------------------------------------------------------------------------
2.g.2........     150                         X    X
                   milliseconds
                   of the
                   airplane
                   response..
               Objective Tests
                are required..
------------------------------------------------------------------------

2.h..........  The simulator must
                accurately
                reproduce the
                following runway
                conditions:
               (1) Dry...........
               (2) Wet...........
               (3) Icy...........
               (4) Patchy Wet....
               (5) Patchy Icy....
               (6) Wet on Rubber
                Residue in
                Touchdown Zone..
------------------------------------------------------------------------
               An SOC is
                required.
------------------------------------------------------------------------
               Objective tests
                are required only
                for dry, wet, and
                icy runway
                conditions; see
                Attachment 2.
------------------------------------------------------------------------
               Subjective tests               X    X
                are required for
                patchy wet,
                patchy icy, and
                wet on rubber
                residue in
                touchdown zone
                conditions; see
                Attachment 3.
------------------------------------------------------------------------
2.i..........  The simulator must             X    X   Simulator pitch,
                simulate:                               side loading,
               (1) Brake and tire                       and directional
                failure dynamics,                       control
                including                               characteristics
                antiskid failure..                      should be
               (2) Decreased                            representative
                brake efficiency                        of the airplane.
                due to high brake
                temperatures, if
                applicable..
               An SOC is
                required..
------------------------------------------------------------------------
2.j..........  The simulator must             X    X
                replicate the
                effects of
                airframe and
                engine icing.
               A Subjective Test
                is required..
------------------------------------------------------------------------
2.k..........  The aerodynamic                     X   See Attachment 2,
                modeling in the                         paragraph 4, for
                simulator must                          further
                include:                                information on
               (1) Low-altitude                         ground effect.
                level-flight
                ground effect;.
               (2) Mach effect at
                high altitude;.
               (3) Normal and
                reverse dynamic
                thrust effect on
                control surfaces;.
               (4) Aeroelastic
                representations;
                and.
               (5) Nonlinearities
                due to sideslip..
               An SOC is required
                and must include
                references to
                computations of
                aeroelastic
                representations
                and of
                nonlinearities
                due to sideslip..
------------------------------------------------------------------------
2.l..........  The simulator must        X    X    X
                have aerodynamic
                and ground
                reaction modeling
                for the effects
                of reverse thrust
                on directional
                control, if
                applicable.
               An SOC is
                required..
------------------------------------------------------------------------
3. Equipment Operation
------------------------------------------------------------------------
3.a..........  All relevant         X    X    X    X
                instrument
                indications
                involved in the
                simulation of the
                airplane must
                automatically
                respond to
                control movement
                or external
                disturbances to
                the simulated
                airplane; e.g.,
                turbulence or
                windshear.
                Numerical values
                must be presented
                in the
                appropriate
                units.
               A subjective test
                is required..
------------------------------------------------------------------------
3.b..........  Communications,      X    X    X    X   See Attachment 3
                navigation,                             for further
                caution, and                            information
                warning equipment                       regarding long-
                must be installed                       range navigation
                and operate                             equipment.
                within the
                tolerances
                applicable for
                the airplane.
               A subjective test
                is required..
------------------------------------------------------------------------
3.c..........  Simulated airplane   X    X    X    X
                systems must
                operate as the
                airplane systems
                operate under
                normal, abnormal,
                and emergency
                operating
                conditions on the
                ground and in
                flight.
               A subjective test
                is required..
------------------------------------------------------------------------

3.d..........  The simulator must   X    X    X    X
                provide pilot
                controls with
                control forces
                and control
                travel that
                correspond to the
                simulated
                airplane. The
                simulator must
                also react in the
                same manner as in
                the airplane
                under the same
                flight
                conditions.
               A objective test
                is required..
------------------------------------------------------------------------
3.e..........  Simulator control              X    X
                feel dynamics
                must replicate
                the airplane.
                This must be
                determined by
                comparing a
                recording of the
                control feel
                dynamics of the
                simulator to
                airplane
                measurements. For
                initial and
                upgrade
                qualification
                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
                flight conditions
                and
                configurations.
               Objective tests
                are required..
------------------------------------------------------------------------
4. Instructor or Evaluator Facilities
------------------------------------------------------------------------
4.a..........  In addition to the   X    X    X    X   The NSPM will
                flight crewmember                       consider
                stations, the                           alternatives to
                simulator must                          this standard
                have at least two                       for additional
                suitable seats                          seats based on
                for the                                 unique flight
                instructor/check                        deck
                airman and FAA                          configurations.
                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
                airplane, but
                must be
                adequately
                secured to the
                floor and
                equipped with
                similar positive
                restraint
                devices.
               A subjective test
                is required..
------------------------------------------------------------------------
4.b..........  The simulator must   X    X    X    X
                have controls
                that enable the
                instructor/
                evaluator to
                control all
                required system
                variables and
                insert all
                abnormal or
                emergency
                conditions into
                the simulated
                airplane 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 must   X    X    X    X
                have instructor
                controls for
                environmental
                conditions
                including wind
                speed and
                direction.
               A subjective test
                is required..
------------------------------------------------------------------------
4.d..........  The simulator must             X    X   For example,
                provide the                             another airplane
                instructor or                           crossing the
                evaluator the                           active runway or
                ability to                              converging
                present ground                          airborne
                and air hazards.                        traffic.
               A subjective test
                is required..
------------------------------------------------------------------------
5. Motion System
------------------------------------------------------------------------
5.a..........  The simulator must   X    X    X    X   For example,
                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 of                       simulated
                the motion in an                        airplane.
                airplane.
               A subjective test
                is required..
------------------------------------------------------------------------
5.b..........  The simulator must   X    X
                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 must             X    X
                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 must   X    X    X    X
                provide for the
                recording of the
                motion system
                response time.
               An SOC is
                required..
------------------------------------------------------------------------

