----------------------------------------------------------------------------------------------------------------
2.b.1......  Trimmed Flight    Torque--3%,        Flight IGE--     for several
              Positions.        Pitch            Sideward,        airspeed
                                Attitude--1.5[deg]   flight.          translational
                                , Bank           Augmentation     airspeed
                                Attitude--2[deg],                     forward
                                Longitudinal                      airspeed. May
                                Control                           be a series of
                                Position--5%.                       tests.
                                Lateral
                                Control
                                Position--5%,
                                Directional
                                Control
                                Position--5%,
                                Collective
                                Control
                                Position--5%.
----------------------------------------------------------------------------------------------------------------

2.b.2......  Critical Azimuth  Torque--3%,        Hover.           for three
                                Pitch            Augmentation     relative wind
                                Attitude--1.5[deg]                    most critical
                                , Bank                            case) in the
                                Attitude--2[deg],                     be a series of
                                Longitudinal                      snapshot
                                Control                           tests.
                                Position--5%,
                                Lateral
                                Control
                                Position--5%,
                                Directional
                                Control
                                Position--5%,
                                Collective
                                Control
                                Position--5%.
----------------------------------------------------------------------------------------------------------------
2.b.3......  Control Response
----------------------------------------------------------------------------------------------------------------
2.b.3.a....  Longitudinal....  Pitch Rate--     Hover            Record results         X    X   This is a
                                10% or     On and Off.      control input.                  test conducted
                                2[deg]/                     response must                   ground effect,
                                sec., Pitch                       show correct                    without
                                Attitude                          trend for                       entering
                                Change--10% or                      cases.                          flight, to
                                1.5[deg].                                                         provide better
                                                                                visual
                                                                                reference.
----------------------------------------------------------------------------------------------------------------
2.b.3.b....  Lateral.........  Roll Rate--      Hover            Record results         X    X   This is a
                                10% or     On and Off.      control input.                  test conducted
                                3[deg]/                     response must                   ground effect,
                                sec., Roll                        show correct                    without
                                Attitude                          trend for                       entering
                                Change--10% or                      cases.                          flight, to
                                3[deg].                                                     visual
                                                                                reference.
----------------------------------------------------------------------------------------------------------------
2.b.3.c....  Directional.....  Yaw Rate--10% or     Augmentation     for a step                      ``short time''
                                2[deg]/                     The Off-axis                    in a hover, in
                                sec., Heading                     response must                   ground effect,
                                Change--10% or                      trend for                       entering
                                2[deg].                     cases.                          flight, to
                                                                                provide better
                                                                                visual
                                                                                reference.
----------------------------------------------------------------------------------------------------------------
2.b.3.d....  Vertical........  Normal           Hover            Record results         X    X
                                Acceleration--   Augmentation     for a step
                                0.1 g.                      The Off-axis
                                                                  response must
                                                                  show correct
                                                                  trend for
                                                                  unaugmented
                                                                  cases.
----------------------------------------------------------------------------------------------------------------
2.c........  Longitudinal Handling Qualities
----------------------------------------------------------------------------------------------------------------
2.c.1......  Control Response  Pitch Rate--     Cruise           Results must be   X    X    X
                                10% or     On and Off.      two cruise
                                2[deg]/                     include
                                sec., Pitch                       minimum power
                                Attitude                          required
                                Change--10% or                      data for a
                                1.5[deg]                    input. The Off-
                                .                                 axis response
                                                                  must show
                                                                  correct trend
                                                                  for
                                                                  unaugmented
                                                                  cases.
----------------------------------------------------------------------------------------------------------------
2.c.2......  Static Stability  Longitudinal     Cruise or        Record results    X    X    X
                                Control          Climb.           for a minimum
                                Position:        Autorotation.    of two speeds
                                10% of     On and Off.      of the trim
                                change from                       speed. May be
                                trim or 0.25 in.                    snapshot
                                (6.3 mm) or                       tests.
                                Longitudinal
                                Control Force
                                : 0.5 lb.
                                (0.223 daN) or
                                10%.
