SAE AIR 5924A-2013 Guidelines for the Integration of Electronic Engine Control Systems for Transport Category (Part 25) and General Aviation (Part 23) Aircraft《带运输种类(第25部分)和通用航空(第2.pdf

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1、_ SAE 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 voluntary, and its applicability and suitability for any particular use, including any patent infringement arising there

2、from, is the sole responsibility of the user.” 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 2013 SAE International All rights reserved. No part of this p

3、ublication 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 permission of SAE. TO PLACE A DOCUMENT ORDER: Tel: 877-606-7323 (inside USA and Canada) Tel: +1 724-776-497

4、0 (outside USA) Fax: 724-776-0790 Email: 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/AIR5924A AEROSPACE INFORMATION REPORT AIR5924 REV. A Issued 2004-02 Revised 2013-

5、01 Superseding AIR5924 Guidelines for the Integration of Electronic Engine Control Systems for Transport Category (Part 25) and General Aviation (Part 23) Aircraft RATIONALE As part of the 5-year review process, this revision adds information on the integration of FADEC systems in general aviation (

6、GA) aircraft. It also adds additional information on FADEC control system integration in Transport category aircraft INTRODUCTION Modern digital electronic engine controls are capable of a much higher level of functional integration with aircraft systems than was possible with their primarily hydrom

7、echanical predecessors, and system designers have taken advantage of this increased capability. Electronic systems also result in a greater degree of physical integration with the aircraft, with increased dependence on aircraft wiring, remote (from the engine) mounted sensors and transducers and eve

8、n control units located within the aircraft. While this is a major impetus for the publication of this report, the report also addresses many issues that apply to hydromechanical controls. This report captures many years of hands-on experience in solving problems arising from powerplant control inte

9、gration and provides a valuable source of lessons-learned from those endeavors. SAE AIR5924A Page 2 of 81 TABLE OF CONTENTS 1. SCOPE 5 1.1 Purpose . 5 1.2 Summary of Revision A 5 1.3 Field of Application 5 2. REFERENCES 8 2.1 Applicable Documents 8 2.1.1 Federal Aviation Administration (FAA) Publica

10、tions . 8 2.1.2 European Aviation Safety Agency 9 2.1.3 Other Documents 9 2.2 Acronyms and Symbols 9 3. APPLICABILITY 10 4. THRUST AND POWER CONTROL . 10 4.1 Control Modes . 10 4.1.1 Primary (or Rating) Mode - Steady State Control Functions 10 4.1.2 Backup, Alternate, or Reversionary Mode - Steady S

11、tate Control Functions . 12 4.1.3 Controller Operation during Engine Transients 12 4.1.4 Use of a Soft Reversionary Mode . 13 4.1.5 Primary or Backup Mode Activation and Switching Between Modes . 14 4.1.6 Initiation of the Primary/Backup Mode at Engine Start . 16 4.2 Thrust Scheduling Logic . 17 4.2

12、.1 Primary Mode 17 4.2.2 Engine Ratings and Thrust Lapse Rates in the Backup (or Alternate) Mode . 39 4.2.3 Automatic Shutdown or Low Thrust/Power Modes . 40 4.3 Auxiliary Functions 41 5. USE OF SENSORS, AIRCRAFT SIGNALS, AND DATA . 41 5.1 Engine Control System Signals and the Use of Aircraft Signal

13、s 41 5.2 Signals Dedicated to an Individual Engine . 41 5.2.1 Thrust Lever Signals and Thrust Reverser Position Signals 42 5.2.2 Engine Sensors and Probes for A/C Environmental Data (see 5.4.2) 42 5.2.3 Cowl and Wing Anti-Ice Signals/Sources . 42 5.2.4 Air/Ground Signals 43 5.2.5 Other Dedicated Sig

14、nals . 43 5.2.6 A Potential Difficulty with Aircraft Discrete Data Words 43 5.3 Aircraft Signals Common to Multiple Engines . 44 5.3.1 Aircraft Air Data Output Signals 44 5.3.2 Other Aircraft Signals 45 5.4 Environmental Air Data Sensor Considerations . 45 5.4.1 Aircraft Probes and Sensors . 45 5.4.

