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<body>

<h1><img src="Images/fsx-bannerjet.jpg" width="800" height="200"></h1>
<h1>Aircraft Configuration Files</h1>
<h2>Overview</h2>

The aircraft configuration file (aircraft.cfg) represents the highest
level of organization
within an aircraft container. Each aircraft has its own configuration
file located in its container (aircraft folder). For example, the
Cessna 182S aircraft.cfg can be found at <br>

<br>

SimObjects\Aircraft\C182\aircraft.cfg<br>

<br>

The aircraft.cfg file specifies the versions of the aircraft included
in the aircraft container, as well as the attributes (name, color,
sound, panels, gauges, and so on) for each aircraft and where to find
the files that define those attributes. Within the aircraft.cfg file
there are a number of sections. Brackets
enclosing the section name identify the various sections. In order for
<i>Flight Simulator</i> to make proper use of any variable, it is important
that the variable be located in the correct section. While exact
spelling is important, none of the terms is case-sensitive.<br>

<br>

<h2>Table of Contents</h2>

<ul id="mozToc">

<!--mozToc h3 3 h4 4--><li><a href="#mozTocId409079">Testing Changes to aircraft.cfg </a>
  </li>

  <li><a href="#mozTocId630926">[fltsim.n]</a></li>

  <li><a href="#mozTocId678569">[general]</a></li>

  <li><a href="#mozTocId311850">[pitot_static]</a></li>

  <li><a href="#mozTocId243173">[weight_and_balance]</a></li>

  <li><a href="#mozTocId717787">[flight_tuning]</a></li>

  <li><a href="#mozTocId136011">[generalenginedata]</a></li>

  <li><a href="#mozTocId50743">[turbineenginedata]</a></li>

  <li><a href="#mozTocId467871">[jet_engine]</a></li>

  <li><a href="#mozTocId245287">[electrical]</a></li>

  <li><a href="#mozTocId836373">[contact_points]</a></li>

  <li><a href="#mozTocId54524">[gear_warning_system]</a></li>

  <li><a href="#mozTocId774770">[brakes]</a></li>

  <li><a href="#mozTocId990703">[hydraulic_system]</a></li>

  <li><a href="#mozTocId810089">[views]</a></li>

  <li><a href="#mozTocId895147">[flaps.n]</a></li>

  <li><a href="#mozTocId77591">[radios]</a></li>

  <li><a href="#mozTocId274992">[lights]</a></li>

  <li><a href="#mozTocId495225">[keyboard_response]</a></li>

  <li><a href="#mozTocId786368">[direction_indicators]</a></li>

  <li><a href="#altimeters">[altimeters]</a></li>
  <li><a href="#mozTocId657009">[attitude_indicators]</a></li>

  <li><a href="#mozTocId854181">[turn_indicators]</a></li>

  <li><a href="#mozTocId729957">[vacuum_system]</a></li>

  <li><a href="#mozTocId465058">[pneumatic_system]</a></li>

  <li><a href="#mozTocId310622">[exits]</a></li>

  <li><a href="#mozTocId547795">[effects]</a></li>

  <li><a href="#mozTocId942782">[autopilot]</a></li>

  <li><a href="#mozTocId38401">[fuel]</a></li>

  <li><a href="#mozTocId548772">[airplane_geometry]</a></li>

  <li><a href="#mozTocId16333">[reference
speeds]</a></li>

  <li><a href="#mozTocId567955">[forcefeedback]</a></li>

  <li><a href="#mozTocId74684">[stall_warning]</a></li>

  <li><a href="#mozTocId14561">[deice_system]</a></li>

  <li><a href="#mozTocId57822">[piston_engine]</a></li>

  <li><a href="#mozTocId804485">[propeller]</a></li>

  <li><a href="#mozTocId600406">[magneticcompass]</a></li>

  <li><a href="#gpws">[gpws]</a></li>
  <li><a href="#mozTocId157738">[cameradefinition.n]</a></li>

  <li><a href="#mozTocId584060">[turboprop_engine]</a></li>

  <li><a href="#mozTocId818226">[airspeed_indicators]</a></li>

  <li><a href="#mozTocId183639">[pressurization]</a></li>

  <li><a href="#mozTocId797074">[variometers]</a></li>

  <li><a href="#mozTocId16616">[yaw_string]</a></li>

  <li><a href="#mozTocId975761">[water
ballast system]</a></li>

  <li><a href="#mozTocId510108">[smokesystem]</a></li>

  <li><a href="#mozTocId200113">Helicopter
Specific Sections</a> </li>

  <li><a href="#mozTocId641828">[helicopter]</a></li>

  <li><a href="#mozTocId36503">[fuselage_aerodynamics]</a></li>

  <li><a href="#mozTocId517455">[mainrotor]</a></li>

  <li><a href="#mozTocId786461">[secondaryrotor]</a></li>
</ul>

<h3><a class="mozTocH3" name="mozTocId409079"></a>Testing
Changes to the aircraft.cfg file
</h3>

To see the effects of a change, the aircraft must be
reloaded.&nbsp; Aircraft are loaded into the memory cache from
disk, so you have to flush the cache to enable your changes to be
reflected in-game. This involves a couple of steps:<br>

<ol>

  <li>Configure a key command to Reload User
Aircraft (which will reload your
aircraft from within the simulation). To do this go to Settings,
Controls
Assignments, and scroll down to the&nbsp;Reload User
Aircraft event.&nbsp; By default, it&rsquo;s
unassigned.&nbsp; Use Change Assignment to configure a keystroke
combination for this event.&nbsp; Once assigned, you can use this
key command to reload the aircraft within the simulation.</li>

  <li>Turn off AI Traffic in the game. AI
traffic aircraft are maintained in the cache and even if you update the
aircraft you are currently piloting, if the same aircraft is
being used by AI traffic, then your cache won&rsquo;t get updated
automatically by simply reloading the plane.&nbsp; So to ensure
your aircraft is reloaded from disk, you must also go to the Settings
Screen, choose Traffic, and set the Air Traffic Density slider all the
way to the left to 0%.</li>

  <li>Now you can test changes made to an aircraft.cfg within the
game by using
the Reload User Aircraft key command after each change, or set of
changes, is made.&nbsp;<br>

  </li>

</ol>

Any errors made in creating or editing the aircraft.cfg file will show
up, along with the following error messages, while an aircraft is being
loaded. The error messages are listed in order; that is, the first
error message represents an error early in the aircraft-loading process.<br>

<br>

<table style="text-align: left; width: 640px;" border="1" cellpadding="2" cellspacing="2">

  <tbody>

    <tr>

      <td align="undefined" valign="undefined"><span style="font-weight: bold;">Error Message</span></td>

      <td align="undefined" valign="undefined"><span style="font-weight: bold;">Description</span></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">Aircraft
initialization failure.&nbsp;</td>

      <td align="undefined" valign="undefined">Indicates
that some essential files are missing from the aircraft
container. If the files are missing, the aircraft will not usually be
displayed in the Select Aircraft dialog box; as a result, this error is
rare.</td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">Failed
to start up the flight model.</td>

      <td align="undefined" valign="undefined">The
.air file was not loaded successfully.</td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">This
is not a Flight Simulator aircraft model.&nbsp;</td>

      <td align="undefined" valign="undefined">The
visual model (.mdl) file for this aircraft is not compatible with <span style="font-style: italic;">Flight Simulator</span> </td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">Visual
model could not be displayed.&nbsp;</td>

      <td align="undefined" valign="undefined">An
error occurred while loading the visual model (.mdl) file.</td>

    </tr>

  </tbody>
</table>

&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;<br>

<h4><a class="mozTocH4" name="mozTocId630926"></a>[fltsim.n]</h4>

<p>Each <span style="font-weight: bold;">[fltsim.n]
</span>section of an aircraft configuration file represents a
different version (configuration) of the aircraft, and is known as a
configuration set. Configuration sets allow a single aircraft container
to represent several aircraft, and allow those aircraft to share
components.</p>

<p>If there is only one section (labeled <span style="font-weight: bold;">[fltsim.0]</span>), it is
because there is only one configuration set in that aircraft container.
If there is more than one configuration set (labeled <span style="font-weight: bold;">[fltsim.0]</span>, <span style="font-weight: bold;">[fltsim.1]</span>, <span style="font-weight: bold;">[fltsim.2]</span>, and so
on), each one refers to a different version of the aircraft. </p>

<p>For instance, there are several versions of the Cessna 182,
all
housed in the same C182 aircraft container (folder).&nbsp;The
various versions must vary by their title, and may also vary other
items such as the panel, description, and sounds.</p>

<p>While these configuration sets share many components, they can
each use different panels. The <span style="font-weight: bold;">panel=</span>
line in the respective&nbsp;fltsim sections thus refer to the
respective panel folder
for each aircraft:&nbsp; For example,&nbsp;<span style="font-weight: bold;">panel=ifr</span> means that
this version of the C182
uses the panel files in the panel.ifr subfolder. </p>

<p>When creating and referencing multiple model, panel, sound,
and texture directories, use the naming convention
<span style="font-style: italic;">foldername.extension</span>,
where the extension is a unique identifier for
that configuration set (for example, .ifr). To refer to the folder from
the
relevant parameter in the aircraft.cfg file, just specify the extension
(for example, <span style="font-weight: bold;">panel=ifr</span>).
If a parameter is not explicitly set&nbsp;it automatically refers
to
the default (extension-less) folder. </p>

<p>The parameters in each configuration set can refer to the same
files, to different files, or to a mix of files. While using different
panels, all Cessna configurations use the same sounds, and thus the
sound parameters in all the&nbsp;fltsim sections point to the
single&nbsp;<span style="font-style: italic;">sound</span>
folder in the C182 folder.</p>

<p>Each aircraft defined by a configuration set will appear as a
separate listing in the Select Aircraft dialog box. The fact that
multiple&nbsp;aircraft share some components is hidden
from the user. From a user&rsquo;s perspective, they are distinct
aircraft (just as if all the common files were duplicated and included
in three distinct aircraft containers). From a developer&rsquo;s
perspective, the aircraft are really just different configuration sets
of the same aircraft. Because they share some files, they make much
more efficient use of disk space.</p>

<p>Within each<span style="font-weight: bold;">
[fltsim.n]</span> section are parameters that define the
details of that particular configuration set:</p>

<p></p>

<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>      </td>

      <td>
      <h5>Description </h5>      </td>

      <td>
      <h5>Examples</h5>      </td>
    </tr>

    <tr>

      <td>title</td>

      <td>The title of the aircraft. </td>

      <td>Airbus A321( <b>title=Airbus A321</b> )<br>

Aircreation582SL( <b>title= Aircreation582SL</b> )<br>

Boeing 737-800( <b>title=Boeing 737-800</b> )<br>

Boeing 747-400( <b>title=Boeing 747-400</b> ) </td>
    </tr>

    <tr>

      <td>sim</td>

      <td>Specifies which .air (flight model) file (located in
the aircraft folder) to use. </td>

      <td>Airbus A321( <b>sim=Airbus_A321</b> )<br>

Aircreation582SL( <b>sim=trike</b> )<br>

Boeing 737-800( <b>sim=Boeing737-800</b> )<br>

Boeing 747-400( <b>sim=Boeing747-400</b> ) </td>
    </tr>

    <tr>

      <td>model</td>

      <td>Specifies which model folder to reference. If no entry
is made, the default folder is used. </td>

      <td>Airbus A321( <b>model=</b> ) </td>
    </tr>

    <tr>

      <td>panel</td>

      <td>Specifies which panel folder to reference. </td>

      <td>Airbus A321( <b>panel=</b> )<br>

Beech Baron 58( <b>panel=g1000</b> )<br>

Cessna Skyhawk 172SP( <b>panel=G1000</b> ) </td>
    </tr>

    <tr>

      <td>sound</td>

      <td>Specifies which sound folder to reference. </td>

      <td>Airbus A321( <b>sound=</b> ) </td>
    </tr>

    <tr>

      <td>texture</td>

      <td>Specifies which texture folder to reference. </td>

      <td>Airbus A321( <b>texture=</b> )<br>

Aircreation582SL( <b>texture=1</b> )<br>

Boeing 737-800( <b>texture=2</b> )<br>

Boeing 747-400( <b>texture=3</b> ) </td>
    </tr>

    <tr>

      <td>kb_checklists</td>

      <td>Specifies which _check.txt file (located in the
aircraft folder) to use on the Checklists tab of the kneeboard. </td>

      <td>Boeing 737-800( <b>kb_checklists=Boeing737-800_check</b>
)<br>

Boeing 747-400( <b>kb_checklists=Boeing747-400_check</b> )<br>

Beech Baron 58( <b>kb_checklists=Beech_Baron_58_check</b>
) </td>
    </tr>

    <tr>

      <td>kb_reference</td>

      <td>Specifies which _ref.txt file (located in the aircraft
folder) to use on the Reference tab of the kneeboard. </td>

      <td>Boeing 737-800( <b>kb_reference=Boeing737-800_ref</b>
)<br>

Boeing 747-400( <b>kb_reference=Boeing747-400_ref</b> )<br>

Beech Baron 58( <b>kb_reference=Beech_Baron_58_ref</b> ) </td>
    </tr>

    <tr>

      <td>atc_id</td>

      <td>The tail number displayed on the exterior of the
aircraft. This parameter can also be edited from the Select Aircraft
dialog (if the atc_id_enable parameter is set to 1).&nbsp;Note that
custom tail numbers burned into textures will not be modified by
this. </td>

      <td>Boeing 737-800( <b>atc_id=N737Z</b> )<br>

Boeing 747-400( <b>atc_id=N747</b> )<br>

Beech Baron 58( <b>atc_id=N058BE</b> ) </td>
    </tr>

    <tr>

      <td>atc_airline</td>

      <td>The ATC system will use the specified airline name with
this aircraft. This is dependant on ATC recognizing the name. ATC will
treat this aircraft as an airliner when this is used in conjunction
with atc_flight_number. </td>

      <td>Boeing 737-800( <b>atc_airline=American Pacific</b>
)<br>

Boeing 747-400( <b>atc_airline=Global Freightways</b> )<br>

Cessna Grand Caravan( <b>atc_airline=Landmark</b> ) </td>
    </tr>

    <tr>

      <td>atc_flight_number</td>

      <td>The ATC system will use this number as part of the
aircrafts callsign. ATC will treat this aircraft as an airliner when
this is used in conjunction with atc_airline. </td>

      <td>Boeing 737-800( <b>atc_flight_number=1123</b>
) </td>
    </tr>

    <tr>

      <td>ui_manufacturer</td>

      <td>This value identifies the manufacturer sub-category
used to group aircraft in the select aircraft dialog inside <i>Flight
Simulator</i>. </td>

      <td>Airbus A321( <b>ui_manufacturer="Airbus"</b>
)<br>

Aircreation582SL( <b>ui_manufacturer="AirCreation"</b> )<br>

Boeing 737-800( <b>ui_manufacturer="Boeing"</b> )<br>

Beech Baron 58( <b>ui_manufacturer="Beechcraft"</b> ) </td>
    </tr>

    <tr>

      <td>ui_type</td>

      <td>This value identifies the type sub-category used to
group aircraft in the select aircraft dialog inside <i>Flight
Simulator</i>. </td>

      <td>Airbus A321( <b>ui_type="A321"</b> )<br>

Aircreation582SL( <b>ui_type= "582 SL Trike"</b> )<br>

Boeing 737-800( <b>ui_type="737-800"</b> )<br>

Boeing 747-400( <b>ui_type="747-400"</b> ) </td>
    </tr>

    <tr>

      <td>ui_variation</td>

      <td>This value identifies the variation sub-category used
to group aircraft in the select aircraft dialog inside <i>Flight
Simulator</i>. </td>

      <td>Aircreation582SL( <b>ui_variation="Green Wing"</b>
)<br>

Boeing 737-800( <b>ui_variation="American Pacific Airways"</b>
)<br>

Boeing 747-400( <b>ui_variation="Global Freightways"</b> )      </td>
    </tr>

    <tr>

      <td>ui_typerole</td>

      <td>This value identifies the role of the aircraft.. </td>

      <td>Airbus A321( <b>ui_typerole="Commercial Airliner"</b>
)<br>

Aircreation582SL( <b>ui_typerole="Single Engine Prop"</b> )<br>

Beech Baron 58( <b>ui_typerole="Twin Engine Prop"</b> )<br>

Beech King Air 350( <b>ui_typerole="Twin Engine TurboProp"</b>
) </td>
    </tr>

    <tr>

      <td>ui_createdby</td>

      <td>This value is used to idenfity the creator of the
configuration file. </td>

      <td>Airbus A321( <b>ui_createdby="Microsoft
Corporation"</b> ) </td>
    </tr>

    <tr>

      <td>description</td>

      <td>The aircraft description can be modified to say
whatever you like about the aircraft. This information will be
displayed in the description box inside <i>Flight Simulator</i>
when the aircraft is
selected. (The \s is used to produce a semicolon ( ; ) punctuation mark
within the in-game description.). </td>

      <td>Boeing 737-800( <b>description="One should
hardly be surprised
that the world's most prolific manufacturer of commercial aircraft is
also the producer of the world's most popular jetliner. The 737 became
the best-selling commercial jetliner worldwide when orders for it hit
1,831 in June 1987 (surpassing Boeing's own 727 as the previous champ).
However, it wasn't always that way\s in the first few years of
production, there were so few orders that Boeing considered canceling
the program. They didn't, and the airplane has more than proven itself
in over three decades of service."</b> )<br>

      <br>

Boeing 747-400( <b>description="More than 30 years ago, the 747
made its first trip from New York to London. Since then, it's become
the standard by which other large passenger jets are judged. Its size,
range, speed and capacity were then, and are now, the best in its
class."</b> ) </td>
    </tr>


    <tr>

      <td>visual_damage</td>

      <td>Setting this flag to 1 enables visual damage (e.g.
parts breaking off) to be seen when crashing the aircraft into the
scenery. Note: visual damage will only work if it is built into the
aircrafts .mdl file. </td>

      <td>Aircreation582SL( <b>visual_damage=1</b> )      </td>
    </tr>

    <tr>

      <td>atc_heavy</td>

      <td>Setting this flag to 1 will result in the ATC system
appending the phrase heavy to the aircrafts callsign. </td>

      <td>Aircreation582SL( <b>atc_heavy=0</b> )<br>

Boeing 747-400( <b>atc_heavy=1</b> ) </td>
    </tr>

    <tr>

      <td>atc_parking_types</td>

      <td>Specifies the preferred parking for this aircraft, used
by ATC. If this line is omitted, ATC will determine parking according
to the type of aircraft and parking available. If multiple values are
listed, preference will be given in the order in which they are listed.
The valid values may be one or more of the following: RAMP, CARGO,
GATE, DOCK, MIL_CARGO, MIL_COMBAT. </td>

      <td>Aircreation582SL( <b>atc_parking_types=RAMP</b>
)<br>

Boeing 747-400( <b>atc_parking_types=CARGO</b> )<br>

de Havilland Dash 8-100( <b>atc_parking_types=GATE,RAMP</b>
) </td>
    </tr>

    <tr>

      <td>atc_id_color</td>

      <td>Specifies, in RGB hexadecimal, the color of the tail
number. The first two characters following the 0x specify the red value
in hex, the second two characters the green, and the third set the
blue. The final two characters are unused. Each value can be between 0
to ff hex, which is 0 to 255 decimal.&nbsp;Note that custom tail
numbers burned
into textures will not be modified by this. </td>

      <td>Cessna Skyhawk 172SP( <b>atc_id_color=0xffffffff</b>
)<br>

Cessna Grand Caravan( <b>atc_id_color=0xff000000</b> )<br>

Extra 300S( <b>atc_id_color=0xffff0000</b> ) </td>
    </tr>

    <tr>

      <td>prop_anim_ratio</td>

      <td>The ratio of rotor revolutions rendered to the actual revolutions in the simulator. </td>

      <td>Bell 206B JetRanger( <b>prop_anim_ratio=-1.76</b>
) </td>
    </tr>

    <tr>

      <td>atc_model</td>

      <td>This is the specific aircraft model that the ATC system
recognizes for this type of aircraft. </td>

      <td>Bell 206B JetRanger( <b>atc_model=</b> ) </td>
    </tr>
  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId678569"></a>[general]</h4>

<p>In addition to the&nbsp;fltsim sections, the general
section
contains information related to all variations of the aircraft. For
example, the Cessna 182RG, 182S, and 182S IFR are all the same type of
aircraft, and contain the same flight model. As such,
there are some things that are not&nbsp;variable
across variations:</p>

<p></p>

<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>atc_type</td>

      <td>This is the specific aircraft type that the ATC system
recognizes for this type of aircraft. </td>

      <td>Aircreation582SL( <b>atc_type=Ultralight</b>
)<br>

Boeing 737-800( <b>atc_type=BOEING</b> )<br>

Beech Baron 58( <b>atc_type=BARON</b> ) </td>

    </tr>

    <tr>

      <td>atc_model</td>

      <td>This is the specific aircraft model that the ATC system
recognizes for this type of aircraft. </td>

      <td>Aircreation582SL( <b>atc_model=Trike</b> )<br>

Boeing 737-800( <b>atc_model=B738</b> )<br>

Boeing 747-400( <b>atc_model=B744</b> ) </td>

    </tr>

    <tr>

      <td>editable</td>

      <td>Unused.</td>

      <td>&nbsp;</td>

    </tr>

    <tr>

      <td>performance</td>

      <td>The performance description for the aircraft
can&nbsp;be
edited. The \t is a tab character, and the \n is a new-line character.
As the flight model for all variations is the same, the performance of
each variation should also be identical. </td>

      <td>Aircreation582SL( <b>performance="Wing span:
10.6 m\nLength:
2.57 m\nWeight: 1.96 m\nHeight: 2.57 m\nEngine: 582 Rotax 1 x CDI 53
hp\nPropeller: 2 wood blades\nFuel tank composite 52 liters ( 8 US
Gal)\nDesigner: MJPP Design\nDate: 15\/11\/02\n\n"</b> )<br>

      <br>

Boeing 737-800( <b>performance="Cruise Speed \n477 kts 550 mph
885 km\/h\n\nEngines \nCFM56-3C1\n\nMaximum Range \n2,059 nm 2,370 mi
3,810 km\n\nService Ceiling \n36, 089 ft 11,000 m\n\nFuel Capacity
\n5,311 U.S. gal 20,104 L\n\nEmpty Weight-Standard \n76,180 lb 34,550
kg\n\nMaximum Gross Weight\n150,000 lb 68,039 kg\n\nLength \n120 ft
36.45 m\n\nWingspan \n94 ft, 9 in 25.9 m\n\nHeight \n36.5 ft 11.13
m\n\nSeating \nSeats 147 to 168\n\nCargo Capacity \n1,373 ft3 38.93
m3\n\n"</b> )<br>

      <br>

Boeing 747-400( <b>performance="Cruise Speed\n0.85 Mach 565 mph
910 km\/h\n\nEngine options\nPratt &amp; Whitney
PW4062\nRolls-Royce RB211-524H\nGeneral Electric CF6-80C2B5F\n\nMaximum
Range\n7,325 nm 13,570 km\n\nMaximum Certified Operating Altitude
45,100 ft 13,747 m\n\nFuel Capacity\n57,285 gal 216,840 L\n\nBasic
Empty Weight\n394,088 lb 178,755 kg\n\nMax Gross Weight 875,000 lb
396,893 kg\n\nLength\n231 ft, 10 in 70.6 m\n\nWingspan\n211 ft, 5 in
64.4 m\n\nHeight\n63 ft, 8 in 19.4 m\n\nSeating Typical 3-class
configuration - 416\nTypical 2-class configuration - 524"</b> ) </td>

    </tr>

    <tr>

      <td>category</td>

      <td>For aircraft, one of airplane or helicopter. </td>

      <td>Airbus A321( <b>Category = airplane</b> )<br>

Maule M7 260C( <b>category = Airplane</b> )<br>

Bell 206B JetRanger( <b>Category = Helicopter</b> ) </td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId311850"></a>[pitot_static]</h4>

<p>The vertical_speed_time_constant parameter can be used to tune
the lag of the Vertical Speed Indicator for the aircraft:</p>

<ul>

  <li>Increasing the time constant decreases the lag, making the
gauge react more quickly.</li>

  <li>Decreasing the time constant increases the lag, making the
gauge react more slowly. </li>

  <li>A value of 0 effectively causes the indication to freeze.
If an instantaneous indication is desired, use an excessively large
value, such as 99. </li>

  <li>If the line is omitted, the default value is 2.0.</li>

</ul>

<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>vertical_speed_time_constant</td>

      <td>Increases or decreases the lag of the vertical speed
indicator. Increasing will cause a more instantaneous reaction in the
VSI. </td>

      <td>Airbus A321( <b>vertical_speed_time_constant = 1</b>
)<br>

Beech Baron 58( <b>vertical_speed_time_constant = 1.0</b> )<br>

DG808S( <b>vertical_speed_time_constant = 4</b> ) </td>

    </tr>

    <tr>

      <td>pitot_heat</td>

      <td>Scale of heat effectiveness, or 0 if not available. </td>

      <td>Airbus A321( <b>pitot_heat = 1.0</b> )<br>

Aircreation582SL( <b>pitot_heat=0.000000</b> )<br>

DG808S( <b>pitot_heat = 0.0</b> ) </td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId243173"></a>[weight_and_balance]</h4>

<p>The weight and center of gravity of the aircraft can be
affected through the
following parameters. The sign convention for positions is positive
equals
longitudinally forward, laterally to the right, and vertically upward. <o:p></o:p></p>

<h5><b>Note</b></h5>

<dl>

  <dd><span style=""></span>In the stock
aircraft,
the station_load.0, 1, etc. parameters are enclosed in quotation marks.<span style="">&nbsp; </span>These are used by internal
language
translation tools, and are not&nbsp;for in-game use.<o:p></o:p></dd>

</dl>

<h5>Moments of Inertia</h5>

<p>A moment of inertia (MOI) defines the mass distribution about
an axis of an aircraft. A moment of inertia for a particular axis is
increased as mass is increased and/or as the given mass is distributed
farther from the axis. This is largely what determines the inertial
characteristics of the aircraft. </p>

The following weight and balance parameters define the MOIs of the
empty aircraft, meaning that the value should not reflect fuel,
passengers or baggage.<span style="font-style: italic;">
Flight Simulator</span> determines the total MOIs with these
influences within the simulation. The units are slugs per foot squared.
Omission
of a parameter will result in <span style="font-style: italic;">Flight
Simulator </span>defaulting to the value
set in the .air file, if one exists.<br>

These values can be estimated with the following formula:<br>

<ul>

  <li>MOI = EmptyWeight * (D^2 / K)</li>

</ul>

Where:<br>

<table style="text-align: left; width: 640px;" border="1" cellpadding="2" cellspacing="2">

  <tbody>

    <tr>

      <td align="undefined" valign="undefined"></td>

      <td style="font-weight: bold;" align="undefined" valign="undefined">Pitch</td>

      <td style="font-weight: bold;" align="undefined" valign="undefined">Roll</td>

      <td style="font-weight: bold;" align="undefined" valign="undefined">Yaw</td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">D
=&nbsp;</td>

      <td align="undefined" valign="undefined">Length
(feet)</td>

      <td align="undefined" valign="undefined">Wingspan
(feet)&nbsp;&nbsp;</td>

      <td align="undefined" valign="undefined">0.5*
(Length+Wingspan) </td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">K =</td>

      <td align="undefined" valign="undefined">810</td>

      <td align="undefined" valign="undefined">1870</td>

      <td align="undefined" valign="undefined">770</td>

    </tr>

  </tbody>
</table>

<br>

This formula yields only rough estimates. Actual values vary based on
aircraft material, installed equipment, and number of engines and their
positions.<br>

