Specifications

Model

  • Maximum Ramp
  • Maximum Takeoff
  • Maximum Landing
  • Maximum Zero Fuel
  • Maximum Fuel – Volume
  • Maximum Fuel – Weight
  • Typical Empty (no crew)
  • Basic Operating Weight (incl. crew, if applicable)
  • Crew
  • Useful Load (Ramp – BOW)
  • Maximum Payload (ZFW or MLW – BOW)
  • Full-Fuel Payload (Useful Load – Fuel)

Citation Excel Eagle

  • 20,200 lb
  • 20,000 lb
  • 18,700 lb
  • 15,000 lb
  • 1,006.0 gal
  • 6,740 lb
  • 12,425 lb
  • 12,825 lb
  • 2 Pilots
  • 7,375 lb
  • 2,175 lb
  • 635 lb

Models

  • Manufacturer
  • Model
  • Type
  • Fuel Type
  • Engine Output – Sea Level
  • Engine Flat Rating Temperature
  • TBO Interval
  • Power Loading (MGTOW / total engine output)
  • Bypass Ratio
  • Prist Required (turbine powered aircraft)

Cessna Citation Excel

  • Pratt & Whitney Canada
  • PW545A
  • Turbofan
  • JetA
  • 3,804 lb
  • ISA + 13C
  • 6,000 hr, 12,000 hr, 17,000 hr
  • 2.63 lb/lb
  • 4.00:1
  • No

Models

  • Overall – Length
  • Overall – Height
  • Overall – Wing Span
  • Overall – Horizontal Stabilizer Span
  • Cabin Door – Height, Front/Rear
  • Cabin Door – Width, Top/Bottom
  • Baggage Door – Height, Front/Rear
  • Baggage Door – Width, Top/Bottom
  • Emergency Exit – Height
  • Emergency Exit – Width

Cessna Citation Excel

  • 51 ft 10 in
  • 17 ft 5 in
  • 55 ft 8 in
  • 21 ft 6 in
  • 54.00 in / 54.00 in
  • 24.00 in / 24.00 in
  • 29.00 in /
  • 25.00 in /
  • 40.00 in
  • 22.00 in

Models

  • Interior – Overall Length (bulkhead to bulkhead)
  • Interior – Cabin Area (cockpit divider to rear bulkhead)
  • Interior – Seating Area (cockpit divider to aft divider)
  • Interior – Height
  • Interior – Width
  • Passenger Seats (standard to maximum)
  • PSI Differential
  • Sea Level Cabin to (altitude)
  • Cabin Altitude at Certified Ceiling
  • 8,000 foot cabin at (altitude)
  • Baggage Capacity – Internal Weight
  • Baggage Capacity – Internal Volume
  • Baggage Capacity – External Weight
  • Baggage Capacity – External Volume

Cessna Citation Excel

  • 24 ft
  • 18 ft 6 in
  • 15 ft 4 in
  • 68.00 in
  • 66.00 in
  • 8 – 9 (9th seat optional)
  • 9.30 psi
  • 25,230 ft
  • 6,800 ft
  • 45,000 ft
  • 84 lb
  • 10.00 ft³
  • 700 lb
  • 80.00 ft³

Models

  • Certification Basis
  • Approved Runway Surfaces
  • Steep Approach Certified?

Cessna Citation Excel

  • Part 25
  • Hard, gravel
  • Yes

Models

  • Announced
  • First Flight
  • FAA Certification
  • First Delivery
  • First Customer Delivery
  • MSG-3 Issued

Cessna Citation Excel

  • 10/1/1994
  • 2/29/1996
  • 4/22/1998
  • 7/2/1998
  • 7/2/1998
  • 1/31/2007

Models

  • Model Number
  • Serial Numbers
  • Production Status
  • Years Produced
  • Total Units Delivered

Cessna Citation Excel

  • 560XL
  • 560-5001 thru -5372
  • Model 560 lineage still in production
  • 1998-2004 (lineage 2004-present)
  • 370 (lineage > 1,000)

Models

  • Avionics Package

Citation Excel Eagle

  • Garmin G5000

Models

  • Takeoff Field Length – Sea Level, ISA, MGTOW
  • Takeoff Distance – 5,000 Feet, 25C
  • – 5,000 Feet, 25C Weight Restriction
  • Takeoff Distance Basis
  • Landing Distance – Sea Level, ISA, MLW
  • Landing Distance – Typical LW with Fuel Reserves
  • Typical LW with Fuel Reserves
  • Max Takeoff and Landing Altitude

