No matter if I'm in the Turbo bonanza or CJ4, during a strong crosswind takeoff I find the aircraft veers off into the wind no matter how much opposite rudder and aileron correction I use during the takeoff roll.   Would love a challenging crosswind takeoff but something seems way off in this regard in the flight models.

Edited January 13, 20215 yr by sidfadc

Weather vaning does seem excessive, I agree.

just took off from EGMC in the CJ4, literally after I set take off power I careered off into the grass.  Pull up!  Pull up!  Skimmed the top of the terminal and could hear the screams lol

The bottom line is that Asobo needs to get their act together and fix the aircraft physics, (all of them) and if people are not complaining enough it will stay as it is, total unrealistic.

Regarding the CJ14 I did some modifications and it can be controlled on a wet rwy  centerline up to 25KTS xwind, I don't know what is the demonstrated xwind component for this aircraft.

Take the flight_model.cfg and save it to a new location as a backup in case you don't like the settings.

Now  delete the content inside flight_model.cfg and copy this new data:

Spoiler

[VERSION]
major = 1
minor = 0

[WEIGHT_AND_BALANCE]
max_gross_weight = 17110 ; Empty weight, (LBS)
empty_weight = 10280 ; 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 = -2.0, 0, 2.5 ; Position of airplane empty weight CG relative to reference datum (FEET), z, x, y
CG_forward_limit = 0.145 ; Gravity center forward limit (longitudinal offset) for longitudinal stability
CG_aft_limit = 0.28 ; Gravity center after limit (longitudinal offset z) w.r.t reference datum for longitudinal stability (FEET)
empty_weight_pitch_MOI = 69403 ; Empty pitch moment of inertia, Jxx (SLUG SQ FEET)
empty_weight_roll_MOI = 13434 ; Empty roll moment of inertia, Jzz (SLUG SQ FEET)
empty_weight_yaw_MOI = 75997 ; Empty yaw moment of inertia, Jyy (SLUG SQ FEET)
empty_weight_coupled_MOI = 100 ; 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 = 9 ; Number of payload stations
station_load.0 = 170, 17.5, -1.2, 4, TT:MENU.PAYLOAD.PILOT, 1
station_load.1 = 170, 17.5, 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 = 100, -7.5, 0, 0, TT:MENU.PAYLOAD.BAGGAGE_01, 6
station_load.8 = 50, -10.5, 0, 0, TT:MENU.PAYLOAD.BAGGAGE_02, 6

[CONTACT_POINTS]
static_pitch = -1.7 ; degrees, pitch when at rest on the ground (+=Up, -=Dn)
static_cg_height = 2.75 ; 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 = 10 ; 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, 16.5, 0, -2.6, 750, 0, 0.7, 35, 0.29, 2.12, 0.33, 10, 10, 0, 260, 260, 2
point.1 = 1, -4.25, -6, -3, 1500, 1, 0.77, 0, 0.14, 2.06, 0.33, 9, 9, 2, 260, 260, 2
point.2 = 1, -4.25, 6, -3, 1500, 2, 0.77, 0, 0.14, 2.06, 0.33, 9, 9, 3, 260, 260, 2
point.3 = 2, -6.5, -25, 1.6, 350, 0, 0, 0, 0, 0, 0, 0, 0, 5, 0, 0, 1
point.4 = 2, -6.5, 25, 1.6, 350, 0, 0, 0, 0, 0, 0, 0, 0, 6, 0, 0, 1
point.5 = 2, -17.4, 0, 1.5, 750, 0, 0, 0, 0, 0, 0, 0, 0, 9, 0, 0, 1
point.6 = 2, 21.9, 0, 1.7, 350, 0, 0, 0, 0, 0, 0, 0, 0, 4, 0, 0, 1
point.7 = 2, -30, 0, 12, 350, 0, 0, 0, 0, 0, 0, 0, 0, 9, 0, 0, 1
point.8 = 2, -3.5, 0, -0.7, 350, 0, 0, 0, 0, 0, 0, 0, 0, 4, 0, 0, 1
point.9 = 2, 15, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 4, 0, 0, 1

