1、I this limit speed data shall be available from the subject airframe manufac- turer as published in the operating manual for the aircraft me and model number and configuration. 3. GENERAL STANDARDS 3.1 Compatibility of Components: If components of the eqitipment require matching to meet the re- quir
2、ements of this standard, they shall be identified in a manner which will assure proper match- ing. Instaliation instructions issued by the Over Speed Warning Instrument manufacturer shall indicate matching requirements if any. 3.2 Accessibility of Controls: Controls which are not normally adjustable
3、 in flight shall not be readily accessible to flight personnel when the instrument is installed in accordance with the manufactur- ers instructions. 3.3 Interchangeability: Instruments which are identified with the same manufacturers part or model number shall be complex4y interchangeable. 3.4 Over
4、Speed Warning Circuit: 3.4.1 The electrical circuit shall be such that should the aircraft exceed the defined maximum operating speed, the internal circuit shall provide for a signai which shall operate an aural warning device. 3.4.2 The electrical circuit shall be designed so that no signal shall b
5、e present to operate the aural warning device for speeds below the maximum operating speed range and a signal shall be present upon attaining the maximum operating speed and shall remain on above the maximum operating speed. Copyrioht 1978 by Society of Automotive Enginears, Inc. All rights reserved
6、. * Printed in U.S.A. COPYRIGHT SAE International (Society of Automotive Engineers, Inc)Licensed by Information Handling ServicesAS8007 -2- 3.5 Self-Test Provision: The instrument shall have test capabilities to confirm the operation of the elec- tricd output signal to the aural warning device. 3.6
7、Maximum Speed Signal Accuracy: 3.6.1 The instrument shall generate and maintain its output signal when the maximum operating speed is achieved or exceeded, and shall operate to the following tolerance relative to that maximum operating speed curve. The output signal shall be removed when the speed f
8、alls below the maximum operating speed curve to the same tolerance, a) For curve sections based on airspeed in knots, Calibrated or equivalent, O to plus G knots (11 km/hr) in excess of the limit speed value. b) Por curve sections based on Mach Number, O to plus , O10 Mach in excess of the limit Mac
9、h number value, 3. G. 2 The above tolerances are applicable for a minimum environmental temperature range of +20“ C through +55“ C (+68“ F through 1131“ F) and in the mounting position defined in the manufacturers installation ins tructions. 3.6.3 For environmental temperatures fram c20“ to -30C fro
10、m 155C to +71“C the tolerance of the output signal shall not exceed: a) Por curve sections based on airspeed in knots, calibrated or equivalent, O to plus 8 knots (15 km/hr) of the maximum speed value. b) For curve section based on Mach number, O to plus O. O15 Mach of the maximum Mach number value.
11、 3.6.4 In those cases where the Over Speed Warning Instrument function is part of an air speed or an air speed/Mach number indicator, the performance specified in 3.6.1, 3.6.2, and 3.6.3 shall be applied to the indicated air speed or Mach number displayed relative to the maximum speed displayed by t
12、he instrument, The performance tolerances specified in 3.6.1, 3.6.2, and 3.6.3 shall not be exceeded relative to the maximum operating speed curve for the instrument. 3.7 Operating Range: 3,7.1 The altitude range for all Over Speed Warning Instruments shall start at -1000 ft (-305 m) pressure altitu
13、de and the upper pressure altitude limit shall be applicable to the aircraft and shall be indicated on the nameplate. 3.7.2 The working airspeed range shall start at least 30 knots (55.56 km/hr) below the lowest airspeed value defined in the maximum operating speed curve, and shall extend at least 5
14、0 knots (93 km/hr) above the highest airspeed value defined in the maximum operating speed curve. 3.8 Aircraft Identification: The aircraft type, model number, and configuration for which the Over Speed Warning instrument has been calibrated and for which it performs its intended function, shall be
15、clearly marked on the instrument nameplate and in the manufacturers installation instructions. Each aircraft type, model and configuration has a defined maximum operating limit speed curve. 3.9 Power Loss: 3.9.1 If electrical power is used as the means to operate any portion of the Over Speed Warnin
