4-25 Table 4-3. Test Maneuver—§ 25.143(i)(2) Step Maneuver 1 Start with the airplane in trim, or as near as possible to being in trim, at the most critical of the following trim speeds:
(1) Trim speed 1.23 VSR, target speed not more than 1.23 VSR.
(2) Trim speed VFE, target speed not less than VFE - 20 knots.
2 Pull up to a suitable pitch attitude, then—
(1) Push over in a continuous maneuver (without changing trim) to reach zero g normal load factor or, if limited by elevator control authority (or other design characteristic), the lowest load factor obtainable at the target speed, as the airplane’s pitch attitude passes through approximately level flight (that is, through the horizon), and
(2) Perform this maneuver with idle power or thrust and with go-around power or thrust.
4.9.4.3.4 Test maneuver for showing compliance with § 25.143(i)(3): Conduct steady heading sideslips to full rudder input, 180 pounds rudder force, or full lateral control authority (whichever comes first) at a trim speed of
1.23 VSR and with the power or thrust needed for a -3° flight path angle.
4.9.5 Controllability Prior to Activation and Operation of the Ice Protection System.
The following is an example of an acceptable test program for showing compliance with § 25.25.143(j).
Maneuvers
4.9.5.1 For the configurations, speeds, and power settings listed below, with the ice accretion specified in the requirement, trim the airplane at the specified speed, conduct a pull-up maneuver to 1.5 g and pushover maneuver to
0.5 g, and show that longitudinal control forces do not reverse.
4.9.5.1.1 High lift devices retracted configuration (or holding configuration if different), holding speed, power or thrust for level flight.
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4.9.5.1.2 Landing configuration, VREF for non-icing conditions, power or thrust for landing approach. If necessary, limit the pull-up maneuver to the point at which stall warning occurs.
4.10 Longitudinal Control, § 25.145.
4.10.1 No specific quantitative evaluations are required for demonstrating compliance with§ 25.145(b) and (c). Qualitative evaluations should be combined with the other testing. Review results of tests on the uncontaminated airplane for any cases of marginal compliance. All tests showing marginal compliance should be repeated with ice accretions on the airplane.
4.10.2 Acceptable Test Program.
The following specifications represent an example of an acceptable test program for compliance with § 25.145(a).
Maneuvers
4.10.2.1 The holding ice accretion should be used.
4.10.2.2 The airplane is at a medium to light weight, aft center-of-gravity position, with symmetric fuel loading.
4.10.2.3 In the configurations listed below, trim the airplane at 1.3 VSR. Reduce speed approximately 1 knot per second using elevator control to 1 second past stall warning and demonstrate prompt recovery to the trim speed using elevator control.
4.10.2.3.1 High lift devices retracted configuration, maximum continuous power or thrust.
4.10.2.3.2 Maximum lift landing configuration, maximum continuous power or thrust.
4.11 Directional and Lateral Control, § 25.147.
To show compliance with § 25.147, applicants should combine qualitative evaluations with the other testing (for example, the roll tests described in paragraphs 4.9.2.3.1 and
4.9.2.4 of this AC). Review the results of the tests on the uncontaminated airplane for any cases of marginal compliance. All tests showing marginal compliance should be repeated with ice accretions on the airplane.
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4.12 Trim, § 25.161.
4.12.1 To show compliance with this requirement, the applicant should combine qualitative evaluations with the other testing. Review results of tests on the uncontaminated airplane for any cases of marginal compliance. All tests showing marginal compliance should be repeated with ice accretions on the airplane. In addition, a specific check should be made to demonstrate compliance with § 25.161(c)(2).
4.12.2 Acceptable Test Program.
The following specifications represent an example of an acceptable test program for compliance with § 25.161(c)(2).
Maneuvers
4.12.2.1 The holding ice accretion should be used.
4.12.2.2 The airplane is at the most critical landing weight, with a forward center of gravity position and symmetric fuel loading.
