1、 AEROSPACESTANDARDSubmitted for recognition as an American National StandardVERTICAL VELOCITY INSTRUMENT(Rate-of-Climb)SAE Technical Standards Board Rules provide that: “This report is published by SAE to advance the state of technical and engineering sciences. Theuse of this report is entirely volu
2、ntary, and its applicability and suitability for any particular use, including any patent infringement arising therefrom, is thesole responsibility 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 wri
3、ttencomments and suggestions.Copyright 1996 Society of Automotive Engineers, Inc.All rights reserved. Printed in U.S.A.Land Sea Air and SpaceFor Advancing MobilityThe Engineering SocietyINTERNATIONAL400 Commonwealth Drive, Warrendale, PA 15096-0001Issued 1978-10Revised 1996-09REV.AS8016 AFOREWORDCha
4、nges in the revision are format/editorial only.1. SCOPE:1.1 Types:This AS covers Vertical Velocity Instruments which display the rate of change of pressure altitudeof an aircraft, as follows:Type A - Direct reading, self-contained, pressure actuatedType B - Electrically or electronically operated, s
5、elf-contained, pressure actuatedType C - Electrically or electronically operated, input from a remote pressure sensor1.2 Range:The range of operation of the instrument and the altitude range when applicable shall be asmarked on the instrument face or nameplate.1.3 Purpose:This SAE Aerospace Standard
6、 (AS) establishes the minimum performance standards for verticalvelocity instruments for aircraft use.SAE AS8016 Revision A- 2 -2. APPLICABLE DOCUMENTS:The following documents shall form a part of this AS to the extent specified herein:2.1 Radio Technical Commission for Aeronautics (RTCA) Document D
7、O-160, “EnvironmentalConditions and Test Procedures for Airborne Electronic/Electrical Equipment and Instruments,”dated 28 February 1975. Copies may be obtained from the RTCA Secretariat, 1717 H Street,N.W., Washington, DC 20006.2.2 U.S. Standard Atmosphere, 1962. Copies may be obtained from the RTC
8、A Secretariat, at theaddress given in 2.1.2.3 “Rules for SAE Use of SI (metric) Units - SAE document J916b,” dated July 1976. Copies maybe obtained from SAE, 400 Commonwealth Drive, Warrendale, PA 15096.3. GENERAL STANDARDS:3.1 Indicating Means:The vertical velocity shall be indicated by means of a
9、pointer, dial tape, drum, or other type ofmoving element, or by a digital display with appropriate direction indication. Relative motion ofthe index with respect to the scale, or of the direction indicator (either the index or the scale maybe the moving element) must be clockwise, up, or to the righ
10、t for ascending vertical velocity.3.2 Display:3.2.1 Graduation (If Applicable): The graduations shall be arranged to provide the maximumreadability consistent with the accuracy of the instrument, with at least 100 ft/minute(30 m/minute), graduations to 1000 ft/minute (300 m/minute). Major graduation
11、s shall be at1000 ft/minute (300 m/minute), intervals and the minor graduations shall be at 500 ft/minute(150 m/minute) intervals.3.2.2 Numerals (If Applicable): The display shall include sufficient numerals to permit quick andpositive identification of each graduation.3.2.3 Limits: The indicating m
12、eans shall be limited in such a way that the moving element will notmove more than (a) 10 degrees for circular display, or (b) 0.25 inch (.6 mm) for linear displaysbeyond the greatest graduation in both ascending and descending directions. When theinstrument is pegged at its maximum rate indication,
13、 the direction of that indication, whetherascending or descending, shall be clear and unambiguous. If a digital display is used, apositive indication shall be provided on the display when the vertical velocity of the aircraftexceeds the instrument readout capability.SAE AS8016 Revision A- 3 -3.2.4 V
14、isibility: The indicating means must be visible from all points within a space defined by asurface generated by lines making an angle of at least 30 degrees with the perpendicular to thedisplay surface and diverging from the perimeter of the instrument window aperture. If integrallighting is provide
15、d, it must make all indicia within the instrument easily readable and not allowany objectionable stray light to come from the instrument.3.2.5 Zero Setting: Means for manually zeroing the instrument shall be provided for Type A, andshall be optional for Types B and C. The zero adjust range shall be
16、not less than 400 ft/minuteup and down movement. These methods shall meet the requirements of 3.5.3.3 Fire Resistance:Except for small parts (such as knobs, fasteners, seals, grommets, and small electrical parts) thatwould not contribute significantly to the propagation of a fire, all materials used
17、 must be self-extinguishing when tested in accordance with the requirements of Federal Aviation Regulation25.1359(d) and Appendix F thereto, with the exception that materials tested may be configured inaccordance with paragraph (b) of Appendix F or may be configured as used.3.4 Reflectance, Cover Gl
18、ass:The total reflectance of the instrument cover glass including the integral lighting wedge, ifapplicable, shall not exceed 10% of the incident light. This reflectance applies over the visiblelight spectrum from 450 millimicrons to 600 millimicrons, and over an incident solid angle of 60perpendicu
19、lar to the viewing plane.3.5 Accessibility of Controls:Controls not normally adjusted in flight must not be readily accessible to flight personnel.3.6 Acceleration Sensitive Device:Any device used in the instrument to superimpose an acceleration-sensitive indication of verticalvelocity on the pressu
20、re-actuated indication of vertical velocity shall be fail safe and shall notdegrade the normal operation of the instrument.3.7 Interchangeability:Instruments which are identified with the same manufacturers part number shall beinterchangeable.3.8 Effects of Tests:Unless otherwise stated, the applica
21、tion of the specified tests shall not produce a condition whichwould be detrimental to the continued performance of the instrument.SAE AS8016 Revision A- 4 -3.9 Mounting Attitude:Should the capability of an instrument to meet its stated performance be limited to a specificrelationship of its axes to
22、 the axes of the aircraft, this limitation must be stated. Instrumentsincorporating acceleration-sensitive devices must have these attitude limitations stated.3.10 Accuracy:Accuracy requirements for this standard are related to the instrument display or electrical outputfor a specified sensor input.
