------------------------------------------------------------------------
                  (b) Trim for straight and   5-15 lbs (2.2-6.6 daN) of
                   level flight with flaps     force (Push).
                   extended to 50% of full
                   flap travel, at a
                   constant airspeed within
                   the flaps-extended
                   airspeed range. Do not
                   adjust trim or power.
                   Retract the flaps to
                   zero. After stabilized,
                   record stick force
                   necessary to maintain
                   original airspeed.
------------------------------------------------------------------------
2.c.4...........  Gear change force
------------------------------------------------------------------------

                  (a) Trim for straight and   2-12 lbs (0.88-5.3 daN) of
                   level flight with landing   force (Pull).
                   gear retracted at a
                   constant airspeed within
                   the landing gear-extended
                   airspeed range. Do not
                   adjust trim or power.
                   Extend the landing gear.
                   After stabilized, record
                   stick force necessary to
                   maintain original
                   airspeed.
------------------------------------------------------------------------
                  OR
------------------------------------------------------------------------
                  b) Trim for straight and    2-12 lbs (0.88-5.3 daN) of
                   level flight with landing   force (Push).
                   gear extended, at a
                   constant airspeed within
                   the landing gear-extended
                   airspeed range. Do not
                   adjust trim or power.
                   Retract the landing gear.
                   After stabilized, record
                   stick force necessary to
                   maintain original
                   airspeed.
------------------------------------------------------------------------
2.b.5...........  Longitudinal trim.........  Must be able to trim
                                               longitudinal stick force
                                               to ``zero'' in each of
                                               the following
                                               configurations: cruise;
                                               approach; and landing.
------------------------------------------------------------------------
2.c.7...........  Longitudinal static         Must exhibit positive
                   stability.                  static stability.
------------------------------------------------------------------------
2.c.8...........  Stall warning (actuation
                   of stall warning device)
                   with nominal gross
                   weight; wings level; and
                   a deceleration rate of
                   not more than three (3)
                   knots per second.
                  (a) Landing configuration.  80-100 knots; < plus-
                                               minus>5[deg] of bank.
                  (b) Clean configuration...  Landing configuration
                                               speed + 10-20%.
------------------------------------------------------------------------
2.c.8.b.........  Phugoid dynamics..........  Must have a phugoid with a
                                               period of 30-60 seconds.
                                               May not reach \1/2\ or
                                               double amplitude in less
                                               than 2 cycles.
------------------------------------------------------------------------
2.d.............  Lateral Directional Tests
------------------------------------------------------------------------
2.d.2...........  Roll response.............  Must have a roll rate of 4-
                  Roll rate must be measured   25 degrees/second.
                   through at least 30[deg]
                   of roll. Aileron control
                   must be deflected \1/3\
                   (33.3 percent) of maximum
                   travel..
------------------------------------------------------------------------
2.d.4.b.........  Spiral stability..........  Initial bank angle (< plus-
                  Cruise configuration and     minus>5[deg]) after 20
                   normal cruise airspeed.     seconds.
                   Establish a 20[deg]-
                   30[deg] bank. When
                   stabilized, neutralize
                   the aileron control and
                   release. Must be
                   completed in both
                   directions of turn..
------------------------------------------------------------------------
2.d.6.b.........  Rudder response...........  3[deg]-6[deg]/second yaw
                  Use 25 percent of maximum    rate.
                   rudder deflection.
                   (Applicable to approach
                   or landing
                   configuration.).
------------------------------------------------------------------------
2.d.7...........  Dutch roll, yaw damper      A period of 2-5 seconds;
                   off. (Applicable to         and \1/2\-2 cycles.
                   cruise and approach
                   configurations.).
------------------------------------------------------------------------
2.d.8...........  Steady state sideslip.....  2[deg]-10[deg] of bank;
                  Use 50 percent rudder       4[deg]-10[deg] of
                   deflection. (Applicable     sideslip; and
                   to approach and landing    2[deg]-10[deg] of aileron.
                   configurations.).
------------------------------------------------------------------------
6. FTD System Response Time
------------------------------------------------------------------------
6.a.............  Flight deck instrument      300 milliseconds or less.
                   systems response to an
                   abrupt pilot controller
                   input. One test is
                   required in each axis
                   (pitch, roll, yaw).
------------------------------------------------------------------------

End QPS Requirements

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

Begin QPS Requirements

5. Alternative Data Sources, Procedures, and Instrumentation: Level 6
FTD Only

    a. Sponsors are not required to use the alternative data
sources, procedures, and instrumentation. However, any sponsor
choosing to use alternative sources must comply with the
requirements in Table B2F.

End QPS Requirements

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

Begin Information

    b. It has become standard practice for experienced FTD
manufacturers to use such techniques as a means of establishing data
bases for new FTD configurations while awaiting the availability of
actual flight test data; and then comparing this new data with the
newly available flight test data. The results of such comparisons
have, as reported by some recognized and experienced simulation
experts, become increasingly consistent and indicate that these
techniques, applied with appropriate experience, are becoming
dependably accurate for the development of aerodynamic models for
use in Level 6 FTDs.

    c. In reviewing this history, the NSPM has concluded that, with
proper care, those who are experienced in the development of
aerodynamic models for FTD application can successfully use these
modeling techniques to acceptably alter the method by which flight
test data may be acquired and, when applied to Level 6 FTDs, does
not compromise the quality of that simulation.
    d. The information in the table that follows (Table of
Alternative Data Sources, Procedures, and Information: Level 6 FTD
Only) is presented to describe an acceptable alternative to data
sources for Level 6 FTD modeling and validation, and an acceptable
alternative to the procedures and instrumentation found in the
flight test methods traditionally accepted for gathering 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 NSPM recommends that use of the alternative
instrumentation noted in Table B2F be coordinated with the NSPM
prior to employment 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 three primary
preconditions and presumptions regarding the objective data and FTD
aerodynamic program modeling.
    (1) Data gathered through the alternative means does not require
angle of attack (AOA) measurements or control surface position
measurements for any flight test. AOA can be sufficiently derived if
the flight test program insures the collection of acceptable level,
unaccelerated, trimmed flight data. Angle of attack may be validated
by conducting the three basic ``fly-by'' trim tests. The FTD time
history tests should begin in level, unaccelerated, and trimmed
flight, and the results should be compared with the flight test
pitch angle.
    (2) A simulation controls system model should be rigorously
defined and fully mature. It should also include accurate gearing
and cable stretch characteristics (where applicable) that are
determined from actual aircraft measurements. Such a model does not
require control surface position measurements in the flight test
objective data for Level 6 FTD applications.
    f. Table B2F is not applicable to Computer Controlled Aircraft
FTDs.
    g. Utilization of these alternate data sources, procedures, and
instrumentation does not relieve the sponsor from compliance with
the balance of the information contained in this document relative
to Level 6 FTDs.
    h. The term ``inertial measurement system'' allows the use of a
functional global positioning system (GPS).

End Information

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

  Table B2F.--Alternative Data Sources, Procedures, and Instrumentation
                               Level 6 FTD
------------------------------------------------------------------------
 <<>> The standards in this table are required if the
  data gathering methods described in paragraph 9 of Appendix B are not
                                  used.
-------------------------------------------------------------------------
                                   Alternative data
   Objective test reference      sources, procedures,       Notes and
       number and title           and instrumentation       reminders
------------------------------------------------------------------------
1.b.1.........................  Data may be acquired    This test is
Performance...................   through a               required only
Takeoff.......................   synchronized video      if RTO is
Ground acceleration time......   recording of a stop     sought.
                                 watch and the
                                 calibrated airplane
                                 airspeed indicator.
                                 Hand-record the
                                 flight conditions and
                                 airplane
                                 configuration.
------------------------------------------------------------------------
1.b.7.........................  Data may be acquired    This test is
Performance...................   through a               required only
Takeoff.......................   synchronized video      if RTO is
Rejected takeoff..............   recording of a stop     sought.
                                 watch and the
                                 calibrated airplane
                                 airspeed indicator.
                                 Hand-record the
                                 flight conditions and
                                 airplane
                                 configuration.
------------------------------------------------------------------------
1.c.1.........................  Data may be acquired
Performance...................   with a synchronized
Climb.........................   video of calibrated
Normal climb all engines         airplane instruments
 operating..                     and engine power
                                 throughout the climb
                                 range.
------------------------------------------------------------------------
1.f.1.........................  Data may be acquired
Performance...................   with a synchronized
Engines.......................   video recording of
Acceleration..................   engine instruments
                                 and throttle position.
------------------------------------------------------------------------
1.f.2.........................  Data may be acquired
Performance...................   with a synchronized
Engines.......................   video recording of
Deceleration..................   engine instruments
                                 and throttle position.
------------------------------------------------------------------------
2.a.1.a.......................  Surface position data
Handling qualities............   may be acquired from
Static control tests..........   flight data recorder
Pitch controller position vs.    (FDR) sensor or, if
 force and surface position      no FDR sensor, at
 calibration..                   selected, significant
                                 column positions
                                 (encompassing
                                 significant column
                                 position data
                                 points), acceptable
                                 to the NSPM, using a
                                 control surface
                                 protractor on the
                                 ground (for airplanes
                                 with reversible
                                 control systems, this
                                 function should be
                                 accomplished with
                                 winds less than 5
                                 kt). Force data may
                                 be acquired by using
                                 a hand held force
                                 gauge at the same
                                 column position data
                                 points.
------------------------------------------------------------------------

