Table 7 - Procedures Condition Power Wings Level TrimSpeed Altitude 1 Refer to Note Trimmed (but not to exceed VNE or VMO/MMO) Altitude for highest dynamic pressure (q) 3 Refer to Note VO Low 4 Refer to Note VO Highest attainable approved altitude Note: 75 percent maximum continuous power or maximum power (reciprocating engine) or maximum cruise power (turbine).
(1) Compliance may be demonstrated by measuring the normal acceleration achieved with the limiting stick force (50 pounds for wheel controls, 35 pounds for stick controls) or by establishing the stick force per g gradient and extrapolating to the appropriate limit. Linear stick force gradients may be extrapolated up to 0.5g maximum. Non-linear stick force gradients that indicate a possible gradient lightening at higher g levels should not be extrapolated more than
0.2g.
c. Data Acquisition and Reduction. The following should be recorded for each test condition:
(1) Weight/c.g.;
(2) Pressure altitude;
(3) Outside air temperature;
(4) Engine power parameters;
(5) Trim setting;
(6) Elevator force;
(7) Normal acceleration at c.g.; and
(8) Gear/flap position.
Note: The test data should be presented in stick force versus g plots. Figure 17 below shows a sample plot. Test results should be compared to the requirements of § 23.155(a).
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/ / , ;, / >- / / ,I ~ / ,,, J , 11/16/2011 AC 23-8C Figure 17 - Stick Force Per G 50 40 30 LBS PULL 20 10 0 CAS= ________
c.g.= ________
0.5 1.0 1.5 2.0 2.5 3.0 3.5 4.0 NORMAL ACCELERATION - G's
d. Stick Force Per G, § 23.155(c). An increase in pull force should be required to produce an increase in normal acceleration throughout the range of required load factor and speed. Any reduction in control force gradient with change in load factor should not be so large or abrupt as to significantly impair the ability of the pilot to maintain control of normal acceleration and pitch rate. The elevator cont rol force should increase progressively with increasing load factor.
(1) Flight tests to satisfy the above must be performed at sufficient points to establish compliance with § 23.155(c) throughout the normal flight envelope. During these tests, the load factor should be increased until either:
(i) The intensity of buffet provides a strong and effective deterrent to further increase of load factor;
(ii) Further increase of load factor requires an elevator control force in excess of 150 pounds for a wheel control or 125 pounds for a stick control or is impossible because of the limitations of the control system; or
(iii) The positive limit maneuvering load factor is achieved.
8. § 23.157 Rate of Roll.
a. Explanation. The purpose of this requirement is to ensure an adequately responsive airplane in the takeoff and approach configuration.
b. Procedures.
(1) Bank Angle. The airplane should be placed in a 30-degree bank and rolled through an angle of 60 degrees. For example, with the airplane in a steady 30-degree left bank, roll through a 30-degree right bank and measure the time. Sections 23.157(b) and (d) should be accomplished by rolling the airplane in both directions.
(2) Controls. Sections 23.157(a) and (c) permit using a favorable combination of controls. The rudder may be used as necessary to achieve a coordinated maneuver.
(3) Weight. The "W" in the formulas is the maximum takeoff weight.
Section 5. Trim
1. § 23.161 Trim.
a. Explanation. The trim requirements ensure that the airplane will not require exceptional skill, strength, or alertness on the pilot's part to maintain a steady flight condition.
The tests require the airplane to be trimmed for hands-off flight for the conditions specified. It should be noted that for single-engine airplanes, lateral-directional trim is required at only one speed, thus ground adjustable tabs are acceptable. If appropriate, lateral baggage loading and fuel asymmetry should be considered in this evaluation. While ground adjustable tabs are acceptable, they are typically installed on simple single engine airplanes and aren’t effective for addressing control forces with significant asymmetry loadings. Applicants should either provide a way to set the ground adjustable tab for specific loadings or install an air adjustable tab. For multiengine airplanes, directional trim is required for a range of speeds.
b. Procedures.
(1) Actuator Settings. Trim actuator travel limits should be set to the minimum allowable.
(2) Altitude and Power. Tests for trim should be conducted in smooth air. Those tests requiring use of maximum continuous power should be conducted at as low an altitude as practical to ensure attaining the required power.
(3) Weight and C.G. Longitudinal trim tests should be conducted at the most critical combinations of weight and c.g. Forward c.g. is usually critical at slow speeds and aft c.g.
critical at high speeds.
