1、Designation: F3179/F3179M 16Standard Specification forPerformance of Aeroplanes1This standard is issued under the fixed designation F3179/F3179M; the number immediately following the designation indicates the yearof original adoption or, in the case of revision, the year of last revision. A number i
2、n parentheses indicates the year of last reapproval.A superscript epsilon () indicates an editorial change since the last revision or reapproval.1. Scope1.1 This specification establishes the airworthiness designstandards associated with general aeroplane performance.1.2 This specification is applic
3、able to small aeroplanes asdefined in Terminology F3060.1.3 The applicant for a design approval shall seek theindividual guidance to their respective civil aviation authority(CAA) body concerning the use of this specification as part ofa certification plan. For information on which CAA regulatorybod
4、ies have accepted this specification (in whole or in part) asa means of compliance to their small aircraft airworthinessregulations (hereinafter referred to as “the Rules”), refer to theASTM Committee F44 webpage (www.astm.org/COMMITTEE/F44.htm) which includes CAA website links.1.4 UnitsThe values s
5、tated in either SI units or inch-pound units are to be regarded separately as standard. Thevalues stated in each system may not be exact equivalents;therefore, each system shall be used independently of the other.Combining values from the two systems may result in noncon-formance with the standard.1
6、.5 This standard does not purport to address all of thesafety concerns, if any, associated with its use. It is theresponsibility of the user of this standard to establish appro-priate safety and health practices and determine the applica-bility of regulatory limitations prior to use.2. Referenced Do
7、cuments2.1 ASTM Standards:2F3060 Terminology for AircraftF3173 Specification for Handling Characteristics of Aero-planesF3174/F3174M Specification for Establishing OperatingLimitations and Information for Aeroplanes3. Terminology3.1 Refer to Terminology F3060.4. Performance Requirements4.1 General:4
8、.1.1 Unless otherwise prescribed, the performance require-ments of this specification shall be met for:4.1.1.1 Still air and standard atmosphere.4.1.1.2 Ambient atmospheric conditions for high-speedLevel 1 and 2 aeroplanes and all Level 3 and 4 aeroplanes.4.1.2 Performance data shall be determined o
9、ver not lessthan the following conditions for all aeroplanes except foraeroplanes with VS0 45 KCAS:(1) Airport altitude from sea level to 3084 m 10 000 ft;(2) The temperature from standard to 30C 86F abovestandard or the maximum ambient atmospheric temperature atwhich compliance with the cooling pro
10、visions of is shown, iflower;(3) With any means for controlling the engine cooling airsupply in the position used in the engine cooling tests;(4) The available propulsive thrust shall correspond toengine power, not exceeding the approved power, less:(a) Installation losses.(b) The power absorbed by
11、the accessories and servicesappropriate to the particular ambient atmospheric conditionsand the particular flight condition.4.1.2.1 The performance, as affected by engine power orthrust, shall be based on a relative humidity:(1) Of 80 % at and below standard temperature.(2) From 80 % at the standard
12、 temperature, varying lin-early down to 34 % at the standard temperature plus 28C plus50F.4.1.3 Unless otherwise prescribed in determining the takeoffand landing distances, changes in the aeroplanesconfiguration, speed, and power shall be made in accordancewith procedures established by the applican
13、t for operation inservice. These procedures shall be able to be executed consis-tently by pilots of average skill in atmospheric conditionsreasonably expected to be encountered in service.4.1.4 Takeoff and landing distances shall be determined ona smooth, dry, hard-surfaced runway.NOTE 1The effect o
14、n these distances of operation on other types ofsurfaces (for example, grass and gravel) when dry, may be determined orderived, and these surfaces listed in the aeroplane flight manual in1This specification is under the jurisdiction ofASTM Committee F44 on GeneralAviation Aircraft and is the direct
15、responsibility of Subcommittee F44.20 on Flight.Current edition approved Feb. 1, 2016. Published March 2016. DOI: 10.1520/F3179_F3179M-16.2For referenced ASTM standards, visit the ASTM website, www.astm.org, orcontact ASTM Customer Service at serviceastm.org. For Annual Book of ASTMStandards volume
16、information, refer to the standards Document Summary page onthe ASTM website.Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States1accordance with Specification F3174/F3174M.4.1.5 For high-speed Level 3 aeroplanes and all Level 4aeroplanes,