<br>

<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>      </td>

      <td>
      <h5>Description </h5>      </td>

      <td>
      <h5>Examples</h5>      </td>
    </tr>

    <tr>

      <td>max_gross_weight</td>

      <td>Maximum design gross weight of the aircraft. </td>

      <td>Airbus A321( <b>max_gross_weight = 150000</b>
)<br>

Aircreation582SL( <b>max_gross_weight= 600.000</b> )<br>

Boeing 747-400( <b>max_gross_weight = 875000</b> )<br>

Beech Baron 58( <b>max_gross_weight = 5524</b> ) </td>
    </tr>

    <tr>

      <td>empty_weight</td>

      <td>Total weight (in pounds) of the aircraft minus usable
fuel, passengers, and cargo. If not specified, the value previously set
in the
.air file will be used. </td>

      <td>Airbus A321( <b>empty_weight = 74170</b> )<br>

Aircreation582SL( <b>empty_weight= 310.000</b> )<br>

Boeing 747-400( <b>empty_weight = 394088</b> )<br>

Beech Baron 58( <b>empty_weight = 3911</b> ) </td>
    </tr>

    <tr>

      <td>reference_datum_position</td>

      <td>Offset (in feet) of the aircraft's reference datum from
the standard <span style="font-style: italic;">Flight
Simulator</span> center point, which is on the centerline
chord aft of the leading edge. By setting the Reference Datum Position,
actual aircraft loading data can be used directly according to the
aircraft's manufacturer. If not specified, the default is 0,0,0<span style="font-style: italic;"></span>. </td>

      <td>Aircreation582SL( <b>reference_datum_position=
0.000, 0.000,
0.000</b> )<br>

Boeing 747-400( <b>reference_datum_position = 83.5, 0, 0</b>
)<br>

Beech Baron 58( <b>reference_datum_position = 6.96, 0, 0</b>
) </td>
    </tr>

    <tr>

      <td>empty_weight_cg_position</td>

      <td>Offset (in feet) of the center of gravity of the basic
empty aircraft (no fuel, passengers, or baggage) from the Reference
Datum Position. </td>

      <td>Aircreation582SL( <b>empty_weight_CG_position=
0.000, 0.000,
0.000</b> )<br>

Boeing 747-400( <b>empty_weight_CG_position = -90.5, 0, 0</b>
)<br>

Beech Baron 58( <b>empty_weight_CG_position = -6.06, 0, 0</b>
) </td>
    </tr>

    <tr>

      <td>max_number_of_stations</td>

      <td>Specifies the maximum number of
stations <span style="font-style: italic;">Flight
Simulator </span>will calculate when the aircraft is loaded.
This allows an unlimited number of stations to be specified. Note that
an excessively large number here results in a longer load time for the
aircraft when selected, although there is no effect on real-time
performance. </td>

      <td>Airbus A321( <b>max_number_of_stations = 50</b>
)<br>

Aircreation582SL( <b>max_number_of_stations=50</b> )<br>

Douglas DC-3( <b>max_number_of_stations =50</b> ) </td>
    </tr>

    <tr>

      <td>station_load.0<br>

to<br>

station_load.n</td>

      <td>Specifies the weight and position of passengers or
payload at a station specified with a unique number, station_load.N.
The first parameter number on each line specifies the weight (in
pounds), followed by the offset (in feet) of the station (longitudinal,
lateral, and vertical) from the Reference Datum Position. The addition
of stations results in a corresponding change in aircraft flight
dynamics due to the change of the total weight and moments of inertia. </td>

      <td>Airbus A321( <b>station_load.0 = 170.0, 41.0,
-1.5, 0.0</b> )<br>

Aircreation582SL( <b>station_load.0=0.000000,0.000000,0.000000,0.000000</b>
)<br>

Boeing 747-400( <b>station_load.0 = 170.0, -19.0, -2.0, 8.0</b>
)<br>

Beech Baron 58( <b>station_load.0 = 170, -6.54, -1.20, 0.0</b>
)<br>

      <br>

Airbus A321( <b>station_load.8 = 4000.0, -27.5,
0.0, 0.0</b> )<br>

Boeing 747-400( <b>station_load.8 = 23800.0, -160.0, 0.0, 0.0</b>
)<br>

Cessna Grand Caravan( <b>station_load.8 = 0, -23.2, -1.5, 0.0</b>
)<br>

Douglas DC-3( <b>station_load.8 = 340.0, -33.7, 0.0, 0.0</b>
)<br>      </td>
    </tr>

    <tr>

      <td>station_name.0<br>

to<br>

station_name.n</td>

      <td>This field is the string name that is used in the
Payload dialog (15 character limit). Omission of this will result in a
generic station name being used. </td>

      <td>McDonnell-Douglas/Boeing MD-83( <b>station_name.0
= "Payload"</b>
)<br>

Cessna Skyhawk 172SP( <b>station_name.1 = "Front Passenger"</b>
)<br>

      <br>

Airbus A321( <b>station_name.0 = "Pilot"</b>
)<br>

Airbus A321( <b>station_name.1 = "Co-Pilot"</b>
)<br>

Airbus A321( <b>station_name.2 = "Crew"</b>
)<br>

Airbus A321( <b>station_name.3 = "First Class"</b>
)<br>

Airbus A321( <b>station_name.4 = "Coach 3-10"</b>
)<br>

Airbus A321( <b>station_name.5 = "Coach 11-18"</b>
)<br>

Airbus A321( <b>station_name.6 = "Coach 19-25"</b>
)<br>

Airbus A321( <b>station_name.7 = "Forward
Baggage"</b> )<br>

Airbus A321( <b>station_name.8 = "Aft Baggage"</b>
) </td>
    </tr>

    <tr>

      <td>empty_weight_pitch_moi</td>

      <td>The moment of inertia (MOI) about the lateral axis. </td>

      <td>Airbus A321( <b>empty_weight_pitch_MOI = 3172439</b>
)<br>

Aircreation582SL( <b>empty_weight_pitch_MOI= 230.000</b> )<br>

Boeing 747-400( <b>empty_weight_pitch_MOI = 24223159</b> )<br>

Beech Baron 58( <b>empty_weight_pitch_MOI = 3905.65</b> ) </td>
    </tr>

    <tr>

      <td>empty_weight_roll_moi</td>

      <td>The moment of inertia (MOI) about the longitudinal
axis. </td>

      <td>Airbus A321( <b>empty_weight_roll_MOI = 2262183</b>
)<br>

Aircreation582SL( <b>empty_weight_roll_MOI= 205.000</b> )<br>

Boeing 747-400( <b>empty_weight_roll_MOI = 13352310</b> )<br>

Beech Baron 58( <b>empty_weight_roll_MOI = 2718.64</b> ) </td>
    </tr>

    <tr>

      <td>empty_weight_yaw_moi</td>

      <td>The moment of inertia (MOI) about the vertical axis. </td>

      <td>Airbus A321( <b>empty_weight_yaw_MOI = 3337024</b>
)<br>

Aircreation582SL( <b>empty_weight_yaw_MOI= 290.000</b> )<br>

Boeing 747-400( <b>empty_weight_yaw_MOI = 39531785</b> )<br>

Beech Baron 58( <b>empty_weight_yaw_MOI = 5291.04</b> ) </td>
    </tr>

    <tr>

      <td>empty_weight_coupled_moi</td>

      <td>The moment of inertia (MOI) about the roll and yaw axis
(usually zero). </td>

      <td>Airbus A321( <b>empty_weight_coupled_MOI = 0</b>
)<br>

Aircreation582SL( <b>empty_weight_coupled_MOI= 0.000</b> )<br>

Beech Baron 58( <b>empty_weight_coupled_MOI= 0.0</b> )<br>

Bombardier CRJ 700( <b>empty_weight_coupled_MOI = 0.0</b>
) </td>
    </tr>
  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId717787"></a>[flight_tuning]</h4>

<h5>Flight control effectiveness parameters</h5>

<p>The elevator, aileron and elevator effectiveness parameters
are
multipliers on the default&nbsp;power of the control surfaces. For
example, a value of 1.1 increases
the effectiveness by 10 percent. Likewise, a value of 0.9 decreases the
effectiveness by 10 percent. A negative number reverses the normal
effect of the control. Omission of a parameter results in the default
value of 1.0.</p>

<h5>Stability parameters</h5>

<p>The pitch, roll and yaw parameters are multipliers on the
default
stability (damping effect) about the corresponding axis of the
airplane. For example, a value of 1.1 increases the damping by 10%.
Likewise, a value of 0.9 decreases the damping by 10%. A negative
number results in an unstable characteristic about the axis. A positive
damping effect is simply a moment in the direction opposite of the
rotational velocity. Omission of a parameter will result in the default
value of 1.0.</p>

<h5>Lift parameter</h5>

<p>The cruise_lift_scalar parameter is a multiplier on the
coefficient of
lift at zero angle of attack Cruise lift in this context refers to
the lift at relatively small angles of attack, which is typical for an
airplane in a cruise condition. This scaling is decreased linearly as
angle of attack moves toward the critical (stall) angle of attack,
which prevents destabilizing low speed and stall characteristics at
high angles of attack. Modify this value to set the angle of attack
(and thus pitch) for a cruise condition. A negative value is not
advised, as this will result in extremely unnatural flight
characteristics.&nbsp;Omission of this parameter results in the
default value of 1.0.</p>

<h5>High Angle of Attack parameters</h5>

<p>The hi_alpha_on_roll and hi_alpha_on_yaw&nbsp; parameters
are multipliers on the effects on
roll and yaw at high angles of attack.&nbsp; The default values are
1.0. </p>

<h5>Propeller-induced turning effect parameters</h5>

<p>The p_factor_on_yaw, torque_on_roll, gyro_precession_on_roll
and
gyro_precession_on_yaw parameters are multipliers on the effects
induced by rotating propellers These are often called &ldquo;left
turning tendencies&rdquo; for clockwise rotating propellers,
although&nbsp;<i>Flight Simulator</i> automatically
handles counter-clockwise rotating
propellers.&nbsp; The default values are 1.0.</p>

<h5>Drag parameters</h5>

<p>Drag is the aerodynamic force that determines the aircraft
speed and acceleration. There are two basic types of drag that the user
can adjust here. Parasitic drag is composed of two basic elements: form
drag, which results from the interference of streamlined airflow, and
skin friction. Parasite drag increases as airspeed increases. Induced
drag results from the production of lift. Induced drag increases as
angle of attack increases.</p>

<p>The parasite_drag_scalar and induced_drag_scalar parameters
are multipliers on the two respective
drag coefficients. For example, a value of 1.1 increases the respective
drag component by 10 percent. A value of 0.9 decreases the drag by 10
Percent. Negative values are not advised, as extremely unnatural flight
characteristics will result.&nbsp; The default values are 1.0.</p>

<p></p>

<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>cruise_lift_scalar</td>

      <td>CL0. </td>

      <td>Airbus A321( <b>cruise_lift_scalar = 1.0</b>
)<br>

Aircreation582SL( <b>cruise_lift_scalar=1.000</b> ) </td>

    </tr>

    <tr>

      <td>parasite_drag_scalar</td>

      <td>Cd0.</td>

      <td>Airbus A321( <b>parasite_drag_scalar = 1.0</b>
)<br>

Aircreation582SL( <b>parasite_drag_scalar=1.000</b> ) </td>

    </tr>

    <tr>

      <td>induced_drag_scalar</td>

      <td>Cdi.</td>

      <td>Airbus A321( <b>induced_drag_scalar = 1.0</b>
)<br>

Aircreation582SL( <b>induced_drag_scalar=1.000</b> ) </td>

    </tr>

    <tr>

      <td>elevator_effectiveness</td>

      <td>Cmde. </td>

      <td>Airbus A321( <b>elevator_effectiveness = 1.0</b>
)<br>

Aircreation582SL( <b>elevator_effectiveness=1.000</b> ) </td>

    </tr>

    <tr>

      <td>aileron_effectiveness</td>

      <td>Clda. </td>

      <td>Airbus A321( <b>aileron_effectiveness = 1.0</b>
)<br>

Aircreation582SL( <b>aileron_effectiveness=1.000</b> ) </td>

    </tr>

    <tr>

      <td>rudder_effectiveness</td>

      <td>Cndr. </td>

      <td>Airbus A321( <b>rudder_effectiveness = 1.0</b>
)<br>

Aircreation582SL( <b>rudder_effectiveness=0.501</b> ) </td>

    </tr>

    <tr>

      <td>pitch_stability</td>

      <td>Cmq. </td>

      <td>Airbus A321( <b>pitch_stability = 1.0</b> )<br>

Aircreation582SL( <b>pitch_stability=1.000</b> ) </td>

    </tr>

    <tr>

      <td>roll_stability</td>

      <td>Clp. </td>

      <td>Airbus A321( <b>roll_stability = 1.0</b> )<br>

Aircreation582SL( <b>roll_stability=1.000</b> ) </td>

    </tr>

    <tr>

      <td>yaw_stability</td>

      <td>Cnr. </td>

      <td>Airbus A321( <b>yaw_stability = 1.0</b> )<br>

Aircreation582SL( <b>yaw_stability=1.000</b> ) </td>

    </tr>

    <tr>

      <td>elevator_trim_effectiveness</td>

      <td>Cmdetr. </td>

      <td>Airbus A321( <b>elevator_trim_effectiveness = 1.0</b>
)<br>

Aircreation582SL( <b>elevator_trim_effectiveness=1.000</b>
) </td>

    </tr>

    <tr>

      <td>aileron_trim_effectiveness</td>

      <td>Cldatr. </td>

      <td>Airbus A321( <b>aileron_trim_effectiveness = 1.0</b>
)<br>

Aircreation582SL( <b>aileron_trim_effectiveness=1.000</b>
) </td>

    </tr>

    <tr>

      <td>rudder_trim_effectiveness</td>

      <td>Cndrtr. </td>

      <td>Airbus A321( <b>rudder_trim_effectiveness = 1.0</b>
)<br>

Aircreation582SL( <b>rudder_trim_effectiveness=1.000</b> )
      </td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">hi_alpha_on_roll</td>

      <td align="undefined" valign="undefined">See notes above. </td>

      <td align="undefined" valign="undefined"></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">hi_alpha_on_yaw</td>

      <td align="undefined" valign="undefined"></td>

      <td align="undefined" valign="undefined"></td>

    </tr>

    <tr>

      <td>p_factor_on_yaw</td>

      <td>See notes above. </td>

      <td>Douglas DC-3( <b>p_factor_on_yaw = 0.5</b>
)<br>

Piper Cub( <b>p_factor_on_yaw = 0.3</b> ) </td>

    </tr>

    <tr>

      <td>torque_on_roll</td>

      <td></td>

      <td>Douglas DC-3( <b>torque_on_roll = 1.0</b> )<br>

Extra 300S( <b>torque_on_roll = 0.5</b> )<br>

Piper Cub( <b>torque_on_roll = 0.3</b> ) </td>

    </tr>

    <tr>

      <td>gyro_precession_on_yaw</td>

      <td>See notes above. </td>

      <td>Douglas DC-3( <b>gyro_precession_on_yaw = 1.0</b>
)<br>

Piper Cub( <b>gyro_precession_on_yaw = 0.3</b> ) </td>

    </tr>

    <tr>

      <td>gyro_precession_on_pitch</td>

      <td></td>

      <td>Douglas DC-3( <b>gyro_precession_on_pitch = 1.0</b>
)<br>

Piper Cub( <b>gyro_precession_on_pitch = 0.3</b> ) </td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId136011"></a>[generalenginedata]</h4>

<p>Every type of aircraft, even a glider, should have this
section in the aircraft.cfg file.&nbsp; Basically, this section
describes the type of engine, the number of engines, where the engines
are located, and a fuel flow scalar to modify how much fuel the engine
requires to produce the calculated power.</p>

<p></p>

<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>      </td>

      <td>
      <h5>Description </h5>      </td>

      <td>
      <h5>Examples</h5>      </td>
    </tr>

    <tr>

      <td>engine_type</td>

      <td>Integer that identifies what type of engine is on the
aircraft. 0 = piston, 1 = Jet, 2 = None, 3 = Helo-turbine, 4 = Rocket
(not supported) 5 = Turboprop. </td>

      <td>Airbus A321( <b>engine_type = 1</b> )<br>

Aircreation582SL( <b>engine_type= 0</b> )<br>

Beech Baron 58( <b>engine_type = 0</b> )<br>

Beech King Air 350( <b>engine_type = 5</b> ) </td>
    </tr>

    <tr>

      <td>engine.0<br>

to<br>

engine.n</td>

      <td>Offset (in feet) of the engine from the Reference Datum
Position (longitudinal, lateral and vertical). Each engine location
specified increases the engine count (maximum of four engines allowed).      </td>

      <td>Airbus A321( <b>Engine.0 = 4.75, -16.1, -4.5</b>
)<br>

Aircreation582SL( <b>Engine.0= -3.000, 0.000, 2.000</b> )<br>

Beech Baron 58( <b>Engine.0 = -1.4, -5.3, 0.0</b> )<br>

      <br>

Boeing 747-400( <b>Engine.0 = -107.5, -69.5, -6.9</b> )<br>

Boeing 747-400( <b>Engine.1 = -76.0, -38.9, -10.4</b> )<br>

Boeing 747-400( <b>Engine.2 = -76.0, 38.9, -10.4</b>
)<br>

Boeing 747-400( <b>Engine.3 = -107.5, 69.5, -6.9</b>
)<br>      </td>
    </tr>

    <tr>

      <td>fuel_flow_scalar</td>

      <td>Scalar for modifying the fuel flow required by the
engine(s). A value of less than 1.0 causes a slower fuel consumption
for a given power setting, a value greater than 1.0 causes the aircraft
to burn more fuel for a given power setting. </td>

      <td>Airbus A321( <b>fuel_flow_scalar = 1</b> )<br>

Aircreation582SL( <b>fuel_flow_scalar= 1.000</b> )<br>

Boeing 747-400( <b>fuel_flow_scalar = 1.0</b> )<br>

Beech Baron 58( <b>fuel_flow_scalar= 0.9</b> ) </td>
    </tr>

    <tr>

      <td>min_throttle_limit</td>

      <td>Defines the minimum throttle position (percent of max).
Normally 0 for piston aircraft and -0.25 for turbine airplane engines
with reverse thrust. </td>

      <td>Airbus A321( <b>min_throttle_limit = -0.25</b>
)<br>

Aircreation582SL( <b>min_throttle_limit=0.000000</b> )<br>

Boeing 747-400( <b>min_throttle_limit = -0.25;</b> )<br>

Beech Baron 58( <b>min_throttle_limit = 0.0;</b> ) </td>
    </tr>

    <tr>

      <td>max_contrail_temperature</td>

      <td>Ambient temperature, in celsius, in which engine vapor
contrails will turn on. The default value is about -39 degrees celsius
for turbine engines. For piston engines, the contrail effect is turned
off unless a temperature value is set here. </td>

      <td>Airbus A321( <b>max_contrail_temperature = -30</b>
) </td>
    </tr>

    <tr>

      <td>master_ignition_switch</td>

      <td>1=Available, 0=Not Available (default). If available,
this switch must be on for the ignition circuit, and thus the engines,
to be operable. Turning it off will stop all engines. </td>

      <td>Douglas DC-3( <b>master_ignition_switch = 1</b>
) </td>
    </tr>

    <tr>

      <td align="undefined" valign="undefined">starter_type</td>

      <td align="undefined" valign="undefined">Set
to 1 for a Manual Starter</td>

      <td align="undefined" valign="undefined">(From <i>Flight Simulator 2004</i>)<br>

Curtiss Jenny( <b>starter_type = 1</b> ) </td>
    </tr>
    <tr>
      <td align="undefined" valign="undefined">thrustanglepitchheading.0</td>
      <td align="undefined" valign="undefined">Thrust pitch and heading angles in degrees ( positive pitch down, postive heading right). </td>
      <td align="undefined" valign="undefined">Cessna Skyhawk 172SP Paint1 ( <b>ThrustAnglePitchHeading.0 = 0,0</b> ) </td>
    </tr>
  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId50743"></a><a name="turbineenginedata"></a>[turbineenginedata]</h4>

<p>A turbine engine ignites fuel and compressed air to create
thrust.&nbsp; These parameters define the power (thrust) output of
a given jet turbine engine.</p>

<p></p>

<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>      </td>

      <td>
      <h5>Description </h5>      </td>

      <td>
      <h5>Examples</h5>      </td>
    </tr>

    <tr>

      <td>fuel_flow_gain</td>

      <td>Fuel flow gain constant. </td>

      <td>Airbus A321( <b>fuel_flow_gain = 0.002</b>
)<br>

Boeing 747-400( <b>fuel_flow_gain = 0.002</b> )<br>

Beech King Air 350( <b>fuel_flow_gain = 0.011</b> )<br>

Bombardier CRJ 700( <b>fuel_flow_gain = 0.0025</b> ) </td>
    </tr>

    <tr>

      <td>inlet_area</td>

      <td>Engine nacelle inlet area, (in square feet). </td>

      <td>Airbus A321( <b>inlet_area = 19.6</b> )<br>

Boeing 747-400( <b>inlet_area = 60.0</b> )<br>

Beech King Air 350( <b>inlet_area = 1.0</b> )<br>

Bombardier CRJ 700( <b>inlet_area = 9.4</b> ) </td>
    </tr>

    <tr>

      <td>rated_n2_rpm</td>

      <td>Second stage compressor rated rpm. </td>

      <td>Airbus A321( <b>rated_N2_rpm = 29920</b> )<br>

Boeing 747-400( <b>rated_N2_rpm = 29920</b> )<br>

Cessna Grand Caravan( <b>rated_N2_rpm = 33000</b> ) </td>
    </tr>

    <tr>

      <td>static_thrust</td>

      <td>Maximum rated static thrust at sea level (lbs). </td>

      <td>Airbus A321( <b>static_thrust = 23500</b> )<br>

Boeing 747-400( <b>static_thrust = 56750</b> )<br>

Beech King Air 350( <b>static_thrust = 158</b> )<br>

Bombardier CRJ 700( <b>static_thrust = 12670</b> ) </td>
    </tr>

    <tr>

      <td>afterburner_available</td>

      <td>Boolean value to indicate if an afterburner is
available; 0 = FALSE, 1 = TRUE. </td>

      <td>Airbus A321( <b>afterburner_available = 0</b>
)<br>

Boeing 747-400( <b>afterburner_available = 0</b> ) </td>
    </tr>

    <tr>

      <td>reverser_available</td>

      <td>Specifies the scalar on the calculated reverse thrust
effect. A value of 0 will cause no reverse thrust to be available. A
value of 1.0 will cause the theoretical normal reverse thrust to be
available. Other values will scale the normal calculated value
accordingly. </td>

      <td>Airbus A321( <b>reverser_available = 1</b>
)<br>

Boeing 747-400( <b>reverser_available = 1</b> ) </td>
    </tr>
    <TR>
      <TD>thrustspecificfuelconsumption</TD>
      <TD>Jet thrust specific fuel consumption.  The ratio of fuel used in pounds per hour, to thrust in pounds. Applies at all speeds. </TD>
      <TD>Boeing 737-800 Paint1( <B>ThrustSpecificFuelConsumption = 0.6</B> )<BR>
        Boeing 747-400 Paint1( <B>ThrustSpecificFuelConsumption = 0.4</B> ) </TD>
    </TR>
    <TR>
      <TD>afterburnthrustspecificfuelconsumption</TD>
      <TD>Jet thrust specific fuel consumption. The ratio of fuel used in pounds per hour, to thrust in pounds. Applies only when the afterburner is active. </TD>
      <TD>Boeing 737-800 Paint1( <B>AfterBurnThrustSpecificFuelConsumption = 0</B> ) </TD>
    </TR>
  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId467871"></a>[jet_engine]</h4>

The thrust_scalar parameter scales the calculated thrust for jet
engines (thrust taken from the<a href="#turbineenginedata">
[TurbineEngineData]</a> section).<br>

<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>thrust_scalar</td>

      <td>Parameter that scales the calculated thrust provided by
the propeller. </td>

      <td>Airbus A321( <b>thrust_scalar = 1.0</b> ) </td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId245287"></a>[electrical]</h4>

<p>These parameters configure the characteristics of the
aircraft's electrical system and its components. Each aircraft has a
battery as well as an alternator or generator for each engine.</p>

Below is a table of&nbsp;electrical section parameters shown
with&nbsp;default values for Bus Type, Max Amp Load and Min Voltage
(the values applied if the parameters are
omitted). The default Min Voltage equals 0.7*Max Battery Voltage. The
list of components also reflects all of the systems currently linked to
the electrical system. If a component is included in the list but the
aircraft does not actually have that system, the component is simply
ignored.<br>

<h5>
Bus Type </h5>

Specifies which bus in the electrical system the component is
connected to, according to the following bus type codes:<br>

<br>

<table style="text-align: left; width: 640px;" border="1" cellpadding="2" cellspacing="2">

  <tbody>

    <tr>

      <td align="undefined" valign="undefined"><span style="font-weight: bold;">Bus Type</span></td>

      <td align="undefined" valign="undefined"><span style="font-weight: bold;">Bus</span></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">0</td>

      <td align="undefined" valign="undefined">Main
Bus (most components connected here)</td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">1</td>

      <td align="undefined" valign="undefined">Avionics
Bus</td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">2</td>

      <td align="undefined" valign="undefined">Battery
Bus</td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">3</td>

      <td align="undefined" valign="undefined">Hot
Battery Bus (bypasses Master switch)</td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">4</td>

      <td align="undefined" valign="undefined">Generator/Alternator
Bus 1 (function of engine 1)</td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">5</td>

      <td align="undefined" valign="undefined">Generator/Alternator
Bus 2 (function of engine 2)</td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">6</td>

      <td align="undefined" valign="undefined">Generator/Alternator
Bus 3 (function of engine 3)</td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">7</td>

      <td align="undefined" valign="undefined">Generator/Alternator
Bus 4 (function of engine 4)</td>

    </tr>

  </tbody>
</table>

<br>

<h5>Max Amp Load</h5>

<p>Max Amp Load is the current required to power the
component, and of course becomes the additional load on the electrical
system.</p>

<h5>Min Voltage</h5>

<p> Min Voltage is the minimum voltage required from the
specified bus for the component to function.</p>
<p>&nbsp;</p>
<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>flap_motor</td>

      <td>Bus type, max amp, min voltage</td>

      <td>Airbus A321( <b>flap_motor = 0, 5 , 17.0</b>
) </td>

    </tr>

    <tr>

      <td>gear_motor</td>

      <td>Bus type, max amp, min voltage</td>

      <td>Airbus A321( <b>gear_motor = 0, 5 , 17.0</b>
) </td>

    </tr>

    <tr>

      <td>autopilot</td>

      <td>Bus type, max amp, min voltage</td>

      <td>Airbus A321( <b>autopilot = 0, 5 , 17.0</b>
) </td>

    </tr>

    <tr>

      <td>avionics_bus</td>

      <td>Bus type, max amp, min voltage</td>

      <td>Airbus A321( <b>avionics_bus = 0, 5, 17.0</b>
)<br>

Boeing 747-400( <b>avionics_bus = 0, 5 , 17.0</b> )<br>

Bombardier CRJ 700( <b>avionics_bus = 0, 5 , 9.5</b> ) </td>

    </tr>

    <tr>

      <td>avionics</td>

      <td>Bus type, max amp, min voltage</td>

      <td>Airbus A321( <b>avionics = 1, 5 , 17.0</b>
)<br>

Bombardier CRJ 700( <b>avionics = 1, 5 , 9.5</b> ) </td>

    </tr>

    <tr>

      <td>pitot_heat</td>

      <td> Bus type, max amp, min voltage</td>

      <td>Airbus A321( <b>pitot_heat = 0, 2 , 17.0</b>
) </td>

    </tr>

    <tr>

      <td>additional_system</td>

      <td>Bus type, max amp, min voltage</td>

      <td>Airbus A321( <b>additional_system = 0, 2, 17.0</b>
)<br>

Beech King Air 350( <b>additional_system = 0, 2 , 17.0</b>
)<br>

Bombardier CRJ 700( <b>additional_system = 0, 2 , 9.5</b>
) </td>

    </tr>

    <tr>

      <td>marker_beacon</td>

      <td>Bus type, max amp, min voltage</td>

      <td>Airbus A321( <b>marker_beacon = 1, 2 , 17.0</b>
)<br>

Bombardier CRJ 700( <b>marker_beacon = 1, 2 , 9.0</b> ) </td>

    </tr>

    <tr>

      <td>gear_warning</td>

      <td>Bus type, max amp, min voltage</td>

      <td>Airbus A321( <b>gear_warning = 0, 2 , 17.0</b>
) </td>

    </tr>

    <tr>

      <td>fuel_pump</td>

      <td>Bus type, max amp, min voltage</td>

      <td>Airbus A321( <b>fuel_pump = 0, 5 , 17.0</b>
)<br>

Bombardier CRJ 700( <b>fuel_pump = 0, 5 , 9.0</b> ) </td>

    </tr>

    <tr>

      <td>starter1</td>

      <td>Bus type, max amp, min voltage</td>

      <td>Airbus A321( <b>starter1 = 0, 20, 17.0</b>
) </td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">starter2</td>