2.a.2.a.......................  Surface position data
Handling qualities............   may be acquired from
Static control tests..........   flight data recorder
Wheel position vs. force and     (FDR) sensor or, if
 surface position calibration..  no FDR sensor, at
                                 selected, significant
                                 column positions
                                 (encompassing
                                 significant column
                                 position data
                                 points), acceptable
                                 to the NSPM, using a
                                 control surface
                                 protractor on the
                                 ground (for airplanes
                                 with reversible
                                 control systems, this
                                 function should be
                                 accomplished with
                                 winds less than 5
                                 kt). Force data may
                                 be acquired by using
                                 a hand held force
                                 gauge at the same
                                 column position data
                                 points.
------------------------------------------------------------------------
2.a.3.a.......................  Surface position data
Handling qualities............   may be acquired from
Static control tests..........   flight data recorder
Rudder pedal position vs.        (FDR) sensor or, if
 force and surface position      no FDR sensor, at
 calibration..                   selected, significant
                                 column positions
                                 (encompassing
                                 significant column
                                 position data
                                 points), acceptable
                                 to the NSPM, using a
                                 control surface
                                 protractor on the
                                 ground (for airplanes
                                 with reversible
                                 control systems, this
                                 function should be
                                 accomplished with
                                 winds less than 5
                                 kt). Force data may
                                 be acquired by using
                                 a hand held force
                                 gauge at the same
                                 column position data
                                 points.
------------------------------------------------------------------------
2.a.4.........................  Breakout data may be
Handling qualities............   acquired with a hand
Static control tests..........   held force gauge. The
Nosewheel steering force......   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.........................  Data may be acquired
Handling qualities............   through the use of
Static control tests..........   force pads on the
Rudder pedal steering            rudder pedals and a
 calibration..                   pedal position
                                 measurement device,
                                 together with design
                                 data for nose wheel
                                 position.
------------------------------------------------------------------------
2.a.6.........................  Data may be acquired
Handling qualities............   through calculations.
Static control tests..........
Pitch trim indicator vs.
 surface position calibration..
------------------------------------------------------------------------
2.a.8.........................  Data may be acquired
Handling qualities............   through the use of a
Static control tests..........   temporary throttle
Alignment of power lever angle   quadrant scale to
 vs. selected engine parameter   document throttle
 (e.g., EPR, N1, Torque,         position. Use a
 Manifold pressure)..            synchronized video to
                                 record steady state
                                 instrument readings
                                 or hand-record steady
                                 state engine
                                 performance readings.
------------------------------------------------------------------------
2.a.9.........................  Use of design or
Handling qualities............   predicted data is
Static control tests..........   acceptable. Data may
Brake pedal position vs.         be acquired by
 force..                         measuring deflection
                                 at ``zero'' and at
                                 ``maximum.''
------------------------------------------------------------------------
2.c.1.........................  Data may be acquired    Power change
Handling qualities............   by using an inertial    dynamics test
Longitudinal control tests....   measurement system      is acceptable
Power change force............   and a synchronized      using the same
                                 video of the            data
                                 calibrated airplane     acquisition
                                 instruments, throttle   methodology.
                                 position, and the
                                 force/position
                                 measurements of
                                 flight deck controls.
------------------------------------------------------------------------
2.c.2.........................  Data may be acquired    Flap/slat change
Handling qualities............   by using an inertial    dynamics test
Longitudinal control tests....   measurement system      is acceptable
Flap/slat change force........   and a synchronized      using the same
                                 video of calibrated     data
                                 airplane instruments,   acquisition
                                 flap/slat position,     methodology.
                                 and the force/
                                 position measurements
                                 of flight deck
                                 controls.
------------------------------------------------------------------------
2.c.4.........................  Data may be acquired    Gear change
Handling qualities............   by using an inertial    dynamics test
Longitudinal control tests....   measurement system      is acceptable
Gear change force.............   and a synchronized      using the same
                                 video of the            data
                                 calibrated airplane     acquisition
                                 instruments, gear       methodology.
                                 position, and the
                                 force/position
                                 measurements of
                                 flight deck controls.
------------------------------------------------------------------------

2.c.5.........................  Data may be acquired
Handling qualities............   through use of an
Longitudinal control tests....   inertial measurement
Longitudinal trim.............   system and a
                                 synchronized video of
                                 flight deck controls
                                 position (previously
                                 calibrated to show
                                 related surface
                                 position) and engine
                                 instrument readings.
------------------------------------------------------------------------
2.c.6.........................  Data may be acquired
Handling qualities............   through the use of an
Longitudinal control tests....   inertial measurement
Longitudinal maneuvering         system and a
 stability (stick force/g)..     synchronized video of
                                 the 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.........................  Data may be acquired
Handling qualities............   through the use of a
Longitudinal control tests....   synchronized video of
Longitudinal static stability.   the airplane flight
                                 instruments and a
                                 hand held force gauge.
------------------------------------------------------------------------
2.c.8.........................  Data may be acquired    Airspeeds may be
Handling qualities............   through a               cross checked
Longitudinal control tests....   synchronized video      with those in
Stall Warning (activation of     recording of a stop     the TIR and
 stall warning device)..         watch and the           AFM.
                                 calibrated airplane
                                 airspeed indicator.
                                 Hand-record the
                                 flight conditions and
                                 airplane
                                 configuration.
------------------------------------------------------------------------
2.c.9.a.......................  Data may be acquired
Handling qualities.              by using an inertial
 Longitudinal control tests.     measurement system
Phugoid dynamics..............   and a synchronized
                                 video of the
                                 calibrated airplane
                                 instruments and the
                                 force/position
                                 measurements of
                                 flight deck controls.
------------------------------------------------------------------------
2.c.10........................  Data may be acquired
Handling qualities............   by using an inertial
Longitudinal control tests....   measurement system
Short period dynamics.........   and a synchronized
                                 video of the
                                 calibrated airplane
                                 instruments and the
                                 force/position
                                 measurements of
                                 flight deck controls.
------------------------------------------------------------------------
2.c.11........................  May use design data,
Handling qualities............   production flight
Longitudinal control tests....   test schedule, or
Gear and flap/slat operating     maintenance
 times..                         specification,
                                 together with an SOC.
------------------------------------------------------------------------
2.d.2.........................  Data may be acquired
Handling qualities............   by using an inertial
Lateral directional tests.....   measurement system
Roll response (rate)..........   and a synchronized
                                 video of the
                                 calibrated airplane
                                 instruments and the
                                 force/position
                                 measurements of
                                 flight deck lateral
                                 controls.
------------------------------------------------------------------------
2.d.3.........................  Data may be acquired
Handling qualities............   by using an inertial
Lateral directional tests.....   measurement system
(a) Roll overshoot............   and a synchronized
OR............................   video of the
(b) Roll response to flight      calibrated airplane
 deck roll controller step       instruments and the
 input..                         force/position
                                 measurements of
                                 flight deck lateral
                                 controls.
------------------------------------------------------------------------
2.d.4.........................  Data may be acquired
Handling qualities............   by using an inertial
Lateral directional tests.....   measurement system
Spiral stability..............   and a synchronized
                                 video of the
                                 calibrated airplane
                                 instruments; the
                                 force/position
                                 measurements of
                                 flight deck controls;
                                 and a stop watch.
------------------------------------------------------------------------
2.d.6.a.......................  Data may be acquired
Handling qualities............   by using an inertial
Lateral directional tests.....   measurement system
Rudder response...............   and a synchronized
                                 video of the
                                 calibrated airplane
                                 instruments; the
                                 force/position
                                 measurements of
                                 rudder pedals.
------------------------------------------------------------------------
2.d.7.........................  Data may be acquired
Handling qualities............   by using an inertial
Lateral directional tests.....   measurement system
Dutch roll, (yaw damper OFF)..   and a synchronized
                                 video of the
                                 calibrated airplane
                                 instruments and the
                                 force/position
                                 measurements of
                                 flight deck controls.
------------------------------------------------------------------------

2.d.8.........................  Data may be acquired
Handling qualities............   by using an inertial
Lateral directional tests.....   measurement system
Steady state sideslip.........   and a synchronized
                                 video of the
                                 calibrated airplane
                                 instruments and the
                                 force/position
                                 measurements of
                                 flight deck controls.
------------------------------------------------------------------------

Attachment 3 to Appendix B to Part 60--Flight Training Device (FTD)
Subjective Evaluation

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

Begin Information

1. Discussion

    a. The subjective tests provide a basis for evaluating the
capability of the FTD to perform over a typical utilization period.
The items listed in the Table of Functions and Subjective Tests are
used to determine whether the FTD competently simulates each
required maneuver, procedure, or task; and verifying correct
operation of the FTD controls, instruments, and systems. The tasks
do not limit or exceed the authorizations for use of a given level
of FTD as described on the Statement of Qualification or as may be
approved by the TPAA. All items in the following paragraphs are
subject to examination.
    b. All simulated airplane systems functions will be assessed for
normal and, where appropriate, alternate operations. 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.
    c. At the request of the TPAA, the NSP Pilot may assess the FTD
for a special aspect of a sponsor's training program during the
functions and subjective portion of an evaluation. Such an
assessment may include a portion of a specific operation (e.g., a
Line Oriented Flight Training (LOFT) scenario) or special emphasis
items in the sponsor's training program. Unless directly related to
a requirement for the qualification level, the results of such an
evaluation would not affect the qualification of the FTD.

