MQTG and the criteria that was in effect prior to its removal from
qualification. However, inactive periods of 2 years or more will
require re-qualification under the standards in effect and current
at the time of requalification.

End Information

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

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

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

Begin QPS Requirement

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

End QPS Requirements

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

Begin Information

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

End Information

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

15. Logging FTD Discrepancies (Sec.  60.20)

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

Begin Information

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

End Information

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

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

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

Begin Information

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

End Information

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

17. Modifications to FTDs (Sec.  60.23)

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

Begin QPS Requirements

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

End QPS Requirements

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

Begin Information

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

End Information

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

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

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

Begin Information

    a. The sponsor's responsibility with respect to Sec.  60.25(a)
is satisfied when the sponsor fairly and accurately advises the user
of the current status of an FTD, including any missing,
malfunctioning, or inoperative (MMI) component(s).
    b. It is the responsibility of the instructor, check airman, or
representative of the administrator conducting training, testing, or
checking to exercise reasonable and prudent judgment to determine if
any MMI component is necessary for the satisfactory completion of a
specific maneuver, procedure, or task.
    c. If the 29th or 30th day of the 30-day period described in
Sec.  60.25(b) is on a Saturday, a Sunday, or a holiday, the FAA
will extend the deadline until the next business day.
    d. In accordance with the authorization described in Sec.
60.25(b), the sponsor may develop a discrepancy prioritizing system
to accomplish repairs based on the level of impact on the capability
of the FTD. Repairs having a larger impact on the FTD's ability to
provide the required training, evaluation, or flight experience will
have a higher priority for repair or replacement.

End Information

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

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

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

Begin Information

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

End Information

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

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

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

Begin Information

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

End Information

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

21. Record Keeping and Reporting (Sec.  60.31)

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

Begin QPS Requirements

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

End Information

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

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

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

Begin Information

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

23. [Reserved].

End Information

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

24. Levels of FTD

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

Begin Information

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

End Information

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

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

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

Begin Information

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

End Information

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

Attachment 1 to Appendix D to Part 60--GENERAL FTD REQUIREMENTS

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

Begin QPS Requirements

1. Requirements

    a. Certain requirements included in this appendix must be
supported with an SOC as defined in Appendix F, which may include
objective and subjective tests. The requirements for SOCs are
indicated in the ``General FTD Requirements'' column in Table D1A of
this appendix.
    b. Table D1A describes the requirements for the indicated level
of FTD. Many devices include operational systems or functions that
exceed the requirements outlined in this section. In any event, all
systems will be tested and evaluated in accordance with this
appendix to ensure proper operation.

End QPS Requirements

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

Begin Information

2. Discussion

    a. This attachment describes the general requirements for
qualifying Level 4 through Level 7 FTDs. The sponsor should also
consult the objectives tests in Attachment 2 of this appendix and
the examination of functions and subjective tests listed in
Attachment 3 of this appendix to determine the complete requirements
for a specific level FTD.
    b. The material contained in this attachment is divided into the
following categories:
    (1) General Flight Deck Configuration.
    (2) Programming.
    (3) Equipment Operation.
    (4) Equipment and Facilities for Instructor/Evaluator Functions.
    (5) Motion System.
    (6) Visual System.
    (7) Sound System.
    c. Table D1A provides the standards for the General FTD
Requirements.
    d. Table D1B provides the tasks that the sponsor will examine to
determine whether the FTD satisfactorily meets the requirements for
flight crew training, testing, and experience.
    e. Table D1C provides the functions that an instructor/check
airman must be able to control in the simulator.

    f. It is not required that all of the tasks that appear on the
List of Qualified Tasks (part of the SOQ) be accomplished during the
initial or continuing qualification evaluation.

End Information

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

                                      Table D1A.--Minimum FTD Requirements
----------------------------------------------------------------------------------------------------------------
                               QPS requirements                                            Information
----------------------------------------------------------------------------------------------------------------
                                                                 FTD level
       Entry No.              General FTD requirements     --------------------               Notes
                                                             4    5    6    7
----------------------------------------------------------------------------------------------------------------
1. General Flight Deck Configuration.
----------------------------------------------------------------------------------------------------------------
1.a....................  The FTD must have a flight deck    ...  ...   X    X   For FTD purposes, the flight
                          that is a replica of the                               deck consists of all that space
                          helicopter, or set of                                  forward of a cross section of
                          helicopters simulated with                             the flight deck at the most
                          controls, equipment, observable                        extreme aft setting of the
                          flight deck indicators, circuit                        pilots' seats including
                          breakers, and bulkheads properly                       additional, required crewmember
                          located, functionally accurate                         duty stations and those
                          and replicating the helicopter                         required bulkheads aft of the
                          or set of helicopters. The                             pilot seats. Bulkheads
                          direction of movement of                               containing only items such as
                          controls and switches must be                          landing gear pin storage
                          identical to that in the                               compartments, fire axes and
                          helicopter or set of                                   extinguishers, spare light
                          helicopters. Crewmember seats                          bulbs, and aircraft documents
                          must afford the capability for                         pouches are not considered
                          the occupant to be able to                             essential and may be omitted.
                          achieve the design ``eye                               If omitted, these items, or the
                          position.'' Equipment for the                          silhouettes of these items, may
                          operation of the flight deck                           be placed on the wall of the
                          windows must be included, but                          simulator, or in any other
                          the actual windows need not be                         location as near as practical
                          operable. Those circuit breakers                       to the original position of
                          that affect procedures or result                       these items.
                          in observable flight deck
                          indications must be properly
                          located and functionally
                          accurate. Fire axes,
                          extinguishers, landing gear
                          pins, and spare light bulbs must
                          be available, and may be
                          represented in silhouette, in
                          the flight simulator. This
                          equipment must be present as
                          near as practical to the
                          original position
----------------------------------------------------------------------------------------------------------------
1.b....................  The FTD must have equipment         X    X
                          (i.e., instruments, panels,
                          systems, circuit breakers, and
                          controls) simulated sufficiently
                          for the authorized training/
                          checking events to be
                          accomplished. The installed
                          equipment, must be located in a
                          spatially correct configuration,
                          and may be in a flight deck or
                          an open flight deck area. Those
                          circuit breakers that affect
                          procedures or result in
                          observable flight deck
                          indications must be properly
                          located and functionally
                          accurate. Additional equipment
                          required for the authorized
                          training and checking events
                          must be available in the FTD but
                          may be located in a suitable
                          location as near as practical to
                          the spatially correct position.
                          Actuation of this equipment must
                          replicate the appropriate
                          function in the helicopter. Fire
                          axes, landing gear pins, and any
                          similar purpose instruments need
                          only be represented in
                          silhouette
----------------------------------------------------------------------------------------------------------------
2. Programming.
----------------------------------------------------------------------------------------------------------------
2.a....................  The FTD must provide the proper    ...   X    X    X
                          effect of aerodynamic changes
                          for the combinations of drag and
                          thrust normally encountered in
                          flight. This must include the
                          effect of change in helicopter
                          attitude, thrust, drag,
                          altitude, temperature, and
                          configuration. Levels 6 and 7
                          additionally require the effects
                          of changes in gross weight and
                          center of gravity.Level 5
                          requires only generic
                          aerodynamic programming.
                         An SOC is required...............
----------------------------------------------------------------------------------------------------------------
2.b....................  The FTD must have the computer      X    X    X    X
                          (analog or digital) capability
                          (i.e., capacity, accuracy,
                          resolution, and dynamic
                          response) needed to meet the
                          qualification level sought.
                         An SOC is required...............
----------------------------------------------------------------------------------------------------------------

