flight_model.cfg

	[VERSION]
major = 1
minor = 0
	[WEIGHT_AND_BALANCE]
max_gross_weight = 39500 ; Empty weight, (LBS)
empty_weight = 30000 ; Empty weight, (LBS)
reference_datum_position = 0, 0, 0 ; Position of reference datum relative to FS(0,0,0) (FEET), z, x, y
empty_weight_CG_position = -5.75, 0, 2 ; Position of airplane empty weight CG relative to reference datum (FEET), z, x, y
CG_forward_limit = 0.24 ; Gravity center forward limit in %MAX (divided by 100: 0.24 = 24%MAC)
CG_aft_limit = 0.40 ; Gravity center aft limit in %MAX (divided by 100: 0.40 = 40%MAC)
empty_weight_pitch_MOI = 315126 ; Empty pitch moment of inertia, Jxx (SLUG SQ FEET)
empty_weight_roll_MOI = 59034 ; Empty roll moment of inertia, Jzz (SLUG SQ FEET)
empty_weight_yaw_MOI = 336344 ; Empty yaw moment of inertia, Jyy (SLUG SQ FEET)
empty_weight_coupled_MOI = 1000 ; Empty transverse moment of inertia, Jyz (SLUG SQ FEET)
activate_mach_limit_based_on_cg = 0 ; Activate mach limitation depending on CG position (true if > 0 /false othewise). Mostly for Concorde).
activate_cg_limit_based_on_mach = 0 ; Activate cg limitation depending on mach value (true if > 0 /false othewise). Mostly for Concorde).
max_number_of_stations = 11 ; Number of payload stations
station_load.0 = 170, 19, -1.2, 4, TT:MENU.PAYLOAD.PILOT, 1
station_load.1 = 170, 19, 1.2, 4, TT:MENU.PAYLOAD.COPILOT, 2
station_load.2 = 170, 0, -1.2, 4, TT:MENU.PAYLOAD.PASSENGER_01, 3
station_load.3 = 170, 0, 1.2, 4, TT:MENU.PAYLOAD.PASSENGER_02, 3
station_load.4 = 0, 3.6, -1.2, 4, TT:MENU.PAYLOAD.PASSENGER_03, 3
station_load.5 = 0, 3.6, 1.2, 4, TT:MENU.PAYLOAD.PASSENGER_04, 3
station_load.6 = 0, -0.6, -1.2, 4, TT:MENU.PAYLOAD.PASSENGER_05, 3
station_load.7 = 0, -0.6, -1.2, 4, TT:MENU.PAYLOAD.PASSENGER_06, 3
station_load.8 = 0, -3.6, -1.2, 4, TT:MENU.PAYLOAD.PASSENGER_07, 3
station_load.9 = 0, -3.6, -1.2, 4, TT:MENU.PAYLOAD.PASSENGER_08, 3
station_load.10 = 100, -7.5, 0, 0, TT:MENU.PAYLOAD.BAGGAGE_01, 6
station_load.11 = 50, -10.5, 0, 0, TT:MENU.PAYLOAD.BAGGAGE_02, 6
	[CONTACT_POINTS]
static_pitch = -2.0 ; degrees, pitch when at rest on the ground (+=Up, -=Dn)
static_cg_height = 3.9 ; feet, altitude of CG when at rest on the ground
gear_system_type = 1 ; gear system type (betweeen 0 and 4) 0 = electrical, 1 = hydraulic, 2 = pneumatic, 3 = manual, 4 = none, 5 = undefined
tailwheel_lock = 0 ; Is tailwheel lock available TRUE/FALSE
max_number_of_points = 11 ; Number of contact points
gear_locked_on_ground = 0 ; Defines whether or not the landing gear handle is locked to down when the plane is on the ground.
gear_locked_above_speed = -1 ; Defines the speed at which the landing gear handle becomes locked in the up position. (-1 = Disabled)
max_speed_full_steering = 10 ; Defines the speed under which the full angle of steering is available (in feet/second).
max_speed_decreasing_steering = 20 ; Defines the speed above which the angle of steering stops decreasing (in feet/second).
min_available_steering_angle_pct = 0.2 ; Defines the percentage of steering which will always be available even above max_speed_decreasing_steering (in percent over 100).
max_speed_full_steering_castering = 20 ; Defines the speed under which the full angle of steering is available for free castering wheels (in feet/second).
