SPECIFICATION AND DESCRIPTION
GRAND CARAVAN EX
February 2016
Revision D
Units 208B-5265 to TBD
GRAND CARAVAN EX
SPECIFICATION
AND DESCRIPTION
UNITS 208B-5265 TO TBD
FEBRUARY 2016
REVISION D
C e ssna A irc raft C ompany
P.O. B ox 7 7 06
W ic hita, Kansas 6 7 27 7 -7 7 06
GRAND CARAVAN EX
INTRODUCTION
This “Specification and Description” is published for the
purpose of providing general information for the evaluation
of the design, performance and equipment of the Cessna
Grand Caravan EX aircraft. Should more detailed data be
required, it can be obtained by contacting:
Cessna Aircraft Company
P.O. Box 7704
Wichita, Kansas 67277
Telephone: 316-517-6081
Fax: 316-517-7850
Also included is the Cessna warranty applicable to the
Cessna Model 208B Grand Caravan EX aircraft and the
Caravan Crew Training Agreement. In the event of any conflict or discrepancy between this document and the basic
purchase agreement to which it may be appended, terms
specified in the basic purchase agreement govern.
Due to the time span between the date of this Specification
and Description and the scheduled delivery date of the aircraft, Cessna reserves the right to revise the “Specification
and Description” whenever occasioned.
This document describes only the Cessna Model 208B
Grand Caravan EX aircraft, Unit Serial Number 5265 and
on, and its powerplant and equipment.
WARNING: This product contains Halon 1211, Halon 1301, and also R-134A. Furthermore, the product was manufactured
with CFC-12 and 1-1-1 Trichloroethane, substances which harm public health and environment by destroying ozone in the
upper atmosphere.
Februar y 201 6, Revision D
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GRAND CARAVAN EX
TABLE OF CONTENTS
CESSNA GRAND CARAVAN EX SPECIFICATION AND DESCRIPTION
SECTION
1.
2.
3.
4.
5.
6.
7.
8.
PAGE
General Description ............................................................................................................................................................
Performance .........................................................................................................................................................................
Structural Design Criteria ................................................................................................................. .................................
Fuselage Group ................................................................................................................................ ...................................
Wing Group ..........................................................................................................................................................................
Empennage Group .............................................................................................................................................................
Landing Gear .................................................................................................................................... ....................................
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.
Floatplane . ............................................................................................................................................................................
11.
Standard Equipment
11.1 Avionics .......................................................................................................................................................................
11.2 Engine Instruments ..................................................................................................................................................
11.3 Flight Instruments .....................................................................................................................................................
11.4 Flight Controls ..................................................................................................................... ......................................
11.5 Environmental ............................................................................................................................................................
11.6 Electrical Power ........................................................................................................................................................
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 Grand Caravan EX Limited Warranty ....................................................................................................
14.2 Pratt & Whitney Canada Inc. ..................................................................................................................................
14.3 Honeywell/Bendix/King Warranty .........................................................................................................................
14.4 Hartzell Limited Warranty .......................................................................................................................................
15.
Grand Caravan EX Crew Training Agreement ..............................................................................................................
FIGURE I — GRAND CARAVAN EX EXTERIOR DIMENSIONS ..................................................................................................
FIGURE II — GRAND CARAVAN EX INTERIOR DIMENSIONS ................................................................................................
FIGURE III — GRAND CARAVAN EX INSTRUMENT PANEL AND PEDESTAL LAYOUT ...................................................
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Februar y 201 6, Revision D
GRAND CARAVAN EX
1. GENERAL DESCRIPTION
1. GENERAL DESCRIPTION
1.1 CERTIFICATION
The Cessna Grand Caravan EX is an unpressurized single-engine high wing turboprop aircraft with fixed landing gear. The aircraft can accommodate up to 14 persons
including a minimum crew of one. (Operations with more
than nine passengers must be approved by the registering country’s aviation authority.) Suitable allowance for
luggage and optional equipment is also provided.
Certification basis is to U.S. FAA FAR Part 23 Requirements—day, night, VFR, IFR and flight-into-icing conditions when equipped with the appropriate options. Export
certification requirements may require additional equipment and charges.
The powerplant is a Pratt and Whitney of Canada PT6A140 turboprop engine mounted in the nose of the aircraft
fuselage.
POWERPLANT .............................................................................. Pratt & Whitney PT6A-140 867 shp @ 1900 rpm
PROPELLER...................... Hartzell, Constant Speed, Full Feathering, Reversible Pitch, 3 Blades, 106 in. Diameter
LOADING
Wing .......................................................................................................................................................................................
31.49 lb/ft2
Power .....................................................................................................................................................................................
10.15 lb/shp
Februar y 201 6, Revision D
3
GRAND CARAVAN EX
1. GENERAL DESCRIPTION
(CONTINUED)
52 ft 1in
11 ft 8 in
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 13’-3 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. Hartzell propeller
ground clearance with
standard tires and extended nose gear strut:
Nose tire inflated and
nose gear barrel extended
3 5/8”: 14 3/4”.
20 ft 6 in
Nose tire deflated and nose strut
fully compressed: 5 7/8”.
15 ft 1 in
MAX
41 ft 7 in
FIGURE I — GR AND CAR AVAN EX EX TERIOR DIMENSIONS
4
(Shown with Optional Cargo Pod Installed)
Februar y 201 6, Revision D
GRAND CARAVAN EX
1. GENERAL DESCRIPTION
51 in
18 in
(CONTINUED)
54 in
46 in
52 in
17 ft 10 in
24 in
Stations
100
332
282
118
53 in
*591/2 in
**64 in
*54 in
**62 in
*51 in
**53 in
356
*42 in
**46 in
21 ft 4 in
117/8 in
35 in
413/4 in
*243/8 in
443/4 in
50 in
24 in
317/8 in
355/8 in
49 in
50 in
24 in
FIGURE II — GR AND CAR AVAN EX INTERIOR DIMENSIONS
Februar y 201 6, Revision D
*Dimensions at cabin floor **Dimensions at lower window line
5
GRAND CARAVAN EX
1. GENERAL DESCRIPTION
(CONTINUED)
1.2 APPROXIMATE DIMENSIONS
Overall Height .....................................................................................................................................................................................