      <td align="undefined" valign="undefined">Bus
type, max amp, min voltage</td>

      <td align="undefined" valign="undefined"></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">starter3</td>

      <td align="undefined" valign="undefined">Bus
type, max amp, min voltage</td>

      <td align="undefined" valign="undefined"></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">starter4</td>

      <td align="undefined" valign="undefined">Bus
type, max amp, min voltage</td>

      <td align="undefined" valign="undefined"></td>

    </tr>

    <tr>

      <td>light_nav</td>

      <td>Bus type, max amp, min voltage</td>

      <td>Airbus A321( <b>light_nav = 0, 5 , 17.0</b>
) </td>

    </tr>

    <tr>

      <td>light_beacon</td>

      <td>Bus type, max amp, min voltage</td>

      <td>Airbus A321( <b>light_beacon = 0, 5 , 17.0</b>
) </td>

    </tr>

    <tr>

      <td>light_landing</td>

      <td>Bus type, max amp, min voltage</td>

      <td>Airbus A321( <b>light_landing = 0, 5 , 17.0</b>
) </td>

    </tr>

    <tr>

      <td>light_taxi</td>

      <td>Bus type, max amp, min voltage</td>

      <td>Airbus A321( <b>light_taxi = 0, 5 , 17.0</b>
) </td>

    </tr>

    <tr>

      <td>light_strobe</td>

      <td>Bus type, max amp, min voltage</td>

      <td>Airbus A321( <b>light_strobe = 0, 5 , 17.0</b>
) </td>

    </tr>

    <tr>

      <td>light_panel</td>

      <td>Bus type, max amp, min voltage</td>

      <td>Airbus A321( <b>light_panel = 0, 5 , 17.0</b>
) </td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">light_cabin</td>

      <td align="undefined" valign="undefined">Bus
type, max amp, min voltage</td>

      <td align="undefined" valign="undefined"></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">prop_sync</td>

      <td align="undefined" valign="undefined">Bus
type, max amp, min voltage</td>

      <td align="undefined" valign="undefined"></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">auto_feather</td>

      <td align="undefined" valign="undefined">Bus
type, max amp, min voltage</td>

      <td align="undefined" valign="undefined"></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">auto_brakes</td>

      <td align="undefined" valign="undefined">Bus
type, max amp, min voltage</td>

      <td align="undefined" valign="undefined"></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">standby_vacuum</td>

      <td align="undefined" valign="undefined">Bus
type, max amp, min voltage</td>

      <td align="undefined" valign="undefined"></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">hydraulic_pump</td>

      <td align="undefined" valign="undefined">Bus
type, max amp, min voltage</td>

      <td align="undefined" valign="undefined"></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">fuel_transfer_pump</td>

      <td align="undefined" valign="undefined">Bus
type, max amp, min voltage</td>

      <td align="undefined" valign="undefined"></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">propeller_deice</td>

      <td align="undefined" valign="undefined">Bus
type, max amp, min voltage</td>

      <td align="undefined" valign="undefined"></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">light_recognition</td>

      <td align="undefined" valign="undefined">Bus
type, max amp, min voltage</td>

      <td align="undefined" valign="undefined"></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">light_wing</td>

      <td align="undefined" valign="undefined">Bus
type, max amp, min voltage</td>

      <td align="undefined" valign="undefined"></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">light_logo</td>

      <td align="undefined" valign="undefined">Bus
type, max amp, min voltage</td>

      <td align="undefined" valign="undefined"></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">directional_gyro</td>

      <td align="undefined" valign="undefined">Bus
type, max amp, min voltage</td>

      <td align="undefined" valign="undefined"></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">directional_gyro_slaving</td>

      <td align="undefined" valign="undefined">Bus
type, max amp, min voltage</td>

      <td align="undefined" valign="undefined"></td>

    </tr>

    <tr>

      <td>max_battery_voltage</td>

      <td>The maximum voltage to which the battery can be
charged.
It is also the voltage available from the battery when the aircraft is
initialized. The battery voltage will decrease from this if the
generators or alternators are not supplying enough current to meet the
demand of the active components.</td>

      <td>Beech Baron 58( <b>max_battery_voltage = 24.0</b>
)<br>

DeHavilland Beaver DHC2( <b>max_battery_voltage = 24</b> )<br>

Extra 300S( <b>max_battery_voltage = 12.0</b> )<br>

Maule M7 260C( <b>max_battery_voltage = 12.0</b> ) </td>

    </tr>

    <tr>

      <td>generator_alternator_voltage</td>

      <td>Voltage of the generators or alternators.</td>

      <td>Beech Baron 58( <b>generator_alternator_voltage
= 28.0</b> )<br>

Bombardier CRJ 700( <b>generator_alternator_voltage = 25.0</b>
)<br>

DeHavilland Beaver DHC2( <b>generator_alternator_voltage = 28</b>
)<br>

Douglas DC-3( <b>generator_alternator_voltage = 25</b> ) </td>

    </tr>

    <tr>

      <td>max_generator_alternator_amps</td>

      <td>Maximum generator/alternator amps.</td>

      <td>Beech Baron 58( <b>max_generator_alternator_amps
= 60.0</b> )<br>

Bombardier CRJ 700( <b>max_generator_alternator_amps = 40.0</b>
)<br>

DeHavilland Beaver DHC2( <b>max_generator_alternator_amps = 50</b>
)<br>

Douglas DC-3( <b>max_generator_alternator_amps = 100</b> )
      </td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">engine_generator_map</td>

      <td align="undefined" valign="undefined">List
of flags, corresponding to the number of engines, indicating whether
there is a generator configured with the engine.</td>

      <td align="undefined" valign="undefined">(From <i>Flight Simulator 2004</i>)<br>

Ford 4-AT-E Tri-Motor( <b>engine_generator_map= 0,1,0</b> )<br>

      </td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">electric_always_available</td>

      <td align="undefined" valign="undefined">Set
to 1 if electric power is available regardless of the state of the
battery or circuit.</td>

      <td align="undefined" valign="undefined"></td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId836373"></a>[contact_points]</h4>

<p>You can configure and adjust the way aircraft reacts to
different kinds of contact, including landing gear contact and
articulation, braking, steering, and damage accrued through excessive
speed.&nbsp;You can also configure each contact point independently
for
each aircraft, and there is no limit to the number of points you can
add.&nbsp;When importing an
aircraft that does not contain this set of data, the program will
generate the data from the .air file the first time the aircraft is
loaded, and then write it to the aircraft.cfg. </p>

<p>Each contact point contains a series of values that define the
characteristics of the point, separated by commas. A contact point has
16 parameters, described in the following table: </p>

<p>&nbsp;</p>

<table border="1" cellpadding="2" cellspacing="2">

  <tbody>

    <tr>

      <td align="undefined" valign="undefined"><span style="font-weight: bold;">Contact Point Parameter (and
example)</span></td>

      <td align="undefined" valign="undefined"><span style="font-weight: bold;">Element</span></td>

      <td align="undefined" valign="undefined"><span style="font-weight: bold;">Description</span></td>

    </tr>

    <tr>

      <td>1 &nbsp;(1)</td>

      <td>Class</td>

      <td>Integer defining the type of contact point: 0 = None, 1
= Wheel, 2 = Scrape, 3 = Skid, 4 = Float, 5 = Water Rudder</td>

    </tr>

    <tr>

      <td>2 (-18.0)</td>

      <td>Longitudinal Position</td>

      <td>The longitudinal distance of the point from the defined
reference datum (feet). Positive is forward (out the nose).</td>

    </tr>

    <tr>

      <td>3 (0)</td>

      <td>Lateral Position</td>

      <td>The lateral distance of the point from the defined
reference
datum (feet). Positive is starboard (right, as viewed from the top with
the airplane pointing &ldquo;up&rdquo;).</td>

    </tr>

    <tr>

      <td>4 (-3.35)</td>

      <td>Vertical Position</td>

      <td>The vertical distance of the point from the defined
reference datum (feet). Positive is up.</td>

    </tr>

    <tr>

      <td>5 (3200)</td>

      <td>Impact Damage Threshold</td>

      <td>The speed at which an impact with the ground can cause
damage (feet/min).</td>

    </tr>

    <tr>

      <td>6 (0)</td>

      <td>Brake Map</td>

      <td>Defines which brake input drives the brake (wheels
only).<br>

0 = None, 1 = Left Brake, 2 = Right Brake.</td>

    </tr>

    <tr>

      <td>7 (0.50)</td>

      <td>Wheel Radius</td>

      <td>Radius of the wheel (feet). </td>

    </tr>

    <tr>

      <td>8 (180)</td>

      <td>Steering Angle</td>

      <td>The maximum angle (positive and negative) that a wheel
can pivot (degrees).</td>

    </tr>

    <tr>

      <td>9 (0.25)</td>

      <td>Static Compression</td>

      <td>This is the distance a landing gear is compressed when
the
empty aircraft is at rest on the ground (feet). This term defines the
&ldquo;strength&rdquo; of the strut, where a smaller number
will
increase the &ldquo;stiffness&rdquo; of the strut.</td>

    </tr>

    <tr>

      <td>10 (2.5)</td>

      <td>Ratio of Maximum Compression to Static Compression</td>

      <td>Ratio of the max dynamic compression available in the
strut
to the static value. Can be useful in coordinating the
&ldquo;compression&rdquo; of the strut when landing.</td>

    </tr>

    <tr>

      <td>11 (0.90)</td>

      <td>Damping Ratio</td>

      <td>This ratio describes how well the ground reaction
oscillations are damped. A value of 1.0 is considered critically
damped, meaning there will be little or no osciallation. A damping
ratio of 0.0 is considered undamped, meaning that the oscillations will
continue with a constant magnitude. Negative values result in an
unstable ground handling situation, and values greater than 1.0 might
also cause instabilities by being &ldquo;over&rdquo; damped.
Typical
values range from 0.6 to 0.95.</td>

    </tr>

    <tr>

      <td>12 (1.0)</td>

      <td>Extension Time</td>

      <td>The amount of time it takes the landing gear to fully
extend
under normal conditions (seconds). A value of zero indicates a fixed
gear.</td>

    </tr>

    <tr>

      <td>13 (4.0)</td>

      <td>Retraction Time</td>

      <td>The amount of time it takes the landing gear to fully
retract
under normal conditions (seconds). A value of zero indicates a fixed
gear.</td>

    </tr>

    <tr>

      <td>14 (0)</td>

      <td>Sound Type</td>

      <td>This integer value will map a point to a type of sound:</td>

    </tr>

    <tr>

      <td>&nbsp;</td>

      <td>&nbsp;</td>

      <td>0 = Center Gear,</td>

    </tr>

    <tr>

      <td>&nbsp;</td>

      <td>&nbsp;</td>

      <td>1 = Auxiliary Gear,</td>

    </tr>

    <tr>

      <td>&nbsp;</td>

      <td>&nbsp;</td>

      <td>2 = Left Gear,</td>

    </tr>

    <tr>

      <td>&nbsp;</td>

      <td>&nbsp;</td>

      <td>3 = Right Gear,</td>

    </tr>

    <tr>

      <td>&nbsp;</td>

      <td>&nbsp;</td>

      <td>4 = Fuselage Scrape,</td>

    </tr>

    <tr>

      <td>&nbsp;</td>

      <td>&nbsp;</td>

      <td>5 = Left Wing Scrape,</td>

    </tr>

    <tr>

      <td>&nbsp;</td>

      <td>&nbsp;</td>

      <td>6 = Right Wing Scrape,</td>

    </tr>

    <tr>

      <td>&nbsp;</td>

      <td>&nbsp;</td>

      <td>7 = Aux1 Scrape,</td>

    </tr>

    <tr>

      <td>&nbsp;</td>

      <td>&nbsp;</td>

      <td>8 = Aux2 Scrape,</td>

    </tr>

    <tr>

      <td>&nbsp;</td>

      <td>&nbsp;</td>

      <td>9 = Tail Scrape.</td>

    </tr>

    <tr>

      <td>15 (0)</td>

      <td>Airspeed Limit</td>

      <td>This is the speed at which landing gear extension
becomes
inhibited (knots). Not used for scrape points or non-retractable gear.</td>

    </tr>

    <tr>

      <td>16 (200)</td>

      <td>Damage from Airspeed</td>

      <td>The speed above which the landing gear accrues damage
(knots). Not used for scrape points or non-retractable gear.</td>

    </tr>

  </tbody>
</table>

<p>&nbsp;</p>

Each contact point's data
set takes the form &ldquo;point.n=&rdquo;, where
&ldquo;n&rdquo; is the index to the particular point, followed
by the data.
<p>&nbsp;</p>

<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>      </td>

      <td>
      <h5>Description </h5>      </td>

      <td>
      <h5>Examples</h5>      </td>
    </tr>

    <tr>

      <td>point.0<br>

to<br>

point.n</td>

      <td>Contact points that match the format described above.</td>

      <td>Airbus A321( <b>point.0=1, 40.00, 0.00, -8.40,
1181.1, 0, 1.442, 55.92, 0.6, 2.5, 0.9, 4.0, 4.0, 0, 220.0, 250.0</b>
)<br>

Aircreation582SL( <b>point.0= 1.000, 2.583, 0.000, -1.000,
1574.803, 0.000, 0.504, 31.860, 0.235, 2.500, 0.731, 0.000, 0.000,
0.000, 0.000, 0.000</b> )
Beech Baron 58( <b>point.0 = 1, 0.82, 0.00, -3.77, 1600, 0,
0.633, 40, 0.42, 4.0, 0.90, 3.0, 3.0, 0, 152, 180</b> )<br>

      <br>

Boeing 747-400( <b>point.0 = 1, -25.0, 0.0, -17.5, 1000.0, 0,
2.0, 70.0, 0.5, 3.5, 0.900, 9.0, 8.0, 0, 220, 250</b> )<br>

Boeing 747-400( <b>point.1 = 1, -114.0, -18.0, -21.3, 2000.0, 1,
2.0, 13.0, 3.0, 2.5, 0.900, 11.0, 9.0, 2, 220, 250</b> )<br>

Boeing 747-400( <b>point.2 = 1, -114.0, 18.0, -21.3, 2000.0, 2,
2.0, 13.0, 3.0, 2.5, 0.900, 11.0, 9.0, 3, 220, 250</b> )<br>

Boeing 747-400( <b>point.3 = 2, -152.6, -103.5, 3.0, 700.0, 0,
0.0, 0.0, 0.0, 0.0, 0.000, 0.0, 0.0, 5, 0, 0</b> )<br>

Boeing 747-400( <b>point.4 = 2, -152.6, 103.5, 3.0, 700.0, 0,
0.0, 0.0, 0.0, 0.0, 0.000, 0.0, 0.0, 6, 0, 0</b> )<br>

Boeing 747-400( <b>point.5 = 2, 3.0, 0.0, 0.0, 700.0, 0, 0.0,
0.0, 0.0, 0.0, 0.000, 0.0, 0.0, 9, 0, 0</b> )<br>

Boeing 747-400( <b>point.6 = 2, -222.7, 0.0, 4.0, 700.0, 0, 0.0,
0.0, 0.0, 0.0, 0.000, 0.0, 0.0, 4, 0, 0</b> )<br>

      <br>      </td>
    </tr>

    <tr>

      <td>max_number_of_points</td>

      <td>Integer value indicating the maximum number of contact
points
the program will look for. </td>

      <td>Airbus A321( <b>max_number_of_points = 21</b>
) </td>
    </tr>

    <tr>

      <td>static_pitch</td>

      <td>The static pitch of the aircraft when at rest on the
ground (degrees). The program uses this value to position the aircraft
at startup, in slew, and at any other time when the simulation is not
actively running. </td>

      <td>Airbus A321( <b>static_pitch=0.04</b> )<br>

Aircreation582SL( <b>static_pitch= 0.000</b> )<br>

Boeing 747-400( <b>static_pitch = -1.5</b> )<br>

Beech Baron 58( <b>static_pitch = 1.56</b> ) </td>
    </tr>

    <tr>

      <td>static_cg_height</td>

      <td>The static height of the aircraft when at rest on the
ground (feet). The program uses this value to position the aircraft at
startup, in slew, and at any other time when the simulation is not
actively running. </td>

      <td>Airbus A321( <b>static_cg_height=7.67</b> )<br>

Aircreation582SL( <b>static_cg_height= 1.000</b> )<br>

Boeing 747-400( <b>static_cg_height = 18.6</b> )<br>

Beech Baron 58( <b>static_cg_height = 3.43</b> ) </td>
    </tr>

    <tr>

      <td>gear_system_type</td>

      <td>This parameter defines the system type which drives the
gear extension and retraction.<br>

0 = electrical<br>

1 = hydraulic<br>

2 = pneumatic<br>

3 = manual<br>

4 = none </td>

      <td>Airbus A321( <b>gear_system_type=1</b> )<br>

Beech Baron 58( <b>gear_system_type=0</b> )<br>

DeHavilland Beaver DHC2( <b>gear_system_type=3</b> ) </td>
    </tr>

    <tr>

      <td>emergency_extension_type</td>

      <td>One of:<br>

None=0,Pump=1,Gravity=2. </td>

      <td>Bombardier CRJ 700( <b>emergency_extension_type=2</b>
) </td>
    </tr>

    <tr>

      <td>tailwheel_lock</td>

      <td>Boolean defining if a tailwheel lock is available
(applicable only on tailwheel airplanes). </td>

      <td>Douglas DC-3( <b>tailwheel_lock = 1</b> ) </td>
    </tr>
  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId54524"></a>[gear_warning_system]</h4>

<p>The following parameters define the functionality of the
aircraft&rsquo;s gear
warning system.<span style="">&nbsp; </span>This
is generally a
function of the throttle lever position and the flap deflection.<span style="">&nbsp;</span></p>

<p><span style=""> </span><o:p></o:p></p>

<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>gear_warning_available</td>

      <td>Sets the type of gear warning system available on the
aircraft, one of:<br>

0 = None, 1 = Normal, 2 = Amphibian (audible alert for water
vs. land setting). </td>

      <td>Airbus A321( <b>gear_warning_available = 1</b>
) </td>

    </tr>

    <tr>

      <td>pct_throttle_limit</td>

      <td>The throttle limit, below which the gear warning will
activate if the gear is not down and locked while the flaps are
deflected to at least the setting for flap_limit_idle below. This flap
limit can be 0 so that the warning effectively is a function of the
throttle. A value between: 0 (idle) and 1.0 (Max throttle). </td>

      <td>Airbus A321( <b>pct_throttle_limit = 0.1</b>
) </td>

    </tr>

    <tr>

      <td>flap_limit_idle</td>

      <td>In conjunction with the throttle limit specified above,
this limit is the flap deflection, above which the warning will
activate if the gear is not down and locked while the throttle is below
the limit specified above. By setting this limit to a value greater
than zero, the pilot can reduce the throttle to idle without activating
the warning. This is often utilized in jets to decelerate/descend the
aircraft. </td>

      <td>Airbus A321( <b>flap_limit_idle = 5.0</b> )<br>

Beech Baron 58( <b>flap_limit_idle = 0.0</b> )<br>

Beech King Air 350( <b>flap_limit_idle = 15.0</b> ) </td>

    </tr>

    <tr>

      <td>flap_limit_power</td>

      <td>The flap limit, above which the warning will activate
(regardless of throttle position). </td>

      <td>Airbus A321( <b>flap_limit_power = 25.5</b>
)<br>

Beech Baron 58( <b>flap_limit_power = 31.5</b> )<br>

Beech King Air 350( <b>flap_limit_power = 30.0</b> )<br>

Douglas DC-3( <b>flap_limit_power = 16.0</b> ) </td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId774770"></a>[brakes]</h4>

<p>The following parameters define the aircraft's braking system:</p>
<p>&nbsp;</p>
<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>parking_brake</td>

      <td>Boolean setting if a parking brake is available on the
aircraft. </td>

      <td>Airbus A321( <b>parking_brake = 1</b> )<br>

Aircreation582SL( <b>parking_brake=1</b> )<br>

DeHavilland Beaver DHC2( <b>parking_brake = 0</b> ) </td>

    </tr>

    <tr>

      <td>toe_brakes_scale</td>

      <td>Sets the scaling of the braking effectiveness. 1.0 is
the default. 0.0 scales the brakes to no effectiveness. </td>

      <td>Airbus A321( <b>toe_brakes_scale = 0.885</b>
)<br>

Aircreation582SL( <b>toe_brakes_scale=1.000031</b> )<br>

Boeing 747-400( <b>toe_brakes_scale = 1.24</b> )<br>

Beech Baron 58( <b>toe_brakes_scale = 1.0</b> ) </td>

    </tr>

    <tr>

      <td>auto_brakes</td>

      <td>The number of increments that the auto-braking switch can be turned to. </td>

      <td>Airbus A321( <b>auto_brakes = 3</b> )<br>

Boeing 737-800( <b>auto_brakes = 4</b> )<br>

Beech Baron 58( <b>auto_brakes = 0</b> ) </td>

    </tr>

    <tr>

      <td>hydraulic_system_scalar</td>

      <td>The ratio of hydraulic system pressure to maximum brake
hydraulic pressure. </td>

      <td>Airbus A321( <b>hydraulic_system_scalar = 1</b>
) </td>

    </tr>

    <tr>

      <td>differential_braking_scale</td>

      <td>Differential braking is a function of the normal both
brakes on and the rudder pedal input. The amount of difference between
the left and right brake is scaled by this value. 1.0 is the normal
setting if differential braking is desired (particularly on tailwheel
airplanes). 0.0 is the setting if no differential braking is desired. </td>

      <td>Douglas DC-3( <b>differential_braking_scale = 1.0</b>
) </td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId990703"></a>[hydraulic_system]</h4>

<p>The following parameters define the aircraft's hydraulic system:</p>
<p>&nbsp;</p>
<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>normal_pressure</td>

      <td>The normal operating pressure of the hydraulic system,
in pounds per square inch. </td>

      <td>Airbus A321( <b>normal_pressure = 3000.0</b>
)<br>

Aircreation582SL( <b>normal_pressure=0.000000</b> )<br>

Beech Baron 58( <b>normal_pressure = 0.0</b> )<br>

DeHavilland Beaver DHC2( <b>normal_pressure = 1000.0</b> )
      </td>

    </tr>

    <tr>

      <td>electric_pumps</td>

      <td>The number of electric hydraulic pumps the aircraft is
configured with. </td>

      <td>Airbus A321( <b>electric_pumps = 0</b> )<br>

Boeing 737-800( <b>electric_pumps = 1</b> ) </td>

    </tr>

    <tr>

      <td>engine_map</td>

      <td>This series of flags sets whether the corresponding
engines of the aircraft are configured with hydraulic pumps. The flags
correspond in order of the engines, starting with the left-most engine
first and moving right. By default, all engines are equiped to drive a
hydraulic pump. </td>

      <td>Airbus A321( <b>engine_map = 1,1,0,0</b> )<br>

Boeing 747-400( <b>engine_map = 1,1,1,1</b> )<br>

Cessna Grand Caravan( <b>engine_map = 1,0,0,0</b> )<br>

DeHavilland Beaver DHC2( <b>engine_map = 1</b> ) </td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId810089"></a>[views]</h4>

<p>The following parameter define the pilot's viewpoint.</p>
<p>&nbsp;</p>
<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>eyepoint</td>

      <td>Longitude, Latitude and Vertical position (in feet)
from
the aircraft;'s datum reference point.. </td>

      <td>Airbus A321( <b>eyepoint=48.2, -1.35, 1.7</b>
)<br>

Aircreation582SL( <b>eyepoint=-0.205052,0.000000,3.604314</b>
)<br>

Boeing 747-400( <b>eyepoint = -18.55, -1.97, 10.7</b> )<br>

Beech Baron 58( <b>eyepoint = -8.213, -0.8612, 2.220</b> )
      </td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">zoom</td>

      <td align="undefined" valign="undefined">Zoom
the view in or out from the viewpoint.</td>

      <td align="undefined" valign="undefined">Default(
      <span style="font-weight: bold;">zoom=1.0</span>
)</td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId895147"></a>[flaps.n]</h4>

<p>For each flap set that is on the aircraft, a corresponding <span style="font-weight: bold;">[flaps.n]</span> section should exist.&nbsp; Most general aviation aircraft and
  smaller jets only have one set of flaps (trailing edge), but it is
  typical for the larger commercial aircraft to have a set of leading
  edge flaps in addition to the trailing edge flaps.&nbsp; The number
  of flap sets are determined by the number of <span style="font-weight: bold;">[flaps.n]</span> sections
contained in the aircraft.cfg file.</p>
<p><br>
  
</p>
<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>type</td>

      <td>Integer value that indicates if this is a leading edge
or trailing edge flap set:<br>

0 = no flaps 1 = trailing edge, 2 = leading edge. </td>

      <td>Airbus A321( <b>type = 1</b> )<br>

Aircreation582SL( <b>type=0</b> )<br>

Boeing 737-800( <b>type = 2</b> )<br>

Cessna Grand Caravan( <b>type=1</b> ) </td>

    </tr>

    <tr>

      <td>span-outboard</td>

      <td>The percentage of half-wing span the flap extends to
(from the wing-fuselage intersection). </td>

      <td>Airbus A321( <b>span-outboard = 0.8</b> )<br>

Aircreation582SL( <b>span-outboard=0.500000</b> )<br>

Beech Baron 58( <b>span-outboard = 0.41</b> )<br>

Beech King Air 350( <b>span-outboard = 0.5</b> ) </td>

    </tr>

    <tr>

      <td>extending-time</td>

      <td>Time it takes for the flap set to extend to the fullest
deflection angle specified (seconds). </td>

      <td>Airbus A321( <b>extending-time = 20</b> )<br>

Aircreation582SL( <b>extending-time=0.000000</b> )<br>

Boeing 737-800( <b>extending-time = 2</b> )<br>

Boeing 747-400( <b>extending-time = 25</b> ) </td>

    </tr>

    <tr>

      <td>flaps-position.0<br>

to<br>

flaps-position.n</td>

      <td>Each element of the flaps-position array indicates the
deflection angle to which the flaps will deflect (in degrees). The
largest
deflection angle will be the one used for full flap deflection. </td>

