<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="A320family" version="2.0" release="BETA"
xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

<fileheader>
	<author> Bicyus (Jon Ortuondo) </author>
	<email> bicyus@gmail.com </email>
	<filecreationdate> 2012-02-15 </filecreationdate>
	<version> 0.99 </version>
	<description> Airbus A321-231 with IAE V2500 Engines </description>
	<note> Revised and fixed by Peter Brendt (jwocky) and Joshua Davidson (it0uchpods). Fork from the A320-Family aircraft project (Thanks to all authors) </note>
	<limitation></limitation>
</fileheader>

<metrics>
	<wingarea  unit="FT2"> 1319.79 </wingarea>
	<wingspan  unit="FT" >  111.26 </wingspan>
	<wing_incidence>          1.03 </wing_incidence>
	<chord     unit="FT" >   13.76 </chord>
	<htailarea unit="FT2">  334.24 </htailarea>
	<htailarm  unit="FT" >   57.88 </htailarm>
	<vtailarea unit="FT2">  248.79 </vtailarea>
	<vtailarm  unit="FT" >   57.33 </vtailarm>

	<!-- location name="AERORP" unit="IN">
		<x> 642.122 </x>
		<y> 0 </y>
		<z> -25.2091 </z>
	</location -->
	<location name="AERORP" unit="IN">
		<x> 700.00 </x>
		<y> 0 </y>
		<z> 0.00 </z>
	</location>

	<location name="EYEPOINT" unit="IN">
		<x> 80 </x>
		<y> -30 </y>
		<z> 70 </z>
	</location>

	<location name="VRP" unit="IN">
		<x> 661.1 </x>
		<y> 0 </y>
		<z> -37 </z>
	</location>

</metrics>

<mass_balance>
	<ixx unit="SLUG*FT2">    611903 </ixx>
	<iyy unit="SLUG*FT2">   1735389 </iyy>
	<izz unit="SLUG*FT2">   2301293 </izz> 
<!--
___________________A320_________A330__________A340
BOW_____________178000________270000________283925
SPAN______________144___________198___________209
LENGTH____________153___________209___________209
ROLL MOI_________1725000______5727777_______10613448
PITCH MOI________2550000______19040141_______13904249
YAW MOI_________3950000______23089847_______24848934

	<ixx unit="SLUG*FT2">   2262183 </ixx>
	<iyy unit="SLUG*FT2">   3172439 </iyy>
	<izz unit="SLUG*FT2">   3337024 </izz>

	<ixx unit="SLUG*FT2">1725000</ixx>
	<iyy unit="SLUG*FT2">2550000</iyy>
	<izz unit="SLUG*FT2">3950000</izz> -->

	<ixy unit="SLUG*FT2">         0 </ixy>
	<ixz unit="SLUG*FT2">         0 </ixz>
	<iyz unit="SLUG*FT2">         0 </iyz>
	<emptywt unit="LBS">80431</emptywt> <!-- #ref-1 page 67, WV016. 90927lbs - 5248x2 (engines)=80431lbs-->

	<!-- 	#### PB: That makes no sense, the whole aircraft is 1479.1339 inches long. 650inches eqauls to about 43.95% MAC with the Airbus limits according to the AMM between 45% and 49%
		Also: The z-axis is -41.73 inches under the zero line of the plane while the pressure point is only -25,91 under the same line and slightly ahead, that causes the plane to behave quite unstable
	-->
	<!-- location name="CG" unit="IN">
		<! - -x> 642.122 </x- - >
		<x> 650.122 </x><! - - At zero load of fuel and cargo/pax the CG goes to 642 - - >
		<y> 0 </y>
		<z> -41.7398 </z>
	</location -->
	<location name="CG" unit="IN">
		<x> 652.00 </x>
		<y> 0 </y>
		<z> 0.00 </z>
	</location>

