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`BOEING
`. BoEING
`Ex. 1041, p. 2
`/' EX.1,041,p.2
`
`

`

`REPLACEMENT PAGE
`
`REVISED: December 20, 1995
`
`t9 1996 by
`Copyri
`AERONAUTICAL RADIO, INC.
`-
`2551 Riva Road
`
`Annapolis, Maryland 21401-7465 USA
`
`ARINC CI-IARACTERISTIC 716-99
`
`AIRBORNE VHF COMMUNICATIONS TRANSCEIVER
`
`Published: January 26, 1996
`
`Prepared by the Airlines Electronic Engineering Committee
`
`Characteristic 716
`
`Characteristic 716
`
`Characteristic 716—1
`
`Characteristic 716-2
`
`Characteristic 716-3
`
`Characteristic 7 1 6-4
`
`Characteristic 7 1 6-5
`
`Characteristic 716-6
`
`Characteristic 716-7
`
`Characteristic 716-8
`
`Characteristic 716-9
`
`Adopted by the Airlines Electronic Engineering Committee:
`
`December 8, 1978
`
`Adopted by the Industry:
`
`February 28, 1978
`
`Adopted by the Airlines Electronic Engineering Committee:
`
`August 30, 1979
`
`Adopted by the Airlines Electronic Engineering Committee:
`
`June 19, 1980
`
`Adopted by the Airlines Electronic Engineering Committee:
`
`September 1, 1981
`
`Adopted by the Airlines Electronic Engineering Committee:
`
`December 9, 1981
`
`Adopted by the Airlines Electronic Engineering Committee:
`
`November 4, 1982
`
`Adopted by the Airlines Electronic Engineering Committee:
`
`October 12, 1983
`
`Adopted by the Airlines Electronic Engineering Committee:
`
`May 24, 1985
`
`Adopted by the Airlines Electronic Engineering Committee:
`
`Adopted by the Airlines Electronic Engineering Committee:
`
`October 20, 1994
`
`October 31, 1995
`
`BOEING
`BOEING
`Ex. 1041, p. 3
`Ex. 1041, p. 3
`
`

`

`REflflaACEmdEN1TBA£H3
`
`I
`
`Activities of AERONAUTICAL RADIO, INC. (ARINC)
`
`and the
`
`Purpose of ARINC Characteristics
`
`FOREWORD
`
`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 fulfilment 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 technical 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 fmalized after investigation and coordination with
`the airlines who have a requirement or anticipate a requirement, with other aircraft operators,
`with the Mflitary 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, not 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 charmel 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. 1041, p. 4
`EX.104l,p.4
`
`

`

`REPLACEMENT PAGE
`
`REVISED: December 39, 1994
`
`mi.
`
`_A_B_!flC CHARACTERISTIC 716
`TABLE OF CONTENTS
`
`ITEM
`
`SUBJECT
`
`PAGE
`
`mmamug
`
`.l:»t.ol~.)1-mun
`
`
`
`
`
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`
`IN’I‘RODUC'I‘IOI_\] AND DESCRIPTION
`Purpose of This Document
`Function of Equipment
`a
`Unit Description
`VHF Transceiver Unit
`Frequency Control
`Antenna
`
`Interchangeability
`General
`Interchangeability Desired for the ARINC 716
`VI-IF Transceiver
`"Generation Interchangeability" Considerations
`Regulatory Approval
`System Parameters
`
`INTERCI-IANGEABILITY STANDARDS
`Introduction
`
`Form Factors, Connectors & Index Pin Coding
`Transceiver Unit
`"Standard Control Panel"
`Antennas
`
`Interwiring
`Power Circuitry
`Primary Power Input
`Power Control Circuitry
`The Common Ground
`Internal Circuit Protection
`Environmental Conditions
`Cooling
`Grounding and Bonding
`
`TRANSCEIVER UNIT DESIGN
`
`Frequency Range and Channeling
`Frequency Selection
`Residual FM Specification
`Transmitter Frequency Offset
`Transmit to Receive Recovery
`Receiver Design
`Sensitivity
`Selectivity
`Undesired Responses
`Cross Modulation
`Audio Output
`Audio Source Impedance
`Output Regulation
`Gain
`Hum Level
`Voice Phase Shift Limit
`Distortion
`Voice Phase Shift Limit
`Automatic Gain Control
`Desensitization and Interference Rejection
`AGC Versus Pulse Interference
`Squelch Versus Pulse Interference
`Pulse Noise Output
`Receiver Operation in the Presence of
`Inband Transmission
`0ut—of-Band FM Broadcast Intermodulation
`Interference
`Out-of-Band FM Broadcast Desensitization
`Interference
`
`m
`
`
`
`mmwmmmmmmmumppm>>HHHHHHHHHHHv|—||—‘Q44qmmmammmmaammmmhhnaanbhc
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`
`
`
`
`BOEWG
`BOEING
`Ex. 1041, p. 5
`BflMLp5
`
`
`
`.l:st.Dk~JI-K--.iO\Lh.3=-u)[~)r—-
`
`

