2016 Feb SD Caravan 208-0580 Rev.D.indd

11.7 Exterior Lights ............................................................................................................................................................. 11.8 Interior Lights ............................................................................................................................................................. 11.9 Powerplant .................................................................................................................................................................. 11.10 Fuel System ................................................................................................................................................................ 11.11 Interior .......................................................................................................................................................................... 11.12 Exterior ......................................................................................................................................................................... 12. Documentation and Technical Publications ................................................................................................................. 13. Maintenance Programs ..................................................................................................................................................... 14. Limited Warranties 14.1 Cessna’s Limited Warranty ..................................................................................................................................... 14.2 Pratt & Whitney Canada Inc. .................................................................................................................................. 14.3 Honeywell/Bendix/King Warranty ......................................................................................................................... 14.4 McCauley Limited Warranty ................................................................................................................................... 15. Caravan Crew Training Agreement .................................................................................................. .............................. FIGURE I — CARAVAN EXTERIOR DIMENSIONS ...................................................................................................................... FIGURE II — CARAVAN INTERIOR DIMENSIONS ...................................................................................................................... FIGURE III — CARAVAN INSTRUMENT PANEL AND PEDESTAL LAYOUT............................................................................ TABLE OF CONTENTS 3 7 8 8 9 9 10 10 10 11 11 11 12 12 12 13 13 14 17 17 17 17 18 18 18 18 18 18 19 19 20 21 22 23 23 25 26 4 5 16 Februar y 2016, Revision D 3 CARAVAN 1. GENERAL DESCRIPTION The Cessna Caravan is an unpressurized single-engine high wing turboprop aircraft with fixed landing gear. The aircraft can accommodate up to fourteen persons includ- ing a minimum crew of one. (Operations with more than nine passengers must be approved by the registering country’s 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 aircraft fuselage. 1.1 CERTIFICATION Certification basis is to U.S. FAA FAR Part 23 Require- ments—day, night, VFR and IFR when equipped with the appropriate options. Export certification requirements may require additional equipment and charges. 1. GENERAL DESCRIPTION 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 ..................................................................................................................................................................................... 28.6 lb/ft2 11.85 lb/shp Februar y 2016, Revision D 4 CARAVAN FIGURE I — CAR AVAN EXTERIOR DIMENSIONS 1. GENERAL DESCRIPTION (CONTINUED) 52 ft 1 in 11 ft 8 in 37 ft 7 in 14 ft-10 1/2 in MAX NOTES: 1. Dimensions shown are based on standard empty weight and proper infl ation of nose and main gear tires. 2. Wing span dimension includes strobe lights. 3. Maximum height shown with nose gear depressed as far as pos- sible. 4. Wheel base length is 11’-7 1/2”. 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 4 1/2”:19”. Nose tire deflated and nose strut fully compressed: 12”. 20 ft 6 in se strut Februar y 2016, Revision D 5 CARAVAN FIGURE II — CAR AVAN INTERIOR DIMENSIONS 1. GENERAL DESCRIPTION (CONTINUED) 49 in 35 in *54 in **62 in *59 1/2 in **64 in *51 in **53 in 17 ft 4 in *42 in **46 in 13 ft 10 in 18 in 54 in 51 in 52 in 46 in 24 in *24 3/8 in 31 7/8 in 35 5/8 in 11 7/8 in 50 in 24 in 41 3/4 in 44 3/4 in Stations 100 118 234 284 308 *Dimensions at cabin floor **Dimensions at lower window line 53 in 24 in 50 in 180 Februar y 2016, Revision D 6 CARAVAN 1. GENERAL DESCRIPTION (CONTINUED) 14 ft 10 in 37 ft 7 in 52 ft 1 in 279.40 ft2 0 degrees +3 degrees 0.586 9.555 66.474 in 20 ft 6 in 70.04 ft2 0° at elevator hinge line 0 degrees 6.0 41.984 in 8 ft 2 in 39.92 ft2 +9.437° at rudder hinge line 4 ft 3 in 17 ft 4 in 5 ft 2 in 11 ft 8 in 11 ft 8 in 8.5 x 10, 8 ply 22 x 8.00 x 8, 6 ply 1.2 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 fin) ................................................................................................................................................................ 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 ..................................................................................................................................................................... Februar y 2016, Revision D 7 CARAVAN 8,035 lb 8,000 lb 7,800 lb 4,230 Est. lb 3,805 Est. lb 332 gal/2224 lb 14 qt 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 ...................................................................................................................................................... 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 performance will vary with individual airplanes and other factors such as environmental conditions and aircraft configuration. 1. GENERAL DESCRIPTION (CONTINUED) 2. PERFORMANCE 1.3 DESIGN WEIGHTS AND CAPACITIES Maximum Ramp Weight ................................................................................................................................................. Maximum Takeoff Weight .............................................................................................................................................. Maximum Landing Weight ............................................................................................................................................. Standard Empty Weight* ................................................................................................................................................ Maximum Useful Load .................................................................................................................................................... Fuel Capacity (usable) at 6.70 lb/gal ............................................................................................................. Oil ....................................................................................................................................................................................................................... * Approximate standard empty weight includes unusable fuel, full operating fluids and full engine oil. Without cargo pod 186 kts 174 kts 932 nm 5.1 hr 1,220 nm 7.1 hr 1,085 nm 7.0 hr 1,295 nm 8.3 hr 1,234 fpm 25,000 ft 1,160 ft 2,055 ft 715 ft 1,625 ft 75 kts 61 kts Februar y 2016, Revision D 8 CARAVAN 4. FUSELAGE GROUP 3. STRUCTURAL DESIGN CRITERIA Construction of the fuselage is of conventional formed sheet metal bulkhead, stringer and skin design. Major elements of the