flight simulator data requirements, in advance with the NSPM.
    (5) A matrix or ``roadmap'' should be provided with the QTG
indicating the appropriate validation data source for each test. The
roadmap should include identification of the revision state of those
contributory avionics systems that could affect specific test
responses if changed.

15. Transport Delay Testing

    a. This paragraph explains how to determine the introduced
transport delay through the flight simulator system so that it does
not exceed a specific time delay. The transport delay should be
measured from control inputs through the interface, through each of
the host computer modules and back through the interface to motion,
flight instrument, and visual systems. The transport delay should
not exceed the maximum allowable interval.
    b. Four specific examples of transport delay are:
    (1) Simulation of classic non-computer controlled aircraft;
    (2) Simulation of computer controlled aircraft using real
airplane black boxes;
    (3) Simulation of computer controlled aircraft using software
emulation of airplane boxes;
    (4) Simulation using software avionics or re-hosted instruments.
    c. Figure A2C illustrates the total transport delay for a non-
computer-controlled airplane or the classic transport delay test.
Since there are no airplane-induced delays for this case, the total
transport delay is equivalent to the introduced delay.
    d. Figure A2D illustrates the transport delay testing method
using the real airplane controller system.
    e. To obtain the induced transport delay for the motion,
instrument and visual signal, the delay induced by the airplane
controller should be subtracted from the total transport delay. This
difference represents the introduced delay and should not exceed the
standards prescribed in Table A1A.
    f. Introduced transport delay is measured from the flight deck
control input to the reaction of the instruments and motion and
visual systems (See Figure A2C).
    g. The control input may also be introduced after the airplane
controller system and the introduced transport delay measured
directly from the control input to the reaction of the instruments,
and simulator motion and visual systems (See Figure A2D).
    h. Figure A2E illustrates the transport delay testing method
used on a flight simulator that uses a software emulated airplane
controller system.
    i. It is not possible to measure the introduced transport delay
using the simulated airplane controller system architecture for the
pitch, roll and yaw axes. Therefore, the signal should be measured
directly from the pilot controller. The flight simulator
manufacturer should measure the total transport delay and subtract
the inherent delay of the actual airplane components because the
real airplane controller system has an inherent delay provided by
the airplane manufacturer. The flight simulator manufacturer should
ensure that the introduced delay does not exceed the standards
prescribed in Table A1A.
    j. Special measurements for instrument signals for flight
simulators using a real airplane instrument display system instead
of a simulated or re-hosted display. For flight instrument systems,
the total transport delay should be measured and the inherent delay
of the actual airplane components subtracted to ensure that the
introduced delay does not exceed the standards prescribed in Table
A1A.
    (1) Figure A2FA illustrates the transport delay procedure
without airplane display simulation. The introduced delay consists
of the delay between the control movement and the instrument change
on the data bus.
    (2) Figure A2FB illustrates the modified testing method required
to measure introduced delay due to software avionics or re-hosted
instruments. The total simulated instrument transport delay is
measured and the airplane delay should be subtracted from this
total. This difference represents the introduced delay and should
not exceed the standards prescribed in Table A1A. The inherent delay
of the airplane between the data bus and the displays is indicated
in figure A2FA. The display manufacturer should provide this delay
time.
    k. Recorded signals. The signals recorded to conduct the
transport delay calculations should be explained on a schematic
block diagram. The flight simulator manufacturer should also provide
an explanation of why each signal was selected and how they relate
to the above descriptions.
    l. Interpretation of results. Flight simulator results vary over
time from test to test due to ``sampling uncertainty.'' All flight
simulators run at a specific rate where all modules are executed
sequentially in the host computer. The flight controls input can
occur at any time in the iteration, but these data will not be
processed before the start of the new iteration. For example, a
flight simulator running at 60 Hz may have a difference of as much
as 16.67 msec between

test results. This does not mean that the test has failed. Instead,
the difference is attributed to variations in input processing. In
some conditions, the host simulator and the visual system do not run
at the same iteration rate, so the output of the host computer to
the visual system will not always be synchronized.
    m. The transport delay test should account for both daylight and
night modes of operation of the visual system. In both cases, the
tolerances prescribed in Table A1A must be met and the motion
response should occur before the end of the first video scan
containing new information.
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BILLING CODE 4910-13-C.
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Begin Information

16. Continuing Qualification Evaluations--Validation Test Data
Presentation

a. Background

    (1) The MQTG is created during the initial evaluation of a
flight simulator. This is the master document, as amended, to which
flight simulator continuing qualification evaluation test results
are compared.
    (2) The currently accepted method of presenting continuing
qualification evaluation test results is to provide flight simulator
results over-plotted with reference data. Test results are carefully
reviewed to determine if the test is within the specified
tolerances. This can be a time consuming process, particularly when
reference data exhibits rapid variations or an apparent anomaly
requiring engineering judgment in the application of the tolerances.
In these cases, the solution is to compare the results to the MQTG.
The continuing qualification results are compared to the results in
the MQTG for acceptance. The flight simulator operator and the NSPM
should look for any change in the flight simulator performance since
initial qualification.

b. Continuing Qualification Evaluation Test Results Presentation

    (1) Flight simulator operators are encouraged to over-plot
continuing qualification validation test results with MQTG flight
simulator results recorded during the initial evaluation and as
amended. Any change in a validation test will be readily apparent.
In addition to plotting continuing qualification validation test and
MQTG results, operators may elect to plot reference data as well.
    (2) There are no suggested tolerances between flight simulator
continuing qualification and MQTG validation test results.
Investigation of any discrepancy between the MQTG and continuing
qualification flight simulator performance is left to the discretion
of the flight simulator operator and the NSPM.
    (3) Differences between the two sets of results, other than
variations attributable to repeatability issues that cannot be
explained, should be investigated.
    (4) The flight simulator should retain the ability to over-plot
both automatic and manual validation test results with reference
data.

End Information

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

Begin QPS Requirements

17. Alternative Data Sources, Procedures, and Instrumentation: Level A
and Level B Simulators Only

    a. Sponsors are not required to use the alternative data
sources, procedures, and instrumentation. However, a sponsor may
choose to use one or more of the alternative sources, procedures,
and instrumentation described in Table A2E.

End QPS Requirements

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

Begin Information

    b. It has become standard practice for experienced simulator
manufacturers to use modeling techniques to establish data bases for
new simulator configurations while awaiting the availability of
actual flight test data. The data generated from the aerodynamic
modeling techniques is then compared to the flight test data when it
becomes available. The results of such comparisons have become
increasingly consistent, indicating that these techniques, applied
with the appropriate experience, are dependable and accurate for the
development of aerodynamic models for use in Level A and Level B
simulators.
    c. Based on this history of successful comparisons, the NSPM has
concluded that those who are experienced in the development of
aerodynamic models may use modeling techniques to alter the method
for acquiring flight test data for Level A or Level B simulators.
    d. The information in Table A2E (Alternative Data Sources,
Procedures, and Instrumentation) is presented to describe an
acceptable alternative to data sources for simulator modeling and
validation and an acceptable alternative to the procedures and
instrumentation traditionally used to gather such modeling and
validation data.
    (1) Alternative data sources that may be used for part or all of
a data requirement are the Airplane Maintenance Manual, the Airplane
Flight Manual (AFM), Airplane Design Data, the Type Inspection
Report (TIR), Certification Data or acceptable supplemental flight
test data.
    (2) The sponsor should coordinate with the NSPM prior to using
alternative data sources in a flight test or data gathering effort.
    e. The NSPM position regarding the use of these alternative data
sources, procedures, and instrumentation is based on the following
presumptions:
    (1) Data gathered through the alternative means does not require
angle of attack (AOA) measurements or control surface position
measurements for any flight test. However, AOA can be sufficiently
derived if the flight test program ensures the collection of
acceptable level, unaccelerated, trimmed flight data. All of the
simulator time history tests that begin in level, unaccelerated, and
trimmed flight, including the three basic trim tests and ``fly-by''
trims, can be a successful validation of angle of attack by
comparison with flight test pitch angle. (Note: Due to the
criticality of angle of attack in the development of the ground
effects model, particularly critical for normal landings and
landings involving cross-control input applicable to Level B
simulators, stable ``fly-by'' trim data will be the acceptable norm
for normal and cross-control input landing objective data for these
applications.)
    (2) The use of a rigorously defined and fully mature simulation
controls system model that includes accurate gearing and cable
stretch characteristics (where applicable), determined from actual
aircraft measurements. Such a model does not require control surface
position measurements in the flight test objective data in these
limited applications.
    f. The sponsor is urged to contact the NSPM for clarification of
any issue regarding airplanes with reversible control systems. Table
A2E is not applicable to Computer Controlled Aircraft FFSs.
    g. Utilization of these alternate data sources, procedures, and
instrumentation (Table A2E) does not relieve the sponsor from
compliance with the balance of the information contained in this
document relative to Level A or Level B FFSs.
    h. The term ``inertial measurement system'' is used in the
following table to include the use of a functional global
positioning system (GPS).
    i. Synchronized video for the use of alternative data sources,
procedures, and instrumentation should have:
    (1) Sufficient resolution to allow magnification of the display
to make appropriate measurement and comparisons; and
    (2) Sufficient size and incremental marking to allow similar
measurement and comparison. The detail provided by the video should
provide sufficient clarity and accuracy to measure the necessary
parameter(s) to at least \1/2\ of the tolerance authorized for the
specific test being conducted and allow an integration of the
parameter(s) in question to obtain a rate of change.