End Information

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

     Table B3A.--Table of Functions and Subjective Tests Level 6 FTD
------------------------------------------------------------------------
                         <<>>
-------------------------------------------------------------------------
       Number                          Operations tasks
------------------------------------------------------------------------
  Tasks in this table are subject to evaluation if appropriate for the
      airplane system or systems simulated as indicated in the SOQ
 Configuration List as defined in Appendix B, Attachment 2 of this part.
------------------------------------------------------------------------
1. Preflight
------------------------------------------------------------------------
                      Accomplish a functions check of all installed
                       switches, indicators, systems, and equipment at
                       all crewmembers' and instructors' stations, and
                       determine that the flight deck (or flight deck
                       area) design and functions replicate the
                       appropriate airplane.
------------------------------------------------------------------------
2. Surface Operations (pre-takeoff)
------------------------------------------------------------------------
2.a.................  Engine start:
------------------------------------------------------------------------
2.a.1...............  Normal start.
------------------------------------------------------------------------
2.a.2...............  Alternative procedures start.
------------------------------------------------------------------------
2.a.3...............  Abnormal procedures start/shut down.
------------------------------------------------------------------------
2.b.................  Pushback/Powerback (powerback requires visual
                       system).
------------------------------------------------------------------------
3. Takeoff (requires appropriate visual system as set out in Table B1A,
 item 6; Appendix B, Attachment 1.)
------------------------------------------------------------------------
3.a.................  Instrument takeoff:
------------------------------------------------------------------------
3.a.1...............  Engine checks (e.g., engine parameter
                       relationships, propeller/mixture controls).
------------------------------------------------------------------------
3.a.2...............  Acceleration characteristics.
------------------------------------------------------------------------
3.a.3...............  Nosewheel/rudder steering.
------------------------------------------------------------------------
3.a.4...............  Landing gear, wing flap, leading edge device
                       operation.
------------------------------------------------------------------------
3.b.................  Rejected takeoff:
------------------------------------------------------------------------
3.b.1...............  Deceleration characteristics.
------------------------------------------------------------------------
3.b.2...............  Brakes/engine reverser/ground spoiler operation.
------------------------------------------------------------------------

3.b.3...............  Nosewheel/rudder steering.
------------------------------------------------------------------------
4. In-Flight Operations
------------------------------------------------------------------------
4.a.................  Normal climb.
------------------------------------------------------------------------
4.b.................  Cruise:
------------------------------------------------------------------------
4.b.1...............  Demonstration of performance characteristics
                       (speed vs. power).
------------------------------------------------------------------------
4.b.2...............  Normal turns.
------------------------------------------------------------------------
4.b.3...............  Demonstration of high altitude handling.
------------------------------------------------------------------------
4.b.4...............  Demonstration of high airspeed handling/overspeed
                       warning.
------------------------------------------------------------------------
4.b.5...............  Demonstration of Mach effects on control and trim.
------------------------------------------------------------------------
4.b.6...............  Steep turns.
------------------------------------------------------------------------
4.b.7...............  In-Flight engine shutdown (procedures only).
------------------------------------------------------------------------
4.b.8...............  In-Flight engine restart (procedures only).
------------------------------------------------------------------------
4.b.9...............  Specific flight characteristics.
------------------------------------------------------------------------
4.b.10..............  Response to loss of flight control power.
------------------------------------------------------------------------
4.b.11..............  Response to other flight control system failure
                       modes.
------------------------------------------------------------------------
4.b.12..............  Operations during icing conditions.
------------------------------------------------------------------------
4.b.13..............  Effects of airframe/engine icing.
------------------------------------------------------------------------
4.c.................  Other flight phase:
------------------------------------------------------------------------
4.c.1...............  Approach to stalls in the following
                       configurations:
------------------------------------------------------------------------
4.c.1.a.............  Cruise.
------------------------------------------------------------------------
4.c.1.b.............  Takeoff or approach.
------------------------------------------------------------------------
4.c.1.c.............  Landing.
------------------------------------------------------------------------
4.c.2...............  High angle of attack maneuvers in the following
                       configurations:
------------------------------------------------------------------------
4.c.2.a.............  Cruise.
------------------------------------------------------------------------
4.c.2.b.............  Takeoff or approach.
------------------------------------------------------------------------
4.c.2.c.............  Landing.
------------------------------------------------------------------------
4.c.3...............  Slow flight
------------------------------------------------------------------------
4.c.4...............  Holding.
------------------------------------------------------------------------
5. Approaches
------------------------------------------------------------------------
5.a.                  ..................................................
5.a.1...............  With use of autopilot and autothrottle, as
                       applicable.
------------------------------------------------------------------------
5.a.2...............  Without use of autopilot and autothrottle, as
                       applicable.
------------------------------------------------------------------------
5.a.3...............  With 10 knot tail wind.
------------------------------------------------------------------------
5.a.4...............  With 10 knot crosswind.
------------------------------------------------------------------------
5.b.................  Precision Instrument Approaches:
------------------------------------------------------------------------
5.b.1...............  With use of autopilot, autothrottle, and autoland,
                       as applicable.
------------------------------------------------------------------------

5.b.2...............  Without use of autopilot, autothrottle, and
                       autoland, as applicable.
------------------------------------------------------------------------
5.b.3...............  With 10 knot tail wind.
------------------------------------------------------------------------
5.b.4...............  With 10 knot crosswind.
------------------------------------------------------------------------
6. Missed Approach
------------------------------------------------------------------------
6.a.................  Manually controlled.
------------------------------------------------------------------------
6.b.................  Automatically controlled (if applicable).
------------------------------------------------------------------------
7. Any Flight Phase, as appropriate
------------------------------------------------------------------------
7.a.................  Normal system operation (installed systems).
------------------------------------------------------------------------
7.b.................  Abnormal/Emergency system operation (installed
                       systems).
------------------------------------------------------------------------
7.c.................  Flap operation.
------------------------------------------------------------------------
7.d.................  Landing gear operation.
------------------------------------------------------------------------
7.e.................  Engine Shutdown and Parking.
------------------------------------------------------------------------
7.e.1...............  Systems operation.
------------------------------------------------------------------------
7.e.2...............  Parking brake operation.
------------------------------------------------------------------------
8. Instructor Operating Station (IOS), as appropriate. Functions in this
 section are subject to evaluation only if appropriate for the airplane
 and/or installed on the specific FTD involved
------------------------------------------------------------------------
8.a.................  Power Switch(es).
------------------------------------------------------------------------
8.b.................  Airplane conditions.
------------------------------------------------------------------------
8.b.1...............  Gross weight, center of gravity, and fuel loading
                       and allocation.
------------------------------------------------------------------------
8.b.2...............  Airplane systems status.
------------------------------------------------------------------------
8.b.3...............  Ground crew functions (e.g., external power, push
                       back).
------------------------------------------------------------------------
8.c.................  Airports.
------------------------------------------------------------------------
8.c.1...............  Selection.
------------------------------------------------------------------------
8.c.2...............  Runway selection.
------------------------------------------------------------------------
8.c.3...............  Preset positions (e.g., ramp, over FAF).
------------------------------------------------------------------------
8.d.................  Environmental controls.
------------------------------------------------------------------------
8.d.1...............  Temperature.
------------------------------------------------------------------------
8.d.2...............  Climate conditions (e.g., ice, rain).
------------------------------------------------------------------------
8.d.3...............  Wind speed and direction.
------------------------------------------------------------------------
8.e.................  Airplane system malfunctions.
------------------------------------------------------------------------
8.e.1...............  Insertion/deletion.
------------------------------------------------------------------------
8.e.2...............  Problem clear.
------------------------------------------------------------------------
8.f.................  Locks, Freezes, and Repositioning.
------------------------------------------------------------------------
8.f.1...............  Problem (all) freeze/release.
------------------------------------------------------------------------
8.f.2...............  Position (geographic) freeze/release.
------------------------------------------------------------------------
8.f.3...............  Repositioning (locations, freezes, and releases).
------------------------------------------------------------------------

8.f.4...............  Ground speed control.
------------------------------------------------------------------------
8.f.5...............  Remote IOS, if installed.
------------------------------------------------------------------------
9. Sound Controls. On/off/adjustment
------------------------------------------------------------------------
10. Control Loading System (as applicable) On/off/emergency stop
------------------------------------------------------------------------
11. Observer Stations
------------------------------------------------------------------------
11.a................  Position.
------------------------------------------------------------------------
11.b................  Adjustments.
------------------------------------------------------------------------

End QPS Requirements

     Table B3B.--Table of Functions and Subjective Tests Level 5 FTD
------------------------------------------------------------------------
                         <<>>
-------------------------------------------------------------------------
       Number                          Operations tasks
------------------------------------------------------------------------
  Tasks in this table are subject to evaluation if appropriate for the
      airplane system or systems simulated as indicated in the SOQ
 Configuration List as defined in Appendix B, Attachment 2 of this part.
------------------------------------------------------------------------
1. Preflight
------------------------------------------------------------------------
                      Accomplish a functions check of all installed
                       switches, indicators, systems, and equipment at
                       all crewmembers' and instructors' stations, and
                       determine that the flight deck (or flight deck
                       area) design and functions replicate the
                       appropriate airplane.
------------------------------------------------------------------------
2. Surface Operations (pre-takeoff)
------------------------------------------------------------------------
2.a.................  Engine start (if installed):
------------------------------------------------------------------------
2.a.1...............  Normal start.
------------------------------------------------------------------------
2.a.2...............  Alternative procedures start.
------------------------------------------------------------------------
2.a.3...............  Abnormal/Emergency procedures start/shut down.
------------------------------------------------------------------------
3. In-Flight Operations
------------------------------------------------------------------------
3.a.................  Normal climb.
------------------------------------------------------------------------
3.b.................  Cruise:
------------------------------------------------------------------------
3.b.1...............  Performance characteristics (speed vs. power).
------------------------------------------------------------------------
3.b.2...............  Normal turns.
------------------------------------------------------------------------
3.c.................  Normal descent.
------------------------------------------------------------------------
4. Approaches
------------------------------------------------------------------------
4.a.................  Coupled instrument approach maneuvers (as
                       applicable for the systems installed).
------------------------------------------------------------------------
5. Any Flight Phase
------------------------------------------------------------------------
5.a.................  Normal system operation (Installed systems).
------------------------------------------------------------------------
5.b.................  Abnormal/Emergency system operation (installed
                       systems).
------------------------------------------------------------------------
5.c.................  Flap operation.
------------------------------------------------------------------------
5.d.................  Landing gear operation.
------------------------------------------------------------------------
5.e.................  Engine Shutdown and Parking (if installed).
------------------------------------------------------------------------
5.e.1...............  Systems operation.
------------------------------------------------------------------------

5.e.2...............  Parking brake operation.
------------------------------------------------------------------------
6. Instructor Operating Station (IOS)
------------------------------------------------------------------------
6.a.................  Power Switch(es).
------------------------------------------------------------------------
6.b.................  Preset positions--ground, air.
------------------------------------------------------------------------
6.c.................  Airplane system malfunctions (Installed systems).
------------------------------------------------------------------------
6.c.1...............  Insertion/deletion.
------------------------------------------------------------------------
6.c.2...............  Problem clear.
------------------------------------------------------------------------

