[fltsim.0] title=Cessna Grand Caravan EDLM PH-PPS sim=Cessna208B model= panel= sound= texture= kb_checklists=Cessna208B_Check kb_reference=Cessna208B_ref atc_id_color=0xff000000 atc_parking_types=RAMP atc_parking_codes=X101 ui_manufacturer=Cessna ui_type="C208B Grand Caravan" ui_variation="PH-PPS" description="This Caravan ist stationed at Marl-Loemuhle/Germany for the local parachuting club." visual_damage=0 [General] atc_type=Cessna atc_model=C208 editable=1 performance="Maximum Speed\n175 kts 324 km\/hr\n\nCruise Speed\n164 kts \t 305 km\/hr at 20,000 ft\n\nEngine\nPratt & Whitney Canada, Inc., PT6A-114A Free Turbine Flat Rated at 675 Shaft hp \n\nPropeller\nThree-Bladed, Constant Speed, Full Feathering, Reversible McCauley, 106-inch diameter\n\nMaximum Endurance\n5.1 hours maximum cruise at 10,000 ft\n6.6 hours maximum cruise at 18,000 ft\n6.4 hours maximum range at 10,000 ft\n7.2 hours maximum range at 18,000 ft\n\nService Ceiling\n22,800 ft 6,949 m\n\nFuel Capacity\n335 gal 1,268 L\n\nEmpty Weight\n4,575 lb 2,075 kg\n\nMaximum Gross Weight\n8,785 lb\t 3,985 kg\n\nUseful Load\n4,000 lb\t 1,814 kg\n\nLength\n41 ft, 7 in 12.7 m\n\nWingspan\n52 ft, 1 in\t 15.8 m\n\nHeight\n15 ft, 5-1\/2 in 4.8 m\n\nSeating\nUp to 14" [WEIGHT_AND_BALANCE] max_gross_weight = 8785 // (pounds) empty_weight = 4575 // (pounds) reference_datum_position = 16.2, 0, 0 // (feet) distance from FlightSim Reference position: (1/4 chord, centerline, waterline) empty_weight_CG_position = -15.4, 0, 0 // (feet) longitudinal, lateral, vertical distance from specified datum max_number_of_stations = 50 station_load.0 = "170, -11.3, -1.5, 0.0, Pilot" // Weight (lbs), longitudinal, lateral, vertical positions from datum (feet) station_load.1 = "170, -11.3, 1.5, 0.0, Passenger 2" // Weight (lbs), longitudinal, lateral, vertical positions from datum (feet) station_load.2 = "0, -13.9, -1.5, 0.0, Passenger 3" // Weight (lbs), longitudinal, lateral, vertical positions from datum (feet) station_load.3 = "0, -13.9, 1.5, 0.0, Passenger 4" // Weight (lbs), longitudinal, lateral, vertical positions from datum (feet) station_load.4 = "170, -17.2, -1.5, 0.0, Passenger 5" // Weight (lbs), longitudinal, lateral, vertical positions from datum (feet) station_load.5 = "170, -17.2, 1.5, 0.0, Passenger 6" // Weight (lbs), longitudinal, lateral, vertical positions from datum (feet) station_load.6 = "150, -20.2, -1.5, 0.0, Passenger 7" // Weight (lbs), longitudinal, lateral, vertical positions from datum (feet) station_load.7 = "150, -20.2, 1.5, 0.0, Passenger 8" // Weight (lbs), longitudinal, lateral, vertical positions from datum (feet) station_load.8 = "0, -23.2, -1.5, 0.0, Passenger 9" // Weight (lbs), longitudinal, lateral, vertical positions from datum (feet) station_load.9 = "0, -23.2, 1.5, 0.0, Passenger 10" // Weight (lbs), longitudinal, lateral, vertical positions from datum (feet) station_load.10= "0, -10.6, 0.0,-5.0, Cargo Pod 1" // Weight (lbs), longitudinal, lateral, vertical positions from datum (feet) station_load.11= "0, -15.2, 0.0,-5.0, Cargo Pod 2" // Weight (lbs), longitudinal, lateral, vertical positions from datum (feet) station_load.12= "50, -19.4, 0.0,-5.0, Cargo Pod 3" // Weight (lbs), longitudinal, lateral, vertical positions from datum (feet) station_load.13= "50, -24.6, 0.0,-5.0, Cargo Pod 4" // Weight (lbs), longitudinal, lateral, vertical positions from datum (feet) ;Moments of Inertia empty_weight_pitch_MOI = 8874.87 empty_weight_roll_MOI = 6026.96 empty_weight_yaw_MOI = 11858.54 empty_weight_coupled_MOI = 0.0 [flight_tuning] cruise_lift_scalar = 1.0 parasite_drag_scalar = 1.0 induced_drag_scalar = 1.0 elevator_effectiveness = 1.0 aileron_effectiveness = 1.0 