--------------------------------------------------------------------------------------------------------------------------------------------------------
1.c...................  Climb.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.c.1.................  Normal Climb, all     3 kts     Clean...............  Flight test data is    X    X    X    X
                         engines operating.    airspeed, 5% or 100 FPM (0.5                          performance manual
                                               m/Sec.) climb rate.                         data is an
                                                                                acceptable
                                                                                alternative. Record
                                                                                at nominal climb
                                                                                speed and mid-
                                                                                initial climb
                                                                                altitude. Flight
                                                                                simulator
                                                                                performance must be
                                                                                recorded over an
                                                                                interval of at
                                                                                least 1,000 ft.
                                                                                (300 m).
--------------------------------------------------------------------------------------------------------------------------------------------------------

1.c.2.................  One engine            3 kts     For part 23           Flight test data is    X    X    X    X
                         Inoperative.          airspeed, 5% or 100 FPM (0.5    part 23. For part     performance manual
                                               m/Sec.) climb rate,   25 airplanes,         data is an
                                               but not less than     Second Segment        acceptable
                                               the climb gradient    Climb.                alternative. Test
                                               requirements of 14                          at weight,
                                               CFR part 23 or part                         altitude, or
                                               25, as appropriate.                         temperature
                                                                                limiting
                                                                                conditions. Record
                                                                                at nominal climb
                                                                                speed. Flight
                                                                                simulator
                                                                                performance must be
                                                                                recorded over an
                                                                                interval of at
                                                                                least 1,000 ft.
                                                                                (300 m).
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.c.3.................  One Engine            10%       Clean...............  Record results for               X    X
                         Inoperative En        time, 10% distance,                         (1550 m) climb
                                               10%                             segment. Flight
                                               fuel used.                                  test data or
                                                                                airplane
                                                                                performance manual
                                                                                data may be used.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.c.4.................  One Engine            3 kts     Approach............  Record results at      X    X    X    X   The airplane should
                         Inoperative           airspeed, 5% or 100 FPM (0.5                          defined in Appendix                       ice systems
                         conditions are        m/Sec.) climb rate,                         F of this part.                           operating normally,
                         authorized).          but not less than                           Flight test data or                       with the gear up
                                               the climb gradient                          airplane                                  and go-around flaps
                                               requirements of 14                          performance manual                        set. All icing
                                               CFR parts 23 or 25                          data may be used.                         accountability
                                               climb gradient, as                          Flight simulator                          considerations
                                               appropriate.                                performance must be                       should be applied
                                                                                recorded over an                          in accordance with
                                                                                interval of at                            the aircraft
                                                                                least 1,000 ft.                           certification or
                                                                                (300 m).                                  authorization for
                                                                                an approach in
                                                                                icing conditions.
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1.d...................  Cruise/Descent.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.d.1.................  Level flight          5% Time.  Cruise..............  Record results for a   X    X    X    X
                         acceleration.                                                     minimum of 50 kts
                                                                                speed increase
                                                                                using maximum
                                                                                continuous thrust
                                                                                rating or
                                                                                equivalent.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.d.2.................  Level flight          5% Time.  Cruise..............  Record results for a   X    X    X    X
                         deceleration.                                                     minimum of 50 kts.
                                                                                speed decrease
                                                                                using idle power.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.d.3.................  Cruise performance..  0.05 EPR  Cruise..............  May be a single                  X    X
                                               or 5%                           snapshot showing
                                               of N1, or 5% of Torque,                         flow or a minimum
                                               5% of                           of 2 consecutive
                                               fuel flow.                                  snapshots with a
                                                                                spread of at least
                                                                                3 minutes in steady
                                                                                flight.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.d.4.................  Idle descent........  3 kt      Clean...............  Record a stabilized,   X    X    X    X
                                               airspeed, 5% or 200 ft/min                            speed at mid-
                                               (1.0m/sec) descent                          altitude. Flight
                                               rate.                                       simulator
                                                                                performance must be
                                                                                recorded over an
                                                                                interval of at
                                                                                least 1,000 ft.
                                                                                (300 m).
--------------------------------------------------------------------------------------------------------------------------------------------------------

1.d.5.................  Emergency descent...  5 kt      N/A.................  Performance must be    X    X    X    X   The stabilized
                                               airspeed, 5% or 300 ft/min                            least 3,000 ft (900                       speed brakes
                                               (1.5m/s) descent                            m).                                       extended, if
                                               rate.                                                                                applicable, at mid-
                                                                                altitude and near
                                                                                Vmo speed or in
                                                                                accordance with
                                                                                emergency descent
                                                                                procedures.
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1.e...................  Stopping.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.e.1.................  Stopping time and     5% of     Landing.............  Record time and        X    X    X    X
                         distance, using       time. For distance                          distance for at
                         manual application    up to 4000 ft (1220                         least 80% of the
                         of wheel brakes and   m): 200                         total time from
                         no reverse thrust     ft (61 m) or 10%,                                  stop. Data is
                                               whichever is                                required for
                                               smaller. For                                weights at medium
                                               distance greater                            and near maximum
                                               than 4000 ft (1220                          landing weights.
                                               m): 5%                          Data for brake
                                               of distance.                                system pressure and
                                                                                position of ground
                                                                                spoilers (including
                                                                                method of
                                                                                deployment, if
                                                                                used) must be
                                                                                provided.
                                                                                Engineering data
                                                                                may be used for the
                                                                                medium gross weight
                                                                                condition.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.e.2.................  Stopping time and     5% time   Landing.............  Record time and        X    X    X    X
                         distance, using       and the smaller of                          distance for at
                         reverse thrust and    10% or                          least 80% of the
                         no wheel brakes on    200 ft                          total time from
                         a dry runway.         (61 m) of distance.                         initiation of
                                                                                reverse thrust to
                                                                                the minimum
                                                                                operating speed
                                                                                with full reverse
                                                                                thrust. Data is
                                                                                required for medium
                                                                                and near maximum
                                                                                landing gross
                                                                                weights. Data on
                                                                                the position of
                                                                                ground spoilers,
                                                                                (including method
                                                                                of deployment, if
                                                                                used) must be
                                                                                provided.
                                                                                Engineering data
                                                                                may be used for the
                                                                                medium gross weight
                                                                                condition.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.e.3.................  Stopping distance,    10% of    Landing.............  Either flight test               X    X
                         using wheel brakes    distance or 200 ft (61 m).                        manufacturer's
                         thrust on a wet                                                   performance manual
                         runway.                                                           data must be used
                                                                                where available.
                                                                                Engineering data
                                                                                based on dry runway
                                                                                flight test
                                                                                stopping distance
                                                                                modified by the
                                                                                effects of
                                                                                contaminated runway
                                                                                braking
                                                                                coefficients are an
                                                                                acceptable
                                                                                alternative.
--------------------------------------------------------------------------------------------------------------------------------------------------------