      <td>Cessna Grand Caravan( <b>flaps-position.0= 0</b>
)<br>

DG808S( <b>flaps-position.0 = -9.0</b> )<br>

Maule M7 260C( <b>flaps-position.0 = -7</b> )<br>

Airbus A321( <b>flaps-position.0 = 0</b> )<br>

Airbus A321( <b>flaps-position.1 = 1</b> )<br>

Airbus A321( <b>flaps-position.2 = 2)</b><br>

Airbus A321( <b>flaps-position.3 = 5</b> )<br>

Airbus A321( <b>flaps-position.4 = 10</b> )<br>

Airbus A321( <b>flaps-position.5 = 15</b> )<br>

Airbus A321( <b>flaps-position.6 = 25</b> )<br>

Airbus A321( <b>flaps-position.7 = 30</b>
)<br>

Airbus A321( <b>flaps-position.8 = 40</b>
) </td>

    </tr>

    <tr>

      <td>damaging-speed</td>

      <td>Speed at which the flaps begin to accrue damage (Knots
Indicated Airspeed, KIAS). </td>

      <td>Airbus A321( <b>damaging-speed = 250</b> )<br>

Boeing 747-400( <b>damaging-speed = 200</b> )<br>

Beech Baron 58( <b>damaging-speed = 152</b> )<br>

Cessna Skyhawk 172SP( <b>damaging-speed = 120</b> ) </td>

    </tr>

    <tr>

      <td>blowout-speed</td>

      <td>Speed at which the flaps depart the aircraft (Knots
Indicated Airspeed, KIAS). </td>

      <td>Airbus A321( <b>blowout-speed = 300</b> )<br>

Boeing 747-400( <b>blowout-speed = 250</b> )<br>

Cessna Skyhawk 172SP( <b>blowout-speed = 150</b> )<br>

Cessna Grand Caravan( <b>blowout-speed = 175</b> ) </td>

    </tr>

    <tr>

      <td>lift_scalar</td>

      <td>The percentage of total lift due to flap deflection
that this flap set is responsible for at full deflection. </td>

      <td>Airbus A321( <b>lift_scalar = 1.0</b> )<br>

Boeing 747-400( <b>lift_scalar = 0.7</b> ) </td>

    </tr>

    <tr>

      <td>drag_scalar</td>

      <td>The percentage of total drag due to flap deflection
that this flap set is responsible for at full deflection. </td>

      <td>Airbus A321( <b>drag_scalar = 1.0</b> )<br>

Boeing 747-400( <b>drag_scalar = 0.9</b> ) </td>

    </tr>

    <tr>

      <td>pitch_scalar</td>

      <td>The percentage of total pitch due to flap deflection
that this flap set is responsible for at full deflection. </td>

      <td>Airbus A321( <b>pitch_scalar= 1.0</b> )<br>

Boeing 747-400( <b>pitch_scalar= 0.9</b> ) </td>

    </tr>

    <tr>

      <td>system_type</td>

      <td>Integer value that indicates what type of system drives
the flaps to deflect:, one of:<br>

0 = Electric<br>

1 = Hydraulic<br>

2 = Pneumatic<br>

3 = Manual<br>

4 = None </td>

      <td>Airbus A321( <b>system_type = 1</b> )<br>

Aircreation582SL( <b>system_type=0</b> )<br>

Cessna Skyhawk 172SP( <b>system_type = 0</b> )<br>

DG808S( <b>system_type = 3</b> ) </td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId77591"></a>[radios]</h4>

<p>There should be a radio section in each
aircraft.cfg.&nbsp; This section configures the radios for each
individual aircraft.&nbsp; Each of the following keywords has a
flag or set of flags, that determine if the particular radio element is
available
in the aircraft.&nbsp; A &ldquo;1&rdquo; is used for true
(or available), and 0 for false (or not available).&nbsp;</p>

<p> </p>

<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>audio.1</td>

      <td>Is there an audio panel, set to 1.. </td>

      <td>Airbus A321( <b>Audio.1 = 1</b> )<br>

DG808S( <b>Audio.1 = 0</b> ) </td>

    </tr>

    <tr>

      <td>com.1</td>

      <td>Two flags, set the first one to 1 if a&nbsp;Com1
radio is available, and the second if&nbsp;it supports a standby
frequency. </td>

      <td>Airbus A321( <b>Com.1 = 1, 1</b> )<br>

Beech King Air 350( <b>Com.1 = 1, 0</b> ) </td>

    </tr>

    <tr>

      <td>com.2</td>

      <td>Two flags, set the first one to 1 if a&nbsp;Com2
radio is available, and the second if&nbsp;it supports a standby
frequency.&nbsp;You cannot have Com2 without Com1. </td>

      <td>Airbus A321( <b>Com.2 = 1, 1</b> )<br>

Beech King Air 350( <b>Com.2 = 1, 0</b> ) </td>

    </tr>

    <tr>

      <td>nav.1</td>

      <td>Three flags, set the first to 1 if&nbsp;there is a
Nav1 receiver, the second if it supports a standby
frequency, and the thrid if it supports a glideslope indication. </td>

      <td>Airbus A321( <b>Nav.1 = 1, 1, 1</b> )<br>

Beech King Air 350( <b>Nav.1 = 1, 0, 1</b> )<br>

DG808S( <b>Nav.1 = 0, 0, 0</b> ) </td>

    </tr>

    <tr>

      <td>nav.2</td>

      <td>Three flags, set the first to 1 if&nbsp;there is a
Nav2 receiver, the second if it supports a standby
frequency, and the thrid if it supports a glideslope
indication.&nbsp;You
cannot have Nav2 without Nav1. </td>

      <td>Airbus A321( <b>Nav.2 = 1, 1, 0</b> )<br>

Beech King Air 350( <b>Nav.2 = 1, 0, 0</b> ) </td>

    </tr>

    <tr>

      <td>adf.1</td>

      <td>If there is an ADF receiver, set to 1. </td>

      <td>Airbus A321( <b>Adf.1 = 1</b> )<br>

DG808S( <b>Adf.1 = 0</b> ) </td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">adf.2</td>

      <td align="undefined" valign="undefined">If
there is an ADF2 receiver, set to 1.</td>

      <td align="undefined" valign="undefined">Bombardier
CRJ 700( <b>Adf.2 = 1</b> )</td>

    </tr>

    <tr>

      <td>transponder.1</td>

      <td>If there is a transponder, set to 1. </td>

      <td>Airbus A321( <b>Transponder.1 = 1</b> )<br>

DG808S( <b>Transponder.1 = 0</b> ) </td>

    </tr>

    <tr>

      <td>marker.1</td>

      <td>If there is a marker beacon receiver, set to 1. </td>

      <td>Airbus A321( <b>Marker.1 = 1</b> )<br>

DG808S( <b>Marker.1 = 0</b> ) </td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId274992"></a>[lights]</h4>

<p class="MsoNormal" style=""><span style="">Each
light that requires a special effect <span style="">should
be entered in this section. The following table gives the codes for the
switches that will turn on the lights.
</span><span style=""></span><o:p></o:p></span></p>

<p class="MsoNormal" style=""><span style=""><o:p>&nbsp;
</o:p>
<table style="text-align: left; width: 200px;" border="1" cellpadding="2" cellspacing="2">

  <tbody>

    <tr>

      <td align="undefined" valign="undefined"><span style="font-weight: bold;">Code</span></td>

      <td align="undefined" valign="undefined"><span style="font-weight: bold;">Switch</span></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">1</td>

      <td align="undefined" valign="undefined"><span style="">Beacon</span></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">2</td>

      <td align="undefined" valign="undefined"><span style="">Strobe</span></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">3</td>

      <td align="undefined" valign="undefined"><span style="">Navigation or Position</span></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">4</td>

      <td align="undefined" valign="undefined"><span style="">Cockpit</span></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">5</td>

      <td align="undefined" valign="undefined"><span style="">Landing</span></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">6</td>

      <td align="undefined" valign="undefined"><span style="">Taxi</span></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">7</td>

      <td align="undefined" valign="undefined"><span style="">Recognition</span></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">8</td>

      <td align="undefined" valign="undefined"><span style="">Wing</span></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">9</td>

      <td align="undefined" valign="undefined"><span style="">Logo</span></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">10</td>

      <td align="undefined" valign="undefined"><span style="">Cabin</span></td>

    </tr>

  </tbody>
</table>

<br>

</span></p>

<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5 style="margin-left: 0px; width: 286px;">Examples</h5>

      </td>

    </tr>

    <tr>

      <td><p>light.0</p>
      <p>to</p>
      <p>light.n</p></td>

      <td><span style="">The first
entry of the line defines which circuit, or switch, the light is
connected
to (s<span style=""></span>ee the code table above).<span style="">&nbsp; </span>Multiple
lights may be connected to a single
switch.<span style="">&nbsp; </span>The next
three entries are the
longitudinal, lateral, and vertical positions of the light in feet.<span style="">&nbsp; </span>The final entry is the
special effect file
name that is triggered (for example, fx_navred).<span style="">&nbsp;
      </span>These files have .fx extensions and should be placed
in
the&nbsp;<span style="font-style: italic;">Microsoft Flight
Simulator X/effects </span>folder.<span style="">&nbsp;</span></span></td>

      <td>Airbus A321( <b>light.0 = 3, -19.14, -47.24,
1.38, fx_navredm ,</b> )<br>

Boeing 747-400( <b>light.0 = 3, -150.30, -102.56, 3.22,
fx_navredh ,</b> )<br>

Beech Baron 58( <b>light.0 = 3, -6.60, -19.29, 0.79, fx_navred ,</b>
)<br>

      <br>

Beech King Air 350( <b>light.0 = 3, 0.56, -28.41, 1.97,
fx_navred ,</b> )<br>

Beech King Air 350( <b>light.1 = 3, 0.56, 28.41, 1.97, fx_navgre
,</b> )<br>

Beech King Air 350( <b>light.2 = 3, -31.20, 0.00, 9.09,
fx_navwhi ,</b> )<br>

Beech King Air 350( <b>light.3 = 2, 0.89, -28.48, 1.87,
fx_strobe ,</b> ) </td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId495225"></a>[keyboard_response]</h4>

<p>The aircraft flight controls can be manipulated by the
keyboard. Because flight controls naturally become more sensitive as
airspeed increases, it can become quite difficult to control the
aircraft via the keyboard at high speeds.&nbsp; To address this
problem, the amount a single keypress increments a flight control is
decreased by a factor of 1/2 at the first airspeed (in knots) listed on
the line for the control, and to 1/8 at the second airspeed, and to
&nbsp;a scale&nbsp;interpolated from these values for all
airspeeds in between. The example below shows
that an elevator will increment by one degree when the airspeed is
zero, by &frac34; of one degree at 50 knots, &frac12;
of one degree at 100 knots, 5/16 of one degree at 140 knots, and 1/8 of
one degree at 180 knots or greater speed.</p>

<p></p>

<table style="text-align: left; width: 200px;" border="1" cellpadding="2" cellspacing="2">

  <tbody>

    <tr>

      <td align="undefined" valign="undefined"><img src="Images/keypress.jpg"></td>

    </tr>

  </tbody>
</table>

<p></p>

<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>elevator</td>

      <td>Two breakpoint speeds for keypress increments.</td>

      <td>Airbus A321( <b>elevator = 150, 250</b> )<br>

Aircreation582SL( <b>elevator=150.000000,250.000000</b> )<br>

Cessna Skyhawk 172SP( <b>elevator = 100, 180</b> )<br>

DG808S( <b>elevator = 160, 360</b> ) </td>

    </tr>

    <tr>

      <td>aileron</td>

      <td>Two breakpoint speeds for keypress increments.</td>

      <td>Airbus A321( <b>aileron = 150, 250</b> )<br>

Aircreation582SL( <b>aileron=150.000000,250.000000</b> )<br>

Cessna Skyhawk 172SP( <b>aileron = 200, 1000</b> )<br>

DG808S( <b>aileron = 160, 360</b> ) </td>

    </tr>

    <tr>

      <td>rudder</td>

      <td>Two breakpoint speeds for keypress increments.</td>

      <td>Airbus A321( <b>rudder = 150, 250</b> )<br>

Aircreation582SL( <b>rudder=150.000000,250.000000</b> )<br>

Cessna Skyhawk 172SP( <b>rudder = 200, 1000</b> )<br>

DG808S( <b>rudder = 160, 360</b> ) </td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId786368"></a>[direction_indicators]</h4>

This section is used to define the characteristics of the direction
indicators on the instrument panels, but&nbsp;does not include the
magnetic compass (which has a separate section).&nbsp; The list of
indicators should be listed in
order: 0,1,2,&hellip;n.&nbsp;<br>

<br>

<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>direction_indicator.0<br>

to<br>

direction_indicator.n</td>

      <td>One or two codes. If the indicator is type 4, then
there must be two entries here (the indicator, and the indicator to
which this one is slaved). &nbsp;The indicator codes are:<br>

0 = None<br>

1 = Vacuum gyro<br>

2 = Electric gyro<br>

3 = Electro-mag slaved compass<br>

4 = Slaved to another indicator</td>

      <td>Airbus A321( <b>direction_indicator.0=3,0</b>
)<br>

Aircreation582SL( <b>direction_indicator.0 = 0</b> )<br>

Cessna Skyhawk 172SP( <b>direction_indicator.0=1,0</b> )<br>

DG808S( <b>direction_indicator.0=0,0</b> )<br>

      <br>

Douglas DC-3( <b>direction_indicator.1=2,0</b>
) </td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">induction_compass.0<br>

to<br>

induction_compass.n</td>

      <td align="undefined" valign="undefined">If
there is an induction compass, one of:<br>

1 = Electric<br>

2 = Anemometer driven </td>

      <td align="undefined" valign="undefined">(From <i>Flight Simulator 2004</i>)<br>

Ryan NYP( <b>induction_compass.0=2</b> ) </td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId657009"></a>[attitude_indicators]</h4>

<p>This section is used to define the characteristics of the attitude
  indicators on the instrument panels. The list of indicators should be
listed in order: 0,1,2,...n.&nbsp;</p>
<p><br>
  
</p>
<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>attitude_indicator.0<br>

to<br>

attitude_indicator.n</td>

      <td>The system which drives the attitude indicator. One of:<br>

0 = none<br>

1 = Vacuum driven gyro<br>

2 = Electrically driven gyro</td>

      <td>Airbus A321( <b>attitude_indicator.0 = 2</b>
)<br>

Aircreation582SL( <b>attitude_indicator.0=1</b> )<br>

Beech Baron 58( <b>attitude_indicator.0 = 1</b> )<br>

DG808S( <b>attitude_indicator.0 = 0</b> )<br>

      <br>

Boeing 747-400( <b>attitude_indicator.1 = 1</b>
)<br>

Douglas DC-3( <b>attitude_indicator.1 = 2</b> ) </td>

    </tr>

  </tbody>
</table>

<p>&nbsp;</p>
<H4>[altimeters]<a name="altimeters"></a></H4>
<TABLE cellSpacing="4" cellPadding="2">
  <TBODY>
    <TR>
      <TD><H5>Property </H5></TD>
      <TD><H5>Description </H5></TD>
      <TD><H5>Examples</H5></TD>
    </TR>
    <TR>
      <TD><p>altimeter.0</p>
      <p>to</p>
      <p>altimeter.n</p></TD>
      <TD>If the parameter is set to 1, a separate altimeter is instantiated, which will operate independently of other altimeters, and can have failures applied to it. </TD>
      <TD><p>Airbus A321 Paint2( <B>altimeter.0=1</B> )<BR>
        Learjet 45( <B>altimeter.0 =   1</B> )</p>
        <p> Airbus A321 Paint2( <b>altimeter.1=1</b> )<br>
      Learjet 45( <b>altimeter.1 =   1</b> ) </p></TD>
    </TR>
  </TBODY>
</TABLE>
<p>&nbsp;</p>
<h4><a class="mozTocH4" name="mozTocId854181"></a>[turn_indicators]</h4>

<p>This section is used to define the characteristics of the turn
indicators on the instrument panels.&nbsp; The list of indicators
should be listed in order: 0,1,2,&hellip;n.&nbsp;</p>

<p> </p>

<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>turn_indicator.0</td>

      <td>Two code values, which define the system on which the
turn indicators are dependant. The first value is&nbsp;for turn,
the second for bank. The codes are:<br>

0 = None<br>

1 = Electrically driven gyro<br>

2 = Vacuum driven gyro</td>

      <td>Airbus A321( <b>turn_indicator.0=0,0</b> )<br>

Aircreation582SL( <b>turn_indicator.0=1,0</b> )<br>

Beech Baron 58( <b>turn_indicator.0=1,1</b> )<br>

DeHavilland Beaver DHC2( <b>turn_indicator.0=1</b> ) </td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId729957"></a>[vacuum_system]</h4>

<p>The following parameters define the aircraft's vacuum system:</p>
<p>&nbsp;</p>
<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>max_pressure</td>

      <td>Maximum pressure in psi. </td>

      <td>Airbus A321( <b>max_pressure=5.15</b> )<br>

Aircreation582SL( <b>max_pressure=5.000000</b> )<br>

Boeing 747-400( <b>max_pressure=5.150000</b> )<br>

DG808S( <b>max_pressure=0</b> ) </td>

    </tr>

    <tr>

      <td>vacuum_type</td>

      <td>Vacuum type, one of:<br>

0 = None<br>

1 = Engine pump (default)<br>

2 = Pneumatic<br>

3 = Venturi. </td>

      <td>Airbus A321( <b>vacuum_type=2</b> )<br>

Aircreation582SL( <b>vacuum_type=1</b> )<br>

DG808S( <b>vacuum_type=0</b> ) </td>

    </tr>

    <tr>

      <td>electric_backup_pressure</td>

      <td>Backup pressure in psi. </td>

      <td>Aircreation582SL( <b>electric_backup_pressure=0.000000</b>
)<br>

Beech Baron 58( <b>electric_backup_pressure=4.900000</b> )<br>

Mooney Bravo( <b>electric_backup_pressure=4.9</b> )<br>

Bell 206B JetRanger( <b>electric_backup_pressure=5.15</b>
) </td>

    </tr>

    <tr>

      <td>engine_map</td>

      <td> This series of flags sets whether the corresponding
engines of the aircraft are configured with vacuum systems. The flags
correspond in order of the engines, starting with the left-most engine
first and moving right.</td>

      <td>Beech Baron 58( <b>engine_map=1,1</b> )<br>

Cessna Skyhawk 172SP( <b>engine_map=1</b> ) </td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId465058"></a>[pneumatic_system]</h4>

<p>The following parameters define the aircraft's pneumatic pressure
  system:</p>
<p>&nbsp;</p>
<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>max_pressure</td>

      <td>The maximum pressure of the pneumatic system. </td>

      <td>Airbus A321( <b>max_pressure=18.000000</b>
)<br>

Aircreation582SL( <b>max_pressure=0.000000</b> )<br>

Grumman Goose G21A( <b>max_pressure = 21.5</b> )<br>

Piper Cub( <b>max_pressure=0</b> ) </td>

    </tr>

    <tr>

      <td>bleed_air_scalar</td>

      <td>The ratio of bleed-air pressure from the engines to pneumatic air pressure in the pneumatic system. </td>

      <td>Airbus A321( <b>bleed_air_scalar=1.000000</b>
)<br>

Aircreation582SL( <b>bleed_air_scalar=0.000000</b> )<br>

Beech Baron 58( <b>bleed_air_scalar=0.00000</b> )<br>

Cessna Grand Caravan( <b>bleed_air_scalar=0.150000</b> ) </td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId310622"></a>[exits]</h4>

<p>The following parameters define the aircraft's exits:</p>
<p>&nbsp;</p>
<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>      </td>

      <td>
      <h5>Description </h5>      </td>

      <td>
      <h5>Examples</h5>      </td>
    </tr>

    <tr>

      <td>number_of_exits</td>

      <td>This value defines the number of simulated exits, or
doors, on the aircraft. </td>

      <td>Airbus A321( <b>number_of_exits = 3</b> )<br>

Aircreation582SL( <b>number_of_exits =1</b> )<br>

Beech Baron 58( <b>number_of_exits = 1</b> )<br>

Cessna Grand Caravan( <b>number_of_exits = 2</b> ) </td>
    </tr>

    <tr>

      <td>exit.0<br>

to<br>

exit.n</td>

      <td>Five values: the open and close rate percent per second
(where 1.0 is fully open), the longitudinal,
lateral, and vertical positions from datum (in feet), and the type of
exit, one of:<br>

0 = Main<br>

1 = Cargo<br>

2 = Emergency </td>

      <td>Airbus A321( <b>exit.0 = 0.4, 40.50,-6.0, 7.0, 0</b>
)<br>

Boeing 737-800( <b>exit.0 = 0.4, 41.3, -6.0, 4.0, 0</b> )<br>

Boeing 747-400( <b>exit.0 = 0.4, -30.30, -9.5, 1, 0</b> )<br>

Bombardier CRJ 700( <b>exit.0 = 0.4, -16.50, -4.5, 0.5, 0</b>
)<br>

Bombardier CRJ 700( <b>exit.1 = 0.4, -74.00, -4.5, 0.5, 1</b>
)<br>

Bombardier CRJ 700( <b>exit.2 = 0.4, -36.50, -2.5, -1.0, 1</b>
) </td>
    </tr>
  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId547795"></a>[effects]</h4>

<p>The effects section of the aircraft.cfg file refers to the visual
  effects that result from various systems or reactions of the aircraft.
  An effect file associated with a keyword in this section will be used
  when the corresponding action is triggered.&nbsp; If no
  entry is made a default effect file will be used. The table below
  outlines the aircraft effects currently
  supported, though of course not all effects are supported on all
aircraft.</p>
<p><br>
  
</p>
<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>      </td>

      <td>
      <h5>Description </h5>      </td>

      <td>
      <h5>Examples</h5>      </td>
    </tr>

    <tr>

      <td>wake</td>

      <td>The wake effect name, followed by an optional 1 if the
effect is to be run for a single iteration. Set this number
to&nbsp;zero or leave blank
(the default), for the effect to continue as long as the respective
action
is active. This optional 1 applies to all effects in this table.</td>

      <td>Airbus A321( <b>wake=fx_wake</b> ) </td>
    </tr>

    <tr>

      <td>water</td>

      <td>The landing, taxiing or taking off from water effect.</td>

      <td>Airbus A321( <b>water=fx_spray</b> ) </td>
    </tr>

    <tr>

      <td>dirt</td>

      <td>The moving on dirt effect.</td>

      <td>Airbus A321( <b>dirt=fx_tchdrt</b> ) </td>
    </tr>

    <tr>

      <td>concrete</td>

      <td>The moving on concrete effect.</td>

      <td>Airbus A321( <b>concrete=fx_sparks</b> )<br>

DG808S( <b>concrete=fx_tchdwn_s</b> ) </td>
    </tr>

    <tr>

      <td>touchdown</td>

      <td>The touchdown effect, which usually is followed by an
optional 1 to indicate the effect is to be run once only.</td>

      <td>Airbus A321( <b>touchdown=fx_tchdwn, 1</b>
)<br>

Aircreation582SL( <b>touchdown=fx_tchdwn_s, 1</b> ) </td>
    </tr>

    <tr>

      <td>startup</td>

      <td>Engine startup.</td>

      <td>Douglas DC-3( <b>startup=fx_engstrt_jenny</b>
)<br>

Piper Cub( <b>startup=fx_engstrt_cub</b> ) </td>
    </tr>

    <tr>

      <td>enginefire</td>

      <td>Engine fire.</td>

      <td>Bell 206B JetRanger( <b>EngineFire=fx_heliFire</b>
) </td>
    </tr>

    <tr>

      <td align="undefined" valign="undefined">windshield_rain_effect_available</td>

      <td align="undefined" valign="undefined">Setting
this flag to zero will turn off the effect of rain on the windshield.
The default is 1.</td>

      <td align="undefined" valign="undefined">(From <i>Flight Simulator 2004</i>)<br>

Curtiss Jenny( <b>windshield_rain_effect_available = 0</b>
)<br>      </td>
    </tr>
    <TR>
      <TD>snowtrack</TD>
      <TD>Snow track effect, used when taking off in snow. </TD>
      <TD>Maule M7 260C Ski paint1( <B>SnowTrack = fx_snowtrack</B> ) </TD>
    </TR>
    <TR>
      <TD>wheelsnowspray</TD>
      <TD>Spray effect when taking off in snow. </TD>
      <TD>Maule M7 260C Ski paint1( <B>WheelSnowSpray = fx_WheelSnowSpray</B> ) </TD>
    </TR>
    <TR>
      <TD>wheelwetspray</TD>
      <TD>Spray effect when taking off from a wet runway. </TD>
      <TD>Maule M7 260C Ski paint1( <B>WheelWetSpray = fx_WheelWetSpray</B> ) </TD>
    </TR>
  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId942782"></a>[autopilot]</h4>

<p>The following parameters determine the functionality of the
aircraft&rsquo;s autopilot system, including the flight director.</p>

<p><br>

</p>

<h5>Navigation Modes:</h5>

<br>

<p>The navigation and glideslope controllers utilize standard
proportional/integral /derivative feedback controllers (PID).&nbsp;
The integrator and derivative controllers have boundaries, which are
the maximum error from the controlled parameter in which these are
active.&nbsp; It is not necessary to have all three components
active.&nbsp; Setting the respective control constant to 0
effectively disables that component, allowing PI or PD controllers to
be utilized. Navigation mode parameters begin with nav_ or gs_.