structure are the front carry-through spar and bulkhead, the rear carry-through spar and landing gear bulkhead, and the forward doorpost. The front carry-through spar and bulkhead is an integral fail-safe structure with forgings at the top for attaching the front wing spar and forgings at the bottom for attaching the wing strut. The rear carry-through and landing gear bulkhead is an integral fail-safe structure with forgings at the top for attaching the rear wing spar and forgings at the bottom for attaching the main landing gear trunnions. The forward doorpost provides the load path for transferring the loads from the engine mount directly to the primary structure. The large cabin area provides comfortable space for a pilot and up to thirteen passengers. (Operations with more than nine passengers are limited to countries that issue approval.) Inside cabin dimensions are 51” high and 62” wide at the front and rear spar bulkhead locations. The cabin narrows slightly toward the tailcone to 52” high and 53” wide just aft of the cargo door. Total length of the cabin from the firewall to the aft bulkhead is 17 ft. 4 in. The cabin floor is flat with the ex- ception of two feet in the aft cabin which is five inches above the main floor and makes up the aft cabin baggage area. Cabin volume, including the pilot and aft cabin baggage area is 341.4 cubic feet. Total volume aft of the pilot and front passenger seat locations is approximately 254 cubic 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 two piece airstair- type door on the right side of the airplane just aft of the wing. A large cargo door is also provided on the left side of the airplane directly across from the airstair door. All doors can be opened with the flaps up or down. The left crew entry door incorporates a conventional door handle, key-operated door lock, conventional interior door handle and window with a small triangular foul weather window. The foul weather window may be opened for ad- ditional ground ventilation. The right crew entry door incor- porates a conventional outside and inside door handle and a manually operated inside door lock. A 4 inch deep x 5 1/2 inch storage area is incorporated into the interior width of both the left and right crew doors. Both doors have a maxi- mum width of 35.65 inches and a maximum height of 44.75 inches and will open 180 degrees forward to latch against the side of the fuselage. 175 KCAS 175 KCAS 150 KCAS 125 KCAS 150 KCAS 133 KCAS 114 KCAS DESIGN SPEEDS (All speeds are at maximum gross weight.) Cruising Maximum Operating Limit (VMO ) ............................................................................................................................. Flap Extension Speeds 0° to 10° ............................................................................................................................................................................. 10° to 20° ........................................................................................................................................................................... 20° to 30° .......................................................................................................................................................................... Maneuvering Speed (VA ) 8000 pounds .................................................................................................................................................................. 6300 pounds ................................................................................................................................................................... 4600 pounds.................................................................................................................................................................... The Caravan certification basis is to FAR Part 23 normal category aircraft. Design limit load factors are +3.8G, -1.52G at a maximum takeoff weight of 8,000 pounds. Ultimate loads are defined as 1.5 times the limit loads. Februar y 2016, Revision D 9 CARAVAN The passenger entry door consists of an upper and lower section. When opened, the upper section swings upward and the lower section drops down providing integral steps to aid in boarding or exiting the airplane. The door open- ing is approximately 24 inches wide and 50 inches high. A two-piece cargo door is installed on the left side of the airplane aft of the wing trailing edge. The cargo door is divided into an upper and lower section. When opened, the upper section swings upward and the lower section opens 180 degrees forward providing a large 49 inch wide by 50 inch high opening in the side of the fuselage which facilitates the loading of bulky cargo into the cabin. The door opening is flush with the floor and has square corners for maximum cargo loading capability. The airplane is equipped with a two-piece plexiglass windshield reinforced with a metal center strip. Twelve side windows of the fixed type are installed in the cabin sides including one each in the two crew entry doors, two windows in the upper section of the cargo door and one window in the upper section of the passenger entry door. The windshield and forward crew door windows are 5/16 inch and 1/4 inch thick respectively. All other windows are 3/16 inch thick tinted plexiglass. 4. FUSELAGE GROUP (CONTINUED) The Caravan utilizes conventional wings with NACA 23000 Series Airfoils. The externally braced, fail-safe wings are constructed of front and rear spars with formed sheet metal ribs, doublers and stringers. The entire structure is covered with aluminum skin. The primary wing spars, wing carry-through spars in the fu- selage and attaching structure are of fail-safe construction for limit flight loads. Fail-safe construction assures that the structure is designed and built in such a way that should any single structural component fail, the remaining struc- ture is capable of carrying certified limit flight loads. 5. WING GROUP The empennage consists of a conventional vertical stabi- lizer, rudder, horizontal stabilizer and elevator, all of which are constructed of a forward and aft spar with formed sheet metal ribs and aluminum skin panels. The horizontal stabiliz- er contains dual jack screw type actuators for operating the elevator trim tabs. An elevator trim tab is attached to each elevator by full length piano-type hinges. Stabilizer abrasion boots are installed along the leading edge of the horizontal stabilizer. 6. EMPENNAGE GROUP Februar y 2016, Revision D 10 CARAVAN 8. PROPULSION 7. LANDING GEAR 8.1 POWERPLANT The propulsion system consists of a single fuselage mount- ed Pratt and Whitney PT6A-114A turboprop engine. The PT6A-114A is flat rated to 675 shp at 1900 RPM. The stan- dard time between overhaul for this engine is 3600 hours. Conventional turboprop controls are used to operate the engine and propeller. They consist of a power lever, emer- gency power lever, propeller control lever and a fuel condi- tion lever. The power and fuel condition levers are engine controls while the propeller control lever controls propeller speed. An emergency power lever is provided to manually control fuel supply to the engine should a malfunction occur in the fuel control unit. Engine operation is monitored by the engine indication sys- tem (EIS) which shows numeric readouts of critical engine, fuel and electrical indications for the following: torque, pro- peller speed, interstage temperature (ITT), gas generator % RPM (Ng), fuel flow, oil pressure, and oil temperature. A wet type standby engine torque gauge is also installed. An inertial separator system is built into the engine air inlet duct to prevent moisture particles from entering the engine inlet plenum. The inertial separator system is mechanically controlled by a push-pull handle located on the 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 of the engine compartment. Mounting provisions are provided for a standby ignition exciter unit. An engine trend recording device and an engine param- eter exceedance monitor will allow operators to monitor the health of the engine through periodic sampling of engine parameters. The engine trend monitor contains logic to de- termine when the aircraft is in a stable cruise flight regime before automatically taking a trend sample. This is an advisory system only. The airplane’s engine indica- tion system is still the primary source of detecting and cor- recting conditions where engine limitations are exceeded. There are no additional aircraft limitations and no perfor- mance change with the engine tend monitor installed. 