     Table B3C.--Table of Functions and Subjective Tests Level 4 FTD
------------------------------------------------------------------------
                         <<>>
-------------------------------------------------------------------------
       Number                          Operations tasks
------------------------------------------------------------------------
  Tasks in this table are subject to evaluation if appropriate for the
      airplane system or systems simulated as indicated in the SOQ
 Configuration List as defined in Appendix B, Attachment 2 of this part.
------------------------------------------------------------------------
1...................  Level 4 FTDs are required to have at least one
                       operational system. The NSPM will accomplish a
                       functions check of all installed systems,
                       switches, indicators, and equipment at all
                       crewmembers' and instructors' stations, and
                       determine that the flight deck (or flight deck
                       area) design and functions replicate the
                       appropriate airplane.
------------------------------------------------------------------------

Attachment 4 to Appendix B to Part 60--Sample Documents

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

Begin Information

Table of Contents

Title of Sample

Figure B4A Sample Letter, Request for Initial, Upgrade, or
Reinstatement Evaluation
Figure B4B Attachment: FSTD Information Form
Figure B4C Sample Qualification Test Guide Cover Page
Figure B4D Sample Statement of Qualification--Certificate
Figure B4E Sample Statement of Qualification--Configuration List
Figure B4F Sample Statement of Qualification--List of Qualified
Tasks
Figure B4G Sample Continuing Qualification Evaluation Requirements
Page
Figure B4H Sample MQTG Index of Effective FSTD Directives
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Attachment 5 to Appendix B to Part 60--FSTD Directives Applicable to
Airplane Flight Training Devices

Appendix C to Part 60--Qualification Performance Standards for
Helicopter Full Flight Simulators

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

Begin Information

    This appendix establishes the standards for Helicopter Full
Flight Simulator (FFS) evaluation and qualification. The Flight
Standards Service, National Simulator Program Manager (NSPM), is
responsible for the development, application, and implementation of
the standards contained within this appendix. The procedures and
criteria specified in this appendix will be used by the NSPM, or a
person assigned by the NSPM, when conducting helicopter FFS
evaluations.

Table of Contents

1. Introduction
2. Applicability (Sec.  60.1) and (Sec.  60.2)
3. Definitions (Sec.  60.3)
4. Qualification Performance Standards (Sec.  60.4)
5. Quality Management System (Sec.  60.5)
6. Sponsor Qualification Requirements (Sec.  60.7)
7. Additional Responsibilities of the Sponsor (Sec.  60.9)
8. FSTD Use (Sec.  60.11)
9. FSTD Objective Data Requirements (Sec.  60.13)
10. Special Equipment and Personnel Requirements for Qualification
of the FSTD (Sec.  60.14)
11. Initial (and Upgrade) Qualification Requirements (Sec.  60.15)
12. Additional Qualifications for a Currently Qualified FSTDs (Sec.
60.16)
13. Previously Qualified FSTDs (Sec.  60.17)
14. Inspection, Continuing Qualification Evaluation, and Maintenance
Requirements (Sec.  60.19)
15. Logging FSTD Discrepancies (Sec.  60.20)
16. Interim Qualification of FSTDs for New Helicopter Types or
Models (Sec.  60.21)
17. Modifications to FSTDs (Sec.  60.23)
18. Operations with Missing, Malfunctioning, or Inoperative
Components (Sec.  60.25)
19. Automatic Loss of Qualification and Procedures for Restoration
of Qualification (Sec.  60.27)
20. Other Losses of Qualification and Procedures for Restoration of
Qualification (Sec.  60.29)
21. Record Keeping and Reporting (Sec.  60.31)
22. Applications, Logbooks, Reports, and Records: Fraud,
Falsification, or Incorrect Statements (Sec.  60.33)
23. [Reserved]
24. [Reserved]
25. FSTD Qualification on the Basis of a Bilateral Aviation Safety
Agreement (BASA) (Sec.  60.37)
Attachment 1 to Appendix C to Part 60--General Simulator
Requirements
Attachment 2 to Appendix C to Part 60--Full Flight Simulator
Objective Tests
Attachment 3 to Appendix C to Part 60--Simulator Subjective
Evaluation
Attachment 4 to Appendix C to Part 60--Sample Documents
Attachment 5 to Appendix C to Part 60--FSTD Directives Applicable to
Helicopter Full Flight Simulators

End Information

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

1. Introduction

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

Begin Information

    a. This appendix contains background information as well as
regulatory and informative material as described later in this
section. To assist the reader in determining what areas are required
and what areas are permissive, the text in this appendix is divided
into two sections: ``QPS Requirements'' and ``Information.'' The QPS
Requirements sections contain details regarding compliance with the
part 60 rule language. These details are regulatory, but are found
only in this appendix. The Information sections contain material
that is advisory in nature, and designed to give the user general
information about the regulation.
    b. Questions regarding the contents of this publication should
be sent to the U.S. Department of Transportation, Federal Aviation
Administration, Flight Standards Service, National Simulator Program
Staff, AFS-205, 100 Hartsfield Centre Parkway, Suite 400, Atlanta,
Georgia 30354. Telephone contact numbers for the NSP are: phone,
404-832-4700; fax,<PHONE_NUMBER>. The general e-mail address for the
NSP office is<EMAIL_ADDRESS>The NSP Internet Web Site
address is: http://www.faa.gov/safety/programs_initiatives/aircraft_aviation/nsp/.
 On this Web Site you will find an NSP

personnel list with telephone and e-mail contact information for
each NSP staff member, a list of qualified flight simulation
devices, advisory circulars, a description of the qualification
process, NSP policy, and an NSP ``In-Works'' section. Also linked
from this site are additional information sources, handbook
bulletins, frequently asked questions, a listing and text of the
Federal Aviation Regulations, Flight Standards Inspector's
handbooks, and other FAA links.
    c. The NSPM encourages the use of electronic media for all
communication, including any record, report, request, test, or
statement required by this appendix. The electronic media used must
have adequate security provisions and be acceptable to the NSPM. The
NSPM recommends inquiries on system compatibility, and minimum
system requirements are also included on the NSP Web site.
    d. Related Reading References.
    (1) 14 CFR part 60.
    (2) 14 CFR part 61.
    (3) 14 CFR part 63.
    (4) 14 CFR part 119
    (5) 14 CFR part 121.
    (6) 14 CFR part 125
    (7) 14 CFR part 135.
    (8) 14 CFR part 141.
    (9) 14 CFR part 142.
    (10) AC 120-35B, Line Operational Simulations: Line-Oriented
Flight Training, Special Purpose Operational Training, Line
Operational Evaluation.
    (11) AC 120-57A, Surface Movement Guidance and Control System
(SMGS).
    (12) AC 150/5300-13, Airport Design.
    (13) AC 150/5340-1G, Standards for Airport Markings.
    (14) AC 150/5340-4C, Installation Details for Runway Centerline
Touchdown Zone Lighting Systems.
    (15) AC 150/5340-19, Taxiway Centerline Lighting System.
    (16) AC 150/5340-24, Runway and Taxiway Edge Lighting System.
    (17) AC 150/5345-28D, Precision Approach Path Indicator (PAPI)
Systems.
    (18) AC 150/5390-2B, Heliport Design.
    (19) International Air Transport Association document, ``Flight
Simulator Design and Performance Data Requirements,'' as amended.
    (20) AC 29-2B, Flight Test Guide for Certification of Transport
Category Rotorcraft.
    (21) AC 27-1A, Flight Test Guide for Certification of Normal
Category Rotorcraft.
    (22) International Civil Aviation Organization (ICAO) Manual of
Criteria for the Qualification of Flight Simulators, as amended.
    (23) Airplane Flight Simulator Evaluation Handbook, Volume I, as
amended and Volume II, as amended, The Royal Aeronautical Society,
London, UK.
    (24) FAA Publication FAA-S-8081 series (Practical Test Standards
for Airline Transport Pilot Certificate, Type Ratings, Commercial
Pilot, and Instrument Ratings).
    (25) The FAA Aeronautical Information Manual (AIM). An
electronic version of the AIM is on the Internet at http://www.faa.gov/atpubs
.

End Information

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

2. Applicability (Sec. Sec.  60.1 and 60.2)

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

Begin Information

    No additional regulatory or informational material applies to
Sec.  60.1, Applicability, or to Sec.  60.2, Applicability of
sponsor rules to persons who are not sponsors and who are engaged in
certain unauthorized activities.

End Information

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

3. Definitions (Sec.  60.3)

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

Begin Information

    See Appendix F of this part for a list of definitions and
abbreviations from part 1 and part 60, including the appropriate
appendices of part 60.

End Information

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

4. Qualification Performance Standards (Sec.  60.4)

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

Begin Information

    No additional regulatory or informational material applies to
Sec.  60.4, Qualification Performance Standards.

End Information

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

5. Quality Management System (Sec.  60.5)

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

Begin Information

    See Appendix E of this part for additional regulatory and
informational material regarding Quality Management Systems.

