1、ELECTRONIC CHRONOMETER- SY-STEM. ARINC CHARACTERISTIC 585-2 PUBLISHED: APRIL 28, 1978 ARINC 585-2 78 O307637 0003099 9 REPLACEMENT PAGE REVISED: December 30, 1977 AERONAUTICAL RADIO, INC. Annapol is , Mary1 and 21401 -_ 2551 Riva Raad - - ARINC Characteristic No. 585-2 ELECTRONIC CHRONOMETER SYSTEM
2、ARINC Characteristic 585-2 was first published on April 28, 1978 .- Prepared by Ai rl i nec Electronic Engi neering Committee Characteristic 585 Approved by the Ai rl ines Electronic Engineering Commi ttee: Mav 18. 1972 Characteristic 585 Approkd by the Air Lines Communications Administrative Charac
3、teristic 585-1 Approved by the Airlines Electronic Engineering Comi ttee Council for Member Airlines on May 24, 1972 on May 22, 1975 FOREWORD Activities of AERONAUTICAL RADIO, INC. (ARINC) and the Purpose of ARINC Characteristics Aeronautical Radio, Inc., is a corporation in which the United States
4、scheduled airlines are the principal stockholders. Other stockholders include a variety of other air transport companies, aircraft manufacturers and foreign flag airlines. Activities of ARINC include the operation of an extensive system of domestic and overseas aeronautical land radio stations, the
5、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 A
6、irlines 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 i
7、s finalized after investigation and coordi- nation 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 Char- acteristic
8、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 endorsem
9、ent of any manufacturers product designed or built to meet the Characteristic. An ARINC Characteristic has a twofold purpose, which is: (1) To indicate to the prospective manufacturers of airline electronic equipment the considered opinion of the airline technical people, coordinated on an industry
10、basis, concerning requisites of new equipment, and (2) To channel new equipment designs in a direction which can result in the maximum possible standardization of those physical and electrical charac- teristics which influence interchangeability of equipment without seriously hampering engineering i
11、nitiative. ii ARINC 585-2 78 O307637 0003L03 3 REPLACEMENT PAGE -REVISED: June 15, 1975 ITEM 1 .o - 1.1 1.2 1.3 1.4 1.4.1 1.4.2 1.5 1.5.1 1.5.2 1.6 2.0 2.1 2.1.1 2.1.2 2.1.1.1 2.2 2;3 2.4 3.0 3.1 3.2 3.3 3.4 3.4.1 3.4.2 3.5 3.5.1 i 3.5.2 3.6 3.7 3.8 3.9 3.10 3.10.1 3.10.2 4.0 4.1 4.2 Attachments 5 A
12、RINC CHARACTERISTIC585 TABLE OF CONTENTS SUBJECT - INTRODUCTION -AND DESCRIPTION Purpose of this Characteri s ti c Function of the Equipment Re1 i abi 1 i ty Unit Descri pti on Time Base Unit Time Display Unit Interchangeability Requirements General Requirements for Interchangeability Interchangeabi
13、lity Requirements for the ARINC 585 Electronic Chronometer System Regu 1 atory Approval STANDARDS REQUIRED TO EFFECT INTERCHANGEABILITY Form Factors and Connectors Time Base Unit Form Factor Cool i ng Time Display Unit Form Factor Signal Characteri s ti cs Standard Interwi ring Power Ci rcui try SYS
14、TEM DESIGN CONSIDERATIONS Time DisDlav Outout Uti1 i zation- Equipment Output Warning Devi ces Input Power Battery Bus Input System Power Input Instrument Power Power Source Brightness Control Instrument Lighting Power Manual Time Setting Chronograph Remote Switch Accuracy of the ECS Time Di spl ay
15、Uni t Setti ng Accuracies Chronograph Setting Accuracy Elapsed Time Setting Accuracy DIGITAL SIGNAL CHARACTERISTICS Time Display Interface Utilization Equipment Interface Environmental Test Categories Time Base Unit Connector Positioning Electronic Chronometer System Interwi ri ng Data Interface Blo
16、ck Diagram Figure 1 - Word/Frame Structure Figure 2 - Digital Data Standards _. b - - - iii - - PAGE 1 1 1 1 1 1 1 1 1 1 1 2 2 2 2 2 2-3 3 4 4 4 4 4 4 4 4 4 4 4 4 4 5 5 5 5 6 6 6 7 8 9 10 11 11 ARINC 585-2 78 m O307637 0003102 5 m THIS PAGE INTENTIONALLY LEFT BLANK - ARINC 585-2 78 0307bL 0003103 7
17、M 1.1 Purpose of this Characteristic Page 1 ARINC CHARACTERISTIC 585 1 .O INTRODUCTION AND ESCRIPTION This document is intended to set forth the basic re- qui rements for an Electronic Chronometer System specifically designed for installation in all types of comnerci al transport aircraft. The inten
18、t of this document is to provide general and specific design guidance for the development and i ns tal 1 ati on of an El ectroni c Chronometer pri - marily for airline use. include the speci fi c requirements necessary to pro- vide the desired operational capability and the standards necessary to ac
