// DHC8-Q200_ver4.6 - MAY 26, 2005 // Design: Jean-Pierre Brisard // Concept, FD, Panel & Sound, Chk/Ref HTML, Docs by Barry Blaisdell // Master Textures & Livery by Bob May // Copyright 2005 - Premier Aircraft Design [fltsim.0] title=DHC8-Q202_FAC_ver4.6 sim=PAD_Dhc8 model= panel= sound= texture=FAC kb_checklists=Dash8_check kb_reference=Dash8_ref atc_id=C-FBCS atc_heavy=0 atc_airline= atc_flight_number= atc_parking_types=gate,ramp atc_parking_codes= ui_manufacturer=DeHavilland ui_type=New PAD Dash8 ui_variation=DHC8-Q202 Bombardier Factory description=FS2004 DeHavilland DHC8-Q202\nTwin Turboprop Regional Airliner\nVisit the Premeir Aircraft Design Web Site\nwww.flightsimnetwork.com\/premaircraft\nAll Files Copyright 2005.\nThe Q200 is designed for airlines and other operators who require an aircraft the same size as the Q100, but with more power and greater payload. Our engineers met the challenge by mating the Q100 airframe with the more powerful Pratt & Whitney PW123 engines found on the larger Q300 aircraft. editable=1 [General] performance=37 Pax Regional Airliner\nLength: 73 ft\nWing Span: 85 ft\nHt: 24 ft-7 in\nWeight:22,100 lb Empty\nMax T\/O Weight:34,500 lb\nPower: 2 x 2,150 SHP P&W 123C/D Turboshafts\nMax Cruise: 297 Kts TAS\nStall Speed 72 Kts\nCeiling: 25,000 ft\nRange: 970 Naut Miles atc_type=Bombardier atc_model=DH8B [Views] eyepoint= -9.780, -2.150, 2.380 //(feet) longitudinal, lateral, vertical distance from reference datum [LIGHTS] //Types: 1=beacon, 2=strobe, 3=navigation, 4=cockpit, 5=Landing light.0 = 1, -64.58, 0.0, 18.0 , fx_beaconh , light.1 = 2, -68.9, 0.0, 1.5, fx_strobeh , light.2 = 2, -28.9, 42.6, 5.6, dhc8fx_strobe, light.3 = 2, -28.9, -42.6, 5.6, dhc8fx_strobe, light.4 = 3, -29.3, -42.65, 5.6, dhc8fx_navred , light.5 = 3, -29.3, 42.65, 5.6, dhc8fx_navgre , [autopilot] autopilot_available= 1 flight_director_available= 1 default_vertical_speed= 1000.0 autothrottle_available= 0 pitch_takeoff_ga=8.0 use_no_default_bank=1 use_no_default_pitch=1 default_pitch_mode=0 default_bank_mode=0 max_pitch=10.000000 max_pitch_acceleration=1.000000 max_pitch_velocity_lo_alt=2.000000 max_pitch_velocity_hi_alt=1.500000 max_pitch_velocity_lo_alt_breakpoint=20000.000000 max_pitch_velocity_hi_alt_breakpoint=28000.000000 max_bank=25.000000 max_bank_acceleration=1.800000 max_bank_velocity=3.000000 max_throttle_rate=0.100000 nav_proportional_control=9.000000 nav_integrator_control=0.250000 nav_derivative_control=0.000000 nav_integrator_boundary=2.500000 nav_derivative_boundary=0.000000 gs_proportional_control=9.520000 gs_integrator_control=0.260000 gs_derivative_control=0.000000 gs_integrator_boundary=0.700000 gs_derivative_boundary=0.000000 yaw_damper_gain=0.000000 [WEIGHT_AND_BALANCE] max_gross_weight = 36300 // (pounds) empty_weight = 23004 // (pounds) reference_datum_position= 31.0, 0, 0 // (feet) distance from FlightSim Ref position: (1/4 chord,c/l, waterline) empty_weight_CG_position= -26.0, 0, 0 // (feet) longitudinal, lateral, vertical distance from specified datum max_number_of_stations = 50 station_load.0 = "170, -9.8, -1.75, 0.0, Pilot" //Pilot Weight (lbs), longitudinal, lateral, vertical positions from datum (feet) station_load.1 = "170, -9.8, 1.75, 0.0, Front Passenger" //Front Passenger Weight (lbs), longitudinal, lateral, vertical positions from datum (feet) station_load.2 = "5000, -26.0, 0.0, 0.0, Payload" //Payload Weight (lbs), longitudinal, lateral, vertical positions from datum (feet) ;Moments of Inertia