----------------------------------------------------------------------------------------------------------------
2.c.3......  Dynamic Stability
----------------------------------------------------------------------------------------------------------------

2.c.3.a....  Long-Term         10%  Cruise           For periodic      X    X    X   The response
              Response.         of calculated    Augmentation     responses,                      may be
                                period, 10% of                      for three full                  throughout the
                                time to \1/2\                     cycles (6                       stated time
                                or double                         overshoots                      for certain
                                amplitude, or                     after input                     helicopters.
                                0.02 of                     that                            cases, the
                                damping                           sufficient to                   test should
                                ratio.For non-                    determine time                  show at least
                                periodic                          to \1/2\ or                     that a
                                responses, the                    double                          divergence is
                                time history                      amplitude,                      identifiable.
                                must be                           whichever is                    For example:
                                matched within                    less.                           Displacing the
                                3[deg]                      terminated                      given time
                                pitch; and                        prior to 20                     normally
                                5                     sec. if the                     excites this
                                kts airspeed                      test pilot                      test or until
                                over a 20 sec                     determines                      a given pitch
                                period                            that the                        attitude is
                                following                         results are                     achieved and
                                release of the                    becoming                        then return
                                controls.                         uncontrollably                  the cyclic to
                                                                  divergent..                     the original
                                                                                position. For
                                                                                non-periodic
                                                                                responses,
                                                                                results should
                                                                                show the same
                                                                                convergent or
                                                                                divergent
                                                                                character as
                                                                                the flight
                                                                                test data.
----------------------------------------------------------------------------------------------------------------
2.c.3.b....  Short-Term        1.5[deg]   Climb.           for at least                    doublet
                                Pitch or 2[deg]/    On and Off.                                      the natural
                                sec. Pitch                                                        frequency of
                                Rate. 0.1 g                                                       normally
                                Normal                                                            excites this
                                Acceleration.                                                     test. However,
                                                                                while input
                                                                                doublets are
                                                                                preferred over
                                                                                pulse inputs
                                                                                for
                                                                                Augmentation-
                                                                                Off tests, for
                                                                                Augmentation-
                                                                                On tests, when
                                                                                the short-term
                                                                                response
                                                                                exhibits 1st-
                                                                                order or
                                                                                deadbeat
                                                                                characteristic
                                                                                s,
                                                                                longitudinal
                                                                                pulse inputs
                                                                                may produce a
                                                                                more coherent
                                                                                response.
----------------------------------------------------------------------------------------------------------------
2.c.4......  Maneuvering       Longitudinal     Cruise or        Record results    X    X    X
              Stability.        Control          Climb.           for at least
                                Position--10% of   On and Off.      at 30[deg]-
                                change from                       45[deg] roll
                                trim or 0.25 in.                    force may be
                                (6.3 mm) or                       shown as a
                                Longitudinal                      cross plot for
                                Control                           irreversible
                                Forces--0.5 lb.                     be a series of
                                (0.223 daN) or                    snapshot
                                10%.
----------------------------------------------------------------------------------------------------------------
2.d........  Lateral and Directional Handling Qualities
----------------------------------------------------------------------------------------------------------------
2.d.1......  Control Response
----------------------------------------------------------------------------------------------------------------
2.d.1.a....  Lateral.........  Roll Rate--      Cruise           Record results    X    X    X
                                10% or     On and Off.      two airspeeds,
                                3[deg]/                     speed at or
                                sec., Roll                        near the
                                Attitude                          minimum power
                                Change--10% or                      airspeed.
                                3[deg].                     for a step
                                                                  control input.
                                                                  The Off-axis
                                                                  response must
                                                                  show correct
                                                                  trend for
                                                                  unaugmented
                                                                  cases.
----------------------------------------------------------------------------------------------------------------

2.d.1.b....  Directional.....  Yaw Rate--10% or     Augmentation     at least two
                                2[deg]/                     including the
                                sec., Yaw                         speed at or
                                Attitude                          near the
                                Change--10% or                      required
                                2[deg].                    Record results
                                                                  for a step
                                                                  control input.
                                                                  The Off-axis
                                                                  response must
                                                                  show correct
                                                                  trend for
                                                                  unaugmented
                                                                  cases..
----------------------------------------------------------------------------------------------------------------
2.d.2......  Directional       Lateral Control  Cruise; or       Record results    X    X    X   This is a
              Static            Position--10% of   Descent          two sideslip                    sideslip test
                                change from      instead of       angles on                       at a fixed
                                trim or 0.25 in.   desired),        the trim                        position.
