[fltsim.0]
title=PC9 RTAF
sim=PC9
model=base
panel=
sound=
texture=RTAF
checklists=
description=The PC-9 is a Swiss designed, two-seat turboprop trainer.  
atc_id=19
ui_manufacturer=Pilatus
ui_type=PC9
ui_variation=Royal Thai Air Force
atc_airline=Air Force
atc_flight_number=19
      
[fltsim.1]
title=PC9 Factory
sim=PC9
model=pc9m
panel=
sound=
texture=PIL
checklists=
description=The PC-9 is a Swiss designed, two-seat turboprop trainer. 
atc_id=HBHPJ
ui_manufacturer=Pilatus
ui_type=PC9M
ui_variation=Factory Demonstrator
              
[fltsim.2]
title=PC9 Swiss
sim=PC9
model=tank
panel=
sound=
texture=SW
checklists=
description=The PC-9 is a Swiss designed, two-seat turboprop trainer. 
atc_id=C401
ui_manufacturer=Pilatus
ui_type=PC9
ui_variation=Swiss Air Force
                        
[fltsim.3]
title=PC9 Roulettes
sim=PC9
model=aus
panel=
sound=
texture=ROUL
checklists=
description=The PC-9 is a Swiss designed, two-seat turboprop trainer. 
atc_id=063
ui_manufacturer=Pilatus
ui_type=PC9/A
ui_variation=RAAF Roulettes
atc_airline=Air Force
atc_flight_number=063
                                         
[fltsim.4]
title=PC9 2FTS
sim=PC9
model=aus
panel=
sound=
texture=2FTS
checklists=
description=The PC-9 is a Swiss designed, two-seat turboprop trainer. 
atc_id=058
ui_manufacturer=Pilatus
ui_type=PC9/A
ui_variation=RAAF 2FTS
atc_airline=Air Force
atc_flight_number=058
                                                           
[fltsim.5]
title=PC9 RAAF
sim=PC9
model=aus2
panel=
sound=
texture=RAAF
checklists=
description=The PC-9 is a Swiss designed, two-seat turboprop trainer. 
atc_id=032
ui_manufacturer=Pilatus
ui_type=PC9/A
ui_variation=RAAF Gray scheme
atc_airline=Air Force
atc_flight_number=032
                            
[fltsim.6]
title=PC9 Slovenia
sim=PC9
model=pc9m
panel=
sound=
texture=SAF
checklists=
description=The PC-9 is a Swiss designed, two-seat turboprop trainer. 
atc_id=66
ui_manufacturer=Pilatus
ui_type=PC9M
ui_variation=Slovenia
atc_airline=Air Force
atc_flight_number=66
                                  
[fltsim.7]
title=PC9 D-EFMT
sim=PC9
model=base
panel=
sound=
texture=DEFMT
checklists=
description=The PC-9 is a Swiss designed, two-seat turboprop trainer. 
atc_id=DEFMT
atc_flight_number=92
ui_manufacturer=Pilatus
ui_type=PC9
ui_variation=German Trainer
                                
[fltsim.8]
title=PC9 Croatia
sim=PC9
model=pc9m
panel=
sound=
texture=CAF
checklists=
description=The PC-9 is a Swiss designed, two-seat turboprop trainer. 
atc_id=064
atc_flight_number=064
atc_airline=Air Force
ui_manufacturer=Pilatus
ui_type=PC9M
ui_variation=Croatia Air Force
              
[General]
atc_type=PILATUS
atc_model=PC9
performance=Max Level Speed :  320 kts \nInitial ROC: 4,000 ft\/min\nMax weight: 7,076lb.\nPowerplant: PT6A-62 950 SHP.


[WEIGHT_AND_BALANCE]
max_gross_weight = 7054.000
empty_weight = 3715.000

reference_datum_position     =  0.0000, 0.0000, 0.0000       // (feet) distance from FlightSim Reference position: (1/4 chord, centerline, waterline)
empty_weight_CG_position=0.0, 0, 0       // (feet) longitudinal, lateral, vertical distance from specified datum

max_number_of_stations=50

station_load.0=200,  0.0, 0.0, 1.7           //Pilot           Weight (lbs), longitudinal, lateral, vertical positions from datum (feet)
station_load.1=200,  -3.4,  0.0, 2.3           //Co-Pilot        Weight (lbs), longitudinal, lateral, vertical positions from datum (feet)

empty_weight_roll_MOI=2165
empty_weight_pitch_MOI=4997
empty_weight_yaw_MOI=5257
empty_weight_coupled_MOI=0.000000

