Control Position--
                                          5%.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.b.2...........  Critical Azimuth.....  Torque--< plus-         Stationary Hover.      Record results for               X      X
                                          minus>3%, Pitch        Augmentation On and    three relative wind
                                          Attitude--< plus-       Off.                   directions
                                          minus>1.5[deg], Bank                          (including the most
                                          Attitude--< plus-                              critical case) in
                                          minus>2[deg],                                 the critical
                                          Longitudinal Control                          quadrant. May be a
                                          Position--< plus-                              series of snapshot
                                          minus>5%, Lateral                             tests.
                                          Control Position--
                                          5%,
                                          Directional Control
                                          Position--< plus-
                                          minus>5%, Collective
                                          Control Position--
                                          5%.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.b.3...........  Control Response
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.b.3.a.........  Longitudinal.........  Pitch Rate--< plus-     Hover. Augmentation    Record results for a             X      X   This is a ``short
                                          minus>10% or 2[deg]/sec,                             The Off-axis                                conducted in a
                                          Pitch Attitude                                response must show                          hover, in ground
                                          Change--< plus-                                correct trend for                           effect, without
                                          minus>10% or                                  unaugmented cases.                          entering
                                          1.5[deg].                                                                                translational
                                                                                flight, to provide
                                                                                better visual
                                                                                reference.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.b.3.b.........  Lateral..............  Roll Rate--< plus-      Hover Augmentation On  Record results for a             X      X   This is a ``short
                                          minus>10% or 3[deg]/sec.                             The Off-axis                                conducted in a
                                          Roll Attitude                                 response must show                          hover, in ground
                                          Change--< plus-                                correct trend for                           effect, without
                                          minus>10% or 3[deg].                                                                             translational
                                                                                flight, to provide
                                                                                better visual
                                                                                reference.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.b.3.c.........  Directional..........  Yaw Rate--< plus-       Hover Augmentation On  Record results for a             X      X   This is a ``short
                                          minus>10% or 2[deg]/sec,                             The Off-axis                                conducted in a
                                          Heading Change--                              response must show                          hover, in ground
                                          10% or                            correct trend for                           effect, without
                                          2[deg].                           unaugmented cases.                          entering
                                                                                translational
                                                                                flight, to provide
                                                                                better visual
                                                                                reference.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.b.3.d.........  Vertical.............  Normal Acceleration--  Hover................  Record results for a             X      X
                                          0.1 g.                            step control input.
                                                                                The Off-axis
                                                                                response must show
                                                                                correct trend for
                                                                                unaugmented cases.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.c.............  Longitudinal Handling Qualities
--------------------------------------------------------------------------------------------------------------------------------------------------------

2.c.1...........  Control Response.....  Pitch Rate--< plus-     Cruise Augmentation    Results must be           X      X      X
                                          minus>10% or 2[deg]/sec,                             cruise airspeeds to
                                          Pitch Attitude                                include minimum
                                          Change--< plus-                                power required
                                          minus>10% or 1.5[deg].                               for a step control
                                                                                input. The Off-axis
                                                                                response must show
                                                                                correct trend for
                                                                                unaugmented cases.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.c.2...........  Static Stability.....  Longitudinal Control   Cruise or Climb,       Record results for a      X      X      X
                                          Position: < plus-       Autorotation,          minimum of two
                                          minus>10% of change    Augmentation On and    speeds on each side
                                          from trim or < plus-    Off.                   of the trim speed.
                                          minus>0.25 in (6.3                            May be a series of
                                          mm) or Longitudinal                           snapshot tests.
                                          Control Force: < plus-
                                          minus>0.5 lb (0.223
                                          daN) or < plus-
                                          minus>10%.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.c.3...........  Dynamic Stability
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.c.3.a.........  Long Term Response...  10% of     Cruise Augmentation    For periodic              X      X      X   The response may be
                                          calculated period,     On and Off.            responses, record                           unrepeatable
                                          10% of                            results for three                           throughout the
                                          time to \1/2\ or                              full cycles (6                              stated time for
                                          double amplitude, or                          overshoots after                            certain helicopters.
                                          0.02 of                           input completed) or                         In these cases, the
                                          damping ratio. For                            that sufficient to                          test should show at
                                          non-periodic                                  determine time to \1/                       least that a
                                          responses, the time                           2\ or double                                divergence is
                                          history must be                               amplitude, whichever                        identifiable. For
                                          matched within < plus-                         is less. For non-                           example: displacing
                                          minus>10% pitch; and                          periodic responses,                         the cyclic for a
                                          10%                               the test may be                             given time normally
                                          airspeed over a 20-                           terminated prior to                         excites this test or
                                          sec period following                          20 sec if the test                          until a given pitch
                                          release of the                                pilot determines                            attitude is achieved
                                          controls.                                     that the results are                        and then return the
                                                                                becoming                                    cyclic to the
                                                                                uncontrollably                              original position.
                                                                                divergent.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.c.3.b.........  Short Term Response..  1.5[deg]   Cruise or Climb.       Record results for at     X      X      X   A control doublet
                                          Pitch or < plus-        Augmentation On and    least two airspeeds.                        inserted at the
                                          minus>2[deg]/sec,      Off.                                                               natural frequency of
                                          Pitch Rate. < plus-                                                                        the aircraft
                                          minus>0.1 g Normal                                                                        normally excites
                                          Acceleration.                                                                             this test.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.c.4...........  Maneuvering Stability  Longitudinal Control   Cruise or Climb.       Record results for at     X      X      X
                                          Position--10% of       Augmentation On and    least two airspeeds
                                          change from trim or    Off.                   at 30[deg]-45[deg]
                                          0.25 in.                          roll angle. The
                                          (6.3 mm) or                                   force may be shown
                                          Longitudinal Control                          as a cross plot for
                                          Forces--< plus-                                irreversible
                                          minus>0.5 lb. (0.223                          systems. May be a
                                          daN) or < plus-                                series of snapshot
                                          minus>10%.                                    tests.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.d.............  Lateral and Directional Handling Qualities
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.d.1...........  Control Response
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.d.1.a.........  Lateral..............  Roll Rate--< plus-      Cruise Augmentation    Record results for at     X      X      X
                                          minus>10% or 3[deg]/sec.,                            including the speed
                                          Roll Attitude                                 at or near the
                                          Change--< plus-                                minimum power
                                          minus>10% or 3[deg].                                 Record results for a
                                                                                step control input.
                                                                                The Off-axis
                                                                                response must show
                                                                                correct trend for
                                                                                unaugmented cases.
--------------------------------------------------------------------------------------------------------------------------------------------------------