empty_weight_pitch_MOI = 111701 empty_weight_roll_MOI = 61201 empty_weight_yaw_MOI = 161691 empty_weight_coupled_MOI = 0 [flight_tuning] cruise_lift_scalar=1.000 parasite_drag_scalar=0.950 induced_drag_scalar=0.950 elevator_effectiveness=0.8 aileron_effectiveness=1.1 rudder_effectiveness=0.8 pitch_stability=2.0 roll_stability=2.0 yaw_stability=2.0 elevator_trim_effectiveness=1.000 aileron_trim_effectiveness=1.000 rudder_trim_effectiveness=1.000 [GeneralEngineData] engine_type = 5 //0=Piston, 1=Jet, 2=None, 3=Helo-Turbine, 4=Rocket, 5=Turboprop Engine.0 = -28.4, -13.3, 2.7 //(feet) longitudinal, lateral, vertical distance from reference datum Engine.1 = -28.4, 13.3, 2.7 //(feet) longitudinal, lateral, vertical distance from reference datum fuel_flow_scalar = 0.60 //Scalar for fuel flow efficiency min_throttle_limit = -0.50 //Minimum percent throttle. Generally negative for turbine reverser [propeller] thrust_scalar = 1.25 //Propeller thrust scalar propeller_type = 0 //0=Constant Speed, 1=Fixed Pitch propeller_diameter = 13.0 //Propeller Diameter, (feet) propeller_blades = 4 //Number of propeller blades propeller_moi = 77 //Propeller moment of inertia beta_max = 45 //Maximum blade pitch angle for constant speed prop, (degrees) beta_min = 12 //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 = 17.0 //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 = .0250 //Square Feet, engine nacelle inlet area rated_N2_rpm = 29920 //RPM, second stage compressor rated value static_thrust = 200 //Lbs, max rated static thrust at Sea Level [turboprop_engine] power_scalar = 1.25 //Scalar on Turboprop power maximum_torque = 7878 //Maximum torque available (ft-lbs) [electrical] //BusTypes:0=MainBus,1=AvionicsBus,2=BatteryBus,3=HotBatteryBus,4-7=Generator/AlternatorBus(1-4) //BusType, MaxAmpLoad, MinVoltage autopilot = 0, 5 , 1.0 avionics_bus = 0, 10, 10.0 avionics = 1, 5 , 10.0 gear_warning = 0, 2 , 1.0 fuel_pump = 0, 5 , 1.0 light_nav = 0, 5 , 1.0 light_beacon = 0, 5 , 1.0 light_landing = 0, 5 , 7.0 light_taxi = 0, 5 , 7.0 light_strobe = 0, 5 , 7.0 light_panel = 0, 5 , 1.0 pitot_heat = 0, 15, 1.0 additional_system = 0, 20, 1.0 marker_beacon = 1, 2, 1.0 starter1 = 0, 20, 1.0 starter2 = 0, 20, 1.0 starter3 = 0, 20, 1.0 starter4 = 0, 20, 1.0 auto_brakes = 0, 15, 1.0 hydraulic_pump = 0, 2, 1.0 fuel_transfer_pump = 0, 5, 1.0 max_battery_voltage=28.0 generator_alternator_voltage=28.0 max_generator_alternator_amps=160.0 electric_always_available=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, -5.0, 0.00, -6.30, 2500, 0, 0.800, 50.0, 0.500, 2.5, 0.9, 5.0, 6.0, 0, 0.0 , 0.0 point.1 = 1, -29.0, -12.99, -6.50, 3000, 1, 1.250, 0.0, 0.675, 2.5, 0.8, 6.0, 7.0, 0, 0.0 , 0.0 point.2 = 1, -29.0, 12.99, -6.50, 3000, 2, 1.250, 0.0, 0.675, 2.5, 0.8, 6.0, 7.0, 0, 0.0 , 0.0 point.3 = 2, -31.6, -42.50, 5.39, 1200, 0, 0.000, 0.0, 0.000, 0.0, 0.0, 0.0, 0.0, 5 point.4 = 2, -31.6, 42.50, 5.39, 1200, 0, 0.000, 0.0, 0.000, 0.0, 0.0, 0.0, 0.0, 6 point.5 = 2, -68.6, 0.00, 1.22, 1200, 0, 0.000, 0.0, 0.000, 0.0, 0.0, 0.0, 0.0, 9 point.6 = 2, 0.0, 0.00, -3.92, 1200, 0, 0.000, 0.0, 0.000, 0.0, 0.0, 0.0, 0.0, 4 point.7= 5, -30.90, 5.250, -7.300, 1600, 0, 0.00, 50.0, 0.0, 0.0, 1.00, 1.1, 1.5, 0, 0.0, 0.0 max_number_of_points = 21 static_pitch = -0.5 //degrees, pitch when at rest on the ground (+=Up, -=Dn) static_cg_height = 7.200 //feet, altitude of CG when at rest on the ground gear_system_type=1 //Hydraulic [gear_warning_system] gear_warning_available = 1 //Normal pct_throttle_limit = 