Section 6. Stability
1. § 23.171 General.
a. Explanation.
(1) Required Stability. The stability portion of part 23 is primarily concerned with static stability. No quantitative values are specified for the degree of stability required. This 78
allows simple test methods or qualitative determinations unless marginal conditions are found to exist. The regulations merely require that the airplane be stable and that it have sufficient change in control force, as it is displaced from the trimmed condition, to produce suitable control feel for safe operation.
(2) Forces. The magnitude of the measured fo rces should increase with departure from the trim speed up to the speed limits specified in § 23.175 or up to the 40 pound force limit specified in § 23.173. The stick forc e variation with speed changes should be stable. In other words, a pull force required to fly slower than trim and a push force required to fly faster than trim and the gradient should be clearly perceptible to the pilot at any speed between 1.3 VS1 and VNE or VFC/MFC. Figure 18 below shows an exam ple of cruise configuration:
PULL (+) STICK FORCE PUSH (-) FRSR +> 40 KNOTS OR 15%VTRIM FRSR +> 40 KNOTS OR 15%VTRIM VTRIM j 11/16/2011 AC 23-8C Figure 18 - Static Longitudinal Stability Data
(i) Speed Range = Greater of + 40 knots (kts) or 15 percent VTRIM + free return speed range (FRSR)
(ii) At speeds below 1.3 VS1 for normal, utility, and acrobatic airplanes, and at speeds below 1.4 VS1 for commuter airplanes, the slope need not be stable, refer to figures 19 and 20. The pull forces can decrease in magn itude with speed decrease down to, but not including, the stall speed VS1; however, the pull force shall in no case fall below zero before the stall is reached.
(iii) Instrumented force measurements are required if there is any uncertainty in the qualitative assessment of the force gradients.
Figure 19 - Low Speed Instabilities; Normal, Utility, and Acrobatic Airplanes FRSR +> 40 KNOTS OR 15% V TRIM FRSR +> 40 KNOTS OR 15% V TRIM PULL (+)
• TRI
SA SAEL (-) 81
FRSR +50 KNOTS FRSR +50 KNOTS PULL (+) VIRIM
STICK BREAKOUT
FORCE FORCE
1.4 VS1 + FRSR PUSH (->
b. Procedures. None required for this section.
2. § 23.173 Static Longitudinal Stability.
a. Explanation.
(1) Demonstration Conditions. The general requirements of § 23.173 are determined from a demonstration of static stability under the conditions specified in § 23.175.
(2) Control Frictions. Section 23.173(b) effectively limits the amount of control friction that will be acceptable since excessive friction would have a masking effect on stability.
If autopilot or stability augmentation systems are of such a design that they tend to increase the friction level of the longitudinal control system, critical static longitudinal stability tests should be conducted with the system installed. Control cable tensions should be set to the maximum.
Note: A procedure that could be used is shown in figure 21 below:
Vpe,M,c
PULL X X t (-r) X .. , I STICK
V, FORCE I I
1.3V51 ~I I
v., 1• FRSR 11 1 PUSH t (·) VNE X= FRSR +(>40 KNOTS OR 15% Vrn,Ml 11/16/2011 AC 23-8C Figure 21 – Static Longitudinal Stability Data over Complete Speed Range
(3) Stable Slope. Section 23.173(c) is extremely genera l. It requires the test pilot's best judgment as to whether the stable slope of the stick force curve versus speed is sufficiently steep so that perceptibility is satisfactory for the safe operation of the airplane.
(4) Maximum Allowable Speed. Should be taken to mean V FE, VLE, VNE, and VFC/MFC, as appropriate.
b. Procedures. Refer to the guidance for § 23.175.
3. § 23.175 Demonstration of Stat ic Longitudinal Stability.
a. Explanation. Section 23.175 requires that, for cruise configuration, static longitudinal stability tests be conducted at representative cruising speeds at high and low altitude up to VNE or VFC/MFC, as appropriate, except that the trim speed need not exceed VH.
Section 23.173(a) states that static longitudinal stability must be shown at any speed that can be obtained; therefore, the longitudinal stability demonstration must cover the entire range from VS1 to VNE or VFC/MFC. Figure 21 shows typical coverage of the speed range in cruise with overlapping data. Mid-range trim points should include speed for best endurance, range, and high-speed cruise.
