P2006T Calculator

Calculate performance, mass & balance for Tecnam P2006T

Use this calculator with caution at your own risk. We strive to ensure everything is correct as long as you're within AFM parameters. It is always your responsibility to check and confirm the numbers and calculations from this website.

This site contains the following calculations

• Mass & Balance; using the graph from the AFM
• Performance tab:
  • Takeoff groundroll and distance, including corrections and safety factor of 1.25
  • Landing groundroll and distance, including correction and safety factor of 1.43
  • OEI Service and Absolute ceiling, rounded down to nearest 1ft
  • OEI and ME climb performance (V-speed, fpm, gradient and angle) using either the MSA, or a pressure altitude 2/3rds of the distance between the elevation and the cruise altitude (both corrected for pressure)
• Results gives detailed information about the interpolation, including all meta data.

Methods of calculation

Takeoff and landing groundroll and distance interpolation

• First, the distances are interpolated between altitudes, for each temperature and weight:
  $$value_{actual} = {value_{high} - value_{low} \over altitude_{high} - altitude_{low}} \cdot (altitude_{actual} - altitude_{low})+value_{low}$$
• Then, the results of these formulas are interpolated between temperatures, for each weight:
  $$value_{actual} = {value_{hot} - value_{cold} \over temp_{hot} - temp_{cold}} \cdot (temp_{actual} - temp_{cold})+value_{cold}$$
• Finally, the result of those formulas are interpolated between weights:
  $$value_{actual} = {value_{heavy} - value_{light} \over mass_{heavy} - mass_{light}} \cdot (mass_{actual} - mass_{light})+value_{light}$$

Temperature correction to minimum altitude

• The following formula is used to calculae the correction to be applied to the DA/MDA:
  $$correction = {-ISA deviaton \over \tfrac{1.98^\circ C}{1000ft}} \cdot \ln\left(1+{\tfrac{1.98^\circ C}{1000ft} \cdot DH/MDH \over 273 ^\circ _{C \rightarrow K} + 15^\circ C + \tfrac{1.98^\circ C}{1000ft} \cdot Elevation }\right)$$ We use this formula, because it is the most versatile and accurate formula referenced by ICAO PANS-OPS, Volume III, Section2, Chapter 4, 4.3, “Temperature correction”, which is the document referenced in doc8168
  
  
• Another forumla, which is referenced in ICAO PANS-OPS, Volume III, Section2, Chapter 4, 4.3, “Temperature correction”, but not used on this site is:
  $$correction = DH/MDH \cdot \left( { -ISA deviation \over Temp_{SeaLevel_{^\circ K}} - 0.5 \cdot \tfrac{1.98^\circ C}{1000ft} \cdot DA/MDA } \right)$$ This formula is (according to ICAO) accurate to within 5% of the actual value, for pressure-elevations up to 10.000ft and for DH/MDH's up to 5.000ft, which is also the range of heights where it is approved for use
  This formula, when applied to an aerodrome at sea level, is also the basis for ICAO PANS-OPS, Volume III, Section2, Chapter 4, table 2-4-1b, where the values have been rounded up to the nearest 10ft. When within limits, this formula yeilds a slightly larger correction than the first one.
  
  
• It is also worth considering that for temperatures above -15C it is also permissible (and much simpler) to add 4% per 10 degrees below ISA to the DH/MDH, regardless of aerodrome elevation, as shown here:
  $$correction = DH/MDH \cdot 4 \% \cdot \left( {-ISAdeviation \over 10^\circ C} \right)$$

Rate of Climb Calculations

• First, the climbrates are interpolated between altitudes, for each temperature and weight:
  $$value_{actual} = {value_{low} - value_{high} \over altitude_{high} - altitude_{low}} \cdot (altitude_{high} - altitude_{actual})+value_{high}$$
• Then, the results of these formulas are interpolated between temperatures, for each weight:
  $$value_{actual} = {value_{cold} - value_{hot} \over temp_{hot} - temp_{cold}} \cdot (temp_{hot} - temp_{actual})+value_{hot}$$
• Finally, the result of those formulas are interpolated between weights:
  $$value_{actual} = {value_{light} - value_{heavy} \over mass_{heavy} - mass_{light}} \cdot (mass_{heavy} - mass_{actual})+value_{heavy}$$

Gradients

Fuel Consumption, Powersetting and Cruise TAS

• First, the values are interpolated between manifold pressures, for each temperature, RPM and altitude:
  $$value_{actual} = {value_{lowMAP} - value_{highMAP} \over MAP_{high} - MAP_{low}} \cdot (MAP_{actual} - MAP_{low})+value_{lowMAP}$$
• Then, the results from above are interpolated between temperatures, for each RPM and altitude: $$value_{actual} = {value_{cold} - value_{warm} \over temp_{warm} - temp_{cold}} \cdot (temp_{warm} - temp_{actual})+value_{warm}$$
• Then, the results from that are interpolated between RPM's for each altitude: $$value_{actual} = {value_{fast} - value_{slow} \over RPM_{fast} - RPM_{slow}} \cdot (RPM_{actual} - RPM_{slow}) + value_{slow}$$
• Finally, the results from that are interpolated between altitudes: $$value_{actual} = {value_{high} - value_{low} \over alt_{high} - alt_{low}} \cdot (alt_{actual} - alt_{low}) + value_{low}$$