max_speed_decreasing_steering_castering = 40 ; Defines the speed above which the angle of steering stops decreasing for free castering wheels  (in feet/second).
min_castering_angle = 0.05236 ; Defines the minimum angle a free castering wheel can take (in radians).
max_castering_angle = 3.14159265358979 ; Defines the maximum angle a free castering wheel can take (in radians).
point.0 = 1, 23.5, 0, -3.6, 750, 0, 0.635, 46.8, 0.334, 2.156, 0.91, 10, 10, 0, 260, 260, 2
point.1 = 1, -8.75, -4.75, -3.6, 1500, 1, 0.635, 0, 0.334, 1.538, 0.546, 9, 9, 2, 260, 260, 2
point.2 = 1, -8.75, 4.75, -3.6, 1500, 2, 0.635, 0, 0.334, 1.538, 0.546, 9, 9, 3, 260, 260, 2
point.3 = 2, 29.6, 0, 1.4, 100, 0, 0, 0, 0, 0, 0, 0, 0, 4, 0, 0, 1
point.4 = 2, 22, 0, 0.2, 500, 0, 0, 0, 0, 0, 0, 0, 0, 4, 0, 0, 1
point.5 = 2, 16, 0, 7.1, 1, 0, 0, 0, 0, 0, 0, 0, 0, 4, 0, 0, 1
point.6 = 2, -16, -32, 1.5, 350, 0, 0, 0, 0, 0, 0, 0, 0, 5, 0, 0, 1
point.7 = 2, -16, 32, 1.5, 350, 0, 0, 0, 0, 0, 0, 0, 0, 6, 0, 0, 1
point.8 = 2, -5, 0, -1.7, 500, 0, 0, 0, 0, 0, 0, 0, 0, 4, 0, 0, 1
point.9 = 2, -27, 0, 2.3, 750, 0, 0, 0, 0, 0, 0, 0, 0, 4, 0, 0, 1
point.10 = 2, -41, 0, 16, 100, 0, 0, 0, 0, 0, 0, 0, 0, 9, 0, 0, 1
	[FUEL]
LeftMain = -6.5, -10, 0, 430, 5 ; For each tank: Tank position (z longitudinal, x lateral, y vertical) (FEET), total fuel capacity (GALLONS), unusable fuel capacity (GALLONS)
RightMain = -6.5, 10, 0, 430, 5
Center1 = 0, 0, 0, 0, 0
Center2 = 0, 0, 0, 0, 0
Center3 = 0, 0, 0, 0, 0
LeftAux = 0, 0, 0, 0, 0
LeftTip = 0, 0, 0, 0, 0
RightAux = 0, 0, 0, 0, 0
RightTip = 0, 0, 0, 0, 0
External1 = 0, 0, 0, 0, 0
External2 = 0, 0, 0, 0, 0
fuel_type = 2 ; 1 = OCTANE 100, 2 = JET_A, 3 = OCTANE 80, 4 = AUTO GAS, 5 = JET B
number_of_tank_selectors = 2 ; Max 4
electric_pump = 1
engine_driven_pump = 1
manual_transfer_pump = 0
manual_pump = 0
anemometer_pump = 0
fuel_dump_rate = 0.02
default_fuel_tank_selector.1 = 1 ; Default fuel selector used in case of autostart for engine 1, default is ALL.
default_fuel_tank_selector.2 = 1 ; Default fuel selector used in case of autostart for engine 2, default is ALL.
default_fuel_tank_selector.3 = 1 ; Default fuel selector used in case of autostart for engine 3, default is ALL.
default_fuel_tank_selector.4 = 1 ; Default fuel selector used in case of autostart for engine 4, default is ALL.
	[AIRPLANE_GEOMETRY]
wing_area = 537 ; Wing area S (SQUARE FEET)
wing_span = 67 ; Wing span b (FEET)
wing_root_chord = 16 ; Wing root chord croot (FEET)
wing_camber = 1 ; (DEGREES)
wing_thickness_ratio = 0.033 ; Local thickness is local_chord(x)*wing_thickness_ratio, x = lateral coord
wing_dihedral = 3.5 ; Dihedral angle Lambda (DEGREES)
wing_incidence = 0 ; Wing incidence (DEGREES)
wing_twist = 0 ; Wing twist epsilon (DEGREES)
oswald_efficiency_factor = 0.75 ; Wing Oswald efficiency factor e (non dimensional)
wing_winglets_flag = 1 ; Has winglets true/false
wing_sweep = 31 ; Wing sweep (DEGREES)
wing_pos_apex_lon = 1.51747 ; Longitudinal (z) position of wing apex w.r.t reference datum (FEET)
wing_pos_apex_vert = 0 ; Vertical (y) position of wing apex w.r.t reference datum (FEET)
htail_area = 100 ; Horizontal tail area (SQUARE FEET)
htail_span = 27 ; Horizontal tail span (FEET)
