// Aircraft.cfg listing for the Ford Tri-Motor
// Microsoft Default aircraft
// to accommodate the Repaints by Garry J. Smith
// of www.gjsmith.net - most repaints commissioned by:
// Edwards C. Moore - a generous and gregarious simmer.



[fltsim.0]
title=AI-Ford 4-AT-E Finland-OH-ALK
SIM=Ford_Trimotor
model=
panel=
sound=
texture=Finland-OH-ALK
atc_id=OH-ALK
ui_manufacturer=AI-Ford-Finland
ui_type=Tri-Motor
ui_variation=Finland-OH-ALK
description=Nicknamed the "Tin Goose," the Ford 4-AT Tri-Motor pioneered early airline and air transport routes. In 1925, the Ford Motor Company bought the Stout Metal Plane Company to gain rights to the Tri-Motor design. In all, 198 Ford Tri-Motors were built. During its years of regular service in the late 1920s and early 1930s, the Ford Tri-Motor helped popularize commercial flight and promote the safety of flying to travelers.
atc_airline=Aero OY
atc_flight_number=
atc_parking_types=RAMP
atc_id_color=0x00000000
atc_id_font=Verdana,-24,1,999,0
atc_parking_codes=TM1


[fltsim.1]
title=AI-Ford 4-AT-E Finland-OH-BLA
SIM=Ford_Trimotor
model=
panel=
sound=
texture=Finland-OH-BLA
atc_id=OH-BLA
ui_manufacturer=AI-Ford-Finland
ui_type=Tri-Motor
ui_variation=Finland-OH-BLA
description=Nicknamed the "Tin Goose," the Ford 4-AT Tri-Motor pioneered early airline and air transport routes. In 1925, the Ford Motor Company bought the Stout Metal Plane Company to gain rights to the Tri-Motor design. In all, 198 Ford Tri-Motors were built. During its years of regular service in the late 1920s and early 1930s, the Ford Tri-Motor helped popularize commercial flight and promote the safety of flying to travelers.
atc_airline=Aero OY
atc_flight_number=
atc_parking_types=RAMP
atc_id_color=0x00000000
atc_id_font=Verdana,-24,1,999,0
atc_parking_codes=TM1

[fltsim.2]
title=AI-Ford 4-AT-E Finland-OH-BLB
SIM=Ford_Trimotor
model=
panel=
sound=
texture=Finland-OH-BLB
atc_id=OH-BLB
ui_manufacturer=AI-Ford-Finland
ui_type=Tri-Motor
ui_variation=Finland-OH-BLB
description=Nicknamed the "Tin Goose," the Ford 4-AT Tri-Motor pioneered early airline and air transport routes. In 1925, the Ford Motor Company bought the Stout Metal Plane Company to gain rights to the Tri-Motor design. In all, 198 Ford Tri-Motors were built. During its years of regular service in the late 1920s and early 1930s, the Ford Tri-Motor helped popularize commercial flight and promote the safety of flying to travelers.
atc_airline=Aero OY
atc_flight_number=
atc_parking_types=RAMP
atc_id_color=0x00000000
atc_id_font=Verdana,-24,1,999,0
atc_parking_codes=TM1

[fltsim.3]
title=AI-Ford 4-AT-E Finland-OH-LAP
SIM=Ford_Trimotor
model=
panel=
sound=
texture=Finland-OH-LAP
atc_id=OH-LAP
ui_manufacturer=AI-Ford-Finland
ui_type=Tri-Motor
ui_variation=Finland-OH-LAP
description=Nicknamed the "Tin Goose," the Ford 4-AT Tri-Motor pioneered early airline and air transport routes. In 1925, the Ford Motor Company bought the Stout Metal Plane Company to gain rights to the Tri-Motor design. In all, 198 Ford Tri-Motors were built. During its years of regular service in the late 1920s and early 1930s, the Ford Tri-Motor helped popularize commercial flight and promote the safety of flying to travelers.
atc_airline=Aero OY
atc_flight_number=
atc_parking_types=RAMP
atc_id_color=0x00000000
atc_id_font=Verdana,-24,1,999,0
atc_parking_codes=TM1

