Specification &Description

April 2005(Units 680-0001 to TBD)

S P E C I F I C AT I O N A N D D E S C R I P T I O N

( U N I T S 6 8 0 - 0 0 0 1 T O T B D )

A P R I L 2 0 0 5

Citation Marketing

Cessna Aircraft Company

P.O. Box 7706

Wichita, Kansas 67277-7706

April 2005

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I N T R O D U C T I O N

This Specification and Description is published for the pur-pose of providing general information for the evaluation ofthe design, performance, and equipment of the CessnaCitation Sovereign, Units 680-0001 to TBD. This documentsupersedes all previous Specification and Description doc-uments and describes only the Cessna Citation SovereignModel 680, its powerplants and equipment.

Due to the time span between the date of thisSpecification and Description and the scheduled deliverydate of the Aircraft, Cessna reserves the right to revisethe "Specification" whenever occasioned by productimprovements, government regulations or other goodcause as long as such revisions do not result in a mate-rial reduction in performance.

In the event of any conflict or discrepancy between thisdocument and the terms and conditions of the purchaseagreement to which it is incorporated, the terms andconditions of the purchase agreement govern.

For additional information contact:

Citation MarketingCessna Aircraft CompanyP.O. Box 7706Wichita, Kansas 67277-7706

Telephone: 316-517-6449Telefax: 316-517-6640

WARNING: This product contains Halon 1211, Halon 1301, and also R-134A. Furthermore, the product wasmanufactured with CFC-12 and 1-1-1 Trichloroethane, substances which harm public health and environment bydestroying ozone in the upper atmosphere.

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TA B L E O F C O N T E N T S

Cessna Citation Sovereign Specification and Description

Section Page

1. General Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32. Performance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53. Structural Design Criteria . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 74. Fuselage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 75. Wing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 86. Empennage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 87. Landing Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 88. Powerplants . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 99. Systems

9.1 Flight Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 99.2 Fuel System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 109.3 Hydraulic System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 109.4 Electrical System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 109.5 Pressurization and Environmental System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 119.6 Oxygen System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 119.7 Ice and Rain Protection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

10. Flight Compartment, Avionics and Instrumentation10.1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1210.2 Flight Compartment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1210.3 Avionics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

11. Interior11.1 Cabin . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1911.2 Baggage Compartment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

12. Exterior . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2013. Additional Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2014. Emergency Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2015. Documentation and Technical Publications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2016. Computerized Maintenance Record Service (CESCOM) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2117. Limited Warranties . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2118. Citation Sovereign Crew Training Agreement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

FIGURE I — CITATION SOVEREIGN EXTERIOR DIMENSIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4FIGURE II — CITATION SOVEREIGN INTERIOR DIMENSIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6FIGURE III — CITATION SOVEREIGN INSTRUMENT PANEL AND PEDESTAL LAYOUT . . . . . . . . . . . . . . . . . . . 18FIGURE IV — CITATION SOVEREIGN STANDARD FLOORPLAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

April 2005

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M A N U FA C T U R E R C E S S N A A I R C R A F T C O M PA N Y

M O D E L 6 8 0

1 . G E N E R A L D E S C R I P T I O NThe Cessna Citation Sovereign is a low-wing monoplanewith retractable tricycle landing gear and a cruciform tail.A pressurized cabin accommodates a crew of two pluseight to twelve passengers (nine is standard). Two Pratt &Whitney Canada (P&WC) PW306C turbofan engines arepylon-mounted on the rear fuselage. Fuel stored in thewings offers generous range for most missions typical ofthis class aircraft. Space for baggage is provided in thetailcone with added storage space available in the cabin.

Multiple structural load paths and system redundancieshave been built in to the airframe. Certain parts with non-critical loads such as the nose and fairings are made ofcomposite materials to save weight. Metal bonding tech-niques have been used in many other areas for addedstrength and reduced weight. Anti-corrosion treatmenthas been applied to metal parts where needed.Lightning protection is incorporated into the airframe.

Cessna provides a third-party training package for pilotsand mechanics as well as a comprehensive warranty as

described in this book. Cessna's worldwide network ofcompany-owned and authorized service centers offers acomplete source for all servicing needs.

Certification

The Model 680 is certified to the requirements of U.S. FAAFederal Aviation Regulation Part 25, transport category,including day, night, VFR, IFR, Category I operations, andflight into known icing conditions. The Sovereign also meetsthe requirements of RVSM certification. (Note: specificapproval is required for operation within RVSM airspace;Cessna offers a fee-based service to assist with thisprocess.) An interior configuration of ten or more passen-gers is not available for FAR Part 135 operations.

The purchaser is responsible for obtaining aircraft oper-ating approval from the relevant civil aviation authority.International certification may require modifications andadditional equipment; such costs are the responsibility ofthe Purchaser.

Approximate Dimensions

Overall Height . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 ft 4 in (6.20 m)Overall Length . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 63 ft 6 in (19.35 m)Overall Width . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 63 ft 4 in (19.30 m)Wing

Span (does not include tip lights) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 63 ft 2 in (19.25 m)Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 515.9 ft2 (47.93 m2)Sweepback (leading edge) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16.3 degreesSweepback (at 25% chord) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.7 degrees

Horizontal TailSpan (overall) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 ft 7 in (8.41 m)Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 138.5 ft2 (12.87 m2)Sweepback (at 25% chord) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22.6 degrees

Vertical TailHeight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 ft 11 in (3.33 m)Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 95.3 ft2 (8.85 m2)Sweep (at 25% chord) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38.3 degrees

Cabin InteriorHeight (maximum over aisle) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 68 in (1.73 m)Width (trim to trim) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66 in (1.68 m)Length (forward pressure bulkhead to aft pressure bulkhead) . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 ft 9 in (9.37 m)

Landing GearTread (main to main) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 ft 0 in (3.05 m)Wheelbase (nose to main) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 ft 10 in (8.49 m)

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FIGURE I — CITATION SOVEREIGN EXTERIOR DIMENSIONS

27 ft 7 in (8.41 m)

20 ft 4 in(6.20 m)

63 ft 6 in (19.35 m)

63 ft 4 in (19.30 m)

10 ft 0 in(3.05 m)

27 ft 10 in (8.49 m)

April 2005

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2 . P E R F O R M A N C E

1 . G E N E R A L D E S C R I P T I O N ( C o n t i n u e d )

Design Weights and Capacities

Maximum Ramp Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30,250 lbs (13,721 kg)Maximum Take Off Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30,000 lbs (13,608 kg)Maximum Landing Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27,100 lbs (12,292 kg)Maximum Zero Fuel Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20,300 lbs (9,208 kg)Fuel Capacity (useable) at 6.70 lbs/gal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11,216 lbs (5,087 kg)

NBAA IFR Range (200 nm alternate) (± 4%) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2,881 nm (5,336 km)(Maximum Takeoff Weight, Full Fuel, Optimal Climband Descent, Maximum Cruise Thrust at 47,000 feet)

Maximum Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 47,000 ft (14,326 m)

Climb Performance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 min to 43,000 (13,106 m)(Maximum Takeoff Weight, from Sea Level, ISA)

Takeoff Runway Length . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3,580 ft (1,091 m)(Maximum Takeoff Weight, Sea Level, ISA,Balanced Field Length per FAR 25, 15° Flaps)

Landing Runway Length . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2,650 ft (808 m)(Maximum Landing Weight, Sea Level, ISA, per FAR 25)

Maximum Cruise Speed (± 3%) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 458 KTAS (848 km/hr or 527 mph)(Mid-Cruise Weight, 35,000 ft (10,668 m), ISA)

Certificated Noise LevelsFlyover . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 71.5 EPNdBLateral . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 87.6 EPNdBApproach . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 91.3 EPNdB

All performance data is based on a standard aircraft con-figuration, operating in International Standard Atmosphereconditions with zero wind. Takeoff and landing fieldlengths are based on a level, hard surface, dry runway.

Actual performance will vary with individual airplanes andother factors such as environmental conditions, aircraftconfiguration, and operational/ATC procedures.

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FIGURE II — CITATION SOVEREIGN INTERIOR DIMENSIONS

66 in (1.68 m)

66 in (1.67 m) 244 in (6.20 m) 59 in (1.50 m)

68 in(1.73 m)

20 in(.51 m)

14 in(.36 m)

11 in(.28 m)

30 in(.76 m)

36 in(.91 m)

55 in(1.40 m)

April 2005

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4 . F U S E L A G E

3 . S T R U C T U R A L D E S I G N C R I T E R I AThe Citation Sovereign airframe is conventional indesign, incorporating aluminum alloys, steel and othermaterials as appropriate. Engineering principles usingmultiple load paths, damage tolerance, low stress levels

and small panel size are incorporated in the primarystructure. Design maneuver limit load factors are -1.2 Gsto +3.0 Gs. Ultimate loads are defined as 1.5 times thelimit loads.

