Transfer System (DITS)" is the controlling document for
`data word formats,
`refresh rates,
`resolutions,
`etc.
`Material in this document on these topics is included for
`reference purpos