[[Continued on page 26727]]

]

[[pp. 26727-26776]] Flight Simulation Training Device Initial and Continuing
Qualification and Use

[[Continued from page 26726]]

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

4.a....................  In addition to the flight           X    X    X    X   These seats need not be a
                          crewmember stations, suitable                          replica of an aircraft seat and
                          seating arrangements for an                            may be as simple as an office
                          instructor/check airman and FAA                        chair placed in an appropriate
                          Inspector must be available.                           position.
                          These seats must provide
                          adequate view of crewmember's
                          panel(s)
----------------------------------------------------------------------------------------------------------------
4.b....................  The FTD must have instructor        X    X    X    X
                          controls that permit activation
                          of normal, abnormal, and
                          emergency conditions, as
                          appropriate. Once activated,
                          proper system operation must
                          result from system management by
                          the crew and not require input
                          from the instructor controls.
----------------------------------------------------------------------------------------------------------------
5. Motion System
----------------------------------------------------------------------------------------------------------------
5.a....................  A motion system may be installed    X    X    X    X
                          in an FTD. If installed, the
                          motion system operation must not
                          be distracting. If a motion
                          system is installed and
                          additional training, testing, or
                          checking credits are being
                          sought, sensory cues must also
                          be integrated. The motion system
                          must respond to abrupt input at
                          the pilot's position within the
                          allotted time, but not before
                          the time when the helicopter
                          responds under the same
                          conditions. The motion system
                          must be measured by latency
                          tests or transport delay tests
                          and may not exceed 150
                          milliseconds. Instrument
                          response must not occur prior to
                          motion onset
----------------------------------------------------------------------------------------------------------------
5.b....................  The FTD must have at least a       ...  ...  ...   X   May be accomplished by a ``seat
                          vibration cueing system for                            shaker'' or a bass speaker
                          characteristic helicopter                              sufficient to provide the
                          vibrations noted at the pilot                          necessary cueing.
                          station(s)
----------------------------------------------------------------------------------------------------------------
6. Visual System
----------------------------------------------------------------------------------------------------------------
6.a....................  The FTD may have a visual system,
                          if desired, although it is not
                          required. If a visual system is
                          installed, it must meet the
                          following criteria:
6.a.1..................  The visual system must respond to   X    X    X
                          abrupt input at the pilot's
                          position.
                         An SOC is required...............
----------------------------------------------------------------------------------------------------------------
6.a.2..................  The visual system must be at        X    X    X
                          least a single channel, non-
                          collimated display.
                         An SOC is required...............
----------------------------------------------------------------------------------------------------------------
6.a.3..................  The visual system must provide at   X    X    X
                          least a field-of-view of 18[deg]
                          vertical/24[deg] horizontal for
                          the pilot flying.
                         An SOC is required...............
----------------------------------------------------------------------------------------------------------------
6.a.4..................  The visual system must provide      X    X    X
                          for a maximum parallax of
                          10[deg] per pilot.
                         An SOC is required...............
----------------------------------------------------------------------------------------------------------------
6.a.5..................  The visual scene content may not    X    X    X
                          be distracting.
                         An SOC is required...............
----------------------------------------------------------------------------------------------------------------
6.a.6..................  The minimum distance from the       X    X    X
                          pilot's eye position to the
                          surface of a direct view display
                          may not be less than the
                          distance to any front panel
                          instrument.
                         An SOC is required...............
----------------------------------------------------------------------------------------------------------------
6.a.7..................  The visual system must provide      X    X    X
                          for a minimum resolution of 5
                          arc-minutes for both computed
                          and displayed pixel size.
                         An SOC is required...............
----------------------------------------------------------------------------------------------------------------

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

                  Table D1B.--Minimum FTD Requirements
------------------------------------------------------------------------
                   QPS requirements                       Information
------------------------------------------------------------------------
                   Subjective           FTD level
                requirements The  --------------------
                FTD must be able
                 to perform the
  Entry No.     tasks associated                             Notes
                with the level of   4    5    6    7
                  qualification
                     sought.
------------------------------------------------------------------------
1. Preflight Procedures
------------------------------------------------------------------------
1.a..........  Preflight            A    A    X    X
                Inspection
                (Flight Deck
                Only) switches,
                indicators,
                systems, and
                equipment.
------------------------------------------------------------------------
1.b..........  APU/Engine start
                and run-up.
------------------------------------------------------------------------
1.b.1........  Normal start         A    A    X    X
                procedures.
------------------------------------------------------------------------
1.b.2........  Alternate start      A    A    X    X
                procedures.
------------------------------------------------------------------------
1.b.3........  Abnormal starts      A    A    X    X
                and shutdowns
                (hot start, hung
                start).
------------------------------------------------------------------------
1.c..........  Taxiing--Ground...  ...  ...  ...   X
------------------------------------------------------------------------
1.d..........  Taxiing--Hover....  ...  ...  ...   X
------------------------------------------------------------------------