Cessna Citation Excel

  • 3,650 ft
  • 5,770 ft
  • None
  • BFL
  • 3,180 ft
  • 2,710 ft
  • 14,900 lb
  • 14,000 ft

Models

  • Rate of Climb
  • Direct Climb to
  • Service Ceiling – All Engines
  • Certified Ceiling

Cessna Citation Excel

  • 3,790 ft/min
  • FL430 in 21 min
  • 44,000 ft
  • 45,000 ft

Models

  • MMO
  • – Altitude Above 26,515 ft
  • Maximum Cruise Speed True Air Speed
  • – Typical Cruise Speed True Air Speed
  • – Cruise Speed Parameter

Cessna Citation Excel

  • 0.750 M
  • Above 26,515 ft
  • 432 kts
  • 400 – 430 kts
  • HSC

Models

  • Calculated Range Parameters
  • Passenger Weight

Cessna Citation Excel

  • NBAA IFR Reserve (100 nm), FL450, 2 Pilots, HSC Power
  • 200lb

Power Setting

  • Average Cruise Speed
  • Range – FullFuel, Max Takeoff Weight
  • Range – 2 Passengers
  • Range – 4 Passengers
  • Range – 6 Passengers
  • Range – 8 Passengers
  • Advertised Range

HSC

  • 0.7 M
  • 1,863 nm
  • 1,875 nm
  • 1,770 nm
  • 1,609 nm
  • 1,449 nm
  • 1,836 nm

LRC

  • 0.642 M
  • 1,993 nm
  • 2,016 nm
  • 1,887 nm
  • 1,705 nm
  • 1,523 nm

– Advertised Range Parameters

NBAA IFR Fuel Reserves (100 nm), HSC, Max Fuel, Max Takeoff Weight

True Air Speed

Models

  • Power Setting
  • Mid-Cruise Weight
  • 10,000 feet
  • 16,000 feet
  • 20,000 feet
  • 26,000 feet
  • 29,000 feet
  • 31,000 feet
  • 33,000 feet
  • 35,000 feet
  • 37,000 feet
  • 39,000 feet
  • 41,000 feet
  • 43,000 feet
  • 45,000 feet

Cessna Citation Excel

  • HSC
  • 17,000 lb
  • 353 kts
  • 385 kts
  • 408 kts
  • 427 kts
  • 428 kts
  • 430 kts
  • 432 kts
  • 430 kts
  • 427 kts
  • 423 kts
  • 418 kts
  • 410 kts
  • 395 kts

Models

  • Parameters
  • Reserve Fuel Amount

Cessna Citation Excel

  • NBAA IFR Reserve (100 nm), HSC Power
  • 1,204 lb

Trip Distance

  • 100 nm Trip
  • 200 nm Trip
  • 300 nm Trip
  • 400 nm Trip
  • 500 nm Trip
  • 700 nm Trip
  • 1000 nm Trip

Time (hh:mm) / Flight Lvl (ft x 1,000)

  • 0:18 hr / @FL 160
  • 0:32 hr / @FL 260
  • 0:46 hr / @FL 330
  • 1:01 hr / @FL 400
  • 1:15 hr / @FL 410
  • 1:44 hr / @FL 410
  • 2:27 hr / @FL 410

Block Fuel

  • 681 lb
  • 1,125 lb
  • 1,444 lb
  • 1,602 lb
  • 1,878 lb
  • 2,485 lb
  • 3,401 lb

Diagrams

Standard cabin
Interior Layout
Exterior front
Exterior Front
Exterior side
Exterior Side
Exterior top
Exterior Top

System Description

Fuel System

Two integral wing tanks, one in each wing. Each tank holds approx. 503 gal of useable fuel (1,006 gal total). Each wing tank supplies its respective engine through use of a primary ejector pump in the sump component of the tank. Three additional transfer ejector pumps scavage fuel to the wing sump. An electric boost pump in each wing supplements primary ejector pump for backup, engine start, fuel transfer, and optional APU only operation.

Fully automatic. Crossfeed capability.

Standard single point pressure refueling/defueling, located on right side of the fuselage just forward of the wing. System is independent of the fuel system. Gravity fuel fill port on each wing.

Utilizes Electronic Engine Control (EEC) fuel controller. EEC is a single channel system with manual mode. Fuel is heated through an oil heat exchanger.

