SAE AS 8017D-2017 Minimum Performance Standard for Anticollision Light Systems.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 2017 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:/standards.sae.org/AS8017D AEROSPACE STANDARD AS8017 REV. D Issued 1978-01 Revised 2017-08 Superseding AS8017C Min

5、imum Performance Standard for Anticollision Light Systems RATIONALE This document establishes minimum performance levels for aircraft anticollision light systems including chromaticity and light intensity in support of TSO and system certifications. Information contained herein has been expanded fro

6、m AS8017C in the areas of measurement orientation, color specifications, qualification criteria and added figures for clarity. Further information has also been added regarding the use of Light Emitting Diode (LED) technology in the areas of effective intensity, flash frequency and continued airwort

7、hiness. 1. SCOPE This SAE Aerospace Standard (AS) establishes minimum performance standards for new equipment anticollision light systems. This Aerospace Standard defines minimum light intensity in terms of “effective intensity“ as defined in paragraph 3.5 of this standard and specified vertical and

8、 horizontal directions about the longitudinal and vertical axis of the airplane. It will also define flash rate and color for the anticollision light system. It is not intended that this standard require the use of any particular light source such as Xenon, LED or any other specific design of lamp.

9、1.1 The anticollision light system will consist of all components necessary to produce the required intensity distribution, flash rate, etc. about the airplane. It may consist of one or more lighting units mounted in various places on the airplane such as top and bottom fuselage, vertical fin, tail

10、cone, wing tips, or other location. Timing devices or power supplies necessary for proper operation of the anticollision light system will also be considered as part of the system. 1.2 The anticollision light system will meet the minimum performance standards for one of the following classes: Aircra

11、ft Type Effective Intensity Class I - Rotorcraft 150 Candelas Class II - Fixed Wing Aircraft 400 Candelas Class III - Fixed Wing Aircraft and Rotorcraft 100 Candelas 1.2.1 It is necessary to establish these classes in order to define performance standards for lights as required by FARs. Amendment 27

12、-10 of FAR 27 and 29-11 of FAR 29 established minimum intensity requirements for Rotorcraft as listed for Class I lights. Generally, all rotorcraft certificated prior to these amendments must meet requirements of Class III lights. Anticollision lights for fixed wing aircraft must meet requirements f

13、or Class III lights if certificated prior to August 11, 1971 and the requirements for Class II lights if certificated after that date. SAE INTERNATIONAL AS8017D Page 2 of 12 2. APPLICABLE DOCUMENTS The following publications form a part of this document to the extent specified herein. The latest iss

14、ue of SAE publications shall apply. The applicable issue of other publications shall be the issue in effect on the date of the purchase order. In the event of conflict between the text of this document and references cited herein, the text of this document takes precedence. Nothing in this document,

15、 however, supersedes applicable laws and regulations unless a specific exemption has been obtained. 2.1 SAE Publications Available from SAE International, 400 Commonwealth Drive, Warrendale, PA 15096-0001, Tel: 877-606-7323 (inside USA and Canada) or +1 724-776-4970 (outside USA), www.sae.org. AIR56

16、89 Light Transmitting Glass Covers for Exterior Aircraft Lighting ARP5029 Measurement Procedures for Strobe Anticollision Lights ARP991 Position and Anticollision Lights - Turbine Powered Fixed-Wing Aircraft ARP5414 Aircraft Lightning Zoning ARP5637 Design and Maintenance Considerations for Aircraft

17、 Eterior Lighting Plastic Lenses ARP6161 Flight Compartment Glare ARP6253 LEDs and Aircraft Applications AS25050 Colors, Aeronautical Lights and Lighting Equipment, General Requirements For J1330 Photometer Laboratory Accuracy Guidelines 2.2 RTCA Publications Available from RTCA, Inc., 1150 18th Str

18、eet, NW, Suite 910, Washington, DC 20036, Tel: 202-833-9339, www.rtca.org. DO-160 Radio Technical Commission for Aeronautics (RTCA), Environmental Conditions and Test Procedures for Airborne Equipment (latest applicable revision). 2.3 U.S. Military Specifications and Standards Copies of these docume