1.e..........  Pre-takeoff Checks   A    A    X    X
------------------------------------------------------------------------
2. Takeoff and Departure Phase
------------------------------------------------------------------------
2.a..........  Normal takeoff....
------------------------------------------------------------------------
2.a.1........  From ground.......  ...  ...  ...   X
------------------------------------------------------------------------
2.a.2........  From hover........  ...  ...  ...   X
------------------------------------------------------------------------
2.a.3........  Running...........  ...  ...  ...   X
------------------------------------------------------------------------
2.b..........  Instrument........  ...  ...   X    X
------------------------------------------------------------------------
2.c..........  Powerplant Failure  ...  ...   X    X
                During Takeoff.
------------------------------------------------------------------------
2.d..........  Rejected Takeoff..  ...  ...  ...   X
------------------------------------------------------------------------
2.e..........  Instrument          ...  ...   X    X
                Departure.
------------------------------------------------------------------------
3. Climb
------------------------------------------------------------------------
3.a..........  Normal............  ...  ...   X    X
------------------------------------------------------------------------
3.b..........  Obstacle clearance  ...  ...  ...   X
------------------------------------------------------------------------
3.c..........  Vertical..........  ...  ...   X    X
------------------------------------------------------------------------
3.d..........  One engine          ...  ...   X    X
                inoperative.
------------------------------------------------------------------------
4. In-flight Maneuvers
------------------------------------------------------------------------
4.a..........  Turns (timed,       ...   X    X    X
                normal, steep).
------------------------------------------------------------------------
4.b..........  Powerplant          ...  ...   X    X
                Failure--Multieng
                ine Helicopters.
------------------------------------------------------------------------
4.c..........  Powerplant          ...  ...   X    X
                Failure--Single-
                Engine
                Helicopters.
------------------------------------------------------------------------
4.d..........  Recovery From       ...  ...  ...   X
                Unusual Attitudes.
------------------------------------------------------------------------
4.e..........  Settling with       ...  ...  ...   X
                Power.
------------------------------------------------------------------------
5. Instrument Procedures
------------------------------------------------------------------------
5.a..........  Instrument Arrival  ...  ...   X    X
------------------------------------------------------------------------
5.b..........  Holding...........  ...  ...   X    X
------------------------------------------------------------------------
5.c..........  Precision
                Instrument
                Approach
------------------------------------------------------------------------
5.c.1........  Normal--All         ...   X    X    X
                engines operating.
------------------------------------------------------------------------
5.c.2........  Manually            ...  ...   X    X
                controlled--One
                or more engines
                inoperative.
------------------------------------------------------------------------
5.d..........  Non-precision       ...   X    X    X
                Instrument
                Approach.
------------------------------------------------------------------------
5.e..........  Missed Approach.
------------------------------------------------------------------------
5.e.1........  All engines         ...  ...   X    X
                operating.
------------------------------------------------------------------------
5.e.2........  One or more         ...  ...   X    X
                engines
                inoperative.
------------------------------------------------------------------------
5.e.3........  Stability           ...  ...   X    X
                augmentation
                system failure.
------------------------------------------------------------------------
6. Landings and Approaches to Landings
------------------------------------------------------------------------
6.a..........  Visual Approaches   ...   X    X    X
                (normal, steep,
                shallow).
------------------------------------------------------------------------
6.b..........  Landings.
------------------------------------------------------------------------

6.b.1........  Normal/crosswind.
------------------------------------------------------------------------
6.b.1.a......  Running...........  ...  ...  ...   X
------------------------------------------------------------------------
6.b.1.b......  From Hover........  ...  ...  ...   X
------------------------------------------------------------------------
6.b.2........  One or more         ...  ...  ...   X
                engines
                inoperative.
------------------------------------------------------------------------
 6.b.3.......  Rejected Landing..  ...  ...  ...   X
------------------------------------------------------------------------
7. Normal and Abnormal Procedures
------------------------------------------------------------------------
7.a..........  Powerplant........   A    A    X    X
------------------------------------------------------------------------
7.b..........  Fuel System.......   A    A    X    X
------------------------------------------------------------------------
7.c..........  Electrical System.   A    A    X    X
------------------------------------------------------------------------
7.d..........  Hydraulic System..   A    A    X    X
------------------------------------------------------------------------
7.e..........  Environmental        A    A    X    X
                System(s).
------------------------------------------------------------------------
7.f..........  Fire Detection and   A    A    X    X
                Extinguisher
                Systems.
------------------------------------------------------------------------
7.g..........  Navigation and       A    A    X    X
                Aviation Systems.
------------------------------------------------------------------------
7.h..........  Automatic Flight     A    A    X    X
                Control System,
                Electronic Flight
                Instrument
                System, and
                Related
                Subsystems.
------------------------------------------------------------------------
7.i..........  Flight Control       A    A    X    X
                Systems.
------------------------------------------------------------------------
7.j..........  Anti-ice and Deice   A    A    X    X
                Systems.
------------------------------------------------------------------------
7.k..........  Aircraft and         A    A    X    X
                Personal
                Emergency
                Equipment.
------------------------------------------------------------------------
7.l..........  Special Missions    ...  ...  ...   X
                tasks (e.g.,
                Night Vision
                goggles, Forward
                Looking Infrared
                System, External
                Loads and as
                listed on the
                SOQ.).
------------------------------------------------------------------------
8. Emergency procedures (as applicable)
------------------------------------------------------------------------
8.a..........  Emergency Descent.  ...  ...   X    X
------------------------------------------------------------------------
8.b..........  Inflight Fire and   ...  ...   X    X
                Smoke Removal.
------------------------------------------------------------------------
8.c..........  Emergency           ...  ...   X    X
                Evacuation.
------------------------------------------------------------------------
8.d..........  Ditching..........  ...  ...  ...   X
------------------------------------------------------------------------
8.e..........  Autorotative        ...  ...  ...   X
                Landing.
------------------------------------------------------------------------
8.f..........  Retreating blade    ...  ...  ...   X
                stall recovery.
------------------------------------------------------------------------
8.g..........  Mast bumping......  ...  ...  ...   X
------------------------------------------------------------------------
8.h..........  Loss of tail rotor  ...  ...   X    X
                effectiveness.
------------------------------------------------------------------------
9. Postflight Procedures
------------------------------------------------------------------------
9.a..........  After-Landing        A    A    X    X
                Procedures.
------------------------------------------------------------------------
9.b..........  Parking and
                Securing
------------------------------------------------------------------------
9.b.1........  Rotor brake          A    A    X    X
                operation.
------------------------------------------------------------------------
9.b.2........  Abnormal/emergency   A    A    X    X
                procedures.
------------------------------------------------------------------------
Note: An ``A'' in the table indicates that the system, task, or
  procedure may be examined if the appropriate aircraft system or
  control is simulated in the FTD and is working properly.