                                (6.3 mm) or      Augmentation     point. The
                                Lateral          On and Off.      force may be
                                Control Force--                   shown as a
                                0.5 lb.                     irreversible
                                (0.223 daN) or                    systems. May
                                10%, Roll                         be a series of
                                Attitude--1.5,                      tests.
                                Directional
                                Control
                                Position--10% of
                                change from
                                trim or 0.25 in.
                                (6.3 mm) or
                                Directional
                                Control Force--
                                1
                                lb. (0.448
                                daN) or 10%,
                                Longitudinal
                                Control
                                Position--10% of
                                change from
                                trim or 0.25 in.
                                (6.3 mm),
                                Vertical
                                Velocity--100
                                fpm (0.50m/
                                sec) or 10%.
----------------------------------------------------------------------------------------------------------------
2.d.3......  Dynamic Lateral and Directional Stability
----------------------------------------------------------------------------------------------------------------
2.d.3.a....  Lateral-          0.5  Cruise or        Record results    X    X    X
              Directional       sec. or 10% of     Augmentation     two airspeeds.
                                period, 10% of                      be initiated
                                time to \1/2\                     with a cyclic
                                or double                         or a pedal
                                amplitude or                      doublet input.
                                0.02 of                     for six full
                                damping ratio,                    cycles (12
                                20% or                      after input
                                1                     completed) or
                                sec of time                       that
                                difference                        sufficient to
                                between peaks                     determine time
                                of bank and                       to \1/2\ or
                                sideslip. For                     double
                                non-periodic                      amplitude,
                                responses, the                    whichever is
                                time history                      less. The test
                                must be                           may be
                                matched within                    terminated
                                10                    prior to 20
                                knots                             sec if the
                                Airspeed;                         test pilot
                                5[deg]/s                    that the
                                Roll Rate or                      results are
                                5[deg]                      uncontrollably
                                Roll Attitude;                    divergent.
                                4[deg]/s
                                Yaw Rate or
                                4[deg]
                                Yaw Angle over
                                a 20 sec
                                period roll
                                angle
                                following
                                release of the
                                controls.
----------------------------------------------------------------------------------------------------------------
2.d.3.b....  Spiral            2[deg]     Climb.           results of a
                                or 10% roll   On and Off.      pedal only or
                                angle.                            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  Correct Trend,   Cruise or        Record the time   X    X    X
              Yaw.              2[deg]     Augmentation     initial entry
                                transient        On and Off.      into cyclic
                                sideslip                          only turns,
                                angle.                            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         N/A............  Required as       X    X    X
                                Simulator                         part of the
                                Capability.                       MQTG. 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         N/A............  Required as       X    X    X
                                Simulator                         part of the
                                Capability.                       MQTG. 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         N/A............  Required as       X    X    X
                                Simulator                         part of the
                                Capability.                       MQTG. The test
                                                                  must
                                                                  demonstrate a
                                                                  smooth turn-
                                                                  around (shift
                                                                  to opposite
                                                                  direction of
                                                                  movement) of
                                                                  the motion
                                                                  system as
                                                                  specified by
                                                                  the applicant
                                                                  for flight
                                                                  simulator
                                                                  qualification.
----------------------------------------------------------------------------------------------------------------
3.d........  Motion system repeatability
----------------------------------------------------------------------------------------------------------------
                               With the same    Accomplished in  Required as       X    X    X   See Paragraph
                                input signal,    both the         part of the                     6.c. in this
                                the test         ``ground''       the MQTG. The                   attachment for
                                results must     mode and in      test is                         additional
                                be repeatable    the ``flight''   accomplished                    information.
                                to within        mode of the      by injecting a                  Note: if there
                                0.05g      operation.       to generate                     difference in
                                actual                            movement of                     the model for
                                platform                          the platform.                   ``ground'' and
                                linear                            The input must                  ``flight''
                                acceleration                      be such that                    operation of
                                in each axis.                     the rotational                  the motion
                                                                  accelerations,                  system, this
                                                                  rotational                      should be
                                                                  rates, and                      described in
                                                                  linear                          an SOC and
                                                                  accelerations                   will not
                                                                  are inserted                    require tests
                                                                  before the                      in both modes.