`

`REPLACEIVIENT PAGE
`
`REVISED: December 20, 1995
`
`ITEM
`
`3.6.8
`3.6.9
`3.6.9.1
`
`3.6.9.2
`3.6.9.3
`3.6.9.4
`3.6.9.4-.1
`3.6.9.4.2
`3.6.9.5
`3.6.9.6
`3.7
`3.7.1
`3.7.2
`3.7.3
`
`3.7.4
`3.7.5
`3.7.5.1
`
`3.7.5.2
`3.7.5.3
`3.7.5.4
`3.7.6
`3.7.7
`3.7.8
`3.7.8.1
`3.7.8.2
`3.7.8.3
`3.7.8.4
`3.7.8.5
`3.7.8.6
`3.7.9
`3.7.10
`
`4.0
`
`4.1
`4.2
`4.2.1
`4.3
`4.3.1
`4.3.2
`
`4.3.3
`4.3.4
`4.3.4.1
`4.3.4.2
`4.3.4.3
`4.3.4.4
`4.3.4.4.!
`4.3.4.4.2
`4.3.4.5
`4.3.4.6
`4.4
`4.4. 1
`4.4.2
`4.4.2.1
`4.4.2.2
`4.4.2.3
`4.4.2.4
`4.4.2.5
`4.4.3
`
`ARINC CHARACTERISTIC 716
`
`TABLE OF CONTEEIS
`
`SUBJECT
`
`PAGE
`
`Squelch Provisions
`SELCAL/Data Output
`Gain
`
`Frequency Response
`Distortion
`Phase Shift
`SELCAL/Data Phase Shift
`Differential Phase Delay
`AGC Attack Time
`AGC Delay Time
`Transmitter Design
`Power Output
`Frequency Stability
`Sidetone
`
`Transmitter Spurious Radiation
`Microphone Input
`Modulation Level
`
`Speech Processing
`Frequency Response
`Distortion
`Leakage
`Key Line
`Data Input
`Modulation Level
`Level Control
`Frequency Response
`Distortion
`Phase Shift
`Differential Delay
`Muting
`Receive to Transmit Turn Around
`
`TRANSCEIVER UNIT DESIGN FOR THE 8.33 kHz
`CI-IANNEL—SPACED MODE OF OPERATION
`Frequency Range and Channeling
`Frequency Selection
`Control Panel Programming
`Receiver Design
`Selectivity
`Cross Modulation
`
`Squelch Provision
`SELCAIJData Output
`Gain
`Frequency Response
`Distortion
`Phase Shift
`SELCAL Phase Shift
`Differential Phase Delay
`AGC Attack Time
`AGC Decay Time
`Transmitter Design
`Frequency Stability
`Microphone Input
`Modulation Level
`Speech Processing
`Frequency Response
`Distortion
`Transmitter Occupied Spectrum
`Data Input
`
`iv
`
`7
`7
`7
`
`7
`7
`7
`7
`7
`7
`7
`7
`7
`8
`8
`
`8
`8
`8
`
`8
`8
`9
`9
`9
`9
`9
`9
`9
`9
`9
`9
`9
`.9
`
`10
`10
`10
`10
`10
`1021
`
`105.
`103.
`10::
`10a
`10a
`103.
`10a
`10b
`101:
`10]:
`10}:
`10b
`10b
`101)
`10b
`101:
`10b
`1013
`10b
`
`BOEING
`BOEING
`Ex. 1041, p. 6
`Ex. 1041, p. 6
`
`