	<pointmass name="Cockpit Crew">
		<weight unit="LBS">400</weight> <!-- MAX: 400lbs, two pilots-->
		<location name="POINTMASS" unit="IN">
			<x>200</x>
			<y>0</y>
			<z>0</z>
		</location>
	</pointmass>
	<pointmass name="Cabin Crew">
		<weight unit="LBS">600</weight> <!-- MAX: 1320lbs, up to six flight-attendants-->
		<location name="POINTMASS" unit="IN">
			<x>696</x>
			<y>0</y>
			<z>0</z>
		</location>
	</pointmass>
	<pointmass name="PAX 0A (60 seats)">
		<weight unit="LBS">6600</weight> <!-- MAX: 13200lbs, 60 seats -->
		<location name="POINTMASS" unit="IN">
			<x>470.1711</x>
			<y>0</y>
			<z>0</z>
		</location>
	</pointmass>
	<pointmass name="PAX 0B (60 seats)">
		<weight unit="LBS">6600</weight> <!-- MAX: 13200lbs, 60 seats -->
		<location name="POINTMASS" unit="IN">
			<x>809.5669</x>
			<y>0</y>
			<z>0</z>
		</location>
	</pointmass>
	<pointmass name="PAX 0C (54 seats)">
		<weight unit="LBS">5940</weight> <!-- MAX: 11880lbs, 54 seats -->
		<location name="POINTMASS" unit="IN">
			<x>1163.2729</x>
			<y>0</y>
			<z>0</z>
		</location>
	</pointmass>
	<pointmass name="Cargo Hold 1">
		<weight unit="LBS">2000</weight> <!-- MAX: 7500.126lbs -->
		<location name="POINTMASS" unit="IN">
			<x>383.4792</x>
			<y>0</y>
			<z>-29.5</z>	<!-- 1.5m and now half of it for the center point of the load -->
		</location>
	</pointmass>
	<!-- Cargo Hold 2 doesn't exist, that is the center tank -->
	<pointmass name="Cargo Hold 3">
		<weight unit="LBS">2000</weight> <!-- MAX: 5384.414lbs -->
		<location name="POINTMASS" unit="IN">
			<x>849.1324</x>
			<y>0</y>
			<z>-29.5</z>
		</location>
	</pointmass>
	<pointmass name="Cargo Hold 4">
		<weight unit="LBS">1500</weight> <!-- MAX: 4651.754lbs -->
		<location name="POINTMASS" unit="IN">
			<x>931.0653</x>
			<y>0</y>
			<z>-29.5</z>
		</location>
	</pointmass>
	<pointmass name="Cargo Hold 5">
		<weight unit="LBS">2000</weight> <!-- MAX: 3300.320lbs -->
		<location name="POINTMASS" unit="IN">
			<x>1068.2634</x>
			<y>0</y>
			<z>0</z>	<!-- Cargo Hold #5 sits higher on the range of the cabin deck, it's only loadable with lifter -->
		</location>
	</pointmass>


</mass_balance>

<ground_reactions>
	<!-- REF-1 page 165 + 271  -->
	<contact type="BOGEY" name="NOSE_LG">
		<location unit="IN">
			<x> 197.6772 </x>
			<y> 0 </y>
			<z> -137.9617 </z> 
		</location>
		<static_friction> 0.8 </static_friction>
		<dynamic_friction> 0.5 </dynamic_friction>
		<rolling_friction> 0.02 </rolling_friction>
		<spring_coeff unit="LBS/FT"> 30935.5 </spring_coeff>
		<damping_coeff unit="LBS/FT/SEC"> 16978.5 </damping_coeff>
		<max_steer unit="DEG"> 70 </max_steer> <!-- REF-1 page 133 -->
		<brake_group> NONE </brake_group>
		<retractable>1</retractable>
	</contact>
	<contact type="BOGEY" name="LEFT_MLG">
		<location unit="IN">
			<!--<x> 699.9243 </x>-->
			<x> 695.3149 </x>
			<y> -149.4094 </y>
			<z> -150.4824 </z>
		</location>
<!-- 		<static_friction> 0.5 </static_friction>  WHAT??? less static than dinamyc friction?-->
		<static_friction> 0.8 </static_friction>
		<dynamic_friction> 0.5 </dynamic_friction>
		<rolling_friction> 0.02 </rolling_friction>
		<spring_coeff unit="LBS/FT"> 59785 </spring_coeff>
		<damping_coeff unit="LBS/FT/SEC"> 23957 </damping_coeff>
		<max_steer unit="DEG"> 0.0 </max_steer>
		<brake_group> LEFT </brake_group>
		<retractable>1</retractable>
	</contact>
	<contact type="BOGEY" name="RIGHT_MLG">
		<location unit="IN">
			<!-- <x> 697.3425 </x> It should be right left simetric
			<x> 699.9243 </x> -->
			<x> 695.3149 </x>
			<y> 149.4094 </y>
			<z> -150.4824 </z>
		</location>
<!-- 		<static_friction> 0.5 </static_friction>  WHAT??? less static than dinamyc friction?-->
		<static_friction> 0.8 </static_friction>
		<dynamic_friction> 0.5 </dynamic_friction>
		<rolling_friction> 0.02 </rolling_friction>
		<!--spring_coeff unit="LBS/FT"> 169785 </spring_coeff>
		<damping_coeff unit="LBS/FT/SEC"> 33957 </damping_coeff-->
		<spring_coeff unit="LBS/FT"> 59785 </spring_coeff>
		<damping_coeff unit="LBS/FT/SEC"> 23957 </damping_coeff>
		<max_steer unit="DEG"> 0.0 </max_steer>
		<brake_group> RIGHT </brake_group>
		<retractable>1</retractable>
	</contact>