[fltsim.4]
title=AI-Ford 4-AT-E Finland-OH-ALL
SIM=Ford_Trimotor
model=
panel=
sound=
texture=Finland-OH-ALL
atc_id=OH-ALL
ui_manufacturer=AI-Ford-Finland
ui_type=Tri-Motor
ui_variation=Finland-OH-ALL
description=Nicknamed the "Tin Goose," the Ford 4-AT Tri-Motor pioneered early airline and air transport routes. In 1925, the Ford Motor Company bought the Stout Metal Plane Company to gain rights to the Tri-Motor design. In all, 198 Ford Tri-Motors were built. During its years of regular service in the late 1920s and early 1930s, the Ford Tri-Motor helped popularize commercial flight and promote the safety of flying to travelers.
atc_airline=Aero OY
atc_flight_number=
atc_parking_types=RAMP
atc_id_color=0x00000000
atc_id_font=Verdana,-24,1,999,0
atc_parking_codes=TM1

[fltsim.5]
title=AI-Ford 4-AT-E Finland-OH-LAK
SIM=Ford_Trimotor
model=
panel=
sound=
texture=Finland-OH-LAK
atc_id=OH-LAK
ui_manufacturer=AI-Ford-Finland
ui_type=Tri-Motor
ui_variation=Finland-OH-LAK
description=Nicknamed the "Tin Goose," the Ford 4-AT Tri-Motor pioneered early airline and air transport routes. In 1925, the Ford Motor Company bought the Stout Metal Plane Company to gain rights to the Tri-Motor design. In all, 198 Ford Tri-Motors were built. During its years of regular service in the late 1920s and early 1930s, the Ford Tri-Motor helped popularize commercial flight and promote the safety of flying to travelers.
atc_airline=Aero OY
atc_flight_number=
atc_parking_types=RAMP
atc_id_color=0x00000000
atc_id_font=Verdana,-24,1,999,0
atc_parking_codes=TM1



// -----------------------------------------------------------------------------------------
// -----------------------------------------------------------------------------------------

[General]
atc_type=Trimotor
atc_model=
editable=0
performance="Maximum Speed\n130 mph	113 kts	209 km/hr\n\nCruise Speed\n110 mph    96 kts	177 km/hr\n\nEngine\nThree 300-hp Wright Whirlwind J-6\n\nPropeller\nTwo-bladed, metal\n\nMaximum Range\n670 mi	1,078 km\n\nService Ceiling\n14,500 ft	4,420 m\n\nFuel Capacity\n231 gal	874 L\n\nEmpty Weight\n6,600 lb	2,994 kg\n\nMaximum Gross Weight\n10,130 lb	4,595 kg\n\nLength\n49 ft, 10  in    15 m\n\nWingspan\n74 ft	22.55 m\n\nHeight\n12 ft, 8  in	3.89 m\n\nSeating\n9\n\nUseful Load\n3,530 lb	1,601 kg"


[WEIGHT_AND_BALANCE]
max_gross_weight = 10130                         // (pounds)
empty_weight =  6600                            // (pounds)

reference_datum_position     =   1.00, 0, 0         // (feet) distance from FlightSim Reference position: (1/4 chord, centerline, waterline)
empty_weight_CG_position     =  -1.64, 0, 0         // (feet) longitudinal, lateral, vertical distance from specified datum

