PerformanceAltimeter SettingField ElevationOATWind30.02 inHg3654DirSpdRunway270100PADACalculated Weight273.6911644-1046.30883563858Head WindX-Wind0LEFT 10No WindWind FactorAll FactorsFuelUSEABLE FUELTakeoff Roll108410841084GallonsWeightUseable Fuel (Gal)50Takeoff Over 50'161616161616R Main25.0175HH:MM of Fuel4:2Rate of Climb1224L Main25.0175Hour Reserve (75%)12.4Landing Over 50'180418041804Main Total50.0350HH:MM Until Reserve3:2Landing Roll101710171017R Aux0Taxi Fuel (Gal)0.5SE Rate of Climb257L Aux0Fuel Available (Gal)37.1Aux Total0.00Minutes of Fuel at 75%180Cruise Climb1220Enter Wt42.0294Climb Deduction (feet)6000Cruise Min Available168Landing/Takeoff Performance Factors (Optional)Grass LengthN/AGrass LengthN/AWet GrassNoWet GrassNo% Upslope0% Downslope0Runway LengthAltitude ChangeSlope10000%ItemWeightArmMomentEmpty Weight2756261000Front Seats43090.638958Rear Seats175128.022400Nose Bag1023.62360Cockpit Bag10153.115310Extension Bag0178.700Zero Fuel Wt338195.873241250Main Fuel300103.531050Aux Fuel0126.00Totals368196.493551750

"Calculated Weight" uses the Totals value from the W&B table. "Manual Weight" allows a custom value.Fuel weight is calculated using 7 lbs/gal for Jet A-1 per DA42 AFM.Adds grass length and wet grass to wind factor.Based on 10% increase in T/O dist per 2% upslope. Not accurate at high slopes.Adds grass length and wet grass to wind factor.Based on 10% increase in Ldg dist per 2% downslope. Not accurate at high slopes.

CG Graph27562756323639353935352736813381275632363935393535272756

Final CGZFW CGCG (In.)Weight (Lb)C.G. vs. Weight Envelope

X-C PlanningFuel Management - Fuel Required For The FlightCruise SpeedPhase of FlightTCMCWinds & TempsTASMHGSDistTimeGPHGALAltitudeOAT% PwrISAISA DevDATASTaxi0.535007808-13380146Climb 60001492.10GGG SAT2302243016815122616624412812.418.2SAT BAZ65573601212147531424601912.43.9Fuel FlowTime, Fuel, Distance to ClimbBAZ HYI4032360121214029131100510.50.9% Power70AltitudeTimeDistanceFuel00000.0GPH 1 Eng5.300000000.0GPH 2 Eng10.500000.000314000.0Winds Aloft Calculator00000.0WindTC00000.0AltitudeDirSpdTW/HW23000000.0300000000000.0400000000000.05000000Climb 26000000Climb 37000972.3311.6Alternate000010.50.080001934.662-3.7Reserve (75% power)10.510.590002907-3.5For Each Intended Touch and Go Add 6 Min At 75% Power0ETE200.01000030711.329-2.6For Each Practice Instrument Approach Add 18Min @ 75% Power0Fuel Required:36.11100032315.6580.912000340206.8Flight Plan Form1300031216.666-2.4Flight TypeN NumberA/C TypeTASDeparture PointETDAltitude1400022713.334-13.3IFR4,0001500017010-5Route16000576.666.617000283.3343.1DestinationETERemarksFuel1800002:04:04AlternatePilotBase# On BoardA/C ColorGGG (800-876-1153)Equipment SuffixADME & MODE CBDME & MODE ADDME - NO TRANSPONDERGGPS APRIRNAV & MODE CTMODE AUMODE CXNO TRANSPONDER

Calculates time using the Useable Fuel field (Cell M12) on the Performance sheet divided by the reserve GPH (Cell O13) on this sheet.ETE is calculated from the ETE on the Fuel Management form above. Selecting "VFR" under flight type will add 20 minutes to the ETE.Adds fuel required for touch & goes (Cell K 14) and practice instrument approaches (Cell K15)Tailwind component is positive; headwind component is negative.Enter winds aloft info. Tool will show headwind/tailwind components for each altitude.Intermediate altitude winds aloft are calculated using linear interpolation.Calculated using LeTourneau Cruise Climb configuration [700fpm at 90% power (14.4GPH) at 100 kts.] NOT BASED ON ANY MANUFACTURER INFO.

FormulasOATPAWeightHeadwind4273.691164436810Weight And BalanceLanding RollWeightArmLow WeightHigh WeightZFW3381TRUE95.87DAWTResultDAWTResultTotal3681TRUE96.49103310171017126311881188Landing DistanceLow WeightHigh WeightDAWTResultDAWTResult1830180418042273.545547882721662166Max Error: 12 ftMax Error: 62ftCG LimitsTakeoff Climb95.282756Low WeightHigh Weight98.033527OAT0ResultOAT0Result98.0339351296.501444127611961224-101104121311961238110492.522756Max Error: 6 ft/min1228Max Error: 17 ft/min92.523236Cruise Climb94.493935Low WeightHigh WeightOAT0ResultOAT=>0OAT0OAT