</p>

<p> </p>

<table class="T1" cellpadding="2" cellspacing="4">
  <tbody>
    <tr>
      <td><h5>Property </h5></td>
      <td><h5>Description </h5></td>
      <td><h5>Examples</h5></td>
    </tr>
    <tr>
      <td>autopilot_available</td>
      <td>Setting this flag to a 1 makes available
        an autopilot system on the aircraft. </td>
      <td>Airbus A321( <b>autopilot_available=1</b> )<br>
        Aircreation582SL( <b>autopilot_available=0</b> )</td>
    </tr>
    <tr>
      <td>flight_director_available</td>
      <td>Setting this flag to a 1 makes available a
        flight director on the aircraft. </td>
      <td>Airbus A321( <b>flight_director_available=1</b> )<br>
        Aircreation582SL( <b>flight_director_available=0</b> )</td>
    </tr>
    <tr>
      <td>default_vertical_speed</td>
      <td>The default vertical speed, in feet per second, that
        the autopilot will command when selecting a large altitude change. </td>
      <td>Airbus A321( <b>default_vertical_speed=1800</b> )<br>
        Boeing 747-400( <b>default_vertical_speed = 1800.0</b> )<br>
        Beech Baron 58( <b>default_vertical_speed= 700.0</b> )<br>
        Beech King Air 350( <b>default_vertical_speed= 1800.0</b> ) </td>
    </tr>
    <tr>
      <td>autothrottle_available</td>
      <td>Setting this flag to a 1 makes available
        an autothrottle system on the aircraft. </td>
      <td>Boeing 747-400( <b>autothrottle_available = 1</b> )<br>
        Beech Baron 58( <b>autothrottle_available= 0</b> )</td>
    </tr>
    <tr>
      <td>autothrottle_arming_required</td>
      <td>Setting this flag to 1 will require that the
        autothrottle be armed prior to it being engaged.
        Setting it to zero allows the autothrottle to be engaged directly. </td>
      <td>Boeing 747-400( <b>autothrottle_arming_required
        = 1</b> )<br>
        Bombardier CRJ 700( <b>autothrottle_arming_required= 0</b> ) </td>
    </tr>
    <tr>
      <td>autothrottle_max_rpm</td>
      <td>This sets the maximum engine speed, in percent, that
        the autothrottle will attempt to maintain. </td>
      <td>Airbus A321( <b>autothrottle_max_rpm = 90</b> )<br>
        Boeing 747-400( <b>autothrottle_max_rpm = 90</b> ) </td>
    </tr>
    <tr>
      <td>autothrottle_takeoff_ga</td>
      <td>Setting this flag to 1 enables takeoff / go-around
        operations with the autothrottle. </td>
      <td>Boeing 747-400( <b>autothrottle_takeoff_ga = 1</b> )<br>
        Bombardier CRJ 700( <b>autothrottle_takeoff_ga= 0</b> )<br>
      </td>
    </tr>
    <tr>
      <td align="undefined" valign="undefined">default_pitch_mode</td>
      <td align="undefined" valign="undefined">This
        determines the default pitch mode when the autopilot logic is turned on.<br>
        0 = None<br>
        1 = Pitch Hold (current pitch angle)<br>
        2 = Altitude Hold (current altitude)<br>
        If no value is set, Pitch Hold will be the default.</td>
      <td align="undefined" valign="undefined"></td>
    </tr>
    <tr>
      <td>pitch_takeoff_ga</td>
      <td>The default pitch that the Takeoff/Go-Around mode
        references. </td>
      <td>Beech Baron 58( <b>pitch_takeoff_ga=8.0</b> )<br>
        Douglas DC-3( <b>pitch_takeoff_ga=0.0</b> ) </td>
    </tr>
    <tr>
      <td>max_pitch</td>
      <td>The maximum pitch angle in degrees that the autopilot
        will command either up or down. </td>
      <td>Airbus A321( <b>max_pitch=10.0</b> )<br>
      </td>
    </tr>
    <tr>
      <td>max_pitch_acceleration</td>
      <td>The maximum angular pitch acceleration, in degrees per
        second squared, that the autopilot will command up or down. </td>
      <td>Airbus A321( <b>max_pitch_acceleration=1.0</b> )<br>
      </td>
    </tr>
    <tr>
      <td>max_pitch_velocity_lo_alt</td>
      <td>The maximum angular pitch velocity, in degrees per
        second, which the autopilot will command when at an altitude below that
        specified by the variable max_pitch_velocity_lo_alt_breakpoint. </td>
      <td>Airbus A321( <b>max_pitch_velocity_lo_alt=2.0</b> )<br>
      </td>
    </tr>
    <tr>
      <td>max_pitch_velocity_hi_alt</td>
      <td>The maximum angular pitch velocity, in degrees per
        second, which the autopilot will command when at an altitude above the
        altitude specified by the variable
        max_pitch_velocity_hi_alt_breakpoint. The maximum velocity is
        interpolated between the hi and lo altitude velocities when between the
        hi and lo altitude breakpoints. </td>
      <td>Airbus A321( <b>max_pitch_velocity_hi_alt=1.5</b> )<br>
      </td>
    </tr>
    <tr>
      <td>max_pitch_velocity_lo_alt_breakpoint</td>
      <td>The altitude below which the autopilot maximum pitch
        velocity is limited by the variable max_pitch_velocity_lo_alt. </td>
      <td>Airbus A321( <b>max_pitch_velocity_lo_alt_breakpoint=20000.0</b> )<br>
      </td>
    </tr>
    <tr>
      <td>max_pitch_velocity_hi_alt_breakpoint</td>
      <td>The altitude above which the autopilot maximum pitch
        velocity is limited by the variable max_pitch_velocity_hi_alt. The
        maximum velocity is interpolated between the hi and lo altitude
        velocities when between the hi and lo altitude breakpoints. </td>
      <td>Airbus A321( <b>max_pitch_velocity_hi_alt_breakpoint=28000.0</b> )<br>
      </td>
    </tr>
    <tr>
      <td>max_bank</td>
      <td>The maximum bank angle in degrees that the autopilot
        will command either left or right.<br></td>
      <td>Airbus A321( <b>max_bank=25.0</b> )<br>
        Boeing 737-800( <b>max_bank=30,25,20,15,10</b> )<br>
        Bombardier CRJ 700( <b>max_bank=30,15</b> )<br>
        Douglas DC-3( <b>max_bank=25.000000</b> ) </td>
    </tr>
    <tr>
      <td>max_bank_acceleration</td>
      <td>The maximum angular bank acceleration, in degrees per
        second squared, that the autopilot will command left or right. </td>
      <td>Airbus A321( <b>max_bank_acceleration=1.8</b> )<br>
      </td>
    </tr>
    <tr>
      <td>max_bank_velocity</td>
      <td>The maximum angular bank velocity, in degrees per
        second, which the autopilot will command left or right. </td>
      <td>Douglas DC-3( <b>max_bank_velocity=3.000000</b> ) </td>
    </tr>
    <tr>
      <td>max_throttle_rate</td>
      <td>This value sets the maximum rate at which the
        autothrottle will move the throttle position. In the example, the
        maximum rate is set to 10% of the total throttle range per second. </td>
      <td>Douglas DC-3( <b>max_throttle_rate=0.100000</b> ) </td>
    </tr>
    <tr>
      <td>nav_proportional_control</td>
      <td>Proportional controller constant in lateral navigation
        modes. </td>
      <td>Airbus A321( <b>nav_proportional_control=12.00</b> )<br>
        Boeing 747-400( <b>nav_proportional_control=16.00</b> )<br>
        Beech Baron 58( <b>nav_proportional_control=9.00</b> )<br>
        Bombardier CRJ 700( <b>nav_proportional_control=11.00</b> ) </td>
    </tr>
    <tr>
      <td>nav_integrator_control</td>
      <td>Integral controller constant in lateral navigation
        modes. </td>
      <td>Airbus A321( <b>nav_integrator_control=0.25</b> )<br>
        Boeing 747-400( <b>nav_integrator_control=0.17</b> )<br>
        Bombardier CRJ 700( <b>nav_integrator_control=0.20</b> )<br>
        Douglas DC-3( <b>nav_integrator_control=0.250000</b> ) </td>
    </tr>
    <tr>
      <td>nav_derivative_control</td>
      <td>Derivative controller constant in lateral navigation
        modes. </td>
      <td>Airbus A321( <b>nav_derivative_control=0.00</b> )<br>
        Douglas DC-3( <b>nav_derivative_control=0.000000</b> ) </td>
    </tr>
    <tr>
      <td>nav_integrator_boundary</td>
      <td>The boundary, or maximum signal error, in degrees in
        which the integrator function is active. In the example, the integrator
        is active when the error is between -2.5 and +2.5 degrees from the
        centerline of the navigation signal. </td>
      <td>Airbus A321( <b>nav_integrator_boundary=2.50</b> )<br>
          <br>
      </td>
    </tr>
    <tr>
      <td>nav_derivative_boundary</td>
      <td>The boundary, or maximum signal error, in degrees in
        which the derivative function is active. In the example, the derivative
        controller is not active because the maximum error is set to 0. </td>
      <td>Airbus A321( <b>nav_derivative_boundary=0.00</b> )<br>
          <br>
      </td>
    </tr>
    <tr>
      <td>gs_proportional_control</td>
      <td>Proportional controller constant in glideslope mode. </td>
      <td>Airbus A321( <b>gs_proportional_control=25.0</b> )<br>
        Boeing 747-400( <b>gs_proportional_control = 18.0</b> )<br>
        Beech Baron 58( <b>gs_proportional_control=9.52</b> )<br>
        Douglas DC-3( <b>gs_proportional_control=9.520000</b> ) </td>
    </tr>
    <tr>
      <td>gs_integrator_control</td>
      <td>Integral controller constant in glideslope mode. </td>
      <td>Airbus A321( <b>gs_integrator_control=0.53</b> )<br>
        Boeing 747-400( <b>gs_integrator_control = 0.33</b> )<br>
        Beech Baron 58( <b>gs_integrator_control=0.26</b> )<br>
        Douglas DC-3( <b>gs_integrator_control=0.260000</b> ) </td>
    </tr>
    <tr>
      <td>gs_derivative_control</td>
      <td>Derivative controller constant in glideslope mode. </td>
      <td>Boeing 747-400( <b>gs_derivative_control = 0.00</b> )<br>
      </td>
    </tr>
    <tr>
      <td>gs_integrator_boundary</td>
      <td>The boundary, or maximum signal error, in degrees in
        which the glideslope integrator function is active. In the example, the
        integrator is active when the error is between -0.7 and +0.7 degrees
        from the centerline of the glideslope signal. </td>
      <td>Boeing 747-400( <b>gs_integrator_boundary = 0.70</b> )<br>
      </td>
    </tr>
    <tr>
      <td>gs_derivative_boundary</td>
      <td>The boundary, or maximum signal error, in degrees in
        which the derivative function is active. In the example, the derivative
        controller is not active because the maximum error is set to 0. </td>
      <td>Boeing 747-400( <b>gs_derivative_boundary = 0.00</b> )<br>
      </td>
    </tr>
    <tr>
      <td>yaw_damper_gain</td>
      <td>The proportional gain on the yaw dampers yaw rate
        error. </td>
      <td>Airbus A321( <b>yaw_damper_gain = 1.0</b> )<br>
        Beech Baron 58( <b>yaw_damper_gain = 0.0</b> ) </td>
    </tr>
    <tr>
      <td>direction_indicator</td>
      <td>Indicates which direction indicator system on the
        aircraft is being referenced by the autopilot.<br>
        0 = the first, and is
        the default. </td>
      <td>Douglas DC-3( <b>direction_indicator=1</b> ) </td>
    </tr>
    <tr>
      <td>attitude_indicator</td>
      <td>Indicates which attitude indicator system on the
        aircraft is being referenced by the autopilot.<br>
        0 = the first, and is
        the default. </td>
      <td>Douglas DC-3( <b>attitude_indicator =1</b> ) </td>
    </tr>
    <tr>
      <td>default_bank_mode</td>
      <td>This determines the default bank mode when the
        autopilot logic is turned on.<br>
        0 = None<br>
        1 = Wing Level Hold<br>
        2 =
        Heading Hold (current heading). <br>
        If no value is set, Wing Level Hold
        will be the default. </td>
      <td>Douglas DC-3( <b>default_bank_mode=2</b> ) </td>
    </tr>
  </tbody>
</table>
<br>

<h5>Miscellaneous default AP modes:</h5>

<p>In <i>Flight Simulator</i>2002,
the following flags were enabled to
allow aircraft to be configured with no pitch and/or bank
modes.&nbsp; While these are still supported in later versions, the
preferred flags are included above in the respective vertical and
lateral sections.&nbsp;</p>

<br>

<table style="text-align: left; width: 834px; height: 76px;" border="1" cellpadding="2" cellspacing="2">

  <tbody>

    <tr>

      <td align="undefined" valign="undefined"><span style="font-weight: bold;">Property</span></td>

      <td align="undefined" valign="undefined"><span style="font-weight: bold;">Description</span></td>

      <td align="undefined" valign="undefined"><span style="font-weight: bold;">Examples</span></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">use_no_default_pitch</td>

      <td align="undefined" valign="undefined">Setting
this flag to 1 will cause the default pitch mode to be "None". It will
actually set the variable default_pitch_mode to zero, so that there is
no default pitch mode when the autopilot logic is activated.<br>

The prefered method is to tset the default_pitch_mode directly.</td>

      <td align="undefined" valign="undefined"></td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">use_no_default_bank</td>

      <td align="undefined" valign="undefined">Setting
this flag to 1 will cause the default bank mode to be "None".
It will actually set the variable default_bank_mode to zero, so that
there is no default bank mode when the autopilot logic is activated.<br>

The prefered method is to tset the default_bank_mode directly.</td>

      <td align="undefined" valign="undefined">See
examples for default_bank_mode</td>

    </tr>

  </tbody>
</table>

<h4><a class="mozTocH4" name="mozTocId38401"></a>[fuel]</h4>

<p>This section defines the characteristics of the fuel system,
including the tanks, fuel type, and the number of fuel
selectors.&nbsp;The number of fuel selectors is intended to match
the number of visual
selectors on the instrument panel.</p>

<p></p>

<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>center1<br>

center2<br>

center3<br>

leftmain<br>

leftaux<br>

lefttip<br>

rightmain<br>

rightaux<br>

righttip<br>

external1<br>

external2</td>

      <td>The longitudinal, lateral, and vertical position of the
tank. Next are the usable and unusable capacities of the tanks. </td>

      <td>Boeing 747-400( <b>Center1 = -83.5, 0.0, -7.0,
17164.0, 0.0</b>
)<br>

Bombardier CRJ 700( <b>Center1 = -48.7, 0.0, -4.0, 982.0, 0.0</b>
)<br>

Boeing 747-400( <b>Center2 = -193.5, 0.0, 6.0,
3300.0, 0.0</b> )<br>

DeHavilland Beaver DHC2( <b>Center3=-10.600000,0.000000,-1.900000,25.000000,0.000000</b>
)<br>

Airbus A321( <b>LeftMain = -3, -19, 0, 1500, 0</b>
)<br>

Beech Baron 58( <b>RightMain = -8.46, 6.45, 0.0, 71.0, 0.0</b>
)<br>

Maule M7 260C( <b>LeftAux = -2.24, -11.4, 2.40, 15.0, 0.00</b>
)<br>

      </td>

    </tr>

    <tr>

      <td>fuel_type</td>

      <td>One of:<br>

1 = Avgas<br>

2 = JetA </td>

      <td>Airbus A321( <b>fuel_type = 2</b> )<br>

Beech Baron 58( <b>fuel_type = 1</b> )<br>

      </td>

    </tr>

    <tr>

      <td>number_of_tank_selectors</td>

      <td>Number of fuel tank selectors (maximum 4 and should be
less
than or equal to the number of engines). </td>

      <td>Aircreation582SL( <b>number_of_tank_selectors=1</b>
)<br>

Beech Baron 58( <b>number_of_tank_selectors = 2</b> ) </td>

    </tr>

    <tr>

      <td>electric_pump</td>

      <td>Boolean that sets whether an electric boost pump is
available, 0 = FALSE, 1 = TRUE. </td>

      <td>Airbus A321( <b>electric_pump=0</b> )<br>

Grumman Goose G21A( <b>electric_pump = 1</b> ) </td>

    </tr>

    <tr>

      <td>fuel_dump_rate</td>

      <td>Percent of fuel that can be dumped per second. </td>

      <td>Airbus A321( <b>fuel_dump_rate = 0.0167</b>
) </td>

    </tr>

    <tr>

      <td>engine_driven_pump</td>

      <td>Set to 0 if the pump is engine driven (1 is the
default). </td>

      <td>Aircreation582SL( <b>engine_driven_pump=0</b>
)<br>

DeHavilland Beaver DHC2( <b>engine_driven_pump=1</b> ) </td>

    </tr>

    <tr>

      <td>manual_pump</td>

      <td>Set to 1 if there is a manual transfer pump.</td>

      <td>DeHavilland Beaver DHC2( <b>manual_transfer_pump=1</b>
) </td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">anemometer_pump</td>

      <td align="undefined" valign="undefined">Set
to 1 if there is an anemometer pump.</td>

      <td align="undefined" valign="undefined">(From <i>Flight Simulator 2004</i>)<br>

Vickers Vimy Transatlantic( <b>anemometer_pump=1</b> ) </td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId548772"></a>[airplane_geometry]</h4>

<p>This section has been added mainly
for reference. Although you can edit
these values by hand here in the aircraft.cfg file, modification of
some of these variables will have little to no effect on airplane
performance, as the flight model aerodynamic coefficients are
all&nbsp;located in the&nbsp;.air file.&nbsp;</p>

<p></p>

<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>      </td>

      <td>
      <h5>Description </h5>      </td>

      <td>
      <h5>Examples</h5>      </td>
    </tr>

    <tr>

      <td>wing_area</td>

      <td>Area of the top surface of the entire wing tip-to-tip
(ft2). </td>

      <td>Airbus A321( <b>wing_area = 1137.0</b> )<br>

Aircreation582SL( <b>wing_area= 150.000</b> )<br>

Boeing 747-400( <b>wing_area = 5825.0</b> )<br>

Beech Baron 58( <b>wing_area = 199.0</b> ) </td>
    </tr>

    <tr>

      <td>wing_span</td>

      <td>Wing span is the horizontal distance from wing-tip to
wing-tip (feet). </td>

      <td>Airbus A321( <b>wing_span = 94.75</b> )<br>

Aircreation582SL( <b>wing_span= 30.000</b> )<br>

Boeing 747-400( <b>wing_span = 211.4</b> )<br>

Beech Baron 58( <b>wing_span = 37.8</b> ) </td>
    </tr>

    <tr>

      <td>wing_root_chord</td>

      <td>Length of the wing chord (leading edge to trailing
edge) at the intersection of the wing and the fuselage (feet). </td>

      <td>Airbus A321( <b>wing_root_chord = 18.0</b>
)<br>

Aircreation582SL( <b>wing_root_chord= 5.000</b> )<br>

Boeing 747-400( <b>wing_root_chord = 48.8</b> )<br>

Beech Baron 58( <b>wing_root_chord = 5.3</b> ) </td>
    </tr>

    <tr>

      <td>wing_dihedral</td>

      <td>When looking at the front of an aircraft, this is the
angle between the wing leading edge and a horizontal line parallel to
the ground (degrees). </td>

      <td>Airbus A321( <b>wing_dihedral = 6.2</b> )<br>

Aircreation582SL( <b>wing_dihedral= 7.998</b> )<br>

Boeing 747-400( <b>wing_dihedral = 7.0</b> )<br>

Beech Baron 58( <b>wing_dihedral = 6.9</b> ) </td>
    </tr>

    <tr>

      <td>wing_incidence</td>

      <td>When looking at the side of an aircraft from the wing
tip, this is the angle the mean wing chord makes with a horizontal line
parallel to the ground, (degrees). Note: this parameter is not used in
the real-time aerodynamic calculations, as it is already factored into
the lift and drag parameters. </td>

      <td>Airbus A321( <b>wing_incidence = 1.0</b> )<br>

Aircreation582SL( <b>wing_incidence= 0.000</b> )<br>

Boeing 747-400( <b>wing_incidence = 2.0</b> )<br>

Cessna Skyhawk 172SP( <b>wing_incidence = 1.5</b> ) </td>
    </tr>

    <tr>

      <td>wing_twist</td>

      <td>This is the difference in wing incidence from the root
chord and the tip chord of the wing, (degrees). Also known as wash-out.      </td>

      <td>Airbus A321( <b>wing_twist = -0.5</b> )<br>

Aircreation582SL( <b>wing_twist= -1.000</b> )<br>

Boeing 747-400( <b>wing_twist = -1.0</b> )<br>

Beech King Air 350( <b>wing_twist = -1.5</b> ) </td>
    </tr>

    <tr>

      <td>oswald_efficiency_factor</td>

      <td>This is a measure of the aerodynamic efficiency of the
wing. A theoretically perfect wing will have a factor of 1.0. </td>

      <td>Aircreation582SL( <b>oswald_efficiency_factor=
0.750</b> )<br>

Boeing 747-400( <b>oswald_efficiency_factor= 0.68</b> )<br>

Beech Baron 58( <b>oswald_efficiency_factor= 0.7</b> ) </td>
    </tr>

    <tr>

      <td>wing_winglets_flag</td>

      <td>Boolean to indicate if the aircraft incorporates the
use of winglets; 0 = FALSE, 1 = TRUE. </td>

      <td>Aircreation582SL( <b>wing_winglets_flag= 0</b>
)<br>

Boeing 747-400( <b>wing_winglets_flag = 1</b> ) </td>
    </tr>

    <tr>

      <td>wing_sweep</td>

      <td>When looking down on top of an aircraft, this is the
angle the wing leading edge makes with a horizontal line perpendicular
to the fuselage, (degrees). </td>

      <td>Airbus A321( <b>wing_sweep = 25.0</b> )<br>

Boeing 747-400( <b>wing_sweep = 37.5</b> )<br>

Beech Baron 58( <b>wing_sweep = 0.0</b> ) </td>
    </tr>

    <tr>

      <td>wing_pos_apex_lon</td>

      <td>Longitudinal distance of the wing apex (measured at
centerline of aircraft) from defined reference point (feet). This
distance is measured positive in the forward (out the aircraft nose)
direction. </td>

      <td>Airbus A321( <b>wing_pos_apex_lon = 8.0</b>
)<br>

Aircreation582SL( <b>wing_pos_apex_lon= 0.000</b> )<br>

Boeing 747-400( <b>wing_pos_apex_lon = -58.2</b> )<br>

Beech Baron 58( <b>wing_pos_apex_lon = -5.6</b> ) </td>
    </tr>

    <tr>

      <td>wing_pos_apex_vert</td>

      <td>Vertical distance of the wing apex (measured at
centerline of aircraft) from defined reference point (feet). This
distance is measured positive in the up direction. </td>

      <td>Boeing 747-400( <b>wing_pos_apex_vert = 0</b>
)<br>

Bombardier CRJ 700( <b>wing_pos_apex_vert = -3.6</b> ) </td>
    </tr>

    <tr>

      <td>htail_area</td>

      <td>Area of the top surface of the entire horizontal tail
(tip-to-tip) (ft2). </td>

      <td>Airbus A321( <b>htail_area = 338.0</b> )<br>

Aircreation582SL( <b>htail_area= 28.000</b> )<br>

Boeing 747-400( <b>htail_area = 1470</b> )<br>

Beech Baron 58( <b>htail_area = 60.0</b> ) </td>
    </tr>

    <tr>

      <td>htail_span</td>

      <td>Horizontal tail span is the horizontal distance from
horizontal tail-tip to horizontal tail -tip (feet). </td>

      <td>Airbus A321( <b>htail_span = 41.7</b> )<br>

Aircreation582SL( <b>htail_span= 7.917</b> )<br>

Boeing 747-400( <b>htail_span = 72.8</b> )<br>

Beech Baron 58( <b>htail_span = 15.9</b> ) </td>
    </tr>

    <tr>

      <td>htail_pos_lon</td>

      <td>Longitudinal distance of the horizontal tail apex
(measured at centerline of aircraft) from defined reference point
(feet). This distance is measured positive in the forward (out the
aircraft nose) direction. </td>

      <td>Airbus A321( <b>htail_pos_lon = -35.0</b> )<br>

Aircreation582SL( <b>htail_pos_lon= -11.417</b> )<br>

Boeing 747-400( <b>htail_pos_lon = -210.0</b> )<br>

Beech Baron 58( <b>htail_pos_lon = -20.1</b> ) </td>
    </tr>

    <tr>

      <td>htail_pos_vert</td>

      <td>Vertical distance of the horizontal tail apex (measured
at centerline of aircraft) from defined reference point, (feet). This
distance is measured&nbsp;positive in the up direction. </td>

      <td>Airbus A321( <b>htail_pos_vert = 0.0</b> )<br>

Bombardier CRJ 700( <b>htail_pos_vert = 12.7</b> )<br>

DeHavilland Beaver DHC2( <b>htail_pos_vert = 0.9</b> ) </td>
    </tr>

    <tr>

      <td>htail_incidence</td>

      <td>When looking at the side of an aircraft from the
horizontal tail tip, this is the angle the mean horizontal tail chord
makes with a horizontal line parallel to the ground (degrees). </td>

      <td>Aircreation582SL( <b>htail_incidence= 0.000</b>
)<br>

Beech Baron 58( <b>htail_incidence = 0.5</b> )<br>

Bombardier CRJ 700( <b>htail_incidence = 4.0</b> ) </td>
    </tr>

    <tr>

      <td>htail_sweep</td>

      <td>When looking down on top of an aircraft, this is the
angle the horizontal tail leading edge makes with a horizontal line
perpendicular to the fuselage (degrees). </td>

      <td>Airbus A321( <b>htail_sweep = 30.0</b> )<br>

Boeing 747-400( <b>htail_sweep = 37.5</b> )<br>

Beech Baron 58( <b>htail_sweep = 0.0</b> ) </td>
    </tr>

    <tr>

      <td>vtail_area</td>

      <td>Area of the surface of one side of the vertical tail
(fuselage-to-tip) (ft2). </td>

      <td>Airbus A321( <b>vtail_area = 224.0</b> )<br>

Aircreation582SL( <b>vtail_area= 7.000</b> )<br>

Boeing 747-400( <b>vtail_area = 1060</b> )<br>

Beech Baron 58( <b>vtail_area = 88.0</b> ) </td>
    </tr>

    <tr>

      <td>vtail_span</td>

      <td>Vertical tail span is the vertical distance from the
vertical tail-fuselage intersection to the tip of the vertical tail
(feet). </td>

      <td>Airbus A321( <b>vtail_span = 20.0</b> )<br>

Aircreation582SL( <b>vtail_span= 3.017</b> )<br>

Boeing 747-400( <b>vtail_span = 37.1</b> )<br>

Beech Baron 58( <b>vtail_span = 10.7</b> ) </td>
    </tr>

    <tr>

      <td>vtail_sweep</td>

      <td>When looking at the side of the vertical tail, this is
the angle the vertical tail leading edge makes with a vertical line
perpendicular to the fuselage (degrees). </td>

      <td>Airbus A321( <b>vtail_sweep = 35.0</b> )<br>

Boeing 747-400( <b>vtail_sweep = 45.0</b> )<br>

Beech Baron 58( <b>vtail_sweep = 0.0</b> ) </td>
    </tr>

    <tr>

      <td>vtail_pos_lon</td>

      <td>Longitudinal distance of the vertical tail apex
(measured at centerline of aircraft) from defined reference point,
(feet). This distance is measured positive in the forward (out the
aircraft nose) direction. </td>

      <td>Airbus A321( <b>vtail_pos_lon = -35.8</b> )<br>

Aircreation582SL( <b>vtail_pos_lon= -11.417</b> )<br>

Boeing 747-400( <b>vtail_pos_lon = -198.5</b> )<br>

Beech Baron 58( <b>vtail_pos_lon = -22.9</b> ) </td>
    </tr>

    <tr>

      <td>vtail_pos_vert</td>

      <td>Vertical distance of the vertical tail apex (measured
at centerline of aircraft) from defined reference point (feet). This
distance is measured positive in the up direction. </td>

      <td>Airbus A321( <b>vtail_pos_vert = 5.8</b> )<br>

Aircreation582SL( <b>vtail_pos_vert= 1.500</b> )<br>

Boeing 747-400( <b>vtail_pos_vert = 26.1</b> )<br>

Beech Baron 58( <b>vtail_pos_vert = 3.1</b> ) </td>
    </tr>

    <tr>

      <td>elevator_area</td>

      <td>Area of the top surface of the entire elevator
(tip-to-tip) (ft2). </td>

      <td>Airbus A321( <b>elevator_area = 70.5</b> )<br>

Aircreation582SL( <b>elevator_area= 12.040</b> )<br>

Boeing 747-400( <b>elevator_area = 327</b> )<br>

Beech Baron 58( <b>elevator_area = 20.0</b> ) </td>
    </tr>

    <tr>

      <td>aileron_area</td>

      <td>Area of the top surface of all the ailerons on the wing
(ft2). </td>

      <td>Airbus A321( <b>aileron_area = 26.9</b> )<br>

Aircreation582SL( <b>aileron_area= 15.000</b> )<br>

Boeing 747-400( <b>aileron_area = 225</b> )<br>

Beech Baron 58( <b>aileron_area = 11.3</b> ) </td>
    </tr>

    <tr>

      <td>rudder_area</td>

      <td>Area of the side surface of the entire rudder (ft2). </td>

      <td>Airbus A321( <b>rudder_area = 56.2</b> )<br>

Aircreation582SL( <b>rudder_area= 2.450</b> )<br>

Boeing 747-400( <b>rudder_area = 230</b> )<br>

Beech Baron 58( <b>rudder_area = 10.5</b> ) </td>
    </tr>

    <tr>

      <td>elevator_up_limit</td>

      <td>Angular limit of the elevator when deflected up
(degrees). </td>

      <td>Airbus A321( <b>elevator_up_limit = 22.5</b>
)<br>

Aircreation582SL( <b>elevator_up_limit= 27.502</b> )<br>

Boeing 747-400( <b>elevator_up_limit = 25</b> )<br>

Beech Baron 58( <b>elevator_up_limit = 17.0</b> ) </td>
    </tr>

    <tr>

      <td>elevator_down_limit</td>

      <td>Angular limit of the elevator when deflected down
(degrees). </td>

      <td>Airbus A321( <b>elevator_down_limit = 19.5</b>
)<br>

Aircreation582SL( <b>elevator_down_limit= 20.626</b> )<br>

Boeing 747-400( <b>elevator_down_limit = 15</b> )<br>

Beech Baron 58( <b>elevator_down_limit = 15.5</b> ) </td>
    </tr>

    <tr>

      <td>aileron_up_limit</td>

      <td>Angular limit of the aileron when deflected up
(degrees). </td>

      <td>Airbus A321( <b>aileron_up_limit = 20.0</b>
)<br>

Aircreation582SL( <b>aileron_up_limit= 19.481</b> )<br>

Boeing 747-400( <b>aileron_up_limit = 25</b> )<br>

Beech Baron 58( <b>aileron_up_limit = 18.0</b> ) </td>
    </tr>

    <tr>

      <td>aileron_down_limit</td>

      <td>Angular limit of the aileron when deflected down
(degrees). </td>

      <td>Airbus A321( <b>aileron_down_limit = 20.0</b>
)<br>

Aircreation582SL( <b>aileron_down_limit= 14.897</b> )<br>

Boeing 747-400( <b>aileron_down_limit = 15</b> )<br>

Beech Baron 58( <b>aileron_down_limit = 18.0</b> ) </td>
    </tr>

    <tr>

      <td>rudder_limit</td>

      <td>Angular limit of the rudder deflection (degrees). </td>

      <td>Airbus A321( <b>rudder_limit = 26.0</b> )<br>

Aircreation582SL( <b>rudder_limit= 23.491</b> )<br>

Boeing 747-400( <b>rudder_limit = 31.5</b> )<br>

Beech Baron 58( <b>rudder_limit = 30.0</b> ) </td>
    </tr>

    <tr>

      <td>elevator_trim_limit</td>

      <td>Angular limit of the elevator trim tab (degrees). </td>

      <td>Airbus A321( <b>elevator_trim_limit = 20.0</b>
)<br>

Aircreation582SL( <b>elevator_trim_limit= 20.000</b> )<br>

Boeing 747-400( <b>elevator_trim_limit = 20</b> )<br>

Beech Baron 58( <b>elevator_trim_limit = 15.0</b> ) </td>
    </tr>

    <tr>

      <td>spoiler_limit</td>

      <td>Angular limit of the wing spoilers on an aircraft,
(degrees). If this limit is zero, no spoilers exist for the aircraft. </td>