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 [GeneralEngineData] engine_type = 5 //0=Piston, 1=Jet, 2=None, 3=Helo-Turbine, 4=Rocket, 5=Turboprop Engine.0 = -2.4, 0.0, 0.0 //(feet) longitudinal, lateral, vertical distance from reference datum fuel_flow_scalar = 1.12 //Scalar for fuel flow efficiency min_throttle_limit = -0.25 //Minimum percent throttle. Generally negative for turbine reverser [propeller] thrust_scalar = 1.0 //Propeller thrust scalar propeller_type = 0 //0=Constant Speed, 1=Fixed Pitch propeller_diameter = 8.8 //Propeller Diameter, (feet) propeller_blades = 3 //Number of propeller blades propeller_moi = 19 //Propeller moment of inertia beta_max = 45 //Maximum blade pitch angle for constant speed prop, (degrees) beta_min = 15.6 //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 = 17.4 //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 = 0 //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 = 88.0 //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 = 1865 //Maximum torque available (ft-lbs) [Flaps.0] type=1 span-outboard=0.5 // Percent span for flap position extending-time=5.7 // Seconds, time to fully extend system_type=0 // 0 = electrical damaging-speed = 175 // KIAS blowout-speed = 175 // KIAS flaps-position.0= 0 // degrees flaps-position.1=10,175 // degrees flaps-position.2=20,150 // degrees flaps-position.3=30,125 // degrees [pitot_static] vertical_speed_time_constant = 1.0 //Increasing this value will cause a more instantaneous reaction in the VSI [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 [LIGHTS] //Types: 1=beacon, 2=strobe, 3=navigation, 4=cockpit light.0 = 3, -16.10, -26.20, 3.3, fx_navred , light.1 = 3, -16.10, 26.20, 3.3, fx_navgre , light.2 = 3, -38.62, 0.00, 1.84, fx_navwhi , light.3 = 2, -16.17, -26.18, 3.32, fx_strobe , light.4 = 2, -16.17, 26.18, 3.32, fx_strobe , light.5 = 1, -39.20, 0.00, 9.55, fx_beacon , light.6 = 4, -9.49, 0.00, 0.98, fx_vclight, [EFFECTS] wake=fx_wake water=fx_nicks_tchwater waterspeed=fx_nicks_wtrspray, 1 dirt=fx_nicks_tchdirt concrete=fx_sparks touchdown=fx_tchdwn_s, 1 [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 = 100, 180 aileron = 200, 1000 rudder = 200, 1000 [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 [attitude_indicators] //Type: 0=None, 1=Vacuum Gyro, 2=Electric Gyro attitude_indicator.0 = 1 [turn_indicators] //Type: 0=None, 1=Electric Gyro, 2=Vacuum Gyro turn_indicator.0=1,0 [airspeed_indicators] airspeed_indicator.0 = 1.183, -24.75 [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, 5 , 17.0 avionics = 1, 5 , 17.0 pitot_heat = 0, 2 , 17.0 additional_system = 0, 2 , 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 //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 [contact_points] point.0 = 1, -4.70, 0.00, -5.40, 1500, 0, 0.5, 22.0, 0.3, 2.5, 0.7, 0.0, 0.0, 0 point.1 = 1, -18.00, -6.00, -5.40, 2500, 1, 0.5, 0.0, 0.3, 2.5, 0.7, 0.0, 0.0, 2 point.2 = 1, -18.00, 6.00, -5.40, 2500, 2, 0.5, 0.0, 0.3, 2.5, 0.7, 0.0, 0.0, 3 point.3 = 2, -15.90, -26.0, 3.00, 1800, 0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 5 point.4 = 2, -15.90 26.0, 3.00, 1800, 0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 6 point.5= 2, -39.23, 0.0, 0.00, 1800, 0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 9 point.6= 2, -2.50, 0.0, -2.17, 1800, 0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 4 point.7= 2, -42.00, 0.0, 10.00, 1800, 0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 7 max_number_of_points = 21 static_pitch = 0.24 //degrees, pitch when at rest on the ground (+=Up, -=Dn) static_cg_height= 5.11 //feet, altitude of CG when at rest on the ground [brakes] parking_brake = 1 //Parking brake available toe_brakes_scale = 