question

Hello

Can you provide repro steps to get into that situation?
Still testing the 747 I assume, did you edit anything?
Our testers tried to get in a similar situation but all values were identical.

Regards,
Sylvain

Hello,

I have tried with the default aircraft and indeed, I don't see this happening.

I am modifying the Salty 747 and I have enabled the legacy tables to allow the N1 to be commanded above 100%. I think that it might be the reason.

I have added my file, so that you can try it yourself:

[VERSION]
major = 1
minor = 0

[GENERALENGINEDATA]
engine_type = 1 ; 0=Piston, 1=Jet, 2=None, 3=Helo-Turbine, 4=Rocket, 5=Turboprop	
fuel_flow_scalar = 1 ; 0.8 ; Fuel flow scalar
min_throttle_limit = -0.25 ; Minimum percent throttle. Generally negative for turbine reverser
master_ignition_switch = 0
starter_type = 2 ; 0=Electric, 1=Manual, 2=Bleed Air
max_contrail_temperature = -39.724
Engine.0 = -119, -69.95, -4.5
ThrustAnglesPitchHeading.0 = 0, 0
Engine.1 = -92, -39.35, -6.8
ThrustAnglesPitchHeading.1 = 0, 0
Engine.2 = -92, 39.35, -6.8
ThrustAnglesPitchHeading.2 = 0, 0
Engine.3 = -119, 69.95, -4.5
ThrustAnglesPitchHeading.3 = 0, 0

[TURBINEENGINEDATA]
use_old_fuelflow_simvar = 0
use_corrected_N2_from_FF_table = 1
use_commanded_Ne_table = 1
use_n2_to_n1_table = 1
fuel_flow_gain = 0.002 ; Gain on fuel flow
inlet_area = 60 ; Square Feet, engine nacelle inlet area
rated_N2_rpm = 11377 ; RPM, second stage compressor rated value
static_thrust = 67425 ; Lbs, max rated static thrust at Sea Level
reverser_available = 2.0
reverser_mach_controlled = 0
afterburner_available = 0
afterburner_throttle_threshold = 0.011
ThrustSpecificFuelConsumption = 0.27
AfterBurnThrustSpecificFuelConsumption = 0.011
mach_0_corrected_commanded_ne_table = 0:1:4.4593:18.5238,0.00:68.00:78.42:78.42,0.14:75.15:86.67:86.67,0.29:82.30:94.91:94.91,0.43:89.45:103.16:103.16,0.57:96.60:111.41:111.41,0.72:103.75:119.65:119.65,0.86:110.90:127.90:127.90,1.00:118.00:136.09:136.09
	
mach_hi_corrected_commanded_ne_table = 0.999:1:4.4593:18.5238,0.00:62.09:71.60:71.60,0.14:68.61:79.13:79.13,0.29:75.14:86.66:86.66,0.43:81.67:94.19:94.19,0.57:88.20:101.72:101.72,0.72:94.73:109.24:109.24,0.86:101.25:116.77:116.77,1.00:107.74:124.25:124.25

corrected_n2_from_ff_table = 0.0:0.0, 0.0254:68.0, 0.0825:88.4, 0.2369:110.5, 0.2886:118.0

n1_and_mach_on_thrust_table = 0.0:0:0.1:0.2:0.3:0.4:0.5:0.6:0.7:0.8:0.9:1.0,0.0:0.000:0.000:0.000:0.000:0.000:0.000:0.000:0.000:0.000:0.000:0.000,28.0:0.041:0.034:0.031:0.029:0.027:0.026:0.024:0.023:0.022:0.021:0.020,30.0:0.048:0.041:0.037:0.035:0.033:0.031:0.029:0.027:0.026:0.025:0.023,35.0:0.071:0.059:0.054:0.051:0.048:0.045:0.042:0.040:0.038:0.036:0.034,40.0:0.098:0.082:0.076:0.070:0.066:0.062:0.059:0.056:0.053:0.050:0.047,45.0:0.132:0.110:0.101:0.094:0.088:0.083:0.079:0.074:0.071:0.067:0.063,50.0:0.171:0.143:0.131:0.122:0.115:0.108:0.102:0.097:0.091:0.087:0.082,55.0:0.216:0.180:0.166:0.154:0.145:0.137:0.129:0.122:0.116:0.110:0.104,60.0:0.267:0.224:0.205:0.191:0.180:0.169:0.160:0.151:0.143:0.136:0.129,65.0:0.326:0.272:0.250:0.233:0.219:0.206:0.195:0.184:0.175:0.165:0.157,70.0:0.391:0.327:0.300:0.280:0.263:0.248:0.234:0.221:0.209:0.198:0.188,74.1:0.450:0.376:0.345:0.322:0.302:0.285:0.269:0.255:0.241:0.228:0.216,97.9:1.000:0.836:0.768:0.716:0.672:0.633:0.598:0.566:0.536:0.508:0.481,110.0:1.285:1.074:0.986:0.919:0.863:0.813:0.768:0.727:0.688:0.652:0.618
	