	<contact type="STRUCTURE" name="NOSE_1">
		<location unit="IN">
			<x> 37.7953 </x>
			<y> 0 </y>
			<z> -38.1374 </z>
		</location>
		<static_friction> 1.0 </static_friction>
		<dynamic_friction> 0.4 </dynamic_friction>
		<rolling_friction> 0.4 </rolling_friction>
		<spring_coeff unit="LBS/FT"> 50000 </spring_coeff>
		<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
		<max_steer unit="DEG"> 0.0 </max_steer>
		<brake_group> NONE </brake_group>
		<retractable>0</retractable>
	</contact>
	<contact type="STRUCTURE" name="NOSE_2">
		<location unit="IN">
			<x> 128.1102 </x>
			<y> 0 </y>
			<z> -55.0271 </z>
		</location>
		<static_friction> 1.0 </static_friction>
		<dynamic_friction> 0.4 </dynamic_friction>
		<rolling_friction> 0.4 </rolling_friction>
		<spring_coeff unit="LBS/FT"> 50000 </spring_coeff>
		<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
		<max_steer unit="DEG"> 0.0 </max_steer>
		<brake_group> NONE </brake_group>
		<retractable>0</retractable>
	</contact>
	<contact type="STRUCTURE" name="CENTER_1">
		<location unit="IN">
			<x> 274.0157 </x>
			<y> 0 </y>
			<z> -60.0665 </z>
		</location>
		<static_friction> 1.0 </static_friction>
		<dynamic_friction> 0.4 </dynamic_friction>
		<rolling_friction> 0.4 </rolling_friction>
		<spring_coeff unit="LBS/FT"> 50000 </spring_coeff>
		<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
		<max_steer unit="DEG"> 0.0 </max_steer>
		<brake_group> NONE </brake_group>
		<retractable>0</retractable>
	</contact>
	<contact type="STRUCTURE" name="CENTER_2">
		<location unit="IN">
			<x> 930 </x>
			<y> 0 </y>
			<z> -60.0665 </z>
		</location>
		<static_friction> 1.0 </static_friction>
		<dynamic_friction> 0.4 </dynamic_friction>
		<rolling_friction> 0.4 </rolling_friction>
		<spring_coeff unit="LBS/FT"> 50000 </spring_coeff>
		<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
		<max_steer unit="DEG"> 0.0 </max_steer>
		<brake_group> NONE </brake_group>
		<retractable>0</retractable>
	</contact>

	<contact type="STRUCTURE" name="ENG_1">
		<location unit="IN">
			<x>589.735</x>	
			<y>-226.575</y>
			<z>-95.567</z>
		</location>
		<static_friction> 1.0 </static_friction>
		<dynamic_friction> 0.4 </dynamic_friction>
		<rolling_friction> 0.4 </rolling_friction>
		<spring_coeff unit="LBS/FT"> 50000 </spring_coeff>
		<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
		<max_steer unit="DEG"> 0.0 </max_steer>
		<brake_group> NONE </brake_group>
		<retractable>0</retractable>
	</contact>
	<contact type="STRUCTURE" name="ENG_2">
		<location unit="IN">
			<x>589.735</x>	
			<y>226.575</y>
			<z>-95.567</z>
		</location>
		<static_friction> 1.0 </static_friction>
		<dynamic_friction> 0.5 </dynamic_friction>
		<rolling_friction> 0.4 </rolling_friction>
		<spring_coeff unit="LBS/FT"> 50000 </spring_coeff>
		<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
		<max_steer unit="DEG"> 0.0 </max_steer>
		<brake_group> NONE </brake_group>
		<retractable>0</retractable>
	</contact>