15 ft 1 in
Overall Length ......................................................................................................................................................................................
41 ft 7 in
WING
Span ........................................................................................................................................................................................................
52 ft 1 in
Area ..... ................................................................................................................................................................................................... 279.40 ft2
Sweepback (at 50% chord) ............................................................................................................................................................... 0 degrees
Dihedral ................................................................................................................................................................................................. +3 degrees
Taper Ratio ............................................................................................................................................................................................
0.586
Aspect Ratio .........................................................................................................................................................................................
9.555
Mean Aerodynamic Chord.................................................................................................................................................................
66.474 in
HORIZONTAL TAIL
Span (overall) ........................................................................................................................................................................................
20 ft 6 in
Area ........................................................................................................................................................................................................
70.04 ft2
Sweepback ................................................................................................................................................................... 0° at elevator hinge line
Aspect Ratio .........................................................................................................................................................................................
6.0
Mean Aerodynamic Chord ................................................................................................................................................................
41.984 in
VERTICAL TAIL
Height (overall) .....................................................................................................................................................................................
8 ft 2 in
Area (including dorsal fin) ................................................................................................................................................................
39.92 ft2
Sweepback ............................................................................................................................................................ +9.437° at rudder hinge line
CABIN INTERIOR
Height (floorboard to headliner) ......................................................................................................................................................
4 ft 3 in
Length - Firewall to Aft Bulkhead (nominal) ..................................................................................................................................
21 ft 4 in
Width (max.) ..........................................................................................................................................................................................
5 ft 2 in
LANDING GEAR
Tread ......................................................................................................................................................................................................
11 ft 8 in
Wheelbase ............................................................................................................................................................................................ 13 ft 3.5 in
Tire Size - Main ................................................................................................................................................................................ 8.5 x 10, 8 ply
Tire Size - Nose ..................................................................................................................................................................... 22 x 8.00 x 8, 6 ply
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Februar y 201 6, Revision D
GRAND CARAVAN EX
1. GENERAL DESCRIPTION
(CONTINUED)
1.3 DESIGN WEIGHTS AND CAPACITIES
Maximum Ramp Weight .................................................................................................................................................
8842 lb
Maximum Takeoff Weight ..............................................................................................................................................
8807 lb
Maximum Landing Weight .............................................................................................................................................
8500 lb
Standard Empty Weight* ................................................................................................................................................
4558 Est. lb
Maximum Useful Load ....................................................................................................................................................
4284 Est. lb
Fuel Capacity (usable) at 6.70 lb/gal .............................................................................................................
335.6 gal/2,246 lb
Oil ....................................................................................................................................................................................................................... 14 qt
* Approximate standard empty weight includes unusable fuel, full operating fluids and full engine oil.
2. PERFORMANCE
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.
With cargo pod
Without cargo pod
Speed (Based on weight 8,807 lbs)
195 kts
Cruise at 10,000 ft .............................................................................................
........................... 185 kts
186 kts
Cruise at 20,000 ft ............................................................................................
........................... 175 kts
Range (with 2,246 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 18,000 ft .............................................................
Endurance .........................................................................................................
Maximum Range Power at 10,000 ft ..............................................................
Endurance .........................................................................................................
Maximum Range Power at 18,000 ft .............................................................
Endurance .........................................................................................................
832 nm
4.4 hr
1,040 nm
5.7 hr
973 nm
6.0 hr
1,125 nm
6.8 hr
........................... 792 nm
...........................
4.4 hr
........................... 985 nm
...........................
5.7 hr
........................... 918 nm
...........................
6.0 hr
........................... 1,052 nm
...........................
6.6 hr
Rate of Climb at Sea Level ...............................................................................................
Service Ceiling ...................................................................................................................
Maximum Certified Altitude .............................................................................................
Maximum Altitude in Icing Conditions ...........................................................................
1,330 fpm
25,000 ft
25,000 ft
20,000 ft
........................... 1,275 fpm
........................... 25,000 ft
........................... 25,000 ft
........................... 20,000 ft
Takeoff Performance (sea level, 8,807 lb)
Ground Roll............................................................................................................
Total Distance Over 50 ft Obstacle .................................................................
1,399 ft
2,160 ft
...........................
...........................
1,399 ft
2,160 ft
Landing Performance (sea level, 8,500 lb, no reverse)
Ground Roll ............................................................................................................
Total Distance Over 50 ft. Obstacle ................................................................
1,039 ft
1,871 ft
...........................
...........................
1,004 ft
1,836 ft
Stall Speed, CAS
Flaps Up, Idle Power ............................................................................................
Flaps Down, Idle Power ....................................................................................
78 kts
61 kts
...........................
...........................
78 kts
61 kts
Februar y 201 6, Revision D
7
GRAND CARAVAN EX
3. STRUCTURAL DESIGN CRITERIA
The Grand Caravan EX 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 8,807 pounds. Ultimate loads are defined as 1.5 times the limit loads.
DESIGN SPEEDS
(All speeds are at maximum gross weight.)
Cruising Maximum Operating Limit (VMO) .............................................................................................................................
175 KCAS
Flap Extension Speeds
0° to 15° .............................................................................................................................................................................
15° to 30° ...........................................................................................................................................................................
150 KCAS
125 KCAS
Maneuvering Speed (VA)
8,807 pounds .................................................................................................................................................................
7,500 pounds ...................................................................................................................................................................
6,250 pounds...................................................................................................................................................................
5,000 pounds...................................................................................................................................................................
148 KCAS
137 KCAS
125 KCAS
112 KCAS
4. FUSELAGE GROUP
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 21 ft. 4 in. The cabin floor is flat with the exception of two feet in the aft cabin which is five inches above
the main floor and makes up the aft cabin baggage area.