Limit SpeedsVMO 8,000 ft (2,438 m) to 29,833 ft (9,093 m) . . . . . . . . . . . . . . . . . . . . . . . . . . . . 305 KIAS (565 km/hr, 351 mph)MMO 29,833 ft (9,093 m) and above . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Mach 0.80

Flap Extension SpeedsVFE 0° to 7° Extension . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 250 KIAS (463 km/hr, 288 mph)VFE 7° to 15° Extension . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 KIAS (370 km/hr, 230 mph)VFE 15° to 35° Extension . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 175 KIAS (324 km/hr, 201 mph)

Landing Gear Operating and Extended SpeedsVLO . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 210 KIAS (389 km/hr, 242 mph)VLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 210 KIAS (389 km/hr, 242 mph)

The fuselage has a constant circular cross section andis attached to the wing without any cutouts for the spar.A dropped isle from just behind the cockpit through thelavatory provides stand-up access throughout the cabin.

The keyed cabin door is located on the forward left-handside of the fuselage. It is hinged at the bottom and has sixlocking cams. The aircraft is certified with a single, pas-sive pressurization seal. In addition, an acoustic sealinflates with service air when the door is closed and theleft throttle is out of cutoff. An integrated handrail extendswith the door when open to assist entering and exiting viathe four-step airstair. A plug-type emergency exit is locat-ed in the lavatory on the right-hand side of the cabin.

The glass windshields are designed to meet bird resist-ance requirements of FAR 25. Openable side windowsare provided on both sides of the cockpit. Reinforcedframe structures surround the main door opening, emer-gency exit, and windshields providing structural continuity.

The nose section houses the avionics bay and otherequipment such as nose wheel steering accumulator,landing gear pneumatic blow-down bottle, emergencybraking bottle, and one of two baggage fire suppression

bottles. Behind the composite radome is the high-reso-lution weather radar antenna and processor.

A large, class C heated baggage compartment in the tail-cone includes two optical smoke detectors and isaccessed from the left side beneath the engine pylonthrough a door with integrated steps. A baggage fireextinguishing system, utilizing Halon, provides a highdischarge bottle (HDB) in the tailcone and a metered dis-charge bottle (MDB) in the nose. The high discharge bot-tle is shared with the APU such that its use for either sys-tem will shut down both. The MDB automatically pro-vides a slow, continuous flow of agent into the baggagecompartment following use of the HDB.

The equipment bay in the tailcone houses the majorcomponents of the hydraulic, environmental, electricaldistribution, engine and baggage fire extinguishing sys-tems, and some avionics. External access to the equip-ment bay is provided through a door on the lower right-hand side of the tailcone. An area work light is provided.Additional equipment may also be accessed throughremovable panels inside the baggage compartment. TheAPU is located in and accessed through service doors inthe aft part of the tailcone.

8

For pitch and yaw, the empennage incorporates theappropriate control surfaces and systems, includingmach trim, rudder bias, and a single yaw damper. Thehorizontal stabilizer is designed with no dihedral and istrimable by an electrically driven actuator. The elevators

each have anti-float tabs that are interconnected to thehorizontal stabilizer. Engine bleed air protects the leadingedge of the horizontal stabilizer from ice. A single rudderon the vertical stabilizer controls yaw with a servo typetrim tab. A red flashing beacon is mounted on the top.

6 . E M P E N N A G E

7 . L A N D I N G G E A RThe main and nose landing gear each use dual wheelassemblies. The landing gear retraction system is elec-trically controlled and hydraulically actuated. Each maingear is a trailing link type and retracts inboard into thewing and belly fairing. The nose gear automatically cen-ters while retracting forward into the nose and, whenretracted, is enclosed by doors. Extension or retractiontakes about eight seconds and all V-speeds associatedwith the gear equal 210 knots. Single chined tires areused on the nose gear for water and slush deflection.Squat switches on all three gear assemblies provideinput to the squat switch logic that affects many systems.Two emergency gear extension methods are provided: apneumatic blow-down system (independent bottle innose) and manual gear release handles.

Multi-disc carbon brakes are installed independently onall four main gear wheels and are hydraulically actuated.Toe pedal pressure is transmitted via cables to the brakemetering valve which regulates main hydraulic systempressure in proportion to pilot input. The metering valvealso applies the brakes automatically during gear retrac-tion to stop wheel spin.

Normal braking power is supplied by the main hydraulicsystem with back-up provided by a pneumatic system. Aseparate electrically driven hydraulic pump may be usedon the ground only for maintenance and to set the parkingbrake when the engines are not running. A digital antiskidsystem provides individual wheel skid protection at anyspeed, and includes touchdown protection, a feature thatprevents braking until the wheels are rotating. The brakeback-up system uses a dedicated nitrogen bottle in thenose and if used, does not provide antiskid protection.

Nose wheel steering is controlled through the rudderpedals and through a handwheel on the pilot's side ledge.The two systems are mechanically linked and are con-nected to the hydraulically powered rack and pinionsteering system on the nose gear. The rudder pedalsallow steering up to 7 degrees either side of center andthe handwheel allows up to 81 degrees. Combined, thenose wheel may be turned up to 85 degrees on eitherside. A back-up NWS accumulator operates automatical-ly if main hydraulic pressure is lost. All ground handlingrequires that the nose gear scissor connector be discon-nected to allow full castering and to prevent damage.

5 . W I N GThe Citation Sovereign utilizes an advanced, moderate-ly swept wing selected for its low aerodynamic drag andfavorable approach and landing characteristics.

A three-spar design gives the wing both structuralintegrity and high internal volume for its integral fueltanks. It is designed to be damage tolerant and incorpo-rates bonding and riveting techniques with doublers toprovide increased skin thickness in highly loaded areas.A shallow drop in the center wing section permits attach-ment of the fuselage without interruption of the cabin

cross-section. Composite fairings blend the wing andfuselage for minimum drag.

Electrically driven aluminum fowler flaps, arranged inthree sections on each wing, and hydraulically drivenspoilers, five sections per wing, are utilized for lift, drag,and roll control. Conventional ailerons are installed nearthe wing tips. The wing leading edges are anti-iced usingengine bleed air. The wing tips include navigation andanti-collision strobe lights and static wicks.

April 2005

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9.1 Flight Controls

The Sovereign's flight controls consist of dual controlwheel columns and adjustable brake and rudder pedals.Unpowered pushrod and cable systems are used toactuate the rudder, elevators, and ailerons. In addition, ahandwheel is provided on the pilot's side ledge to controlthe hydraulically powered rack and pinion nose wheelsteering system. The handwheel provides 81° of nosewheel deflection either side of center versus 7° for therudder pedals. Corrosion resistant stainless steel cablesare used in all primary and secondary systems.

The one-piece, trimable, horizontal stabilizer has rightand left pilot-actuated elevators. Dual independent cablesystems are routed from each pilot's controls to therespective elevator with a mechanical disconnect handleon the pedestal. Stick shakers on each pilot's control col-umn plus an aural tone provide stall warning in additionto instrument indications.

The single rudder is connected to the rudder pedals bya cable system that is split through the non-containmentzone. A single yaw damper is included to augment later-al stability throughout the flight envelope. A two-chamberrudder bias system is incorporated for automatic controlenhancement during engine-out conditions. The biassystem is connected to the rudder through a variableleverage actuator that automatically adjusts for airspeed,providing the greatest leverage below 125 knots.

There are five hydraulically actuated spoiler panels oneach wing. The middle three panels modulate in con-junction with the ailerons to augment roll control. All fivefunction as speed brakes in flight and after landing. Theaileron surfaces are operated by the pilot's yoke whilethe roll spoilers are hydraulically actuated and are oper-ated by the copilot's yoke. The two otherwise independ-ent systems are interconnected in the cockpit by amechanical disconnect system. Within the cable linkage

9 . S Y S T E M S

8 . P O W E R P L A N T STwo Pratt & Whitney Canada PW306C turbofan enginesare installed on each side of the rear fuselage. Thisengine is a 4.4 to one, high bypass ratio, twin spooldesign with a damage resistant wide chord fan. Behindthe fan, four axial and one centrifugal compressor stageslead to a high efficiency, low emission, through-flow com-bustor and five turbine stages. Two stage variable inletguide vanes and bleed-off valves are controlled by theFADEC to optimize compressor performance and engineoperability. A forced exhaust mixer improves fuel burnand reduces noise. Maximum static takeoff thrust at sealevel is flat rated to 5,770 pounds (25.66 kN) up to 91°F(ISA+18°C). Advanced alloys and cooling technologiesallow for 6,000 hours between overhauls.