1.e.4.................  Stopping distance,    10% of    Landing.............  Either flight test               X    X
                         using wheel brakes    distance or 200 ft (61 m).                        performance manual
                         thrust on an icy                                                  data must be used,
                         runway.                                                           where available.
                                                                                Engineering data
                                                                                based on dry runway
                                                                                flight test
                                                                                stopping distance
                                                                                modified by the
                                                                                effects of
                                                                                contaminated runway
                                                                                braking
                                                                                coefficients are an
                                                                                acceptable
                                                                                alternative.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.f...................  Engines.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.f.1.................  Acceleration........  (10% Tt)  Approach or landing.  Record engine power    X    X    X    X   See Appendix F of
                                               and (10% Ti, or                            Torque) from flight                       definitions of Ti
                                               0.25                            idle to go-around                         and Tt.
                                               sec.).                                      power for a rapid
                                                                                (slam) throttle
                                                                                movement.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.f.2.................  Deceleration........  (10% Tt)  Ground..............  Record engine power    X    X    X    X   See Appendix F of
                                               and (10% Ti, or                            Torque) from Max T/                       definitions of Ti
                                               0.25                            O power to 90%                            and Tt.
                                               sec.).                                      decay of Max T/O
                                                                                power for a rapid
                                                                                (slam) throttle
                                                                                movement.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2. Handling Qualities.
--------------------------------------------------------------------------------------------------------------------------------------------------------
                        For simulators requiring Static or Dynamic tests at the controls (i.e., column, wheel,                      Contact the NSPM for
                         rudder pedal), special test fixtures will not be required during initial or upgrade                         clarification of
                         evaluations if the sponsor's QTG/MQTG shows both test fixture results and the results                       any issue regarding
                         of an alternative approach, such as computer plots produced concurrently, that                              airplanes with
                         provide satisfactory agreement. Repeat of the alternative method during the initial                         reversible
                         or upgrade evaluation satisfies this test requirement. For initial and upgrade                              controls.
                         evaluations, the control dynamic characteristics must be measured at and recorded
                         directly from the flight deck controls, and must be accomplished in takeoff, cruise,
                         and landing flight conditions and configurations. Testing of position versus force is
                         not applicable if forces are generated solely by use of airplane hardware in the FFS.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a...................  Static Control Tests.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a.1.a...............  Pitch Controller      2 lb      Ground..............  Record results for     X    X    X    X   Test results should
                         Position vs. Force    (0.9 daN) breakout,                         an uninterrupted                          be validated (where
                         and Surface           10% or                          control sweep to                          possible) with in-
                         Position              5 lb                            the stops.                                flight data from
                         Calibration.          (2.2 daN) force,                                                                      tests such as
                                               2[deg]                                                                    longitudinal static
                                               elevator.                                                                             stability or
                                                                                stalls. Static and
                                                                                dynamic flight
                                                                                control tests
                                                                                should be
                                                                                accomplished at the
                                                                                same feel or impact
                                                                                pressures.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a.1.b...............  (Reserved)
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a.2.a...............  Roll Controller       2 lb      Ground..............  Record results for     X    X    X    X   Test results should
                         Position vs. Force    (0.9 daN) breakout,                         an uninterrupted                          be validated with
                         and Surface           10% or                          control sweep to                          in-flight data from
                         Position              3 lb                            the stops.                                tests such as
                         Calibration.          (1.3 daN) force,                                                                      engine out trims,
                                               2[deg]                                                                    or steady state
                                               aileron, 3[deg]                                                                          and dynamic flight
                                               spoiler angle.                                                                        control tests
                                                                                should be
                                                                                accomplished at the
                                                                                same feel or impact
                                                                                pressures.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a.2.b...............  (Reserved)
--------------------------------------------------------------------------------------------------------------------------------------------------------