2.d.1.b.........  Directional..........  Yaw Rate--< plus-       Cruise Augmentation    Record data for at        X      X      X
                                          minus>10% or 2[deg]/sec.,                            including the speed
                                          Yaw Attitude Change--                         at or near the
                                          10% or                            minimum power
                                          2[deg].                           required airspeed.
                                                                                Record results for a
                                                                                step control input.
                                                                                The Off-axis
                                                                                response must show
                                                                                correct trend for
                                                                                unaugmented cases.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.d.2...........  Directional Static     Lateral Control        Cruise; or Climb (may  Record results for at     X      X      X   This is a steady
                   Stability.             Position--< plus-       use Descent instead    least two sideslip                          heading sideslip
                                          minus>10% of change    of Climb if            angles on either                            test.
                                          from trim or < plus-    desired),              side of the trim
                                          minus>0.25 in. (6.3    Augmentation On and    point. The force may
                                          mm) or Lateral         Off.                   be shown as a cross
                                          Control Force--< plus-                         plot for
                                          minus>0.5 lb. (0.223                          irreversible
                                          daN) or 10%, Roll                             systems. May be a
                                          Attitude--< plus-                              series of snapshot
                                          minus>1.5,                                    tests.
                                          Directional Control
                                          Position--< plus-
                                          minus>10% of change
                                          from trim or < plus-
                                          minus>0.25 in. (6.3
                                          mm) or Directional
                                          Control Force--< plus-
                                          minus>1 lb. (0.448
                                          daN) or 10%.,
                                          Longitudinal Control
                                          Position--< plus-
                                          minus>10% of change
                                          from trim or < plus-
                                          minus>0.25 in. (6.3
                                          mm), Vertical
                                          Velocity--< plus-
                                          minus>100 fpm (0.50m/
                                          sec) or 10%.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.d.3...........  Dynamic Lateral and Directional Stability
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.d.3.a.........  Lateral-Directional    0.5 sec.   Cruise or Climb.       Record results for at     X      X      X
                   Oscillations.          or 10%     Augmentation On/Off.   least two airspeeds.
                                          of period, < plus-                             The test must be
                                          minus>10% of time to                          initiated with a
                                          \1/2\ or double                               cyclic or a pedal
                                          amplitude or < plus-                           doublet input.
                                          minus>0.02 of                                 Record results for
                                          damping ratio, < plus-                         six full cycles (12
                                          minus>20% or 1 sec of time                           input completed) or
                                          difference between                            that sufficient to
                                          peaks of bank and                             determine time to or
                                          sideslip. For non-                            double amplitude,
                                          periodic responses,                           whichever is less.
                                          the time history                              For non-periodic
                                          must be matched                               response, the test
                                          within < plus-                                 may be terminated
                                          minus>10% yaw; 10% roll                                the test pilot
                                          angle, and < plus-                             determines that the
                                          minus>10% airspeed,                           results are becoming
                                          over a 20 sec period                          uncontrollably
                                          roll angle following                          divergent.
                                          release of the
                                          controls.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.d.3.b.........  Spiral Stability.....  2[deg] or  Cruise or Climb.       Record the results of     X      X      X
                                          10% roll   Augmentation On and    a release from pedal
                                          angle.                 Off.                   only or cyclic only
                                                                                turns for 20 sec.
                                                                                Results must be
                                                                                recorded from turns
                                                                                in both directions.
                                                                                Terminate check at
                                                                                zero roll angle or
                                                                                when the test pilot
                                                                                determines that the
                                                                                attitude is becoming
                                                                                uncontrollably
                                                                                divergent.
--------------------------------------------------------------------------------------------------------------------------------------------------------

2.d.3.c.........  Adverse/Proverse Yaw.  Correct Trend, < plus-  Cruise or Climb.       Record the time           X      X      X
                                          minus>2[deg]           Augmentation On and    history of initial
                                          transient sideslip     Off.                   entry into cyclic
                                          angle.                                        only turns, using
                                                                                only a moderate rate
                                                                                for cyclic input.
                                                                                Results must be
                                                                                recorded for turns
                                                                                in both directions.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3. Motion System
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.a.............  Frequency Response
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                         Based on Simulator     N/A..................  Required as part of       X      X      X
                                          Capability.                                   MQTG but not
                                                                                required as part of
                                                                                continuing
                                                                                qualification
                                                                                evaluations. The
                                                                                test must
                                                                                demonstrate
                                                                                frequency response
                                                                                of the motion system
                                                                                as specified by the
                                                                                applicant for flight
                                                                                simulator
                                                                                qualification.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.b.............  Leg Balance
--------------------------------------------------------------------------------------------------------------------------------------------------------
                  Leg Balance..........  Based on Simulator     N/A..................  Required as part of       X      X      X
                                          Capability.                                   MQTG but not
                                                                                required as part of
                                                                                continuing
                                                                                evaluations. The
                                                                                test must
                                                                                demonstrate motion
                                                                                system leg balance
                                                                                as specified by the
                                                                                applicant for flight
                                                                                simulator
                                                                                qualification.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.c.............  Turn Around
--------------------------------------------------------------------------------------------------------------------------------------------------------
                  Turn Around..........  Based on Simulator     N/A..................  Required as part of       X      X      X
                                          Capability.                                   MQTG but not
                                                                                required as part of
                                                                                continuing
                                                                                qualification
                                                                                evaluations. 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   See Paragraph 5.c. in
                                          signal, the test       the ``ground'' mode    the MQTG and at each                        this attachment for
                                          results must be        and in the             continuing                                  additional
                                          repeatable to within   ``flight'' mode of     qualification                               information. Note:
                                          0.05g      the motion system      evaluation. The test                        if there is no
                                          actual platform        operation.             is accomplished by                          difference in the
                                          linear acceleration                           injecting a motion                          model for ``ground''
                                          in each axis.                                 signal to generate                          and ``flight''
                                                                                movement of the                             operation of the
                                                                                platform. The input                         motion system, this
                                                                                must be such that                           should be described
                                                                                the rotational                              in an SOC and will
                                                                                accelerations,                              not require tests in
                                                                                rotational rates,                           both modes.
                                                                                and linear
                                                                                accelerations are
                                                                                inserted before the
                                                                                transfer from
                                                                                helicopter center of
                                                                                gravity to the pilot
                                                                                reference point with
                                                                                a minimum amplitude
                                                                                of 5[deg]/sec/sec,
                                                                                10[deg]/sec and
                                                                                0.3g, respectively.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.e.............  Motion Cueing Performance Signature
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                Required as part of                         See paragraph 5.d.,
                                                                                MQTG but not                                of this attachment,
                                                                                required as part of                         Motion cueing
                                                                                continuing                                  performance
                                                                                qualification                               signature.
                                                                                evaluations. These
                                                                                tests must be run
                                                                                with the motion
                                                                                buffet mode disabled.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.e.1...........  Takeoff (all engines)  As specified by the    Ground...............  Pitch attitude due to     X      X      X   Associated to test
                                          sponsor for flight                            initial climb should                        number 1.c.1.
                                          simulator                                     dominate over cab
                                          qualification.                                tilt due to
                                                                                longitudinal
                                                                                acceleration.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.e.2...........  Hover performance      As specified by the    Ground...............  .....................            X      X   Associated to test
                   (IGE and OGE).         sponsor for flight                                                                        number 1.d.
                                          simulator
                                          qualification.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.e.3...........  Autorotation (entry).  As specified by the    Flight...............  .....................            X      X   Associated to test
                                          sponsor for flight                                                                        number 1.i.
                                          simulator
                                          qualification.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.e.4...........  Landing (all engines)  As specified by the    Flight...............  .....................     X      X      X   Associated to test
                                          sponsor for flight                                                                        number 1.j.1.
                                          simulator
                                          qualification.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.e.5...........  Autorotation           As specified by the    Flight...............  .....................            X      X   Associated to test
                   (landing).             sponsor for flight                                                                        number 1.j.4.
                                          simulator
                                          qualification.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.e.6...........  Control Response
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.e.6.a.........  Longitudinal.........  As specified by the    Flight...............  .....................     X      X      X   Associated to test
                                          sponsor for flight                                                                        number 2.c.1.
                                          simulator
                                          qualification.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.e.6.b.........  Lateral..............  As specified by the    Ground...............  .....................     X      X      X   Associated to test
                                          sponsor for flight                                                                        number 2.d.1.a.
                                          simulator
                                          qualification.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.e.6.c.........  Directional..........  As specified by the    .....................  .....................     X      X      X   Associated to test
                                          sponsor for flight                                                                        number 2.d.1.c.
                                          simulator
                                          qualification.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.f.............  Characteristic Motion Cues--For all of the following tests, the simulator test results                           Characteristic motion
                   must exhibit the overall appearance and trends of the helicopter data, with at least                             cues may be separate
                   three (3) of the predominant frequency ``spikes'' being present within 2 Hz.                         from the ``main''
                                                                                motion system.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.f.1...........  Thrust effect with     .....................  Ground...............  The test must be                        X
                   brakes set.                                                          conducted within 5%
                                                                                of the maximum
                                                                                possible thrust with
                                                                                brakes set.
--------------------------------------------------------------------------------------------------------------------------------------------------------