n2_to_n1_table = 0:0:0.999,0.00:0.00:0.00,10.00:0.86:0.94,20.00:2.37:2.59,30.00:4.61:5.05,40.00:7.60:8.33,50.00:11.33:12.41,60.00:15.80:17.30,70.00:22.03:24.13,80.00:32.95:36.09,90.00:47.01:51.49,100.00:64.59:70.74,120.00:111.93:122.60

jet_density_on_ff_table = 0.000460:0.3522, 0.000585:0.3847, 0.000737:0.4131, 0.000890:0.4695, 0.001066:0.5505, 0.001267:0.6420, 0.001496:0.7532, 0.001756:0.7786, 0.002049:0.8956, 0.002378:1.0
	
epr_max = 1.4
epr_tc = 14
epr_tuning_constant = 1
oil_temp_cooling_constant = 0
oil_temp_heating_constant = 700
oil_temp_tc = 0.07
oil_temp_tuning_constant = 1
oil_press_max = 12384
oil_press_tc = 0.8
oil_press_tuning_constant = 1
fuel_flow_max_itt_factor = 2.0
fuel_flow_min_itt_factor = 0.9 ; 0.72
n1_cooling_factor = 0.01
itt_peak_temperature = 3012 ; 2141
itt_tc = 2 ; 2
itt_tuning_constant = 1
itt_cooling_factor = 0.01
egt_peak_temperature = 1917
egt_tc = 2 ; 2
egt_tuning_constant = 1
fuel_press_max = 2376
fuel_press_tc = 2
fuel_press_tuning_constant = 1
variable_inlet = 0
primary_nozzle_available = 0
primary_nozzle_afterburner_offset = 0.14
primary_nozzle_n1_mach_to_nozzle_pos = 0.000000:0.000000:2.000000,53.000000:0.660000:0.100000,65.000000:0.690000:0.330000,96.000000:0.700000:0.440000
starter_N1_max_pct = 12 ; Pct, percentage of max rpm that reached using only starter.
starter_N1_rate = 12 ; Rate at which the starter N1 increases.

ignition_auto_type = "Starter,Flaps,AntiIce,N2" ; If the Ignition is set to AUTO - specifies how that is handled. 0(default) = Always on, 1 = Ignition follows starter status, 2 = Ignition enabled when Flaps are not neutral, when AntiIce is enabled, or when N1/N2 is below 50%.

min_condition_lever_for_combustion = 0.01 ; % - Minimum position of the Condition lever to obtain a combustion. Default at 0.01.
min_n1_for_combustion = 10 ; % - Minimum N1 required to maintain a combustion
min_n2_for_combustion = 19.4 ; % - Minimum N2 required to maintain a combustion
min_n1_for_starter_cutoff = 200 ; % - Minimum N1 at which the starter is automatically disabled
min_n2_for_starter_cutoff = 50 ; % - Minimum N2 at which the starter is automatically disabled
min_n2_for_apu_bleed_air_cutoff = 200 ; % - Minimum N2 at which the APU Bleed Air is automatically disabled
n2_from_bleed_air_psi_table = 0:0, 4:8, 10:18, 18:25 ; Table which contains the n2 generated depending on the pression from the bleed air from the APU (in psi).
bleed_air_on_n2_tc = 1 ; Time constant which contains the speed at which the bleed air pressure affect the N2 of the turbine.
N1_to_oil_pressure_table = 0:0, 0.21:0.88, 0.9:0.954, 1:1 ; % of max Oil Pressure for % N1.
n1_normal_tc = 0.5 ; Float factor changing N1 acceleration during normal use of the engine
n1_start_max_rate = 1.0 ; Float limiting N1 acceleration during starter use
n1_start_combustion_max_rate = 2.0 ; Float limiting N1 acceleration during startup when cumbustion has started

idle_fuel_flow = 1714 ; pound per hour
low_idle_n1 = 20.2 
low_idle_n2 = 68
high_n1 = 106.7
high_n2 = 118.0
high_fuel_flow = 20000
min_n2_for_fuel_flow = 22
mach_influence_on_n1 = 10
fuel_flow_max = 25000
fuel_flow_controller_p = 0.5
fuel_flow_controller_i = 0.1
fuel_flow_controller_d = 0.5
fuel_flow_controller_iboundary = 5
fuel_flow_controller_dboundary = 100
	
max_torque_protection = 0 ; 0 = no protection, value of the torque triggering a protection by automatically limiting the fuelflow
	
max_n1_protection = 0 ; 0 = no protection, value of the n1 triggering a protection by automatically limiting the fuelflow
	
max_n2_protection = 0 ; 0 = no protection, value of the n2 triggering a protection by automatically limiting the fuelflow
	
max_egt_protection = 0 ; 0 = no protection, value of the egt triggering a protection by automatically limiting the fuelflow
	
[JET_ENGINE]
thrust_scalar = 1 ; 0.85
	
[DISABLED_CONTROLS]
DisableFuelValveControls = 0 ; Disable fuel valve controls
DisableMixtureControls = 1 ; Disable mixture controls
DisableParkingBrakeControls = 0 ; Disable parking brake controls
DisablePropellerControls = 1 ; Disable propeller controls

Hello,

Any update on this?

Thanks!