Cessna Caravan Amphibian Specificatios & Description

7/25/2019 Cessna Caravan Amphibian Specificatios & Description

1/25

Specification &

DescriptionFebruary 2013, Revision B

Units 208-0546 and on


2/25

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

E F F E C T I V E S E R I A L N U M B E R 2 0 8 - 0 5 4 6 A N D O N

F E B R U A R Y 2 0 1 3

R E V I S I O N B

Caravan Marketing

Cessna Aircraft Company

P.O. Box 7704

Wichita, Kansas 67277-7704

Telephone (316) 517-6081

Fax (316) 517-7250

Copyright 2013 Cessna Aircraft Company


3/25

February 2013, Revision B

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

This Specification and Description is published for thepurpose of providing general information for the evalu-ation of the design, performance and equipment of theCessna Caravan aircraft. Should more detailed data berequired, it can be obtained by contacting:

Cessna Aircraft CompanyP.O. Box 7704Wichita, Kansas 67277Telephone: 316-517-6081Fax: 316-517-7850

This document describes only the Cessna Model 208Caravan aircraft, Unit Serial Number 546 and on, and itspowerplant and equipment.

Also included is the Cessna warranty applicable to theCessna Model 208 Caravan aircraft and the CaravanCrew Training Agreement. In the event of any conflict ordiscrepancy between this document and the basic pur-chase agreement to which it may be appended, termsspecified in the basic purchase agreement govern.

Due to the time span between the date of this Specifi-cation and Description and the scheduled delivery dateof the aircraft, Cessna reserves the right to revise theSpecification and Description whenever occasioned.

WARNING: This product contains Halon 1211 and Halon 1301. Furthermore, the product is manufactured with 1-1-1Trichloroethane, substances which harm public health and environment by destroying ozone in the upper atmo-sphere.


4/25


2

Cessna Caravan Specification and Description

Section

Pag

1. General Description ..........................................................................................................................2. Performance .....................................................................................................................................3. Structural Design Criteria .................................................................................................................4. Fuselage Group ................................................................................................................................5. Wing Group ......................................................................................................................................6. Empennage Group ...........................................................................................................................7. Landing Gear ....................................................................................................................................8. Propulsion

8.1 Powerplant .................................................................................................................................8.2 Propeller .....................................................................................................................................

9. Systems

9.1 Flight Controls .....................................................................................................................9.2 Fuel System .........................................................................................................................9.3 Electrical System .................................................................................................................9.4 Lighting System ...................................................................................................................9.5 Environmental System..........................................................................................................9.6 Pitot-Static System ..............................................................................................................9.7 Vacuum System ................................................................................................................

9.8 Garmin G1000 Avionics System ..........................................................................................10. Corrosion Proofing ............................................................................................................................

11. Floatplane ..................................................................................................................................... 12. Standard Caravan Equipment

12.1 Avionics ...............................................................................................................................12.2 Engine Instruments .............................................................................................................12.3 Flight Instruments ................................................................................................................12.4 Flight Controls .....................................................................................................................12.5 Environmental ......................................................................................................................12.6 Electrical Power ..............................................................................................................12.7 Exterior Lights ......................................................................................................................12.8 Interior Lights .......................................................................................................................

12.9 Powerplant ........................................................................................................................... 12.10 Fuel System.......................................................................................................................... 12.11 Interior ............................................................................................................................ 12.12 Exterior ................................................................................................................................ 13. Documentation and Technical Publications .................................................................................

14. Maintenance Programs .................................................................................................................

15. Limited Warranties15.1 Cessnas Limited Warranty .............................................................................................15.2 Pratt & Whitney Canada Inc. ...............................................................................................15.3 Honeywell/Bendix/King Warranty ....................................................................................

15.4 McCauley Limited Warranty ........................................................................................... 16. Caravan Crew Training Agreement ..................................................................................................FIGURE I CARAVAN EXTERIOR DIMENSIONS ..................................................................................................FIGURE II CARAVAN CABIN, DOOR, AND WINDOW DIMENSIONS .................................................................

FIGURE III CARAVAN FLIGHT DECK ..................................................................................................................

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

3-467

7-8888

8-99

99

10101010

10-111111

11-12

13

13131313

13-1414141414

14-1515

15-1616-17

18-2119

20-2120-21

2156

12


5/25


The Cessna Caravan is an unpressurized single-enginehigh wing turboprop aircraft with fixed landing gear. Theaircraft can accommodate up to fourteen persons includ-ing a minimum crew of one. (Operations with more thannine passengers must be approved by the registeringcountrys aviation authority.) Suitable allowance for lug-gage and optional equipment is also provided.

The powerplant is a Pratt and Whitney of Canada PT6A-114A turboprop engine mounted in the nose of the air-craft fuselage.

Certification basis is to U.S. FAA FAR Part 23 Require-mentsday, night, VFR and IFR when equipped with theappropriate options. Export certification requirementsmay require additional equipment and charges.

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

M O D E L 2 0 81 . G E N E R A L D E S C R I P T I O N

POWERPLANT.............................................................................. Pratt & Whitney PT6A-114A 675 shp @ 1900 rpm

PROPELLER........ McCauley, Anti - Ice ,Constant Speed, Full Feathering, Reversible Pitch, 3 Blades, 106 in. Diameter

LOADING

Wing ..........................................................................................................................................................Power ........................................................................................................................................................

APPROXIMATE DIMENSIONS

Overall Height ..........................................................................................................................................Overall Length .........................................................................................................................................Wing

Span (overall) ...............................................................................................................................

Area ..............................................................................................................................................Sweepback (at 50% chord) .......................................................................................................... Dihedral ........................................................................................................................................ Taper Ratio ................................................................................................................................... Aspect Ratio ................................................................................................................................. Mean Aerodynamic Chord.............................................................................................................Horizontal Tail

Span (overall) ...............................................................................................................................Area ..............................................................................................................................................Sweepback .....................................................................................................................

Dihedral ....................................................................................................................................... Aspect Ratio ................................................................................................................................. Mean Aerodynamic Chord ............................................................................................................

Vertical Tail Height (overall) .............................................................................................................................

Area (including dorsal din) ............................................................................................................Sweepback ................................................................................................................

Cabin Interior

Height (floorboard to headliner).....................................................................................................Length - Firewall to Aft Bulkhead (nominal) ..................................................................................Width (max.) .................................................................................................................................

Landing Gear

Tread .............................................................................................................................................Wheelbase ....................................................................................................................................

Tire Size - Main ............................................................................................................................ Tire Size - Nose ......................................................................................................................

28.6 lb/ft2

11.85 lb/shp

14 ft 10 in37 ft 7 in

52 ft 1 in

279.40 ft2

0 degrees+3 degrees

0.5869.555

66.474 in

20 ft 6 in70.04 ft2

0 at elevator hinge line0 degrees

6.0

41.984 in

8 ft 2 in39.92 ft2

+9.437 at rudder hinge line

4 ft 3 in17 ft 4 in5 ft 2 in

11.66 ft11.62 ft

8.50 x 10, 8 ply22 x 8.00 x 8, 6 ply


6/25


4

52 ft 1 in

11 ft 8 in

37 ft 7 in

14 ft-1MA

FIGURE I CARAVAN EXTERIOR DIMENSIONS

NOTES:

1. Dimensions shown are based on

standard empty weight and proper

inflation of nose and main gear

tires.

2. Wing span dimension includes

strobe lights.

3. Maximum height shown with

nose gear depressed as far as

possible.

4. Wheel base length is 11-71/2.

5. Wing area is 279.4 square feet.

6. Minimum turning radius (* pivot

point to outboard wing tip strobe

light ) is 33 - 8 .

7. McCauley propeller

ground clearance with

standard tires and

extended nose gear fork:

Nose tire inflated and

nose gear barrel extended

41/2 :19.

Nose tire deflated and nose strut

fully compressed: 12.

106 in (McCauley)

PIVOT POINT PIVOT POINT

20 ft 6 in


7/25


FIGURE II CARAVAN DOORS AND WINDOWS DIMENSIONS

49 in

14 in

35in

*54 in**62 in

*591/2in**64 in

*51 in**53 in

17 ft 4 in

*42 in**46 in

13 ft 10 in18 in

54 in51 in 52 in46 in

24 in

*243/8in

317/8 in

355/8in

117/8in

50 in

24 in

413/4in 443/4in

Stations 100 118 234 284 308

CARAVAN CABIN DIMENSIONS

*Dimensions at cabin floor **Dimensions at lower window line

53 in

24 in

50 in

180


8/25


6

1 . G ENERAL D E SCR I P T I ON

2 . P E R FORMANCE

Design Weights and CapacitiesMaximum Ramp Weight ........................................................................................................................