Engine start is accomplished electrically through astarter-generator powered by any of the followingsources: the aircraft's two batteries, the auxiliary powerunit, the other running engine, or a ground power unit.Both low- and high-pressure engine bleed air is extract-ed for anti-ice and environmental requirements. Fan airis tapped for pre-cooling of bleed air. A continuous loopfire detection system monitors the nacelle area to detectand warn if a fire occurs. A two-shot fire extinguishingsystem is provided.

Dual channel Full Authority Digital Electronic Controls(FADECs) provide automation and efficiency in enginemanagement. Detents in the throttle quadrant (takeoff,maximum continuous, high speed cruise) permit optimalpower settings based on ambient conditions for eachphase of flight. The system also provides engine protec-tion, synchronization, and diagnostic capability.

Hydraulically actuated, target-type thrust reversers areattached to each engine. Deployment takes about onesecond. The effect of the thrust reversers on runwayperformance is accounted for under some conditions.

Auxiliary Power Unit (APU)

A Honeywell RE100[CS] auxiliary power unit is installedin the tailcone and may be started at up to 20,000 feetand operated up to 30,000 feet. Fuel burn for the APU isabout 110 to 125 pph.

The APU is not approved for unattended use. However, itselectronic control unit monitors all parameters and willautomatically shut down the APU if operating limits areexceeded. If fire is detected, the extinguisher (shared withthe baggage compartment) will automatically dischargeafter eight seconds, if not activated sooner by the crew.

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to the ailerons, a ratio changer provides airspeed-dependent variable mechanical advantage to the pilotsfor moving the control surfaces at different airspeeds. Athigh airspeeds the force to move the yoke is reduced byapproximately 30 percent.

All trim is electrically controlled. The rudder trim knob andthe split aileron trim switches (both on the pedestal) acti-vate motors to change the base position of their respec-tive servo tabs. Split elevator trim switches on each yokeaffect the electrically driven primary stabilizer trim actua-tor to change the angle of incidence of the horizontal sta-bilizer to any point between negative 6.9 and positive 1.2degrees. A secondary electric actuator serves as back-upand is controlled by a guarded split switch on thepedestal. When the horizontal stabilizer moves, the inter-connected anti-float tabs on each elevator also move tocompliment aerodynamic forces. A mach trim system isinstalled and is effective between 0.76 and 0.80 mach butis not required for dispatch. An integral control lock is pro-vided for the ailerons, elevators and rudder.

Aluminum fowler flaps are arranged in three sections perwing and are controlled through a lever with detents onthe pedestal. Asymmetric protection and soft-start areincorporated in the design with one electric motor drivingthe flaps to one of four positions: up, 7°, 15°, and 35°.Between 15° and 35° a signal is sent to the stabilizer trimactuator to automatically adjust to prevent pitch changes.

9.2 Fuel System

Two integral fuel tanks, one in each wing, provideapproximately 11,216 pounds (5,087 kg) of usable fuel.System operation is fully automatic with each enginereceiving fuel from its respective wing tank. Crossfeedcapability is provided and, when selected, enables bothengines to receive fuel from a single tank. Tank to tanktransfer is not possible.

Electric boost pumps located in the wing roots supplyfuel during engine start, APU start, crossfeed, and asneeded to supply the required fuel pressure. For eachengine a two-stage engine driven pump provides fuel atlow and high pressure. Low pressure fuel flows to thefuel/oil heat exchanger and the fuel filter. High pressurefuel is sent back to the primary and scavenge motiveflow pumps in the wing tanks and to the hydromechani-cal metering unit (HMU). The HMU delivers fuel to theengine and to the variable guide vanes actuator and isfully controlled by the FADECs according to pilot

demand and ambient conditions. The fuel/oil heatexchangers eliminate the need for an anti-ice additive.

Fuel levels are monitored by an active probe system.Refueling is accomplished through over wing filler portswith locking caps or through the single point refueling /defueling system, which does not require electricalpower. Maximum fuel through the single point system is1,600 gallons or 10,720 pounds (4,862 kg). To fill to max-imum capacity, the over wing filler ports must be used.

9.3 Hydraulic System

A closed-center, constant pressure 3,000 psi (206.8 bar)hydraulic system operates the landing gear, brakes,nose wheel steering, spoilers, and thrust reversers.Hydraulic pressure is supplied by two engine drivenpressure compensating pumps, one located on eachengine. Either pump can supply enough flow to operatethe system. An electrically powered pump located in thefairing behind the wing performs certain maintenancefunctions and is available only on the ground to set thebrakes for parking. Ground connections to service thesystem are located on the right side below the engine.

9.4 Electrical System

The Sovereign's electrical system incorporatesEuropean compliant, split bus architecture with a bus tie,designed so that essential equipment operation will notbe interrupted in the event of a single power source ordistribution system failure.

Two 28-volt DC, 300 ampere, engine-driven starter/gen-erators supply primary electrical power. Generator con-trol units provide static regulation, overvoltage, feederfault, and ground fault protection for each generator.Each engine also drives an alternator to support a dedi-cated AC system for electrical anti-icing of the wind-shield. Power for the dual channel FADECs is providedby aircraft power during initial engine start, then byengine driven permanent magnet alternators for normaloperations. One static inverter supplies AC power for theneeds of the cabin.

Two 24-volt, 44-amp-hour, nickel-cadmium batteries aremounted inside access panels on each side of the fuselagejust behind the wings to supply power for starting andemergency requirements. Power for all engine and APUstarts is either provided by or assisted by the batteries tominimize the burden on the generators. A receptacle abovethe right side battery allows connection of an external

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9 . S Y S T E M S ( C o n t i n u e d )power unit. Battery voltage, amperage, and temperaturemonitoring and battery disconnect systems are provided.

Exterior lighting consists of one red flashing beacon, twoanti-collision strobes, two wing inspection lights, naviga-tion lights, two taxi lights (located on the nose gear), andtwo landing/recognition lights (located at the wing roots).

9.5 Pressurization and Environmental System

The pressurization and air conditioning systems utilizeengine or APU bleed air through a single air cyclemachine (ACM) to pressurize and air condition the cabinand defog the cabin and cockpit side windows. Ram airfor cabin ventilation is available when the pressurizationsystem is not in use. Pressurization is controlled by twooutflow valves located in the aft pressure bulkhead. Thepressurization controller automatically schedules cabinaltitude and rate of change. Ozone converters areincluded in the bleed air system. The system provides a7,230 foot (2,204 m) cabin altitude at 47,000 feet(14,326 m) (9.3 psi or 0.64 bar nominal maximum work-ing pressure). Sea level cabin altitude can be maintainedto 25,230 feet (7,690 m).

Bleed air is conditioned as it passes through the ACMand is distributed to the cabin and cockpit via overheadair ducts and outlets, under floor ducts, and sideledge airducts. Two thermostats and a dual-zone temperaturecontroller automatically maintain the cabin and cockpittemperatures separately. The cabin temperature is con-trolled from the VIP seat location.

9.6 Oxygen System

A 76.0 cubic foot (2.15 m3) oxygen bottle, located in thebelly fairing, is provided with a high pressure gauge andbottle-mounted pressure regulator. A second 76.0 cubicfoot oxygen bottle is available as an option. Pressuredemand masks are provided for the crew while automat-ic dropout, constant-flow oxygen masks are provided ateach passenger seat and the lavatory. Oxygen flow to thecabin is controlled by a sequencing regulator valve foroptimal passenger usage.

9.7 Ice and Rain Protection

Engine bleed air is used for anti-ice protection of theengine inlets and the leading edges of the wing and hor-izontal stabilizer. Bleed air plumbing is monitored forleaks using eutectic salt sensing lines. The pitot tubesand static ports (mains and standby), and the angle ofattack probe are electrically anti-iced using main oremergency DC power. The repellant-coated glass wind-shields are also electrically heated, however, power forthe windshields is provided by dedicated AC alternators,one on each engine, and is on whenever the engines arerunning. A windshield ice detection light is mounted onthe glareshield and two wing inspection lights are mount-ed on the fuselage to assist in detection of ice buildupduring night flights. The two-speed blower fan mountedin the nose avionics bay for avionics cooling is availableto assist with rain removal from the windshields duringtaxi operations.

