1、AEROSPACE STANDARDAS8039REV.AIssued 1985-01Reaffirmed 2008-02Revised 2002-02Minimum Performance StandardGeneral Aviation Flight RecorderNOTICEChanges in this Revision are format/editorial only.INTRODUCTIONThe standards contained herein apply to recording equipment intended primarily for installation
2、 in multi-engine, turbine powered aircraft (fixed and rotary wing) for automatically recording flight data parameters and audio information. This standard is not intended for large aircraft operating under Code of Federal Regulations Title 14, Aeronautics & Space, part 121.TABLE OF CONTENTSINTRODUCT
3、ION 11. SCOPE .41.1 Basic Types of Flight Recorders.41.2 Purpose 42. APPLICABLE DOCUMENTS52.1 Code of Federal Regulations, Title 14 52.2 Industry Standards52.3 Military Specifications .52.4 SAE Documents .52.5 RTCA Documents.53. GENERAL REQUIREMENTS.63.1 Material.63.2 Workmanship6SAE Technical Stand
4、ards 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 therefrom, is the sole res
5、ponsibility of the user.” SAE reviews each technical report at least every five years at which time it may be reaffirmed, revised, or cancelled. SAE invites your written comments and suggestions. Copyright 2008 SAE International All rights reserved. No part of this publication may be reproduced, sto
6、red 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: 724-776-4970 (outside USA) Fax: 724-776-0790 Em
7、ail: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.org SAE AS8039 Revision A- 2 -TABLE OF CONTENTS (Continued)3.3 Compatibility .63.4 Interchangeability63.5 Accessibility of Controls63.6 Operation of Controls63.7 Fault Monitoring 63.7.1 Fault Monitoring 63.7.2 Monitoring Effects .73.8 Input
8、Circuit Protection .73.9 Fire Hazard .73.10 Marking .73.10.1 Environmental Categories73.10.2 Type of Recorder73.10.3 Nominal Power Input Rating 73.10.4 External Marking 73.10.5 Application Marking83.11 Documentation Requirements83.11.1 Operating Instructions 83.11.2 Equipment Limitations83.11.3 Inst
9、allation Procedures.83.11.4 Schematic Drawings 83.11.5 Wiring Diagrams.83.11.6 Specifications .83.11.7 Recorder Calibration 83.11.8 Qualification Test Procedures and Report83.11.9 Instructions/Documentation for Data Transcription 83.11.10 Readout Information.83.11.11 Specifications and Schematics fo
10、r Readout Devices.84. DESIGN CONSIDERATION .94.1 Recording Channels.94.2 Recording Methods 94.3 Bulk Erase94.4 Locating Requirement 94.4.1 Non Ejectable Recorders .94.4.2 Ejectable Recorders.95. MINIMUM PERFORMANCE STANDARDS IN AMBIENT ENVIRONMENT.95.1 Ambient Conditions 95.2 Automatic Operation.95.
11、3 Audio Recording.105.3.1 Recording Duration.105.3.2 Audio Frequency Response .105.3.3 Input Signal Level.10SAE AS8039 Revision A- 3 -TABLE OF CONTENTS (Continued)5.3.4 Distortion.105.3.5 Audio Noise Level - Without Input Signal .105.3.6 Wow and Flutter .105.3.7 Stray Magnetic Field.115.3.8 Cockpit
12、Area Microphone Assembly 115.4 Flight Data Recording 115.4.1 Automatic Cessation of Recording.115.4.2 Parameters.115.4.2.1 Continuous Recording115.4.2.2 Data Compression Recording 115.4.3 Error Rate.185.4.3.1 Continuous Recording185.4.3.2 Data Compression Recording 185.4.4 FDR Data Readout Interface
13、185.4.5 Recording Duration 185.4.6 Retention of Recorded Information 185.4.7 Baseline Data.186. MINIMUM PERFORMANCE STANDARD IN SEVERE ENVIRONMENTS 196.1 Environmental Conditions 196.1.1 Certification 196.2 Temperature and Altitude Tests196.3 Humidity Test .196.4 Shock Test .196.5 Vibration Test .19
14、6.6 Explosion Test196.7 Waterproofness Test 206.8 Fluids Susceptibility Test206.9 Sand and Dust Test206.10 Fungus Resistance Test.206.11 Salt Spray Test.206.12 Magnetic Effect 206.13 Power Input Test 206.14 Voltage Spike Conducted Test .216.15 Audio Frequency Conducted Susceptibility Test216.16 Indu
15、ced Signal Susceptibility Test216.17 Radio Frequency Susceptibility Test (Radiated and Conducted).216.18 Emission of Radio Frequency Energy Test 217. CRASH SURVIVABILITY217.1 Signal Recording217.2 Non Ejectable Recorders .227.2.1 Impact Shock Test22SAE AS8039 Revision A- 4 -TABLE OF CONTENTS (Contin
16、ued)7.2.2 Penetration Resistance Test .227.2.3 Static Crush227.2.4 Fire Test .227.2.5 Water Immersion Test 227.2.6 Fluid Immersion Test237.3 Ejectable Recorders.237.3.1 Automatic Ejection Test237.3.2 Impact Shock Test237.3.3 Fire Test .237.3.4 Water Immersion Test 237.3.5 Fluid Immersion Test237.4 S
17、ignal Reproduction.24TABLE 1 SAE General Aviation Flight Recorder Minimum FlightData Parameter List for Fixed Wing Aircraft.12TABLE 2 SAE General Aviation Flight Recorder Minimum FlightData Parameter List for Rotary Wing Aircraft.14TABLE 3 Altitude Record Error Table 171. SCOPE:1.1 Basic Types of Fl
18、ight Recorders:This standard covers three (3) basic types of flight recorders as defined below:TYPE I Cockpit Voice Recorder (only) - Records voice communication (among flight crew and radio communication to and from aircraft crew) and cockpit area sound.TYPE II Flight Data Recorder (only) - Records