17、 the following also apply:4.1.5.1 Unless otherwise prescribed, the applicant shallselect the takeoff, en route, approach, and landing configura-tions for the aeroplane;4.1.5.2 The aeroplane configuration may vary with weight,altitude, and temperature to the extent they are compatible withthe operati
18、ng procedures required by 4.1.5.3;4.1.5.3 Unless otherwise prescribed, in determining thecritical engine-inoperative takeoff performance, takeoff flightpath, the accelerate-stop distance, changes in the aeroplanesconfiguration, speed, and power shall be made in accordancewith procedures established
19、by the applicant for operation inservice;4.1.5.4 Procedures for the execution of discontinued ap-proaches and balked landings associated with the conditionsprescribed in 4.12.3.4 and 4.17.3 shall be established; and4.1.5.5 The procedures established under 4.1.5.3 and 4.1.5.4shall:(1) Be able to be c
20、onsistently executed by a crew ofaverage skill in atmospheric conditions reasonably expected tobe encountered in service,(2) Use methods or devices that are safe and reliable, and(3) Include allowance for any reasonably expected timedelays in the execution of the procedures.4.2 Stalling Speed:4.2.1
21、VS0and VS1are the stalling speeds or the minimumsteady flight speeds in knots (KCAS) at which the aeroplane iscontrollable with:4.2.1.1 The propulsive thrust not greater than zero at thestalling speed, or, if the resultant thrust has no appreciableeffect on the stalling speed, with engine(s) at mini
22、mum flightthrust and throttle(s) closed with:(1) The propeller(s) in the takeoff position;(2) The aeroplane in the configuration existing in the test,in which VS0and VS1are being used;(3) The center of gravity in the position that results in thehighest value of VS0and VS1; and(4) The weight used whe
23、n VS0or VS1are being used as afactor to determine compliance with a required performancestandard.4.2.2 VS0and VS1shall be determined by flight tests usingthe procedure and meeting the flight characteristics specified inthe appropriate stall handling characteristics testing.4.3 Takeoff Speeds:4.3.1 T
24、he rotation speed, VR, is the speed at which the pilotmakes a control input with the intention of lifting the aeroplaneout of contact with the runway or water surface.4.3.1.1 For low-speed Levels 1, 2, and 3 multienginelandplanes, VRshall not be less than the greater of 1.05 VMCor1.10 VS1.4.3.1.2 Fo
25、r single-engine landplanes, VRshall not be lessthan VS1.4.3.1.3 For seaplanes and amphibians taking off from water,VRmay be any speed that is shown to be safe under allreasonably expected conditions, including turbulence and com-plete failure of the critical engine.4.3.2 The speed at 15 m 50 ft abov
26、e the takeoff surfacelevel shall not be less than:4.3.2.1 For low-speed Level 1 aeroplanes with VS0 45knots, not less than 1.3 VS1;4.3.2.2 For low-speed Levels 1, 2, and 3 multiengineaeroplanes, the highest of:(1) A speed that is shown to be safe for continued flight (oremergency landing, if applica
27、ble) under all reasonable ex-pected conditions, including turbulence and complete failure ofthe critical engine;(2) 1.10 VMC;or(3) 1.20 VS1.4.3.2.3 For Level 1 with a VS0 45 knots and all Levels 2and 3 single-engine aeroplanes, the higher of:(1) A speed that is shown to be safe under all reasonablye
28、xpected conditions, including turbulence and complete enginefailure, or(2) 1.20 VS1.4.3.3 For high-speed multiengine aeroplanes and all Level 4aeroplanes, the following apply:4.3.3.1 The value, V1, shall be established in relation to VEFas follows:(1) The value, VEF, is the calibrated airspeed at wh
29、ich thecritical engine is assumed to fail. The value, VEF, shall beselected by the applicant but shall not be less than 1.05 VMCdetermined under Specification F3173 or, at the option of theapplicant, not less than VMCGdetermined under SpecificationF3173.(2) The takeoff decision speed, V1, is the cal
30、ibrated air-speed on the ground at which, as a result of engine failure orother reasons, the pilot is assumed to have made a decision tocontinue or discontinue the takeoff. The takeoff decision speed,V1, shall be selected by the applicant but shall not be less thanVEFplus the speed gained with the c
31、ritical engine inoperativeduring the time interval between the instant at which thecritical engine is failed and the instant at which the pilotrecognizes and reacts to the engine failure, as indicated by thepilots application of the first retarding means during theaccelerate-stop determination of 4.