                                                                  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                     See paragraph
                                                                  part of MQTG.                   6.d., of this
                                                                  These tests                     attachment,
                                                                  must be run                     Motion cueing
                                                                  with the                        performance
                                                                  motion buffet                   signature.
                                                                  mode disabled.
----------------------------------------------------------------------------------------------------------------
3.e.1......  Takeoff (all      As specified by  Ground.........  Pitch attitude    X    X    X   Associated to
              engines).         the sponsor                       due to initial                  test number
                                for flight                        climb must                      1.c.1.
                                simulator                         dominate over
                                qualification.                    cab tilt due
                                                                  to
                                                                  longitudinal
                                                                  acceleration.
----------------------------------------------------------------------------------------------------------------
3.e.2......  Hover             As specified by  Ground.........                         X    X   Associated to
              performance       the sponsor                                                       test number
              (IGE and OGE).    for flight                                                        1.d.
                                simulator
                                qualification.
----------------------------------------------------------------------------------------------------------------
3.e.3......  Autorotation      As specified by  Flight.........                         X    X   Associated to
              (entry).          the sponsor                                                       test number
                                for flight                                                        1.i.
                                simulator
                                qualification.
----------------------------------------------------------------------------------------------------------------

3.e.4......  Landing (all      As specified by  Flight.........                    X    X    X   Associated to
              engines).         the sponsor                                                       test number
                                for flight                                                        1.j.1.
                                simulator
                                qualification.
----------------------------------------------------------------------------------------------------------------
3.e.5......  Autorotation      As specified by  Flight.........                         X    X   Associated to
              (landing).        the sponsor                                                       test number
                                for flight                                                        1.j.4.
                                simulator
                                qualification.
----------------------------------------------------------------------------------------------------------------
3.e.6......  Control Response
----------------------------------------------------------------------------------------------------------------
3.e.6.a....  Longitudinal....  As specified by  Flight.........                    X    X    X   Associated to
                                the sponsor                                                       test number
                                for flight                                                        2.c.1.
                                simulator
                                qualification.
----------------------------------------------------------------------------------------------------------------
3.e.6.b....  Lateral.........  As specified by  Ground.........                    X    X    X   Associated to
                                the sponsor                                                       test number
                                for flight                                                        2.d.1.a.
                                simulator
                                qualification.
----------------------------------------------------------------------------------------------------------------
3.e.6.c....  Directional.....  As specified by                                     X    X    X   Associated to
                                the sponsor                                                       test number
                                for flight                                                        2.d.1.c.
                                simulator
                                qualification.
----------------------------------------------------------------------------------------------------------------
3.f........  Characteristic Motion (Vibration) Cues--For all of the following     ...  ...  ...  Characteristic
              tests, the simulator test results must exhibit the overall                          motion cues
              appearance and trends of the helicopter data, with at least three                   may be
              (3) of the predominant frequency ``spikes'' being present within                    separate from
              2 Hz.                                                                   the ``main''
                                                                                motion system.
----------------------------------------------------------------------------------------------------------------
3.f.1......  Vibrations--to    +3db to -6db or  (a) On ground    Characteristic              X   Correct trend
              include 1/Rev     10% of    (b) In flight..   include those                   comparison of
              vibrations        nominal                           that result                     vibration
              (where ``n'' is   vibration                         from operation                  amplitudes
              the number of     level in                          of the                          between
              main rotor        flight cruise                     helicopter                      different
              blades).          and correct                       (for example,                   maneuvers;
                                trend (see                        high airspeed,                  e.g., if the 1/
                                comment).                         retreating                      rev vibration
                                                                  blade stall,                    amplitude in
                                                                  extended                        the helicopter
                                                                  landing gear,                   is higher
                                                                  vortex ring or                  during steady
                                                                  settling with                   state turns
                                                                  power) in so                    than in level
                                                                  far as                          flight this
                                                                  vibration                       increasing
                                                                  marks an event                  trend should
                                                                  or helicopter                   be
                                                                  state, which                    demonstrated
                                                                  can be sensed                   in the
                                                                  in the flight                   simulator.