      <td>Airbus A321( <b>spoiler_limit = 60.0</b> )<br>

Aircreation582SL( <b>spoiler_limit= 59.989</b> )<br>

Boeing 747-400( <b>spoiler_limit = 45</b> )<br>

Beech Baron 58( <b>spoiler_limit = 0.0</b> ) </td>
    </tr>

    <tr>

      <td>spoiler_extension_time</td>

      <td>Spoiler extension time in seconds. </td>

      <td>Airbus A321( <b>spoiler_extension_time = 2.0</b>
)<br>

Aircreation582SL( <b>spoiler_extension_time=5.000000</b> )<br>

Cessna Grand Caravan( <b>spoiler_extension_time = 0.2</b> )<br>

DG808S( <b>spoiler_extension_time = 1.0</b> ) </td>
    </tr>

    <tr>

      <td>spoilerons_available</td>

      <td>Boolean to indicate if the spoilers also behave as
spoilerons for roll control (if spoilers are available): 0 = FALSE, 1 =
TRUE. </td>

      <td>Airbus A321( <b>spoilerons_available = 1</b>
)<br>

Aircreation582SL( <b>spoilerons_available= 0</b> )<br>

Beech Baron 58( <b>spoilerons_available = 0</b> ) </td>
    </tr>

    <tr>

      <td>aileron_to_spoileron_gain</td>

      <td>If spoilerons are available, this value is the constant
used in determining the amount of spoiler deflection per aileron
deflection. </td>

      <td>Airbus A321( <b>aileron_to_spoileron_gain = 3</b>
)<br>

Beech Baron 58( <b>aileron_to_spoileron_gain = 0</b> )<br>

Bombardier CRJ 700( <b>aileron_to_spoileron_gain = 4.6</b>
) </td>
    </tr>

    <tr>

      <td>min_ailerons_for_spoilerons</td>

      <td>This value indicates at what aileron deflection the
spoilers are become active for roll control, (degrees). </td>

      <td>Airbus A321( <b>min_ailerons_for_spoilerons = 10</b>
)<br>

Beech Baron 58( <b>min_ailerons_for_spoilerons = 0</b> )<br>

Bombardier CRJ 700( <b>min_ailerons_for_spoilerons = 5</b>
) </td>
    </tr>

    <tr>

      <td>min_flaps_for_spoilerons</td>

      <td>This value indicates at what minimum flap handle
position the spoilerons become active. </td>

      <td>Bombardier CRJ 700( <b>min_flaps_for_spoilerons=
0.0</b> ) </td>
    </tr>

    <tr>

      <td>auto_spoiler_available</td>

      <td>Set to 1 if auto spoiler is available. </td>

      <td>Airbus A321( <b>auto_spoiler_available = 1</b>
)<br>

Beech Baron 58( <b>auto_spoiler_available = 0</b> ) </td>
    </tr>

    <tr>

      <td>positive_g_limit_flaps_up</td>

      <td>Design g load tolerance (flaps up). </td>

      <td>Airbus A321( <b>positive_g_limit_flaps_up = 4.0</b>
)<br>

Beech Baron 58( <b>positive_g_limit_flaps_up = 3.0</b> )<br>

DG808S( <b>positive_g_limit_flaps_up = 5.5</b> ) </td>
    </tr>

    <tr>

      <td>positive_g_limit_flaps_down</td>

      <td>Design g load tolerance (flaps down). </td>

      <td>Airbus A321( <b>positive_g_limit_flaps_down= 3.0</b>
)<br>

Aircreation582SL( <b>positive_g_limit_flaps_down=2.000000</b>
)<br>

DG808S( <b>positive_g_limit_flaps_down= 5.5</b> ) </td>
    </tr>

    <tr>

      <td>negative_g_limit_flaps_up</td>

      <td>Design g load tolerance (negative, flaps up). </td>

      <td>Airbus A321( <b>negative_g_limit_flaps_up = -3.0</b>
)<br>

Beech Baron 58( <b>negative_g_limit_flaps_up = -2.0</b> )<br>

Cessna Skyhawk 172SP( <b>negative_g_limit_flaps_up = -1.5</b>
) </td>
    </tr>

    <tr>

      <td>negative_g_limit_flaps_down</td>

      <td>Design g load tolerance (negative, flaps down). </td>

      <td>Airbus A321( <b>negative_g_limit_flaps_down= -2.0</b>
)<br>

Cessna Skyhawk 172SP( <b>negative_g_limit_flaps_down= -1.5</b>
)<br>

DG808S( <b>negative_g_limit_flaps_down= -3.5</b> ) </td>
    </tr>

    <tr>

      <td>load_safety_factor</td>

      <td>Design g load safety factor. </td>

      <td>Airbus A321( <b>load_safety_factor = 1.5</b>
) </td>
    </tr>


    <tr>
      <td>fly_by_wire</td>
      <td>Fly by wire system available. </td>
      <td>Airbus A321<b> (fly_by_wire = 1) </b></td>
    </tr>
    <tr>

      <td>spoiler_handle_available</td>

      <td>Boolean that configures the airplane with manual
control of the spoiler deflections. 0 = FALSE, 1 = TRUE. </td>

      <td>Cessna Grand Caravan( <b>spoiler_handle_available
= 0</b> ) </td>
    </tr>

    <tr>

      <td>flap_to_aileron_scale</td>

      <td>Flaperons - deflection of ailerons due to flap
deflection. </td>

      <td>DeHavilland Beaver DHC2( <b>flap_to_aileron_scale
= 0.3</b> )<br>

DG808S( <b>flap_to_aileron_scale = 0.5</b> ) </td>
    </tr>

    <tr>

      <td align="undefined" valign="undefined">aileron_to_rudder_scale</td>

      <td align="undefined" valign="undefined">Link
the rudder to aileron input. </td>

      <td align="undefined" valign="undefined">(From <i>Flight Simulator 2004</i>)<br>

Wright Flyer( <b>aileron_to_rudder_scale = 0.4</b> ) </td>
    </tr>
  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId16333"></a>[reference
speeds]</h4>

<p>The values given in this section are mainly for reference, as
the performance of the aircraft is held in the .air file.</p>

<p></p>

<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>flaps_up_stall_speed</td>

      <td>Stall speed of the aircraft in a clean (flaps up)
configuration at standard sea level conditions, (Knots True Airspeed,
KTAS). </td>

      <td>Airbus A321( <b>flaps_up_stall_speed = 142.0</b>
)<br>

Aircreation582SL( <b>flaps_up_stall_speed= 24.000</b> )<br>

Boeing 747-400( <b>flaps_up_stall_speed = 140.0</b> )<br>

Beech Baron 58( <b>flaps_up_stall_speed = 84.0</b> ) </td>

    </tr>

    <tr>

      <td>full_flaps_stall_speed</td>

      <td>Stall speed of the aircraft in a dirty (flaps full
down) configuration at standard sea level conditions, (Knots True
Airspeed, KTAS). </td>

      <td>Airbus A321( <b>full_flaps_stall_speed = 113.0</b>
)<br>

Aircreation582SL( <b>full_flaps_stall_speed= 24.000</b> )<br>

Boeing 747-400( <b>full_flaps_stall_speed = 112.0</b> )<br>

Beech Baron 58( <b>full_flaps_stall_speed = 75.0</b> ) </td>

    </tr>

    <tr>

      <td>cruise_speed</td>

      <td>Typical cruise speed of the aircraft in a clean (flaps
up) configuration at a typical cruise altitude, (Knots True Airspeed,
KTAS). </td>

      <td>Airbus A321( <b>cruise_speed = 477.0</b> )<br>

Aircreation582SL( <b>cruise_speed= 84.560</b> )<br>

Boeing 747-400( <b>cruise_speed = 505.0</b> )<br>

Beech Baron 58( <b>cruise_speed = 180.0</b> ) </td>

    </tr>

    <tr>

      <td>max_mach</td>

      <td>Maximum design mach of the aircraft. This generally
only applies to turbine airplanes. </td>

      <td>Airbus A321( <b>max_mach = 0.82</b> )<br>

Boeing 747-400( <b>max_mach = 0.92</b> )<br>

Beech King Air 350( <b>max_mach = 0.58</b> )<br>

Bombardier CRJ 700( <b>max_mach = 0.83</b> ) </td>

    </tr>

    <tr>

      <td>max_indicated_speed</td>

      <td>Maximum design indicated airspeed. Also referred to as
Never Exceed Speed or Red Line of the aircraft, (Knots Indicated
Airspeed). </td>

      <td>Airbus A321( <b>max_indicated_speed = 340</b>
)<br>

Aircreation582SL( <b>max_indicated_speed=65.000000</b> )<br>

Boeing 747-400( <b>max_indicated_speed = 365.0</b> )<br>

Beech Baron 58( <b>max_indicated_speed = 223</b> ) </td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId567955"></a>[forcefeedback]</h4>

As detailed in the tables below, the parameters in this
section of an aircraft.cfg file define the forces generated by that
aircraft if the user is operating a force feedback joystick.<br>

<h5>Stick shaker parameters</h5>

These parameters define the simulated stick shaker force felt in the
stick or yoke when flying an aircraft equipped with a stick shaker
(such as the Learjet 45).<br>

<h5>Gear bump parameters</h5>

These parameters define the simulated forces transferred from the
airframe and gear drag to the stick or yoke when the
aircraft&rsquo;s nose and main landing gear is raised or lowered
(cycled). In fixed-gear aircraft this effect won't be felt because, by
definition, the landing gear doesn't move. Different aircraft have
different gear geometries that result in each of the gear mechanisms
starting and ending its cycle at a different time. The timing deltas
are brief, typically less than a second between the time that each gear
starts and ends its cycle.<br>

<h5>Ground bumps parameters</h5>

These parameters collectively define a composite force that simulates
the forces felt through an aircraft's ground steering controls as the
aircraft travels over an uneven surface. The parameters are divided
into two subgroups (numbered 1 and 2), and define the behavior of two
distinct forces. The combination of the two forces define a
composite force that is transferred to the stick or yoke. The two
forces are both sinusoidal periodic forces, with frequencies determined
by the following linear equation:<br>

<ul>

  <li>frequency = (ground_bumps_slope * aircraft_ground_speed) +
ground_bumps_intercept</li>

</ul>

The ground_bumps_magnitude parameters set the magnitude of the force.
The ground_bumps_angle parameters set the direction from which the
force is felt.<br>

<h5>Crash parameters</h5>

These parameters define the simulated forces felt in the stick or yoke
when the aircraft crashes. The parameters are divided into two
subgroups (numbered 1 and 2), and define the behavior of two distinct
crash-induced forces. The first force is a constant force that lasts
for 0.5 seconds. After 0.5 seconds, it stops and the second force
starts. The second force is a periodic square wave force; its amplitude
declines linearly to 0.<br>

<br>

<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>gear_bump_nose_magnitude</td>

      <td>Integer from 0 - 10000. </td>

      <td>Airbus A321( <b>gear_bump_nose_magnitude=3000</b>
)<br>

Aircreation582SL( <b>gear_bump_nose_magnitude=6000</b> ) </td>

    </tr>

    <tr>

      <td>gear_bump_nose_direction</td>

      <td>Integer from 0 - 35999 degrees. </td>

      <td>Airbus A321( <b>gear_bump_nose_direction=18000</b>
) </td>

    </tr>

    <tr>

      <td>gear_bump_nose_duration</td>

      <td>Integer,&nbsp;microseconds. </td>

      <td>Airbus A321( <b>gear_bump_nose_duration=250000</b>
) </td>

    </tr>

    <tr>

      <td>gear_bump_left_magnitude</td>

      <td>Integer from 0 - 10000. </td>

      <td>Airbus A321( <b>gear_bump_left_magnitude=2700</b>
)<br>

Aircreation582SL( <b>gear_bump_left_magnitude=6000</b> ) </td>

    </tr>

    <tr>

      <td>gear_bump_left_direction</td>

      <td>Integer from 0 - 35999 degrees. </td>

      <td>Airbus A321( <b>gear_bump_left_direction=35500</b>
)<br>

Beech Baron 58( <b>gear_bump_left_direction=9000</b> ) </td>

    </tr>

    <tr>

      <td>gear_bump_left_duration</td>

      <td>Integer, microseconds. </td>

      <td>Airbus A321( <b>gear_bump_left_duration=250000</b>
) </td>

    </tr>

    <tr>

      <td>gear_bump_right_magnitude</td>

      <td>Integer from 0 - 10000. </td>

      <td>Airbus A321( <b>gear_bump_right_magnitude=2700</b>
)<br>

Aircreation582SL( <b>gear_bump_right_magnitude=6000</b> ) </td>

    </tr>

    <tr>

      <td>gear_bump_right_direction</td>

      <td>Integer from 0 - 35999 degrees. </td>

      <td>Airbus A321( <b>gear_bump_right_direction=00500</b>
)<br>

Beech Baron 58( <b>gear_bump_right_direction=27000</b> ) </td>

    </tr>

    <tr>

      <td>gear_bump_right_duration</td>

      <td>Integer, microseconds. </td>

      <td>Airbus A321( <b>gear_bump_right_duration=250000</b>
) </td>

    </tr>

    <tr>

      <td>ground_bumps_magnitude1</td>

      <td>Integer from 0 - 10000. </td>

      <td>Airbus A321( <b>ground_bumps_magnitude1=1300</b>
)<br>

Aircreation582SL( <b>ground_bumps_magnitude1=3250</b> )<br>

DG808S( <b>ground_bumps_magnitude1=2500</b> )<br>

Douglas DC-3( <b>ground_bumps_magnitude1=2600</b> ) </td>

    </tr>

    <tr>

      <td>ground_bumps_angle1</td>

      <td>Integer from 0 - 35999 degrees. </td>

      <td>Aircreation582SL( <b>ground_bumps_angle1=8900</b>
) </td>

    </tr>

    <tr>

      <td>ground_bumps_intercept1</td>

      <td>Floating point number, from 0 to 1,000,000 cycles
pInteger
fromer second.</td>

      <td>Airbus A321( <b>ground_bumps_intercept1=3.0</b>
)<br>

Aircreation582SL( <b>ground_bumps_intercept1=5.0</b> )<br>

DG808S( <b>ground_bumps_intercept1=10.0</b> )<br>

Extra 300S( <b>ground_bumps_intercept1=4.0</b> ) </td>

    </tr>

    <tr>

      <td>ground_bumps_slope1</td>

      <td>Floating point number, from 0 to 1,000,000 cycles
pInteger fromer second.</td>

      <td>Airbus A321( <b>ground_bumps_slope1=0.20</b>
)<br>

Aircreation582SL( <b>ground_bumps_slope1=0.48</b> )<br>

DG808S( <b>ground_bumps_slope1=0.300</b> )<br>

Douglas DC-3( <b>ground_bumps_slope1=0.6</b> ) </td>

    </tr>

    <tr>

      <td>ground_bumps_magnitude2</td>

      <td>Integer from 0 - 10000. </td>

      <td>Airbus A321( <b>ground_bumps_magnitude2=200</b>
)<br>

Aircreation582SL( <b>ground_bumps_magnitude2=750</b> )<br>

DG808S( <b>ground_bumps_magnitude2=350</b> )<br>

Douglas DC-3( <b>ground_bumps_magnitude2=1200</b> ) </td>

    </tr>

    <tr>

      <td>ground_bumps_angle2</td>

      <td>0 - 35999 degrees. </td>

      <td>Airbus A321( <b>ground_bumps_angle2=09100</b>
)<br>

Aircreation582SL( <b>ground_bumps_angle2=9100</b> ) </td>

    </tr>

    <tr>

      <td>ground_bumps_intercept2</td>

      <td>Floating point number, from 0 to 1,000,000 cycles
pInteger fromer second.</td>

      <td>Airbus A321( <b>ground_bumps_intercept2=1.075</b>
)<br>

Aircreation582SL( <b>ground_bumps_intercept2=0.075</b> )<br>

Bombardier CRJ 700( <b>ground_bumps_intercept2 =1.075</b> )<br>

Douglas DC-3( <b>ground_bumps_intercept2=0.085</b> ) </td>

    </tr>

    <tr>

      <td>ground_bumps_slope2</td>

      <td>Floating point number, from 0 to 1,000,000 cycles
pInteger fromer second.</td>

      <td>Airbus A321( <b>ground_bumps_slope2=0.035</b>
)<br>

Aircreation582SL( <b>ground_bumps_slope2=1.0</b> )<br>

Douglas DC-3( <b>ground_bumps_slope2=0.65</b> )<br>

Extra 300S( <b>ground_bumps_slope2=0.7</b> ) </td>

    </tr>

    <tr>

      <td>crash_magnitude1</td>

      <td>Sets the magnitude of the first force, from 0 to 10000.
      </td>

      <td>Airbus A321( <b>crash_magnitude1=10000</b>
) </td>

    </tr>

    <tr>

      <td>crash_direction1</td>

      <td>Sets the direction from which first force is felt, from
0 to 35999. </td>

      <td>Airbus A321( <b>crash_direction1=01000</b>
) </td>

    </tr>

    <tr>

      <td>crash_magnitude2</td>

      <td>Sets the initial magnitude of the second force, from 0
to 10000. </td>

      <td>Airbus A321( <b>crash_magnitude2=10000</b>
) </td>

    </tr>

    <tr>

      <td>crash_direction2</td>

      <td>Sets the direction from which the second force is felt,
from 0 to 35999. </td>

      <td>Airbus A321( <b>crash_direction2=9000</b>
) </td>

    </tr>

    <tr>

      <td>crash_period2</td>

      <td>Determines the frequency (frequency = 1/period) of the
second crash force, in microseconds. </td>

      <td>Airbus A321( <b>crash_period2=75000</b> ) </td>

    </tr>

    <tr>

      <td>crash_duration2</td>

      <td>Sets the amount of time that the second crash force is
felt, in microseconds. </td>

      <td>Airbus A321( <b>crash_duration2=2500000</b>
)<br>

Douglas DC-3( <b>crash_duration2=3500000</b> ) </td>

    </tr>

    <tr>

      <td>stick_shaker_magnitude</td>

      <td>Integer from 0 - 10000. </td>

      <td>Beech Baron 58( <b>stick_shaker_magnitude=5000</b>
) </td>

    </tr>

    <tr>

      <td>stick_shaker_direction</td>

      <td>Integer from 0 - 35999 degrees. </td>

      <td>Beech Baron 58( <b>stick_shaker_direction=0</b>
) </td>

    </tr>

    <tr>

      <td>stick_shaker_period</td>

      <td>In microseconds. </td>

      <td>Beech Baron 58( <b>stick_shaker_period=111111</b>
) </td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId74684"></a>[stall_warning]</h4>

<p>This section defines the stall warning system of the aircraft.</p>
<p>&nbsp;</p>
<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>type</td>

      <td>This flag determines the type of stall warning system,
one of:<br>

0 = None<br>

1 = Suction<br>

2 = Electric </td>

      <td>Airbus A321( <b>type=2</b> )<br>

Aircreation582SL( <b>type=0</b> )<br>

Cessna Skyhawk 172SP( <b>type=1</b> ) </td>

    </tr>

    <tr>

      <td>stick_shaker</td>

      <td>Set to 1 if the aircraft has a stick shaker.</td>

      <td>Airbus A321( <b>stick_shaker=1</b> )<br>

Aircreation582SL( <b>stick_shaker=0</b> ) </td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId14561"></a>[deice_system]</h4>

<p>This section defines the deice system of the aircraft.</p>
<p>&nbsp;</p>
<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>structural_deice_type</td>

      <td>Type of deicer, of one:<br>

0 = None<br>

1 = Heated Leading Edge<br>

2 = Bleed Air Boots<br>

3 = Eng Pump Boots. </td>

      <td>Airbus A321( <b>structural_deice_type=1</b>
)<br>

Aircreation582SL( <b>structural_deice_type=0</b> )<br>

Beech Baron 58( <b>structural_deice_type=3</b> )<br>

Beech King Air 350( <b>structural_deice_type=2</b> ) </td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId57822"></a>[piston_engine]</h4>

<p>A piston engine&rsquo;s power can be determined through a
series of equations that represent the&nbsp;Otto cycle
of a four-stroke piston engine, multiplied by the number of pistons
available.&nbsp; This section contains all the information <span style="font-style: italic;">Flight
Simulator</span> needs to be able to determine how much power the
engines are
capable of producing.&nbsp;&nbsp;Power can also be scaled from
the
calculated values generated for piston engines with the
&ldquo;power_scalar&rdquo; value.</p>

<p></p>

<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>      </td>

      <td>
      <h5>Description </h5>      </td>

      <td>
      <h5>Examples</h5>      </td>
    </tr>

    <tr>

      <td>max_rpm_mechanical_efficiency_scalar</td>

      <td>Scalar value that can be modified to tune the
mechanical efficiency of the engine at maximum rpm. Increase this value
to increase the mechanical efficiency, decrease it to decrease the
mechanical efficiency. </td>

      <td>Beech Baron 58( <b>max_rpm_mechanical_efficiency_scalar=
1.0</b>
) </td>
    </tr>

    <tr>

      <td>idle_rpm_mechanical_efficiency_scalar</td>

      <td>Scalar value that can be modified to tune the
mechanical efficiency of the engine at idle rpm. Increase this value to
increase the mechanical efficiency, decrease it to decrease the
mechanical efficiency. </td>

      <td>Beech Baron 58( <b>idle_rpm_mechanical_efficiency_scalar=
1.0</b>
) </td>
    </tr>

    <tr>

      <td>max_rpm_friction_scalar</td>

      <td>Scalar value that can be modified to tune the internal
friction of the engine at maximum rpm. Increase this value to increase
the friction, decrease it to decrease the friction. </td>

      <td>Aircreation582SL( <b>max_rpm_friction_scalar=1.000</b>
)<br>      </td>
    </tr>

    <tr>

      <td>idle_rpm_friction_scalar</td>

      <td>Scalar value that can be modified to tune the internal
friction of the engine at idle rpm. Increase this value to increase the
friction, decrease it to decrease the friction, (can be used to tune
the rpm at which the engine idles). </td>

      <td>Aircreation582SL( <b>idle_rpm_friction_scalar=1.000</b>
)<br>      </td>
    </tr>

    <tr>

      <td>cylinder_displacement</td>

      <td>Cubic inches per cylinder displacement. </td>

      <td>Aircreation582SL( <b>cylinder_displacement=
55.000</b> )<br>

Beech Baron 58( <b>cylinder_displacement= 91.7</b> )<br>

Cessna Skyhawk 172SP( <b>cylinder_displacement= 90.0</b> )<br>

DeHavilland Beaver DHC2( <b>cylinder_displacement= 109.4</b>
) </td>
    </tr>

    <tr>
      <td>two_stroke_cycle</td>
      <td>Two stroke engine. </td>
      <td>Aircreation582SL Blue( <B>two_stroke_cycle = 1</B> )</td>
    </tr>
    <tr>

      <td>compression_ratio</td>

      <td>Compression ratio of each cylinder. </td>

      <td>Aircreation582SL( <b>compression_ratio= 11.500</b>
)<br>

Beech Baron 58( <b>compression_ratio= 8.0</b> )<br>

Cessna Skyhawk 172SP( <b>compression_ratio= 8.5</b> )<br>

DeHavilland Beaver DHC2( <b>compression_ratio= 6.0</b> ) </td>
    </tr>

    <tr>

      <td>number_of_cylinders</td>

      <td>Integer value; number of cylinders in the engine. </td>

      <td>Aircreation582SL( <b>number_of_cylinders= 2</b>
)<br>

Beech Baron 58( <b>number_of_cylinders= 6</b> )<br>

Cessna Skyhawk 172SP( <b>number_of_cylinders=4</b> )<br>

DeHavilland Beaver DHC2( <b>number_of_cylinders=9</b> ) </td>
    </tr>

    <tr>

      <td>max_rated_rpm</td>

      <td>Maximum rated revolutions per minute (RPM) of the
engine (red line). </td>

      <td>Aircreation582SL( <b>max_rated_rpm= 5500.000</b>
)<br>

Beech Baron 58( <b>max_rated_rpm= 2700.0</b> )<br>

Cessna Skyhawk 172SP( <b>max_rated_rpm= 2700</b> )<br>

DeHavilland Beaver DHC2( <b>max_rated_rpm= 2300</b> ) </td>
    </tr>

    <tr>

      <td>max_rated_hp</td>

      <td>Maximum rated brake horsepower output of the engine. </td>

      <td>Aircreation582SL( <b>max_rated_hp= 53.600</b>
)<br>

Beech Baron 58( <b>max_rated_hp= 300.0</b> )<br>

Cessna Skyhawk 172SP( <b>max_rated_hp= 180</b> )<br>

DeHavilland Beaver DHC2( <b>max_rated_hp= 450</b> ) </td>
    </tr>

    <tr>

      <td>fuel_metering_type</td>

      <td>Integer value indicating the fuel metering type, one of:<br>

0 =
Fuel Injected<br>

1 = Gravity Carburetor,<br>

2 = Aerobatic Carburetor. </td>

      <td>Aircreation582SL( <b>fuel_metering_type= 1</b>
)<br>

Beech Baron 58( <b>fuel_metering_type= 0</b> )<br>

DeHavilland Beaver DHC2( <b>fuel_metering_type = 1</b> ) </td>
    </tr>

    <tr>

      <td>cooling_type</td>

      <td>Integer value indicating the method of engine cooling,
one of:<br>

0 = air cooled<br>

1 = liquid cooled. </td>

      <td>Aircreation582SL( <b>cooling_type= 1</b> )<br>

Beech Baron 58( <b>cooling_type= 0</b> ) </td>
    </tr>

    <tr>

      <td>normalized_starter_torque</td>

      <td>This value can be modified to increase/decrease the
torque supplied by the starter to get the prop turning. Increase this
value for a greater torque effect, decrease it for a lower torque
setting. </td>

