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基本信息

ARP5416
Aircraft Lightning Test Methods
Aircraft Lightning Test Methods< - Self-propelled de-icing/anti-icing vehicles - Functional requirements >=
2005-03-01
有效
【范围】 This document is one of a set covering the whole spectrum of aircraft interaction with lightning. This document is intended to describe how to conduct lightning direct effects tests and indirect system upset effects tests. Indirect effects upset and damage tolerance tests for individual equipment items are addressed in DO-160/ED-14. Documents relating to other aspects of the certification process, including definition of the lightning environment, zoning, and indirect effects certification are listed in Section 2. This document presents test techniques for simulated lightning testing of aircraft and the associated systems. This document does not include design criteria nor does it specify which items should or should not be tested. Acceptable levels of damage and/or pass/fail criteria for the qualification tests must be approved by the cognizant certification authority for each particular case. When lightning tests are a part of a certification plan, the test methods described herein are an acceptable means, but not the only means, of meeting the test requirements of the certification plan. Each test method is set out in a uniform format, describing the test purpose, test object, test setup, test waveforms (voltage and/or current), measurements and data recording, test procedure and data interpretation. Guidance is provided on how to select the appropriate test or series of tests, and how the test results can be assessed. Natural lightning is a complex and variable phenomenon and its interaction with different types of vehicles may be manifested in many different ways. It is not intended that every test described herein be applied to every system requiring lightning verification tests. The document is written so that specific aspects of the environment can be called out for each specific program as dictated by the vehicle design, performance and mission constraints.strRefField
【与前一版的变化】

包含缩略语

A:
AC:
C:
cm:
d or D:
dB:
DC:
f or F:
ft:
G:
Hg:
Hz:
i or I:
K:
kA:
kHz:
kV:
L:
m:
mA:
MHz:
μH:
μJ:
μs:
mm:
mmHg:
M Ω:
nH:
p:
P:
pF:
ps:
Ω:
Q:
R:
s:
V:
W:
Z:
AC:
ANSI:
AOA:
ARP:
ATL:
CFC:
CFR:
CFRP:
CN:
CS:
CW:
EED:
EASA:
EM:
EMC:
ETDL:
EUROCAE:
EUT:
FAA:
FADEC:
FAR:
FFT:
FHA:
FRP:
HIRF:
HV:
IEC:
IMA:
IR:
LISN:
LRU:
MIL-STD:
NIST:
RF:
RTCA:
SAE:
SLPM:
SSA:
TCL:
TLD:

引用文件/被引文件

“Certification Considerations for Highly Integrated or Complex Aircraft Systems”
"Aircraft Lightning Environment and Related Test Waveforms"
"Certification of Aircraft Electrical/Electronic Systems for the Indirect Effects of Lightning"
"Aircraft Lightning Zoning"
"User's Manual for Certification of Aircraft Electrical/Electronic Systems for the Indirect Effects of Lightning"
"Lightning Test Waveforms and Techniques for Aerospace Vehicles and Hardware"
"Test Waveforms and Techniques for Assessing the Effects of Lightning Induced Transients"
"Protection of Airplane Fuel Systems Against Fuel Vapor Ignition Due to Lightning”
“Protection of Aircraft Electrical/Electronic Systems for the Indirect Effects of Lightning”
RTCA Document DO-160D
"Equipment
"System Design Analysis"
"Certification of Normal Category Rotorcraft"
"Certification of Transport Category Rotorcraft"
"Environmental Conditions and Test Procedures for Airborne Equipment"
"Environmental Conditions and Test Procedures for Airborne Equipment"
"Certification Considerations for Highly Integrated or Complex Aircraft Systems"
"Certification of Aircraft Electrical/Electronic Systems for the Indirect Effects of Lightning"
"Aircraft Lightning Environment and Related Test Waveforms Standard"
"Aircraft Lightning Zoning Standard”
“General Requirements for Calibration Laboratories and Measuring and Test Equipment”
“High-Voltage Test Techniques - Part 2: Measuring Systems”
(R) Electronic Engine Control Design Guide for Electromagnetic Environmental Effects
Aircraft Lightning Environment and Related Test Waveforms
User’s Manual for Certification of Aircraft Electrical/Electronic Systems for the Indirect Effects of Lightning
Aircraft Lightning Direct Effects Certification
Fitting, Plug-in Union, Ring Locked, 24 Degree Cone, Fluid Connection, 5080 psi (35 000 kPa), Specification for

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包含图表

Initial Leader Attac
Leader Connection Po
Initial Leader Attac
Arrangement for Prot
Arrangement for Swep
Arrangement for Swep
Test Setup to Determ
Test Setup to Determ
Typical Jet Divertin
Test on Transparency
Test on Windshield
Typical Setup for Da
Typical Metal Skin I
Lightning Induced Vo
Induced Voltage Meas
Typical Test Current
Helicopter Ground Pl
Small Aircraft Retur
Large Transport Airc
Schematic Representa
Swept Frequency Test
formula 1
formula 2
Transfer Function Ex
Example for Establis
Pulse Test Setup
Typical Conductor Op
Typical Wire Bundle
Typical Conductor Sh
Simultaneous Injecti
Simultaneous Injecti
Wire Bundle Shield T
Wire Bundle Shield T
Swept Frequency Wire
Harness Current Hand
Harness Current Hand
Examples of Applicat
DC Sparkover Voltage
Equivalent Flight Al
An Example of Contro

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