19、hieve i nterchangeabi 1 i ty. Equipment manufacturers should note that this docu- ment aims to encourage them to produce maintenance- free, high performance devi ces rather than equipment of minimal weight and dimensions. They are at lib- erty to accomplish this objective by means of design techniqu
20、es they consider to be the most appropriate, as their airline customers are interested primarily in the end result rather than the means employed to achieve it. 1.2 Function of the Equipment The function of the Electronic chronometer System is to provide time-of-day (GMT) indication to the flight cr
21、ew, as well as providing this data in digital form for use by other avionic systems. In addition, the Electronic Chronometer System should provide a digital Elapsed Time Indicator (hours and minutes) with a start/stop/reset function and a chronograph function (minutes and seconds) also with a start/
22、 stopIreset function. 1.3 Reliability The operational use of this system demands the ut- most attention to the need for reliability of the El ectroni c Chronometer System. included in aircraft minimum equipment lists, the importance of equipment re1 i abi 1 i ty cannot be over- emphasized. 1.4 Unit
23、Description As such, this guidance will Since clocks are 1.4.1 Time Base Unit (TBU) The Time Base Unit houses the necessary components and electronic circuitry needed to provide digitally coded output signals representing time. other time is provided depending on the setting by the operator.) This u
24、nit accepts external comnands required for setting of the internal time base and provi des txro independent buffered digital outputs. In addition, the Time Base Unit provides a source of power for external display units. (GMT or 1.4.2 Time Display Unit (TDU) The Time Display Unit contains the displa
25、y ele- ments and provides the controls necessary for re- setting the Time Base Unit. elapsed time (hours, minutes) .- control is leca3ed- on In addition, the , the TDU as is the chronograph (minutes, seconds) control. Provision for remote control of the chrono- graph (start/stop/reset) by externally
26、-mounted mo- mentary push-button, switch, or other optional means is -also to be provided. 1.5 Interchangeability Requirements 1.5.1 General Requirements for Interchangeability One of the primary functions of an ARINC Equipment Characteristic is to designate, in addition to cer- tain performance par
27、ameters, the interchangeability required of aircraft equipment produced by various manufacturers. Manufacturers are referred to Sec- tion 1.6 of ARINC Report No, 414 for the airline industrys defi ni tions of Terms and General Re- quirements for interchangeability. As explained in that Report, the d
28、egree of interchangeability considered necessary and attainable for each par- ticular equipment is specified in the pertinent ARINC Equipment Characteri sti c. Furthermore, “Generation Interchangeabil i ty“ is stated as a requirement by the airline industry. Generation Interchangeability“ assures th
29、at fu- ture evolutionary equipment improvements and the inclusion of additional functions in new equip- ments during the next few years do not violate the interwiring and form factor standards set forth in this Document. The provisions to assure “Generation Interchangeability“ are set forth as can b
30、est be predicted in various places through- out this Document to guide manufacturers in fu- ture developments. 1.5.2 Interchangeability ReqUirements for the ARINC 585 Electronic Chronometer System Unit interchangeability is required for the Time Base Unit and the Time Display Unit (Indicator). regar
31、dless of the manufacturing source of the individual items. 1 ,6 Regul a tory Approval The ECS should meet all applicable FCC and FAA re- quirements. Manufacturers should obtain all neces- sary information on these requirements from the FCC and the FAA as they are not stated in this Charac- teristic
32、nor are they available from ARINC. The en- vironmental test categories to which the equipment should be declared may be found in Attachment 1. t- e- Page 2 ARINC CHARACTERISTIC 585 2.0 STANDARDS REQUIRED TOI EFFECT INTERCHANGEABILITY It is of prime importance that the Industry estab- lish specific f
33、orm factors, mounting provisions, in- terwiring, input and output interfaces and power 6 supply requirements for the Electronic Chronometer System. These standards are necessary to ensure the continued independent design and development of both the equipment and the airframe installation. It should
34、be noted that although this ARINC Charac- teristic does not preclude the use of different form factors and i nterwi ring 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 des