`

`E
`
`REPLACEMENT PAGE
`
`REVISED: December 30, 1994
`
`5.0
`5. 1
`
`5.2
`
`6.0
`6.1
`6.2
`6.3
`6.4
`
`'7 .0
`7.1
`7.2
`7.3
`7.4
`
`7.5
`
`ATTACHMENTS
`
`-
`
`1
`2
`
`3
`4
`5
`6
`7
`
`8
`
`9
`10
`11
`
`1
`
`Appendices
`
`1
`
`2
`3
`
`ARINC CI-IARACTERISTIC 716
`TABLE OF CONTENTS
`
`ANTENNAS
`General
`
`Antenna Consideration for Multiple Systems
`Operations
`
`AUTOMATIC TEST EQUIPMENT PROVISIONS
`General
`Unit Identification
`Pin Allocation
`Use of ATLAS Language
`
`'
`
`BUILT-IN-TEST EQUIPMENT (BITE)
`Built-In-Test Equipment (BITE)
`BITE Display
`Fault Monitor
`Sclf—Test Initiation
`
`Monitor Memory Output
`
`Transceiver Unit Connector Positioning
`Standard Interwiring
`Notes Applicable to the Standard Interwiring
`Receiver Selectivity
`Environmental Test Categories
`Typical VHF Communications Antenna
`Standard "Four-Wire" Microphone Interface
`Control Panel Guidelines
`Standard Control Panel Outline Drawing
`Assumed Test Procedures for Desensitization and
`
`Interference Rejection
`Typical Test Procedures: Audio Output
`Receiver Selectivity
`Transmitter Spectrum Mask
`
`Excerpts from the International Standards and Recommended
`Practices Aeronautical Telecommunications Annex 10
`to the Convention on International Civil Aviation
`Bibliography
`Frequency—Channel Pairing Plan
`
`1 1
`1 1
`
`11A
`
`11A
`11A
`11A
`11A
`11A
`
`11B
`11B
`11B
`11B
`11B
`
`‘ 11B
`
`12
`13
`14 — 14A
`15
`16
`17
`18
`19
`20
`
`-
`
`20A
`2013
`' 20C
`20D
`
`21-52
`
`53
`54
`
`v
`
`BOEING
`BOEING
`Ex. 1041, p. 7
`Ex. 1041, p. 7
`
`El Q
`
`L
`
`‘I
`
`FT;
`i
`
`__
`E’
`
`,
`J
`
`5'
`
`:
`
`i
`
`L: \ '
`
`' 3‘
`
`’
`Ll
`1
`
`'
`
`I
`
`I
`
`'
`
`I
`
`'
`
`'
`
`I
`
`ll
`
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`
`