	<contact type="STRUCTURE" name="TAIL_1">
		<location unit="IN">
			<x> 1097.9921 </x>
			<y> 0 </y>
			<z> -44.7722 </z>
		</location>
		<static_friction> 1.0 </static_friction>
		<dynamic_friction> 0.4 </dynamic_friction>
		<rolling_friction> 0.4 </rolling_friction>
		<spring_coeff unit="LBS/FT"> 50000 </spring_coeff>
		<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
		<max_steer unit="DEG"> 0.0 </max_steer>
		<brake_group> NONE </brake_group>
		<retractable>0</retractable>
	</contact>
	<contact type="STRUCTURE" name="TAIL_2">
		<location unit="IN">
			<x> 1225 </x>
			<y> 0 </y>
			<z> -18.8067 </z>
		</location>
		<static_friction> 1.0 </static_friction>
		<dynamic_friction> 0.4 </dynamic_friction>
		<rolling_friction> 0.4 </rolling_friction>
		<spring_coeff unit="LBS/FT"> 50000 </spring_coeff>
		<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
		<max_steer unit="DEG"> 0.0 </max_steer>
		<brake_group> NONE </brake_group>
		<retractable>0</retractable>
	</contact>
	<contact type="STRUCTURE" name="TAIL_3">
		<location unit="IN">
			<x> 1341.6142 </x>
			<y> 0 </y>
			<z> -10.2599 </z>
		</location>
		<static_friction> 1.0 </static_friction>
		<dynamic_friction> 0.4 </dynamic_friction>
		<rolling_friction> 0.4 </rolling_friction>
		<spring_coeff unit="LBS/FT"> 50000 </spring_coeff>
		<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
		<max_steer unit="DEG"> 0.0 </max_steer>
		<brake_group> NONE </brake_group>
		<retractable>0</retractable>
	</contact>
	<contact type="STRUCTURE" name="TAIL_4">
		<location unit="IN">
			<x> 1469.0945 </x>
			<y> 0 </y>
			<z> 47.4138 </z>
		</location>
		<static_friction> 1.0 </static_friction>
		<dynamic_friction> 1 </dynamic_friction>
		<rolling_friction> 1 </rolling_friction>
		<spring_coeff unit="LBS/FT"> 50000 </spring_coeff>
		<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
		<max_steer unit="DEG"> 0.0 </max_steer>
		<brake_group> NONE </brake_group>
		<retractable>0</retractable>
	</contact>
	<contact type="STRUCTURE" name="WING_TIP_1">
		<location unit="IN">
			<x> 838.8898 </x>
			<y> -667.5197 </y>
			<z> 35.7926 </z>
		</location>
		<static_friction> 1.0 </static_friction>
		<dynamic_friction> 0.4 </dynamic_friction>
		<rolling_friction> 0.4 </rolling_friction>
		<spring_coeff unit="LBS/FT"> 50000 </spring_coeff>
		<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
		<max_steer unit="DEG"> 0.0 </max_steer>
		<brake_group> NONE </brake_group>
		<retractable>0</retractable>
	</contact>
	<contact type="STRUCTURE" name="WING_TIP_2">
		<location unit="IN">
			<x> 838.8898 </x>
			<y> 667.5197 </y>
			<z> 35.7926 </z>
		</location>
		<static_friction> 1.0 </static_friction>
		<dynamic_friction> 1 </dynamic_friction>
		<rolling_friction> 1 </rolling_friction>
		<spring_coeff unit="LBS/FT"> 50000 </spring_coeff>
		<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
		<max_steer unit="DEG"> 0.0 </max_steer>
		<brake_group> NONE </brake_group>
		<retractable>0</retractable>
	</contact>
</ground_reactions>

<propulsion>

	<engine file="v2533_a5">
	<location unit="IN">
		<x> 620.0683 </x>
		<y> -226.575 </y>
		<z> -45.567 </z>
	</location>
	<orient unit="DEG">
		<roll> 0.0 </roll>
		<pitch> 2.2 </pitch>
		<yaw> 1 </yaw>
	</orient>
	<feed>3</feed>
	<feed>1</feed>
	<feed>2</feed>
	<thruster file="direct">
		<location unit="IN">
		<x> 655.4820 </x>
		<y> -226.575 </y>
		<z> 0.000 </z>
		</location>
		<orient unit="DEG">
		<roll> 0.0 </roll>
		<pitch> 2.2 </pitch>
		<yaw> 1 </yaw>
		</orient>
	</thruster>
	</engine>

	<engine file="v2533_a5">
	<location unit="IN">
		<x> 620.0683 </x>
		<y> 226.575 </y>
		<z> -45.567 </z>
	</location>
	<orient unit="DEG">
		<roll> 0.0 </roll>
		<pitch> 2.2 </pitch>
		<yaw> -1 </yaw>
	</orient>
	<feed>3</feed>
	<feed>5</feed>
	<feed>4</feed>
	<thruster file="direct">
		<location unit="IN">
		<x> 655.4820 </x>
		<y> 226.575 </y>
		<z> 0.000 </z>
		</location>
		<orient unit="DEG">
		<roll> 0.0 </roll>
		<pitch> 2.2 </pitch>
		<yaw> -1 </yaw>
		</orient>
	</thruster>
	</engine>


	<tank type="FUEL">    <!-- Left Tank (Wing tip Ventilation Surge) 0 -->
		<location unit="IN">
			<x> 783.0709 </x>
			<y> -574.4148 </y>
			<z> 3.1080 </z>
		</location>
		<capacity unit="LBS"> 412 </capacity><!-- 1 percent of total capacity, needs 20C to be filled -->
		<contents unit="LBS"> 0 </contents>
		