max_number_of_stations =50

station_load.0  = "170.0,   4.9, -1.5, 1.0, Pilot"              //Weight (lbs), longitudinal, lateral, vertical positions from datum (feet)
station_load.1  =   "0.0,   4.9,  1.5, 1.0, Co-Pilot"           //Weight (lbs), longitudinal, lateral, vertical positions from datum (feet)
station_load.2  = "170.0,   1.2, -1.5, 0.0, Passenger 1"        //Weight (lbs), longitudinal, lateral, vertical positions from datum (feet)
station_load.3  = "170.0,   1.2,  1.5, 0.0, Passenger 2"        //Weight (lbs), longitudinal, lateral, vertical positions from datum (feet)
station_load.4  =   "0.0,  -2.0, -1.5, 0.0, Passenger 3"        //Weight (lbs), longitudinal, lateral, vertical positions from datum (feet)
station_load.5  = "170.0,  -2.0,  1.5, 0.0, Passenger 4"        //Weight (lbs), longitudinal, lateral, vertical positions from datum (feet)
station_load.6  = "170.0,  -4.4, -1.5, 0.0, Passenger 5"        //Weight (lbs), longitudinal, lateral, vertical positions from datum (feet)
station_load.7  = "170.0,  -4.4,  1.5, 0.0, Passenger 6"        //Weight (lbs), longitudinal, lateral, vertical positions from datum (feet)
station_load.8  =   "0.0,  -6.8, -1.5, 0.0, Passenger 7"        //Weight (lbs), longitudinal, lateral, vertical positions from datum (feet)
station_load.9  =   "0.0,  -6.8,  1.5, 0.0, Passenger 8"        //Weight (lbs), longitudinal, lateral, vertical positions from datum (feet)
station_load.10 =   "0.0,  -7.9, -1.5, 0.0, Passenger 9"        //Weight (lbs), longitudinal, lateral, vertical positions from datum (feet)
station_load.11 = "250.0, -10.2,  0.0, 0.0, Baggage"            //Weight (lbs), longitudinal, lateral, vertical positions from datum (feet)

;Moments of Inertia
empty_weight_pitch_MOI   = 14885.4
empty_weight_roll_MOI    = 13264.7
empty_weight_yaw_MOI     = 28402.6
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
p_factor_on_yaw          = 0.5

[Flaps.0]
type= 0
span-outboard= 0.5
extending-time= 0.0
system_type= 0
flaps-position.0= 0.0, 0.0
flaps-position.1= 0.0, 0.0

[GeneralEngineData]
engine_type = 0                                 //0=Piston, 1=Jet, 2=None, 3=Helo-Turbine, 4=Rocket, 5=Turboprop
Engine.0 =  3.5, -9.6, 0.0                      //(feet) longitudinal, lateral, vertical distance from reference datum
Engine.1 = 12.2,  0.0, 0.0                      //(feet) longitudinal, lateral, vertical distance from reference datum
Engine.2 =  3.5,  9.6, 0.0                      //(feet) longitudinal, lateral, vertical distance from reference datum
fuel_flow_scalar= 1.0                           //Fuel flow scalar
min_throttle_limit = 0.0                        //Minimum percent throttle.  Generally negative for turbine reverser
master_ignition_switch = 1                      //Master Ignition Switch

[piston_engine]
power_scalar = 1.0                              //Piston power scalar
cylinder_displacement= 108.33                    //Cubic inches per cylinder
compression_ratio= 5.1                          //Compression ratio
number_of_cylinders=9                           //Number of cylinders
max_rated_rpm= 2000                             //Max rated RPM
max_rated_hp= 300                               //Max rated HP
fuel_metering_type= 1                           //0=Fuel Injected, 1=Gravity Carburetor, 2=Aerobatic Carburetor
cooling_type= 0                                 //0=Cooling type Air, 1=Cooling type Liquid
normalized_starter_torque= 0.3                  //Starter torque factor
turbocharged= 0                                 //Is it turbocharged? 0=FALSE, 1=TRUE
max_design_mp= 0                                //Max design manifold pressure, (inHg)
min_design_mp= 0                                //Min design manifold pressure, (inHg)
critical_altitude= 0                            //Altitude to which the turbocharger will provide max design manifold pressure (feet)
emergency_boost_type= 0                         //0=None, 1=Water Injection, 2=Methanol/Water injection, 3=War Emergency Power
emergency_boost_mp_offset= 0                    //Additional manifold pressure supplied by emergency boost
emergency_boost_gain_offset= 0                  //Multiplier on manifold pressure due to emergency boost
fuel_air_auto_mixture= 0                        //Automixture available? 0=FALSE, 1=TRUE
auto_ignition= 0                                //Auto-Ignition available? 0=FALSE, 1=TRUE
max_rpm_mechanical_efficiency_scalar= 1.0       //Scalar on maximum RPM mechanical efficiency
idle_rpm_mechanical_efficiency_scalar= 1.0      //Scalar on idle RPM mechanical efficiency
max_rpm_friction_scalar= 1.0                    //Scalar on maximum RPM friction
idle_rpm_friction_scalar= 1.0                   //Scalar on idle RPM friction