                  Table D1C.--Table of FTD System Tasks
------------------------------------------------------------------------
                   QPS requirements                        Information
------------------------------------------------------------------------
                   Subjective            FTD level
             requirements In order --------------------
               to be qualified at
             the FTD qualification
              level indicated, the
 Entry No.    FTD must be able to                             Notes
              perform at least the   4    5    6    7
              tasks associate with
                 that level of
                 qualification.
------------------------------------------------------------------------
1. Instructor Operating Station (IOS)
------------------------------------------------------------------------
1.a........  Power switch(es).....   A    X    X    X
------------------------------------------------------------------------
1.b........  Helicopter conditions   A    A    X    X   e.g., GW, CG,
                                                         Fuel loading,
                                                         Systems,
                                                         Ground. Crew.
------------------------------------------------------------------------
1.c........  Airports/Heliports/     A    X    X    X   e.g., Selection,
              Helicopter Landing                         Surface,
              Areas.                                     Presets,
                                                         Lighting
                                                         controls.
------------------------------------------------------------------------
1.d........  Environmental           A    X    X    X   e.g., Temp and
              controls.                                  Wind.
------------------------------------------------------------------------
1.e........  Helicopter system       A    A    X    X
              malfunctions
              (Insertion/deletion).
------------------------------------------------------------------------
1.f........  Locks, Freezes, and     A    X    X    X
              Repositioning (as
              appropriate).
------------------------------------------------------------------------
1.g........  Sound Controls. (On/   ...   X    X    X
              off/adjustment).
------------------------------------------------------------------------
1.h........  Motion/Control         ...   A    X    X
              Loading System, as
              appropriate. On/off/
              emergency stop.
------------------------------------------------------------------------
2. Observer Seats/Stations
------------------------------------------------------------------------
2.a........  Position/Adjustment/    A    X    X    X
              Positive restraint
              system.
------------------------------------------------------------------------
Note: An ``A'' in the table indicates that the system, task, or
  procedure may be examined if the appropriate simulator system or
  control is in the FTD and is working properly.

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

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

Begin Information

1. Discussion

    a. If relevant winds are present in the objective data, the wind
vector (magnitude and direction) should be noted as part of the data
presentation, expressed in conventional terminology, and related to
the runway being used for the test.
    b. The format for numbering the objective tests in Appendix C of
this part, Attachment 2, Table C2A, and the objective tests in
Appendix D of this part, Attachment 2, Table D2A, is identical.
However, each test required for FFSs is not necessarily required for
FTDs, and each test required for FTDs is not necessarily required
for FFSs. When a test number (or series of numbers) is not required,
the term ``Reserved'' is used in the table at that location.
Following this numbering format provides a degree of commonality
between the two tables and substantially reduces the potential for
confusion when referring to objective test numbers for either FFSs
or FTDs.
    c. A Level 4 FTD does not require objective tests and is not
addressed in the following table.

End Information

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

Begin QPS Requirements

2. Test Requirements

    a. The ground and flight tests required for qualification are
listed in Table D2A Objective Evaluation Tests. Computer generated
FTD test results must be provided for each test except where an
alternate test is specifically authorized by the NSPM. If a flight
condition or operating condition is required for the test but does
not apply to the helicopter being simulated or to the qualification
level sought, it may be disregarded (e.g., engine out climb
capability for a single-engine helicopter). Each test result is
compared against the validation data described in Sec.  60.13, and
in Appendix B of this part. The results must be produced on an
appropriate recording device acceptable to the NSPM and must include
FTD number, date, time, conditions, tolerances, and appropriate
dependent variables portrayed in comparison to the validation data.
Time histories are required unless otherwise indicated in Table D2A.
All results must be labeled using the tolerances and units given.
    b. Table D2A in this attachment sets out the test results
required, including the parameters, tolerances, and flight
conditions for FTD validation. Tolerances are provided for the
listed tests because mathematical modeling and acquisition and
development of reference data are often inexact. All tolerances
listed in the following tables are applied to FTD performance. When
two tolerance values are given for a parameter, the less restrictive
may be used unless otherwise indicated. In those cases where a
tolerance is expressed only as a percentage, the tolerance
percentage applies to the maximum value of that parameter within its
normal operating range as measured from the neutral or zero position
unless otherwise indicated.
    c. Certain tests included in this attachment must be supported
with an SOC. In Table D2A, requirements for SOCs are indicated in
the ``Test Details'' column.
    d. When operational or engineering judgment is used in making
assessments for flight test data applications for FTD validity, such
judgment must not be limited to a single parameter. For example,
data that exhibit rapid variations of the measured parameters may
require interpolations or a ``best fit'' data section. All relevant
parameters related to a given maneuver or flight condition must be
provided to allow overall interpretation. When it is difficult or
impossible to match FTD to helicopter data throughout a time
history, differences must be justified by providing a comparison of
other related variables for the condition being assessed.
    e. The FTD may not be programmed so that the mathematical
modeling is correct only at the validation test points. Unless noted
otherwise, tests must represent helicopter performance and handling
qualities at operating weights and centers of gravity (CG) typical
of normal operation. If a test is supported by aircraft data at one
extreme weight or CG, another test supported by aircraft data at
mid-conditions or as close as possible to the other extreme is
necessary. Certain tests that are relevant only at one extreme CG or
weight condition need not be repeated at the other extreme. The
results of the tests for Level 6 are expected to be indicative of
the device's performance and handling qualities throughout all of
the following:
    (1) The helicopter weight and CG envelope.
    (2) The operational envelope.
    (3) Varying atmospheric ambient and environmental conditions--
including the extremes authorized for the respective helicopter or
set of helicopters.