		<priority>4</priority>
		<type>JET-A1</type>
		<temperature>50</temperature>
	</tank>
	<tank type="FUEL">    <!-- Left Tank (Outer) 1 -->
		<location unit="IN">
			<x> 739.5669 </x>
			<y> -457.4259 </y>
			<z> -8.0898 </z>
		</location>
		<capacity unit="LBS"> 1520.00 </capacity><!-- correct by FCOM -->
		<contents unit="LBS"> 1520 </contents><!-- outer filled first than inner -->
		<standpipe unit="LBS">21</standpipe><!-- minimun fuel on pipes -->
		<priority>2</priority>
		<type>JET-A1</type>
		<temperature>50</temperature>
	</tank>
	<tank type="FUEL">    <!-- Left Tank (Inner) 2 -->
		<location unit="IN">
			<x> 652.5591 </x>
			<y> -236.2992 </y>
			<z> -33.9470 </z>
		</location>
		<capacity unit="LBS"> 11982 </capacity><!-- correct by FCOM -->
		<contents unit="LBS"> 4480 </contents>
		<standpipe unit="LBS">31</standpipe><!-- minimun fuel on pipes -->
		<priority>3</priority>
		<type>JET-A1</type>
		<temperature>50</temperature>
	</tank>
	<tank type="FUEL">    <!-- Center Tank 3 -->
		<location unit="IN">
			<x> 522.0473 </x>
			<y> 0 </y>
			<z> -47.0 </z>
		</location>
		<capacity unit="LBS"> 14281 </capacity><!-- correct by FCOM -->
		<contents unit="LBS"> 0 </contents> <!-- wing tanks filled first -->
		<standpipe unit="LBS">43</standpipe><!-- minimun fuel on pipes -->
		<priority>1</priority>
		<type>JET-A1</type>
		<temperature>50</temperature>
	</tank>
	<tank type="FUEL">    <!-- Right Tank (Inner) 4 -->
		<location unit="IN">
			<x> 652.5591 </x>
			<y> 236.2992 </y>
			<z> -33.9470 </z>
		</location>
		<capacity unit="LBS"> 11982 </capacity><!-- correct by FCOM -->
		<contents unit="LBS"> 4480 </contents>
		<standpipe unit="LBS">31</standpipe><!-- minimum fuel on pipes -->
		<priority>3</priority>
		<type>JET-A1</type>
		<temperature>50</temperature>
	</tank>
	<tank type="FUEL">    <!-- Right Tank (Outer) 5 -->
		<location unit="IN">
			<x> 739.5669 </x>
			<y> 457.4259 </y>
			<z> -8.0898 </z>
		</location>
		<capacity unit="LBS"> 1520 </capacity><!-- need review -->
		<contents unit="LBS"> 1520 </contents><!-- outer tank filled first than inner tank -->
		<standpipe unit="LBS">21</standpipe><!-- minimun fuel on pipes -->
		<priority>2</priority>
		<type>JET-A1</type>
		<temperature>50</temperature>
	</tank>
	<tank type="FUEL">    <!-- Right Tank (Wing tip Ventilation Surge) 6 -->
		<location unit="IN">
			<x> 783.0709 </x>
			<y> 574.4148 </y>
			<z> 3.1080 </z>
		</location>
		<capacity unit="LBS"> 412 </capacity><!-- 1 percent of total fuel capacity, needs 20C-->
		<contents unit="LBS"> 0 </contents>
		<priority>4</priority>
		<type>JET-A1</type>
		<temperature>50</temperature>
	</tank>
</propulsion>

<system file="pushback" />
<!--system file="a320-fuel" /-->
<system file="glass-effect1" />
<system file="it-fbw" />
<system file="fmgc" />

<flight_control name="FCS: A320">
	<channel name="Pitch">
	<summer name="Pitch Trim Sum">
		<input>/controls/flight/elevator-sum</input>
		<input>/controls/flight/elevator-trim</input>
		<clipto>
			<min>-1</min>
			<max>1</max>
		</clipto>
	</summer>

	<aerosurface_scale name="Elevator Control">
		<input>fcs/pitch-trim-sum</input>
		<gain>0.015</gain>
		<range>
			<min>-20</min>
			<max>20</max>
		</range>
		<output>fcs/elevator-pos-rad</output>
	</aerosurface_scale>
	<aerosurface_scale name="Elevator Position Normalizer">
		<input>fcs/pitch-trim-sum</input>
		<range>
			<min>-1</min>
			<max>1</max>
		</range>
		<output>fcs/elevator-pos-norm</output>
	</aerosurface_scale>
	</channel>
	<channel name="Roll">
	<summer name="Roll Trim Sum">
		<input>/controls/flight/aileron-sum</input>
		<input>/controls/flight/aileron-trim</input>
		<clipto>
		<min>-1</min>
		<max>1</max>
		</clipto>
	</summer>

	<aerosurface_scale name="Left Aileron Control">
		<input>fcs/roll-trim-sum</input>
		<gain>0.02</gain>
		<range>
		<min>-15</min>
		<max>15</max>
		</range>
		<output>fcs/left-aileron-pos-rad</output>
	</aerosurface_scale>

	<aerosurface_scale name="Right Aileron Control">
		<input>-fcs/roll-trim-sum</input>
		<gain>0.02</gain>
		<range>
		<min>-15</min>
		<max>15</max>
		</range>
		<output>fcs/right-aileron-pos-rad</output>
	</aerosurface_scale>