8.2 PROPELLER The Caravan is equipped with a 106 inch diameter metal propeller. The three-blade, anti-ice, constant speed, full feathering, single acting, reversible pitch propeller is manufactured by McCauley, model 3GFR34C703. The pro- peller is controlled by a propeller governor and an over- speed governor mounted on and driven by the reduction gear-box. The overspeed governor acts as a safeguard against propeller overspeed should the primary propeller governor fail. The landing gear is of the non-retracting, tricycle type with a steerable nose wheel and two main wheels. Shock ab- sorption is provided by the tubular spring steel main land- ing gear struts with an inter-tube connecting the two outer tubes. The tires are tube-type; standard nose tire is 22 x 8.00 x 8, 6 ply and main gear tires are 8.50 x 10, 8 ply. The nose gear tire is mounted on an extended nose gear strut providing additional ground clearance. The nose gear shock absorption is provided by the oil snubber combined with a drag link spring providing vertical and aft displace- ment restraint. Each main gear wheel is equipped with a hydraulically actuated four piston brake. Nose gear steering is accomplished by using the rudder pedals which turns the nose wheel through an arc of ap- proximately 15° each side of center. By applying either left or right brake, the degree of turn may be increased up to 51.5° each side of center. The minimum turning radius of the airplane, using differential braking and nose wheel steering during taxiing, is 33 feet 8 inches. Februar y 2016, Revision D 11 CARAVAN 9. SYSTEMS 9.1 FLIGHT CONTROLS The Caravan’s flight control system consists of conventional aileron, elevator and rudder control surfaces. In addition, a pair of slot lip spoilers are mounted above the outboard ends of the flaps. The control surfaces are manually oper- ated through mechanical linkage using a control wheel for the ailerons, spoilers and elevator and rudder/brake pedals for the rudder. The rudder control utilizes a rudder pedal cable system driving 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 operation of the left-hand mounted brake cylinders. The brake cylin- ders have a remote reservoir mounted on the forward side of the engine firewall for convenient access. Rudder trim system consists of a trim wheel driving a flex shaft which, in turn, adjusts rudder pressure. The elevator control system features a conventional cable drive system. The elevator is connected to the cables by a bellcrank and push-pull rod. Elevator trim is accomplished through two elevator trim tabs by utilizing the vertically mounted trim control wheel on the control pedestal. An electric elevator trim system is avail- able with an autopilot installation. The aileron control system is a combination of cables, quad- rants, bellcranks and push-pull rods. A push-pull rod drives 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 system through 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 driven and incorporate a trailing edge angle with leading edge vor- tex generators to reduce stall speed and provide enhanced lateral stability. A selector and mechanical type follow-up in- dicator is provided in the control pedestal. The flap system consists 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 electric drive motor provides a back-up flap actuation system in the event of failure of the primary motor. 9.2 FUEL SYSTEM The Caravan fuel system consists of two vented integral fuel tanks (one in each wing formed by the front and rear spars), a fuel reservoir, engine fuel system, quantity and flow instrumentation, and the necessary lines, controls, valves and pumps to complete the system. Fuel system capacity is 335.6 U.S. gallons (332 gallons usable). Filling the fuel tanks is 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 or both at the same time. Fuel quantity is measured by four fuel level probes (two in each wing tank) and indicated on the engine indication sys- tem (EIS). The fuel quantity system is calibrated in gallons based on 6.7 pounds per gallon. Fuel quantity indications are displayed in pounds. Wing fuel level caution advisories, 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 is approximately 25 gallons or less. A warning advisory is also provided to indicate low fuel level in the fuel reservoir tank. 9.3 ELECTRICAL SYSTEM The Caravan is equipped with a 28-volt, direct-current elec- trical system. The system uses a 24-volt, 38 ampere-hour sealed lead acid as a source of electrical energy and a 200-amp engine-driven starter generator. (An optional 300- amp engine-driven starter generator is available.) Power is supplied to most general electrical and all avionics circuits through two general buses, two avionics buses and a bat- tery bus. The battery bus is energized continuously for ELT reset, clock, cabin/courtesy light functions and engine trend monitor processor. Februar y 2016, Revision D 12 CARAVAN 9. SYSTEMS (CONTINUED) A generator control unit provides the electrical control function necessary for the operation of the starter-generator. Electrical system operation can be monitored on the Engine Indication System (EIS) display on the MFD (in normal mode). Battery Amps and Battery Volts can be viewed on either EIS page (Engine or System). Generator and (Standby) Alternator Amps can be viewed on the EIS System page. The Crew Alert- ing System (CAS) Annunication Window is located on each Primary Flight Display (PFD) and can present appropriate mes- sages (i.e. warning, caution and advisory) pertaining to various engine and aircraft systems as may be applicable. 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 provided to prevent the external power and the battery from being con- nected together during starting, and incorporates polarity re- versal and overvoltage protection. The external power recep- tacle is installed on the left side of the engine compartment near the firewall. A standby electrical system is installed for use as a standby power source in the event the main generator system mal- functions in flight. The system includes a belt-driven alternator 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 are also included. 