systems, are not required to meet the general FTD requirements, the
objective test requirements, and the subjective test requirements of
Attachments 1, 2, and 3 of this appendix as long as the FTD
continues to meet the test requirements contained in the MQTG
developed under the original qualification basis.
    c. [Reserved]
    d. FTDs qualified prior to May 30, 2008, may be updated. If an
evaluation is deemed appropriate or necessary by the NSPM after such
an update, the evaluation will not require an evaluation to
standards beyond those against which the FTD was originally
qualified.

End QPS Requirements

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Begin Information

    e. Other certificate holders or persons desiring to use an FTD
may contract with FTD sponsors to use FTDs previously qualified at a
particular level for an airplane type and approved for use within an
FAA-approved flight training program. Such FTDs are not required to
undergo an additional qualification process, except as described in
Sec.  60.16.
    f. Each FTD user must obtain approval from the appropriate TPAA
to use any FTD in an FAA-approved flight training program.
    g. The intent of the requirement listed in Sec.  60.17(b), for
each FTD to have an SOQ within 6 years, is to have the availability
of that statement (including the configuration list and the
limitations to authorizations) to provide a complete picture of the
FTD inventory regulated by the FAA. The issuance of the statement
will not require any additional evaluation or require any adjustment
to the evaluation basis for the FTD.
    h. Downgrading of an FTD is a permanent change in qualification
level and will necessitate the issuance of a revised SOQ to reflect
the revised qualification level, as appropriate. If a temporary
restriction is placed on an FTD because of a missing,
malfunctioning, or inoperative component or on-going repairs, the
restriction is not a permanent change in qualification level.
Instead, the restriction is temporary and is removed when the reason
for the restriction has been resolved.
    i. The NSPM will determine the evaluation criteria for an FTD
that has been removed from active status for a prolonged period. The
criteria will be based on the number of continuing qualification
evaluations and quarterly inspections missed during the period of
inactivity. For example, if the FTD were out of service for a 1 year
period, it would be necessary to complete the entire QTG, since all
of the quarterly evaluations would have been missed. The NSPM will
also consider how the FTD was stored, whether parts were removed
from the FTD and whether the FTD was disassembled.
    j. The FTD will normally be requalified using the FAA-approved
MQTG and the criteria that was in effect prior to its removal from
qualification. However, inactive periods of 2 years or more will
require re-qualification under the standards in effect and current
at the time of requalification.

End Information

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14. Inspection, Continuing Qualification, Evaluation, and Maintenance
Requirements (Sec.  60.19).

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

Begin QPS Requirement

    a. The sponsor must conduct a minimum of four evenly spaced
inspections throughout the year. The objective test sequence and
content of each inspection in this sequence must be developed by the
sponsor and must be acceptable to the NSPM.
    b. The description of the functional preflight check must be
contained in the sponsor's QMS.
    c. Record ``functional preflight'' in the FTD discrepancy log
book or other acceptable location, including any item found to be
missing, malfunctioning, or inoperative.
    d. During the continuing qualification evaluation conducted by
the NSPM, the sponsor must also provide a person knowledgeable about
the operation of the aircraft and the operation of the FTD.

End QPS Requirements

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Begin Information

    e. The sponsor's test sequence and the content of each quarterly
inspection required

in Sec.  60.19(a)(1) should include a balance and a mix from the
objective test requirement areas listed as follows:
    (1) Performance.
    (2) Handling qualities.
    (3) Motion system (where appropriate).
    (4) Visual system (where appropriate).
    (5) Sound system (where appropriate).
    (6) Other FTD systems.
    f. If the NSP evaluator plans to accomplish specific tests
during a normal continuing qualification evaluation that requires
the use of special equipment or technicians, the sponsor will be
notified as far in advance of the evaluation as practical; but not
less than 72 hours. Examples of such tests include latencies,
control sweeps, or motion or visual system tests.
    g. The continuing qualification evaluations described in Sec.
60.19(b) will normally require 4 hours of FTD time. However,
flexibility is necessary to address abnormal situations or
situations involving aircraft with additional levels of complexity
(e.g., computer controlled aircraft). The sponsor should anticipate
that some tests may require additional time. The continuing
qualification evaluations will consist of the following:
    (1) Review of the results of the quarterly inspections conducted
by the sponsor since the last scheduled continuing qualification
evaluation.
    (2) A selection of approximately 8 to 15 objective tests from
the MQTG that provide an adequate opportunity to evaluate the
performance of the FTD. The tests chosen will be performed either
automatically or manually and should be able to be conducted within
approximately one-third (1/3) of the allotted FTD time.
    (3) A subjective evaluation of the FTD to perform a
representative sampling of the tasks set out in attachment 3 of this
appendix. This portion of the evaluation should take approximately
two-thirds (2/3) of the allotted FTD time.
    (4) An examination of the functions of the FTD may include the
motion system, visual system, sound system as applicable, instructor
operating station, and the normal functions and simulated
malfunctions of the airplane systems. This examination is normally
accomplished simultaneously with the subjective evaluation
requirements.
    h. The requirement established in Sec.  60.19(b)(4) regarding
the frequency of NSPM-conducted continuing qualification evaluations
for each FTD is typically 12 months. However, the establishment and
satisfactory implementation of an approved QMS for a sponsor will
provide a basis for adjusting the frequency of evaluations to exceed
12-month intervals.

15. Logging FTD Discrepancies (Sec.  60.20)

    No additional regulatory or informational material applies to
Sec.  60.20. Logging FTD Discrepancies.

16. Interim Qualification of FTDs for New Airplane Types or Models
(Sec.  60.21)

    No additional regulatory or informational material applies to
Sec.  60.21, Interim Qualification of FTDs for New Airplane Types or
Models.

End Information

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17. Modifications to FTDs (Sec.  60.23)

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Begin QPS Requirements

    a. The notification described in Sec. 60.23(c)(2) must include a
complete description of the planned modification, with a 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

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Begin Information

    c. FSTD Directives are considered modification of an FTD. See
Attachment 4 of this appendix for a sample index of effective FSTD
Directives.

End Information

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

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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. It is the responsibility of the instructor, check airman, or
representative of the administrator conducting training, testing, or
checking to exercise reasonable and prudent judgment to determine if
any MMI component is necessary for the satisfactory completion of a
specific maneuver, procedure, or task.
    c. If the 29th or 30th day of the 30-day period described in
60.25(b) is on a Saturday, a Sunday, or a holiday, the FAA will
extend the deadline until the next business day.
    d. 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

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

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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

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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

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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 record keeping 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

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

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Begin Information

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

End Information

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23. [Reserved]

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 device that may have an open airplane-specific
flight deck area, or an enclosed airplane-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 device that may have an open airplane-specific
flight deck area, or an enclosed airplane-specific flight deck;
generic aerodynamic programming; at least one operating system; and
control loading that is representative of the simulated airplane
only 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, nosewheel steering, trim, brakes) must be
physical controls. All other controls, switches, and knobs may be
touch sensitive activation.
    (3) Level 6. A device that has an enclosed airplane-specific
flight deck; airplane-specific aerodynamic programming; all
applicable airplane systems operating; control loading that is
representative of the simulated airplane 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.

End Information

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25. FTD 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, FTD Qualification on the Basis of a Bilateral Aviation
Safety Agreement (BASA).