8
Cabin volume, including the pilot and aft cabin baggage
area is 427 cubic feet. Total volume aft of the pilot and front
passenger seat locations is approximately 340 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 airstairtype 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 additional ground ventilation. The right crew entry door incorporates 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 maximum 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.
Februar y 201 6, Revision D
GRAND CARAVAN EX
4. FUSELAGE GROUP
(CONTINUED)
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
opening is approximately 24 inches wide and 50 inches
high.
The door opening is flush with the floor and has square
corners for maximum cargo loading capability.
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 airplane is equipped with a two-piece plexiglass
windshield reinforced with a metal center strip. Sixteen
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.
5. WING GROUP
The Grand Caravan EX 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 fuselage 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 structure is capable of carrying certified limit flight loads.
6. EMPENNAGE GROUP
The empennage consists of a conventional vertical stabilizer, 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 stabilizer contains dual jack screw type actuators for operating the
Februar y 201 6, Revision D
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.
9
GRAND CARAVAN EX
7. LANDING GEAR
The landing gear is of the non-retracting, tricycle type with
a steerable nose wheel and two main wheels. Shock absorption is provided by the tubular spring steel main landing 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 14 3/4 in. ground clearance. The nose gear shock
absorption is provided by the oil snubber combined with
a drag link spring providing vertical and aft displacement
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 approximately 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.
8. PROPULSION
8.1 POWERPLANT
The propulsion system consists of a single fuselage mounted Pratt and Whitney PT6A-140 turboprop engine. The
PT6A-140 is rated to 867 shp at 1900 rpm. The standard
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, emergency power lever, propeller control lever and a fuel condition 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 system (EIS) which shows numeric readouts of critical engine,
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 gauge is also installed. Engine
torque is limited by a sensor that reduces fuel flow if an over
torque occurs.
An inertial separator system is built into the engine air inlet
duct to prevent moisture particles from entering the engine
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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 energized by a dual channel ignition exciter mounted on the right side of the engine compartment.
Mounting provisions are provided for a standby ignition exciter unit.
A P&WC FAST Engine Trend Monitor is an engine trend recording device and an engine parameter exceedance monitor which will allow operators to monitor the health of the
engine through periodic sampling of engine parameters.
The engine trend monitor contains logic to determine when
the aircraft is in a stable cruise flight regime before automatically taking a trend sample. If an optional SIM card is
installed and the GSM feature is activated through P&WC
the data is automatically uploaded via built-in cell phone
transmitter after landing.
This is an advisory system only. The airplane’s engine indication system is still the primary source of detecting and
correcting conditions where engine limitations are exceeded. There are no additional aircraft limitations and no performance change with the P&WC FAST Engine Trend Monitor installed.
Februar y 201 6, Revision D
GRAND CARAVAN EX
8. PROPULSION
(CONTINUED)
8.2 PROPELLER
The Grand Caravan EX is equipped with a 106 inch diameter
metal propeller. The three-blade, constant speed, full feathering, single acting, reversible pitch propeller is manufactured by Hartzell, model HC-B3TN-3AF(Y). The propeller is
controlled by a propeller governor and an overspeed 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.
9. SYSTEMS
9.1 FLIGHT CONTROLS
The Grand Caravan EX’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 operated 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 design of inner torque tubes serve to allow co-pilot operation
of the left-hand mounted brake cylinders. The brake cylinders 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 available with the standard autopilot installation.
Februar y 201 6, Revision D
The aileron control system is a combination of cables, quadrants, bellcranks and push-pull rods. A push-pull rod drives
the ailerons.
An aileron trim system consists of a pedestal mounted control knob, cables, fail-safe actuator, pushrods and trim tabs.
The left aileron incorporates a servo tab while the right aileron 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 control. The spoilers are interconnected with the aileron system
through a pushrod mounted to an arm on the aileron bellcrank. 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 vortex generators to reduce stall speed and provide enhanced
lateral stability. A selector and mechanical type follow-up indicator is provided in the control pedestal. The flap system
consists of an electrically driven screwjack actuator, a primary and standby motor, and a system of cables, bellcranks
and pushrods connected to the flaps. The standby electric
drive motor provides back-up flap actuation in the event of
failure of the primary motor.
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GRAND CARAVAN EX
9. SYSTEMS
(CONTINUED)
9.2 FUEL SYSTEM
The Grand Caravan EX 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 339.1 U.S. gallons (335 gallons usable). Filling the
fuel tanks is accomplished through filler caps in each wing.
Normal operation is with both tanks on. The pilot can mechanically 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 system (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 advisory system (CAS). The appropriate FUEL LOW (CAS) message will illuminate when the fuel in the respective tank is
approximately 25 gallons or less. A warning advisory is also
provided to indicate a low fuel level in the fuel reservoir
tank.
9.3 ELECTRICAL SYSTEM
The Grand Caravan EX is equipped with a 28-volt, directcurrent electrical system. The system uses a 24-volt, 38
ampere-hour sealed lead acid battery 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 battery bus. The battery bus is energized
continuously for ELT reset, Hobbs Meter, cabin/courtesy light
functions and engine trend monitor processor.
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 Bus 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
12
Alerting System (CAS) Annunication Window is located on
each Primary Flight Display (PFD) and can present appropriate messages (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 during maintenance work. Ground service circuitry is provided
to prevent the external power and the battery from being
connected together during starting, and incorporates polarity reversal and overvoltage protection. The external power
receptacle 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 malfunctions 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 are also included.
9.4 LIGHTING SYSTEM
Exterior LED lighting consists of two navigation lights, two
landing lights, two taxi/recognition lights, two strobe lights,
a flashing beacon and two underwing courtesy lights. All
exterior lights are controlled by toggle switches located on
the lighting control panel on the left side of the instrument
panel.
