The power plants give propulsion to the aircraft. The aircraft is equipped with two Honeywell AS907 high bypass turbofans and hydraulically actuated thrust reversers. They are attached to pylons on the left and right side of the rear fuselage.

The engine is a two-spool direct drive turbofan engine. A single-stage fan is driven by a three-stage low-pressure turbine. The engine has a four-stage axial compressor, a single-stage centrifugal compressor, a through-flow annular combustor, 16 fuel nozzles, 2 igniters, and a two-stage high-pressure turbine. An accessory gearbox mounts the engine air turbine starter and provides accessory drive pads for mounting the hydraulic pump and generator, as well as lubricating the engine.

The engine air system ensures that the compressor operates smoothly during its full speed range and keeps the engine at a satisfactory temperature. Hot air prevents ice accumulation in the air intake area. Bleed air pressurizes seals and buffer cavities. Intake air cools the generators.

The engine oil system supplies filtered oil at the correct pressure and rate of flow to lubricate and cool engine areas. The oil flows to the engine bearings related seals, splines, and gears inside the engine and to the accessory gearbox.

The full authority digital engine control (FADEC) system supplies all control and monitoring functions for the engines and thrust reversers. The engine fuel system supplies sufficient fuel to the fuel injectors to maintain the desired engine thrust during ground and flight operation. The engine fuel system is also used for compressor variable geometry actuators, to cool the engine oil (heat transfer) and provide motive flow for the scavenge and main ejector pumps.

The engine start system is helps with assisted ground starts, assisted inflight starts, and windmill inflight starts. It supplies electrical energy to the engine ignition system, fuel to the engine fuel system, and high-pressure air to the engine cranking system. The ignition system operates in continuous or automatic ignition mode, which automatically provides ignition during a stall, combustor blowout, or momentary loss of fuel.

The hydraulically operated thrust reversers help stop the aircraft on landing and during a rejected takeoff (RTO). The system is operable on the ground only; the reversers do not deploy in flight. The power plant controls include a throttle quadrant and engine control panel located on the center console.

The engine indicating system measures parameters of the engine operation and sends the electrical signals to the electronic control units (ECUs). Each ECU changes the signals into the data that supplies the indications on the engine indicating and crew alerting system (EICAS) display.

The engine indicating system measures parameters of the engine operation and sends the electrical signals to the electronic control units (ECUs). Each ECU changes the signals into the data that supplies the indications on the engine indicating and crew alerting system (EICAS) display.

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