9.4 LIGHTING SYSTEM Exterior lighting consists of three navigation lights, two land- ing lights, two taxi/recognition lights, two strobe lights, a fl ashing beacon and two underwing courtesy lights. All ex- terior lights are controlled by toggle switches located on the lighting control panel on the left side of the instrument panel. The G1000 instrument panel incorporates LED backlighting controlled manually through the instrument panel dimmer bus. When the dimmer bus is not used, photocell technol- ogy automatically controls backlight adjustments to optimize display appearance through a broad range of cockpit light- ing conditions. Other miscellaneous lighting provided include pilot and co-pilot control wheel map lights, cabin/courtesy lights, passenger reading lights and a no smoking/seat belt advisory sign. 9.5 ENVIRONMENTAL SYSTEM The temperature and volume of airflow to the cabin is regu- lated by the cabin heating, ventilating and defrosting system. In the heating system, hot engine compressor outlet air is routed through system components to obtain the correct air temperature before air is routed to the cabin air distribution system. Controls are provided to direct the heated air to the forward and/or aft portions of the cabin for heating and to the windshield for defrosting. Outside ventilating air is obtained from an inlet on each side of the forward fuselage and through two ram air inlets, one on each wing at the upper end of the wing struts. The wing ven- tilating air is routed through the wing into a plenum chamber located in the center of the cabin top. The plenum distributes the ventilating air to individual overhead outlets at each seat position. The forward fuselage ram air inlets provide ventila- tion 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 operations, both on the ground or in flight. 9.6 PITOT-STATIC SYSTEM The left hand pitot-static system supplies ram air and static pressure to the number one AHRS (Attitude Heading Refer- ence System), and also to the standby altimeter. The system is composed of a heated pitot-static tube mounted on the lead- ing edge of the left wing, a static pressure alternate source valve, a drain valve located behind the instrument panel and the associated plumbing necessary to connect the instru- ments and sources. The right hand pitot-static system supplies ram air and static pressure to the number two AHRS. The system is composed of a heated pitot-static tube mounted on the leading edge of the right wing, a drain valve located behind the instrument panel, and associated plumbing. Februar y 2016, Revision D 13 CARAVAN 9.7 VACUUM SYSTEM A vacuum system provides the suction necessary to oper- ate the standby attitude indication. Vacuum is obtained by passing regulated compressor bleed air through a vacuum ejector. The vacuum system consists of the bleed air pres- sure regulator, a vacuum ejector, a vacuum relief valve, and a vacuum system air filter. The system is monitored via a warning flag on the standby attitude indicator. 9.8 GARMIN G1000 AVIONICS SYSTEM The integrated avionics system incorporates three 10-inch displays; the pilot’s primary flight display (PFD), the multi- function display (MFD) and the co-pilot’s PFD. The system includes a single audio system control panel and a separate autopilot controller. The fully integrated Garmin G1000 system will provide the following communication/navigation/surveillance (CNS) functions: Dual VHF NAV/Glideslope/Localizer receivers, dual VHF com transceivers, dual WAAS GPS receivers and Mode S transponders. The KN-63 DME is an integrated dis- play and offers NAV1/NAV2 switching. Crew alerts are dis- played on the PFD. The automatic flight control system (AFCS) incorporates a GFC-700 three-axis autopilot with pitch trim and GFC-710 autopilot controller. Avionics cooling is provided by two cowl deck fans and three display fans. The cowl deck fans are powered from the electrical bus. The display fans provide cooling air to each of the three display units and are powered from the display power circuits. Avionic circuit breakers are located on an exclusive panel located on the lower left-hand instrument panel. 9. SYSTEMS (CONTINUED) Februar y 2016, Revision D 14 CARAVAN 10. FLOATPLANE The Caravan floatplane provisions consist of hoisting rings, inboard fuel filling ports, extended chord rudder, short airstair door cables (loose equipment), and microphone relocation. The hoisting rings include four rings which attach to the left and right sides of both the front and rear spar wing-to-fuse- lage attach fittings. To gain access to the hoisting rings, it is necessary to remove the wing-to-fuselage fairing strips. Inboard fuel ports with anti-siphon doors provide an easily accessible fuel filler location when refueling on floats. Due to wing dihedral, use of inboard filler ports for refueling will reduce maximum usable fuel to 240 gallons. The extended chord rudder increases the surface area of the rudder to pro- vide greater control when floats are installed on the aircraft. The hand microphone is located on the center pedestal to al- low clearance for the emergency lever that is used to manu- ally lower the wheels on the floats. WIPLINE 8750 FLOAT INSTALLATION The Caravan can be converted to a floatplane or an amphib- ian when equipped with Wipline 8750 Series Floats manufac- tured, installed and warranted by Wipaire, Inc. (The optional 300-amp starter/generator is not compatible with this instal- lation.) The floats are part of a Wipaire, Inc. STC and are installed by Wipaire, Inc. after aircraft acceptance and delivery from Cessna Aircraft Company. Wipline floats are FAA certified and TSO approved, and meet Federal CAR-3.372 buoyancy regu- lations 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 fax info@wipaire.com http//www.wipaire.com. Februar y 2016, Revision D 15 CARAVAN 10. FLOATPLANE (CONTINUED) The Following Performance Figures Are Provided By Wipaire, Inc. And Have Not Been Tested By Cessna Aircraft Company. SPECIFICATIONS FOR THE 8750 AMPHIBIOUS FLOAT DIMENSIONS (EXTERNAL) Length (nose of float to extended water rudder)......................................................................................................................... Height - hull ............................................................................................................................................................................................. Width - hull ............................................................................................................................................................................................... WEIGHT Amphibious 8750 on the Cessna 208 Caravan .............................................................................................................. *Exchange = Float installation weight minus aircraft landing gear weight. PERFORMANCE FOR THE 8750 AMPHIBIOUS 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 take off weight ..................................................................................................................................................................... Maximum range* (cruise speed, 10,000 ft) ...................................................................................................................................... Stall speed (landing configuration) .................................................................................................................................................... Standard Empty Weight (Estimated) .................................................................................................................................................. Maximum Useful Load (Estimated) .................................................................................................................................................... *Range based on 332 gal. usable fuel and includes takeoff, climb, descent and 45 minute reserve. 