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
              would respond under                   information
              the same conditions.                  regarding Latency
              Latency: The                  and Transport Delay
              FTD instrument and,                   testing may be found
              if applicable, the                    in Appendix A,
              motion system and                     Attachment 2,
              the visual system                     paragraph 14.
              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..
             An objective test is
              required..
------------------------------------------------------------------------
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.
             A subjective test is
              required..
------------------------------------------------------------------------
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..
             A subjective test is
              required..
------------------------------------------------------------------------
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..
             A subjective test is
              required..
------------------------------------------------------------------------
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.
             A subjective test is
              required..
------------------------------------------------------------------------
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.
             An objective test is
              required..
------------------------------------------------------------------------

3.f........  The FTD must provide         X
              control forces and
              control travel of
              sufficient precision
              to manually fly an
              instrument approach.
             A subjective test is
              required..
------------------------------------------------------------------------
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).
             A subjective test is
              required..
------------------------------------------------------------------------
4.b........  The FTD must have       X    X    X
              instructor controls
              that permit
              activation of
              normal, abnormal,
              and emergency
              conditions as may be
              appropriate. Once
              activated, proper
              system operation
              must result from
              system management by
              the crew and not
              require input from
              the instructor
              controls.
             A subjective test is
              required..
------------------------------------------------------------------------
5. Motion System (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 are
              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
              would respond under
              the same conditions.
             A subjective test is
              required..
------------------------------------------------------------------------
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 are
              tests and may not                     acceptable.
              exceed 300
              milliseconds.
              Instrument response
              may not occur prior
              to motion onset.
             An objective test is
              required..
------------------------------------------------------------------------
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...
             A subjective test is
              required..
------------------------------------------------------------------------
6.a.2......  The visual system       X    X    X
              must be at least a
              single channel, non-
              collimated display.
             An SOC is required...
             A subjective test is
              required..
------------------------------------------------------------------------
6.a.3......  The visual system       X    X    X
              must provide at
              least a field of
              view of 18[deg]
              vertical/24[deg]
              horizontal for the
              pilot flying.
             An SOC is required...
------------------------------------------------------------------------
6.a.4......  The visual system       X    X    X
              must provide for a
              maximum parallax of
              10[deg] per pilot.
             An SOC is required...
------------------------------------------------------------------------
6.a.5......  The visual scene        X    X    X
              content may not be
              distracting.
             An SOC is required...
             A subjective test is
              required..
------------------------------------------------------------------------

6.a.6......  The minimum 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...
             An objective test 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
------------------------------------------------------------------------
              <<>>                  <>
------------------------------------------------------------------------
                   Subjective         FTD level
             requirements In order ---------------
               to be qualified at
             the FTD qualification
              level indicated, the
              FTD must be able to
   Number     perform at least the                         Notes
             tasks associated with   4    5    6
                 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 Tasks vs. FTD Level
------------------------------------------------------------------------
                <<>>                  <>
------------------------------------------------------------------------
               Subject requirements In    FTD level
                order to be qualified  ---------------
                      at the FTD
                 qualification level
    Number     indicated, the FTD must                       Notes
                be able to perform at    4    5    6
                   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,
                                                        Surface,
                                                        Presets,
                                                        Lighting
                                                        controls.
------------------------------------------------------------------------
1.d..........  Environmental controls.   X    X    X   e.g., Temp, Wind.
------------------------------------------------------------------------
1.e..........  Airplane system           A    X    X
                malfunctions
                (Insertion/deletion).
------------------------------------------------------------------------
1.f..........  Locks, Freezes, and       X    X    X
                Repositioning.
------------------------------------------------------------------------
1.g..........  Sound Controls. (On/off/  X    X    X
                adjustment).
------------------------------------------------------------------------
1.h..........  Motion/Control Loading    A    X    X
                System, as
                appropriate. On/off/
                emergency stop.
------------------------------------------------------------------------
2. Observer Seats/Stations
------------------------------------------------------------------------
2.a..........  Position/Adjustment/      X    X    X
                Positive restraint
                system.
------------------------------------------------------------------------