    f. When comparing the parameters listed to those of the
helicopter, sufficient data must also be provided to verify the
correct flight condition and helicopter configuration changes. For
example, to show that control force is within the parameters for a
static stability test, data to show the correct airspeed, power,
thrust or torque, helicopter configuration, altitude, and other
appropriate datum identification parameters must also be given. If
comparing short period dynamics, normal acceleration may be used to
establish a match to the helicopter, but airspeed, altitude, control
input, helicopter configuration, and other appropriate data must
also be given. If comparing landing gear change dynamics, pitch,
airspeed, and altitude may be used to establish a match to the
helicopter, but landing gear position must also be provided. All
airspeed values must be properly annotated (e.g., indicated versus
calibrated). In addition, the same variables must be used for
comparison (e.g., compare inches to inches rather than inches to
centimeters).
    g. The QTG provided by the sponsor must clearly describe how the
FTD will be set up and operated for each test. Each FTD subsystem
may be tested independently, but overall integrated testing of the
FTD must be accomplished to assure that the total FTD system meets
the prescribed standards. A manual test procedure with explicit and
detailed steps for completing each test must also be provided.
    h. For previously qualified FTDs, the tests and tolerances of
this attachment may be used in subsequent continuing qualification
evaluations for any given test if the sponsor has submitted a
proposed MQTG revision to the NSPM and has received NSPM approval.
    i. Tests of handling qualities must include validation of
augmentation devices. FTDs for highly augmented helicopters will be
validated both in the unaugmented configuration (or failure state
with the maximum permitted degradation in handling qualities) and
the augmented configuration. Where various levels of handling
qualities result from failure states, validation of the effect of
the failure is necessary. For those performance and static handling
qualities tests where the primary concern is control position in the
unaugmented configuration, unaugmented data are not required if the
design of the system precludes any affect on control position. In
those instances where the unaugmented helicopter response is
divergent and non-repeatable, it may not be feasible to meet the
specified tolerances. Alternative requirements for testing will be
mutually agreed upon by the sponsor and the NSPM on a case-by-case
basis.
    j. Some tests will not be required for helicopters using
helicopter hardware in the FTD flight deck (e.g., ``helicopter
modular controller''). These exceptions are noted in Section 2
``Handling Qualities'' in Table D2A of this attachment. However, in
these cases, the sponsor must provide a statement that the
helicopter hardware meets the appropriate manufacturer's
specifications and the sponsor must have supporting information to
that fact available for NSPM review.
    k. In cases where light-class helicopters are being simulated,
prior coordination with the NSPM on acceptable weight ranges is
required. The terms ``light,'' ``medium,'' and ``near maximum,'' may
not be appropriate for the simulation of light-class helicopters.

End QPS Requirements

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

Begin Information

    l. In those cases where the objective test results authorize a
``snapshot test'' or a ``series of snapshot test'' results in lieu
of a time-history result, the sponsor or other data provider must
ensure that a steady state condition exists at the instant of time
captured by the ``snapshot.'' The steady state condition must exist
from 4 seconds prior to, through 1 second following, the instant of
time captured by the snap shot.
    m. Refer to AC 120-27, Aircraft Weight and Balance; and FAA-H-
8083-1, Aircraft Weight and Balance Handbook, for more information.

End Information

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

                                                Table D2A.--Flight Training Device (FTD) Objective Tests
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                         QPS requirements                                                                Information
--------------------------------------------------------------------------------------------------------------------------------------------------------
                       Test                                                                                FTD level
--------------------------------------------------      Tolerances         Flight conditions       Test details     ---------------         Notes
         Entry No.                  Title                                                                             5    6    7
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.                          Performance
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.a.......................  Engine Assessment.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.a.1.....................  Start Operations.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.a.1.a...................  Engine start and       Light Off Time--      Ground with the       Record each engine    ...   X    X
                             acceleration           10% or    Rotor Brake Used      start from the
                             (transient).           1 sec.    and Not Used.         initiation of the
                                                    Torque--5% Rotor                              steady state idle
                                                    Speed--3% Fuel Flow--                        state idle to
                                                    10% Gas                         operating RPM.
                                                    Generator Speed--
                                                    5%
                                                    Power Turbine
                                                    Speed--5% Gas
                                                    Turbine Temp.--
                                                    30[deg]C.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.a.1.b...................  Steady State Idle and  Torque--3% Rotor                              state idle and
                             conditions.            Speed--1.5% Fuel                             conditions. May be
                                                    Flow--5% Gas                                snapshot tests.
                                                    Generator Speed--
                                                    2%
                                                    Power Turbine
                                                    Speed--2% Turbine
                                                    Gas Temp.--20[deg]C.
--------------------------------------------------------------------------------------------------------------------------------------------------------

1.a.2.....................  Power Turbine Speed    10% of    Ground..............  Record engine         ...   X    X
                             Trim.                  total change of                             response to trim
                                                    power turbine                               system actuation in
                                                    speed; or 0.5% change
                                                    of rotor speed.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.a.3.....................  Engine and Rotor       Torque--5% Rotor                              a step input to the
                                                    Speed--1.5%.                                 conducted
                                                                                concurrently with
                                                                                climb and descent
                                                                                performance tests.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.b.......................  Reserved.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.c.......................  Takeoff.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.c.1.....................  All Engines..........  Airspeed--3 kt,           Initial Segment of    takeoff flight path
                                                    Altitude--20 ft (6.1 m)                         and takeoff from a
                                                    Torque--3%, Rotor                             criteria apply only
                                                    Speed--1.5%,                                 at airspeeds above
                                                    Vertical Velocity--                         effective
                                                    100 fpm                         translational lift.
                                                    (0.50 m/sec) or                             Results must be
                                                    10%, Pitch                                  recorded from the
                                                    Attitude--1.5[deg],                             takeoff to at least
                                                    Bank Attitude--                             200 ft (61 m) AGL.
                                                    2[deg],
                                                    Heading--2[deg],
                                                    Longitudinal
                                                    Control Position--
                                                    10%,
                                                    Lateral Control
                                                    Position--10%,
                                                    Directional Control
                                                    Position--10%,
                                                    Collective Control
                                                    Position--10%.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.c.2. through 1.c.3......  Reserved.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.d.......................  Hover.
--------------------------------------------------------------------------------------------------------------------------------------------------------
                            Performance..........  Torque--3%, Pitch       (IGE); and Out of     light and heavy
                                                    Attitude--1.5[deg],                             be a series of
                                                    Bank Attitude--                             snapshot tests.
                                                    1.5[deg],
                                                    Longitudinal
                                                    Control Position--
                                                    5%,
                                                    Lateral Control
                                                    Position--5%,
                                                    Directional Control
                                                    Position--5%,
                                                    Collective Control
                                                    Position--5%.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.e.......................  Vertical Climb.
--------------------------------------------------------------------------------------------------------------------------------------------------------
                            Performance..........  Vertical Velocity--   From OGE Hover......  Record results for    ...  ...   X
                                                    100 fpm                         light and heavy
                                                    (0.50 m/sec) or                             gross weights. May
                                                    10%,                            be a series of
                                                    Directional Control                         snapshot tests.
                                                    Position--5%,
                                                    Collective Control
                                                    Position--5%.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.f.......................  Level Flight.
--------------------------------------------------------------------------------------------------------------------------------------------------------