                                                                  deck.                           Additional
                                                                 [See Table C1A,                  examples of
                                                                  table entries                   vibrations may
                                                                  5.e. and 5.f.].                 include:
                                                                                (a) Low & High
                                                                                speed
                                                                                transition to
                                                                                and from
                                                                                hover;
                                                                                (b) Level
                                                                                flight;
                                                                                (c) Climb and
                                                                                descent
                                                                                (including
                                                                                vertical
                                                                                climb;
                                                                                (d) Auto-
                                                                                rotation;
                                                                                (e) Steady
                                                                                Turns.
----------------------------------------------------------------------------------------------------------------
3.f.2......  Buffet--Test      +3db to -6db or  On ground and    Characteristic              X   The recorded
              against           10% of                      include those                   for
              results for       nominal                           that result                     characteristic
              characteristic    vibration                         from operation                  buffets should
              buffet motion     level in                          of the                          allow the
              that can be       flight cruise                     helicopter                      checking of
              sensed in the     and correct                       (for example,                   relative
              flight deck.      trend (see                        high airspeed,                  amplitude for
                                comment).                         retreating                      different
                                                                  blade stall,                    frequencies.
                                                                  extended                       For atmospheric
                                                                  landing gear,                   disturbance,
                                                                  vortex ring or                  general
                                                                  settling with                   purpose models
                                                                  power) in so                    are acceptable
                                                                  far as a                        which
                                                                  buffet marks                    approximate
                                                                  an event or                     demonstrable
                                                                  helicopter                      flight test
                                                                  state, which                    data.
                                                                  can be sensed
                                                                  in the flight
                                                                  deck.
                                                                 [See Table C1A,
                                                                  table entries
                                                                  5.e. and 5.f.].
----------------------------------------------------------------------------------------------------------------
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       Takeoff, climb,  One test is       X
                                less) after      and descent.     required in
                                helicopter                        each axis
                                response.                         (pitch, roll
                                                                  and yaw) for
                                                                  each of the
                                                                  three
                                                                  conditions
                                                                  (take-off,
                                                                  cruise, and
                                                                  approach or
                                                                  landing).
----------------------------------------------------------------------------------------------------------------
                               100 ms (or       Climb, cruise,   One test is            X    X
                                less) after      descent, and     required in
                                helicopter       hover.           each axis
                                response.                         (pitch, 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       N/A............  A separate test   X
                                less) after                       is required in
                                controller                        each axis
                                movement.                         (pitch, roll,
                                                                  and yaw).
----------------------------------------------------------------------------------------------------------------
                               100 ms (or       N/A............  A separate test        X    X
                                less) after                       is required in
                                controller                        each axis
                                movement.                         (pitch, roll,
                                                                  and yaw)..
----------------------------------------------------------------------------------------------------------------
4.b........  Field-of-view
----------------------------------------------------------------------------------------------------------------
4.b.1......  Continuous field- The simulator    N/A............  An SOC is         X             Horizontal
              of-view.          must provide a                    required and                    field-of-view
                                continuous                        must explain                    is centered on
                                field-of-view                     the geometry                    the zero
                                of at least                       of the                          degree azimuth
                                75[deg]                           installation.                   line relative
                                horizontally                     Additional                       to the
                                and 30[deg]                       horizontal                      aircraft
                                vertically per                    field-of-view                   fuselage.
                                pilot seat or                     capability may                  Field-of-view
                                the number of                     be added at                     may be
                                degrees                           the sponsor's                   measured using
                                necessary to                      discretion                      a visual test
                                meet the                          provided the                    pattern
                                visual ground                     minimum field-                  filling the
                                segment                           of-view is                      entire visual
                                requirement,                      retained..                      scene (all
                                whichever is                                                      channels) with
                                greater. Both                                                     a matrix of
                                pilot seat                                                        black and
                                visual systems                                                    white 5[deg]
                                must be                                                           squares.
                                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- The simulator    N/A............  An SOC is              X        Horizontal
              of-view.          must provide a                    required and                    field-of-view
                                continuous                        must explain                    is centered on
                                field-of-view                     the geometry                    the zero
                                of at least                       of the                          degree azimuth
                                146[deg]                          installation.                   line relative
                                horizontally                     Horizontal                       to the
                                and 36[deg]                       field-of-view                   aircraft
                                vertically or                     of at least                     fuselage.