[flight_tuning]
cruise_lift_scalar=1.0
parasite_drag_scalar=.80
induced_drag_scalar=1.0
elevator_effectiveness=.8
aileron_effectiveness=1.5
rudder_effectiveness=1.0
pitch_stability=1.0
roll_stability=1.0
yaw_stability=1.0
elevator_trim_effectiveness=1.0
aileron_trim_effectiveness=1.0
rudder_trim_effectiveness=1.0


[exits]
number_of_exits=2
exit_rate.0=0.6   
exit_rate.1=0.4   

[GeneralEngineData]
engine_type=5                                 //0=Piston, 1=Jet, 2=None, 3=Helo-Turbine, 4=Rocket, 5=Turboprop
Engine.0=10.7, 0.0, 0.7                      //(feet) longitudinal, lateral, vertical distance from reference datum
fuel_flow_scalar=1.0                   //Scalar for fuel flow efficiency


[propeller]
thrust_scalar=1.0                   //Propeller thrust scalar
propeller_type=0                     //0=Constant Speed, 1=Fixed Pitch
propeller_diameter=8.0                   //Propeller Diameter, (feet)
propeller_blades=4                     //Number of propeller blades
propeller_moi=15.1                    //Propeller moment of inertia
beta_max=45                    //Maximum blade pitch angle for constant speed prop, (degrees)
beta_min=5.0                  //Minimum blade pitch angle for constant speed prop, (degrees)
min_gov_rpm=25520                 //Miminum governed RPM
prop_tc=0.004                 //Prop time-constant
gear_reduction_ratio=16.5                  //Propeller gear reduction ratio
fixed_pitch_beta=0                     //Fixed pitch angle of fixed pitch prop, (degrees)
low_speed_theory_limit=80                    //Speed at which low speed theory becomes blended in (feet/second)
prop_sync_available=1                     //Prop synchronization available? 0=FALSE, 1=TRUE
prop_deice_available=1                     //Prop de-icing available? 0=FALSE, 1=TRUE
prop_feathering_available=1                    //Prop feathering available?  0=FALSE, 1=TRUE
prop_auto_feathering_available=1               //Prop auto-feathering available?  0=FALSE, 1=TRUE
min_rpm_for_feather=700                   //Minimum RPM for prop feathering
beta_feather=79.3                  //Feathering pitch angle (degrees)
power_absorbed_cf=0.9                   //Coefficient of friction for power absorbed by propeller
defeathering_accumulators_available=0          //Defeathering accumulators available? 0=FALSE, 1=TRUE 
prop_reverse_available=1                     //Prop reverse available?  0=FALSE, 1=TRUE
minimum_on_ground_beta=1.0                   //Miminum pitch angle on ground, (degrees)
minimum_reverse_beta=-14.0                 //Minimum pitch angle in reverse, (degrees)

[TurbineEngineData]
fuel_flow_gain=0.011                 //Gain on fuel flow
inlet_area=1.0                   //Square Feet, engine nacelle inlet area
rated_N2_rpm=33000                 //RPM, second stage compressor rated value
static_thrust=158                   //Lbs, max rated static thrust at Sea Level

[turboprop_engine]
power_scalar=1.0                   //Scalar on Turboprop power
maximum_torque=2900                  //Maximum torque available (ft-lbs)


[electrical]
;BusType, MaxAmpLoad, MinVoltage       BusTypes:0=MainBus,1=AvionicsBus,2=BatteryBus,3=HotBatteryBus,4-7=Generator/AlternatorBus(1-4)
flap_motor=0, 5 , 17.0
gear_motor=0, 5 , 17.0
autopilot=0, 5 , 17.0
avionics_bus=0, 10, 17.0
avionics=1, 5 , 17.0
pitot_heat=0, 2 , 17.0
additional_system=0, 20, 17.0
marker_beacon=1, 2 , 17.0
gear_warning=0, 2 , 17.0
fuel_pump=0, 5 , 17.0
starter1=0, 20, 17.0
light_nav=0, 5 , 17.0
light_beacon=0, 5 , 17.0
light_landing=0, 5 , 17.0
light_taxi=0, 5 , 17.0
light_strobe=0, 5 , 17.0
light_panel=0, 5 , 17.0