The G1000 displays and bezels, the audio panel and the
autopilot control utilize either automatic or manual means
of lighting control, based on crew setting of the “Avionics”
potentiometer. The panel mounted G1000 equipment will
revert to automatic dimming using GDU bezel photocell
input when the “Avionics” knob is near the extreme CCW
position. Moving the potentiometer clockwise places the
G1000 panel equipment into manual mode of selection for
display brightness throughout the rest of its travel. Other
lighting is provided for standby instruments and other nonG1000 avionics, pilot and co-pilot control wheel map lights,
LH, Center and RH flood lights, cabin/courtesy lights, passenger reading lights and a no smoking/seat belt advisory
sign. All interior lighting is LED with the exception of pilot
and copilot control wheel map lights.
Februar y 201 6, Revision D
GRAND CARAVAN EX
9. SYSTEMS
(CONTINUED)
9.5 ENVIRONMENTAL SYSTEM
9.7 VACUUM SYSTEM
The temperature and volume of airflow to the cabin is regulated 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.
A vacuum system provides the suction necessary to operate the standby attitude indicator. Vacuum is obtained by
passing regulated compressor bleed air through a vacuum
ejector. The vacuum system consists of the bleed air pressure regulator, a vacuum ejector, a vacuum relief valve, and
a vacuum system air filter. Vacuum system failure is indicated via a warning flag on the standby attitude indicator.
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 ventilating 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 ventilation through panel outlets to the flight deck.
A fan driven ventilation system provides supplemental cabin ventilation through two overhead mounted ventilators. An
optional air conditioning system is available that provides
comfortable cabin temperataures 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 ADC (Air Data Computer) and
to the standby airspeed indicator. It also provides static
pressure to the standby altimeter. The system is composed
of a heated pitot-static tube mounted on the leading 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 instruments
and sources.
9.8 GARMIN G1000 AVIONICS SYSTEM
The integrated avionics system incorporates 3 ten-inch
displays; the pilot’s primary flight display (PFD), the multifunction 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 Transponder. The KN-63 DME can be selected to
either NAV1 or NAV2 via PFD softkeys. Crew alerts are displayed on the PFDs.
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.
The right hand pitot-static system supplies ram air and static
pressure to the number two ADC. 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 201 6, Revision D
13
GRAND CARAVAN EX
10. FLOATPLANE
The Grand Caravan EX 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-fuselage 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 provide greater control when floats are installed on the aircraft.
The hand microphone is located on the center pedestal to allow clearance for the emergency lever that is used to manually lower the wheels on the floats.
14
WIPLINE 8750 FLOAT INSTALLATION
The Caravan can be converted to a floatplane or an amphibian when equipped with Wipline 8750 Series Floats manufactured, installed, and warranted by Wipaire, Inc. (The optional
300-amp starter/generator is not compatible with this installation.)
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 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 fax
info@wipaire.com
http//www.wipaire.com.
Februar y 201 6, Revision D
GRAND CARAVAN EX
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) ...........................................................................................................................
31’-9”
Height - hull .............................................................................................................................................................................................
3’-3”
Width - hull ...............................................................................................................................................................................................
3’-6”
WEIGHT
Amphibious 8750 on the Cessna 208B Grand Caravan EX ........................................................................................ 1,678 lbs/1,142 lbs*
*Exchange = Float installation weight minus aircraft landing gear weight.
PERFORMANCE FOR THE 8750 AMPHIBIOUS FLOAT - CESSNA 208B GRAND CARAVAN EX
PT6A-140 (867 HP)
Cruise Speed (75%) ............................................................................................................................................................................... 159 KTAS
1,826 ft
Take off run (land) ..................................................................................................................................................................................
Take off over 50 ft. obstacle (land) ....................................................................................................................................................
2,425 ft
Take off run (water) ................................................................................................................................................................................
2,000 ft
Take off over 50 ft. obstacle (water) ..................................................................................................................................................
3,270 ft
Rate of climb ........................................................................................................................................................................................... 1,212 ft/min
Service ceiling ......................................................................................................................................................................................... 20,000 ft
Gross weight (land & water) Requires Wipaire Gross Weight Kit STC ...................................................................................... 9,062 lbs
Landing weight (land) Requires Wipaire Gross Weight Kit STC ................................................................................................. 9,062 lbs
Landing weight (water) Requires Wipaire Gross Weight Kit STC ............................................................................................... 9,062 lbs
Maximum take off weight ..................................................................................................................................................................... 9,062 lbs
Maximum range* (cruise speed, 10,000 ft) ......................................................................................................................................
820 nmt
Stall speed (landing configuration) ....................................................................................................................................................
59 KCAS
Standard Empty Weight (Estimated) .................................................................................................................................................
Amphibian
5,800 lbs
Maximum Useful Load (Estimated) .................................................................................................................................................... 3,262 lbs
*Range based on 332 gal. usable fuel and includes takeoff, climb, descent and 45 minute reserve.
