SAE AS 5498-2001 Minimum Operational Performance Specification for Inflight Icing Detection Systems《飞行中冰检测系统的最低操作性能规范》.pdf

1、400 Commonwealth Drive, Warrendale, PA 15096-0001AEROSPACE STANDARDAS5498Issued 2001-10Minimum Operational Performance Specification for Inflight Icing Detection SystemsFOREWORD1. The development of these guidelines was jointly accomplished by EUROCAE Working Group 54 and the Society of Automotive E

2、ngineers (SAE) AC-9C through a consensus process. It was accepted by the Council of EUROCAE on June 2001 and SAE on September 2001.2. SAE, Inc. and EUROCAE are, respectively, US and international not-for-profit making organizations, formed to advance the art and science of aviation and aviation elec

3、tronic systems for the benefit of the public.3. Since SAE or EUROCAE are not official agencies of any US or European government, their recommendations may not be regarded as statements of official government policy unless so enunciated by the appropriate government organization, conference of govern

4、ments, or agency having statutory jurisdiction over any matters to which the recommendations relate.Reaffirmed 2009-12SAE Technical Standards Board Rules provide that: “This report is published by SAE to advance the state of technical and engineering sciences. The use of this report is entirely volu

5、ntary, and its applicability and suitability for any particular use, including any patent infringement arising therefrom, is the sole responsibility of the user.” SAE reviews each technical report at least every five years at which time it may be reaffirmed, revised, or cancelled. SAE invites your w

6、ritten comments and suggestions. Copyright 2009 SAE International All rights reserved. No part of this publication may be reproduced, stored in a retrieval system or transmitted, in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without the prior written per

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8、echnical/standards/AS5498Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SAE AS5498 - 2 -TABLE OF CONTENTSCHAPTER 11. SCOPE .51.1 Purpose and Scope .51.2 Applications51.3 Functionality and Descriptio

9、n of System61.4 System Classification.71.4.1 Classification By Use .71.4.2 Classification By Sensing Method71.5 Definitions and Abbreviations.81.6 References.111.6.1 Reference Documents .111.6.2 Applicable Documents .11CHAPTER 22. GENERAL DESIGN REQUIREMENTS132.1 Design Requirements.132.1.1 Airworth

10、iness And Certification 132.1.2 Controls132.1.3 Effects Of Tests 132.1.4 Software Management.132.1.5 Operational Minimum Requirements132.1.6 Minimum Structural Considerations .142.1.7 Additional Design Criteria.142.2 Reporting Requirements 152.2.1 Summary Report162.2.2 Substantiating Test Data/Analy

11、sis162.3 Other Requirements.172.3.1 Qualification Testing Responsibility172.3.2 Test Samples .17CHAPTER 33. MINIMUM OPERATIONAL PERFORMANCE SPECIFICATION UNDER STANDARDCONDITIONS .183.1 Overview 183.2 Functional Minimum Requirements183.2.1 FIDS That Detect Ice Accretion183.2.2 FIDS That Detect Icing

12、 Conditions.19Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SAE AS5498 - 3 -TABLE OF CONTENTS (Continued)CHAPTER 44. MINIMUM PERFORMANCE SPECIFICATION UNDER ENVIRONMENTAL CONDITIONS .204.1 Introduc

13、tion 204.2 Testing204.3 Fluids Susceptibility (EUROCAE ED-14D/RTCA DO-160D, Section 11).204.3.1 Test Applicability 204.3.2 Fluids To Be Tested234.4 Hail Strike.23CHAPTER 55. TEST PROCEDURES 245.1 General 245.1.1 Reports i.e., compliance with the particular procedure or specification is mandatory and

14、 no alternative may be applied.b. “Should”: The use of the word “Should” (and phrases such as “It is recommended that.”, etc.) indicates that although the procedure or criterion is regarded as the preferred option, alternative procedures, specifications or criteria may be applied, provided that the

15、manufacturer, installer or tester can provide information or data to adequately support and justify the alternative.1.3 Functionality and Description of System:Icing instrumentation systems provide information to the flight crew and/or airplane systems concerning inflight icing. Components of the sy

16、stem may be intrusive or non-intrusive to the airflow. The system may be directly or indirectly sensitive to the physical phenomena of inflight icing. Some possible icing instrumentation technologies include: latent heat of fusion, changes in the natural frequency of vibrating components, visual cue

