must be
                determined by
                comparing a
                recording of the
                control feel
                dynamics of the
                simulator to
                helicopter
                measurements.
                For initial and
                upgrade
                evaluations, the
                control dynamic
                characteristics
                must be measured
                and recorded
                directly from
                the flight deck
                controls, and
                must be
                accomplished in
                takeoff, cruise,
                and landing
                conditions and
                configurations.
               Objective tests
                are required.
------------------------------------------------------------------------
4. Instructor/Evaluator Facilities
------------------------------------------------------------------------
4.a..........  In addition to        X      X      X   The NSPM will
                the flight                              consider
                crewmember                              alternatives to
                stations, the                           this standard
                simulator must                          for additional
                have at least                           seats based on
                two suitable                            unique flight
                seats for the                           deck
                instructor/check                        configurations.
                airman and FAA
                inspector. These
                seats must
                provide adequate
                vision to the
                pilot's panel
                and forward
                windows. All
                seats other than
                flight crew
                seats need not
                represent those
                found in the
                helicopter but
                must be
                adequately
                secured to the
                floor and
                equipped with
                similar positive
                restraint
                devices.
               A subjective test
                is required.
------------------------------------------------------------------------
4.b..........  The simulator         X      X      X
                must have
                controls that
                enable the
                instructor/
                evaluator to
                control all
                required system
                variables and
                insert all
                abnormal or
                emergency
                conditions into
                the simulated
                helicopter
                systems as
                described in the
                sponsor's FAA-
                approved
                training
                program, or as
                described in the
                relevant
                operating manual
                as appropriate.
               A subjective test
                is required.
------------------------------------------------------------------------
4.c..........  The simulator         X      X      X
                must have
                instructor
                controls for
                environmental
                conditions
                including wind
                speed and
                direction.
               A subjective test
                is required.
------------------------------------------------------------------------
4.d..........  The simulator                X      X   For example,
                must provide the                        another aircraft
                instructor or                           crossing the
                evaluator the                           active runway
                ability to                              and converging
                present ground                          airborne
                and air hazards.                        traffic.
               A subjective test
                is required.
------------------------------------------------------------------------

4.e..........  The simulator                X      X   This is a
                must provide the                        selectable
                instructor or                           condition that
                evaluator the                           is not required
                ability to                              for all
                present the                             operations on or
                effect of re-                           near the ground.
                circulating dust
                or snow
                conditions that
                develop as a
                result of rotor
                downwash.
               A subjective test
                is required.
------------------------------------------------------------------------
5. Motion System
------------------------------------------------------------------------
5.a..........  The simulator         X      X      X   For example,
                must have motion                        touchdown cues
                (force) cues                            should be a
                perceptible to                          function of the
                the pilot that                          rate of descent
                are                                     (RoD) of the
                representative                          simulated
                of the motion in                        helicopter.
                a helicopter.
------------------------------------------------------------------------
               A subjective test
                is required.
------------------------------------------------------------------------
5.b..........  The simulator         X
                must have a
                motion (force
                cueing) system
                with a minimum
                of three degrees
                of freedom (at
                least pitch,
                roll, and heave).
               An SOC is
                required.
------------------------------------------------------------------------
5.c..........  The simulator                X      X
                must have a
                motion (force
                cueing) system
                that produces
                cues at least
                equivalent to
                those of a six-
                degrees-of-
                freedom,
                synergistic
                platform motion
                system (i.e.,
                pitch, roll,
                yaw, heave,
                sway, and surge).
               An SOC is
                required.
------------------------------------------------------------------------
5.d..........  The simulator         X      X      X
                must provide for
                the recording of
                the motion
                system response
                time.
               An SOC is
                required.
------------------------------------------------------------------------
5.e..........  The simulator
                must provide
                motion effects
                programming to
                include the
                following:
                  (1) Runway         X      X      X
                   rumble, oleo
                   deflections,
                   effects of
                   ground speed,
                   uneven
                   runway,
                   characteristi
                   cs.
                  (2) Buffets
                   due to
                   transverse
                   flow effects.
                  (3) Buffet
                   during
                   extension and
                   retraction of
                   landing gear.
                  (4) Buffet due
                   to retreating
                   blade stall.
                  (5) Buffet due
                   to settling
                   with power.
                  (6)
                   Representativ
                   e cues
                   resulting
                   from
                   touchdown.
                  (7) Rotor
                   vibrations.
               A subjective test
                is required for
                each.
              ----------------------------------------------------------
                  (8) Tire                  X      X
                   failure
                   dynamics.
                  (9) Engine
                   malfunction
                   and engine
                   damage.
                  (10) Airframe
                   ground strike.
               A subjective test
                is required for
                each.
              ----------------------------------------------------------
                  (11) Motion                      X   For air
                   vibrations                           turbulence,
                   that result                          general purpose
                   from                                 disturbance
                   atmospheric                          models that
                   disturbances.                        approximate
                                                        demonstrable
                                                        flight test data
                                                        are acceptable.
------------------------------------------------------------------------
5.f..........  The simulator                       X   The simulator
                must provide                            should be
                characteristic                          programmed and
                motion                                  instrumented in
                vibrations that                         such a manner
                result from                             that the
                operation of the                        characteristic
                helicopter (for                         buffet modes can
                example,                                be measured and
                retreating blade                        compared to
                stall, extended                         helicopter data.
                landing gear,
                settling with
                power) in so far
                as vibration
                marks an event
                or helicopter
                state, which can
                be sensed in the
                flight deck.
               A subjective test
                is required.
               An objective test
                is required.
------------------------------------------------------------------------
6............  Visual System....                       Additional
                                                        horizontal field
                                                        of view
                                                        capability may
                                                        be added at the
                                                        sponsor's
                                                        discretion
                                                        provided the
                                                        minimum field of
                                                        view is
                                                        retained.
------------------------------------------------------------------------
6.a..........  The simulator         X      X      X   .................
                must have a
                visual system
                providing an out-
                of-the-flight
                deck view.
               A subjective test
                is required.
------------------------------------------------------------------------