Februar y 201 6, Revision D
15
GRAND CARAVAN EX
11. STANDARD EQUIPMENT
FIGURE III — GRAND CARAVAN EX INSTRUMENT PANEL AND PEDESTAL LAYOUT
(Some options may be shown)
16
Februar y 201 6, Revision D
GRAND CARAVAN EX
11. STANDARD EQUIPMENT
11.1 AVIONICS
(CONTINUED)
Fuel Quantity
Fuel Flow
Standard Avionics Kit (includes Two Headsets)
Ammeter/Voltmeter
Garmin G1000 System includes:
Standby Engine Instrument
GDU 1040A Pilot & Co-Pilot Primary Flight Display (PFD)
Engine Torque Gauge, Wet Type
GDU 1040A Multi Function Display (MFD)
Digital FAST Engine Trend Monitoring System
GDC 74A Dual Air Data Computer (ADC)
11.3 FLIGHT INSTRUMENTS
GEA 71 Engine/Airframe Unit
GIA 63W Dual Integrated Avionics Unit (Includes Comm,
Nav, GPS)
Indications Displayed on each PFD:
GRS 77 Dual Attitude and Heading Reference System
(AHRS)
Attitude with Slip/Skid Indication
GMA 1347 Single Audio System with Integrated Marker
Beacon Receiver
Vertical Deviation, Glideslope and Glidepath
GMC 710 Autopilot Mode Controller
GSA 80/81 Servo Actuators with GSM 86 Servo Mounts
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)
Airspeed
Altitude
Vertical Speed
Horizontal Situation Indication
Outside Air Temperature
System Time
Generic Timer
Wind Data
Standby Flight Instruments:
Airspeed Indicator
Attitude Gyro
Altimeter
Avionics Cooling, (2) cowl deck fans and (3) display fans
Magnetic Compass,
PA System with Aft Cabin Speakers
Heated Pitot System, Pilot & Co-Pilot
Intercom
Alternate Static Source
Cabin Headset Jacks
Static Source Drains
11.2 ENGINE INDICATION SYSTEM (EIS)
Instrument Static System
Second Independent Pitot-Static System
Displayed on MFD During Normal Operations:
11.4 FLIGHT CONTROLS
Engine and System Displays - Show numeric readouts of
critical engine, fuel and electrical indications and calculations for the following:
Brake, Parking
Torque
Control Cables — Corrosion Resistant Steel
Interstage Turbine Temperature
Control Lock, Ailerons and Elevator
Gas Generator Speed
Flight Control System, Pilot & Co-Pilot (Includes All-Purpose Control Wheel, Pedals and Toe Brakes)
Propeller Speed
Oil Pressure
Oil Temperature
Brakes, Hydraulic, Toe-Operated
Friction Lock, Engine Controls
Powerplant, Quadrant Type Controls:
Condition Lever
Februar y 201 6, Revision D
17
GRAND CARAVAN EX
11. STANDARD EQUIPMENT
(CONTINUED)
Primary Engine Power
Door and Passenger Door)
Back-Up Engine Power, (Emergency Power Lever)
Overhead Flood (Pilot and Copilot) (3)
Propeller, Speed and Feather
Passenger Reading Lights (14)
Rudder Gust Lock
Dimming Controls, Switch Panel, Avionics Circuit Breaker
Panel, Left Hand Panel & Environmental Panel
Trim System (Aileron/Rudder (Manual), Elevator (Manual &
Electric Pilot & Co-Pilot)
11.9 POWERPLANT
Wing Flaps, Electric Pre-Select with Standby Motor
Chip Detector Installation
11.5 ENVIRONMENTAL
Defroster, Windshield (Pilot and Copilot)
Cowling, Rigid-Mounted (Quick Removable) Lower and
Easily Openable Upper Sides
Heating System, Cabin (Bleed Air Type)
Cowl Locks
Soundproofing
Engine Inlet Cover (2) and Propeller Tie-Down Sleeve
Ventilation System, Cockpit (Ram Air)
Engine, Turboprop PT6A-140, 867 SHP, 3600 TBO
Ventilator, Adjustable, Cabin Air
Engine Wash Ring (Integral)
Ventilation System, Fan Driven
Engine Support, Vibration Isolation
11.6 ELECTRICAL POWER
Battery, 24 Volt, 38 Amp/Hr, Sealed Lead-Acid
Filter, Integral, Full Flow Oil
Fire Detection System, Engine Compartment
Battery Switch (On-Off )
Ignition System Exciter Unit Mounting (Provisions for
Mounting Standby Unit)
Circuit Breakers, Electrical
Ignition System (Dual Ignitors)
Generator Control Unit
Intake Inertial Separator (Manual)
Generator Switch (Trip-On-Reset)
Oil Cooler, High Capacity
Ground Service Plug Receptacle
Overspeed Governor
Starter/Generator, 200 Amp
Propeller, 3 Blade Aluminum, Constant Speed, Full Feathering, Reversible – Hartzell
Power Outlet, 12V Cockpit And Cabin
Standby Electrical System, 75 amp
11.7 EXTERIOR LIGHTS (LED)
Propeller Governor
Propeller Spinner (Polished)
Shielding, Engine Ignition
Beacon – Omni Flash (Red)
Shutdown Fuel Collector, Engine
Courtesy, Under Wing
Oil Sight Gage
Landing, L.H. and R.H. (Wing Leading Edge-Outboard)
11.10 FUEL SYSTEM
Navigation (2)
Strobe (2) Wing Tip Mounted
Taxi, L.H. and R.H. (Wing Leading Edge-Inboard)
Ice Detection
11.8 INTERIOR LIGHTS (LED)
Fuel Boost Switch, Auxiliary
Fuel Caps with Anti-Siphon Doors
Fuel Control Heater, Engine
Fuel Filter with Quick Drain
Fuel Low Level Warning System
LED Backlit Instrument Panel Lighting
Fuel Pump, Auxiliary (Electric)
Map Light, Control Wheel Mounted, Pilot & Co-Pilot (Variable Intensity)
Fuel Pump, Engine
Fuel Reservoir with Quick Drain
Overhead Courtesy (4) (Forward and Mid Cabin, Cargo
18
Februar y 201 6, Revision D
GRAND CARAVAN EX
11. STANDARD EQUIPMENT
(CONTINUED)
Fuel Selector Valves
Window, Foul Weather, Pilot Door
Fuel Shutoff Valve
Windows Tinted All-Around
Fuel Tanks
11.12 EXTERIOR
Fuel Valves, Quick Drain (8)
Fuel Vents, Non-Icing
Anti-Precipitation Static Kit
Fuel Sampler Cup
Bonding Straps, Control Surface (Aileron, Elevator and
Rudder)
11.11 INTERIOR
Cargo Pod Provisions with Twisted Stack
Aircraft Keys
Corrosion Proofing, External
Approach Plate Holder, L.H. & R.H.