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 Advisory Circulars
(AC) 25-7, as may be amended, Flight Test Guide for Certification of
Transport Category Airplanes, and (AC) 23-8, as may be amended,
Flight Test Guide for Certification of Part 23 Airplanes, for
references and examples regarding flight testing requirements and
techniques.
    d. If relevant winds are present in the objective data, the wind
vector should be clearly noted as part of the data presentation,
expressed in conventional terminology, and related to the runway
being used for the test.
    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.
    c. Certain tests included in this attachment must be supported
with a Statement of Compliance and Capability (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. 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 snapshot.
    i. For previously qualified FTDs, the tests and tolerances of
this attachment may be used in subsequent continuing qualification
evaluations for any given test if the sponsor has submitted a
proposed MQTG revision to the NSPM and has received NSPM approval.
    j. 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.
    k. Testing Computer Controlled Airplane (CCA) simulators, or
other highly augmented airplane simulators, flight test data is
required for the Normal (N) and/or Non-normal (NN) control states,
as indicated in this Attachment. Where test results are independent
of control state, Normal or Non-normal control data may be used. All
tests in Table A2A require test results in the Normal control state
unless specifically noted otherwise in the Test Details section
following the CCA designation. The NSPM will determine what tests
are appropriate for airplane simulation data. When making this
determination, the NSPM may require other levels of control state
degradation for specific airplane tests. Where Non-normal control
states are required, test data must be provided for one or more Non-
normal control states, and must include the least augmented state.
Where applicable, flight test data must record Normal and Non-normal
states for:
    (1) Pilot controller deflections or electronically generated
inputs, including location of input; and
    (2) Flight control surface positions unless test results are not
affected by, or are independent of, surface positions.
    l. 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.
    m. 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.

End QPS Requirements

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

                            Table B2A.--Flight Training Device (FTD) Objective Tests
----------------------------------------------------------------------------------------------------------------
                                             <<>>
-----------------------------------------------------------------------------------------------------------------
             Test                                                                        FTD     <>
-------------------------------                        Flight                           level  -----------------
                                   Tolerances        conditions       Test details   ----------
   Number           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 < plus-                      acceleration                required only
               Time.             minus>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  3%    Dry Runway......  Record time for         X
                                 time or < plus-                      at least 80% of
                                 minus>1 second.                     the segment
                                                                     from initiation
                                                                     of the Rejected
                                                                     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, < plus-                    or airplane
               operating.        minus>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: < plus-   Approach or       Record engine      X    X   Tt is the total
                                 minus>10% Tt,     Landing.          power (N1, N2,              time from
                                 or < plus-                           EPR, Torque,                initial
                                 minus>0.25 sec.                     Manifold                    throttle
                                Level 5: < plus-                      Pressure) from              movement to
                                 minus>1 sec.                        idle to maximum             reaching 90% of
                                                                     takeoff power               go around
                                                                     for a rapid                 power.
                                                                     (slam) throttle
                                                                     movement.
----------------------------------------------------------------------------------------------------------------
1.f.2.......  Deceleration....  Level 6: < plus-   Ground..........  Record engine      X    X   Tt is the total
                                 minus>10% Tt,                       power (N1, N2,              time from
                                 or < plus-                           EPR, Torque,                initial
                                 minus>0.25 sec.                     Manifold                    throttle
                                Level 5: < plus-                      Pressure) from              movement to
                                 minus>1 sec.                        maximum takeoff             reaching 90%
                                                                     power to idle               decay of
                                                                     for a rapid                 maximum takeoff
                                                                     (slam) throttle             power.
                                                                     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, < plus-                    uninterrupted
               Surface           minus>10% or                        control sweep
               Position          5                       to the stops.
               Calibration.      lb (2.2 daN)
                                 force, < plus-
                                 minus>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, < plus-                    qualification               qualification
                                 minus>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, < plus-                    uninterrupted
               Surface           minus>10% or                        control sweep
               Position          3                       to the stops.
               Calibration.      lb (1.3 daN)
                                 force, < plus-
                                 minus>2[deg]
                                 aileron, < plus-
                                 minus>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, < plus-                    qualification               qualification
                                 minus>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, < plus-                    uninterrupted
               Surface           minus>10% or                        control sweep
               Position          5                       to the stops.
               Calibration.      lb (2.2 daN)
                                 force, < plus-
                                 minus>27[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, < plus-                    qualification               qualification
                                 minus>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, < plus-                    uninterrupted
               Force.            minus>10% or                        control sweep
                                 3                       to the stops.
                                 lb (1.3 daN)
                                 force.
----------------------------------------------------------------------------------------------------------------
2.a.5.......  Rudder Pedal      < plus-            Ground..........  Record results          X
               Steering          minus>2[deg]                        of an
               Calibration.      nosewheel angle.                    uninterrupted
                                                                     control sweep
                                                                     to the stops.
----------------------------------------------------------------------------------------------------------------

