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基本信息

【标准号】: AIR5060A
【中文名称】: (R) Electronic Engine Control Design Guide for Electromagnetic Environmental Effects
【英文名称】: (R) Electronic Engine Control Design Guide for Electromagnetic Environmental Effects
【发布时间】
【实施时间】: 2011-08-01
【有效性】: 有效
【起草人】
【起草单位】
【提出单位】
【归口单位】
【批准单位】
【分类】
【备案号】
【自动关键词】

【范围】

The purpose of this document is to provide reference material for establishing compatibility of electronic gas turbine engine control systems and associated components with the electromagnetic environment and achieving compliance with associated airworthiness requirements. 1.1 Introduction The modern gas turbine engine used for aircraft propulsion is equipped with an ever increasing variety of electrical and electronic systems which provide for engine control, instrumentation, and auxiliary functions. Today’s aircraft engines currently in service or in development employ full authority digital engine control (FADEC) systems. The criticality of the electronics employed in these systems, with regard to continued safe operation of the aircraft, has led to a greater emphasis on ensuring that the equipment is immune to both natural and man-made electromagnetic environments. Some engine control systems employ electronics in a less than full authority role in the form of "supervisory" or “trimming" controls or limiters. Such systems are still required to be compatible with the electromagnetic environment although the allowable effects on the system and the pass/fail criteria for system testing may differ. In addition to the control system itself, typical aircraft gas turbine equipment includes many other electronic or electrical devices; these include solenoid operated valves to control anti-icing or environmental air supplies, position indicating and pressure operated switches, ignition systems, permanent magnet alternators, etc. Many engines are also equipped with engine monitoring systems or data concentrator units which provide a digital data bus interface to other aircraft electronic systems. Signal control and power levels range from a small fraction of a milliwatt to several hundred thousand watts during ignition discharges. Acquiring, understanding, and efficiently applying the assortment of specifications, both civil and military, can be a daunting prospect for the engine component supplier or the equipment designer. Arbitrarily applying stringent Electromagnetic Compatibility (EMC) requirements to individual components and subsystems may result in unnecessary size, cost, and weight penalties. The Project Engineer or Engineering Manager is frequently called upon to make decisions and judgments for which some basic knowledge of electromagnetic environmental effects and associated design, test, and certification compliance is essential. This document aims to be a central source of information, providing reference and guidance material into each electromagnetic phenomenon. The electromagnetic environment is divided into its main constituents, these being: a. Electromagnetic Interference (EMI), including High Intensity Radiated Fields (HIRF) b. Lightning c. Electromagnetic Pulse (EMP) Within each chapter, the topic is broken down further into the following main sections: a. Introduction b. Description of the Environment c. Certification/Qualification Requirements d. Design Considerations e. Compliance Methods A bibliography is provided for those seeking a more detailed treatment of any given topic, and references are made to any appropriate industry specification where applicable. Electromagnetic Compatibility is essentially an air vehicle issue; for a subsystem, such as the engine control, compatibility must be established with other equipment in the aircraft but it is the complete air vehicle which is exposed to, and must be certified/qualified for, the external HIRF or Lightning/EMP threat. A definition of requirements at the subsystem level is required in order to design and test the equipment, prior to the availability of the full-up aircraft, and/or to substitute for full-up aircraft testing. Testing and analysis at the subsystem level is also required in order to achieve engine certification (FAR Part 33) or qualification. However the subsystem levels are dependent upon other equipment electrically connected to the engine, cable routing and shielding, and the effectiveness of the aircraft structure as an electromagnetic shield.strRefField