15、2 Engine Sensor and Probe Configurations (For Determining Aircraft Air Data) 50 5.5 FADEC System Air Data Selection Logic . 54 5.5.1 Ambient Pressure Selection Logic 55 5.5.2 Total Temperature Selection Logic . 58 5.5.3 Total Pressure Selection Logic . 60 5.5.4 Airspeed and Mach Number Selection Log

16、ic 60 5.6 Thrust Management Computer (TMC) Selection of TAT 61 6. INSTRUMENTATION AND FLIGHT-CREW INTERFACES . 61 6.1 Aircraft Located Engine Displays and Switches . 61 6.1.1 Thrust Setting Parameter Display - Primary Mode of Operation 62 6.1.2 Thrust Setting Parameter Display - Backup Mode of Opera

17、tion. 64 6.1.3 Primary Mode Fail and Backup Mode Active Indications, and Backup Mode Command Switches . 65 6.2 Display of Information Concerning FADEC System Faults and Dispatch 65 SAE AIR5924A Page 3 of 81 7. MAINTENANCE CONSIDERATIONS 69 7.1 Approaches for Implementing Dispatch of FADEC Systems in

18、 Non-Full-Up Configurations . 69 7.2 The Use of a CMC and Display of Information Concerning FADEC System Dispatchability . 70 8. HARDWARE AND ENVIRONMENTAL ISSUES 72 8.1 Signals Dedicated to a Given Engine Control . 72 8.1.1 Thrust Lever Position Transducer . 72 8.1.2 Channel Reset Signals . 74 8.2

19、Signals and Wiring from a Common or Potentially Common Source . 76 8.2.1 Wiring in General 76 8.2.2 Common Wiring 76 8.2.3 Common Signals . 76 8.3 FADEC System Power Supply Considerations 77 8.3.1 Come-Alive Speed 77 8.3.2 Power Source Management . 78 8.3.3 Interrupt Support . 78 8.4 Backup Power Co

20、nsiderations 78 8.4.1 The Use of Aircraft Power as a Backup Electrical Power Source 78 8.4.2 Threshold for FADEC System Operation on its Dedicated Power Source . 79 8.5 HIRF and Lightning Considerations 80 8.5.1 HIRF Protection . 80 8.5.2 Lightning Protection 80 8.5.3 Continued Airworthiness of the

21、FADEC System with regard to HIRF/Lightning/EMI . 81 9. CERTIFICATION . 81 10. NOTES 81 FIGURE 1 STATION DEFINITIONS USED HEREIN . 6 FIGURE 2 TYPICAL FADEC SYSTEM 7 FIGURE 3 EXAMPLE OF THRUST VERSUS THRUST LEVER ANGLE 11 FIGURE 4 NORMAL MODE THRUST SCHEDULE AS COMPARED WITH TYPICAL ALTERNATE (OR BACK

22、UP) MODE SCHEDULE FOR FORWARD THRUST 14 FIGURE 5 LOGIC FOR MODE SELECTION . 15 FIGURE 6 TYPICAL ALTITUDE DEPENDENT FAN SPEED VERSUS THROTTLE LEVER ANGLE (NEED TO SHOW THE DOTTED LINES FOR THE CRUISE, CLIMB AND T.O./MCT POWER SETTING DETENTS (FLATS) . 19 FIGURE 7 TYPICAL ALTITUDE DEPENDENT THRUST SCH

23、EDULES VERSUS THRUST LEVER POSITION 20 FIGURE 8 EXAMPLE OF MULTIPLIER SCHEDULE 22 FIGURE 9 A DETENTED OR “FIXED POSITION” THROTTLE QUADRANT . 23 FIGURE 10 CROSS-SECTION OF A DETENTED OR “FIXED POSITION” THROTTLE QUADRANT 24 FIGURE 11 THRUST VERSUS THROTTLE LEVER ANGLE WITHOUT DETENTS . 25 FIGURE 12

24、THRUST RATING/MODE SELECTION PANEL . 26 FIGURE 13 TYPICAL THRUST RATING SELECTION DISPLAY ON-GROUND, PRE-FLIGHT 27 FIGURE 14 TYPICAL THRUST RATING SELECTION DISPLAY IN-FLIGHT 27 FIGURE 15 AMBIENT TEMPERATURE LAPSE FROM AGL . 31 FIGURE 16 THRUST AS A FUNCTION OF AMBIENT TEMPERATURE AND ALTITUDE INCRE