`

`
`BOEINGBOEING
`BOEING
`Ex. 1041, p. 8
`
`Ex. 1041, p. 8Ex. 1041, p. 8
`
`

`

`REPLACEMENT PAGE
`
`REVISED: December .30, 1994
`ARINC CHARACTERISTIC 716 - Page 1
`
`1.0 INTRODUCTION AND DESCRIPTION
`
`1.1 Pugpose of This Document
`
`1.3.2 Frguency Control
`
`.
`
`This document sets forth the desired characteristics of a
`new generation VHF Communications Transceiver System
`intended for installation in all
`types of commercial
`transport aircraft.
`The intent of this document is to
`provide general and specific design guidance for the
`development and installation of a VHF Transceiver
`primarily for airline use.
`It will describe the desired
`operation capability of the equipment and the standards
`necessary to ensure interchanageability.
`
`Section 3.0 is applicable to the 25 kHz channel-spaced
`voice and data modes of operation.
`Section 4.0 is
`applicable to an optional 8.33 kHz channel-spaced voice
`mode of operation and defines only the characteristics
`specific to the 8.33 kHz channel-spaced mode of
`operation, such as the channeling, the frequency selection,
`the selectivity,
`the frequency stability,
`the frequency
`response, and the transmitter occupied spectrum. The
`characteristics in Section 3.0 are also applicable to the
`optional 8.33 kHz channel-spaced voice mode of
`operation unless otherwise specified in Section 4.0.
`
`COMMENTARY
`
`The 8.33 kl-Iz channel-spaced mode of operation for
`voice communications, if implemented concurrently
`with the 25 kHz channel-spaced modes of operation,
`would require dual-bandwidth receivers to ensure
`inter-operability of the airborne transceivers with the
`current (25 kHz) and proposed European narrowband
`(8.33 kl-Iz) VHF voice communications systems.
`The narrowband mode of operation is limited to
`voice communications.
`
`Equipment manufacturers should note that this document
`encourages
`them to produce maintenance-free, high
`performance equipment rather than that of minimum
`weight and size. They are at liberty to accomplish this
`objective by means of the techniques they consider to be
`the most appropriate. The airline customers are interested
`primarily in the end result
`rather
`than the means
`employed to achieve it.
`
`1.2 Function of fluipment
`
`The function of the VHF Communication Transceiver is
`to
`provide
`the
`aircraft with
`a
`voice
`or
`data
`communications
`capability with
`the
`ground
`via
`conventional VI-IF circuits.
`
`1.3 Unit Description
`
`1.3.1 VHF Transceiver Unit
`
`the
`should house all
`The VHF Transceiver unit
`components, electronics circuitry, etc. , incident to channel
`selection, receiving and transmitting functions of VHF
`air-ground-air communications.
`
`Manual frequency control of the VHF Transceiver should
`be accomplished from a VHF frequency control unit or
`the equivalent data input
`from a centralized radio
`management system.
`The VHF Transceiver control
`should utilize the 2-wire serial digital frequency!’function
`selection system defined in ARINC Specification 429.
`
`1.3.3 Antenna
`
`The VHF Comm. antenna should be vertically polarized
`and provide omnidirectional azimuth radiation pattern
`coverage.
`
`1.4 Interchangeabiligz
`
`1.4.1 General
`
`One of the primary functions of an ARINC Equipment
`Characteristic is to designate,
`in addition to certain
`performance parameters,
`the interchangeability in an
`aircraft of equipment produced by various manufacturers.
`The manufacturer is referred to Section 1.6 of ARINC
`Report 414 for definitions of
`terms
`and general
`requirements
`for
`the
`airline
`industry
`for
`interchangeability. As explained in that report, the degree
`of interchangeability considered necessary and attainable
`for each particular system is specified in the pertinent
`ARINC Equipment Characteristic for that system.
`
`1.4.2 Interchangeability Desired for the ARINC 716
`VHF Transceiver
`
`Unit interchangeabilty is required for the transceiver
`regardless of manufacturing source. In recognition of the
`widely varying control unit designs expected in the future,
`unit interchangeability is not sought in the control unit
`except, however, that electrical interface of controls shall
`conform to the digital signal standards set forth in this
`characteristic.
`
`1.4.3 "Generation Interchangeabilig“ Considerations
`
`In defining the equipment described in this characteristic,
`the air transport
`industry has chosen to depart from
`several of its previous VHF transceiver standards.
`In
`order to achieve the full benefit of the economics offered
`by these changes, the industry desires that no provisions
`be made in the equipment for backward compatibility with
`with earlier
`generations of VHF Communication
`equipment described by ARINC 520, ARINC 546,
`ARINC 566 and ARINC 566A.
`
`Unchanged, however, is the industry’s tradititional desire
`that future evolutionary equipment improvements and the
`inclusion of additional functions innew equipments during
`the next few years, do not violate the interwiring and
`form factor
`standards
`set
`forth in this document.
`Provisions to ensure forward-looking "generation
`
`
`
`E
`
`I
`
`BOEWG
`BOEING
`Ex. 1041, p. 9
`Ex.104],p.9
`
`