                                the number of                     146[deg]                        Field-of-view
                                degrees                           (including not                  may be
                                necessary to                      less than                       measured using
                                meet the                          73[deg]                         a visual test
                                visual ground                     measured                        pattern
                                segment                           either side of                  filling the
                                requirement,                      the center of                   entire visual
                                whichever is                      the design eye                  scene (all
                                greater. The                      point).                         channels) with
                                minimum                           Additional                      a matrix of
                                horizontal                        horizontal                      black and
                                field-of-view                     field-of-view                   white 5[deg]
                                coverage must                     capability may                  squares.
                                be plus and                       be added at
                                minus one-half                    the sponsor's
                                (\1/2\) of the                    discretion
                                minimum                           provided the
                                continuous                        minimum field-
                                field-of-view                     of-view is
                                requirement,                      retained..
                                centered on                      Vertical field-
                                the zero                          of-view of at
                                degree azimuth                    least 36[deg]
                                line relative                     measured from
                                to the                            the pilot's
                                aircraft                          and co-pilot's
                                fuselage. Any                     eye point..
                                geometric
                                error between
                                the Image
                                Generator eye
                                point and the
                                pilot eye
                                point must be
                                8[deg] or
                                less.
----------------------------------------------------------------------------------------------------------------
4.b.3......  Continuous field- Continuous       N/A............  An SOC is                   X   The horizontal
              of-view.          field-of-view                     required and                    field-of-view
                                of at least                       must explain                    is
                                176[deg]                          the geometry                    traditionally
                                horizontal and                    of the                          described as a
                                56[deg]                           installation.                   180[deg] field-
                                vertical field-                  Horizontal                       of-view.
                                of-view for                       field-of-view                   However, the
                                each pilot                        is centered on                  field-of-view
                                simultaneously                    the zero                        is technically
                                . Any                             degree azimuth                  no less than
                                geometric                         line relative                   176[deg].
                                error between                     to the                          Field-of-view
                                the Image                         aircraft                        may be
                                Generator eye                     fuselage.                       measured using
                                point and the                     Horizontal                      a visual test
                                pilot eye                         field-of-view                   pattern
                                point must be                     must be at                      filling the
                                8[deg] or                         least 176[deg]                  entire visual
                                less.                             (including not                  scene (all
                                                                  less than                       channels) with
                                                                  88[deg] either                  a matrix of
                                                                  side of the                     black and
                                                                  center of the                   white 5[deg]
                                                                  design eye                      squares.
                                                                  point).
                                                                  Additional
                                                                  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    N/A............  The ratio is                X   Measurements
              ratio.            5:1.                              calculated by                   may be made
                                                                  dividing the                    using a 1[deg]
                                                                  brightness                      spot
                                                                  level of the                    photometer and
                                                                  center, bright                  a raster drawn
                                                                  square                          test pattern
                                                                  (providing at                   filling the
                                                                  least 2 foot-                   entire visual
                                                                  lamberts or 7                   scene (all
                                                                  cd/m\2\) by                     channels) with
                                                                  the brightness                  a test pattern
                                                                  level of any                    of black and
                                                                  adjacent dark                   white squares,
                                                                  square.                         5 per 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         Not less than    N/A............  Measure the                 X   Measurements
              brightness.       six (6) foot-                     brightness of                   may be made
                                lamberts (20                      the center,                     using a 1[deg]
                                cd/m\2\).                         white square                    spot
                                                                  while                           photometer and
                                                                  superimposing                   a raster drawn
                                                                  a highlight on                  test pattern
                                                                  that white                      filling the
                                                                  square. The                     entire visual
                                                                  use of                          scene (all
                                                                  calligraphic                    channels) with
                                                                  capabilities                    a test pattern
                                                                  to enhance the                  of black and
                                                                  raster                          white squares,
                                                                  brightness is                   5 per square,
                                                                  acceptable;                     with a white
                                                                  however,                        square in the
                                                                  measuring                       center of each
                                                                  light points                    channel.
                                                                  is not
                                                                  acceptable.