Maximum Takeoff Weight ......................................................................................................................

Maximum Landing Weight .....................................................................................................................

Standard Empty Weight* .......................................................................................................................

Maximum Useful Load ..........................................................................................................................

Fuel Capacity (usable) at 6.7 lb/gal ....................................................................................................

Oil .........................................................................................................................................................

* Approximate standard empty weight includes unusable fuel, full operating fluids and full engine oil.

8035 lb

8000 lb

7800 lb

4239 Est. lb

3796 Est. lb

332 gal/2224 lb

14 qt

All performance data is based on a standard aircraft configuration in International Standard Atmosphere conditions.Takeoff and landing field lengths are based on level, hard surface, dry runways with zero wind. Actual performancewill vary with individual airplanes and other factors such as environmental conditions and aircraft configuration.

Without cargo pod186 kts174 kts

932 nm5.1 h

1220 nm7.13 h

1085 nm7 h

1295 nm8.3 h

1234 fpm

25,000 f

1160 f2055 f

715 f1625 f

75 kts61 kts

Speed (Based on weight 8,000 lbs) ....................................................................................................Max Cruise at 10,000 ft ............................................................................................................................

Max Cruise at 20,000 ft ..........................................................................................................................

Range (with 2224 pounds usable fuel and fuel allowance for engine start, taxi, takeoff, climb, descent and 45 minutes reserve)

Maximum Cruise Power at 10,000 ft ................................................................................................. Endurance ......................................................................................................................................

Maximum Cruise Power at 20,000 ft ................................................................................................. Endurance ...................................................................................................................................... Maximum Range Power at 10,000 ft ................................................................................................. Endurance ...................................................................................................................................... Maximum Range Power at 20,000 ft ................................................................................................. Endurance ......................................................................................................................................

Rate of Climb at Sea Level ............................................................................................................................

Maximum Certified Altitude ............................................................................................................................

Takeoff Performance (sea level, 8000 lb)Ground Roll........................................................................................................................................

Total Distance Over 50 ft Obstacle ....................................................................................................

Landing Performance (sea level, 7800 lb, no reverse) Ground Roll ....................................................................................................................................... Total Distance Over 50 ft. Obstacle ...................................................................................................

Stall Speed, CAS Flaps Up, Idle Power .........................................................................................................................

Flaps Down, Idle Power ...................................................................................................................


9/25


Construction of the fuselage is of conventional formedsheet metal bulkhead, stringer and skin design. Major el-ements of the structure are the front carry-through sparand bulkhead, the rear carry-through spar and landinggear bulkhead, and the forward doorpost. The front carry-through spar and bulkhead is an integral fail-safe struc-ture with forgings at the top for attaching the front wingspar and forgings at the bottom for attaching the wing

strut. The rear carry-through and landing gear bulkheadis an integral fail-safe structure with forgings at the topfor attaching the rear wing spar and forgings at the bot-tom for attaching the main landing gear trunnions. Theforward doorpost provides the load path for transferringthe loads from the engine mount directly to the primarystructure.

The large cabin area provides comfortable space for a pi-lot and up to thirteen passengers. (Operations with morethan nine passengers are limited to countries that issueapproval.) Inside cabin dimensions are 51 high and 62wide at the front and rear spar bulkhead locations. The

cabin narrows slightly toward the tailcone to 52 high and53 wide just aft of the cargo door. Total length of thecabin from the firewall to the aft bulkhead is 17 ft. 4 in.The cabin floor is flat with the exception of two feet in theaft cabin which is five inches above the main floor andmakes up the aft cabin baggage area.

Cabin volume, including the pilot and aft cabin baggagearea is 341.4 cubic feet. Total volume aft of the pilot andfront passenger seat locations is approximately 254 cu-bic feet.

Entry to, and exit from the airplane is accomplished

through an entry door on each side of the cabin at the

pilot and front passenger seat location and through a twopiece airstair-type door on the right side of the airplane

just aft of the wing. A large cargo door is also providedon the left side of the airplane directly across from theairstair door. All doors can be opened with the flaps upor down.

The left crew entry door incorporates a conventional door

handle, key-operated Medco door lock, conventionalinterior door handle and window with a small triangularfoul weather window. The foul weather window may beopened for additional ground ventilation. The right crewentry door incorporates a conventional outside and in-side door handle and a manually operated inside doorlock. A 4 inch deep x 5 1/2 inch Kydex storage area isincorporated into the interior width of both the left andright crew doors. Both doors have a maximum width of35.65 inches and a maximum height of 44.75 inches andwill open 180 degrees forward to latch against the sideof the fuselage.

The passenger entry door consists of an upper and lowersection. When opened, the upper section swings upwardand the lower section drops down providing integral stepsto aid in boarding or exiting the airplane. The door open-ing is approximately 24 inches wide and 50 inches high.

The primary opening is the two-piece cargo door installedon the left side of the airplane aft of the wing trailingedge. The cargo door is divided into an upper and lowersection. When opened, the upper section swings upwardand the lower section opens 180 degrees forward provid-ing a large 49 inch wide by 50 inch high opening in theside of the fuselage which facilitates the loading of bulky

cargo into the cabin. The door opening is flush with the

DESIGN SPEEDS (All speeds are at maximum gross weight.)Cruising Maximum Operating Limit (V

MO) ..................................................................................................

Flap Extension Speeds 0 to 10 ........................................................................................................................................ 10 to 20 .....................................................................................................................................

20 to 30 .....................................................................................................................................Maneuvering Speed (V

A)

8000 pounds .............................................................................................................................. 6300 pounds................................................................................................................................

4600 pounds................................................................................................................................

3 . S T R U C T U R A L D E S I G N C R I T E R I A

The Caravan certification basis is to FAR Part 23 normalcategory aircraft.Design limit load factors are +3.8G, -1.52G at a maxi-

mum takeoff weight of 8,000 pounds. Ultimate loads aredefined as 1.5 times the limit loads.

175 KCAS

175 KCAS150 KCAS125 KCAS

150 KCAS133 KCAS114 KCAS

4 . F U S E L A G E G R O U P


10/25


8

floor and has square corners for maximum cargo loadingcapability.

The airplane is equipped with a two-piece plexiglasswindshield reinforced with a metal center strip. Twelveside windows of the fixed type are installed in the cabin

sides including one each in the two crew entry doors, twowindows in the upper section of the cargo door and onewindow in the upper section of the passenger entry doorThe windshield and forward crew door windows are 5/16inch and 1/4 inch thick respectively. All other windows are3/16 inch thick tinted plexiglass.

4 . F U S E L A G E G R O U P ( C o n t i n u e d )

The Caravan utilizes conventional wings with NACA23000 Series Airfoils. The externally braced, fail-safewings are constructed of front and rear spars withformed sheet metal ribs, doublers and stringers. Theentire structure is covered with aluminum skin.

The primary wing spars, wing carry-through spars inthe fuselage and attaching structure are of fail-safeconstruction for limit flight loads. Fail-safe constructionassures that the structure is designed and built in sucha way that should any single structural component fail,

the remaining structure is capable of carrying certifiedlimit flight loads.

5. W I N G G R O U P

The empennage consists of a conventional vertical sta-bilizer, rudder, horizontal stabilizer and elevator, all ofwhich are constructed of a forward and aft spar withformed sheet metal ribs and aluminum skin panels. Thehorizontal stabilizer contains dual jack screw type actua-

tors for operating the elevator trim tabs. An elevator trimtab is attached to each elevator by full length piano-typehinges. Stabilizer abrasion boots are installed along theleading edge of the horizontal stabilizer.

6. EMPENNAGE GROUP

The landing gear is of the non-retracting, tricycle typewith a steerable nose wheel and two main wheels. Shockabsorption is provided by the tubular spring steel main

landing gear struts with an inter-tube connecting the twoouter tubes. The tires are tube-type; standard nose tire is22 x 8.00 x 8, 6 ply and main gear tires are 8.50 x 10, 8ply. The nose gear tire is mounted on an extended nosegear strut providing additional ground clearance. Thenose gear shock absorption is provided by the oil snub-ber combined with a drag link spring providing vertical

and aft displacement restraint. Each main gear wheel isequipped with a hydraulically actuated four piston brake.

Nose gear steering is accomplished by using the rudderpedals which turns the nose wheel through an arc of ap-proximately 15 each side of center. By applying eitherleft or right brake, the degree of turn may be increasedup to 51.5 each side of center. The minimum turningradius of the airplane, using differential braking and nosewheel steering during taxiing, is 33 feet 8 inches.

7. LANDING GEAR

8.1 Powerplant

The propulsion system consists of a single fuselagemounted Pratt and Whitney PT6A-114A turboprop en-

gine. The PT6A-114A is flat rated to 675 shp at 1900 rpm.Time between overhaul for this engine is 3600 hours.