2.a.3.a...............  Rudder Pedal          5 lb      Ground..............  Record results for     X    X    X    X   Test results should
                         Position vs. Force    (2.2 daN) breakout,                         an uninterrupted                          be validated with
                         and Surface           10% or                          control sweep to                          in-flight data from
                         Position              5 lb                            the stops.                                tests such as
                         Calibration.          (2.2 daN) force,                                                                      engine out trims,
                                               2[deg]                                                                    or steady state
                                               rudder angle.                                                                         sideslips. Static
                                                                                and dynamic flight
                                                                                control tests
                                                                                should be
                                                                                accomplished at the
                                                                                same feel or impact
                                                                                pressures.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a.3.b...............  (Reserved)
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a.4.................  Nosewheel Steering    2 lb      Ground..............  Record results of an   X    X    X    X
                         Controller Force      (0.9 daN) breakout,                         uninterrupted
                         and Position          10% or                          control sweep to
                         Calibration.          3 lb                            the stops.
                                               (1.3 daN) force,
                                               2[deg]
                                               nosewheel angle.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a.5.................  Rudder Pedal          2[deg]    Ground..............  Record results of an   X    X    X    X
                         Steering              nosewheel angle.                            uninterrupted
                         Calibration.                                                      control sweep to
                                                                                the stops.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a.6.................  Pitch Trim Indicator  0.5[deg]  Ground..............                         X    X    X    X   The purpose of the
                         vs. Surface           of computed trim                                                                      test is to compare
                         Position              surface angle.                                                                        FFS against design
                         Calibration.                                                                                data or equivalent.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a.7.................  Pitch Trim Rate.....  10% trim  Ground and approach.  The trim rate must     X    X    X    X
                                               rate ([deg]/sec).                           be checked using
                                                                                the pilot primary
                                                                                trim (ground) and
                                                                                using the autopilot
                                                                                or pilot primary
                                                                                trim in flight at
                                                                                go-around flight
                                                                                conditions.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a.8.................  Alignment of Flight   5[deg]    Ground..............  Requires               X    X    X    X
                         Deck Throttle Lever   of throttle lever                           simultaneous
                         vs. Selected Engine   angle, or 3% N1, or                             engines. The
                                               .03                             tolerances apply
                                               EPR, or 3% maximum                            data and between
                                               rated manifold                              engines. In the
                                               pressure, or 3% torque.                            powered airplanes,
                                               For propeller-                              if a propeller
                                               driven airplanes                            lever is present,
                                               where the propeller                         it must also be
                                               control levers do                           checked. For
                                               not have angular                            airplanes with
                                               travel, a tolerance                         throttle
                                               of 0.8                          ``detents,'' all
                                               inch (2                         detents must be
                                               cm.) applies.                               presented. May be a
                                                                                series of snapshot
                                                                                test results.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a.9.................  Brake Pedal Position  5 lb      Ground..............  Hydraulic system       X    X    X    X   FFS computer output
                         vs. Force and Brake   (2.2 daN) or 10%                            pressure must be                          results may be used
                         System Pressure       force, 150 psi (1.0                          position through a
                                               MPa) or 10% brake
                                               system pressure.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.b...................  Dynamic Control Tests.
--------------------------------------------------------------------------------------------------------------------------------------------------------
                        Tests 2.b.1., 2.b.2., and 2.b.3. are not applicable if dynamic response is generated    ...  ...  ...  ...
                         solely by use of airplane hardware in the FFS. Power setting is that required for
                         level flight unless otherwise specified.
--------------------------------------------------------------------------------------------------------------------------------------------------------

2.b.1.................  Pitch Control.......  For underdamped       Takeoff, Cruise, and  Data must show                   X    X   ``n'' is the
                                               systems: 10% of time                           displacement in                           of a full cycle of
                                               from 90% of initial                         both directions.                          oscillation. Refer
                                               displacement (0.9                           Tolerances apply                          to paragraph 4 of
                                               Ad) to first zero                           against the                               this attachment for
                                               crossing and 10 (n+1)% of                          each period                               Static and dynamic
                                               period thereafter.                          (considered                               flight control
                                               10%                             independently).                           tests should be
                                               amplitude of first                          Normal control                            accomplished at the
                                               overshoot applied                           displacement for                          same feel or impact
                                               to all overshoots                           this test is 25% to                       pressures.
                                               greater than 5% of                          50% of full throw
                                               initial                                     or 25% to 50% of
                                               displacement (.05                           the maximum
                                               Ad). 1                          allowable pitch
                                               overshoot (first                            controller
                                               significant                                 deflection for
                                               overshoot must be                           flight conditions
                                               matched). For                               limited by the
                                               overdamped systems:                         maneuvering load
                                               10% of                          envelope.
                                               time from 90% of
                                               initial
                                               displacement (0.9
                                               Ad) to 10% of
                                               initial
                                               displacement (0.1
                                               Ad). For the
                                               alternate method
                                               see paragraph 4 of
                                               this attachment.
                                               The slow sweep is
                                               the equivalent to
                                               the static test
                                               2.a.1. For the
                                               moderate and rapid
                                               sweeps: 2 lb (0.9
                                               daN) or 10% dynamic
                                               increment above the
                                               static force.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.b.2.................  Roll Control........  For underdamped       Takeoff, Cruise, and  Data must show                   X    X   ``n'' is the
                                               systems: 10% of time                           displacement in                           of a full cycle of
                                               from 90% of initial                         both directions.                          oscillation. Refer
                                               displacement (0.9                           Tolerance applies                         to paragraph 4 of
                                               Ad) to first zero                           against the                               this attachment for
                                               crossing, and 10 (n+1)% of                          each period                               Static and dynamic
                                               period thereafter.                          (considered                               flight control
                                               10%                             independently).                           tests should be
                                               amplitude of first                          Normal control                            accomplished at the
                                               overshoot, applied                          displacement for                          same feel or impact
                                               to all overshoots                           this test is 25% to                       pressures.
                                               greater than 5% of                          50% of the maximum
                                               initial                                     allowable roll
                                               displacement (.05                           controller
                                               Ad), 1                          deflection for
                                               overshoot (first                            flight conditions
                                               significant                                 limited by the
                                               overshoot must be                           maneuvering load
                                               matched). For                               envelope.
                                               overdamped systems:
                                               10% of
                                               time from 90% of
                                               initial
                                               displacement (0.9
                                               Ad) to 10% of
                                               initial
                                               displacement
                                               (0.1Ad). For the
                                               alternate method
                                               see paragraph 4 of
                                               this attachment.
                                               The slow sweep is
                                               the equivalent to
                                               the static test
                                               2.a.2. For the
                                               moderate and rapid
                                               sweeps: 2 lb (0.9
                                               daN) or 10% dynamic
                                               increment above the
                                               static force.
--------------------------------------------------------------------------------------------------------------------------------------------------------