5.e..........  The simulator must        X    X    X
                provide motion
                effects
                programming to
                include:
               (1) Thrust effect
                with brakes set..
               (2) Runway rumble,
                oleo deflections,
                effects of ground
                speed, uneven
                runway,
                centerline
                lights, and
                taxiway
                characteristics..
               (3) Buffets on the
                ground due to
                spoiler/
                speedbrake
                extension and
                thrust reversal..
               (4) Bumps
                associated with
                the landing gear..
               (5) Buffet during
                extension and
                retraction of
                landing gear..
               (6) Buffet in the
                air due to flap
                and spoiler/
                speedbrake
                extension..
               (7) Approach-to-
                Stall buffet..
               (8) Representative
                touchdown cues
                for main and nose
                gear..
               (9) Nosewheel
                scuffing, if
                applicable..
               (10) Mach and
                maneuver buffet..
------------------------------------------------------------------------
               A subjective test
                is required.
------------------------------------------------------------------------
5.f..........  The simulator must                  X   The simulator
                provide                                 should be
                characteristic                          programmed and
                motion vibrations                       instrumented in
                that result from                        such a manner
                operation of the                        that the
                airplane if the                         characteristic
                vibration marks                         buffet modes can
                an event or                             be measured and
                airplane state                          compared to
                that can be                             airplane data.
                sensed in the
                flight deck.
               An objective test
                is required..
------------------------------------------------------------------------
6. Visual System
------------------------------------------------------------------------
6.a..........  The simulator must   X    X    X    X
                have a visual
                system providing
                an out-of-the-
                flight deck view.
               A subjective test
                is required..
------------------------------------------------------------------------
6.b..........  The simulator must   X    X
                provide a
                continuous
                collimated field
                of view of at
                least 45[deg]
                horizontally and
                30[deg]
                vertically per
                pilot seat or the
                number of degrees
                necessary to meet
                the visual ground
                segment
                requirement,
                whichever is
                greater. 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.
                Additional field
                of view
                capability may be
                added at the
                sponsor's
                discretion
                provided the
                minimum fields of
                view are
                retained.
               An SOC must
                explain the
                geometry of the
                installation. An
                SOC is required..
------------------------------------------------------------------------
6.c..........  (Reserved)
------------------------------------------------------------------------
6.d..........  The simulator must             X    X   The horizontal
                provide a                               field of view is
                continuous                              traditionally
                collimated visual                       described as a
                field of view of                        180[deg] field
                at least 176[deg]                       of view.
                horizontally and                        However, the
                36[deg]                                 field of view is
                vertically or the                       technically no
                number of degrees                       less than
                necessary to meet                       176[deg].
                the visual ground
                segment
                requirement,
                whichever is
                greater. 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.
                Additional field
                of view
                capability may be
                added at the
                sponsor's
                discretion
                provided the
                minimum fields of
                view are
                retained.
               An SOC must
                explain the
                geometry of the
                installation..
               An SOC is
                required..
------------------------------------------------------------------------

6.e..........  The visual system    X    X    X    X   Non-realistic
                must be free from                       cues might
                optical                                 include image
                discontinuities                         ``swimming'' and
                and artifacts                           image ``roll-
                that create non-                        off,'' that may
                realistic cues.                         lead a pilot to
               A subjective test                        make incorrect
                is required..                           assessments of
                                                        speed,
                                                        acceleration, or
                                                        situational
                                                        awareness.
------------------------------------------------------------------------
6.f..........  The simulator must   X    X    X    X
                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 must
                have instructor
                controls for the
                following:
               (1) Visibility in
                statute miles
                (km) and runway
                visual range
                (RVR) in ft.(m)..
               (2) Airport
                selection..
               (3) Airport
                lighting..
------------------------------------------------------------------------
               A subjective test    X    X    X    X
                is required.
------------------------------------------------------------------------
6.h..........  The simulator must   X    X    X    X
                provide visual
                system
                compatibility
                with dynamic
                response
                programming.
               A subjective test
                is required..
------------------------------------------------------------------------
6.i..........  The simulator must   X    X    X    X   This will show
                show that the                           the modeling
                segment of the                          accuracy of RVR,
                ground visible                          glideslope, and
                from the                                localizer for a
                simulator flight                        given weight,
                deck is the same                        configuration,
                as from the                             and speed within
                airplane flight                         the airplane's
                deck (within                            operational
                established                             envelope for a
                tolerances) when                        normal approach
                at the correct                          and landing.
                airspeed, in the
                landing
                configuration, at
                a main wheel
                height of 100
                feet (30 meters)
                above the
                touchdown zone,
                and with
                visibility of
                1,200 ft (350 m)
                RVR.
               An SOC is
                required..
               An objective test
                is required..
------------------------------------------------------------------------
6.j..........  The simulator must        X    X    X
                provide visual
                cues necessary to
                assess sink rates
                (provide depth
                perception)
                during takeoffs
                and landings, to
                include:
               (1) Surface on
                runways,
                taxiways, and
                ramps..
               (2) Terrain
                features..
               A subjective test
                is required..
------------------------------------------------------------------------
6.k..........  The simulator must   X    X    X    X   Visual attitude
                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
               A subjective test                        display on the
                is required..                           attitude
                                                        indicator.
------------------------------------------------------------------------
6.l..........  The simulator must             X    X
                provide for quick
                confirmation of
                visual system
                color, RVR,
                focus, and
                intensity.
               An SOC is
                required..
               A subjective test
                is required..
------------------------------------------------------------------------
6.m..........  The simulator must             X    X
                be capable of
                producing at
                least 10 levels
                of occulting.
               A subjective test
                is required..
------------------------------------------------------------------------
6.n..........  Night Visual         X    X    X    X
                Scenes. When used
                in training,
                testing, or
                checking
                activities, 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.
                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.
               A subjective test
                is required..
------------------------------------------------------------------------

6.o..........  Dusk (or Twilight)             X    X
                Visual Scenes.
                When used in
                training,
                testing, or
                checking
                activities, 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
                airplane landing
                lights. If
                provided,
                directional
                horizon lighting
                must have correct
                orientation and
                be consistent
                with surface
                shading effects.
                Total night or
                dusk (twilight)
                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..
               A subjective test
                is required..
------------------------------------------------------------------------
6.p..........  Daylight Visual                     X   Brightness
                Scenes. The                             capability may
                simulator must                          be demonstrated
                provide daylight                        with a test
                visual scenes                           pattern of white
                with sufficient                         light using a
                scene content to                        spot photometer.
                recognize the
                airport, the
                terrain, and
                major landmarks
                around the
                airport. The
                scene content
                must allow a
                pilot to
                successfully
                accomplish a
                visual landing.
                Any ambient
                lighting must not
                ``washout'' the
                displayed visual
                scene. Total
                daylight 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
                mandatory for
                level D, and
                applicable to any
                level of
                simulator
                equipped with a
                ``daylight''
                visual system.
------------------------------------------------------------------------
               An SOC is
                required.
------------------------------------------------------------------------
               A subjective test
                is required.
------------------------------------------------------------------------
6.q..........  The simulator must                  X   For example:
                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 illusions                       approach path,
                to pilots.                              unique
                                                        topographic
                                                        features.
------------------------------------------------------------------------
               A subjective test
                is required.
------------------------------------------------------------------------
6.r..........  The simulator must                  X
                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.s..........  The simulator must                  X
                present visual
                scenes of wet and
                snow-covered
                runways,
                including runway
                lighting
                reflections for
                wet conditions,
                partially
                obscured lights
                for snow
                conditions, or
                suitable
                alternative
                effects.
------------------------------------------------------------------------

