ARINC 739-1-1990 Multi-Purpose Control and Display Unit《多用途控制和显示器系统1986包括附录1》.pdf

1、MULTI-PURPOSE CONTROLAND DISPLAY UNITARINC CHARACTERISTIC 739-1PUBLISHED: JUNE 20, 1990AN DOCUMENTPrepared byAIRLINES ELECTRONIC ENGINEERING COMMITTEEPublished byAERONAUTICAL RADIO, INC.2551 RIVA ROAD, ANNAPOLIS, MARYLAND 21401This document is based on material submitted by variousparticipants durin

2、g the drafting process. Neither AEEC norARINC has made any determination whether these materialscould be subject to claims of patent or other proprietary rights bythird parties, and no representation or warranty, express orimplied, is made in this regard. Any use of or reliance on thisdocument shall

3、 constitute an acceptance hereof “as is“ and besubject to this disclaimer.REPLACEMENT PAGE REVISED: June 1, 1990Copyright 1995 byAERONAUTICAL RADIO, INC.2551 Riva RoadAnnapolis, Maryland 21401-7465 USAARINC CHARACTERISTIC 739-1MULTI-PURPOSE CONTROL AND DISPLAY UNITPublished: June 20, 1990Prepared by

4、 the Airlines Electronic Engineering CommitteeCharacteristic 739 Adopted by the Airlines Electronic Engineering Committee: March 21, 1986Characteristic 739-1 Adopted by the Airlines Electronic Engineering Committee: December 8, 1988FOREWORDActivities of AERONAUTICAL RADIO, INC. (ARINC)and thePurpose

5、 of ARINC CharacteristicsAeronautical Radio, Inc. is a corporation in which the United States scheduled airlines arethe principal stockholders. Other stockholders include a variety of other air transport companies,aircraft manufacturers and foreign flag airlines.Activities of ARINC include the opera

6、tion of an extensive system of domestic andoverseas aeronautical land radio stations, the fulfillment of systems requirements to accomplishground and airborne compatibility, the allocation and assignment of frequencies to meet thoseneeds, the coordination incident to standard airborne compatibility,

7、 the allocation and assignmentof frequencies to meet those needs, the coordination incident to standard airborne communicationsand electronics systems and the exchange of technical information. ARINC sponsors the AirlinesElectronic Engineering Committee (AEEC), composed of airline technical personne

8、l. The AEECformulates standards for electronic equipment and systems for the airlines. The establishmentof Equipment Characteristics is a principal function of this Committee.An ARINC Equipment Characteristic is finalized after investigation and coordination withthe airlines who have a requirement o

9、r 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 companiesare in general agreement. Such a release does not commi

10、t any airline or ARINC to purchaseequipment so described nor does it establish or indicate recognition of the existence of anoperational requirement for such equipment, not does it constitute endorsement of anymanufacturers product designed or built to meet the Characteristic. An ARINC Characteristi

11、chas a twofold purpose, which is:(1) To indicate to the prospective manufacturers of airline electronic equipment theconsidered opinion of the airline technical people, coordinated on an industrybasis, concerning requisites of new equipment, and(2) To channel new equipment designs in a direction whi

12、ch can result in themaximum possible standardization of those physical and electrical characteristicswhich influence interchangeability of equipment without seriously hamperingengineering initiative.iiREPLACEMENT PAGE REVISED: June 1, 1990ARINC CHARACTERISTIC 739TABLE OF CONTENTSITEM SUBJECT PAGE1.0

13、 INTRODUCTION AND DESCRIPTION 11.1 Purpose of This Document 11.2 Functions 11.3 System Description 11.4 Interchangeability 11.4.1 General 11.4.2 Interchangeability Desired for the ARINC 739 MCDU 11.4.3 “Generation Interchangeability“ Consideration 11.5 Regulatory Approval 12.0 INTERCHANGEABILITY STA

14、NDARDS 22.1 Introduction 22.2 Form Factor 22.3 Environmental Conditions 22.4 Interwiring 22.5 Thermal Interface and Design 22.6 Power Circuitry 22.6.1 Primary Power Input 22.6.2 Power Control Circuitry 2-32.6.3 The Common Ground 32.6.4 The AC Common Cold 32.7 Weights 32.8 Grounding and Bonding 33.0

15、MCDU DESCRIPTION 43.1 General 43.2 Display 43.3 Keyboard 43.3.1 Basic Function Keys 43.3.2 Specific Function Keys 43.3.3 Alpha-Numeric Keys 43.3.4 Panel Illumination and Annunciator Lights 4-53.4 MCDU Operation and Display 53.4.1 Typical MCDU Initiation 53.4.2 MCDU Menu 53.4.3 Subsystem Specific Men

16、u 53.4.4 Non-Menu Operation 53.4.5 Scratchpad and Data Field Entry 5-63.4.6 Clearing Data Fields 63.4.7 Exiting 63.4.8 Proposed Philosophy to Menu Stepping 63.5 MCDU Outputs 63.6 MCDU Inputs 63.7 System Communication 63.7.1 Subsystem Identification 6-73.7.2 Menu Generation 73.7.2.1 Initial Menu 73.7