2.a.6.......  Pitch Trim        < plus-            Ground..........                          X   The purpose of
               Indicator vs.     minus>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      < plus-            Ground..........  Requires                X
               Flight deck       minus>5[deg] of                     simultaneous
               Throttle Lever    throttle lever                      recording for
               vs. Selected      angle or < plus-                     all engines.
               Engine            minus>0.8 in (2                     The tolerances
               Parameter.        cm) for power                       apply against
                                 control without                     airplane data
                                 angular travel,                     and between
                                 or < plus-                           engines. In the
                                 minus>3% N1, or                     case of
                                 < plus-                              propeller
                                 minus>0.03 EPR,                     powered
                                 or < plus-                           airplanes, if a
                                 minus>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.
                                 force.                              Power change
                                                                     dynamics test
                                                                     as described in
                                                                     test 2.c.1 of
                                                                     Table A2A of
                                                                     this part will
                                                                     be accepted.
----------------------------------------------------------------------------------------------------------------
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.
                                 force.            approach to       Flap/Slat
                                                   landing.          change dynamics
                                                                     test as
                                                                     described in
                                                                     test 2.c.2 of
                                                                     Table A2A of
                                                                     this part will
                                                                     be accepted.
----------------------------------------------------------------------------------------------------------------
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.
                                 force.            (extension).      Gear change
                                                                     dynamics test
                                                                     as described in
                                                                     test 2.c.4 of
                                                                     Table A2A of
                                                                     this part will
                                                                     be accepted.
----------------------------------------------------------------------------------------------------------------
2.c.5.......  Longitudinal      < plus-            Cruise,           Record steady-     X    X
               Trim.             minus>0.5[deg]    Approach, and     state condition
                                 trim surface      Landing.          with wings
                                 angle < plus-                        level and
                                 minus>1[deg]                        thrust set for
                                 elevator < plus-                     level flight.
                                 minus>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.
----------------------------------------------------------------------------------------------------------------

2.c.6.......  Longitudinal      5 lb  Cruise,           Continuous time         X
               Maneuvering       (< plus-           Approach, and     history data or
               Stability         minus>2.2 daN)    Landing.          a series of
               (Stick Force/g).  or < plus-                           snapshot tests
                                 minus>10% pitch                     may be used.
                                 controller                          Record results
                                 force                               up to 30[deg]
                                 Alternative                         of bank for
                                 method: < plus-                      approach and
                                 minus>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.
----------------------------------------------------------------------------------------------------------------
2.c.7.......  Longitudinal      5 lb  Approach........  May be a series    X    X
               Static            (< plus-                             of snapshot
               Stability.        minus>2.2 daN)                      test results.
                                 or < plus-                           Record results
                                 minus>10% pitch                     for at least 2
                                 controller                          speeds above
                                 force.                              and 2 speeds
                                Alternative                          below trim
                                 method: < plus-                      speed. The
                                 minus>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.
----------------------------------------------------------------------------------------------------------------
2.c.8.......  Stall Warning     3     Second Segment    The stall          X    X
               (actuation of     kts. airspeed,    Climb, and        maneuver must
               stall warning     < plus-            Approach or       be entered with
               device.).         minus>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.
----------------------------------------------------------------------------------------------------------------
2.c.9.a.....  Phugoid Dynamics  10%   Cruise..........  The test must      X
                                 period, < plus-                      include
                                 minus>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.
----------------------------------------------------------------------------------------------------------------
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.
----------------------------------------------------------------------------------------------------------------
2.c.10......  Short Period      < plus-            Cruise..........                          X
               Dynamics.         minus>1.5[deg]
                                 pitch angle or
                                 < plus-
                                 minus>2[deg]/
                                 sec pitch rate,
                                 < plus-
                                 minus>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 < plus-         Approach or       for normal roll
                                 minus>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 < plus-         Landing.          initiation of
               Roll Controller   minus>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.).
----------------------------------------------------------------------------------------------------------------
2.d.4.a.....  Spiral Stability  Correct trend     Cruise..........  Record results          X   Airplane data
                                 and < plus-                          for both                    averaged from
                                 minus>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].
----------------------------------------------------------------------------------------------------------------
2.d.4.b.....  Spiral Stability  Correct trend...  Cruise..........                     X        Airplane data
                                                                                averaged from
                                                                                multiple tests
                                                                                in same
                                                                                direction may
                                                                                be used.
----------------------------------------------------------------------------------------------------------------
2.d.5.......  (Reserved)
----------------------------------------------------------------------------------------------------------------
2.d.6.a.....  Rudder Response.  < plus-            Approach or       A rudder step           X
                                 minus>2[deg]/     Landing.          input of 20%-
                                 sec or < plus-                       30% rudder
                                 minus>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.).
----------------------------------------------------------------------------------------------------------------
2.d.6.b.....  Rudder Response.  Roll rate < plus-  Approach or       May be roll        X
                                 minus>2[deg]/     Landing.          response to a
                                 sec, bank angle                     given rudder
                                 < plus-                              deflection.
                                 minus>3[deg].
----------------------------------------------------------------------------------------------------------------
2.d.7.......  Dutch Roll (Yaw   0.5   Cruise, and       Record results          X
               Damper OFF).      sec. or < plus-    Approach or       for at least 6
                                 minus>10% of      Landing.          complete cycles
                                 period, < plus-                      with stability
                                 minus>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.
----------------------------------------------------------------------------------------------------------------
2.d.8.......  Steady State      For given rudder  Approach or       May be a series    X    X
               Sideslip.         position < plus-   Landing.          of snapshot
                                 minus>2[deg]                        test results.
                                 bank angle,                         Propeller
                                 < plus-                              driven
                                 minus>1[deg]                        airplanes must
                                 sideslip angle,                     test in each
                                 10%                     direction.
                                 or < plus-                           Sideslip angle
                                 minus>2[deg]                        is matched only
                                 aileron, < plus-                     for
                                 minus>10% or                        repeatability
                                 < plus-                              and only on
                                 minus>5[deg]                        continuing
                                 spoiler or                          qualification
                                 equivalent                          evaluations.
                                 roll,
                                 controller
                                 position or
                                 force.
----------------------------------------------------------------------------------------------------------------
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.  ................  ................  ................            If Transport
                                                                                Delay is the
                                                                                chosen method
                                                                                to demonstrate
                                                                                relative
                                                                                responses, the
                                                                                sponsor and the
                                                                                NSPM will use
                                                                                the latency
                                                                                values to
                                                                                ensure proper
                                                                                simulator
                                                                                response when
                                                                                reviewing those
                                                                                existing tests
                                                                                where latency
                                                                                can be
                                                                                identified
                                                                                (e.g., short
                                                                                period, roll
                                                                                response,
                                                                                rudder
                                                                                response).

