2013 BCA Purchase Planning Handbook

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P u r c h a s e P l a n n i n g H a n d b o o k P u r c h a s e P l a n n i n g H a n d b o o k

For an aircraft to be listed in thePurchasePl anning Handbook , a productionconforming article must have flown by

May 1 of th is year. The di mens ion s,

weights and performance characteristicsof each model listed are representative ofthe current production aircraft being builtor for which a type certificate applicationhas been f iled. The Basic Operating

Weights we publish should be represen-tative of actual production turboprop andturbofan aircraft because we ask manu-facturers to supply us with the average

weights of the last 10 commercial aircraftthat have been delivered. However, spotchecks of some ma nufacturers BOWnumbers reveal anomalies. Prospectivebuyers are advised to verify the actual

weights of aircraft with options.

The takeoff field length distances arebased on Maximum Takeoff Weightunless otherwise indicated in the tables.

Please note that all data preliminary

in the remarks section indicates thatactual aircraf t weight, dimension andperformance numbers may vary consid-erably after the model is certified anddelivery of completed aircraft begins.

Manufacturer, Modeland Type Designation

In some cases, the airplane manufacturersname is abbreviated, but the companysfull name and address can be found in theAirframe Suppliers Directory at our

website. The model name and the typedesignation also are included in this group.

BCAEquipped PricePrice estimates are first quarter, current

year dollars for the next available delivery.Some aircraft have long lead times, thus

the actual price will be higher than ourpublished price. Note well, manufacturersmay adjust prices without notification.

Piston-powered airplanes Computedretail price with at least the level ofequipment specified in the BCARequiredEquipment List

Turbine-powered airplanes Averageprice of 10 of the last 12 commercialdeliveries, if available. Some manu-facturers decline to provide us withactual prices of delivered aircraft. Theaircraft serial numbers aren't neces-sarily consecutive because of variationsin completion time and because someaircraft may be configured for non-

commercial, special missions.

CharacteristicsSeating Crew + Typical Executive

Seating/Maximum SeatingFor example, 2+8/19 indicates t hat

the aircraft requires two pilots, thereare eight seats in the typical executiveconfiguration and the aircraft is certifiedfor up 19 to passenger seats. A four-placesingle-engine aircraft is shown as 1+3/3,indicating that one pilot is required andthere are three other seats available for

How to Use the Airplane Charts

Lavatory

Aft Baggage

Compartment

Passenger CabinGalley

Cabin Length

Cockpit

ll

Cabin Length

Baggage

Cabin Length

HowToChart_0513.indd 1 4/22/13 1:03 PM


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passengers. We require two pilots for allturbofan airplanes, except for single-pilotcertified aircraft such as the Eclipse 550,Cessna Citation CJ series and SyberjetSJ30-2, which have, or will have, a largepercentage of single-pilot operators. Fourcrewmembers are specified for ultra-long-range aircraft three pilots andone fl ight attendant.

Each occupant of a turbine-poweredairplane is assumed to weigh 200 lb., thusallowing for stowed luggage and carry-onitems. In t he case of piston-engineairplanes, we assume each occupant

we ig hs 170 lb . Th er e is no lu gg ag eallowance for piston-engine airplanes.

Wing Loading MTOW divided bytotal wing area

Power Loading MTOW divided

by total rated horsepower or total ratedthrustFAR Part 36 certified noise levels

Flyover noise in A-weighted decibels(dBA) for small and turboprop aircraft.For turbofan-powered aircraft, we providePart 36 EPNdB (effective perceived noiselevels) for takeoff, sideline and approach.

DimensionsExternal length, height and spandimensions are provided for use in deter-mining hangar and/or tie-down spacerequirements.

Internal length, height and width arebased on a completed interior, including

insulation, upholstery, carpet, car petpadding and fixtures. Note well: Thesedimensions are not based upon metal-to-metal measurements. They must reflectthe actual net dimensions with all soft

goods installed. Some manufacturersprovide optimistic measurements, thusprospective buyers are advised to measureaircraft themselves.

A s show n in t he Cab in Int er io rDimensions illustration, for smallairplanes other than cabin-class models,the length is measured from the forwardbulkhead ahead of the rudder pedals tothe back of the rearmost passenger seat inits normal, upright position.

For so-called cabin-class and largeraircraft, we show the overall length ofthe passenger cabin, measured from theaft side of the forward cabin div ider tothe aft-most bulkhead of the cabin. Theaft-most point is defined by the rear side ofa baggage compartment that is accessibleto passengers in flight or the aft pressure

bulkhead. The overall length is reducedby the length of any permanent mountedsystem or structure that is installed in thefuselage ahead of the aft bulkhead. Forexample, some aircraft have full fuselagecross-section fuel tanks mounted ahead ofthe aft pressure bulkhead.

The second lengt h number is the netlength of the cabin that may be occupiedby passengers. Its measured from theaft side of t he forward cabin div iderto an aft point defined by the rear ofthe cabin f loor capable of supportingpassenger seats, the rear wall of an aftgalley or lavatory, an auxiliary pressurebulkhead or the front wall of the pres-

surized baggage compartment. Someaircraft have the same net and overallinterior length because the manufactureroffers at least one interior configuration

with the aft-most passenger seat located

next to the front wall of the aft luggagecompartment.