Conventional turboprop controls are used to operatethe engine and propeller. They consist of a power lever,emergency power lever, propeller control lever and a fuelcondition lever. The power and fuel condition levers areengine controls while the propeller control lever controlspropeller speed. An emergency power lever is providedto manually control fuel supply to the engine should amalfunction occur in the fuel control unit.

Engine operation is monitored by the engine indication

system (EIS) which shows numeric readouts of criticalengine, fuel and electrical indications for the following:torque, propeller speed, interstage temperature (ITT),gas generator % RPM (Ng), fuel flow, oil pressure, and

oil temperature. A wet type standby engine torque gaugeis also installed.

An inertial separator system is built into the engine airinlet duct to prevent moisture particles from entering theengine inlet plenum. The inertial separator system is me-chanically controlled by a push-pull handle located onthe left side of the instrument panel.

Engine ignition is provided by two igniters that are ener-gized by the ignition exciter mounted on the right side ofthe engine compartment. Mounting provisions are pro-vided for a standby ignition exciter unit.

8. PROPULSION


11/25


9 . S Y S T E M S

9.1 Flight Controls

The Caravans flight control system consists of conventionalaileron, elevator and rudder control surfaces. In addition,a pair of slot lip spoilers are mounted above the outboardends of the flaps. The control surfaces are manually oper-ated through mechanical linkage using a control wheel forthe ailerons, spoilers and elevator and rudder/brake pedalsfor the rudder.

The rudder control utilizes a rudder pedal cable systemdriving the rudder. The floor mounted rudder bars are gear

interconnected to maintain cable tension. Conventional de-sign of inner torque tubes serve to allow co-pilot operationof the left-hand mounted brake cylinders. The brake cylin-ders have a remote reservoir mounted on the forward sideof the engine firewall for convenient access.

Rudder trim system consists of a trim wheel driving a flexshaft which, in turn, adjusts rudder pressure.

The elevator control system features a conventional cabledrive system. The elevator is connected to the cables by abellcrank and push-pull rod.

Elevator trim is accomplished through two elevator trim tabs

by utilizing the vertically mounted trim control wheel on thecontrol pedestal. An electric elevator trim system is avail-able with an autopilot installation.

The aileron control system is a combination of cables,quadrants, bellcranks and push-pull rods. A push-pull roddrives the ailerons.

An aileron trim system consists of a pedestal mounted con-trol knob, cables, fail-safe actuator, pushrods and trim tabs.The left aileron incorporates a servo tab while the right aile-ron incorporates a trimmable servo tab.

A pair of slot lip spoilers mounted above the outboard ends

of the flaps are incorporated to improve low speed roll con-trol. The spoilers are interconnected with the aileron systemthrough a pushrod mounted to an arm on the aileron bell-crank. Spoiler travel is proportional to aileron up travel.

The single slotted, semi-fowler flaps are electrically drivenand incorporate a trailing edge angle with leading edge vor-tex generators to reduce stall speed and provide enhancedlateral stability. A selector and mechanical type follow-up in-dicator is provided in the control pedestal. The flap systemconsists of an electrically driven screwjack actuator, a pri-mary and standby motor, and a system of cables, bellcranks

and pushrods connected to the flaps. The standby electricdrive motor provides a back-up flap actuation system in theevent of failure of the primary motor.

9.2 Fuel System

The Caravan fuel system consists of two vented integralfuel tanks (one in each wing formed by the front and rearspars), a fuel reservoir, engine fuel system, quantity and flowinstrumentation, and the necessary lines, controls, valvesand pumps to complete the system. Fuel system capacity is335.6 U.S. gallons (332 gallons usable). Filling the fuel tanksis accomplished through filler caps in each wing.

Normal operation is with both tanks on. The pilot can me-chanically select fuel from either left or right fuel tanks orboth at the same time.

Fuel quantity is measured by four fuel level probes (two ineach wing tank) and indicated on the engine indication sys-tem (EIS). The fuel quantity system is calibrated in gallonsbased on 6.7 pounds per gallon. Fuel quantity indicationsare displayed in pounds. Wing fuel level cautionadvisories,one for each wing tank, are provided through the crew advi-sory system (CAS) The appropriate FUEL LOW (CAS) mes-sage will illuminate when the fuel in the respective tank isapproximately 25 gallons or less. A warning advisory is alsoprovided to indicate low fuel level in the fuel reservoir tank.

An Altair Digital ADAS Engine Trend Monitor is an enginetrend recording device and an engine parameter exceed-ance monitor which will allow operators to monitor thehealth of the engine through periodic sampling of engineparameters. The engine trend monitor contains logic todetermine when the aircraft is in a stable cruise flight re-gime before automatically taking a trend sample.

This is an advisory system only. The airplanes engine in-dication system is still the primary source of detecting andcorrecting conditions where engine limitations are exceed-ed. There are no additional aircraft limitations and no perfor-

mance change with the Altair Engine Trend Monitor installed.

8.2 Propeller

The Caravan is equipped with a 106 inch diameter met-al propeller. The three-blade, anti-ice, constant speed,full feathering, single acting, reversible pitch propelleris manufactured by McCauley, model 3GFR34C703.The propeller is controlled by a propeller governor andan overspeed governor mounted on and driven by thereduction gear-box. The overspeed governor acts asa safeguard against propeller overspeed should theprimary propeller governor fail.

8 . P RO PU LS IO N ( C o n t i n u e d )


12/25


10

9.3 Electrical System

The Caravan is equipped with a 28-volt, direct-current elec-trical system. The system uses a 24-volt, 38ampere-hoursealed lead acid as a source of electrical energy and a200-amp engine-driven starter generator. (An optional 300-amp engine-driven starter generator is available.) Power issupplied to most general electrical and all avionics circuitsthrough two general buses, two avionics buses and a bat-tery bus. The battery bus is energized continuously for ELTreset, clock, cabin/courtesy light functions and engine trendmonitor processor.

A generator control unit provides the electrical control func-

tion necessary for the operation of the starter-generator.

Electrical system operation can be monitored on the En-gine Indication System (EIS) display on the MFD (in normalmode). Battery Amps and Battery Volts can be viewed on ei-ther EIS page (Engine or System). Generator and (Standby)Alternator Amps can be viewed on the EIS System page.The Crew Alerting System (CAS) Annunication Window is lo-cated on each Primary Flight Display (PFD) and can presentappropriate messages (i.e. warning, caution and advisory)pertaining to various engine and aircraft systems as may beapplicable.

A standard ground service plug receptacle permits the use

of an external power source for cold weather starting or dur-ing maintenance work. Ground service circuitry is providedto prevent the external power and the battery from beingconnected together during starting, and incorporates polar-ity reversal and overvoltage protection. The external powerreceptacle is installed on the left side of the engine compart-ment near the firewall.

A standby electrical system is installed for use as a standbypower source in the event the main generator system mal-functions in flight. The system includes a belt-driven alterna-tor operated at a 75-amp capacity rating.

One automotive-style 12-volt power outlet is located in the

cockpit. Two cabin power outlets in the passenger area areavailable as an option.

9.4 Lighting System

Exterior lighting consists of three navigation lights, two land-ing lights, two taxi/recognition lights, two strobe lights, aflashing beacon and two underwing courtesy lights. All ex-terior lights are controlled by toggle switches located on thelighting control panel on the left side of the instrument panel.

The G1000 instrument panel incorporates LED backlightingcontrolled manually through the instrument panel dimmerbus. When the dimmer bus is not used, photocell technol-

ogy automatically controls backlight adjustments to optimizedisplay appearance through a broad range of cockpit light-ing conditions. Other miscellaneous lighting provided includepilot and co-pilot control wheel map lights, cabin/courtesylights, passenger reading lights and a no smoking/seat beltadvisory sign.

9.5 Environmental System

The temperature and volume of airflow to the cabin is regu-lated by the cabin heating, ventilating and defrosting systemIn the heating system, hot engine compressor outlet air isrouted through system components to obtain the correct airtemperature before air is routed to the cabin air distribution

system. Controls are provided to direct the heated air to theforward and/or aft portions of the cabin for heating and to thewindshield for defrosting.

Outside ventilating air is obtained from an inlet on each sideof the forward fuselage and through two ram air inlets, oneon each wing at the upper end of the wing struts. The wingventilating air is routed through the wing into a plenum cham-ber located in the center of the cabin top. The plenum distrib-utes the ventilating air to individual overhead outlets at eachseat position. The forward fuselage ram air inlets provideventilation through panel outlets to the flight deck.