----------------------------------------------------------------------------------------------------------------
4.e........  Surface           Not greater      N/A............  An SOC is              X    X   When the eye is
              resolution.       than two (2)                      required and                    positioned on
                                arc minutes.                      must include                    a 3[deg] glide
                                                                  the                             slope at the
                                                                  appropriate                     slant range
                                                                  calculations                    distances
                                                                  and an                          indicated with
                                                                  explanation of                  white runway
                                                                  those                           markings on a
                                                                  calculations.                   black runway
                                                                  Level B                         surface, the
                                                                  requires                        eye will
                                                                  surface                         subtend two
                                                                  resolution not                  (2) arc
                                                                  greater than                    minutes: (1) A
                                                                  three (3) arc                   slant range of
                                                                  minutes.                        6,876 ft with
                                                                                stripes 150 ft
                                                                                long and 16 ft
                                                                                wide, spaced 4
                                                                                ft apart. (2)
                                                                                For
                                                                                Configuration
                                                                                A, a slant
                                                                                range of 5,157
                                                                                feet with
                                                                                stripes 150 ft
                                                                                long and 12 ft
                                                                                wide, spaced 3
                                                                                ft apart. (3)
                                                                                For
                                                                                Configuration
                                                                                B, a slant
                                                                                range of 9,884
                                                                                feet, with
                                                                                stripes 150 ft
                                                                                long and 5.75
                                                                                ft wide,
                                                                                spaced 5.75 ft
                                                                                apart.
----------------------------------------------------------------------------------------------------------------
4.f........  Light point size  Not greater      N/A............  An SOC is              X    X   Light point
                                than five (5)                     required and                    size may be
                                arc minutes.                      must include                    measured using
                                                                  the relevant                    a test pattern
                                                                  calculations                    consisting of
                                                                  and an                          a centrally
                                                                  explanation of                  located single
                                                                  those                           row of light
                                                                  calculations.                   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                                                                         A 1[deg] spot
              contrast 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    N/A............  An SOC is         X
                                10:1.                             required and
                                                                  must include
                                                                  the relevant
                                                                  calculations.
----------------------------------------------------------------------------------------------------------------
4.g.2......                    Not less than    N/A............  An SOC is              X    X
                                25:1.                             required and
                                                                  must include
                                                                  the relevant
                                                                  calculations.
----------------------------------------------------------------------------------------------------------------
4.h........  Visual ground segment
----------------------------------------------------------------------------------------------------------------

                               The visible      Landing          The QTG must      X    X    X   Pre-positioning
                                segment in the   configuration,   contain                         for this test
                                simulator must   with the         appropriate                     is encouraged,
                                be 20% of     trimmed for      and a drawing                   achieved via
                                the segment      the              showing the                     manual or
                                computed to be   appropriate      data used to                    autopilot
                                visible from     airspeed,        establish the                   control to the
                                the helicopter   where the MLG    helicopter                      desired
                                flight deck.     are at 100 ft    location and                    position.
                                This tolerance   (30 m) above     the segment of
                                may be applied   the plane of     the ground
                                at the far end   the touchdown    that is
                                of the           zone, on the     visible
                                displayed        electronic       considering
                                segment.         glide slope      design eye
                                However,         with an RVR      point, the
                                lights and       value set at     helicopter
                                ground objects   1,200 ft (350    attitude,
                                computed to be   m).              flight deck
                                visible from                      cut-off angle,
                                the helicopter                    and a
                                flight deck at                    visibility of
                                the near end                      1200 ft (350
                                of the visible                    m) RVR.
                                segment must                      Simulator
                                be visible in                     performance
                                the simulator.                    must be
                                                                  measured
                                                                  against the
                                                                  QTG
                                                                  calculations.
                                                                  The data
                                                                  submitted 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. All
              tests in this section must be presented using an unweighted \1/3\-
              octave band format from band 17 to 42 (50 Hz to 16 kHz). A minimum
               20 second average must be taken at the location corresponding to
                 the helicopter data set. The helicopter and flight simulator
                    results must be produced using comparable data analysis
                                          techniques.
----------------------------------------------------------------------------------------------------------------
5.a........  Basic requirements
----------------------------------------------------------------------------------------------------------------

5.a.1......  Ready for engine   5   Ground.........  Normal                      X
              start.            dB per \1/3\                      condition
                                octave band.                      prior to
                                                                  engine start.
                                                                  The APU must
                                                                  be on if
                                                                  appropriate.
----------------------------------------------------------------------------------------------------------------
5.a.2......  All engines at     5   Ground.........  Normal                      X
              idle; rotor not   dB per \1/3\                      condition
              turning (if       octave band.                      prior to lift-
              applicable) and                                     off.
              rotor turning.