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10.1 General

Described below is the Citation Sovereign standard avionicssuite as referred to in the Limited Warranties (section 17).

• Four Modular Avionics Units (MAU) - Honeywell, Two MAR-950s, Two MAR-951s

• Four 8 x 10 inch Flat Panel Liquid Crystal Display Units -Honeywell DU-1080s Designated As:• Two Primary Flight Displays (PFD)• One Multi-Function Display (MFD)• One Engine Indication and Crew Alerting System (EICAS)

• Dual Air Data Modules (ADM) - Honeywell AZ-200• Dual Attitude Heading Reference Systems (AHRS) - Collins

AHC-3000• Dual Angle of Attack Sensors (AOA)• Dual Automatic Flight Control Systems (AFCS) with Three

Axis Autopilot and Flight Director - Honeywell• Flight Guidance Controller Panel (GP) - Honeywell GP-400• Dual Multi-Functional Control Display Units (MCDU) with

Integrated Flight Management Systems (FMS) and GlobalPositioning System (GPS) Receivers - Honeywell MC-850

• Dual Aural Warnings / Tone Generation Systems• Dual EFIS Clocks with Elapse Timers• Dual Remote Mounted Modular Radio Cabinets - Honeywell

MRC-855 Including the Following LRUs:• Dual VHF Communication Transceivers• Dual Mode S Diversity Transponders - Honeywell XS-857A• Dual Navigation Receivers (VOR/Localizer/Glideslope/

Marker Beacon)• Dual Distance Measuring Equipment (DME) Receivers• Single Automatic Direction Finder (ADF)

• Dual Digital Audio Panels - Honeywell AV-850A• Dual Cursor Control Devices (CCD) - Honeywell CC-950• Color Weather Radar With Turbulence Detection - Honeywell

Primus 880• Traffic Collision Avoidance System (TCAS) - Honeywell CAS

67A TCAS II• Enhanced Ground Proximity Warning System (EGPWS,

Class A) - Honeywell• Single Radio Altimeter - Honeywell AA-300• Standby Instruments With Dedicated Air Data Computer,

Magnetometer, and Battery Including:• Electronic Standby Instrument System (ESIS) - L-3

Communications GH-3000 (referred to as Standby Flight Display - SFD)

• Electronic Horizontal Situation Indicator (EHSI) - L-3Communications EHSI-3000

• Electronic Standby Engine Indicators (SEI) - Ametek• Aircraft Diagnostics Maintenance System• Fault Recording and Ground Maintenance Access and

Downloading• Cockpit Voice Recorder (CVR) - L-3 Communications FA-

2100• Three Frequency Emergency Locator Transmitter (ELT) -

SERPE-EISM Kannad 406 AF

10.2 Flight Compartment

Two crew stations are provided with dual controls includ-ing control columns with stick shakers, adjustable rudderpedals, and brakes. A handwheel for the nose wheelsteering is provided on the pilot's side ledge.

Rheostats control all cockpit lighting systems. Panellights and electroluminescent (EL) lights provide illumi-nation and blue-white background lighting for all cockpitinstruments and switches. Floodlights and individuallycontrolled left and right map lights are located in theoverhead panel. Indirect supplemental LED lightingunder the glareshield also functions as the emergencylighting for the panel. A day/night switch allowsbright/dim control of the panel, EL, and flood lighting.Monorail sunvisors are standard. One AC outlet is pro-vided in the cockpit for crew use. Circuit breakers for theavionics and most systems are located on the cockpitsidewalls beside each pilot seat.

The emergency oxygen system provides two quick-don-ning, pressure demand masks with microphones foreach crewmember.

The crew seats are fully adjustable including thigh andlumbar support and include a five-point restraint systemwith two inertia reel shoulder harnesses each.Sheepskin cover assemblies and dual stowable arm-rests are standard. A total of eight air outlets are strate-gically placed for air circulation in the cockpit. Dualcupholders are installed in each side ledge, and mapand pencil storage pockets reside just below each sideconsole. For navigation chart storage, dual chart casesare provided behind each crew seat. Additional chartstorage is available in the closet behind the pilot's seat.

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10.3 Avionics

The Honeywell Primus EPIC system is a highly integrat-ed display, flight guidance, navigation, and communica-tion system with its primary data presented on four 8 x10 inch (.20 x .25 m) full color flat-panel liquid crystal dis-plays units (DUs). The two outboard displays are pri-mary flight displays (PFD) and the two inboard functionas a multi-function display (MFD) and an engine indicat-ing and crew alerting system (EICAS).

The backbone of the system is a series of four modularavionics units (MAUs). Each unit is host to various fieldreplaceable circuit cards or modules that perform specificfunctions. Each MAU is powered by a different electricalbus and cooled individually. Two MAUs reside in the noseand two in the tailcone. All systems are networked throughinternal and external high-speed bi-directional buses.Nearly all aircraft systems are integrated through the MAUsfor processing, coordinating, monitoring, and display.

Some of the major subsystems include:

• Four Electronic Flight Information System (EFIS)Display Units (PFDs, MFD, EICAS);

• Dual Modular Radio Cabinets (MRC) ContainingCommunication, Navigation, and Surveillance Radios;

• Dual Channel Automatic Flight Control System(AFCS);

• Situational Awareness Sensors, i.e. Weather, Traffic,and Terrain

A. Electronic Flight Information System (EFIS)

The EFIS system on the Citation Sovereign presents tothe pilots all the essential information required for flight.Navigation, communication, and the condition of the air-craft are all monitored and displayed on the four displayunits. The DUs have integral symbol generators andcooling fans, and are interchangeable. Each are directlyinterfaced to the MAUs.

Two attitude heading reference system (AHRS) comput-ers are installed to supply attitude, heading, and flightdynamics information to the flight control and displaysystem. Solid-state sensors and a magnetic flux gateprovide highly accurate and reliable data.

A total of three heated pitot sources and six heated stat-ic sources feed data to the two main air data modules(ADM) and a backup air data computer (ADC). All three

computers are integrated into the pitot-static system tocalculate and correct raw static and dynamic air pres-sures from the ram and static sources. Cross plumbingminimizes yaw errors in the static pressure signals.

Dual reversionary controllers are provided to allow dim-ming and to meet the manual reversion needs of theDUs, AHRS, and ADMs.

Primary Flight Displays (PFD)

The Sovereign's PFDs present to the pilots the funda-mental flight information for location and attitude inspace. Additional information provides improved situa-tional awareness and safety. The primary sources ofinput for display on the PFDs are the AHRS, ADMs, andthe various navigation and situation receivers, all ofwhich are processed through the MAUs.

The attitude sphere is shown in the upper half withrespect to an aircraft symbol, and incorporates a singlecue or cross pointer flight director command bar presen-tation. To the left of the attitude is the airspeed tape anddigits with the ability to show V-speeds, flap speeds,Mach speed, and overspeed and stall speed warnings.An angle of attack indicator (AOA) may be shown fulltime or only when the flaps and gear are down. Withinspecific parameters a windshear warning will flash nearthe center of the attitude display. The marker beacon,glideslope, and slip-skid indicators are each shown inthis area. Although traffic is shown on the multi-functiondisplay, a resolution advisory (RA) will generate "avoid-ance" and "fly-to" target symbology on the PFD in lieu ofthe flight director command bars.

To the right are altimeter and vertical speed indications.The altimeter setting may be shown in inches or hec-topascals and the altitude may be shown in meters inaddition to feet if desired. A vertical navigation (VNAV)target and bug will appear when activated beside thealtitude tape. A low altitude awareness feature triggeredby the radio altimeter will cause the lower portion of thetape to be shaded brown when radio altitude is less than550 feet. Other terrain avoidance warnings appear astriggered by the EGPWS such as "below glideslope."Both the altitude and airspeed tapes feature trend vectorthermometers that forecast respective values six sec-onds ahead.

The lower half of the PFD displays heading, navigation,and certain weather data. The heading is displayed as a

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1 0 . F L I G H T C O M PA R T M E N T, A V I O N I C S A N D I N S T R U M E N TAT I O N( C o n t i n u e d )full compass rose or a partial compass arc. Traditionalbearing pointers and course indicators are shown on thecompass rose format. For greater situational awareness,the FMS map and weather displays may be overlaid ona 90 degree arc format. The active lateral navigationinformation is displayed on and beside the rose, arc ormap and includes bearings, identifiers, time and dis-tance to waypoint or DME station, and groundspeed.The current wind speed and vector are shown as well asweather radar status. A digital clock and elapse timer areshown on the left and controlled through the PFD displaycontroller and the multi-function control display unit(MCDU). Autopilot/flight director and FMS annunciationsand modes are also displayed on the PFD.