A fan driven ventilation system provides supplemental cabin

ventilation through two overhead mounted ventilators. An op-tional air conditioning system is available that provides com-fortable cabin temperatures during hot weather operationsboth on the ground or in flight.

9.6 Pitot-Static System

The left hand pitot-static system supplies ram air and staticpressure to the number one AHRS (Attitude Heading Reference System), and also to the standby altimeter. The sys-tem is composed of a heated pitot-static tube mounted onthe leading edge of the left wing, a static pressure alternatesource valve, a drain valve located behind the instrumentpanel and the associated plumbing necessary to connect the

instruments and sources.

The right hand pitot-static system supplies ram air and staticpressure to the number two AHRS. The system is composedof a heated pitot-static tube mounted on the leading edge ofthe right wing, a drain valve located behind the instrumenpanel, and associated plumbing.

9.7 Vacuum System

A vacuum system provides the suction necssary to operate the standby attitude indication. Vacuum is obtained bypassing regulated compressor bleed air through a vacuumejector. The vacuum system consists of the bleed air pres-

9 . S Y S T E M S ( C o n t i n u e d )


13/25


1

sure regulator, a vacuum ejector, a vacuum relief valve, and avacuum system air filter. The system is monitored via a warn-ing flag on the standby attitude indicator.

9.8 Garmin G1000 Avionics System

The integrated avionics system incorporates 3 ten-inchdisplays; the pilots primary flight display (PFD), the multi-function display (MFD) and the co-pilots PFD. The systemincludes a single audio system control panel and a separateautopilot controller.

The fully integrated Garmin G1000 system will provide thefollowing communication/navigation/surveillance (CNS) func-

tions: Dual VHF NAV/Glideslope/Localizer receivers, dualVHF com transceivers, dual WAAS GPS receivers and Mode

S transponder. The KN-63 DME is an integrated display andoffers Nav1/Nav2 switching. Crew alerts are displayed on thePFD.

The automatic flight control system (AFCS) incorporates aGFC-700 three-axis autopilot with pitch trim and GFC-710autopilot controller.

Avionics cooling is provided by two cowl deck fans and threedisplay fans. The cowl deck fans are powered from the elec-trical bus. The display fans provide cooling air to each of thethree display units and are powered from the display powercircuits.

Avionic circuit breakers are located on an exclusive panel lo-cated on the lower left-hand instrument panel..

9 . S Y S T E M S ( C o n t i n u e d )

The Caravan includes corrosion proofing as standardequipment. Detail parts receive a chemical film conver-sion coating and are epoxy primed.

Interior surfaces of integral wing fuel bays are primedwith a fuel resistant epoxy primer for corrosion protection.

Steel parts in contact with aluminum structure, in gen-eral, are cadmium-plated with a chromate dip. Fasteners

utilized in the joining process of the steel to aluminumassemblies are installed wet primed for improved corro-sion protection.

The engine mount structure receives a heat resistantenamel finish providing protection in thermal environ-ments up to 400 F.

Polyurethane paint is included as standard exterior paint.

10. CORROSION PROOFING

The The Caravan floatplane provisions consist of hoist-ing rings, inboard fuel filling ports, extended chord rud-der, short airstair door cables (loose equipment), andmicrophone relocation.

The hoisting rings include four rings which attach to theleft and right sides of both the front and rear spar wing-to-fuselage attach fittings. To gain access to the hoist-ing rings, it is necessary to remove the wing-to-fuselagefairing strips. Inboard fuel ports with anti-siphon doorsprovide an easily accessible fuel filler location when re-

fueling onfloats. Due to wing dihedral, use of inboardfiller ports for refueling will reduce maximum usable fuel

to 240 gallons. The extended chord rudder increasesthe surface area of the rudder to provide greater controlwhen floats are installed on the aircraft. The hand micro-phone is located on the center pedestal to allow clear-ance for the emergency lever that is used to manuallylower the wheels on the floats.

Wipline 8000 Float Installation

The Caravan can be converted to a floatplane or an am-phibian when equipped with Wipline 8000 Series Floatsmanufactured, installed and warranted by Wipaire, Inc.(The optional 300-amp starter/generator is not compat-ible with this installation.)

The floats are part of a Wipaire, Inc. STC and are in-stalled by Wipaire, Inc. after aircraft acceptance and de-livery from Cessna Aircraft Company. Wipline floats areFAA certified and TSO approved, and meet Federal CAR-3.372 buoyancy regulations for flooded compartments.

For additional information contact:

Wipaire, Inc.1700 Henry Avenue, Fleming Field,South St. Paul, MN 55075(651) 451-1205(651) 457-7875 [email protected]//www.wipaire.com.

11. FLOATPLANE


14/25


12 FIGURE III CARAVAN FLIGHT DECK

11. FLOATPLANE

Standard Garmin G1000 Avionics Package (Options also pictured)

30-414

3-23-4

1446 lbs/976 lbs*1154 lbs/676 lbs*

162 KTAS1,101 ft2,102 ft1,919 ft3,015 ft

1,110 ft/min20,000 ft8,360 lbs7,800 lbs8,360 lbs8,035 lbs8,000 lbs

790 nmt59 kts

The Following Performance Figures Are Provided By Wipaire, Inc. And Have Not Been Tested By Cessna Aircraft Company.

Specifications For The 8000 Float

Dimensions (external)Length - including extended nose gear & extended water rudder ..........................................................Length - nose to stop ..............................................................................................................................Height - hull ............................................................................................................................................Width - hull .............................................................................................................................................Weight

Amphibious 8000 on the Cessna 208 Caravan ....................................................................................Seaplane 8000 on the Cessna 208 Caravan .......................................................................................*Exchange = Float installation weight minus aircraft landing gear weight.

Performance For The 8000 Float - Cessna 208 Caravan PT6A-114A (675 HP)

Cruise Speed (75%) ...............................................................................................................................Take off run (land) ..................................................................................................................................Take off over 50 ft. obstacle (land) .........................................................................................................Take off run (water) .................................................................................................................................Take off over 50 ft. obstacle (water) .......................................................................................................Rate of climb ..........................................................................................................................................Service ceiling ........................................................................................................................................Gross weight (land & water) Requires Wipaire Gross Weight Kit STC ..................................................Landing weight (land) Requires Wipaire Gross Weight Kit STC ............................................................Landing weight (water) Requires Wipaire Gross Weight Kit STC ..........................................................Maximum ramp weight ...........................................................................................................................Maximum take off weight ........................................................................................................................

Maximum range* (cruise speed, 10,000 ft) ............................................................................................Stall speed (landing configuration) .........................................................................................................

Floatplane AmphibianStandard Empty Weight (Estimated) ................................................................................. 5,393 lbs 5,685 lbsMaximum Useful Load (Estimated) ................................................................................... 2,967 lbs 2,675 lbs*Range based on 332 gal. usable fuel and includes takeoff, climb, descent and 30 minute reserve.All performance data is estimated and will vary with individual airplanes and numerous factors affecting flight performance.


15/25


1

1 2 . STANDARD CARAVAN EQUIPMENT

12.1 AVIONICSStandard Avionics Kit (includes Two Headsets)Garmin G1000 System includes:GDU 1040A Pilot & Co-Pilot Primary Flight Display(PFD)GDU 1040A Multi Function Display (MFD)GDC 74A Dual Air Data Computer (ADC)GEA 71 Engine/Airframe UnitGRS 77 Dual Attitude and Heading Reference System(AHRS)GMA 1347 Single Audio System with Integrated MarkerBeacon ReceiverGTX 33 Mode S TransponderGarmin Relative Terrain/ObstaclesGarmin Flight Charts CapableGarmin Safe Taxi CapableKN-63 DMESwitch, Avionics Power (Two) (On-Off)

Artex ME-406 2-Frequency (Non-Nav Interfaced) ELTwith Remote Switch and Monitor Light (Dorsal FinInstallation)

Avionics Cooling, (2) cowl deck fans and (3) displayfansPA System with Aft Cabin Speakers

12.2 ENGINE INDICATION SYSTEM (EIS)

Displayed on MFD During Normal Operations:

Engine and Systems Displays - Show numeric read-

outs of critical engine, fuel and electrical indications

and calculations for the following:

TorqueInterstage Turbine TemperatureeGas Generator SpeedPropeller SpeedOil PressureOil TemperatureFuel Quantity

Fuel FlowAmmeter/VoltmeterStandby Engine Instrument: Engine Torque Gauge, Wet Type

Altair Digital ADAS Engine Trend Monitoring System

12.3 FLIGHT INSTRUMENTS

Indications Displayed on each PFD:

AirspeedAttitude with Slip/Skid IndicationAltitudeVertical Deviation, Glideslope and Glidepath