End Information

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

                      Table A2E.--Alternative Data Sources, Procedures, and Instrumentation
----------------------------------------------------------------------------------------------------------------
    QPS REQUIREMENTS The standards in this table are required if the data gathering            Information
             methods described in paragraph 9 of  Appendix A are not used.             -------------------------
---------------------------------------------------------------------------------------
       Table of objective tests            Sim level       Alternative data sources,
--------------------------------------------------------        procedures, and                   Notes
     Test entry number and title          A        B            instrumentation
----------------------------------------------------------------------------------------------------------------
1.a.1. Performance. Taxi. Minimum           X        X   TIR, AFM, or Design data may   ........................
 Radius turn.                                             be used.
----------------------------------------------------------------------------------------------------------------
1.a.2. Performance. Taxi Rate of Turn                X   Data may be acquired by using  A single procedure may
 vs. Nosewheel Steering Angle.                            a constant tiller position,    not be adequate for all
                                                          measured with a protractor     airplane steering
                                                          or full rudder pedal           systems, therefore
                                                          application for steady state   appropriate measurement
                                                          turn, and synchronized video   procedures must be
                                                          of heading indicator. If       devised and proposed
                                                          less than full rudder pedal    for NSPM concurrence.
                                                          is used, pedal position must
                                                          be recorded.
----------------------------------------------------------------------------------------------------------------
1.b.1. Performance. Takeoff. Ground         X        X   Preliminary certification      ........................
 Acceleration Time and Distance.                          data may be used. Data may
                                                          be acquired by using a stop
                                                          watch, calibrated airspeed,
                                                          and runway markers during a
                                                          takeoff with power set
                                                          before brake release. Power
                                                          settings may be hand
                                                          recorded. If an inertial
                                                          measurement system is
                                                          installed, speed and
                                                          distance may be derived from
                                                          acceleration measurements.
----------------------------------------------------------------------------------------------------------------
1.b.2. Performance. Takeoff. Minimum        X        X   Data may be acquired by using  Rapid throttle
 Control Speed--ground (Vmcg) using                       an inertial measurement        reductions at speeds
 aerodynamic controls only (per                           system and a synchronized      near Vmcg may be used
 applicable airworthiness standard)                       video of calibrated airplane   while recording
 or low speed, engine inoperative                         instruments and force/         appropriate parameters.
 ground control characteristics.                          position measurements of       The nosewheel must be
                                                          flight deck controls.          free to caster, or
                                                                                equivalently freed of
                                                                                sideforce generation.
----------------------------------------------------------------------------------------------------------------

1.b.3. Performance. Takeoff. Minimum        X        X   Data may be acquired by using  ........................
 Unstick Speed (Vmu) or equivalent                        an inertial measurement
 test to demonstrate early rotation                       system and a synchronized
 takeoff characteristics.                                 video of calibrated airplane
                                                          instruments and the force/
                                                          position measurements of
                                                          flight deck controls.
----------------------------------------------------------------------------------------------------------------
1.b.4. Performance. Takeoff. Normal         X        X   Data may be acquired by using  ........................
 Takeoff.                                                 an inertial measurement
                                                          system and a synchronized
                                                          video of calibrated airplane
                                                          instruments and force/
                                                          position measurements of
                                                          flight deck controls. AOA
                                                          can be calculated from pitch
                                                          attitude and flight path.
----------------------------------------------------------------------------------------------------------------
1.b.5. Performance. Takeoff. Critical       X        X   Data may be acquired by using  Record airplane dynamic
 Engine Failure during Takeoff.                           an inertial measurement        response to engine
                                                          system and a synchronized      failure and control
                                                          video of calibrated airplane   inputs required to
                                                          instruments and force/         correct flight path.
                                                          position measurements of
                                                          flight deck controls.
----------------------------------------------------------------------------------------------------------------
1.b.6. Performance. Takeoff.                X        X   Data may be acquired by using  The ``1:7 law'' to 100
 Crosswind Takeoff.                                       an inertial measurement        feet (30 meters) is an
                                                          system and a synchronized      acceptable wind
                                                          video of calibrated airplane   profile.
                                                          instruments and force/
                                                          position measurements of
                                                          flight deck controls.
----------------------------------------------------------------------------------------------------------------
1.b.7. Performance. Takeoff. Rejected       X        X   Data may be acquired with a    ........................
 Takeoff.                                                 synchronized video of
                                                          calibrated airplane
                                                          instruments, thrust lever
                                                          position, engine parameters,
                                                          and distance (e.g., runway
                                                          markers). A stop watch is
                                                          required..
----------------------------------------------------------------------------------------------------------------
1.c. 1. Performance. Climb. Normal          X        X   Data may be acquired with a    ........................
 Climb all engines operating..                            synchronized video of
                                                          calibrated airplane
                                                          instruments and engine power
                                                          throughout the climb range.
----------------------------------------------------------------------------------------------------------------
1.c.2. Performance. Climb. One engine       X        X   Data may be acquired with a    ........................
 Inoperative Climb.                                       synchronized video of
                                                          calibrated airplane
                                                          instruments and engine power
                                                          throughout the climb range.
----------------------------------------------------------------------------------------------------------------
1.c.4. Performance. Climb. One Engine       X        X   Data may be acquired with a    ........................
 Inoperative Approach Climb (if                           synchronized video of
 operations in icing conditions are                       calibrated airplane
 authorized).                                             instruments and engine power
                                                          throughout the climb range.
----------------------------------------------------------------------------------------------------------------
1.d.1. Cruise/Descent. Level flight         X        X   Data may be acquired with a    ........................
 acceleration..                                           synchronized video of
                                                          calibrated airplane
                                                          instruments, thrust lever
                                                          position, engine parameters,
                                                          and elapsed time.
----------------------------------------------------------------------------------------------------------------
1.d.2. Cruise/Descent. Level flight         X        X   Data may be acquired with a    ........................
 deceleration..                                           synchronized video of
                                                          calibrated airplane
                                                          instruments, thrust lever
                                                          position, engine parameters,
                                                          and elapsed time.
1.d.4. Cruise/Descent. Idle descent..       X        X   Data may be acquired with a    ........................
                                                          synchronized video of
                                                          calibrated airplane
                                                          instruments, thrust lever
                                                          position, engine parameters,
                                                          and elapsed time.
----------------------------------------------------------------------------------------------------------------
1.d.5. Cruise/Descent. Emergency            X        X   Data may be acquired with a    ........................
 Descent.                                                 synchronized video of
                                                          calibrated airplane
                                                          instruments, thrust lever
                                                          position, engine parameters,
                                                          and elapsed time.
----------------------------------------------------------------------------------------------------------------
1.e.1. Performance. Stopping.               X        X   Data may be acquired during    ........................
 Deceleration time and distance,                          landing tests using a stop
 using manual application of wheel                        watch, runway markers, and a
 brakes and no reverse thrust on a                        synchronized video of
 dry runway.                                              calibrated airplane
                                                          instruments, thrust lever
                                                          position and the pertinent
                                                          parameters of engine power.
----------------------------------------------------------------------------------------------------------------