17、s, ultrasonic waves, optical methods such as IR cameras, the friction between a rotating cylinder and scraper, etc. Icing instrumentation systems are divided into two types: FIDS and Aerodynamic Performance Monitoring Systems (APMS). FIDS are further divided into those that detect ice accretion and

18、those that detect icing conditions.A FIDS that detects ice accretion informs the flight crew and/or systems about the presence of ice accretions on reference airplane surfaces. FIDS that detect ice accretion may also inform the crew or a system about ice thickness, ice accretion rate, liquid water c

19、ontent, cloud droplet size, and/or accretion location. This MOPS only defines testing for ice detection, ice thickness, ice accretion rate, and liquid water content. FIDS that detect ice accretion may be located on or remote from the monitored airplane surfaces.A FIDS that detects icing conditions p

20、rovides information to the flight crew and/or airplane systems concerning atmospheric icing conditions. The output of a FIDS that detects icing conditions informs the flight crew and/or airplane systems about the presence of atmospheric conditions that are conducive to the accretion of ice on airpla

21、ne surfaces. A FIDS that detects icing conditions is not necessarily sensitive to the presence of ice accretions.A FIDS may include a processing unit to perform signal processing, sensor monitoring, data communication or other functions. The processing unit may either be integrated with or separate

22、from the sensor(s). A FIDS may be connected to a device to provide information to the cockpit crew. The FIDS may communicate with other onboard equipment or systems.Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license

23、 from IHS-,-,-SAE AS5498 - 7 -1.3 (Continued):An Aerodynamic Performance Monitoring System (APMS) informs the flight crew and/or airplane systems about aerodynamic performance degradation, which may be due to ice accretions, over monitored surfaces. This aerodynamic performance degradation may resul

24、t in degraded airplane performance and handling qualities. An APMS is not directly sensitive to ice accretions. These systems are not considered in this specification.1.4 System Classification:1.4.1 Classification By Use: This MOPS will consider two classes of Flight Icing Detection Systems (FIDS) t

25、hat detect ice accretion or icing conditions: ADVISORY systems and PRIMARY systems.An ADVISORY FIDS annunciates the presence of ice accretion or icing conditions. The cockpit crew is responsible for monitoring the icing as defined in the Airplane Flight Manual (AFM). Typical methods include monitori

26、ng: total air temperature visible moisture criteria visible ice accretion specific airframe ice accretion thicknessFIDSActivation by the cockpit crew of the anti-icing or deicing system(s) remains a requirement. The ADVISORY FIDS provides information to advise the cockpit crew of the presence of ice

27、 accretion or icing conditions, but it can only be used in conjunction with other means to determine the need or timing of anti-icing or deicing system activation.A PRIMARY FIDS annunciates the presence of ice accretion or icing conditions and may also provide information to other airplane systems.

28、The PRIMARY FIDS can further be classified as PRIMARY automatic or PRIMARY manual. In a PRIMARY automatic system, the FIDS automatically activates anti-icing or deicing systems. In a PRIMARY manual system, the cockpit crew activates the ice protection systems based on the FIDS annunciation.1.4.2 Cla

29、ssification By Sensing Method: Flight Icing Detection Systems that detect ice accretion and are covered by this document include the following classes: FIDS that make a measurement on a reference surface correlated to ice accumulation on a monitored surface (i.e., probe type sensors) FIDS that make

30、a direct measurement on a reference surface which is part of a monitored surface (i.e., flush mounted sensors) FIDS that make a remote measurement on a reference surface which is part of a monitored surface (i.e., optical camera methods)In addition, this document includes FIDS that detect icing cond

31、itions. This document considers all FIDS that detect icing conditions as a single class.Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SAE AS5498 - 8 -1.5 Definitions and Abbreviations:TABLE 1 - Def

32、initionsCopyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SAE AS5498 - 9 -TABLE 1 - Definitions (Continued)Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproductio

33、n or networking permitted without license from IHS-,-,-SAE AS5498 - 10 -TABLE 2 - AbbreviationsCopyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SAE AS5498 - 11 -1.6 References:NOTE: Title 14 of the US

34、 Code of Federal Regulations (14 CFR), Federal Aviation Regulation (FAR) Part XX documents are referred to as “FAR XX” in the body of this document.1.6.1 Reference Documents: The following documents are incorporated by reference:EUROCAE ED-14D - Environmental Conditions and Test Procedures for Airbo