3.f.2...........  Buffet with landing    .....................  Flight...............  The test must be                        X   The airspeed selected
                   gear extended.                                                       conducted at an                             for this test should
                                                                                airspeed below                              be within the range
                                                                                landing gear                                where the operator
                                                                                limiting airspeed.                          typically conducts
                                                                                operations with the
                                                                                landing gear
                                                                                extended.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.f.3...........  Buffet at approach-to- .....................  Flight...............  The test must be                        X
                   stall.                                                               conducted for
                                                                                approach to stall.
                                                                                Post stall
                                                                                characteristics are
                                                                                not required.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.f.4...........  Buffet at high         .....................  Flight...............  .....................                   X
                   airspeeds.
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.f.5...........  In-flight vibrations.  .....................  Flight (clean          .....................                   X
                                                                 configuration).
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.f.6...........  Thrust effect with     .....................  Ground...............  The test must be                        X
                   brakes set.                                                          conducted within 5%
                                                                                of the maximum
                                                                                possible thrust with
                                                                                brakes set.
--------------------------------------------------------------------------------------------------------------------------------------------------------
4. Visual System
--------------------------------------------------------------------------------------------------------------------------------------------------------
4.a.............  Visual System Response Time: (Choose either test 4.a.1. or 4.a.2. to satisfy test 4.a.,
                   Visual System Response Time Test. This test is also sufficient for motion system response
                   timing and flight deck instrument response timing.)
--------------------------------------------------------------------------------------------------------------------------------------------------------
4.a.1...........  Latency
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                         150 ms (or less)       Takeoff, climb, and    One test is required      X
                                          after helicopter       descent.               in each axis (pitch,
                                          response.                                     roll and yaw) for
                                                                                each of the three
                                                                                conditions (take-
                                                                                off, cruise, and
                                                                                approach or landing).
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                         100 ms (or less)       Climb, cruise,         One test is required             X      X
                                          after helicopter       descent, and hover.    in each axis (pitch,
                                          response.                                     roll and yaw) for
                                                                                each of the three
                                                                                conditions (take-
                                                                                off, cruise, and
                                                                                approach or landing).
--------------------------------------------------------------------------------------------------------------------------------------------------------
4.a.2...........  Transport Delay
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                If Transport Delay is
                                                                                the chosen method to
                                                                                demonstrate relative
                                                                                responses, the
                                                                                sponsor and the NSPM
                                                                                will use the latency
                                                                                values to ensure
                                                                                proper simulator
                                                                                response when
                                                                                reviewing those
                                                                                existing tests where
                                                                                latency can be
                                                                                identified (e.g.,
                                                                                short period, roll
                                                                                response, rudder
                                                                                response).
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                         150 ms (or less)       N/A..................  A separate test is        X
                                          after controller                              required in each
                                          movement.                                     axis (pitch, roll,
                                                                                and yaw).
--------------------------------------------------------------------------------------------------------------------------------------------------------

                                         100 ms (or less)       N/A..................  A separate test is               X      X
                                          after controller                              required in each
                                          movement.                                     axis (pitch, roll,
                                                                                and yaw).
--------------------------------------------------------------------------------------------------------------------------------------------------------
4.b.............  Field of View
--------------------------------------------------------------------------------------------------------------------------------------------------------
4.b.1...........  Continuous field of    The simulator must     N/A..................  An SOC is required        X                 Horizontal field of
                   view.                  provide a continuous                          and must explain the                        view is centered on
                                          field of view of at                           geometry of the                             the zero degree
                                          least 75[deg]                                 installation.                               azimuth line
                                          horizontally and                              Additional                                  relative to the
                                          30[deg] vertically                            horizontal field of                         aircraft fuselage.
                                          per pilot seat or                             view capability may                         Field of view may be
                                          the number of                                 be added at the                             measured using a
                                          degrees necessary to                          sponsor's discretion                        visual test pattern
                                          meet the visual                               provided the minimum                        filling the entire
                                          ground segment                                field of view is                            visual scene (all
                                          requirement,                                  retained.                                   channels) with a
                                          whichever is                                                                              matrix of black and
                                          greater. Both pilot                                                                       white 5[deg]
                                          seat visual systems                                                                       squares.
                                          must be operable
                                          simultaneously. Wide-
                                          angle systems
                                          providing cross-
                                          flight deck viewing
                                          (for both pilots
                                          simultaneously) must
                                          provide a minimum
                                          field of view of at
                                          least 146[deg]
                                          horizontally and
                                          36[deg] vertically.
                                          Any geometric error
                                          between the Image
                                          Generator eye point
                                          and the pilot eye
                                          point must be 8[deg]
                                          or less.
--------------------------------------------------------------------------------------------------------------------------------------------------------
4.b.2...........  Continuous field of    The simulator must     N/A..................  An SOC is required               X          Horizontal field of
                   view.                  provide a continuous                          and must explain the                        view is centered on
                                          field of view of at                           geometry of the                             the zero degree
                                          least 146[deg]                                installation.                               azimuth line
                                          horizontally and                              Horizontal field of                         relative to the
                                          36[deg] vertically                            view of at least                            aircraft fuselage.
                                          or the number of                              146[deg] (including                         Field of view may be
                                          degrees necessary to                          not less than                               measured using a
                                          meet the visual                               73[deg] measured                            visual test pattern
                                          ground segment                                either side of the                          filling the entire
                                          requirement,                                  center of the design                        visual scene (all
                                          whichever is                                  eye point).                                 channels) with a
                                          greater. The minimum                          Additional                                  matrix of black and
                                          horizontal field of                           horizontal field of                         white 5[deg]
                                          view coverage must                            view capability may                         squares.
                                          be plus and minus                             be added at the
                                          one-half (\1/2\) of                           sponsor's discretion
                                          the minimum                                   provided the minimum
                                          continuous field of                           field of view is
                                          view requirement,                             retained. Vertical
                                          centered on the zero                          field of view of at
                                          degree azimuth line                           least 36[deg]
                                          relative to the                               measured from the
                                          aircraft fuselage.                            pilot's and co-
                                          Any geometric error                           pilot's eye point.
                                          between the Image
                                          Generator eye point
                                          and the pilot eye
                                          point must be 8[deg]
                                          or less.
--------------------------------------------------------------------------------------------------------------------------------------------------------