`

`ADDED: December 30, 1994
`ARINC CHARACTERISTIC 716 - Page 1A
`
`1.0 INTRODUCTION AND DESCRIPTION §cont’d1
`
`1.4.3 "Generation Interchangeability‘ Considerations
`§cont’d1
`
`(as best can be predicated) are
`interchangeability"
`included in this document to guide manufacturers in future
`developments.
`
`1.5 Regglatog Apgroval
`
`The equipment must meet all applicable FAA and FCC
`regulatory requirements. Manufacturers are urged to
`obtain all necessary information from the FAA and the
`FCC for such regulatory approval. This information is
`not contained in this characteristic, nor is it available
`from ARINC.
`
`1. 6
`
`System Parameters
`
`System parameters applicable to air-ground-air VI-IF
`communications may be found in Appendix 1
`to this
`Characteristic.
`‘They have been excerpted from ICAO
`Annex 10, “International Standards and Recommended
`Practices, Aeronautical Telecommunications", and from
`the report of the ICAO’s 7th Air Navigation Conference.
`
`NEXT PAGE INTENTIONAILY LEFT BLANK
`BOEING
`A
`BOEING
`Ex. 1041, p. 10
`EX. 1041, p. 10
`
`

`

`
`
`ET‘ET‘
`
`
`
`L_L_
`
`
`
`11
`
`
`
`CC
`
`
`
` l[I l[I
`
`
`:_:_
`
`EE
`
`
`
`::
`
`
`
`*1*1
`
`
`
`}}
`
`
`
`II
`
`
`
`II
`
`
`
`II
`
`
`
`IIII
`
`
`
`llll
`
`
`
`IIII
`
`
`
`IIII
`
`
`
`''
`
`BOEING
`
`BOEINGBOEING
`Ex. 1041, p. 11
`
`Ex. 1041, p. 11Ex. 1041, p. 11
`
`

