description of the operational and engineering effect the proposed
modification will have on the operation of the FTD and the results
that are expected with the modification incorporated.
    b. Prior to using the modified FTD:
    (1) All the applicable objective tests completed with the
modification incorporated, including any necessary updates to the
MQTG (e.g., accomplishment of FSTD Directives) must be acceptable to
the NSPM; and
    (2) The sponsor must provide the NSPM with a statement signed by
the MR that the factors listed in Sec.  60.15(b) are addressed by
the appropriate personnel as described in that section.

End QPS Requirements

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

Begin Information

    c. FSTD Directives are considered modification of an FTD. See
Attachment 4, Figure D4H for a sample index of effective FSTD
Directives. See Attachment 6 for a list of all effective FSTD
Directives applicable to Helicopter FTDs.

End Information

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

18. Operation with Missing, Malfunctioning, or Inoperative Components
(Sec.  60.25)

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

Begin Information

    a. The sponsor's responsibility with respect to Sec.  60.25(a)
is satisfied when the sponsor fairly and accurately advises the user
of the current status of an FTD, including any missing,
malfunctioning, or inoperative (MMI) component(s).
    b. If the 29th or 30th day of the 30-day period described in
Sec.  60.25(b) is on a Saturday, a Sunday, or a holiday, the FAA
will extend the deadline until the next business day.
    c. In accordance with the authorization described in Sec.
60.25(b), the sponsor may develop a discrepancy prioritizing system
to accomplish repairs based on the level of impact on the capability
of the FTD. Repairs having a larger impact on the FTD's ability to
provide the required training, evaluation, or flight experience will
have a higher priority for repair or replacement.

End Information

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

19. Automatic Loss of Qualification and Procedures for Restoration of
Qualification (Sec.  60.27)

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

Begin Information

    If the sponsor provides a plan for how the FTD will be
maintained during its out-of-service period (e.g., periodic exercise
of mechanical, hydraulic, and electrical systems; routine
replacement of hydraulic fluid; control of the environmental factors
in which the FTD is to be maintained.) there is a greater likelihood
that the NSPM will be able to determine the amount of testing that
required for requalification.

End Information

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

20. Other Losses of Qualification and Procedures for Restoration of
Qualification (Sec.  60.29)

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

Begin Information

    If the sponsor provides a plan for how the FTD will be
maintained during its out-of-service period (e.g., periodic exercise
of mechanical, hydraulic, and electrical systems; routine
replacement of hydraulic fluid; control of the environmental factors
in which the FTD is to be maintained.) there is a greater likelihood
that the NSPM will be able to determine the amount of testing that
required for requalification.

End Information

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

21. Recordkeeping and Reporting (Sec.  60.31)

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

Begin QPS Requirements

    a. FTD modifications can include hardware or software changes.
For FTD modifications involving software programming changes, the
record required by Sec.  60.31(a)(2) must consist of the name of the
aircraft system software, aerodynamic model, or engine model change,
the date of the change, a summary of the change, and the reason for
the change.
    b. If a coded form for recordkeeping is used, it must provide
for the preservation and retrieval of information with appropriate
security or controls to prevent the inappropriate alteration of such
records after the fact.

End QPS Requirements

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

22. Applications, Logbooks, Reports, and Records: Fraud, Falsification,
or Incorrect Statements (Sec.  60.33)

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

Begin Information

    No additional regulatory or informational material applies to
Sec.  60.33, Applications, Logbooks, Reports, and Records: Fraud,
Falsification, or Incorrect Statements.

23. [Reserved]

End Information

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

24. Levels of FTD

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

Begin Information

    a. The following is a general description of each level of FTD.
Detailed standards and tests for the various levels of FTDs are
fully defined in Attachments 1 through 3 of this appendix.
    (1) Level 4. A Level 4 device is one that may have an open
helicopter-specific flight deck area, or an enclosed helicopter-
specific flight deck and at least one operating system. Air/ground
logic is required (no aerodynamic programming required). All
displays may be flat/LCD panel representations or actual
representations of displays in the aircraft. All controls, switches,
and knobs may be touch sensitive activation (not capable of manual
manipulation of the flight controls) or may physically replicate the
aircraft in control operation.
    (2) Level 5. A Level 5 device is one that may have an open
helicopter-specific flight deck area, or an enclosed helicopter-
specific flight deck and a generic aerodynamic program with at least
one operating system and control loading representative of the
simulated helicopter. The control loading need only represent the
helicopter at an approach speed and configuration. All displays may
be flat/LCD panel representations or actual representations of
displays in the aircraft. Primary and secondary flight controls
(e.g., rudder, aileron, elevator, flaps, spoilers/speed brakes,
engine controls, landing gear, nose wheel steering, trim, brakes)
must be physical controls. All other controls, switches, and knobs
may be touch sensitive activation.
    (3) Level 6. A Level 6 device is one that has an enclosed
helicopter-specific flight deck and aerodynamic program with all
applicable helicopter systems operating and control loading that is
representative of the simulated helicopter throughout its ground and
flight envelope and significant sound representation. All displays
may be flat/LCD panel representations or actual representations of
displays in the aircraft, but all controls, switches, and knobs must
physically replicate the aircraft in control operation.
    (4) Level 7. A Level 7 device is one that has an enclosed
helicopter-specific flight deck and aerodynamic program with all
applicable helicopter systems operating and control loading that is
representative of the simulated helicopter throughout its ground and
flight envelope and significant sound representation. All displays
may be flat/LCD panel representations or actual representations of
displays in the aircraft, but all controls, switches, and knobs must
physically replicate the aircraft in control operation. It also has
a visual system that provides an out-of-the-flight deck view,
providing cross-flight deck viewing (for both pilots simultaneously)
of a field of view of at least 146[deg] horizontally and 36[deg]
vertically as well as a vibration cueing system for characteristic
helicopter vibrations noted at the pilot station(s).

End Information

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

25. FSTD Qualification on the Basis of a Bilateral Aviation Safety
Agreement (BASA) (Sec.  60.37)

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

Begin Information

    No additional regulatory or informational material applies to
Sec.  60.37, FSTD Qualification on the Basis of a Bilateral Aviation
Safety Agreement (BASA).

End Information

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

Attachment 1 to Appendix D to Part 60--General FTD Requirements

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

Begin QPS Requirements

1. Requirements

    a. Certain requirements included in this appendix must be
supported with a Statement of Compliance and Capability (SOC), which
may include objective and subjective tests. The SOC will confirm
that the requirement was satisfied, and describe how the requirement
was met. The requirements for SOCs and tests are indicated in the
``General FTD Requirements'' column in Table D1A of this appendix.
    b. Table D1A describes the requirements for the indicated level
of FTD. Many devices include operational systems or functions that
exceed the requirements outlined in this section. In any event, all
systems will be tested and evaluated in accordance with this
appendix to ensure proper operation.

End QPS Requirements

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

Begin Information

2. Discussion

    a. This attachment describes the general requirements for
qualifying Level 4 through Level 7 FTDs. The sponsor should also
consult the objectives tests in Attachment 2 and the examination of
functions and subjective tests listed in Attachment 3 to determine
the complete requirements for a specific level FTD.
    b. The material contained in this attachment is divided into the
following categories:
    (1) General Flight Deck Configuration.
    (2) Programming.
    (3) Equipment Operation.
    (4) Equipment and facilities for instructor/evaluator functions.
    (5) Motion System.
    (6) Visual System.
    (7) Sound System.
    c. Table D1A provides the standards for the General FTD
Requirements.
    d. Table D1B provides the tasks that the sponsor will examine to
determine whether the FSTD satisfactorily meets the requirements for
flight crew training, testing, and experience.
    e. Table D1C provides the functions that an instructor/check
airman must be able to control in the simulator.
    f. It is not required that all of the tasks that appear on the
List of Qualified Tasks (part of the SOQ) be accomplished during the
initial or continuing qualification evaluation.