0.68 //Brake scalar [hydraulic_system] normal_pressure = 3000.0 //PSI electric_pumps = 0 //no electric pumps engine_map = 1,0,0,0 //pump on Eng1 [Views] eyepoint= -12.1, -1.4, 2.12 //(feet) longitudinal, lateral, vertical distance from reference datum [fuel] LeftMain = -17.0, -1.1, 2.5, 166.0, 3.6 //Longitudinal (feet), Lateral (feet), Vertical (feet), Usable(gallons), Unusable (gallons) RightMain = -17.0, 1.1, 2.5, 166.0, 3.6 //Longitudinal (feet), Lateral (feet), Vertical (feet), Usable(gallons), Unusable (gallons) fuel_type = 2 //Fuel type: 1 = Avgas, 2 = JetA number_of_tank_selectors = 1 electric_pump=1 [exits] number_of_exits = 2 exit_rate.0 = 0.4 ;Percent per second exit_rate.1 = 0.4 ;Percent per second [airplane_geometry] wing_area = 279.0 //Square feet wing_span = 52.1 //Feet wing_root_chord = 6.4 //Feet wing_dihedral = 3.9 //Degrees wing_incidence = 2.5 //Degrees wing_twist = -1.7 //Degrees oswald_efficiency_factor= 0.7 //Measure of lift effeciency of wing wing_winglets_flag = 0 //Are winglets available? wing_sweep = 0.0 //Degrees, wing leading edge wing_pos_apex_lon = -14.5 //Feet, longitudinal distance from reference point, negative going aft wing_pos_apex_vert = 0.0 //Feet, vertical distance from reference point, positive going up htail_area = 39.0 //Square feet htail_span = 11.7 //Feet htail_pos_lon = -30.9 //Feet, longitudinal distance from reference point, negative going aft htail_pos_vert = 0.0 //Feet, vertical distance from reference point, positive going up htail_incidence = 2.0 //Degrees htail_sweep = 5.0 //Degrees, horizontal tail leading edge vtail_area = 18.0 //Square feet vtail_span = 4.8 //Feet, tip to body vtail_sweep = 45.0 //Degrees, vertical tail leading edge vtail_pos_lon = -28.8 //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 = 16.6 //Square feet aileron_area = 18.3 //Square feet rudder_area = 6.7 //Square feet elevator_up_limit = 28.0 //Degrees elevator_down_limit = 21.0 //Degrees aileron_up_limit = 20.0 //Degrees aileron_down_limit = 15.0 //Degrees rudder_limit = 24.0 //Degrees elevator_trim_limit = 19.5 //Degrees spoiler_limit = 20.0 //Degrees spoilerons_available = 1 //Spoilerons Available? aileron_to_spoileron_gain = 1 //Aileron to spoileron gain min_ailerons_for_spoilerons = 0 //Degrees min_flaps_for_spoilerons = 0 //Minimum flap handle position when spoilerons activate spoiler_handle_available = 0 //Defaults to True if spoiler limit > 0, else False. Should be False for spoilerons only [Reference Speeds] flaps_up_stall_speed = 78.0 //Knots True (KCAS) full_flaps_stall_speed = 60.8 //Knots True (KCAS) cruise_speed = 155.0 //Knots True (KTAS) max_mach = 0.60 max_indicated_speed = 175 ////Red line (KIAS) [autopilot] autopilot_available= 1 flight_director_available= 1 default_vertical_speed= 1000.0 autothrottle_available= 0 pitch_takeoff_ga=8.0 max_pitch=10.0 max_pitch_acceleration=1.0 max_pitch_velocity_lo_alt=2.0 max_pitch_velocity_hi_alt=1.5 max_pitch_velocity_lo_alt_breakpoint=20000.0 max_pitch_velocity_hi_alt_breakpoint=28000.0 max_bank=25.0 max_bank_acceleration=1.8 max_bank_velocity=3.00 max_throttle_rate=0.10 nav_proportional_control=9.00 nav_integrator_control=0.25 nav_derivative_control=0.00 nav_integrator_boundary=2.50 nav_derivative_boundary=0.00 gs_proportional_control=9.52 gs_integrator_control=0.26 gs_derivative_control=0.00 gs_integrator_boundary=0.70 gs_derivative_boundary=0.00 yaw_damper_gain = 0.0 [forcefeedback] 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=35500 ; 0 - 35999 degrees gear_bump_left_duration=250000 ; in microseconds gear_bump_right_magnitude=2700 ; 0 - 10000 gear_bump_right_direction=00500 ; 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 [stall_warning] type=2