Left and right PFD display controllers provide the princi-ple pilot interface with the respective PFD. Several but-tons allow selection of navigation sources for the differ-ent course deviation indicators and the format for thenavigation display: full compass or arc mode. TheWX/TERR button permits weather radar video or terrainvideo to be superimposed on the arc mode. The ET but-ton operates the elapse timer. Two knobs (each dualconcentric) are used to select approach minimums andaltimeter settings.

Multi-Function Display (MFD)

The MFD shows navigation, communication, traffic, terrain,and weather information for each flight. Various coloredlines and symbols show airports, navaids, waypoints, andtrack lines to provide either a north-up, or heading-up pic-ture of the lateral navigational situation at multiple scales.Vertical navigation may also be selected for display.

Four menu categories reside at the top of the MFD:CHECKLIST, TCAS, MAP, and PLAN. Selection and con-trol of menu items is accomplished through two cursorcontrol devises (CCD) in the pedestal. Selection of 'MAP'view shows the flight plan in a 120° arc with the headingup and a centrally-fixed aircraft symbol. Selection of the'PLAN' view shows true north up and the aircraft symbolin motion as oriented by its heading. Weather radargraphics or terrain information from the EGPWS (exclu-sive of each other) may be selected through the MAPmenu. Selection of 'CHECKLIST' opens several optionsat the bottom center of the display including normal,abnormal, and emergency checklists. 'TCAS' will showthe traffic options and may be displayed on both the MAPand PLAN views.

A portion of the lower half of the display contains full-timeinformation. The full-time data is always in view andincludes navigation and communication frequencies,transponder setting, temperatures, speeds, a timer, cur-rent waypoint identifier with ETE, and the current modeof the TCAS and weather radar. The central mainte-nance computer is also accessed through the MFD. TheCCD is used to interact with these functions.

Engine Indicating and Crew Alerting System (EICAS)

The Sovereign's EICAS display is divided into four sec-tions: engine instruments, aircraft systems, radio tuning,and crew alerting system annunciations.

The engine instrument area shows engine, oil, and fuelparameters in various combinations of vertical tapes anddigits. In some cases, pilots have the option to show dig-its full time or only in the event of exceedances. Ram airtemperature, FADEC and igniter status, and thrustreverser indications appear in this area also. All displaysare intuitively color coded to represent normal andabnormal conditions.

The aircraft systems section shows status and values forthe electrical and hydraulic systems. All three trim axispositions and the flaps, speed brakes, and spoiler posi-tions are shown in a visually synoptic presentation,including digits for the flaps and horizontal stabilizerangles. The communication, navigation, and transpon-der functions are shown at the bottom of the EICAS dis-play and are controlled via the cursor control devise inthe same way as for the MFD.

Crew alerts are processed by the modular avionics units(MAUs) and displayed in colored text in the lower left sec-tion of the EICAS. Up to 12 messages may be displayedat a time with access to additional messages by scrolling.Explicit rules are employed to govern the color, order,flashing, and scrolling of all messages. Special logic andtiming of messages and the combining of redundantmessages are performed by the MAUs to minimize work-load and distractions, and to provide pilots with the mostrelevant information for the flight regime and condition.

A dual aural warning function (AWF), part of the MAUs,prioritizes any alert conditions between EGPWS, TCAS,and EICAS systems to command pilot attention asrequired. Left and right red Master Warning and amberMaster Caution switchlights are also activated accordingto MAU logic.

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1 0 . F L I G H T C O M PA R T M E N T, A V I O N I C S A N D I N S T R U M E N TAT I O N( C o n t i n u e d )B. Cursor Control Device (CCD)

The Sovereign features two cursor control devices(CCD) mounted aft of the throttle quadrant. The CCDsare the primary means of pilot interface with the EFIS byallowing a cursor to be moved about on the EICAS andMFD to select and change such things as MFD menusand radio frequencies.

Each CCD is ergonomically designed for the hand to restand allow the fingers to manipulate the trackball to movethe cursor on the display units. Each pilot may placetheir own cursor (pilot-blue, copilot-green) on the MFD orthe EICAS by pressing one of the three display selectionkeys immediately ahead of the trackball. The PFDs mayalso be selected (by the respective pilot only) for chang-ing HSI display range, however, the cursor itself will notbe visible. 'Enter' buttons on each side are used to makeselections and are both identical in function. Two con-centric knobs are used to change the digits or range ofthe selected function. A dedicated TCAS button bringsthe TCAS menu into view.

C. Multi-functional Control Display Units (MCDU)

Forward of the throttle quadrant are two MCDUs, pro-viding all FMS functions, a means to change variousavionics settings, and a second radio tuning method.The crew operates the units through use of keys anddual concentric knobs. The two units are synchronizedto coordinate data entry from one to the other. The bot-tom line on the screen is a scratchpad for initial entryuntil the data is selected.

Navigation, Surveillance

The navigation radios incorporate all the common func-tions including VOR, ILS/localizer, glideslope, markerbeacon, ADF, DME, and GPS. Each DME module iscapable of tracking four channels at the same time. TheADF has two selectable bandwidths; a narrow bandmode to reduce noise during navigation and a wide bandmode to improve clarity when listening to voice signals.The two transponders are Mode-S and utilize two anten-nae each for diversity function. The two GPS receivermodules are located in two of the MAUs.

Communication

The VHF communication radios provide 25 or 8.33 kHzspacing. In addition to radio tuning, the radio pages pro-

vide the means for setting 12 NAV and 12 COM fre-quencies into memory. All radios and transponders arephysically located in two modular radio cabinets (MRC)in the tailcone.

Flight Management System (FMS)

The FMS functions are accessed from the Flight Planpage on the MCDU. Plans may be created, stored,accessed and activated as needed. The active flight planwill automatically tune the navigation radios enroute.Precision guidance from the FMSs meets the opera-tional requirements of oceanic/remote, NAT MNPS,RNP10, and RNP5/BRNAV. The navigation databaserequires periodic updates via subscription and may beuploaded to the aircraft via the connectors on the aftpedestal. Cessna provides an interface kit for use with aPurchaser-supplied laptop computer to accomplish theupdates. The Honeywell FMS annual subscription fee isthe responsibility of the Purchaser and may be activatedduring delivery.

Several features are presented on the Avionics Setuppage: elapse and flight timers, EGPWS settings, displaysettings for various EFIS functions such as the flightdirector command bars and the AOA indicator, test func-tions, and V-speeds.

D. Automatic Flight Control System (AFCS)

Automatic flight control is provided in the Sovereign by adual autopilot system (AP) including actuators, one elec-tric servo per axis, a yaw damper (not required for dis-patch), and a guidance panel (GP) in the center-top ofthe instrument panel. The system is designed with dualchannel architecture to provide "fail-operational / fail-passive" capability, meaning, the failure of one channelcauses automatic reversion to the other channel withoutany loss of functionality.

The main pilot interface to the AFCS is through theguidance panel. Pushbutton engagement of the autopi-lot is near the center of the panel, as well as couplingto the desired PFD. When engaged, basic modes aremaintained by the autopilot. Alternatively, the flightdirector (FD) may be activated to show command barson the respective PFD in the selected mode. The APand FD may be coupled to provide automatic flight con-trol. Lateral and vertical modes are selected on the GPbeside the heading and altitude select knobs. Two

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course select knobs are also located on the GP for usein the navigation modes. Two pitch wheels, one in thecenter of the GP and one on the pedestal, allow pilotinput for pitch angle, the airspeed bug, and to selectvertical speed rate. In addition to normal modes ofoperation, the AFCS provides touch control steering(TCS) via switches on each yoke, stall protection, andan emergency descent mode.

E. Digital Audio Amplifiers, Headsets andSpeakers

Dual Honeywell AV-850A digital audio amplifiers providetransmitter selection from microphone inputs and directaudio outputs for all receivers to either the speaker orheadphones at each crew station. Also included are anavigation station identification filter, marker beaconmuting, separate headphone and speaker volume con-trol, automatic receiver audio selection, cabin address,and voice activated interphone.

Two Telex Airman 750 headphones with boom micro-phones are provided. Dual Telex hand microphoneslatch on each control column and two cockpit speakersare mounted overhead. Cockpit speaker mute switchesare located on the far left and right of the tilt panel.Speakers are also provided in the cabin and vanity area.