2.b.3.................  Yaw Control.........  For underdamped       Takeoff, Cruise, and  Data must show                   X    X   ``n'' is the
                                               systems: 10% of time                           displacement in                           of a full cycle of
                                               from 90% of initial                         both directions.                          oscillation. Refer
                                               displacement (0.9                           Tolerance applies                         to paragraph 4 of
                                               Ad) to first zero                           against the                               this attachment for
                                               crossing, and 10 (n+1)% of                          each period                               Static and dynamic
                                               period thereafter.                          (considered                               flight control
                                               10%                             independently).                           tests should be
                                               amplitude of first                          Normal control                            accomplished at the
                                               overshoot applied                           displacement for                          same feel or impact
                                               to all overshoots                           this test is 25% to                       pressures.
                                               greater than 5% of                          50% of the maximum
                                               initial                                     allowable yaw
                                               displacement (.05                           controller
                                               Ad). 1                          deflection for
                                               overshoot (first                            flight conditions
                                               significant                                 limited by the
                                               overshoot must be                           maneuvering load
                                               matched). For                               envelope.
                                               overdamped systems:
                                               10% of
                                               time from 90% of
                                               initial
                                               displacement (0.9
                                               Ad) to 10% of
                                               initial
                                               displacement (0.1
                                               Ad). For the
                                               alternate method
                                               (see paragraph 4 of
                                               this attachment).
                                               The slow sweep is
                                               the equivalent to
                                               the static test
                                               2.a.3. For the
                                               moderate and rapid
                                               sweeps: 2 lb (0.9
                                               daN) or 10% dynamic
                                               increment above the
                                               static force.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.b.4.................  Small Control         0.15[deg]/sec                         be typical of minor
                                               body pitch rate or                          corrections made
                                               20% of                          while established
                                               peak body pitch                             on an ILS approach
                                               rate applied                                course, using from
                                               throughout the time                         0.5[deg]/sec to
                                               history.                                    2[deg]/sec pitch
                                                                                rate. The test must
                                                                                be in both
                                                                                directions, showing
                                                                                time history data
                                                                                from 5 seconds
                                                                                before until at
                                                                                least 5 seconds
                                                                                after initiation of
                                                                                control input.
                                                                                CCA: Test in normal
                                                                                and non-normal
                                                                                control states..
--------------------------------------------------------------------------------------------------------------------------------------------------------

2.b.5.................  Small Control         0.15[deg]/sec                         be typical of minor
                                               body roll rate or                           corrections made
                                               20% of                          while established
                                               peak body roll rate                         on an ILS approach
                                               applied throughout                          course, using from
                                               the time history.                           0.5[deg]/sec to
                                                                                2[deg]/sec roll
                                                                                rate. The test may
                                                                                be run in only one
                                                                                direction; however,
                                                                                for airplanes that
                                                                                exhibit non-
                                                                                symmetrical
                                                                                behavior, the test
                                                                                must include both
                                                                                directions. Time
                                                                                history data must
                                                                                be recorded from 5
                                                                                seconds before
                                                                                until at least 5
                                                                                seconds after
                                                                                initiation of
                                                                                control input.
                                                                                CCA: Test in normal
                                                                                and non-normal
                                                                                control states..
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.b.6.................  Small Control         0.15[deg]/sec                         be typical of minor
                                               body yaw rate or                            corrections made
                                               20% of                          while established
                                               peak body yaw rate                          on an ILS approach
                                               applied throughout                          course, using from
                                               the time history.                           0.5[deg]/sec to
                                                                                2[deg]/sec yaw
                                                                                rate. The test may
                                                                                be run in only one
                                                                                direction; however,
                                                                                for airplanes that
                                                                                exhibit non-
                                                                                symmetrical
                                                                                behavior, the test
                                                                                must include both
                                                                                directions. Time
                                                                                history data must
                                                                                be recorded from 5
                                                                                seconds before
                                                                                until at least 5
                                                                                seconds after
                                                                                initiation of
                                                                                control input.
                                                                                CCA: Test in normal
                                                                                and non-normal
                                                                                control states..
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.c...................  Longitudinal Control Tests.
--------------------------------------------------------------------------------------------------------------------------------------------------------
                        Power setting is that required for level flight unless otherwise specified.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.c.1.................  Power Change          3 kt      Approach............  Power is changed       X    X    X    X
                         Dynamics.             airspeed, 100 ft (30 m)                         setting required
                                               altitude, 20% or 1.5[deg]                              maximum continuous
                                               pitch angle.                                thrust or go-around
                                                                                power setting.
                                                                                Record the
                                                                                uncontrolled free
                                                                                response from at
                                                                                least 5 seconds
                                                                                before the power
                                                                                change is initiated
                                                                                to 15 seconds after
                                                                                the power change is
                                                                                completed.
                                                                                CCA: Test in normal
                                                                                and non-normal
                                                                                control states..
--------------------------------------------------------------------------------------------------------------------------------------------------------