6.b..........  The simulator         X
                must provide a
                continuous field
                of view of at
                least 75[deg]
                horizontally and
                30[deg]
                vertically per
                pilot seat. Both
                pilot seat
                visual systems
                must be operable
                simultaneously.
                The minimum
                horizontal field
                of view coverage
                must be plus and
                minus one-half
                (\1/2\) of the
                minimum
                continuous field
                of view
                requirement,
                centered on the
                zero degree
                azimuth line
                relative to the
                aircraft
                fuselage. An SOC
                must explain the
                geometry of the
                installation.
               An SOC is
                required.
------------------------------------------------------------------------
6.c..........  The simulator                X          Optimization of
                must provide a                          the vertical
                continuous                              field of view
                visual field of                         may be
                view of at least                        considered with
                146[deg]                                respect to the
                horizontally and                        specific
                36[deg]                                 helicopter
                vertically per                          flight deck cut-
                pilot seat. Both                        off angle. The
                pilot seat                              sponsor may
                visual systems                          request the NSPM
                must be operable                        to evaluate the
                simultaneously.                         FFS for specific
                Horizontal field                        authorization(s)
                of view is                              for the
                centered on the                         following:
                zero degree                            (1) Specific
                azimuth line                            areas within the
                relative to the                         database needing
                aircraft                                higher
                fuselage. The                           resolution to
                minimum                                 support
                horizontal field                        landings, take-
                of view coverage                        offs and ground
                must be plus and                        cushion
                minus one-half                          exercises and
                (\1/2\) of the                          training away
                minimum                                 from a heliport,
                continuous field                        including
                of view                                 elevated
                requirement,                            heliport,
                centered on the                         helidecks and
                zero degree                             confined areas.
                azimuth line                           (2) For cross-
                relative to the                         country flights,
                aircraft                                sufficient scene
                fuselage. An SOC                        details to allow
                must explain the                        for ground to
                geometry of the                         map navigation
                installation.                           over a sector
                Capability for a                        length equal to
                field of view in                        30 minutes at an
                excess of the                           average cruise
                minimum is not                          speed.
                required for                           (3) For offshore
                qualification at                        airborne radar
                Level C.                                approaches
                However, where                          (ARA),
                specific tasks                          harmonized
                require extended                        visual/radar
                fields of view                          representations
                beyond the                              of
                146[deg] by                             installations.
                36[deg] (e.g.,
                to accommodate
                the use of
                ``chin windows''
                where the
                accommodation is
                either integral
                with or separate
                from the primary
                visual system
                display), then
                the extended
                fields of view
                must be
                provided. When
                considering the
                installation and
                use of augmented
                fields of view,
                the sponsor must
                meet with the
                NSPM to
                determine the
                training,
                testing,
                checking, and
                experience tasks
                for which the
                augmented field
                of view
                capability may
                be required.
               An SOC is
                required.
               A subjective test
                is required.
------------------------------------------------------------------------
6.d..........  The simulator                       X   Optimization of
                must provide a                          the vertical
                continuous                              field of view
                visual field of                         may be
                view of at least                        considered with
                176[deg]                                respect to the
                horizontally and                        specific
                56[deg]                                 airplane flight
                vertically per                          deck cut-off
                pilot seat. Both                        angle. The
                pilot seat                              sponsor may
                visual systems                          request the NSPM
                must be operable                        to evaluate the
                simultaneously.                         FFS for specific
                Horizontal field                        authorization(s)
                of view is                              for the
                centered on the                         following:
                zero degree                            (1) Specific
                azimuth line                            areas within the
                relative to the                         database needing
                aircraft                                higher
                fuselage. The                           resolution to
                minimum                                 support
                horizontal field                        landings, take-
                of view coverage                        offs and ground
                must be plus and                        cushion
                minus one-half                          exercises and
                (\1/2\) of the                          training away
                minimum                                 from a heliport,
                continuous field                        including
                of view                                 elevated
                requirement,                            heliport,
                centered on the                         helidecks and
                zero degree                             confined areas.
                azimuth line                           (2) For cross-
                relative to the                         country flights,
                aircraft                                sufficient scene
                fuselage. An SOC                        details to allow
                must explain the                        for ground to
                geometry of the                         map navigation
                installation.                           over a sector
                Capability for a                        length equal to
                field of view in                        30 minutes at an
                excess of the                           average cruise
                minimum is not                          speed.
                required for                           (3) For offshore
                qualification at                        airborne radar
                the Zero Flight                         approaches
                Time (ZFT)                              (ARA),
                level. However,                         harmonized
                where specific                          visual/radar
                tasks require                           representations
                extended fields                         of
                of view beyond                          installations.
                the 176[deg] by
                56[deg] (e.g.,
                to accommodate
                the use of
                ``chin windows''
                where the
                accommodation is
                either integral
                with or separate
                from the primary
                visual system
                display), then
                the extended
                fields of view
                must be
                provided. When
                considering the
                installation and
                use of augmented
                fields of view,
                the sponsor must
                meet with the
                NSPM to
                determine the
                training,
                testing,
                checking, and
                experience tasks
                for which the
                augmented field
                of view
                capability may
                be required.
               An SOC is
                required.
               An objective test
                is required.
------------------------------------------------------------------------
6.e..........  The visual system     X      X      X   Non-realistic
                must be free                            cues might
                from optical                            include image
                discontinuities                         ``swimming'' and
                and artifacts                           image ``roll-
                that create non-                        off,'' that may
                realistic cues.                         lead a pilot to
                                                        make incorrect
                                                        assessments of
                                                        speed,
                                                        acceleration and/
                                                        or situational
                                                        awareness.
               A subjective test
                is required.
------------------------------------------------------------------------

6.f..........  The simulator         X      X      X
                must have
                operational
                landing lights
                for night
                scenes. Where
                used, dusk (or
                twilight) scenes
                require
                operational
                landing lights.
               A subjective test
                is required.
------------------------------------------------------------------------
6.g..........  The simulator         X      X      X
                must have
                instructor
                controls for the
                following:
                  (1) Visibility
                   in statute
                   miles
                   (kilometers)
                   and runway
                   visual range
                   (RVR) in ft.
                   (meters)..
                  (2) Airport or
                   landing area
                   selection..
                  (3) Airport or
                   landing area
                   lighting..
               A subjective test
                is required.
------------------------------------------------------------------------
6.h..........  Each airport          X      X      X
                scene displayed
                must include the
                following:
                  (1) Airport
                   runways and
                   taxiways..
                  (2) Runway
                   definition:.
                  (a) Runway
                   surface and
                   markings..
                  (b) Lighting
                   for the
                   runway in
                   use,
                   including
                   runway
                   threshold,
                   edge,
                   centerline,
                   touchdown
                   zone, VASI
                   (or PAPI),
                   and approach
                   lighting of
                   appropriate
                   colors, as
                   appropriate..
                  (c) Taxiway
                   lights..
               A subjective test
                is required.
------------------------------------------------------------------------
6.i..........  The distances at      X      X      X
                which runway
                features are
                visible, as
                measured from
                runway threshold
                to a helicopter
                aligned with the
                runway on an
                extended 3[deg]
                glide slope must
                not be less than
                listed below:
                  (1) Runway
                   definition,
                   strobe
                   lights,
                   approach
                   lights,
                   runway edge
                   white lights
                   and VASI or
                   PAPI system
                   lights from 5
                   statute miles
                   (8 km) of the
                   runway
                   threshold..
                  (2) Runway
                   centerline
                   lights and
                   taxiway
                   definition
                   from 3
                   statute miles
                   (4.8 km)..
                  (3) Threshold
                   lights and
                   touchdown
                   zone lights
                   from 2
                   statute miles
                   (3.2 km)..
                  (4) Runway
                   markings
                   within range
                   of landing
                   lights for
                   night scenes
                   and as
                   required by
                   three (3) arc-
                   minutes
                   resolution on
                   day scenes..
               A subjective test
                is required.
------------------------------------------------------------------------
6.j..........  The simulator         X      X      X
                must provide
                visual system
                compatibility
                with dynamic
                response
                programming.
               A subjective test
                is required.
------------------------------------------------------------------------
6.k..........  The simulator         X      X      X   This will show
                must show that                          the modeling
                the segment of                          accuracy of the
                the ground                              scene with
                visible from the                        respect to a pre-
                simulator flight                        determined
                deck is the same                        position from
                as from the                             the end of the
                helicopter                              runway ``in
                flight deck                             use.''
                (within
                established
                tolerances) when
                at the correct
                airspeed and
                altitude, at a
                main wheel
                height of 100
                feet (30 meters)
                above the
                touchdown zone.
               An SOC is
                required.
               An objective test
                is required.
------------------------------------------------------------------------
6.l..........  The simulator         X
                must provide
                visual cues
                necessary to
                assess rate of
                change of
                height, height
                AGL, and
                translational
                displacement and
                rates during
                takeoffs and
                landings.
               A subjective test
                is required.
------------------------------------------------------------------------
6.m..........  The simulator                X      X   Examples of
                must have night                         general terrain
                and dusk (or                            characteristics
                twilight) visual                        are fields,
                scene                                   roads, and
                capability,                             bodies of water.
                including
                general terrain
                characteristics
                and significant
                landmarks, free
                from apparent
                quantization.
                The dusk (or
                twilight) scene
                must enable
                identification
                of a visible
                horizon and
                general terrain
                characteristics.
               A subjective test
                is required.
------------------------------------------------------------------------