End Information

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Attachment 1 to Appendix B to Part 60--General FTD REQUIREMENTS

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

Begin QPS Requirements

1. Requirements

    a. Certain requirements included in this appendix must be
supported with an SOC as defined in Appendix F, which may include
objective and subjective tests. The requirements for SOCs are
indicated in the ``General FTD Requirements'' column in Table B1A of
this appendix.
    b. Table B1A 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 6 FTDs. The sponsor should also
consult the objectives tests in Attachment 2 of this appendix and
the examination of functions and subjective tests listed in
Attachment 3 of this appendix 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 B1A provides the standards for the General FTD
Requirements.
    d. Table B1B provides the tasks that the sponsor will examine to
determine whether the FTD satisfactorily meets the requirements for
flight crew training, testing, and experience, and provides the
tasks for which the simulator may be qualified.
    e. Table B1C 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 B1A.--Minimum FTD Requirements
------------------------------------------------------------------------
                 QPS Requirements                       Information
------------------------------------------------------------------------
                                      FTD level
 Entry No.        General FTD      ---------------         Notes
                  requirements       4    5    6
------------------------------------------------------------------------
1. General Flight Deck Configuration
------------------------------------------------------------------------
1.a........  The FTD must have a               X   For FTD purposes, the
              flight deck that is                   flight deck consists
              a replica of the                      of all that space
              airplane simulated                    forward of a cross
              with controls,                        section of the
              equipment,                            fuselage at the most
              observable flight                     extreme aft setting
              deck indicators,                      of the pilots' seats
              circuit breakers,                     including
              and bulkheads                         additional, required
              properly located,                     flight crewmember
              functionally                          duty stations and
              accurate and                          those required
              replicating the                       bulkheads aft of the
              airplane. The                         pilot seats. For
              direction of                          clarification,
              movement of controls                  bulkheads containing
              and switches must be                  only items such as
              identical to that in                  landing gear pin
              the airplane. Pilot                   storage
              seat(s) must afford                   compartments, fire
              the capability for                    axes and
              the occupant to be                    extinguishers, spare
              able to achieve the                   light bulbs,
              design ``eye                          aircraft documents
              position.''                           pouches are not
              Equipment for the                     considered essential
              operation of the                      and may be omitted.
              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.
------------------------------------------------------------------------

1.b........  The FTD must have       X    X
              equipment (e.g.,
              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
              location and may be
              in a flight deck or
              an open flight deck
              area. Additional
              equipment required
              for the authorized
              training/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
              equipment must
              replicate the
              appropriate function
              in the airplane.
              Fire axes, landing
              gear pins, and any
              similar purpose
              instruments need
              only be represented
              in silhouette.
------------------------------------------------------------------------
2. Programming
------------------------------------------------------------------------
2.a........  The FTD must provide         X    X
              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
              airplane attitude,
              thrust, drag,
              altitude,
              temperature, and
              configuration.
             Level 6 additionally
              requires 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 the   X    X    X
              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        X    X   The intent is to
              the flight deck                       verify that the FTD
              instruments must be                   provides instrument
              measured by latency                   cues that are,
              tests, or transport                   within the stated
              delay tests, and may                  time delays, like
              not exceed 300                        the airplane
              milliseconds. The                     responses. For
              instruments must                      airplane response,
              respond to abrupt                     acceleration in the
              input at the pilot's                  appropriate,
              position within the                   corresponding
              allotted time, but                    rotational axis is
              not before the time                   preferred.
              when the airplane                     Additional
              responds under the                    information
              same conditions.                      regarding Latency
                                                    and Transport Delay
                                                    testing may be found
                                                    in Appendix A,
                                                    Attachment 2,
                                                    paragraph 15.
              Latency: The
              FTD instrument and,
              if applicable, the
              motion system and
              the visual system
              response must not be
              prior to that time
              when the airplane
              responds and may
              respond up to 300
              milliseconds after
              that time under the
              same conditions.
              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.
------------------------------------------------------------------------
3. Equipment Operation
------------------------------------------------------------------------
3.a........  All relevant                 X    X
              instrument
              indications involved
              in the simulation of
              the airplane must
              automatically
              respond to control
              movement or external
              disturbances to the
              simulated airplane;
              e.g., turbulence or
              winds.
------------------------------------------------------------------------
3.b........  Navigation equipment         X    X
              must be installed
              and operate within
              the tolerances
              applicable for the
              airplane.
------------------------------------------------------------------------
             Level 6 must also
              include
              communication
              equipment (inter-
              phone and air/
              ground) like that in
              the airplane and, if
              appropriate to the
              operation being
              conducted, an oxygen
              mask microphone
              system.

             Level 5 need have
              only that navigation
              equipment necessary
              to fly an instrument
              approach.
------------------------------------------------------------------------
3.c........  Installed systems       X    X    X
              must simulate the
              applicable airplane
              system operation,
              both on the ground
              and in flight.
              Installed 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.
             Level 6 must simulate
              all applicable
              airplane flight,
              navigation, and
              systems operation.
             Level 5 must have at
              least functional
              flight and
              navigational
              controls, displays,
              and instrumentation.
             Level 4 must have at
              least one airplane
              system installed and
              functional.
------------------------------------------------------------------------
3.d........  The lighting            X    X    X   Back-lighted panels
              environment for                       and instruments may
              panels and                            be installed but are
              instruments must be                   not required.
              sufficient for the
              operation being
              conducted.
------------------------------------------------------------------------
3.e........  The FTD must provide              X
              control forces and
              control travel that
              correspond to the
              airplane being
              simulated. Control
              forces must react in
              the same manner as
              in the airplane
              under the same
              flight conditions.
------------------------------------------------------------------------
3.f........  The FTD must provide         X
              control forces and
              control travel of
              sufficient precision
              to manually fly an
              instrument approach.
------------------------------------------------------------------------
4. Instructor or Evaluator Facilities
------------------------------------------------------------------------
4.a........  In addition to the      X    X    X   These seats need not
              flight crewmember                     be a replica of an
              stations, suitable                    aircraft seat and
              seating arrangements                  may be as simple as
              for an instructor/                    an office chair
              check airman and FAA                  placed in an
              Inspector must be                     appropriate
              available. These                      position.
              seats must provide
              adequate view of
              crewmember's
              panel(s).
------------------------------------------------------------------------
4.b........  The FTD must have       X    X    X
              instructor controls
              that permit
              activation of
              normal, abnormal,
              and emergency
              conditions as
              appropriate. Once
              activated, proper
              system operation
              must result from
              system management by
              the crew and not
              require input from
              the instructor
              controls.
------------------------------------------------------------------------
5. Motion System (not required)
------------------------------------------------------------------------
5.a........  The FTD may have a           X    X   The motion system
              motion system, if                     standards set out in
              desired, although it                  part 60, Appendix A
              is not required. If                   for at least Level A
              a motion system is                    simulators is
              installed and                         acceptable.
              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 airplane
              responds under the
              same conditions.
------------------------------------------------------------------------
5.b........  If a motion system is             X   The motion system
              installed, it must                    standards set out in
              be measured by                        part 60, Appendix A
              latency tests or                      for at least Level A
              transport delay                       simulators is
              tests and may not                     acceptable.
              exceed 300
              milliseconds.
              Instrument response
              may not occur prior
              to motion onset.
------------------------------------------------------------------------
6. Visual System
------------------------------------------------------------------------
6.a........  The FTD may have a      X    X    X
              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
              must respond to
              abrupt input at the
              pilot's position.
             An SOC 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...
------------------------------------------------------------------------
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...
------------------------------------------------------------------------
6.a.6......  The minimum distance    X    X    X
              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 is             X   Directly projected,
              installed and                         non-collimated
              additional training,                  visual displays may
              testing, or checking                  prove to be
              credits are being                     unacceptable for
              sought on the basis                   dual pilot
              of having a visual                    applications.
              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...
------------------------------------------------------------------------
7. Sound System
------------------------------------------------------------------------
7.a........  The FTD must simulate             X
              significant flight
              deck sounds
              resulting from pilot
              actions that
              correspond to those
              heard in the
              airplane.
------------------------------------------------------------------------