[FUEL]
LeftMain = -3.5, -6, 0.5, 430, 5 ; For each tank: Tank position (z longitudinal, x lateral, y vertical) (FEET), total fuel capacity (GALLONS), unusable fuel capacity (GALLONS)
RightMain = -3.5, 6, 0.5, 430, 5
Center1 = -3.6, 0, 0, 0, 0
Center2 = -3.6, 0, 0, 0, 0
Center3 = -3.6, 0, 0, 0, 0
LeftAux = -3.6, 0, 0, 0, 0
LeftTip = -3.6, 0, 0, 0, 0
RightAux = -3.6, 0, 0, 0, 0
RightTip = -3.6, 0, 0, 0, 0
External1 = -3.6, 0, 0, 0, 0
External2 = -3.6, 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.
fuel_transfer_pump.0 = 19, 20, 0.0714, 1
fuel_transfer_pump.1 = 20, 19, 0.0714, 2

[AIRPLANE_GEOMETRY]
wing_area = 330 ; Wing area S (SQUARE FEET)
wing_span = 50.8 ; Wing span b (FEET)
wing_root_chord = 11 ; Wing root chord croot (FEET)
wing_camber = 1 ; (DEGREES)
wing_thickness_ratio = 0.02 ; Local thickness is local_chord(x)*wing_thickness_ratio, x = lateral coord
wing_dihedral = 3.7 ; Dihedral angle Lambda (DEGREES)
wing_incidence = 0 ; Wing incidence (DEGREES)
wing_twist = -4 ; Wing twist epsilon (DEGREES)
oswald_efficiency_factor = 0.75 ; Wing Oswald efficiency factor e (non dimensional)
wing_winglets_flag = 0 ; Has winglets true/false
wing_sweep = 16 ; 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 = 50 ; Horizontal tail area (SQUARE FEET)
htail_span = 22.3 ; Horizontal tail span (FEET)
htail_pos_lon = -28.5 ; Longitudinal (z) position of horizontal tail  w.r.t reference datum (FEET)
htail_pos_vert = 12 ; Vertical (y) position of horizontal tail  w.r.t reference datum (FEET)
htail_incidence = 2 ; Horizontal tail incidence (DEGREES)
htail_sweep = 20 ; Horizontal tail sweep angle (DEGREES)
htail_thickness_ratio = 0.04 ; Local thickness is local_chord(x)*htail_thickness_ratio, x = lateral coord
vtail_area = 40 ; Vertical tail area (SQUARE FEET)
vtail_span = 7 ; Vertical tail span (FEET)
vtail_sweep = 45 ; Vertical tail sweep angle (DEGREES)
vtail_pos_lon = -21 ; Longitudinal (z) position of vertical tail  w.r.t reference datum (FEET)
vtail_pos_vert = 8 ; 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 = 48 ; Nose to tail (FEET)
fuselage_diameter = 5.68
fuselage_center_pos = 3, 0, 3
elevator_area = 30 ; Elevator area (SQUARE FEET)
aileron_area = 14.1 ; Elevator area (SQUARE FEET)
rudder_area = 30 ; Elevator area (SQUARE FEET)
elevator_up_limit = 25.5 ; Elevator max deflection up angle (DEGREES)
elevator_down_limit = 12 ; Elevator max deflection down angle (absolute value) (DEGREES)
aileron_up_limit = 23 ; Aileron max deflection  angle (DEGREES)
aileron_down_limit = 20 ; Aileron max deflection down angle (absolute value) (DEGREES)
rudder_limit = 16 ; Rudder max deflection angle (absolute value) (DEGREES)
rudder_trim_limit = 16 ; 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 = 0 ; 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 = 0 ; Auto spoilers available true/false
auto_spoiler_min_speed = 0 ; 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 = -1.7 ; 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 = 4 ; 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, 200:0.9, 400:0.33
aileron_elasticity_table = 0:1, 80:1, 200:0.9, 400:0.33
rudder_elasticity_table = 0:1, 80:1, 200:0.9, 400:0.33
elevator_trim_elasticity_table = 0:1, 80:1, 200:0.9, 400:0.33