4.12.2.3 In the maximum lift landing configuration, trim the airplane at the most critical of—
4.12.2.3.1 1.3 VSR1 at idle power or thrust, or
4.12.2.3.2 VREF with the power or thrust for a -3° flight path angle.
4.13 Stability—General, § 25.171.
To show compliance with this requirement, applicants should combine qualitative evaluations with the other testing. Each tendency to change speed when trimmed and a need for frequent trim inputs should be specifically investigated.
4.14 Demonstration of Static Longitudinal Stability, § 25.175.
4.14.1 To show compliance with § 25.175, the applicant should test each of the following cases. In general, it is not necessary to test in the cruise configuration at low speed (§ 25.175(b)(2)) or in the cruise configuration with landing gear extended (§ 25.175(b)(3)); nor is it necessary to test at high altitude. Maximum speed for substantiation of stability characteristics in icing conditions (as prescribed by § 25.253(c)) is the lowest of—
• 300 knots calibrated airspeed (CAS),
• VFC, or
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• A speed at which it is demonstrated that the airframe will be free of ice accretion due to the effects of increased dynamic pressure.
4.14.2 Acceptable Test Program.
The following specifications represent an example of an acceptable test program for demonstrating static longitudinal stability.
Maneuvers
4.14.2.1 The holding ice accretion should be used.
4.14.2.2 The airplane is at a high landing weight, aft center-of-gravity position, with symmetric fuel loading.
4.14.2.3 In the configurations listed in paragraphs 4.14.2.3.1 through 4.14.2.3.4 below, trim the airplane at the specified speed. The power or thrust should be set and stability demonstrated over the speed ranges as stated in § 25.175(a) through (d), as applicable.
4.14.2.3.1 Climb: With high lift devices retracted, trim at the speed for best rate of climb, except that the speed need not be less than 1.3 VSR.
4.14.2.3.2 Cruise: With high lift devices retracted, trim at VMO or 250 knots CAS, whichever is lower.
4.14.2.3.3 Approach: With the high lift devices in the approach position appropriate to the highest lift landing configuration, trim at 1.3 VSR.
4.14.2.3.4 Landing: With the highest lift landing configuration, trim at 1.3 VSR.
4.15 Static Lateral–Directional Stability, § 25.177.
4.15.1 Use steady heading sideslips to show compliance with the directional and lateral stability requirements. The maximum sideslip angles obtained should be recorded and may be used to substantiate a crosswind value for landing. (See paragraph 4.19 of this AC.) Section 25.177(c) requires directional and lateral control movements and forces to be substantially proportional to the angle of sideslip without reversing.
4.15.2 Acceptable Test Program.
The following specifications represent an example of an acceptable test program for demonstrating static directional and lateral stability.
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Maneuvers
4.15.2.1 The holding ice accretion should be used.
4.15.2.2 The airplane is at a medium to light weight, aft center-of-gravity position, with symmetric fuel loading.
4.15.2.3 In the configurations listed below, trim the airplane at the specified speed and conduct steady heading sideslips to full rudder authority, 180 pounds of rudder pedal force, or full lateral control authority, whichever comes first:
4.15.2.3.1 High lift devices retracted configuration: Trim at best rate-of-climb speed, but need not be less than 1.3 VSR.
4.15.2.3.2 Lowest lift takeoff configuration: Trim at the all-engines-operating initial climb speed.
4.15.2.3.3 Highest lift landing configuration: Trim at VREF.
4.16 Dynamic Stability, § 25.181.
If the uncontaminated airplane has no borderline compliance test results for § 25.181, dynamic stability tests with ice accretions on the airplane are not necessary. The applicant should combine qualitative evaluations with other testing. Each difficulty in achieving precise attitude control and each tendency to sustain oscillations in turbulence should be investigated.
4.17 Stall Demonstration, § 25.201/Stall Characteristics, § 25.203.
4.17.1 The applicant should conduct sufficient stall testing to demonstrate that the stall characteristics comply with the requirements of §§ 25.201 and 25.203. In general, it is not necessary to conduct a stall program that encompasses all weights, center-of-gravity positions, altitudes, high lift configurations, deceleration device configurations, straight and turning flight attitudes, and thrust or power settings. The applicant can establish a reduced test matrix based on a review of the stall characteristics of the uncontaminated airplane. However, additional tests may be necessary if—
4.17.1.1 The stall characteristics with ice accretion show a significant difference from those on the uncontaminated airplane,
4.17.1.2 The testing indicates borderline compliance, or
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4.17.1.3 The activation point of a stall identification system (for example, a stick pusher) is reset for icing conditions.
