SAE AS 8014-1986 Minimum Performance Standard Stall Warning Equipment.pdf

1、SAE AS*8OL4 8b 8357340 0034087 9 W AEROSPACE STANDARD The Engineerng Society e A =For Advancing Mobility Land Sea Air and Space 400 COMMONWEALTH DRIVE. WARRENOALE, PA 15096 Submitted for recognition as an American National Standard 14 IN I MU14 PERF ORtIANCE STANDARD STALL WARNING EQUIPMENT F “01- O

2、3 AS 8014 Issued 9-8-86 1. PURPOSE: . This Aerospace Standard establishes the minimum performance requi rements for Sta1 1 Warni ng Equipment. _. 2. SCOPE: 2.1 Definition: This Aerospace Standard covers two basic Stall Warning Systems, one measures air flow and pressure distribution on the airfoil a

3、nd the other measures the angle of airflow with respect to an arbitrary reference line. Each type of system includes, as a minimum, a sensor and the means for activating a device which warns the pilot of an impending stall. 2.2 Sensor Category Usage: Sensors will be categorized for operation in eith

4、er of the fo 1 oui ng: Category A - For use on aircraft certified for flight into known icing condi ti ons . Category B - For use on aircraft not certified for flight into known i ci ng condi ti ons. 3 GENERAL STANDARDS : 3.1 Stall Warning Signal: The signal must be capable of continuously activatin

5、g the warning device during conditions under which warning is required. 3.2 Interchangeability: 3.2.1 System and components which are identified with the same part number shall be completely interchangeable. 3.2.2 If the equipment components require matching for proper operation and to ineet the req

6、uireiiients of this standard, they shall be identified in a nianner which will assure proper matching. Instal lation instructions issued by the manufacturer shall indicate these matchi ng requi rements . SAE Technical Board Rules provide that: “This repart is published by SAE to advance the state of

7、 technical and engineering sciences. The use of this report isentirely voluntary, and its applicability and suitability for any particular use, including any patent infringement arising therefrom, is the sole responsibility of the user.“ SAE reviews each technical report at least every five years at

8、 which time it may be reaffirmed, revised, or cancelled. SAE invites your written comments and suggestions. Copyright 1986 Society of Automotive Engineers, Inc. All rights reserved. Printed in U.S.A. - - SAE AS*OL4 86 8357340 0034070 5 m AS 8014 I -AC -0 Paae 2 3.2.3 Aircraft Identification: The air

9、craft type and model number if applicable for which the Stall Warning Equipment has been calibrated and for which it performs its intended function, shall be clearly marked on the equipment namepl ate and in the manufacturers instal 1 ation instructions. category shall al so be identified (i .e, TSO

10、-C54-A). The TSO 3.3 Adjustments: Adjustments which are not nomiially adjusted in flight shall not be readily accessible to flight personnel, when the equipment is iristal led in accordance with the equipment manufacturers instructions. 3.4 Precipitation: The sensor shall be designed so that it will

11、 continue to function properly and give reliable stall warning during flight through rait of 150 mm/lir, 3.5 Drainage: Drain holes shall be provided for a sensor where necessary and such holes shall not result in any errors exceeding those specified in Paragraph 4. 3.6 Fire Resistance: Except for sm

12、all parts (such as knobs, fasteners, seals, grommets, and small el ectrical parts) that Wou1 d not contri bute significantly to the propagation of a fire, all materials must be sel f-extinguishing when tested in accordance with the requirements of Federal Aviation Regulation 25.1359 (d) and Appendix

13、 F thereto, with the exception that materials tested may be configured in accordance with paragraph (b) of Appendix F or may be configured as used. 4. PERFORMANCE STANDARUS: Un1 esc otherwise specified, al 1 tests for performance may be conducted with the equipment (individual coinponents) subjected

14、 to a vibration of 0.002 to 0.005 in. double amplitude at a frequency of 1500 to 2000 cycleslmin to minimize friction. 4.1 Actuation Point: Warning Signal and shall sense the conditions which determine the actuation The Stall Warning Equipment must generate the Stall point consSclent with the airfra

15、me manufacturers stall data and to the equipment manufacturers defined to1 erances over the envi ronmental range of the system. required, while in the case of a pressure distribution device a force accuracy will be required. The actuation point may be adjustable, in which case the manufacturer shall

16、 declare the range and tolerances to which the sigrial initiation point may be adjusted. Signal with the accuracy specified in Paragraph 4.1 under conditions of up to 5“ of Yaw in each direction. In the case of an airstream device, an accuracy in degrees is 4.2 Sideslip: The Stall Warning Equipment

17、must generate the Stall Warning 4.3 Electrical Power Monitor: Equipment which uses power to compute the stall warning actuation point must incorporate means to provide adequate power monitoring. operation of the equipment, the monitor shall provide, in a positive manner, a wariing signal to indicate

18、 the power failure or Eialfunction, When sufficietit power is not available, to ensure proper SAE AS*BO14 Bb 83573qO 0034071 7 Page 3 -a I AS 8014 4.4 Stall Warning Computer (If Applicable): 4.4.1 Aircraft Configuration: If coiripensation for aircraft configuration (flap extension, slats, etc. 1 cha