[AERODYNAMICS]
lift_coef_pitch_rate = -21.65623
lift_coef_daoa = 0.0
lift_coef_delta_elevator = -1.25480
lift_coef_horizontal_incidence = 0.0
lift_coef_flaps = 0.50180
lift_coef_spoilers = -0.10000
drag_coef_zero_lift = 0.02270
drag_coef_flaps = 0.14530
drag_coef_gear = 0.00500
drag_coef_spoilers = 0.10000
side_force_slip_angle = -2.76027
side_force_roll_rate = 0.46763
side_force_yaw_rate = 3.17528
side_force_delta_rudder = -2.95991
pitch_moment_horizontal_incidence = 0.0
pitch_moment_delta_elevator = -5.17207
pitch_moment_delta_trim = -5.17207
pitch_moment_pitch_damping = -384.10074
pitch_moment_aoa_0 = -0.11408
pitch_moment_daoa = 0.0
pitch_moment_flaps = 0.01969
pitch_moment_gear = 0.00306
pitch_moment_spoilers = -0.03020
pitch_moment_delta_elevator_propwash = -1.29302
pitch_moment_pitch_propwash = 0.0
roll_moment_slip_angle = 0.20555
roll_moment_roll_damping = -1.26308
roll_moment_yaw_rate = -0.23831
roll_moment_spoilers = 0.0
roll_moment_delta_aileron = -0.21060
roll_moment_delta_rudder = 0.20046
roll_moment_delta_aileron_trim_scalar = -0.21060
yaw_moment_slip_angle = 0.95206
yaw_moment_roll = 0.05510
yaw_moment_yaw_damping = -1300
yaw_moment_yaw_propwash = 0.0
yaw_moment_delta_aileron = 0.00286
yaw_moment_delta_rudder = 0.1
yaw_moment_delta_rudder_propwash = 0.18139
yaw_moment_delta_rudder_trim_scalar = 0.72557
compute_aero_center = 0
aero_center_lift = -2.60000
lift_coef_aoa_table = -3.15:0, -0.8:-1.073, -0.4:-0.795, -0.2:-0.980, -0.1:-0.656, 0:0.038, 0.20:1.275, 0.23:1.390, 0.26:1.194, 0.29:1.035, 0.31:0.973, 0.4:0.733, 0.8:1.078, 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:-1.131, -0.4:-0.526, -0.2:-0.613, -0.1:-0.436, 0:0, 0.20:0.767, 0.23:0.788, 0.26:0.887, 0.29:0.898, 0.31:0.868, 0.4:0.765, 0.8:1.364, 3.15:0
pitch_moment_delta_elevator_aoa_table = -180:-1, -40:0.211, -20:0.180, -14:0.725, -7:0.955, 0:1, 7:1.023, 14:0.943, 20:0.390, 40:0.168, 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 = 0.45
aileron_effectiveness = 0.4
rudder_effectiveness = 1
rudder_maxangle_scalar = 0.50
pitch_stability = 0.25
roll_stability = 0.25
yaw_stability = 1.4
pitch_gyro_stability = 1
roll_gyro_stability = 1
yaw_gyro_stability = 1
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
wingflex_scalar = 1
wingflex_offset = 0
stall_coef_at_min_weight = 0.78

[REFERENCE SPEEDS]
full_flaps_stall_speed = 90 ; Knots True (KTAS)
flaps_up_stall_speed = 105 ; Knots True (KTAS)
cruise_speed = 451 ; Knots True (KTAS)
cruise_mach = 0.74
crossover_speed = 285 ; Knots Indicated (KIAS)
max_mach = 0.77
max_indicated_speed = 500 ; Red line (KIAS)
max_flaps_extended = 200
normal_operating_speed = 305
airspeed_indicator_max = 400
rotation_speed_min = 115 ; Min speed required (Kts)
climb_speed = 138 ; Climb speed (Kts)
cruise_alt = 42000 ; (ft)
takeoff_speed = 115 ; 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 = 118 ; Approach speed (Kts)
best_glide = 135 ; Best Glide (Kts)

[INTERACTIVE POINTS]
number_of_interactive_points = 4
interactive_point.0 = 0, 4, -30, -2.5, 3, 0, 0, -90, 0, 0, 0, 0, 0, 0
interactive_point.1 = 0, 4, 30, -2.5, 3, 0, 0, 90, 0, 0, 0, 0, 0, 0
interactive_point.2 = 0, -22, -13, -2.5, 4, 0, 0, -135, 0, 0, 0, 0, 0, 0
interactive_point.3 = 0, -22, 23, -2.5, 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 = 1 ; Flap system type 0 = electrical, 1 = hydraulic, 2 = pneumatic, 3 = manual, 4 = none
span-outboard = 0.57 ; 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 = 1.6 ; Scalar coefficient to ponderate global flap lift coef (non dimensioned)
drag_scalar = 1.6 ; Scalar coefficient to ponderate global flap drag coef (non dimensioned)
pitch_scalar = 1 ; Scalar coefficient to ponderate global flap pitch coef (non dimensioned)
max_on_ground_position = 2 ; Dynamically set in-tool to last flap-position index by defaut when -1 is found.
flaps-position.0 = 0, -1, 0, 0, 0, 0, 0
flaps-position.1 = 15, -1, 0.5, 0, 0, 0, 0
flaps-position.2 = 35, -1, 1, 0, 0, 0, 0

One more thing, I have set the following settings for the rudder:

sensitivty (both) -74%

dead zone 0%

neutral 0%

extremity dead zone 0%

reactivity 50%

I have T-Pendular-Rudder and it works ok.

