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  1. Manufacturer's manual has until 3600 meters only because this manuals are generic and the manufacturer considers this minimum distance for maximum reduced thrust and weight of the aircraft, in real life each operator of aircraft has its own tables for each airport that they operate. But if you have 4500 meters of runway you can do the calculations with 3600 meters, is valid. Regards.
  2. The latest version of the aircraft performance with cold and dark and trueglass removed: 5,4 FPS And 737PMDG default status: 29,7 FPS
  3. Same here too. The performance is still very poor for me, 3-7FPS in FSIA with clear skies, disabled trueglass and F/O Displays. PMDG and other addons 30FPS in same conditions, I have limited FPS in 30FPS.
  4. Hello, I am going to try explain how calculate the ZFWCG. It is something difficult because in the Flight Simulator there is some data that we can not get. Ok, we must know that it is the 'DATUM' for calculate ZFWCG. The DATUM is an imaginary vertical reference plane or line chosen by the aircraft manufacturer from which all arms used for weight and balance computation are measured. In the next image we have all necessary measures to calculate the ZFWCG: Ok, We calculate ZFWCG with the next equation: ZFWCG = D - F*L/ZFW Where: D = Distance from Datum to Main Wheels, it would 2,3M + 17,6M = 19.9M F= Net weight Nosewheel, this date we haven't it in Flight Simulator, suppose it is 7.000 kg L= Distance from Nosewheel to Main wheels, it would 17,6M ZFW= 42.000 kg ZFWCG = 19,9 - 7.000*17,6/42.000 ZFWCG= 17 meters from Datum. Ok, now we have to convert in % of MAC (Mean aerodynamic chord) for this we use another equation: ZFWCG% = CG from LEMAC * 100/MAC in meters Where: CG from LEMAC(Leading edge of the mean aerodynamic chord), it would 17M-15M = 2M MAC would 22M - 15M = 7M ZFWCG% = 2*100/7 ZFWCG% = 28,5% For me this is very dificult to calculate in the Flight Simulator because some date as LEMAC and TEMAC distance and net weight nosewheel we haven't it. Regards.
  5. Hello raunzos, The table are from Flight Crew Operation Manual (Performance chapter) is real documentation. You can get here Regards.
  6. Hello friends, First of all thanks to the development team for this amazing aircraft. My name is Jose Antonio Montiel from Málaga I am 24 years old, I am aircraft mechanic in the real life and I have worked a few in the B717-200, at present I work in the B737. I would like to share my little knowledge with you. In the B717 there are two types of reduced thrust: * Limit thrust: is a % lower of thrust for the total thrust in the current OAT or FLEX/Assume Temperature. TO1 -10% TO2 -20% . *FLEX TEMP: is a temperature that we put in the FMS so that the FADEC misleads the engine to assume more temperature than it actually is and thus obtain a lower thrust. Ok, how do we calculate our FLEX TEMP for current conditions? We have: * T/O Weight 53.000 Kgs * Airport Elevation 1.000ft * RWY Lenght 2.200 Meters and dry * Winds 10 HW * Slope 0% * OAT 20ºC * Flaps configuration 13º * Type Engine BR700-715C1-30 So that we can know our FLEX TEMP we have to calculate our maximum temperature that we can assume with our take off weight, how? Ok we go to de FCOM performance dispach and choose the table for our conditions: The first step is RWY Lenght corrections: Is 2.290 Meters. And second stet calculate our Max FLEX TEMP with T/O Weight 53.000 kgs FLEX TEMP is 40ºC, 45ºC It could not be because the Maximum take off weight(performance, not structural) is less than we have 51.300 kgs and the same for Climb Limit weight (performance). Regards