                            Performance and        Torque--3% Pitch        On and Off).          two gross weight                     performance at
                             Control Positions.     Attitude--1.5[deg]                              with varying trim                    maximum endurance
                                                    Sideslip Angle--                            speeds throughout                    airspeed.
                                                    2[deg]                          the airspeed
                                                    Longitudinal                                envelope. May be a
                                                    Control Position--                          series of snapshot
                                                    5%                              tests.
                                                    Lateral Control
                                                    Position--5%
                                                    Directional Control
                                                    Position--5% Collective
                                                    Control Position--
                                                    5%.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.g.......................  Climb.
--------------------------------------------------------------------------------------------------------------------------------------------------------
                            Performance and        Vertical Velocity--   All engines           Record results for     X    X    X
                             Trimmed Flight         100 fpm   operating.            two gross weight
                             Control Positions.     (61 m/sec) or 10% Pitch       inoperative.          combinations. The
                                                    Attitude--1.5[deg]        System(s) On and      be for normal climb
                                                    Sideslip Angle--      Off.                  power conditions.
                                                    2[deg]                          May be a series of
                                                    Longitudinal                                snapshot tests.
                                                    Control Position--
                                                    5%
                                                    Lateral Control
                                                    Position--5%
                                                    Directional Control
                                                    Position--5% Collective
                                                    Control Position--
                                                    5%.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.h.......................  Descent.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.h.1.....................  Descent Performance    Torque--3% Pitch        (5 m/sec) rate of     two gross weight
                             Control Positions.     Attitude--1.5[deg]        normal approach       combinations. May
                                                    Sideslip Angle--      speed.                be a series of
                                                    2[deg]   Augmentation           snapshot tests.
                                                    Longitudinal          System(s) On and
                                                    Control Position--    Off.
                                                    5%
                                                    Lateral Control
                                                    Position--5%
                                                    Directional Control
                                                    Position--5% Collective
                                                    Control Position--
                                                    5%.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.h.2.....................  Autorotation           Pitch Attitude--      Steady descents.      Record results for     X    X    X
                             Performance and        1.5[deg]        System(s) On and      conditions. Data
                             Control Positions.     Sideslip Angle--      Off.                  must be recorded
                                                    2[deg]                          for normal
                                                    Longitudinal                                operating RPM.
                                                    Control Position--                          (Rotor speed
                                                    5%                              tolerance applies
                                                    Lateral Control                             only if collective
                                                    Position--5%                                    full down.) Data
                                                    Directional Control                         must be recorded
                                                    Position--5% Collective                         kts, 5
                                                    Control Position--                          kts through at
                                                    5%.                             least maximum glide
                                                                                distance airspeed.
                                                                                May be a series of
                                                                                snapshot tests.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.i.......................  Autorotation.
--------------------------------------------------------------------------------------------------------------------------------------------------------

                            Entry................  Rotor Speed--3% Pitch                              rapid throttle
                                                    Attitude 2[deg] Roll                           If accomplished in
                                                    Attitude--3[deg] Yaw                            must be for the
                                                    Attitude--5[deg]                                airspeed. If
                                                    Airspeed--5 kts.                                climb, results must
                                                    Vertical Velocity--                         be for the maximum
                                                    200 fpm                         rate of climb
                                                    (1.00 m/sec) or 10%.                        airspeed at or near
                                                                                maximum continuous
                                                                                power.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.j.......................  Landing.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.j.1.....................  All Engines..........  Airspeed--3 kts,                                the approach and
                                                    Altitude--20 ft (6.1 m)                         (running landing or
                                                    Torque--3%, Rotor                             hover). The
                                                    Speed--1.5%, Pitch                           to those segments
                                                    Attitude--1.5[deg],                             effective
                                                    Bank Attitude--                             translational lift.
                                                    1.5[deg],                             from 200 ft AGL (61
                                                    Heading--2[deg],                               or to where the
                                                    Longitudinal                                hover is
                                                    Control Position--                          established prior
                                                    10%,                            to landing.
                                                    Lateral Control
                                                    Position--10%,
                                                    Directional Control
                                                    Position--10%,
                                                    Collective Control
                                                    Position--10%.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.j.2. through 1.j.3......  Reserved.
--------------------------------------------------------------------------------------------------------------------------------------------------------

1.j.4.....................  Autorotational         Torque--3%, Rotor                             of an                                containing all
                                                    Speed--3%, Vertical                          deceleration and                     for a complete
                                                    Velocity--100 fpm (0.50                         stabilized                           is not available
                                                    m/sec) or 10%,                              autorotational                       from the aircraft
                                                    Pitch Attitude--                            descent, to touch                    manufacturer for
                                                    2[deg],                         down.                                this test, and
                                                    Bank Attitude--                                                                  other qualified
                                                    2[deg],                                                              flight test
                                                    Heading--5[deg],                                                                    available to
                                                    Longitudinal                                                                     acquire this data,
                                                    Control Position--                                                               the sponsor must
                                                    10%,                                                                 coordinate with the
                                                    Lateral Control                                                                  NSPM to determine
                                                    Position--10%,                                                                       appropriate to
                                                    Directional Control                                                              accept alternative
                                                    Position--10%,                                                                       Alternative
                                                    Collective Control                                                               approaches to this
                                                    Position--10%.                                                                       that may be
                                                                                acceptable are: (1)
                                                                                A simulated
                                                                                autorotational
                                                                                flare and reduction
                                                                                of rate of descent
                                                                                (ROD) at altitude;
                                                                                or (2) a power-on
                                                                                termination
                                                                                following an
                                                                                autorotational
                                                                                approach and flare.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.                          Handling Qualities
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a.......................  Control System         Contact the NSPM for
                             Mechanical             clarification of
                             Characteristics.       any issue regarding
                                                    helicopters with
                                                    reversible controls.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a.1.....................  Cyclic...............  Breakout--0.25 lbs        conditions. Trim On   an uninterrupted
                                                    (0.112 daN) or 25%.   and Off. Friction     control sweep to
                                                    Force--1.0 lb (0.224   On and Off.           test does not apply
                                                    daN) or 10%.                                if aircraft
                                                                                hardware modular
                                                                                controllers are
                                                                                used.).
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a.2.....................  Collective and Pedals  Breakout--0.5 lb (0.224   conditions. Trim On   an uninterrupted
                                                    daN) or 25%. Force--  and Off. Friction     control sweep to
                                                    1.0 lb    Off. Augmentation     the stops.
                                                    (0.224 daN) or 10%.   On and Off.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a.3.....................  Brake Pedal Force vs.  5 lbs     Ground; Static        ....................   X    X    X
                             Position.              (2.224 daN) or 10%.   conditions.
--------------------------------------------------------------------------------------------------------------------------------------------------------