6.n..........  The simulator                X      X
                must provide
                visual cues
                necessary to
                assess rate of
                change of
                height, height
                AGL, as well as
                translational
                displacement and
                rates during
                takeoff, low
                altitude/low
                airspeed
                maneuvering,
                hover, and
                landing.
               A subjective test
                is required.
------------------------------------------------------------------------
6.o..........  The simulator         X      X      X   Visual attitude
                must provide for                        vs. simulator
                accurate                                attitude is a
                portrayal of the                        comparison of
                visual                                  pitch and roll
                environment                             of the horizon
                relating to the                         as displayed in
                simulator                               the visual scene
                attitude.                               compared to the
                                                        display on the
                                                        attitude
                                                        indicator.
               A subjective test
                is required.
------------------------------------------------------------------------
6.p..........  The simulator                X      X
                must provide for
                quick
                confirmation of
                visual system
                color, RVR,
                focus, and
                intensity.
               An SOC is
                required.
               A subjective test
                is required.
------------------------------------------------------------------------
6.q..........  The simulator                X      X
                must be capable
                of producing at
                least 10 levels
                of occulting.
               A subjective test
                is required.
------------------------------------------------------------------------
6.r..........  Night Visual          X      X      X
                Scenes. The
                simulator must
                provide night
                visual scenes
                with sufficient
                scene content to
                recognize the
                airport, the
                terrain, and
                major landmarks
                around the
                airport. The
                scene content
                must allow a
                pilot to
                successfully
                accomplish a
                visual landing.
                Night scenes, as
                a minimum, must
                provide
                presentations of
                sufficient
                surfaces with
                appropriate
                textural cues
                that include
                self-illuminated
                objects such as
                road networks,
                ramp lighting,
                and airport
                signage, to
                conduct a visual
                approach, a
                landing, and
                airport movement
                (taxi). Scenes
                must include a
                definable
                horizon and
                typical terrain
                characteristics
                such as fields,
                roads and bodies
                of water and
                surfaces
                illuminated by
                airplane landing
                lights.
------------------------------------------------------------------------
6.s..........  Dusk (Twilight)              X      X
                Visual Scenes.
                The simulator
                must provide
                dusk (or
                twilight) visual
                scenes with
                sufficient scene
                content to
                recognize the
                airport, the
                terrain, and
                major landmarks
                around the
                airport. The
                scene content
                must allow a
                pilot to
                successfully
                accomplish a
                visual landing.
                Dusk (or
                twilight)
                scenes, as a
                minimum, must
                provide full
                color
                presentations of
                reduced ambient
                intensity,
                sufficient
                surfaces with
                appropriate
                textural cues
                that include
                self-illuminated
                objects such as
                road networks,
                ramp lighting
                and airport
                signage, to
                conduct a visual
                approach,
                landing and
                airport movement
                (taxi). Scenes
                must include a
                definable
                horizon and
                typical terrain
                characteristics
                such as fields,
                roads and bodies
                of water and
                surfaces
                illuminated by
                representative
                aircraft
                lighting (e.g.,
                landing lights).
                If provided,
                directional
                horizon lighting
                must have
                correct
                orientation and
                be consistent
                with surface
                shading effects.
                Total scene
                content must be
                comparable in
                detail to that
                produced by
                10,000 visible
                textured
                surfaces and
                15,000 visible
                lights with
                sufficient
                system capacity
                to display 16
                simultaneously
                moving objects.
               An SOC is
                required.
------------------------------------------------------------------------

6.t..........  Daylight Visual                     X
                Scenes. The
                simulator must
                have daylight
                visual scenes
                with sufficient
                scene content to
                recognize the
                airport, the
                terrain, and
                major landmarks
                around the
                airport. The
                scene content
                must allow a
                pilot to
                successfully
                accomplish a
                visual landing.
                No ambient
                lighting may
                ``washout'' the
                displayed visual
                scene. Total
                scene content
                must be
                comparable in
                detail to that
                produced by
                10,000 visible
                textured
                surfaces and
                6,000 visible
                lights with
                sufficient
                system capacity
                to display 16
                simultaneously
                moving objects.
                The visual
                display must be
                free of apparent
                quantization and
                other
                distracting
                visual effects
                while the
                simulator is in
                motion.
               Note: These
                requirements are
                applicable to
                any level of
                simulator
                equipped with a
                daylight visual
                system.
               An SOC is
                required.
------------------------------------------------------------------------
               A subjective test
                is required.
               Objective tests
                are required.
------------------------------------------------------------------------
6.w..........  The simulator                       X   For example:
                must provide                            short runways,
                operational                             landing
                visual scenes                           approaches over
                that portray                            water, uphill or
                physical                                downhill
                relationships                           runways, rising
                known to cause                          terrain on the
                landing                                 approach path,
                illusions to                            unique
                pilots.                                 topographic
                                                        features.
               A subjective test
                is required.
------------------------------------------------------------------------
6.x..........  The simulator                       X
                must provide
                special weather
                representations
                of light,
                medium, and
                heavy
                precipitation
                near a
                thunderstorm on
                takeoff and
                during approach
                and landing.
                Representations
                need only be
                presented at and
                below an
                altitude of
                2,000 ft. (610
                m) above the
                airport surface
                and within 10
                miles (16 km) of
                the airport.
               A subjective test
                is required.
------------------------------------------------------------------------
6.y..........  The simulator                       X   The NSPM will
                must present                            consider
                visual scenes of                        suitable
                wet and snow-                           alternative
                covered runways,                        effects.
                including runway
                lighting
                reflections for
                wet conditions,
                and partially
                obscured lights
                for snow
                conditions.
               A subjective test
                is required.
------------------------------------------------------------------------
6.z..........  The simulator                       X
                must present
                realistic color
                and
                directionality
                of all airport
                lighting.
               A subjective test
                is required.
------------------------------------------------------------------------
7.a..........  The simulator         X      X      X
                must provide
                flight deck
                sounds that
                result from
                pilot actions
                that correspond
                to those that
                occur in the
                helicopter.
------------------------------------------------------------------------
7.b..........  Volume control,       X      X      X
                if installed,
                must have an
                indication of
                the sound level
                setting.
------------------------------------------------------------------------
7.c..........  The simulator                X      X
                must accurately
                simulate the
                sound of
                precipitation,
                windshield
                wipers, and
                other
                significant
                helicopter
                noises
                perceptible to
                the pilot during
                normal and
                abnormal
                operations, and
                include the
                sound of a crash
                (when the
                simulator is
                landed in an
                unusual attitude
                or in excess of
                the structural
                gear
                limitations);
                normal engine
                sounds; and the
                sounds of gear
                extension and
                retraction.
               An SOC is
                required.
               A subjective test
                is required.
------------------------------------------------------------------------
7.d..........  The simulator                       X
                must provide
                realistic
                amplitude and
                frequency of
                flight deck
                noises and
                sounds.
                Simulator
                performance must
                be recorded,
                compared to
                amplitude and
                frequency of the
                same sounds
                recorded in the
                helicopter, and
                made a part of
                the QTG.
               An objective test
                is required.
------------------------------------------------------------------------