19、nts are available at http:/quicksearch.dla.mil. MIL-DTL-7989 Covers, Light-Transmitting, for Aeronautical Lights, General Specification for SAE INTERNATIONAL AS8017D Page 3 of 12 2.4 Other Publications Code of Federal Regulations Title 14, Part 23, 25, 27, 29. Some applicable sections may include, b

20、ut are not limited to the following: 2-.1397 Color Specifications 2-.1401 Anticollision Light System 25.1701 25.1729 Electrical Wiring Interconnection Systems (EWIS) Department of Transportation, Federal Aviation Administration, Aircraft Certification Service, Washington, DC TSO-C96 Technical Standa

21、rd Order, Anticollision Light Systems AC 20-30 Advisory Circular, Aircraft Position Light and Anticollision Light Installations AC 20-74 Advisory Circular, Aircraft Position and Anticollision Light Measurements 3. GENERAL STANDARDS 3.1 Class I - Rotorcraft - 150 Candelas 3.1.1 Color: Each light in t

22、he system will produce light having an Aviation Red color as defined in Section 3.4. 3.1.2 Minimum Effective Intensity: The system must provide effective intensity equal to or exceeding the values shown in Figure 1 for any vertical plane (intensities are per 14 CFR Part 27 and z is not greater than

23、0.002. b. Aviation White x is not less than 0.300 and not greater than 0.540; y is not less than x0.040; or y00.010, whichever is the smaller; and y is not greater than x+0.020 nor 0.6360.400x; Where y0 is the y coordinate of the Planckian radiator for the value of x considered. 3.4.1 Alternate Colo

24、r Definitions Alternate color definition that has been practiced by industrys TSO and certification programs. a. Aviation Red: Purple Boundary y = 0.980 x Yellow Boundary y = 0.335 b. Aviation White: Yellow Boundary x = 0.500 Red Boundary y = 0.382 Purple Boundary y = 0.047 + 0.762x Blue Boundary x

25、= 0.285 Green Boundary y = 0.150 + 0.640x and y = 0.440 A representation of the color definitions is shown in Figure 4. SAE INTERNATIONAL AS8017D Page 6 of 12 Figure 4 - Aviation color definitions in CIE1931 color diagram 3.4.2 For Class II and Class III systems where both Aviation Red and Aviation

26、White lights are used to comprise the anticollision light system, in areas where the red and white overlap, a mixture of the colors is permitted. 3.5 Effective Intensity The light intensity in any direction for either Aviation Red or Aviation White as applicable, must meet the requirements of 3.1.2,

27、 3.2.2 or 3.3.2 as applicable. The following relation must be assumed: m a x12tte tt2.0dt)t(II 21 where: Ie = effective intensity (candelas) I(t) = instantaneous intensity as a function of time t2 - t1 = flash time interval (seconds) Normally, the maximum value of effective intensity is obtained whe

28、n t2 and t1 are chosen so that the effective intensity is equal to the instantaneous intensity at t2 and t1. The computed value for effective intensity will vary for a given light-time curve with choice of values for t2 and t1. SAE INTERNATIONAL AS8017D Page 7 of 12 3.5.1 Some anticollision light sy

29、stems may be designed to produce multiple flashes within a short time interval. Reference Figure 5. Where all flashes in a multiple flash or burst of flashes are contained within a time interval of 0.2 seconds, the “effective“ intensity as defined in 3.5 may be computed in either of two methods to d

30、emonstrate compliance with minimum effective intensity requirements of 3.1.2, 3.2.2 or 3.3.2. Figure 5 - Examples of multiple flashes 3.5.1.1 The effective intensity of any one flash in the burst can be computed using the energy in that single flash as the numerator and the time duration of that fla

31、sh as the denominator of the formula in 3.5. 3.5.1.2 The effective intensity can be computed by adding together the energy of each flash in the burst to form the numerator of the formula in 3.5 for effective intensity. In this case, the value for (t2 - t1) will be the total time from the beginning o

32、f the first flash to the end of the last flash in the burst, subject to rule in 3.5. 3.5.2 Where the anticollision light system consists of more than one light to provide total required coverage shown in 3.1.2, 3.2.2 or 3.3.2, the required intensity in any one direction must be provided by a single