                Table B1B.--Table of Tasks vs. FTD Level
------------------------------------------------------------------------
                 QPS requirements                       Information
------------------------------------------------------------------------
                   Subjective         FTD level
                Requirements--In   ---------------
             order to be qualified
                   at the FTD
              qualification level
               indicated, the FTD
 Entry No.      must be able to                            Notes
              perform at least the   4    5    6
             tasks associated with
                 that level of
               qualification. See
              Notes 1 and 2 at the
                end of the Table
------------------------------------------------------------------------
1. Preflight Procedures.
------------------------------------------------------------------------
1.a........  Preflight Inspection    A    A    X
              (flight deck only).
------------------------------------------------------------------------
1.b........  Engine Start.........   A    A    X
------------------------------------------------------------------------
1.c........  Pre-takeoff Checks...   A    A    X
------------------------------------------------------------------------
2. Takeoff and Departure Phase.
------------------------------------------------------------------------
2.a........  Rejected Takeoff       ...  ...   A
              (requires visual
              system).
------------------------------------------------------------------------
2.b........  Departure Procedure..  ...   X    X
------------------------------------------------------------------------
3. In-flight Maneuvers.
------------------------------------------------------------------------

3.a........  a. Steep Turns.......  ...   X    X
------------------------------------------------------------------------
3.b........  b. Approaches to       ...   A    X
              Stalls.
------------------------------------------------------------------------
3.c........  c. Engine Failure      ...   A    X
              (procedures only)--
              Multiengine Airplane.
------------------------------------------------------------------------
3.d........  d. Engine Failure      ...   A    X
              (procedures only)--
              Single-Engine
              Airplane.
------------------------------------------------------------------------
3.e........  e. Specific Flight      A    A    A
              Characteristics
              incorporated into
              the user's FAA
              approved flight
              training program.
------------------------------------------------------------------------
4. Instrument Procedures.
------------------------------------------------------------------------
4.a........  Standard Terminal      ...   A    X
              Arrival/Flight
              Management System
              Arrival.
------------------------------------------------------------------------
4.b........  Holding..............  ...   A    X
------------------------------------------------------------------------
4.c........  Precision Instrument,  ...   A    X   e.g., Autopilot,
              all engines                           Manual (Flt. Dir.
              operating.                            Assisted), Manual
                                                    (Raw Data).
------------------------------------------------------------------------
4.d........  Non-precision          ...   A    X   e.g., NDB, VOR, VOR/
              Instrument, all                       DME, VOR/TAC, RNAV,
              engines operating.                    LOC, LOC/BC, ADF,
                                                    and SDF.
------------------------------------------------------------------------
4.e........  Circling Approach      ...  ...   A
              (requires visual
              system).
------------------------------------------------------------------------
4.f........  Missed Approach......  ...   A    X
------------------------------------------------------------------------
5. Normal and Abnormal Procedures.
------------------------------------------------------------------------
5.a........  Engine (including       A    A    X
              shutdown and
              restart--procedures
              only).
------------------------------------------------------------------------
5.b........  Fuel System..........   A    A    X
------------------------------------------------------------------------
5.c........  Electrical System....   A    A    X
------------------------------------------------------------------------
5.d........  Hydraulic System.....   A    A    X
------------------------------------------------------------------------
5.e........  Environmental and       A    A    X
              Pressurization
              Systems.
------------------------------------------------------------------------
5.f........  Fire Detection and      A    A    X
              Extinguisher Systems.
------------------------------------------------------------------------
5.g........  Navigation and          A    A    X
              Avionics Systems.
------------------------------------------------------------------------
5.h........  Automatic Flight        A    A    X
              Control System,
              Electronic Flight
              Instrument System,
              and Related
              Subsystems.
------------------------------------------------------------------------
5.i........  Flight Control          A    A    X
              Systems.
------------------------------------------------------------------------
5.j........  Anti-ice and Deice      A    A    X
              Systems.
------------------------------------------------------------------------
5.k........  Aircraft and Personal   A    A    X
              Emergency Equipment.
------------------------------------------------------------------------
6. Emergency Procedures.
------------------------------------------------------------------------
6.a........  Emergency Descent      ...   A    X
              (maximum rate).
------------------------------------------------------------------------
6.b........  Inflight Fire and      ...   A    X
              Smoke Removal.
------------------------------------------------------------------------
6.c........  Rapid Decompression..  ...   A    X
------------------------------------------------------------------------
6.d........  Emergency Evacuation.   A    A    X
------------------------------------------------------------------------
7. Postflight Procedures.
------------------------------------------------------------------------
7.a........  After-Landing           A    A    X
              Procedures.
------------------------------------------------------------------------

7.b........  Parking and Securing.   A    A   X
------------------------------------------------------------------------
Note 1: An ``A'' in the table indicates that the system, task, or
  procedure, although not required to be present, may be examined if the
  appropriate airplane system is simulated in the FTD and is working
  properly.
Note 2: Items not installed or not functional on the FTD and not
  appearing on the SOQ Configuration List, are not required to be listed
  as exceptions on the SOQ.

         Table B1C.--Table of FTD System Tasks QPS requirements
------------------------------------------------------------------------
                 QPS Requirements                       Information
------------------------------------------------------------------------
                   Subjective         FTD level
                Requirements  In   ---------------
             order to be qualified
                   at the FTD
              qualification level
 Entry No.     indicated, the FTD                          Notes
                must be able to      4    5    6
              perform at least the
             tasks associated with
                 that level of
                 qualification.
------------------------------------------------------------------------
1. Instructor Operating Station (IOS).
------------------------------------------------------------------------
1.a........  Power switch(es).....   X    X    X
------------------------------------------------------------------------
1.b........  Airplane conditions..   A    X    X   e.g., GW, CG, Fuel
                                                    loading, Systems,
                                                    Ground Crew.
------------------------------------------------------------------------
1.c........  Airports/Runways.....   X    X    X   e.g., Selection and
                                                    Presets; Surface and
                                                    Lighting controls if
                                                    equipped with a
                                                    visual system.
------------------------------------------------------------------------
1.d........  Environmental           X    X    X   e.g., Temp, Wind.
              controls.
------------------------------------------------------------------------
1.e........  Airplane system         A    X    X
              malfunctions
              (Insertion/deletion).
------------------------------------------------------------------------
1.f........  Locks, Freezes, and     X    X    X
              Repositioning.
------------------------------------------------------------------------
1.g........  Sound Controls. (On/    X    X    X
              off/adjustment).
------------------------------------------------------------------------
1.h........  Motion/Control          A    A    A
              Loading System, as
              appropriate. On/off/
              emergency stop.
------------------------------------------------------------------------
2. Observer Seats/Stations.
------------------------------------------------------------------------
2.a........  Position/Adjustment/    X    X   X
              Positive restraint
              system.
------------------------------------------------------------------------
Note 1: An ``A'' in the table indicates that the system, task, or
  procedure, although not required to be present, may be examined if the
  appropriate system is in the FTD and is working properly.

Attachment 2 to Appendix B to Part 60--Flight Training Device (FTD)
Objective Tests

