Specification & Description - BenAir

1 Specification &DescriptionJuly 2010(G1000 equipped units 208B-2000 and on) Specification AND DESCRIPTIONEFFECTIVE WITH SERIAL NUMBER 208B-2160 AND ONJULY 2010 Caravan MarketingCessna Aircraft Box 7704 Wichita, Kansas 67277-7704 Telephone (316) 517-6081 Fax (316) 517-7250 July 20101 INTRODUCTIONThis Specification and Description is published for thepurpose of providing general information for the evalua-tion of the design, performance and equipment of theCessna Grand Caravan aircraft. Should more detaileddata be required, it can be obtained by contacting:Cessna Aircraft Box 7704 Wichita, Kansas 67277 Telephone: 316-517-6081 Fax: 316-517-7850 This document describes only the Cessna Model 208 BGrand Caravan aircraft, Unit Serial Number 2160 andon, and its powerplant and included is the Cessna warranty applicable to theCessna Model 208B Grand Caravan aircraft and theGrand Caravan Crew Training Agreement. In the eventof any conflict or discrepancy between this documentand the basic purchase agreement to which it may beappended, terms specified in the basic purchase agree-ment to the time span between the date of thisSpecification and Description and the scheduled deliverydate of the aircraft, Cessna reserves the right to revisethe Specification and Description whenever :This product contains Halon 1211, Halon 1301, and also R-134A.

2 Furthermore, the product wasmanufactured with CFC-12 and 1-1-1 Trichloroethane, substances which harm public health and environment bydestroying ozone in the upper atmosphere. 2 TABLE OF CONTENTSC essna Grand Caravan Specification and of Contents ..21. General Description ..3-42. Performance ..43. Structural Design Criteria ..74. Fuselage Group ..7-85. Wing Group ..86. Empennage Group ..87. Landing Powerplant .. Propeller ..99. Controls .. System .. System .. Systems .. System .. System .. G1000 Avionics Corrosion Standard Grand Caravan Avionics .. Engine Flight Instruments .. Flight Controls .. Electrical Power .. Exterior Interior Lights .. Fuel Exterior ..1412. Documentation and Technical Maintenance Programs ..15-1714. Limited Cessna s Limited Warranty .. Pratt & Whitney Canada Inc.. McCauley Limited Warranty .. Honeywell/Bendix/King Warranty .. Garmin Warranty .. Goodrich Avionics Systems Limited Grand Caravan Crew Training Agreement.

3 22 FIGURE I GRAND CARAVAN EXTERIOR II GRAND CARAVAN CABIN, DOORS, AND WINDOWS DIMENSIONS ..6 FIGURE III GRAND CARAVAN FLIGHT DECK ..12 July 20103 MANUFACTURERCESSNA AIRCRAFT COMPANYMODEL208B1. GENERAL DESCRIPTIONThe Cessna Grand Caravan is an unpressurized single-engine high wing turboprop aircraft with fixed landinggear. The aircraft can accommodate up to 14 personsincluding a minimum crew of one. (Operations with morethan nine passengers must be approved by the register-ing country s aviation authority.) Suitable allowance forluggage and optional equipment is also powerplant is a Pratt and Whitney of Canada PT6A-114A turboprop engine mounted in the nose of the air-craft basis is to FAA FAR Part 23 Requirements day, night, VFR, IFR and flight-into-icingconditions when equipped with the appropriate certification requirements may require additionalequipment and ..Pratt & Whitney PT6A-114A 675 shp @ 1900 rpmPROPELLER.

