Specifi cation & Description - Founders Aviation

1 Specifi cation &DescriptionPreliminaryMarch 2013, Revision BUnits 680-0501 to TBDSPECIFICATION AND DESCRIPTIONUNITS 680-0501 TO TBDMARCH 2013 REVISION BPRELIMINARYC itation MarketingCessna aircraft Box 7706 Wichita, Kansas 67277-7706 Copyright 2013 Cessna aircraft CompanyMarch 2013, Revision B, Preliminary1 INTRODUCTIONThis Specifi cation and Description is published for the pur-pose of providing general information for the evaluation of the design, performance, and equipment of the Cessna Citation Sovereign, Units 680-0501 to TBD. This docu-ment supersedes all previous Specifi cation and Descrip-tion documents and describes only the Cessna Citation Sovereign Model 680, its powerplants and to the time span between the date of this Specifi - cation and Description and the scheduled delivery date of the aircraft , Cessna reserves the right to revise the Specifi cation whenever occasioned by product improve-ments, government regulations or other good cause as long as such revisions do not result in a material reduc-tion in the event of any confl ict or discrepancy between this document and the terms and conditions of the purchase agreement to which it is incorporated, the terms and con-ditions of the purchase agreement additional information contact:Citation MarketingCessna aircraft Box 7706 Wichita, Kansas 67277-7706 Telephone: 316-517-6449 Telefax: 316-517-6640 WARNING.

2 This product contains Halon 1211 and Halon 1301. Furthermore, the product is manufactured with 1-1-1 Trichloroethane, substances which harm public health and environment by destroying ozone in the upper atmo-sphere. March 2013, Revision B, Preliminary2 Cessna Citation Sovereign Specification and DescriptionSection Page 1. General Description .. Certifi cation .. Approximate Dimensions .. Design Weights and 2. Performance .. 3. Structural Design Criteria .. 4. Fuselage .. 5. Wing .. 6. Empennage .. 7. Landing Gear .. 8. Powerplants .. 9. Systems .. Flight Controls.

3 Fuel System .. Hydraulic System .. Electrical System .. Pressurization and Environmental System .. Oxygen System .. Ice and Rain Protection .. 10. Flight Compartment, Instrumentation and Avionics .. General .. Instrument and Control Panel .. Avionics .. 11. Interior .. Cabin .. Baggage Compartments .. 12. Exterior .. 13. Additional Equipment .. 14. Emergency Equipment.

4 15. Documentation and Technical Publications .. 16. Computerized Maintenance Record Service .. 17. Limited Warranties .. Cessna Citation Sovereign Limited Warranty .. New Engine Warranty .. Summary of Honeywell APU 18. Citation Sovereign Crew Training Agreement .. FIGURE I CITATION Sovereign EXTERIOR DIMENSIONS .. FIGURE II CITATION Sovereign INTERIOR DIMENSIONS .. FIGURE III CITATION Sovereign INSTRUMENT PANEL AND PEDESTAL LAYOUT .. FIGURE IV CITATION Sovereign STANDARD FLOORPLAN .. TABLE OF CONTENTS33366778889991010101111111313131 316161618181818191919202122451219 March 2013, Revision B, Preliminary3 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.

5 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 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 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 CertificationThe Model 680 is certifi ed to the requirements of 14 CFR Part 25, Transport Category, including day, night, VFR, IFR, fl ight into known icing conditions and for steep approach operations.

6 The Sovereign is compliant with all RVSM certifi cation requirements (Note: specifi c approval is required for operation within RVSM airspace; Cessna offers a no charge service to assist with this process.) The Purchaser is responsible for obtaining aircraft op-erating approval from the relevant civil Aviation author-ity. International certifi cation requirements may include modifi cations and/or additional equipment; such costs are the responsibility of the CESSNA aircraft COMPANYMODEL 6801. GENERAL Approximate DimensionsOverall Height ..Overall Length .. Overall Width .. Wing Area .. Sweepback (leading edge) .. Sweepback (at 25% chord) .. Horizontal Tail Span (overall).