19、 aircraft flight data parameters.TYPE III Cockpit Voice/Flight Data Recorder Combination - Records all TYPE I and TYPE II requirements in a composite unit.All requirements specified in Sections 3, 4, 5, 6 and 7 of this standard shall be applicable to all recorder types unless otherwise noted.1.2 Pur
20、pose:This Aerospace Standard (AS) specifies minimum performance standards for recording automatically aircraft flight parameters and (or) aural communication between flight crew members, aural warning sounds, and communications to and from aircraft necessary for flight operations. It is the intent o
21、f this standard to allow for the use of individual Cockpit Voice Recorder (CVR) or Flight Data Recorder (FDR) equipment, or a combination CVR/FDR. These equipments have been identified as TYPE I, II and III, thereafter as identified by paragraph 1.1.SAE AS8039 Revision A- 5 -2. APPLICABLE DOCUMENTS:
22、The following documents shall form a part of this standard to the extent specified. In the event of conflict between these documents and this standard, the contents of this standard shall govern.2.1 Code of Federal Regulations, Title 14:Applicable as specified herein. Copies may be purchased from Th
23、e Superintendent of Documents, U.S. Government Printing Office, Washington, D.C. 20402.a. Title 14 - Code of Federal Regulations Aeronautics & Space2.2 Industry Standards:a. RS-232 Interface Between Data Terminal Equipment and Data Communication Equipment Employing Serial Binary Data InterchangeRS-4
24、22A Electrical Characteristics of Balanced Voltage Digital Interface CircuitsCopies may be purchased from Electronic Industries Association, Standard Sales Office, 2001 “I“ Street, N.W. Washington, D.C. 20006.b. Magnetic Tape Recording and Reproducing April 1965Copies may be purchased from National
25、Association of Broadcasters, 477 Madison Avenue, New York, N.Y.c. IEEE STANDARD 488 - Standard Interface for Programmable Instrumentation (1978)Copies may be purchased from Institute of Electrical and Electronic Engineers, Inc., 345 East 47th Street, New York, N.Y. 10017.2.3 Military Specifications:
26、a. MIL-S-17526 - Sands, MoldingCopies may be purchased from Naval Publications and Forms Center, 5801 Tabor Avenue, Philadelphia, PA 19120.2.4 SAE Documents:Not applicable2.5 RTCA Documents:a. RTCA/DO-160A - Environmental Conditions and Test Procedures for Airborne Equipment, January 1980Copies may
27、be purchased from the Radio Technical Commission for Aeronautics Secretariat, 1425 “K“ Street, N.W., Suite 500, Washington, D.C. 20005.SAE AS8039 Revision A- 6 -3. GENERAL REQUIREMENTS:3.1 Material:Material shall be of a quality which experience and/or tests have demonstrated to be suitable and depe
28、ndable for use in aircraft.3.2 Workmanship:Workmanship shall be consistent with high grade aircraft manufacturing practices.3.3 Compatibility:If components are individually acceptable but require matching for proper operation, they shall be identified in a manner that will ensure performance to the
29、requirements of this standard.3.4 Interchangeability:Components or systems which are identified with the same manufacturer part or model number shall be completely interchangeable.3.5 Accessibility of Controls:Controls which are not normally adjustable in flight shall not be readily accessible to fl
30、ight personnel when the recorder is installed in accordance with the manufacturers instructions.3.6 Operation of Controls:The design of the equipment shall be such that the controls intended for use during flight (if any) cannot be operated in any possible position, combinations or sequences that wo
31、uld result in a condition detrimental to the continued performance of the equipment or have any detrimental effect on associated equipments.3.7 Fault Monitoring:3.7.1 Fault Monitoring: Automatic means shall be provided to indicate malfunctions that cause loss of recorded audio or flight data. Means
32、shall be provided for remote indication of a malfunction. Monitoring shall include as a minimum:a. Presence of input powerb. Generation of a data streamc. Data write/read function is operabled. Audio channels are functioningSAE AS8039 Revision A- 7 -3.7.2 Monitoring Effects: The inclusion of self-te
33、st and fault monitoring shall not produce a condition detrimental to other aircraft systems or sensed signals to be recorded.3.8 Input Circuit Protection:Each signal input circuit shall include suitable circuitry to minimize the flight recorder system from inducing errors, malfunctions, and failures
34、 in the aircraft system being monitored. The circuitry shall protect the aircraft sensors, transducers or instrument system against all reasonably probable malfunctions including non-programmed multiplex switch closures. The protection shall continue to exist even in the event of any reasonably prob