Vertical SpeedHorizontal Situation IndicationOutside Air TemperatureSystem TimeGeneric TimerWind DataStandby Instruments Airspeed Indicator Attitude Gyro AltimeterMagnetic CompassHeated Pitot System, Pilot & Co-Pilot

Alternate Static Source

Static Source DrainsInstrument Static SystemSecond Independent Pitot-Static System

12.4 FLIGHT CONTROLS

Brake, ParkingBrakes, Hydraulic, Toe-OperatedControl Cables Corrosion Resistant SteelControl Lock, Ailerons and ElevatorFlight Control System, Pilot & Co-Pilot (Includes All-Purpose Control Wheel, Pedals and Toe Brakes)Friction Lock, Engine ControlsPowerplant, Quadrant Type Controls:

Condition Lever Primary Engine Power Back-Up Engine Power (Emergency Fuel Control)Propeller, Speed and FeatherRudder, Extended ChordRudder Gust LockTrim System (Aileron/Rudder (Manual), Elevator (Manu-al & Electric Pilot & Co-Pilot)Wing Flaps, Electric Pre-Select with Standby Motor

12.5 ENVIRONMENTAL

Defroster, Windshield (Pilot and Copilot)Heating System, Cabin (Bleed Air Type)

SoundproofingVentilation System, Cockpit (Ram Air)Ventilator, Adjustable, Cabin AirVentilation System, Fan Driven

12.6 ELECTRICAL POWER

Battery, 24 Volt, 38 Amp/Hr, Sealed Lead-AcidBattery Switch (On-Off)Circuit Breakers, ElectricalGenerator Control UnitGenerator Switch (Trip-On-Reset)Ground Service Plug Receptacle


16/25


14

Starter/Generator, 200 AmpGenerator Control Unit Mounting (Provisions for Mount-ing Standby Unit)Power Outlet, 12V CockpitStandby Electrical System, 75 amp

12.7 EXTERIOR LIGHTS

Beacon Omni Flash (Red)Courtesy, Under WingIce DetectionLanding, L.H. and R.H. (Wing Leading Edge-Outboard)Navigation (3)Strobe (2) Wing Tip Mounted

Taxi, L.H. and R.H. (Wing Leading Edge-Inboard)12.8 INTERIOR LIGHTS

LED Backlit Instrument Panel LightingMap Light Control Wheel Mounted, Pilot & Co-Pilot (Vari-able Intensity)Overhead Courtesy (3) (Aisle, Aft Cargo Area andPassenger Door)Overhead Flood (Pilot and Copilot) (3)Passenger Reading Lights (8)Dimming Controls, Switch Panel, Avionics Circuit Break-er Panel, Left Hand Panel & Environmental Panel

12.9 POWERPLANT

Chip Detector InstallationCowling, Rigid-Mounted (Quick Removable) Lower andEasily Openable Upper SidesCowl Locks, MedcoEngine Inlet Cover (2) & Propeller Tie-Down SleeveEngine, Turboprop PT6A-114A, 675 SHP, 3600 TBOEngine Wash Ring (Integral)Engine Support, Vibration IsolationFilter, Integral, Full Flow OilFire Detection System, Engine CompartmentIgnition System Excitor Unit Mounting (Provisions forMounting Standby Unit)

Ignition System (Dual Ignitors)Intake Inertial Separator (Manual)Oil Cooler, High CapacityOverspeed GovernorPropeller, 3 Blade Aluminum, Anti-Ice, Constant Speed,Full Feathering, Reversible McCauleyPropeller GovernorPropeller Spinner (Polished)Shielding, Engine IgnitionShutdown Fuel Collector, EngineValve, Oil Quick Drain

12.10 FUEL SYSTEM

Fuel Boost Switch, AuxiliaryFuel Caps with Anti-Siphon DoorsFuel Control Heater, EngineFuel Filling Ports, (4)Fuel Filter with Quick DrainFuel Low Level Warning SystemFuel Pump, Auxiliary (Electric)Fuel Pump, EngineFuel Reservoir with Quick DrainFuel Selector ValvesFuel Shutoff Valve

Fuel Tanks, 332 Gallons UsableFuel Valves, Quick Drain (8)Fuel Vents, Non-IcingFuel Sampler Cup

12.11 INTERIOR

Aircraft KeysApproach Plate Holder, L.H. & R.H.Baggage Area Partition NetBaggage Tie-Down Straps (4)Beverage Cup Holders (Pilot and Copilot)Cargo Tie-Down Fittings ProvisionsCargo Tie-Down Fittings (Baggage Area)

Checklist, Pilots (Laminated)Corrosion Proofing, InternalCrew Door Storage Area LH, RHDe-Ice Partial Plumbing (Wing & Stabilizers) (Consists ofDifficult to Install Plumbing)Fire Extinguisher Cabin Hand TypeFloor Covering, Lightweight VinylGlareshield, PaddedHandbook, Customer Care, Includes Engine/Flight Logs,Warranty, Etc.Handbook, Pilots OperatingHeadliner VinylHooks, Clothes Hanger

Instrument Panel MetalMap/Glove CompartmentOxygen System, Partial Installation (Consists of Difficultto Install Plumbing)Passenger Door Cables, 2 SetsPilot and Co-pilot Restraint Integral 5 Point Lap andShoulder Harness with Inertial ReelPilots LH Pre-Flight Assist HandlePlotter, Weight & Balance (Cargo & Passengers)Pockets, Map and StorageRecorder, Flight HourRelocated Microphone Installation

1 2 . STANDARD CARAVAN EQUIPMENT ( C o n t i n u e d )


17/25


1

Seats, Pilot & Copilot, Adjustable Fore, Aft and Verticalwith Articulating Recline and Arm RestSign, Fasten Seat Belts & No SmokingStep, Cabin Entrance, Retractable (LH & RH Crew EntryDoors)Sunvisors, RosenWindow, Foul Weather, Pilot DoorWindows Tinted All-Around

12.12 EXTERIOR

Anti-Precipitation Static KitBonding Straps, Control Surface (Aileron, Elevator andRudder)

Cargo Pod Provisions with Straight StackCorrosion Proofing, ExternalDoor, Cargo, Two-Piece (Left Side of Aircraft, with UpperDoor Unlocked Annunciator Light)Door, Copilot (Full Opening)Door, Pilot (Full Opening)Door, Passenger with Airstair Feature (Right Side of

Aircraft with Upper Door Unlocked Annunciator Light)

Hoisting RingsJack Points (Fuselage and Main Landing Gear)Landing Gear, Fixed, Nose, SteerableLanding Gear, Fixed, MainLock, Key-Operated (One Key Fits All Doors)Paint, All Over (Modified Polyurethane)Stabilizer Abrasion BootsStall Warning System, HeatedTires, 8.50 x 10, 8 Ply Main, 22 x 8.00, 6 ply Nose WithExtended Nose Gear ForkTie-Down Provisions, AircraftTow BarSunvisors, RosenWindow, Foul Weather, Pilot Door

Windows Tinted All-AroundStall Warning System, HeatedTailstandTires, Tube Type, with Extended Nose Gear Fork, Main8.50 x 10, 8 plyTie-Down Rings, AircraftTow Bar

1 2 . STANDARD CARAVAN EQUIPMENT ( C o n t i n u e d )

1 3 . D O C U M E N T AT I O N A N D T E C H N I C A L P U B L I C A T O N S

U.S. Standard Airworthiness Certificate, FAA8100-2; Ex-port Certificate of Airworthiness, FAA8130-4 or Special

Airworthiness Certificate FAA8130-7 as appropriate;

Equipment ListWeight and Balance ReportGarmin Cockpit Resource GuidePilots Operating Manual

Abbreviated Procedures ChecklistLog Books (Aircraft and Engines)

Additional Miscellaneous Information Concerning Engineand Airframe Support

Passenger Briefing CardsCessna CESCOM Instruction Manual

CESSNA TECHNICAL INFORMATIONCessna makes available a complete system of manualsand catalogs for the operation and maintenance of theCaravan. All Cessna and related technical information islisted in the Cessna Customer Care Supplies and Publi-cations Catalog.

Cessna manuals are kept current through periodic revi-sions. Aircraft operators and designated maintenancefacilities can receive these revisions by mail througha subscription service. The subscription is free for thefirst year to owners of new aircraft. A subscription fee ischarged thereafter.

The following manuals are provided on CD-ROM withthe purchase of a new Caravan:

Service Maintenance ManualIllustrated Parts CatalogWiring Diagram ManualStructural Repair ManualService Bulletins

Avionics Wiring Diagram (custom diagram of theactual avionic installation)

The following materials are provided by Pratt & WhitneyCanada:

Combined Engine Maintenance Manual & IllustratedParts Catalog CDOne set Engine Service Bulletins Including Spare

Parts Bulletins and Service Information Letters (Paper)Free revision coverage for one yearService Bulletins are also available by on-line or e-mail subscription at www.pwc.ca or through the Prattand Whitney Help Desk at (800) 268-8000.