----------------------------------------------------------------------------------------------------------------
5.a.3......  Hover...........   5   Hover..........                              X
                                dB per \1/3\
                                octave band.
----------------------------------------------------------------------------------------------------------------
5.a.4......  Climb...........   5   En-route climb.  Medium altitude             X
                                dB per \1/3\
                                octave band.
----------------------------------------------------------------------------------------------------------------
5.a.5......  Cruise..........   5   Cruise.........  Normal cruise               X
                                dB per \1/3\                      configuration.
                                octave band.
----------------------------------------------------------------------------------------------------------------
5.a.6......  Final approach..   5   Landing........  Constant                    X
                                dB per \1/3\                      airspeed, gear
                                octave band.                      down.
----------------------------------------------------------------------------------------------------------------
5.b........  Special cases
----------------------------------------------------------------------------------------------------------------
                               5    As appropriate.                              X   These special
                                dB per \1/3\                                                      cases are
                                octave band.                                                      identified as
                                                                                particularly
                                                                                significant
                                                                                during
                                                                                critical
                                                                                phases of
                                                                                flight and
                                                                                ground
                                                                                operations for
                                                                                a specific
                                                                                helicopter
                                                                                type or model.
----------------------------------------------------------------------------------------------------------------
5.c........  Background noise
----------------------------------------------------------------------------------------------------------------
                               3    As appropriate.  Results of the              X   The simulated
                                dB per \1/3\                      background                      sound will be
                                octave band.                      noise at                        evaluated to
                                                                  initial                         ensure that
                                                                  qualification                   the background
                                                                  must be                         noise does not
                                                                  included in                     interfere with
                                                                  the MQTG.                       training,
                                                                  Measurements                    testing, or
                                                                  must be made                    checking.
                                                                  with the
                                                                  simulation
                                                                  running, the
                                                                  sound muted,
                                                                  and a ``dead''
                                                                  flight deck.
----------------------------------------------------------------------------------------------------------------
5.d........  Frequency response
----------------------------------------------------------------------------------------------------------------
                               5                     Applicable only             X   Measurements
                                dB on three                       to Continuing                   are compared
                                (3)                               Qualification                   to those taken
                                consecutive                       Evaluations.                    during initial
                                bands when                        If frequency                    qualification
                                compared to                       response plots                  evaluation.
                                initial                           are provided
                                evaluation;                       for each
                                and 2 dB                        initial
                                when comparing                    evaluation,
                                the average of                    these plots
                                the absolute                      may be
                                differences                       repeated at
                                between                           the continuing
                                initial and                       qualification
                                continuing                        evaluation
                                qualification                     with the
                                evaluation.                       following
                                                                  tolerances
                                                                  applied:
                                                                 (a) The
                                                                  continuing
                                                                  qualification
                                                                  \1/3\ octave
                                                                  band
                                                                  amplitudes
                                                                  must not
                                                                  exceed  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 AC 25-7, as amended,
Flight Test Guide for Certification of Transport Category Airplanes,
and AC 23-8, as 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 hover and cruise
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 hover and cruise flight
conditions and configurations.
    (3) For helicopters with irreversible control systems,
measurements may be obtained on the ground if proper pitot-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 satisfies 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
helicopter 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 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, 20% of Subsequent
                                             Peaks
T(Ad).....................................  5% of Ad =
                                             residual band

    Significant overshoots. First overshoot and 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, FFS Objective Tests, Entries
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

[GRAPHIC] [TIFF OMITTED] TR09MY08.034

BILLING CODE 49-13-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 g-rms\2\/Hz would describe a heavy
buffet and may be seen in the deep stall regime. Alternatively, a
1x10-6 g-rms\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).
    Note: In the example, ``g-rms\2\'' is the mathematical
expression for ``g's root mean squared.''
    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 simulator motion systems to
provide adequate onset 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
Level C and Level D 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
------------------------------------------------------------------------

BILLING CODE 4910-13-P

[GRAPHIC] [TIFF OMITTED] TR09MY08.035

BILLING CODE 4910-13-C

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 comply 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:
    (i) 70 dB @ 50 Hz;
    (ii) 55 dB @ 1000 Hz;
    (iii) 30 dB @ 16 kHz.
    (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