1.e.2. Performance. Ground.                 X        X   Data may be acquired during
 Deceleration Time and Distance,                          landing tests using a stop
 using reverse thrust and no wheel                        watch, runway markers, and a
 brakes.                                                  synchronized video of
                                                          calibrated airplane
                                                          instruments, thrust lever
                                                          position and pertinent
                                                          parameters of engine power.
----------------------------------------------------------------------------------------------------------------
1.f.1. Performance. Engines.                X        X   Data may be acquired with a    ........................
 Acceleration.                                            synchronized video recording
                                                          of engine instruments and
                                                          throttle position.
----------------------------------------------------------------------------------------------------------------
1.f.2. Performance. Engines.                X        X   Data may be acquired with a    ........................
 Deceleration.                                            synchronized video recording
                                                          of engine instruments and
                                                          throttle position.
----------------------------------------------------------------------------------------------------------------
2.a.1.a. Handling Qualities. Static         X        X   Surface position data may be   For airplanes with
 Control Checks. Pitch Controller                         acquired from flight data      reversible control
 Position vs. Force and Surface                           recorder (FDR) sensor or, if   systems, surface
 Position Calibration.                                    no FDR sensor, at selected,    position data
                                                          significant column positions   acquisition should be
                                                          (encompassing significant      accomplished with winds
                                                          column position data           less than 5 kts.
                                                          points), acceptable to the
                                                          NSPM, using a control
                                                          surface protractor on the
                                                          ground. Force data may be
                                                          acquired by using a hand
                                                          held force gauge at the same
                                                          column position data points.
----------------------------------------------------------------------------------------------------------------
2.a.2.a. Handling Qualities. Static         X        X   Surface position data may be   For airplanes with
 Control Checks. Roll Controller                          acquired from flight data      reversible control
 Position vs. Force and Surface                           recorder (FDR) sensor or, if   systems, surface
 Position Calibration.                                    no FDR sensor, at selected,    position data
                                                          significant wheel positions    acquisition should be
                                                          (encompassing significant      accomplished with winds
                                                          wheel position data points),   less than 5 kts.
                                                          acceptable to the NSPM,
                                                          using a control surface
                                                          protractor on the ground.
                                                          Force data may be acquired
                                                          by using a hand held force
                                                          gauge at the same wheel
                                                          position data points.
----------------------------------------------------------------------------------------------------------------
2.a.3.a. Handling Qualities. Static         X        X   Surface position data may be   For airplanes with
 Control Checks. Rudder Pedal                             acquired from flight data      reversible control
 Position vs. Force and Surface                           recorder (FDR) sensor or, if   systems, surface
 Position Calibration.                                    no FDR sensor, at selected,    position data
                                                          significant rudder pedal       acquisition should be
                                                          positions (encompassing        accomplished with winds
                                                          significant rudder pedal       less than 5 kts.
                                                          position data points),
                                                          acceptable to the NSPM,
                                                          using a control surface
                                                          protractor on the ground.
                                                          Force data may be acquired
                                                          by using a hand held force
                                                          gauge at the same rudder
                                                          pedal position data points.
----------------------------------------------------------------------------------------------------------------
2.a.4. Handling Qualities. Static           X        X   Breakout data may be acquired  ........................
 Control Checks. Nosewheel Steering                       with a hand held force
 Controller Force and Position.                           gauge. The remainder of the
                                                          force to the stops may be
                                                          calculated if the force
                                                          gauge and a protractor are
                                                          used to measure force after
                                                          breakout for at least 25% of
                                                          the total displacement
                                                          capability.
----------------------------------------------------------------------------------------------------------------
2.a.5. Handling Qualities. Static           X        X   Data may be acquired through   ........................
 Control Checks. Rudder Pedal                             the use of force pads on the
 Steering Calibration.                                    rudder pedals and a pedal
                                                          position measurement device,
                                                          together with design data
                                                          for nosewheel position.
----------------------------------------------------------------------------------------------------------------
2.a.6. Handling Qualities. Static           X        X   Data may be acquired through   ........................
 Control Checks. Pitch Trim Indicator                     calculations.
 vs. Surface Position Calibration.
----------------------------------------------------------------------------------------------------------------
2.a.7. Handling qualities. Static           X        X   Data may be acquired by using  ........................
 control tests. Pitch trim rate.                          a synchronized video of
                                                          pitch trim indication and
                                                          elapsed time through range
                                                          of trim indication.
----------------------------------------------------------------------------------------------------------------

2.a.8. Handling Qualities. Static           X        X   Data may be acquired through   ........................
 Control tests. Alignment of Flight                       the use of a temporary
 deck Throttle Lever Angle vs.                            throttle quadrant scale to
 Selected engine parameter.                               document throttle position.
                                                          Use a synchronized video to
                                                          record steady state
                                                          instrument readings or hand-
                                                          record steady state engine
                                                          performance readings.
----------------------------------------------------------------------------------------------------------------
2.a.9. Handling qualities. Static           X        X   Use of design or predicted     ........................
 control tests. Brake pedal position                      data is acceptable. Data may
 vs. force and brake system pressure                      be acquired by measuring
 calibration.                                             deflection at ``zero'' and
                                                          ``maximum'' and calculating
                                                          deflections between the
                                                          extremes using the airplane
                                                          design data curve.
----------------------------------------------------------------------------------------------------------------
2.c.1. Handling qualities.                  X        X   Data may be acquired by using  ........................
 Longitudinal control tests. Power                        an inertial measurement
 change dynamics.                                         system and a synchronized
                                                          video of calibrated airplane
                                                          instruments and throttle
                                                          position.
----------------------------------------------------------------------------------------------------------------
2.c.2. Handling qualities.                  X        X   Data may be acquired by using  ........................
 Longitudinal control tests. Flap/                        an inertial measurement
 slat change dynamics.                                    system and a synchronized
                                                          video of calibrated airplane
                                                          instruments and flap/slat
                                                          position.
----------------------------------------------------------------------------------------------------------------
2.c.3. Handling qualities.                  X        X   Data may be acquired by using  ........................
 Longitudinal control tests. Spoiler/                     an inertial measurement
 speedbrake change dynamics.                              system and a synchronized
                                                          video of calibrated airplane
                                                          instruments and spoiler/
                                                          speedbrake position.
----------------------------------------------------------------------------------------------------------------
2.c.4. Handling qualities.                  X        X   Data may be acquired by using  ........................
 Longitudinal control tests. Gear                         an inertial measurement
 change dynamics.                                         system and a synchronized
                                                          video of calibrated airplane
                                                          instruments and gear
                                                          position.
----------------------------------------------------------------------------------------------------------------
2.c.5. Handling qualities.                  X        X   Data may be acquired through   ........................
 Longitudinal control tests.                              use of an inertial
 Longitudinal trim.                                       measurement system and a
                                                          synchronized video of flight
                                                          deck controls position
                                                          (previously calibrated to
                                                          show related surface
                                                          position) and the engine
                                                          instrument readings.
----------------------------------------------------------------------------------------------------------------
2.c.6. Handling qualities.                  X        X   Data may be acquired through   ........................
 Longitudinal control tests.                              the use of an inertial
 Longitudinal maneuvering stability                       measurement system and a
 (stick force/g).                                         synchronized video of
                                                          calibrated airplane
                                                          instruments; a temporary,
                                                          high resolution bank angle
                                                          scale affixed to the
                                                          attitude indicator; and a
                                                          wheel and column force
                                                          measurement indication.
----------------------------------------------------------------------------------------------------------------
2.c.7. Handling qualities.                  X        X   Data may be acquired through   ........................
 Longitudinal control tests.                              the use of a synchronized
 Longitudinal static stability.                           video of airplane flight
                                                          instruments and a hand held
                                                          force gauge.
----------------------------------------------------------------------------------------------------------------
2.c.8. Handling qualities.                  X        X   Data may be acquired through   Airspeeds may be cross
 Longitudinal control tests. Stall                        a synchronized video           checked with those in
 characteristics.                                         recording of a stop watch      the TIR and AFM.
                                                          and calibrated airplane
                                                          airspeed indicator. Hand-
                                                          record the flight conditions
                                                          and airplane configuration.
----------------------------------------------------------------------------------------------------------------
2.c.9. Handling qualities.                  X        X   Data may be acquired by using  ........................
 Longitudinal control tests. Phugoid                      an inertial measurement
 dynamics.                                                system and a synchronized
                                                          video of calibrated airplane
                                                          instruments and force/
                                                          position measurements of
                                                          flight deck controls.
----------------------------------------------------------------------------------------------------------------
2.c.10. Handling qualities.                          X   Data may be acquired by using  ........................
 Longitudinal control tests. Short                        an inertial measurement
 period dynamics.                                         system and a synchronized
                                                          video of calibrated airplane
                                                          instruments and force/
                                                          position measurements of
                                                          flight deck controls.
----------------------------------------------------------------------------------------------------------------

