SAE AIR5924A
Superseded
A superseded Standard is one, which is fully replaced by another Standard, which is a new edition of the same Standard.
View Superseded by
Guidelines for the Integration of Electronic Engine Control Systems for Transport Category (Part 25) and General Aviation (Part 23) Aircraft
Hardcopy , PDF
19-01-2024
English
16-01-2013
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1. SCOPE
2. REFERENCES
3. APPLICABILITY
4. THRUST AND POWER CONTROL
5. USE OF SENSORS, AIRCRAFT SIGNALS, AND DATA
6. INSTRUMENTATION AND FLIGHT-CREW INTERFACES
7. MAINTENANCE CONSIDERATIONS
8. HARDWARE AND ENVIRONMENTAL ISSUES
9. CERTIFICATION
10. NOTES
Specifies methodologies and approaches that have been used to install and integrate full-authority-digital-engine-control (FADEC) systems on transport category aircraft.
| DocumentType |
Standard
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| Pages |
81
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| PublisherName |
SAE International
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| Status |
Superseded
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| SupersededBy | |
| Supersedes |
This SAE Aerospace Information Report (AIR) provides methodologies and approaches that have been 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 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 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 today’s transport category engines 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.
| FAA AC 23.1311-1 : 2011 | INSTALLATION OF ELECTRONIC DISPLAY IN PART 23 AIRPLANES |
| FAA AC 21-16 : 2011 | RTCA DOCUMENT DO-160 VERSIONS D, E, F, AND G, "ENVIRONMENTAL CONDITIONS AND TEST PROCEDURES FOR AIRBORNE EQUIPMENT" |
| SAE ARP5107B | Guidelines for Time-Limited-Dispatch (TLD) Analysis for Electronic Engine Control Systems |
| RTCA DO 178 : C2011 | SOFTWARE CONSIDERATIONS IN AIRBORNE SYSTEMS AND EQUIPMENT CERTIFICATION |
| FAA AC 20-88 : A | GUIDELINES ON THE MARKING OF AIRCRAFT POWERPLANT INSTRUMENTS (DISPLAYS) |
| FAA AC 20-53 : 2006 | PROTECTION OF AIRCRAFT FUEL SYSTEMS AGAINST FUEL VAPOR IGNITION CAUSED BY LIGHTNING |
| FAA AC 25-11 : 2014 | ELECTRONIC FLIGHT DISPLAYS |
| FAA AC 20-136 : 2011 | AIRCRAFT ELECTRICAL AND ELECTRONIC SYSTEM LIGHTNING PROTECTION |
| FAA AC 20-158 : 2014 | THE CERTIFICATION OF AIRCRAFT ELECTRICAL AND ELECTRONIC SYSTEMS FOR OPERATION IN THE HIGH-INTENSITY RADIATED FIELDS (HIRF) ENVIRONMENT |
| SAE AIR6181 | Electronic Propulsion Control System/Aircraft Interface Control Documents |
| SAE AS755E | Aircraft Propulsion System Performance Station Designation and Nomenclature |
| FAA AC 25-13 : 0 | REDUCED AND DERATED TAKEOFF THRUST (POWER) PROCEDURES |
| FAA AC 33.28-1 : 0 | COMPLIANCE CRITERIA FOR 14 CFR SECTION 33.28, AIRCRAFT ENGINES, ELECTRICAL AND ELECTRONIC ENGINE CONTROL SYSTEMS |
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