Door, Cargo, Two-Piece (Left Side of Aircraft, with Upper
Door Unlocked Annunciator Light)
Baggage Area Partition Net
Baggage Tie-Down Straps (4)
Beverage Cup Holders (Pilot and Copilot)
Door, Copilot (Full Opening)
Door, Pilot (Full Opening)
Cargo Tie-Down Fittings Provisions
Door, Passenger with Airstair Feature (Right Side of Aircraft
with Upper Door Unlocked Annunciator Light)
Cargo Tie-Down Fittings (Baggage Area)
Jack Points (Fuselage and Main Landing Gear)
Checklist, Pilot’s (Laminated)
Landing Gear, Fixed, Nose, Steerable
Crew Door Storage Area RH, LH
Landing Gear, Fixed, Main
Fire Extinguisher Cabin– Hand Type
Lock, Key-Operated (One Key Fits All Doors)
Floor Covering, Lightweight Vinyl
Paint, All Over (Modified Polyurethane)
Glareshield
Stabilizer Abrasion Boots
Handbook, Customer Care, Includes Engine/Flight Logs,
Warranty, Etc.
Stall Warning System, Heated
Handbook, Pilot’s Operating
Tailstand
Headliner – Vinyl
Tires, Tube Type, 8.50 x 10, 8 ply Main; 22 x 8.00, 6 ply
Nose With Extended Nose Gear Fork
Instrument Panel – Metal
Tie-Down Rings, Aircraft
Map/Glove Compartment
Tow Bar
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
Seats, Pilot & Copilot, Adjustable Fore, Aft and Vertical with
Articulating Recline and Arm Rest
Sign, Fasten Seat Belts & No Smoking
Step, Cabin Entrance, Retractable (RH & LH Crew Entry
Doors)
Sunvisors
Februar y 201 6, Revision D
19
GRAND CARAVAN EX
12. DOCUMENTATION AND TECHNICAL
PUBLICATIONS
U.S. Standard Airworthiness Certificate, FAA8100-2; Export
Certificate of Airworthiness, FAA8130-4 or Special Airworthiness Certificate FAA8130-7 as appropriate;
Equipment List
Weight and Balance Report
Garmin Cockpit Reference Guide
Pilot’s Operating Handbook and 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
Cessna CESCOM Instruction Manual
CESSNA TECHNICAL INFORMATION
Cessna makes available a complete system of manuals and
catalogs for the operation and maintenance of the Grand
Caravan EX. All Cessna and related technical information,
as well as revision information, is listed on www.cessnasupport.com.
Cessna manuals are kept current through periodic revisions. Aircraft operators and designated maintenance
facilities can receive these revisions, by various mediums,
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 by your choice of DVD,
Download, Online or iPad mobile app 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
avionic installation)
CesNav Weight and Balance Calculator (CLCalc)
*Please note: for download, online and mobile app – these
publications are Windows based and registration with www.
cessnasupport.com is required. Up to four additional user
access’ available.
20
The following materials provided by Pratt & Whitney
Canada:
Combined Engine Maintenance Manual & Illustrated
Parts Catalog CD
One set Engine Service Bulletins Including Spare Parts
Bulletins and Service Information Letters (Paper)
Free revisions coverage for one year
Service Bulletins are also available by on-line or
email subscription at www.pwc.ca or through the
Pratt & 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 publications
are in use. The checklist is available online at www.cessnasupport.com.
PILOT’S OPERATING HANDBOOK
Revisions to the Pilot’s Operating Handbook will be mailed
periodically to the registered aircraft owner on file.
CESSNA OWNER ADVISORY
Cessna Owner Advisories provide owners of Cessna aircraft
up-to-the-minute information about mandatory and beneficial service requirements and the latest in product improvements. Owner Advisories summarize new Service Bulletins
or Service Newsletters 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
owners 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, provide
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, international
subscriptions are available, although a subscription fee will
be charged.
Cessna aircraft owners may register, for free, with www.
cessnasupport.com to obtain a login that allows access to
PDF versions of Service Bulletins and Newsletters. Weekly
email notification of released service information is available with registration to the site.
Februar y 201 6, Revision D
GRAND CARAVAN EX
13. MAINTENANCE PROGRAMS
COMPUTERIZED MAINTENANCE RECORD
SERVICE
FLIGHT-DATA ACQUISITION,
AND TRANSMISSION (FAST)
Seller will provide a computerized maintenance record
service for one (1) full year from the date of delivery of a
Grand Caravan EX to the purchaser. Currently, this service
is provided by CAMP Systems International, Inc.
Cessna has chosen the FAST system as standard equipment on the Caravan to allow operators to easily monitor
and maintain the aircraft engine.
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 permanent aircraft records of maintenance performed.
Reports will be available which reflect the aircraft status, upcoming 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 reliability will also be available.
STORAGE,
The FAST 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 is uploaded to P&WC data analysis servers automatically by GSM cell phone signal upon engine shutdown if a
SIM card is installed and the GSM subscription service is activated through P&WC. Otherwise data can be uploaded to
P&WC data analysis servers via a supplied USB cable connected to a laptop. The P&WC WebECT (tm) website formats
the data into customized reports for use as analysis tools.
The on-line system is the standard service, however, a paper 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.
CARAVAN INSPECTION PROGRAM
The Caravan Inspection Program is task based, integrating
all inspections into an easy to follow sequence. The benefits of the old Phase Card program are now available to all
customers.
Februar y 201 6, Revision D
21
GRAND CARAVAN EX
14. LIMITED WARRANTIES
The standard Grand Caravan EX Aircraft Limited Warranty
which covers the aircraft, other than the Pratt & Whitney
Canada (P&WC) engine and associated engine accessories,
the Honeywell avionics, and the Hartzell 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 Requested Equipment (CRQ) from Seller’s Limited Aircraft Warranty. Following Seller’s Limited Warranty, the engine and
engine accessory warranty of P&WC, the avionics warranty
of Honeywell, and the propeller warranty of Hartzell 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 GRAND CARAVAN EX
LIMITED WARRANTY (LIMITED WARRANTY)
Seller expressly warrants each new Grand Caravan EX Aircraft (exclusive of engine and engine accessories supplied
by P&WC, avionics supplied by Honeywell, and the propeller supplied by Hartzell which are covered by their separate
warranties), 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 occurs
first, for Garmin avionics;
(c) One year for all Optional Avionics;
(d) One year for Actuators, Brakes, GCUs, Starter Generators, 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 Furnishings, and Paint.