Interior height is measured at the centerof the cross section. It may be based onan aisle that is dropped several inchesbelow the main cabin floor that supportsthe passenger seats. Some aircrafthave dropped aisles of varying depths,resulting in less available interior heightin certain sections of the cabin, such asthe f loor sections below the passengerseats.

Two width d imensions are shown formultiengine turbine airplanes one atthe widest part of the cabin and the otherat floor level. The dimensions, however,are not completely indicative of the usablespace in a specific aircraft because of indi-

vidual variances in interior furnishings.

PowerNumber of engines, if greater than

one, and the abbreviated name of themanufacturer: Honeywell, CFMI CFM International, TCM TeledyneContinental, IAE International AeroEngines, Lyc Textron Lycoming,P&WC Pratt & Whitney Canada, RR Rolls-Royce and Wms WilliamsInternational

Output takeoff rated horsepower forpropeller-driven aircraft or pounds thrustfor turbofan aircraft. If an engine is flatrated, enabling it to produce takeoff ratedoutput at a higher than ISA (standard day)

ambient temperature, the f lat rating limitis shown as ISA+XXC. Highly flat ratedengines, i.e. engines that can producetakeoff rated thrust at a much higher thanstandard ambient temperature, typicallyprovide substantially improved highdensity altitude and high-altitude cruiseperformance.

Inspection Interval is the longest,scheduled hourly major maintena nceinterval for the engine, either t for TBOor c for compressor zone inspection.OC is shown only for engines that haveon condition repair or replace partsmaintenance.

Weights (lb.)Weight categories are listed as appropriateto each class of aircraft.

Max Ramp Maximum ramp weightfor taxi

Max Takeoff Maximum takeoffweight as determined by structural limits

Max Landing Maximum la ndingweight as determined by structural limits

Zero Fuel Maximum zero fuelweight , shown by c, indicati ng thecertified MZFW or b, a BCA-computed

weight ba sed on MT OW minus the



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weight of f uel required to fly 1.5 hr. athigh-speed cruise

Max ramp, max takeoff and max landingweights may be the same for light aircraftthat may only have a certified max takeoff

weight.EOW/BOW Empty Operating

Weight is shown for piston-poweredairplanes. Basic Operating Weight,in contrast, is based on the averageEOW weight of the last 10 commercialdeliveries, plus 200 lb. for each requiredcrewmember. We require four crew-members, three flight crew and one cabinattendant for ultra-long-range aircraft.

Basic Operating Weight, which essen-tially is EOW plus required fl ight crew,is shown for turbine-powered airplanes.EOW is based on the factory standard

weight, plus items specif ied in the BCARequired Equipment List, less fuel and oil.There is no requirement to add in the

weight of cabin stores, but some manufac-turers choose to include galley stores andpassenger supplies as part of the BOWbuild up. Life vest, life rafts and appro-priate deep-water surv ival equipmentare included in the weight buildup of the80,000+ lb., ultra-long-range aircraft.

Max Payload Zero Fuel weightminus E OW or BOW, as appropriate.For piston-engine airplanes, Max Payloadfrequently is a computed value becauseit is based on the BCA(b) computedmaximum ZFW.

Executive Payload Based on 170lb. per occupant for multiengine piston-engine airplanes and 200 lb. per occupantfor turbine-engine airplanes, as shownin the executive seating section of theCharacteristics section. Both pilots

and passengers, however, are counted asoccupants in piston-engine air planes.Only passengers are counted as occupantsin turbine-powered airplanes because therequired crew is included in the BOW.

If the E xecutive Payload exceeds theMaximum Payload, we u se MaximumPayload. Executive payload is notcomputed for single-engine pistonairplanes.

Max Fuel Usable fuel weight basedon 6.0 lb. per U.S. gallon for avgas or6.7 lb. per U.S. gallon for jet fuel. Fuelcapacity includes optional, auxiliary andlong-range tanks, unless otherwise noted.

Available Payload With Full Fuel MaxRamp weight minus the tanks-full weight,not to exceed Zero Fuel weight minusEOW or BOW

Avai lable Fuel Wit h Maximum Payload Max Ramp weight minus Zero Fuelweight, not to exceed ma xi mum fuelcapacity

Available Fuel With Executive PayloadAvailable fuel weight based on max rampminus BOW plus executive payload, up tothe actual fuel capacity

LimitsBCAlists V speeds and other limits asappropriate to the class of airplane. Theseare the abbreviations used on the charts:

VNE Never exceed speed (red line forpiston-engine airplanes)

VNO Normal operating speed (top of

the green arc for piston-engine airplanes)VMO Maxi mum operating speed

(red line for turbine-powered airplanes)MMO Maximum operating Mach

number (red line for turbofan-powered

airplanes and a few turboprop airplanes)FL/VMO Transition altitude at which

Vmo equals Mmo (large turboprop andturbofan aircraft)

VA Maneuvering speed (except forcertain large turboprop and all turbofanaircraft)

VDEC Accelerate/stop decision speed(multiengine piston and light multiengineturboprop airplanes)

VMCA Minimum control airspeed,airborne (multiengine piston and lightmultiengine turboprop airplanes)

VSO Max imum stalling speed,landing configuration (single-engineairplanes)

VX Best angle-of-climb speed(single-engine airplanes)

VXSE Best angle-of-climb speed,

one-engine inoperative (multienginepiston and multiengine turbopropairplanes under 12,500 lb.)