                                 Table C1B.--Table of Tasks vs. Simulator Level
----------------------------------------------------------------------------------------------------------------
                            <<>>      Simulator levels                Information
                        ----------------------------------------------------------------------------------------
                         Subjective Requirements The
         Number           simulator must be able to
                              perform the tasks         B      C      D                    Notes
                          associated with that level
                              of qualification.
----------------------------------------------------------------------------------------------------------------
1. Preflight Procedures
----------------------------------------------------------------------------------------------------------------
1.a....................  Preflight Inspection            X      X      X
                          (Flight deck only)
                          switches, indicators,
                          systems, and equipment.
----------------------------------------------------------------------------------------------------------------
1.b....................  APU/Engine start and run-up.
----------------------------------------------------------------------------------------------------------------
1.b.1..................  Normal start procedures....     X      X      X
----------------------------------------------------------------------------------------------------------------
1.b.2..................  Alternate start procedures.     X      X      X
----------------------------------------------------------------------------------------------------------------
1.b.3..................  Abnormal starts and             X      X      X
                          shutdowns (hot start, hung
                          start).
----------------------------------------------------------------------------------------------------------------
1.c....................  Taxiing--Ground............     X      X      X
----------------------------------------------------------------------------------------------------------------
1.d....................  Taxiing--Hover.............     X      X      X
----------------------------------------------------------------------------------------------------------------
1.e....................  Pre-takeoff Checks.........     X      X      X
----------------------------------------------------------------------------------------------------------------
2. Takeoff and Departure Phase
----------------------------------------------------------------------------------------------------------------
2.a....................  Normal takeoff
----------------------------------------------------------------------------------------------------------------
2.a.1..................  From ground................     X      X      X
----------------------------------------------------------------------------------------------------------------
2.a.2..................  From hover.................     X      X      X
----------------------------------------------------------------------------------------------------------------
2.a.3..................  Running....................     X      X      X
----------------------------------------------------------------------------------------------------------------
2.b....................  Instrument.................     X      X      X
----------------------------------------------------------------------------------------------------------------
2.c....................  Powerplant Failure During       X      X      X
                          Takeoff.
----------------------------------------------------------------------------------------------------------------
2.d....................  Rejected Takeoff...........     X      X      X
----------------------------------------------------------------------------------------------------------------
2.e....................  Instrument Departure.......     X      X      X
----------------------------------------------------------------------------------------------------------------
3. Climb
----------------------------------------------------------------------------------------------------------------
3.a....................  Normal.....................     X      X      X
----------------------------------------------------------------------------------------------------------------
3.b....................  Obstacle clearance.........     X      X      X
----------------------------------------------------------------------------------------------------------------
3.c....................  Vertical...................     X      X      X
----------------------------------------------------------------------------------------------------------------
3.d....................  One engine inoperative.....     X      X      X
----------------------------------------------------------------------------------------------------------------
4. In-flight Maneuvers
----------------------------------------------------------------------------------------------------------------
4.a....................  Turns (timed, normal,           X      X      X
                          steep).
----------------------------------------------------------------------------------------------------------------
4.b....................  Powerplant Failure--            X      X      X
                          Multiengine Helicopters.
----------------------------------------------------------------------------------------------------------------
4.c....................  Powerplant Failure--Single-     X      X      X
                          Engine Helicopters.
----------------------------------------------------------------------------------------------------------------
4.d....................  Recovery From Unusual           X      X      X
                          Attitudes.
----------------------------------------------------------------------------------------------------------------
4.e....................  Settling with Power........     X      X      X
----------------------------------------------------------------------------------------------------------------
4.f....................  Specific Flight                 A      A      A
                          Characteristics
                          incorporated into the
                          user's FAA approved flight
                          training program.
----------------------------------------------------------------------------------------------------------------
5. Instrument Procedures
----------------------------------------------------------------------------------------------------------------
5.a....................  Instrument Arrival.........     X      X      X
----------------------------------------------------------------------------------------------------------------
5.b....................  Holding....................     X      X      X
----------------------------------------------------------------------------------------------------------------
5.c....................  Precision Instrument Approach
----------------------------------------------------------------------------------------------------------------
5.c.1..................  Normal--All engines             X      X      X
                          operating.
----------------------------------------------------------------------------------------------------------------

5.c.2..................  Manually controlled--One or     X      X      X
                          more engines inoperative.
----------------------------------------------------------------------------------------------------------------
5.d....................  Non-precision Instrument        X      X      X
                          Approach.
----------------------------------------------------------------------------------------------------------------
5.e....................  Missed Approach
----------------------------------------------------------------------------------------------------------------
5.e.1..................  All engines operating......     X      X      X
----------------------------------------------------------------------------------------------------------------
5.e.2..................  One or more engines             X      X      X
                          inoperative.
----------------------------------------------------------------------------------------------------------------
5.e.3..................  Stability augmentation          X      X      X
                          system failure.
----------------------------------------------------------------------------------------------------------------
6. Landings and Approaches to Landings
----------------------------------------------------------------------------------------------------------------
6.a....................  Visual Approaches (normal,      X      X      X
                          steep, shallow).
----------------------------------------------------------------------------------------------------------------
6.b....................  Landings
----------------------------------------------------------------------------------------------------------------
6.b.1..................  Normal/crosswind
----------------------------------------------------------------------------------------------------------------
6.b.1.a................  Running....................     X      X      X
----------------------------------------------------------------------------------------------------------------
6.b.1.b................  From Hover.................     X      X      X
----------------------------------------------------------------------------------------------------------------
6.b.2..................  One or more engines             X      X      X
                          inoperative.
----------------------------------------------------------------------------------------------------------------
6.b.3..................  Rejected Landing...........     X      X      X
----------------------------------------------------------------------------------------------------------------
7. Normal and Abnormal Procedures
----------------------------------------------------------------------------------------------------------------
7.a....................  Powerplant.................     X      X      X
----------------------------------------------------------------------------------------------------------------
7.b....................  Fuel System................     X      X      X
----------------------------------------------------------------------------------------------------------------
7.c....................  Electrical System..........     X      X      X
----------------------------------------------------------------------------------------------------------------
7.d....................  Hydraulic System...........     X      X      X
----------------------------------------------------------------------------------------------------------------
7.e....................  Environmental System(s)....     X      X      X
----------------------------------------------------------------------------------------------------------------
7.f....................  Fire Detection and              X      X      X
                          Extinguisher Systems.
----------------------------------------------------------------------------------------------------------------
7.g....................  Navigation and Aviation         X      X      X
                          Systems.
----------------------------------------------------------------------------------------------------------------
7.h....................  Automatic Flight Control        X      X      X
                          System, Electronic Flight
                          Instrument System, and
                          Related Subsystems.
----------------------------------------------------------------------------------------------------------------
7.i....................  Flight Control Systems.....     X      X      X
----------------------------------------------------------------------------------------------------------------
7.j....................  Anti-ice and Deice Systems.     X      X      X
----------------------------------------------------------------------------------------------------------------
7.k....................  Aircraft and Personal           X      X      X
                          Emergency Equipment.
----------------------------------------------------------------------------------------------------------------
7.l....................  Special Missions tasks          A      A      X
                          (e.g., Night Vision
                          goggles, Forward Looking
                          Infrared System, External
                          Loads and as may be listed
                          on the Statement of
                          Qualification.).
----------------------------------------------------------------------------------------------------------------
8. Emergency Procedures (as applicable)
----------------------------------------------------------------------------------------------------------------
8.a....................  Emergency Descent..........     X      X      X
----------------------------------------------------------------------------------------------------------------
8.b....................  Inflight Fire and Smoke         X      X      X
                          Removal.
----------------------------------------------------------------------------------------------------------------
8.c....................  Emergency Evacuation.......     X      X      X
----------------------------------------------------------------------------------------------------------------
8.d....................  Ditching...................     X      X      X
----------------------------------------------------------------------------------------------------------------
8.e....................  Autorotative Landing.......     X      X      X
----------------------------------------------------------------------------------------------------------------
8.f....................  Retreating blade stall          X      X      X
                          recovery.
----------------------------------------------------------------------------------------------------------------

8.g....................  Mast bumping...............     X      X      X
----------------------------------------------------------------------------------------------------------------
8.h....................  Loss of tail rotor              X      X      X
                          effectiveness.
----------------------------------------------------------------------------------------------------------------
9. Postflight Procedures
----------------------------------------------------------------------------------------------------------------
9.a....................  After-Landing Procedures...     X      X      X
----------------------------------------------------------------------------------------------------------------
9.b....................  Parking and Securing
----------------------------------------------------------------------------------------------------------------
9.b.1..................  Rotor brake operation......     X      X      X
----------------------------------------------------------------------------------------------------------------
9.b.2..................  Abnormal/emergency              X      X      X
                          procedures.
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
Note: An ``A'' in the table indicates that the system, task, or procedure may be examined if the appropriate
  aircraft system or control is simulated in the FSTD and is working properly.