2.d.1. Handling qualities. Lateral          X        X   Data may be acquired by using  ........................
 directional tests. Minimum control                       an inertial measurement
 speed, air (Vmca or Vmci), per                           system and a synchronized
 applicable airworthiness standard or                     video of calibrated airplane
 Low speed engine inoperative                             instruments and force/
 handling characteristics in the air.                     position measurements of
                                                          flight deck controls.
----------------------------------------------------------------------------------------------------------------
2.d.2. Handling qualities. Lateral          X        X   Data may be acquired by using  May be combined with
 directional tests. Roll response                         an inertial measurement        step input of flight
 (rate).                                                  system and a synchronized      deck roll controller
                                                          video of calibrated airplane   test, 2.d.3.
                                                          instruments and force/
                                                          position measurements of
                                                          flight deck lateral controls.
----------------------------------------------------------------------------------------------------------------
2.d.3. Handling qualities. Lateral          X        X   Data may be acquired by using  ........................
 directional tests. Roll response to                      an inertial measurement
 flight deck roll controller step                         system and a synchronized
 input.                                                   video of calibrated airplane
                                                          instruments and force/
                                                          position measurements of
                                                          flight deck lateral controls.
----------------------------------------------------------------------------------------------------------------
2.d.4. Handling qualities. Lateral          X        X   Data may be acquired by using  ........................
 directional tests. Spiral stability.                     an inertial measurement
                                                          system and a synchronized
                                                          video of calibrated airplane
                                                          instruments; force/position
                                                          measurements of flight deck
                                                          controls; and a stop watch.
----------------------------------------------------------------------------------------------------------------
2.d.5. Handling qualities. Lateral          X        X   Data may be hand recorded in-  Trimming during second
 directional tests. Engine                                flight using high resolution   segment climb is not a
 inoperative trim.                                        scales affixed to trim         certification task and
                                                          controls that have been        should not be conducted
                                                          calibrated on the ground       until a safe altitude
                                                          using protractors on the       is reached.
                                                          control/trim surfaces with
                                                          winds less than 5 kts.OR
                                                          Data may be acquired during
                                                          second segment climb (with
                                                          proper pilot control input
                                                          for an engine-out condition)
                                                          by using a synchronized
                                                          video of calibrated airplane
                                                          instruments and force/
                                                          position measurements of
                                                          flight deck controls.
----------------------------------------------------------------------------------------------------------------
2.d.6. Handling qualities. Lateral          X        X   Data may be acquired by using  ........................
 directional tests. Rudder response.                      an inertial measurement
                                                          system and a synchronized
                                                          video of calibrated airplane
                                                          instruments and force/
                                                          position measurements of
                                                          rudder pedals.
----------------------------------------------------------------------------------------------------------------
2.d.7. Handling qualities. Lateral          X        X   Data may be acquired by using  ........................
 directional tests. Dutch roll, (yaw                      an inertial measurement
 damper OFF).                                             system and a synchronized
                                                          video of calibrated airplane
                                                          instruments and force/
                                                          position measurements of
                                                          flight deck controls.
----------------------------------------------------------------------------------------------------------------
2.d.8. Handling qualities. Lateral          X        X   Data may be acquired by using
 directional tests. Steady state                          an inertial measurement
 sideslip.                                                system and a synchronized
                                                          video of calibrated airplane
                                                          instruments and force/
                                                          position measurements of
                                                          flight deck controls.
                                                         Ground track and wind
                                                          corrected heading may be
                                                          used for sideslip angle..
----------------------------------------------------------------------------------------------------------------
2.e.1. Handling qualities. Landings.                 X   Data may be acquired by using  ........................
 Normal landing.                                          an inertial measurement
                                                          system and a synchronized
                                                          video of calibrated airplane
                                                          instruments and force/
                                                          position measurements of
                                                          flight deck controls.
----------------------------------------------------------------------------------------------------------------
2.e.3. Handling qualities. Landings.                 X   Data may be acquired by using  ........................
 Crosswind landing.                                       an inertial measurement
                                                          system and a synchronized
                                                          video of calibrated airplane
                                                          instruments and force/
                                                          position measurements of
                                                          flight deck controls.
----------------------------------------------------------------------------------------------------------------

2.e.4. Handling qualities. Landings.                 X   Data may be acquired by using  ........................
 One engine inoperative landing.                          an inertial measurement
                                                          system and a synchronized
                                                          video of calibrated airplane
                                                          instruments and the force/
                                                          position measurements of
                                                          flight deck controls. Normal
                                                          and lateral accelerations
                                                          may be recorded in lieu of
                                                          AOA and sideslip.
----------------------------------------------------------------------------------------------------------------
2.e.5. Handling qualities. Landings.   .......       X   Data may be acquired by using  ........................
 Autopilot landing (if applicable).                       an inertial measurement
                                                          system and a synchronized
                                                          video of calibrated airplane
                                                          instruments and force/
                                                          position measurements of
                                                          flight deck controls.Normal
                                                          and lateral accelerations
                                                          may be recorded in lieu of
                                                          AOA and sideslip.
----------------------------------------------------------------------------------------------------------------
2.e.6. Handling qualities. Landings.   .......       X   Data may be acquired by using  ........................
 All engines operating, autopilot, go                     an inertial measurement
 around.                                                  system and a synchronized
                                                          video of calibrated airplane
                                                          instruments and force/
                                                          position measurements of
                                                          flight deck controls. Normal
                                                          and lateral accelerations
                                                          may be recorded in lieu of
                                                          AOA and sideslip.
----------------------------------------------------------------------------------------------------------------
2.e.7. Handling qualities. Landings.                 X   Data may be acquired by using  ........................
 One engine inoperative go around.                        an inertial measurement
                                                          system and a synchronized
                                                          video of calibrated airplane
                                                          instruments and force/
                                                          position measurements of
                                                          flight deck controls. Normal
                                                          and lateral accelerations
                                                          may be recorded in lieu of
                                                          AOA and sideslip.
----------------------------------------------------------------------------------------------------------------
2.e.8. Handling qualities. Landings.                 X   Data may be acquired by using  ........................
 Directional control (rudder                              an inertial measurement
 effectiveness with symmetric thrust).                    system and a synchronized
                                                          video of calibrated airplane
                                                          instruments and force/
                                                          position measurements of
                                                          flight deck controls. Normal
                                                          and lateral accelerations
                                                          may be recorded in lieu of
                                                          AOA and sideslip.
----------------------------------------------------------------------------------------------------------------
2.e.9. Handling qualities. Landings.                 X   Data may be acquired by using  ........................
 Directional control (rudder                              an inertial measurement
 effectiveness with asymmetric                            system and a synchronized
 reverse thrust).                                         video of calibrated airplane
                                                          instruments and force/
                                                          position measurements of
                                                          flight deck controls. Normal
                                                          and lateral accelerations
                                                          may be recorded in lieu of
                                                          AOA and sideslip.
----------------------------------------------------------------------------------------------------------------
2.f. Handling qualities. Ground                      X   Data may be acquired by using  ........................
 effect. Test to demonstrate ground                       calibrated airplane
 effect.                                                  instruments, an inertial
                                                          measurement system, and a
                                                          synchronized video of
                                                          calibrated airplane
                                                          instruments and force/
                                                          position measurements of
                                                          flight deck controls.
----------------------------------------------------------------------------------------------------------------

End Information

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

Attachment 3 to Appendix A to Part 60--Simulator Subjective Evaluation

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

Begin QPS Requirements

1. Requirements

    a. Except for special use airport models, described as Class
III, all airport models required by this part must be
representations of real-world, operational airports or
representations of fictional airports and must meet the requirements
set out in Tables A3B or A3C of this attachment, as appropriate.
    b. If fictional airports are used, the sponsor must ensure that
navigational aids and all appropriate maps, charts, and other
navigational reference material for the fictional airports (and
surrounding areas as necessary) are compatible, complete, and
accurate with respect to the visual presentation of the airport
model of this fictional airport. An SOC must be submitted that
addresses navigation aid installation and performance and other
criteria (including obstruction clearance protection) for all
instrument approaches to the fictional airports that are available
in the simulator. The SOC must reference and account for information
in the terminal instrument procedures manual and the construction
and availability of the required maps, charts, and other
navigational material. This material must be clearly marked ``for
training purposes only.''
    c. When the simulator is being used by an instructor or
evaluator for purposes of training, checking, or testing under this
chapter, only airport models classified as Class I, Class II, or
Class III may be used by the instructor or evaluator. Detailed
descriptions/definitions of these classifications are found in
Appendix F of this part.
    d. When a person sponsors an FFS maintained by a person other
than a U.S. certificate holder, the sponsor is accountable for that
FFS originally meeting, and

continuing to meet, the criteria under which it was originally
qualified and the appropriate Part 60 criteria, including the
airport models that may be used by instructors or evaluators for
purposes of training, checking, or testing under this chapter.
    e. Neither Class II nor Class III airport visual models are
required to appear on the SOQ, and the method used for keeping
instructors and evaluators apprised of the airport models that meet
Class II or Class III requirements on any given simulator is at the
option of the sponsor, but the method used must be available for
review by the TPAA.
    f. When an airport model represents a real world airport and a
permanent change is made to that real world airport (e.g., a new
runway, an extended taxiway, a new lighting system, a runway
closure) without a written extension grant from the NSPM (described
in paragraph 1.g. of this section), an update to that airport model
must be made in accordance with the following time limits:
    (1) For a new airport runway, a runway extension, a new airport
taxiway, a taxiway extension, or a runway/taxiway closure--within 90
days of the opening for use of the new airport runway, runway
extension, new airport taxiway, or taxiway extension; or within 90
days of the closure of the runway or taxiway.
    (2) For a new or modified approach light system--within 45 days
of the activation of the new or modified approach light system.
    (3) For other facility or structural changes on the airport
(e.g., new terminal, relocation of Air Traffic Control Tower)--
within 180 days of the opening of the new or changed facility or
structure.
    g. If a sponsor desires an extension to the time limit for an
update to a visual scene or airport model or has an objection to
what must be updated in the specific airport model requirement, the
sponsor must provide a written extension request to the NSPM stating
the reason for the update delay and a proposed completion date, or
explain why the update is not necessary (i.e., why the identified
airport change will not have an impact on flight training, testing,
or checking). A copy of this request or objection must also be sent
to the POI/TCPM. The NSPM will send the official response to the
sponsor and a copy to the POI/TCPM. If there is an objection, after
consultation with the appropriate POI/TCPM regarding the training,
testing, or checking impact, the NSPM will send the official
response to the sponsor and a copy to the POI/TCPM.