VY Best rate-of-climb speed (single-engine airplanes)

VYSE Best rate-of-climb speed, one-engine inoperative (multiengine pistonand multiengine turboprop airplanesunder 12,500 lb.).

V2 Takeoff safety speed (largeturboprops and turbofan airplanes)

VREF Reference landing approachspeed (large turboprops and turbofanairplanes, four passengers, NBAA IFRreserves; eight passengers for ultra-long-range aircraft)

PSI Cabin pressure differential (allpressurized airplanes)

Airport PerformanceA pproved Fl ight M a nua l t akeof frunway performance is shown forsea-level, standard day and for 5,000-ft.elevation/25C day density altitude.

All-engine takeoff distance (TO) is shownfor single-engine and multiengine piston,and turboprop airplanes with an MTOWof less than 12,500 lb. Takeoff distancesand speeds assume Maximum Takeoff

weight, unless otherwise noted.Accelerate/Stop distance (A/S) is shown

for small multiengine piston and small

turboprop airplanes. Takeoff field length(TOFL), the greater of the one-engineinoperative (OEI) takeoff distance or theaccelerate/stop distance, is shown for FARPart 23 Commuter Category and FARPart 25 airplanes. If the accelerate/stopand accelerate/stop distances are equal,the TOFL is the balanced field length.

Landing distance ( LD) is shownfor FAR Part 23 Commuter Categoryand FAR Part 25 Transport Categoryairplanes. The landing weight is BOWplus four passengers and NBAA IFR fuel

P u r c h a s e P l a n n i n g H a n d b o o k

NBAA IFR RANGE PROFILE

Climb to 5,000 ft andHold Five Minutes forClearance to Alternate

Standard InstrumentApproach(Fuel = 5 MinuteHold @ 5,000 ft)

Conditions:Origin, destination and alternate

airports are sea level elevation, ISA, zero wind,

maximum of three cruise levels,

30-minute VFR fuel reserve at alternate.

Ste

pC

limb

IntermediateCruise

Taxi:10

akeoff:01

3,0

00-fpmD

escent

toInitialApproachFix

3,0

00-fpmD

escentto

VFRLandingatAlternate

Long-Range Cruisefor 200 nmAlternate

Initial Cruise

Final Cruise

Ste

pCl

imb

Cli

mb

to

200

nm

Alt

ern

ate

Cru

ise

Altit

ud

e



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reserves. We assume th at 80,000+ lb.ultra-long-range aircraft will have eightpassengers on board.

The V2 and V speeds are useful forreference when comparing the TOFLand LD numbers because they provide anindication of potential minimum-lengthrunway performance when low RCR orrunway gradient is a factor.

BCAlists two additional numbers forlarge turboprop- and turbofan-poweredairplanes. First, we publish the mission

weight, which is the lower of: (1) the actualtakeoff weight with four passengers (eightpassengers for ultra-long-range aircraft)and full fuel when departing from a5,000-ft./25C airport or (2) the maximumallowable takeoff weight when departing

with the same passenger load and at the

same density altitude.For two-engine aircraft, the missionweight, when departing from a 5,000-ft./ISA+20C airport, may be less than the

MTOW because of FAR Part 25 second-segment, one-engine-inoperative, climbperformance requirements. Aircraft

wit h h ighly f lat-rated eng ines a re lesslikely to have a Mission Weight that isperformance limited when departingfrom hot and high airports.

For three-engine aircraft, the missionweight usually is based on full tanks andthe actual number of passengers, ratherthan being performance limited.

Second, we publish the NBAA I FR

range for the hot and high departuremission weight, assuming a transitioninto standard day, ISA flight conditionsafter takeoff. For purposes of computingNBAA IFR range, the aircraft is flownat the long-range cruise speed shown inthe Cruise block or at the same speed asshown in the Range block.

ClimbThe all-engine time to climb provides anindication of overall climb performance,especially if the aircraft has an all-engineservice ceili ng well above our sampletop-of-climb altitudes. We provide theall-engine time to climb to one of three

specific altitudes, based on type of aircraftdeparting at MTOW from a sea-level,standard-day airport: (1) FL 100 (10,000ft.) for normally aspirated single-engineand multiengine piston aircraft, pluspressurized single-engine piston aircraftand unpressurized turboprop aircraft;(2) FL 250 for pressurized single-engineand multi-engine turboprop aircraft; or(3) FL 370 for turbofan-powered aircraft.