htail_pos_lon = -38.5 ; Longitudinal (z) position of horizontal tail  w.r.t reference datum (FEET)
htail_pos_vert = 16 ; Vertical (y) position of horizontal tail  w.r.t reference datum (FEET)
htail_incidence = 0.9 ; Horizontal tail incidence (DEGREES)
htail_sweep = 35 ; Horizontal tail sweep angle (DEGREES)
htail_thickness_ratio = 0.02 ; Local thickness is local_chord(x)*htail_thickness_ratio, x = lateral coord
vtail_area = 120 ; Vertical tail area (SQUARE FEET)
vtail_span = 10 ; Vertical tail span (FEET)
vtail_sweep = 45 ; Vertical tail sweep angle (DEGREES)
vtail_pos_lon = -27 ; Longitudinal (z) position of vertical tail  w.r.t reference datum (FEET)
vtail_pos_vert = 10 ; Vertical (y) position of vertical tail  w.r.t reference datum (FEET)
vtail_thickness_ratio = 0.04 ; Local thickness is local_chord(x)*vtail_thickness_ratio, x = lateral coord
fuselage_length = 60 ; Nose to tail (FEET)
fuselage_diameter = 7.81
fuselage_center_pos = 5, 0, 3.5
elevator_area = 70 ; Elevator area (SQUARE FEET)
aileron_area = 13.5 ; Elevator area (SQUARE FEET)
rudder_area = 40 ; Elevator area (SQUARE FEET)
elevator_up_limit = 15 ; Elevator max deflection up angle (DEGREES)
elevator_down_limit = 14 ; Elevator max deflection down angle (absolute value) (DEGREES)
aileron_up_limit = 16 ; Aileron max deflection  angle (DEGREES)
aileron_down_limit = 15.2 ; Aileron max deflection down angle (absolute value) (DEGREES)
rudder_limit = 32 ; Rudder max deflection angle (absolute value) (DEGREES)
rudder_trim_limit = 32 ; Rudder trim max deflection angle (absolute value) (DEGREES)
elevator_trim_limit = 15 ; Elevator trim max angle (absolute value) (DEGREES)
spoiler_limit = 60 ; Spoiler max deflection angle (absolute value) (DEGREES)
spoilerons_available = 1 ; Aircraft has spoilerons true/false
aileron_to_spoileron_gain = 4.6 ; Aileron influence on spoileron angle (non-dimensional)
min_ailerons_for_spoilerons = 5 ; Minimum aileron deflection (absolute value) in which spoilerons are active (DEGREES)
min_flaps_for_spoilerons = 0 ; Minimum flaps deflection (absolute value) in which spoilerons are active (DEGREES)
spoiler_extension_time = 2 ; Spoilers extension time (SECONDS)
spoiler_handle_available = 1 ; Spoiler handles available true/false
auto_spoiler_available = 1 ; Auto spoilers available true/false
auto_spoiler_min_speed = 40 ; Auto spoilers minimum trigger speed
positive_g_limit_flaps_up = 3 ; Flap positive load limit when up. Same dimension as gravity vector FEET/SECONDS^2
positive_g_limit_flaps_down = 2.1 ; Flap positive load limit when down. Same dimension as gravity vector FEET/SECONDS^2
negative_g_limit_flaps_up = -2.4 ; Flap negative load limit when up. Same dimension as gravity vector FEET/SECONDS^2
negative_g_limit_flaps_down = -1.8 ; Flap negative load limit when down. Same dimension as gravity vector FEET/SECONDS^2
load_safety_factor = 1 ; Flap negative load limit when down. Same dimension as gravity vector FEET/SECONDS^2
elevator_trim_neutral = 1.5 ; Elevator trim max angle (absolute value) (DEGREES), for indicators only (no influence on flight model)
aileron_to_rudder_scale = 0 ; non-dimensional
flap_to_aileron_scale = 0 ; non-dimensional
fly_by_wire = 0 ; Fly-by-wire available true/false