2.a.4.....................  Trim System Rate (all  Rate--10%.            conditions. Trim      applies to the
                                                                          On. Friction Off.     recorded value of
                                                                                the trim rate.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a.5.....................  Control Dynamics (all  10% of    Hover/Cruise Trim On  Results must be       ...   X    X   Control Dynamics for
                             axes).                 time for first zero   Friction Off.         recorded for a                       irreversible
                                                    crossing and 10 (N+1)% of                          displacement in                      be evaluated in a
                                                    period thereafter.                          both directions in                   ground/static
                                                    10% of                          each axis, using                     condition. Refer to
                                                    amplitude of first                          25% to 50% of full                   paragraph 3 of this
                                                    overshoot. 20% of                                                                     additional
                                                    amplitude of 2nd                                                                 information. ``N''
                                                    and subsequent                                                                   is the sequential
                                                    overshoots greater                                                               period of a full
                                                    than 5% of initial                                                               cycle of
                                                    displacement. 1 overshoot.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a.6.....................  Freeplay.............  0.10 in.  Ground; Static        Record and compare     X    X    X
                                                    (2.5      conditions.           results for all
                                                    mm).                                        controls.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.b.......................  Low Airspeed Handling Qualities.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.b.1.....................  Trimmed Flight         Torque 3% Pitch        IGE--Sideward,        several airspeed
                                                    Attitude 1.5[deg] Bank   forward flight.       translational
                                                    Attitude 2[deg]          Off.                  for 45 kts. forward
                                                    Longitudinal                                airspeed. May be a
                                                    Control Position                            series of snapshot
                                                    5%                              tests.
                                                    Lateral Control
                                                    Position 5%
                                                    Directional Control
                                                    Position 5% Collective
                                                    Control Position
                                                    5%.
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2.b.2.....................  Critical Azimuth.....  Torque 3% Pitch        Augmentation On and   three relative wind
                                                    Attitude 1.5[deg],                             (including the most
                                                    Bank Attitude 2[deg],                               the critical
                                                    Longitudinal                                quadrant. May be a
                                                    Control Position                            series of snapshot
                                                    5%,                             tests.
                                                    Lateral Control
                                                    Position 5%,
                                                    Directional Control
                                                    Position 5%,
                                                    Collective Control
                                                    Position 5%.
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2.b.3.....................  Control Response.
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2.b.3.a...................  Longitudinal.........  Pitch Rate--10% or 2[deg]/sec.                           The Off-axis
                                                    Pitch Attitude                              response must show
                                                    Change--10% or                                unaugmented cases.
                                                    1.5[deg].                                   This test must be
                                                                                conducted in a
                                                                                hover, in ground
                                                                                effect, without
                                                                                entering
                                                                                translational
                                                                                flight.
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2.b.3.b...................  Lateral..............  Roll Rate--10% or 3[deg]/sec.                           The Off-axis                         conducted in a
                                                    Roll Attitude                               response must show                   hover, in ground
                                                    Change--10% or 3[deg].                                                                    translational
                                                                                flight, to provide
                                                                                better visual
                                                                                reference.
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2.b.3.c...................  Directional..........  Yaw Rate--10% or 2[deg]/sec.                           The Off-axis
                                                    Heading Change--                            response must show
                                                    10% or                          correct trend for
                                                    2[deg].                         unaugmented cases.
                                                                                This test must be
                                                                                conducted in a
                                                                                hover, in ground
                                                                                effect, without
                                                                                entering
                                                                                translational
                                                                                flight.
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2.b.3.d...................  Vertical.............  Normal Acceleration   Hover Augmentation    Record results for a  ...  ...   X
                                                    0.1g.     On and Off.           step control input.
                                                                                The Off-axis
                                                                                response must show
                                                                                correct trend for
                                                                                unaugmented cases.
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2.c.......................  Longitudinal Handling Qualities.
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2.c.1.....................  Control Response.....  Pitch Rate--10% or 2[deg]/sec.                           cruise airspeeds to
                                                    Pitch Attitude                              include minimum
                                                    Change--10% or 1.5[deg].                             for a step control
                                                                                input. The Off-axis
                                                                                response must show
                                                                                correct trend for
                                                                                unaugmented cases.
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2.c.2.....................  Static Stability.....  Longitudinal Control  Cruise or Climb.      Record results for a   X    X    X
                                                    Position: 10% of change   Augmentation On and   speeds on each side
                                                    from trim or 0.25 in. (6.3                         May be a series of
                                                    mm) or Longitudinal                         snapshot tests.
                                                    Control Force:
                                                    0.5 lb.
                                                    (0.223 daN) or
                                                    10%.
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2.c.3.....................  Dynamic Stability.
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2.c.3.a...................  Long Term Response...  10% of    Cruise Augmentation   Record results for     X    X    X   The response for
                                                    calculated period.    On and Off.           three full cycles                    certain helicopters
                                                    10% of                          (6 overshoots after                  may be unrepeatable
                                                    time to \1/2\ or                            input completed) or                  throughout the
                                                    double amplitude,                           that sufficient to                   stated time. In
                                                    or 0.02                         determine time to                    these cases, the
                                                    of damping ratio.                           \1/2\ or double                      test should show at
                                                    For non-periodic                            amplitude,                           least that a
                                                    responses, the time                         whichever is less.                   divergence is
                                                    history must be                             For non-periodic                     identifiable. For
                                                    matched within                              responses, the test                  example: Displacing
                                                    3[deg]                          may be terminated                    the cyclic for a
                                                    pitch; and 5 kts                                 the test pilot                       excites this test
                                                    airspeed over a 20                          determines that the                  or until a given
                                                    sec period                                  results are                          pitch attitude is
                                                    following release                           becoming                             achieved and then
                                                    of the controls.                            uncontrollably                       return the cyclic
                                                                                divergent. Displace                  to the original
                                                                                the cyclic for one                   position. For non-
                                                                                second or less to                    periodic responses,
                                                                                excite the test.                     results should show
                                                                                The result will be                   the same convergent
                                                                                either convergent                    or divergent
                                                                                or divergent and                     character as the
                                                                                must be recorded.                    flight test data.
                                                                                If this method
                                                                                fails to excite the
                                                                                test, displace the