These data are published as time-to-climbin minutes/climb altitude. For example,if a non-pressurized twin-engine piston

aircraft can depart from a sea-level airportat MTOW and climb to 10,000 ft. in 8min., the time to climb is expressed as 8/FL 100.

We also publish the init ial a ll-engineclimb feet per nautical mile gradient, plusinitial engine-out climb rate and gradient,for single-engine and multiengine pistonsand turboprops with MTOWs of 12,500lb. or less.

The one-engine-inoperat ive (OE I)climb rate for multi-engine aircraft at

MTOW is der ived from the AirplaneFlight Manual. OEI climb rate andgradient is based on landing gear retractedand wing flaps in the takeoff configu-ration used to compute the publishedtakeoff distance. The climb gradient forsuch airplanes is obtained by dividing

the product of the climb rate (fpm) in theAirplane Flight Manual times 60 by theV or V climb speed, as appropriate.

The OEI cl imb gr adients we showfor FAR Part 23 Commuter Categoryand FAR Part 25 Transport Categoryaircraft are the second-segment netclimb performance numbers publishedin the AFMs. Please note: The AFMnet second-segment climb performancenumbers are adjusted downward by 0.8%to compensate for variations in pilottechnique and ambient conditions.

The OEI climb gradient is computedat the same flap configuration used tocalculate the takeoff field length.

Ceilings (ft.)Maximum Certif icated Altitude

Max imum allowable operat ing alt itude

determined by airworthiness authoritiesAll-Engine Service Ceiling Maximum

altitude at which at least a 100-fpm rateof climb can be attained, assuming t heaircraft departed a sea-level, standard-dayairport at MTOW and climbed direct lyto altitude

OEI (Engine Out) Service CeilingMaximum altitude at which a 50-fpm rateof climb can be attained, assuming t heaircraft departed a sea-level, standard-dayairport at MTOW and climbed direct lyto altitude

Sea-Level Cabin (SLC) Altitude Ma xi mum cr ui se alt it ude at which a14.7-psia, sea-level cabin altitude can bemaintained in a pressurized airplane

Cruise

Cruise performance is computed usingEOW with four occupants or BOW withfour passengers and one-half fuel load.Ultra-long-range aircraft carry eightpassengers for purposes of computingcruise performance. Assume 170 lb. foreach occupant of a piston-engine airplaneand 200 lb. for each occupant of a turbine-powered aircraft.

Long Range True Air Speed (TAS),fuel flow in pounds/hour, flight level (FL)cruise altitude and specific range for long-range cruise by the manufacturer

Recommended (Piston-Engine Airplanes)

TAS, fuel flow in pounds/hour, FLcruise altitude and specific range for

normal cruise performance specif ied bythe manufacturer

High Speed TAS, fuel flow inpounds/hour, FL cruise altitude and



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specific range for short-range, high-speed performance specified by themanufacturer

Speed, fuel f low, specific ra nge andaltitude in each category are based onone mid-weight cru ise point and thesedata reflect standard day conditions.

They are not an average for the overa llmission and they are not representativeof the above standard day temperatures atcruise altitudes commonly encountered ineveryday operations.

BCA imposes a 12,000-ft. maximumcabin altitude requirement on CAR3/FAR Part 23 normally aspirated aircraft.

Turbocharged a irplanes are limited toFL 250, providing they are fitted withsupplemental oxygen systems havingsufficient capacity for all occupants for

the duration of the mission. PressurizedCAR3/FAR Part 23 aircraft are limitedto a maximum cabin altitude of 10,000ft. For FAR Part 23 Commuter Categoryand FAR Part 25 aircraft, the maximumcabin altitude for computing cruiseperformance is 8,000 ft.

To conserve space, we use f light levels(FL) for all cruise altitudes, which isappropriate considering that we assumestandard day ambient temperature andpressure conditions. Cruise performanceis subject to BCAs verification.

RangeBCA shows various paper missions for

each aircraft that illustrate range versuspayload tradeoffs, runway and cruiseperformance, plus fuel efficiency. Similarto the cruise profile calculations, BCAlimits the maximum altitude to 12,000 ft.for normally aspirated, non-pressurizedCAR3/FAR Part 23 aircraft, 25,000 ft.for turbocharged airplanes with supple-mental oxygen, 10,000 ft. cabin altitude

for pressurized C AR 3/FAR Part 23airplanes and 8,000 ft. cabin altitude forFAR Part 23 Commuter Category or FARPart 25 aircraft.

Seats-Full Range (Single-Engine Piston

Airp lanes) Based on typical executiveconfiguration with all seats filled with 170lb. occupants, with maximum available fuelless 45-min. IFR fuel reserves. We use thelower of seats full or maximum payload

Tanks Ful l Range (Single-Eng ine Piston

Airplanes) Based on one 170-lb. pilot,full fuel less 45-min. IFR fuel reserves

Executive Payload(Multiengine PistonAirplanes and Single-Engine Turboprops) Based on typical executive configuration

with all seats filled with 170-lb. occupants,maximum available fuel less 45-min. IFRfuel reserves. We use the lower of seats

full or maximum payload.Maximum Fuel With Available Payload

(Single-Engine Turboprops) Based onBOW, plus full f uel and the maximumavailable payload up to maximum ramp

weight . Range is based on ar rivi ng atdestination with NBAA IFR fuel reserves,but only a 100-mi. alternate is required.