elevator_elasticity_table = 0:1, 80:1, 120:0.75, 200:0.5, 450:0.33
aileron_elasticity_table = 0:1, 80:1, 120:0.75, 200:0.5, 450:0.25
rudder_elasticity_table = 0:1, 80:1, 120:0.75, 200:0.5, 450:0.25
elevator_trim_elasticity_table = 0:1, 80:1, 120:0.75, 200:0.5, 450:0.25
	[AERODYNAMICS]
lift_coef_pitch_rate = -11.40447
lift_coef_daoa = 0.0
lift_coef_delta_elevator = -1.39946
lift_coef_horizontal_incidence = 0.0
lift_coef_flaps = 0.65510
lift_coef_spoilers = -0.10000
drag_coef_zero_lift = 0.02330
drag_coef_flaps = 0.14470
drag_coef_gear = 0.00500
drag_coef_spoilers = 0.05000
side_force_slip_angle = -3.71452
side_force_roll_rate = 0.50713
side_force_yaw_rate = 3.81422
side_force_delta_rudder = -4.11296
pitch_moment_horizontal_incidence = 0.0
pitch_moment_delta_elevator = -5.85435
pitch_moment_delta_trim = -5.85435
pitch_moment_pitch_damping = -229.71300
pitch_moment_aoa_0 = -0.29284
pitch_moment_daoa = 0.0
pitch_moment_flaps = -0.25598
pitch_moment_gear = 0.00232
pitch_moment_spoilers = 0.00308
pitch_moment_delta_elevator_propwash = -1.46359
pitch_moment_pitch_propwash = 0.0
roll_moment_slip_angle = 0.40583
roll_moment_roll_damping = -0.84722
roll_moment_yaw_rate = -0.58929
roll_moment_spoilers = 0.0
roll_moment_delta_aileron = -0.13180
roll_moment_delta_rudder = 0.48399
roll_moment_delta_aileron_trim_scalar = -0.13180
yaw_moment_slip_angle = 1.15862
yaw_moment_roll = 0.04373
yaw_moment_yaw_damping = -9.29122
yaw_moment_yaw_propwash = 0.0
yaw_moment_delta_aileron = -0.00011
yaw_moment_delta_rudder = 1.40293
yaw_moment_delta_rudder_propwash = 0.35073
yaw_moment_delta_rudder_trim_scalar = 1.40293
compute_aero_center = 0
aero_center_lift = -5.50000
lift_coef_aoa_table = -3.15:0, -0.8:-1.256, -0.4:-1.072, -0.2:-0.761, -0.1:-0.331, 0:0.147, 0.20:0.975, 0.23:1.071, 0.26:1.153, 0.29:1.016, 0.31:0.973, 0.4:1.005, 0.8:1.307, 3.15:0
lift_coef_ground_effect_mach_table = 0.054:1.25
lift_coef_mach_table = 0:1
lift_coef_delta_elevator_mach_table = 0:0
lift_coef_daoa_mach_table = 0:0
lift_coef_pitch_rate_mach_table = 0:0
lift_coef_horizontal_incidence_mach_table = 0:0
drag_coef_zero_lift_mach_tab = 0:0.000, 0.5:0.000, 0.55:0.000, 0.6:0.000, 0.65:0.000, 0.7:0.000, 0.75:0.000, 0.8:0.000, 0.85:0.000, 0.9:0.000, 0.95:0.000, 1.0:2.000, 1.1:2.000, 1.5:2.000
side_force_slip_angle_mach_table = 0:0
side_force_delta_rudder_mach_table = 0:0
side_force_yaw_rate_mach_table = 0:0
side_force_roll_rate_mach_table = 0:0
pitch_moment_aoa_table = -3.15:0, -0.8:-1.635, -0.4:-1.385, -0.2:-0.667, -0.1:-0.378, 0:0, 0.20:0.946, 0.23:1.068, 0.26:1.183, 0.29:1.399, 0.31:1.489, 0.4:1.728, 0.8:2.243, 3.15:0
pitch_moment_delta_elevator_aoa_table = -180:-1, -40:0.113, -20:0.401, -10:0.771, -5:0.947, 0:1, 5:0.897, 10:0.704, 20:0.380, 40:-0.100, 180:-1
pitch_moment_horizontal_incidence_aoa_table = 0:1
pitch_moment_daoa_aoa_table = 0:1
pitch_moment_pitch_alpha_table = 0:1
pitch_moment_delta_elevator_mach_table = 0:0
pitch_moment_daoa_mach_table = 0:0
pitch_moment_pitch_rate_mach_table = 0:0
pitch_moment_horizontal_incidence_mach_table = 0:0
pitch_moment_aoa_0_mach_table = 0:0
roll_moment_aoa_table = 0:0
roll_moment_slip_angle_aoa_table = 0:1
roll_moment_roll_rate_aoa_table = 0:1
roll_moment_delta_aileron_aoa_table = 0:1
roll_moment_slip_angle_mach_table = 0:0
