SAE AS 6296-2016 Electronic Flight Instrument System (EFIS) Displays.pdf

1、_ SAE Technical Standards Board RulHVSURYLGHWKDW7KLVUHSRUWLVSXEOLVKHGE6$(WRDGYDQFHWK HVWDWHRIWHFKQLFDODQGHQJLQHHULQJVFLHQFHV7KHXVHRIWKLV report is entirely voluntary, and its applicability and suitability for any particular use, including any patent infringement arisLQJWKHUHIURPLVWKHVROHUHVSRQVLELOL

2、WRIWKHXVHU SAE reviews each technical report at least every five years at which time it may be revised, reaffirmed, stabilized, or cancelled. SAE invites your written comments and suggestions. Copyright 2016 SAE International All rights reserved. No part of this publication may be reproduced, stored

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4、ail: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.org SAE values your input. To provide feedback on this Technical Report, please visit http:/www.sae.org/technical/standards/AS6296 AEROSPACE STANDARD AS6296 Issued 2016-03 Electronic Flight Instrument System (EFIS) Displays RATIONALE Histori

5、cally, FAA Technical Standard Orders (TSOs) and associated industry Minimum Operational Performance Specifications (MOPS) were developed to address sensor and indicator requirements for single functions, such as airspeed, altitude, or fuel flow. In contrast, modern Electronic Flight Instrument Syste

6、m (EFIS) displays normally present indications for multiple functions, but do not normally include the sensor. Until now, a MOPS did not exist to address the operational/functional requirements for such an EFIS display. Requirements for this type of EFIS typically consist of a few requirements for e

7、ach function, drawn from many TSOs and associated MOPS. As a result, TSO applications for EFIS displays have multiple deviations to many TSOs and may include incomplete TSO authorizations. This document is intended to facilitate EFIS TSO authorizations by addressing only the EFIS display requirement

8、s for a broad set of aircraft functions. This document provides criteria for EFIS displays that are intended for use in the flight deck by the flight crew in aircraft to include, but not limited to, Title 14 CFR Part 23, 25, 27, and 29. SAE INTERNATIONAL AS6296 Page 2 of 91 TABLE OF CONTENTS 1. SCOP

9、E 5 2. REFERENCES 6 2.1 Applicable Documents 6 2.1.1 SAE Publications . 6 2.1.2 Code of Federal Regulations (CFR) . 7 2.1.3 RTCA/EUROCAE Publications . 7 2.2 Related Informational Publications . 8 2.2.1 SAE Publications . 8 2.2.2 FAA Reference Documents 9 2.2.3 RTCA/EUROCAE Publications . 11 2.3 Def

10、initions . 11 3. GENERAL STANDARDS 11 3.1 Material 11 3.1.1 Workmanship 12 3.2 Compatibility of Components 12 3.3 Equipment Functions and Mechanical Operations . 12 3.4 Interchangeability 12 3.5 Operation and Accessibility of Controls 12 3.6 Self-Test Capability . 12 3.7 Effect of Tests . 12 3.8 Mal

11、functions and Failure Indications . 13 3.8.1 Malfunction Indication . 13 3.8.2 Power Failure Indication 13 3.8.3 Fail Safe Provision 13 3.9 Multiple Mode Indications 13 3.10 Source Selection . 13 3.11 Display. 13 3.11.1 Multi-Page Display Capability . 13 3.11.2 Discernibility 14 3.11.3 Critical Info

12、rmation 14 3.11.4 Information Limit Indication . 14 3.11.5 Scale Indications . 14 3.11.6 Ambiguity 14 3.11.7 Symbology 14 3.12 Display Latency . 14 3.13 Orientation . 15 3.14 Identification 15 3.14.1 Declaration of EFIS Functions 15 4. MINIMUM PERFORMANCE STANDARDS UNDER STANDARD CONDITIONS . 15 4.1

13、 Flight Instrument Functions . 16 4.1.1 Airspeed 16 4.1.2 Vertical Velocity (Rate of Climb) . 17 4.1.3 Altimeter 18 4.1.4 Attitude (Bank and Pitch) 21 4.1.5 Direction Indicator . 22 4.1.6 Maximum Allowable Airspeed . 23 4.1.7 Mach 23 4.1.8 Turn and Slip . 24 4.1.9 Airborne Low-Range Radio Altimeter

14、. 24 4.1.10 Automatic Flight Guidance and Control System . 25 4.2 Navigation and Communication Functions . 25 4.2.1 Very High Frequency Omnidirectional Range (VOR) . 25 4.2.2 Distance Measuring Equipment (DME) . 26 4.2.3 Localizer 27 4.2.4 Glideslope . 28 SAE INTERNATIONAL AS6296 Page 3 of 91 4.2.5

15、Marker Beacon 29 4.2.6 Automatic Direction Finding (ADF) . 29 4.2.7 Stand-Alone Airborne Navigation Equipment Using the Global Positioning System Augmented by the Satellite Based Augmentation System (GPS/SBAS) . 30 4.2.8 Flight Management System using Multi-sensor Inputs . 35 4.2.9 Microwave Landing

