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  1. Hello Chris, Sorry for the delay, I worked out of my country for a time. I am going to try explain below: The law dictates that takeoff thrust may only be reduced by a maximum of 25% from nominal maximum thrust. Therefore, if you thrust limit the engine by 10% or 20% upon 100% (nominal thrust) you obtain 90% or 80% as nominal thrust, you can then apply a further 25% reduction upon this thrust limit with an assumed temperature/FLEX TEMP, in others word upon 90% or 80% you can reduce others 25% in total will be a maximun of -35% or -45% thrust reduction. It is a small trap to comply with the law and to extend the life of the engines even more. How to calculate? simple the aircraft operator chooses the thrust limit in according with the same tables above but calculated for a thrust limit of 10% or 20%. I don't have this tables, I have only the generics and it's 100% thrust. Regards.
  2. 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.
  3. Hello raunzos, The table are from Flight Crew Operation Manual (Performance chapter) is real documentation. You can get here Regards.
  4. 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