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

Begin Information

1. Discussion

    a. For the purposes of this attachment, the flight conditions
specified in the Flight Conditions Column of Table B2A, are defined
as follows:
    (1) Ground--on ground, independent of airplane configuration;
    (2) Take-off--gear down with flaps/slats in any certified
takeoff position;
    (3) First segment climb--gear down with flaps/slats in any
certified takeoff position (normally not above 50 ft AGL);
    (4) Second segment climb--gear up with flaps/slats in any
certified takeoff position (normally between 50 ft and 400 ft AGL);
    (5) Clean--flaps/slats retracted and gear up;
    (6) Cruise--clean configuration at cruise altitude and airspeed;
    (7) Approach--gear up or down with flaps/slats at any normal
approach position as recommended by the airplane manufacturer; and
    (8) Landing--gear down with flaps/slats in any certified landing
position.
    b. The format for numbering the objective tests in Appendix A,
Attachment 2, Table A2A, and the objective tests in Appendix B,
Attachment 2, Table B2A, is identical. However, each test required
for FFSs is not necessarily required for FTDs. Also, each test
required for FTDs is not necessarily required for FFSs. Therefore,
when a test number (or series of numbers) is not required, the term
``Reserved'' is used in the table at that location. Following this
numbering format provides a degree of commonality between the two
tables and substantially reduces the potential for confusion when
referring to objective test numbers for either FFSs or FTDs.
    c. The reader is encouraged to review the Airplane Flight
Simulator Evaluation Handbook, Volumes I and II, published by the
Royal Aeronautical Society, London, UK, and FAA AC 25-7, as amended,
Flight Test Guide for Certification of Transport Category Airplanes,
and AC 23-8, as amended, Flight Test Guide for Certification of Part
23 Airplanes, for references and examples regarding flight testing
requirements and techniques.
    d. If relevant winds are present in the objective data, the wind
vector should be clearly noted as part of the data presentation,
expressed in conventional terminology, and related to the runway
being used for the test.
    e. A Level 4 FTD does not require objective tests and therefore,
Level 4 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 B2A Objective 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 airplane being simulated or to the qualification level
sought, it may be disregarded (e.g., an engine out missed approach
for a single-engine airplane; a maneuver using reverse thrust for an
airplane without reverse thrust capability). Each test result is
compared against the validation data described in Sec.  60.13, and
in Appendix B. The results must be produced on an appropriate
recording device acceptable to the NSPM and 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 B2A. All
results must be labeled using the tolerances and units given.
    b. Table B2A 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. In those cases where a
tolerance is expressed only as a percentage, the tolerance
percentage applies to the maximum value of that parameter within its
normal operating range as measured from the neutral or zero position
unless otherwise indicated.
    c. Certain tests included in this attachment must be supported
with a SOC. In Table B2A, 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 may not be limited to a single parameter. For example, data
that exhibit rapid variations of the measured parameters may require
interpolations or a ``best fit'' data 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 airplane data throughout a time history,
differences must be justified by providing a comparison of other
related variables for the condition being assessed.
    e. It is not acceptable to program the FTD so that the
mathematical modeling is correct only at the validation test points.
Unless noted otherwise, tests must represent airplane performance
and handling qualities at operating weights and centers of gravity
(CG) typical of normal operation. If a test is supported by 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 airplane weight and CG envelope;
    (2) The operational envelope; and
    (3) Varying atmospheric ambient and environmental conditions--
including the extremes authorized for the respective airplane or set
of airplanes.
    f. When comparing the parameters listed to those of the
airplane, sufficient data must also be provided to verify the
correct flight condition and airplane configuration changes. For
example, to show that control force is within the parameters for a
static stability test, data to show the correct airspeed, power,
thrust or torque, airplane configuration, altitude, and other
appropriate datum identification parameters must also be given. If
comparing short period dynamics, normal acceleration may be used to
establish a match to the airplane, but airspeed, altitude, control
input, airplane configuration, and other appropriate data must also
be given. If comparing landing gear change dynamics, pitch,
airspeed, and altitude may be used to establish a match to the
airplane, but landing gear position must also be provided. All
airspeed values must be properly annotated (e.g., indicated versus
calibrated). In addition, the same variables must be used for
comparison (e.g., compare inches to inches rather than inches to
centimeters).
    g. The QTG provided by the sponsor must clearly describe how the
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. 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.
    i. FTDs are evaluated and qualified with an engine model
simulating the airplane data supplier's flight test engine. For
qualification of alternative engine models (either variations of the
flight test engines or other manufacturer's engines) additional
tests with the alternative engine models may be required. This
attachment contains guidelines for alternative engines.
    j. Testing Computer Controlled Aircraft (CCA) simulators, or
other highly augmented airplane simulators, flight test data is
required for the Normal (N) and/or Non-normal (NN) control states,
as indicated in this attachment. Where test results are independent
of control state, Normal or Non-normal control data may be used. All
tests in Table B2A require test results in the Normal control state
unless specifically noted otherwise in the Test Details section
following the CCA designation. The NSPM will determine what tests
are appropriate for airplane simulation data. When making this
determination, the NSPM may require other levels of control state
degradation for specific airplane tests. Where Non-normal control
states are required, test data must be provided for one or more Non-
normal control states, and must include the least augmented state.
Where applicable, flight test data must record Normal and Non-normal
states for:
    (1) Pilot controller deflections or electronically generated
inputs, including location of input; and
    (2) Flight control surface positions unless test results are not
affected by, or are independent of, surface positions.
    k. Tests of handling qualities must include validation of
augmentation devices. FTDs for highly augmented airplanes will be
validated both in the unaugmented configuration (or failure state
with the maximum permitted degradation in handling qualities) and
the augmented configuration. Where various levels of handling
qualities result from failure states, validation of the effect of
the failure is necessary. Requirements for testing will be mutually
agreed to between the sponsor and the NSPM on a case-by-case basis.
    l. Some tests will not be required for airplanes using airplane
hardware in the FTD flight deck (e.g., ``side stick controller'').
These exceptions are noted in Section 2 ``Handling Qualities'' in
Table B2A of this attachment. However, in these cases, the sponsor
must provide a statement that the airplane hardware meets the
appropriate manufacturer's specifications and the sponsor must have
supporting information to that fact available for NSPM review.
    m. For objective test purposes, see Appendix F of this part for
the definitions of ``Near maximum,'' ``Light,'' and ``Medium'' gross
weight.

End QPS Requirements

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

Begin Information

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

End Information

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

                            Table B2A.--Flight Training Device (FTD) Objective Tests
----------------------------------------------------------------------------------------------------------------
                                                QPS requirements
-----------------------------------------------------------------------------------------------------------------
             Test                                                                        FTD       Information
-------------------------------                        Flight                           level  -----------------
                                   Tolerances        conditions       Test details   ----------
  Entry No.         Title                                                              5    6         Notes
----------------------------------------------------------------------------------------------------------------
1. Performance
----------------------------------------------------------------------------------------------------------------
1.a.........  (Reserved)
----------------------------------------------------------------------------------------------------------------
1.b.........  Takeoff
----------------------------------------------------------------------------------------------------------------
1.b.1.......  Ground            5%    Takeoff.........  Record                  X   This test is
               Acceleration      time or 1 sec.                        time for a                  if RTO training
                                                                     minimum of 80%              credit is
                                                                     of the segment              sought.
                                                                     from brake
                                                                     release to VR.
                                                                    Preliminary
                                                                     aircraft
                                                                     certification
                                                                     data may be
                                                                     used.
----------------------------------------------------------------------------------------------------------------
1.b.2.        (Reserved)
through
 1.b.6..
----------------------------------------------------------------------------------------------------------------
1.b.7.......  Rejected Takeoff  5%    Dry Runway......  Record time for         X   This test is
                                 time or 1.5 sec.                      the segment                 if RTO training
                                                                     from initiation             credit is
                                                                     of the Rejected             sought.
                                                                     Takeoff to full
                                                                     stop.
----------------------------------------------------------------------------------------------------------------
1.b.8.......  (Reserved)
----------------------------------------------------------------------------------------------------------------
1.c.........  Climb
----------------------------------------------------------------------------------------------------------------
1.c.1.......  Normal Climb all  3 kt  Clean...........  Flight test data   X    X
               engines           airspeed, 5% or                         performance
                                 100                     manual data may
                                 ft/min (0.5 m/                      be used. Record
                                 sec) climb rate.                    at nominal
                                                                     climb speed and
                                                                     at nominal
                                                                     altitude. May
                                                                     be a snapshot
                                                                     test result.
                                                                     FTD performance
                                                                     must be
                                                                     recorded over
                                                                     an interval of
                                                                     at least 1,000
                                                                     ft (300 m).
----------------------------------------------------------------------------------------------------------------
1.c.2.        (Reserved)
through
 1.c.4..
----------------------------------------------------------------------------------------------------------------
1.d.........  (Reserved)
----------------------------------------------------------------------------------------------------------------
1.e.........  (Reserved)
----------------------------------------------------------------------------------------------------------------
1.f.........  Engines
----------------------------------------------------------------------------------------------------------------
1.f.1.......  Acceleration....  Level 6: 10% Tt,     Landing.          power (N1, N2,              of this part
                                 or 0.25 sec.                     Manifold                    of Ti and Tt.
                                Level 5: 1 sec.                        idle to maximum
                                                                     takeoff power
                                                                     for a rapid
                                                                     (slam) throttle
                                                                     movement.
----------------------------------------------------------------------------------------------------------------
1.f.2.......  Deceleration....  Level 6: 10% Tt,                       power (N1, N2,              of this part
                                 or 0.25 sec.                     Manifold                    of Ti and Tt.
                                Level 5: 1 sec.                        maximum takeoff
                                                                     power to idle
                                                                     for a rapid
                                                                     (slam) throttle
                                                                     movement.
----------------------------------------------------------------------------------------------------------------
2. Handling Qualities
----------------------------------------------------------------------------------------------------------------