19、nge is necessary, the Computer must be capable of accepting signals from the Stall Warning Sensor (or computed signal from other sources) and other selected transmi tters (F1 ap, Airspeed, Gear, etc.), and must provide an output for the Stall Uarning signalling device with the accuracy specified in

20、Paragraph 4.1. designed so that a failure in it (with the exception of shorted wires on the input leads) will not adversely affect the operation of other devices which furnish sigrials to it. The Computer shall be 4.4.2 Secondary Outputs: Tne Sta1 1 Warning Computer may have other outputs, that are

21、derived within the Stall WarRing Equiprnent; however, they must be sufficiently isolated from the Stall Warning Signal -such that any- failure modes of the secondary outputs do not affect the Stall Warning performance of Paragraph 4.1. 5. EbiVIRONKENTHL CONDITIONS: and to demonstrate that the equipm

22、ent is designed to meet these speci f icati ons . The fol1 owing tests are for qual i fication purposes 5.1 Test Requi reinents : The fol 1 owing envi ronmental tests shall be performed under the environmental conditions set forth in Radio Technical Commission for Aeronautics (RTCA) Document DO-1 60

23、6, entitled, “Environmental Conditions and Test Procedures for Airborne El ectronic/El ectrical Equipment and Instruments“, dated 20 July 1984. with Paragraph 3.2, of DO-160B. Ttie order of tests must be in accordance The test procedures specified or referenced are satisfactory for use in determinin

24、g the performance of Stall Warning Equipment under normal and extreme envi ronmental conditions. Al ternate approved test procedures that provide equivalent results may be used. The manufacturer must specify the categorized 1 imi ts for each of the fol 1 owing environments. must meet the performance

25、 standards in Paragraph 4 of this report under the envi ronmerital tests 1 i sted bel ow: The equipment a) Temperature - Altitude b) Temperature Vari ati on c) tiuinidity d) Shock e) Vibration f) Power Input 9) Vol tage Spike- Conducted -.-_ . - SAE AS*8OLL1 Ab 8357340 0034072 7 AS 8014 I h) i ) Iii

26、duced Signal Suscepti bi 1 i ty j) Radio Frequency Susceptibil ity k) m) Explosion 5.2 Icing Tests: In addition to those tests in Paragraph 5.1, the icing tests described iri Paragraphs 5.2.1 and 5.2.2 shall be performed on all Category “A“ sensors as defined in Paragraph 2.2 Conducted Audio Frequer

27、icy Susceptibility Test Emission of Radio Frequency Enersy 5.2.1 Anti-Icing: The sensor shall be tested in an icing wind tunnel at an indicated airpseed of 175 t 25 knots, and an ambient temperature of -10“ - + 5C. The following conditTotis shall be maintained during the test: Liquid Water Content i

28、 .o - t 5% gm/l:13 Droplet Size 12.5 - t 5% microns The test speciineti shall remain free of interfering ice accumulation for a period of 15 min after stability of above conditions is achieved. 5.2.2 e-Icing: Under the conditions of Paragraph 5.2.1, turn off the power to the heaters and allow the ex

29、posed part of the element to build up approximately 1/4 in. of ice. Apply heater power and the time required to clear the ice cap shall not be more than 2 min. 5.3 Hermetically Sealed Equipment: The tests described in Paragraphs 5.3.1 and 5.3.2 apply to hermetically sealed equipment only. 5.3.7 Ther

30、mal Shock Test: exposure to water at 85“ i- 2C without the evidence of inoicture penetration or damage to coating or enclosure. shall consist o% immersing the component in water at 85“ i- 2C for a period of 30 min and then within 5 s of removal from the Kath, the component shall be immersed for a pe

31、riod of 30 min in the other bath maintained at 5“ t 2C. This cycle shall be repeated continuously, one cycle following tTie other until four cycles have been completed. Following this test, the component shall be subjected to the Sealing Test specified in Paragraph 5.3.2. result of this test. The co

32、mponent shall be subjected to four cycles of Each cycle of the test No component leakage shall occur as a a SAE AS88OLq 86 8357340 0034073 O Page 5 AS 8014 5.3.2 Seal Test: The equipment shall be immersed in a suitable liquid such as water. reduced to approximately 1-1/4 in, of mercury (Hg) and main

33、tained for one min or until air bubbles cease to be given off by the liquid, whichever is longer. Any bubbles coming from within the equipment case shall be considered as leakage and shall be cause for rejection. Bubbles which are the result of entrapped air in the various exterior parts of the case

34、 shall not be considered as leakage. Other test methods which provide evidence equal to the iinmersion test of the integrity of the equipments seal may be used. If the equipment incorporates non-hermetically sealed appurtenances, such as a case extension, these appurtenances may be removed prior to the Seal Test Eie absolute pressure of the air above the liquid shall then be Tne absolute pressure shall then be increased to 2-1/2 in. Hg. PREPARED BY SAE COMblITTEE A-4, AIRCRAFT I N ST RUNE NTS