Cessna 208 Fam Course

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Art Williams and Harry Wendt Aeronautical Aeronautical Engineering School ISO 9001:2008 Certified QMS

Cessna 208 Familiarisation Course The Cessna 208 Caravan, also known as the Cargo master , is a single turboprop engine, fixed-gear short-haul regional airliner and utility aircraft built in the USA by Cessna Cessna.. The airplane typically seats nine passengers, with a single person crew, although with a FAR Part 23 waiver, it can seat up to fourteen passengers. The aircraft aircraft is also used for cargo feederliner operations. The prototype first flew in December 1982 for two years of certification and testing. The production model model was certified by the FAA in October of 1984. Since then, the Caravan has undergone a number of design evolutions. evo lutions. Working with FedEx FedEx,, Cessna produced produced first the Cargomaster, and followed that with the stretched and upgraded Super Cargomaster. The passenger model, model, the Grand G rand Caravan, was derived from the Super Cargomaster. Cessna offers the 208B in many configurations. The basic 208 airframe can be outfitted with various types of of landing landing gear, gear, allowing it to operate in a wide variety of environments. environments. Some common adaptations include skis skis,, enlarged tires for unprepared runways,, and pontoon floats on the Caravan Amphibian model. runways

AIRPLANE OVERALL Length (Overall)

37.58 Feet

Height (Maximum) (Maximum) 14.83 Feet Wing Span (Overall) (Overall) 52.16 Feet Propeller Diameter Diameter (Hartzell) (Hartzell) 100.00 Inches Inches Propeller Diameter (McCauley) 106.0 Inches Inches Propeller Ground Clearance (Nose tire inflated and nose strut fully extended 4.50 inches) (Hartzell)

14.52 Inches

Propeller Ground Clearance Clearance (Nose tire inflated and nose strut fully extended 4.50 inches) (McCauley)

Issue: 1, Revision: 1

11.53 Inches

Aircraft Fam. Course (C208)

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Landing Gear Track Width (Centerline to centerline MLG tire): Standard Tires

11.66 Feet

Optional Tires

11.66 Feet

Wheelbase (At static static empty weight) 11.62 Feet

FUSELAGE Cabin Width (Maximum sidewall to sidewall)

62.00 Inches

Cabin Height (Floorboard to headliner)

51.00 Inches

Cabin Volume (Including rear baggage area) Cargo Pod

341.4 Cubic Feet 83.7 Cubic Feet

WINGS Area (Includes cabin top)

279.40 Square Feet

Chord Length and Root W.S. 35.00

77.995 Inches

Mean Aerodynamic Chord (W.S. 141.45)

66.398 Inches

Wing Station 308.00

48.108 Inches

Projected Tip (W.S. 310.00) 47.892 Inches Issue: 1, Revision: 1


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Models 208A Caravan I the basic introductory model, outfitted for passenger operation.* 208A Caravan 675 the current production model of the basic Caravan, with higherpowered PT6A-114A engine. 208A Cargomaster Developed with FedEx FedEx,, a pure cargo version of the Caravan. FedEx took delivery of 40 of these aircraft. 208B Grand Caravan A stretch of the Caravan I by 4 feet. The 208B also f eatures a more powerful PT6A-114A engine. 208B Super Cargomaster The cargo variant of the 208B series. FedEx took delivery of 260 of these. Caravan Amphibian A 208A Caravan with Wipaire 8000 floats in place of the landing gear, for water landings. landings . Some models of the floats are amphibious, also allowing land landing.

General Info Cruise Speed -175knots324 km/h Engine- Pratt & Whitney Canada, Inc., Free Turbine. Flat Rated at 675 shaft horsepower PT6A-114A. Propeller -McCauley three-bladed, constant speed, full feathering, reversible, 106-inch diameter

Powerplants 208 - One 450kW (600shp) Pratt & Whitney Canada PT6A-114 turboprop driving a three blade variable pitch Hartzell propeller. prop eller. 208-675, 208B Super Cargomaster & Grand Caravan - One 505kW (675shp) PT6A-114A.



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Fuselage The fuselage is constructed of aluminum Alloy and is divided into three major sections:Forward Section Center Section Tail cone section

The Forward Section The fuselage forward section consists of mainly The instrument panel The avionics panel Circuit breaker panel Center pedestal

Center Section The center section contains of the Cargo/ passenger compartment, Seat rails and access plates.

The Tail Cone section The tail cone section contains the oxygen cylinder, filler valve access plate, flight control cables, Emergency locator transmitter, baggage p artition, access plates and stinger.



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Aileron controls The aileron controls consists of cables, Qudrants, bellcranks and push pull rods. The System is divided into two loops Low tension loop-In the fuselage High tension Loop- In the wings Roll Spoilers Pair of Roll spoilers are mounted above the outboard ends of the Flaps These are incorporated to improve low speed roll control. These spoilers are interconnected with the aileron system through a push rod mounted to an arm on the aileron bellcranks. These Spoilers only move upwards.

Aileron trims The Right (Stbd) trim tab is actuated by the pilot it is actuated by use of Cables, Jack screw actuator and push rods. The Left (Port) trim tab is a servo tab and is mechanically displaced in the opposite direction when the aileron is moved

Elevator Control Is a conventional cable system, consists of a FWD and AFT bellcrank and a push pull rod. These are located under the cabin floor. The aft bellcrank connects to the elevator torque tube via the push rod.



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Elevator trim The elevator trim is located on the trailing edges of the elevator both Left and right. This Tab consists of a sprocket/chain and cable assembly. It is actuated by a trim wheel located on the center pedestal in the cockpit.

Rudder Control The rudder control is a conventional cable and bellcrank system .It is controlled by manually movement of the rudder pedals in the cockpit.

Rudder trim This consists of a trim wheel driving a flex shaft which is connected to the rudder pedals shaft. This movement moves the rudder.

Flaps The wing flaps consist of a cabin mounted electrically driven jackscrew type actuators. The system consists of Two flap motors A Main and a Standby Motor. The system actuation is achieved by the use of bellcranks and push rods.

Fuel System The fuel system holds 332.0 US gals total. The fuel is contained in the wings in a wet



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Wing cavity in each wing. Filing of the tanks is accom plished through outboard fuel filler caps. Both tanks are connected to a center reservoir Tank before it is fed to the engine.

Landing Gear The Landing gear is a fixed gear, employing a rugged r ugged three piece tubular main gear spring assembly and a steerable nose gear equipped with an oil snubber shock strut and a tubular spring drag link. Main gear shock absorption is provided by a tubular spring steel main gear spring with a center main gear tube connecting the two outer main gear legs at the gear attached trunnions.

Brake System The brake system is hydraulic operated. It has two (2) master cylinders and a brake reservoir. The reservoir supplies the fluid for actuating the br ake.

Electrical System The electrical system is a 28 V, single wire negative ground direct current system. Power is supplied by a 200A Starter /generator and a 28V lead acid battery .Power may also be supplied through an external connection. An optional stand by electrical power source is provided by a belt driven 70A Alternator



January 3, 2011

Cessna 208 Fam Course

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