31’-9” 3’-3” 3’-6” 1,678 lbs/1,142 lbs* 154 KTAS 1,431 ft 2,422ft 2,341 ft 3,660 ft 947 ft/min 20,000 ft 8,750 lbs 8,750 lbs 8,750 lbs 8,750 lbs 900 nmt 60 KCAS Amphibian 5,600 lbs 3,150 lbs Februar y 2016, Revision D 16 CARAVAN FIGURE III — CARAVAN INSTRUMENT PANEL AND PEDESTAL LAYOUT 11. STANDARD EQUIPMENT ( Some options may be shown ) Februar y 2016, Revision D 17 CARAVAN 11. STANDARD EQUIPMENT (CONTINUED) 11.1 AVIONICS Standard 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 Unit GRS 77 Dual Attitude and Heading Reference System (AHRS) GMA 1347 Single Audio System with Integrated Marker Beacon Receiver GTX 33 Mode S Transponder Garmin Relative Terrain/Obstacles Garmin Flight Charts Capable Garmin Safe Taxi Capable KN-63 DME Switch, Avionics Power (Two) (On-Off ) Artex ME-406 2-Frequency (Non-Nav Interfaced) ELT with Remote Switch and Monitor Light (Dorsal Fin Installation) Avionics Cooling, (2) cowl deck fans and (3) display fans PA System with Aft Cabin Speakers Cabin Headset Jacks 11.2 ENGINE INDICATION SYSTEM (EIS) Displayed on MFD During Normal Operations: Engine and Systems Displays - Show numeric readouts of critical engine, fuel and electrical indications and cal- culations for the following: Torque Interstage Turbine Temperature Gas Generator Speed Propeller Speed Oil Pressure Oil Temperature Fuel Quantity Fuel Flow Ammeter/Voltmeter Standby Engine Instrument: Engine Torque Gauge, Wet Type Engine Trend Monitoring System 11.3 FLIGHT INSTRUMENTS Indications Displayed on each PFD: Airspeed Attitude with Slip/Skid Indication Altitude Vertical Deviation, Glideslope and Glidepath Vertical Speed Horizontal Situation Indication Outside Air Temperature System Time Generic Timer Wind Data Standby Instruments Airspeed Indicator Attitude Gyro Altimeter Magnetic Compass Heated Pitot System, Pilot & Co-Pilot Alternate Static Source Static Source Drains Instrument Static System Second Independent Pitot-Static System 11.4 FLIGHT CONTROLS Brake, Parking Brakes, Hydraulic, Toe-Operated Control Cables — Corrosion Resistant Steel Control Lock, Ailerons and Elevator Flight Control System, Pilot & Co-Pilot (Includes All-Pur- pose Control Wheel Friction Lock, Engine Controls Powerplant, Quadrant Type Controls: Condition Lever Primary Engine Power (Power Control Lever) Back-Up Engine Power (Emergency Power Lever) Propeller, Speed and Feather Rudder, Extended Chord Rudder Gust Lock Trim System (Aileron/Rudder (Manual), Elevator (Manual & Februar y 2016, Revision D 18 CARAVAN Electric Pilot & Co-Pilot) Wing Flaps, Electric Pre-Select with Standby Motor 11.5 ENVIRONMENTAL Defroster, Windshield (Pilot and Copilot) Heating System, Cabin (Bleed Air Type) Soundproofing Ventilation System, Cockpit (Ram Air) Ventilator, Adjustable, Cabin Air Ventilation System, Fan Driven 11.6 ELECTRICAL POWER Battery, 24 Volt, 38 Amp-Hr, Sealed Lead-Acid Battery Switch (On-Off ) Circuit Breakers, Electrical Generator Control Unit Generator Switch (Trip-On-Reset) Ground Service Plug Receptacle Starter/Generator, 200 Amp Generator Control Unit Mounting (Provisions for Mounting Standby Unit) Power Outlet(s), 12V Cockpit And Cabin Standby Electrical System, 75 amp 11.7 EXTERIOR LIGHTS Beacon – Omni Flash (Red) Courtesy, Under Wing Ice Detection Landing, 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) 11.8 INTERIOR LIGHTS LED Backlit Instrument Panel Lighting Map Light Control Wheel Mounted, Pilot & Co-Pilot (Vari- able Intensity) Overhead Courtesy (3) (Aisle, Aft Cargo Area and Passenger Door) Overhead Flood (Pilot and Copilot) (3) Passenger Reading Lights (8) Dimming Controls, Switch Panel, Avionics Circuit Breaker Panel, Left Hand Panel & Environmental Panel 11.9 POWERPLANT Chip Detector Installation Cowling, Rigid-Mounted (Quick Removable) Lower and Easily Openable Upper Sides Cowl Locks Engine Inlet Cover (2) & Propeller Tie-Down Sleeve Engine, Turboprop PT6A-114A, 675 SHP, 3600 TBO Engine Wash Ring (Integral) Engine Support, Vibration Isolation Filter, Integral, Full Flow Oil Fire Detection System, Engine Compartment Ignition System Excitor Unit Mounting (Provisions for Mounting Standby Unit) Ignition System (Dual Ignitors) Intake Inertial Separator (Manual) Oil Cooler, High Capacity Overspeed Governor Propeller, 3 Blade Aluminum, Anti-Ice, Constant Speed, Full Feathering, Reversible – McCauley Propeller Governor Propeller Spinner (Polished) Shielding, Engine Ignition Shutdown Fuel Collector, Engine Valve, Oil Quick Drain 11.10 FUEL SYSTEM Fuel Boost Switch, Auxiliary Fuel Caps with Anti-Siphon Doors Fuel Control Heater, Engine Fuel Filling Ports, (4) Fuel Filter with Quick Drain Fuel Low Level Warning System Fuel Pump, Auxiliary (Electric) Fuel Pump, Engine Fuel Reservoir with Quick Drain Fuel Selector Valves Fuel Shutoff Valve 11. STANDARD EQUIPMENT (CONTINUED) Februar y 2016, Revision D 19 CARAVAN 11. STANDARD EQUIPMENT (CONTINUED) Fuel Tanks, 332 Gallons Usable Fuel Valves, Quick Drain (8) Fuel Vents, Non-Icing Fuel Sampler Cup 11.11 INTERIOR Aircraft Keys Approach Plate Holder, L.H. & R.H. Baggage Area Partition Net Baggage Tie-Down Straps (4) Beverage Cup Holders (Pilot and Copilot) Cargo Tie-Down Fittings Provisions Cargo Tie-Down Fittings (Baggage Area) Checklist, Pilot’s (Laminated) Crew Door Storage Area LH, RH De-Ice Partial Plumbing (Wing & Stabilizers) Fire Extinguisher Cabin– Hand Type Floor Covering, Lightweight Vinyl Glareshield Handbook, Customer Care, Includes Engine/Flight Logs, Warranty, Etc. Handbook, Pilot’s Operating Headliner – Vinyl Instrument Panel – Metal Map/Glove Compartment Oxygen System, Partial Installation (Consists of Difficult to Install Plumbing) Pilot and Co-pilot Restraint – Integral 5 Point Lap and Shoulder Harness with Inertial Reel Pilot’s LH Pre-Flight Assist Handle Plotter, Weight & Balance (Cargo & Passengers) Pockets, Map and Storage Recorder, Flight Hour Relocated Microphone Installation Seats, Pilot & Copilot, Adjustable Fore, Aft and Vertical with Articulating Recline and Arm Rest Sign, Fasten Seat Belts & No Smoking Step, Cabin Entrance, Retractable (LH & RH Crew Entry Doors) Sunvisors Window, Foul Weather, Pilot Door Windows Tinted All-Around 11.12 EXTERIOR Anti-Precipitation Static Kit Bonding Straps, Control Surface (Aileron, Elevator and Rudder) Cargo Pod Provisions with Straight Stack Corrosion Proofing, External Door, Cargo, Two-Piece (Left Side of Aircraft, with Upper Door 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 Rings Jack Points (Fuselage and Main Landing Gear) Landing Gear, Fixed, Nose, Steerable Landing Gear, Fixed, Main Lock, Key-Operated (One Key Fits All Doors) Paint, All Over (Modified Polyurethane) Stabilizer Abrasion Boots Stall Warning System, Heated Tires, 8.50 x 10, 8 Ply Main, 22 x 8.00, 6 ply Nose With Extended Nose Gear Fork Tie-Down Provisions, Aircraft Tow Bar Februar y 2016, Revision D 20 CARAVAN 12.DOCUMENTATION AND TECHNICAL U.S. Standard Airworthiness Certificate, FAA8100-2; Export Certificate of Airworthiness, FAA8130-4 or Special Airwor- thiness Certificate FAA8130-7 as appropriate; Equipment List Weight and Balance Report Garmin Cockpit Reference Guide Pilot’s Operating Handbook FAA Approved Airplane Flight Manual Pilot’s Abbreviated Checklist Log Books (Aircraft and Engines) Additional Miscellaneous Information Concerning Engine and Airframe Support; Passenger Briefing Cards CAMP/CESCOM Instruction Manual CESSNA TECHNICAL INFORMATION Cessna makes available a complete system of manuals and catalogs for the operation and maintenance of the Caravan. All Cessna and related technical information is listed on www.cessnasupport.com. Cessna manuals are kept current through periodic revi- sions. Aircraft operators and designated maintenance facilities can receive these revisions through a subscription service. The subscription is free for the first year to owners of new aircraft. A subscription fee is charged thereafter. The following manuals are provided on DVD, download, online or Mobile App for iPad with the purchase of a new Caravan: Service Maintenance Manual Illustrated Parts Catalog Wiring Diagram Manual Structural Repair Manual Service Bulletins Avionics Wiring Diagram (custom diagram of the actual avionics installation) The following materials are provided by Pratt & Whitney Canada: Combined Engine Maintenance Manual & Illustrated Parts Catalog (available online at the P&WC portal) One set Engine Service Bulletins Including Spare Parts Bulletins and Service Information Letters (available online at the P&WC portal) Free revision coverage for one year Service Bulletins are also available by on-line or e- mail subscription at www.pwc.ca or through the Pratt