¤¤¤¤¤¤¤¤¤¤¤¤¤
----------------------------------------------------------------------------------------------------------------

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

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 3.
     Motion System, paragraph 5.
     Sound System, paragraph 6.
     Engineering Simulator Validation Data, paragraph 8.
     Approval Guidelines for Engineering Simulator
Validation Data, paragraph 9.
     Validation Test Tolerances, paragraph 10.
     Validation Data Road Map, paragraph 11.
     Acceptance Guidelines for Alternative Engines Data,
paragraph 12.
     Acceptance Guidelines for Alternative Avionics,
paragraph 13.
     Transport Delay Testing, paragraph 14.
     Continuing Qualification Evaluation Validation Data
Presentation, paragraph 15.

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 that 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 recurrent 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 FAA Advisory Circulars (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
------------------------------------------------------------------------
 <<>>  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
     Number           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; < plus-
                                               minus>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)......  Must have a roll rate of
                                               4[deg]-25[deg]/second.
                  Roll rate must be measured
                   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..........  Initial bank angle (< plus-
                                               minus>5[deg]) after 20
                                               seconds.
                  Cruise configuration and
                   normal cruise airspeed.
                   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...........  2[deg]-6[deg]/second yaw
                                               rate.
                  Use 25 percent of maximum
                   rudder 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.....  2[deg]-10[deg] of bank;
                                               4[deg]-10[deg] of
                                               sideslip; and
                  Use 50 percent rudder       2[deg]-10[deg] of aileron.
                   deflection. (Applicable
                   to approach and landing
                   configurations.)
------------------------------------------------------------------------
6. FTD System Response Time
------------------------------------------------------------------------
6.a.............  Latency...................  300 milliseconds or less.
                  Flight deck 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
------------------------------------------------------------------------
 <<>>  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
     Number           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
                   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.4...........  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.  60-90 knots; < plus-
                                               minus>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.............  Must have a roll rate of
                  Roll rate must be measured   4[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..........  Initial bank angle (< plus-
                  Cruise configuration and     minus>5[deg]) after 20
                   normal 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...........  3[deg]-6[deg]/second yaw
                  Use 25 percent of maximum    rate.
                   rudder 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.....  2[deg]-10[deg] of bank; 4-
                  Use 50 percent rudder        10 degrees of sideslip;
                   deflection. (Applicable     and 2[deg]-10[deg] of
                   to approach and landing     aileron.
                   configurations.).
------------------------------------------------------------------------
6. FTD System Response Time
------------------------------------------------------------------------
6.a.............  Flight deck instrument      300 milliseconds or less.
                   systems response to an
                   abrupt pilot controller
                   input. One test is
                   required in each axis
                   (pitch, roll, yaw).
------------------------------------------------------------------------

