The G-IIB is a low wing, twin fanjet pressurized aircraft. It is designed for all weather flying and operations. The basic aircraft is certified to 43,000 feet above sea level for flight. The aircraft’s initial design is for safety and ease of maintenance. The aircraft structure consists of a fuselage, wing and stabilizers. The general dimensions of the G-IIB are; length 79 feet 11 inches, width 77 feet 10 inches and height 24 feet 10 inches.
The main entrance door is on the left forward side of the fuselage just aft of the cockpit. The door may be opened either from inside or outside the aircraft. While inside the aircraft the door must be unlocked and pushed outward to allow the door to free-fall open. When locking the door there are six sliding bayonets that extend into the fuselage. One bayonet activates the pressurization of the door seal when the door handle is locked. The door seal must be in working order to maintain cabin pressurization.
The Gulfstream IIB has a rear baggage door that operates on the same principle as the forward entrance door. It also is able to be opened inside and outside the aircraft. Ideally this location is where all baggage will be loaded on the aircraft. By doing so excess wear on the cabin interior may be avoided.
The cabin incorporates four emergency escape windows, two windows located over each wing. In all there are six exits for egress in case an emergency requires a quick departure from the aircraft.
The wing is an all metal swept back design. Within each wing are the fuel tanks. The wing is called a wet wing since fuel is contained within the sealed metal wing design. The leading edge of the wing contains air space where ducted hot bleed air from the engines may be routed to prevent ice from forming.
A vertical stabilizer is attached to the top of the fuselage and a horizontal stabilizer is attached to the vertical stabilizer. Neither stabilizer has ducted air passing in the leading edge for anti-icing.
The engines are attached to the aircraft via the pylons. The pylon acts as an airfoil and contains the services to the engine.
There are at least fourteen sub-systems that are required to complete the functionality of the Gulfstream IIB. They are; electrical power, fuel, power plant, auxiliary power unit, hydraulics, landing gear and brakes, flight controls, pneumatic system, air conditioning and pressurization, oxygen, anti ice, fire detection and extinguishing, pitot static, and autopilot. All of these systems need to be operational to begin a flight safely.