The Global series aircraft has a conventional tricycle landing gear with a dual wheel installation on each gear assembly. The landing gear system consists of a landing gear extension and retraction system, manual release system, nosewheel steering system and a brake system.

The main landing gear assembly (mounted at eachwing root) is an inboard retracting, lever suspension type, fitted with a mixed gas/oil shockstrut. The nose gear assembly (mounted on the forward fuselage centerline) is forward retracting and has an internal gas/oil shock strut. Both the main and nose landing gear are fully enclosed by landing gear doors while retracted.

Normal landing gear extension and retraction is electrically controlled by the landing gear electronic control unit (LGECU), and carried out in response to the movement of the landing gear selector lever in the flight deck. Hydraulic pressure from systems No. 2 and 3 is used for gear extension and retraction, and for a normal brake operation.

The landing gear electronic control unit (LGECU) provides landing gear and door position information for status display, warnings, and gear control. It also provides weight-on-wheels (air ground/mode) information to other aircraft systems.

In the event of a failure in the normal landing gear extend system, emergency extension of the main and nose gear is achieved through the manual release system.

The nose gear is equipped with a steer by wire electronically controlled steering system, which provides precise control from the cockpit via the nosewheel steering hand wheel or the rudder pedals. The nosewheel steering system is controlled and monitored by the steering control unit (SCU).

The main wheels are equipped with carbon disk brakes controlled by a brake by wire antiskid system with an auto braking capability. The brake system is controlled and monitored by the brake control unit (BCU).

---