End Information

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

6. Sponsor Qualification Requirements (Sec.  60.7)

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

Begin Information

    a. The intent of the language in Sec.  60.7(b) is to have a
specific FFS, identified by the sponsor, used at least once in an
FAA-approved flight training program for the helicopter simulated
during the 12-month period described. The identification of the
specific FFS may change from one 12-month period to the next 12-
month period as long as that sponsor sponsors and uses at least one
FFS at least once during the prescribed period. There is no minimum
number of hours or minimum FFS periods required.
    b. The following examples describe acceptable operational
practices:
    (1) Example One.
    (a) A sponsor is sponsoring a single, specific FFS for its own
use, in its own facility or elsewhere--this single FFS forms the
basis for the sponsorship. The sponsor uses that FFS at least once
in each 12-month period in that sponsor's FAA-approved flight
training program for the helicopter simulated. This 12-month period
is established according to the following schedule:
    (i) If the FFS was qualified prior to May 30, 2008, the 12-month
period begins on the date of the first continuing qualification
evaluation conducted in accordance with Sec.  60.19 after (60 days
after date of publication of the final rule in the Federal Register)
and continues for each subsequent 12-month period;
    (ii) A device qualified on or after May 30, 2008, will be
required to undergo an initial or upgrade evaluation in accordance
with Sec.  60.15. Once the initial or upgrade evaluation is
complete, the first continuing qualification evaluation will be
conducted within 6 months. The 12-month continuing qualification
evaluation cycle begins on that date and continues for each
subsequent 12-month period.
    (b) There is no minimum number of hours of FFS use required.
    (c) The identification of the specific FFS may change from one
12-month period to the next 12-month period as long as that sponsor
sponsors and uses at least one FFS at least once during the
prescribed period.
    (2) Example Two.
    (a) A sponsor sponsors an additional number of FFSs, in its
facility or elsewhere. Each additionally sponsored FFS must be--
    (i) Used by the sponsor in the sponsor's FAA-approved flight
training program for the helicopter simulated (as described in Sec.
60.7(d)(1)); or
    (ii) Used by another FAA certificate holder in that other
certificate holder's FAA-approved flight training program for the
helicopter simulated (as described in Sec.  60.7(d)(1)). This 12-
month period is established in the same manner as in example one; or
    (iii) Provided a statement each year from a qualified pilot,
(after having flown the helicopter, not the subject FFS or another

FFS, during the preceding 12-month period) stating that the subject
FFS's performance and handling qualities represent the helicopter
(as described in Sec.  60.7(d)(2)). This statement is provided at
least once in each 12-month period established in the same manner as
in example one.
    (b) There is no minimum number of hours of FFS use required.
    (3) Example Three.
    (a) A sponsor in New York (in this example, a Part 142
certificate holder) establishes ``satellite'' training centers in
Chicago and Moscow.
    (b) The satellite function means that the Chicago and Moscow
centers must operate under the New York center's certificate (in
accordance with all of the New York center's practices, procedures,
and policies; e.g., instructor and/or technician training/checking
requirements, record keeping, QMS program).
    (c) All of the FFSs in the Chicago and Moscow centers could be
dry-leased (i.e., the certificate holder does not have and use FAA-
approved flight training programs for the FFSs in the Chicago and
Moscow centers) because--
    (i) Each FFS in the Chicago center and each FFS in the Moscow
center is used at least once each 12-month period by another FAA
certificate holder in that other certificate holder's FAA-approved
flight training program for the helicopter (as described in Sec.
60.7(d)(1)); or
    (ii) A statement is obtained from a qualified pilot (having
flown the helicopter, not the subject FFS or another FFS during the
preceding 12-month period) stating that the performance and handling
qualities of each FFS in the Chicago and Moscow centers represent
the helicopter (as described in Sec.  60.7(d)(2)).

End Information

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

7. Additional Responsibilities of the Sponsor (Sec.  60.9)

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

Begin Information

    The phrase ``as soon as practicable'' in Sec.  60.9(a) means
without unnecessarily disrupting or delaying beyond a reasonable
time the training, evaluation, or experience being conducted in the
FSTD.

End Information

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8. FSTD Use (Sec.  60.11)

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

Begin Information

    No additional regulatory or informational material applies to
Sec.  60.11, FSTD Use.

End Information

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

9. FSTD Objective Data Requirements (Sec.  60.13)

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

Begin QPS Requirements

    a. Flight test data used to validate FFS performance and
handling qualities must have been gathered in accordance with a
flight test program containing the following:
    (1) A flight test plan consisting of:
    (a) The maneuvers and procedures required for aircraft
certification and simulation programming and validation
    (b) For each maneuver or procedure--
    (i) The procedures and control input the flight test pilot and/
or engineer used.
    (ii) The atmospheric and environmental conditions.
    (iii) The initial flight conditions.
    (iv) The helicopter configuration, including weight and center
of gravity.
    (v) The data to be gathered.
    (vi) All other information necessary to recreate the flight test
conditions in the FFS.
    (2) Appropriately qualified flight test personnel.
    (3) An understanding of the accuracy of the data to be gathered
using appropriate alternative data sources, procedures, and
instrumentation that is traceable to a recognized standard as
described in Attachment 2, Table C2D.
    (4) Appropriate and sufficient data acquisition equipment or
system(s), including appropriate data reduction and analysis methods
and techniques, as would be acceptable to the FAA's Aircraft
Certification Service.
    b. The data, regardless of source, must be presented:
    (1) in a format that supports the FFS validation process;
    (2) in a manner that is clearly readable and annotated correctly
and completely;
    (3) with resolution sufficient to determine compliance with the
tolerances set forth in Attachment 2, Table C2A of this appendix.
    (4) with any necessary instructions or other details provided,
such as yaw damper or throttle position; and
    (5) without alteration, adjustments, or bias; however the data
may be rescaled, digitized, or otherwise manipulated to fit the
desired presentation.
    c. After completion of any additional flight test, a flight test
report must be submitted in support of the validation data. The
report must contain sufficient data and rationale to support
qualification of the FFS at the level requested.
    d. As required by Sec.  60.13(f), the sponsor must notify the
NSPM when it becomes aware that an addition to, an amendment to, or
a revision of data that may relate to FFS performance or handling
characteristics is available. The data referred to in this paragraph
are those data that are used to validate the performance, handling
qualities, or other characteristics of the aircraft, including data
related to any relevant changes occurring after the type certificate
was issued. The sponsor must--
    (1) Within 10 calendar days, notify the NSPM of the existence of
this data; and
    (2) Within 45 calendar days, notify the NSPM of--
    (a) The schedule to incorporate this data into the FFS; or
    (b) The reason for not incorporating this data into the FFS.
    e. In those cases where the objective test results authorize a
``snapshot test'' or a ``series of snapshot test results'' in lieu
of a time-history result, the sponsor or other data provider must
ensure that a steady state condition exists at the instant of time
captured by the ``snapshot.'' The steady state condition must exist
from 4 seconds prior to, through 1 second following, the instant of
time captured by the snapshot.

End QPS Requirements

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

Begin Information

    f. The FFS sponsor is encouraged to maintain a liaison with the
manufacturer of the aircraft being simulated (or with the holder of
the aircraft type certificate for the aircraft being simulated if
the manufacturer is no longer in business), and, if appropriate,
with the person who supplied the aircraft data package for the FFS
in order to facilitate the notification required by Sec.  60.13(f).
    g. It is the intent of the NSPM that for new aircraft entering
service, at a point well in advance of preparation of the
Qualification Test Guide (QTG), the sponsor should submit to the
NSPM for approval, a descriptive document (a validation data
roadmap) containing the plan for acquiring the validation data,
including data sources. This document should clearly identify
sources of data for all required tests, a description of the
validity of these data for a specific engine type and thrust rating
configuration, and the revision levels of all avionics affecting the
performance or flying qualities of the aircraft. Additionally, this
document should provide other information, such as the rationale or
explanation for cases where data or data parameters are missing,
instances where engineering simulation data are used or where flight
test methods require further explanations. It should also provide a
brief narrative describing the cause and effect of any deviation
from data requirements. The aircraft manufacturer may provide this
document.
    h. There is no requirement for any flight test data supplier to
submit a flight test plan or program prior to gathering flight test
data. However, the NSPM notes that inexperienced data gatherers
often provide data that is irrelevant, improperly marked, or lacking
adequate justification for selection. Other problems include
inadequate information regarding initial conditions or test
maneuvers. The NSPM has been forced to refuse these data submissions
as validation data for an FFS evaluation. It is for this reason that
the NSPM recommends that any data supplier not previously
experienced in this area review the data necessary for programming
and for validating the performance of the FFS, and discuss the
flight test plan anticipated for acquiring such data with the NSPM
well in advance of commencing the flight tests.
    i. The NSPM will consider, on a case-by-case basis, whether to
approve supplemental validation data derived from flight data
recording systems such as a Quick Access Recorder or Flight Data
Recorder.

End Information

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

10. Special Equipment and Personnel Requirements for Qualification of
the FSTD (Sec.  60.14)

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

Begin Information

    a. In the event that the NSPM determines that special equipment
or specifically qualified persons will be required to conduct an
evaluation, the NSPM will make every attempt to notify the sponsor
at least one (1) week, but in no case less than 72 hours, in advance
of the evaluation. Examples of special equipment include spot
photometers, flight control measurement devices, and sound
analyzers. Examples of specially qualified personnel include
individuals specifically qualified to install or use any special
equipment when its use is required.
    b. Examples of a special evaluation include an evaluation
conducted after an FFS is moved, at the request of the TPAA, or as a
result of comments received from users of the FFS that raise
questions about the continued qualification or use of the FFS.