4.b.3...........  Continuous field of    Continuous field of    N/A..................  An SOC is required                      X   The horizontal field
                   view.                  view of at least                              and must explain the                        of view is
                                          176[deg] horizontal                           geometry of the                             traditionally
                                          and 56[deg] vertical                          installation.                               described as a
                                          field of view for                             Horizontal field of                         180[deg] field of
                                          each pilot                                    view is centered on                         view. However, the
                                          simultaneously. Any                           the zero degree                             field of view is
                                          geometric error                               azimuth line                                technically no less
                                          between the Image                             relative to the                             than 176[deg]. Field
                                          Generator eye point                           aircraft fuselage.                          of view may be
                                          and the pilot eye                             Horizontal field of                         measured using a
                                          point must be 8[deg]                          view must be at                             visual test pattern
                                          or less.                                      least 176[deg]                              filling the entire
                                                                                (including not less                         visual scene (all
                                                                                than 88[deg] either                         channels) with a
                                                                                side of the center                          matrix of black and
                                                                                of the design eye                           white 5[deg]
                                                                                point). Additional                          squares.
                                                                                horizontal field of
                                                                                view capability may
                                                                                be added at the
                                                                                sponsor's discretion
                                                                                provided the minimum
                                                                                field of view is
                                                                                retained. Vertical
                                                                                field of view must
                                                                                not be less than a
                                                                                total of 56[deg]
                                                                                measured from the
                                                                                pilot's and co-
                                                                                pilot's eye point.
--------------------------------------------------------------------------------------------------------------------------------------------------------
4.c.............  Surface contrast       Not less than 5:1....  N/A..................  The ratio is                            X   Measurements may be
                   ratio.                                                               calculated by                               made using a 1[deg]
                                                                                dividing the                                spot photometer and
                                                                                brightness level of                         a raster drawn test
                                                                                the center, bright                          pattern filling the
                                                                                square (providing at                        entire visual scene
                                                                                least 2 foot-                               (all channels) with
                                                                                lamberts or 7 cd/m2)                        a test pattern of
                                                                                by the brightness                           black and white
                                                                                level of any                                squares, 5 per
                                                                                adjacent dark square.                       square, with a white
                                                                                square in the center
                                                                                of each channel.
                                                                                During contrast
                                                                                ratio testing,
                                                                                simulator aft-cab
                                                                                and flight deck
                                                                                ambient light levels
                                                                                should be zero.
--------------------------------------------------------------------------------------------------------------------------------------------------------
4.d.............  Highlight brightness.  Not less than six (6)  N/A..................  Measure the                             X   Measurements may be
                                          foot-lamberts (20 cd/                         brightness of the                           made using a 1[deg]
                                          m\2\).                                        center, white square                        spot photometer and
                                                                                while superimposing                         a raster drawn test
                                                                                a highlight on that                         pattern filling the
                                                                                white square. The                           entire visual scene
                                                                                use of calligraphic                         (all channels) with
                                                                                capabilities to                             a test pattern of
                                                                                enhance the raster                          black and white
                                                                                brightness is                               squares, 5 per
                                                                                acceptable; however,                        square, with a white
                                                                                measuring light                             square in the center
                                                                                points is not                               of each channel.
                                                                                acceptable.
--------------------------------------------------------------------------------------------------------------------------------------------------------

4.e.............  Surface resolution...  Not greater than two   N/A..................  An SOC is required               X      X   The eye will subtend
                                          (2) arc minutes.                              and must include the                        two (2) arc minutes
                                                                                appropriate                                 when positioned on a
                                                                                calculations and an                         3[deg] glide slope,
                                                                                explanation of those                        6,876 ft slant range
                                                                                calculations.                               from the centrally
                                                                                located threshold of
                                                                                a black runway
                                                                                surface painted with
                                                                                white threshold bars
                                                                                that are 16 ft wide
                                                                                with 4-foot gaps
                                                                                between the bars.
                                                                                This requirement is
                                                                                the same as 4 arc
                                                                                minutes per optical
                                                                                line pair.
--------------------------------------------------------------------------------------------------------------------------------------------------------
4.f.............  Light point size.....  Not greater than five  N/A..................  An SOC is required               X      X   Light point size may
                                          (5) arc-minutes.                              and must include the                        be measured using a
                                                                                relevant                                    test pattern
                                                                                calculations and an                         consisting of a
                                                                                explanation of those                        centrally located
                                                                                calculations.                               single row of light
                                                                                points reduced in
                                                                                length until
                                                                                modulation is just
                                                                                discernible in each
                                                                                visual channel. A
                                                                                row of 48 lights
                                                                                will form a 4[deg]
                                                                                angle or less.
--------------------------------------------------------------------------------------------------------------------------------------------------------
4.g.............  Light point contrast   .....................  .....................  .....................                       A 1[deg] spot
                   ratio.                                                                                photometer may be
                                                                                used to measure a
                                                                                square of at least
                                                                                1[deg] filled with
                                                                                light points (where
                                                                                light point
                                                                                modulation is just
                                                                                discernible) and
                                                                                compare the results
                                                                                to the measured
                                                                                adjacent background.
                                                                                During contrast
                                                                                ratio testing,
                                                                                simulator aft-cab
                                                                                and flight deck
                                                                                ambient light levels
                                                                                should be zero.
--------------------------------------------------------------------------------------------------------------------------------------------------------
4.g.1...........  .....................  Not less than 10:1...  N/A..................  An SOC is required        X
                                                                                and must include the
                                                                                relevant
                                                                                calculations.
--------------------------------------------------------------------------------------------------------------------------------------------------------
4.g.2...........  .....................  Not less than 25:1...  N/A..................  An SOC is required               X      X
                                                                                and must include the
                                                                                relevant
                                                                                calculations.
--------------------------------------------------------------------------------------------------------------------------------------------------------
4.h.............  Visual ground segment
--------------------------------------------------------------------------------------------------------------------------------------------------------