End QPS Requirements

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

Begin Information

2. Discussion

    a. The subjective tests provide a basis for evaluating the
capability of the simulator to perform over a typical utilization
period; determining that the simulator accurately simulates each
required maneuver, procedure, or task; and verifying correct
operation of the simulator controls, instruments, and systems. The
items listed in the following Tables are for simulator evaluation
purposes only. They may not be used to limit or exceed the
authorizations for use of a given level of simulator, as described
on the SOQ, or as approved by the TPAA.
    b. The tests in Table A3A, Operations Tasks, in this attachment,
address pilot functions, including maneuvers and procedures (called
flight tasks), and are divided by flight phases. The performance of
these tasks by the NSPM includes an operational examination of the
visual system and special effects. There are flight tasks included
to address some features of advanced technology airplanes and
innovative training programs. For example, ``high angle-of-attack
maneuvering'' is included to provide a required alternative to
``approach to stalls'' for airplanes employing flight envelope
protection functions.
    c. The tests in Table A3A, Operations Tasks, and Table A3G,
Instructor Operating Station of this attachment, address the overall
function and control of the simulator including the various
simulated environmental conditions; simulated airplane system
operations (normal, abnormal, and emergency); visual system
displays; and special effects necessary to meet flight crew
training, evaluation, or flight experience requirements.
    d. All simulated airplane systems functions will be assessed for
normal and, where appropriate, alternate operations. Normal,
abnormal, and emergency operations associated with a flight phase
will be assessed during the evaluation of flight tasks or events
within that flight phase. Simulated airplane systems are listed
separately under ``Any Flight Phase'' to ensure appropriate
attention to systems checks. Operational navigation systems
(including inertial navigation systems, global positioning systems,
or other long-range systems) and the associated electronic display
systems will be evaluated if installed. The NSP pilot will include
in his report to the TPAA, the effect of the system operation and
any system limitation.
    e. Simulators demonstrating a satisfactory circling approach
will be qualified for the circling approach maneuver and may be
approved for such use by the TPAA in the sponsor's FAA-approved
flight training program. To be considered satisfactory, the circling
approach will be flown at maximum gross weight for landing, with
minimum visibility for the airplane approach category, and must
allow proper alignment with a landing runway at least 90[deg]
different from the instrument approach course while allowing the
pilot to keep an identifiable portion of the airport in sight
throughout the maneuver (reference--14 CFR 91.175(e)).
    f. At the request of the TPAA, the NSPM may assess a device to
determine if it is capable of simulating certain training activities
in a sponsor's training program, such as a portion of a Line
Oriented Flight Training (LOFT) scenario. Unless directly related to
a requirement for the qualification level, the results of such an
evaluation would not affect the qualification level of the
simulator. However, if the NSPM determines that the simulator does
not accurately simulate that training activity, the simulator would
not be approved for that training activity.
    g. The FAA intends to allow the use of Class III airport models
when the sponsor provides the TPAA (or other regulatory authority)
an appropriate analysis of the skills, knowledge, and abilities
(SKAs) necessary for competent performance of the tasks in which
this particular media element is used. The analysis should describe
the ability of the FFS/visual media to provide an adequate
environment in which the required SKAs are satisfactorily performed
and learned. The analysis should also include the specific media
element, such as the airport model. Additional sources of
information on the conduct of task and capability analysis may be
found on the FAA's Advanced Qualification Program (AQP) Web site at:
http://www.faa.gov/education--research/training/aqp/.
    h. The TPAA may accept Class III airport models without
individual observation provided the sponsor provides the TPAA with
an acceptable description of the process for determining the
acceptability of a specific airport model, outlines the conditions
under which such an airport model may be used, and adequately
describes what restrictions will be applied to each resulting
airport or landing area model. Examples of situations that may
warrant Class--III model designation by the TPAA include the
following:
    (a) Training, testing, or checking on very low visibility
operations, including SMGCS operations.
    (b) Instrument operations training (including instrument
takeoff, departure, arrival, approach, and missed approach training,
testing, or checking) using--
    (i) A specific model that has been geographically ``moved'' to a
different location and aligned with an instrument procedure for
another airport.
    (ii) A model that does not match changes made at the real-world
airport (or landing area for helicopters) being modeled.
    (iii) A model generated with an ``off-board'' or an ``on-board''
model development tool (by providing proper latitude/longitude
reference; correct runway or landing area orientation, length,
width, marking, and lighting information; and appropriate adjacent
taxiway location) to generate a facsimile of a real world airport or
landing area.
    i. Previously qualified simulators with certain early generation
Computer Generated Image (CGI) visual systems, are limited by the
capability of the Image Generator or the display system used. These
systems are:
    (1) Early CGI visual systems that are excepted from the
requirement of including runway numbers as a part of the specific
runway marking requirements are:
    (a) Link NVS and DNVS.
    (b) Novoview 2500 and 6000.
    (c) FlightSafety VITAL series up to, and including, VITAL III,
but not beyond.
    (d) Redifusion SP1, SP1T, and SP2.
    (2) Early CGI visual systems are excepted from the requirement
of including runway numbers unless the runways are used for LOFT
training sessions. These LOFT airport models require runway numbers
but only for the specific runway end (one direction) used in the
LOFT session. The systems required to display runway numbers only
for LOFT scenes are:

    (a) FlightSafety VITAL IV.
    (b) Redifusion SP3 and SP3T.
    (c) Link-Miles Image II.
    (3) The following list of previously qualified CGI and display
systems are incapable of generating blue lights. These systems are
not required to have accurate taxi-way edge lighting:
    (a) Redifusion SP1.
    (b) FlightSafety Vital IV.
    (c) Link-Miles Image II and Image IIT
    (d) XKD displays (even though the XKD image generator is capable
of generating blue colored lights, the display cannot accommodate
that color).

End Information

?>---------------------------------------------------------------------

                                   Table A3A.--Functions and Subjective Tests
----------------------------------------------------------------------------------------------------------------
                                                QPS Requirements
-----------------------------------------------------------------------------------------------------------------
                                                                                Simulator level
                  Entry No.                                  Operations tasks                -------------------
                                                                                A    B    C    D
----------------------------------------------------------------------------------------------------------------
Tasks in this table are subject to evaluation if appropriate for the airplane simulated as indicated in the
 SOQ Configuration List or the level of simulator qualification involved. Items not installed or not
 functional on the simulator and, therefore, not appearing on the SOQ Configuration List, are not required
 to be listed as exceptions on the SOQ.
----------------------------------------------------------------------------------------------------------------
1...........................................  Preparation For Flight........................   X    X    X    X
                                              Preflight. Accomplish a functions check of all
                                               switches, indicators, systems, and equipment
                                               at all crewmembers' and instructors' stations
                                               and determine that the flight deck design and
                                               functions are identical to that of the
                                               airplane simulated.
----------------------------------------------------------------------------------------------------------------
2...........................................  Surface Operations (Pre-Take-Off)
----------------------------------------------------------------------------------------------------------------
    2.a.....................................  Engine Start
----------------------------------------------------------------------------------------------------------------
        2.a.1...............................  Normal start..................................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        2.a.2...............................  Alternate start procedures....................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        2.a.3...............................  Abnormal starts and shutdowns (e.g., hot/hung    X    X    X    X
                                               start, tail pipe fire).
----------------------------------------------------------------------------------------------------------------
    2.b.....................................  Pushback/Powerback............................  ...   X    X    X
----------------------------------------------------------------------------------------------------------------
    2.c.....................................  Taxi
----------------------------------------------------------------------------------------------------------------
        2.c.1...............................  Thrust response...............................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        2.c.2...............................  Power lever friction..........................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        2.c.3...............................  Ground handling...............................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        2.c.4...............................  Nosewheel scuffing............................             X    X
----------------------------------------------------------------------------------------------------------------
        2.c.5...............................  Brake operation (normal and alternate/           X    X    X    X
                                               emergency).
----------------------------------------------------------------------------------------------------------------
        2.c.6...............................  Brake fade (if applicable)....................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
3...........................................  Take-off.
----------------------------------------------------------------------------------------------------------------
    3.a.....................................  Normal........................................
----------------------------------------------------------------------------------------------------------------
        3.a.1...............................  Airplane/engine parameter relationships.......   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        3.a.2...............................  Acceleration characteristics (motion).........   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        3.a.3...............................  Nosewheel and rudder steering.................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        3.a.4...............................  Crosswind (maximum demonstrated)..............   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        3.a.5...............................  Special performance (e.g., reduced V1, max de-   X    X    X    X
                                               rate, short field operations).
----------------------------------------------------------------------------------------------------------------
        3.a.6...............................  Low visibility take-off.......................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        3.a.7...............................  Landing gear, wing flap leading edge device      X    X    X    X
                                               operation.
----------------------------------------------------------------------------------------------------------------
        3.a.8...............................  Contaminated runway operation.................  ...  ...   X    X
----------------------------------------------------------------------------------------------------------------
    3.b.....................................  Abnormal/emergency
----------------------------------------------------------------------------------------------------------------
        3.b.1...............................  Rejected Take-off.............................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        3.b.2...............................  Rejected special performance (e.g., reduced      X    X    X    X
                                               V1, max de-rate, short field operations).
----------------------------------------------------------------------------------------------------------------