Ferry (Multiengine Piston Airplanes and

Single-Engine Turboprops) Based on one170-lb. pilot, maximum fuel less 45-min.IFR fuel reserves

Please note: None of the m issionsfor piston-engine aircraft includes fuelfor diverting to an alternate. However,single-engine turboprops are required to

have NBAA IFR fuel reserves, but only a100 mi. alternate is required.

NBAA IFR range format cruiseprofiles, having a 200 mi. alternate, areused for FAR Part 25 Transport Categoryturbine-powered aircraft. In the case ofFAR Part 23 turboprops, including thosecertified in the Commuter Category, andFAR Part 23 turbofan aircraft , only a 100

mi. alternate is needed. The differencein alternate requi rements should bekept in mind when comparing rangeperformance of various classes of aircraft.

Avai lable Fuel With Maximum Payload

(Multiengine Turbine Airplanes) Basedon aircraft loaded to maximum zero fuel

weight with maximum available fuel up tomaximum ramp weight, less NBAA IFRfuel reserves at destination

Avai lable Payload Wit h Maximum Fuel

(Multiengine Turbine Airplanes) Basedon BOW plus full fuel and ma ximumavailable payload up to maximum ramp

weight . Ra nge ba sed on NBA A IFRreserves at destination.

Full/Maximum Fuel With Four Passengers

(Multiengine Turbine Airplanes) Based onBOW plus four 200-lb. passengers and the

lesser of full fuel or maximum availablefuel up to maximum ramp weight. Ultra-long-range aircraft must have eightpassengers on board.

Ferry (Multiengine Turbine Airplanes)Based on BOW, required crew and fullfuel, arriving at destination with NBAAIFR fuel reserves

We al low 2,00 0-f t. increment stepclimbs above the initial cruise altitude toimprove specific range performance, eventhough current air traffic rules in North

America prov ide for 4,000-ft . a ltitudesemicircular directional traffic separationabove FL 290. The altitude shown in therange section is the highest cruise altitude

for the trip not the initial cruise ormid-mission altitude.

The range profiles are in nautical miles,and the average speed is computed bydividing that distance by the total fl ighttime or weight-off-wheels time en route.

The Fuel Used or Trip Fuel includes thefuel consumed for start, tax i, takeoff,cruise, descent and landing approach butnot after-landing taxi or reserves.

The Specif ic Ra nge is obt ai ned bydividing the distance flown by the totalfuel burn. The Altitude is the highestcruise altitude achieved on the specificmission profile shown.

MissionsVarious paper mi ssions are computedto illustrate the runway requirements,speeds, fuel burns and specific range,plus cruise altitudes. The mission rangesare chosen to be representative for theairplane category. All fixed-distancemissions are flown with four passengerson board, except for ultra-long-rangeairplanes, which have eight passengers onboard. The pilot is counted as a passengeron board piston-engine airplanes. Ifan airplane cannot complete a specific

P u r c h a s e P l a n n i n g H a n d b o o k

Liftoff35'

Gear Up

Flaps Up (If Applicable)

Obsta

cle

Accelerate-GoTakeoff Field Length

Initial OEI Climb(Gear Down)

Obstacle

HeightAbove

Reference

Zero

First

Segment

Crucial Second

Segment

Third or Transition

Segment

Fourth or Final

Segment

OEI En RouteClimb Performance

Takeoff Flight Path/OEI Climb Gradient (Gear Up)

BrakeRelease

ReferenceZero Actual Climb Gradient Required

to Clear Close-in Obstruction

Accelerate-StopDistance

Distance From Reference ZeroDistance From Reference Zero

BrakeRelease

ReferenceZero Actual Climb Gradient Required

to Clear Close-in Obstruction

Accelerate-StopDistance

Flaps Up (If Applicable)

FAR Part 25 and Part 23 Commuter Category OEI Climb Performance



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fixed distance mission with the appro-priate payload, BCAshows a reduction ofpayload in the remarks section or marksthe fields NP (Not Possible) at our option.

Runway performance is obtained fromthe Approved Airplane Flight Manual.

Takeoff distance is listed for single-engineairplanes; accelerate/stop distance is listedfor piston twins and light turboprops; andtakeoff field length, which often corre-sponds to balanced field length, is usedfor FAR Part 23 Commuter Category andFAR Part 25 large Transport Categoryairplanes.

Flight Time (takeoff to touchdown,or weight-off-wheels, time) is shown forturbine air planes. Some piston-enginemanufacturers also include taxi time,resulting in a chock-to-chock, Block

Time measurement. Fuel Used, though,is the actual block fuel burn for each typeof aircraf t, but it does not include fuelreserves. The cruise altitude shown is that

which is specified by the manufacturer forfixed-distance missions.