	<aerosurface_scale name="Left Aileron position normalized">
		<input>fcs/left-aileron-pos-deg</input>
		<domain>
		<min>-15</min>
		<max>15</max>
		</domain>
		<range>
		<min>-1</min>
		<max>1</max>
		</range>
		<output>fcs/left-aileron-pos-norm</output>
	</aerosurface_scale>

	<aerosurface_scale name="Right Aileron position normalized">
		<input>fcs/right-aileron-pos-deg</input>
		<domain>
		<min>-15</min>
		<max>15</max>
		</domain>
		<range>
		<min>-1</min>
		<max>1</max>
		</range>
		<output>fcs/right-aileron-pos-norm</output>
	</aerosurface_scale>
	</channel>
	<channel name="Throttle">
	<pure_gain name="fcs/throttle1">
		<input>/controls/engines/engine[0]/throttle-fdm</input>
		<gain>1</gain>
		<output>fcs/throttle-cmd-norm</output>
		<output>fcs/throttle-pos-norm</output>
	</pure_gain>
	<pure_gain name="fcs/throttle2">
		<input>/controls/engines/engine[1]/throttle-fdm</input>
		<gain>1</gain>
		<output>fcs/throttle-cmd-norm[1]</output>
		<output>fcs/throttle-pos-norm[1]</output>
	</pure_gain>
	</channel>

	<channel name="Yaw">
	<pure_gain name="fcs/rudder-cmd">
		<input>/controls/flight/rudder-fdm</input>
		<gain>-1</gain>
		<output>fcs/rudder-cmd-norm</output>
	</pure_gain>
	
   <summer name="Rudder Command Sum">
      <input>fcs/rudder-cmd-norm</input>
      <input>fcs/yaw-trim-cmd-norm</input>
      <clipto>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </clipto>
   </summer>

   <scheduled_gain name="Yaw Damper Rate">
      <input>velocities/r-aero-rad_sec</input>
      <table>
        <independentVar lookup="row">velocities/ve-kts</independentVar>
         <tableData>
            30     0.00
            60     2.00
         </tableData>
      </table>
   </scheduled_gain>

   <scheduled_gain name="Yaw Damper Beta">
      <input>aero/beta-rad</input>
      <table>
        <independentVar lookup="row">velocities/ve-kts</independentVar>
        <tableData>
           30     0.00
           60     0.00
        </tableData>
      </table>
   </scheduled_gain>

   <summer name="Yaw Damper Sum">
      <input>fcs/yaw-damper-beta</input>
      <input>fcs/yaw-damper-rate</input>
      <clipto>
        <min> -0.1 </min>
        <max>  0.1 </max>
      </clipto>
   </summer>

   <scheduled_gain name="Yaw Damper Final">
      <input>fcs/yaw-damper-sum</input>
      <table>
        <independentVar lookup="row">velocities/ve-kts</independentVar>
        <tableData>
           30         0.0
           31         1.0
        </tableData>
      </table>
   </scheduled_gain>

   <summer name="Rudder Sum">
      <input>fcs/rudder-command-sum</input>
      <input>fcs/yaw-damper-final</input>
      <clipto>
        <min> -1 </min>
        <max>  1 </max>
      </clipto>
   </summer>

   <aerosurface_scale name="Rudder Control">
      <input>fcs/rudder-sum</input>
      <range>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </range>
      <output>fcs/rudder-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="rudder normalization">
      <input>fcs/rudder-pos-rad</input>
      <domain>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </domain>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/rudder-pos-norm</output>
   </aerosurface_scale>

	</channel>

	<channel name="Flaps">

		<kinematic name="Flaps Control">
			<input>/controls/flight/flaps</input>
			<traverse>
			<setting>
				<position>0</position>
				<time>0</time>
			</setting>
			<setting>
				<position>35</position>
				<time>40</time>
			</setting>
			</traverse>
			<output>fcs/flap-pos-deg</output>
		</kinematic>

		<aerosurface_scale name="Flap position normalized">
			<input>fcs/flap-pos-deg</input>
			<domain>
				<min>0</min>
				<max>35</max>
			</domain>
			<range>
				<min>0</min>
				<max>1</max>
			</range>
			<output>fcs/flap-pos-norm</output>
		</aerosurface_scale>

	</channel>

	<channel name="Slats">

		<kinematic name="Slats Control">
			<input>/controls/flight/slats</input>
			<traverse>
			<setting>
				<position>0</position>
				<time>0</time>
			</setting>
			<setting>
				<position>27</position>
				<time>30</time>
			</setting>
			</traverse>
			<output>fcs/slat-pos-deg</output>
		</kinematic>