End Information

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

11. Initial (and Upgrade) Qualification Requirements (Sec.  60.15)

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

Begin QPS Requirements

    a. In order to be qualified at a particular qualification level,
the FFS must:
    (1) Meet the general requirements listed in Attachment 1;
    (2) Meet the objective testing requirements listed in Attachment
2; and
    (3) Satisfactorily accomplish the subjective tests listed in
Attachment 3.
    b. The request described in Sec.  60.15(a) must include all of
the following:
    (1) A statement that the FFS meets all of the applicable
provisions of this part and all applicable provisions of the QPS.
    (2) A confirmation that the sponsor will forward to the NSPM the
statement described in Sec.  60.15(b) in such time as to be received
no later than 5 business days prior to the scheduled evaluation and
may be forwarded to the NSPM via traditional or electronic means.
    (3) A qualification test guide (QTG), acceptable to the NSPM,
that includes all of the following:
    (a) Objective data obtained from aircraft testing or another
approved source.
    (b) Correlating objective test results obtained from the
performance of the FFS as prescribed in the appropriate QPS.
    (c) The result of FFS subjective tests prescribed in the
appropriate QPS.
    (d) A description of the equipment necessary to perform the
evaluation for initial qualification and the continuing
qualification evaluations.
    c. The QTG described in paragraph (a)(3) of this section, must
provide the documented proof of compliance with the simulator
objective tests in Attachment 2, Table C2A of this appendix.
    d. The QTG is prepared and submitted by the sponsor, or the
sponsor's agent on behalf of the sponsor, to the NSPM for review and
approval, and must include, for each objective test:
    (1) Parameters, tolerances, and flight conditions.
    (2) Pertinent and complete instructions for the conduct of
automatic and manual tests.
    (3) A means of comparing the FFS test results to the objective
data.
    (4) Any other information as necessary, to assist in the
evaluation of the test results.
    (5) Other information appropriate to the qualification level of
the FFS.
    e. The QTG described in paragraphs (a)(3) and (b) of this
section, must include the following:
    (1) A QTG cover page with sponsor and FAA approval signature
blocks (see Attachment 4, Figure C4C, for a sample QTG cover page).
    (2) A continuing qualification evaluation schedule requirements
page. This page will be used by the NSPM to establish and record the
frequency with which continuing qualification evaluations must be
conducted and any subsequent changes that may be determined by the
NSPM in accordance with Sec.  60.19. See Attachment 4, Figure C4G,
for a sample Continuing Qualification Evaluation Requirements page.
    (3) An FFS information page that provides the information listed
in this paragraph (see Attachment 4, Figure C4B, for a sample FFS
information page). For convertible FFSs, the sponsor must submit a
separate page for each configuration of the FFS.
    (a) The sponsor's FFS identification number or code.
    (b) The helicopter model and series being simulated.
    (c) The aerodynamic data revision number or reference.
    (d) The source of the basic aerodynamic model and the
aerodynamic coefficient data used to modify the basic model.
    (e) The engine model(s) and its data revision number or
reference.
    (f) The flight control data revision number or reference.
    (g) The flight management system identification and revision
level.
    (h) The FFS model and manufacturer.
    (i) The date of FFS manufacture.
    (j) The FFS computer identification.
    (k) The visual system model and manufacturer, including display
type.
    (l) The motion system type and manufacturer, including degrees
of freedom.
    (4) A Table of Contents.
    (5) A log of revisions and a list of effective pages.
    (6) List of all relevant data references.
    (7) A glossary of terms and symbols used (including sign
conventions and units).
    (8) Statements of compliance and capability (SOCs) with certain
requirements. SOCs must provide references to the sources of
information that show the capability of the FFS to comply with the
requirement, a rationale explaining how the referenced material is
used, mathematical equations and parameter values used, and the
conclusions reached; i.e., that the FFS complies with the
requirement.
    (9) Recording procedures or equipment required to accomplish the
objective tests.
    (10) The following information for each objective test
designated in Attachment 2, Table C2A, as applicable to the
qualification level sought:
    (a) Name of the test.
    (b) Objective of the test.
    (c) Initial conditions.
    (d) Manual test procedures.
    (e) Automatic test procedures (if applicable).
    (f) Method for evaluating FFS objective test results.
    (g) List of all relevant parameters driven or constrained during
the automatically conducted test(s).
    (h) List of all relevant parameters driven or constrained during
the manually conducted test(s).
    (i) Tolerances for relevant parameters.
    (j) Source of Validation Data (document and page number).
    (k) Copy of the Validation Data (if located in a separate
binder, a cross reference for the identification and page number for
pertinent data location must be provided).
    (l) Simulator Objective Test Results as obtained by the sponsor.
Each test result must reflect the date completed and must be clearly
labeled as a product of the device being tested.
    f. A convertible FFS is addressed as a separate FFS for each
model and series helicopter to which it will be converted and for
the FAA qualification level sought. If a sponsor seeks qualification
for two or more models of a helicopter type using a convertible FFS,
the sponsor must submit a QTG for each helicopter model, or a QTG
for the first helicopter model and a supplement to that QTG for each
additional helicopter model. The NSPM will conduct evaluations for
each helicopter model.
    g. Form and manner of presentation of objective test results in
the QTG:
    (1) The sponsor's FFS test results must be recorded in a manner
acceptable to the NSPM, that allows easy comparison of the FFS test
results to the validation data (e.g., use of a multi-channel
recorder, line printer, cross plotting, overlays, transparencies).
    (2) FFS results must be labeled using terminology common to
helicopter parameters as opposed to computer software
identifications.
    (3) Validation data documents included in a QTG may be
photographically reduced only if such reduction will not alter the
graphic scaling or cause difficulties in scale interpretation or
resolution.
    (4) Scaling on graphical presentations must provide the
resolution necessary to evaluate the parameters shown in Attachment
2, Table C2A of this appendix.
    (5) Tests involving time histories, data sheets (or
transparencies thereof) and FFS test results must be clearly marked
with appropriate reference points to ensure an accurate comparison
between the FFS and the helicopter with respect to time. Time
histories recorded via a line printer are to be clearly identified
for cross plotting on the helicopter data. Over-plots must not
obscure the reference data.
    h. The sponsor may elect to complete the QTG objective and
subjective tests at the manufacturer's facility or at the sponsor's
training facility. If the tests are conducted at the manufacturer's
facility, the sponsor must

repeat at least one-third of the tests at the sponsor's training
facility in order to substantiate FFS performance. The QTG must be
clearly annotated to indicate when and where each test was
accomplished. Tests conducted at the manufacturer's facility and at
the sponsor's training facility must be conducted after the FFS is
assembled with systems and sub-systems functional and operating in
an interactive manner. The test results must be submitted to the
NSPM.
    i. The sponsor must maintain a copy of the MQTG at the FFS
location.
    j. All FFSs for which the initial qualification is conducted
after May 30, 2014, must have an electronic MQTG (eMQTG) including
all objective data obtained from helicopter testing, or another
approved source (reformatted or digitized), together with
correlating objective test results obtained from the performance of
the FFS (reformatted or digitized) as prescribed in this appendix.
The eMQTG must also contain the general FFS performance or
demonstration results (reformatted or digitized) prescribed in this
appendix, and a description of the equipment necessary to perform
the initial qualification evaluation and the continuing
qualification evaluations. The eMQTG must include the original
validation data used to validate FFS performance and handling
qualities in either the original digitized format from the data
supplier or an electronic scan of the original time-history plots
that were provided by the data supplier. A copy of the eMQTG must be
provided to the NSPM.
    k. All other FFSs not covered in subparagraph ``j'' must have an
electronic copy of the MQTG by May 30, 2014. A copy of the eMQTG
must be provided to the NSPM. This may be provided by an electronic
scan presented in a Portable Document File (PDF), or similar format
acceptable to the NSPM.
    l. During the initial (or upgrade) qualification evaluation
conducted by the NSPM, the sponsor must also provide a person who is
a user of the device (e.g., a qualified pilot or instructor pilot
with flight time experience in that aircraft) and knowledgeable
about the operation of the aircraft and the operation of the FFS.

End QPS Requirements

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Begin Information

    m. Only those FFSs that are sponsored by a certificate holder as
defined in Appendix F will be evaluated by the NSPM. However, other
FFS evaluations may be conducted on a case-by-case basis as the
Administrator deems appropriate, but only in accordance with
applicable agreements.
    n. The NSPM will conduct an evaluation for each configuration,
and each FFS must be evaluated as completely as possible. To ensure
a thorough and uniform evaluation, each FFS is subjected to the
general simulator requirements in Attachment 1, the objective tests
listed in Attachment 2, and the subjective tests listed in
Attachment 3 of this appendix. The evaluations described herein will
include, but not necessarily be limited to the following:
    (1) Helicopter responses, including longitudinal and lateral-
directional control responses (see Attachment 2 of this appendix).
    (2) Performance in authorized portions of the simulated
helicopter's operating envelope, to include tasks evaluated by the
NSPM in the areas of surface operations, takeoff, climb, cruise,
descent, approach, and landing as well as abnormal and emergency
operations (see Attachment 2 of this appendix).
    (3) Control checks (see Attachment 1 and Attachment 2 of this
appendix).
    (4) Flight deck configuration (see Attachment 1 of this
appendix).
    (5) Pilot, flight engineer, and instructor station functions
checks (see Attachment 1 and Attachment 3 of this appendix).
    (6) Helicopter systems and sub-systems (as appropriate) as
compared to the helicopter simulated (see Attachment 1 and
Attachment 3 of this appendix).
    (7) FFS systems and sub-systems, including force cueing
(motion), visual, and aural (sound) systems, as appropriate (see
Attachment 1 and Attachment 2 of this appendix).
    (8) Certain additional requirements, depending upon the
qualification level sought, including equipment or circumstances
that may become hazardous to the occupants. The sponsor may be
subject to Occupational Safety and Health Administration
requirements.
    o. The NSPM administers the objective and subjective tests,
which includes an examination of functions. The tests include a
qualitative assessment of the FFS by an NSP pilot. The NSP
evaluation team leader may assign other qualified personnel to
assist in accomplishing the functions examination and/or the
objective and subjective tests performed during an evaluation when
required.
    (1) Objective tests provide a basis for measuring and evaluating
FFS performance and determining compliance with the requirements of
this part.
    (2) Subjective tests provide a basis for:
    (a) Evaluating the capability of the FFS to perform over a
typical utilization period;
    (b) Determining that the FFS satisfactorily simulates each
required task;
    (c) Verifying correct operation of the FFS controls,
instruments, and systems; and
    (d) Demonstrating compliance with the requirements of this part.
    p. The tolerances for the test parameters listed in Attachment 2
of this appendix reflect the range of tolerances acceptable to the
NSPM for FFS validation and are not to be confused with design
tolerances specified for FFS manufacture. In making decisions
regarding tests and test results, the NSPM relies on the use of
operational and engineering judgment in the application of data
(including consideration of the way in which the flight test was
flown and way the data was gathered and applied), data
presentations, and the applicable tolerances for each test.
    q. In addition to the scheduled continuing qualification
evaluation, each FFS is subject to evaluations conducted by the NSPM
at any time without prior notification to the sponsor. Such
evaluations would be accomplished in a normal manner (i.e.,
requiring exclusive use of the FFS for the conduct of objective and
subjective tests and an examination of functions) if the FFS is not
being used for flight crewmember training, testing, or checking.
However, if the FFS were being used, the evaluation would be
conducted in a non-exclusive manner. This non-exclusive evaluation
will be conducted by the FFS evaluator accompanying the check
airman, instructor, Aircrew Program Designee (APD), or FAA inspector
aboard the FFS along with the student(s) and observing the operation
of the FFS during the training, testing, or checking activities.
    r. Problems with objective test results are handled as follows:
    (1) If a problem with an objective test result is detected by
the NSP evaluation team during an evaluation, the test may be
repeated or the QTG may be amended.
    (2) If it is determined that the results of an objective test do
not support the level requested but do support a lower level, the
NSPM may qualify the FFS at that lower level. For example, if a
Level D evaluation is requested and the FFS fails to meet sound test
tolerances, it could be qualified at Level C.
    s. After an FFS is successfully evaluated, the NSPM issues a
certificate of qualification (COQ) to the sponsor. The NSPM
recommends the FFS to the TPAA, who will approve the FFS for use in
a flight training program. The COQ will be issued at the
satisfactory conclusion of the initial or continuing qualification
evaluation and will list the tasks for which the FSTD is qualified,
referencing the tasks described in Table C1B in attachment 1.
However, it is the sponsor's responsibility to obtain TPAA approval
prior to using the FSTD in an FAA-approved flight training program.
    t. Under normal circumstances, the NSPM establishes a date for
the initial or upgrade evaluation within ten (10) working days after
determining that a complete QTG is acceptable. Unusual circumstances
may warrant establishing an evaluation date before this
determination is made. A sponsor may schedule an evaluation date as
early as 6 months in advance. However, there may be a delay of 45
days or more in rescheduling and completing the evaluation if the
sponsor is unable to meet the scheduled date. See Attachment 4,
Figure C4A, Sample Request for Initial, Upgrade, or Reinstatement
Evaluation.
    u. The numbering system used for objective test results in the
QTG should closely follow the numbering system set out in Attachment
2, FFS Objective Tests, Table C2A.
    v. Contact the NSPM or visit the NSPM Web site for additional
information regarding the preferred qualifications of pilots used to
meet the requirements of Sec.  60.15(d).
    w. Examples of the exclusions for which the FFS might not have
been subjectively tested by the sponsor or the NSPM and for which
qualification might not be sought or granted, as described in Sec.
60.15(g)(6), include takeoffs and landing from slopes and pinnacles.