CESSNA REVISION STATUS CHECKLIST

The Revision Status Checklist is used to verify that onlythe most current Cessna maintenance and aircraft op-eration publications are in use. The checklist is availableby subscription and is revised every 90 days.


18/25


16

CESCOM

Cessna will provide a computerized maintenance recordservice for one (1) full year from the date of delivery of aCessna Caravan to the purchaser.

This service will provide owners and operators with thereports necessary for the efficient control of maintenanceactivities. It will provide an accurate and simple methodof keeping up with aircraft components, inspections, ser-vice bulletins and airworthiness directives while providingpermanent aircraft records of maintenance performed.

Reports will be available which reflect the aircraft sta-tus, upcoming scheduled maintenance and a recap ofthe previous months reported maintenance activity.Semi-annual reports concerning projected annual main-tenance requirements, component removal history andfleet-wide component reliability will also be available.

The on-line system is the standard service, however, apaper service is available at an additional charge. Theon-line system is accessible using a local computerwith Internet capability. Data is electronically transferredthrough Internet connections between the customer andCessna on a regular basis to keep information up-to-date

at both locations. In addition to the standard CESCOMreports, customer specific reports and maintenance re-cords can be generated at the local computer wheneverthe customer wishes.

CARAVAN PHASE CARD INSPECTION PROGRAM

The Caravan Phase Card Inspection Program is designedspecifically for operators engaged in CFR 14, Part 135and other high-use operations (minimum of 400 hours peryear). Actual field experience demonstrates an average 30percent reduction in scheduled maintenance labor hoursover progressive or periodic inspection programs.

The Phase Card Program is accomplished using workcards which list specific tasks to achieve during eachinspection. The work cards provide the mechanic withstep-by-step, easy-to-follow instructions, service manu-al chapter references, special diagrams and applicablenotes, cautions and warnings. The program is complet-ed through twelve phases scheduled every 200 hours

A mini-check is performed at 100-hour intervals. Thiscarefully scheduled and specifically planned program en-sures a safer and more reliable aircraft through inspec-tions conducted in a thorough, systematic, and deliber-ate manner.

ALTAIR DATA ACQUISITION SYSTEM & TURBINE

TRACKER

Cessna has chosen the Altair ADAS system as standardequipment on the Caravan to allow operators to easilymonitor and maintain the aircraft engine.

The ADAS system records engine parameters, indicat-ed airspeed, pressure altitude, outside air temperatureflight hour meter, battery voltage, and the positions of theparticle separator, emergency power lever and bleed aircabin heat switch.

Data retrieval is handled using a special software pro-gram installed on a laptop or handheld computer. Datadelivery is handled using the computer to transfer the air-craft data to the Turbine Tracker (tm) website. The Tur-bine Tracker (tm) website formats the data into custom-ized reports for use as analysis tools.

ENGINE CONDITION TREND MONITORING

Pratt & Whitney Canada developed this program for usewith the PT6A-114 engines installed in Caravan aircraftThis is a system of calculating and graphically present-ing recorded engine instruction indications. The recorded

1 4 . M A I N T E N A N C E P R O G R A M S

CESSNA OWNER ADVISORY

Cessna Owner Advisories provide owners of Cessna air-craft up-to-the-minute information about mandatory andbeneficial service requirements and the latest in productimprovements. Owner Advisories summarize new Ser-vice Bulletins or Service Newsletters and indicate anyaction required by the owner, the time required for theowner to comply, and the existence of any associatedcredit allowances.

Cessna Owner Advisories are mailed automatically toowners of U.S. registered Cessna aircraft using the

latest name and address provided to the FAA. OwnerAdvisories can be mailed to a different address byrequest, provided the subject aircraft is still covered byCessna warranty. International owners of Cessna aircrafcovered by Cessna warranty receive Owner Advisoriesthrough a complimentary subscription. After warrantyexpiration, international subscriptions are available,although a subscription fee will be charged. Revisionsfor the Pilots Operating Handbook and Pilots Abbrevi-ated Checklist and/or Log of Approved Supplements areincluded with the Owner Advisory when applicable.

1 3 . D O C U M E N T AT I O N A N D T E C H N I C A L P U B L I C A T O N S (Continued)


19/25


1

indications are then mathematically adjusted for com-parison of actual engine performance to typical engineperformance characteristics.

Two important features are available to owners and op-erators using engine trend monitoring:

1. It allows for early detection of compressor and/or tur-bine deterioration, thereby minimizing secondary prob-lems and overall repair costs.

2. It allows for hot section inspections to be accom-plished on an on condition basis instead of at a sched-uled recommended 1800-hour interval provided the fol-

lowing requirements are met:

*Monitoring is implemented within the first 100 hours inservice or after completion of the hot section inspection

*Certain other requirements are met as stipulated byPratt & Whitney

On condition hot sections are hot sections accom-plished only when necessary, which results in significant-ly reduced operating costs.

Open Account Information

With an active open account, Caravan owners are ableto purchase spare parts at the current published list pricedirectly from Cessna Parts Distribution. The open ac-count can also be used to purchase Cessna publicationsand other items.

PRATT & WHITNEY ENGINE MAINTENANCEPROGRAMS

Fleet Services

The Fleet Services business unit offers pay-by-the-hourprograms for both the airline and corporate markets. The

airline program is entitled Fleet Management Program(FMP) while the corporate program is entitled EagleService Plan (ESP). The objective of these programsis to establish a stable, simplified engine managementand financial planning tool, which will guarantee operat-ing costs tailored to suit individual requirements.

These programs provide predictability of costs associ-ated with engine maintenance and minimize the effort re-quired for the operator to effectively manage its engines.These plans eliminate the risk of high cost surprises.

The programs currently offered include:

Term Cost Plan (TCP)

Under the TCP the operator pays a guaranteed hourlyrate on a monthly basis per engine flying hour. The rate isbased on support services selected from a comprehen-sive menu of options.

Event Cost Plan (ECP)

As with the TCP, the operator pays a guaranteed hour-ly rate per engine flying hour. The payment occurs foreach individual engine at the time of its shop visit, where

the charge is based upon the total engine hours flown bythe engine since its last shop visit.

Maintenance Cost Guarantee Plan (MCG) - Airline

The MCG is a not to exceed cost guarantee. No month-ly payments are due. The operator covers the mainte-nance expenses as they occur and account reconcilia-tion takes place at agreed intervals. If the agreed hourlyrate is exceeded, the over run costs are settled in ac-cordance with the terms of the agreement. The operatorretains the full benefit of any cost under runs.

Eagle Service Plan (ESP)

Four plans are available for the corporate operator de-pending on the level of coverage selected. P&WC pro-vides the operator with coverage of specified enginemaintenance expenses in return for a monthly paymentbased on an established rate per engine operating hour.

Once signed on, you will benefit from having a P&WCrepresentative dedicated to providing the essential coor-dination and support you expect.

Telephone Number: (450) 468-7681

Fax Number (450) 468-3772

1 4 . M A I N T E N A N C E P R O G R A M S (Continued)


20/25


18

The standard Cessna Caravan Aircraft Limited Warrantywhich covers the aircraft, other than the Pratt & WhitneyCanada (P&WC) engine and associated engine acces-sories, the Honeywell avionics, and the McCauley pro-peller which are warranted separately, is set forth be-low. Cessna specifically excludes vendor subscriptionservices and the availability of vendor service providersfor Optional and Customer Requested Equipment (CRQ)from Cessnas Limited Aircraft Warranty. Following Cess-nas Limited Warranty, the engine and engine accessorywarranty of P&WC, the avionics warranty of Honeywell,and the propeller warranty of McCauley are set forth. Allwarranties are incorporated by reference and made part

of the Purchase Agreement. All warranties are adminis-tered by Cessnas Warranty Department.

15.1 Cessna Caravan Limited Warranty (Limited

Warranty)

Cessna Aircraft Company (Cessna) expressly war-rants each new Cessna Caravan Aircraft (exclusive ofengine and engine accessories supplied by P&WC, avi-onics supplied by Honeywell, and the propeller suppliedby which are covered by their separate warranties), in-cluding other factory-installed avionics and other factory-installed optional equipment to be free from defects in

material and workmanship under normal use and servicefor the following periods after delivery:

(a) One (1) year unlimited hours OR two (2) years /1,000hour limit on all aircraft components manufactured byCessna;

(b) Five years or 5,000 operating hours, whichever oc-curs first, for Garmin avionics;

(c) One year for all Optional Avionics;

(d) One year for Actuators, Brakes, GCUs, Starter Gen-erators, Valves, Windshields, and Vendor items including

engine accessories supplied by Cessna unless otherwisestated in the Optional Equipment and Selection Guide;

(e) One year for CRQs, Interior Components, InteriorFurnishings, and Paint.