200 nm (Piston-engine airplanes)500 nm (Piston-engine airplanes)300 nm (Turbine-engine airplanes,

except ultra-long range)600 nm (Turbine-engine airplanes,

except ultra-long range)1,000 nm (All turbine-engine

airplanes)3,000 nm (Ultra-long-range

turbine-engine airplanes)

6,000 nm ( Ultra-long-rangeturbine-engine airplanes)

RemarksIn this section, BCAgenerally includesthe base price, i f it is available orapplicable; the certification basis and

year; and any notes about e stimat ions,limitations or qualifications regardingspecifications, performance or price.

Al l pr ices are in 2013 dol lars, FOB at aU.S. delivery point, unless otherwisenoted. The certification basis includesthe regulation under which the a irplane

was originally ty pe certi fied, the yea rin which it was originally certified and,

if applicable, subsequent years duringwhich the airplane was re-certified.

GeneralThe fol low ing abbrev iat ions are usedthroughout the tables: NA means notavailable; indicates the informationis not applicable; and NP signifies thatspecific performance is not possible. BCA

Jets 20,000 lb

Jets 12,500 lb

Turboprops 12,500 lb

Single-Engine Turboprops

Multiengine Pistons, Turbocharged

Multiengine Pistons

Single-Engine Pistons, Pressurized

Single-Engine Pistons, Turbocharged

Single-Engine Pistons

lRequired lDual required

BCARequired Equipment List

POWERPLANT SYSTEMS

Batt temp indicator (nicad only, for each battery) l l l l l

Engine synchronization l l

Fire detection, each engine l l l l l

Fire extinguishing, each engine l l l

Propeller, reversible pitch l l lPropellers, synchronized l l

Thrust reversers/attenuators l l

AVIONICS

ADF l l l l lAir data computer l l l lAltitude alerter l l l l l

Altitude encoder l l l l l l l l l l

Antennas, headsets, microphones l l l l l l l l l lAudio control panel l l l l l l l l l lAutomatic flight guidance, 2-axis, alt hold l l l Automatic flight guidance, 3-axis, alt hold l l l l l l l

DME l l l l lEFIS l l l lELT l l l l l l l l l lFlight director l l l lFMS, TSO C115 or GPS, TSO C129 IFR approach l l l l l l l l l lGlideslope receiver l l l l l l l l l lHSI, slaved (or equivalent EFIS function) l l l l l l l l l lMarker beacon receiver l l l l l l l l l l

Radio altimeter l l l l l

Radiotelephone l l l

RMI (or equivalent function on EFIS display) l l l l lRVSM certification l l

TAWS l l

TCAS I/II (FAR Part 25 airplanes only) l lTransponder l l l l l l l l l lVHF comm, 25-kHz spacing l l l l l l l l l lVHF comm, 8.33-kHz spacing l l

VHF nav, 360-channel l l l l l l l l l lWeather radar l l l l l

GENERAL

Air conditioning, vapor cycle (not required with APU) l l l l l l

Anti-skid brakes l l l

APU (required for air-start engines, ACM air conditioning) l

Cabin/cockpit dividers l l l

Corrosion-proofing, internal l l l l l l l l l lExterior paint, tinted windows l l l l l l l l l lFire extinguisher, cabin l l l l l

Fire extinguisher, cockpit l l l l l l l l l lFuel tanks, long-range l l l l l l l l

Ground power jack l l l l l l l l l lHeadrests, air vents, all seats l l l l l l l l l lLavatory l l lLights, strobe/anti-collision beacon, navigation, landing/taxi l l l l l l l l l lLights, internally lighted instrument, cockpit flood, courtesy l l l l l l l l l lOxygen, supplemental, all seats l l l l l l lRefreshment center l l l lSeats, crew, articulating l l l l l l l l l lSeats, passenger, reclining l l l l l l l l l l

Shoulder harness, all seats and crew with inertia reel l l l l l l l l l lTables, cabin work l l l l l

ICE AND RAIN PROTECTION

Alternate static pressure source (not required with 2 DADC) l l l l l l lApproval, flight into known icing l l l l l l l lIce protection plates l l

Pitot heat l l l l l l l l l lStatic wicks l l l l l l l l l lWindshield rain removal, mechanical or repellent coating l l l lINSTRUMENTATION

Angle-of-attack stall margin indicator l l

EGT l l l l l

IVSI (or equivalent EFIS, DADC function) l l l lOutside air temperature gauge l l l l l l l l l lPrimary flight instruments l l l l l l l l l l



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B u s i n e s s A i r p l a n e sB u s i n e s s A i r p l a n e s

SINGLE-ENGINE PISTONS NORMALLY ASPIRATEDManufacturer Cirrus Design Cessna Piper Aircraft Cirrus Design Mooney

Model SR20SkylaneCE-182T

ArrowPA-28R-201

SR22Ovation2 GX

M-20R

BCAEquipped Price $319,900 $398,100 $462,400 $479,900 $495,000

Characteristics

Seating 1+3/4 1+3/3 1+3/3 1+3/4 1+3/4

Wing Loading 21.0 17.8 16.2 23.5 19.3

Power Loading 15.25 13.48 13.75 11.61 12.03

Noise (dBA) 83.4 77.7 77.7 83.7 78.7

ExternalDimensions

(ft.)