              For FTDs requiring Static tests at the controls (i.e., column, wheel,             Testing of
               rudder pedal), special test fixtures will not be required during                  position versus
               initial or upgrade evaluations if the sponsor's QTG/MQTG shows both               force is not
               test fixture results and the results of an alternative approach, such             applicable if
               as computer plots produced concurrently, that show satisfactory                   forces are
               agreement. Repeat of the alternative method during the initial or                 generated
               upgrade evaluation would then satisfy this test requirement.                      solely by use
                                                                                of airplane
                                                                                hardware in the
                                                                                FTD.
----------------------------------------------------------------------------------------------------------------
2.a.........  Static Control Tests
----------------------------------------------------------------------------------------------------------------
2.a.1.a.....  Pitch Controller  2 lb  Ground..........  Record results          X
               Position vs.      (0.9 daN)                           for an
               Force and         breakout, 10% or                        control sweep
               Position          5                       to the stops.
               Calibration.      lb (2.2 daN)
                                 force, 2[deg]
                                 elevator.
----------------------------------------------------------------------------------------------------------------
2.a.1.b.....  Pitch Controller  2 lb  As determined by  Record results     X        Applicable only
               Position vs.      (0.9 daN)         sponsor.          during initial              on continuing
               Force.            breakout, 10% or                        evaluation for              evaluations.
                                 5                       an                          The intent is
                                 lb (2.2 daN)                        uninterrupted               to design the
                                 force.                              control sweep               control feel
                                                                     to the stops.               for Level 5 to
                                                                     The recorded                be able to
                                                                     tolerances                  manually fly an
                                                                     apply to                    instrument
                                                                     subsequent                  approach; and
                                                                     comparisons on              not to compare
                                                                     continuing                  results to
                                                                     qualification               flight test or
                                                                     evaluations.                other such
                                                                                data.
----------------------------------------------------------------------------------------------------------------
2.a.2.a.....  Roll Controller   2 lb  Ground..........  Record results          X
               Position vs.      (0.9 daN)                           for an
               Force and         breakout, 10% or                        control sweep
               Position          3                       to the stops.
               Calibration.      lb (1.3 daN)
                                 force, 2[deg]
                                 aileron, 3[deg]
                                 spoiler angle.
----------------------------------------------------------------------------------------------------------------
2.a.2.b.....  Roll Controller   2 lb  As determined by  Record results     X        Applicable only
               Position vs.      (0.9 daN)         sponsor.          during initial              on continuing
               Force.            breakout, 10% or                        evaluation for              evaluations.
                                 3                       an                          The intent is
                                 lb (1.3 daN)                        uninterrupted               to design the
                                 force.                              control sweep               control feel
                                                                     to the stops.               for Level 5 to
                                                                     The recorded                be able to
                                                                     tolerances                  manually fly an
                                                                     apply to                    instrument
                                                                     subsequent                  approach; and
                                                                     comparisons on              not to compare
                                                                     continuing                  results to
                                                                     qualification               flight test or
                                                                     evaluations.                other such
                                                                                data.
----------------------------------------------------------------------------------------------------------------
2.a.3.a.....  Rudder Pedal      5 lb  Ground..........  Record results          X
               Position vs.      (2.2 daN)                           for an
               Force and         breakout, 10% or                        control sweep
               Position          5                       to the stops.
               Calibration.      lb (2.2 daN)
                                 force, 2[deg]
                                 rudder angle.
----------------------------------------------------------------------------------------------------------------

2.a.3.b.....  Rudder Pedal      5 lb  As determined by  Record results     X        Applicable only
               Position vs.      (2.2 daN)         sponsor.          during initial              on continuing
               Force.            breakout, 10% or                        evaluation for              evaluations.
                                 5                       an                          The intent is
                                 lb (2.2 daN)                        uninterrupted               to design the
                                 force.                              control sweep               control feel
                                                                     to the stops.               for Level 5 to
                                                                     The recorded                be able to
                                                                     tolerances                  manually fly an
                                                                     apply to                    instrument
                                                                     subsequent                  approach; and
                                                                     comparisons on              not to compare
                                                                     continuing                  results to
                                                                     qualification               flight test or
                                                                     evaluations.                other such
                                                                                data.
----------------------------------------------------------------------------------------------------------------
2.a.4.......  Nosewheel         2 lb  Ground..........  Record results          X
               Steering          (0.9 daN)                           of an
               Controller        breakout, 10% or                        control sweep
                                 3                       to the stops.
                                 lb (1.3 daN)
                                 force.
----------------------------------------------------------------------------------------------------------------
2.a.5.......  Rudder Pedal      2[deg]                        of an
               Calibration.      nosewheel angle.                    uninterrupted
                                                                     control sweep
                                                                     to the stops.
----------------------------------------------------------------------------------------------------------------
2.a.6.......  Pitch Trim        0.5[deg]                                                  the test is to
               Surface           of computed                                                     compare the FTD
               Position          trim surface                                                    against design
               Calibration.      angle.                                                          data or
                                                                                equivalent.
----------------------------------------------------------------------------------------------------------------
2.a.7.......  (Reserved)
----------------------------------------------------------------------------------------------------------------
2.a.8.......  Alignment of      5[deg] of                     simultaneous
               Throttle Lever    throttle lever                      recording for
               vs. Selected      angle or 0.8 in (2                     The tolerances
               Parameter.        cm) for power                       apply against
                                 control without                     airplane data
                                 angular travel,                     and between
                                 or 3% N1, or                     case of
                                 0.03 EPR,                     powered
                                 or 3%                            propeller lever
                                 maximum rated                       is present, it
                                 manifold                            must also be
                                 pressure, or                        checked. For
                                 3%                      airplanes with
                                 torque.                             throttle
                                                                     ``detents,''
                                                                     all detents
                                                                     must be
                                                                     presented. May
                                                                     be a series of
                                                                     snapshot test
                                                                     results.
----------------------------------------------------------------------------------------------------------------
2.a.9.......  Brake Pedal       5 lb  Ground..........  Two data points         X   Test not
               Position vs.      (2.2 daN) or                        are required:               required unless
               Force.            10% force.                          Zero and                    RTO credit is
                                                                     maximum                     sought.
                                                                     deflection.
                                                                     Computer output
                                                                     results may be
                                                                     used to show
                                                                     compliance.
----------------------------------------------------------------------------------------------------------------
2.b.........  (Reserved)
----------------------------------------------------------------------------------------------------------------
2.c.........  Longitudinal Control Tests
----------------------------------------------------------------------------------------------------------------
Power setting is that required for level flight unless otherwise specified.
----------------------------------------------------------------------------------------------------------------
2.c.1.......  Power Change      5 lb  Approach........  May be a series    X    X
               Force.            (2.2 daN) or,                       of snapshot
                                 20%                     test results.
                                 pitch conrol                        Power change
                                 force.                              dynamics test
                                                                     as described in
                                                                     test 2.c.1 of
                                                                     Table A2A of
                                                                     this part will
                                                                     be accepted.
                                                                     CCA: Test in
                                                                     Normal and Non-
                                                                     normal control
                                                                     states.
----------------------------------------------------------------------------------------------------------------