4 McCauley, Anti-Ice, Constant Speed, Full Feathering, Reversible Pitch, 3 Blades, 106 in. lb/ft2 Power .. lb/shpAPPROXIMATE DIMENSIONSO verall Height ..14 ft 10 inOverall Length ..41 ft 7 inWingSpan (overall) ..52 ft 1 inArea .. ft2 Sweepback (at 50% chord) ..0 degreesDihedral ..+3 degreesTaper Ratio .. Ratio .. Aerodynamic Chord .. inHorizontal TailSpan (overall) ..20 ft 6 inArea .. ft2 Sweepback ..0 at elevator hinge lineAspect Ratio .. Aerodynamic Chord .. inVertical TailHeight (overall) ..8 ft 2 inArea (including dorsal fin) .. ft2 Sweepback ..+ at rudder hinge lineCabinHeight (floorboard to headliner) ..4 ft 3 inLength Firewall to Aft Bulkhead (nominal) ..21 ft 4 inWidth (max.) ..5 ft 2 inLanding GearTread .. ftWheelbase .. ftTire Size Main .. x 10, 8 plyTire Size x x 8, 6 ply42. PERFORMANCE1. GENERAL Description (Continued)DESIGN WEIGHT AND CAPACITIESM aximum Ramp lbMaximum Take Off Weight ..8750 lbMaximum Weight (Cargo Pod Installed Flight into Icing).

5 8550 lbMaximum Landing lb*Standard Empty Weight ..4514 Est. lbMaximum Useful Load ..4271 Est. lbFuel Capacity (usable) @ gal/2224 lbOil ..14 qt*Approximate standard empty weight includes unusable fuel, full operating fluids and full engine performance data is based on a standard aircraft con-figuration in International Standard Atmosphere and landing field lengths are based on level, hardsurface, dry runways with zero wind. Actual performancewill vary with individual airplanes and other factors such asenvironmental conditions and aircraft ..Without cargo pod (8,750 lbs.) ..With cargo pod (8,750 lbs.)Cruise at 10,000 ft..184 ktsCruise at 20,000 ft..174 ktsRANGE (with 2224 pounds usable fuel and fuel allowance for engine start, taxi, takeoff, climb, descent and 45 minutes reserve)Maximum Cruise Power at 10,000 nm ..862 nmEndurance .. hr .. hrMaximum Cruise Power at 18,000 ft ..1109 nm ..1044 nmEndurance .. hr .. hrMaximum Range Power at 10,000 ft.

6 1026 nm ..963 nmEndurance .. hr .. hrMaximum Range Power at 18,000 nm ..1076 nmEndurance .. hr .. hrRate of Climb at Sea fpm ..925 fpmService Ceiling ..23,700 ft ..22,800 ftMaximum Certified Altitude ..25,000 ft ..25,000 ftMaximum Altitude in Icing Conditions ..20,000 ft ..20,000 ftTakeoff Performance (sea level, 8750 lb)Ground Roll ..1365 ft ..1405 ftTotal Distance Over 50 ft Obstacle ..2420 ft ..2500 ftLanding Performance (sea level, 8500 lb, no reverse)Ground Roll ..950 ft ..915 ftTotal Distance Over 50 ft. Obstacle ..1795 ft ..1740 ftSTALL Speed, CASF laps Up, Idle Power ..78 kts ..78 ktsFlaps Down, Idle Power ..61 kts ..61 ktsJuly 20105(Shown with Optional Cargo Pod Installed)52 ft 1 in 106 in (McCauley)11 ft 8 in 20 ft 6 in PIVOT POINT* PIVOT POINT* 15 ft 5 1/2inMAX. 41 ft 7 inFIGURE I GRAND CARAVAN EXTERIOR DIMENSIONSNOTES:1. Dimensions shown are based onstandard empty weight and properinflation of nose and main gear Wing span dimension includesstrobe Maximum height shown with nosegear depressed as far as Wheel base length is 13 -31/2.