//0  Class                        <0=none,1=wheel, 2=scrape, 3=float>
//1  Longitudinal Position        (feet)
//2  Lateral Position             (feet)
//3  Vertical Position            (feet)
//4  Impact Damage Threshold      (Feet Per Minute)
//5  Brake Map                    (0=None, 1=Left, 2=Right)
//6  Wheel Radius                 (feet)
//7  Steer Angle                  (degrees)
//8  Static Compression           (feet)  (0 if rigid)
//9  Max/Static Compression Ratio
//10 Damping Ratio                (0=Undamped, 1=Critically Damped)
//11 Extension Time               (seconds)
//12 Retraction Time              (seconds)
//13 Sound Type
//14 Airspeed limit for retraction     (KIAS)
//15 Airspeed that gear gets damage at (KIAS)

[contact_points]
point.0=1,  6.6,   0.00, -4.45, 2500, 0, 0.596, 45, .2, 2, 0.9,  4,  4, 0, 180, 225
point.1=1,  -1.67,  -3.8, -4.4, 2500, 1, 0.596,  0.0, .2, 2.5, 0.9,  4,  4, 2, 180, 225
point.2=1,  -1.67,   3.8, -4.4, 2500, 2, 0.596,  0.0, .2, 2.5, 0.9,  4,  4, 3, 180, 225
point.3=2,  -1.2,   16.5, 0, 1500, 0, 0,  0.0, 0, 0, 0,  0,  0, 6, 0.0, 0.0
point.4=2,  -1.2,   -16.5, 0, 1500, 0, 0,  0.0, 0, 0, 0,  0,  0, 5, 0.0, 0.0
point.5=2,  -1.2,   0, -1.8, 1500, 0, 0,  0.0, 0, 0, 0,  0,  0, 4, 0.0, 0.0
point.6=2,  -16.7,   0, -1.1, 1500, 0, 0,  0.0, 0, 0, 0,  0,  0, 9, 0.0, 0.0
point.7=2,  9.5,   0, -1, 1500, 0, 0,  0.0, 0, 0, 0,  0,  0, 4, 0.0, 0.0


static_pitch=1
static_cg_height=4.3

[Views]
eyepoint=0, 0, 2.8


[flaps.0]
type=1                                    // 1 - tail, 2 - lead
span-outboard=0.5                                  // 0.0 .. 1.0
extending-time=4                                    // seconds
flaps-position.0=0                                    // degrees
flaps-position.1=20                                   // degrees
flaps-position.2=40                                   // degrees
damaging-speed=250                                  // KIAS
blowout-speed=300                                  // KIAS

[Radios]
// Radio Type=availiable, standby frequency, has glide slope
Audio.1=1
Com.1=1, 1
Com.2=1, 1
Nav.1=1, 1, 1
Nav.2=1, 1, 0
Adf.1=1
Transponder.1=1
Marker.1=1

[smokesystem] 
smoke.0=0, -25, 0, fx_smoke_r

[keyboard_response]
//Breakpoint speeds (knots) on the keyboard increments of control surfaces.
//Speed at which the incremenet is reduced to  1/2 and 1/8 respectively.
elevator=150, 250
aileron=150, 250
rudder=150, 250

[direction_indicators]
//1 Type: 0=None, 1=Vacuum Gyro, 2=Electric Gyro, 3=Electro-Mag Slaved Compass, 4=Slaved to another
//2 Indicator number of slaving indicator if Type=4
direction_indicator.0=3,0

[LIGHTS]
//Types: 1=beacon, 2=strobe, 3=navigation, 4=cockpit
light.0=3,   0.9, -16.4,  0.25, fx_navred ,
light.1=3,   0.9,  16.4,  0.25, fx_navgre ,
light.3=2,   0.605, -16.7,  .33, fx_strobe ,
light.4=2,   0.605,  16.7,  .33, fx_strobe ,
light.5=1, -6.65,   0.00,  3.1, fx_beacon ,
light.7=4,   .075,   0.00,  1.60, fx_vclight,

[EFFECTS]
wake=fx_wake
water=fx_spray
dirt=fx_tchdrt
concrete=fx_sparks
touchdown=fx_tchdwn_s, 1