                                         The visible segment    Landing                The QTG must contain      X      X      X   Pre-position for this
                                          in the simulator       configuration,         appropriate                                 test is encouraged,
                                          must be within 20%     trimmed for            calculations and a                          and may be achieved
                                          of the segment         appropriate            drawing showing the                         via manual or
                                          computed to be         airspeed, at 100 ft    data used to                                autopilot control to
                                          visible from the       (30m) above the        establish the                               the desired
                                          helicopter flight      touchdown zone, on     helicopter location                         position.
                                          deck. The              glide slope with an    and the segment of
                                          tolerance(s) may be    RVR value set at       the ground that is
                                          applied at either or   1,200 ft (350m).       visible considering
                                          both ends of the                              design eyepoint, the
                                          displayed segment.                            helicopter attitude,
                                          However, lights and                           flight deck cut-off
                                          ground objects                                angle, and a
                                          computed to be                                visibility of 1200
                                          visible from the                              ft (350 m) RVR.
                                          helicopter flight                             Simulator
                                          deck at the near end                          performance must be
                                          of the visible                                measured against the
                                          segment must be                               QTG calculations.
                                          visible in the                               The data submitted
                                          simulator.                                    must include at
                                                                                least the following:.
                                                                                (1) Static helicopter
                                                                                dimensions as
                                                                                follows:.
                                                                                (i) Horizontal and
                                                                                vertical distance
                                                                                from main landing
                                                                                gear (MLG) to
                                                                                glideslope reception
                                                                                antenna..
                                                                                (ii) Horizontal and
                                                                                vertical distance
                                                                                from MLG to pilot's
                                                                                eyepoint..
                                                                                (iii) Static flight
                                                                                deck cutoff angle..
                                                                                (2) Approach data as
                                                                                follows:.
                                                                                (i) Identification of
                                                                                runway..
                                                                                (ii) Horizontal
                                                                                distance from runway
                                                                                threshold to
                                                                                glideslope intercept
                                                                                with runway..
                                                                                (iii) Glideslope
                                                                                angle..
                                                                                (iv) Helicopter pitch
                                                                                angle on approach..
                                                                                (3) Helicopter data
                                                                                for manual testing:.
                                                                                (i) Gross weight.....
                                                                                (ii) Helicopter
                                                                                configuration..
                                                                                (iii) Approach
                                                                                airspeed..
                                                                                If non-homogenous fog
                                                                                is used to obscure
                                                                                visibility, the
                                                                                vertical variation
                                                                                in horizontal
                                                                                visibility must be
                                                                                described and be
                                                                                included in the
                                                                                slant range
                                                                                visibility
                                                                                calculation used in
                                                                                the computations.
--------------------------------------------------------------------------------------------------------------------------------------------------------
5. Sound System
--------------------------------------------------------------------------------------------------------------------------------------------------------

                  The sponsor will not be required to repeat the helicopter tests (i.e., tests 5.a.1. through 5.a.8. (or 5.b.1. through 5.b.9.) and
                   5.c., as appropriate) during continuing qualification evaluations if frequency response and background noise test results are within
                   tolerance when compared to the initial qualification evaluation results, and the sponsor shows that no software changes have occurred
                   that will affect the helicopter test results. If the frequency response test method is chosen and fails, the sponsor may elect to fix
                   the frequency response problem and repeat the test or the sponsor may elect to repeat the helicopter tests. If the helicopter tests
                   are repeated during continuing qualification evaluations, the results may be compared against initial qualification evaluation
                   results or helicopter master data
--------------------------------------------------------------------------------------------------------------------------------------------------------
5.a.............  Basic requirements
--------------------------------------------------------------------------------------------------------------------------------------------------------
5.a.1...........  Ready for engine        5 dB per  Ground...............  Normal condition                        X   .....................
                   start.                 \1/3\ octave band.                            prior to engine
                                                                                start. The APU
                                                                                should be on if
                                                                                appropriate.
--------------------------------------------------------------------------------------------------------------------------------------------------------
5.a.2...........  All engines at idle;    5 dB per  Ground...............  Normal condition                        X   .....................
                   rotor not turning      \1/3\ octave band.                            prior to lift-off.
                   (if applicable) and
                   rotor turning.
--------------------------------------------------------------------------------------------------------------------------------------------------------
5.a.3...........  Hover................  5 dB per   Hover................  .....................                   X
                                          \1/3\ octave band.
--------------------------------------------------------------------------------------------------------------------------------------------------------
5.a.4...........  Climb................   5 dB per  En-route climb.......  Medium altitude......                   X   .....................
                                          \1/3\ octave band.
--------------------------------------------------------------------------------------------------------------------------------------------------------
5.a.5...........  Cruise...............   5 dB per  Cruise...............  Normal cruise                           X   .....................
                                          \1/3\ octave band.                            configuration.
--------------------------------------------------------------------------------------------------------------------------------------------------------
5.a.6...........  Final approach.......   5 dB per  Landing..............  Constant airspeed,                      X   .....................
                                          \1/3\ octave band.                            gear down.
--------------------------------------------------------------------------------------------------------------------------------------------------------
5.b.............  Special cases
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                          5 dB per  As appropriate.......  .....................                   X   These special cases
                                          \1/3\ octave band.                                                                        are identified as
                                                                                particularly
                                                                                significant during
                                                                                critical phases of
                                                                                flight and ground
                                                                                operations for a
                                                                                specific helicopter
                                                                                type or model.
--------------------------------------------------------------------------------------------------------------------------------------------------------
5.c.............  Background noise
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                         3 dB per   As appropriate.......  Results of the                          X   The simulated sound
                                          \1/3\ octave band.                            background noise at                         will be evaluated to
                                                                                initial                                     ensure that the
                                                                                qualification must                          background noise
                                                                                be included in the                          does not interfere
                                                                                MQTG. Measurements                          with training,
                                                                                must be made with                           testing, or
                                                                                the simulation                              checking.
                                                                                running, the sound
                                                                                muted, and a
                                                                                ``dead'' flight deck.
--------------------------------------------------------------------------------------------------------------------------------------------------------
5.d.............  Frequency response
--------------------------------------------------------------------------------------------------------------------------------------------------------

                                         5 dB on    .....................  Applicable only to                      X   Measurements are
                                          three (3)                                     Continuing                                  compared to those
                                          consecutive bands                             Qualification                               taken during initial
                                          when compared to                              Evaluations.                                qualification
                                          initial evaluation;                          If frequency response                        evaluation.
                                          and  2                            plots are provided
                                          dB when comparing                             for each channel at
                                          the average of the                            the initial
                                          absolute differences                          evaluation, these
                                          between initial and                           plots may be
                                          continuing                                    repeated at the
                                          qualification                                 continuing
                                          evaluation.                                   qualification
                                                                                evaluation with the
                                                                                following tolerances
                                                                                applied:.
                                                                                (a) The continuing
                                                                                qualification \1/3\
                                                                                octave band
                                                                                amplitudes should
                                                                                not exceed < plus-
                                                                                minus> 5 dB for
                                                                                three consecutive
                                                                                bands when compared
                                                                                to initial results.
                                                                                (b) The average of
                                                                                the sum of the
                                                                                absolute differences
                                                                                between initial and
                                                                                continuing
                                                                                qualification
                                                                                results must not
                                                                                exceed 2 dB (refer
                                                                                to table C2C in
                                                                                Appendix C).
--------------------------------------------------------------------------------------------------------------------------------------------------------

-----------------------------------------------------------------------

Begin Information

3. General

    a. If relevant winds are present in the objective data, the wind
vector should be clearly noted as part of the data presentation,
expressed in conventional terminology, and related to the runway
being used for test near the ground.
    b. The reader is encouraged to review the Airplane Flight
Simulator Evaluation Handbook, Volumes I and II, published by the
Royal Aeronautical Society, London, UK, and FAA Advisory Circulars
(AC) 25-7, as may be amended, Flight Test Guide for Certification of
Transport Category Airplanes, and (AC) 23-8, as may be amended,
Flight Test Guide for Certification of Part 23 Airplanes, for
references and examples regarding flight testing requirements and
techniques.