35、able failure within the isolation circuitry itself and with power-off conditions.3.9 Fire Hazard:Except for small parts (such as knobs, fasteners, seals, grommets, and small electrical parts) that would not contribute significantly to the propagation of a fire, all external materials shall be self-e
36、xtinguishing when tested in accordance with the requirements of The Code of Federal Regulations Title 14, Aeronautics & Space, Part 25, Appendix F, with the exception that materials tested may be configured in accordance with paragraph (d) of Appendix F or may be configured as used.3.10 Marking:The
37、equipment shall be legibly and permanently marked, as specified in 14 CFR Part 45, and indicate:3.10.1 The environmental categories for which it has been qualified to operate in accordance with RTCA/DO-160A.3.10.2 Type of recorder (See SECTION NO. 1)3.10.3 Nominal power input rating, (voltage, AC po
38、wer and frequency or DC current).3.10.4 External marking shall be applied to the unit containing the storage medium on two (2) places, as large as practical, with the following warning (second marking French or an alternate language):FLIGHT RECORDER - - DO NOT OPENENREGISTREUR DE VOL - - NE PAS OUVR
39、IRSAE AS8039 Revision A- 8 -3.10.5 Application Marking: Each recorder shall be plainly identified or marked on its identification label to establish installation applicability for which a recorder is designed. The identification marking shall be one of the following for the applicable aircraft insta
40、llation.a. “Install on Fixed Wing Aircraft Only“b. “Install on Rotary Wing Aircraft Only“c. “Install on Fixed or Rotary Wing Aircraft“The above marking selection shall be based on the recorders ability to meet the applicable requirements of paragraph 3.10.1 and 4.1 with respect to environmental oper
41、ations and parameters.3.11 Documentation Requirements:In accordance with 14 CFR Part 21, Paragraph 31 requirements, manufacturers shall furnish to the appropriate approving agencies the following technical data:3.11.1 Operating Instructions3.11.2 Equipment Limitations3.11.3 Installation Procedures a
42、nd Limitations3.11.4 Schematic Drawings3.11.5 Wiring Diagrams3.11.6 Specifications3.11.7 Recorder Calibration and Maintenance Procedures3.11.8 Qualification Test Procedures and Report3.11.9 Instructions and documentation, mathematics and logic required for data transcription for TYPE II and TYPE III
43、 recorders.3.11.10 Readout information to demonstrate that the manufacturer has facilities capable of:a. Retrieving recorded audio data from TYPES I and III recorders.b. Producing a printout of all recorded parameters from TYPES II and III recorders.3.11.11 Specification and schematics for special r
44、eadout devices as may be required under Section 5, paragraph 5.4.4.SAE AS8039 Revision A- 9 -4. DESIGN CONSIDERATION:4.1 Recording Channels:TYPES I and III recorders shall be capable of recording simultaneously at least two channels of audio information. TYPES II and III recorders shall be capable o
45、f recording flight data information as given in Tables 1 or 2.4.2 Recording Methods:Any recording method which meets the standard test conditions and the environmental test conditions is acceptable. If an electromechanical system of recording is used, the mean recording speed shall not vary more tha
46、n 2 percent from the design speed when the recorder is powered by a constant frequency source or within the supply voltage tolerance.4.3 Bulk Erase:The recorder(s) shall contain no provisions for bulk erase of the stored information.4.4 Locating Requirements:4.4.1 Non Ejectable Recorders: The record
47、er (unit containing the storage medium) color shall be international orange and shall have reflective material located on three (3) sides. Provision shall be made for an underwater locator beacon (ULB) to be attached to the crash protected container. The attachment shall be such that the ULB shall n
48、ot become detached when subject to the shock test of 7.2.1.4.4.2 Ejectable Recorders: After ejection, the ejectable package shall be capable of floatation and shall emit a suitable radio beacon signal on a standard distress frequency. The recorder ejectable package color shall be international orang
49、e with reflective material located on all sides except the side(s) exposed to the external environment when installed in the aircraft.5. MINIMUM PERFORMANCE STANDARDS IN AMBIENT ENVIRONMENT:5.1 Ambient Conditions:Unless otherwise specified, all tests shall be made at ambient conditions specified in RTCA/DO-160A.5.2 Automatic Operation:5.2.1 When power is applied to the aircraft, TYPE I recorders shall record continuously in a manner as specified herein.5.2.1.1 TYPE I recorders shall cease recording when the signal defined in 5.4.1-b is present.SAE AS