End Information

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

                  Table D1A.--Minimum FTD Requirements
------------------------------------------------------------------------
                <<>>
------------------------------------------------------
                                        FTD level       <>
    Number         General FTD    --------------------       notes
                  requirements      4    5    6    7
------------------------------------------------------------------------
1. General Flight Deck Configuration
------------------------------------------------------------------------
1.a..........  The FTD must have   ...  ...   X    X   For FTD purposes,
                a flight deck                           the flight deck
                that is a replica                       consists of all
                of the                                  that space
                helicopter, or                          forward of a
                set of                                  cross section of
                helicopters                             the flight deck
                simulated with                          at the most
                controls,                               extreme aft
                equipment,                              setting of the
                observable flight                       pilots' seats
                deck indicators,                        including
                circuit breakers,                       additional,
                and bulkheads                           required
                properly located,                       crewmember duty
                functionally                            stations and
                accurate and                            those required
                replicating the                         bulkheads aft of
                helicopter or set                       the pilot seats.
                of helicopters.
                The direction of
                movement of
                controls and
                switches must be
                identical to that
                in the helicopter
                or set of
                helicopters.
                Crewmember seats
                must afford the
                capability for
                the occupant to
                be able to
                achieve the
                design ``eye
                position.''
                Equipment for the
                operation of the
                flight deck
                windows must be
                included, but the
                actual windows
                need not be
                operable. Fire
                axes,
                extinguishers,
                and spare light
                bulbs must be
                available in the
                flight simulator,
                but may be
                relocated to a
                suitable location
                as near as
                practical to the
                original
                position. Fire
                axes, landing
                gear pins, and
                any similar
                purpose
                instruments need
                only be
                represented in
                silhouette.
               An SOC is
                required.
------------------------------------------------------------------------
1.b..........  The FTD must have    X    X   ...  ...
                equipment (i.e.,
                instruments,
                panels, systems,
                circuit breakers,
                and controls)
                simulated
                sufficiently for
                the authorized
                training/checking
                events to be
                accomplished. The
                installed
                equipment, must
                be located in a
                spatially correct
                configuration,
                and may be in a
                flight deck or an
                open flight deck
                area. Additional
                equipment
                required for the
                authorized
                training and
                checking events
                must be available
                in the FTD but
                may be located in
                a suitable
                location as near
                as practical to
                the spatially
                correct position.
                Actuation of this
                equipment must
                replicate the
                appropriate
                function in the
                helicopter. Fire
                axes, landing
                gear pins, and
                any similar
                purpose
                instruments need
                only be
                represented in
                silhouette.
               An SOC is
                required.
------------------------------------------------------------------------
2. Programming
------------------------------------------------------------------------
2.a..........  The FTD must        ...   X    X    X   .................
                provide the
                proper effect of
                aerodynamic
                changes for the
                combinations of
                drag and thrust
                normally
                encountered in
                flight. This must
                include the
                effect of change
                in helicopter
                attitude, thrust,
                drag, altitude,
                temperature, and
                configuration.
               Levels 6 and 7
                additionally
                require the
                effects of
                changes in gross
                weight and center
                of gravity.
               Level 5 requires
                only generic
                aerodynamic
                programming.
               An SOC is
                required.
------------------------------------------------------------------------
2.b..........  The FTD must have    X    X    X    X
                the computer
                (analog or
                digital)
                capability (i.e.,
                capacity,
                accuracy,
                resolution, and
                dynamic response)
                needed to meet
                the qualification
                level sought.
               An SOC is
                required.
------------------------------------------------------------------------
2.c..........  Relative responses
                of the flight
                deck instruments
                must be measured
                by latency tests
                or transport
                delay tests, and
                may not exceed
                150 milliseconds.
                The instruments
                must respond to
                abrupt input at
                the pilot's
                position within
                the allotted
                time, but not
                before the time
                that the
                helicopter or set
                of helicopters
                would respond
                under the same
                conditions.

                Latency:   ...   X    X    X   The intent is to
                The FTD                                 verify that the
                instrument and,                         FTD provides
                if applicable,                          instrument cues
                the motion system                       that are, within
                and the visual                          the stated time
                system response                         delays, like the
                must not be prior                       helicopter
                to that time when                       responses. For
                the helicopter                          helicopter
                responds and may                        response,
                respond up to 150                       acceleration in
                milliseconds                            the appropriate,
                after that time                         corresponding
                under the same                          rotational axis
                conditions.                             is preferred.
                Transport
                Delay: As an
                alternative to
                the Latency
                requirement, a
                transport delay
                objective test
                may be used to
                demonstrate that
                the FTD system
                does not exceed
                the specified
                limit. The
                sponsor must
                measure all the
                delay encountered
                by a step signal
                migrating from
                the pilot's
                control through
                all the
                simulation
                software modules
                in the correct
                order, using a
                handshaking
                protocol, finally
                through the
                normal output
                interfaces to the
                instrument
                display and, if
                applicable, the
                motion system,
                and the visual
                system.
               An objective test
                is required.
------------------------------------------------------------------------
3. Equipment Operation
------------------------------------------------------------------------
3.a..........  All relevant         A    X    X    X
                instrument
                indications
                involved in the
                simulation of the
                helicopter must
                automatically
                respond to
                control movement
                or external
                disturbances to
                the simulated
                helicopter or set
                of helicopters;
                e.g., turbulence
                or winds.
               A subjective test
                is required.
------------------------------------------------------------------------
3.b..........  Navigation           A    X    X    X
                equipment must be
                installed and
                operate within
                the tolerances
                applicable for
                the helicopter or
                set of
                helicopters.
               Levels 6 and 7
                must also include
                communication
                equipment (inter-
                phone and air/
                ground) like that
                in the
                helicopter.
               Level 5 only needs
                that navigation
                equipment
                necessary to fly
                an instrument
                approach.
               A subjective test
                is required.
------------------------------------------------------------------------
3.c..........  Installed systems    A    X    X    X
                must simulate the
                applicable
                helicopter system
                operation both on
                the ground and in
                flight. At least
                one helicopter
                system must be
                represented.
                Systems must be
                operative to the
                extent that
                applicable
                normal, abnormal,
                and emergency
                operating
                procedures
                included in the
                sponsor's
                training programs
                can be
                accomplished.
               Levels 6 and 7
                must simulate all
                applicable
                helicopter
                flight,
                navigation, and
                systems
                operation.
               Level 5 must have
                functional flight
                and navigational
                controls,
                displays, and
                instrumentation.
               A subjective test
                is required.
------------------------------------------------------------------------
3.d..........  The lighting         X    X    X    X   Back-lighted
                environment for                         panels and
                panels and                              instruments may
                instruments must                        be installed but
                be sufficient for                       are not
                the operation                           required.
                being conducted.
               A subjective test
                is required.
------------------------------------------------------------------------
3.e..........  The FTD must        ...  ...   X    X
                provide control
                forces and
                control travel
                that correspond
                to the replicated
                helicopter or set
                of helicopters.
                Control forces
                must react in the
                same manner as in
                the helicopter or
                set of
                helicopters under
                the same flight
                conditions.
               A subjective test
                is required.
------------------------------------------------------------------------
3.f..........  The FTD must        ...   X   ...  ...
                provide control
                forces and
                control travel of
                sufficient
                precision to
                manually fly an
                instrument
                approach. The
                control forces
                must react in the
                same manner as in
                the helicopter or
                set of
                helicopters under
                the same flight
                conditions.
               A subjective test
                is required.
------------------------------------------------------------------------