16、 System (MLS) . 41 4.2.10 VHF Radio . 42 4.2.11 HF Radio . 43 4.3 Engine and Fuel Management Functions . 44 4.3.1 Temperature 44 4.3.2 Fuel Flow . 44 4.3.3 Manifold Pressure . 45 4.3.4 Fuel, Oil, and Hydraulic Pressure . 46 4.3.5 Tachometer . 46 4.3.6 Fuel and Oil Quantity 46 4.4 Weather Surveillanc

17、e and Avoidance Functions 47 4.4.1 Windshear Warning and Escape Guidance 47 4.4.2 Weather and Ground Mapping Radar . 48 4.4.3 Airborne Passive Thunderstorm Detection . 51 4.4.4 Optional Display Equipment for Weather and Ground Mapping Radar Indicators . 52 4.5 Terrain Surveillance and Avoidance Func

18、tions 53 4.5.1 Terrain Awareness and Ground Proximity 53 4.5.2 Helicopter TAWS . 55 4.6 Traffic Surveillance and Avoidance Functions 56 4.6.1 Traffic Collision Avoidance System (TCAS I and II) . 56 4.6.2 Traffic Advisory System 61 5. MINIMUM PERFORMANCE STANDARDS UNDER ENVIRONMENTAL CONDITIONS 64 5.

19、1 Additional Functional Requirements under Environmental Conditions . 65 5.1.1 Airspeed Performance 65 5.1.2 Vertical Speed Performance . 65 5.1.3 Manifold Pressure Performance . 65 5.1.4 Tachometer Performance . 65 5.1.5 Automatic Flight Guidance and Control System . 65 6. GLOSSARY OF TERMS . 74 6.

20、1 Words and Phrases . 74 6.2 Abbreviations 75 7. NOTES 83 7.1 Revision Indicator 83 APPENDIX A DECLARATION OF EFIS DISPLAY FUNCTIONS . 84 APPENDIX B AIR SPEED SCALE ERROR PERFORMANCE OVER TEMPERATURE ENVIRONMENT . 91 Figure 1 Electronic Flight Instrument System (EFIS) functions covered by this MOPS

21、. 5 Figure 2 RA pitch cues on a PFD 60 Figure 3 Declaration of electronic flight instrument functions selected from AS6296 . 86 Figure 4 Example - Declaration of electronic flight instrument functions selected from AS6296 . 88 Figure 5 Declaration of electronic flight instrument error contribution .

22、 90 Table 1 Airspeed scale error system tolerance 17 Table 2 Vertical speed scale error tolerance . 18 Table 3 Cold temperature correction - altitude correction chart . 19 Table 4 Scale and hysteresis errors for increasing and decreasing altitude (at ambient room temperature) . 20 Table 5 Barometric

23、 setting mechanism 21 Table 6 Radio altitude scale error tolerance 25 Table 7 Standard SBAS function labels . 31 Table 8 Non-numeric display requirements . 32 Table 9 Non-numeric display requirements (modes) . 33 Table 10 MLS channels and frequencies . 42 SAE INTERNATIONAL AS6296 Page 4 of 91 Table

24、11 Frequency channel spacing and channel identification 43 Table 12 Classification by temperature accuracies . 44 Table 13 Standard set of visual and aural terrain alerts 54 Table 14 Displayed aircraft symbols (examples) . 61 Table 15 Performance required during environmental conditions . 66 Table 1

25、6 Performance required during environmental conditions . 69 Table 17 Performance required during environmental conditions . 72 Table B1 Air speed scale error performance over temperature environment 91 SAE INTERNATIONAL AS6296 Page 5 of 91 1. SCOPE This SAE Aerospace Standard (AS) specifies minimum

26、performance standards for Electronic Flight Information System (EFIS) displays that are head-down and intended for use in the flight deck by the flight crew in all 14 CFR Part 23, 25, 27, and 29 aircraft. This document is expected to be used by multiple regulatory agencies as the basic requirement f

27、or a technical standard order for EFIS displays. The requirements and recommendations in this document are intended to apply to, but are not limited to, the following types of display functions: x Primary Flight and Primary Navigation displays, including vertical situation and horizontal situation f

28、unctions. x Displays that provide flight crew alerts, which may include engine instrument, aircraft systems information/control. x Control displays including communication, navigation and system control displays. x Information displays, which may include navigation displays used for situation awaren

29、ess only, supplemental data, and maintenance and documentation displays. x Display Systems including a Display Unit (display) and a symbol generator. The display functions herein were based on the display aspects of functions covered by previous TSOs that included an end-to-end system, including sen

30、sors. This document does not address video display terminals or video monitors without the means to generate symbols. The symbol generating function may be contained within the display or may be external to the display unit and part of the display system. This document is not intended to address the