        3.b.3...............................  Takeoff with a propulsion system malfunction     X    X    X    X
                                               (allowing an analysis of causes, symptoms,
                                               recognition, and the effects on aircraft
                                               performance and handling) at the following
                                               points: ..
                                              (i) Prior to V1 decision speed................
                                              (ii) Between V1 and Vr (rotation speed).......
                                              (iii) Between Vr and 500 feet above ground
                                               level.
----------------------------------------------------------------------------------------------------------------
        3.b.4...............................  With wind shear...............................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        3.b.5...............................  Flight control system failures,                  X    X    X    X
                                               reconfiguration modes, manual reversion and
                                               associated handling.
----------------------------------------------------------------------------------------------------------------
        3.b.6...............................  Rejected takeoff with brake fade..............  ...  ...   X    X
----------------------------------------------------------------------------------------------------------------
        3.b.7...............................  Rejected, contaminated runway.................  ...  ...   X    X
----------------------------------------------------------------------------------------------------------------
4...........................................  Climb.
----------------------------------------------------------------------------------------------------------------
    4.a.....................................  Normal........................................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
    4.b.....................................  One or more engines inoperative...............   X    X    X    X
----------------------------------------------------------------------------------------------------------------
5...........................................  Cruise
----------------------------------------------------------------------------------------------------------------
    5.a.....................................  Performance characteristics (speed vs. power).   X    X    X    X
----------------------------------------------------------------------------------------------------------------
    5.b.....................................  High altitude handling........................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
    5.c.....................................  High Mach number handling (Mach tuck, Mach       X    X    X    X
                                               buffet) and recovery (trim change).
----------------------------------------------------------------------------------------------------------------
    5.d.....................................  Overspeed warning (in excess of Vmo or Mmo)...   X    X    X    X
----------------------------------------------------------------------------------------------------------------
    5.e.....................................  High IAS handling.............................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
6...........................................  Maneuvers
----------------------------------------------------------------------------------------------------------------
    6.a.....................................  High angle of attack, approach to stalls,        X    X    X    X
                                               stall warning, buffet, and g-break (take-off,
                                               cruise, approach, and landing configuration).
----------------------------------------------------------------------------------------------------------------
    6.b.....................................  Flight envelope protection (high angle of        X    X    X    X
                                               attack, bank limit, overspeed, etc.).
----------------------------------------------------------------------------------------------------------------
    6.c.....................................  Turns with/without speedbrake/spoilers           X    X    X    X
                                               deployed.
----------------------------------------------------------------------------------------------------------------
    6.d.....................................  Normal and steep turns........................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
    6.e.....................................  In flight engine shutdown and restart            X    X    X    X
                                               (assisted and windmill).
----------------------------------------------------------------------------------------------------------------
    6.f.....................................  Maneuvering with one or more engines             X    X    X    X
                                               inoperative, as appropriate.
----------------------------------------------------------------------------------------------------------------
    6.g.....................................  Specific flight characteristics (e.g., direct    X    X    X    X
                                               lift control).
----------------------------------------------------------------------------------------------------------------
    6.h.....................................  Flight control system failures,                  X    X    X    X
                                               reconfiguration modes, manual reversion and
                                               associated handling.
----------------------------------------------------------------------------------------------------------------
7...........................................  Descent.
----------------------------------------------------------------------------------------------------------------
    7.a.....................................  Normal........................................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
    7.b.....................................  Maximum rate (clean and with speedbrake, etc.)   X    X    X    X
----------------------------------------------------------------------------------------------------------------
    7.c.....................................  With autopilot................................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
    7.d.....................................  Flight control system failures,                  X    X    X    X
                                               reconfiguration modes, manual reversion and
                                               associated handling.
----------------------------------------------------------------------------------------------------------------
8...........................................  Instrument Approaches and Landing. Those instrument approach and
                                               landing tests relevant to the simulated airplane type are
                                               selected from the following list. Some tests are made with
                                               limiting wind velocities, under wind shear conditions, and with
                                               relevant system failures, including the failure of the Flight
                                               Director. If Standard Operating Procedures allow use autopilot
                                               for non-precision approaches, evaluation of the autopilot will be
                                               included. Level A simulators are not authorized to credit the
                                               landing maneuver
----------------------------------------------------------------------------------------------------------------
    8.a.....................................  Precision.....................................
----------------------------------------------------------------------------------------------------------------

        8.a.1...............................  PAR...........................................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        8.a.2...............................  CAT I/GBAS (ILS/MLS) published approaches.....   X    X    X    X
----------------------------------------------------------------------------------------------------------------
                                              (i) Manual approach with/without flight          X    X    X    X
                                               director including landing.
                                              (ii) Autopilot/autothrottle coupled approach     X    X    X    X
                                               and manual landing.
                                              (iii) Manual approach to DH and go-around all    X    X    X    X
                                               engines.
                                              (iv) Manual one engine out approach to DH and    X    X    X    X
                                               go-around.
                                              (v) Manual approach controlled with and          X    X    X    X
                                               without flight director to 30 m (100 ft)
                                               below CAT I minima.
                                                A. With cross-wind (maximum demonstrated)...   X    X    X    X
                                                B. With windshear...........................   X    X    X    X
                                              (vi) Autopilot/autothrottle coupled approach,    X    X    X    X
                                               one engine out to DH and go-around.
                                              (vii) Approach and landing with minimum/         X    X    X    X
                                               standby electrical power.
----------------------------------------------------------------------------------------------------------------
        8.a.3...............................  CAT II/GBAS (ILS/MLS) published approaches....   X    X    X    X
----------------------------------------------------------------------------------------------------------------
                                              (i) Autopilot/autothrottle coupled approach to   X    X    X    X
                                               DH and landing.
                                              (ii) Autopilot/autothrottle coupled approach     X    X    X    X
                                               to DH and go-around.
                                              (iii) Autocoupled approach to DH and manual go-  X    X    X    X
                                               around.
                                              (iv) Category II published approach              X    X    X    X
                                               (autocoupled, autothrottle).
----------------------------------------------------------------------------------------------------------------
        8.a.4...............................  CAT III/GBAS (ILS/MLS) published approaches...   X    X    X    X
----------------------------------------------------------------------------------------------------------------
                                              (i) Autopilot/autothrottle coupled approach to   X    X    X    X
                                               land and rollout.
                                              (ii) Autopilot/autothrottle coupled approach     X    X    X    X
                                               to DH/Alert Height and go-around.
                                              (iii) Autopilot/autothrottle coupled approach    X    X    X    X
                                               to land and rollout with one engine out.
                                              (iv) Autopilot/autothrottle coupled approach     X    X    X    X
                                               to DH/Alert Height and go-around with one
                                               engine out.
                                              (v) Autopilot/autothrottle coupled approach      X    X    X    X
                                               (to land or to go around).
                                                A. With generator failure...................   X    X    X    X
                                                B. With 10 knot tail wind...................   X    X    X    X
                                                C. With 10 knot crosswind...................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
    8.b.....................................  Non-precision
----------------------------------------------------------------------------------------------------------------
        8.b.1...............................  NDB...........................................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        8.b.2...............................  VOR, VOR/DME, VOR/TAC.........................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        8.b.3...............................  RNAV (GNSS/GPS)...............................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        8.b.4...............................  ILS LLZ (LOC), LLZ (LOC)/BC...................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        8.b.5...............................  ILS offset localizer..........................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        8.b.6...............................  Direction finding facility (ADF/SDF)..........   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        8.b.7...............................  Airport surveillance radar (ASR)..............   X    X    X    X
----------------------------------------------------------------------------------------------------------------
9...........................................  Visual Approaches (Visual Segment) and Landings. Flight simulators
                                               with visual systems, which permit completing a special approach
                                               procedure in accordance with applicable regulations, may be
                                               approved for that particular approach procedure
----------------------------------------------------------------------------------------------------------------
    9.a.....................................  Maneuvering, normal approach and landing, all    X    X    X    X
                                               engines operating with and without visual
                                               approach aid guidance.
----------------------------------------------------------------------------------------------------------------
    9.b.....................................  Approach and landing with one or more engines    X    X    X    X
                                               inoperative.
----------------------------------------------------------------------------------------------------------------
    9.c.....................................  Operation of landing gear, flap/slats and        X    X    X    X
                                               speedbrakes (normal and abnormal).
----------------------------------------------------------------------------------------------------------------
    9.d.....................................  Approach and landing with crosswind (max.        X    X    X    X
                                               demonstrated).
----------------------------------------------------------------------------------------------------------------
    9.e.....................................  Approach to land with wind shear on approach..   X    X    X    X
----------------------------------------------------------------------------------------------------------------
    9.f.....................................  Approach and landing with flight control         X    X    X    X
                                               system failures, reconfiguration modes,
                                               manual reversion and associated handling
                                               (most significant degradation which is
                                               probable).
----------------------------------------------------------------------------------------------------------------
    9.g.....................................  Approach and landing with trim malfunctions...   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        9.g.1...............................  Longitudinal trim malfunction.................   X    X    X    X
----------------------------------------------------------------------------------------------------------------