               A subjective test
                is required.
------------------------------------------------------------------------
6.t..........  The simulator must                  X
                present realistic
                color and
                directionality of
                all airport
                lighting.
------------------------------------------------------------------------
               A subjective test
                is required.
------------------------------------------------------------------------
7. Sound System
------------------------------------------------------------------------
7.a..........  The simulator must   X    X    X    X
                provide flight
                deck sounds that
                result from pilot
                actions that
                correspond to
                those that occur
                in the airplane.
------------------------------------------------------------------------
7.b..........  Volume control, if   X    X    X    X
                installed, must
                have an
                indication of the
                sound level
                setting.
------------------------------------------------------------------------
7.c..........  The simulator must             X    X
                accurately
                simulate the
                sound of
                precipitation,
                windshield
                wipers, and other
                significant
                airplane noises
                perceptible to
                the pilot during
                normal
                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 and
                thrust reversal
                sounds; and the
                sounds of flap,
                gear, and spoiler
                extension and
                retraction.
------------------------------------------------------------------------
               An SOC is
                required.
------------------------------------------------------------------------
               A subjective test
                is required.
------------------------------------------------------------------------
7.d..........  The simulator must                  X
                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
                airplane, and be
                made a part of
                the QTG.
------------------------------------------------------------------------
               Objective tests
                are required.
------------------------------------------------------------------------

             Table A1B.--Table of Tasks vs. Simulator Level
------------------------------------------------------------------------
                <<>>                   <>
------------------------------------------------------------------------
                   Subjective        Simulator levels
                requirements  In   --------------------
             order to be qualified
                at the simulator
              qualification level
                 indicated, the
   Number      simulator must be                              Notes
               able to perform at    A    B    C    D
                least the tasks
              associated with that
                    level of
                 qualification.
------------------------------------------------------------------------
 1. Preflight Procedures
------------------------------------------------------------------------
1.a........  Preflight Inspection    X    X    X    X
              (flight deck only).
------------------------------------------------------------------------
1.b........  Engine Start.........   X    X    X    X
------------------------------------------------------------------------
1.c........  Taxiing..............             X    X
------------------------------------------------------------------------
1.d........  Pre-takeoff Checks...   X    X    X    X
------------------------------------------------------------------------
 2. Takeoff and Departure Phase
------------------------------------------------------------------------
2.a........  Normal and Crosswind              X    X
              Takeoff.
------------------------------------------------------------------------
2.b........  Instrument Takeoff...   X    X    X    X
------------------------------------------------------------------------
2.c........  Engine Failure During   A    X    X    X
              Takeoff.
------------------------------------------------------------------------
2.d........  Rejected Takeoff.....   X    X    X    X
------------------------------------------------------------------------
2.e........  Departure Procedure..   X    X    X    X
------------------------------------------------------------------------
 3. Inflight Maneuvers
------------------------------------------------------------------------

3.a........  Steep Turns..........   X    X    X    X
------------------------------------------------------------------------
3.b........  Approaches to Stalls.   X    X    X    X
------------------------------------------------------------------------
3.c........  Engine Failure--        X    X    X    X
              Multiengine Airplane.
------------------------------------------------------------------------
3.d........  Engine Failure--        X    X    X    X
              Single-Engine
              Airplane.
------------------------------------------------------------------------
3.e........  Specific Flight         A    A    A    A
              Characteristics
              incorporated into
              the user's FAA
              approved flight
              training program.
------------------------------------------------------------------------
3.f........  Recovery From Unusual   X    X    X    X   Within the
              Attitudes.                                 normal flight
                                                         envelope
                                                         supported by
                                                         applicable
                                                         simulation
                                                         validation
                                                         data.
------------------------------------------------------------------------
 4. Instrument Procedures
------------------------------------------------------------------------
4.a........  Standard Terminal       X    X    X    X
              Arrival/Flight
              Management System
              Arrivals Procedures.
------------------------------------------------------------------------
4.b........  Holding..............   X    X    X    X
------------------------------------------------------------------------
4.c........  Precision Instrument.
------------------------------------------------------------------------
4.c.1......  All engines operating   X    X    X    X   e.g., Autopilot,
                                                         Manual (Flt.
                                                         Dir. Assisted),
                                                         Manual (Raw
                                                         Data).
------------------------------------------------------------------------
4.c.2......  One engine              X    X    X    X   e.g., Manual
              inoperative.                               (Flt. Dir.
                                                         Assisted),
                                                         Manual (Raw
                                                         Data).
------------------------------------------------------------------------
4.d........  d. Non-precision        X    X    X    X   e.g., NDB, VOR,
              Instrument Approach.                       VOR/DME, VOR/
                                                         TAC, RNAV, LOC,
                                                         LOC/BC, ADF,
                                                         and SDF.
------------------------------------------------------------------------
4.e........  e. Circling Approach.   X    X    X    X   Specific
                                                         authorization
                                                         required.
------------------------------------------------------------------------
4.f........  Missed Approach......
------------------------------------------------------------------------
4.f.1......  Normal...............   X    X    X    X
------------------------------------------------------------------------
4.f.2......  One engine              X    X    X    X
              Inoperative.
------------------------------------------------------------------------
 5. Landings and Approaches to Landings
------------------------------------------------------------------------
5.a........  Normal and Crosswind         R    X    X
              Approaches and
              Landings.
------------------------------------------------------------------------
5.b........  Landing From a               R    X    X
              Precision/Non-
              Precision Approach.
------------------------------------------------------------------------
5.c........  Approach and Landing         R    X    X
              with (Simulated)
              Engine Failure--
              Multiengine Airplane.
------------------------------------------------------------------------
5.d........  Landing From Circling        R    X    X
              Approach.
------------------------------------------------------------------------
5.e........  Rejected Landing.....   X    X    X    X
------------------------------------------------------------------------
5.f........  Landing From a No            R    X    X
              Flap or a
              Nonstandard Flap
              Configuration
              Approach.
------------------------------------------------------------------------
 6. Normal and Abnormal Procedures
------------------------------------------------------------------------
6.a........  Engine (including       X    X    X    X
              shutdown and
              restart).
------------------------------------------------------------------------
6.b........  Fuel System..........   X    X    X    X
------------------------------------------------------------------------
6.c........  Electrical System....   X    X    X    X
------------------------------------------------------------------------
6.d........  Hydraulic System.....   X    X    X    X
------------------------------------------------------------------------
6.e........  Environmental and       X    X    X    X
              Pressurization
              Systems.
------------------------------------------------------------------------