4. Instructor or Evaluator Facilities
------------------------------------------------------------------------
4.a..........  In addition to the   X    X    X    X   These seats need
                flight crewmember                       not be a replica
                stations,                               of an aircraft
                suitable seating                        seat and may be
                arrangements for                        as simple as an
                an instructor/                          office chair
                check airman and                        placed in an
                FAA Inspector                           appropriate
                must be                                 position.
                available. These
                seats must
                provide adequate
                view of
                crewmember's
                panel(s).
               A subjective test
                is required.
------------------------------------------------------------------------
4.b..........  The FTD must have    X    X    X    X
                instructor
                controls that
                permit activation
                of normal,
                abnormal, and
                emergency
                conditions, as
                may be
                appropriate. Once
                activated, proper
                system operation
                must result from
                system management
                by the crew and
                not require input
                from the
                instructor
                controls.
               A subjective test
                is required.
------------------------------------------------------------------------
5. Motion System
------------------------------------------------------------------------
5.a..........  The FTD may have a   X    X    X   ...
                motion system; if
                desired, although
                it is not
                required. If
                installed, the
                motion system
                operation may not
                be distracting.
               A subjective test
                is required.
------------------------------------------------------------------------
5.b..........  Although it is not   X    X    X   ...
                required, if a
                motion system is
                installed and
                additional
                training,
                testing, or
                checking credits
                are being sought
                on the basis of
                having a motion
                system, the
                motion system
                operation may not
                be distracting
                and must be
                coupled closely
                to provide
                integrated
                sensory cues. The
                motion system
                must also respond
                to abrupt input
                at the pilot's
                position within
                the allotted
                time, but not
                before the time
                when the
                helicopter would
                respond under the
                same conditions,
                it must be
                measured by
                latency tests or
                transport delay
                tests and may not
                exceed 150
                milliseconds.
                Instrument
                response may not
                occur prior to
                motion onset.
               An objective test
                is required.
------------------------------------------------------------------------
5.c..........  The FTD must have   ...  ...  ...   X   May be
                at least a                              accomplished by
                vibration cueing                        a ``seat
                system for                              shaker'' or a
                characteristic                          bass speaker
                helicopter                              sufficient to
                vibrations noted                        provide the
                at the pilot                            necessary
                station(s).                             cueing.
               If a motion system
                is installed,
                although it is
                not required, it
                must be measured
                by latency tests
                or transport
                delay tests and
                may not exceed
                100 milliseconds.
                Instrument
                response may not
                occur prior to
                motion onset.
               A subjective test
                is required.
------------------------------------------------------------------------
6. Visual System
------------------------------------------------------------------------
6.a..........  The FTD may have a
                visual system, if
                desired, although
                it is not
                required. If a
                visual system is
                installed, it
                must meet the
                following
                criteria:.
------------------------------------------------------------------------
6.a.1........  The visual system    X    X    X   ...
                must respond to
                abrupt input at
                the pilot's
                position.
               An SOC is
                required.
               A Subjective Test
                is required.
------------------------------------------------------------------------
6.a.2........  The visual system    X    X    X   ...
                must be at least
                a single channel,
                non-collimated
                display.
               An SOC is
                required.
               A Subjective Test
                is required.
------------------------------------------------------------------------
6.a.3........  The visual system    X    X    X   ...
                must provide at
                least a field of
                view of 18[deg]
                vertical/24[deg]
                horizontal for
                the pilot flying.
               An SOC is
                required.
------------------------------------------------------------------------

6.a.4........  The visual system    X    X    X   ...
                must provide for
                a maximum
                parallax of
                10[deg] per pilot.
               An SOC is
                required.
------------------------------------------------------------------------
6.a.5........  The visual scene     X    X    X   ...
                content may not
                be distracting.
               An SOC is
                required.
               A Subjective Test
                is required.
------------------------------------------------------------------------
6.a.6........  The minimum          X    X    X   ...
                distance from the
                pilot's eye
                position to the
                surface of a
                direct view
                display may not
                be less than the
                distance to any
                front panel
                instrument.
               An SOC is
                required.
------------------------------------------------------------------------
6.a.7........  The visual system    X    X    X   ...
                must provide for
                a minimum
                resolution of 5
                arc-minutes for
                both computed and
                displayed pixel
                size.
               An SOC is
                required.
------------------------------------------------------------------------
6.b..........  If a visual system   X    X    X   ...
                is installed and
                additional
                training,
                testing, or
                checking credits
                are being sought
                on the basis of
                having a visual
                system, a visual
                system meeting
                the standards set
                out for at least
                a Level A FFS
                (see Appendix A
                of this part)
                will be required.
                A ``direct-
                view,'' non-
                collimated visual
                system (with the
                other
                requirements for
                a Level A visual
                system met) may
                be considered
                satisfactory for
                those
                installations
                where the visual
                system design
                ``eye point'' is
                appropriately
                adjusted for each
                pilot's position
                such that the
                parallax error is
                at or less than
                10[deg]
                simultaneously
                for each pilot.
               An SOC is
                required.
               An objective test
                is required.
------------------------------------------------------------------------
6.c..........  The FTD must        ...  ...  ...   X   Optimization of
                provide a                               the vertical
                continuous visual                       field of view
                field of view of                        may be
                at least 146[deg]                       considered with
                horizontally and                        respect to the
                36[deg]                                 specific
                vertically for                          helicopter
                both pilot seats,                       flight deck cut-
                simultaneously.                         off angle. When
                The minimum                             considering the
                horizontal field                        installation/use
                of view coverage                        of augmented
                must be plus and                        fields of view,
                minus one-half                          as described
                (\1/2\) of the                          here, it will be
                minimum                                 the
                continuous field                        responsibility
                of view                                 of the sponsor
                requirement,                            to meet with the
                centered on the                         NSPM to
                zero degree                             determine the
                azimuth line                            training,
                relative to the                         testing,
                aircraft                                checking, or
                fuselage.                               experience tasks
                Additional                              for which the
                horizontal field                        augmented field
                of view                                 of view
                capability may be                       capability may
                added at the                            be critical to
                sponsor's                               that approval.
                discretion
                provided the
                minimum field of
                view is retained.
                Capability for a
                field of view in
                excess of these
                minima is not
                required for
                qualification at
                Level 7. However,
                where specific
                tasks require
                extended fields
                of view beyond
                the 146[deg] by
                36[deg] (e.g., to
                accommodate the
                use of ``chin
                windows'' where
                the accommodation
                is either
                integral with or
                separate from the
                primary visual
                system display),
                then such
                extended fields
                of view must be
                provided.
               An SOC is required
                and must explain
                the geometry of
                the installation.
               An objective test
                is required.
------------------------------------------------------------------------
7. Sound System
------------------------------------------------------------------------
7.a..........  The FTD must        ...  ...   X    X
                simulate
                significant
                flight deck
                sounds resulting
                from pilot
                actions that
                correspond to
                those heard in
                the helicopter.
               A subjective test
                is required.
------------------------------------------------------------------------
Note: An ``A'' in the table indicates that the system, task, or
  procedure may be examined if the appropriate helicopter system or
  control is simulated in the FTD and is working properly.