and Whitney Help Desk at (800) 268-8000. CESSNA REVISION STATUS CHECKLIST The Revision Status Checklist is used to verify that only the most current Cessna maintenance and aircraft operation publications are in use. The checklist is available monthly on www.cessnasupport.com. CESSNA OWNER ADVISORY Cessna Owner Advisories provide owners of Cessna air- craft up-to-the-minute information about mandatory service requirements and the latest in product improvements. Own- er Advisories summarize new Service Bulletins or Service Letters and indicate any action required by the owner, the time required for the owner to comply, and the existence of any associated “credit allowances.” Cessna Owner Advisories are mailed automatically to own- ers of U.S. registered Cessna aircraft using the latest name and address provided to the FAA. Owner Advisories can be mailed to a different address by request, provided the subject aircraft is still covered by Cessna warranty. International owners of Cessna aircraft covered by Cessna warranty receive Owner Advisories through a complimentary subscription. After warranty expiration, in- ternational subscriptions are available, although a subscrip- tion fee will be charged. Revisions for the Pilot’s Operat- ing Handbook and/or Log of Approved Supplements are included with the Owner Advisory when applicable. PUBLICATIONS Februar y 2016, Revision D 21 CARAVAN PROPARTS A professional aircraft parts support program co-managed through the contract holder and Cessna Service Parts & Programs providing fixed price coverage for all airframe systems, avionics components and wear / TBO items for fi ve years or 3,000 hours, whichever occur first and annual minimum of 100 hours per contract year. Additional details available on request. (Separate agreement required.) COMPUTERIZED MAINTENANCE RECORD SERVICE Seller will provide a computerized maintenance record service for one (1) full year from the date of delivery of a Caravan to the purchaser. Currently, this service is provid- ed by CAMP Systems International, Inc. This service will provide owners and operators with the reports necessary for the efficient control of maintenance activities. It will provide an accurate and simple method of keeping up with aircraft components, inspections, service bulletins and airworthiness directives while providing per- manent aircraft records of maintenance performed. Reports will be available which reflect the aircraft status, up- coming scheduled maintenance and a recap of the previous month’s reported maintenance activity. Semi-annual reports concerning projected annual maintenance requirements, component removal history and fleet-wide component reli- ability will also be available. The on-line system is the standard service, however, a pa- per service is available at an additional charge. The on-line system is accessible using a local computer with Internet capability. Data is electronically transferred through Internet connections between the customer and CAMP on a regular basis to keep information up-to-date at both locations. In addition to the standard reports, customer specific reports and maintenance records can be generated at the local computer whenever the customer wishes. DATA ACQUISITION SYSTEM A data acquisition system is provided as standard equip- ment on the Caravan to allow operators to easily monitor and maintain the aircraft engine. This system records engine parameters, indicated airspeed, pressure altitude, outside air temperature, flight hour meter, battery voltage, and the positions of the particle separator, emergency power lever and bleed air cabin heat switch. Data retrieval is handled using a special software program installed on a laptop or handheld computer. Data delivery is handled using the computer to transfer the aircraft data to the Turbine Tracker website. The Turbine Tracker website formats the data into customized reports for use as analysis tools. *Certain other requirements are met as stipulated by Pratt & Whitney “On condition” hot sections are hot sections accomplished only when necessary, which results in significantly reduced operating costs. Open Account Information With an active open account, Caravan owners are able to purchase spare parts at the current published list price di- rectly from Cessna Parts Distribution. The open account can also be used to purchase Cessna publications and other items. 13. MAINTENANCE PROGRAMS Februar y 2016, Revision D 22 CARAVAN 14. LIMITED WARRANTIES The standard Caravan Aircraft Limited Warranty which cov- ers the aircraft, other than the Pratt & Whitney Canada (P&WC) engine and associated engine accessories, the Honeywell avionics, and the McCauley propeller which are warranted separately, is set forth below. Seller specifically excludes vendor subscription services and the availability of vendor service providers for Optional and Customer Re- quested Equipment (CRQ) from Seller’s Limited Aircraft War- ranty. Following Seller’s Limited Warranty, the engine and engine accessory warranty of P&WC, the avionics warranty of Honeywell, and the propeller warranty of McCauley are set forth. All warranties are incorporated by reference and made part of the Purchase Agreement. All warranties are administered by Seller’s Warranty Department. 14.1 CESSNA CARAVAN LIMITED WARRANTY (LIMITED WARRANTY) Seller expressly warrants each new Caravan Aircraft (exclu- sive of engine and engine accessories supplied by P&WC, avionics supplied by Honeywell, and the propeller supplied by McCauley, which are covered by their separate warran- ties), including other factory-installed avionics and other factory-installed optional equipment to be free from defects in material and workmanship under normal use and service for the following periods after delivery: (a) One (1) year unlimited hours OR two (2) years /1,000 hour limit on all aircraft components manufactured by Seller; (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 Seller unless otherwise stated in the Optional Equipment and Selection Guide; (e) One year for CRQs, Interior Components, Interior Fur- nishings, and Paint. Any remaining term of this Limited Warranty is automatically transferred to subsequent purchasers of the aircraft. Seller’s obligation under this Limited Warranty is limited to repairing or replacing, in Seller’s sole discretion, with ex- change, overhauled, or new parts, any part or parts which: (1) fail within the applicable warranty period, (2) are returned at the warranty recipient’s expense to the facility where the replacement part is procured, whether through Seller Service Parts & Programs or a service facility authorized by Seller to perform service on the aircraft (collectively “Sup- port Facility”), (3) are accompanied by a properly executed claim form, and (4) are found by Seller or its designee to be defective. Replacement parts must be procured through a Support Fa- cility and are only warranted for the remainder of the appli- cable original aircraft warranty period. A new warranty pe- riod is not established for replacement parts. The repair or replacement of defective parts under this Limited Warranty will be made by a service facility authorized by Seller to per- form service on the aircraft (“Authorized Service Facility”) without charge to the warranty recipient for parts and/or la- bor for removal, installation, and/or actual repair of such de- fective parts. All expedited freight, transportation expenses, import duties, customs brokerage fees, sales taxes, and use taxes, if any, on such warranty repairs or replacement parts are the warranty recipient’s sole responsibility. (Location of Authorized Service Facilities will be furnished by Seller on request.) This Limited Warranty applies to only items detailed herein which have been used, maintained, and operated in accor- dance with Seller and other