【与前一版的变化】

包含缩略语

AC：
A/C：
ACARS：
ACT：
ADC：
AF：
ADF：
AFCS：
AMJ：
AMC：
APU：
ARINC：
ASW：
ATL：
BB：
BCI：
BITE：
BW：
CDU：
CE：
CCF：
CLB：
CM：
CRT：
CS：
DB：
DC：
DFDAU：
DFDR：
DITS：
DM：
DME：
DMV：
DoD：
E3：
EADI：
EASA：
ECS：
E/E：
EEC：
EED：
EEHWG：
E-FIELD：
EFIS：
EGT：
EHSI：
EICAS：
EM：
EMC：
EME：
EMI：
EMIC：
EMICP：
EMITP：
EMITR：
EMP：
EMV：
EPR：
ESD：
ESE：
ETDL：
EUROCAE：
EUT：
FAA：
FADEC：
FAR：
FCC：
FCC：
FDEP：
FMC：
Gr/Ep：
GPS：
H-Field：
HIRF：
HMC：
Hz：
IEEE：
IEMP：
IF：
JAR：
JSC：
KHz：
LISN：
LLC：
LRU：
MHz：
NIST：
NPA：
NPRM：
OATS：
PEDS：
PMA：
PRF：
RAE：
RE：
RF：
RFM：
RMS：
RS：
RTCA：
SCD：
SGEMP：
SIL：
STC：
TCL：
TD：
TLA：
TLD：
TRA：
TSO：
TVS：
TWT：

替代标准

AIR5060

引用文件/被引文件

ARP5107: Guidelines for Time-Limited-Dispatch Analysis for Electronic Engine. Control Systems
ARP5412: Aircraft Lightning Environment and Related Test Waveforms
ARP5414: Aircraft Lightning Zoning
ARP5415: User’s Manual for Certification of Aircraft Electrical/Electronic Systems for the Indirect Effects of Lightning
ARP5416: Aircraft Lightning Test Methods
ARP5583: Guide to Certification of Aircraft in a High Intensity Radiated Field (HIRF) Environment
FAA AC20-136A: Protection of Aircraft Electrical/Electronic Systems against the Indirect Effects of Lightning.
FAA AC 20-53A: Protection of Airplane Fuel Systems against Fuel Vapor Ignition Due to Lightning
FAA AC 33.28-1: Compliance Criteria for 14 CFR 33.28
FAA AC 33.28-2: Guidance Material for 14 CFR 33.28
FAA AC 33.4-3: Instructions for Continued Airworthiness
FAA AC 20-155: Aircraft Lightning Protection Certification-April 28
FAA AC 21-16: RTCA
FAA AC 20-158: The Certification of Aircraft Electrical and Electronic System for Operation in the High-Intensity Radiated Field (HIRF) Environment
RTCA/DO-160E: Section 22
RTCA/DO-160ED14: Environmental Conditions and Test Procedures for Airborne Equipment
MlL-C-38999/27: Connector
MlL-HBK-217F: Military Handbook
MlL-HBK-237: Electromagnetic Compatibility Management
MlL-HBK-253: Guidance for the Design and Test of Systems Protected Against the Effects of Electromagnetic Energy
MIL-STD-202: Test Method Standard
MlL-STD-461F: Requirements for the Control of Electromagnetic Interference Characteristics of Subsystems and Equipment
MIL-STD-464A: DoD Interface Standard
MlL-STD-704E: Aircraft Electrical Power Characteristics
MIL-STD-810: Military Standard Environmental Test Methods and Engineering Guidelines
MlL-STD-882: Systems Safety Program for Systems and Associated Subsystems and Equipment
MlL-STD-1310: Shipboard Bonding
MlL-STD-1377: (NAVY)
Effectiveness of Cable: Connector and Weapon Enclosure Shielding and Filters in Precluding Hazards of Electromagnetic Radiation to Ordnance
SAE ARP1481A: Corrosion Control and Electrical Conductivity in Enclosure Design
SAE ARP1870: Aerospace Systems Electrical Bonding and Grounding for Electromagnetic Compatibility and Safety.
SAE ARP5414: “Aircraft Zoning”
SAE ARP5416: “Aircraft Lightning Test Methods
SAE ARP5577: “Aircraft Direct Effects Certification”.
SAE ARP5583: “Guide to Certification of Aircraft in a High Intensity Radiated Field (HIRF) Environment”.