The Cessna Citation Sovereign+ is a low-wing aircraft with retractable tricycle landing gear and a cruciform tail. A pressurized cabin accommodates a crew of two plus eight to twelve passengers (nine is standard). Two Pratt & Whitney Canada (P&WC) PW306D FADEC controlled turbofan engines are pylon-mounted on the rear fuse- lage. Fuel stored in the wings offers generous range for missions typical of this class aircraft. Space for baggage is provided in the tailcone with additional storage space available in the cabin.
Multiple structural load paths and system redundan- cies have been built into the aluminum airframe. Metal bonding techniques have been used in many areas for added strength and reduced weight. Certain parts with non-critical loads such as the nose radome and fairings are made of composite materials to save weight. The airframe design incorporates anti-corrosion applications and lightning protection.
Cessna offers a third-party training package for pilots and mechanics, and various manufacturers’ warranties as described in this book. Cessna’s worldwide network of authorized service centers provides a complete source for all servicing needs.
The Citation Sovereign+ utilizes an advanced, moder- ately swept wing selected for its low aerodynamic drag and favorable approach and landing characteristics. The winglets were designed to improve the range and perfor- mance characteristics while maintaining the low aerody- namic drag. A three-spar design gives the wing both structural integ- rity and high internal volume for its integral fuel tanks. It is designed to be damage tolerant and incorporates bonding and riveting techniques with doublers to provide increased skin thickness in highly loaded areas. A shallow drop in the center wing section permits attachment of the fuselage without interruption of the cabin cross- section. Composite fairings blend the wing and fuselage for minimum drag.
Electrically driven aluminum fowler ﬂ aps, arranged in three sections on each wing, and hydraulically driven spoilers, ﬁ ve sections per wing, are utilized for lift, re- duction, drag, and roll control. Conventional ailerons are installed near the wing tips. The wing leading edges are anti-iced using engine bleed air. The winglets include navigation and anti-collision lights and static wicks.
The main and nose landing gear each use dual wheel assemblies. The landing gear retraction system is electrically controlled and hydraulically actuated. Each main gear is a trailing link type and retracts inboard into the wing and belly fairing. The nose gear automatically centers while retracting forward into the nose and, when retracted, is enclosed by doors. Extension or retraction takes about eight seconds and all V-speeds associated with the gear equal 210 knots. Single chined tires are used on the nose gear for water and slush deﬂ ection. Squat switches on all three gear assemblies provide in- put to the squat switch logic that affects many systems. Two emergency gear extension methods are provided: a pneumatic blow-down system (independent bottle in nose) and manual gear release handles.
Multi-disc carbon brakes are installed independently on all four main gear wheels and are hydraulically actu- ated. Toe pedal pressure is transmitted via cables to the brake metering valve which regulates main hydraulic system pressure in proportion to pilot input. The metering valve also applies the brakes automatically during gear retraction to stop wheel spin.