applicable manuals, bulletins, and other written instructions. However, this Limited War- ranty does not apply to items that have been subjected to misuse, abuse, negligence, accident, or neglect; to items that have been installed, repaired, or altered by repair fa- cilities not authorized by Seller; or to items that, in the sole judgment of Seller, have been installed, repaired, or altered by other than Authorized Service Facilities contrary to ap- plicable manuals, bulletins, and/or other written instructions provided by Seller so that the performance, stability, or re- liability of such items are adversely affected. This Limited Warranty does not apply to normal maintenance services (such as engine adjustments, cleaning, control rigging, brake and other mechanical adjustments, and maintenance Februar y 2016, Revision D 23 CARAVAN inspections); or to the replacement of service items (such as brake linings, lights, filters, hoses, belts, tires, and rub- ber-like items); or to normal deterioration of appurtenances (such as paint, cabinetry, and upholstery), corrosion or struc- tural components due to wear, exposure, and neglect. WITH THE EXCEPTION OF THE WARRANTY OF TITLE AND TO THE EXTENT ALLOWED BY APPLICABLE LAW, THIS LIMITED WARRANTY IS EXPRESSLY IN LIEU OF ANY OTHER WARRANTIES, EXPRESSED OR IMPLIED, IN FACT OR BY LAW, APPLICABLE TO THE AIRCRAFT. SELLER SPECIFICALLY DISCLAIMS AND EXCLUDES ALL OTHER WARRANTIES, INCLUDING, BUT NOT LIMITED TO, ANY IMPLIED WARRANTY OF MERCHANTABILITY OR FIT- NESS FOR A PARTICULAR PURPOSE. THE AFOREMEN- TIONED REMEDIES OF REPAIR OR REPLACEMENT ARE THE ONLY REMEDIES UNDER THIS LIMITED WARRANTY. SELLER EXPRESSLY AND SPECIFICALLY DISCLAIMS ALL OTHER REMEDIES, OBLIGATIONS, AND LIABILITIES, IN- CLUDING, BUT NOT LIMITED TO, LOSS OF AIRCRAFT USE, LOSS OF TIME, INCONVENIENCE, COMMERCIAL LOSS, LOSS OF PROFITS, LOSS OF GOODWILL, AND ANY AND ALL OTHER CONSEQUENTIAL AND INCIDEN- TAL DAMAGES. SELLER NEITHER ASSUMES NOR AU- THORIZES ANYONE ELSE TO ASSUME ON ITS BEHALF ANY FURTHER OBLIGATIONS OR LIABILITIES PERTAIN- ING TO THE AIRCRAFT NOT CONTAINED IN THIS LIM- ITED WARRANTY. THIS LIMITED WARRANTY 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 WICHI- TA, KANSAS. THE PARTIES HERETO CONSENT TO PER- SONAL JURISDICTION IN THE FORUM CHOSEN. 14.2 PRATT & WHITNEY CANADA INC. (AB- BREVIATED NEW ENGINE WARRANTY) Pratt & Whitney Canada Inc. (P&WC) warrants that each new PT6A-114A engine complete with installed accessories at time of delivery will be free from defects in material and manufacture. P&WC’s liability and purchaser’s remedy un- der this warranty are limited to the repair or replacement at P&WC’s option of goods returned to P&WC or to a loca- tion designated by P&WC which are shown to P&WC’s rea- sonable satisfaction to have been defective, provided that written notice of defect shall have been given by Purchaser to P&WC or its designee within one thousand (1,000) flying hours after delivery of the engine to the first user. The repair or replacement of defective goods under the Warranty will be made by P&WC or its designee without charge for parts or reasonable labor for removal, installation and/or actual repair of such defective goods, and reasonable transpor- tation charges, except import duties, sales or use taxes, if any, on replacement. Transportation charges for the return of defective goods to P&WC or its designee and their re- shipment to Purchaser and the risk of loss thereof will be borne by P&WC. THE FOREGOING WARRANTIES ARE EXCLUSIVE AND ARE GIVEN AND ACCEPTED IN LIEU OF ANY AND ALL OTHER WARRANTIES, EXPRESSED OR IMPLIED, IN- CLUDING WITHOUT LIMITATION THE IMPLIED WAR- RANTY OF MERCHANTABILITY AND ANY OBLIGATION, LIABILITY, RIGHT, CLAIM OR REMEDY IN CONTRACT OR TORT WHETHER OR NOT ARISING FROM P&WC’S NEG- LIGENCE, ACTUAL OR IMPUTED. THE REMEDIES OF THE PURCHASER FOR ANY BREACH OF WARRANTY SHALL BE LIMITED TO THOSE PROVIDED HEREIN TO THE EX- CLUSION OF ANY AND ALL OTHER REMEDIES INCLUD- ING, WITHOUT LIMITATION, INCIDENTAL OR CONSE- QUENTIAL DAMAGES. NO VARIATION OR EXTENSION OF THE FOREGOING WARRANTIES, REMEDIES OR THIS LIMITATION WILL BE BINDING UPON P&WC UNLESS AP- PROVED IN WRITING BY A DULY AUTHORIZED OFFICER OF P&WC. The above abbreviated warranty is for the purposes of the Specification and Description. For complete details of the PT6A-114A engine warranty, please refer to P&WC’s full PT6A-114A warranty policy. 14.3 HONEYWELL/BENDIX/KING WARRANTY A. General Aviation Avionic products manufactured by Hon- eywell/Bendix/King, General Aviation Division (collectively referred to herein as “Honeywell/Bendix/King”) are war- ranted against defects in design, material or workmanship caused by Honeywell/Bendix/King or its authorized agent(s) for the Warranty Period as defined in Paragraph (B) of this 14. LIMITED WARRANTIES (CONTINUED) Februar y 2016, Revision D 24 CARAVAN statement which occur under normal and intended use and service, subject to all of the qualifications and conditions hereinafter stated. 1. Warranty coverage is only offered to purchasers who make warranty registrations within eighteen (18) months of the product’s factory shipping date. Dem- onstration or stock aircraft usage is restricted to 100 hours service prior to warranty registration. Warranty coverage, therefore, may be unavailable or limited, de- pending upon the usage or time the product in ques- tion may have remained unsold in the custody of the O.E.M. (Original Equipment Manufacturer), his agent, or the retail dealer, a matter as to which the seller is ex- pected to maintain accurate records and provide same, upon demand, to any purchaser or Honeywell/Bendix/ King. 2. Warranty coverage for products otherwise not eli- gible by reason of expiration of the eighteen (18) month period specified above may again become eligible for warranty protection, provided (a) that warranty registra- tion occurs within thirty (30) months of the product’s factory shipping date and (b) that the products are sub- mitted to Honeywell/Bendix/King for inspection and certification and then the promulgated Honeywell/Ben- dix/King certification fee is paid. B. The Warranty Period for products shall begin upon the date 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 following procedures: 1. Products shall be returned to an authorized Honey- well/Bendix/King Service Center or Honeywell/Bendix/ King Regional Product Support Repair/Overhaul Facil- ity, with transportation charges prepaid. 2. After correction, the products shall be returned to the purchaser with surface transportation charges prepaid, except for returns to purchasers in foreign countries. 3. The risk of loss or damage to all products in transit shall be borne by the party initiating the transportation of such products unless the purchaser makes a request for a specific mode of transportation. In such case, the risk of loss and the cost of shipment shall be borne by the purchaser. All items repaired or replaced hereunder shall be warranted for the unexpired portion of the original Warranty Period. D. This warranty specifically excludes defects which Honey- well/Bendix/King determines to be the result of: 1. Abuse, accident, or misuse; 2. Contamination, negligence, tampering, or improper storage or maintenance; 3. Repair or attempted repair by unauthorized persons or use of non- Honeywell/Bendix/King or unau- thorized repair or replacement parts; or 4. Products not installed by an authorized Honeywell/ Bendix/King Installation Facility in accordance with the appropriate installation manual. E. The Warranty as set out in paragraph (A) is the only war- ranty for Honeywell/Bendix/King General Aviation Avionics Products and is in lieu of all other warranties express or implied, including the implied warranties of merchantability and fitness for a particular purpose which are herewith ex- pressly excluded and disclaimed. F. The remedies as set out in Paragraph (C) hereof state the entire liability of Honeywell/Bendix/King and constitute the sole and exclusive remedy of the purchaser. Honeywell/ Bendix/King shall not be liable for any other claim, loss, or damage, including, but not limited to incidental, consequen- tial, or other kinds of damages whether based on contract, tort, negligence, or other theory of product liability. G. Honeywell/Bendix/King reserves the right to make de- sign changes, additions to, and improvements in its prod- ucts without the obligation to install same in products previ- ously manufactured. 