6.f........  Fire Detection and      X    X    X    X
              Extinguisher Systems.
------------------------------------------------------------------------
6.g........  Navigation and          X    X    X    X
              Avionics Systems.
------------------------------------------------------------------------
6.h........  Automatic Flight        X    X    X    X
              Control System,
              Electronic Flight
              Instrument System,
              and Related
              Subsystems.
------------------------------------------------------------------------
6.i........  Flight Control          X    X    X    X
              Systems.
------------------------------------------------------------------------
6.j........  Anti-ice and Deice      X    X    X    X
              Systems.
------------------------------------------------------------------------
6.k........  Aircraft and Personal   X    X    X    X
              Emergency Equipment.
------------------------------------------------------------------------
 7. Emergency Procedures
------------------------------------------------------------------------
7.a........  Emergency Descent       X    X    X    X
              (Max. Rate).
------------------------------------------------------------------------
7.b........  Inflight Fire and       X    X    X    X
              Smoke Removal.
------------------------------------------------------------------------
7.c........  Rapid Decompression..   X    X    X    X
------------------------------------------------------------------------
7.d........  Emergency Evacuation.   X    X    X    X
------------------------------------------------------------------------
 8. Postflight Procedures
------------------------------------------------------------------------
8.a........  After-Landing           X    X    X    X
              Procedures.
------------------------------------------------------------------------
8.b........  Parking and Securing.   X    X    X    X
------------------------------------------------------------------------
------------------------------------------------------------------------
``A''--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.
``R''--indicates that the simulator may be qualified for this task for
  recurrent training.
``X''--indicates that the simulator must be able to perform this task
  for this level of qualification.

                                   Table A1C.--Table of Simulator System Tasks
----------------------------------------------------------------------------------------------------------------
                              <<>>                                     <<>>
----------------------------------------------------------------------------------------------------------------
                                  Subjective requirements  In   Simulator levels
                                    order to be qualified at  --------------------
                                  the simulator qualification
                                      level indicated, the
             Number                simulator must be able to                                   Notes
                                   perform at least the tasks   A    B    C    D
                                   associated with that level
                                       of qualification.
----------------------------------------------------------------------------------------------------------------
1. Instructor Operating Station (IOS), as appropriate
----------------------------------------------------------------------------------------------------------------
1.a.............................  Power switch(es)...........   X    X    X    X
----------------------------------------------------------------------------------------------------------------
1.b.............................  Airplane conditions........   X    X    X    X   e.g., GW, CG, Fuel loading
                                                                                and Systems.
----------------------------------------------------------------------------------------------------------------
1.c.............................  Airports / Runways.........   X    X    X    X   e.g., Selection, Surface,
                                                                                Presets, Lighting controls.
----------------------------------------------------------------------------------------------------------------
1.d.............................  Environmental controls.....   X    X    X    X   e.g., Clouds, Visibility,
                                                                                RVR, Temp, Wind, Ice, Snow,
                                                                                Rain, and Windshear.
----------------------------------------------------------------------------------------------------------------
1.e.............................  Airplane system               X    X    X    X
                                   malfunctions (Insertion/
                                   deletion).
----------------------------------------------------------------------------------------------------------------
1.f.............................  Locks, Freezes, and           X    X    X    X
                                   Repositioning.
----------------------------------------------------------------------------------------------------------------
2. Sound Controls
----------------------------------------------------------------------------------------------------------------
2.a.............................  On/off/adjustment..........   X    X    X    X
----------------------------------------------------------------------------------------------------------------
3. Motion/Control Loading System
----------------------------------------------------------------------------------------------------------------
3.a.............................  On /off/emergency stop.....   X    X    X    X
----------------------------------------------------------------------------------------------------------------
4. Observer Seats/Stations
----------------------------------------------------------------------------------------------------------------

4.a.............................  Position/Adjustment/          X    X    X    X
                                   Positive restraint system.
----------------------------------------------------------------------------------------------------------------

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

                            Table of Contents
------------------------------------------------------------------------
           Paragraph No.                            Title
------------------------------------------------------------------------
1.................................  Introduction.
------------------------------------------------------------------------
2.................................  Test Requirements.
------------------------------------------------------------------------
                                    Table A2A, Objective Tests.
------------------------------------------------------------------------
3.................................  General.
------------------------------------------------------------------------
4.................................  Control Dynamics.
------------------------------------------------------------------------
5.................................  Ground Effect.
------------------------------------------------------------------------
6.................................  Motion System.
------------------------------------------------------------------------
7.................................  Sound System.
------------------------------------------------------------------------
8.................................  Additional Information About Flight
                                     Simulator Qualification for New or
                                     Derivative Airplanes.
------------------------------------------------------------------------
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 (Flight-
                                     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.
------------------------------------------------------------------------

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

Begin Information

1. Introduction

    a. For the purposes of this attachment, the flight conditions
specified in the Flight Conditions Column of Table A2A, are defined
as follows:
    (1) Ground--on ground, independent of airplane configuration;
    (2) Take-off--gear down with flaps/slats in any certified
takeoff position;
    (3) First segment climb--gear down with flaps/slats in any
certified takeoff position (normally not above 50 ft AGL);
    (4) Second segment climb--gear up with flaps/slats in any
certified takeoff position (normally between 50 ft and 400 ft AGL);
    (5) Clean--flaps/slats retracted and gear up;
    (6) Cruise--clean configuration at cruise altitude and airspeed;
    (7) Approach--gear up or down with flaps/slats at any normal
approach position as recommended by the airplane manufacturer; and
    (8) Landing--gear down with flaps/slats in any certified landing
position.
    b. The format for numbering the objective tests in Appendix A,
Attachment 2, Table A2A, and the objective tests in Appendix B,
Attachment 2, Table B2A, is identical. However, each test required
for FFSs is not necessarily required for FTDs. Also, each test
required for FTDs is not necessarily required for FFSs. Therefore,
when a test number (or series of numbers) is not required, the term
``Reserved'' is used in the table at that location. Following this
numbering format provides a degree of commonality between the two
tables and substantially reduces the potential for confusion when
referring to objective test numbers for either FFSs or FTDs.
    c. The reader is encouraged to review the Airplane Flight
Simulator Evaluation Handbook, Volumes I and II, published by the
Royal Aeronautical Society, London, UK, and FAA Advisory Circulars
(AC) 25-7, as may be amended, Flight Test Guide for Certification of
Transport Category Airplanes, and (AC) 23-8, as may be amended,
Flight Test Guide for Certification of Part 23 Airplanes, for
references and examples regarding flight testing requirements and
techniques.
    d. If relevant winds are present in the objective data, the wind
vector should be clearly noted as part of the data presentation,
expressed in conventional terminology, and related to the runway
being used for the test.