                  Table D1B.--Minimum FTD Requirements
------------------------------------------------------------------------
               <<>>                 <<>>
------------------------------------------------------------------------
                  Subjective          FTD level
               requirements The --------------------
               FTD must be able
                to perform the
   Number      tasks associated                             Notes
              with the level of   4    5    6    7
                qualification
                   sought.
------------------------------------------------------------------------
1. Preflight Procedures
------------------------------------------------------------------------
1.a.........  Preflight           A    A    X    X
               Inspection
               (Flight Deck
               Only) switches,
               indicators,
               systems, and
               equipment.
------------------------------------------------------------------------
1.b.........  APU/Engine start
               and run-up.
------------------------------------------------------------------------
1.b.1.......  Normal start        A    A    X    X
               procedures.
------------------------------------------------------------------------
1.b.2.......  Alternate start     A    A    X    X
               procedures.
------------------------------------------------------------------------
1.b.3.......  Abnormal starts     A    A    X    X
               and shutdowns
               (hot start, hung
               start).
------------------------------------------------------------------------
1.c.........  Taxiing--Ground..  ...  ...  ...   X
------------------------------------------------------------------------
1.d.........  Taxiing--Hover...  ...  ...  ...   X
------------------------------------------------------------------------
1.e.........  Pre-takeoff         A    A    X    X
               Checks.
------------------------------------------------------------------------
2. Takeoff and Departure Phase
------------------------------------------------------------------------
2.a.........  Normal takeoff...
------------------------------------------------------------------------
2.a.1.......  From ground......  ...  ...  ...   X
------------------------------------------------------------------------
2.a.2.......  From hover.......  ...  ...  ...   X
------------------------------------------------------------------------
2.a.3.......  Running..........  ...  ...  ...   X
------------------------------------------------------------------------
2.b.........  Instrument.......  ...  ...   X    X
------------------------------------------------------------------------
2.c.........  Powerplant         ...  ...   X    X
               Failure During
               Takeoff.
------------------------------------------------------------------------
2.d.........  Rejected Takeoff.  ...  ...  ...   X
------------------------------------------------------------------------
2.e.........  Instrument         ...  ...   X    X
               Departure.
------------------------------------------------------------------------
3. Climb
------------------------------------------------------------------------
3.a.........  Normal...........  ...  ...   X    X
------------------------------------------------------------------------
3.b.........  Obstacle           ...  ...  ...   X
               clearance.
------------------------------------------------------------------------
3.c.........  Vertical.........  ...  ...   X    X
------------------------------------------------------------------------
3.d.........  One engine         ...  ...   X    X
               inoperative.
------------------------------------------------------------------------
4. In-flight Maneuvers
------------------------------------------------------------------------
4.a.........  Turns (timed,      ...   X    X    X
               normal, steep).
------------------------------------------------------------------------
4.b.........  Powerplant         ...  ...   X    X
               Failure--Multien
               gine Helicopters.
------------------------------------------------------------------------
4.c.........  Powerplant         ...  ...   X    X
               Failure--Single-
               Engine
               Helicopters.
------------------------------------------------------------------------
4.d.........  Recovery From      ...  ...  ...   X
               Unusual
               Attitudes.
------------------------------------------------------------------------
4.e.........  Settling with      ...  ...  ...   X
               Power.
------------------------------------------------------------------------
5. Instrument Procedures
------------------------------------------------------------------------
5.a.........  Instrument         ...  ...   X    X
               Arrival.
------------------------------------------------------------------------
5.b.........  Holding..........  ...  ...   X    X
------------------------------------------------------------------------
5.c.........  Precision
               Instrument
               Approach
------------------------------------------------------------------------
5.c.1.......  Normal--All        ...   X    X    X
               engines
               operating.
------------------------------------------------------------------------
5.c.2.......  Manually           ...  ...   X    X
               controlled--One
               or more engines
               inoperative.
------------------------------------------------------------------------

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

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

                  Table D1C.--Table of FTD System Tasks
------------------------------------------------------------------------
                   <<>>                         <<
------------------------------------------------------------ Information
                  Subjective              FTD level               >>
               requirements  In ----------------------------------------
                 order to be
               qualifed at the
              FTD qualification
               level indicated,
   Number      the FTD must be
               able to perform           4          5  6  7     Notes
                 at least the
               tasks associate
               with that level
              of qualification.
------------------------------------------------------------------------
1. Instructor Operating Station (IOS)
------------------------------------------------------------------------
1.a.........  Power switch(es).  A................  X  X  X
------------------------------------------------------------------------
1.b.........  Helicopter         A................  A  X  X  e.g., GW,
               conditions.                                   CG, Fuel
                                                             loading,
                                                             Systems,
                                                             Ground.
                                                              Crew.
------------------------------------------------------------------------
1.c.........  Airports /         A................  X  X  X   e.g.,
               Heliports /                                   Selection,
               Helicopter                                    Surface,
               Landing Areas.                                Presets,
                                                             Lighting
                                                             controls.
------------------------------------------------------------------------
1.d.........  Environmental      A................  X  X  X  e.g., Temp
               controls.                                     and Wind.
------------------------------------------------------------------------
1.e.........  Helicopter system  A................  A  X  X
               malfunctions
               (Insertion /
               deletion).
------------------------------------------------------------------------
1.f.........  Locks, Freezes,    A................  X  X  X
               and
               Repositioning
               (as appropriate).
------------------------------------------------------------------------
1.g.........  Sound Controls.    .................  X  X  X
               (On / off /
               adjustment).
------------------------------------------------------------------------
1.fh........  Motion / Control   .................  A  X  X
               Loading System,
               as appropriate.
               On / off /
               emergency stop.
------------------------------------------------------------------------
2. Observer Seats / Stations
------------------------------------------------------------------------
2.a.........  Position /         A................  X  X  X
               Adjustment /
               Positive
               restraint system.
------------------------------------------------------------------------

Attachment 2 to Appendix D to Part 60--

Flight Training Device (FTD) Objective Tests

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

Begin Information

1. Discussion

    a. If relevant winds are present in the objective data, the wind
vector (magnitude and direction) should be noted as part of the data
presentation, expressed in conventional terminology, and related to
the runway being used for the test.
    b. The format for numbering the objective tests in Appendix C,
Attachment 2, Table C2A, and the objective tests in Appendix D,
Attachment 2, Table D2A, is identical. However, each test required
for FFSs is not necessarily required for FTDs, and each test
required for FTDs is not necessarily required for FFSs. 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. A Level 4 FTD does not require objective tests and is not
addressed in the following table.