             Table C1C.--Table of Tasks vs. Simulator Level
------------------------------------------------------------------------
                <<>>
------------------------------------------------------
                   Subjective       Simulator levels
               requirements  The ---------------------
               simulator must be                          Information
                able to perform                              notes
    Number         the tasks
                associated with     B      C      D
                 that level of
                 qualification
------------------------------------------------------------------------
1............  Instructor Operating Station (IOS), as appropriate
------------------------------------------------------------------------
1.a..........  Power switch(es).     X      X      X
------------------------------------------------------------------------
1.b..........  Helicopter            X      X      X   e.g., GW, CG,
                conditions.                             Fuel loading,
                                                        Systems, Ground
                                                        Crew.
------------------------------------------------------------------------
1.c..........  Airports/             X      X      X   e.g., Selection,
                Heliports/                              Surface,
                Helicopter                              Presets,
                Landing Areas.                          Lighting
                                                        controls.
------------------------------------------------------------------------
1.d..........  Environmental         X      X      X   e.g., Clouds,
                controls.                               Visibility, RVR,
                                                        Temp, Wind, Ice,
                                                        Snow, Rain, and
                                                        Windshear.
------------------------------------------------------------------------
1.e..........  Helicopter system     X      X      X
                malfunctions
                (Insertion/
                deletion).
------------------------------------------------------------------------
1.f..........  Locks, Freezes,       X      X      X
                and
                Repositioning.
------------------------------------------------------------------------
2............  Sound Control
------------------------------------------------------------------------
2.a..........  On/off/adjustment     X      X      X
------------------------------------------------------------------------
3............  Motion/Control Loading System
------------------------------------------------------------------------
3.a..........  On/off/emergency      X      X      X
                stop.
------------------------------------------------------------------------
4............  Observer Seats/Stations
------------------------------------------------------------------------
4.a..........  Position/             X      X      X   .................
                Adjustment/
                Positive
                restraint system.
------------------------------------------------------------------------

Attachment 2 to Appendix C to Part 60--Full Flight Simulator Objective
Tests

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

Begin Information

                            Table of Contents
------------------------------------------------------------------------
        Paragraph No.                            Title
------------------------------------------------------------------------
1...........................  Introduction.
------------------------------------------------------------------------
2...........................  Test Requirements.
------------------------------------------------------------------------
                              Table C2A, Objective Test.
------------------------------------------------------------------------

3...........................  General.
------------------------------------------------------------------------
4...........................  Control Dynamics.
------------------------------------------------------------------------
5...........................  [Reserved].
------------------------------------------------------------------------
6...........................  Motion System.
------------------------------------------------------------------------
7...........................  Sound System.
------------------------------------------------------------------------
8...........................  Additional Information About Flight
                               Simulator Qualification for New or
                               Derivative Helicopter.
------------------------------------------------------------------------
9...........................  Engineering Simulator--Validation Data.
------------------------------------------------------------------------
10..........................  [Reserved].
------------------------------------------------------------------------
11..........................  Validation Test Tolerances.
------------------------------------------------------------------------
12..........................  Validation Data Roadmap.
------------------------------------------------------------------------
13..........................  Acceptance Guidelines for Alternative
                               Engines Data.
------------------------------------------------------------------------
14..........................  Acceptance Guidelines for Alternative
                               Avionics (Flights-Related Computers and
                               Controllers).
------------------------------------------------------------------------
15..........................  Transport Delay Testing.
------------------------------------------------------------------------
16..........................  Continuing Qualification Evaluations--
                               Validation Test Data Presentation.
------------------------------------------------------------------------
17..........................  Alternative Data Sources, Procedures, and
                               Instrumentation: Level A and Level B
                               Simulators Only.
------------------------------------------------------------------------

1. Introduction

    a. If relevant winds are present in the objective data, the wind
vector (magnitude and direction) should be clearly noted as part of
the data presentation, expressed in conventional terminology, and
related to the runway being used for the test.
    b. The NSPM will not evaluate any simulator unless the required
SOC indicates that the motion system is designed and manufactured to
safely operate within the simulator's maximum excursion,
acceleration, and velocity capabilities (see Motion System in the
following table).
    c. Table C2A addresses helicopter simulators at Levels B, C, and
D because there are no Level A Helicopter simulators.

End Information

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

Begin QPS Requirements

2. Test Requirements

    A. The ground and flight tests required for qualification are
listed in Table C2A. FFS Objective Tests. Computer generated
simulator tests results must be provided for each test except where
an alternative test is specifically authorized by the NSPM. If a
flight condition or operating condition is required for the test but
does not apply to the helicopter being simulated or to be
qualification level sought, it may be disregarded (e.g., an engine
out missed approached for a single-engine helicopter, or a hover
test for a Level B simulator) Each test result if compared against
the validation data described in Sec.  6013 and in this appendix.
Although use of a driver program designed to automatically
accomplish the test is encouraged for all simulators and required
for level C and Level D simulators, each test must be able to be
accomplished manually while recording all appropriate parameters.
The request must be produced on an appropriate recording device
accepted to the NSPM and must include simulator number, data, time,
condition, tolerances, and appropriate dependent variables portrayed
in comparison to the validation data. Time histories are required
unless otherwise indicated in Table C2A. All results must be labeled
using the tolerances and units given.
    b. Table C2A sets out the test results required, including the
parameters, tolerances, and flight conditions for simulator
validation. Tolerances are provided for the listed tests because
mathematical modeling and acquisition/development of reference data
are often inexact. All tolerances listed in the following tables are
applied to simulator performance. When two tolerance values are
given for a parameter, the less restrictive value may be used unless
otherwise indicated.
    c. Certain tests included in this attachment must be supported
with a Statement of Compliance and Capability (SOC). In Table C2A,
requirements for SOCs are indicated in the ``Test Details'' column.
    d. When operational or engineering judgment is used in making
assessments for flight test data applications for simulator
validity, such judgment may not be limited to a single parameter.
For example, data that exhibit rapid variations of the measured
parameters may require interpolations or a ``best fit'' data
selection. All relevant parameters related to a given maneuver or
flight condition must be provided to allow overall interpretation.
When it is difficult or impossible to match simulator to helicopter
data throughout a time history, differences must be justified by
providing a comparison of other related variables for the condition
being assessed.
    e. The FFS may not be programmed so that the mathematical
modeling is correct only at the validation test points. Unless noted
otherwise, simulator tests must represent helicopter performance and
handling qualities at operating weights and centers of gravity (CG)
typical of normal operation. If a test is supported by helicopter
data at one extreme weight or CG, another test supported by
helicopter data at mid-conditions or as close as possible to the
other extreme must be included. Certain tests that are relevant only
at one extreme CG or weight condition need not be repeated at the
other extreme. Tests of handling qualities must include validation
of augmentation devices.
    f. When comparing the parameters listed to those of the
helicopter, sufficient data must also be provided to verify the
correct flight condition and helicopter configuration changes. For
example, to show that control force is within 0.5 pound
(0.22 daN) in a static stability test, data to show the correct
airspeed, power, thrust or torque, helicopter configuration,
altitude, and other appropriate datum identification parameters must
also be given. If comparing short period dynamics, normal
acceleration may be used to establish a match to the helicopter, but
airspeed, altitude, control input, helicopter configuration, and
other appropriate data must also be given. All airspeed values must
be properly annotated (e.g., indicated versus calibrated). In
addition, the same variables