23、 For Type A and B instruments, the accuracy relates output topressure input to the instrument, since they are self-contained. For Type C instruments, theaccuracy relates output to the input at the remote sensor; if matching of the instrument to theremote sensor is necessary to maintain the required
24、overall accuracy, this must be so stated onthe instrument nameplate.3.11 Power Malfunction Indication:For Type B and C instruments, means must be incorporated in the instrument to indicate theloss of signal to the instrument and/or the loss of electrical power to the instrument. Theindicating means
25、must indicate a failure or malfunction in a positive manner.4. PERFORMANCE STANDARDS UNDER STANDARD CONDITIONS:The test conditions applicable to a determination of the performance of vertical velocity instrumentsare set forth in Appendix A of this AS. All instruments shall be tested in accordance wi
26、th themanufacturers recommendations. The manufacturer shall conduct sufficient tests to provecompliance with these Minimum Performance Standards. Test equipment used to demonstrate therequired performance shall be described and its accuracy specified.4.1 Zero Setting:The pointer zero setting mechani
27、sm, where applicable, shall operate smoothly throughout itsrange, which shall not be less than 400 fpm (120 m/minute) up and down movement.4.2 Scale Error:4.2.1 When subjected to the rates of change of pressure specified in Table 1 for the instrumentrange, Types A and B instruments shall meet the to
28、lerances specified in that table.4.2.2 Type C indicators must be tested in a manner equivalent to the testing of Type A and B. Inputsignals equivalent to the pressure input to the sensor for the instrument range must be used,and the error from the sensor input to the indicator output must be in acco
29、rdance with Table 1.SAE AS8016 Revision A- 5 -TABLE 1Test Rate Test RateStandard Altitude Standard Altitude Ascent and Descent Ascent and Descent Tolerance ToleranceTest Interval Test Interval Feet Per Minute Meters Per Minute Feet Per Minute Meters Per MinuteFeet Meters (ft/minute) (m/minute) (ft/m
30、inute) (m/minute)Between 2,000 to 2,500 600 to 750 500 150 100 302,000 to 3,000 600 to 900 1,000 305 200 612,000 to 4,000 600 to 1200 2,000 610 300 912,000 to 5,000 600 to 1500 3,000 915 300 912,000 to 6,000 600 to 1800 4,000 1220 400 1222,000 to 7,000 600 to 2400 5,000 1525 500 152Between 15,000 to
31、 17,000 4500 to 5200 2,000 610 300 9115,000 to 19,000 4500 to 5800 4,000 1220 400 122Between 28,000 to 30,000 8550 to 9150 2,000 610 300 9128,000 to 32,000 8550 to 9800 4,000 1220 400 1224.3 Pointer Damping, Types A and B:The pointer damping of the instrument on ascent and descent, when timed over t
32、he followingtest interval, shall be between 3 and 12 seconds:TABLE 2Instrument Range Instrument Range Test Interval Test Intervalft/minute m/minute ft/minute m/minute0-2000 610 1800-180 549-61All greater ranges All greater ranges 2000-200 610-61This test may be conducted by applying slight vacuum or
33、 pressure to the static pressureconnection of the instrument, instantaneously releasing this vacuum or pressure, and measuringthe time for the pointer to cover the test interval as it approaches zero. Vibration shall be appliedduring this test. (See Appendix A.)Where other than exponential type damp
34、ing is used, the pointer shall not lag by more than theequivalent of 12 seconds in the above test, and the pointer oscillation shall be damped to anamplitude no greater than exists with the 3 second exponential damping as specified above.4.4 Friction, Types A and B:With no vibration applied, the ins
35、trument shall be tested in a manner similar to that used in thepointer lag test, as in 4.3. The pointer shall move smoothly toward zero and shall stop within200 ft/minute (61 m/minute) of zero.SAE AS8016 Revision A- 6 -4.5 Leakage Type A and B; Type C, as Applicable:With a suction of 15 inches of me
36、rcury (50.7 kPa) applied to the static pressure connection, theleakage shall not cause more than 0.05 inch of mercury (0.17 kPa) pressure drop during a1-minute period. With a pressure of 10 inches of mercury (33.8 kPa) applied to the staticpressure connection, the leakage shall not cause more than 0