25、ASE AT CONSTANT MACH NUMBER 31 FIGURE 17 THRUST LIMITING FUNCTION AT LOW AIRSPEED . 33 FIGURE 18 MOVING THRUST LEVER AUTO-THRUST SYSTEM 35 FIGURE 19 NON-MOVING THRUST LEVER AUTO-THRUST SYSTEM . 35 FIGURE 20 ALL ENGINES OPERATING; AVAILABLE THRUST SCHEDULES (CANNOT SET MAXIMUM CONTINUOUS THRUST) . 39

26、 FIGURE 21 ASPIRATED TOTAL AIR TEMPERATURE PROBE (COURTESY OF ROSEMOUNT AEROSPACE INC. THE EXTERNAL SHAPE OF THE TAT PROBE IN THE FIGURE IS A REGISTERED TRADEMARK OF ROSEMOUNT AEROSPACE INC.) 47 FIGURE 22 TYPICAL CROSS-MANIFOLDED BODY STATIC PRESSURE SENSING CONFIGURATION . 49 FIGURE 23 TYPICAL BODY

27、 OR NACELLE STATIC PRESSURE SENSING PORT . 49 SAE AIR5924A Page 4 of 81 FIGURE 24 NON-ASPIRATED TAT PROBE (COURTESY OF ROSEMOUNT AEROSPACE INC. THE EXTERNAL SHAPE OF THE TAT PROBE IN THE FIGURE IS A REGISTERED TRADEMARK OF ROSEMOUNT AEROSPACE INC.) 51 FIGURE 25 ENGINE INLET MOUNTED P2/T2 PROBE (COUR

28、TESY OF ROSEMOUNT AEROSPACE INC. THE EXTERNAL SHAPE OF THE P2/T2 PROBE IN THE FIGURE IS A REGISTERED TRADEMARK OF ROSEMOUNT AEROSPACE INC.) 53 FIGURE 26 TYPICAL FADEC SELECTION LOGIC FOR STATIC PRESSURE, TOTAL TEMPERATURE, AND TOTAL PRESSURE INFORMATION . 56 FIGURE 27 TYPICAL PRESENTATION OF POWERPL

29、ANT DATA . 62 FIGURE 28 TYPICAL FADEC ENGINE THRUST DISPLAY . 63 FIGURE 29 TYPICAL EICAS SYSTEM WITH MULTI-FUNCTION DISPLAY . 71 TABLE 1 LIST OF ACRONYMS AND SYMBOLS 9 SAE AIR5924A Page 5 of 81 1. SCOPE This SAE Aerospace Information Report (AIR) provides methodologies and approaches that have been

30、used to install and integrate full-authority-digital-engine-control (FADEC) systems on transport category aircraft. Although most of the information provided is based on turbofan engines installed on large commercial transports, many of the issues raised are equally applicable to corporate, general

31、aviation, regional and commuter aircraft, and to military installations, particularly when commercial aircraft are employed by military users. The word “engine” is used to designate the aircraft propulsion system. The engine station designations used in this report are shown in Figure 1. Most of the

32、 material concerns an Electronic Engine Control (EEC) with its associated software, and its functional integration with the aircraft. However, the report also addresses the physical environment associated with the EEC and its associated wiring and sensors. Since most of todays transport category eng

33、ines use dual-channel full-authority digital engine control (FADEC) systems, this is the configuration which is addressed. A typical FADEC system configuration is shown in Figure 2. 1.1 Purpose This report provides guidance to engine/control designers and aircraft system designers on the issues asso

34、ciated with the installation and integration of engine control systems with aircraft systems. Future technologies employed may be different from those addressed in this report, but the basic concepts are the same. The readers must judge the importance of the concepts being addressed to the technolog

35、y that they are employing in a new application. The examples used have satisfied the requirements in existence at the time of design/certification; they are not considered requirements. 1.2 Summary of Revision A This revision provides information on the integration of FADEC systems in general aviati

36、on (GA) aircraft and adds additional information on FADEC control system integration in Transport aircraft. 1.3 Field of Application The field of application is aerospace, primarily for FADEC equipped engines targeted for commercial Transport and GA aircraft installations. The information contained