17、.2.2 Menu Changes 7-83.7.2.3 Alternate Menu Display 83.7.3 Data Communication 8iiiREPLACEMENT PAGE REVISED: June 1, 1990ARINC CHARACTERISTIC 739TABLE OF CONTENTSITEM SUBJECT PAGE3.7.3.1 Subsystem Initiated Messages 83.7.3.1.1 Subsystems Not Currently Active 83.7.3.1.2 Active Subsystems 83.7.3.2 MCDU

18、 Data Request 8-93.7.3.3 Message Transfer 93.7.3.4 Control Word 93.7.3.5 Data Word 93.7.3.6 Background/Vector Words 93.7.3.7 Discrete Word 9-103.7.3.8 Button Push Word 103.8 Built-In Test Equipment (BITE) 103.8.1 BITE Consideration 103.8.2 BITE Display 103.8.3 Self-Test 104.0 NAVIGATION AND DISPLAY

19、CONTROL 114.1 Introduction 114.2 Functional Requirements 114.2.1 System Selection and Control 114.2.2 Navigation Radio Tuning 114.2.2.1 Mode Selection 114.2.2.2 General Operation 114.2.2.3 Navigation Tuning Page Functions 114.2.2.3.1 Tuning Inhibit 114.2.2.4 Interface Requirements 124.2.3 Standby Na

20、vigation 124.2.3.1 Mode Selection 124.2.3.2 Operation 124.2.3.2.1 General 124.2.3.2.2 Navigation and Guidance 124.2.3.2.3 CDU Page Access 124.2.3.2.4 Navigation Computations 134.2.3.2.5 Map Display 134.2.3.3 Interface Requirement 134.2.4 Alternate EFIS Control 134.2.4.1 General 134.2.4.2 Page Access

21、 13-144.2.4.3 Interface 144.2.5 Alternate EICAS Control 144.2.5.1 General 144.2.5.2 Page Access 144.2.5.3 Interface 144.2.6 System Communication 144.2.6.1 Inter-system 144.3 Hardware Requirements 154.3.1 General 154.3.2 Form Factor 154.4 Standby Navigation Lateral Guidance 15ivATTACHMENTS1 Standard

22、Interwiring 16Notes on Standard Interwiring 172 Address Labels 183 Digital Word Formats 19-224 Character Code Assignments (Derived from ISO #5) 245 Environmental Test Categories 256 Typical System Configuration 267 Typical Front Panel Layout 278 Glossary 289-1 Optional Specialized MCDU Functions 299

23、-2 MCDU Pin Assignments 30vARINC CHARACTERISTIC 739 - Page 11.0 INTRODUCTION AND DESCRIPTION1.1 Purpose of This DocumentThis document sets forth the desired characteristics of aMulti-Purpose Control and Display Unit (MCDU) intendedfor installation in commercial transport aircraft. Theintent of this

24、document is to provide general and specificdesign guidance for the development of the MCDU. Itdescribes the desired operational capability of theequipment and the standards necessary to ensureinterchangeability.Equipment manufacturers should note that this documentencourages them to produce maintena

25、nce-free, highperformance equipment rather than that of minimumweight and size. They are at liberty to accomplish thisobjective by means of the techniques they consider to bethe most appropriate. Their airline customers areinterested primarily in the end result rather than the meansemployed to achie

26、ve it.Avionics systems optimization can be achieved on boardmodern aircraft by minimizing the cost, weight and size ofavionics. The use of one or more MCDUs will contributeto this goal.By the use of identical MCDUs, the specific control anddisplay units for ACARS, AIDS, CFDS and other systemscan be

27、eliminated. There would be substantial savingsdue to:1. Elimination of CDU spares2. Simplification of cockpit3. Easier crew operation training (common procedures)4. Flexibility to accommodate other systems (e.g., ModeS)5. MCDU can be applicable to any aircraft.1.2 FunctionsThe MCDU is expected to co

28、mmunicate with multiplesystems one at a time (equivalent to multi-purposeswitch). System selection is by use of keys on the MCDU(dedicated keys or by menu item key) and is achieved bysending different user system address labels on a commonoutput command data bus. See Attachment 6.The MCDU should pro

29、vide means for manually selectingsubsystems connected and for inserting system controlparameters and modes of operation. In addition, it shouldprovide display capability for various subsystems outputsas well as for the verification of data entered intomemory. Certain annunciations related to systemo

30、peration may also be included.Providing that the standardized protocols and messagestructures are used, the MCDU can be used with anysystem regardless of application. It is therefore truly multi-purpose.1.3 System DescriptionThe MCDU is essentially a “dumb“ box. It contains onlythe circuitry and pro

31、cessing necessary to accept alpha-numeric message codes and display them on the screen,and circuitry for transmitting command codes relating toline keys or keyboard keys. Data communication isdetermined by standard protocols and message formats,within the selected system. The structure and content o