End Information

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

Begin QPS Requirements

2. Test Requirements

    a. The ground and flight tests required for qualification are
listed in Table of A2A, FFS Objective Tests. Computer generated
simulator test 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 airplane being simulated or to the
qualification level sought, it may be disregarded (e.g., an engine
out missed approach for a single-engine airplane or a maneuver using
reverse thrust for an airplane without reverse thrust capability).
Each test result is compared against the validation data described
in Sec.  60.13 and in this appendix. Although use of a driver
program designed to automatically accomplish the tests is encouraged
for all simulators and required for Level C and Level D simulators,
it must be possible to conduct each test manually while recording
all appropriate parameters. The results must be produced on an
appropriate recording device acceptable to the NSPM and must include
simulator number, date, time, conditions, tolerances, and
appropriate dependent variables portrayed in comparison to the
validation data. Time histories are required unless otherwise
indicated in Table A2A. All results must be labeled using the
tolerances and units given.
    b. Table A2A in this attachment 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 and
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 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 A2A,
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 must 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 airplane
data throughout a time history, differences must be justified by
providing a comparison of other related variables for the condition
being assessed.

    e. It is not acceptable to program the FFS so that the
mathematical modeling is correct only at the validation test points.
Unless otherwise noted, simulator tests must represent airplane
performance and handling qualities at operating weights and centers
of gravity (CG) typical of normal operation. If a test is supported
by airplane data at one extreme weight or CG, another test supported
by airplane 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
airplane, sufficient data must also be provided to verify the
correct flight condition and airplane configuration changes. For
example, to show that control force is within the parameters for a
static stability test, data to show the correct airspeed, power,
thrust or torque, airplane 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 airplane, but airspeed, altitude, control
input, airplane configuration, and other appropriate data must also
be given. If comparing landing gear change dynamics, pitch,
airspeed, and altitude may be used to establish a match to the
airplane, but landing gear position must also be provided. 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. 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.
    i. Simulators are evaluated and qualified with an engine model
simulating the airplane data supplier's flight test engine. For
qualification of alternative engine models (either variations of the
flight test engines or other manufacturers' engines) additional
tests with the alternative engine models may be required. This
Attachment contains guidelines for alternative engines.
    j. For testing Computer Controlled Airplane (CCA) simulators, or
other highly augmented airplane simulators, flight test data is
required for the Normal (N) and/or Non-normal (NN) control states,
as indicated in this Attachment. Where test results are independent
of control state, Normal or Non-normal control data may be used. All
tests in Table A2A require test results in the Normal control state
unless specifically noted otherwise in the Test Details section
following the CCA designation. The NSPM will determine what tests
are appropriate for airplane simulation data. When making this
determination, the NSPM may require other levels of control state
degradation for specific airplane tests. Where Non-normal control
states are required, test data must be provided for one or more Non-
normal control states, and must include the least augmented state.
Where applicable, flight test data must record Normal and Non-normal
states for:
    (1) Pilot controller deflections or electronically generated
inputs, including location of input; and
    (2) Flight control surface positions unless test results are not
affected by, or are independent of, surface positions.
    k. Tests of handling qualities must include validation of
augmentation devices. FFSs for highly augmented airplanes 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. Requirements for testing will be mutually
agreed to between the sponsor and the NSPM on a case-by-case basis.
    l. Some tests will not be required for airplanes using airplane
hardware in the simulator flight deck (e.g., ``side stick
controller''). These exceptions are noted in Section 2 ``Handling
Qualities'' in Table A2A of this attachment. However, in these
cases, the sponsor must provide a statement that the airplane
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 airplane 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 airplane being simulated or as limited
by the minimum practical operating weight of the test airplane.
``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.'')
    n. In those cases where the objective test results authorize a
``snapshot test'' or a ``series of snapshot tests'' 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 snapshot.

End QPS Requirements

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

                                                 Table A2A.--Full Flight Simulator (FFS) Objective Tests
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                      <<>>
-----------------------------------------------------------------------------------------------------------------------------------
                    Test                                                                                Simulator level    Information  notes
---------------------------------------------       Tolerance        Flight  conditions       Test details     --------------------
        Number                  Title                                                                            A    B    C    D
--------------------------------------------------------------------------------------------------------------------------------------------------------
1. Performance
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.a...................  Taxi
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.a.1.................  Minimum Radius Turn.  3 ft      Ground..............  Record both Main and        X    X    X
                                               (0.9 m) or 20% of                           Nose gear turning
                                               airplane turn                               radius. This test
                                               radius.                                     is to be
                                                                                accomplished
                                                                                without the use of
                                                                                brakes and only
                                                                                minimum thrust,
                                                                                except for
                                                                                airplanes requiring
                                                                                asymmetric thrust
                                                                                or braking to turn.
--------------------------------------------------------------------------------------------------------------------------------------------------------