        9.g.2...............................  Lateral-directional trim malfunction..........   X    X    X    X
----------------------------------------------------------------------------------------------------------------
    9.h.....................................  Approach and landing with standby (minimum)      X    X    X    X
                                               electrical/hydraulic power.
----------------------------------------------------------------------------------------------------------------
    9.i.....................................  Approach and landing from circling conditions    X    X    X    X
                                               (circling approach).
----------------------------------------------------------------------------------------------------------------
    9.j.....................................  Approach and landing from visual traffic         X    X    X    X
                                               pattern.
----------------------------------------------------------------------------------------------------------------
    9.k.....................................  Approach and landing from non-precision          X    X    X    X
                                               approach.
----------------------------------------------------------------------------------------------------------------
    9.l.....................................  Approach and landing from precision approach..   X    X    X    X
----------------------------------------------------------------------------------------------------------------
    9.m.....................................  Approach procedures with vertical guidance       X    X    X    X
                                               (APV), e.g., SBAS.
----------------------------------------------------------------------------------------------------------------
10..........................................  Missed Approach
----------------------------------------------------------------------------------------------------------------
    10.a....................................  All engines...................................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
    10.b....................................  One or more engine(s) out.....................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
    10.c....................................  With flight control system failures,             X    X    X    X
                                               reconfiguration modes, manual reversion and
                                               associated handling.
----------------------------------------------------------------------------------------------------------------
11..........................................  Surface Operations (Landing roll and taxi).
----------------------------------------------------------------------------------------------------------------
    11.a....................................  Spoiler operation.............................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
    11.b....................................  Reverse thrust operation......................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
    11.c....................................  Directional control and ground handling, both   ...   X    X    X
                                               with and without reverse thrust.
----------------------------------------------------------------------------------------------------------------
    11.d....................................  Reduction of rudder effectiveness with          ...   X    X    X
                                               increased reverse thrust (rear pod-mounted
                                               engines).
----------------------------------------------------------------------------------------------------------------
    11.e....................................  Brake and anti-skid operation with dry, patchy  ...  ...   X    X
                                               wet, wet on rubber residue, and patchy icy
                                               conditions.
----------------------------------------------------------------------------------------------------------------
    11.f....................................  Brake operation, to include auto-braking         X    X    X    X
                                               system where applicable.
----------------------------------------------------------------------------------------------------------------
12..........................................  Any Flight Phase.
----------------------------------------------------------------------------------------------------------------
    12.a....................................  Airplane and engine systems operation.........
----------------------------------------------------------------------------------------------------------------
        12.a.1..............................  Air conditioning and pressurization (ECS).....   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        12.a.2..............................  De-icing/anti-icing...........................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        12.a.3..............................  Auxiliary power unit (APU)....................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        12.a.4..............................  Communications................................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        12.a.5..............................  Electrical....................................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        12.a.6..............................  Fire and smoke detection and suppression......   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        12.a.7..............................  Flight controls (primary and secondary).......   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        12.a.8..............................  Fuel and oil, hydraulic and pneumatic.........   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        12.a.9..............................  Landing gear..................................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        12.a.10.............................  Oxygen........................................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        12.a.11.............................  Engine........................................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        12.a.12.............................  Airborne radar................................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        12.a.13.............................  Autopilot and Flight Director.................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        12.a.14.............................  Collision avoidance systems. (e.g., (E)GPWS,     X    X    X    X
                                               TCAS).
----------------------------------------------------------------------------------------------------------------
        12.a.15.............................  Flight control computers including stability     X    X    X    X
                                               and control augmentation.
----------------------------------------------------------------------------------------------------------------

        12.a.16.............................  Flight display systems........................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        12.a.17.............................  Flight management computers...................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        12.a.18.............................  Head-up guidance, head-up displays............   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        12.a.19.............................  Navigation systems............................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        12.a.20.............................  Stall warning/avoidance.......................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        12.a.21.............................  Wind shear avoidance equipment................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        12.a.22.............................  Automatic landing aids........................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
    12.b....................................  Airborne procedures
----------------------------------------------------------------------------------------------------------------
        12.b.1..............................  Holding.......................................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        12.b.2..............................  Air hazard avoidance (traffic, weather).......  ...  ...   X    X
----------------------------------------------------------------------------------------------------------------
        12.b.3..............................  Wind shear....................................  ...  ...   X    X
----------------------------------------------------------------------------------------------------------------
        12.b.4..............................  Effects of airframe ice.......................  ...  ...   X    X
----------------------------------------------------------------------------------------------------------------
    12.c....................................  Engine shutdown and parking
----------------------------------------------------------------------------------------------------------------
        12.c.1..............................  Engine and systems operation..................   X    X    X    X
----------------------------------------------------------------------------------------------------------------
        12.c.2..............................  Parking brake operation.......................   X    X    X    X
----------------------------------------------------------------------------------------------------------------

               Table A3B.--Functions and Subjective Tests
------------------------------------------------------------------------
                            QPS Requirements
-------------------------------------------------------------------------
                                                        Simulator level
     Entry No.       For qualification at the stated -------------------
                      level--Class I airport models    A    B    C    D
------------------------------------------------------------------------
This table specifies the minimum airport model content and functionality
 to qualify a simulator at the indicated level. This table applies only
 to the airport models required for simulator qualification; i.e., one
 airport model for Level A and Level B simulators; three airport models
 for Level C and Level D simulators.
------------------------------------------------------------------------
                         Begin QPS Requirements
------------------------------------------------------------------------
1.................  Functional test content requirements for Level A and
                     Level B simulators. The following is the minimum
                     airport model content requirement to satisfy visual
                     capability tests, and provides suitable visual cues
                     to allow completion of all functions and subjective
                     tests described in this attachment for simulators
                     at Levels A and B.
------------------------------------------------------------------------
    1.a...........  A minimum of one (1)               X    X
                     representative airport model.
                     This model identification must
                     be acceptable to the sponsor's
                     TPAA, selectable from the IOS,
                     and listed on the SOQ.
------------------------------------------------------------------------
    1.b...........  The fidelity of the airport        X    X
                     model must be sufficient for
                     the aircrew to visually
                     identify the airport; determine
                     the position of the simulated
                     airplane within a night visual
                     scene; successfully accomplish
                     take-offs, approaches, and
                     landings; and maneuver around
                     the airport on the ground as
                     necessary.
------------------------------------------------------------------------
    1.c...........  Runways:........................   X    X
------------------------------------------------------------------------
        1.c.1.....  Visible runway number...........   X    X
------------------------------------------------------------------------
        1.c.2.....  Runway threshold elevations and    X    X
                     locations must be modeled to
                     provide sufficient correlation
                     with airplane systems (e.g.,
                     altimeter).
------------------------------------------------------------------------
        1.c.3.....  Runway surface and markings.....   X    X
------------------------------------------------------------------------
        1.c.4.....  Lighting for the runway in use     X    X
                     including runway edge and
                     centerline.
------------------------------------------------------------------------
        1.c.5.....  Lighting, visual approach aid      X    X
                     and approach lighting of
                     appropriate colors.
------------------------------------------------------------------------

