An Estimation of the Maximum Take-off Weight Commuter Category Aircraft Based on Airstrip Condition on Remote High Terrain Area

The conditions of the runway on remote high terrain area with mountain conditions are the problem for the aircraft. The short of runway length and the higher location can affect to the take-off performance of the aircraft. Thus the determination of the maximum take-off weight is critical in order for the aircraft to take-off safely. The purpose of this research is to determine the maximum take-off weight for 19 passengers commuter category and double engine propeller driven aircraft based on runway condition at ISA +20 on remote high terrain area. The intended of runway conditions are the altitude of the runway location, the slope of the runway, the surface condition of the runway and the wind speed around the runway. The take-off distance approach based on aerodynamic characteristics, geometry, and power plant is described. The results obtained that the aircraft can take off at remote high terrain area with an altitude above 5000 feet and runway length of 393 m to 600 m for all engine operative conditions.