(1) VS1. Trim at VS1 + (>40 kts or 15 percent) + an estimate of the free return speed range (FRSR), perform static longitudinal stability tests from the trim speed within the speed range ensuring that the aircraft does not stall.
(2) VH. Determine V H at lowest altitude at MCP, perform longitudinal static stability tests within the prescribed speed range but do not exceed VNE.
(3) Additional trim points. Select additional trim points, for example, speed for best range and endurance, and so forth, until the speed range covered by data, refer to figure 22.
(4) Highest operating altitude. Go to highest operating altitude, depending on pressurization, oxygen requirements, and so forth, trim at VH, and repeat the test to a maximum speed of VFC/MFC or VNE, whichever comes first. Note that a stable slope above VNE, or VFC/MFC, or outside the (>40 kts or 15 percent) is desired, but not required.
b. Procedures.
(1) Section 23.l75(a) Climb .
(i) Stabilized Method. The airplane should be tr immed in smooth air for the conditions required by the regulation. Tests should be conducted at the critical combinations of weight and c.g. Normally, light weight and aft c.g. are critical.
(a) After observing trim speed, apply a pull force and stabilize at a slower speed. Continue this process in increments of 10 to 20 knots, depending on the speed spread being investigated, until reaching minimum speed for steady unstalled flight. At some stabilized point, the pull force should be gradually relaxed to allow the airplane to slowly return toward trim speed and zero stick force. Depending on the amount of friction in the control system, the eventual speed at which the airplane stabilizes will be somewhat less than the original trim speed. As required by § 23.173, the new speed, cal led free-return speed, must be within 10 percent (7.5 percent for commuter category airplanes in cruise) of the trim speed.
(b) Starting again at the trim speed, push forces should be applied and gradually relaxed in the same manner as previously described at speeds up to 115 percent of the trim speed, and the same determination should be made.
(c) The flight test data band should be ± 2,000 feet from the trim altitude to minimize changes in power/thrust with altitude at a fixed throttle setting that could affect static longitudinal stability. High performance airplane s in the climb configuration sometimes require a number of iterations to stay within the data band. Or if the airplane has a very high thrust to weight ratio, it may need 3,000 feet as used for part 25 airplanes (refer to AC 25-7).
(2) Section 23.175(b), Cruise
(i) Acceleration-Deceleration Method. The stabilized flight test technique described in paragraph (1)(i) above is suitable for low performance airplanes or airplane configurations with low climb performance. The acceleration-deceleration method is particularly suitable for airplanes with high cruise speed. The airplane is trimmed at the desired airspeed and the power/thrust setting noted. Powe r/thrust is then increased to accelerate the airplane to the extreme speed of the desired data band. The power/thrust is then reset to the original trim power setting and the airplane allowed to decelerate at a constant altitude back to the original trim speed. Longitudinal static stability data is obtained during the deceleration to trim speed with the power and the elevator trim position the same as the original trim data point.
The data below trim speed is obtained in a similar manner by reducing power to decelerate the airplane to the lowest speed in the data band, reset the power to trim conditions, and record the data during the level acceleration back to trim speed. If, because of thrust/drag relationships, the airplane has difficulty returning to the trim data point, small altitude changes within ± 2,000 feet can also be used to coax an airplane acceleration-deceleration back to trim speed, but level flight 84
is preferred if possible. The data to be measured approximately every ten knots are speed and elevator stick force.
(3) Other Stability Test Procedures. The balance of the static longitudinal stability requirements are flown using either the stabilized method or the acceleration-deceleration method, but using the configurations, trim points, and speed ranges prescribed in § 23.175.
c. Data Acquisition and Reduction. Force readings can be made with a hand-held force gauge, fish scale, or by electronic means, and plotted against calibrated airspeed to determine compliance with the regulation. Refer to figure 22 for an example of the data plot.
Collect test data within a reasonable altitude band of the trim point altitude, such as ±2,000 feet.
Stick force measurements must be made unless:
(1) Changes in speed. Changes in speed are clearly reflected by changes in stick forces; and
(2) Maximum forces. The maximum forces obtained under §§ 23.173 and 23.175 are not excessive.