2.c.2.................  Flap/Slat Change      3 kt      Takeoff through       Record the             X    X    X    X
                         Dynamics.             airspeed, 100 ft (30 m)   retraction, and       response from at
                                               altitude, 20% or 1.5[deg]                              configuration
                                               pitch angle.                                change is initiated
                                                                                to 15 seconds after
                                                                                the configuration
                                                                                change is completed.
                                                                                CCA: Test in normal
                                                                                and non-normal
                                                                                control states..
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.c.3.................  Spoiler/Speedbrake    3 kt      Cruise..............  Record the             X    X    X    X
                         Change Dynamics.      airspeed, 100 ft (30 m)                         response from at
                                               altitude, 20% or 1.5[deg]                              configuration
                                               pitch angle.                                change is initiated
                                                                                to 15 seconds after
                                                                                the configuration
                                                                                change is
                                                                                completed. Record
                                                                                results for both
                                                                                extension and
                                                                                retraction.
                                                                                CCA: Test in normal
                                                                                and non-normal
                                                                                control states..
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.c.4.................  Gear Change Dynamics  3 kt      Takeoff               Record the time        X    X    X    X
                                               airspeed, 100 ft (30 m)   Approach              uncontrolled free
                                               altitude, 20% or 1.5[deg]                              least 5 seconds
                                               pitch angle.                                before the
                                                                                configuration
                                                                                change is initiated
                                                                                to 15 seconds after
                                                                                the configuration
                                                                                change is completed.
                                                                                CCA: Test in normal
                                                                                and non-normal
                                                                                control states..
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.c.5.................  Longitudinal Trim...  0.5[deg]  Cruise, Approach,     Record steady-state    X    X    X    X
                                               trim surface angle,   and Landing.          condition with
                                               1[deg]                          wings level and
                                               elevator, 1[deg] pitch                          level flight. May
                                               angle, 5% net thrust                         snapshot tests.
                                               or equivalent.                             CCA: Test in normal
                                                                                or non-normal
                                                                                control states..
--------------------------------------------------------------------------------------------------------------------------------------------------------

2.c.6.................  Longitudinal          5 lb      Cruise, Approach,     Continuous time        X    X    X    X
                         Maneuvering           (2.2      and Landing.          history data or a
                         Stability (Stick      daN) or 10% pitch                             tests may be used.
                                               controller force.                           Record results up
                                               Alternative method:                         to 30[deg] of bank
                                               1[deg]                          for approach and
                                               or 10%                          landing
                                               change of elevator.                         configurations.
                                                                                Record results for
                                                                                up to 45[deg] of
                                                                                bank for the cruise
                                                                                configuration. The
                                                                                force tolerance is
                                                                                not applicable if
                                                                                forces are
                                                                                generated solely by
                                                                                the use of airplane
                                                                                hardware in the
                                                                                FFS. The
                                                                                alternative method
                                                                                applies to
                                                                                airplanes that do
                                                                                not exhibit ``stick-
                                                                                force-per-g''
                                                                                characteristics.
                                                                                CCA: Test in normal
                                                                                and non-normal
                                                                                control states.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.c.7.................  Longitudinal Static   5 lb      Approach............  Record results for     X    X    X    X
                         Stability.            (2.2                            at least 2 speeds
                                               daN) or 10% pitch                             below trim speed.
                                               controller force.                           May be a series of
                                               Alternative method:                         snapshot test
                                               1[deg]                          results. The force
                                               or 10%                          tolerance is not
                                               change of elevator.                         applicable if
                                                                                forces are
                                                                                generated solely by
                                                                                the use of airplane
                                                                                hardware in the
                                                                                FFS. The
                                                                                alternative method
                                                                                applies to
                                                                                airplanes that do
                                                                                not exhibit speed
                                                                                stability
                                                                                characteristics.
                                                                                CCA: Test in normal
                                                                                or non-normal
                                                                                control states..
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.c.8.................  Stall                 3 kt      Second Segment        The stall maneuver     X    X    X    X
                         Characteristics.      airspeed for          Climb, and Approach   must be entered
                                               initial buffet,       or Landing.           with thrust at or
                                               stall warning, and                          near idle power and
                                               stall speeds. 2[deg] bank                           Record the stall
                                               for speeds greater                          warning signal and
                                               than stick shaker                           initial buffet, if
                                               or initial buffet.                          applicable. Time
                                               Additionally, for                           history data must
                                               those simulators                            be recorded for
                                               with reversible                             full stall and
                                               flight control                              initiation of
                                               systems: 10% or 5 lb (2.2                             occur in the proper
                                               daN) Stick/Column                           relation to buffet/
                                               force (prior to ``g                         stall. FFSs of
                                               break'' only).                              airplanes
                                                                                exhibiting a sudden
                                                                                pitch attitude
                                                                                change or ``g
                                                                                break'' must
                                                                                demonstrate this
                                                                                characteristic.
                                                                                CCA: Test in normal
                                                                                and non-normal
                                                                                control states..
--------------------------------------------------------------------------------------------------------------------------------------------------------