1.a.2.................  Rate of Turn vs.      10% or    Ground..............  Record a minimum of         X    X    X
                         Nosewheel Steering    2[deg]/                         two speeds, greater
                         Angle (NWA).          sec. turn rate.                             than minimum
                                                                                turning radius
                                                                                speed, with a
                                                                                spread of at least
                                                                                5 knots groundspeed.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.b...................  Takeoff                                                           All commonly used
                                                                                takeoff flap
                                                                                settings are to be
                                                                                demonstrated at
                                                                                least once in the
                                                                                tests for minimum
                                                                                unstick (1.b.3.),
                                                                                normal takeoff
                                                                                (1.b.4.), critical
                                                                                engine failure on
                                                                                takeoff (1.b.5.),
                                                                                or crosswind
                                                                                takeoff (1.b.6.).
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.b.1.................  Ground Acceleration   5% time   Takeoff.............  Record acceleration    X    X    X    X   May be combined with
                         Time and Distance.    and distance or                             time and distance                         normal takeoff
                                               5% time                         for a minimum of                          (1.b.4.) or
                                               and 200                         80% of the time                           rejected takeoff
                                               ft (61 m) of                                from brake release                        (1.b.7.). Plotted
                                               distance.                                   to VR.                                    data should be
                                                                                Preliminary aircraft                       shown using
                                                                                certification data                        appropriate scales
                                                                                may be used..                             for each portion of
                                                                                the maneuver.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.b.2.................  Minimum Control       25% of    Takeoff.............  Engine failure speed   X    X    X    X   If a Vmcg test is
                         Speed--ground         maximum airplane                            must be within                            not available an
                         (Vmcg) using          lateral deviation                           1 knot                        acceptable
                         aerodynamic           or 5 ft                         of airplane engine                        alternative is a
                         controls only (per    (1.5 m).                                    failure speed.                            flight test snap
                         applicable            Additionally, for                           Engine thrust decay                       engine deceleration
                         airworthiness         those simulators of                         must be that                              to idle at a speed
                         standard) or          airplanes with                              resulting from the                        between V1 and V1 -
                         alternative low       reversible flight                           mathematical model                        10 knots, followed
                         speed engine          control systems:                            for the engine                            by control of
                         inoperative test to   Rudder pedal force;                         variant applicable                        heading using
                         demonstrate ground    10% or                          to the full flight                        aerodynamic control
                         control               5 lb                            simulator under                           only. Recovery
                         characteristics.      (2.2 daN).                                  test. If the                              should be achieved
                                                                                modeled engine is                         with the main gear
                                                                                not the same as the                       on the ground. To
                                                                                airplane                                  ensure only
                                                                                manufacturer's                            aerodynamic control
                                                                                flight test engine,                       is used, nosewheel
                                                                                a further test may                        steering should be
                                                                                be run with the                           disabled (i.e.,
                                                                                same initial                              castored) or the
                                                                                conditions using                          nosewheel held
                                                                                the thrust from the                       slightly off the
                                                                                flight test data as                       ground.
                                                                                the driving
                                                                                parameter.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.b.3.................  Minimum Unstick       3 kts     Takeoff.............  Record main landing    X    X    X    X   Vmu is defined as
                         Speed (Vmu) or        airspeed < plus-                             gear strut                                the minimum speed
                         equivalent test to    minus>1.5[deg]                              compression or                            at which the last
                         demonstrate early     pitch angle.                                equivalent air/                           main landing gear
                         rotation takeoff                                                  ground signal.                            leaves the ground.
                         characteristics.                                                  Record from 10 kt                         Main landing gear
                                                                                before start of                           strut compression
                                                                                rotation until at                         or equivalent air/
                                                                                least 5 seconds                           ground signal
                                                                                after the                                 should be recorded.
                                                                                occurrence of main                        If a Vmu test is
                                                                                gear lift-off.                            not available,
                                                                                alternative
                                                                                acceptable flight
                                                                                tests are a
                                                                                constant high-
                                                                                attitude take-off
                                                                                run through main
                                                                                gear lift-off or an
                                                                                early rotation take-
                                                                                off.
--------------------------------------------------------------------------------------------------------------------------------------------------------

1.b.4.................  Normal Takeoff......  3 kts     Takeoff.............  Record takeoff         X    X    X    X   This test may be
                                               airspeed < plus-                             profile from brake                        used for ground
                                               minus>1.5[deg]                              release to at least                       acceleration time
                                               pitch angle < plus-                          200 ft (61 m) above                       and distance
                                               minus>1.5[deg]                              ground level (AGL).                       (1.b.1.). Plotted
                                               angle of attack                             If the airplane has                       data should be
                                               20 ft                           more than one                             shown using
                                               (6 m) height.                               certificated                              appropriate scales
                                               Additionally, for                           takeoff                                   for each portion of
                                               those simulators of                         configurations, a                         the maneuver.
                                               airplanes with                              different
                                               reversible flight                           configuration must
                                               control systems:                            be used for each
                                               Stick/Column Force;                         weight. Data are
                                               10% or                          required for a
                                               5 lb                            takeoff weight at
                                               (2.2 daN).                                  near maximum
                                                                                takeoff weight with
                                                                                a mid-center of
                                                                                gravity and for a
                                                                                light takeoff
                                                                                weight with an aft
                                                                                center of gravity,
                                                                                as defined in
                                                                                Appendix F.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.b.5.................  Critical Engine       3 kts     Takeoff.............  Record takeoff         X    X    X    X
                         Failure on Takeoff.   airspeed < plus-                             profile at near
                                               minus>1.5[deg]                              maximum takeoff
                                               pitch angle, < plus-                         weight from prior
                                               minus>1.5[deg]                              to engine failure
                                               angle of attack,                            to at least 200 ft
                                               20 ft                           (61 m) AGL. Engine
                                               (6 m) height, < plus-                        failure speed must
                                               minus>3[deg]                                be within 3 kts of
                                               2[deg]                          airplane data.
                                               bank angle, < plus-
                                               minus>2[deg]
                                               sideslip angle.
                                               Additionally, for
                                               those simulators of
                                               airplanes with
                                               reversible flight
                                               control systems:
                                               Stick/ Column
                                               Force; < plus-
                                               minus>10% or 5 lb (2.2
                                               daN)); Wheel Force;
                                               10% or
                                               3 lb
                                               (1.3 daN); and
                                               Rudder Pedal Force;
                                               10% or
                                               5 lb
                                               (2.2 daN).
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.b.6.................  Crosswind Takeoff...  3 kts     Takeoff.............  Record takeoff         X    X    X    X   In those situations
                                               airspeed, < plus-                            profile from brake                        where a maximum
                                               minus>1.5[deg]                              release to at least                       crosswind or a
                                               pitch angle, < plus-                         200 ft (61 m) AGL.                        maximum
                                               minus>1.5[deg]                              Requires test data,                       demonstrated
                                               angle of attack,                            including                                 crosswind is not
                                               20 ft                           information on wind                       known, contact the
                                               (6 m) height, < plus-                        profile for a                             NSPM.
                                               minus>2[deg] bank                           crosswind component
                                               angle, < plus-                               of at least 60% of
                                               minus>2[deg]sidesli                         the maximum wind
                                               p angle; < plus-                             measured at 33 ft
                                               minus>3[deg]                                (10 m) above the
                                               heading angle.                              runway.
                                               Correct trend at
                                               groundspeeds below
                                               40 kts. for rudder/
                                               pedal and heading.
                                               Additionally, for
                                               those simulators of
                                               airplanes with
                                               reversible flight
                                               control systems:
                                               Stick/Column Force;
                                               10% or
                                               5 lb
                                               (2.2 daN) stick/
                                               column force, < plus-
                                               minus>10% or 3 lb (1.3daN)
                                               wheel force, < plus-
                                               minus>10% or 5 lb (2.2
                                               daN) rudder pedal
                                               force.
--------------------------------------------------------------------------------------------------------------------------------------------------------