Any remaining term of this Limited Warranty is automatically
transferred to subsequent purchasers of the aircraft.
22
Seller’s obligation under this Limited Warranty is limited to
repairing or replacing, in Seller’s sole discretion, with exchange, 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 “Support 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 Facility and are only warranted for the remainder of the applicable original aircraft warranty period. A new warranty period 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 perform service on the aircraft (“Authorized Service Facility”)
without charge to the warranty recipient for parts and/or labor for removal, installation, and/or actual repair of such defective 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 accordance with Seller and other applicable manuals, bulletins,
and other written instructions. However, this Limited Warranty 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 facilities 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 applicable manuals, bulletins, and/or other written instructions
provided by Seller so that the performance, stability, or reliability 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 201 6, Revision D
GRAND CARAVAN EX
14. LIMITED WARRANTIES
inspections); or to the replacement of service items (such
as brake linings, lights, filters, hoses, belts, tires, and rubber-like items); or to normal deterioration of appurtenances
(such as paint, cabinetry, and upholstery), corrosion or structural 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 FITNESS FOR A PARTICULAR PURPOSE. THE AFOREMENTIONED REMEDIES OF REPAIR OR REPLACEMENT ARE
THE ONLY REMEDIES UNDER THIS LIMITED WARRANTY.
SELLER EXPRESSLY AND SPECIFICALLY DISCLAIMS ALL
OTHER REMEDIES, OBLIGATIONS, 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 AND ALL OTHER CONSEQUENTIAL AND INCIDENTAL DAMAGES. SELLER NEITHER ASSUMES NOR AUTHORIZES ANYONE ELSE TO ASSUME ON ITS BEHALF
ANY FURTHER OBLIGATIONS OR LIABILITIES PERTAINING TO THE AIRCRAFT NOT CONTAINED IN THIS LIMITED 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 WICHITA, KANSAS. THE PARTIES HERETO CONSENT TO PERSONAL JURISDICTION IN THE FORUM CHOSEN.
14.2 PRATT & WHITNEY CANADA INC. (ABBREVIATED NEW ENGINE WARRANTY)
Pratt & Whitney Canada Inc. (P&WC) warrants that each
new PT6A-140 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 under this warranty are limited to the repair or replacement
at P&WC’s option of goods returned to P&WC or to a location designated by P&WC which are shown to P&WC’s rea-
Februar y 201 6, Revision D
(CONTINUED)
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 transportation 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 reshipment 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, 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&WC’S NEGLIGENCE, ACTUAL OR IMPUTED. THE REMEDIES OF THE
PURCHASER 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 OR EXTENSION
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 of
the Specification and Description. For complete details of
the PT6A-140 engine warranty, please refer to P&WC’s full
PT6A-140 warranty policy.
14.3 HONEYWELL/BENDIX/KING
WARRANTY
A. General Aviation Avionic products manufactured by
Honeywell/Bendix/King, General Aviation Division (collectively referred to herein as “Honeywell/Bendix/King”) are
warranted 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
23
GRAND CARAVAN EX
14. LIMITED WARRANTIES
(B) of this 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. Demonstration or
stock aircraft usage is restricted to 100 hours service prior
to warranty registration. Warranty coverage, therefore,
may be unavailable or limited, depending upon the usage
or time the product in question 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 expected to maintain accurate records and
provide same, upon demand, to any purchaser or Honeywell/Bendix/King.
2. Warranty coverage for products otherwise not eligible
by reason of expiration of the eighteen (18) month period
specified above may again become eligible for warranty
protection, provided (a) that warranty registration occurs
within thirty (30) months of the product’s factory shipping
date and (b) that the products are submitted to Honeywell/
Bendix/King for inspection and certification and then the
promulgated Honeywell/Bendix/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 violation 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 Honeywell/
Bendix/King Service Center or Honeywell/Bendix/King
Regional Product Support Repair/Overhaul Facility, 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.
24
(CONTINUED)
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 Honeywell/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 unauthorized 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
warranty 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 expressly 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,
consequential, 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 design changes, additions to, and improvements in its products without the obligation to install same in products previously manufactured.
Februar y 201 6, Revision D
GRAND CARAVAN EX
14. LIMITED WARRANTIES
14.4 HARTZELL PROPELLER
(CONTINUED)
C. TERMS AND CONDITIONS OF LIMITED WARRANTY
COVERAGE
A. COVERAGE PROVIDED
Products Other Than De-Ice Boots
Hartzell Propeller Inc. (“Hartzell”) warrants to the original retail purchaser (the “Purchaser”) that it will repair or replace
defects in material or workmanship in the components of a
product manufactured by Hartzell, other than a de-ice boot,
for a period of one (1) year from the date the product is first
placed into service, or for the first 1000 operating hours of
use of the product, whichever occurs first, subject to the
other terms and conditions of this limited warranty.
De-Ice Boots
Hartzell warrants to the Purchaser that it will repair or replace defects in material or workmanship in the components of a de-ice boot manufactured by Hartzell, for a period of eighteen (18) months from the date the de-ice boot is
first placed into service, or for the first 2000 operating hours
of use of the product, whichever occurs first, subject to the
other terms and conditions of this limited warranty.
All of the products identified above are hereinafter referred
to as the “Products,” and their components hereinafter referred to as “Components.”
B. DISCLAIMER OR LIMITATION OF WARRANTIES
Unless prohibited by applicable law, and except for the
limited warranties set forth above, Hartzell hereby disclaims any and all express and implied warranties, including but not limited to implied warranties of merchantability and fitness for a particular purpose. In the event
disclaimer of implied warranties is not permitted under
applicable law, such implied warranties, including but not
limited to implied warranties of merchantability and fitness for a particular purpose, are limited in duration and
in scope of coverage to the duration and scope of coverage of the limited warranty.