2.c.2.......  Flap/Slat Change  5 lb  Takeoff through   May be a series    X    X
               Force.            (2.2 daN) or,     initial flap      of snapshot
                                 20%   retraction, and   test results.
                                 pitch conrol      approach to       Flap/Slat
                                 force.            landing.          change dynamics
                                                                     test as
                                                                     described in
                                                                     test 2.c.2 of
                                                                     Table A2A of
                                                                     this part will
                                                                     be accepted.
                                                                     CCA: Test in
                                                                     Normal and Non-
                                                                     normal control
                                                                     states.
----------------------------------------------------------------------------------------------------------------
2.c.3.......  (Reserved)
----------------------------------------------------------------------------------------------------------------
2.c.4.......  Gear Change       5 lb  Takeoff           May be a series    X    X
               Force.            (2.2 daN) or,     (retraction)      of snapshot
                                 20%   and Approach      test results.
                                 pitch conrol      (extension).      Gear change
                                 force.                              dynamics test
                                                                     as described in
                                                                     test 2.c.4 of
                                                                     Table A2A of
                                                                     this part will
                                                                     be accepted.
                                                                     CCA: Test in
                                                                     Normal and Non-
                                                                     normal control
                                                                     states.
----------------------------------------------------------------------------------------------------------------
2.c.5.......  Longitudinal      0.5[deg]    Approach, and     state condition
                                 trim surface      Landing.          with wings
                                 angle 1[deg]                        thrust set for
                                 elevator 1[deg]                        May be a series
                                 pitch angle                         of snapshot
                                 5%                      tests Level 5
                                 net thrust or                       may use
                                 equivalent.                         equivalent
                                                                     stick and trim
                                                                     controllers in
                                                                     lieu of
                                                                     elevator and
                                                                     trim surface.
                                                                     CCA: Test in
                                                                     Normal and Non-
                                                                     normal control
                                                                     states.
----------------------------------------------------------------------------------------------------------------
2.c.6.......  Longitudinal      5 lb  Cruise,           Continuous time         X
               Maneuvering       (2.2 daN)    Landing.          a series of
               (Stick Force/g).  or 10% pitch                     may be used.
                                 controller                          Record results
                                 force                               up to 30[deg]
                                 Alternative                         of bank for
                                 method: 1[deg] or                     landing
                                 10%                     configurations.
                                 change of                           Record results
                                 elevator.                           for up to
                                                                     45[deg] of bank
                                                                     for the cruise
                                                                     configuration.
                                                                     The force
                                                                     tolerance is
                                                                     not applicable
                                                                     if forces are
                                                                     generated
                                                                     solely by the
                                                                     use of airplane
                                                                     hardware in the
                                                                     FTD. The
                                                                     alternative
                                                                     method applies
                                                                     to airplanes
                                                                     that do not
                                                                     exhibit ``stick-
                                                                     force-per-g''
                                                                     characteristics
                                                                     . CCA: Test in
                                                                     Normal and Non-
                                                                     normal control
                                                                     states.
----------------------------------------------------------------------------------------------------------------

2.c.7.......  Longitudinal      5 lb  Approach........  May be a series    X    X
               Static            (2.2 daN)                      test results.
                                 or 10% pitch                     for at least 2
                                 controller                          speeds above
                                 force.                              and 2 speeds
                                Alternative                          below trim
                                 method: 1[deg] or                     force tolerance
                                 10%                     is not
                                 change of                           applicable if
                                 elevator.                           forces are
                                                                     generated
                                                                     solely by the
                                                                     use of airplane
                                                                     hardware in the
                                                                     FTD. The
                                                                     alternative
                                                                     method applies
                                                                     to airplanes
                                                                     that do not
                                                                     exhibit speed
                                                                     stability
                                                                     characteristics
                                                                     . Level 5 must
                                                                     exhibit
                                                                     positive static
                                                                     stability, but
                                                                     need not comply
                                                                     with the
                                                                     numerical
                                                                     tolerance. CCA:
                                                                     Test in Normal
                                                                     and Non-normal
                                                                     control states.
----------------------------------------------------------------------------------------------------------------
2.c.8.......  Stall Warning     3     Second Segment    The stall          X    X
               (actuation of     kts. airspeed,    Climb, and        maneuver must
               stall warning     2[deg]      Landing.          thrust at or
                                 bank for speeds                     near idle power
                                 greater than                        and wings level
                                 actuation of                        (1g). Record
                                 stall warning                       the stall
                                 device or                           warning signal
                                 initial buffet.                     and initial
                                                                     buffet if
                                                                     applicable.
                                                                     CCA: Test in
                                                                     Normal and Non-
                                                                     normal control
                                                                     states.
----------------------------------------------------------------------------------------------------------------
2.c.9.a.....  Phugoid Dynamics  10%   Cruise..........  The test must      X
                                 period, 10% of                        whichever is
                                 time to \1/2\                       less of the
                                 or double                           following:
                                 amplitude or                        Three full
                                 .02                     cycles (six
                                 of damping                          overshoots
                                 ratio.                              after the input
                                                                     is completed),
                                                                     or the number
                                                                     of cycles
                                                                     sufficient to
                                                                     determine time
                                                                     to \1/2\ or
                                                                     double
                                                                     amplitude. CCA:
                                                                     Test in Non-
                                                                     normal control
                                                                     state.
----------------------------------------------------------------------------------------------------------------
2.c.9.b.....  Phugoid Dynamics  10%   Cruise..........  The test must      X
                                 period,                             include
                                 Representative                      whichever is
                                 damping.                            less of the
                                                                     following:
                                                                     Three full
                                                                     cycles (six
                                                                     overshoots
                                                                     after the input
                                                                     is completed),
                                                                     or the number
                                                                     of cycles
                                                                     sufficient to
                                                                     determine
                                                                     representative
                                                                     damping. CCA:
                                                                     Test in Non-
                                                                     normal control
                                                                     state.
----------------------------------------------------------------------------------------------------------------
2.c.10......  Short Period      1.5[deg]                      normal control
                                 pitch angle or                      state.
                                 2[deg]/
                                 sec pitch rate,
                                 0.10g
                                 acceleration..
----------------------------------------------------------------------------------------------------------------
2.d.........  Lateral Directional Tests
----------------------------------------------------------------------------------------------------------------
Power setting is that required for level flight unless otherwise specified.
----------------------------------------------------------------------------------------------------------------
2.d.1.......  (Reserved)
----------------------------------------------------------------------------------------------------------------
2.d.2.......  Roll Response     10%   Cruise, and       Record results     X    X
               (Rate).           or 2[deg]/     Landing.          controller
                                 sec roll rate.                      deflection (one-
                                                                     third of
                                                                     maximum roll
                                                                     controller
                                                                     travel). May be
                                                                     combined with
                                                                     step input of
                                                                     flight deck
                                                                     roll controller
                                                                     test (see
                                                                     2.d.3.).
----------------------------------------------------------------------------------------------------------------