0.1 //Percent throttle that activates warning flap_limit_idle = 15.0 //Flap angle that activates warning at idle flap_limit_power = 30.0 //Flap angle that activates warning at above idle [Radios] // Radio Type=availiable, standby frequency, has glide slope Audio.1=1 Com.1=1,0 Com.2=1, 0 Nav.1=1, 0, 1 Nav.2=1, 0, 0 Adf.1=1 Transponder.1=1 Marker.1=1 [brakes] parking_brake = 1 //Parking brake available toe_brakes_scale = 1.06 //Brake scalar [hydraulic_system] normal_pressure = 3000.0 //PSI electric_pumps = 0 //no electric pumps engine_map = 1,1,0,0 //pumps on Eng1,2 [flaps.0] type = 1 // 1 - tail, 2 - lead span-outboard = 0.8 // 0.0 .. 1.0 extending-time = 6 // seconds flaps-position.0 = 0 // degrees, KIAS flaps-position.1 = 5 // degrees, KIAS flaps-position.2 = 15 // degrees, KIAS flaps-position.3 = 35 // degrees, KIAS damaging-speed = 250 // KIAS blowout-speed = 300 // KIAS [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 [EFFECTS] wake=fx_wake water=fx_spray dirt=fx_tchdrt concrete=fx_sparks touchdown=fx_tchdwn, 1 [fuel] LeftMain = -31.1, -9.1, 3.9, 420.0, 0.0 //Longitudinal (feet), Lateral (feet), Vertical (feet), Usable(gallons), Unusable (gallons) RightMain = -31.1, 9.1, 3.9, 420.0, 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 electric_pump=1 [airplane_geometry] wing_area = 585.0 //Square feet wing_span = 85.0 //Feet wing_root_chord = 7.0 //Feet wing_dihedral = 2.5 //Degrees wing_incidence = 0.000 //Degrees wing_twist = -3.0 //Degrees oswald_efficiency_factor= 0.7500 //Measure of lift effeciency of wing wing_winglets_flag = 0 //Are winglets available? wing_sweep = 3.0 //Degrees, wing leading edge wing_pos_apex_lon = -25.0 //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 = 97.0 //Square feet htail_span = 26.0 //Feet htail_pos_lon = -58.9 //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 = -2.500 //Degrees htail_sweep = 8.0 //Degrees, horizontal tail leading edge vtail_area = 106.0 //Square feet vtail_span = 11.7 //Feet, tip to body vtail_sweep = 30.0 //Degrees, vertical tail leading edge vtail_pos_lon = -54.9 //Feet, longitudinal distance from reference point, negative going aft vtail_pos_vert = 3.4 //Feet, vertical distance from reference point, positive going up elevator_area = 53.5 //Square feet aileron_area = 12.1 //Square feet rudder_area = 46.4 //Square feet elevator_up_limit = 17.0 //Degrees elevator_down_limit = 15.5 //Degrees aileron_up_limit = 18.0 //Degrees aileron_down_limit = 18.0 //Degrees rudder_limit = 17.0 //Degrees elevator_trim_limit = 85.0 //Degrees spoiler_limit = 60.0 //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 = 92.0 //Knots True (KTAS) full_flaps_stall_speed = 72.0 //Knots True (KTAS) cruise_speed = 270.0 //Knots True (KTAS) max_indicated_speed = 242 //Red line (KIAS) max_mach=0.560000 [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= 150.0, 250.0 aileron= 150.0, 250.0 rudder= 150.0, 250.0 [stall_warning] type=1 [direction_indicators] direction_indicator.0=3,0 [exits] number_of_exits=2 exit_rate.0=0.4 ;Percent per second exit_rate.1=0.4 ;Percent per second [direction_indicators] direction_indicator.0=3,0 [brakes] toe_brakes_scale=1.062532 parking_brake=1 [gear_warning_system] gear_warning_available=1 pct_throttle_limit=0.099976 flap_limit_power=30.022988 flap_limit_idle=15.011494 [hydraulic_system] electric_pumps=0 engine_map=1,1,0,0 normal_pressure=3000.000000 [stall_warning] type=1 [attitude_indicators] attitude_indicator.0=1 [turn_indicators] turn_indicator.0=1,0