1.b.7.................  Rejected Takeoff....  5% time   Takeoff.............  Record time and        X    X    X    X   Autobrakes will be
                                               or 1.5                          distance from brake                       used where
                                               sec < plus-                                  release to full                           applicable.
                                               minus>7.5% distance                         stop. Speed for
                                               or 250                          initiation of the
                                               ft (76                          reject must be at
                                               m).                                         least 80% of V1
                                                                                speed. The airplane
                                                                                must be at or near
                                                                                the maximum takeoff
                                                                                gross weight. Use
                                                                                maximum braking
                                                                                effort, auto or
                                                                                manual.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.b.8.................  Dynamic Engine        20% or    Takeoff.............  Engine failure speed             X    X   For safety
                         Failure After         2[deg]/                         must be within                            considerations,
                         Takeoff.              sec body angular                            3 Kts                         airplane flight
                                               rates.                                      of airplane data.                         test may be
                                                                                Record Hands Off                          performed out of
                                                                                from 5 secs. before                       ground effect at a
                                                                                to at least 5 secs.                       safe altitude, but
                                                                                after engine                              with correct
                                                                                failure or 30[deg]                        airplane
                                                                                Bank, whichever                           configuration and
                                                                                occurs first.                             airspeed.
                                                                                Engine failure may
                                                                                be a snap
                                                                                deceleration to
                                                                                idle.
                                                                                (CCA: Test in Normal
                                                                                and Non-normal
                                                                                control state.).
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.c...................  Climb
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.c.1.................  Normal Climb, all     3 kts     Clean...............  Flight test data is    X    X    X    X
                         engines operating.    airspeed, < plus-                            preferred, however,
                                               minus>5% or 100 FPM (0.5                          performance manual
                                               m/Sec.) climb rate.                         data is an
                                                                                acceptable
                                                                                alternative. Record
                                                                                at nominal climb
                                                                                speed and mid-
                                                                                initial climb
                                                                                altitude. Flight
                                                                                simulator
                                                                                performance must be
                                                                                recorded over an
                                                                                interval of at
                                                                                least 1,000 ft.
                                                                                (300 m).
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.c.2.................  One engine            3 kts     For part 23           Flight test data is    X    X    X    X
                         Inoperative.          airspeed, < plus-      airplanes, in         preferred, however,
                                               minus>5% or 100 FPM (0.5    part 23. For part     performance manual
                                               m/Sec.) climb rate,   25 airplanes,         data is an
                                               but not less than     Second Segment        acceptable
                                               the climb gradient    Climb.                alternative. Test
                                               requirements of 14                          at weight,
                                               CFR part 23 or part                         altitude, or
                                               25, as appropriate.                         temperature
                                                                                limiting
                                                                                conditions. Record
                                                                                at nominal climb
                                                                                speed. Flight
                                                                                simulator
                                                                                performance must be
                                                                                recorded over an
                                                                                interval of at
                                                                                least 1,000 ft.
                                                                                (300 m).
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.c.3.................  One Engine            10%       Clean...............  Record results for               X    X
                         Inoperative En        time, < plus-                                at least a 5,000 ft
                         route Climb.          minus>10% distance,                         (1550 m) climb
                                               10%                             segment. Flight
                                               fuel used.                                  test data or
                                                                                airplane
                                                                                performance manual
                                                                                data may be used.
--------------------------------------------------------------------------------------------------------------------------------------------------------