        1.c.6.....  Representative taxiway lights...   X    X
------------------------------------------------------------------------
2.................  Functional test content requirements for Level C and
                     Level D simulators. The following is the minimum
                     airport model content requirement to satisfy visual
                     capability tests, and provide suitable visual cues
                     to allow completion of all functions and subjective
                     tests described in this attachment for simulators
                     at Levels C and D. Not all of the elements
                     described in this section must be found in a single
                     airport model. However, all of the elements
                     described in this section must be found throughout
                     a combination of the three (3) airport models
                     described in entry 2.a.
------------------------------------------------------------------------
    2.a...........  A minimum of three (3)                       X    X
                     representative airport models.
                     The model identifications must
                     be acceptable to the sponsor's
                     TPAA, selectable from the IOS,
                     and listed on the SOQ.
------------------------------------------------------------------------
        2.a.1.....  Night and Twilight (Dusk) scenes             X    X
                     required.
------------------------------------------------------------------------
        2.a.2.....  Daylight scenes required........                  X
------------------------------------------------------------------------
        2.b.......  Two parallel runways and one                 X    X
                     crossing runway, displayed
                     simultaneously; at least two of
                     the runways must be able to be
                     lighted fully and
                     simultaneously.
                    Note: This requirement may be
                     demonstrated at either a
                     fictional airport or a real-
                     world airport. However, if a
                     fictional airport is used, this
                     airport must be listed on the
                     SOQ.
------------------------------------------------------------------------
    2.c...........  Runway threshold elevations and              X    X
                     locations must be modeled to
                     provide sufficient correlation
                     with airplane systems (e.g.,
                     HGS, GPS, altimeter); slopes in
                     runways, taxiways, and ramp
                     areas must not cause
                     distracting or unrealistic
                     effects, including pilot eye-
                     point height variation.
------------------------------------------------------------------------
    2.d...........  Representative airport                       X    X
                     buildings, structures and
                     lighting.
------------------------------------------------------------------------
    2.e...........  At least one useable gate, at                X    X
                     the appropriate height
                     (required only for those
                     airplanes that typically
                     operate from terminal gates).
------------------------------------------------------------------------
    2.f...........  Representative moving and static             X    X
                     gate clutter (e.g., other
                     airplane, power carts, tugs,
                     fuel trucks, and additional
                     gates).
------------------------------------------------------------------------
    2.g...........  Representative gate/apron                    X    X
                     markings (e.g., hazard
                     markings, lead-in lines, gate
                     numbering) and lighting.
------------------------------------------------------------------------
    2.h...........  Representative runway markings,              X    X
                     lighting, and signage,
                     including a windsock that gives
                     appropriate wind cues.
------------------------------------------------------------------------
    2.i...........  Representative taxiway markings,             X    X
                     lighting, and signage necessary
                     for position identification,
                     and to taxi from parking to a
                     designated runway and return to
                     parking.
------------------------------------------------------------------------
    2.j...........  A low visibility taxi route                       X
                     (e.g., Surface Movement
                     Guidance Control System, follow-
                     me truck, daylight taxi lights)
                     must also be demonstrated.
------------------------------------------------------------------------
    2.k...........  Representative moving and static             X    X
                     ground traffic (e.g., vehicular
                     and airplane), including the
                     capability to present ground
                     hazards (e.g., another airplane
                     crossing the active runway).
------------------------------------------------------------------------
    2.l...........  Representative moving airborne               X    X
                     traffic, including the
                     capability to present air
                     hazards (e.g., airborne traffic
                     on a possible collision course).
------------------------------------------------------------------------
    2.m...........  Representative depiction of                  X    X
                     terrain and obstacles as well
                     as significant and identifiable
                     natural and cultural features,
                     within 25 NM of the reference
                     airport.
------------------------------------------------------------------------
    2.n...........  Appropriate approach lighting                X    X
                     systems and airfield lighting
                     for a VFR circuit and landing,
                     non-precision approaches and
                     landings, and Category I, II
                     and III precision approaches
                     and landings.
------------------------------------------------------------------------
    2.o...........  Representative gate docking aids             X    X
                     or a marshaller.
------------------------------------------------------------------------
    2.p...........  Portrayal of physical                             X
                     relationships known to cause
                     landing illusions (e.g., short
                     runways, landing approaches
                     over water, uphill or downhill
                     runways, rising terrain on the
                     approach path).
                    This requirement may be met by a
                     SOC and a demonstration of two
                     landing illusions. The
                     illusions are not required to
                     be beyond the normal
                     operational capabilities of the
                     airplane being simulated. The
                     demonstrated illusions must be
                     available to the instructor or
                     check airman at the IOS for
                     training, testing, checking, or
                     experience activities.
------------------------------------------------------------------------
    2.q...........  Portrayal of runway surface                       X
                     contaminants, including runway
                     lighting reflections when wet
                     and partially obscured lights
                     when snow is present, or
                     suitable alternative effects.
------------------------------------------------------------------------

3.................  Airport model management. The following is the
                     minimum airport model management requirements for
                     simulators at Levels A, B, C, and D.
------------------------------------------------------------------------
    3.a...........  Runway and approach lighting       X    X    X    X
                     must fade into view in
                     accordance with the
                     environmental conditions set in
                     the simulator, and the distance
                     from the object.
------------------------------------------------------------------------
    3.b...........  The direction of strobe lights,    X    X    X    X
                     approach lights, runway edge
                     lights, visual landing aids,
                     runway centerline lights,
                     threshold lights, and touchdown
                     zone lights must be replicated.
------------------------------------------------------------------------
4.................  Visual feature recognition. The following is the
                     minimum distances at which runway features must be
                     visible for simulators at Levels A, B, C, and D.
                     Distances are measured from runway threshold to an
                     airplane aligned with the runway on an extended
                     3[deg] glide-slope in simulated meteorological
                     conditions that recreate the minimum distances for
                     visibility. For circling approaches, all tests
                     apply to the runway used for the initial approach
                     and to the runway of intended landing.
------------------------------------------------------------------------
    4.a...........  Runway definition, strobe          X    X    X    X
                     lights, approach lights, and
                     runway edge white lights from 5
                     sm (8 km) of the runway
                     threshold.
------------------------------------------------------------------------
    4.b...........  Visual Approach Aid lights (VASI             X    X
                     or PAPI) from 5 sm (8 km) of
                     the runway threshold.
------------------------------------------------------------------------
    4.c...........  Visual Approach Aid lights (VASI   X    X
                     or PAPI) from 3 sm (5 km) of
                     the runway threshold.
------------------------------------------------------------------------
    4.d...........  Runway centerline lights and       X    X    X    X
                     taxiway definition from 3 sm (5
                     km).
------------------------------------------------------------------------
    4.e...........  Threshold lights and touchdown     X    X    X    X
                     zone lights from 2 sm (3 km).
------------------------------------------------------------------------
    4.f...........  Runway markings within range of    X    X    X    X
                     landing lights for night scenes
                     as required by the surface
                     resolution test on day scenes.
------------------------------------------------------------------------
    4.g...........  For circling approaches, the       X    X    X    X
                     runway of intended landing and
                     associated lighting must fade
                     into view in a non-distracting
                     manner.
------------------------------------------------------------------------
5.................  Airport model content. The following sets out the
                     minimum requirements for what must be provided in
                     an airport model and also identifies the other
                     aspects of the airport environment that must
                     correspond with that model for simulators at Levels
                     A, B, C, and D. For circling approaches, all tests
                     apply to the runway used for the initial approach
                     and to the runway of intended landing. If all
                     runways in an airport model used to meet the
                     requirements of this attachment are not designated
                     as ``in use,'' then the ``in use'' runways must be
                     listed on the SOQ (e.g., KORD, Rwys 9R, 14L, 22R).
                     Models of airports with more than one runway must
                     have all significant runways not ``in-use''
                     visually depicted for airport and runway
                     recognition purposes. The use of white or off white
                     light strings that identify the runway threshold,
                     edges, and ends for twilight and night scenes are
                     acceptable for this requirement. Rectangular
                     surface depictions are acceptable for daylight
                     scenes. A visual system's capabilities must be
                     balanced between providing airport models with an
                     accurate representation of the airport and a
                     realistic representation of the surrounding
                     environment. Airport model detail must be developed
                     using airport pictures, construction drawings and
                     maps, or other similar data, or developed in
                     accordance with published regulatory material;
                     however, this does not require that such models