must be used for comparison (e.g., compare inches to inches rather
than inches to centimeters).
    g. The QTG provided by the sponsor must clearly describe how the
simulator will be set up and operated for each test. Each simulator
subsystem may be tested independently, but overall integrated
testing of the simulator must be accomplished to assure that the
total simulator system meets the prescribed standards. A manual test
procedure with explicit and detailed steps for completing each test
must also be provided.
    h. In those cases where the objective test results authorize a
``snapshot test'' or a ``series of snapshot test results'' in lieu
of a time-history result, the sponsor or other data provider must
ensure that a steady state condition exists at the instant of time
captured by the ``snapshot.'' The steady state condition must exist
from 4 seconds prior to, through 1 second following, the instant of
time captured by the snap shot.
    i. For previously qualified simulators, the tests and tolerances
of this attachment may be used in subsequent continuing
qualification evaluations for any given test if the sponsor has
submitted a proposed MQTG revision to the NSPM and has received NSPM
approval.
    j. Motion System Tests:
    (a) The minimum excursions, accelerations, and velocities for
pitch, roll, and yaw must be measurable about a single, common
reference point and must be achieved by driving one degree of
freedom at a time.
    (b) The minimum excursions, accelerations, and velocities for
heave, sway, and surge may be measured about different, identifiable
reference points and must be achieved by driving one degree of
freedom at a time.
    k. Tests of handling qualities must include validation of
augmentation devices. FFSs for highly augmented helicopters will be
validated both in the unaugmented configuration (or failure state
with the maximum permitted degradation in handling qualities) and
the augmented configuration. Where various levels of handling
qualities result from failure states, validation of the effect of
the failure is necessary. For those performance and static handling
qualities tests where the primary concern is control position in the
unaugmented configuration, unaugmented data are not required if the
design of the system precludes any effect on control position. In
those instances where the unaugmented helicopter response is
divergent and non-repeatable, it may not be feasible to meet the
specified tolerances. Alternative requirements for testing will be
mutually agreed upon by the sponsor and the NSPM on a case-by-case
basis.
    l. Some tests will not be required for helicopters using
helicopter hardware in the simulator flight deck (e.g., ``helicopter
modular controller''). These exceptions are noted in Table C2A of
this attachment. However, in these cases, the sponsor must provide a
statement that the helicopter hardware meets the appropriate
manufacturer's specifications and the sponsor must have supporting
information to that fact available for NSPM review.
    m. For objective test purposes, ``Near maximum'' gross weight is
a weight chosen by the sponsor or data provider that is not less
than the basic operating weight (BOW) of the helicopter being
simulated plus 80% of the difference between the maximum
certificated gross weight (either takeoff weight or landing weight,
as appropriate for the test) and the BOW. ``Light'' gross weight is
a weight chosen by the sponsor or data provider that is not more
than 120% of the BOW of the helicopter being simulated or as limited
by the minimum practical operating weight of the test helicopter.
``Medium'' gross weight is a weight chosen by the sponsor or data
provider that is within 10 percent of the average of the numerical
values of the BOW and the maximum certificated gross weight. (Note:
BOW is the empty weight of the aircraft plus the weight of the
following: normal oil quantity; lavatory servicing fluid; potable
water; required crewmembers and their baggage; and emergency
equipment. (References: Advisory Circular 120-27, ``Aircraft Weight
and Balance;'' and FAA-H-8083-1, ``Aircraft Weight and Balance
Handbook.'').

End QPS Requirements

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

                                                 Table C2A.--Full Flight Simulator (FFS) Objective Tests
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                      <<>>                                                          <>
--------------------------------------------------------------------------------------------------------------------------------------------------------
                  Test                                                                                Simulator level
----------------------------------------      Tolerance(s)         Flight condition         Test details     ---------------------         Notes
     Number               Title                                                                                B      C      D
--------------------------------------------------------------------------------------------------------------------------------------------------------
1. Performance
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.a.............  Engine Assessment
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.a.1...........  Start Operations
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.a.1.a.........  Engine start and       Light Off Time--< plus- Ground with the Rotor  Record each engine        X      X      X
                   acceleration           minus>10% or 1 sec.,          Used, if applicable.   initiation of the
                                          Torque--< plus-                                start sequence to
                                          minus>5%, Rotor                               steady state idle
                                          Speed--< plus-                                 and from steady
                                          minus>3%, Fuel Flow--                         state idle to
                                          10%, Gas                          operating RPM.
                                          Generator Speed--
                                          5%,
                                          Power Turbine Speed--
                                          5%, Gas
                                          Turbine Temp.--< plus-
                                          minus>30[deg]C.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.a.1.b.........  Steady State Idle and  Torque--< plus-         Ground...............  Record both steady        X      X      X
                   Operating RPM          minus>3%, Rotor                               state idle and
                   conditions.            Speed--< plus-                                 operating RPM
                                          minus>1.5%, Fuel                              conditions. May be a
                                          Flow--< plus-                                  series of snapshot
                                          minus>5%, Gas                                 tests.
                                          Generator Speed--
                                          2%,
                                          Power Turbine Speed--
                                          2%,
                                          Turbine Gas Temp.--
                                          20[deg]C.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.a.2...........  Power Turbine Speed    10% of     Ground...............  Record engine             X      X      X
                   Trim.                  total change of                               response to trim
                                          power turbine speed,                          system actuation in
                                          or 0.5%                           both directions.
                                          change of rotor
                                          speed.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.a.3...........  Engine and Rotor       Torque--< plus-         Climb and descent....  Record results using      X      X      X
                   Speed Governing.       minus>5%, Rotor                               a step input to the
                                          Speed--1.5%.                                  collective. May be
                                                                                conducted
                                                                                concurrently with
                                                                                climb and descent
                                                                                performance tests.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.b.............  Surface Operations
--------------------------------------------------------------------------------------------------------------------------------------------------------

1.b.1...........  Minimum Radius Turn..  3 ft.      Ground...............  If brakes are used,       X      X      X
                                          (0.9m) or 20% of                              brake pedal position
                                          helicopter turn                               and brake system
                                          radius.                                       pressure must be
                                                                                matched to the
                                                                                helicopter flight
                                                                                test value.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.b.2...........  Rate of Turn vs.       10% or     Ground Takeoff.......  If brakes are used,       X      X      X
                   Pedal Deflection,      2[deg]/                           brake pedal position
                   Brake Application,     sec. Turn Rate.                               and brake system
                   or Nosewheel Angle,                                                  pressure must be
                   as applicable.                                                       matched to the
                                                                                helicopter flight
                                                                                test value.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.b.3...........  Taxi.................  Pitch Angle--< plus-    Ground...............  Record results for        X      X      X
                                          minus>1.5[deg],                               control position and
                                          Torque--< plus-                                pitch attitude
                                          minus>3%,                                     during ground taxi
                                          Longitudinal Control                          for a specific
                                          Position--< plus-                              ground speed, wind
                                          minus>5%, Lateral                             speed and direction,
                                          Control Position--                            and density altitude.
                                          5%,
                                          Directional Control
                                          Position < plus-
                                          minus>5%, Collective
                                          Control Position--
                                          5%.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.b.4...........  Brake Effectiveness..  10% of     Ground...............                            X      X      X
                                          time and distance.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.c.............  Takeoff
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.c.1...........  All Engines..........  Airspeed--< plus-       Ground/Takeoff and     Record results of         X      X      X
                                          minus>3 kt,            Initial Segment of     takeoff flight path
                                          Altitude--< plus-       Climb.                 as appropriate to
                                          minus>20 ft (6.1m),                           helicopter model
                                          Torque--< plus-                                simulated (running
                                          minus>3%, Rotor                               takeoff for Level B,
                                          Speed--< plus-                                 takeoff from a hover
                                          minus>1.5%, Vertical                          for Level C and D).
                                          Velocity--< plus-                              For Level B, the
                                          minus>100 fpm (0.50m/                         criteria apply only
                                          sec) or 10%, Pitch                            to those segments at
                                          Attitude--< plus-                              airspeeds above
                                          minus>1.5[deg], Bank                          effective
                                          Attitude--< plus-                              translational lift.
                                          minus>2[deg],                                 Results must be
                                          Heading--< plus-                               recorded from the
                                          minus>2[deg],                                 initiation of the
                                          Longitudinal Control                          takeoff to at least
                                          Position--< plus-                              200 ft (61m) AGL.
                                          minus>10%, Lateral
                                          Control Position--
                                          10%,
                                          Directional Control
                                          Position--< plus-
                                          minus>10%,
                                          Collective Control
                                          Position--< plus-
                                          minus>10%..
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.c.2...........  One Engine             Airspeed--< plus-       Ground/Takeoff; and    Record takeoff flight     X      X      X
                   Inoperative            minus>3 kt,            Initial Segment of     path as appropriate
                   continued takeoff.     Altitude--< plus-       Climb.                 to helicopter model
                                          minus>20 ft (6.1m),                           simulated. Results
                                          Torque--< plus-                                must be recorded
                                          minus>3%, Rotor                               from the initiation
                                          Speed--< plus-                                 of the takeoff to at
                                          minus>1.5%,Vertical                           least 200 ft (61m)
                                          Velocity--< plus-                              AGL.
                                          minus>100 fpm (0.50m/
                                          sec) or 10%, Pitch
                                          Attitude--< plus-
                                          minus>1.5[deg], Bank
                                          Attitude--< plus-
                                          minus>2[deg],
                                          Heading--< plus-
                                          minus>2[deg],
                                          Longitudinal Control
                                          Position-- < plus-
                                          minus>10%, Lateral
                                          Control Position--
                                          10%,
                                          Directional Control
                                          Position--< plus-
                                          minus>10%,
                                          Collective Control
                                          Position--< plus-
                                          minus>10%.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.c.3...........  One Engine             Airspeed   Ground, Takeoff......  Time history from the            X      X
                   inoperative,           3 kt; Altitude < plus-                         takeoff point to
                   rejected takeoff.      minus> 20 ft (6.1m),                          touchdown. Test
                                          Torque                            conditions near
                                          3%, Rotor Speed                               limiting performance.
                                           1.5%,
                                          Pitch Attitude < plus-
                                          minus> 1.5[deg],
                                          Roll angle < plus-
                                          minus> 1.5[deg],
                                          Heading
                                          2[deg], Longitudinal
                                          Control Position
                                           10%,
                                          Lateral Control
                                          Position < plus-
                                          minus> 10%,
                                          Directional Control
                                          Position < plus-
                                          minus> 10%,
                                          Collective Control
                                          Position < plus-
                                          minus> 10%,
                                          Distance: < plus-
                                          minus> 7.5% or  30m (100ft).
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.d.............  Hover
--------------------------------------------------------------------------------------------------------------------------------------------------------