4.17.2 Acceptable Test Program.
Turning flight stalls at decelerations greater than 1 knot per second are not required.
Note that slow decelerations (much slower than 1 knot per second) may be critical on airplanes with anticipation logic in their stall protection system or on airplanes with low directional stability, where large sideslip angles could develop. The following specifications represent an example of an acceptable test program subject to the provisions outlined above.
Maneuvers
4.17.2.1 The holding ice accretion should be used.
4.17.2.2 The airplane should be loaded to a medium to light weight, aft center-of-gravity position, with symmetric fuel loading.
4.17.2.3 The tests should be conducted at the normal stall test altitude.
4.17.2.4 In the configurations listed in paragraphs 4.17.2.4.1 through 4.17.2.4.4 below, trim the airplane at the same initial stall speed factor used for stall speed determination. For power on stalls, use the power setting as defined in § 25.201(a)(2), but with ice accretions on the airplane. Decrease speed at a rate not to exceed 1 knot per second to stall identification and recover using the same recovery maneuver as for the uncontaminated airplane.
4.17.2.4.1 High lift devices retracted configuration: Straight/Power Off, Straight/Power On, Turning/Power Off, Turning/Power On.
4.17.2.4.2 Lowest lift takeoff configuration: Straight/Power On, Turning/Power Off.
4.17.2.4.3 Highest lift takeoff configuration: Straight/Power Off, Turning/Power On.
4.17.2.4.4 Highest lift landing configuration: Straight/Power Off, Straight/Power On, Turning/Power Off, Turning/Power On.
4.17.2.5 For the configurations listed in paragraphs 4.17.2.4.1 and 4.17.2.4.4 above, and each other configuration if deemed more critical, in 1 knot per second deceleration rates down to stall warning with wings level and power off, roll the airplane left and right up to 10° of bank using the lateral control.
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4.18 Stall Warning, § 25.207.
4.18.1 To show compliance with § 25.207, the applicant should assess stall warning in conjunction with stall speed testing and stall demonstration/characteristics testing (§§ 25.103, 25.201, and 25.203, and paragraphs 4.2 and 4.17 of this AC, respectively), and in tests with faster entry rates.
4.18.2 Normal Ice Protection System Operation.
The following specifications represent an example of an acceptable test program for stall warning in slow-down turns of at least 1.5 g and at entry rates of at least 2 knots per second:
Maneuvers
4.18.2.1 The holding ice accretion should be used.
4.18.2.2 The airplane should be loaded to a medium to light weight, aft center-of-gravity position, with symmetric fuel loading.
4.18.2.3 The test should be conducted at the normal stall test altitude.
4.18.2.4 In the configurations listed in paragraphs 4.18.2.4.1 through 4.18.2.4.3 below, trim the airplane at 1.3 VSR with the power or thrust necessary to maintain straight level flight. Maintain the trim power or thrust during the test demonstrations. Increase speed as necessary before establishing at least 1.5 g and a deceleration of at least 2 knots per second. Decrease speed until 1 second after stall warning and recover using the same recovery maneuver as for the uncontaminated airplane.
4.18.2.4.1 High lift devices retracted configuration.
4.18.2.4.2 Lowest lift takeoff configuration.
4.18.2.4.3 Highest lift landing configuration.
4.18.3 Stall Warning Prior to Activation and Operation of the Ice Protection System.
The following represents an acceptable means for showing compliance with § 25.207(h).
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Maneuvers
4.18.3.1 In the configurations listed in paragraphs 4.18.3.1.1 and 4.18.3.1.2 below, with the ice accretion specified in the requirement, trim the airplane at 1.3 VSR.