16、g Instrument, provisions shail be incorporated in the instrument to detect the loss of this power. An indication of the loss of electrical operating power shall be provided in a positive manner. An output signal equiva- lent to a maximum speed limit warning is one acceptable means of indicating the
17、loss of power. COPYRIGHT SAE International (Society of Automotive Engineers, Inc)Licensed by Information Handling ServicesSAE AS*8007 78 W 8357340 O034036 T W -3- 1 AS8007 3.9.2 Power loss to the instrument from an external source, e.g. aural warning power, shall not require a power loss signal from
18、 the instrument as in 3.9.1. 3.10 Fire Hazard: Except for small parts (such as hobs, fasteners, seals, grommets, and small electrical parts) that would not contribute significantly to the propagation of a fire, all materials used must be self-extinguishing when tested in accordance with the requirem
19、ents of Federal Aviation Regulation 25.1359 (d) and Appendix !IFTf thereto, with the exception that materials tested may be configured in accordance with paragraph (b) of Appendix Ttf or may be configured as used. 4. PERFORMANCE UNDER STANDARD CONDITIONS 4.1 Standard Atmospheric Conditions: Unless o
20、therwise specified herein, all tests shall be conducted at atmospheric conditions specified in paragraph 3.4 of DO-160. (Environmental Conditions and Test Procedures for Airborne Electronics/Electrical Equipment and Instruments, dated Feb. 28, 1975). 4.2 Attitude: Unless otherwise specified herein,
21、all tests shall be conducted with the instrument in its normal operating position as defined in the manufacturers installation instructions. 4.3 Power Conditions: Unless otherwise specified herein, all individual performance tests shall be conducted at the power ratings defined by the manufacturer i
22、n the installation instructions for the instrument. 4.4 Vibration to Minimize Friction: 4.4.1 Reciprocating Engine Powered Aircraft: Unless otherwise specified, tests shall be conducted with the equipment subjected to a maximum vibration of 0.005 in. (0.127 mm) total excursion at any frequency from
23、20 to 35 Hertz, provided the equipment is mounted in its noimal operating pasition. 4.4.2 Turbine Powered Aircraft: Unless otherwise specified, tests shall be conducted with the equipment subjected to a maximum vibration of O. O01 in. (O. 025 mm) total excursion at any frequency from 10 to 60 Hertz,
24、 provided the equipment is mounted in its normal operating position. NOTE: If vibration exceeding the values specified above is required during normal operation in order to meet the accuracy requirements specified in this performance standard, it shall be the responsibility of the equipment manu- fa
25、cturer to either provide such vibration internally to the equipment or notify the user that such vibration is required to be applied to the equipment, when installed in an aircraft. 4.5 Perormance Tests: The instrument shall be tested to demonstrate compliance with 3.4, 3.5, 3.6, 3.9 of this standar
26、d. 4.5.1 The performance tests specified shall be conducted in accordance with the requirements specified by the manufacturer, and at least three test points in each maximum allowable speed curve section shall be included to assure conformance to the curve sections. When the curve contains reversal
27、in direc- tion, e. g., airspeed transition to Mach No., the reversal point shall be tested to assure that the transition occurs at the correct altitude level. 4.6 Balance Error (Attitudel: If the instrument is subjected to Balance Error (Mechanical balance), the instrument shall be tested in the fol
28、lowing positions, and the performance as specified in 4.6.1 and 4.6.1.1, shaU be met. 1) 2) 3) Normal operating position (as specified by the instrument manufacturer) Instrument rotated clockwise around its X (longitudinal) axis, 90“ from its normal position. Instrument rotated clocks and at appropr
29、iate airspeed values to adequagly represent the maximum operating speed curve for the subject aircraft, as defined below. 4.10.1 For MOS curve sections based on air speed, at each specified altitude level the applied static pressure shall be held constant and the applied differential pressure varied