[propeller]
thrust_scalar = 1.0                             //Propeller thrust scalar
propeller_type= 1                               //0=Constant Speed, 1=Fixed Pitch
propeller_diameter= 8.9                         //Propeller Diameter, (feet)
propeller_blades= 2                             //Number of propeller blades
propeller_moi= 12.3                             //Propeller moment of inertia
beta_max= 0                                     //Maximum blade pitch angle for constant speed prop, (degrees)
beta_min= 0                                     //Minimum blade pitch angle for constant speed prop, (degrees)
min_gov_rpm= 1400                               //Miminum governed RPM
prop_tc= 0.0                                    //Prop time-constant
gear_reduction_ratio= 1.0                       //Propeller gear reduction ratio
fixed_pitch_beta= 25                            //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= 0                         //Prop de-icing available? 0=FALSE, 1=TRUE
prop_feathering_available= 0                    //Prop feathering available?  0=FALSE, 1=TRUE
prop_auto_feathering_available= 0               //Prop auto-feathering available?  0=FALSE, 1=TRUE
min_rpm_for_feather= 0                          //Minimum RPM for prop feathering
beta_feather= 0                                 //Feathering pitch angle (degrees)
power_absorbed_cf= 0                            //Coefficient of friction for power absorbed by propeller by feathered prop
defeathering_accumulators_available= 0          //Defeathering accumulators available? 0=FALSE, 1=TRUE 
prop_reverse_available= 0                       //Prop reverse available?  0=FALSE, 1=TRUE
minimum_on_ground_beta= 0                       //Miminum pitch angle on ground, (degrees)
minimum_reverse_beta= 0                         //Minimum pitch angle in reverse, (degrees)


        //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, -36.5,   0.0,  0.5, 1200.0, 0, 0.74, 180.0, 0.240, 2.5, 0.695, 0.0, 0.0, 0.0, 0.0, 0.0
point.1=1,   0.1,  -9.3, -8.2, 1600.0, 1, 1.53,   0.0, 0.504, 2.5, 0.686, 0.0, 0.0, 2.0, 0.0, 0.0
point.2=1,   0.1,   9.3, -8.2, 1600.0, 2, 1.53,   0.0, 0.504, 2.5, 0.682, 0.0, 0.0, 3.0, 0.0, 0.0
point.3=2,  -1.6, -38.5,  5.0,  800.0, 0, 0.00,   0.0, 0.000, 0.0, 0.000, 0.0, 0.0, 5.0, 0.0, 0.0
point.4=2,  -1.6,  38.5,  5.0,  800.0, 0, 0.00,   0.0, 0.000, 0.0, 0.000, 0.0, 0.0, 6.0, 0.0, 0.0
point.5=2, -36.0,   0.0, 10.2,  800.0, 0, 0.00,   0.0, 0.000, 0.0, 0.000, 0.0, 0.0, 9.0, 0.0, 0.0
point.6=2,  11.0,   0.0, -3.0,  800.0, 0, 0.00,   0.0, 0.000, 0.0, 0.000, 0.0, 0.0, 4.0, 0.0, 0.0

static_pitch = 13.4
static_cg_height = 7.26

[brakes]
parking_brake = 1       //Parking brake available
toe_brakes_scale = 0.5  //Brake scalar
differential_braking_scale = 1.0        //Delta on the amount of brake when the rudder pedals deflected

[hydraulic_system]
normal_pressure = 0.0    //PSI

[Views]
eyepoint = 4.731, -1.012, 3.771

[LIGHTS]
//Types: 1=beacon, 2=strobe, 3=navigation, 4=cockpit, 5=landing
light.0 = 3,  -2.05, -38.9,  4.91, fx_navred ,
light.1 = 3,  -2.05,  38.9,  4.91, fx_navgre ,
light.2 = 4,  5.95, 0.00, 2.65, fx_vclight,
light.3 = 4,  -2.00,   0.00,  2.50, fx_vclighth,

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

[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 =200, 1000
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=0,0