F. Weather Radar

The Honeywell Primus 880 weather radar is a four-colorweather and turbulence detection sensor consisting ofan integrated receiver/transmitter/12-inch antenna unitwith an independent controller mounted on the pedestal.The system provides 10,000 watts of transmitter power,120 degree scan angle, ±15 degrees tilt, and turbulencedetection to 50 nm. The system also includes severaladditional features: Altitude compensated tilt which auto-matically adjusts the tilt angle with changes in altitude;Target alert notifies the pilots of hazardous targets out-side the selected range; Sector scan narrows the scanrange and increases the scan rate; and ground mappingfor depicting terrain features.

G. Traffic Collision Alert System (TCAS)

The Honeywell CAS 67A TCAS II System monitors trafficsurrounding the aircraft and provides collision avoidanceguidance when necessary. The system monitors inputfrom the transponders, radio altimeter, AHRS, and air datato generate a traffic map display of up to 30 nearby aircraft

on the MFD. Resolution advisories generate audible alertsand a corresponding pitch command on the PFDs. Thesystem includes Software Change 7 required to meetEuropean ACAS II requirements.

H. Terrain Avoidance Warning System (TAWS)

The Honeywell Enhanced Ground Proximity Warningmodule (EGPWS) is a Class A TAWS that helps preventaccidents caused by controlled flight into terrain (CFIT)or severe windshear. The system provides basic groundproximity warning, windshear detection and alerting, andterrain awareness alerting and warning. The system dis-plays proximate terrain information in color on the MFDand gives both audible and visual warnings. The terraindatabase includes all charted manmade obstacles inNorth America and some obstacles in other parts of theworld. The EGPWS installation on the CitationSovereign will meet and/or exceed 14 CFR Part 91, 14CFR Part 135, and JAR-OPs 1 requirements.

I. Radio Altimeter

The Honeywell AA-300 Radio Altimeter system providesheight above the terrain from 2,500 feet (762 m) totouchdown. This information is integrated with functionsin the EFIS, TCAS II, and EGPWS and is presented onthe PFDs.

J. Backup And Emergency Instruments

Standby instruments are installed in the center of theinstrument panel and are normally powered by the air-craft's main DC power. In the event power is interrupted,the standby battery in the nose compartment providesup to 3 hours additional duration. A panel switch controlsoperation and testing.

Four standby annunciators are located at the top of thecenter panel and are included on the emergency bus:low fuel, stabilizer no takeoff, generator off, and oil pres-sure low.

The secondary flight display (SFD) receives data fromthe standby air data computer and normally shows atti-tude, air data, slip/skid, and menu items. The SFD alsobacks up the EHSI and may show heading and naviga-tion information.

The electronic horizontal situation indicator (EHSI) uses adedicated magnetometer and signals from the navigationradios and FMS to present heading, range, navigation,

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1 0 . F L I G H T C O M PA R T M E N T, A V I O N I C S A N D I N S T R U M E N TAT I O N( C o n t i n u e d )and course deviation data in an HSI format. A standbyslave switch on the panel may be used to select direc-tional gyro mode when necessary.

Standby engine indications (SEI) include N1%, N2% andITT for each engine and are displayed in digits on thestandby engine indicator at the bottom of the centerpanel. Exceedances cause the respective digits to flash.

The cockpit voice recorder (CVR) has four high qualityand two standard quality channels, loop-recorded for 30minutes and 2 hours respectively from the pilot and copi-lot's audio communications and the area microphone(just above the EICAS) to a crash-survivable solid-stateflash memory unit in the tailcone. The CVR is equippedwith a six year lithium battery and an underwater locatorbeacon. The control head is located on the pedestal.

A three-frequency emergency locator transmitter (ELT)is mounted overhead in the aft baggage compartmentand, if activated, transmits the standard emergency sig-nal on 121.5 and 243 MHz plus aircraft specific encoded

data on the COSPAS-SARSAT satellite frequency of406.025 MHz. The ELT houses its own six-year lithiumbattery pack and meets or exceeds all FAA and JAA cer-tification requirements. The transmitter will activate auto-matically or manually via a remote control panel locatedin the cockpit aft of the copilot’s circuit breaker panel.

K. Other Cockpit Instrumentation

Additional cockpit instrumentation includes the following:

• External lighting switch panel including landing, taxi,recognition, and anti-collision

• Rotary test knob for functional testing of 10 differentsystems

• An event marker button on the left side panel sends afive-minute engine and FADEC trace to the enginediagnostic system for future maintenance downloadand analysis

• A flight time meter

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1. Oxygen Pressure Indicator2. Digital Audio Control Panel3. PFD / MFD Reversion Control4. PFD / MFD Source Control5. Flight Guidance Control Panel6. Primary Flight Display (PFD)7. Multi-Functional Display (MFD) and Engine

Indicating and Crew Alerting System (EICAS)

8. Standby Flight Display (SFD)9. Standby Electronic Horizontal Situation Indicator

(EHSI)10. Standby Engine Indicator (SEI)11. Multi-Function Control Display Unit (MCDU)12. Weather Radar Controller13. Cursor Control Device (CCD)14. Cockpit Voice Recorder (CVR)

FIGURE III — CITATION SOVEREIGN INSTRUMENT PANEL AND PEDESTAL LAYOUT

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1 1 . I N T E R I O R11.1 Cabin

The Citation Sovereign is sized to offer passenger com-fort and flexibility for a variety of interior arrangements. Afull range of fabrics, leathers, carpets, laminates, select-ed wood veneers and metal finishes are available to cus-tom configure the interior furnishings to meet a wide vari-ety of customer tastes. Certified burn-resistant materialsare used throughout the cockpit and cabin. Baggedsoundproofing and insulation are consistent with this cat-egory of aircraft, its operating speeds, and environment.

The flight compartment (discussed in section 10.2) is sep-arated from the cabin by dividers. The cabin is approxi-mately 25 feet 3 inches (7.70 m) long and extends fromthe flight compartment dividers to the aft pressure bulk-head. The constant section of the cabin provides a con-tinuous width of 66 inches (1.68 m) measured softgoodsto softgoods. A dropped aisle with indirect lighting extendsaft from the cockpit divider to the aft wall of the lavatoryand provides a cabin height of 68 inches (1.73 m) meas-ured softgoods to softgoods.

Cabin-length indirect LED lighting is provided overhead inthe Passenger Service Units (PSU) with infinite adjust-ment settings. Entrance and emergency exit lights arealso provided. Fifteen elliptical windows with pleated elec-tric window shades allow generous natural lightingthroughout the cabin and lavatory.

The standard aircraft features a right hand refreshmentcenter (31 inches wide) with two hot beverage tanks, largeice drawer, large trash receptacle, numerous storageareas, glassware capability and provisions for amplecatering. A left hand coat closet forward of the cabin entrydoor accommodates navigation charts, flight manuals, andcoat and briefcase storage as well as a fire extinguisher.

The cabin supports a variety of seating configurations.The standard arrangement accommodates nine passen-gers in a double-club with a single forward side facingseat just aft of the refreshment center. The eight pedestalseats track forward and aft 7 inches (.18 m) and laterally4 inches (.10 m) on the seat base with 360 degree swivel-ing capability. These seats recline to an infinite number ofpositions including full berthing. All passenger seats areequipped with seat belts, an inertia reel shoulder harness,and an overwater life vest stored in the seat base shroud.

ENTRANCE-

-

EMERGENCY

EXIT

FIGURE IV — CITATION SOVEREIGN STANDARD FLOORPLAN

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1 1 . I N T E R I O R ( C o n t i n u e d )Individual air outlets and reading lights are provided inthe PSU above each passenger seat and over the vani-ty. The customer may designate a VIP seat to incorporateall indirect lighting and cabin temperature controls. Twocupholders are built into the side ledge next to each seat.Four executive tables fold out from between each facingpair of seats and are illuminated by direct reading lights.Six individual 110 VAC outlets (four in the cabin, oneeach in the cockpit and lavatory) are installed to operatelaptop computers, etc. Dropout, constant-flow oxygenmasks are installed over the aisle for emergency use.

The aft lavatory has an externally serviceable flushing toi-let (non-belted) and is separated from the cabin by slidingdivider doors. It includes a vanity sink with temperaturecontrolled water and numerous storage compartments.Within the lavatory a large centerline closet accommo-dates several hanging clothes bags, coats, briefcases andadditional storage for passenger amenities.