                  Performance..........  Torque--< plus-         In Ground Effect       Record results for               X      X
                                          minus>3%, Pitch        (IGE); and Out of      light and heavy
                                          Attitude--< plus-       Ground Effect (OGE).   gross weights. May
                                          minus>1.5[deg], Bank                          be a series of
                                          Attitude--< plus-                              snapshot tests.
                                          minus>1.5[deg],
                                          Longitudinal Control
                                          Position--< plus-
                                          minus>5%, Lateral
                                          Control Position--
                                          5%,
                                          Directional Control
                                          Position--< plus-
                                          minus>5%, Collective
                                          Control Position--
                                          5%.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.e.............  Vertical Climb
--------------------------------------------------------------------------------------------------------------------------------------------------------
                  Performance..........  Vertical Velocity--    From OGE Hover.......  Record results for               X      X
                                          100 fpm                           light and heavy
                                          (0.50 m/sec) or                               gross weights. May
                                          10%,                              be a series of
                                          Directional Control                           snapshot tests.
                                          Position--< plus-
                                          minus>5%, Collective
                                          Control Position--
                                          5%.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.f.............  Level Flight
--------------------------------------------------------------------------------------------------------------------------------------------------------
                  Performance and        Torque--< plus-         Cruise (Augmentation   Record results for        X      X      X   This test validates
                   Trimmed Flight         minus>3%, Pitch        On and Off).           two gross weight and                        performance at
                   Control Positions.     Attitude--< plus-                              CG combinations with                        speeds above maximum
                                          minus>1.5[deg],                               varying trim speeds                         endurance airspeed.
                                          Sideslip Angle--                              throughout the
                                          2[deg],                           airspeed envelope.
                                          Longitudinal Control                          May be a series of
                                          Position--< plus-                              snapshot tests.
                                          minus>5%, Lateral
                                          Control Position--
                                          5%,
                                          Directional Control
                                          Position--< plus-
                                          minus>5%, Collective
                                          Control Position--
                                          5%.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.g.............  Climb
--------------------------------------------------------------------------------------------------------------------------------------------------------
                  Performance and        Vertical Velocity--    All engines            Record results for        X      X      X
                   Trimmed Flight         100 fpm    operating; One         two gross weight and
                   Control Positions.     (6.1m/sec) or < plus-   engine inoperative;    CG combinations. The
                                          minus>10%, Pitch       Augmentation           data presented must
                                          Attitude--< plus-       System(s) On and Off.  be for normal climb
                                          minus>1.5[deg],                               power conditions.
                                          Sideslip Angle--                              May be a series of
                                          2[deg],                           snapshot tests.
                                          Longitudinal Control
                                          Position--< plus-
                                          minus>5%, Lateral
                                          Control Position--
                                          5%,
                                          Directional Control
                                          Position--< plus-
                                          minus>5%, Collective
                                          Control Position--
                                          5%.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.h.............  Descent
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.h.1...........  Descent Performance    Torque--< plus-         At or near 1,000 fpm   Results must be           X      X      X
                   and Trimmed Flight     minus>3%, Pitch        (5 m/sec) rate of      recorded for two
                   Control Positions.     Attitude--< plus-       descent (RoD) at       gross weight and CG
                                          minus>1.5[deg],        normal approach        combinations. May be
                                          Sideslip Angle--       speed. Augmentation    a series of snapshot
                                          2[deg],    System(s) On and Off.  tests.
                                          Longitudinal Control
                                          Position--< plus-
                                          minus>5%, Lateral
                                          Control Position--
                                          5%,
                                          Directional Control
                                          Position--< plus-
                                          minus>5%, Collective
                                          Control Position--
                                          5%.
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1.h.2...........  Autorotation           Pitch Attitude--< plus- Steady descents.       Record results for        X      X      X
                   Performance and        minus>1.5[deg],        Augmentation           two gross weight
                   Trimmed Flight         Sideslip Angle--       System(s) On and Off.  conditions. Data
                   Control Positions.     2[deg],                           must be recorded for
                                          Longitudinal Control                          normal operating
                                          Position--< plus-                              RPM. (Rotor speed
                                          minus>5%, Lateral                             tolerance applies
                                          Control Position--                            only if collective
                                          5%,                               control position is
                                          Directional Control                           full down.) Data
                                          Position--< plus-                              must be recorded for
                                          minus>5%, Collective                          speeds from 50 kts,
                                          Control Position--                            5 kts
                                          5%,                               through at least
                                          Vertical Velocity                             maximum glide
                                          100 fpm                           distance airspeed.
                                          or 10%, Rotor Speed                           May be a series of
                                          1.5%.                             snapshot tests.
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1.i.............  Autorotation
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                  Entry................  Rotor Speed--< plus-    Cruise or Climb......  Record results of a              X      X
                                          minus>3%, Pitch                               rapid throttle
                                          Attitude < plus-                               reduction to idle.
                                          minus>2[deg], Roll                            If the cruise
                                          Attitude--< plus-                              condition is
                                          minus>3[deg], Yaw                             selected, comparison
                                          Attitude--< plus-                              must be made for the
                                          minus>5[deg],                                 maximum range
                                          Airspeed--< plus-                              airspeed. If the
                                          minus>5 kts,                                  climb condition is
                                          Vertical Velocity--                           selected, comparison
                                          200 fpm                           must be made for the
                                          (1.00 m/sec) or 10%.                          maximum rate of
                                                                                climb airspeed at or
                                                                                near maximum
                                                                                continuous power.
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1.j.............  Landing
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1.j.1...........  All Engines..........  Airspeed--< plus-       Approach.............  Record results of the     X      X      X
                                          minus>3 kts.,                                 approach and landing
                                          Altitude--< plus-                              profile as
                                          minus>20 ft. (6.1                             appropriate to the
                                          m), Torque--< plus-                            helicopter model
                                          minus>3%, Rotor                               simulated (running
                                          Speed--< plus-                                 landing for Level B,
                                          minus>1.5%, Pitch                             or approach to a
                                          Attitude--< plus-                              hover for Level C
                                          minus>1.5[deg], Bank                          and D). For Level B,
                                          Attitude--< plus-                              the criteria apply
                                          minus>1.5[deg],                               only to those
                                          Heading--< plus-                               segments at
                                          minus>2[deg],                                 airspeeds above
                                          Longitudinal Control                          effective
                                          Position--< plus-                              translational lift.
                                          minus>10%, Lateral
                                          Control Position--
                                          10%,
                                          Directional Control
                                          Position--< plus-
                                          minus>10%,
                                          Collective Control
                                          Position--< plus-
                                          minus>10%.
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1.j.2...........  One Engine             Airspeed--< plus-       Approach.............  Record results for        X      X      X
                   Inoperative.           minus>3 kts,                                  both Category A and
                                          Altitude--< plus-                              Category B
                                          minus>20 ft (6.1 m),                          approaches and
                                          Torque--< plus-                                landing as
                                          minus>3%, Rotor                               appropriate to
                                          Speed--< plus-                                 helicopter model
                                          minus>1.5%, Pitch                             simulated. For Level
                                          Attitude--< plus-                              B, the criteria
                                          minus>1.5[deg], Bank                          apply only to those
                                          Attitude--< plus-                              segments at
                                          minus>1.5[deg],                               airspeeds above
                                          Heading--< plus-                               effective
                                          minus>2[deg],                                 translational lift.
                                          Longitudinal Control
                                          Position--< plus-
                                          minus>10%, Lateral
                                          Control Position--
                                          10%,
                                          Directional Control
                                          Position--< plus-
                                          minus>10%,
                                          Collective Control
                                          Position--< plus-
                                          minus>10%.
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1.j.3...........  Balked Landing.......  Airspeed--< plus-       Approach.............  Record the results        X      X      X
                                          minus>3 kts,                                  for the maneuver