[attitude_indicators]
//Type: 0=None, 1=Vacuum Gyro, 2=Electric Gyro
attitude_indicator.0 = 0

[turn_indicators]
//Type: 0=None, 1=Electric Gyro, 2=Vacuum Gyro
turn_indicator.0=2,0

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

[electrical]
max_battery_voltage = 12
generator_alternator_voltage = 13
max_generator_alternator_amps = 25
engine_generator_map= 0,1,0

[fuel]
LeftMain = -1.0, -5.9, 3.6, 100.0, 0.0  //Longitudinal (feet), Lateral (feet), Vertical (feet), Usable(gallons), Unusable (gallons)
RightMain= -1.0,  5.9, 3.6, 100.0, 0.0  //Longitudinal (feet), Lateral (feet), Vertical (feet), Usable(gallons), Unusable (gallons)
Center1  = -1.0,  0.0, 3.6,  31.0, 0.0  //Longitudinal (feet), Lateral (feet), Vertical (feet), Usable(gallons), Unusable (gallons)
fuel_type = 1                                //Fuel type: 1 = Avgas, 2 = JetA
number_of_tank_selectors = 3                    
electric_pump=0

[airplane_geometry]
wing_area               = 785.0                 //Square feet
wing_span               = 74.0                  //Feet
wing_root_chord         = 12.84                 //Feet
wing_dihedral           = 0.0                   //Degrees
wing_incidence          = 2.0                   //Degrees
wing_twist              = 0.0                  //Degrees
oswald_efficiency_factor= 0.6                   //Measure of lift effeciency of wing
wing_winglets_flag      = 0                     //Are winglets available?
wing_sweep              = 1.5                   //Degrees, wing leading edge
wing_pos_apex_lon       = 1.50                 //Feet, longitudinal distance from reference point, negative going aft
wing_pos_apex_vert      = 4.3                   //Feet, vertical distance from reference point, positive going up

htail_area              = 114.0                  //Square feet
htail_span              = 21.7                  //Feet
htail_pos_lon           = -32.4                 //Feet, longitudinal distance from reference point, negative going aft
htail_pos_vert          = 3.9                   //Feet, vertical distance from reference point, positive going up
htail_incidence         = 0.0                   //Degrees
htail_sweep             = 0.0                   //Degrees, horizontal tail leading edge

vtail_area              = 61.0                  //Square feet
vtail_span              = 9.4                   //Feet, tip to body
vtail_sweep             = 44.0                   //Degrees, vertical tail leading edge
vtail_pos_lon           = -32.4                 //Feet, longitudinal distance from reference point, negative going aft
vtail_pos_vert          = 6.1                   //Feet, vertical distance from reference point, positive going up

elevator_area           = 52.8                  //Square feet
aileron_area            = 33.8                  //Square feet
rudder_area             = 23.0                  //Square feet
elevator_up_limit       = 30.0                  //Degrees
elevator_down_limit     = 20.0                  //Degrees
aileron_up_limit        = 20.0                  //Degrees
aileron_down_limit      = 20.0                  //Degrees
rudder_limit            = 30.0                  //Degrees
elevator_trim_limit     = 19.5                  //Degrees
spoiler_limit           = 0.0                   //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    = 50.4                  //Knots True (KTAS)
full_flaps_stall_speed  = 50.4                  //Knots True (KTAS)
cruise_speed            = 76.5                  //Knots True (KTAS)
max_indicated_speed     = 145                   //Red line (KIAS)

[autopilot]
autopilot_available= 0
flight_director_available= 0

[forcefeedback]
ground_bumps_magnitude1=2600            ; 0 - 10000
ground_bumps_angle1=8900                ; 0 - 35999 degrees
ground_bumps_intercept1=5.0
ground_bumps_slope1=0.6
ground_bumps_magnitude2=1200            ; 0 - 10000
ground_bumps_angle2=9100                ; 0 - 35999 degrees
ground_bumps_intercept2=0.085
ground_bumps_slope2=0.65
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=3500000                 ; in microseconds

[exits]
number_of_exits = 1
exit_rate.0 = 0.4                               ;Percent per second

[stall_warning]
type=1