11.2 Baggage Compartment

The Sovereign has forward and aft baggage storageclosets in the cabin to accommodate passengers' carry-on luggage and coats. The following limits apply:• Forward coat closet - 140 lbs (63.5 kg), 8 ft3 (0.23 m3)• Aft bulkhead closet - 275 lbs (124.7 kg), 27 ft3 (0.76 m3)• Combined total - 415 lbs (188.2 kg), 35 ft3 (0.99 m3)

In addition, a heated baggage compartment with a coatrod is located in the tailcone subject to the following limits:• 1,000 lbs (453 kg), 100 ft3 (2.83 m3) total• Floor loading limit - 150 lbs (68.0 kg) per ft2• Coat rod - 50 lbs (22.7 kg), part of the total limit

The compartment is located on the left hand side and isaccessible through a lockable door with an integral step.A toggle switch is recessed into the door frame to controlthe baggage compartment lights. If inadvertently left on,the lights will turn off automatically when the door closes.

1 2 . E X T E R I O RDistinctive exterior styling featuring polyurethane paint in a variety of colors is provided.

1 5 . D O C U M E N TAT I O N A N D T E C H N I C A L P U B L I C AT I O N S

1 3 . A D D I T I O N A L E Q U I P M E N T

• FMS Interface Kit• Pitot Covers• Static Discharge Wick Covers• Engine Inlet and Exhaust Covers• Thrust Reverser Stow Locks• Emergency Door Ground-Locking Pin

• Center Aisle Carpet Assembly• Interior Cleaning Kit• Six Umbrellas• Cargo Net• Jack Pad Adapters • Main Landing Gear Jacking Adapters

1 4 . E M E R G E N C Y E Q U I P M E N T• Fire Extinguisher in Cockpit and Cabin• Individual Overwater Life Vests• Crew and Passenger Oxygen• Emergency Exit Lights

• Emergency Lighting Battery Packs• First Aid Kit• Flashlight (2-D cell)• Water Barrier

• U.S. Standard Airworthiness Certificate FAA8100-2,Export Certificate of Airworthiness FAA8130-4,or Special Airworthiness Certificate FAA8130-7as appropriate

• Weight and Balance Data Sheets• Flight Manual• Equipment List• Weight and Balance Report• Pilot's Operating Manual• Abbreviated Procedures Checklist• Interior Components Operations Manual

• Log Books (Aircraft and Engines)• Avionics Wiring Booklet *• Maintenance Manual (Airframe) *• Illustrated Parts Catalog (Airframe) *• Wiring Diagram Manual (Airframe) *• Weight and Balance Manual *• Interior Maintenance Manual *• Component Maintenance Manual *• Structural Repair Manual *• Nondestructive Testing Manual *• Illustrated Tool and Equipment Manual *

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1 6 . C O M P U T E R I Z E D M A I N T E N A N C E R E C O R D S E R V I C E ( C E S C O M )

Cessna will provide an online computerized mainte-nance record service for one full year from the date ofdelivery of a Citation Sovereign to the Purchaser.

This service will provide management and operationspersonnel with the reports necessary for the efficientcontrol of maintenance activities. The service providesan accurate and simple method of keeping up with air-craft components, inspections, service bulletins and air-worthiness directives while providing permanent aircraftrecords of maintenance performed.

Reports, available on demand, show the current status,upcoming scheduled maintenance activity and the history

of the aircraft maintenance activity in an online formatwhich is printable locally. Semi-annual reports concerningprojected annual maintenance requirements, componentremoval history and fleet-wide component reliability areprovided as part of the service.

Services are provided though a secure internet siterequiring a computer with internet connectivity. A localprinter is required to print paper versions of the onlinereports and documentation. If receiving these servicesthrough the internet is not feasible for an operation, apaper based service delivered through the U.S. mail isavailable at an additional fee.

The standard Citation Sovereign Aircraft (Aircraft)Limited Warranty covers the aircraft, other than Pratt &Whitney Canada (P&WC), engines and associatedengine accessories and the Honeywell auxiliary powerunit (APU) and the associated APU accessories whichare warranted separately and directly by P&WC andHoneywell, respectively, is set forth below. Cessnaspecifically excludes vendor subscription services andthe availability of vendor service providers for Optionaland Special Equipment Request (SER) equipment fromCessna’s Limited Aircraft Warranty. Following Cessna’sLimited Warranty, the P&WC engine and engine acces-sory warranty is set forth as well as an outline of theHoneywell APU and APU accessories warranty. All war-ranties are incorporated by reference and made a part ofthe Purchase Agreement. All warranties are adminis-tered by Cessna.

Cessna Citation Sovereign Limited Warranty(Limited Warranty)

Cessna Aircraft Company (Cessna) expressly warrantseach new Citation Sovereign Aircraft (exclusive ofengines and engine accessories supplied by P&WC orAPU and APU accessories supplied by Honeywell, bothof which are covered by their individual and separatewarranties), including factory-installed avionics andother factory-installed optional equipment to be freefrom defects in material and workmanship under normaluse and service for the following periods after deliveryto the first user: (a) Five years or 5,000 operating hours,whichever occurs first, for Aircraft component partsmanufactured by Cessna; (b) Five years or 5,000 oper-ating hours, whichever occurs first for standardHoneywell aircraft avionics; (c) Two years for all otherstandard aircraft avionics; and (d) One year for optional

1 7 . L I M I T E D W A R R A N T I E S

* These publications are provided on CD-ROM.** These publications / revisions are provided directly from Pratt & Whitney, Canada.*** These publications / revisions are provided directly from Honeywell.

1 5 . D O C U M E N TAT I O N A N D T E C H N I C A L P U B L I C AT I O N S( C o n t i n u e d )• Maintenance Manual (Engine) **• Illustrated Parts Catalog (Engine) **• Service Bulletins and Service Letters (Engine) **• Maintenance Manual (APU) ***• Illustrated Parts Catalog (APU) ***• Service Bulletins and Service Letters (APU) ***• Additional Miscellaneous Information Concerning

Engine and Airframe Support

• Passenger Information Cards• Parts Warranty Listing

Cessna will provide Service Bulletins, Service Lettersand manual revisions for documents published byCessna for five years beginning from the start date ofairframe warranty.

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avionics, Special Equipment Requests (SERs), interiorfurnishings and exterior paint and all vendor itemsincluding engine or APU accessories supplied byCessna unless otherwise stated in the OptionalEquipment Selection Guide. Any remaining term of thisLimited Warranty is transferable to subsequent pur-chasers.

Cessna's obligation under this Limited Warranty is limit-ed to repairing or replacing, at its sole option, any part orparts which within the applicable warranty period arereturned at the owner's expense to the facility where thereplacement part was purchased with completed claiminformation and which are found defective by Cessna.(Replacement parts must be procured through CitationParts Distribution or any Cessna-authorized CitationService Facility and are only warranted for the remainderof the applicable original aircraft warranty period. A newwarranty period is not established for replacementparts.) The repair or replacement of defective partsunder this Limited Warranty will be made by or throughany Cessna or Cessna-authorized Citation ServiceFacility without charge for parts or labor for removal,installation, and/or actual repair. All import duties, cus-toms brokerage charges, sales taxes and use taxes, ifany, on such warranty repairs or replacement parts arethe warranty recipient's sole responsibility. (Location ofCessna and Cessna-authorized Citation ServiceFacilities will be furnished by Cessna upon request.)

This Limited Warranty applies to only items detailed here-in which have been used, maintained, and operated inaccordance with Cessna and other applicable manuals,bulletins, and other written instructions. However, thisLimited Warranty does not apply to items that have beensubjected to misuse, abuse, negligence, or accident; toitems that have been installed, repaired, or altered byrepair facilities not authorized by Cessna; or to items that,in the sole judgment of Cessna, have been installed,repaired, or altered by other than Cessna-owned servicefacilities contrary to applicable manuals, bulletins, and/orother written instructions provided by Cessna so that theperformance, stability, or reliability of such items areadversely affected. Limited Warranty does not apply tonormal maintenance services (such as engine adjust-ments, cleaning, control rigging, brake and other mechan-ical adjustments, and maintenance inspections); or to thereplacement of service items (such as brake linings,

lights, filters, de-ice boots, hoses, belts, tires, and rubber-like items); or to normal deterioration of appurtenances(such as paint, cabinetry, and upholstery) or structuralcomponents due to wear and exposure.