4. Control Dynamics

    a. General. The characteristics of a helicopter flight control
system have a major effect on the handling qualities. A significant
consideration in pilot acceptability of a helicopter is the ``feel''
provided through the flight controls. Considerable effort is
expended on helicopter feel system design so that pilots will be
comfortable and will consider the helicopter desirable to fly. In
order for an FFS to be representative, it should ``feel'' like the
helicopter being simulated. Compliance with this requirement is
determined by comparing a recording of the control feel dynamics of
the FFS to actual helicopter measurements in the takeoff, cruise and
landing configurations.
    (1) Recordings such as free response to an impulse or step
function are classically used to estimate the dynamic properties of
electromechanical systems. In any case, it is only possible to
estimate the dynamic properties as a result of only being able to
estimate true inputs and responses. Therefore, it is imperative that
the best possible data be collected since close matching of the FFS
control loading system to the helicopter system is essential. The
required dynamic control tests are described in Table C2A of this
attachment.
    (2) For initial and upgrade evaluations, the QPS requires that
control dynamics characteristics be measured and recorded directly
from the flight controls (Handling Qualities--Table C2A). This
procedure is usually accomplished by measuring the free response of
the controls using a step or impulse input to excite the system. The
procedure should be accomplished in the takeoff, cruise and landing
flight conditions and configurations.
    (3) For helicopters with irreversible control systems,
measurements may be obtained on the ground if proper pilot-static
inputs are provided to represent airspeeds typical of those
encountered in flight. Likewise, it may be shown that for some
helicopters, hover, climb, cruise, and autorotation have like
effects. Thus, one may suffice for another. If either or both
considerations apply, engineering validation or helicopter
manufacturer rationale should be submitted as justification for
ground tests or for eliminating a configuration. For FFSs requiring
static and dynamic tests at the controls, special test fixtures will
not be required during initial and upgrade evaluations if the QTG
shows both test fixture results and the results of an alternate
approach (e.g., computer plots that were produced concurrently and
show satisfactory agreement). Repeat of the alternate method during
the initial evaluation would satisfy this test requirement.
    b. Control Dynamics Evaluations. The dynamic properties of
control systems are often stated in terms of frequency, damping, and
a number of other classical measurements. In order to establish a
consistent means of validating test results for FFS control loading,
criteria are needed that will clearly define the measurement
interpretation and the applied tolerances. Criteria are needed for
underdamped, critically damped and overdamped systems. In the case
of an underdamped system with very light damping, the system may be
quantified in terms of frequency and damping. In critically damped
or overdamped systems, the frequency and damping are not readily
measured from a response time history. Therefore, the following
suggested measurements may be used:
    (1) For Levels C and D simulators. Tests to verify that control
feel dynamics represent the helicopter should show that the dynamic
damping cycles (free response of the controls) match those of the
helicopter within specified tolerances. The NSPM recognizes that
several different testing

methods may be used to verify the control feel dynamic response. The
NSPM will consider the merits of testing methods based on
reliability and consistency. One acceptable method of evaluating the
response and the tolerance to be applied is described below for the
underdamped and critically damped cases. A sponsor using this method
to comply with the QPS requirements should perform the tests as
follows:
    (a) Underdamped Response. Two measurements are required for the
period, the time to first zero crossing (in case a rate limit is
present) and the subsequent frequency of oscillation. It is
necessary to measure cycles on an individual basis in case there are
non-uniform periods in the response. Each period will be
independently compared to the respective period of the helicopter
control system and, consequently, will enjoy the full tolerance
specified for that period. The damping tolerance will be applied to
overshoots on an individual basis. Care should be taken when
applying the tolerance to small overshoots since the significance of
such overshoots becomes questionable. Only those overshoots larger
than 5 percent of the total initial displacement should be
considered significant. The residual band, labeled T(Ad)
on Figure C2A is 5 percent of the initial displacement
amplitude Ad from the steady state value of the
oscillation. Only oscillations outside the residual band are
considered significant. When comparing FFS data to helicopter data,
the process should begin by overlaying or aligning the FFS and
airplane steady state values and then comparing amplitudes of
oscillation peaks, the time of the first zero crossing, and
individual periods of oscillation. The FFS should show the same
number of significant overshoots to within one when compared against
the helicopter airplane data. The procedure for evaluating the
response is illustrated in Figure C2A.
    (b) Critically damped and Overdamped Response. Due to the nature
of critically damped and overdamped responses (no overshoots), the
time to reach 90 percent of the steady state (neutral point) value
should be the same as the helicopter within 10 percent.
The simulator response must be critically damped also. Figure C2B
illustrates the procedure.
    (c) Special considerations. Control systems that exhibit
characteristics other than classical overdamped or underdamped
responses should meet specified tolerances. In addition, special
consideration should be given to ensure that significant trends are
maintained.
    (2) Tolerances.
    (a) The following summarizes the tolerances, ``T'' for
underdamped systems, and ``n'' is the sequential period of a full
cycle of oscillation. See Figure C2A of this attachment for an
illustration of the referenced measurements.

T(P0).....................................  10% of P0.
T(P1).....................................  20% of P1.
T(P2).....................................  30% of P2.
T(Pn).....................................  10(n+1)% of Pn.
T(An).....................................  10% of A1.
T(Ad).....................................  5% of Ad =
                                             residual band.
Significant overshoots....................  First overshoot and < plus-
                                             minus>1 subsequent
                                             overshoots.

    (b) The following tolerance applies to critically damped and
overdamped systems only. See Figure C2B for an illustration of the
reference measurements:

T(P0).....................................  10% of P0.

End Information

-----------------------------------------------------------------------

Begin QPS Requirement

    c. Alternative method for control dynamics evaluation.
    (1) An alternative means for validating control dynamics for
aircraft with hydraulically powered flight controls and artificial
feel systems is by the measurement of control force and rate of
movement. For each axis of pitch, roll, and yaw, the control must be
forced to its maximum extreme position for the following distinct
rates. These tests are conducted under normal flight and ground
conditions.
    (a) Static test--Slowly move the control so that a full sweep is
achieved within 95-105 seconds. A full sweep is defined as movement
of the controller from neutral to the stop, usually aft or right
stop, then to the opposite stop, then to the neutral position.
    (b) Slow dynamic test--Achieve a full sweep within 8-12 seconds.
    (c) Fast dynamic test--Achieve a full sweep in within 3-5
seconds.

    Note: Dynamic sweeps may be limited to forces not exceeding 100
lbs. (44.5 daN).

    (d) Tolerances.
    (i) Static test--see Table C2A, Full Flight Simulator (FFS)
Objective Tests, Items 2.a.1., 2.a.2., and 2.a.3.
    (ii) Dynamic test 2 lbs (0.9 daN) or 10%
on dynamic increment above static test.