1.c.4.................  One Engine            3 kts     Approach............  Record results at      X    X    X    X   The airplane should
                         Inoperative           airspeed, < plus-                            near maximum gross                        be configured with
                         Approach Climb (if    minus>5% or 100 FPM (0.5                          defined in Appendix                       ice systems
                         conditions are        m/Sec.) climb rate,                         F. Flight test data                       operating normally,
                         authorized).          but not less than                           or airplane                               with the gear up
                                               the climb gradient                          performance manual                        and go-around flaps
                                               requirements of 14                          data may be used.                         set. All icing
                                               CFR parts 23 or 25                          Flight simulator                          accountability
                                               climb gradient, as                          performance must be                       considerations
                                               appropriate.                                recorded over an                          should be applied
                                                                                interval of at                            in accordance with
                                                                                least 1,000 ft.                           the aircraft
                                                                                (300 m).                                  certification or
                                                                                authorization for
                                                                                an approach in
                                                                                icing conditions.
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1.d...................  Cruise/Descent
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1.d.1.................  Level flight          5% Time.  Cruise..............  Record results for a   X    X    X    X
                         acceleration.                                                     minimum of 50 kts
                                                                                speed increase
                                                                                using maximum
                                                                                continuous thrust
                                                                                rating or
                                                                                equivalent.
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1.d.2.................  Level flight          5% Time.  Cruise..............  Record results for a   X    X    X    X
                         deceleration.                                                     minimum of 50 kts.
                                                                                speed decrease
                                                                                using idle power.
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1.d.3.................  Cruise performance..  0.05 EPR  Cruise..............  May be a single                  X    X
                                               or 5%                           snapshot showing
                                               of N1, or < plus-                            instantaneous fuel
                                               minus>5% of Torque,                         flow or a minimum
                                               5% of                           of 2 consecutive
                                               fuel flow.                                  snapshots with a
                                                                                spread of at least
                                                                                3 minutes in steady
                                                                                flight.
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1.d.4.................  Idle descent........  3 kt      Clean...............  Record a stabilized,   X    X    X    X
                                               airspeed, < plus-                            idle power descent
                                               minus>5% or 200 ft/min                            speed at mid-
                                               (1.0m/sec) descent                          altitude. Flight
                                               rate.                                       simulator
                                                                                performance must be
                                                                                recorded over an
                                                                                interval of at
                                                                                least 1,000 ft.
                                                                                (300 m).
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1.d.5.................  Emergency descent...  5 kt      N/A.................  Performance must be    X    X    X    X   The stabilized
                                               airspeed, < plus-                            recorded over an                          descent should be
                                               minus>5% or 300 ft/min                            least 3,000 ft (900                       speed brakes
                                               (1.5m/s) descent                            m).                                       extended, if
                                               rate.                                                                                applicable, at mid-
                                                                                altitude and near
                                                                                Vmo speed or in
                                                                                accordance with
                                                                                emergency descent
                                                                                procedures.
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1.e...................  Stopping
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1.e.1.................  Stopping time and     5% of     Landing.............  Record time and        X    X    X    X
                         distance, using       time. For distance                          distance for at
                         manual application    up to 4000 ft (1220                         least 80% of the
                         of wheel brakes and   m): 200                         total time from
                         no reverse thrust     ft (61 m) or < plus-                         touch down to full
                         on a dry runway.      minus>10%,                                  stop. Data is
                                               whichever is                                required for
                                               smaller. For                                weights at medium
                                               distance greater                            and near maximum
                                               than 4000 ft (1220                          landing weights.
                                               m): 5%                          Data for brake
                                               of distance.                                system pressure and
                                                                                position of ground
                                                                                spoilers (including
                                                                                method of
                                                                                deployment, if
                                                                                used) must be
                                                                                provided.
                                                                                Engineering data
                                                                                may be used for the
                                                                                medium gross weight
                                                                                condition.
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1.e.2.................  Stopping time and     5% time   Landing.............  Record time and        X    X    X    X
                         distance, using       and the smaller of                          distance for at
                         reverse thrust and    10% or                          least 80% of the
                         no wheel brakes on    200 ft                          total time from
                         a dry runway.         (61 m) of distance.                         initiation of
                                                                                reverse thrust to
                                                                                the minimum
                                                                                operating speed
                                                                                with full reverse
                                                                                thrust. Data is
                                                                                required for medium
                                                                                and near maximum
                                                                                landing gross
                                                                                weights. Data on
                                                                                the position of
                                                                                ground spoilers,
                                                                                (including method
                                                                                of deployment, if
                                                                                used) must be
                                                                                provided.
                                                                                Engineering data
                                                                                may be used for the
                                                                                medium gross weight
                                                                                condition.
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1.e.3.................  Stopping distance,    10% of    Landing.............  Either flight test               X    X
                         using wheel brakes    distance or < plus-                          data or
                         and no reverse        minus>200 ft (61 m).                        manufacturer's
                         thrust on a wet                                                   performance manual
                         runway.                                                           data must be used
                                                                                where available.
                                                                                Engineering data
                                                                                based on dry runway
                                                                                flight test
                                                                                stopping distance
                                                                                modified by the
                                                                                effects of
                                                                                contaminated runway
                                                                                braking
                                                                                coefficients are an
                                                                                acceptable
                                                                                alternative.
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1.e.4.................  Stopping distance,    10% of    Landing.............  Either flight test               X    X
                         using wheel brakes    distance or < plus-                          or manufacturer's
                         and no reverse        minus>200 ft (61 m).                        performance manual
                         thrust on an icy                                                  data must be used,
                         runway.                                                           where available.
                                                                                Engineering data
                                                                                based on dry runway
                                                                                flight test
                                                                                stopping distance
                                                                                modified by the
                                                                                effects of
                                                                                contaminated runway
                                                                                braking
                                                                                coefficients are an
                                                                                acceptable
                                                                                alternative.
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1.f...................  Engines
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1.f.1.................  Acceleration........  10% Tt    Approach or landing.  Record engine power    X    X    X    X   Ti, is the total
                                               and 10%                         (N1, N2, EPR,                             time from initial
                                               Ti, or < plus-                               Torque) from flight                       throttle movement
                                               minus>0.25 sec.                             idle to go-around                         until reaching a
                                                                                power for a rapid                         10% response of
                                                                                (slam) throttle                           engine power. Tt is
                                                                                movement.                                 the total time from
                                                                                initial throttle
                                                                                movement to
                                                                                reaching 90% of go
                                                                                around power.
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1.f.2.................  Deceleration........  10% Tt    Ground..............  Record engine power    X    X    X    X   Ti, is the total
                                               and 10%                         (N1, N2, EPR,                             time from initial
                                               Ti, or < plus-                               Torque) from Max T/                       throttle movement
                                               minus>0.25 sec.                             O power to 90%                            until reaching a
                                                                                decay of Max T/O                          10% response of
                                                                                power for a rapid                         engine power. Tt is
                                                                                (slam) throttle                           the total time from
                                                                                movement.                                 initial throttle
                                                                                movement to
                                                                                reaching 90% decay
                                                                                of maximum takeoff
                                                                                power.
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2. Handling Qualities
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                        For simulators requiring Static or Dynamic tests at the controls (i.e., column, wheel,                      Contact the NSPM for
                         rudder pedal), special test fixtures will not be required during initial or upgrade                         clarification of
                         evaluations if the sponsor's QTG/MQTG shows both test fixture results and the results                       any issue regarding
                         of an alternative approach, such as computer plots produced concurrently, that                              airplanes with
                         provide satisfactory agreement. Repeat of the alternative method during the initial                         reversible
                         or upgrade evaluation would then satisfy this test requirement. For initial and                             controls.
                         upgrade evaluations, the control dynamic characteristics must be measured at and
                         recorded directly from the flight deck controls, and must be accomplished in takeoff,
                         cruise, and landing flight conditions and configurations. Testing of position versus
                         force is not applicable if forces are generated solely by use of airplane hardware in
                         the full flight simulator
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2.a...................  Static Control Tests
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2.a.1.a...............  Pitch Controller      2 lb      Ground..............  Record results for     X    X    X    X   Test results should
                         Position vs. Force    (0.9 daN) breakout,                         an uninterrupted                          be validated (where
                         and Surface           10% or                          control sweep to                          possible) with in-
                         Position              5 lb                            the stops.                                flight data from
                         Calibration.          (2.2 daN) force,                                                                      tests such as
                                               2[deg]                                                                    longitudinal static
                                               elevator.                                                                             stability or
                                                                                stalls. Static and
                                                                                dynamic flight
                                                                                control tests
                                                                                should be
                                                                                accomplished at the
                                                                                same feel or impact
                                                                                pressures.
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2.a.1.b...............  (Reserved)
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2.a.2.a...............  Roll Controller       2 lb      Ground..............  Record results for     X    X    X    X   Test results should
                         Position vs. Force    (0.9 daN) breakout,                         an uninterrupted                          be validated with
                         and Surface           10% or                          control sweep to                          in-flight data from
                         Position              3 lb                            the stops.                                tests such as
                         Calibration.          (1.3 daN) force,                                                                      engine out trims,
                                               2[deg]                                                                    steady state or
                                               aileron, < plus-                                                                       sideslips. Static
                                               minus>3[deg]                                                                          and dynamic flight
                                               spoiler angle.                                                                        control tests