35、rne EquipmentRTCA DO-160D - Environmental Conditions and Test Procedures for Airborne EquipmentEUROCAE ED-12B - Software Considerations in Airborne Systems and Equipment CertificationRTCA DO-178B - Software Considerations in Airborne Systems and Equipment CertificationJAR 23 First Issue - Normal, Ut

36、ility, Aerobatic and Commuter Category AeroplanesJAR 25 Change 14 - Large Aeroplanes14 CFR Part 23 Amendment 23-53 (FAR 23) - Airworthiness Standards: Normal, Utility, Acrobatic, and Commuter Category Airplanes14 CFR Part 25 Amendment 25-98 (FAR 25) - Airworthiness Standards: Transport Category Airp

37、lanes14 CFR Part 21 Amendment 21-76 (FAR 21) - Certification Procedures for Products and Parts1.6.2 Applicable Documents:EUROCAE ED-79/SAE ARP4754 - Certification Considerations for Highly-Integrated or Complex Aircraft Systems - November 1996EUROCAE ED-104 - Minimum Operational Performance Specific

38、ation for Ground Ice Detection SystemsSAE ARP4761 - Guidelines and Methods for Conducting the Safety Assessment Process on Civil Airborne Systems and Equipment - December 1996JSSG-2010-5 Joint Service Specification Guide - Crew Systems Aircraft Lighting Handbook - October 30, 1998SAE AIR4367 - Aircr

39、aft Ice Detectors and Icing Rate Measuring InstrumentsCopyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SAE AS5498 - 12 -1.6.2 (Continued):SAE ARP4256 - Design Objectives for Liquid Crystal Displays fo

40、r Part 25 (Transport) - December 1996MIL-STD-1472E - Human EngineeringSAE AS8034 - Minimum Performance Standard for Airborne Multipurpose Electronic Displays - Reaffirmed May 1993FAA Aircraft Icing Handbook DOT/FAA/CT-88/8-1 - Updated Sept 93FAA AC 20.73 - Advisory Circular - Aircraft Ice Protection

41、 - April 21, 1971FAA AC 23.1419-2A - Certification of Part 23 Airplanes for Flight in Icing Conditions - August 19, 1998FAA AC 25.1419-1 - Certification of Transport Category Airplanes for Flight in Icing ConditionsJAR-E - Engines14 CFR Part 33 Amendment 33-19 (FAR 33) - Airworthiness Standards: Air

42、craft Engines14 CFR Part 91 Amendment 91-258 (FAR 91) - General Operating and Flight Rules14 CFR Part 121 Amendment 121-271 (FAR 121) - Certification and Operations: Domestic, Flag, and Supplemental Air Carriers and Commercial Operators of Large Aircraft14 CFR Part 135 Amendment 135-75 (FAR 135) - A

43、ir Taxi Operators and Commercial OperatorsJAR/OPS 1 - Commercial Air Transportation (Aeroplanes)Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SAE AS5498 - 13 -CHAPTER 22. GENERAL DESIGN REQUIREMENT

44、S:2.1 Design Requirements:2.1.1 Airworthiness And Certification:The FIDS shall comply with any applicable airworthiness requirements, the scope of which should be defined in the airplane specification. The system may also be regulated by the airplane specification. In the event of conflict, airworth

45、iness requirements shall prevail. Regulatory bodies include the United States Federal Aviation Administration (FAA) and the European Joint Aviation Authorities (JAA). The FAA and the JAA regulate the design of airplanes with the following airworthiness standards: FAR/JAR 23 for normal, utility, acro

46、batic, and commuter category airplanes FAR/JAR 25 for transport category airplanesConsideration should also be given to operational regulations.2.1.2 Controls: The operation of FIDS controls intended for use during flight, in all possible positions, combinations and sequences, shall not result in a

47、condition, the presence or continuation of which would be detrimental to the continued performance of the system.2.1.3 Effects Of Tests: Unless otherwise stated, the design of the system shall be such that, during and after the application of operational tests, no condition exists which would be det

48、rimental to the subsequent performance of the equipment.2.1.4 Software Management: Software design shall follow the guidelines specified in document EUROCAE ED-12/RTCA DO-178 “Software Considerations in Airborne Systems and Equipment Certification.” The software criticality level will depend on the particular equipment function and application as defined by the airplane specification.2.1.5 Operational Minimum Requirements:2.1.5.1 Built-in Test Equipment (BITE): Any FIDS certificated as primary shall incorporate built-in test equipment (BITE) and annunciate detected ice detec