Specifications

SECTION I
MODEL 560 DESCRIPTION AND SPECIFICATIONS
GENERAL DESCRIPTION
The Cessna Citation Encore is certified in accordance with FAR Part 25 airworthiness standards and
utilizes the fail-safe construction concept. It combines systems simplicity with ease of access to reduce
maintenance requirements. Low takeoff and landing speeds permit operation at small and unimproved
airports. Front fan type turbofan engines contribute to overall operating efficiency and performance.
FLIGHT CONTROLS
Ailerons provide lateral control of the airplane and are operated mechanically by control wheel
movement. A trim tab control mechanically operates a trim tab attached to the trailing edge of the left
aileron, which provides aerodynamic movement of the aileron
Rudder provides control of the airplane about the vertical axis and is controlled mechanically by the dual
rudder pedals, located in the flight compartment. The trim tab on the rudder trailing edge is controlled
mechanically by a rudder trim wheel located on the control pedestal
Elevators provide longitudinal control of the airplane and are operated mechanically by fore and aft
movement of the control wheel. A trim tab is located on the trailing edge of each elevator. The trim tab is
electrically operated and has manual override control
Flaps increase the lift of the wing when partially extended and increase drag to help reduce speed when
fully extended. Flaps are actuated hydraulically and controlled mechanically through the preselect handle
and indicator follow-up system
Speed brakes provide fast, precise speed control. Speed brakes are hydraulically actuated and
manually controlled by a switch on the throttle pedestal. Safety override microswitches prevent extension
above 85% N
2
throttle position. Speed brakes will automatically retract if the throttle levers are advanced
beyond 85% N
2
.
ENGINES
Two Pratt & Whitney Canada Inc. PW535A turbofans installed on the rear fuselage produce 3400
pounds of thrust each. Ice protection and fire detection and extinguishing systems are incorporated. Fuel
is carried in two integral wing tanks with each engine normally supplied from its respective side. The
engines utilize a hydromechanical fuel control, and cross-feeding can be selected. Fueling is done through
an overwing port in each tank, in addition to a single-point pressure refueling point. Target-type thrust
reversers are individually operated by conventional “piggy back” controls mounted on the throttles.
FUSELAGE
Sequentially from front to rear are the avionics bay, nose baggage area, forward pressure bulkhead;
flight deck, passenger and aft cabin compartments; rear pressure bulkhead and aft compartment (including
tailcone/equipment and aft baggage compartments).
Approximately fifteen cubic feet of baggage space is available in the nose, except in airplanes which
have certain avionics options. The flight deck is equipped with dual controls and has two seats, equipped
with a five-point restraint system, that can be moved fore and aft, vertically, and tilted.
The passenger compartment provides seating and an air outlet, light and oxygen mask for each
occupant. The seats may be moved laterally away from the sidewall, tracked fore or aft, and reclined, with
the exception of the aft two seats which will not track fore and aft. The aft cabin compartment, which may
be closed off with a privacy curtain, has another 26 cubic feet of storage space and a toilet. The aft
compartment contains equipment and systems components and 25 cubic feet of additional baggage space.
ELECTRICAL SYSTEM
The main Direct Current (DC) buses are supplied from two starter/generators. Engine starting and
secondary DC power is available from either the battery or an external source. Two static inverters provide
power to the Alternating Current (AC) buses.
HYDRAULIC SYSTEM
Engine-driven pumps supply pressure for operation of the landing gear, flaps, speed brakes and thrust
reversers through an open center system. The main gear is equipped with wheel brakes mechanically
operated by a brake control (metering) valve. Pneumatic backup is available for landing gear extension and
braking.
I 56OMB-01 Configuration AA 1-3