      <td>Beech Baron 58( <b>normalized_starter_torque= 0.3</b>
) </td>
    </tr>

    <tr>

      <td>turbocharged</td>

      <td>Boolean to indicate if the engine is turbocharged; 0 =
FALSE, 1 = TRUE. </td>

      <td>Aircreation582SL( <b>turbocharged= 0</b> )<br>

DeHavilland Beaver DHC2( <b>turbocharged= 1</b> ) </td>
    </tr>

    <tr>

      <td>max_design_mp</td>

      <td>If a turbocharger is present, this value indicates the
maximum design manifold pressure supplied by the turbocharger (inHg). </td>

      <td>Beech Baron 58( <b>max_design_mp= 0.0</b> )<br>

DeHavilland Beaver DHC2( <b>max_design_mp= 36.5</b> ) </td>
    </tr>

    <tr>

      <td>min_design_mp</td>

      <td>If a turbocharger is present, this value indicates the
minimum design manifold pressure of the turbocharger (inHg). </td>

      <td>Beech Baron 58( <b>min_design_mp= 1.0</b> )<br>

DeHavilland Beaver DHC2( <b>min_design_mp= 10</b> ) </td>
    </tr>

    <tr>

      <td>critical_altitude</td>

      <td>Altitude to which the turbocharger, if present, will
provide the maximum design manifold pressure (feet). </td>

      <td>Beech Baron 58( <b>critical_altitude= 0.0</b>
)<br>

DeHavilland Beaver DHC2( <b>critical_altitude= 5000</b> ) </td>
    </tr>

    <tr>

      <td>emergency_boost_type</td>

      <td>Integer value indicating the emergency boost type
available, one of:<br>

0 = None<br>

1 = Water Injection<br>

2 = Methanol/Water Injection<br>

3 = War Emergency Power, (typically used in WWII combat aircraft). </td>

      <td>Aircreation582SL( <b>emergency_boost_type= 0</b>
) </td>
    </tr>

    <tr>

      <td>emergency_boost_mp_offset</td>

      <td>Additional manifold pressure supplied by emergency
boost, if available. </td>

      <td>Aircreation582SL( <b>emergency_boost_mp_offset=
0.000</b> )</td>
    </tr>

    <tr>

      <td>emergency_boost_gain_offset</td>

      <td>Multiplier on manifold pressure due to emergency boost.      </td>

      <td>Aircreation582SL( <b>emergency_boost_gain_offset=
0.000</b> ) </td>
    </tr>

    <tr>

      <td>fuel_air_auto_mixture</td>

      <td>Boolean to indicate if automatic fuel-to-air mixture is
available; 0 = FALSE, 1 = TRUE. </td>

      <td>Aircreation582SL( <b>fuel_air_auto_mixture= 0</b>
) </td>
    </tr>

    <tr>

      <td>auto_ignition</td>

      <td>Boolean to indicate if automatic ignition is available;
0 = FALSE, 1 = TRUE. </td>

      <td>Aircreation582SL( <b>auto_ignition= 0</b>
) </td>
    </tr>

    <tr>

      <td>power_scalar</td>

      <td>Changing this value affects the amount of power
delivered by the engine to the propellor shaft. </td>

      <td>Beech Baron 58( <b>power_scalar = 1.0</b>
) </td>
    </tr>

    <tr>
      <td>bestpowerspecificfuelconsumption</td>
      <td>SFC at Best Power mixture ratio. </td>
      <td>Cessna Skyhawk 172SP Paint1( <B>BestPowerSpecificFuelConsumption=0.49</B> ) </td>
    </tr>
    <tr>

      <td>magneto_order_left_right_both</td>

      <td>Sets the order of the magneto switch direction. </td>

      <td>Douglas DC-3( <b>magneto_order_left_right_both =
1</b> ) </td>
    </tr>

    <tr>

      <td align="undefined" valign="undefined">number_of_magnetos</td>

      <td align="undefined" valign="undefined">Number
of magnetos.</td>

      <td align="undefined" valign="undefined">(From <i>Flight Simulator 2004)</i><br>

Curtiss Jenny( <b>number_of_magnetos = 1</b> ) </td>
    </tr>
  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId804485"></a>[propeller]</h4>

<p>The thrust generated by a given propeller is a function of the
power delivered through the propeller shaft, rpm, blade angle, airplane
speed, and ambient density.</p>

<p></p>

<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>propeller_type</td>

      <td>Integer that identifies what type of propeller is on
the aircraft, one of:<br>

0 = Constant Speed<br>

1 = Fixed Pitch. </td>

      <td>Aircreation582SL( <b>propeller_type= 1</b>
)<br>

Beech Baron 58( <b>propeller_type= 0</b> )<br>

Beech King Air 350( <b>propeller_type = 0</b> ) </td>

    </tr>

    <tr>

      <td>propeller_diameter</td>

      <td>Diameter of propeller blades, tip to tip, in feet. </td>

      <td>Aircreation582SL( <b>propeller_diameter= 5.000</b>
)<br>

Beech Baron 58( <b>propeller_diameter= 6.4</b> )<br>

Beech King Air 350( <b>propeller_diameter = 8.8</b> )<br>

Cessna Skyhawk 172SP( <b>propeller_diameter= 6.3</b> ) </td>

    </tr>

    <tr>

      <td>propeller_blades</td>

      <td>Integer value indicating the number of blades on the
propeller (2, 3 or 4). </td>

      <td>Aircreation582SL( <b>propeller_blades= 2</b>
)<br>

Beech Baron 58( <b>propeller_blades= 3</b> )<br>

Beech King Air 350( <b>propeller_blades = 4</b> )<br>

Cessna Grand Caravan( <b>propeller_blades = 3</b> ) </td>

    </tr>

    <tr>

      <td>propeller_moi</td>

      <td>Propeller moment of inertia, (slug ft2). </td>

      <td>Aircreation582SL( <b>propeller_moi= 3.000</b>
)<br>

Beech Baron 58( <b>propeller_moi= 6.9</b> )<br>

Beech King Air 350( <b>propeller_moi = 24</b> )<br>

Cessna Skyhawk 172SP( <b>propeller_moi= 5.0</b> ) </td>

    </tr>

    <tr>

      <td>beta_max</td>

      <td>Maximum blade pitch angle for constant speed prop
(degrees). (Not used if fixed pitch.). </td>

      <td>Aircreation582SL( <b>beta_max= 0</b> )<br>

Beech Baron 58( <b>beta_max= 45.0</b> )<br>

Beech King Air 350( <b>beta_max = 45</b> )<br>

DeHavilland Beaver DHC2( <b>beta_max= 24.0</b> ) </td>

    </tr>

    <tr>

      <td>beta_min</td>

      <td>Minimum blade pitch angle for constant speed prop
(degrees). (Not used if fixed pitch.). </td>

      <td>Aircreation582SL( <b>beta_min= 0</b> )<br>

Beech Baron 58( <b>beta_min= 15.2</b> )<br>

Beech King Air 350( <b>beta_min = 15.2</b> )<br>

Cessna Grand Caravan( <b>beta_min = 15.6</b> ) </td>

    </tr>

    <tr>

      <td>min_gov_rpm</td>

      <td>The minimum rpm controlled by the governor for a
constant speed prop. </td>

      <td>Aircreation582SL( <b>min_gov_rpm= 0</b> )<br>

Beech Baron 58( <b>min_gov_rpm= 1100.0</b> )<br>

Beech King Air 350( <b>min_gov_rpm = 25520</b> )<br>

DeHavilland Beaver DHC2( <b>min_gov_rpm= 800</b> ) </td>

    </tr>

    <tr>

      <td>prop_tc</td>

      <td>Time constant for prop. </td>

      <td>Aircreation582SL( <b>prop_tc= 0.100</b> )<br>

Beech Baron 58( <b>prop_tc= 0.1</b> )<br>

Beech King Air 350( <b>prop_tc = 0.004</b> )<br>

Cessna Skyhawk 172SP( <b>prop_tc= 0</b> ) </td>

    </tr>

    <tr>

      <td>gear_reduction_ratio</td>

      <td>The reduction ratio from the engine output rpm to prop
rpm. </td>

      <td>Aircreation582SL( <b>gear_reduction_ratio= 1.000</b>
)<br>

Beech Baron 58( <b>gear_reduction_ratio= 1.0</b> )<br>

Beech King Air 350( <b>gear_reduction_ratio = 17.6</b> )<br>

Cessna Grand Caravan( <b>gear_reduction_ratio = 17.4</b> )
      </td>

    </tr>

    <tr>

      <td>fixed_pitch_beta</td>

      <td>Blade pitch angle for fixed pitch prop (degrees). (Not
used if constant speed.). </td>

      <td>Aircreation582SL( <b>fixed_pitch_beta= 28.000</b>
)<br>

Beech Baron 58( <b>fixed_pitch_beta= 0.0</b> )<br>

Beech King Air 350( <b>fixed_pitch_beta = 0</b> )<br>

Cessna Skyhawk 172SP( <b>fixed_pitch_beta= 20</b> ) </td>

    </tr>

    <tr>

      <td>low_speed_theory_limit</td>

      <td>The speed at which low-speed propeller theory gets
blended into the high speed propeller theory, (feet/second). </td>

      <td>Aircreation582SL( <b>low_speed_theory_limit=
80.000</b> )<br>

Beech Baron 58( <b>low_speed_theory_limit= 80.0</b> )<br>

Beech King Air 350( <b>low_speed_theory_limit = 80</b> )<br>

Cessna Skyhawk 172SP( <b>low_speed_theory_limit= 80</b> ) </td>

    </tr>

    <tr>

      <td>prop_sync_available</td>

      <td>Boolean to indicate if propeller-sync is available
(twin engine aircraft); 0 = FALSE, 1 = TRUE. </td>

      <td>Aircreation582SL( <b>prop_sync_available= 0</b>
)<br>

Beech Baron 58( <b>prop_sync_available= 1</b> )<br>

Beech King Air 350( <b>prop_sync_available = 1</b> )<br>

Cessna Grand Caravan( <b>prop_sync_available = 0</b> ) </td>

    </tr>

    <tr>

      <td>prop_deice_available</td>

      <td>Boolean to indicate if propeller de-icing is available;
0 = FALSE, 1 = TRUE. </td>

      <td>Aircreation582SL( <b>prop_deice_available= 0</b>
)<br>

Beech Baron 58( <b>prop_deice_available= 1</b> )<br>

Beech King Air 350( <b>prop_deice_available = 1</b> ) </td>

    </tr>

    <tr>

      <td>prop_feathering_available</td>

      <td>Boolean to indicate if prop feathering is available
(constant speed prop only); 0 = FALSE, 1 = TRUE. </td>

      <td>Aircreation582SL( <b>prop_feathering_available= 0</b>
)<br>

Beech Baron 58( <b>prop_feathering_available= 1</b> ) </td>

    </tr>

    <tr>

      <td>prop_auto_feathering_available</td>

      <td>Boolean to indicate if prop auto-feathering is
available (constant speed prop only); 0 = FALSE, 1 = TRUE. </td>

      <td>Aircreation582SL( <b>prop_auto_feathering_available=
0</b> )<br>

Beech King Air 350( <b>prop_auto_feathering_available= 1</b>
) </td>

    </tr>

    <tr>

      <td>min_rpm_for_feather</td>

      <td>Minimum rpm at which the prop will feather (if
feathering is available). </td>

      <td>Beech Baron 58( <b>min_rpm_for_feather= 700.0</b>
)<br>

Beech King Air 350( <b>min_rpm_for_feather = 700</b> )<br>

Cessna Skyhawk 172SP( <b>min_rpm_for_feather= 0</b> ) </td>

    </tr>

    <tr>

      <td>beta_feather</td>

      <td>Propeller pitch angle when feathered (degrees). </td>

      <td>Beech Baron 58( <b>beta_feather= 82.5</b> )<br>

Beech King Air 350( <b>beta_feather = 79.3</b> )<br>

Cessna Skyhawk 172SP( <b>beta_feather= 0</b> ) </td>

    </tr>

    <tr>

      <td>power_absorbed_cf</td>

      <td>Coefficient of friction power absorbed by propeller. </td>

      <td>Beech Baron 58( <b>power_absorbed_cf=
0.9</b> )<br>

Beech King Air 350( <b>power_absorbed_cf = 0.9</b> )<br>

Cessna Skyhawk 172SP( <b>power_absorbed_cf= 0</b> ) </td>

    </tr>

    <tr>

      <td>defeathering_accumulators_available</td>

      <td>Boolean to indicate if de-feathering accumulators are
available; 0 = FALSE, 1 = TRUE. </td>

      <td>Aircreation582SL( <b>defeathering_accumulators_available=
0</b> ) </td>

    </tr>

    <tr>

      <td>prop_reverse_available</td>

      <td>Specifies the scalar on the calculated propeller
reverser effect. A value of 0 will cause no reverse thrust to be
available. A value of 1.0 will cause the theoretical normal thrust to
be available. Other values will scale the normal calculated value
accordingly. </td>

      <td>Aircreation582SL( <b>prop_reverse_available= 0</b>
)<br>

Beech King Air 350( <b>prop_reverse_available = 1</b> ) </td>

    </tr>

    <tr>

      <td>minimum_on_ground_beta</td>

      <td>Minimum blade pitch angle when the aircraft is on the
ground (degrees). </td>

      <td>Aircreation582SL( <b>minimum_on_ground_beta=
0.000</b> )<br>

Beech Baron 58( <b>minimum_on_ground_beta= 0.0</b> )<br>

Beech King Air 350( <b>minimum_on_ground_beta = 1.0</b> )<br>

Cessna Skyhawk 172SP( <b>minimum_on_ground_beta= 0</b> ) </td>

    </tr>

    <tr>

      <td>minimum_reverse_beta</td>

      <td>Minimum blade pitch angle when the propeller is in
reverse (degrees). </td>

      <td>Aircreation582SL( <b>minimum_reverse_beta= 0.000</b>
)<br>

Beech Baron 58( <b>minimum_reverse_beta= 0.0</b> )<br>

Beech King Air 350( <b>minimum_reverse_beta = -14.0</b> )<br>

Cessna Skyhawk 172SP( <b>minimum_reverse_beta= 0</b> ) </td>

    </tr>

    <tr>

      <td>thrust_scalar</td>

      <td>Parameter that scales the calculated thrust provided by
the propeller. </td>

      <td>Aircreation582SL( <b>thrust_scalar=1.000</b>
)<br>

Beech Baron 58( <b>thrust_scalar = 1.0</b> )<br>

Beech King Air 350( <b>thrust_scalar = 1.0</b> ) </td>

    </tr>

    <tr>

      <td>feathering_switches</td>

      <td>Boolean indicating if feathering switches are
available. 0 = FALSE, 1 = TRUE. Feathering switches (as found on the
Douglas DC3), allow the pilot to automatically feather the propeller
via a switch, regardless of the propeller lever position. </td>

      <td>Douglas DC-3( <b>feathering_switches = 1</b>
) </td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">number_of_propellers</td>

      <td align="undefined" valign="undefined">The
number of propellers driven per engine.</td>

      <td align="undefined" valign="undefined">See
the Wright Flyer from <span style="font-style: italic;">Flight
Simulator</span> 2004 for an example of an aircraft with one
engine and two propellers.</td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">engine_map</td>

      <td align="undefined" valign="undefined">Set
of flags that allows the propellers to be driven by a different engine.</td>

      <td align="undefined" valign="undefined">See
the Wright Flyer from <span style="font-style: italic;">Flight
Simulator</span> 2004.</td>

    </tr>

    <tr>

      <td align="undefined" valign="undefined">propeller.0<br>

to <br>

propeller.1</td>

      <td align="undefined" valign="undefined">This
parameter allows for the propeller to be located at the specified
offset (longitudinal, lateral and vertical) in feet from the engine
that is driving it.</td>

      <td align="undefined" valign="undefined">See
the Wright Flyer from <span style="font-style: italic;">Flight
Simulator</span> 2004.</td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId600406"></a>[magneticcompass]</h4>

<p>This section defines the magnetic compass characteristics of the
  aircraft.</p>
<p>&nbsp;</p>
<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>compass.0</td>

      <td>Set to 1 for a vertical compass (with no dip errors). </td>

      <td>Aircreation582SL( <b>Compass.0 = 1</b> ) </td>

    </tr>

  </tbody>
</table>

<p>&nbsp;</p>
<H4>[gpws<a name="gpws"></a>]</H4>
<p>This section sepcifies the details of the ground proximity warning system.</p>
<p>&nbsp;</p>
<TABLE cellSpacing="4" cellPadding="2">
  <TBODY>
    <TR>
      <TD><H5>Property </H5></TD>
      <TD><H5>Description </H5></TD>
      <TD><H5>Examples</H5></TD>
    </TR>
    <TR>
      <TD>max_warning_height</TD>
      <TD>The height below which a warning is activated. </TD>
      <TD>Boeing 737-800 Paint1( <B>max_warning_height = 1000</B> ) </TD>
    </TR>
    <TR>
      <TD>sink_rate_fpm</TD>
      <TD>If an aircraft exceeds this  rate of descent a warning is activated. </TD>
      <TD>Boeing 737-800 Paint1( <B>sink_rate_fpm = -1500</B> ) </TD>
    </TR>
    <TR>
      <TD>excessive_sink_rate_fpm</TD>
      <TD>If an aircraft exceeds this  rate of descent an urgent warning is activated. </TD>
      <TD>Boeing 737-800 Paint1( <B>excessive_sink_rate_fpm = -2000</B> ) </TD>
    </TR>
    <TR>
      <TD>climbout_sink_rate_fpm</TD>
      <TD>If an aircraft starts to descend during takeoff, and exceeds this rate of descent, a warning is activated. </TD>
      <TD>Boeing 737-800 Paint1( <B>climbout_sink_rate_fpm = -100</B> ) </TD>
    </TR>
    <TR>
      <TD>flap_and_gear_sink_rate_fpm</TD>
      <TD>If an aircraft is landing, and exceeds this rate of descent without flaps or gear extended, a warning is activated. </TD>
      <TD>Boeing 737-800 Paint1( <B>flap_and_gear_sink_rate_fpm= -100</B> ) </TD>
    </TR>
  </TBODY>
</TABLE>
<p>&nbsp;</p>
<h4><a class="mozTocH4" name="mozTocId157738"></a>[cameradefinition.n]</h4>

<p>This section shows the camera properties most used by aircraft.
  An aircraft can have multiple cameradefinition sections, which should
be numbered from 0 to n. For a full definition of all the properties that can be set for a camera definition, refer to the <a href="../../Core Utilities Kit/Camera Configuration/Camera Configuration.htm">Camera Configuration</a> document. All of the properties described in that document can be used in an aircraft camera definition in an aircraft configuration file. </p>
<p><br>
  
</p>
<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>      </td>

      <td>
      <h5>Examples</h5>      </td>
    </tr>

    <tr>

      <td>title</td>

      <td>Boeing 747-400( <b>Title = "Right Side Window"</b>
)<br>

Cessna Skyhawk 172SP( <b>Title = "Right Wing"</b> )<br>

DeHavilland Beaver DHC2( <b>Title = "Right Float"</b> )<br>

Extra 300S( <b>Title = "Tail"</b> ) </td>
    </tr>

    <tr>

      <td>guid</td>

      <td>Boeing 747-400( <b>Guid =
{54F54B8A-3EC2-2D4E-8D10-B8F9D0F16ACC}</b> )<br>

Cessna Skyhawk 172SP( <b>Guid =
{C690EAFD-223A-42d0-99E0-681ADF93BB59}</b> )<br>

DeHavilland Beaver DHC2( <b>Guid =
{B0CA7E72-F3D9-F748-8BF5-108D197B2469}</b> )<br>

Extra 300S( <b>Guid = {D8D67955-2E9B-4e75-9D8B-8EFFBBFAC64A}</b>
) </td>
    </tr>

    <tr>

      <td>description</td>

      <td>Boeing 747-400( <b>Description = "View of the
right wing from the passenger cabin"</b> )<br>

Cessna Skyhawk 172SP( <b>Description = "View from the right wing
tip looking at the cockpit"</b> )<br>

DeHavilland Beaver DHC2( <b>Description = "View from the aft end
of the right float looking forward"</b> )<br>

Extra 300S( <b>Description = "Looking forward from the tip of
the vertical stabilizer"</b> ) </td>
    </tr>

    <tr>

      <td>origin</td>

      <td>Boeing 747-400( <b>Origin = Center</b> )<br>

Extra 300S( <b>Origin = Virtual Cockpit</b> ) </td>
    </tr>

    <tr>

      <td>snappbhadjust</td>

      <td>Boeing 747-400( <b>SnapPbhAdjust = Swivel</b>
)<br>

DeHavilland Beaver DHC2( <b>SnapPbhAdjust = None</b> ) </td>
    </tr>

    <tr>

      <td>snappbhreturn</td>

      <td>Boeing 747-400( <b>SnapPbhReturn = FALSE</b>
) </td>
    </tr>

    <tr>

      <td>panpbhadjust</td>

      <td>Boeing 747-400( <b>PanPbhAdjust = Swivel</b>
)<br>

DeHavilland Beaver DHC2( <b>PanPbhAdjust = None</b> ) </td>
    </tr>

    <tr>

      <td>panpbhreturn</td>

      <td>Boeing 747-400( <b>PanPbhReturn = FALSE</b>
) </td>
    </tr>

    <tr>

      <td>track</td>

      <td>Boeing 747-400( <b>Track = None</b> ) </td>
    </tr>

    <tr>

      <td>showaxis</td>

      <td>Boeing 747-400( <b>ShowAxis = FALSE</b> )<br>

Extra 300S( <b>ShowAxis = TRUE</b> ) </td>
    </tr>

    <tr>

      <td>allowzoom</td>

      <td>Boeing 747-400( <b>AllowZoom = TRUE</b> )<br>

Extra 300S( <b>AllowZoom = FALSE</b> ) </td>
    </tr>

    <tr>

      <td>initialzoom</td>

      <td>Boeing 747-400( <b>InitialZoom = 1.0</b> )<br>

Cessna Skyhawk 172SP( <b>InitialZoom = 0.75</b> )<br>

DeHavilland Beaver DHC2( <b>InitialZoom = .5</b> )<br>

Extra 300S( <b>InitialZoom = 0.4</b> ) </td>
    </tr>

    <tr>

      <td>showweather</td>

      <td>Boeing 747-400( <b>ShowWeather = Yes</b> )      </td>
    </tr>

    <tr>

      <td>initialxyz</td>

      <td>Boeing 747-400( <b>InitialXyz = 5.5, 0.75, -13</b>
)<br>

Cessna Skyhawk 172SP( <b>InitialXyz = 7.5, 0.75, 0</b> )<br>

DeHavilland Beaver DHC2( <b>InitialXyz = 1.5, .5, -3.9</b>
)<br>

Extra 300S( <b>InitialXyz = 0, 2.0, -3.9</b> ) </td>
    </tr>

    <tr>

      <td>initialpbh</td>

      <td>Boeing 747-400( <b>InitialPbh = 0, 0, 95</b>
)<br>

Cessna Skyhawk 172SP( <b>InitialPbh = 5, 0, 270</b> )<br>

DeHavilland Beaver DHC2( <b>InitialPbh = 0, 0, 0</b> )<br>

Extra 300S( <b>InitialPbh = 10, 0, 0</b> ) </td>
    </tr>

    <tr>

      <td>xyzadjust</td>

      <td>Boeing 747-400( <b>XyzAdjust = TRUE</b> ) </td>
    </tr>

    <tr>

      <td>category</td>

      <td>Boeing 747-400( <b>Category=Aircraft</b> )<br>

Extra 300S( <b>Category = VC</b> ) </td>
    </tr>

    <tr>

      <td>momentumeffect</td>

      <td>Boeing 747-400( <b>MomentumEffect=TRUE</b>
)<br>

Extra 300S( <b>MomentumEffect = TRUE</b> ) </td>
    </tr>

    <tr>

      <td>clipmode</td>

      <td>Boeing 747-400( <b>ClipMode=Minimum</b> ) </td>
    </tr>

    <tr>

      <td>zoompanscalar</td>

      <td>Extra 300S( <b>ZoomPanScalar = 1.0</b> ) </td>
    </tr>

    <tr>

      <td>showlensflare</td>

      <td>Extra 300S( <b>ShowLensFlare=FALSE</b> ) </td>
    </tr>
  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId584060"></a>[turboprop_engine]</h4>

<p>The amount of power generated by an engine and the power
required for a propeller to turn through the air determine the increase
and decrease of the rpm.&nbsp; A turboprop engine is really a
combination of a turbine engine and a propeller.&nbsp; The values
in this section are included to modify values
specific to the turboprop.</p>

<p></p>

<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>      </td>

      <td>
      <h5>Description </h5>      </td>

      <td>
      <h5>Examples</h5>      </td>
    </tr>

    <tr>

      <td>power_scalar</td>

      <td>Changing this value affects the amount of power
delivered by the engine to the propellor shaft. </td>

      <td>Beech King Air 350( <b>power_scalar = 1.0</b>
)<br>

Bell 206B JetRanger( <b>power_scalar = 1.0</b> ) </td>
    </tr>

    <tr>

      <td>maximum_torque</td>

      <td>Maximum shaft-torque available from the engine
(ft-lbs). </td>

      <td>Beech King Air 350( <b>maximum_torque = 3270</b>
)<br>

Cessna Grand Caravan( <b>maximum_torque = 1865</b> )<br>

de Havilland Dash 8-100( <b>maximum_torque = 7878</b> ) </td>
    </tr>
    <tr>
      <td>powerspecificfuelconsumption</td>
      <td>Brake power specific fuel consumption (turboprop only). </td>
      <td>Beech King Air 350 Paint1( <B>PowerSpecificFuelConsumption = 0.55</B> ) </td>
    </tr>
  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId818226"></a>[airspeed_indicators]</h4>

<p>This section is used to define the characteristics of the
airspeed indicators on the instrument panels.&nbsp; The list of
indicators should be listed in order: 0,1,2,&hellip;n.&nbsp;
These characteristics define the calibration between calibrated
airspeed and indicated airspeed.&nbsp;</p>

<p></p>

<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>airspeed_indicator.0<br>

to<br>

airspeed_indicator.n</td>

      <td>The first parameter is a
scalar on the calibrated airspeed, and the second is an offset in
knots.&nbsp; The offset is applied first, then the
scalar.&nbsp; The default value for the scalar is 1.0 and the
default for the offset is 0.0, thus by default indicated airspeed is
equal to calibrated airspeed.</td>

      <td>Cessna Grand Caravan( <b>airspeed_indicator.0 =
1.183, -24.75</b> )<br>

DeHavilland Beaver DHC2( <b>airspeed_indicator.0 = 1, 0</b>
)<br>

Maule M7 260C( <b>airspeed_indicator.0 = 1.3, -24.0</b> ) </td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId183639"></a>[pressurization]</h4>

<p>This section defines the presssurization characteristics of the
  aircraft.</p>
<p>&nbsp;</p>
<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>design_cabin_pressure</td>

      <td></td>

      <td>Cessna Grand Caravan( <b>design_cabin_pressure =
0</b> ) </td>

    </tr>

    <tr>

      <td>max_pressure_differential</td>

      <td></td>

      <td>Cessna Grand Caravan( <b>max_pressure_differential
= 0</b> ) </td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId797074"></a>[variometers]</h4>

<p>This section defines the variometers characteristics of the aircraft.</p>
<p>&nbsp;</p>
<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>variometer.0</td>

      <td></td>

      <td>DG808S( <b>variometer.0=1</b> ) </td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId16616"></a>[yaw_string]</h4>

<p>This section defines the yaw string characteristics of the aircraft.</p>
<p>&nbsp;</p>
<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>yaw_string_available</td>