End QPS Requirement

-----------------------------------------------------------------------

Begin Information

    d. The FAA is open to alternative means that are justified and
appropriate to the application. For example, the method described
here may not apply to all manufacturers' systems and certainly not
to aircraft with reversible control systems. Each case is considered
on its own merit on an ad hoc basis. If the FAA finds that
alternative methods do not result in satisfactory performance, more
conventionally accepted methods will have to be used.
BILLING CODE 4910-13-P

End Information

-----------------------------------------------------------------------

[GRAPHIC] [TIFF OMITTED] TP22OC07.032

BILLING CODE 4910-13-C

End Information

-----------------------------------------------------------------------

5. [Reserved]

-----------------------------------------------------------------------

Begin Information

6. Motion System

    a. General.
    (1) Pilots use continuous information signals to regulate the
state of the helicopter. In concert with the instruments and
outside-world visual information, whole-body motion feedback is
essential in assisting the pilot to control the helicopter dynamics,
particularly in the presence of external disturbances. The motion
system should meet basic objective performance criteria, and be
subjectively tuned at the pilot's seat position to represent the
linear and angular accelerations of the helicopter during a
prescribed minimum set of maneuvers and conditions. The response of
the motion cueing system should be repeatable.

    (2) The Motion System tests in Section 3 of Table C2A are
intended to qualify the FFS motion cueing system from a mechanical
performance standpoint. Additionally, the list of motion effects
provides a representative sample of dynamic conditions that should
be present in the flight simulator. An additional list of
representative, training-critical maneuvers, selected from Section
1, (Performance tests) and Section 2, (Handling Qualities tests) in
Table C2A, that should be recorded during initial qualification (but
without tolerance) to indicate the flight simulator motion cueing
performance signature have been identified (reference Section 3.e).
These tests are intended to help improve the overall standard of FFS
motion cueing.
    b. Motion System Checks. The intent of test 3a, Frequency
Response, test 3b, Leg Balance, and test 3c, Turn-Around Check, as
described in the Table of Objective Tests, is to demonstrate the
performance of the motion system hardware, and to check the
integrity of the motion set-up with regard to calibration and wear.
These tests are independent of the motion cueing software and should
be considered robotic tests.
    c. Motion System Repeatability. The intent of this test is to
ensure that the motion system software and motion system hardware
have not degraded or changed over time. This diagnostic test should
be completed during continuing qualification checks in lieu of the
robotic tests. This will allow an improved ability to determine
changes in the software or determine degradation in the hardware.
The following information delineates the methodology that should be
used for this test.
    (1) Input: The inputs should be such that rotational
accelerations, rotational rates, and linear accelerations are
inserted before the transfer from helicopter center of gravity to
pilot reference point with a minimum amplitude of 5 deg/sec/sec, 10
deg/sec and 0.3 g, respectively, to provide adequate analysis of the
output.
    (2) Recommended output:
    (a) Actual platform linear accelerations; the output will
comprise accelerations due to both the linear and rotational motion
acceleration;
    (b) Motion actuators position.
    d. Motion Cueing Performance Signature.
    (1) Background. The intent of this test is to provide
quantitative time history records of motion system response to a
selected set of automated QTG maneuvers during initial
qualification. It is not intended to be a comparison of the motion
platform accelerations against the flight test recorded
accelerations (i.e., not to be compared against helicopter cueing).
If there is a modification to the initially qualified motion
software or motion hardware (e.g., motion washout filter, simulator
payload change greater than 10%) then a new baseline may need to be
established.
    (2) Test Selection. The conditions identified in Section 3.e. in
Table C2A are those maneuvers where motion cueing is the most
discernible. They are general tests applicable to all types of
helicopters and should be completed for motion cueing performance
signature at any time acceptable to the NSPM prior to or during the
initial qualification evaluation, and the results included in the
MQTG.
    (3) Priority. Motion system should be designed with the intent
of placing greater importance on those maneuvers that directly
influence pilot perception and control of the helicopter motions.
For the maneuvers identified in section 3.e. in Table C2A, the
flight simulator motion cueing system should have a high tilt co-
ordination gain, high rotational gain, and high correlation with
respect to the helicopter simulation model.
    (4) Data Recording. The minimum list of parameters provided
should allow for the determination of the flight simulator's motion
cueing performance signature for the initial qualification
evaluation. The following parameters are recommended as being
acceptable to perform such a function:
    (a) Flight model acceleration and rotational rate commands at
the pilot reference point;
    (b) Motion actuators position;
    (c) Actual platform position;
    (d) Actual platform acceleration at pilot reference point.
    e. Motion Vibrations.
    (1) Presentation of results. The characteristic motion
vibrations may be used to verify that the flight simulator can
reproduce the frequency content of the helicopter when flown in
specific conditions. The test results should be presented as a Power
Spectral Density (PSD) plot with frequencies on the horizontal axis
and amplitude on the vertical axis. The helicopter data and flight
simulator data should be presented in the same format with the same
scaling. The algorithms used for generating the flight simulator
data should be the same as those used for the helicopter data. If
they are not the same then the algorithms used for the flight
simulator data should be proven to be sufficiently comparable. As a
minimum the results along the dominant axes should be presented and
a rationale for not presenting the other axes should be provided.
    (2) Interpretation of results. The overall trend of the PSD plot
should be considered while focusing on the dominant frequencies.
Less emphasis should be placed on the differences at the high
frequency and low amplitude portions of the PSD plot. During the
analysis, certain structural components of the flight simulator have
resonant frequencies that are filtered and may not appear in the PSD
plot. If filtering is required, the notch filter bandwidth should be
limited to 1 Hz to ensure that the buffet feel is not adversely
affected. In addition, a rationale should be provided to explain
that the characteristic motion vibration is not being adversely
affected by the filtering. The amplitude should match helicopter
data as described below. However, if the PSD plot was altered for
subjective reasons, a rationale should be provided to justify the
change. If the plot is on a logarithmic scale it may be difficult to
interpret the amplitude of the buffet in terms of acceleration. For
example, a 1x10-3 grams\2\/Hz would describe a heavy
buffet and may be seen in the deep stall regime. Alternatively, a
1x10-6 grams\2\/Hz buffet is almost imperceptable; but
may represent a flap buffet at low speed. The previous two examples
differ in magnitude by 1000. On a PSD plot this represents three
decades (one decade is a change in order of magnitude of 10; and two
decades is a change in order of magnitude of 100).
    f. Table C2B, Motion System Recommendations for Level C and
Level D Helicopter Simulators, contains a description of the
parameters that should be present in a ZFT level simulator motion
system to provide adequate on-set motion cues to helicopter pilots.
The information provided covers the six axes of motion (pitch, roll,
yaw, vertical, lateral, and longitudinal) and addresses
displacement, velocity, and acceleration. Also included is
information about the parameters for initial rotational and linear
acceleration. The parameters listed in this table apply only to ZFT
level simulators, and are presented here as recommended targets for
motion system capability. They are not requirements.