31、 display of single function equipment (e.g., airspeed). Two functions are required as a minimum. This document does not address the sensors or computational engines (e.g., TAWs computer, navigation computer, or TCAS processor) that transmit their data to the EFIS display. EFIS Display This EFIS Disp

32、lay MOPS Original End-to-end System MOPS from which this MOPS was derived. Figure 1 - Electronic Flight Instrument System (EFIS) functions covered by this MOPS Displays Processing Controls Sensors SAE INTERNATIONAL AS6296 Page 6 of 91 Functions that are not covered in this document include: Overspee

33、d Warning; Air Traffic Control Radar Beacon System (ATCRBS)/Mode Select (Mode S); Automatic Dependent Surveillance - Broadcast (ADS-B); Traffic Information System - Broadcast (TIS-B); Electronic Map Display; Synthetic Vision; Enhanced Vision; Head-Up Displays (HUD); and Head Worn Displays (HWD). Thi

34、s document does address the following types of control functions: x Control functions related to the data presented on the EFIS display(s). x Control means that are integrated into the displays. NOTE: This document is expected to be used for a technical standard order for EFIS displays. This documen

35、t does not address the hardware, physical, or optical (ocular) requirements of the EFIS displays. Those requirements are addressed in AS8034B. This document is subject to change to keep pace with experience and technical advances. Many functions often included in an EFIS in existing systems were con

36、sidered for this MOPS. In general, the functions that were not included here were excluded because it was too complicated to extract and separate the display requirements from the sensor requirements. In other cases, the display requirements in the original MOPS were too extensive to add to this doc

37、ument without essentially replicating the original MOPS. Applicants will need to apply separately for approval for those functions. 2. REFERENCES The documents listed in 2.1 are those referenced within various parts of this document as guidance or direction. The documents listed in 2.2 are provided

38、for informational purposes only and do not form a part of the requirements of this document. 2.1 Applicable Documents The following publications form a part of this document only to the extent that they are explicitly invoked by the requirements within this Aerospace Standard (AS). The latest issue

39、of all SAE International publications shall apply except in cases where referring documents call out specific versions. In the event of conflict between these documents and this standard, the contents of this standard shall govern. 2.1.1 SAE Publications Available from SAE International, 400 Commonw

40、ealth Drive, Warrendale, PA 15096-0001, Tel: 877-606-7323 (inside USA and Canada) or +1 724-776-4970 (outside USA), www.sae.org. AIR1093 Numeral, Letter and Symbol Dimensions for Aircraft Instrument Displays ARP4102/7 Electronic Displays ARP4761 Guidelines and Methods for Conducting the Safety Asses

41、sment Process on Civil Airborne Systems and Equipment ARP5289 Electronic Aeronautical Symbols ARP5621 Electronic Display of Aeronautical Information (Charts) AS8034B Minimum Performance Standard for Airborne Multipurpose Electronic Displays SAE INTERNATIONAL AS6296 Page 7 of 91 2.1.2 Code of Federal

42、 Regulations (CFR) Copies of 14 CFR parts 21 and 45 are available from the Superintendent of Documents, U.S. Government Printing Office (GPO), P.O. Box 979050, St. Louis, MO 63197, Tel: (202) 512-1800, fax (202) 512-2250. You can also order copies online DWZZZDFFHVVJSRJRY6HOHFW$FFHVVWKHQ2QOLQH%RRNVW

43、RUH6HOHFW$YLDWLRQWKHQDFURVVWKHGLVSODDUHHDPSOHVRIDQDFFHSWDEOHPHDQVRILQG LFDWLQJIDLOXUH 3.8.2 Power Failure Indication Means shall be provided to indicate when electrical power (voltage and/or current of all required phases) is not sufficient for proper operation of display and/or display system. A bl

44、ank display is an example of an acceptable means of indicating failure. 3.8.3 Fail Safe Provision No single failure or malfunction of the display system shall introduce unsafe conditions to interconnected equipment. Unsafe conditions of the display system results from failures, malfunctions, externa

45、l events, errors, or combinations thereof. A Failure Modes and Effects Analysis (FMEA) should be performed to identify, isolate, and mitigate individual failures of the display. This is needed for a System Safety Assessment (SSA) for an aircraft airworthiness determination. ARP4761 Table 1 shows the

46、 failure condition severity as related to probability objectives and assurance levels for components and systems in aircraft. 3.9 Multiple Mode Indications When a display and/or display system has more than one mode, each mode of operation shall be indicated on the display, including any armed modes

47、, transitions, and reversions. Selector switch position is not an acceptable means of indication. One example of an acceptable exception is the depiction of the Horizontal Situation Indicator (HSI)-Full Compass versus Arc mode, which does not require a mode indication. NOTE: For the purposes of this document, a mode is not a function. Examples of modes on a display include heading-up versus track up (i.e., flight path is on top) or north up (magnetic north is shown on top). A mode could also be an alternate display format, such as a normal or primary mode versus a reversionary mode. 3.1