`

`REPLACEMENT PAGE
`
`ARINC CI-IARACTERISTIC 716 - Page 2 ‘
`
`REVISED: December 30, 1994
`
`2.0 INTERCHANGEABILITY STANDARDS
`
`2.1 Introduction
`
`COMMENTARY
`
`This Section of this Characteristic sets forth the specific
`form factor, mounting provisions, interwiring, input and
`output interfaces and power supply characteristics desired
`for this VHF Communications Transceiver.
`
`this
`although
`that
`note
`should
`Manufacturers
`Characteristic does not preclude the use of different form
`factors and interwiring features, the practical problem of
`redesigning what will
`then be a
`standard aircraft
`installation to accommodate some special system could
`very well make the use of that other design prohibitively
`expensive for the customer. They should recognize,
`therefore,
`the practical
`advantages of developing
`equipment in accordance with the standards set forth in
`this document.
`
`2.2 Form Factors, Connectors & Index Pin Coding
`
`2.2. 1 Transceiver Unit
`
`The Transceiver should comply with the dimensional
`standards in ARINC Specification 600, “Air Transport
`Avionics Equipment Interfaces (NIC Phase 1)" , for the 3
`MCU form factor. The Transceiver" should also comply
`with ARINC 600 standards in respect of weight, racking
`attachments, front and rear projections and cooling.
`
`¢—1
`
`The Transceiver should be provided with a low insertion
`force, size 1 shell ARINC 600 service connector. This
`connection, which
`should
`accommodate
`service
`interconnections in its middle insert (MP), automatic test
`equipment
`interconnections in its top insert (TP) and
`coaxial and power interconnections in its bottom insert
`(BP),
`should be located on the center grid of the
`receiver’s rear panel. Index pin code 04 should be used.
`
`The ATE interconnection insert ('I‘P) will not be included
`in the mating half of the connector installed in the aircraft
`since ATE interconnections are employed in the bench
`testing of the receiver only.
`This insert should be
`provided with a protective cover to prevent contamination
`of the contacts during the time the receiver is installed in
`the aircraft. Further guidance on the ATE interface will
`(3-8 | be found in Chapter 6 of this document.
`
`C-1
`
`2.2.2 "Standard Control Panel"
`
`Frequency control of the ARINC 716 VHF Transceiver
`is effected by means of facilities provided on a VHF
`NAVICOMM control panel, a dedicated control panel on
`the data entry panel of a centralized radio management
`system. The approach used in a given airframe will be
`the choice of the airline and/or the airframe manufacturer.
`Guidance on the design of a VI-IF COMM control panel
`suitable for use with the ARINC 716 VI-IF Transceiver
`
`in
`may be found in Attachment 7 to this document,
`accordance with the tradition in ARINC Equipment
`Characteristics of setting forth certain standardized
`provisions for a "Standard Control Panel" which should
`be made available by equipment manufacturers for those
`customers having "standard" needs.
`
`The Mythical "Standard Control Panel"
`
`The term "Standard Control Panel" as used in this
`
`Characteristic applies to a control panel conforming
`to the functional specification in Attachment 7 of this
`Characteristic and having form factor and connector
`functions as
`set
`forth therein.
`The standard
`interwiring is included in Attachment 2.
`
`2.2.3 Antennas
`
`There are no specific form factors set forth herein for the
`antennas to be employed with this particular equipment as
`there are numerous designs presently on the market for
`the purpose. Attachment 5 shows a typical antenna.
`Designers of new antennas are encouraged to survey the
`present antenna mounting provisions and maintain
`compatibility insofar as is practicable with the present
`standard mountings, depending upon, of course, on the
`particular aircraft type for which the antenna is intended
`and the need to minimize weight. It is recognized that for
`most air transport applications the antennas will be
`integrated into the airframe design and it is, therefore,
`only in special installations or retrofit installations where
`specific “antenna units" would be needed.
`
`Further general information on antennas may be found in ¢
`Section 5.0.
`
`2. 3 Interwiring
`
`The standard interwiring to he installed for the VHF
`COMM Transceiver is set forth in Attachment 2. This
`interwiring is designed to provide the degree of
`interchangeability
`specified
`in
`Section
`1.4,
`and
`manufacturers are cautioned not
`to rely upon special
`wires, cabling or shielding for use with particular units
`because they will not exist in the standard installation.
`
`COMMENTARY
`
`Why Standardize Interwiring?
`
`The standardized interwiring is perhaps the heart of
`all ARINC Characteristics.
`It is this feature which
`
`to complete his
`customer
`the airline
`allows
`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.
`
`The reader’s attention is directed to the interwiring
`guidance in ARINC Report No. 414, Section 5.0. This
`material defines all of the basic standards utilized in
`
`equipment
`all
`and
`installations
`airframe wiring
`manufacturers should make themselves familiar with it.
`
`BOEING
`_BOE|NG
`Ex. 1041, p. 12
`Ex. 1041, p. 12
`
`