2.d.3.......  Roll Response to  10%   Approach or       Record from             X
               Flight deck       or 2[deg]                        roll through 10
               Step Input.       bank angle.                         seconds after
                                                                     control is
                                                                     returned to
                                                                     neutral and
                                                                     released. May
                                                                     be combined
                                                                     with roll
                                                                     response (rate)
                                                                     test (see
                                                                     2.d.2.). CCA:
                                                                     Test in Non-
                                                                     normal control
                                                                     state.
----------------------------------------------------------------------------------------------------------------
2.d.4.a.....  Spiral Stability  Correct trend     Cruise..........  Record results          X   Airplane data
                                 and 3[deg] or                     directions. As              multiple tests
                                 10%                     an alternate                in same
                                 bank angle in                       test,                       direction may
                                 30 seconds.                         demonstrate the             be used.
                                                                     lateral control
                                                                     required to
                                                                     maintain a
                                                                     steady turn
                                                                     with a bank
                                                                     angle of
                                                                     30[deg]. CCA:
                                                                     Test in Non-
                                                                     normal control
                                                                     state.
----------------------------------------------------------------------------------------------------------------
2.d.4.b.....  Spiral Stability  Correct trend...  Cruise..........  CCA: Test in Non-  X        Airplane data
                                                                     normal control              averaged from
                                                                     state.                      multiple tests
                                                                                in same
                                                                                direction may
                                                                                be used.
----------------------------------------------------------------------------------------------------------------
2.d.5.......  (Reserved)
----------------------------------------------------------------------------------------------------------------
2.d.6.a.....  Rudder Response.  2[deg]/     Landing.          input of 20%-
                                 sec or 10% yaw                       pedal throw
                                 rate.                               must be used.
                                                                     Not required if
                                                                     rudder input
                                                                     and response is
                                                                     shown in Dutch
                                                                     Roll test (test
                                                                     2.d.7.). CCA:
                                                                     Test in Normal
                                                                     and Non-normal
                                                                     control states.
----------------------------------------------------------------------------------------------------------------
2.d.6.b.....  Rudder Response.  Roll rate 2[deg]/     Landing.          response to a               accomplished as
                                 sec, bank angle                     given rudder                a yaw response
                                 3[deg].                       CCA: Test in                case the
                                                                     Normal and Non-             procedures and
                                                                     normal control              requirements of
                                                                     states.                     test 2.d.6.a.
                                                                                will apply.
----------------------------------------------------------------------------------------------------------------
2.d.7.......  Dutch Roll (Yaw   0.5   Cruise, and       Record results
               Damper OFF).      sec. or 10% of      Landing.          complete cycles
                                 period, 10% of                        augmentation
                                 time to \1/2\                       OFF, or the
                                 or double                           number of
                                 amplitude or                        cycles
                                 .02                     sufficient to
                                 of damping                          determine time
                                 ratio.                              to \1/2\ or
                                                                     double
                                                                     amplitude. CCA:
                                                                     Test in Non-
                                                                     normal control
                                                                     state.
----------------------------------------------------------------------------------------------------------------
2.d.8.......  Steady State      For given rudder  Approach or       Use at least two   X    X
               Sideslip.         position 2[deg]                        positions, one
                                 bank angle,                         of which must
                                 1[deg]                        allowable
                                 sideslip angle,                     rudder.
                                 10%                     Propeller
                                 or 2[deg]                        airplanes must
                                 aileron, 10% or                        direction. May
                                 5[deg]                        snapshot test
                                 spoiler or                          results.
                                 equivalent                          Sideslip angle
                                 roll,                               is matched only
                                 controller                          for
                                 position or                         repeatability
                                 force.                              and only on
                                                                     continuing
                                                                     qualification
                                                                     evaluations.
----------------------------------------------------------------------------------------------------------------

2.e.          (Reserved)
through 2.h.
----------------------------------------------------------------------------------------------------------------
3. (Reserved)
----------------------------------------------------------------------------------------------------------------
4. (Reserved)
----------------------------------------------------------------------------------------------------------------
5. (Reserved)
----------------------------------------------------------------------------------------------------------------
6. FTD System Response Time
----------------------------------------------------------------------------------------------------------------
6.a.........  Latency.
----------------------------------------------------------------------------------------------------------------
                                300 ms (or less)  Take-off,         One test is        X    X
                                 after airplane    cruise, and       required in
                                 response.         approach or       each axis
                                                   landing.          (pitch, roll
                                                                     and yaw) for
                                                                     each of the
                                                                     three
                                                                     conditions
                                                                     (take-off,
                                                                     cruise, and
                                                                     approach or
                                                                     landing).
----------------------------------------------------------------------------------------------------------------
              Transport Delay
----------------------------------------------------------------------------------------------------------------
                                300 ms (or less)  N/A.............  A separate test    X    X   If Transport
                                 after                               is required in              Delay is the
                                 controller                          each axis                   chosen method
                                 movement.                           (pitch, roll,               to demonstrate
                                                                     and yaw).                   relative
                                                                                responses, the
                                                                                sponsor and the
                                                                                NSPM will use
                                                                                the latency
                                                                                values to
                                                                                ensure proper
                                                                                simulator
                                                                                response when
                                                                                reviewing those
                                                                                existing tests
                                                                                where latency
                                                                                can be
                                                                                identified
                                                                                (e.g., short
                                                                                period, roll
                                                                                response,
                                                                                rudder
                                                                                response).
----------------------------------------------------------------------------------------------------------------

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

Begin Information

3. For additional information on the following topics, please refer to
Appendix A, Attachment 2, and the indicated paragraph within that
attachment

     Control Dynamics, paragraph 4.
     Motion System, paragraph 6.
     Sound System, paragraph 7.
     Engineering Simulator Validation Data, paragraph 9.
     Validation Test Tolerances, paragraph 11.
     Validation Data Road Map, paragraph 12.
     Acceptance Guidelines for Alternative Engines Data,
paragraph 13.
     Acceptance Guidelines for Alternative Avionics,
paragraph 14.
     Transport Delay Testing, paragraph 15.
     Continuing Qualification Evaluation Validation Data
Presentation, paragraph 16.

End Information

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

4. Alternative Objective Data for FTD Level 5

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

Begin QPS Requirements

    a. This paragraph (including the following tables) is relevant
only to FTD Level 5. It is provided because this level is required
to simulate the performance and handling characteristics of a set of
airplanes with similar characteristics, such as normal airspeed/
altitude operating envelope and the same number and type of
propulsion systems (engines).
    b. Tables B2B through B2E reflect FTD performance standards that
are acceptable to the FAA. A sponsor must demonstrate that a device
performs within these parameters, as applicable. If a device does
not meet the established performance parameters for some or for all
of the applicable tests listed in Tables B2B through B2E, the
sponsor may use NSP accepted flight test data for comparison
purposes for those tests.
    c. Sponsors using the data from Tables B2B through B2E must
comply with the following:
    (1) Submit a complete QTG, including results from all of the
objective tests appropriate for the level of qualification sought as
set out in Table B2A. The QTG must highlight those results that
demonstrate the performance of the FTD is within the allowable
performance ranges indicated in Tables B2B through B2E, as
appropriate.
    (2) The QTG test results must include all relevant information
concerning the conditions under which the test was conducted; e.g.,
gross weight, center of gravity, airspeed, power setting, altitude
(climbing, descending, or level), temperature, configuration, and
any other parameter that impacts the conduct of the test.
    (3) The test results become the validation data against which
the initial and all subsequent continuing qualification evaluations
are compared. These subsequent evaluations will use the tolerances
listed in Table B2A.

    (4) Subjective testing of the device must be performed to
determine that the device performs and handles like an airplane
within the appropriate set of airplanes.

End QPS Requirements

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

Begin Information

    d. The reader is encouraged to consult the Airplane Flight
Simulator Evaluation Handbook, Volumes I and II, published by the
Royal Aeronautical Society, London, UK, and AC 25-7, Flight Test
Guide for Certification of Transport Category Airplanes, and AC 23-
8A, Flight Test Guide for Certification of Part 23 Airplanes, as
amended, for references and examples regarding flight testing
requirements and techniques.