End Information

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12. Additional Qualifications for a Currently Qualified FSTD (Sec.
60.16)

    No additional regulatory or informational material applies to
Sec.  60.16, Additional Qualifications for a Currently Qualified
FFS.

13. Previously Qualified FSTDs (Sec.  60.17)

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Begin QPS Requirements

    a. In instances where a sponsor plans to remove an FFS from
active status for a period of less than two years, the following
procedures apply:
    (1) The NSPM must be notified in writing and the notification
must include an estimate of the period that the FFS will be
inactive.
    (2) Continuing Qualification evaluations will not be scheduled
during the inactive period.
    (3) The NSPM will remove the FFS from the list of qualified
FSTDs on a mutually established date not later than the date on
which the first missed continuing qualification evaluation would
have been scheduled.
    (4) Before the FFS is restored to qualified status, it must be
evaluated by the NSPM. The evaluation content and the time required
to accomplish the evaluation is based on the number of continuing
qualification evaluations and sponsor-conducted quarterly
inspections missed during the period of inactivity.
    (5) The sponsor must notify the NSPM of any changes to the
original scheduled time out of service.
    b. Simulators qualified prior to May 30, 2008, are not required
to meet the general simulation requirements, the objective test
requirements, and the subjective test requirements of attachments 1,
2, and 3, of this appendix as long as the simulator continues to
meet the test requirements contained in the MQTG developed under the
original qualification basis.
    c. After (1 year after date of publication of the final rule in
the Federal Register) each visual scene or airport model beyond the
minimum required for the FSTD qualification level that is installed
in and available for use in a qualified FSTD must meet the
requirements described in Attachment 3 of this appendix.

End QPS Requirements

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Begin Information

    d. Other certificate holders or persons desiring to use an FFS
may contract with FFS sponsors to use FFSs previously qualified at a
particular level for a helicopter type and approved for use within
an FAA-approved flight training program. Such FFSs are not required
to undergo an additional qualification process, except as described
in Sec.  60.16.
    e. Each FFS user must obtain approval from the appropriate TPAA
to use any FFS in an FAA-approved flight training program.
    f. The intent of the requirement listed in Sec.  60.17(b), for
each FFS to have a Statement of Qualification within 6 years, is to
have the availability of that statement (including the configuration
list and the limitations to authorizations) to provide a complete
picture of the FFS inventory regulated by the FAA. The issuance of
the statement will not require any additional evaluation or require
any adjustment to the evaluation basis for the FFS.
    g. Downgrading of an FFS is a permanent change in qualification
level and will necessitate the issuance of a revised Statement of
Qualification to reflect the revised qualification level, as
appropriate. If a temporary restriction is placed on an FFS because
of a missing, malfunctioning, or inoperative component or on-going
repairs, the restriction is not a permanent change in qualification
level. Instead, the restriction is temporary and is removed when the
reason for the restriction has been resolved.
    h. It is not the intent of the NSPM to discourage the
improvement of existing simulation (e.g., the ``updating'' of a
visual system to a newer model, or the replacement of the IOS with a
more capable unit) by requiring the ``updated'' device to meet the
qualification standards current at the time of the update. Depending
on the extent of the update, the NSPM may require that the updated
device be evaluated and may require that an evaluation include all
or a portion of the elements of an initial evaluation. However, the
standards against which the device would be evaluated are those that
are found in the MQTG for that device.
    i. The NSPM will determine the evaluation criteria for an FSTD
that has been removed from active status. The criteria will be based
on the number of continuing qualification evaluations and quarterly
inspections missed during the period of inactivity. For example, if
the FFS were out of service for a 1 year period, it would be
necessary to complete the entire QTG, since all of the quarterly
evaluations would have been missed. The NSPM will also consider how
the FFS was stored, whether parts were removed from the FFS and
whether the FFS was disassembled.
    j. The FFS will normally be requalified using the FAA-approved
MQTG and the criteria that was in effect prior to its removal from
qualification. However, inactive periods of 2 years or more will
require requalification under the standards in effect and current at
the time of requalification.

End Information

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

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

Begin QPS Requirements

    a. The sponsor must conduct a minimum of four evenly spaced
inspections throughout the year. The objective test sequence and
content of each inspection must be developed by the sponsor and must
be acceptable to the NSPM.
    b. The description of the functional preflight inspection must
be contained in the sponsor's QMS.
    c. Record ``functional preflight'' in the FFS discrepancy log
book or other acceptable location, including any item found to be
missing, malfunctioning, or inoperative.
    d. During the continuing qualification evaluation conducted by
the NSPM, the sponsor must also provide a person knowledgeable about
the operation of the aircraft and the operation of the FFS.
    e. The NSPM will conduct continuing qualification evaluations
every 12 months unless:
    (1) The NSPM becomes aware of discrepancies or performance
problems with the device that warrants more frequent evaluations; or
    (2) The sponsor implements a QMS that justifies less frequent
evaluations. However, in no case shall the frequency of a continuing
qualification evaluation exceed 36 months.

End QPS Requirements

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

Begin Information

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

station, and the normal functions and simulated malfunctions of the
simulated helicopter systems. This examination is normally
accomplished simultaneously with the subjective evaluation
requirements.

End Information

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15. Logging FSTD Discrepancies (Sec.  60.20)

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Begin Information

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

End Information

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16. Interim Qualification of FSTDs for New Helicopter Types or Models
(Sec.  60.21)

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Begin Information

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

End Information

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17. Modifications to FSTDs (Sec.  60.23)

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Begin QPS Requirements

    a. The notification described in Sec.  60.23(c)(2) must include
a complete description of the planned modification, with a
description of the operational and engineering effect the proposed
modification will have on the operation of the FFS and the results
that are expected with the modification incorporated.
    b. Prior to using the modified FFS:
    (1) All the applicable objective tests completed with the
modification incorporated, including any necessary updates to the
MQTG (e.g., accomplishment of FSTD Directives) must be acceptable to
the NSPM; and
    (2) The sponsor must provide the NSPM with a statement signed by
the MR that the factors listed in Sec.  60.15(b) are addressed by
the appropriate personnel as described in that section.

End QPS Requirements

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Begin Information

    (3) FSTD Directives are considered modifications of an FFS. See
Attachment 4 for a sample index of effective FSTD Directives. See
Attachment 6 for a list of all effective FSTD Directives applicable
to Helicopter FFSs.

End Information

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

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Begin Information

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

End Information

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

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

Begin Information

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

End Information

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

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

Begin Information

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

End Information

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21. Recordkeeping and Reporting (Sec.  60.31)

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Begin QPS Requirements

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

End QPS Requirements

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

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Begin Information

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

23. [Reserved]

24. [Reserved]

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

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

End Information

Attachment 1 to Appendix C to Part 60--General Simulator Requirements

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

Begin QPS Requirements

1. Requirements

    a. Certain requirements included in this appendix must be
supported with a Statement of Compliance and Capability (SOC), which
may include objective and subjective tests. The SOC will confirm
that the requirement was satisfied, and describe how the requirement
was met, such as gear modeling approach or coefficient of friction
sources. The requirements for SOCs and tests are indicated in the
``General Simulator Requirements'' column in Table C1A of this
appendix.
    b. Table C1A describes the requirements for the indicated level
of FFS. Many devices include operational systems or functions that
exceed the requirements outlined in this section. However, all
systems will be tested and evaluated in accordance with this
appendix to ensure proper operation.