32、fmessages, menus and interpretation of commands iscarried out by software in the user system and not in theMCDU.1.4 Interchangeability1.4.1 GeneralOne of the primary functions of an ARINC EquipmentCharacteristic is to designate, in addition to certainperformance parameters, the interchangeability de

33、sired ofaircraft equipment produced by various manufacturers.The manufacturer is referred to Section 1.6 of ARINCReport 414 for definitions of Terms and GeneralRequirements for the airline industry forinterchangeability. As explained in that report, the degreeof interchangeability considered necessa

34、ry and attainablefor each particular equipment is specified in the pertinentARINC Equipment Characteristic.1.4.2 Interchangeability Desired for the ARINC 739MCDUUnit interchangeability is desired for the MCDUregardless of manufacturing source. The physicalattributes, the electrical interfaces and op

35、eration of theMCDU were defined to accommodate application to awide variety of avionics. The standards necessary toachieve this level of interchangeability are set forth in thisCharacteristic.1.4.3 “Generation Interchangeability“ ConsiderationsIn defining the equipment described in this Characterist

36、ic,the air transport industry has chosen to depart from severalof its previous control function standards. In order toachieve the full benefit of the economies offered by thesechanges, the industry desires that no provisions be madein this equipment for backward compatibility with earliergenerations

37、 of equipment.Unchanged, however, is the industrys traditional desirethat future evolutionary equipment improvements and theinclusion of additional functions in new equipments in thenext few years do not violate the interwiring and formfactor standards set forth in this document. Provisions toensure

38、 forward-looking “generation interchangeability“ (asbest can be predicted) are included in this document toguide manufacturers in future developments.1.5 Regulatory ApprovalThe MCDU should meet all applicable FCC and FAAregulatory requirements. Manufacturers are urged toobtain all necessary informat

39、ion from the FAA and theFCC on such regulatory approval. This information is notcontained in this Characteristic, nor is it available fromARINC.REPLACEMENT PAGE REVISED: June 1, 1990ARINC CHARACTERISTIC 739 - Page 22.0 INTERCHANGEABILITY STANDARDS2.1 IntroductionThis Section sets forth the specific

40、form factor, mountingprovisions, interwiring, input and output interfaces andpower supply characteristics desired for the Multi-PurposeControl and Display Unit. These standards are necessaryto ensure the continued independent design anddevelopment of both the equipment and the airframeinstallations.

41、Manufacturers should note that although this Characteristicdoes not preclude the use of standards different from thoseset forth herein, the practical problems of redesigning astandard airframe installation to accommodate a specialequipment could make the use of that equipmentprohibitively expensive

42、for the customer. They shouldrecognize, therefore, the practical advantages ofdeveloping equipment in accordance with the standards setforth in this document.2.2 Form FactorThe MCDU should be packaged as a standard dzus-mounted control panel 9“ high by 5.75“ wide. The depthbehind the panel should no

43、t exceed 10.5“, excluding theconnector. A connector type MS 24264R 20 B 41PN-1should be used having pin assignments as shown inAttachment 1. As an option for navigation and displaycontrol functions, a second connector specified as MS24266R 20 B 41P6 should be used. See Section 4.3.2.COMMENTARYThese

44、characteristics reflect current availabletechnology. Cost, weight, and electrical powerconsumption reduction may be achieved bydeveloping a smaller and simpler MCDU. Use of flatscreen technology will undoubtedly allow design ofsmaller units. Thus, equipment manufacturers mayoffer MCDUs of less than

45、9“ panel height and 10.5“panel depth. It is desirable that a “step“ to a smallerMCDU would also be addressed in this Characteristicfor the purpose of standardization. Manufacturersdesiring to build a smaller MCDU should informARINC in order that the industry can respond tomake known their desires fo

46、r a new form factordefinition.2.3 Environmental ConditionsThe MCDU should be specified environmentally in termsof the requirements of RTCA Document DO-160B,“Environmental Conditions and Test Procedures forAirborne Equipment“. Attachment 5 to this Characteristictabulates the relevant environmental ca

47、tegories.2.4 InterwiringThe standard interwiring for the MCDU is set forth inAttachment 1 to this Characteristic. This interwiring isdesigned to provide the degree of interchangeabilityspecified in Section 1.4. The equipment manufacturer iscautioned not to rely upon special wires, cabling orshieldin

48、g for use with his particular units because theywill not exist in the standard installation.COMMENTARYWhy Standardize Interwiring?The standardized interwiring is perhaps the heart ofall ARINC Characteristics. It is this feature whichallows the airline customer to complete hisnegotiation with the air

49、frame manufacturer so that thelatter can proceed with installation engineering andinitial fabrication prior to airline commitment on aspecial source of equipment. This provides theequipment manufacturer with many valuable monthsin which to put final “polish“ on his equipment indevelopment.The readers attention is directed to the interwiringguidance in ARINC Report 414, Section 5.0. Thismaterial defines all of the basic standards utilized inthe airframe wiring installations, and all equipmentmanufacturers should make themselves familiar withit.2.5 Thermal Interface and DesignThe internal