30、. First by slowly increasing the differential pressure (airspeed) until an output signal is generated. The output signal shall be gen- erated within the requirements of 3.6.1 (a) or 3.6.1 (b) as applicable. Then the airspeed shall be increased by 20 knots (37 km/hr) and the signal shall remain on. T
31、he differential pressure shall then be slowly decreased until the warning signal just goes off. The output signal shall have gone off for values below the nominal maximum speed as defined by the maximum operating limit speed curve. 4.10.2 For selected values of maximum operating Mach number and alti
32、tude, the altitude level shall be held constant and the differential pressure shall be increased until an output signal has just been generated. The differential pressure shall be readjusted so that the output signal just goes off and the differential pressure shall now be held at that point. The al
33、titude level shall then be increased (pressure lowered) until the output signal just comes on. The requirements of 3.6.1 (b) shaU be met, The altitude level shall then be lowered (pressure increased) until the output signal just goes off. The output signal shall have remained on for the performance
34、as defined by 3.6.1 (b). 5. PERFORMANCE STANDARD UNDER ENVIRONMENTAL CONbITIONS 5.1 When the Over Speed Warning Instrument forms part of an aircraft system, such as an Air Data Com- puter, the Over Speed Warning function shall meet the performance requirement specified in Sections 3 and 4 herein for
35、 the environmental conditions specified for that aircraft system. 5.1.1 When the Over Speed Warning Instrument is independent of any aircraft system, the manufacturer shail define the exact. environmental conditions and/or categories of R. T. C. A. DO-160 Appendix under which the equipment will perf
36、orm to the requirements of this standard. The applicable environmental condition and categories shail be specified in the manufacturers installation instructions or on the equipment nameplate. 5.1.2 Unless otherwise specified by the manufacturer, the measurement procedures applicable to a determina-
37、 tion of the performance of the instrument under environmental conditions shall be as set forth in R. T. C. A., Document DO-160, entitled llEnvironrnental Conditions and Test Procedures for Airborne Electronic/Electrical Equipment and Instruments, dated 28 February 1975. 5.2 Environmental Categories
38、: The environmental categories appropriate to the installation of this instru- ment in the individual airframe shall be defined by the manufacturer in the installation instructions and/or as marked on the instrument in accordance with R. T. C.A. , DO-160, Appendix “A“ as applicable, and shall be the
39、 environmental categories to which the instrument shall have been tested and approved to. Environmenhl conditions and categories which Mer from those defined in Appendix “A1 of DO-160 shall be clearly defined in the manufacturers installation instructions. 5.2.1 Performance tests which are required
40、after subjection to test environments may be conducted after exposure to several environmentd conditions. 5.2.2 The equipment shall be subjected to the specified environmental conditions as per the procedures de- fined in R.T. C.A., DO-160, and shall not be damaged by being subjected to these enviro
41、nmental tests. COPYRIGHT SAE International (Society of Automotive Engineers, Inc)Licensed by Information Handling Services- _-_ _ _._ _ _ SAE AS*B007 78 8357340 0034037 5 AS8007 I -6- i, 2.3 The following list of environmental test categories and conditions are considered as the minimum test require
42、ments: a) b) Temperature/Altitude Tests (DO-160 applicable categories, paragraph section 4. O). Temperature Variation Tests (DO-160, paragraph section 5. O). c) Humidity Test (DO-160, paragraph section 6. O). d) Shock Tests (DO-160, paragraph section 7. O). e) Vibration Tests (DO-160 Applicable cate
43、gories, paragraph section 8. O). f) Magnetic Effect (DO-160 applicable class, paragraph section 15. O). g) Power input Test (DO-160 applicable categories, paragraph section 16. O). h) Voltage Spare Conducted Test (DO-160 applicable categories, paragraph section 17. O). i) Audio Frequency Conducted s
44、usceptibility Test (DO-160, paragraph section 18. O). j) Induced Signai Susceptibility Test (DO-160, applicable categories, paragraph section 19. O). ir) Decompression (DO-160, paragraph section 4.6.2). PREPARED BY SAE COMMITTEE A-4, AIRCRAFT INSTRUMENTS COPYRIGHT SAE International (Society of Automotive Engineers, Inc)Licensed by Information Handling Services