Length 26.0 29.0 24.7 26.0 26.9Height 8.9 9.3 7.9 8.9 8.3

Span 38.3 36.0 35.4 38.3 36.1

InternalDimensions

(ft.)

Length 8.0 7.2 7.7 8.0 8.1

Height 4.1 4.0 3.7 4.1 3.7

Width 4.1 3.5 3.5 4.1 3.6

Power

EngineCont

IO-360-ESLyc

IO-540-AB1A5Lyc

IO-360-C1C6Cont

IO-550-NCont

IO-550-G

Output (hp) 200 230 200 310 280

Inspection Interval 2,000t 2,000t 2,000t 2,000t 2,000t

Weights (lb.)

Max Ramp 3,050 3,110 2,758 3,600 3,374

Max Takeoff 3,050 3,100 2,750 3,600 3,368

Max Landing 3,050 2,950 2,750 3,600 3,200

Zero Fuel 2,900c 2,976b 2,636b 3,400c 3,224b

EOW 2,128 1,968 1,798 2,260 2,260

Max Payload 772 1,008 838 1,140 964

Useful Load 922 1,142 960 1,340 1,114Max Baggage 130 200 200 130 120

Max Fuel 336 522 432 552 600

Available Payload w/Max Fuel 586 620 528 788 514

Available Fuel w/Max Payload 150 135 122 200 150

Limits

VNE 204 175 183 205 195

VNO 166 140 146 176 174

VA 131 110 118 140 127

AirportPerformance

TO (SL elev./ISA temp.) 2,221 1,514 1,600 1,756 1,620

TO (5,000 elev.@25C) 3,752 2,708 3,250 3,016 2,500

VSO 61 50 55 64 59

VX 83 65 78 88 80

VY 96 80 90 108 105

ClimbTime to Climb (min.)/Altit ude 16/FL 100 15/FL 100 16/FL 100 11/FL 100 12/FL 100

Initial Gradient (ft./nm) 581 694 560 775 714

Ceiling (ft.) Service 17,500 18,100 16,200 17,500 20,000

Cruise

Long

Range

TAS 140 125 124 160 163

Fuel Flow 50 61 51 68 50

Altitude FL 080 FL 120 FL 100 FL 080 FL 120

Specific Range 2.800 2.049 2.431 2.353 3.260

Recommended

TAS 152 135 130 171 186

Fuel Flow 63 69 68 92 84


Specific Range 2.413 1.957 1.912 1.859 2.214

High Speed

TAS 159 144 137 180 190

Fuel Flow 70 83 76 107 96


Specific Range 2.271 1.735 1.803 1.682 1.979

Ranges

Seats Full

Nautical Miles 584 770 537 1,118 1,075

Average Speed 140 123 121 162 161

Fuel Used 210 401 156 492 438

Specific Range/Altitude 2.781/FL 080 1.920/FL 120 3.442/FL 070 2.272/FL 080 2.454/FL 120

Tanks Full

Nautical Miles 764 927 926 1,118 1,465

Average Speed 140 123 121 162 173

Fuel Used 275 477 408 492 558


Missions(4 occupants)

200 nm

Runway 1,446 1,515 1,600 1,303 1,230

Block Time 1+18 1+37 1+29 1+09 1+13

Fuel Used 100 123 125 127 115


500 nm

Runway 1,446 1,515 1,600 1,519 1,290

Block Time 3+17 3+52 3+50 2+49 2+58

Fuel Used 226 269 278 305 221


Remarks

Suggested Base Price $319,900 $398,100 $431,490 $479,900 $495,000

Certification Basis

FAR 23, 1999Includes Garmin

Perspective avionics.

FAR 23, 1996/2001Includes Garmin G1000with GFC700 autopilot.

CAR 3, 1976/2001Includes Garmin G500.

FAR 23, 2000Includes Garmin

Perspective avionics;MTOW increased by

200 lb.

CAR 3/FAR 23, 1955/94Includes Garmin G1000.


10/25

www.AviationWeek.com/bca Business & Commercial Aviation May 2013 35


SINGLE-ENGINE PISTONS NORMALLY ASPIRATEDManufacturer Mooney Cessna GA8 Airvan (Pty) Ltd. Beechcraft Corp.

ModelOvation3M-20R

StationairCE-206H

AirvanGA-8

Bonanza G36G36

BCAEquipped Price $520,000 $557,500 $726,960 $765,900

Characteristics

Seating 1+3/4 1+5/5 1+6/7 1+4/5

Wing Loading 19.3 20.7 20.7 20.2

Power Loading 10.86 12.00 13.33 12.17

Noise (dBA) NA 84.5 84.9 76.7

ExternalDimensions

(ft.)

Length 26.9 28.3 29.3 27.5Height 8.3 9.3 12.8 8.6

Span 36.1 36.0 40.7 33.5

InternalDimensions

(ft.)