Some states do not allow limitations on how long an implied warranty lasts, so above limitation may not apply to
you.
Februar y 201 6, Revision D
In order to obtain coverage under Hartzell’s limited warranty, the Purchaser must notify Hartzell in writing of the warranty claim as soon as possible after obtaining knowledge
of the potential claim, and in any event not later than ten (10)
days following expiration of the limited warranty. Hartzell
may withhold warranty repairs pending proof from Purchaser of the date the Product was placed into service, including
a fully completed warranty registration card. Hartzell shall
provide warranty repair or disposition instructions based on
a written statement from the Purchaser describing the alleged defect. All initial transportation and handling charges
must be prepaid by the Purchaser until warrantability is determined by Hartzell, at which time Hartzell may reimburse
none, some, or all of these charges, at Hartzell’s discretion.
In the event Hartzell determines, at its sole discretion, that
the Product or Component thereof is covered under the limited warranty, Hartzell shall, at its election, either:
(1) Have the Product or Component repaired and returned
to Purchaser;
(2) Deliver to Purchaser a replacement Product or Component; or
(3) Issue a credit to the Purchaser in the amount of the actual purchase price for the Product. Hartzell reserves the right
to replace Products or Components with remanufactured
or re-designed Products or Components of substantially
equivalent quality. All warranty repair work will be accomplished at Hartzell’s principal place of business, a Hartzell
Recommended Service Facility, or a third-party location preapproved in writing by Hartzell.
In the event Hartzell determines that the alleged defect is
not covered by the limited warranty, the Product or Component will be returned to Purchaser, as is, transportation and
handling charges collect. The only remedies under this limited warranty are as set forth above. Any Product repaired,
or replacement Product provided, shall retain the balance of
the limited warranty provided for herein. This limited warranty is not transferable to any person or entity. This limited warranty does not extend to future performance of a Product.
25
GRAND CARAVAN EX
14. LIMITED WARRANTIES
D. WHAT IS NOT COVERED BY THIS LIMITED WARRANTY
This limited warranty does not provide coverage for any of
the following:
1. Normal maintenance and service.
2. Consumable Products and Components, and Products
and Components that have reached the end of their normal
usable life.
3. Product components not manufactured by Hartzell, which
components may or may not be covered under warranties
made by the manufacturers of those components.
4. Products and Components not purchased through Hartzell or one of its authorized distributors, or any Products or
Components purchased by way of auction, salvage, or repossession.
5. Conditions, damage, or issues caused by, in whole or in
part, or in any way related to:
(CONTINUED)
E. DISCLAIMER OF INCIDENTAL AND CONSEQUENTIAL
DAMAGES
Hartzell hereby disclaims any and all incidental, consequential, special, direct, and indirect damages arising out
of or relating to the Products, including but not limited
to loss of use, inconvenience, lost profits, cover, rental
replacements, costs and expenses of “troubleshooting,”
and transportation and delivery expenses not pre-approved in writing by Hartzell. In no event shall Hartzell’s
liability with respect to any Product, whether under this
limited warranty, any implied warranty, in tort, or otherwise, exceed the price paid by Purchaser for the Product.
These disclaimers are independent of any failure of the
essential purpose of any warranties or remedies provided
to Purchaser, and shall survive any determination that a
warranty or remedy failed of its essential purpose. Some
states do not allow the exclusion or limitation of incidental or consequential damages, so the above limitation or
exclusion may not apply to you.
a. Accident, misuse, theft, or negligence.
F. STATUTE OF LIMITATIONS
b. Failure to comply with any instruction provided by
Hartzell or its suppliers with respect to the use, operation, maintenance, or service of the Products.
No action may be brought against Hartzell for breach of its
limited warranty, any applicable implied warranty, or for any
other claim relating to the Product, more than ten (10) days
after expiration of the applicable limited warranty period.
c. Alteration or modification of the Products or any
Components.
G. GOVERNING LAW
d. Acts of God or other environmental conditions.
e. Use of the Products for purposes other than their normal use.
f. Failure to seek and obtain warranty coverage in a
timely matter.
g. Deterioration or fading due to wear, exposure, or
other cause, including but not limited
to
rust,
cosmetic blemishes, and discoloration.
h. Acts or omissions of any person or entity other than
Hartzell.
This limited warranty shall be governed by, construed, and
enforced in accordance with the laws of the State of Ohio,
without reference to conflict of law principles. The United
Nations Convention on Contracts for the International Sale
of Goods shall not apply to this limited warranty.
H. NO AUTHORITY
No person or entity has authority to alter the terms of this
limited warranty or make any warranties or representations
on behalf of Hartzell. THIS WARRANTY GIVES YOU SPECIFIC LEGAL RIGHTS, AND YOU MAY ALSO HAVE OTHER
RIGHTS WHICH VARY FROM STATE TO STATE.
Hartzell Propeller Inc.
One Propeller Place Piqua, Ohio 45356
Phone: 937-778-4320
26
Februar y 201 6, Revision D
GRAND CARAVAN EX
15. GRAND CARAVAN EX CREW TRAINING
AGREEMENT
Training for one (1) Grand Caravan EX Crew will be furnished
to First Retail Purchaser (hereinafter called the “Purchaser”),
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 designated training organization.
a. A simulator shall be utilized which is FAA certified to
provide training to proficiency in accordance with trainer’s
standards.
b. In lieu of a model specific simulator, training will be provided in the most appropriate type simulator available.
c. Location of training to be Wichita, Kansas, unless mutually
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 Trainer’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.
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 Purchaser 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 Purchaser 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 Wichita, Kansas, at least seven (7) days prior to scheduled training. 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; however, 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 delay in providing training due to causes beyond its or their
reasonable control.
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 English 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.
Februar y 201 6, Revision D
8. All Training furnished to Purchaser under the Agreement 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 mutually 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.
27
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© 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-208B-0216