Hydraulic System

Single, open-center, 1500 psi hydraulic system operates landing gear, flaps, speed brakes, two-position horizontal tail, and thrust reversers. Circulates at 60 psi.

Hydraulic pressure supplied by two engine-driven pumps. Either pump has the capacity to power all systems.

An independent, closed-center, hydraulic system is used for wheel brakes. Powered by an electric pump in the left side of the nose compartment. Operates at 1,000 psi. Motor only runs when landing gear are in the down position.

Flight Control System

Ailerons, elevator and rudder are mechanically operated by use of cables. Rudder and aileron are interconnected .

The aileron, elevator and rudder have manual trimmed control surfaces. Aileron trim has one tab on left aileron. Elevator trim tabs on both elevators can be positioned mechanically or electrically. Rudder trim incorporates servo/trim tab for reducing pedal pressures. A rudder-aileron interconnect via torsion bungee coordinates roll and yaw inputs.

Two-position stabilizer with takeoff/landing setting or cruise setting. Operates automatically based upon flap setting and are hydraulically actuated.

Fowler type inboard and outboard actuated flaps are electrically controlled and hydraulically actuated with a range of 0 to 35 degrees down.

Speed brakes on upper and lower surfaces of each wing are electrically controlled and hydraulically actuated. Speed brakes can be extended to within 50 ft AGL.

Mechanical nose wheel steering through rudder pedals.

Rudder bias system increases rudder travel from 22 degrees to 28.5 degrees in the event of an engine failure. Utilizes engine bleed air to power a pneumatic actuator. Rudder bias and rudder bias heater must also be operational for dispatch.

Stick shaker stall warning system. Stick pusher not required.

Mechanically operated control lock engages, ailerons, elevators, rudder, and throttles.

Environmental System

Uses bleed air for pressurization and air conditioning. Digital controller regulates two outflow values in aft pressure bulkhead. In auto mode, only set destination elevation. Controller has an auto-schedule for controlling pressure and rates of change – 600 fpm cabin climb rate and 500 fpm descent rate to fully depressurized by 1,500 ft. above landing altitude.

Emergency dump available for rapid depressurization. Emergency pressurization source from left engine directly into the cabin – no temperature control in that mode.

Single air cycle machine for cooling. Bleed air passes through pylon-mounted heat exchangers, then through a primary heat exchanger, then through the air cycle machine. Air outputted from ACM is routed through a water separator and then into the cool air overhead distribution system or mixed with hot bleed air and ducted through the floor and armrests distribution system. Two ozone converters filter engine bleed air prior to ACM.

Standard vapor cycle air conditioning system incorporates an aft cabin evaporator which supplies cool air through the overhead system and forward evaporator that blows cool air directly into the cabin through a floorboard grating. Operates up to 18,000 ft or on the ground by either a ground power cart or one operating engine.

Separate cabin and cockpit distribution systems/temperature zones controlled in cockpit. Optional cabin temperature control.

Honeywell RE100XL APU installation removes standard vapor cycle air conditioner. APU for ground cooling and inflight use. Can be started up to 20,000 ft and operated up to 30,000 ft. APU is not approved for unattended operation.

O2: 76 cu ft bottle standard.

1/02: 100% fresh air is delivered to the cabin.

Electrical System

Two, 28 volt DC, 300 ampere engine-driven starter-generators supply power through two buses that operate in parallel. (Starter-generators rated at 200 amps for ground operation.)

AC power from engine-driven alternators is used to power the electric windshield only. An AC inverter powers the electroluminescent panel lighting.

Standard 24 volt, 44 amp-hour nickel-cadmium battery housed in the LH aft fairing. External 28 volt DC power receptacle is located below the LH side below the engine pylon. APU supplies electrical power on the ground.

Ice and Rain Systems

Engine bleed air for anti-ice protection on engine inlets and wing leading edges. Pneumatic boots for de-ice protection on horizontal stabilizer leading edge surfaces. Electrically heated windshields (AC power) for anti-ice and defog capabilities.

Electrical heating elements on pitot tubes, static ports, TAS probe, and angle of attack probe. Windshield rain removal accomplished with high speed air by electric fan in nose avionics compartment.

Power Plants

Two Pratt & Whitney PW545A two stage, turbofans. A centrifugal compressor is driven by a high pressure turbine. Single fan and axial compressors driven by three low pressure turbines. Combustion chamber is a reverse flow design.