		<aerosurface_scale name="Slat position normalized">
			<input>fcs/slat-pos-deg</input>
			<domain>
			<min>0</min>
			<max>27</max>
			</domain>
			<range>
			<min>0</min>
			<max>1</max>
			</range>
			<output>fcs/slat-pos-norm</output>
		</aerosurface_scale>

	</channel>

	<channel name="Landing Gear">

		<kinematic name="Gear Control">
			<input>gear/gear-cmd-norm</input>
			<traverse>
			<setting>
				<position>0</position>
				<time>0</time>
			</setting>
			<setting>
				<position>1</position>
				<time>10</time>
			</setting>
			</traverse>
			<output>gear/gear-pos-norm</output>
		</kinematic>
	</channel>

	<channel name="Speedbrake">
		<kinematic name="Speedbrake">
			<input>fcs/speedbrake-cmd-norm</input>
			<traverse>
			<setting>
				<position>0</position>
				<time>0</time>
			</setting>
			<setting>
				<position>1</position>
				<time>1</time>
			</setting>
			</traverse>
			<output>fcs/speedbrake-pos-norm</output>
		</kinematic>
	</channel>
    
	<channel name="Tiller">
		
		<switch name="/controls/gear/tiller-disabled">
			<default value="0"/>
			<test logic="AND" value="1">
				/controls/gear/tiller-enabled == 0
			</test>
		</switch>
        
        <fcs_function name="Nose Wheel Steering 0">
            <function name="fcs/steer-nose-deg[0]">
                <description>Steering command for nose gear</description>
                <sum>
                    <product>
                        <table>
                            <independentVar lookup="row">/controls/gear/tiller-cmd-norm</independentVar>
                            <independentVar lookup="column">/controls/flight/rudder</independentVar>
                            <tableData>
                                -1   0   1
                                -1 -70 -70 -70
                                0  -7   0   7
                                1  70  70  70
                            </tableData>
                        </table>
                        <property>/controls/gear/tiller-enabled</property>
                    </product>
                    <product>
                        <product>
                            <property>/controls/flight/rudder</property>
                            <value>70</value>
                        </product>
                        <property>/controls/gear/tiller-disabled</property>
                    </product>
                </sum>
            </function>
        </fcs_function>
        
        <!-- simulate rotational friction -->
        <actuator name="Gear Nose Actuator">
            <input>fcs/steer-nose-deg[0]</input>
            <rate_limit>70</rate_limit>
            <output>fcs/steer-pos-deg[0]</output>
        </actuator>
        
    </channel>

    
</flight_control>


	<aerodynamics>

		<axis name="LIFT">

			<function name="aero/force/Lift_alpha">
				<description>Lift due to alpha</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<table>
						<independentVar lookup="row">aero/alpha-rad</independentVar>
						<tableData>
							-0.20 -0.900
							 0.00  0.103
							 0.15  1.600
							 0.23  1.900
							 0.60  1.000
						</tableData>
					</table>
				</product>
			</function>

			<function name="aero/force/Lift_flap">
				<description>Delta Lift due to flaps</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<table>
						<independentVar lookup="row">fcs/flap-pos-norm</independentVar>
						<tableData>
							0.000  0.00000
							0.290  0.00250
							0.596  0.00700
							0.645  0.01300
							1.000  0.01700
						</tableData>
					</table>
				</product>
			</function>

			<function name="aero/force/Lift_slats">
				<description>Delta Lift due to slats</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>fcs/slat-pos-deg</property>
					<value> 0.01000 </value>
				</product>
			</function>

			<function name="aero/force/Lift_speedbrake">
				<description>Delta Lift due to speedbrake</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>fcs/speedbrake-pos-norm</property>
					<value>-0.15</value>
				</product>
			</function>

			<function name="aero/force/Lift_elevator">
				<description>Lift due to Elevator Deflection</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>fcs/elevator-pos-rad</property>
					<value>0.04</value>
				</product>
			</function>

		</axis>

		<axis name="DRAG">

			<function name="aero/force/Drag_basic">
				<description>Drag at zero lift</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<table>
						<independentVar lookup="row">aero/alpha-rad</independentVar>
						<tableData>
							-1.57    1.300
							-0.26    0.021
							 0.00    0.012
							 0.26    0.028
							 1.57    1.350
						</tableData>
					</table>
				</product>
			</function>

			<function name="aero/force/Drag_induced">
				<description>Induced drag</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>aero/cl-squared</property>
					<value>0.041</value>
				</product>
			</function>

			<function name="aero/force/Drag_mach">
				<description>Drag due to mach</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<table>
						<independentVar lookup="row">velocities/mach</independentVar>
						<tableData>
							 0.00      0.000
							 0.79      0.000
							 1.10      0.023
							 1.80      0.015
						</tableData>
					</table>
				</product>
			</function>

			<function name="aero/force/Drag_flap">
				<description>Drag due to flaps</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>fcs/flap-pos-deg</property>
					<value> 0.00120 </value>
				</product>
			</function>

