The aircraft has a landing gear system that retracts during the take-off phase and extends for the landing. Also, it is the primary support of the aircraft when it is on the ground.

The landing gear system is arranged in a retractable tricycle configuration consisting of two main landing gear assemblies and a steerable nose landing gear assembly. Each landing gear assembly has twin wheels and tires.

The aircraft has a main landing gear installation near the root of each wing. It also has a nose landing gear which is installed on the center line of the forward fuselage, below the flight compartment.

The main and nose landing gear doors are mechanically linked to the landing gear assemblies. They move with the gear during extension and retraction.

Normal extension and retraction of the landing gear is powered by the left hydraulic system. Landing gear position monitoring is provided by the proximity sensor electronic unit (PSEU) and is displayed by the engine indicating and crew alerting system (EICAS). The landing gear emergency extension system deploys the landing gear, if normal extension of the landing gear is inoperative.

Each of the main landing gear is equipped with self adjusting multidisc carbon brakes. The left hydraulic system powers the brakes of the inboard wheels. The right hydraulic system powers the brakes of the outboard wheels. The brake-by-wire system provides antiskid control and locked wheel protection. The PARK/EMER BRAKE operates both the inboard and outboard brakes; however, antiskid is not available when using emergency brakes.

The nosewheel steering (NWS) provides directional control of the aircraft during ground operations. The nosewheel steering provides electrically controlled and hydraulically powered actuation of the nose landing gear steering actuator mounted on the nose gear assembly.