14. LIMITED WARRANTIES (CONTINUED) Februar y 2016, Revision D 25 CARAVAN 14.4 MCCAULEY LIMITED WARRANTY McCauley Propeller Systems, a Division of Textron Avia- tion, Wichita, Kansas, U.S.A., expressly warrants its new or remanufactured products therefore sold by McCauley to be free from defects in material and workmanship under nor- mal use and service for a period of thirty six (36) months after delivery to the original retail purchaser. McCauley’s obligation under this warranty is limited to re- pairing or replacing, at its option, any part or parts which, within the thirty six (36) month period as above set forth shall be returned transportation charges pre-paid to Mc- Cauley at Wichita, Kansas or to any McCauley appointed Service Facility authorized by such appointment to service the McCauley product of the type involved and which upon examination shall disclose to McCauley’s satisfaction to have been thus defective. Any remaining term of this Lim- ited Warranty is transferable to subsequent purchasers. The repair or replacement of defective parts under this war- ranty will be made by McCauley or its authorized Service Facilities without charge for parts or labor for the actual re- pair 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 McCau- ley products or service parts therefor which have been sub- ject to misuse, negligence or accident or which shall have been repaired or altered outside of McCauley’s factory in any way so as in the judgment of McCauley to affect ad- versely its performance, stability or reliability nor to normal maintenance service. To the extent allowed by applicable law, THIS WARRANTY IS EXPRESSLY IN LIEU OF ANY OTHER WARRANTIES, EX- PRESSED OR IMPLIED IN FACT OR BY LAW, INCLUDING ANY IMPLIED WARRANTY OF MERCHANTABILITY OR FIT- NESS FOR A PARTICULAR PURPOSE. THE REMEDIES OF REPAIR OR REPLACEMENT AS ABOVE SET FORTH ARE THE ONLY REMEDIES UNDER THIS WARRANTY. McCAU- LEY DISCLAIMS ANY OBLIGATION OR LIABILITY WHETHER IN CONTRACT OR IN TORT (AND WHETHER FOR NEGLI- GENCE, STRICT LIABILITY, PRODUCT LIABILITY OR OTHER- WISE), INCLUDING LOSS OF USE OF THE PRODUCT WAR- RANTED, LOSS OF TIME, INCONVENIENCE, COMMERCIAL LOSS OR ANY OTHER DIRECT, CONSEQUENTIAL, SPECIAL OR INCIDENTAL DAMAGES. THIS WARRANTY IS IN LIEU OF ANY OTHER OBLIGATION OR LIABILITY ON THE PART OF McCAULEY TO ANYONE OF ANY NATURE WHATSO- EVER by reason of the manufacture, sale, lease or use of the warranted products and McCauley neither assumes nor authorizes anyone to assume for it any other obligation or liability in connection with such warranted products. 14. LIMITED WARRANTIES (CONTINUED) Februar y 2016, Revision D 26 CARAVAN 15. CARAVAN CREW TRAINING AGREEMENT Training for one (1) Caravan Crew will be furnished to First Retail Purchaser (hereinafter called the “Purchaser”), sub- ject 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) me- chanic 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 certified to provide training to proficiency in accordance with train- er’s standards. b. In lieu of a model specific simulator, training will be pro- vided in the most appropriate type simulator available. c. Location of training to be Wichita, Kansas, unless mu- tually agreed otherwise. The organization conducting the training is hereinafter called the “Trainer.” 3. Training furnished shall consist of the following: a. Flight simulation training to simulator proficiency in accordance with Trainer’s standards but not to exceed seven and one half (7.5) total hours for each pilot. b. Ground School training for each pilot and classroom instruction for each mechanic in accordance with Train- er’s standards. c. Flight training to flight proficiency in accordance with Trainer’s standards not to exceed five (5) total hours per pilot, shall be conducted in the customer’s aircraft. 4. Purchaser shall be responsible for: a. Transportation of crew to and from training site and for living expenses during training. b. Providing an interpreter during the course of training for any of Purchaser’s crew not conversant with the Eng- lish language. c. Payment to Trainer for additional simulator or flight training beyond that required to attain proficiency in accordance with Trainer’s standards for the course in which the pilot is enrolled. d. All aircraft for flight training as well as all landing fees, fuel costs, aircraft maintenance and insurance and all other direct costs of operation, including applicable taxes required in connection with the operation of said aircraft during such flight training. e. Extra charges, if any, for scheduling pilots in separate training classes. f. Reimbursing to Cessna the retail rate for training in the event of training before actual sale/delivery, if sale/ delivery is cancelled. 5. Seller or Trainer shall schedule all training, furnish Pur- chaser schedules of training and endeavor to schedule training at a convenient time for Purchaser. A cancellation fee of Two Hundred Dollars ($200) will be paid by Purchas- er if crew fails to appear for scheduled training, except for reasons beyond its reasonable control, unless Purchaser gives Seller written notice of cancellation received at Wich- ita, Kansas, at least seven (7) days prior to scheduled train- ing. In the event of such cancellation Seller shall reschedule training for the next available class. 6. Neither Seller nor Trainer shall be responsible for the competency of Purchaser’s crew during and after training. Trainer will make the same efforts to qualify Purchaser’s crew as it makes in training of other Caravan crews; how- ever, Seller and Trainer cannot guarantee Purchaser’s crew shall qualify for any license, certificate or rating. 7. Neither Seller nor Trainer shall be responsible for any de- lay in providing training due to causes beyond its or their reasonable control. 8. All Training furnished to Purchaser under the Agree- ment will be scheduled to commence no earlier than three (3) months prior to delivery and will be completed within twelve (12) months after delivery of the aircraft unless mutu- ally agreed otherwise. Signature of the Purchaser to the Purchase Agreement to which this Training Agreement is attached as a part of the Specification and Description shall constitute acceptance by Purchaser of the foregoing terms and conditions relative to training to be furnished by Seller. U.S. + 1.844.44.TXTAV | INTERNATIONAL +1.316.517.8270 | TXTAV.COM © 2016 Textron Aviation Inc. The names of aircraft manufactured by Textron Aviation Inc. (“TAI”) (or formerly by its subsidiaries Cessna Aircraft Company (“Cessna”) and Beechcraft Corporation (“Beechcraft”) including Hawker aircraft); some names for products or services of TAI, Cessna, Beechcraft or their subsidiaries, and logos are registered trademarks or registered service marks or trademarks or service marks of Textron Innovation Inc., used by permission, or Beechcraft whether or not appearing in large print, with trade marking symbols or otherwise denoting rights to or ownership of the same. Third party products names, marks, etc., whether or not appearing in large print or with trade marking symbols or otherwise denoting right or ownership of the same, belong to their respective owners. February 2016 S&D-208-0580