33、light. A light in a direction from more than one light source cannot be added together to show compliance. 3.5.3 Flash Frequency The flash frequency in paragraphs 3.1.3, 3.2.3 and 3.3.3 apply to individual lights which can comprise the anticollision light system. Where two or more lights are visible

34、 from a given direction of viewing, the effective flash frequency is the frequency at which the airplanes complete anticollision system is observed from a distance and applies to each sector of light including any overlaps that exist when a system consists of more than one light source. In overlaps,

35、 flash frequencies may exceed 100, but not 180, cycles per minute. 3.5.4 Multiple Flashes and Flash Synchronization Where a timing system is used so that multiple lights or single lights in multiple flash modes in a system always flash in a given time relationship with each other, all flashes visibl

36、e in a given direction which occur in a 0.2 second time interval will be considered as one flash for purposes of counting flashes. This is indicated in Figure 5. SAE INTERNATIONAL AS8017D Page 8 of 12 3.5.5 Flash Duration LED based anticollision lights are capable of a significantly longer duration

37、flash time interval (on time) compared to other technologies such as flash tubes. Assuming a square shaped flash, a longer duration flash time interval increases the effective intensity without an increase of instantaneous intensity. Academic research has shown that shorter duration flashes with hig

38、her peak intensities are more conspicuous than longer duration flashes with lower peak intensities despite having the same effective intensity. While longer flash time intervals can comply with the effective intensity and flash frequency regulations, in order to maximize conspicuity unnecessarily lo

39、ng flash time intervals should be avoided. 3.6 Measurements 3.6.1 Laboratory ambient temperature shall be 25 10 C. 3.6.2 Input Power Intensity measurements should be performed at nominal input voltage. Compliance shall be demonstrated by testing or other means at the lower and higher normal voltage

40、limits to show compliance for all normal input voltages. 3.6.3 Forced Air Cooling There should be no external forced air cooling (fans and other drafts) during measurements, except in cases where their use is required to simulate the aircrafts operating environment. 3.6.4 Warm Up and Stabilization F

41、or purposes of demonstrating compliance with this specification, all photometric and color measurements for LED sources shall be made after a minimum warm up period of 30 minutes or after the light has reached thermal stabilization, whichever is longer. Stabilization shall be defined as the point in

42、 which light output does not change by more than 3% over a 15 minute period. The minimum warm up period for Xenon or other light sources shall be 5 minutes or after the light has reached thermal stabilization, whichever is longer. 3.6.5 Cover Lens Intensity measurements must comply with the cover le

43、ns in place. However, intensity measurements can be performed with or without the aircraft cover lens installed. When measuring without the cover lens, analyses shall be used to show compliance. 3.7 Definition of Operating Lifetime Operating Lifetime is the duration for which the light is expected t

44、o meet the minimum intensity requirements when intensities are measured per 3.6. Environmental and installation conditions affect Operating Lifetime. In the case of LED based lights, lumen maintenance is a function of LED junction temperature and drive current. Lumen maintenance for typical laborato

45、ry ambient conditions (T = 25 C 5 C) and other elevated or lower expected flight test temperatures and their exposure times (71 C with a 3 knot wind for 3 hours per day, for example) can be used to help estimate actual Operating Lifetimes for particular flight patterns. This data would be used to de

46、fine the aircrafts installation environment. Continuing airworthiness can be achieved by a number of methods, some of which are: Limiting on-wing Operating Lifetime based on an estimation of component laboratory life with adjustments which take into account actual operating conditions on-the-ground

47、and in-flight, or; Limiting on-wing Operating Lifetime based on active feedback from an integrated light sensor or; Requiring Aircraft operators to measure intensity levels at reqularly scheduled maintenance intervals to insure compliance. SAE INTERNATIONAL AS8017D Page 9 of 12 Consideration should

48、be given to failure modes where a light continues to operate at a degraded level of performance. The probability and effects of these failure modes must be considered, including how an operator can determine when a light no longer meets regulatory performance requirements. For example, in LED based

49、systems the light may continue to illuminate even if one or more individual LEDs no longer illuminate. This analysis also includes driver circuitry, flash controllers or other integrated electronics. 3.8 Photometric Testing Orientation For purposes of demonstrating compliance with this specification, all photometric measurements shall be performed with the horizontal and vertical planes a