End Information

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

Begin QPS Requirements

2. Test Requirements

    a. The ground and flight tests required for qualification are
listed in Table D2A Objective Evaluation Tests. Computer generated
FTD test results must be provided for each test except where an
alternate test is specifically authorized by the NSPM. If a flight
condition or operating condition is required for the test but does
not apply to the helicopter being simulated or to the qualification
level sought, it may be disregarded (e.g., engine out climb
capability for a single-engine helicopter). Each test result is
compared against the validation data described in Sec.  60.13, and
in Appendix B. The results must be produced on an appropriate
recording device acceptable to the NSPM and

[[Continued on page 59850]]

]

[[pp. 59850-59899]] Flight Simulation Training Device Initial and Continuing
Qualification and Use

[[Continued from page 59849]]

must include FTD 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 D2A. All results must be labeled using the
tolerances and units given.
    b. Table D2A in this attachment sets out the test results
required, including the parameters, tolerances, and flight
conditions for FTD 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 FTD 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 D2A,
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 FTD 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 section. 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 FTD to helicopter data throughout a time
history, differences must be justified by providing a comparison of
other related variables for the condition being assessed.
    e. The FTD may not be programmed so that the mathematical
modeling is correct only at the validation test points. Unless noted
otherwise, tests must represent helicopter performance and handling
qualities at operating weights and centers of gravity (CG) typical
of normal operation. If a test is supported by aircraft data at one
extreme weight or CG, another test supported by aircraft data at
mid-conditions or as close as possible to the other extreme is
necessary. Certain tests that are relevant only at one extreme CG or
weight condition need not be repeated at the other extreme. The
results of the tests for Level 6 are expected to be indicative of
the device's performance and handling qualities throughout all of
the following:
    (1) The helicopter weight and CG envelope.
    (2) The operational envelope.
    (3) Varying atmospheric ambient and environmental conditions--
including the extremes authorized for the respective helicopter or
set of helicopters.
    f. When comparing the parameters listed to those of the
helicopter, sufficient data must also be provided to verify the
correct flight condition and helicopter configuration changes. For
example, to show that control force is within the parameters for a
static stability test, data to show the correct airspeed, power,
thrust or torque, helicopter configuration, altitude, and other
appropriate datum identification parameters must also be given. If
comparing short period dynamics, normal acceleration may be used to
establish a match to the helicopter, but airspeed, altitude, control
input, helicopter configuration, and other appropriate data must
also be given. If comparing landing gear change dynamics, pitch,
airspeed, and altitude may be used to establish a match to the
helicopter, 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
FTD will be set up and operated for each test. Each FTD subsystem
may be tested independently, but overall integrated testing of the
FTD must be accomplished to assure that the total FTD system meets
the prescribed standards. A manual test procedure with explicit and
detailed steps for completing each test must also be provided.
    h. In those cases where the objective test results authorize a
``snapshot test'' or a ``series of snapshot test'' results in lieu
of a time-history result, the sponsor or other data provider must
ensure that a steady state condition exists at the instant of time
captured by the ``snapshot.'' The steady state condition must exist
from 4 seconds prior to, through 1 second following, the instant of
time captured by the snap shot.
    i. For previously qualified FTDs, the tests and tolerances of
this attachment may be used in subsequent continuing qualification
evaluations for any given test if the sponsor has submitted a
proposed MQTG revision to the NSPM and has received NSPM approval.
    j. Tests of handling qualities must include validation of
augmentation devices. FTDs for highly augmented helicopters will be
validated both in the unaugmented configuration (or failure state
with the maximum permitted degradation in handling qualities) and
the augmented configuration. Where various levels of handling
qualities result from failure states, validation of the effect of
the failure is necessary. For those performance and static handling
qualities tests where the primary concern is control position in the
unaugmented configuration, unaugmented data are not required if the
design of the system precludes any effect on control position. In
those instances where the unaugmented helicopter response is
divergent and non-repeatable, it may not be feasible to meet the
specified tolerances. Alternative requirements for testing will be
mutually agreed upon by the sponsor and the NSPM on a case-by-case
basis.
    k. Some tests will not be required for helicopters using
helicopter hardware in the FTD flight deck (e.g., ``helicopter
modular controller''). These exceptions are noted in Section 2
``Handling Qualities'' in Table D2A of this attachment. However, in
these cases, the sponsor must provide a statement that the
helicopter hardware meets the appropriate manufacturer's
specifications and the sponsor must have supporting information to
that fact available for NSPM review.
    l. For objective test purposes, ``Near maximum'' gross weight is
a weight chosen by the sponsor or data provider that is not less
than the basic operating weight (BOW) of the helicopter being
simulated plus 80% of the difference between the maximum
certificated gross weight (either takeoff weight or landing weight,
as appropriate for the test) and the BOW. ``Light'' gross weight is
a weight chosen by the sponsor or data provider that is not more
than 120% of the BOW of the helicopter being simulated or as limited
by the minimum practical operating weight of the test helicopter.
``Medium'' gross weight is a weight chosen by the sponsor or data
provider that is within 10 percent of the average of the numerical
values of the BOW and the maximum certificated gross weight. 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.

End QPS Requirements

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

Begin Information

    Refer to Advisory Circular 120-27, ``Aircraft Weight and
Balance;'' and FAA-H-8083-1, ``Aircraft Weight and Balance
Handbook'' for more information.

End Information

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

                                                Table D2A.--Flight Training Device (FTD) Objective Tests
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                       <<>>
------------------------------------------------------------------------------------------------------------------------------------
                      Test                                                                                FTD level         <>
------------------------------------------------      Tolerances       Flight conditions       Test details    ---------------------        Notes
          Number                   Title                                                                          5      6      7
--------------------------------------------------------------------------------------------------------------------------------------------------------
1. Performance
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.a. Engine Assessment
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.a.1....................  Start Operations....
--------------------------------------------------------------------------------------------------------------------------------------------------------

1.a.1.a..................  Engine start and      Light Off Time--     Ground with the      Record each engine             X      X
                            acceleration          10% or   Rotor Brake Used     start from the
                            (transient).          1 sec.   and Not Used.        initiation of the
                                                  Torque--< plus-                            start sequence to
                                                  minus>5% Rotor                            steady state idle
                                                  Speed--< plus-                             and from steady
                                                  minus>3% Fuel                             state idle to
                                                  Flow--< plus-                              operating RPM.
                                                  minus>10% Gas
                                                  Generator Speed--
                                                  5%
                                                  Power Turbine
                                                  Speed--< plus-
                                                  minus>5% Gas
                                                  Turbine Temp.--
                                                  30
                                                  [deg]C.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.a.1.b..................  Steady State Idle     Torque--< plus-       Ground.............  Record both steady      X      X      X
                            and Operating RPM     minus>3% Rotor                            state idle and
                            conditions.           Speed--< plus-                             operating RPM
                                                  minus>1.5% Fuel                           conditions. May be
                                                  Flow--< plus-                              a series of
                                                  minus>5% Gas                              snapshot tests.
                                                  Generator Speed--
                                                  2%
                                                  Power Turbine
                                                  Speed--< plus-
                                                  minus>2% Turbine
                                                  Gas Temp.--< plus-
                                                  minus>20 [deg]C.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.a.2....................  Power Turbine Speed   10% of   Ground.............  Record engine                  X      X
                            Trim.                 total change of                           response to trim
                                                  power turbine                             system actuation
                                                  speed.                                    in both directions.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.a.2.a..................  Engine and Rotor      Torque--< plus-       Climb Descent......  Record results                 X      X
                            Speed Governing.      minus>5% Rotor                            using a step input
                                                  Speed--< plus-                             to the collective.
                                                  minus>1.5%.                               May be conducted
                                                                                concurrently with
                                                                                climb and descent
                                                                                performance tests.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.a.3....................  Reserved............
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.b. Reserved
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.c. Takeoff
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.c.1....................  All Engines.........  Airspeed--< plus-     Ground/Takeoff and   Record results of                     X
                                                  minus>3 kt,          Initial Segment of   takeoff flight
                                                  Altitude--< plus-     Climb.               path (running
                                                  minus>20 ft (6.1                          takeoff and
                                                  m) Torque--< plus-                         takeoff from a
                                                  minus>3%, Rotor                           hover). The
                                                  Speed--< plus-                             criteria apply
                                                  minus>1.5%,                               only to those
                                                  Vertical Velocity--                       segments at
                                                  100                           airspeeds above
                                                  fpm (0.50 m/sec)                          effective
                                                  or 10%, Pitch                             translational
                                                  Attitude--< plus-                          lift. Results must
                                                  minus>1.5[deg],                           be recorded from
                                                  Bank Attitude--                           the initiation of
                                                  < plus-                                    the takeoff to at
                                                  minus>2[deg],                             least 200 ft (61
                                                  Heading--< plus-                           m) AGL.
                                                  minus>2[deg],
                                                  Longitudinal
                                                  Control Position--
                                                  10%,
                                                  Lateral Control
                                                  Position--< plus-
                                                  minus>10%,
                                                  Directional
                                                  Control Position--
                                                  10%,
                                                  Collective Control
                                                  Position--< plus-
                                                  minus>10%.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.c.2. through 1.c.3.      Reserved............
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.d. Hover
--------------------------------------------------------------------------------------------------------------------------------------------------------