`

`L1
`
`REPLACEMENT PAGE
`
`REVISED: January 15, 1982
`ARINC CI-IARACTERISTIC 716 - Page 3
`
`2.0 INTERCHANGEABILITY STANDARDS ]cont’d!
`
`The reader is also cautioned to give consideration to the
`specific notes in Attachment 2 as they apply to the
`standard interwiring.
`
`2.4 Power Circuitry
`
`2.4.1 Priming Power Input
`
`The V}-IF Transceiver and Control Panel should be
`designed to use 27.5 volts DC primary power. The
`aircraft
`power
`supply
`characteristics,
`utilization,
`equipment design limitations, and general guidance
`material are set forth in ARINC Report No. 413A,
`"Guidance for Aircraft Electrical Power Utilization and
`Transient Protection."
`
`One circuit breaker of the size shown in Attachment 2
`should be provided in the standard installation.
`
`2.4.2 Power Control Circuitry
`
`There should be no master on/off power switching within
`the VHF Transceiver. Any user desiring power onfoff
`control for the unit should provide, through the medium
`of a switching function installed in the airframe, means of
`interrupting the primary power to the equipment.
`It
`should be noted that primary power onfoff switches for
`the VHF Transceiver will not be needed in most
`
`installations, and power will be wired directly to the
`equipment from the circuit breaker panel.
`
`2.4.3 The 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 ship’s structure.
`They
`should not be used as common returns for any circuits
`carrying AC currents.
`
`2.4.4.
`
`Internal Circuit Protection
`
`the
`for
`The basic master power protection means
`transceiver will be external
`to the unit and utilize a
`standard circuit 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.
`
`If internal protection by fuses is employed, these fuses
`should not be accessible when the set is installed in the
`
`aircraft radio rack, but should be replaceable only when
`the guipment goes through the service shop.
`
`If such subdistribution circuit protection is by means of
`circuit breakers,
`the majority prefer
`that
`these be
`accessible on the front panel of the equipment so that they
`can be reset in service.
`-
`
`2.5 Environmental Conditions
`
`The VHF Transceiver should he specified environmentally
`in terms of the requirements of RTCA Document DO-
`160, "Environmental Conditions and Test Procedures for
`Airborne Electronic/Electrical Equipment
`and
`Instruments", dated February 28, 1975. Attachment 4 to
`this Characteristic tabulates the relevant environmental
`categories.
`
`2.6 Cooling
`
`The VHF Transceiver 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 installation should
`provide an air flow rate of 13.6 kgfhr of 40°C air and the
`unit should not dissipate more than an average of 62 watts
`of energy. The coolant air pressure drop through the
`equipment should be 5 i 3 mm at standard conditions of
`1013.25 mbars. This pressure drop does not include the
`drop through a returning orifice when such orifice-is
`located external to the equipment case.
`
`¢-4
`
`COMMENTARY
`
`The specified cooling air flow rate is based on an
`estimated average power dissipation. However, it
`should be noted that power dissipation 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
`600
`(NIC)
`for
`the maximum
`dissipation.
`
`COMMENTARY
`
`Equipment failures in aircraft due to inadequate
`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 VHF Transceivers
`and
`aircraft
`installations.
`
`2.7 Grounding and Bonding
`
`The attention of equipment and airframe manufacturers is
`drawn to the guidance material
`in Section 3.2.4 of
`ARINC Specification 600 and Appendix 1 of ARINC
`Specification 404A on the subject of equipment and radio
`rack grounding and bonding.
`
`BOEING
`BOEING
`Ex. 1041, p. 13
`EX. 1041, p. 13
`
`