Fuel control is through a single channel Electronic Engine Control (EEC) with manual mode. Throttle detents send signals to EEC in auto mode. Aircraft can be dispatched in manual mode. Engine Diagnostic System (EDS) provides for troubleshooting.

Engine equipped with ground idle system which automatically reduces idle speed eight seconds after landing gear squat switches have sensed a landing. Normal flight idle is 56.5%.

Target-type thrust reversers are standard (hydraulically operated). Engine synchronizer is standard.

Equipped with fire detection loop (each engine) and two Freon fire extinguishing bottles (for both engines), electrically operated.

Landing Gear and Brakes

Landing gear is electrically controlled and hydraulically actuated. Main gear are trailing-link design with single wheel assembly and air over oil struts. Held up by mechanical uplocks that are normally released hydraulically.

Nose wheel is mechanically steered by the rudder pedals.

Emergency extension through a manual release of the uplocks and gravity free-fall and through a pneumatic blow-down and lock system.

Brakes: Carbon disc brakes on main wheels operate through separate hydraulic system using an electric pump housed in the LH nose compartment. System operates only when gear are down.

Standard digital anti-skid system must be operational for takeoff.

Pneumatic back-up system with bottle on LH side of forward pressure bulkhead (same system used for emergency gear extension).

There is no turn-around time limitation on the brakes, other than an Ops Manual explanation that says “The parking brake should not be set if the brakes are very hot”.

Avionics and Cockpit

Garmin G5000 avionics system featuring a fully integrated glass flight deck, integrated autopilot and EICAS systems, dual touchscreen controllers, weather radar and Sirius/XM weather datalink, Garmin Flitecharts, Garmin Safe Taxi, and WAAS GPS-guided LPV approach capability to 200’ minimums.  Also includes RVSM and ADS-B compliance.

Standard equipment includes:

Standard Avionics Equipment

  • Three GDU 1450W 14” displays (2 PFD and 1 MFD)
  • Dual GCU 275 controllers
  • GMC 700 dual autopilot
  • GEA 7100 engine/airframe EICAS system
  • Dual GIA 64E GPS/NAV/COM
  • Dual GTX 3000 ADS-B transponders (ADS-B Out)
  • Dual GTC 575 touchscreen controllers
  • Dual GMA 36B audio panels
  • GWX 75 radar with 12” antenna
  • GDL 69A Sirius/XM weather datalink (subscription required)
  • TAWS A
  • Dual GRS 79 AHRS
  • Dual GDC 7400 RVSM ADC

Additional Avionics and Standard Equipment

  • Honeywell TCAS 2000
  • Meggitt II standby ADI
  • ATG 5000 Wi-Fi
  • USB ports at each cockpit seat, at each forward club seat, at each forward-facing aft seat

No overhead or side switches, gages, or controls.

Cabin and Baggage System

Constant cross section with 11 windows and a 13 inch wide dropped aisle extends from cockpit divider to the aft bulkhead. 6,800 ft cabin at 45,000 ft.

Standard Interior: Eight individual passenger seats in a forward club configuration. Seats are pedestal mounted, track fore and aft 7 inches, laterally 3.6 inches, 360 degree swivel and infinite recline (fully berthable). Seats have a single, inboard, lift-type armrest (dual armrest an option). Seat dimensions: 19″ seat cushion width (17.5″ with dual armrests), 20″ back cushion width. Side facing seat: width = 20″, seating depth = 14″.

LH & RH tables.

Aft LH belted, flushing toilet. Lav divider has sliding privacy doors with mirror treatment. Aft centerline closet. LH forward refreshment center – measures 23.7″ wide.

Cockpit divider with 1/2 length curtain.

Up to 9 passenger seating arrangement including RH forward 2-place side-facing couch and belted seat in the aft Lav (9th seat optional). Cockpit sliding doors, various forward closets and refreshment centers, dual arm rests. Externally serviceable RH non-belted toilet. Entertainment systems

Baggage: Aft tailcone baggage compartment not heated nor pressurized. Aft baggage door sill height: 44″.

Airframe

Eleven (11) boundary layer energizers on leading edge of each wing – all required for dispatch. Stall strip on leading edge of each wing.

Fifty two (52) vortex generators on top of wings. Up to 3 may be missing for dispatch provided the aircraft is limited to FL410.

Limitations: Anti-skid must be operational for takeoff. Rudder bias and rudder bias heating system must be operational.

Flaps are composite.

Outside fuselage diameter = 72.5 in.

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