 

Edited January 14, 20215 yr by charliearon
massive text into a spoiler

Can I use this with the CJ4 mod? I’m pretty sure they have modified the physics. 

Edited January 14, 20215 yr by w6kd
mod edit: removed two pages of quoted text for a one line comment.

Just give me time please. This is without mod, I will just make available only a few changes.

I need about 45 min.

 

There certain wind when you going to feel just that. However, currently wind vs friction model is bit exaggerated

 

 

Under

[AERODYNAMICS]

change

pitch_moment_pitch_damping = -1301

yaw_moment_yaw_damping= -1300

yaw_moment_delta_rudder = 0.1

[FLIGHT_TUNING]

change

rudder_effectiveness = 1
rudder_maxangle_scalar = 0.50

yaw_stability = 1.4

Settings for the rudder:

sensitivty (both) -74%

dead zone 0%

neutral 0%

extremity dead zone 0%

reactivity 50%

Those are temporary adjustments, and even with those during xwinds the airplanes don't react correct due to faulty code from Asobo in turbulence and winds.

6 minutes ago, sd_flyer said:

There certain wind when you going to feel just that. However, currently wind vs friction model is bit exaggerated

 

 

Those are serious deviations from normal operations, it doesn't make it right if is on YouTube.

So much for stabilized t.os. and approaches.

When there is an emergency to land that's something else, but knowingly doing these kind of "aerobatics" almost loss of directional control with s turns on the rwy just to stay on the pavement, banking over 30 degrees left and right under knowing such turbulence, almost tail strikes, uncontrollable pitch changes between 10 and 20 degrees during rotation and climb out it's something to wonder why when under normal operations you have fuel to go to the alternate or delay departure.

Macho man, company pressure and no PIC decision?

 

22 minutes ago, killthespam said:

 

Where abouts is the file I need to edit?

Thanks! 

Edited January 14, 20215 yr by fakeflyer737

8 minutes ago, killthespam said:

Those are serious deviations from normal operations, it doesn't make it right if is on YouTube.

So much for stabilized t.os. and approaches.

When there is an emergency to land that's something else, but knowingly doing these kind of "aerobatics" almost loss of directional control with s turns on the rwy just to stay on the pavement, banking over 30 degrees left and right under knowing such turbulence, almost tail strikes, uncontrollable pitch changes between 10 and 20 degrees during rotation and climb out it's something to wonder why when under normal operations you have fuel to go to the alternate or delay departure.

Macho man, company pressure and no PIC decision?

 

Just FYI those are mostly take off not approaches. And when strong gusts comes that how it looks. This not macho or pressure, that how we fight gusts; otherwise, commercial aviation would just rest on the ground  🙂

Just tried Jackson Hole and Driggs with roughly 20+ knots blowing directly across the runway. Was unable to land OR take off properly. Real bummer!  The approach was great (and dramatic bobbing around) however, and the A/P crabbed it well but was also unable to maintain centerline to the MAP.

So I had a similar issue on take-offs after I upgraded to rudder pedals finally over the holidays.  I had temporarily been without rudder for a couple months after swapping from my X52 to a Honeycomb yoke (still using the X52 throttle).  I don't really remember having issues with rudder on the X52's twist rudder but maybe because it was easier to make small adjustments on it vs I'm new to pedals.

 

Anyway, I has having similar issues where I would need a lot of right rudder to stay straight then approaching V1 all of a sudden the AC would shoot off to the right and the fix that was suggested due to the "weathervaning" issue was to turn on take-off rudder assist.  That's definitely fixed that problem.  Won't help with landings though.

Real world aircraft can handle considerably more than the "demonstrated crosswind" figure from the POH that is true, it is very conservative.

HOWEVER if you mess up and ground loop and the crosswind component was greater than the POH demonstrated figure you may have serious issues convincing your insurance assessor as to why they should pay up.

 

 

33 minutes ago, Flyfaster_MTN002 said:

Just tried Jackson Hole and Driggs with roughly 20+ knots blowing directly across the runway. Was unable to land OR take off properly. Real bummer!  The approach was great (and dramatic bobbing around) however, and the A/P crabbed it well but was also unable to maintain centerline to the MAP.

Is that with the new settings?

I just a test flight and had no issues, something is not right. I will put some pictures.