			<function name="aero/force/Drag_slats">
				<description>Drag due to slats</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>fcs/flap-pos-deg</property>
					<value> 0.00200 </value>
				</product>
			</function>

			<function name="aero/force/Drag_gear">
				<description>Drag due to gear</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>gear/gear-pos-norm</property>
					<value>0.030</value>
				</product>
			</function>

			<function name="aero/force/Drag_speedbrake">
				<description>Drag due to speedbrakes</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>fcs/speedbrake-pos-norm</property>
					<value>0.03</value>
				</product>
			</function>

			<function name="aero/force/Drag_beta">
				<description>Drag due to sideslip</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<table>
						<independentVar lookup="row">aero/beta-rad</independentVar>
						<tableData>
							-1.57    1.230
							-0.26    0.050
							 0.00    0.000
							 0.26    0.050
							 1.57    1.230
						</tableData>
					</table>
				</product>
			</function>

			<function name="aero/force/Drag_elevator">
				<description>Drag due to Elevator Deflection</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<abs><property>fcs/elevator-pos-norm</property></abs>
					<value>0.045</value>
				</product>
			</function>

		</axis>

		<axis name="SIDE">

			<function name="aero/force/Side_beta">
				<description>Side force due to beta</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>aero/beta-rad</property>
					<value>-1</value>
				</product>
			</function>

		</axis>

		<axis name="ROLL">

			<function name="aero/moment/Roll_beta">
				<description>Roll moment due to beta</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>aero/beta-rad</property>
					<value>-0.1</value>
				</product>
			</function>

			<function name="aero/moment/Roll_damp">
				<description>Roll moment due to roll rate</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>aero/bi2vel</property>
					<property>velocities/p-aero-rad_sec</property>
					<value>-0.95</value>
				</product>
			</function>

			<function name="aero/moment/Roll_yaw">
				<description>Roll moment due to yaw rate</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>aero/bi2vel</property>
					<property>velocities/r-aero-rad_sec</property>
					<value>0.005</value>
				</product>
			</function>

			<function name="aero/moment/Roll_aileron">
				<description>Roll moment due to aileron</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>fcs/left-aileron-pos-rad</property>
					<value>0.20</value>
				</product>
			</function>

			<function name="aero/moment/Roll_rudder">
				<description>Roll moment due to rudder</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>fcs/rudder-pos-rad</property>
					<value>0.003</value>
				</product>
			</function>

		</axis>

		<axis name="PITCH">

			<function name="aero/moment/Pitch_alpha">
				<description>Pitch moment due to alpha</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/cbarw-ft</property>
					<property>aero/alpha-rad</property>
					<value>-0.6</value>
				</product>
			</function>

			<function name="aero/moment/Pitch_elevator">
				<description>Pitch moment due to elevator</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/cbarw-ft</property>
					<property>fcs/elevator-pos-rad</property>
					<table>
						<independentVar lookup="row">velocities/mach</independentVar>
						<tableData>
							0.0     -1.900
							2.0     -0.900
						</tableData>
					</table>
				</product>
			</function>

			<function name="aero/moment/Pitch_damp">
				<description>Pitch moment due to pitch rate</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/cbarw-ft</property>
					<property>aero/ci2vel</property>
					<property>velocities/q-aero-rad_sec</property>
					<value>-140</value>
				</product>
			</function>

			<function name="aero/moment/Pitch_alphadot">
				<description>Pitch moment due to alpha rate</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/cbarw-ft</property>
					<property>aero/ci2vel</property>
					<property>aero/alphadot-rad_sec</property>
					<value>-1</value>
				</product>
			</function>

		</axis>

		<axis name="YAW">

			<function name="aero/moment/Yaw_beta">
				<description>Yaw moment due to beta</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>aero/beta-rad</property>
					<value>0.12</value>
				</product>
			</function>

			<function name="aero/moment/Yaw_damp">
				<description>Yaw moment due to yaw rate</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>aero/bi2vel</property>
					<property>velocities/r-aero-rad_sec</property>
					<value>-0.2</value>
				</product>
			</function>

			<function name="aero/moment/Yaw_rudder">
				<description>Yaw moment due to rudder</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>fcs/rudder-pos-rad</property>
					<value>-0.2</value>
				</product>
			</function>

			<function name="aero/moment/Yaw_aileron">
				<description>Adverse yaw</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>fcs/left-aileron-pos-rad</property>
					<value>0</value>
				</product>
			</function>

		</axis>

	</aerodynamics>

	<external_reactions>
		<force name="pushback" frame="BODY">
			<location unit="IN">
				<x>294</x>
				<y>0</y>
				<z>-149</z>
			</location>
			<direction>
				<x>1</x>
				<y>0</y>
				<z>0</z>
			</direction>
		</force>
	</external_reactions>
</fdm_config>