35、ign prohibitively expensive for the customer, Thus, manufacturers should recognize the practical advantages of deve1 opi ng equipment in accordance with the form factor, interwiring and input and output interface standards of this Characteristic. 2.1 Form Factors and Connectors . 2.1.1 Time Base Uni
36、t Form Factor The Time Base Unit should be contained in a short 1/4 ATR case (See ARINC Specification 404 for case dimensions.) The rear connector should be a single shell connector mounted coding pins up on the ver- tical center line of the unit as defined in ARINC Specification 404. The unit conne
37、ctor should be MIL-C-81659 number M81659/31 A2-0025 with index code 70. This corresponds to ITT Cannon part num- ber DPXB-57-34P-O070 and/or AFIP part nuniber The mating aircraft rack connector should be MIL-C-81659 number M81659/29A2-0026 wi th index code 70. It should be noted that all 57 pins are
38、 not re- quired. need be actually provided. This 57 pin insert was selected because of the avai 1 abi li ty of i ndi vi dual - ly inserted “poke home“ pins and contacts which can be assenbled leaving the unused spaces in the con- nector for future spares. An outline control drawing showing the posit
39、ion of the connector may be found in Attachment 2. Connector pin assignments are set forth in Attach- ment 3. - The Time Base Unit should conform to all the speci- fi c requirements of dimensi on tolerances, hol d-downs , projections, handless extractors and specified limits on weight and center of
40、gravity as set forth in ARINC Specification 404. Hold-down on the box should be Type “A“. See Section 30.4 of ARINC Report No. 414 for further details on shock mountings and equip- ment racki ng to1 erances , COMMENTARY RM1 R57P-0070, Only the pins called out on the interwiring . . -Manufacturers sh
41、ould take note of the desire of . other airlines who desre high reliability and believe that a larger box with attendant lower power density (and therefore temperature) is - one way to achieve it. 2.1.1.1 Cooling The thermal design of the Time Base Unit should be such that forced air cooling is not
42、required, Un- wanted heat generated in the equipment should be conducted to the outer surfaces of the case, from where it may be rkmoved by convection-and radiation. Provisions for ARINC forced air cooling will NOT form part of the standard AIRNC 585 installation on the ai rframe. To enable other me
43、thods of cooling to be employed, however, the bottom surface of the case should be drilled in accordance with the requirements of ARINC Specification 404. Also, holes should be provided in the upper part of each side panel. (The top cur- face, however, should not be drilled.) Either cool- ing augmen
44、tation in the standard installation, by the passage of convection air through the box, or full forced air cooling may then be employed by an i ndi vi dual user, as he wi s hes, Equipment desi gners my not interpret this as a license to ignore the “standard“ requirement stated above. Devi ations from
45、 this “standard“ will be made at the option of the user only. 2.1.2 Time Display Unit Form Factor The TDU should be contained in a 3ATI case of no more than 5 inch depth behind the panel (not in- cluding connector), An alternate TDU utilizing a 2ATI case with a 5 inch depth is also recognized by thi
46、s characteristic as a users option. See ARINC Specification 408 for these indicator case dimen- sions. The TDU should employ an MS 3122E16-26P connector mounted in accordance with ARINC 408, 2.2 Signal Characteristics The signal characteristics required to insure inter- changeability is set forth in
47、 Section 4 Standard Signal Characteristics. 2.3 Standard Interyiring The interwiring which should be used in the “Stand- ard Installation“ is set forth in Attachment 3. COMMENTARY Why 5tandardi ie Interwi ri ng? The standardi zed i nterwiri ng is perhaps the heart of al 1 ARINC Characteri stics. It
48、is this feature which allows the airline customer to comt)lete his neaotiation with the It should be noted that some airlines wanted to include an option to provide a krarf 1/4 ATR in the characteristic. This request was dropped when it was pointed out that the present 1/4 ATP height dimension is sp
49、ecified as a maximum and therefore a lower height box is not precluded. airframe manufacturer so that the latter can proceed with the engineering and initial fabricatlon stages prior to airline camnit- ment 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. ARINC 585-2 78 - O307637 0003305 O -1 I ARINC CHARACTERISTIC 585 2.0 STANDARDS REQUIRED TO EFFECT INTERCHANGEABILITY 2.3 Standard Interwiring (Contd) The readers attention is directed to the interwiring