Any remaining term of this Limited Warranty is automati-cally transferred to subsequent purchasers of the aircraft.

Cessnas obligation under this Limited Warranty is limitedto repairing or replacing, in Cessnas sole discretion, withexchange, overhauled, or new parts, any part or partswhich: (1) fail within the applicable warranty period, (2)

are returned at the warranty recipients expense to the

facility where the replacement part is procured, whetherthrough Cessna Service Parts & Programs or a servicefacility authorized by Cessna to perform service on theaircraft (collectively Support Facility), (3) are accompa-nied by a properly executed claim form, and (4) are foundby Cessna or its designee to be defective.

Replacement parts must be procured through a SupporFacility and are only warranted for the remainder of theapplicable original aircraft warranty period. A new warranty period is not established for replacement partsThe repair or replacement of defective parts under thisLimited Warranty will be made by a service facility autho-

rized by Cessna to perform service on the aircraft (Au-thorized Service Facility) without charge to the warrantyrecipient for parts and/or labor for removal, installationand/or actual repair of such defective parts. All expeditedfreight, transportation expenses, import duties, customsbrokerage fees, sales taxes, and use taxes, if any, onsuch warranty repairs or replacement parts are the war-ranty recipients sole responsibility. (Location of Authorized Service Facilities will be furnished by Cessna onrequest.)

This Limited Warranty applies to only items detailedherein which have been used, maintained, and operated

in accordance with Cessna and other applicable manu-als, bulletins, and other written instructions. Howeverthis Limited Warranty does not apply to items that havebeen subjected to misuse, abuse, negligence, accidentor neglect; to items that have been installed, repaired, oaltered by repair facilities not authorized by Cessna; or toitems that, in the sole judgment of Cessna, have been in-stalled, repaired, or altered by other than Authorized Service Facilities contrary to applicable manuals, bulletinsand/or other written instructions provided by Cessna sothat the performance, stability, or reliability of such itemsare adversely affected. This Limited Warranty does noapply to normal maintenance services (such as engine

adjustments, cleaning, control rigging, brake and othermechanical adjustments, and maintenance inspections)or to the replacement of service items (such as brake linings, lights, filters, de-ice boots, hoses, belts, tires, andrubber-like items); or to normal deterioration of appurte-nances (such as paint, cabinetry, and upholstery), corrosion or structural components due to wear, exposureand neglect.

WITH THE EXCEPTION OF THE WARRANTY OF TI-

TLE AND TO THE EXTENT ALLOWED BY APPLICA-

BLE LAW, THIS LIMITED WARRANTY IS EXPRESSLY

IN LIEU OF ANY OTHER WARRANTIES, EXPRESSED

1 5 . L I M I T E D W A R R A N T I E S


21/25


1

OR IMPLIED, IN FACT OR BY LAW, APPLICABLE TOTHE AIRCRAFT. CESSNA SPECIFICALLY DISCLAIMS

AND EXCLUDES ALL OTHER WARRANTIES, IN-

CLUDING, BUT NOT LIMITED TO, ANY IMPLIED

WARRANTY OF MERCHANTABILITY OR FITNESS

FOR A PARTICULAR PURPOSE. THE AFOREMEN-

TIONED REMEDIES OF REPAIR OR REPLACEMENT

ARE THE ONLY REMEDIES UNDER THIS LIMITED

WARRANTY. CESSNA EXPRESSLY AND SPECIFI-

CALLY DISCLAIMS ALL OTHER REMEDIES, OBLI-

GATIONS, AND LIABILITIES, INCLUDING, BUT NOT

LIMITED TO, LOSS OF AIRCRAFT USE, LOSS OF

TIME, INCONVENIENCE, COMMERCIAL LOSS, LOSS

OF PROFITS, LOSS OF GOODWILL, AND ANY ANDALL OTHER CONSEQUENTIAL AND INCIDENTAL

DAMAGES. CESSNA NEITHER ASSUMES NOR AU-

THORIZES ANYONE ELSE TO ASSUME ON ITS BE-

HALF ANY FURTHER OBLIGATIONS OR LIABILITIES

PERTAINING TO THE AIRCRAFT NOT CONTAINED

IN THIS LIMITED WARRANTY. THIS LIMITED WAR-

RANTY SHALL BE CONSTRUED UNDER THE LAWS

OF THE STATE OF KANSAS AND ANY DISPUTES

AND/OR CLAIMS ARISING THERFROM SHALL BE

EXCLUSIVELY RESOLVED IN THE STATE AND/OR

FEDERAL COURTS LOCATED IN WICHITA, KANSAS.

THE PARTIES HERETO CONSENT TO PERSONAL

JURISDICTION IN THE FORUM CHOSEN.

15.2 PRATT & WHITNEY CANADA INC. (Abbrevi-

ated New Engine Warranty)

Pratt & Whitney Canada Inc. (P&WC) warrants that eachnew PT6A-114A engine complete with installed accesso-ries at time of delivery will be free from defects in mate-rial and manufacture. P&WCs liability and purchasersremedy under this warranty are limited to the repair or re-placement at P&WCs option of goods returned to P&WCor to a location designated by P&WC which are shown toP&WCs reasonable satisfaction to have been defective,

provided that written notice of defect shall have beengiven by Purchaser to P&WC or its designee within onethousand (1,000) flying hours after delivery of the engineto the first user. The repair or replacement of defectivegoods under the Warranty will be made by P&WC or itsdesignee without charge for parts or reasonable labor forremoval, installation and/or actual repair of such defec-tive goods, and reasonable transportation charges, ex-cept import duties, sales or use taxes, if any, on replace-ment. Transportation charges for the return of defectivegoods to P&WC or its designee and their reshipment toPurchaser and the risk of loss thereof will be borne byP&WC.

THE FOREGOING WARRANTIES ARE EXCLUSIVEAND ARE GIVEN AND ACCEPTED IN LIEU OF ANY

AND ALL OTHER WARRANTIES, EXPRESSED OR

IMPLIED, INCLUDING WITHOUT LIMITATION THE

IMPLIED WARRANTY OF MERCHANTABILITY AND

ANY OBLIGATION, LIABILITY, RIGHT, CLAIM OR

REMEDY IN CONTRACT OR TORT WHETHER OR

NOT ARISING FROM P&WCS NEGLIGENCE, AC-

TUAL OR IMPUTED. THE REMEDIES OF THE PUR-

CHASER FOR ANY BREACH OF WARRANTY SHALL

BE LIMITED TO THOSE PROVIDED HEREIN TO THE

EXCLUSION OF ANY AND ALL OTHER REMEDIES

INCLUDING, WITHOUT LIMITATION, INCIDENTAL OR

CONSEQUENTIAL DAMAGES. NO VARIATION OREXTENSION OF THE FOREGOING WARRANTIES,

REMEDIES OR THIS LIMITATION WILL BE BINDING

UPON P&WC UNLESS APPROVED IN WRITING BY A

DULY AUTHORIZED OFFICER OF P&WC.

The above abbreviated warranty is for the purposes ofthe Specification and Description. For complete de-tails of the PT6A-114A engine warranty, please refer toP&WCs full PT6A-114A warranty policy.

15.3 HONEYWELL

Honeywell/Bendix/King Warranty

A. General Aviation Avionic products manufactured byHoneywell/Bendix/King, General Aviation Division (col-lectively referred to herein as Honeywell/Bendix/King)are warranted against defects in design, material orworkmanship caused by Honeywell/Bendix/King or itsauthorized agent(s) for the Warranty Period as defined inParagraph (B) of this statement which occur under nor-mal and intended use and service, subject to all of thequalifications and conditions hereinafter stated.

1. Warranty coverage is only offered to purchaserswho make warranty registrations within eighteen(18) months of the products factory shipping date.Demonstration or stock aircraft usage is restricted to100 hours service prior to warranty registration.Warranty coverage, therefore, may be unavailableor limited, depending upon the usage or time theproduct in question may have remained unsold inthe custody of the O.E.M. (Original Equipment Man-ufacturer), his agent, or the retail dealer, a matter asto which the seller is expected to maintain accuraterecords and provide same, upon demand, to anypurchaser or Honeywell/Bendix/King.

1 5 . 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 )


22/25


20


2. Warranty coverage for products otherwise noteligible by reason of expiration of the eighteen (18)month period specified above may again become el-igible for warranty protection, provided (a) that war-ranty registration occurs within thirty (30) months ofthe products factory shipping date and (b) that theproducts are submitted to Honeywell/Bendix/Kingfor inspection and certification and then the pro-mulgated Honeywell/Bendix/King certification fee ispaid.