                           Performance.........  Torque--< plus-       In Ground Effect     Record results for                    X
                                                  minus>3%, Pitch      (IGE); and Out of    light and heavy
                                                  Attitude--< plus-     Ground Effect        gross weights. May
                                                  minus>1.5[deg],      (OGE).               be a series of
                                                  Bank Attitude--                           snapshot tests.
                                                  < plus-
                                                  minus>1.5[deg],
                                                  Longitudinal
                                                  Control Position--
                                                  5%,
                                                  Lateral Control
                                                  Position--< plus-
                                                  minus>5%,
                                                  Directional
                                                  Control Position--
                                                  5%,
                                                  Collective Control
                                                  Position--< plus-
                                                  minus>5%.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.e. Vertical Climb
--------------------------------------------------------------------------------------------------------------------------------------------------------
                           Performance.........  Vertical Velocity--  From OGE Hover.....  Record results for                    X
                                                  100                           light and heavy
                                                  fpm (0.50 m/sec)                          gross weights. May
                                                  or < plus-                                 be a series of
                                                  minus>10%,                                snapshot tests.
                                                  Directional
                                                  Control Position--
                                                  5%,
                                                  Collective Control
                                                  Position--< plus-
                                                  minus>5%.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.f. Level Flight
--------------------------------------------------------------------------------------------------------------------------------------------------------
                           Performance and       Torque--< plus-       Cruise               Record results for      X      X      X   This test validates
                            Trimmed Flight        minus>3% Pitch       (Augmentation On     two gross weight                          performance at
                            Control Positions.    Attitude--< plus-     and Off).            and CG                                    speeds above
                                                  minus>1.5[deg]                            combinations with                         maximum endurance
                                                  Sideslip Angle--                          varying trim                              airspeed.
                                                  2[deg]                        speeds throughout
                                                  Longitudinal                              the airspeed
                                                  Control Position--                        envelope. May be a
                                                  5%                            series of snapshot
                                                  Lateral Control                           tests.
                                                  Position--< plus-
                                                  minus>5%
                                                  Directional
                                                  Control Position--
                                                  5%
                                                  Collective Control
                                                  Position--< plus-
                                                  minus>5%.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.g. Climb
--------------------------------------------------------------------------------------------------------------------------------------------------------
                           Performance and       Vertical Velocity--  All engines          Record results for      X      X      X
                            Trimmed Flight        100      operating. One       two gross weight
                            Control Positions.    fpm (61m/sec) or     engine               and CG
                                                  10%      inoperative.         combinations. The
                                                  Pitch Attitude--     Augmentation         data presented
                                                  < plus-               System(s) On and     must be for normal
                                                  minus>1.5[deg]       Off.                 climb power
                                                  Sideslip Angle--                          conditions. May be
                                                  2[deg]                        a series of
                                                  Longitudinal                              snapshot tests.
                                                  Control Position--
                                                  5%
                                                  Lateral Control
                                                  Position--< plus-
                                                  minus>5%
                                                  Directional
                                                  Control Position--
                                                  5%
                                                  Collective Control
                                                  Position--< plus-
                                                  minus>5%.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.h. Descent
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.h.1....................  Descent Performance   Torque--< plus-       At or near 1,000     Record results for      X      X      X
                            and Trimmed Flight    minus>3% Pitch       fpm (5 m/sec) rate   two gross weight
                            Control Positions.    Attitude--< plus-     of descent (RoD)     and CG
                                                  minus>1.5[deg]       at normal approach   combinations. May
                                                  Sideslip Angle--     speed.               be a series of
                                                  2[deg]   Augmentation         snapshot tests.
                                                  Longitudinal         System(s) On and
                                                  Control Position--   Off.
                                                  5%
                                                  Lateral Control
                                                  Position--< plus-
                                                  minus>5%
                                                  Directional
                                                  Control Position--
                                                  5%
                                                  Collective Control
                                                  Position--< plus-
                                                  minus>5%.
--------------------------------------------------------------------------------------------------------------------------------------------------------

1.h.2....................  Autorotation          Pitch Attitude--     Steady descents.     Record results for      X      X      X
                            Performance and       < plus-               Augmentation         two gross weight
                            Trimmed Flight        minus>1.5[deg]       System(s) On and     conditions. Data
                            Control Positions.    Sideslip Angle--     Off.                 must be recorded
                                                  2[deg]                        for normal
                                                  Longitudinal                              operating RPM.
                                                  Control Position--                        (Rotor speed
                                                  5%                            tolerance applies
                                                  Lateral Control                           only if collective
                                                  Position--< plus-                          control position
                                                  minus>5%                                  is full down.)
                                                  Directional                               Data must be
                                                  Control Position--                        recorded for
                                                  5%                            speeds from 50
                                                  Collective Control                        kts., < plus-
                                                  Position--5 kts
                                                  minus>5%.                                 through at least
                                                                                maximum glide
                                                                                distance airspeed.
                                                                                May be a series of
                                                                                snapshot tests.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.i. Autorotation
--------------------------------------------------------------------------------------------------------------------------------------------------------
                           Entry...............  Rotor Speed--< plus-  Cruise; or Climb...  Record results of a            X      X
                                                  minus>3% Pitch                            rapid throttle
                                                  Attitude < plus-                           reduction to idle.
                                                  minus>2[deg] Roll                         If accomplished in
                                                  Attitude--< plus-                          cruise, results
                                                  minus>3[deg] Yaw                          must be for the
                                                  Attitude--< plus-                          maximum range
                                                  minus>5[deg]                              airspeed. If
                                                  Airspeed--< plus-                          accomplished in
                                                  minus>5 kts.                              climb, results
                                                  Vertical Velocity--                       must be for the
                                                  200                           maximum rate of
                                                  fpm (1.00 m/sec)                          climb airspeed at
                                                  or 10%.                                   or near maximum
                                                                                continuous power.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.j. Landing
--------------------------------------------------------------------------------------------------------------------------------------------------------