7 5. Wing area is square Minimum turning radius (* pivot pointto outboard wing tip strobe light) is33 -8 .7. McCauley propeller ground clearance with standard tires and ext-ended nose gear strut:Nose tire inflated and nose gear barrel extended35/8 : 14 3/4 .Nose tire deflated and nose strutfully compressed: 5 7/8 .651 in54 in52 in*51 in**53 in*54 in**62 in*591/2in**64 in46 inStationsFIGURE II GRAND CARAVAN DOORS AND WINDOWS DIMENSIONSGRAND CARAVAN CABIN DIMENSIONS*Dimensions at cabin floor **Dimensions at lower window line*42 in** 46 in53 in17 ft 10 in 118 100 282 332 35624 in 18 in 50 in24 in 50 in24 in14 in49 in 41 3/4in44 3/4in24 3/8in31 7/8in 11 7/8in 35 5/8in 35 in 21 ft 4 in July 201074. FUSELAGE GROUP3. STRUCTURAL DESIGN CRITERIAThe Grand Caravan certification basis is to FAR Part 23normal category limit load factors are + , at a maxi-mum takeoff weight of 8,750 pounds. Ultimate loads aredefined as times the limit SPEEDS(All speeds are at maximum gross weight.)

8 Cruising Maximum Operating Limit (VMO)..175 KCASFlap Extension Speeds (VFE)0 to 10 ..175 KCAS10 to 20 ..150 KCAS20 to 30 ..125 KCASM aneuvering Speed (VA)8750 pounds ..148 KCAS7500 pounds ..137 KCAS6250 pounds ..125 KCAS5000 KCASC onstruction of the fuselage is of conventional formedsheet metal bulkhead, stringer and skin design. Majorelements of the structure are the front carry-through sparand bulkhead, the rear carry-through spar and landinggear bulkhead, and the forward doorpost. The frontcarry-through spar and bulkhead is an integral fail-safestructure with forgings at the top for attaching the frontwing spar and forgings at the bottom for attaching thewing strut. The rear carry-through and landing gear bulk-head is an integral fail-safe structure with forgings at thetop for attaching the rear wing spar and forgings at thebottom for attaching the main landing gear forward doorpost provides the load path for trans-ferring the loads from the engine mount directly to theprimary large cabin area provides comfortable space for apilot and up to thirteen passengers.

9 (Operations withmore than nine passengers are limited to countries thatissue approval.) Inside cabin dimensions are 51" highand 62" wide at the front and rear spar bulkhead loca-tions. The cabin narrows slightly toward the tailcone to52" high and 53" wide just aft of the cargo door. Totallength of the cabin from the firewall to the aft bulkhead is21 ft. 4 in. The cabin floor is flat with the exception of twofeet in the aft cabin which is five inches above the mainfloor and makes up the aft cabin baggage volume, including the pilot and aft cabin baggagearea is 427 cubic feet. Total volume aft of the pilot and frontpassenger seat locations is approximately 340 cubic feet. Entry to, and exit from the airplane is accomplishedthrough an entry door on each side of the cabin at the pilotand front passenger seat location and through a two pieceairstair-type door on the right side of the airplane just aftof the wing. A large cargo door is also provided on the leftside of the airplane directly across from the airstair doors can be opened with the flaps up or left crew entry door incorporates a conventionaldoor handle, key-operated Medco door lock, conven-tional interior door handle and window with a small tri-angular foul weather window.

10 The foul weather windowmay be opened for additional ground ventilation. Theright crew entry door incorporates a conventional out-side and inside door handle and a manually operatedinside door lock. A 4 inch deep x 5 1/2 inch Kydex stor-age area is incorporated into the interior width of boththe left and right crew doors. Both doors have a maxi-mum width of inches and a maximum height inches and will open 180 degrees forward to latchagainst the side of the passenger entry door consists of an upper and lowersection. When opened, the upper section swings upwardand the lower section drops down providing integral stepsto aid in boarding or exiting the airplane. The door open-ing is approximately 24 inches wide and 50 inches empennage consists of a conventional vertical stabi-lizer, rudder, horizontal stabilizer and elevator, all of whichare constructed of a forward and aft spar with formedsheet metal ribs and aluminum skin panels.