roll_moment_delta_rudder_mach_table = 0:0
roll_moment_delta_aileron_mach_table = 0:0
roll_moment_yaw_rate_mach_table = 0:0
roll_moment_roll_rate_mach_table = 0:0
yaw_moment_aoa_table = 0:0
yaw_moment_slip_angle_aoa_table = 0:1
yaw_moment_yaw_rate_aoa_table = 0:1
yaw_moment_delta_rudder_aoa_table = 0:1
yaw_moment_slip_angle_mach_table = 0:0
yaw_moment_delta_rudder_mach_table = 0:0
yaw_moment_delta_aileron_mach_table = 0:0
yaw_moment_yaw_rate_mach_table = 0:0
yaw_moment_roll_rate_mach_table = 0:0
elevator_scaling_table = 0:1
aileron_scaling_table = 0:1
rudder_scaling_table = 0:1
aileron_load_factor_effectiveness_table = 0:1
lift_coef_at_drag_zero = 0.10000
lift_coef_at_drag_zero_flaps = 0.10000
	[FLIGHT_TUNING]
cruise_lift_scalar = 1
parasite_drag_scalar = 1
induced_drag_scalar = 1
flap_induced_drag_scalar = 1
elevator_effectiveness = 1
elevator_maxangle_scalar = 1
aileron_effectiveness = 2
rudder_effectiveness = 1
rudder_maxangle_scalar = 0.5
pitch_stability = 0.25
roll_stability = 0.25
yaw_stability = 0.25
elevator_trim_effectiveness = 1
aileron_trim_effectiveness = 1
rudder_trim_effectiveness = 1
hi_alpha_on_roll = 0
hi_alpha_on_yaw = 0
p_factor_on_yaw = 0
torque_on_roll = 0
gyro_precession_on_roll = 0
gyro_precession_on_yaw = 0
engine_wash_on_roll = 0 ; Torque effect
	[REFERENCE SPEEDS]
full_flaps_stall_speed = 111 ; Knots True (KTAS)
flaps_up_stall_speed = 140 ; Knots True (KTAS)
cruise_speed = 483 ; Knots True (KTAS)
crossspeed = 305 ; (KIAS)
cruise_mach = 0.79
max_mach = 0.84 ; (Mmo)
max_indicated_speed = 500 ; Red line (KIAS)
max_flaps_extended = 200
normal_operating_speed = 320
airspeed_indicator_max = 600
rotation_speed_min = 120 ; Min speed required (Kts)
climb_speed = 185 ; Climb speed (Kts)
cruise_alt = 41000 ; (ft)
takeoff_speed = 120 ; Takeoff Speed (Kts)
spawn_cruise_altitude = 5000 ; Spawn Cruise Altitude (ft)
spawn_descent_altitude = 500 ; Spawn Descent Altitude (ft)
best_angle_climb_speed = 0 ; Best angle climb speed (Kts)
approach_speed = 149 ; Approach speed (Kts)
spawn_altitude = 5000 ; Spawn Altitude (ft)
	[INTERACTIVE POINTS]
number_of_interactive_points = 4
interactive_point.0 = 0, 10, -28, -3, 3, 0, 0, -90, 0, 0, 0, 0, 0, 0
interactive_point.1 = 0, 10, 28, -3, 3, 0, 0, 90, 0, 0, 0, 0, 0, 0
interactive_point.2 = 0, -30, -20, -3, 4, 0, 0, -135, 0, 0, 0, 0, 0, 0
interactive_point.3 = 0, -30, 20, -3, 4, 0, 0, 135, 0, 0, 0, 0, 0, 0
	;===================== FLAPS =====================
	[FLAPS.0]
type = 1 ; Flap type 0 = None, 1 = trailing edge, 2 = leading edge
system_type = 0 ; Flap system type 0 = electrical, 1 = hydraulic, 2 = pneumatic, 3 = manual, 4 = none
span-outboard = 0.7 ; Outboard span area (added area) (percentage, non dimensional)
extending-time = 5 ; Flap extension time (SECONDS)
damaging-speed = 275 ; Speed above which flap is damaged (Kts)
blowout-speed = 305 ; Speed above which flap is blown out (Kts)
maneuvering_flaps = 0
lift_scalar = 1.64 ; Scalar coefficient to ponderate global flap lift coef (non dimensioned)
drag_scalar = 0 ; Scalar coefficient to ponderate global flap drag coef (non dimensioned)
pitch_scalar = 0 ; Scalar coefficient to ponderate global flap pitch coef (non dimensioned)
max_on_ground_position = 3 ; Dynamically set in-tool to last flap-position index by defaut when -1 is found.