37、herein may also be useful for engine integration into rotorcraft and those military aircraft which are derivatives of civil aircraft. SAE AIR5924A Page 6 of 81 FIGURE 1 - STATION DEFINITIONS USED HEREIN SAE AIR5924A Page 7 of 81 FIGURE 2 - TYPICAL FADEC SYSTEM SAE AIR5924A Page 8 of 81 2. REFERENCES

38、 2.1 Applicable Documents The following publications form a part of this report to the extent specified herein. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained. 2.1.1 Federal Aviation Administration (FAA) Publications 14 CFR

39、 Parts 23, 25, 27, 29, 33 and Advisory Circulars (ACs) available from Federal Aviation Administration, 800 Independence Avenue, SW, Washington, DC 20591. A few of the ACs are: AC 20-53B, Protection of Aircraft Fuel Systems Against Fuel Vapor Ignition Caused by Lightning, issued June 2006. AC 20-88A,

40、 Guidelines on the Marking of Aircraft Powerplant Instruments (Displays), issued September 30, 1985. AC 25-11A, Electronic Flight Deck Displays, issued June 21, 2007. AC 20-136B, Aircraft Electrical and Electronic Systems Lightning Protection, issued September 2011. AC 20-158, The Certification of A

41、ircraft Electrical and Electronic Systems for Operation in the High-Intensity Radiated Fields (HIRF) Environment, issued July 2007. AC 21-16G, RTCA Document DO-160 D, E, F, G, Environmental Conditions and Test Procedures for Airborne Equipment. AC23-1311-1B, Installation of Electronic Display in Par

42、t 23 Airplanes with change 1 incorporated, issued February 17, 2009. AC 25-13, Reduced and Derated Takeoff Thrust (Power) Procedures, issued May 4, 1988. AC 33.28-1, Compliance Criteria for 14 CFR 33.28, Aircraft Engines, Electrical and Electronic Control Systems, issued June 29, 2001. Transport Air

43、craft Directorate Policy Letters: Policy Letter TAD 95-001, The Role of Maintenance Computers in Exposure Time Assumptions for Quantitative Safety Analyses, issued February 22, 1995. Policy Letter TAD 00-113-1028, Availability of All-Engine Maximum Continuous Thrust (MCT), issued July 31, 2000. Engi

44、ne and Propeller Directorate Policy Letter: Policy Letter: ANE-1993-33.28TLD-R1, Policy for Time Limited Dispatch (TLD) of Engines Fitted with Full Authority Digital Engine Controls (FADEC) Systems, issued June 29, 2001. Small Aircraft Directorate Memos: Full Authority Digital Engine Control (FADEC)

45、 Installation Compliance Review, issued 28 January 2009. SAE AIR5924A Page 9 of 81 2.1.2 European Aviation Safety Agency Certification Specification (CS) 23/25/27/29/E 2.1.3 Other Documents AS755 Aircraft Propulsion System Performance Station Designation and Nomenclature ARP5107 Guidelines for Time-

46、Limited-Dispatch (TLD) Analysis for Electronic Engine Control Systems AIR6181 Electronic Propulsion Control System/Aircraft Interface Control Documents RTCA DO-178C Software Considerations in Airborne Systems and Equipment Certifications (issued December 1992, and ERRATA sheet issued December 2011)

47、Goodrich Total Temperature Sensor Technical Report 5755, Rev. B, dated 1990 2.2 Acronyms and Symbols TABLE 1 - LIST OF ACRONYMS AND SYMBOLS Meaning Comments ADC Air-data Computer AGL Above Ground Level AFM Aircraft Flight Manual ATM Assumed Temperature Method ATTCS Automatic Take-off Thrust Control

48、System Also known as APR or ATR (Automatic Power or Thrust Reserve) CMC Central Maintenance Computer CMR Certification Maintenance Requirement ECS Environmental Control System EEC Electronic Engine Control This term may be used to describe just the basic electronic engine control unit EICAS Engine I

49、ndication and Cockpit Advisory System System for displaying engine parameters and warnings to the flight crew. Also known as ECAM (Electronic Centralized Aircraft Monitoring) EPR Engine Pressure Ratio FADEC Full-authority Digital Engine Control This term is generally used to represent to whole engine control system, including wire harnesses, fuel metering unit, etc. FOD Foreign Object Damage GA General Aviation GW