1.j.1....................  All Engines.........  Airspeed--< plus-     Approach...........  Record results of                     X
                                                  minus>3 kts.,                             the approach and
                                                  Altitude--< plus-                          landing profile
                                                  minus>20 ft.(6.1                          (running landing
                                                  m) Torque--< plus-                         or approach to a
                                                  minus>3%, Rotor                           hover). The
                                                  Speed--< plus-                             criteria apply
                                                  minus>1.5%, Pitch                         only to those
                                                  Attitude--< plus-                          segments at
                                                  minus>1.5[deg],                           airspeeds above
                                                  Bank Attitude--                           effective
                                                  < plus-                                    translational
                                                  minus>1.5[deg],                           lift. Record the
                                                  Heading--< plus-                           results from 200
                                                  minus>2[deg],                             ft. AGL (61 m) to
                                                  Longitudinal                              the landing or to
                                                  Control Position--                        where the hover is
                                                  10%,                          established prior
                                                  Lateral Control                           to landing.
                                                  Position--< plus-
                                                  minus>10%,
                                                  Directional
                                                  Control Position--
                                                  10%,
                                                  Collective Control
                                                  Position--< plus-
                                                  minus>10%.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.j.2. through 1.j.3.      Reserved............
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.j.4....................  Autorotational        Torque--< plus-       Landing............  Record the results                    X
                            Landing.              minus>3%, Rotor                           of an
                                                  Speed--< plus-                             autorotational
                                                  minus>3%, Vertical                        deceleration and
                                                  Velocity--< plus-                          landing from a
                                                  minus>100 fpm                             stabilized
                                                  (0.50 m/sec) or                           autorotational
                                                  10%, Pitch                                descent, to touch
                                                  Attitude--< plus-                          down.
                                                  minus>2[deg], Bank
                                                  Attitude--< plus-
                                                  minus>2[deg],
                                                  Heading--< plus-
                                                  minus>5[deg],
                                                  Longitudinal
                                                  Control Position--
                                                  10%,
                                                  Lateral Control
                                                  Position--< plus-
                                                  minus>10%,
                                                  Directional
                                                  Control Position--
                                                  10%,
                                                  Collective Control
                                                  Position--< plus-
                                                  minus>10%.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2. Handling Qualities
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2.a......................  Control System        Contact the NSPM
                            Mechanical            for clarification
                            Characteristics.      of any issue
                                                  regarding
                                                  helicopters with
                                                  reversible
                                                  controls.
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2.a.1....................  Cyclic..............  Breakout--< plus-     Ground; Static       Record results for      X      X      X
                                                  minus>0.25 lbs.      conditions. Trim     an uninterrupted
                                                  (0.112 daN) or       On and Off.          control sweep to
                                                  25%. Force--< plus-   Friction Off.        the stops. (This
                                                  minus>1.0 lb.        Augmentation On      test does not
                                                  (0.224 daN) or 10%.  and off.             apply if aircraft
                                                                                hardware modular
                                                                                controllers are
                                                                                used.)
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2.a.2....................  Collective and        Breakout--< plus-     Ground; Static       Record results for      X      X      X
                            Pedals.               minus>0.5 lb.        conditions. Trim     an uninterrupted
                                                  (0.224 daN) or       On and Off.          control sweep to
                                                  25%. Force--< plus-   Friction Off         the stops.
                                                  minus>1.0 lb.        Augmentation On
                                                  (0.224 daN) or 10%.  and Off.
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2.a.3....................  Brake Pedal Force     5 lbs.   Ground; Static                               X      X      X
                            vs. Position.         (2.224 daN) or 10%.  conditions.
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2.a.4....................  Trim System Rate      Rate--< plus-         Ground; Static       The tolerance           X      X      X
                            (all applicable       minus>10%.           conditions. Trim     applies to the
                            systems).                                  On Friction Off.     recorded value of
                                                                                the trim rate.
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2.a.5....................  Control Dynamics      10% of   Hover/Cruise Trim    Results must be                X      X   Control Dynamics
                            (all axes).           time for first       On Friction Off.     recorded for a                            for irreversible
                                                  zero crossing and                         normal control                            control systems
                                                  10                            displacement in                           may be evaluated
                                                  (N+1)% of period                          both directions in                        in a ground/static
                                                  thereafter. < plus-                        each axis, using                          condition. Refer
                                                  minus>10% of                              25% to 50% of full                        to paragraph 3 of
                                                  amplitude of first                        throw.                                    this attachment
                                                  overshoot. < plus-                                                                   for additional
                                                  minus>20% of                                                                        information. ``N''
                                                  amplitude of 2nd                                                                    is the sequential
                                                  and subsequent                                                                      period of a full
                                                  overshoots greater                                                                  cycle of
                                                  than 5% of initial                                                                  oscillation.
                                                  displacement.
                                                  1
                                                  overshoot.
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2.a.6....................  Freeplay............  0.10 in  Ground; Static       Record and compare      X      X      X
                                                                       conditions.          results for all
                                                                                controls.
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2.b. Low Airspeed Handling Qualities
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2.b.1....................  Trimmed Flight        Torque < plus-        Translational        Record results for                    X
                            Control Positions.    minus>3% Pitch       Flight IGE--         several airspeed
                                                  Attitude < plus-      Sideward,            increments to the
                                                  minus>1.5[deg]       rearward, and        translational
                                                  Bank Attitude        forward flight.      airspeed limits
                                                  2[deg]   Augmentation On      and for 45 kts.
                                                  Longitudinal         and Off.             forward airspeed.
                                                  Control Position                          May be a series of
                                                  5%                            snapshot tests.
                                                  Lateral Control
                                                  Position < plus-
                                                  minus>5%
                                                  Directional
                                                  Control Position
                                                  5%
                                                  Collective Control
                                                  Position < plus-
                                                  minus>5%.
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2.b.2....................  Critical Azimuth....  Torque < plus-        Stationary Hover.    Record results for                    X
                                                  minus>3% Pitch       Augmentation On      three relative
                                                  Attitude < plus-      and Off.             wind directions
                                                  minus>1.5[deg],                           (including the
                                                  Bank Attitude                             most critical
                                                  < plus-                                    case) in the
                                                  minus>2[deg],                             critical quadrant.
                                                  Longitudinal                              May be a series of
                                                  Control Position                          snapshot tests.
                                                  5%,
                                                  Lateral Control
                                                  Position < plus-
                                                  minus>5%,
                                                  Directional
                                                  Control Position
                                                  5%,
                                                  Collective Control
                                                  Position < plus-
                                                  minus>5%.
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2.b.3....................  Control Response....
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2.b.3.a..................  Longitudinal........  Pitch Rate--< plus-   Hover. Augmentation  Record results for                    X   This is a ``short
                                                  minus>10% or 2[deg]/sec.                         input. The Off-
                                                  Pitch Attitude                            axis response must
                                                  Change--< plus-                            show correct trend
                                                  minus>10% or                              for unaugmented
                                                  1.5[deg].                                 cases. This test
                                                                                must be conducted
                                                                                in a hover, in
                                                                                ground effect,
                                                                                without entering
                                                                                translational
                                                                                flight.
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2.b.3.c..................  Directional.........  Yaw Rate--< plus-     Hover Augmentation   Record results for                    X   This is a ``short
                                                  minus>10% or 2[deg]/sec.                         input. The Off-
                                                  Heading Change--                          axis response must
                                                  10% or                        show correct trend
                                                  2[deg].                       for unaugmented
                                                                                cases. This test
                                                                                must be conducted
                                                                                in a hover, in
                                                                                ground effect,
                                                                                without entering
                                                                                translational
                                                                                flight.
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2.b.3.d..................  Vertical............  Normal Acceleration  Hover..............  Record results for                    X
                                                  0.1g.                         a step control
                                                                                input. The Off-
                                                                                axis response must
                                                                                show correct trend
                                                                                for unaugmented
                                                                                cases.
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2.c. Longitudinal Handling Qualities
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2.c.1....................  Control Response....  Pitch Rate--< plus-   Cruise Augmentation  Results must be         X      X      X
                                                  minus>10% or 2[deg]/sec.                         cruise airspeeds
                                                  Pitch Attitude                            to include minimum
                                                  Change--< plus-                            power required
                                                  minus>10% or 1.5[deg].                           for a step control
                                                                                input. The Off-