                                                                                cyclic to the
                                                                                predetermined
                                                                                maximum desired
                                                                                pitch attitude and
                                                                                return to the
                                                                                original position.
                                                                                If this method is
                                                                                used, record the
                                                                                results.
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2.c.3.b...................  Short Term Response..  1.5[deg]  Cruise or Climb.      Record results for    ...   X    X   A control doublet
                                                    Pitch or 2[deg]/sec.     Off.                  airspeeds.                           natural frequency
                                                    Pitch Rate. 0.1 g Normal                                                               normally excites
                                                    Acceleration.                                                                    this test. However,
                                                                                while input
                                                                                doublets are
                                                                                preferred over
                                                                                pulse inputs for
                                                                                Augmentation-Off
                                                                                tests, for
                                                                                Augmentation-On
                                                                                cases, when the
                                                                                short term response
                                                                                exhibits 1st-order
                                                                                or deadbeat
                                                                                characteristics,
                                                                                longitudinal pulse
                                                                                inputs may produce
                                                                                a more coherent
                                                                                response.
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2.c.4.....................  Maneuvering Stability  Longitudinal Control  Cruise or Climb.      Record results for    ...   X    X
                                                    Position--10% of change   Off.                  airspeeds at
                                                    from trim or 0.25 in. (6.3                         bank angle. The
                                                    mm) or Longitudinal                         force may be shown
                                                    Control Forces--                            as a cross plot for
                                                    0.5 lb.                         irreversible
                                                    (0.223 daN) or                              systems. May be a
                                                    10%.                            series of snapshot
                                                                                tests.
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2.d.......................  Lateral and Directional Handling Qualities.
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2.d.1.....................  Control Response.
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2.d.1.a...................  Lateral..............  Roll Rate--10% or 3[deg]/sec.                           airspeeds,
                                                    Roll Attitude                               including the speed
                                                    Change--10% or 3[deg].                               required airspeed.
                                                                                Record results for
                                                                                a step control
                                                                                input. The Off-axis
                                                                                response must show
                                                                                correct trend for
                                                                                unaugmented cases.
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2.d.1.b...................  Directional..........  Yaw Rate--10% or 2[deg]/sec.                           Airspeeds,
                                                    Yaw Attitude                                including the speed
                                                    Change--10% or 2[deg].                               required airspeed.
                                                                                Record results for
                                                                                a step control
                                                                                input. The Off-axis
                                                                                response must show
                                                                                correct trend for
                                                                                unaugmented cases.
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2.d.2.....................  Directional Static     Lateral Control       Cruise; or Climb      Record results for     X    X    X   This is a steady
                             Stability.             Position--10% of change   instead of Climb if   sideslip angles on                   test at a fixed
                                                    from trim or 0.25 in. (6.3   Augmentation On and   trim point. The                      position.
                                                    mm) or Lateral        Off.                  force may be shown
                                                    Control Force--                             as a cross plot for
                                                    0.5 lb.                         irreversible
                                                    (0.223 daN) or 10%.                         systems. May be a
                                                    Roll Attitude--                             series of snapshot
                                                    1.5                             tests.
                                                    Directional Control
                                                    Position--10% of change
                                                    from trim or 0.25 in. (6.3
                                                    mm) or Directional
                                                    Control Force--
                                                    1 lb.
                                                    (0.448 daN) or 10%.
                                                    Longitudinal
                                                    Control Position--
                                                    10% of
                                                    change from trim or
                                                    0.25
                                                    in. (6.3 mm).
                                                    Vertical Velocity--
                                                    100 fpm
                                                    (0.50m/sec) or 10%.
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2.d.3.....................  Dynamic Lateral and Directional Stability.
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2.d.3.a...................  Lateral-Directional    0.5 sec.  Cruise or Climb       Record results for     X    X    X
                             Oscillations.          or 10%    Augmentation On and   at least two
                                                    of period. 10% of time                           must be initiated
                                                    to \1/2\ or double                          with a cyclic or a
                                                    amplitude or 0.02 of                               input. Record
                                                    damping ratio.                              results for six
                                                    20% or                          full cycles (12
                                                    1 sec                           overshoots after
                                                    of time difference                          input completed) or
                                                    between peaks of                            that sufficient to
                                                    bank and sideslip.                          determine time to
                                                    For non-periodic                            \1/2\ or double
                                                    responses, the time                         amplitude,
                                                    history must be                             whichever is less.
                                                    matched within                              The test may be
                                                    10                              terminated prior to
                                                    knots Airspeed;                             20 sec if the test
                                                    5[deg]/                         pilot determines
                                                    s Roll Rate or                              that the results
                                                    5[deg]                          are becoming
                                                    Roll Attitude;                              uncontrollably
                                                    4[deg]/                         divergent.
                                                    s Yaw Rate or 4[deg] Yaw
                                                    Angle over a 20 sec
                                                    period roll angle
                                                    following release
                                                    of the controls.
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2.d.3.b...................  Spiral Stability.....  2[deg]    Cruise or Climb.      Record the results     X    X    X
                                                    or 10%    Augmentation On and   of a release from
                                                    roll angle.           Off.                  pedal only or
                                                                                cyclic only turns
                                                                                for 20 sec. Results
                                                                                must be recorded
                                                                                from turns in both
                                                                                directions.
                                                                                Terminate check at
                                                                                zero roll angle or
                                                                                when the test pilot
                                                                                determines that the
                                                                                attitude is
                                                                                becoming
                                                                                uncontrollably
                                                                                divergent.
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2.d.3.c...................  Adverse/Proverse Yaw.  Correct Trend, 2[deg]          Augmentation On and   history of initial
                                                    transient sideslip    Off.                  entry into cyclic
                                                    angle.                                      only turns, using
                                                                                only a moderate
                                                                                rate for cyclic
                                                                                input. Results must
                                                                                be recorded for
                                                                                turns in both
                                                                                directions.
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3.                          Reserved
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4.                          Visual System