B. The Warranty Period for products shall begin upon thedate of delivery of the product to the purchaser and shall

end two years thereafter.

C. Any product Honeywell/Bendix/King finds to be in vio-lation of the warranty as set out in Paragraph (A) hereof,at the option of Honeywell/Bendix/King, shall be repaired,replaced, or exchanged, in accordance with the followingprocedures:

1. Products shall be returned to an authorized Hon-eywell/Bendix/King Service Center or Honeywell/Bendix/King Regional Product Support Repair/Over-haul Facility, with transportation charges prepaid.

2. After correction, the products shall be returned tothe purchaser with surface transportation chargesprepaid, except for returns to purchasers in foreigncountries.

3. The risk of loss or damage to all products in tran-sit shall be borne by the party initiating the transpor-tation of such products unless the purchaser makesa request for a specific mode of transportation. Insuch case, the risk of loss and the cost of shipmentshall be borne by the purchaser.

All items repaired or replaced hereunder shall be war-ranted for the unexpired portion of the original Warranty

Period.

D. This warranty specifically excludes defects whichHoneywell/Bendix/King determines to be the result of:

1. Abuse, accident, or misuse;

2. Contamination, negligence, tampering, or improp-er storage or maintenance;

3. Repair or attempted repair by unauthorized per-

sons or use of non- Honeywell/Bendix/King or unauthorized repair or replacement parts; or

4. Products not installed by an authorized Honey-well/Bendix/King Installation Facility in accordance with the appropriate installation manual.

E. The Warranty as set out in paragraph (A) is the onlywarranty for Honeywell/Bendix/King General Aviation

Avionics Products and is in lieu of all other warrantiesexpress or implied, including the implied warranties omerchantability and fitness for a particular purpose whichare herewith expressly excluded and disclaimed.

F. The remedies as set out in Paragraph (C) hereof statethe entire liability of Honeywell/Bendix/King and con-stitute the sole and exclusive remedy of the purchaserHoneywell/Bendix/King shall not be liable for any otherclaim, loss, or damage, including, but not limited to incidental, consequential, or other kinds of damages whether based on contract, tort, negligence, or other theory oproduct liability.

G. Honeywell/Bendix/King reserves the right to makedesign changes, additions to, and improvements in itsproducts without the obligation to install same in prod-ucts previously manufactured.

15.4 McCAULEY LIMITED WARRANTY

Cessna Aircraft Company, McCauley Accessory Division, Wichita, Kansas, U.S.A. McCAULEY, expresslywarrants its new or remanufactured products thereforesold by McCauley to be free from defects in material andworkmanship under normal use and service for a periodof thirty six (36) months after delivery to the original retaipurchaser.

McCauleys obligation under this warranty is limited torepairing or replacing, at its option, any part or parts

which, within the thirty six (36) month period as above seforth shall be returned transportation charges pre-paidto McCauley at Wichita, Kansas or to any McCauley ap-pointed Service Facility authorized by such appointmento service the McCauley product of the type involved andwhich upon examination shall disclose to McCauleyssatisfaction to have been thus defective. Any remainingterm of this Limited Warranty is transferable to subsequent purchasers.


23/25


2


The repair or replacement of defective parts under thiswarranty will be made by McCauley or its authorized Ser-vice Facilities without charge for parts or labor for the ac-tual repair of such defective parts, except import duties,sales or use taxes, if any, on replacements.

The provisions of this warranty do not apply to any Mc-Cauley products or service parts therefor which havebeen subject to misuse, negligence or accident or whichshall have been repaired or altered outside of McCau-leys factory in any way so as in the judgment of Mc-Cauley to affect adversely its performance, stability orreliability nor to normal maintenance service.

To the extent allowed by applicable law, THIS WAR-RANTY IS EXPRESSLY IN LIEU OF ANY OTHER WAR-RANTIES, EXPRESSED OR IMPLIED IN FACT ORBY LAW, INCLUDING ANY IMPLIED WARRANTY OFMERCHANTABILITY OR FITNESS FOR A PARTICU-

LAR PURPOSE. THE REMEDIES OF REPAIR OR RE-PLACEMENT AS ABOVE SET FORTH ARE THE ONLYREMEDIES UNDER THIS WARRANTY. McCAULEYDISCLAIMS ANY OBLIGATION OR LIABILITY WHETH-ER IN CONTRACT OR IN TORT (AND WHETHER FORNEGLIGENCE, STRICT LIABILITY, PRODUCT LIABIL-ITY OR OTHERWISE), INCLUDING LOSS OF USEOF THE PRODUCT WARRANTED, LOSS OF TIME,INCONVENIENCE, COMMERCIAL LOSS OR ANYOTHER DIRECT, CONSEQUENTIAL, SPECIAL OR IN-CIDENTAL DAMAGES. THIS WARRANTY IS IN LIEUOF ANY OTHER OBLIGATION OR LIABILITY ON THEPART OF McCAULEY TO ANYONE OF ANY NATURE

WHATSOEVER by reason of the manufacture, sale,lease or use of the warranted products and McCauleyneither assumes nor authorizes anyone to assume forit any other obligation or liability in connection with suchwarranted products.

1 6 . C A R A VA 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) Caravan Crew will be furnished toFirst Retail Purchaser (hereinafter called the Purchas-er), subject to the following:

1. A crew shall consist of up to two (2) licensed pilots with

current experience for the training sought and one (1)mechanic with A&P licenses or equivalent experience.

2. Training shall be conducted by Cessna or by its desig-nated training organization.

a. A simulator shall be utilized which is FAA certifiedto provide training to proficiency in accordance withtrainers standards.

b. In lieu of a model specific simulator, training will beprovided in the most appropriate type simulator avail-able.

c. Location of training to be Wichita, Kansas, unlessmutually agreed otherwise. The organization con-ducting the training is hereinafter called the Trainer.

3. Training furnished shall consist of the following:

a. Flight simulation training to simulator proficiencyin accordance with Trainers standards but not to ex-ceed seven and one half (7.5) total hours for eachpilot.

b. Ground School training for each pilot and class-room instruction for each mechanic in accordancewith Trainers standards.

c. Flight training to flight proficiency in accordancewith Trainers standards not to exceed five (5) totalhours per pilot, shall be conducted in the customersaircraft.

4. Purchaser shall be responsible for:

a. Transportation of crew to and from training site andfor living expenses during training.

b. Providing an interpreter during the course of train-ing for any of Purchasers crew not conversant withthe English language.

c. Payment to Trainer for additional simulator or flighttraining beyond that required to attain proficiency inaccordance with Trainers standards for the course inwhich the pilot is enrolled.

d. All aircraft for flight training as well as all landingfees, fuel costs, aircraft maintenance and insuranceand all other direct costs of operation, including appli-cable taxes required in connection with the operationof said aircraft during such flight training.

e. Extra charges, if any, for scheduling pilots in sepa-rate training classes.

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


24/25


22

1 6 . C A R A VA N C R E W T R A I N I N G A G R E E M E N T ( C o n t i n u e d )

5. Seller or Trainer shall schedule all training, furnishPurchaser schedules of training and endeavor to sched-ule training at a convenient time for Purchaser. A cancel-lation fee of Two Hundred Dollars ($200) will be paid byPurchaser if crew fails to appear for scheduled training,except for reasons beyond its reasonable control, unlessPurchaser gives Seller written notice of cancellation re-ceived at Wichita, Kansas, at least seven (7) days priorto scheduled training. In the event of such cancellationSeller shall reschedule training for the next availableclass.

6. Neither Seller nor Trainer shall be responsible for the

competency of Purchasers crew during and after train-ing. Trainer will make the same efforts to qualify Pur-chasers crew as it makes in training of other Caravancrews; however, Seller and Trainer cannot guaranteePurchasers crew shall qualify for any license, certificateor rating.

7. Neither Seller nor Trainer shall be responsible for anydelay in providing training due to causes beyond its ortheir reasonable control.

8. All Training furnished to Purchaser under the Agree-ment will be scheduled to commence no earlier thanthree (3) months prior to delivery and will be completedwithin twelve (12) months after delivery of the aircraft un-less mutually agreed otherwise.

Signature of the Purchaser to the Purchase Agreementto which this Training Agreement is attached as a partof the Specification and Description shall constitute ac-ceptance by Purchaser of the foregoing terms and condi-tions relative to training to be furnished by Seller.

Purchaser agrees that Cessna may provide names, ad-dresses and contact information to Trainer for the pur-pose of class enrollment.


25/25

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

Documents

Cessna Caravan Amphibian Specificatios & Description