                                                                                axis response must
                                                                                show correct trend
                                                                                for unaugmented
                                                                                cases.
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2.c.2....................  Static Stability....  Longitudinal         Cruise or Climb.     Record results for      X      X      X
                                                  Control Position:    Autorotation.        a minimum of two
                                                  10% of   Augmentation On      speeds on each
                                                  change from trim     and Off.             side of the trim
                                                  or < plus-                                 speed. May be a
                                                  minus>0.25 in.                            series of snapshot
                                                  (6.3 mm) or                               tests.
                                                  Longitudinal
                                                  Control Force:
                                                  0.5
                                                  lb. (0.223 daN) or
                                                  10%.
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2.c.3....................  Dynamic Stability...
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2.c.3.a..................  Long Term Response..  10% of   Cruise Augmentation  Record results for      X      X      X   The response for
                                                  calculated period.   On and Off.          three full cycles                         certain
                                                  10% of                        (6 overshoots                             helicopters may be
                                                  time to \1/2\ or                          after input                               unrepeatable
                                                  double amplitude,                         completed) or that                        throughout the
                                                  or < plus-                                 sufficient to                             stated time.
                                                  minus>0.02 of                             determine time to
                                                  damping ratio. For                        \1/2\ or double
                                                  non-periodic                              amplitude,
                                                  responses, the                            whichever is less.
                                                  time history must                         For non-periodic
                                                  be matched within                         responses, the
                                                  10%                           test may be
                                                  pitch; and < plus-                         terminated prior
                                                  minus>10% airspeed                        to 20 sec if the
                                                  over a 20 sec                             test pilot
                                                  period following                          determines that
                                                  release of the                            the results are
                                                  controls.                                 becoming
                                                                                uncontrollably
                                                                                divergent.
                                                                                Displace the
                                                                                cyclic for one
                                                                                second or less to
                                                                                excite the test.
                                                                                The result will be
                                                                                either convergent
                                                                                or divergent and
                                                                                must be recorded.
                                                                                If this method
                                                                                fails to excite
                                                                                the test, displace
                                                                                the cyclic to the
                                                                                predetermined
                                                                                maximum desired
                                                                                pitch attitude and
                                                                                return to the
                                                                                original position.
                                                                                If this method is
                                                                                used, record the
                                                                                results.
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2.c.3.b..................  Short Term Response.  < plus-               Cruise or Climb.     Record results for             X      X   A control doublet
                                                  minus>1.5[deg]       Augmentation On      at least two                              inserted at the
                                                  Pitch or < plus-      and Off.             airspeeds.                                natural frequency
                                                  minus>2[deg]/sec.                                                                   of the aircraft
                                                  Pitch Rate. < plus-                                                                  normally excites
                                                  minus>0.1 g Normal                                                                  this test.
                                                  Acceleration.
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2.c.4....................  Maneuvering           Longitudinal         Cruise or Climb.     Record results for             X      X
                            Stability.            Control Position--   Augmentation On      at least two
                                                  10% of   and Off.             airspeeds at
                                                  change from trim                          30[deg]-45[deg]
                                                  or < plus-                                 bank angle. The
                                                  minus>0.25 in.                            force may be shown
                                                  (6.3 mm) or                               as a cross plot
                                                  Longitudinal                              for irreversible
                                                  Control Forces--                          systems. May be a
                                                  0.5                           series of snapshot
                                                  lb. (0.223 daN) or                        tests.
                                                  10%.
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2.d. Lateral and Directional Handling Qualities
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2.d.1....................  Control Response....
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2.d.1.a..................  Lateral.............  Roll Rate--< plus-    Cruise Augmentation  Record results for      X      X      X
                                                  minus>10% or 3[deg]/sec.                         airspeeds,
                                                  Roll Attitude                             including the
                                                  Change--< plus-                            speed at or near
                                                  minus>10% or 3[deg].                             required airspeed.
                                                                                Record results for
                                                                                a step control
                                                                                input. The Off-
                                                                                axis response must
                                                                                show correct trend
                                                                                for unaugmented
                                                                                cases.
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2.d.1.b..................  Directional.........  Yaw Rate--< plus-     Cruise Augmentation  Record data for at      X      X      X
                                                  minus>10% or 2[deg]/sec.                         Airspeeds,
                                                  Yaw Attitude                              including the
                                                  Change--< plus-                            speed at or near
                                                  minus>10% or 2[deg].                             required airspeed.
                                                                                Record results for
                                                                                a step control
                                                                                input. The Off-
                                                                                axis response must
                                                                                show correct trend
                                                                                for unaugmented
                                                                                cases.
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2.d.2....................  Directional Static    Lateral Control      Cruise; or Climb     Record results for      X      X      X   This is a steady
                            Stability.            Position--< plus-     (may use Descent     at least two                              heading sideslip
                                                  minus>10% of         instead of Climb     sideslip angles on                        test.
                                                  change from trim     if desired)          either side of the
                                                  or < plus-            Augmentation On      trim point. The
                                                  minus>0.25 in.       and Off.             force may be shown
                                                  (6.3 mm) or                               as a cross plot
                                                  Lateral Control                           for irreversible
                                                  Force--< plus-                             systems. May be a
                                                  minus>0.5 lb.                             series of snapshot
                                                  (0.223 daN) or                            tests.
                                                  10%. Roll
                                                  Attitude--< plus-
                                                  minus>1.5
                                                  Directional
                                                  Control Position--
                                                  10% of
                                                  change from trim
                                                  or < plus-
                                                  minus>0.25 in.
                                                  (6.3 mm) or
                                                  Directional
                                                  Control Force--
                                                  1 lb.
                                                  (0.448 daN) or
                                                  10%. Longitudinal
                                                  Control Position--
                                                  10% of
                                                  change from trim
                                                  or < plus-
                                                  minus>0.25 in.
                                                  (6.3 mm). Vertical
                                                  Velocity--< plus-
                                                  minus>100 fpm
                                                  (0.50m/sec) or 10%.
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2.d.3....................  Dynamic Lateral and
                            Directional
                            Stability.
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2.d.3.a..................  Lateral-Directional   0.5      Cruise or Climb      Record results for      X      X      X
                            Oscillations.         sec. or < plus-       Augmentation On/     at least two
                                                  minus>10% of         Off.                 airspeeds. The
                                                  period. < plus-                            test must be
                                                  minus>10% of time                         initiated with a
                                                  to \1/2\ or double                        cyclic or a pedal
                                                  amplitude or < plus-                       doublet input.
                                                  minus>0.02 of                             Record results for
                                                  damping ratio.                            six full cycles
                                                  20% or                        (12 overshoots
                                                  1 sec                         after input
                                                  of time difference                        completed) or that
                                                  between peaks of                          sufficient to
                                                  bank and sideslip.                        determine time to
                                                                                \1/2\ or double
                                                                                amplitude,
                                                                                whichever is less.
                                                                                For non-periodic
                                                                                response, the test
                                                                                may be terminated
                                                                                prior to 20 sec if
                                                                                the test pilot
                                                                                determines that
                                                                                the results are
                                                                                becoming
                                                                                uncontrollably
                                                                                divergent.
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2.d.3.b..................  Spiral Stability....  2[deg]   Cruise or Climb.     Record the results      X      X      X
                                                  or 10%   Augmentation On      of a release from
                                                  roll angle.          and Off.             pedal only or
                                                                                cyclic only turns
                                                                                for 20 sec.
                                                                                Results must be
                                                                                recorded from
                                                                                turns in both
                                                                                directions.
                                                                                Terminate check at
                                                                                zero roll angle or
                                                                                when the test