4.18.3.1.1 High lift devices retracted configuration: Straight Flight/Power Off.
4.18.3.1.2 Landing configuration: Straight Flight/Power Off.
4.18.3.2 At deceleration rates of up to 1 knot per second, reduce the speed until 1 second past stall warning, and demonstrate that stalling can be prevented using the same recovery maneuver as used for the uncontaminated airplane, without encountering any adverse characteristics (for example, rapid wing roll-off). If stall warning for the airplane with ice accretion is provided by a different means than it is for the airplane without ice accretion, the following requirements must be met:
4.18.3.2.1 Section 25.207(h)(3)(ii) requires that stalling be preventable even if the pilot takes no recovery action for at least 3 seconds after stall warning.
4.18.3.2.2 Section 25.207(i) requires that satisfactory stall characteristics be demonstrated if stall warning is provided by a different means in icing conditions than for non-icing conditions.
4.19 Wind Velocities, § 25.237. To show compliance with this requirement:
4.19.1 Crosswind landings with the landing ice accretion should be evaluated on an opportunity basis.
4.19.2 Results of the steady heading sideslip tests with landing ice may be used to establish the safe crosswind component of this requirement. If the flight test data show that the maximum sideslip angle demonstrated is similar to that shown with the uncontaminated airplane, and the flight characteristics (control forces and deflections, for example) are similar, then the non-contaminated airplane crosswind component test result is considered valid for icing conditions.
4.19.3 If results of the comparison discussed in paragraph 4.19.2 above are not clearly similar, and in the absence of a more extensive analysis, the applicant may use a conservative analysis based on results of the steady heading sideslip tests to establish the safe crosswind component value. The crosswind value may be estimated from:
4-33 𝑉𝐶𝑊 = 𝑉𝑅𝐸𝐹 ∗ sin(𝑠𝑖𝑑𝑒𝑠𝑙𝑖𝑝 𝑎𝑛𝑔𝑙𝑒)1.5 Where:
VCW is the crosswind component, and VREF is the landing reference speed appropriate to a minimum landing weight, and Sideslip angle is that demonstrated at VREF (see paragraph 4.15 of this AC).
4.20 Vibration and Buffeting, § 25.251.
To show compliance with this requirement:
4.20.1 Combine qualitative evaluations with the other testing, including speeds up to the maximum speed obtained in the longitudinal stability tests. (See paragraph 4.14 of this AC).
4.20.2 Demonstrate that the airplane is free from harmful vibration due to residual ice accumulation. This may be done in conjunction with the natural icing tests.
4.20.3 Evaluate an airplane with pneumatic deicing boots up to VDF/MDF, both with the deicing boots operating (including deicing boot inflation cycles) and not operating. It is not necessary to do this demonstration with ice accretions on the airplane.
4.21 Natural Icing Conditions, § 25.1419(b).
To show compliance with this requirement, the applicant should perform additional flight testing.
4.21.1 Whether flight testing has been performed with artificial or simulated ice accretions or in natural icing conditions, additional limited flight testing described in this section should be conducted in the natural atmospheric icing conditions specified in part 25, Appendix C, and, if necessary, in the icing conditions described in Appendix O. (AC 25-28 provides guidance on when it is necessary to perform flight testing in the natural atmospheric icing conditions of Appendix O). If flight testing with simulated ice accretions is the primary means for showing compliance, the objective of the tests described in this section is to corroborate the handling characteristics and performance results obtained in the flight testing with simulated ice accretions. Validating all aspects of predicted ice accretions through natural icing flight tests is not required. The flight testing should confirm the general physical characteristics and location of the ice accretions and their effect on airplane performance and handling characteristics. The applicant should make at least a qualitative assessment to confirm that the artificial ice accretions are conservative relative to ice accretions resulting from natural atmospheric icing conditions, and that ice in natural atmospheric icing conditions does not accrete in unexpected places.
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4.21.2 It is acceptable for some ice to be shed during the testing due to air loads or wing flexure, etc. However, the applicant should attempt to accomplish the test maneuvers as soon as possible after exiting the icing cloud in order to minimize atmospheric influences on ice shedding.
4.21.3 Acceptable Test Program.
During each of the maneuvers specified in paragraph 4.21.4 below, the behavior of the airplane should be consistent with that obtained with simulated ice accretions. There should be no unusual control responses or uncommanded airplane motions.