2.c.9.................  Phugoid Dynamics....  10%       Cruise..............  The test must          X    X    X    X
                                               period, 10% of time                           is less of the
                                               to \1/2\ or double                          following: Three
                                               amplitude or .02 of                                overshoots after
                                               damping ratio.                              the input is
                                                                                completed), or the
                                                                                number of cycles
                                                                                sufficient to
                                                                                determine time to
                                                                                \1/2\ or double
                                                                                amplitude.
                                                                                CCA: Test in Non-
                                                                                normal control
                                                                                states.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.c.10................  Short Period          1.5[deg]  Cruise..............  CCA: Test in Normal    X    X    X    X
                         Dynamics..            pitch angle or                              and Non-normal
                                               2[deg]/                         control states.
                                               sec pitch rate,
                                               0.10g
                                               acceleration.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.c.11................  (Reserved)
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.d...................  Lateral Directional Tests.
--------------------------------------------------------------------------------------------------------------------------------------------------------
                        Power setting is that required for level flight unless otherwise specified.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.d.1.................  Minimum Control       3 kt      Takeoff or Landing    Takeoff thrust must    X    X    X    X   Low Speed Engine
                         Speed, Air (Vmca or   airspeed.             (whichever is most    be used on the                            Inoperative
                         Vmcl), per                                  critical in the       operating                                 Handling may be
                         Applicable                                  airplane).            engine(s). A time                         governed by a
                         Airworthiness                                                     history or a series                       performance or
                         Standard or Low                                                   of snapshot tests                         control limit that
                         Speed Engine                                                      may be used.                              prevents
                         Inoperative                                                      CCA: Test in Normal                        demonstration of
                         Handling                                                          or Non-normal                             Vmca or Vmcl in the
                         Characteristics in                                                control state..                           conventional
                         the Air.                                                                                manner.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.d.2.................  Roll Response         10% or    Cruise, and Approach  Record results for     X    X    X    X
                         (Rate)..              2[deg]/   or Landing.           normal roll
                                               sec roll rate.                              controller
                                               Additionally, for                           deflection (about
                                               those simulators of                         one-third of
                                               airplanes with                              maximum roll
                                               reversible flight                           controller travel).
                                               control systems:                            May be combined
                                               10% or                          with step input of
                                               3 lb                            flight deck roll
                                               (1.3 daN) wheel                             controller test
                                               force.                                      (2.d.3.).
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.d.3.................  Roll Response to      10% or    Approach or Landing.  Record from            X    X    X    X   With wings level,
                         Flight Deck Roll      2[deg]                          initiation of roll                        apply a step roll
                         Controller Step       bank angle.                                 through 10 seconds                        control input using
                         Input.                                                            after control is                          approximately one-
                                                                                returned to neutral                       third of the roll
                                                                                and released. May                         controller travel.
                                                                                be combined with                          When reaching
                                                                                roll response                             approximately
                                                                                (rate) test (2.d.2).                      20[deg] to 30[deg]
                                                                                CCA: Test in Normal                        of bank, abruptly
                                                                                and Non-normal                            return the roll
                                                                                control states.                           controller to
                                                                                neutral and allow
                                                                                approximately 10
                                                                                seconds of airplane
                                                                                free response.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.d.4.................  Spiral Stability....  Correct trend and     Cruise, and Approach  Record results for     X    X    X    X
                                               2[deg]    or Landing.           both directions.
                                               or 10%                          Airplane data
                                               bank angle in 20                            averaged from
                                               seconds. Alternate                          multiple tests may
                                               test requires                               be used. As an
                                               correct trend and                           alternate test,
                                               2[deg]                          demonstrate the
                                               aileron.                                    lateral control
                                                                                required to
                                                                                maintain a steady
                                                                                turn with a bank
                                                                                angle of 28[deg] to
                                                                                32[deg].
                                                                                CCA: Test in Non-
                                                                                normal control
                                                                                state.
--------------------------------------------------------------------------------------------------------------------------------------------------------

2.d.5.................  Engine Inoperative    1[deg]    Second Segment        May be a series of     X    X    X    X   The test should be
                         Trim.                 rudder angle or       Climb, and Approach   snapshot tests.                           performed in a
                                               1[deg]    or Landing.                                                     manner similar to
                                               tab angle or                                                                          that for which a
                                               equivalent pedal,                                                                     pilot is trained to
                                               2[deg]                                                                    trim an engine
                                               sideslip angle.                                                                       failure condition.
                                                                                Second segment
                                                                                climb test should
                                                                                be at takeoff
                                                                                thrust. Approach or
                                                                                landing test should
                                                                                be at thrust for
                                                                                level flight.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.d.6.................  Rudder Response.....  2[deg]/   Approach or Landing.  Record results for     X    X    X    X
                                               sec or 10% yaw rate.                         augmentation system
                                                                                ON and OFF. A
                                                                                rudder step input
                                                                                of 20%-30% rudder
                                                                                pedal throw is used.
                                                                                CCA: Test in Normal
                                                                                and Non-normal
                                                                                control states.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.d.7.................  Dutch Roll, (Yaw      0.5 sec   Cruise, and Approach  Record results for          X    X    X
                         Damper OFF).          or 10%    or Landing.           at least 6 complete
                                               of period, 10% of time                           stability
                                               to \1/2\ or double                          augmentation OFF.
                                               amplitude or .02 of                                normal control
                                               damping ratio.                              state..
                                               20% or
                                               1 sec
                                               of time difference
                                               between peaks of
                                               bank and sideslip.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.d.8.................  Steady State          For given rudder      Approach or Landing.  Use at least two       X    X    X    X
                         Sideslip.             position 2[deg] bank                           one of which must
                                               angle, 1[deg]                                allowable rudder.
                                               sideslip angle,                             Propeller driven
                                               10% or                          airplanes must test
                                               2[deg]                          in each direction.
                                               aileron, 10% or 5[deg]                                results.
                                               spoiler or
                                               equivalent roll,
                                               controller position
                                               or force.
                                               Additionally, for
                                               those simulators of
                                               airplanes with
                                               reversible flight
                                               control systems:
                                               10% or
                                               3 lb
                                               (1.3 daN) wheel
                                               force 10% or 5 lb (2.2
                                               daN) rudder pedal
                                               force.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.e...................  Landings.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.e.1.................  Normal Landing......  3 kt      Landing.............  Record results from         X    X    X   Tests should be
                                               airspeed, 1.5[deg]                              (61 m) AGL to                             normal landing flap
                                               pitch angle, 1.5[deg]                             CCA: Test in Normal                        applicable). One
                                               angle of attack,                            and Non-normal                            should be at or
                                               10% or                          control states..                          near maximum
                                               10 ft                                                                     certificated
                                               (3 m) height.                                                                         landing weight. The
                                               Additionally, for                                                                     other should be at
                                               those simulators of                                                                   light or medium
                                               airplanes with                                                                        landing weight.
                                               reversible flight
                                               control systems:
                                               10% or
                                               5 lbs
                                               (2.2
                                               daN) stick/column
                                               force.
--------------------------------------------------------------------------------------------------------------------------------------------------------