`

`REPLACEMENT PAGE
`
`ARINC CHARACTERISTIC 716 - Page 4
`
`REVISED: November 30, 1983
`
`3.0 TRANSCEIVER UNIT DESIGN
`
`3.1
`
`Frguency Range and Channeling
`
`The transceiver should operate on a total of 760 channels
`spaced 25 kHz apart in the band 118.000 to 137.000
`MHz. Channel changing time should not exceed 60 ms.
`
`COMMENTARY
`
`The VHF transceiver should recognize fr uencylfunction
`words with Source/Destination Identifiere?SDI) bits 9 and
`10 encoded with its own installation number or encoded
`with "00",
`the "all-call" code as defined in ARINC c—5
`Specification 429. See Note 1 to Attachment 2 for pin
`encoding of the installation numbers.
`
`Prior to the publication of Supplement 5 of this
`Characteristic,
`the upper frequency limit was 136
`MHz, with the ability to operate in the band 136-138
`MHz when needed. The 1979 World Administrative
`Radio Conference of the ITU allocated an additional
`1 MHz of spectrum to the Aeronautical Mobile (R)
`Service, resulting in the new allocation 118 to 137
`V M1-Iz. "While operational requirements have not yet
`been fully identified, the users desire that all ARINC
`716 radios operate over that frequency band.
`
`3.2 Fgguency Selection
`
`The transceiver should be designed to utilize the serial
`digital frequency/function selection system described in
`ARINC Specification 720. Two serial digital data input
`ports should be provided, one labeled "Freq./Funct.
`Select Data Input Port A" and the other "Freq./Funct.
`Select Data Input Port B".
`(See Attachment 2 to this
`document for the connector
`in assignments.)
`The
`receiver should determine whicli) of these ports should be
`open to admit data by reference to the binary state of -the
`tuning-data source selection discrete. It should respond to
`data delivered to the "A" port and ignore data delivered
`to the "B" port when the source selection discrete is in the
`"ground" state. It should respond to data delivered to the
`"B" ort and ignore data delivered to the "A" port when
`the iscrete is in the "open circuit" state. The "ground"
`state of the discrete is defined as a voltage between 0 and
`+3.5 VDC at the connector pin assigned to the discrete
`in Attachment 2. The maximum current flow in the
`discrete wire in this condition should not exceed 20 m.A.
`The "open "circuit" state is defined as a voltage greater
`than wt-18.5 VDC (+30 VDC maximum) at this pm or a
`resistance to DC ground from this pin of greater than
`500,000 Qs.
`
`When the transceiver is installed in an aircraft in which a
`dedicated control panel su plies tuning information, the
`data bus from that panel s ould be connected to the "B"
`port on the receiver.
`The "A" port and the source
`selection discrete are unused. When the receiver is
`installed in an aircraft
`in which a centralized radio
`management
`s stem is employed,
`its normal control
`source should e connected to the "A" port, its back-up
`source to the "B" port and the source selection discrete
`wired in the manner described in the radio management
`specification.
`
`ARINC Specification 429, "Mark 33 Digital Information
`Transfer System (DITS)", defines the format of the serial
`digital tuning signal delivered to the transceiver and the
`word repetition rate (5 per second minimum). Should this
`rate fall below 5 per second (word removal from the bus
`signifies tuning mformation source failure),
`the word
`signlstatus matrix indicates an invalid condition, or the
`word parity fail to be odd, the trahsceiver should remain
`tuned to and operate on the last valid frequency received.
`
`3.3 Residual FM Specification
`
`A modulation index of l or better should be achieved
`across the entire range of the transceiver.
`
`3.4 Transmitter Fguency Offset
`
`The transceiver should be capable of double-channel
`operation,
`i.e.,
`transmitting on a frequency higher by
`some whole number of megahertz than that on which its
`receiver is tuned. Sufficient flexibili
`should be provided
`to permit the same or a different v no for this offset to
`be selected for each whole megahertz of receiving
`frequency.
`
`Double-channel o eration should be effected by the
`grounding of the "
`requency Offset Enable" wire, either
`y the control panel or other source.
`
`COMMENTARY
`
`The amount of separation of transmit and receive
`frequencies
`that might
`be
`em loyed
`in
`communications systems of the future has not yet
`been determined.
`It is assumed that once they are
`established, however, offset values will be subject to
`no more than very infr uent change.
`It
`is
`anticipated, therefore, that o set selection for each
`receive frequency will be made wi