Additionally, during the level turns and bank-to-bank rolls, there should be no buffeting or stall warning.
Maneuvers
4.21.4 Ice Accretion Maneuvers.
4.21.4.1 Holding scenario.
4.21.4.1.1 The maneuvers specified in table 4-4. below should be carried out with ice accretions defined in paragraphs 4.21.4.1.2 and 4.21.4.1.3 below, which is representative of normal operation of the ice protection system:
4.21.4.1.2 Ice on unprotected parts. A target accretion thickness equivalent to the 45-minute dry air ice accretions on an unprotected part of the wing should be the objective. (A thickness of 2 inches is normally a minimum value, unless a lesser value is agreed to with the responsible ACO).
4.21.4.1.3 Ice on protected parts. The ice accretion thickness should be that resulting from normal operation of the ice protection system.
4.21.4.1.4 For airplanes with control surfaces that may be susceptible to jamming due to ice accretion (for example, elevator horns exposed to the air flow), the holding speed that is critical with respect to this ice accretion should be used.
4-35 Table 4-4. Holding Scenario—Maneuvers
4.21.4.2 Approach/Landing Scenario.
4.21.4.2.1 The maneuvers specified in table 4-5 of this AC should be carried out with successive accretions in different configurations on unprotected surfaces.
4.21.4.2.2 Each test condition should be accomplished with the ice accretion that exists at that point.
4.21.4.2.3 The final ice accretion (Test Condition 3) represents the sum of the amounts that would accrete during a normal descent from holding to landing in icing conditions.
4.21.5 For airplanes with unpowered elevator controls, unless the applicant can adequately substantiate the critical simulated ice accretion used to demonstrate compliance with the controllability requirement, the pushover test of paragraph 4.9.4.3.3 should be repeated with a thin accretion of natural ice.
4.21.6 Existing propeller speed limits or, if required, revised propeller speed limits for flight in icing, should be verified by flight tests in natural icing conditions.
Airplane Configuration Center-of- Gravity Position Trim Speed Maneuver Flaps up, Gear up Any position in the aft range Holding, except
1.3 VSR for the stall maneuver Level, 40° banked turn;
Bank-to-bank rapid roll, 30° - 30°;
Speedbrake extension, retraction;
Full straight stall (1 knot per second deceleration rate, wings level, power off) Flaps in intermediate positions, gear up Any position in the aft range
1.3 VSR Deceleration to the speed reached 3 seconds after activation of stall warning in a 1 knot per second deceleration Landing flaps, gear down Any position in the aft range VREF Level, 40° banked turn;
Bank-to-bank rapid roll, 30° - 30°;
Speedbrake extension, retraction (if approved);
Full straight stall (1 knot per second deceleration rate, wings level, power off)
4-36 Table 4-5. Approach/Landing Scenario—Maneuvers Test Condition Ice Accretion Thickness* Airplane Configuration Center-of- Gravity Position Trim Speed Maneuver — First 0.5 inch Flaps up, gear up Any position in the aft range Holding No specific test 1 Additional
0.25 inch
(0.75 inch total) First intermediate flaps, gear up Any position in the aft range Holding, except
1.3 VSR for the deceleration maneuver Level 40° banked turn;
Bank-to-bank rapid roll, 30°- 30°;
Speed brake extension and retraction (if approved);
Deceleration to the speed reached 3 seconds after activation of stall warning in a 1 knot per second deceleration.
2 Additional
0.25 inch
(1.00 inch total) Further intermediate flaps, gear up (as applicable) Any position in the aft range
1.3 VSR Bank-to-bank rapid roll, 30° - 30°;
Speed brake extension and retraction (if approved);
Deceleration to the speed reached 3 seconds after activation of stall warning in a 1 knot per second deceleration.
3 Additional
0.25 inch
(1.25 inch total) Landing flaps, gear down Any position in the aft range VREF Bank-to-bank rapid roll, 30° - 30°;
Speed brake extension and retraction (if approved), Bank to 40°;
Full straight stall (1 knot per second deceleration rate, wings level, power off).
* The indicated thickness is that accumulated on the parts of the unprotected airfoil most likely to accumulate ice.