flaps-position.0 = 0, -1, 0
flaps-position.1 = 7, 250, 0.5
flaps-position.2 = 15, 210, 0.75
flaps-position.3 = 35, 180, 1
	[FLAPS.1]
type = 2 ; Flap type 0 = None, 1 = trailing edge, 2 = leading edge
system_type = 0 ; Flap system type 0 = electrical, 1 = hydraulic, 2 = pneumatic, 3 = manual, 4 = none
span-outboard = 0.7 ; Outboard span area (added area) (percentage, non dimensional)
extending-time = 5 ; Flap extension time (SECONDS)
damaging-speed = 275 ; Speed above which flap is damaged (Kts)
blowout-speed = 305 ; Speed above which flap is blown out (Kts)
maneuvering_flaps = 0
lift_scalar = 0 ; Scalar coefficient to ponderate global flap lift coef (non dimensioned)
drag_scalar = 0 ; Scalar coefficient to ponderate global flap drag coef (non dimensioned)
pitch_scalar = 1.64 ; Scalar coefficient to ponderate global flap pitch coef (non dimensioned)
max_on_ground_position = 3 ; Dynamically set in-tool to last flap-position index by defaut when -1 is found.
flaps-position.0 = 0, -1, 0
flaps-position.1 = 7, -1, 0.5
flaps-position.2 = 15, -1, 0.75
flaps-position.3 = 35, -1, 1
	[FLAPS.2]
type = 1 ; Flap type 0 = None, 1 = trailing edge, 2 = leading edge
system_type = 0 ; Flap system type 0 = electrical, 1 = hydraulic, 2 = pneumatic, 3 = manual, 4 = none
span-outboard = 0.7 ; Outboard span area (added area) (percentage, non dimensional)
extending-time = 5 ; Flap extension time (SECONDS)
damaging-speed = 275 ; Speed above which flap is damaged (Kts)
blowout-speed = 305 ; Speed above which flap is blown out (Kts)
maneuvering_flaps = 0
lift_scalar = 0 ; Scalar coefficient to ponderate global flap lift coef (non dimensioned)
drag_scalar = 1.64 ; Scalar coefficient to ponderate global flap drag coef (non dimensioned)
pitch_scalar = 0 ; Scalar coefficient to ponderate global flap pitch coef (non dimensioned)
max_on_ground_position = 3 ; Dynamically set in-tool to last flap-position index by defaut when -1 is found.
flaps-position.0 = 0, -1, 0
flaps-position.1 = 7, -1, 0.5
flaps-position.2 = 15, -1, 0.75
flaps-position.3 = 35, -1, 1

25 minutes ago, odourboy said:

Have you been able to do this successfully with the longitude (or another premium locked aircraft)?

Yes, I did so for the tbm930. I took the flight_model.cfg from asobo-aircraft-generic-turbo-singleengine and changed the elevator, aileron and rudder sensitivities

1 minute ago, willy647 said:

Yes, I did so for the tbm930

...but the TBM is not encrypted so your attempt would not be blocked.

1 minute ago, hangar said:

...but the TBM is not encrypted so your attempt would not be blocked.

Ok, then someone will just have to try it and see if it works .....

43 minutes ago, odourboy said:

Have you been able to do this successfully with the longitude (or another premium locked aircraft)?

Apparently he has not...and I don't own Premium version with the Longitude.

But I do have the Deluxe version and if you like, perhaps later tonight I can try making an obvious flight model change to one of those planes, such as the Baron and see if it works there at least.

Edited September 21, 20205 yr by hangar

2 hours ago, willy647 said:

 

 

Deleted.

 

Edited September 21, 20205 yr by killthespam