WITH THE EXCEPTION OF THE WARRANTY OFTITLE AND TO THE EXTENT ALLOWED BY APPLICA-BLE LAW, THIS LIMITED WARRANTY IS EXPRESSLYIN LIEU OF ANY OTHER WARRANTIES, EXPRESSEDOR IMPLIED, IN FACT OR BY LAW, APPLICABLE TOTHE AIRCRAFT. CESSNA SPECIFICALLY DISCLAIMSAND EXCLUDES ALL OTHER WARRANTIES, INCLUD-ING, BUT NOT LIMITED TO, ANY IMPLIED WARRANTYOF MERCHANTABILITY OR FITNESS FOR A PARTIC-ULAR PURPOSE. THE AFOREMENTIONED REME-DIES OF REPAIR OR REPLACEMENT ARE THE ONLYREMEDIES UNDER THIS LIMITED WARRANTY.CESSNA EXPRESSLY AND SPECIFICALLY DIS-CLAIMS ALL OTHER REMEDIES, OBLIGATIONS, ANDLIABILITIES, INCLUDING, BUT NOT LIMITED TO,LOSS OF AIRCRAFT USE, LOSS OF TIME, INCONVE-NIENCE, COMMERCIAL LOSS, LOSS OF PROFITS,LOSS OF GOODWILL, AND ANY AND ALL OTHERCONSEQUENTIAL AND INCIDENTAL DAMAGES.CESSNA NEITHER ASSUMES NOR AUTHORIZESANYONE ELSE TO ASSUME ON ITS BEHALF ANYFURTHER OBLIGATIONS OR LIABILITIES PERTAIN-ING TO THE AIRCRAFT NOT CONTAINED IN THISLIMITED WARRANTY.

New Engine Warranty

The following is an outline of the Pratt & WhitneyCanada (P&WC), warranty for new PW306C engines.

P&WC warrants that at the time of delivery all parts of anew engine comply with the relevant specification andare free from defects in material and/or manufacturingworkmanship.

This warranty shall take effect immediately upon deliv-ery of the engine to the original operator, either installedin an aircraft or delivered as a spare, and shall remainin force until the expiration of 3,000 engine operatinghours (EOH) or Five (5) years, whichever occurs first.Notice of warranty defect must be provided to P&WCwithin 30 days of the occurrence, and P&WC reservesthe right to refuse any warranty claim received morethan 180 days after the removal from operation of anyengine or engine part.

1 7 . L I M I T E D W A R R A N T I E S ( C o n t i n u e d )

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1 7 . L I M I T E D W A R R A N T I E S ( C o n t i n u e d )

Application

This warranty is applicable only to engines operated onnon-military aircraft used for commercial, corporate, orprivate transportation service.

Coverage

P&WC will repair or replace any parts found to be defec-tive due to a defect in material and/or manufacturingworkmanship (including resultant damage to theengine) within 3,000 EOH or 5 years, whichever occursfirst. P&WC will pay reasonable engine removal andreinstallation costs and reasonable transportation costs(excluding insurance, duties, customs brokeragecharges and taxes) to and from a facility designated byP&WC, Warranty Administration.

Extended Coverage

After expiration of new engine warranty, P&WC will pro-vide commercial support to assist an operator in theevent of extensive damage to an engine resulting froma chargeable defect. This maximum event cost will bebased on total engine hours and cycles run since new,or since last overhaul, adjusted for engine age, as wellas environmental and operating conditions. P&WCreserves the right to cancel or change this extendedcoverage at any time.

Operator’s Responsibility

The operator is responsible for operating and maintain-ing the engine in accordance with P&WC’s writteninstructions. Any warranty work performed on theengines must be carried out at a facility designated byP&WC, Warranty Administration. P&WC shall not beresponsible for defects or damages resulting fromimproper use, improper maintenance, normal wear,accident or foreign object damage (FOD).

Limitations

Other terms and conditions apply to the warranty andextended engine service policy outlined above. A com-plete copy of the warranty for new engines and extend-ed engine service policy will be available from P&WC,Warranty Administration. In no event shall P&WC beresponsible for incidental or consequential damages.

For complete information on how this warranty mayapply and for more complete warranty details, pleasewrite to:

Manager, Warranty Administration (01RD4)Pratt & Whitney Canada1000 Marie VictorinLongueuil, QC J4G 1A1Canada

Summary of Honeywell APU Warranty

The following is an outline of the Honeywell warranty forthe new RE100[CS] APU.

Each RE100[CS] APU sold for installation as originalequipment on new aircraft will, at the time of delivery tothe aircraft operator, be free from defects in materialand workmanship and shall conform to the applicablespecifications. Warranty shall expire after five (5) yearsor 2,500 APU operating hours, whichever occurs first.

The above APU warranty is provided as a generaldescription only. Specific terms and conditions are avail-able through Honeywell (Garrett Division) or Cessna.

For complete information on how this warranty mayapply and for more complete warranty details, pleasewrite to:

Honeywell EnginesPost Office Box 29003Phoenix, Arizona 85038-9003

1 8 . C I TAT I O N S O V E R E I G N C R E W T R A I N I N G A G R E E M E N T

Training for one (1) Citation Sovereign crew will be fur-nished to First Retail Purchaser (hereinafter called the“Purchaser”), subject to the following:

1. A crew shall consist of up to two (2) licensed pilotswith current private or commercial instrument and

multi-engine ratings and a minimum of 1,500 hourstotal airplane pilot time and up to two (2) mechanicswith A&P licenses or equivalent experience.

2. Training shall be conducted by Cessna or by itsdesignated training organization.

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1 8 . C I TAT I O N S O V E R E I G N C R E W T R A I N I N G ( C o n t i n u e d )a. A simulator shall be utilized which is FAA certi-

fied to provide training for the CE-680 FAA typerating.

b. In lieu of a model specific simulator, training willbe provided in the most appropriate type simula-tor available capable of accomplishing the FAAtype rating, with differences training provided.

c. Additional training as requested by the customer,shall be conducted in the customer’s aircraft.

d. Location of training to be Wichita, Kansas,unless mutually agreed otherwise. The organi-zation conducting the training is hereinaftercalled the “Trainer.”

3. Training furnished shall consist of the following:

a. Flight training to flight proficiency in accordancewith Trainer's standards aimed toward type cer-tification of two (2) Captains under applicableFederal Air Regulations not to exceed five (5)total hours for the two (2) pilots.

b. Flight simulation training to simulator proficiencyin accordance with Trainer's standards but not toexceed fifty (50) total hours for both pilots.

c. Ground School training for each pilot and class-room instruction for each mechanic in accor-dance with Trainer's standards.

4. Purchaser shall be responsible for:

a. Transportation of crew to and from training siteand for living expenses during training.

b. Providing an interpreter during the course oftraining for any of Purchaser's crew not conver-sant with the English language.

c. Payment to Trainer for additional simulator orflight training beyond that required to attain pro-ficiency in accordance with Trainer's standardsfor the course in which the pilot is enrolled.

d. All aircraft required for flight training as well as alllanding fees, fuel costs, aircraft maintenance andinsurance and all other direct costs of operation,

including applicable taxes required in connectionwith the operation of said aircraft during suchflight training.

e. Extra charges, if any, for scheduling pilots inseparate training classes.

f. Reimbursing to Cessna the retail rate for trainingin the event of training before actual sale/deliv-ery, if sale/delivery is cancelled.

5. Seller or Trainer shall schedule all training, furnishPurchaser schedules of training and endeavor toschedule training at a convenient time for Purchaser.A cancellation fee of Two Hundred Dollars ($200)will be paid by Purchaser if crew fails to appear forscheduled training, except for reasons beyond itsreasonable control, unless Purchaser gives Sellerwritten notice of cancellation received at Wichita,Kansas, at least seven (7) days prior to scheduledtraining. In the event of such cancellation Seller shallreschedule training for the next available class.

6. Neither Seller nor Trainer shall be responsible forthe competency of Purchaser's crew during andafter training. Trainer will make the same efforts toqualify Purchaser's crew as it makes in training ofother Citation Sovereign crews; however, Seller andTrainer cannot guarantee Purchaser's crew shallqualify for any license, certificate or rating.

7. Neither Seller nor Trainer shall be responsible forany delay in providing training due to causes beyondits or their reasonable control.

8. All Training furnished to Purchaser under theAgreement will be scheduled to commence no earlierthan three (3) months prior to delivery and will becompleted within twelve (12) months after delivery ofthe Aircraft unless mutually agreed otherwise.

Signature of the Purchaser to the Purchase Agreementto which this Training Agreement is attached as a part ofthe Specification and Description shall constitute accept-ance by Purchaser of the foregoing terms and conditionsrelative to training to be furnished by Seller. Purchaseragrees that Seller can provide Purchaser’s name andaddress to the training organization for the purpose ofcoordinating training.

Citation Marketing Cessna Aircraft Company, P.O. Box 7706, Wichita, Kansas 67277-7706, Telefax 316-517-6640