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11/16/2011 AC 23-8C Figure 22 - Static Longitudinal Stability Plot (Cruise Condition) 20 15STICK FORCE (POUNDS) 10 PULL 5 0 5 PUSH 10 70 90 110 130 150 170 190
1.3 VS1 VNE
CALIBRATED AIRSPEED (KNOTS)
4. § 23.177 Static Direction and Lateral Stability.
a. Explanation.
(1) Purpose. The purpose of this section is to require positive dire ctional and lateral stability and to verify the absence of rudder lock tendencies.
(2) Directional Stability. In § 23.177(a), the determination of "appropriate" wings level sideslip (previously referred to as skid) angles will depend on sound judgment in considering such things as airplane size, maneuverability, control harmony, and forces to determine the magnitude of wings level sideslip angles that the airplane will probably experience in service. Tests are conti nued beyond these "appropriate" angles up to the point where full rudder control is used or a force limit of 150 pounds, as specified in § 23.143, is reached. The rudder force may lighten, but may not reverse. The rudder force tests are conducted at speeds between 1.2 VS1 and VA. The directional stab ility tests are conducted at speeds from 1.2 VS1 to VNE or the maximum allowable speed for the configuration, whichever is limiting.
(3) Lateral Stability (Dihedral Effect). The static lateral stability tests (reference § 23.177(b)) take a similar approach since the basic requirement must be met up to maximum sideslip angles "appropriate to the type of airplane." Up to this angle, the airplane must demonstrate a tendency to raise the low wing when the ailerons are freed. The static lateral stability may not be negative at 1.2 VS1 in the takeoff configuration and 1.3 VS1 in other configurations.
(4) Forces. The requirement of § 23.177(d) is to be tested at a speed of 1.2 VS1 and larger than "appropriate" sideslip angles. At angles up to those that require full rudder or aileron 86
control, or until the rudder or aileron force limits specified in the table in § 23.143 are reached, the aileron and rudder force may lighten but may not reverse.
(5) Maximum Allowable Speed. Should be taken to mean V FE, VLE, VNE, and VFC/MFC, as appropriate.
(6) Autopilot or Stability Augmentation Systems (SAS). If autopilot or SAS are of such a design that they tend to increase the friction levels of the lateral and directional controls systems, then critical lateral and directional tests should be conducted with those systems installed, but not operating.
b. Procedures.
(1) Altitude. The tests should be conducted at the highest practical altitude considering engine power and aerodynamic damping.
(2) Loading. The airplane should be loaded to a nominal condition. Large lateral imbalance may mask lateral stability.
(3) Directional. To check static directional stabi lity with the airplane in the desired configuration and stabilized on the trim speed, the airplane is slowly yawed in both directions keeping the wings level with ailerons. When the rudder is released, the airplane should tend to return to straight flight. Some deadband around neutral is acceptable. Refer to paragraph
23.161. for guidance on ground adjustable tabs.
(4) Lateral. To check lateral stabil ity with a particular configuration and trim speed, conduct sideslips at the trim speed by maintaining the airplane's heading with rudder and banking with ailerons. Refer to paragraph 23.161 for guidance on ground adjustable tabs.
Section 23.177(b) requires the slip angle to be appropriate to the type of airplane and the bank angle to be at least l0 degrees. Some airplane s cannot maintain a heading in a slip with a l0 degree bank angle. In those cases , the slip should be performed with no less than a l0 degree bank and full opposite rudder and the heading allowed to vary. When the ailerons are released, the low wing should return to level. Some d eadband around neutral is acceptable. The pilot should not assist the ailerons during this evaluation. The pilot should hold the rudder as the wings level. For cases where there is not enough rudder to hold a steady heading, with bank angle, the pilot should use full rudder until the bank angle lowers to that where a steady heading can be maintained, then the rudder should be modulated as required to maintain the steady heading as the wings level.
c. Data Acquisition. Data recorded should be sufficient for showing compliance.
5. § 23.179 Stability. Reserved.
6. § 23.181 Dynamic Stability.
a. Explanation. Longitudinal Dynamic Stability.
(1) Short and Long Period Modes. Most normally configured airplanes will exhibit two distinct longitudinal modes of motion. The short period mode is the first response experienced after disturbing the airplane from its trim condition with the elevator control. It involves a succession of pitch acceleration, pitch rate, and pitch attitude changes that occur so rapidly the airspeed does not change significantly. Angle-of-attack will change in response to the pitching motions and produce accompanying changes in normal acceleration. Vertical gusts 87