End Information

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

Table B2B.--Alternative Data Source for FTD Level 5 Small, Single Engine
                        (Reciprocating) Airplane
------------------------------------------------------------------------
QPS requirement The performance parameters in this table must be used to
   program the FTD if flight test data is not used to program the FTD.
-------------------------------------------------------------------------
               Applicable test
---------------------------------------------   Authorized performance
    Entry No.         Title and procedure                range
------------------------------------------------------------------------
1...............  Performance.
------------------------------------------------------------------------
1.c.............  Climb
------------------------------------------------------------------------
1.c.1...........  Normal climb with nominal   Climb rate = 500-1200 fpm
                   gross weight, at best       (2.5-6 m/sec).
                   rate-of-climb airspeed.
------------------------------------------------------------------------
1.f.............  Engines.
------------------------------------------------------------------------
1.f.1...........  Acceleration; idle to       2-4 Seconds.
                   takeoff power.
------------------------------------------------------------------------
1.f.2...........  Deceleration; takeoff       2-4 Seconds.
                   power to idle.
------------------------------------------------------------------------
2...............  Handling Qualities
------------------------------------------------------------------------
2.c.............  Longitudinal Tests
------------------------------------------------------------------------
2.c.1...........  Power change force
------------------------------------------------------------------------
                  (a) Trim for straight and   5-15 lbs (2.2-6.6 daN) of
                   level flight at 80% of      force (Pull).
                   normal cruise airspeed
                   with necessary power.
                   Reduce power to flight
                   idle. Do not change trim
                   or configuration. After
                   stabilized, record column
                   force necessary to
                   maintain original
                   airspeed.
------------------------------------------------------------------------
                  OR
------------------------------------------------------------------------
                  (b) Trim for straight and   5-15 lbs (2.2-6.6 daN) of
                   level flight at 80% of      force (Push).
                   normal cruise airspeed
                   with necessary power. Add
                   power to maximum setting.
                   Do not change trim or
                   configuration. After
                   stabilized, record column
                   force necessary to
                   maintain original
                   airspeed..
------------------------------------------------------------------------
2.c.2...........  Flap/slat change force
------------------------------------------------------------------------
                  (a) Trim for straight and   5-15 lbs (2.2-6.6 daN) of
                   level flight with flaps     force (Pull).
                   fully retracted at a
                   constant airspeed within
                   the flaps-extended
                   airspeed range. Do not
                   adjust trim or power.
                   Extend the flaps to 50%
                   of full flap travel.
                   After stabilized, record
                   stick force necessary to
                   maintain original
                   airspeed.
------------------------------------------------------------------------
                  OR
------------------------------------------------------------------------
                  (b) Trim for straight and   5-15 lbs (2.2-6.6 daN) of
                   level flight with flaps     force (Push).
                   extended to 50% of full
                   flap travel, at a
                   constant airspeed within
                   the flaps-extended
                   airspeed range. Do not
                   adjust trim or power.
                   Retract the flaps to
                   zero. After stabilized,
                   record stick force
                   necessary to maintain
                   original airspeed.
------------------------------------------------------------------------
2.c.4...........  Gear change force
------------------------------------------------------------------------
                  (a) Trim for straight and   2-12 lbs (0.88-5.3 daN) of
                   level flight with landing   force (Pull).
                   gear retracted at a
                   constant airspeed within
                   the landing gear-extended
                   airspeed range. Do not
                   adjust trim or power.
                   Extend the landing gear.
                   After stabilized, record
                   stick force necessary to
                   maintain original
                   airspeed.
------------------------------------------------------------------------
                  OR
------------------------------------------------------------------------

                  (b) Trim for straight and   2-12 lbs (0.88-5.3 daN) of
                   level flight with landing   force (Push).
                   gear extended, at a
                   constant airspeed within
                   the landing gear-extended
                   airspeed range. Do not
                   adjust trim or power.
                   Retract the landing gear.
                   After stabilized, record
                   stick force necessary to
                   maintain original
                   airspeed.
------------------------------------------------------------------------
2.c.5...........  Longitudinal trim.........  Must be able to trim
                                               longitudinal stick force
                                               to ``zero'' in each of
                                               the following
                                               configurations: cruise;
                                               approach; and landing.
------------------------------------------------------------------------
2.c.7...........  Longitudinal static         Must exhibit positive
                   stability.                  static stability.
------------------------------------------------------------------------
2.c.8...........  Stall warning (actuation
                   of stall warning device)
                   with nominal gross
                   weight; wings level; and
                   a deceleration rate of
                   not more than three (3)
                   knots per second.
------------------------------------------------------------------------
                  (a) Landing configuration.  40-60 knots;
                                               5[deg] of bank.
------------------------------------------------------------------------
                  (b) Clean configuration...  Landing configuration
                                               speed + 10-20%.
------------------------------------------------------------------------
2.c.9.b.........  Phugoid dynamics..........  Must have a phugoid with a
                                               period of 30-60 seconds.
                                               May not reach \1/2\ or
                                               double amplitude in less
                                               than 2 cycles.
------------------------------------------------------------------------
2.d.............  Lateral Directional Tests.
------------------------------------------------------------------------
2.d.2...........  Roll response (rate). Roll  Must have a roll rate of
                   rate must be measured       40[deg]-25[deg]/second.
                   through at least 30[deg]
                   of roll. Aileron control
                   must be deflected \1/3\
                   (33.3 percent) of maximum
                   travel.
------------------------------------------------------------------------
2.d.4.b.........  Spiral stability. Cruise    Initial bank angle ( 5[deg]) after 20
                   cruise airspeed.            seconds.
                   Establish a 20[deg]-
                   30[deg] bank. When
                   stabilized, neutralize
                   the aileron control and
                   release. Must be
                   completed in both
                   directions of turn.
------------------------------------------------------------------------
2.d.6.b.........  Rudder response. Use 25     2[deg]-6[deg]/second yaw
                   percent of maximum rudder   rate.
                   deflection. (Applicable
                   to approach or landing
                   configuration.).
------------------------------------------------------------------------
2.d.7...........  Dutch roll, yaw damper      A period of 2-5 seconds;
                   off. (Applicable to         and \1/2\-2 cycles.
                   cruise and approach
                   configurations.).
------------------------------------------------------------------------
2.d.8...........  Steady state sideslip. Use  2[deg]-10[deg] of bank;
                   50 percent rudder           4[deg]-10[deg] of
                   deflection. (Applicable     sideslip; and 2[deg]-
                   to approach and landing     10[deg] of aileron.
                   configurations.).
------------------------------------------------------------------------
6...............  FTD System Response Time
------------------------------------------------------------------------
6.a.............  Latency. Flight deck        300 milliseconds or less.
                   instrument systems
                   response to an abrupt
                   pilot controller input.
                   One test is required in
                   each axis (pitch, roll,
                   yaw).
------------------------------------------------------------------------

 Table B2C.--Alternative Data Source for FTD Level 5 Small, Multi-Engine
                        (Reciprocating) Airplane
------------------------------------------------------------------------
QPS requirement The performance parameters in this table must be used to
   program the FTD if flight test data is not used to program the FTD.
-------------------------------------------------------------------------
               Applicable test
---------------------------------------------   Authorized performance
    Entry No.         Title and procedure                range
------------------------------------------------------------------------
1. Performance
------------------------------------------------------------------------
1.c.............  Climb
------------------------------------------------------------------------
1.c.1...........  Normal climb with nominal   Climb airspeed = 95-115
                   gross weight, at best       knots.
                   rate-of-climb airspeed.    Climb rate = 500-1500 fpm
                                               (2.5-7.5 m/sec)
------------------------------------------------------------------------

1.f.............  Engines
------------------------------------------------------------------------
1.f.1...........  Acceleration; idle to       2-5 Seconds.
                   takeoff power.
------------------------------------------------------------------------
1.f.2...........  Deceleration; takeoff       2-5 Seconds.
                   power to idle.
------------------------------------------------------------------------
2. Handling Qualities
------------------------------------------------------------------------
2.c.............  Longitudinal Tests........
------------------------------------------------------------------------
2.c.1...........  Power change force........
------------------------------------------------------------------------
                  (a) Trim for straight and   10-25 lbs (2.2-6.6 daN) of
                   level flight at 80% of      force (Pull).
                   normal cruise airspeed
                   with necessary power.
                   Reduce power to flight
                   idle. Do not change trim
                   or configuration. After