End QPS Requirements

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Begin Information

2. Discussion

    a. This attachment describes the general simulator requirements
for qualifying a helicopter FFS. The sponsor should also consult the
objective tests in Attachment 2 and the examination of functions and
subjective tests listed in Attachment 3 to determine the complete
requirements for a specific level simulator.

    b. The material contained in this attachment is divided into the
following categories:
    (1) General flight deck configuration.
    (2) Simulator programming.
    (3) Equipment operation.
    (4) Equipment and facilities for instructor/evaluator functions.
    (5) Motion system.
    (6) Visual system.
    (7) Sound system.
    c. Table C1A provides the standards for the General Simulator
Requirements.
    d. Table C1B provides the tasks that the sponsor will examine to
determine whether the FSTD satisfactorily meets the requirements for
flight crew training, testing, and experience, and provides the
tasks for which the simulator may be qualified.
    e. Table C1C provides the functions that an instructor/check
airman must be able to control in the simulator.
    f. It is not required that all of the tasks that appear on the
List of Qualified Tasks (part of the SOQ) be accomplished during the
initial or continuing qualification evaluation.
    g. Table C1A addresses only Levels B, C, and D helicopter
simulators because there are no Level A Helicopter simulators.

End Information 1

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               Table C1A.--Minimum Simulator Requirements
------------------------------------------------------------------------
                     <<>
                requirements>>>  ---------------------------------------
    Number    -------------------
               General Simulator    B      C      D          Notes
                  Requirements
------------------------------------------------------------------------
1. General Flight Deck Configuration
------------------------------------------------------------------------
1.a..........  The simulator         X      X      X   For simulator
                must have a                             purposes, the
                flight deck that                        flight deck
                is a replica of                         consists of all
                the helicopter                          that space
                being simulated.                        forward of a
                The simulator                           cross section of
                must have                               the fuselage at
                controls,                               the most extreme
                equipment,                              aft setting of
                observable                              the pilots'
                flight deck                             seats including
                indicators,                             additional,
                circuit                                 required flight
                breakers, and                           crewmember duty
                bulkheads                               stations and
                properly                                those required
                located,                                bulkheads aft of
                functionally                            the pilot seats.
                accurate and                            For
                replicating the                         clarification,
                helicopter. The                         bulkheads
                direction of                            containing only
                movement of                             items such as
                controls and                            landing gear pin
                switches must be                        storage
                identical to                            compartments,
                that in the                             fire axes or
                helicopter.                             extinguishers,
                Pilot seats must                        spare light
                afford the                              bulbs, and
                capability for                          aircraft
                the occupant to                         documents
                be able to                              pouches are not
                achieve the                             considered
                design ``eye                            essential and
                position''                              may be omitted.
                established for
                the helicopter
                being simulated.
                Equipment for
                the operation of
                the flight deck
                windows must be
                included, but
                the actual
                windows need not
                be operable.
                Fire axes,
                extinguishers,
                and spare light
                bulbs must be
                available in the
                FFS but may be
                relocated to a
                suitable
                location as near
                as practical to
                the original
                position. Fire
                axes, landing
                gear pins, and
                any similar
                purpose
                instruments need
                only be
                represented in
                silhouette.
               An SOC is
                required.
------------------------------------------------------------------------
1.b..........  Those circuit         X      X      X
                breakers that
                affect
                procedures and/
                or result in
                observable
                flight deck
                indications must
                be properly
                located and
                functionally
                accurate
               An SOC is
                required.
------------------------------------------------------------------------
2. Programming
------------------------------------------------------------------------
2.a..........  A flight dynamics     X      X      X
                model that
                accounts for
                various
                combinations of
                drag and thrust
                normally
                encountered in
                flight must
                correspond to
                actual flight
                conditions,
                including the
                effect of change
                in helicopter
                attitude,
                thrust, drag,
                altitude,
                temperature,
                gross weight,
                moments of
                inertia, center
                of gravity
                location, and
                configuration.
               An SOC is
                required.
------------------------------------------------------------------------
2.b..........  The simulator         X      X      X
                must have the
                computer
                capacity,
                accuracy,
                resolution, and
                dynamic response
                needed to meet
                the
                qualification
                level sought.
               An SOC is
                required.
------------------------------------------------------------------------
2.c..........  Ground handling
                and aerodynamic
                programming must
                include the
                following:
               A subjective test
                is required.
------------------------------------------------------------------------
2.c.1........  Ground effect....     X      X      X   Applicable areas
                                                        include flare
                                                        and touch down
                                                        from a running
                                                        landing as well
                                                        as for in-ground-
                                                        effect (IGE)
                                                        hover. A
                                                        reasonable
                                                        simulation of
                                                        ground effect
                                                        includes
                                                        modeling of
                                                        lift, drag,
                                                        pitching moment,
                                                        trim, and power
                                                        while in ground
                                                        effect.
               Level B does not
                require hover
                programming.
               An SOC is
                required.
------------------------------------------------------------------------

2.c.2........  Ground reaction..     X      X      X   Reaction of the
                                                        helicopter upon
                                                        contact with the
                                                        landing surface
                                                        during landing
                                                        (e.g., strut
                                                        deflection, tire
                                                        or skid
                                                        friction, side
                                                        forces) may
                                                        differ with
                                                        changes in gross
                                                        weight,
                                                        airspeed, rate
                                                        of descent on
                                                        touchdown, and
                                                        slide slip.
               Level B does not
                require hover
                programming.
               An SOC is
                required.
------------------------------------------------------------------------
2.d..........  The simulator                X      X   This may include
                must provide for                        an automated
                manual and                              system, which
                automatic                               could be used
                testing of                              for conducting
                simulator                               at least a
                hardware and                            portion of the
                software                                QTG tests.
                programming to                          Automatic
                determine                               ``flagging'' of
                compliance with                         out-of-tolerance
                simulator                               situations is
                objective tests                         encouraged.
                as prescribed in
                Attachment 2.
               An SOC is
                required.
------------------------------------------------------------------------
2.e..........  The relative                            The intent is to
                responses of the                        verify that the
                motion system,                          simulator
                visual system,                          provides
                and flight deck                         instrument,
                instruments must                        motion, and
                be measured by                          visual cues that
                latency tests or                        are like the
                transport delay                         helicopter
                tests. Motion                           responses within
                onset should                            the stated time
                occur before the                        delays. For
                start of the                            helicopter
                visual scene                            response,
                change (the                             acceleration in
                start of the                            the appropriate
                scan of the                             corresponding
                first video                             rotational axis
                field containing                        is preferred.
                different
                information) but
                must occur
                before the end
                of the scan of
                that video
                field.
                Instrument
                response may not
                occur prior to
                motion onset.
                Test results
                must be within
                the following
                limits:
------------------------------------------------------------------------
2.e.1........  Response must be      X
                within 150
                milliseconds of
                the helicopter
                response.
               Objective Tests
                are required.
               See Attachment 2
                for Transport
                Delay and
                Latency Tests.
------------------------------------------------------------------------
2.e.2........  Response must be             X      X
                within 100
                milliseconds of
                the helicopter
                response.
               Objective Tests
                are required.
               See Attachment 2
                for Transport
                Delay and
                Latency Tests.
------------------------------------------------------------------------
2.f..........  The simulator                X      X   Simulator pitch,
                must simulate                           side loading,
                brake and tire                          and directional
                failure dynamics                        control
                (including                              characteristics
                antiskid                                should be
                failure, if                             representative
                appropriate).                           of the
                                                        helicopter.
               An SOC is
                required.
------------------------------------------------------------------------
2.g..........  The aerodynamic              X      X   See Attachment 2
                modeling in the                         for further
                simulator must                          information on
                include:                                ground effect.
                  (1) Ground
                   effect,.
                  (2) Effects of
                   airframe and
                   rotor icing
                   (if
                   applicable),.
                  (3)
                   Aerodynamic
                   interference
                   effects
                   between the
                   rotor wake
                   and fuselage,.
                  (4) Influence
                   of the rotor
                   on control
                   and
                   stabilization
                   systems,.
                  (5)
                   Representatio
                   ns of
                   settling with
                   power, and.
                  (6) Retreating
                   blade stall..
               An SOC is
                required.
               A demonstration
                of icing effects
                (if applicable)
                is required.
------------------------------------------------------------------------
2.h..........  The simulator         X      X      X
                must provide for
                realistic mass
                properties,
                including gross
                weight, center
                of gravity, and
                moments of
                inertia as a
                function of
                payload and fuel
                loading.
               An SOC is
                required and
                must include a
                range of
                tabulated target
                values to enable
                a subjective
                test of the mass
                properties model
                to be conducted
                from the
                instructor's
                station.
------------------------------------------------------------------------
3. Equipment Operation
------------------------------------------------------------------------

3.a..........  All relevant          X      X      X
                instrument
                indications
                involved in the
                simulation of
                the helicopter
                must
                automatically
                respond to
                control movement
                or external
                disturbances to
                the simulated
                helicopter;
                e.g., turbulence
                or windshear.
                Numerical
                values, must be
                presented in the
                appropriate
                units.
               A subjective test
                is required.
------------------------------------------------------------------------
3.b..........  Communications,       X      X      X   See Attachment 3
                navigation,                             for further
                caution, and                            information
                warning                                 regarding long-
                equipment must                          range navigation
                be installed and                        equipment.
                operate within
                the tolerances
                applicable for
                the helicopter
                being simulated.
               A subjective test
                is required.
------------------------------------------------------------------------
3.c..........  Simulated             X      X      X
                helicopter
                systems must
                operate as the
                helicopter
                systems would
                operate under
                normal,
                abnormal, and
                emergency
                operating
                conditions on
                the ground and
                in flight.
               A subjective test
                is required.
------------------------------------------------------------------------
3.d..........  The simulator         X      X      X
                must provide
                pilot controls
                with control
                forces and
                control travel
                that correspond
                to the simulated
                helicopter. The
                simulator must
                also react in
                the same manner
                as the
                helicopter under
                the same flight
                conditions.
               An objective test
                is required.
------------------------------------------------------------------------
3.e..........  Simulator control            X      X
                feel dynamics
                must replicate
                the helicopter
                simulated. This