[fuel]
LeftMain=0.0, -8.9, -0.6, 70.6, 0.0     //Longitudinal (feet), Lateral (feet), Vertical (feet), Usable(gallons), Unusable (gallons)
RightMain=0.0,  8.9, -0.6, 70.6, 0.0     //Longitudinal (feet), Lateral (feet), Vertical (feet), Usable(gallons), Unusable (gallons)
fuel_type=2                                //Fuel type: 1 = Avgas, 2 = JetA
number_of_tank_selectors=1                    


[airplane_geometry]
wing_area=175.3                 //Square feet
wing_span=33.5                  //Feet
wing_root_chord=5.16                  //Feet
wing_dihedral=7.0                   //Degrees
wing_incidence=1.0                   //Degrees
wing_twist=-2.                  //Degrees
oswald_efficiency_factor=0.7                   //Measure of lift effeciency of wing
wing_winglets_flag=0                     //Are winglets available?
wing_sweep=3.5                   //Degrees, wing leading edge
wing_pos_apex_lon=1.29                   //Feet, longitudinal distance from reference point, negative going aft
wing_pos_apex_vert=-1.5                   //Feet, vertical distance from reference point, positive going up
htail_area=19.38                  //Square feet
htail_span=11                  //Feet
htail_pos_lon=-16.3                 //Feet, longitudinal distance from reference point, negative going aft
htail_pos_vert=0.5                   //Feet, vertical distance from reference point, positive going up
htail_incidence=-.5                  //Degrees
htail_sweep=13.0                  //Degrees, horizontal tail leading edge
vtail_area=9.26                  //Square feet
vtail_span=3.7                   //Feet, tip to body
vtail_sweep=15.0                  //Degrees, vertical tail leading edge
vtail_pos_lon=-13.7                 //Feet, longitudinal distance from reference point, negative going aft
vtail_pos_vert=1.5                   //Feet, vertical distance from reference point, positive going up
elevator_area=17.22                  //Square feet
aileron_area=16.9                  //Square feet
rudder_area=9.69                   //Square feet
elevator_up_limit=18.5                  //Degrees
elevator_down_limit=16                  //Degrees
aileron_up_limit=20.0                  //Degrees
aileron_down_limit=11.0                  //Degrees
rudder_limit=24.0                  //Degrees
elevator_trim_limit=15.0                  //Degrees
spoiler_limit=80.0                  //Degrees
spoilerons_available=0                     //Spoilerons Available?
aileron_to_spoileron_gain=0                   //Aileron to spoileron gain
min_ailerons_for_spoilerons=0                 //Degrees
min_flaps_for_spoilerons=0                    //Minimum flap handle position when spoilerons activate

[Reference Speeds]
flaps_up_stall_speed=96.0                  //Knots True (KTAS)
full_flaps_stall_speed=76.8                  //Knots True (KTAS)
cruise_speed=300.0                 //Knots True (KTAS)

[autopilot]
autopilot_available=1
flight_director_available=0
default_vertical_speed=2000.0
autothrottle_available=0
pitch_takeoff_ga=15.000000

[forcefeedback]
stick_shaker_magnitude=5000             ; 0 - 10000
stick_shaker_direction=0                ; 0 - 35999 degrees
stick_shaker_period=111111              ; in microseconds
gear_bump_nose_magnitude=3000           ; 0 - 10000
gear_bump_nose_direction=18000          ; 0 - 35999 degrees
gear_bump_nose_duration=250000          ; in microseconds
gear_bump_left_magnitude=2700           ; 0 - 10000
gear_bump_left_direction=9000           ; 0 - 35999 degrees
gear_bump_left_duration=250000          ; in microseconds
gear_bump_right_magnitude=2700          ; 0 - 10000
gear_bump_right_direction=27000         ; 0 - 35999 degrees
gear_bump_right_duration=250000         ; in microseconds
ground_bumps_magnitude1=1300            ; 0 - 10000
ground_bumps_angle1=08900               ; 0 - 35999 degrees
ground_bumps_intercept1=3.0
ground_bumps_slope1=0.20
ground_bumps_magnitude2=200             ; 0 - 10000
ground_bumps_angle2=09100               ; 0 - 35999 degrees
ground_bumps_intercept2=1.075
ground_bumps_slope2=0.035
crash_magnitude1=10000                  ; 0 - 10000
crash_direction1=01000                  ; 0 - 35999 degrees
crash_magnitude2=10000                  ; 0 - 10000
crash_direction2=9000                   ; 0 - 35999 degrees
crash_period2=75000                     ; in microseconds
crash_duration2=2500000                 ; in microseconds