      <td></td>

      <td>DG808S( <b>yaw_string_available=1</b> ) </td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId975761"></a>[water
ballast system]</h4>

<p>This section defines the water ballast system of the aircraft.</p>
<p>&nbsp;</p>
<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>tank.0</td>

      <td>Front Fuselage. </td>

      <td>DG808S( <b>Tank.0 = 7.79, -2.75, 0.0, 0.0, 1</b>
) </td>

    </tr>

    <tr>

      <td>tank.1</td>

      <td>Rear Fuselage. </td>

      <td>DG808S( <b>Tank.1 = 3.57, -3.28, 0.0, 0.0, 2</b>
) </td>

    </tr>

    <tr>

      <td>tank.2</td>

      <td>Left Outboard. </td>

      <td>DG808S( <b>Tank.2 = 9.25, -0.60, -10.5, 0.0, 2</b>
) </td>

    </tr>

    <tr>

      <td>tank.3</td>

      <td>Left Inboard. </td>

      <td>DG808S( <b>Tank.3 = 16.38, -0.66, -4.5, 0.0, 1</b>
) </td>

    </tr>

    <tr>

      <td>tank.4</td>

      <td>Right Inboard. </td>

      <td>DG808S( <b>Tank.4 = 16.38, -0.66, 4.5, 0.0, 1</b>
) </td>

    </tr>

    <tr>

      <td>tank.5</td>

      <td>Right Outboard. </td>

      <td>DG808S( <b>Tank.5 = 9.25, -0.60, 10.5, 0.0, 2</b>
) </td>

    </tr>

    <tr>

      <td>numberofreleasevalves</td>

      <td>Number of release valves.</td>

      <td>DG808S( <b>NumberOfReleaseValves = 2</b> )
      </td>

    </tr>

    <tr>

      <td>dumprate</td>

      <td>Gallons per second. </td>

      <td>DG808S( <b>DumpRate = 0.18494</b> ) </td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId510108"></a>[smokesystem]</h4>

<p>The section describes how to configure a smoke system for an
aircraft. You can set multiple smoke points on an
aircraft.</p>

<p> </p>

<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>smoke.0<br>

to<br>

smoke.n</td>

      <td>The longitudinal, lateral and vertical position of the
smoke emitter, in feet, and the smoke effect file name.</td>

      <td>Extra 300S( <b>smoke.0=-10.00, -0.70, 0.0,
fx_smoke_w</b> ) </td>

    </tr>

  </tbody>
</table>

<br>

<h4>[folding wings]</h4>
<p>This section describes the folding wing characteristics of the aircraft. Note that these are folding wings used to store an aircraft more compactly when on the ground, or on deck, and not the variable sweep wings used on some supersonic aircraft. Variable sweep wings are not supported in <i>Flight Simulator X</i>. </p>
<p>&nbsp;</p>
<table class="T1" cellpadding="2" cellspacing="4">
 <tbody>

    <tr>

      <td align="undefined" valign="undefined">
      <h5><span style="font-weight: bold;">Property</span></h5>      </td>

      <td align="undefined" valign="undefined">
      <h5><span style="font-weight: bold;">Description</span></h5>      </td>

      <td align="undefined" valign="undefined">
      <h5><span style="font-weight: bold;">Examples</span></h5>      </td>
    </tr>

    <tr>

      <td align="undefined" valign="undefined">wing_fold_system_type</td>

      <td align="undefined" valign="undefined"><p>One of: </p>
      <p>0: None (the default)</p>
      <p>1: Manual</p>
      <p>2: Pneumatic</p>
      <p>3: Electrical</p>
      <p>4: Hydraulic </p></td>

      <td align="undefined" valign="undefined"><p>From <i>Microsoft &reg; Combat Flight Simulator</i>: </p>
        <p>F4F-4 Wildcat (<b>wing_fold_system_type = 4
        </b>)</p>
      </td>
    </tr>

    <tr>

      <td align="undefined" valign="undefined">fold_rates</td>

      <td align="undefined" valign="undefined">Two values, the percentage per second, to fully extend and retract. </td>

      <td align="undefined" valign="undefined">F4F-4 Wildcat (<b>fold_rates = 0.12,0.11</b>)</td>
    </tr>
  </tbody>
</table>

<br>
<h4>[anemometers]</h4>
<p>This section describes the positions of the anemometers in the aircraft.</p>
<p>&nbsp;</p>
<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>
      </td>

      <td>
      <h5>Description </h5>
      </td>

      <td>
      <h5>Examples</h5>
      </td>
    </tr>

    <tr>

      <td>anemometer.0<br>
to<br>
anemometer.n</td>

      <td>The longitudinal, lateral and vertical position of the anemometer from Datum. </td>

      <td>(From <i>Flight Simulator 2004)</i><br>
Ryan NYP( <b>anemometer.0 = -10.0, 0.0, 2.7</b> )<br>
Vickers Vimy 
Transatlantic( <b>anemometer.0 = 9.6, 0.0, -2.2</b> ) 
      </td>
    </tr>
  </tbody>
</table>
<br>

<h4>[realismconstants]</h4>
<p>This section describes some realism constraints, dealing in particular with the early aircraft available in <span style="font-style: italic;">Flight Simulator</span> 2004. The values entered are used to make an aircraft more stable.</p>
<p>&nbsp;</p>
<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>
      </td>

      <td>
      <h5>Description </h5>
      </td>

      <td>
      <h5>Examples</h5>
      </td>
    </tr>

    <tr>

      <td>rollmomentfrombeta</td>

      <td>Scalar and offset applied to the roll moment from beta. </td>

      <td>(From <i>Flight Simulator 2004</i>)<br>
Wright Flyer( 
      <b>RollMomentFromBeta = -0.5, 0</b> ) </td>
    </tr>

    <tr>

      <td>rollmomentfromailerons</td>

      <td>Scale and offset applied to the roll moment from the ailerons. </td>

      <td>Wright Flyer( <b>RollMomentFromAilerons = 1.5, 0</b> ) </td>
    </tr>

    <tr>

      <td>pitchmomentzeroalpha</td>

      <td>Scale and offset applied to the zero angle of attach. </td>

      <td>Wright Flyer( <b>PitchMomentZeroAlpha = 1.0, 0.002</b> ) </td>
    </tr>
  </tbody>
</table>
<br>
<br>

<h3><a class="mozTocH3" name="mozTocId200113"></a>Helicopter
Specific Sections</h3>

The following sections are specific to helicopters only.&nbsp;
<i>Flight Simulator</i> supports two different types of
helicopters.&nbsp; The first
are helicopters that are based on the Bell 206 model.&nbsp; The
relevant air files are examined to make this
determination.&nbsp; The second type is based on the new Robinson
R22 model.&nbsp; The R22&rsquo;s aerodynamics is based on the
data found in the aircraft.cfg.&nbsp; The <span style="font-weight: bold;">[helicopter]</span> section
is
the only helicopter-specific section that is used by the Bell 206
method.&nbsp; The R22 utilizes all the
other&nbsp;helicopter-specific sections.<br>

&nbsp;
<h4><a class="mozTocH4" name="mozTocId641828"></a>[helicopter]</h4>

The
low_realism_stability_scale parameter scales the stability of the Bell
206B helicopter in low realism settings to make the aircraft easier to
fly. The stability factor is broken down into three components: pitch,
roll, and yaw damping.<br>

Here&rsquo;s how the simulation uses this parameter:<br>

1.&nbsp;&nbsp;&nbsp;
The stability factor is scaled according to the pitch, roll, and yaw
values set. For
example, increasing the first value (pitch) to 1.1 increases the
pitch-damping factor by 10 percent.<br>

2.&nbsp;&nbsp;&nbsp; The stability factor
is scaled by the General Flight Model Realism slider in the Realism
Settings dialog box. At the highest realism setting, it is scaled to 0%
(no additional damping); at the minimum setting, it is scaled to 100
percent. Changes to the stability factor in the .cfg have their
largest effect when the Realism Setting is set to minimum, and have no
effect when Realism Setting is set to maximum. Increasing these values
excessively will result in excessive damping, making it hard to control
the helicopter.<br>
<br>
<table class="T1" cellpadding="2" cellspacing="4"><tbody>
<tr><td><h5>Property </h5></td><td><h5>Description  </h5></td><td><h5>Examples</h5></td></tr>
<tr>
<td>low_realism_stability_scale</td><td>
Pitch , Bank, Yaw Scalars on Stability in Low Realism Settings. </td><td>
Bell 206B JetRanger( <b>low_realism_stability_scale = 1.0, 1.0, 1.0</b> )
</td></tr>
<tr>
<td>reference_length</td><td>The length of the helicopter, in feet.
</td>
<td>
Robinson R22( <b>reference_length       = 21.58</b> )
</td></tr>
<tr>
<td>reference_frontal_area</td><td>The cross section area of the fuselage, in feet  squared, as viewed from head on to the helicopter.
</td>
<td>
Robinson R22( <b>reference_frontal_area = 17.7</b> )
</td></tr>
<tr>
<td>reference_side_area</td><td>Total side area of the fuselage, in feet  squared, as viewed from directly abeam of the helicopter.
</td>
<td>
Robinson R22( <b>reference_side_area    = 44.5</b> )
</td></tr>
<tr>
<td>side_aero_center</td><td>The longitudinal position, in feet, from the  datum of the helicopter that represents the lateral aerodynamic center.
</td>
<td>
Robinson R22( <b>side_aero_center       = -12.5</b> )
</td></tr>
<tr>
<td>right_trim_scalar</td><td>Scalar on the effect of the trim that counters  dissymmetry of lift.&nbsp; The trim normally  induces a roll moment to the right, but a negative value will create a left  moment.
</td>
<td>
Robinson R22( <b>right_trim_scalar      = 1.0</b> )
</td></tr>
<tr>
<td>correlator_available</td><td>This flag determines if a collective/throttle  correlator is configured on the helicopter.
</td>
<td>
Robinson R22( <b>correlator_available   = 1</b> )
</td></tr>
<tr>
<td>governed_pct_rpm_ref</td><td>Defines the percent rpm that the governor attempts  to maintain.&nbsp; 1.0 = 100% of &ldquo;rated&rdquo; rpm,  although a few percent above that is normal.
</td>
<td>
Robinson R22( <b>governed_pct_rpm_ref   = 1.04</b> )
</td></tr>
<tr>
<td>governor_pid</td><td><p>Proportional &ndash;  Integral &ndash; Derivative (PID) feedback controller that works to maintain the  reference rpm.&nbsp; The series of numbers  are:</p>
  <ol>
    <li>proportional  controller constant</li>
    <li>integral  controller constant</li>
    <li>derivative  controller constant</li>
    <li>max rpm  error (where 1.0 = 100%) in which the integrator portion is active</li>
    <li>max  rpm error (where 1.0 = 100%) in which the derivative portion is active</li>
  </ol>
  </td>
<td>
Robinson R22( <b>governor_pid = 0.4, 0, 0.1, 0, 0.2</b> )
</td></tr>
<tr>
<td>rotor_brake_scalar</td><td>Scalar on the effect of the rotor brake.
</td>
<td>
Robinson R22( <b>rotor_brake_scalar     = 1.0</b> )
</td></tr>
<tr>
<td>torque_scalar</td><td>Scalar on the effect that the rotor has on the  yawing moment of the helicopter.
</td>
<td>
Robinson R22( <b>torque_scalar          = 1.0</b> )
</td></tr>
<tr>
<td>cyclic_roll_control_scalar</td><td>Scalar on the amount of roll control authority  from lateral movement of the cyclic.
</td>
<td>
Robinson R22( <b>cyclic_roll_control_scalar  =1.0</b> )
</td></tr>
<tr>
<td>cyclic_pitch_control_scalar</td><td>Scalar on the amount of pitch control authority  from fore/aft movement of the cyclic.
</td>
<td>
Robinson R22( <b>cyclic_pitch_control_scalar =1.0</b> )
</td></tr>
<tr>
<td>pedal_control_scalar</td><td>Scalar on the amount of yaw control authority  from movement of the anti-torque pedals.
</td>
<td>
Robinson R22( <b>pedal_control_scalar        =1.0</b> )
</td></tr>
<tr>
<td>collective_on_rotor_torque_scalar</td><td>Scalar on the amount of torque exerted on the  rotor system due to the collective pitch of the rotor blades.&nbsp; Increasing this constant will result in the  rotor rpm tending to decelerate more dramatically as collective is increased.
</td>
<td>
Robinson R22( <b>collective_on_rotor_torque_scalar = 1.0</b> )
</td></tr>
</tbody></table>
<br>
<h4><a class="mozTocH4" name="mozTocId36503"></a>[fuselage_aerodynamics]</h4>

<p>This section defines the aerodynamic characteristics of R22 type
  helicopters.</p>
<p>&nbsp;</p>
<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>drag_force_cf</td>

      <td>Coefficient of longitudinal drag. </td>

      <td>Robinson R22( <b>drag_force_cf = 0.55</b>
) </td>

    </tr>

    <tr>

      <td>side_drag_force_cf</td>

      <td>Coefficient of lateral drag. </td>

      <td>Robinson R22( <b>side_drag_force_cf = 10.0</b>
) </td>

    </tr>

    <tr>

      <td>pitch_damp_cf</td>

      <td>Pitch damping coefficient (resistance to pitch
velocity). </td>

      <td>Robinson R22( <b>pitch_damp_cf = -2.0</b>
) </td>

    </tr>

    <tr>

      <td>roll_damp_cf</td>

      <td>Roll damping coefficient (resistance to roll velocity).
      </td>

      <td>Robinson R22( <b>roll_damp_cf = -2.0</b> )
      </td>

    </tr>

    <tr>

      <td>yaw_damp_cf</td>

      <td>Yaw damping coefficient (resistance to yaw velocity). </td>

      <td>Robinson R22( <b>yaw_damp_cf = -0.1</b> ) </td>

    </tr>

    <tr>

      <td>yaw_stability_cf</td>

      <td>Yaw stability coefficient. This is the weathervane
effect. </td>

      <td>Robinson R22( <b>yaw_stability_cf = 0.27</b>
) </td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId517455"></a>[mainrotor]</h4>

<p>This section defines the main rotor characteristics of R22 type
  helicopters.</p>
<p>&nbsp;</p>
<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>position</td>

      <td>The longitudinal, lateral, and vertical distance
vector, in feet, from the datum position of the helicopter. This
position should be the center of the main rotor. </td>

      <td>Robinson R22( <b>Position = -8.5, 0, 4.91</b>
) </td>

    </tr>

    <tr>

      <td>radius</td>

      <td>The radius of the rotor, in feet. </td>

      <td>Robinson R22( <b>Radius = 12.583</b> ) </td>

    </tr>

    <tr>

      <td>max_disc_angle</td>

      <td>The maximum absolute deflection angle up or down, in
degrees, that the rotor disc can move with the cyclic. </td>

      <td>Robinson R22( <b>max_disc_angle = 5.0</b>
) </td>

    </tr>

    <tr>

      <td>ratedrpm</td>

      <td>The rated rpm value for the main rotor. </td>

      <td>Robinson R22( <b>RatedRpm = 510</b> ) </td>

    </tr>

    <tr>

      <td>number_of_blades</td>

      <td>The number of blades in the rotor. </td>

      <td>Robinson R22( <b>Number_of_blades = 2</b>
) </td>

    </tr>

    <tr>

      <td>weight_per_blade</td>

      <td>Approximate weight, in pounds, of each rotor blade. </td>

      <td>Robinson R22( <b>Weight_per_blade = 26.0</b>
) </td>

    </tr>

    <tr>

      <td>weight_to_moi_factor</td>

      <td>The constant used in calculating the moment of inertia
of the rotor disc. The MOI algorithm is a function of the number of
blades, their weight, and this constant. Increasing this constant will
increase the inertia of the disc. </td>

      <td>Robinson R22( <b>Weight_to_moi_factor = 0.58</b>
) </td>

    </tr>

    <tr>

      <td>inflow_vel_reference</td>

      <td>The reference inflow velocity of the air mass moving
through the rotor disc. Increasing this value will result in more
thrust being generated. </td>

      <td>Robinson R22( <b>inflow_vel_reference = 34.0</b>
) </td>

    </tr>

  </tbody>
</table>

<br>

<h4><a class="mozTocH4" name="mozTocId786461"></a>[secondaryrotor]</h4>

<p>This section defines the secondary rotor characteristics of R22 type
  helicopters.</p>
<p>&nbsp;</p>
<table class="T1" cellpadding="2" cellspacing="4">

  <tbody>

    <tr>

      <td>
      <h5>Property </h5>

      </td>

      <td>
      <h5>Description </h5>

      </td>

      <td>
      <h5>Examples</h5>

      </td>

    </tr>

    <tr>

      <td>position</td>

      <td>The longitudinal, lateral, and vertical distance
vector, in feet, from the datum position of the helicopter. This
position should be the center of the main rotor. </td>

      <td>Robinson R22( <b>Position = -22.8, -0.74, 1.8</b>
) </td>

    </tr>

    <tr>

      <td>tailrotor</td>

      <td>This flag, if set to 1, configures the secondary rotor
as a tail rotor, or anti-torque. </td>

      <td>Robinson R22( <b>TailRotor = 1</b> ) </td>

    </tr>

    <tr>

      <td>radius</td>

      <td>The radius of the rotor, in feet. </td>

      <td>Robinson R22( <b>Radius = 1.75</b> ) </td>

    </tr>

  </tbody>
</table>

<br>

<h2>The Kneeboard, Model, Sound, Texture and Panel Files<a name="TheKneedboardModelSoundTextureandPanelFiles"></a></h2>

<h3>The kneeboard content files</h3>

In <span style="font-style: italic;">Flight Simulator</span>,
all of the kneeboard content is presented via HTML (.htm) files. The
kneeboard includes six pages:<br>

<h4>Briefing</h4>

Displays the briefing for the flight, if there is one. The text
displayed on the Briefing page of the kneeboard is flight-specific, and
is located in the corresponding subdirectory of the Flights directory.
To learn more about creating briefings for flights you create, see the
&ldquo;All About Flights&rdquo; article in the Learning Center.<br>

<h4>Radio</h4>

Logs the last 10 Air Traffic Control radio transmissions to your
aircraft. The text displayed on the Radio page of the kneeboard is
automatically generated as you use the Air Traffic Control feature. The
text cannot be modified.<br>

<h4>Navigation Log</h4>

Provides a list of waypoints, headings, and other information for a
flight plan created using the Flight Planner. The text displayed on the
Navigation Log page of the kneeboard is automatically generated from an
active flight plan. The text cannot be modified.<br>

<h4>Key Commands</h4>

Provides a complete list of keyboard commands. The text displayed on
the Key Commands tab of the kneeboard is located in the main Aircraft
folder, and is named kneeboard_keys.htm.<br>

<h4>Checklists</h4>

Lists step-by-step procedures for the aircraft you're flying that (when
used in conjunction with the speeds on the Reference page) make for a
more realistic <i>Flight Simulator</i> experience. The text displayed on the
Checklists page is aircraft-specific, and saved in an .htm file in the
aircraft container (aircraft folder) associated with each aircraft. The
file for the Checklists page is named aircraftname_check.htm where
aircraftname is the name of the aircraft (e.g., extra300s_check.htm).<br>

<h4>Reference</h4>

Lists recommended speeds for the aircraft you're flying: how fast to
fly during each phase of flight, and what the limits are. The text
displayed on the Reference page is aircraft-specific, and saved in an
.htm file in the aircraft container (aircraft folder) associated with
each aircraft. The file for the Reference page is named
aircraftndame_ref.htm where aircraftname is the name of the aircraft
(e.g., extra300s_ref.htm).<br>

In order for the the Checklist and Reference pages to display, two
lines must be present in the aircraft.cfg file, in the [fltsim.0]
section at the top:<br>

<ul>

  <li>kb_checklists=aircraftname_check</li>

  <li>kb_reference=aircraftname_ref</li>

</ul>

where aircraftname is the name of the aircraft (e.g., extra300s_check
and extra_300s_ref). Note that no .htm extension is needed here.<br>

<h5>Creating or modifying the Checklist and Reference pages</h5>

You can create or open kneeboard .htm files with NotePad or any other
text editing program that can read and save files in&nbsp;text
format, and edit them using HTML 4.0 conventions.<br>

After you've made changes to any kneeboard .htm files, be sure to
reload the page on the kneeboard: select a different page on the
kneeboard, then return to the page you modified.<br>

<br>

<h3>The panel.cfg file</h3>

The panel.cfg file is located in an aircraft&rsquo;s Panel folder,
and defines the characteristics of the aircraft&rsquo;s cockpit,
including window settings, view settings, and gauges. For a full
explanation of the structure of a panel.cfg file and instructions for
editing it, see <a href="../Panels and Gauges SDK/Panel Configuration Files.htm">Panel Configuration Files</a>.<br>

<h3>The model.cfg file</h3>

The model.cfg file is located in an aircraft&rsquo;s Model folder,
and specifies which visual models (.mdl files), exterior and interior, to render during normal
flight and optionally after  a crash. Note that this is a change from <i>Flight Simulator 2004</i>, with the interior model being separated from the exterior model. If a legacy model exists with both interior and exterior in the same .mdl file, the models will be rendered correctly with a single normal parameter. However this method of storing models is inefficient, as the interior model is never needed on all the aircraft that are not being controlled by the user. When designing new models, it is strongly recommended that the model file be separated into the two parts. <br>

<h4>[models]</h4>

<p>&nbsp;</p>
<table class="T1" cellpadding="2" cellspacing="4">
  <tbody>
    <tr>
      <td><h5>Property </h5></td>
      <td><h5>Description </h5></td>
      <td><h5>Examples</h5></td>
    </tr>
    <tr>
      <td>normal</td>
      <td>External 3D model used under normal circumstances.</td>
      <td> Aircreation_582SL( <b>normal=AirCreation_582SL</b> )<br>
        B737_800( <b>normal=B737_800</b> )<br>
        b747_400( <b>normal=B747_400</b> )<br>
        beech_baron_58( <b>normal=Beech_Baron_58</b> )<br>
        Beech_King_Air_350( <b>normal=Beech_King_Air_350</b> )<br>
        Bombardier_CRJ_700( <b>normal=Bombardier_CRJ_700</b> )<br>
        C172( <b>normal=Cessna172SP</b> )<br>
        C208B( <b>normal=C208B</b> )</td>
    </tr>
    <tr>
      <td align="undefined" valign="undefined">interior</td>
      <td align="undefined" valign="undefined">Internal, virtual cockpit, model. </td>
      <td align="undefined" valign="undefined">Aircreation_582SL( <B>interior=AirCreation_582SL_Interior</B> )<BR>
        B737_800( <B>interior=B737_800_interior</B> )<BR>
        b747_400( <B>interior=B747_400_interior</B> )<BR>
        beech_baron_58( <B>interior=Beech_Baron_58_interior</B> )<BR>
        Beech_King_Air_350( <B>interior=beech_king_air_350_interior</B> )<BR>
        Bombardier_CRJ_700( <B>interior=Bombardier_CRJ_700_Interior</B> )<BR>
        C172( <B>interior=cessna172sp_interior</B> )<BR>
        C208B( <B>interior=c208b_interior</B> )</td>
    </tr>
    <tr>
      <td align="undefined" valign="undefined">crash</td>
      <td align="undefined" valign="undefined">3D
        model used if aircraft crashes.</td>
      <td align="undefined" valign="undefined">No
        examples of crash models are shipped with <span style="font-style: italic;">Flight Simulator</span>.</td>
    </tr>
  </tbody>
</table>
<p>&nbsp;</p>
<h3>
The sound.cfg file</h3>

The sound.cfg file is located in an aircraft&rsquo;s Sound folder,
and defines the sounds to use for that aircraft (such as the sound of
the engine at various speeds, the sound of the landing gear going down,
and so on). Refer to the <a href="Sound Configuration Files.htm">Sound Configuration files</a> document for more
details.<br>

<h3>
The Texture folder</h3>

An aircraft&rsquo;s textures are defined by the .bmp files in the
aircraft&rsquo;s Texture folder, and are&nbsp;projected onto
the aircraft&rsquo;s parts as
specified in the aircraft&rsquo;s visual model (.mdl) file, located
in the Model folder. Texture file names must correspond to the texture
files that are referenced in the .mdl file. If the file names don't
correspond, the textures will not be rendered.<br>

<span style="font-style: italic;">
Flight Simulator</span> texture files
are&nbsp;mipmapped.&nbsp; A mipmapped
texture consists of a sequence of images, each of which is a
progressively lower resolution, prefiltered representation of the same
image. Mipmapping is a computationally low-cost way of improving the
quality of rendered textures. Each prefiltered image, or level, in the
mipmap is a power of two smaller than the previous level. A
high-resolution level is used for objects that are close to the viewer.
Lower-resolution levels are used as the object moves farther away.<br>

To edit a mipmapped texture, you&rsquo;ll need to use Image Tool,
an image editing application included with the <span style="font-style: italic;">Flight Simulator</span>&nbsp;SDK.
Be sure to save a copy of the original file before attempting to
modify it. <br>

A texture can also be edited using a simple graphics application such
as Microsoft Paint, though it will be saved as a standard .bmp file
instead of a mipmapped .bmp. <span style="font-style: italic;">Flight
Simulator</span> will automatically
generate the mipmaps for the texture, although these mipmaps may not
be of as high a quality as mipmaps created using Image Tool.<br>

&nbsp;<br>

<h3>Notes on using aliasing</h3>

<p>Aliasing allows multiple aircraft containers to use the same
files
(panels, flight models, sounds etc.). This saves disk space and makes
file organization more efficient. You can alias an aircraft&rsquo;s
panel.cfg, model.cfg, and sound.cfg files from any other
aircraft. Whereas configuration sets allow aircraft within
a single aircraft container to share components, aliasing allows
aircraft in different aircraft containers to share components.</p>

<p>
To alias an aircraft&rsquo;s panel.cfg, model.cfg, or sound.cfg
file from another aircraft&rsquo;s, simply change the aliasing .cfg
file to read:</p>

<p><span style="font-weight: bold;">
[fltsim]</span><br style="font-weight: bold;">

<span style="font-weight: bold;">
alias=<span style="font-style: italic;">aircraftname</span>\panel</span><br>

or<br>

<span style="font-weight: bold;">
[fltsim]</span><br style="font-weight: bold;">

<span style="font-weight: bold;">
alias=<span style="font-style: italic;">aircraftname</span>\model</span><br>

or<br>

<span style="font-weight: bold;">
[fltsim]</span><br style="font-weight: bold;">

<span style="font-weight: bold;">
alias=<span style="font-style: italic;">aircraftname</span>\sound</span></p>

<p><span style="font-weight: bold;"></span><br>

Aliased files are searched for in the following order:</p>

<ol>

  <li>Relative path from the Aircraft folder</li>

  <li>Relative path from the <span style="font-style: italic;">Flight
Simulator</span>&nbsp;folder</li>

</ol>

<p></p>

<h5>
An example</h5>

<p>
Let&rsquo;s say you&rsquo;ve imported a Boeing 757 aircraft
from the Web into <i>Flight Simulator X </i>, but want to use the 737-400 panel
when flying it. Instead of duplicating all the 737-400 panel files
(Panel.cfg and .bmps) and putting them in the new 757 aircraft
container, you can alias to them in their existing location from the
757 panel.cfg file. Just change the 757 panel.cfg file to read:<br>

[<span style="font-weight: bold;">fltsim]</span><br style="font-weight: bold;">

<span style="font-weight: bold;">
alias=\B737_400\panel</span><br>

The 757 aircraft would then use the 737-400 panel.cfg file
(and&nbsp;the
associated .bmps). The syntax for aliasing model.cfg and sound.cfg
files is identical.</p>

<br>

<br>

<div style="text-align: center;">
  <p>&nbsp;</p>
  <p>&copy; 2006 Microsoft Corporation. All rights reserved. </p>
  <p align="center">~~@~~ </p>
</div>

</body>
</html>