                                          Altitude--< plus-                              initiated from a
                                          minus>20 ft (6.1 m),                          stabilized approach
                                          Torque--< plus-                                at the landing
                                          minus>3%, Rotor                               decision point (LDP).
                                          Speed--< plus-
                                          minus>1.5%, Pitch
                                          Attitude--< plus-
                                          minus>1.5[deg], Bank
                                          Attitude--< plus-
                                          minus>1.5[deg],
                                          Heading--< plus-
                                          minus>2[deg],
                                          Longitudinal Control
                                          Position--< plus-
                                          minus>10%, Lateral
                                          Control Position--
                                          10%,
                                          Directional Control
                                          Position--< plus-
                                          minus>10%,
                                          Collective Control
                                          Position--< plus-
                                          minus>10%.
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1.j.4...........  Autorotational         Torque--< plus-         Landing..............  Record the results of            X      X
                   Landing.               minus>3%, Rotor                               an autorotational
                                          Speed--< plus-                                 deceleration and
                                          minus>3%, Vertical                            landing from a
                                          Velocity--< plus-                              stabilized
                                          minus>100 fpm (0.50                           autorotational
                                          m/sec) or 10%, Pitch                          descent, to touch
                                          Attitude--< plus-                              down.
                                          minus>2[deg], Bank
                                          Attitude--< plus-
                                          minus>2[deg],
                                          Heading--< plus-
                                          minus>5[deg],
                                          Longitudinal Control
                                          Position--< plus-
                                          minus>10%, Lateral
                                          Control Position--
                                          10%,
                                          Directional Control
                                          Position--< plus-
                                          minus>10%,
                                          Collective Control
                                          Position--< plus-
                                          minus>10%.
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2. Handling Qualities
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2.a.............  Control System Mechanical Characteristics
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                  For simulators requiring Static or Dynamic tests at the controls (i.e., cyclic,                                  Contact the NSPM for
                   collective, and pedal), special test fixtures will not be required during initial or                             clarification of any
                   upgrade evaluations if the sponsor's QTG/MQTG shows both test fixture results and the                            issue regarding
                   results of an alternative approach, such as computer plots produced concurrently showing                         helicopters with
                   satisfactory agreement. Repeat of the alternative method during the initial or upgrade                           reversible controls
                   evaluation would then satisfy this test requirement. For initial and upgrade evaluations,                        or where the
                   the control dynamic characteristics must be measured at and recorded directly from the                           required validation
                   flight deck controls, and must be accomplished in hover, climb, cruise, and autorotation.                        data is not
                                                                                attainable.
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2.a.1...........  Cyclic...............  Breakout--< plus-       Ground; Static         Record results for an     X      X      X   Flight Test Data for
                                          minus>0.25 lbs         conditions with the    uninterrupted                               this test does not
                                          (0.112 daN) or 25%;    hydraulic system (if   control sweep to the                        require the rotor to
                                          Force--< plus-          applicable)            stops. (This test                           be engaged/turning.
                                          minus>1.0 lb (0.224    pressurized;           does not apply if                           The phrase ``if
                                          daN) or 10%.           supplemental           aircraft hardware                           applicable''
                                                                 hydraulic              modular controllers                         regarding stability
                                                                 pressurization         are used.)                                  augmentation systems
                                                                 system may be used.                                                means if an
                                                                 Trim On and Off.                                                   augmentation system
                                                                 Friction Off                                                       is available and if
                                                                 Augmentation (if                                                   this system may be
                                                                 applicable) On and                                                 operational on the
                                                                 Off.                                                               ground under static
                                                                                conditions as
                                                                                described here.
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2.a.2...........  Collective/Pedals....  Breakout--< plus-       Ground; Static         Record results for an     X      X      X   Flight Test Data for
                                          minus>0.5 lb (0.224    conditions with the    uninterrupted                               this test does not
                                          daN) or 25%; Force--   hydraulic system (if   control sweep to the                        require the rotor to
                                          1.0 lb     applicable)            stops.                                      be engaged/turning.
                                          (0.224 daN) or 10%.    pressurized;                                                       The phrase ``if
                                                                 supplemental                                                       applicable''
                                                                 hydraulic                                                          regarding stability
                                                                 pressurization                                                     augmentation system
                                                                 system may be used.                                                means if a stability
                                                                 Trim On and Off.                                                   augmentation system
                                                                 Friction Off.                                                      is available and if
                                                                 Augmentation (if                                                   this system may be
                                                                 applicable) On and                                                 operational on the
                                                                 Off.                                                               ground under static
                                                                                conditions as
                                                                                described here.''
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2.a.3...........  Brake Pedal Force vs.  5 lbs      Ground; Static         .....................     X      X      X
                   Position.              (2.224 daN) or 10%.    conditions.
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2.a.4...........  Trim System Rate (all  Rate--10%  Ground; Static         The tolerance applies     X      X      X   .....................
                   applicable systems).                          conditions. Trim On,   to the recorded
                                                                 Friction Off.          value of the trim
                                                                                rate.
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2.a.5...........  Control Dynamics (all  10% of     Hover/Cruise, Trim     Results must be                  X      X   Typically, control
                   axes).                 time for first zero    On, Friction Off.      recorded for a                              displacement of 25%
                                          crossing and < plus-                           normal control                              to 50% is necessary
                                          minus>10 (N+1)% of                            displacement in both                        for proper
                                          period thereafter,                            directions in each                          excitation. Control
                                          10% of                            axis.                                       Dynamics for
                                          amplitude of first                                                                        irreversible control
                                          overshoot, 20% of                                                                         systems may be
                                          amplitude of 2nd and                                                                      evaluated in a
                                          subsequent                                                                                ground/static
                                          overshoots greater                                                                        condition.
                                          than 5% of initial                                                                        Additional
                                          displacement, < plus-                                                                      information on
                                          minus>1 overshoot.                                                                        control dynamics is
                                                                                found later in this
                                                                                attachment. ``N'' is
                                                                                the sequential
                                                                                period of a full
                                                                                cycle of
                                                                                oscillation.
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2.a.6...........  Control System         2%         Ground; Static         Record and compare        X      X      X   Flight Test Data for
                   Freeplay.              control                conditions; with the   results for all                             this test does not
                                          displacement, but      hydraulic system (if   controls.                                   require the rotor to
                                          not to exceed < plus-   applicable)                                                        be engaged/turning.
                                          minus>0.15 in.         pressurized;
                                                                 supplemental
                                                                 hydraulic
                                                                 pressurization
                                                                 system may be used.
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2.b.............  Low Airspeed Handling Qualities
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2.b.1...........  Trimmed Flight         Torque--< plus-         Translational Flight   Record results for               X      X
                   Control Positions.     minus>3%, Pitch        IGE--Sideward,         several airspeed
                                          Attitude--< plus-       rearward, and          increments to the
                                          minus>1.5[deg], Bank   forward flight.        translational
                                          Attitude--< plus-       Augmentation On and    airspeed limits and
                                          minus>2[deg],          Off.                   for 45 kts forward
                                          Longitudinal Control                          airspeed. May be a
                                          Position--< plus-                              series of snapshot
                                          minus>5%. Lateral                             tests.
                                          Control Position--
                                          5%,
                                          Directional Control
                                          Position--< plus-
                                          minus>5%, Collective