    Table C2B.--Motion System Recommendations for Level C and Level D
                          Helicopter Simulators
------------------------------------------------------------------------

------------------------------------------------------------------------
a..........  Motion System Envelope
a.1........  Pitch
a.1.a......     Displacement.  25[deg].
a.1.b......     Velocity.....  20[deg]/sec.
a.1.c......     Acceleration.  100[deg]/sec\2\.
a.2........  Roll
a.2.a......     Displacement.  25[deg].
a.2.b......     Velocity.....  20[deg]/sec.
a.2.c......     Acceleration.  100[deg]/sec\2\.
a.3........  Yaw
a.3.a......     Displacement.  25[deg].
a.3.b......     Velocity -...  20[deg]/sec.
a.3.c......     Acceleration.  100[deg]/sec\2\.
a.4........  Vertical
a.4.a......     Displacement.  34 in.

a.4.b......     Velocity.....  24 in.
a.4.c......     Acceleration.  0.8 g.
a.5........  Lateral
a.5.a......     Displacement.  45 in.
a.5.b......     Velocity.....  28 in/sec.
a.5.c......     Acceleration.  0.6 g.
a.6........  Longitudinal
a.6.a......     Displacement.  34 in.
a.6.b......     Velocity.....  28 in/sec.
a.6.c......     Acceleration.  0.6 g.
a.7........  Initial Rotational Acceleration Ratio
                .............  All axes 300[deg]/ sec\2\/sec.
a.8........  Initial Linear Acceleration Ratio
a.8.a......     Vertical.....  6g/sec.
a.8.b......     Lateral......  3g/sec.
a.8.c......     Longitudinal.  3g/sec.
------------------------------------------------------------------------

[GRAPHIC] [TIFF OMITTED] TP22OC07.064

BILLING CODE 4910-13-C

    Note: Motion system baseline performance repeatability tests
should be repeated if the simulator weight changes for any reason
(i.e., visual change or structural change). The new results should
be used for future comparison.

7. Sound System

    a. General. The total sound environment in the helicopter is
very complex, and changes with atmospheric conditions, helicopter
configuration, airspeed, altitude, and power settings. Flight deck
sounds are an important component of the flight deck operational
environment and provide valuable information to the flight crew.
These aural cues can either assist the crew (as an indication of an
abnormal situation), or hinder the crew (as a distraction or
nuisance). For effective training, the flight simulator should
provide flight deck sounds that are perceptible to the pilot during
normal and abnormal operations, and that are comparable to those of
the helicopter. The flight simulator operator should carefully
evaluate background noises in the location where the device will be
installed. To demonstrate compliance with the sound requirements,
the objective or validation tests in this attachment were selected
to provide a representative sample of normal static conditions
typically experienced by a pilot.
    b. Alternate propulsion. For FFS with multiple propulsion
configurations, any condition listed in Table C2A in this attachment
should be presented for evaluation as part of the QTG if identified
by the helicopter manufacturer or other data supplier as
significantly different due to a change in propulsion system (engine
or propeller).
    c. Data and Data Collection System.
    (1) Information provided to the flight simulator manufacturer
should be presented in the format suggested by the ``International
Air Transport Association (IATA) Flight Simulator Design and
Performance Data Requirements,'' as amended. This

information should contain calibration and frequency response data.
    (2) The system used to perform the tests listed in Table C2A
should comply with the following standards:
    (a) The specifications for octave, half octave, and third octave
band filter sets may be found in American National Standards
Institute (ANSI) S1.11-1986.
    (b) Measurement microphones should be type WS2 or better, as
described in International Electrotechnical Commission (IEC) 1094-4-
1995.
    (3) Headsets. If headsets are used during normal operation of
the helicopter they should also be used during the flight simulator
evaluation.
    (4) Playback equipment. Playback equipment and recordings of the
QTG conditions should be provided during initial evaluations.
    (5) Background noise.
    (a) Background noise is the noise in the flight simulator that
is not associated with the helicopter, but is caused by the flight
simulator's cooling and hydraulic systems and extraneous noise from
other locations in the building. Background noise can seriously
impact the correct simulation of helicopter sounds, and should be
kept below the helicopter sounds. In some cases, the sound level of
the simulation can be increased to compensate for the background
noise. However, this approach is limited by the specified tolerances
and by the subjective acceptability of the sound environment to the
evaluation pilot.
    (b) The acceptability of the background noise levels is
dependent upon the normal sound levels in the helicopter being
represented. Background noise levels that fall below the lines
defined by the following points, may be acceptable:
    (Note: These limits are for unweighted 1/3 octave band sound
levels. Meeting these limits for background noise does not ensure an
acceptable flight simulator. Helicopter sounds that fall below this
limit require careful review and may require lower limits on
background noise.)
    (6) Validation testing. Deficiencies in helicopter recordings
should be considered when applying the specified tolerances to
ensure that the simulation is representative of the helicopter.
Examples of typical deficiencies are:
    (a) Variation of data between tail numbers.
    (b) Frequency response of microphones.
    (c) Repeatability of the measurements.

                       Table C2C.--Example of Recurrent Frequency Response Test Tolerance
----------------------------------------------------------------------------------------------------------------
                                                                      Initial        Recurrent
                      Band center frequency                           results         results        Absolute
                                                                      (dBSPL)         (dBSPL)       difference
----------------------------------------------------------------------------------------------------------------
50..............................................................            75.0            73.8             1.2
63..............................................................            75.9            75.6             0.3
80..............................................................            77.1            76.5             0.6
100.............................................................            78.0            78.3             0.3
125.............................................................            81.9            81.3             0.6
160.............................................................            79.8            80.1             0.3
200.............................................................            83.1            84.9             1.8
250.............................................................            78.6            78.9             0.3
315.............................................................            79.5            78.3             1.2
400.............................................................            80.1            79.5             0.9
500.............................................................            80.7            79.8             0.9
630.............................................................            81.9            80.4             1.5
800.............................................................            73.2            74.1             0.9
1000............................................................            79.2            80.1             0.9
1250............................................................            80.7            82.8             2.1
1600............................................................            81.6            78.6             3.0
2000............................................................            76.2            74.4             1.8
2500............................................................            79.5            80.7             1.2
3150............................................................            80.1            77.1             3.0
4000............................................................            78.9            78.6             0.3
5000............................................................            80.1            77.1             3.0
6300............................................................            80.7            80.4             0.3
8000............................................................            84.3            85.5             1.2
10000...........................................................            81.3            79.8             1.5
12500...........................................................            80.7            80.1             0.6
16000...........................................................            71.1            71.1             0.0
                                                                 -----------------------------------------------
                                                                              Average                        1.1
----------------------------------------------------------------------------------------------------------------

8. Additional Information About Flight Simulator Qualification for New
or Derivative Helicopters

    a. Typically, a helicopter manufacturer's approved final data
for performance, handling qualities, systems or avionics is not
available until well after a new or derivative helicopter has
entered service. However, flight crew training and certification
often begins several months prior to the entry of the first
helicopter into service. Consequently, it may be necessary to use
preliminary data provided by the helicopter manufacturer for interim
qualification of flight simulators.
    b. In these cases, the NSPM may accept certain partially
validated preliminary helicopter and systems data, and early release
``red label'' avionics data in order to permit the necessary program
schedule for training, certification, and service introduction.
    c. Simulator sponsors seeking qualification based on preliminary