7 Area .. Sweep (at 25% chord) .. Vertical Tail Height .. Area .. Sweepback (at 25% chord) .. Cabin Interior Height (maximum over aisle).. Width (trim to trim).. Length (forward pressure bulkhead to aft pressure bulkhead).. Landing Gear Tread (main to main).. Wheelbase (nose to main)..20 ft 4 in ( m)63 ft 6 in ( m)72 ft 4 in ( m)72 ft 4 in ( m) ft2 ( m2) degrees27 ft 7 in ( m) ft2 ( m2) degrees10 ft 11 in ( m) ft2 ( m2) degrees68 in ( m)66 in ( m)30 ft 9 in ( m)10 ft 0 in ( m)27 ft 10 in ( m)March 2013, Revision B, Preliminary427 ft 7 in ( m)72 ft 4 in ( m)10 ft 0 in ( m)27 ft 10 in ( m)63 ft 6 in ( m)20 ft 4 in( m) 1. GENERAL DESCRIPTIONFIGURE I CITATION SOVEREIGN EXTERIOR DIMENSIONSM arch 2013, Revision B, Preliminary51. GENERAL DESCRIPTIONFIGURE II CITATION SOVEREIGN INTERIOR DIMENSIONS66 in ( m)244 in ( m)59 in ( m)30 in (.)

8 76 m)55 in ( m)11 in (.28 m)14 in (.36 m)20 in (.51 m)36 in (.91 m)68 in ( m)66 in ( m)March 2013, Revision B, Preliminary61. GENERAL DESCRIPTIONT akeoff Runway Length .. (Maximum Takeoff Weight, Sea Level, ISA, Balanced Field Length per FAR 25, 15 Flaps)Climb Performance .. (Maximum Takeoff Weight, Sea Level, ISA)Maximum Altitude .. Maximum Cruise Speed ( 3%) .. (Mid-Cruise Weight, 35,000 ft (10,668 m), ISA)NBAA IFR Range (200 nm alternate) ( 4%) .. (Maximum Takeoff Weight, Full Fuel, Optimal Climb and Descent, Maximum Cruise Thrust at 47,000 feet)Landing Runway Length .. (Maximum Landing Weight, Sea Level, ISA, per FAR 25)Certifi cated Noise Levels Flyover .. Lateral .. 3,650 ft (1,113 m)31 min to 45,000 ft (13,716 m)47,000 ft (14,326 m)458 KTAS (848 km/hr or 527 mph)3,000 nm (5,556 km or 3,452 mi)2,680 ft (817 m) EPNdB2.

9 Design Weights and CapacitiesMaximum Ramp Weight .. Maximum Takeoff Weight .. Maximum Landing Weight .. Maximum Zero Fuel Weight .. Standard Empty Weight* .. Useful Load .. Fuel Capacity (usable) at lb/gal .. * Standard empty weight includes unusable fuel, full oil, standard interior, and standard ,025 lb (14,073 kg)30,775 lb (13,959 kg)27,575 lb (12,508 kg)21,000 lb (9,525 kg)17,710 lb (8,033 kg)12,645 lb (5,736 kg)11,390 lb (5,166 kg)All performance data is based on a standard aircraft confi guration, operating in International Standard Atmosphere (ISA) conditions with zero wind. Takeoff and landing fi eld lengths are based on a level, hard surface, dry runway. Actual performance will vary with individual airplanes and other factors such as environmental conditions, aircraft confi guration, and operational/ATC 2013, Revision B, Preliminary7 The fuselage has a constant circular cross section and is attached to the wing without any cutouts for the spar.

10 A dropped aisle from just behind the cockpit through the lavatory provides stand-up access throughout the cabin. The keyed cabin door is located on the forward left-hand side of the fuselage. It is hinged at the bottom and has six locking cams. The aircraft is certifi ed with a single, passive pressurization seal. In addition, an acoustic seal infl ates with service air when the door is closed and the left engine is running. An integrated handrail extends with the door when open to assist entering and exiting via the four-step airstair. A plug-type emergency exit is located in the lavatory on the right-hand side of the cabin. The glass windshields are designed to meet bird resis-tance requirements of 14 CFR Part 25. Openable side windows are provided on both sides of the cockpit. Rein-forced frame structures surround the main door opening, emergency exit, and windshields, providing structural nose section houses some avionics components and other equipment such as the nose wheel steering accumulator, landing gear pneumatic blow-down bottle, emergency braking bottle, and one of two baggage fi re suppression bottles.