Table B2D.--Alternative Data Source for FTD Level 5 Small, Single Engine
                       (Turbo-Propeller) Airplane
------------------------------------------------------------------------
 <<>> The performance parameters in this table must be
 used to program the FTD in flight test data is not used to program the
                                  FTD.
-------------------------------------------------------------------------
               Applicable test
---------------------------------------------   Authorized performance
     Number           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 = 800-1800 fpm
                                               (4-9 m/sec).
------------------------------------------------------------------------
1.f.............  Engines
------------------------------------------------------------------------
1.f.1...........  Acceleration; idle to       4-8 Seconds.
                   takeoff power.
------------------------------------------------------------------------
1.f.2...........  Deceleration; takeoff       3-7 Seconds.
                   power to idle.
------------------------------------------------------------------------
2. Handling Qualities
------------------------------------------------------------------------
2.c.............  Longitudinal Tests
------------------------------------------------------------------------
2.c.1...........  Power change force
------------------------------------------------------------------------
                  (a) Trim for straight and   8 lbs (3.5 daN) of Push
                   level flight at 80% of      force--8 lbs (3.5 daN) of
                   normal cruise airspeed      Pull force.
                   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   12-22 lbs (5.3-9.7 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.b.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.  60-90 knots; < plus-
                                               minus>5[deg] of bank.
------------------------------------------------------------------------
                  (b) Clean configuration...  Landing configuration
                                               speed + 10-20%.
------------------------------------------------------------------------
2.c.8.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.............  Must have a roll rate of
                  Roll rate must be measured   4[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..........  Initial bank angle (< plus-
                  Cruise configuration and     minus>5[deg]) after 20
                   normal 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...........  3[deg]-6[deg]/second yaw
                  Use 25 percent of maximum    rate.
                   rudder 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\-3 cycles.
                   cruise and approach
                   configurations.).
------------------------------------------------------------------------
2.d.8...........  Steady state sideslip.....  2[deg]-10[deg] of bank;
                  Use 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.............  Flight deck instrument      300 milliseconds or less.
                   systems response to an
                   abrupt pilot controller
                   input. One test is
                   required in each axis
                   (pitch, roll, yaw).
------------------------------------------------------------------------

Table B2E.--Alternative Data Source for FTD Level 5 Multi-Engine (Turbo-
                           Propeller) Airplane
------------------------------------------------------------------------
 <<>> The performance parameters in this table must be
 used to program the FTD in flight test data is not used to program the
                                  FTD.
-------------------------------------------------------------------------
               Applicable test
---------------------------------------------   Authorized performance
     Number           Title and procedure                range
------------------------------------------------------------------------
1. Performance
------------------------------------------------------------------------
1.c.............  Climb.....................
------------------------------------------------------------------------
1.b.1...........  Normal climb with nominal   Climb airspeed = 120-140
                   gross weight, at best       knots.
                   rate-of-climb airspeed.    Climb rate = 1000-3000 fpm
                                               (5-15 m/sec)
------------------------------------------------------------------------
1.f.............  Engines
------------------------------------------------------------------------
1.f.1...........  Acceleration; idle to       2-6 Seconds.
                   takeoff power.
------------------------------------------------------------------------
1.f.2...........  Deceleration; takeoff       1-5 Seconds.
                   power to idle.
------------------------------------------------------------------------
2. Handling Qualities
------------------------------------------------------------------------
2.c.............  Longitudinal Tests
------------------------------------------------------------------------
2.c.1...........  Power change force
------------------------------------------------------------------------
                  (a) Trim for straight and   8 lbs (3.5 daN) of Push
                   level flight at 80% of      force to 8 lbs (3.5 daN)
                   normal cruise airspeed      of Pull force.
                   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   12-22 lbs (5.3-9.7 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