32、5.4.3.3.2 The rotation speed, VR, in terms of calibratedairspeed, shall be selected by the applicant and shall not be lessthan the greatest of the following:(1) V1;(2) 1.05 VMCdetermined under Specification F3173;(3) 1.10 VS1;or(4) The speed that allows attaining the initial climb-outspeed, V2, befo
33、re reaching a height of 11 m 35 ft above thetakeoff surface in accordance with 4.6.4.3.3.3 For any given set of conditions, such as weight,altitude, temperature, and configuration, a single value of VRshall be used to show compliance with both the one-engine-inoperative takeoff and all-engines-opera
34、ting takeoff require-ments.F3179/F3179M 1624.3.3.4 The takeoff safety speed, V2, in terms of calibratedairspeed, shall be selected by the applicant so as to allow thegradient of climb required in 4.12 but shall not be less than1.10 VMCor less than 1.20 VS1.4.3.3.5 The one-engine-inoperative takeoff
35、distance, using anormal rotation rate at a speed 5 knots less than VR, establishedin accordance with 4.3.3.2, shall be shown not to exceed thecorresponding one-engine-inoperative takeoff distance, deter-mined in accordance with 4.12 and 4.7, using the establishedVR. The takeoff, otherwise performed
36、in accordance with 4.6,shall be continued safely from the point at which the aeroplaneis 11 m 35 ft above the takeoff surface and at a speed not lessthan the established V2minus 5 knots.4.3.3.6 The applicant shall show, with all engines operating,that marked increases in the scheduled takeoff distan
37、ces,determined in accordance with 4.7, do not result from over-rotation of the aeroplane or out-of-trim conditions.4.4 Takeoff Performance:4.4.1 For low-speed Level 1 aeroplanes with VS0 45 knots,the distance required to takeoff from a dry, level, hard surfaceand climb over a 15 m 50 ft obstacle sha
38、ll not exceed 500 m1640 ft for still air and a standard atmosphere using speedsdetermined in accordance with 4.3.1 and 4.3.2 at sea level with:4.4.1.1 The engine(s) operating within approved operatinglimitations, and4.4.1.2 The cowl flaps in the normal takeoff position.4.4.2 For low-speed Level 1 ae
39、roplanes with VS045ktandlow-speed Levels 2 and 3 aeroplanes, the distance shall bedetermined that is required to takeoff and climb to a height of15 m 50 ft above the takeoff surface for each weight, altitude,and temperature within the operational limits established fortakeoff using speeds determined
40、 in accordance with 4.3.1 and4.3.2 with:(1) Takeoff power on each engine,(2) Wing flaps in the takeoff position(s), and(3) Landing gear extended.4.4.3 For high-speed aeroplanes and all Level 4 aeroplanes,takeoff performance, as required by 4.5 through 4.7, shall bedetermined with the operating engin
41、e(s) within approvedoperating limitations.4.5 Accelerate-Stop DistanceFor high-speed multiengineaeroplanes and all Level 4 aeroplanes, the accelerate-stopdistance shall be determined as follows:4.5.1 The accelerate-stop distance is the sum of the dis-tances necessary to:4.5.1.1 Accelerate the aeropl
42、ane from a standing start to VEFwith all engines operating;4.5.1.2 Accelerate the aeroplane from VEFto V1, assumingthe critical engine fails at VEF;4.5.1.3 Come to a full stop from the point at which V1isreached.4.5.2 Means other than wheel brakes may be used todetermine the accelerate-stop distance
43、s if that means it is:4.5.2.1 Safe and reliable,4.5.2.2 Used so that consistent results can be expected undernormal operating conditions,4.5.2.3 Such that exceptional skill is not required to controlthe aeroplane.4.6 Takeoff PathFor high-speed multiengine aeroplanesand all Level 4 aeroplanes, the ta
44、keoff path is as follows:4.6.1 The takeoff path extends from a standing start to apoint in the takeoff at which the aeroplane is 457 m 1500 ftabove the takeoff surface at or below which height thetransition from the takeoff to the en-route configuration shall becompleted.4.6.1.1 The takeoff path sha
45、ll be based on the proceduresprescribed in 4.1;4.6.1.2 The aeroplane shall be accelerated on the ground toVEFat which point the critical engine shall be made inoperativeand remain inoperative for the rest of the takeoff;4.6.1.3 After reaching VEF, the aeroplane shall be acceler-ated to V2.4.6.2 Duri
46、ng the acceleration to speed, V2, the nose gearmay be raised off the ground at a speed not less than VR.However, landing gear retraction shall not be initiated until theaeroplane is airborne.4.6.3 During the takeoff path determination, in accordancewith 4.6.1 and 4.6.2:4.6.3.1 The slope of the airbo
47、rne part of the takeoff pathshall not be negative at any point;4.6.3.2 The aeroplane shall reach V2before it is 11 m 35 ftabove the takeoff surface and shall continue at a speed as closeas practical to, but not less than V2, until it is 122 m 400 ftabove the takeoff surface;4.6.3.3 At each point alo
48、ng the takeoff path, starting at thepoint at which the aeroplane reaches 122 m 400 ft above thetakeoff surface, the available gradient of climb must not be lessthan 1.2 %;4.6.3.4 Except for gear retraction and automatic propellerfeathering, the aeroplane configuration shall not be changed,and no cha
49、nge in power that requires action by the pilot may bemade, until the aeroplane is 122 m 400 ft above the takeoffsurface.4.6.4 The takeoff path to 11 m 35 ft above the takeoffsurface shall be determined by a continuous demonstratedtakeoff.4.6.5 The takeoff path from 11 m 35 ft above the takeoffsurface shall be determined by synthesis from segments.4.6.5.1 The segments shall be clearly defined and related todistinct changes in configuration, power, and speed;4.6.5.2 The weight of the aeroplane, the configuration, andthe power shall be assume