2.e.2.................  Minimum Flap Landing  3 kt      Minimum Certified     Record results from              X    X
                                               airspeed, 1.5[deg]        Configuration.        (61 m) AGL to
                                               pitch angle, 1.5[deg]                              with airplane at
                                               angle of attack,                            near Maximum
                                               10% or                          Landing Weight.
                                               10 ft
                                               (3 m) height.
                                               Additionally, for
                                               those simulators of
                                               airplanes with
                                               reversible flight
                                               control systems:
                                               10% or
                                               5 lbs
                                               (2.2 daN) stick/
                                               column force.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.e.3.................  Crosswind Landing...  3 kt      Landing.............  Record results from         X    X    X   In those situations
                                               airspeed, 1.5[deg]                              (61 m) AGL, through                       crosswind or a
                                               pitch angle, 1.5[deg]                              down, to 50%                              demonstrated
                                               angle of attack,                            decrease in main                          crosswind is not
                                               10% or                          landing gear                              known, contact the
                                               10 ft                           touchdown speed.                          NSPM.
                                               (3 m) height 2[deg] bank                           include information
                                               angle, 2[deg]                                for a crosswind
                                               sideslip angle                              (expressed as
                                               3[deg]                          direct head-wind
                                               heading angle.                              and direct cross-
                                               Additionally, for                           wind components) of
                                               those simulators of                         60% of the maximum
                                               airplanes with                              wind measured at 33
                                               reversible flight                           ft (10 m) above the
                                               control systems:                            runway.
                                               10% or
                                               3 lb
                                               (1.3 daN) wheel
                                               force 10% or 5 lb (2.2
                                               daN) rudder pedal
                                               force.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.e.4.................  One Engine            3 kt      Landing.............  Record results from         X    X    X
                         Inoperative Landing.  airspeed, 1.5[deg]                              (61 m) AGL, through
                                               pitch angle, 1.5[deg]                              down, to 50%
                                               angle of attack,                            decrease in main
                                               10%                             landing gear
                                               height or 10 ft (3 m);                          less.
                                               2[deg]
                                               bank angle, 2[deg]
                                               sideslip angle,
                                               3[deg]
                                               heading.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.e.5.................  Autopilot landing     5 ft      Landing.............  If autopilot                X    X    X   See Appendix F of
                         (if applicable).      (1.5 m) flare                               provides rollout                          this part for
                                               height, 0.5 sec Tf,                           lateral deviation
                                               or 10%Tf, 140 ft/min                            main landing gear
                                               (0.7 m/sec) rate of                         touchdown speed or
                                               descent at touch-                           less. Time of
                                               down. 10 ft (3 m)                           mode engage and
                                               lateral deviation                           main gear touchdown
                                               during rollout.                             must be noted.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.e.6.................  All engines           3 kt                            Normal, all-engines-        X    X    X
                         operating,            airspeed, 1.5[deg]                              around with the
                         around.               pitch angle, 1.5[deg]                              (if applicable) at
                                               angle of attack.                            medium landing
                                                                                weight.
                                                                                CCA: Test in normal
                                                                                or non-normal
                                                                                control states..
--------------------------------------------------------------------------------------------------------------------------------------------------------

2.e.7.................  One engine            3 kt                            The one engine              X    X    X
                         inoperative go        airspeed, 1.5[deg]                              around is required
                                               pitch angle, 1.5[deg]                              certificated
                                               angle of attack,                            landing weight with
                                               2[deg]                          the critical engine
                                               bank angle, 2[deg]                                manual controls. If
                                               slideslip angle.                            applicable, an
                                                                                additional engine
                                                                                inoperative go
                                                                                around test must be
                                                                                accomplished with
                                                                                the autopilot
                                                                                engaged.
                                                                                CCA: Non-autopilot
                                                                                test in Non-normal
                                                                                control state..
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.e.8.................  Directional control   2[deg]/   Landing.............  Record results              X    X    X
                         (rudder               sec yaw rate. 5 kts                                 speed approximating
                         symmetric reverse     airspeed.                                   touchdown speed to
                         thrust.                                                           the minimum thrust
                                                                                reverser operation
                                                                                speed. With full
                                                                                reverse thrust,
                                                                                apply yaw control
                                                                                in both directions
                                                                                until reaching
                                                                                minimum thrust
                                                                                reverser operation
                                                                                speed.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.e.9.................  Directional control   5 kt      Landing.............  Maintain heading            X    X    X
                         (rudder               airspeed. 3[deg]                                with full reverse
                         asymmetric reverse    heading angle.                              thrust on the
                         thrust.                                                           operating
                                                                                engine(s). Record
                                                                                results starting
                                                                                from a speed
                                                                                approximating
                                                                                touchdown speed to
                                                                                a speed at which
                                                                                control of yaw
                                                                                cannot be
                                                                                maintained or until
                                                                                reaching minimum
                                                                                thrust reverser
                                                                                operation speed,
                                                                                whichever is
                                                                                higher. The
                                                                                tolerance applies
                                                                                to the low speed
                                                                                end of the data
                                                                                recording.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.f...................  Ground Effect.
--------------------------------------------------------------------------------------------------------------------------------------------------------
                        Test to demonstrate   1[deg]    Landing.............  The Ground Effect           X    X    X   See paragraph on
                         Ground Effect.        elevator 0.5[deg]                              validated by the                          this attachment for
                                               stabilizer angle,                           test selected and a                       additional
                                               5% net                          rationale must be                         information.
                                               thrust or                                   provided for
                                               equivalent, 1[deg] angle                          particular test.
                                               of attack, 10% height or
                                               5 ft
                                               (1.5 m), 3 kt
                                               airspeed, 1[deg] pitch
                                               angle.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.g...................  Windshear.
--------------------------------------------------------------------------------------------------------------------------------------------------------
                        Four tests, two       See Attachment 5 of   Takeoff and Landing.  Requires windshear               X    X   See Attachment 5 of
                         takeoff and two       this appendix.                              models that provide                       this appendix for
                         landing, with one                                                 training in the                           information related
                         of each conducted                                                 specific skills                           to Level A and B
                         in still air and                                                  needed to recognize                       simulators.
                         the other with                                                    windshear phenomena
                         windshear active to                                               and to execute
                         demonstrate                                                       recovery
                         windshear models.                                                 procedures. See
                                                                                Attachment 5 of
                                                                                this appendix for
                                                                                tests, tolerances,
                                                                                and procedures.
--------------------------------------------------------------------------------------------------------------------------------------------------------