37、.05 inch of mercury (0.71 kPa)pressure drop during a 1-minute period. The total volume of the static pressure system duringthese tests shall be 100 10 inches3(1.6 L .16 L).4.6 Attitude Error:With the instrument vented to ambient pressure and the pointer approximately zeroed, thedifference between th
38、e pointer indication in its normal operating position and when it is in anyother position shall not exceed 50 ft/minute (15 m/minute). Instruments incorporatingacceleration-sensitive devices shall be allowed to stabilize at each reading attitude beforecompliance with this requirement is tested.4.7 A
39、cceleration-Sensitive Device Testing:It shall be the responsibility of the instrument manufacturer to specify the method of test in orderto show compliance with 3.6.4.8 Overpressure (Type A):Within 5 minutes following a rate of descent of 30,000 ft/minute (9150 m/minute) the instrumentmust return to
40、 plus or minus 100 ft/minute (30 m/minute) of the initial reading. The test altitudeshall be within the altitude range specified for the instrument.5. MINIMUM PERFORMANCE STANDARDS UNDER ENVIRONMENTAL CONDITIONS:Unless otherwise specified herein, the measurement procedures applicable to a determinat
41、ion ofthe performance under environmental conditions are set forth in Radio Technical Commission forAeronautics (RTCA) Document No. DO-160 entitled, “Environmental Conditions and TestProcedures for Airborne Electronic/Electrical Equipment and Instruments,“ dated 28 February 1975.Performance tests wh
42、ich must be made after subjection to test environments may be made afterexposure to several environmental conditions. The order of tests must be in accordance withparagraph 3.2 of DO-160. The test procedures specified or referenced are satisfactory for use indetermining the performance of vertical v
43、elocity instruments under normal and extremeenvironmental conditions; equipment category is to be as specified by the manufacturer. Alternateapproved test procedures that provide equivalent results may be used.5.1 Magnetic Effect:When subjected to the test of DO-160, paragraph 15.0, the instrument m
44、ust meet therequirements of Class A or Z.SAE AS8016 Revision A- 7 -5.2 Temperature:5.2.1 Low Temperature: When subjected to the tests of DO-160, paragraph 4.4, the instrument mustoperate electrically and mechanically, and the requirements of 4.2 of this AS must be met. After subjection to this test,
45、 the requirements of 4.2 and 4.4 of this AS shall be met.5.2.2 High Temperature: When subjected to the tests of DO-160, paragraph 4.5, the instrumentmust operate electrically and mechanically, and the requirements of 4.2 of this AS must be met.After subjection to this test, the requirements of 4.2 a
46、nd 4.4 of this AS shall be met.5.2.3 Temperature Variation: When subjected to the tests of DO-160, paragraph 5.0, the instrumentmust operate electrically and mechanically and the requirements of 4.2 of this AS must be met.After subjection to this test, the requirements of 4.2 and 4.4 of this AS must
47、 be met.5.3 Altitude:When subjected to the tests of DO-160, paragraph 4.6, the instrument must operate electricallyand mechanically, and the requirements of 4.2 of this AS must be met.5.4 Vibration:When subjected to the tests of DO-160, paragraph 8.0, the instrument must operate electricallyand mech
48、anically, and the requirements of 4.2 of this AS must be met. After subjection to thistest, the requirements of 4.2 and 4.4 of this AS must be met. Vibration test requirements byaircraft type and equipment location shall be as specified by the manufacturer.5.5 Shock Test:After subjection to the test
49、s of DO-160, paragraph 7.0, the instrument must operate electricallyand mechanically, and the requirements of 4.2 and 4.4 of this AS must be met.5.6 Humidity:Immediately following subjection to the tests of DO-160, paragraph 6.3.1, standard humidityenvironment, the requirements of 4.2 and 4.4 of this AS must be met.5.7 Power Input (Type B and C):5.7.1 Normal Electrical Input Variation Test: When subjected to the tests of DO-160, paragraphs16.3.1.1 or 16.3.2.1, the instrument must operate electrically and mechanically and meet therequirements of 4.2 of t