2.h...................  Flight Maneuver and Envelope Protection Functions.
--------------------------------------------------------------------------------------------------------------------------------------------------------
                        The requirements of tests h(1) through (6) of this attachment are applicable to
                         computer controlled aircraft only. Time history results are required for simulator
                         response to control inputs during entry into envelope protection limits including
                         both normal and degraded control states if the function is different. Set thrust as
                         required to reach the envelope protection function.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.h.1.................  Overspeed...........  5 kt      Cruise..............                              X    X    X
                                               airspeed.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.h.2.................  Minimum Speed.......  3 kt      Takeoff, Cruise, and                              X    X    X
                                               airspeed.             Approach or Landing.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.h.3.................  Load Factor.........  0.1 g     Takeoff, Cruise.....                              X    X    X
                                               normal load factor.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.h.4.................  Pitch Angle.........  1.5[deg]  Cruise, Approach....                              X    X    X
                                               pitch angle.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.h.5.................  Bank Angle..........  2[deg]    Approach............                              X    X    X
                                               or 10%
                                               bank angle.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.h.6.................  Angle of Attack.....  1.5[deg]  Second Segment                                    X    X    X
                                               angle of attack.      Climb, and Approach
                                                                     or Landing.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3. Motion System.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.a...................  Frequency response.
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                              Based on Simulator    N/A.................  Required as part of    X    X    X    X
                                               Capability.                                 the MQTG. The test
                                                                                must demonstrate
                                                                                frequency response
                                                                                of the motion
                                                                                system.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.b...................  Leg balance.
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                              Based on Simulator    N/A.................  Required as part of    X    X    X    X
                                               Capability.                                 the MQTG. The test
                                                                                must demonstrate
                                                                                motion system leg
                                                                                balance as
                                                                                specified by the
                                                                                applicant for
                                                                                flight simulator
                                                                                qualification.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.c...................  Turn-around check.
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                              Based on Simulator    N/A.................  Required as part of    X    X    X    X
                                               Capability.                                 the MQTG. The test
                                                                                must demonstrate a
                                                                                smooth turn-around
                                                                                (shift to opposite
                                                                                direction of
                                                                                movement) of the
                                                                                motion system as
                                                                                specified by the
                                                                                applicant for
                                                                                flight simulator
                                                                                qualification.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.d...................  Motion system repeatability.
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                              With the same input   Accomplished in both  Required as part of    X    X    X    X   This test ensures
                                               signal, the test      the ``ground'' mode   the MQTG. The                             that motion system
                                               results must be       and in the            assessment                                hardware and
                                               repeatable to         ``flight'' mode of    procedures must be                        software (in normal
                                               within 0.05 g actual   operation.            that the motion                           operating mode)
                                               platform linear                             system hardware and                       continue to perform
                                               acceleration.                               software (in normal                       as originally
                                                                                flight simulator                          qualified.
                                                                                operating mode)                           Performance changes
                                                                                continue to perform                       from the original
                                                                                as originally                             baseline can be
                                                                                qualified.                                readily identified
                                                                                with this
                                                                                information.
--------------------------------------------------------------------------------------------------------------------------------------------------------

3.e...................  Motion cueing performance signature. Required as part of MQTG. For the following set                        These tests should
                         of maneuvers record the relevant motion variables.                                                          be run with the
                                                                                motion buffet mode
                                                                                disabled. See
                                                                                paragraph 6.d., of
                                                                                this attachment,
                                                                                Motion cueing
                                                                                performance
                                                                                signature.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.e.1.................  Takeoff rotation (VR  As specified by the   Ground..............  Pitch attitude due     X    X    X    X   Associated with test
                         to V2).               sponsor for flight                          to initial climb                          1.b.4.
                                               simulator                                   must dominate over
                                               qualification.                              cab tilt due to
                                                                                longitudinal
                                                                                acceleration.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.e.2.................  Engine failure        As specified by the   Ground..............                         X    X    X    X   Associated with test
                         between V1 and VR.    sponsor for flight                                                                    1.b.5.
                                               simulator
                                               qualification.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.e.3.................  Pitch change during   As specified by the   Flight..............                              X    X    X   Associated with test
                         go-around.            sponsor for flight                                                                    2.e.6.
                                               simulator
                                               qualification.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.e.4.................  Configuration         As specified by the   Flight..............                         X    X    X    X   Associated with
                         changes.              sponsor for flight                                                                    tests 2.c.2. and
                                               simulator                                                                             2.c.4.
                                               qualification.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.e.5.................  Power change          As specified by the   Flight..............                         X    X    X    X   Associated with test
                         dynamics.             sponsor for flight                                                                    2.c.1.
                                               simulator
                                               qualification.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.e.6.................  Landing flare.......  As specified by the   Flight..............                              X    X    X   Associated with test
                                               sponsor for flight                                                                    2.e.1.
                                               simulator
                                               qualification.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.e.7.................  Touchdown bump......  As specified by the   Ground..............                                   X    X   Associated with test
                                               sponsor for flight                                                                    2.e.1.
                                               simulator
                                               qualification.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.f...................  Characteristic motion vibrations. The recorded test results for characteristic buffets
                         must allow the comparison of relative amplitude versus frequency.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.f.1.................  Thrust effect with    Simulator test        Ground..............  The test must be                      X
                         brakes set.           results must                                conducted within 5%
                                               exhibit the overall                         of the maximum
                                               appearance and                              possible thrust
                                               trends of the                               with brakes set.
                                               airplane data, with
                                               at least three (3)
                                               of the predominant
                                               frequency
                                               ``spikes'' being
                                               present within
                                               2 Hz.