Length 8.1 9.3 11.6 12.6

Height 3.7 4.1 3.7 4.2

Width 3.6 3.5 4.2 3.5

Power

EngineCont

IO-550-G-APLyc

IO-540-AC1A5Lyc

IO-540-K1A5Cont

IO-550-B

Output (hp) 310 300 300 300

Inspection Interval 2,000t 2,000t 2,000t 1,700t

Weights (lb.)

Max Ramp 3,374 3,614 4,014 3,663

Max Takeoff 3,368 3,600 4,000 3,650

Max Landing 3,200 3,600 4,000 3,650

Zero Fuel 3,197b 3,449b 3,849b 3,509b

EOW 2,260 2,254 2,241 2,630

Max Payload 937 1,195 1,608 879

Useful Load 1,114 1,360 1,773 1,033

Max Baggage 120 180 180 670

Max Fuel 600 522 540 444

Available Payload w/Max Fuel 514 838 1,233 589

Available Fuel w/Max Payload 177 166 166 154

Limits

VNE 195 182 185 203

VNO 174 149 143 165

VA 127 125 121 139

AirportPerformance

TO (SL elev./ISA temp.) 1,620 1,860 1,860 1,913

TO (5,000 elev.@25C) 2,500 3,670 3,670 3,450

VSO 59 57 57 59

VX 80 70 70 84

VY 105 86 86 100

ClimbTime to Climb (min.)/Altit ude 10/FL 100 15/FL 100 15/FL 100 14/FL 100

Initial Gradient (ft./nm) NA 691 787 730

Ceiling (ft.) Service NA 15,700 20,000 18,500

Cruise

Long

Range

TAS 163 127 127 160

Fuel Flow 50 78 78 71

Altitude FL 120 FL 120 FL 120 FL 80

Specific Range 3.260 1.628 1.628 2.254

Recommended

TAS 186 135 135 167

Fuel Flow 84 88 88 86


Specific Range 2.214 1.534 1.534 1.942

High Speed

TAS 196 142 142 174

Fuel Flow 114 101 101 94


Specific Range 1.719 1.406 1.406 1.851

Ranges

Seats Full

Nautical Miles 1,075 415 487 273

Average Speed 161 123 124 153

Fuel Used 438 295 339 140

Specific Range/Altitude 2.454/FL 120 1.407/FL 120 1.437/FL 120 1.950/FL 040

Tanks Full

Nautical Miles 1,465 690 690 859

Average Speed 173 125 125 159

Fuel Used 558 464 464 403



200 nm

Runway 1,230 1,860 1,860 1,694

Block Time 1+13 1+38 1+38 1+11

Fuel Used 115 157 157 130


500 nm

Runway 1,290 1,860 1,860 2,054

Block Time 2+58 3+55 3+55 2+54

Fuel Used 221 339 339 304


Remarks

Suggested Base Price $520,000 $557,500 $726,960 $759,000

Certification BasisCAR 3/FAR 23, 1955/94;

STC SA02483CHIncludes Garmin G1000.

FAR 23, 1998Includes Garmin G1000 with

GFC700 autopilot.

FAR 23 A 54

All data preliminary;includes Garmin G500.

CAR 3, 1956/69/83/2005

Restyled interior;new, lightweight A/C system;Garmin G1000 with SVS.


11/25



SINGLE-ENGINE PISTONS TURBOCHARGEDManufacturer Cessna Cessna Cirrus Design Cessna

ModelTurbo Skylane

CE-T182TSkylane JT-A

CE-J182TSR22TSR 22

Turbo StationairCE-T206H

BCAEquipped Price $443,500 $515,000 $569,900 $597,500

Characteristics

Seating 1+3/3 1+3/3 1+3/4 1+5/5

Wing Loading 17.8 17.8 23.5 20.7

Power Loading 13.19 13.66 11.43 11.61

Noise (dBA) 75.4 NA 80.3 75.8

ExternalDimensions

(ft.)

Length 29.0 28.5 26.0 28.3Height 9.3 9.3 8.9 9.3

Span 36.0 36.0 38.3 36.0

InternalDimensions

(ft.)

Length 7.2 7.2 8.0 9.3

Height 4.0 4.0 4.1 4.1

Width 3.5 3.5 4.1 3.7

Power

EngineLyc

TIO-540-AK1ASMA

SR305-230E-C1Cont

TSIO-550-KLyc

TIO-540-AJ1A

Output (hp) 235 227 315 310

Inspection Interval 2,000t NA 2,000t 2,000t

Weights (lb.)

Max Ramp 3,112 3,110 3,609 3,617

Max Takeoff 3,100 3,100 3,600 3,600

Max Landing 2,950 2,950 3,600 3,600

Zero Fuel 2,953b NA 3,400c 3,429b

EOW 2,029 2,092 2,342 2,336

Max Payload 924 NA 1,058 1,093

Useful Load 1,083 1,018 1,267 1,281Max Baggage 200 200 130 180

Max Fuel 522 583 552 522

Available Payload w/Max Fuel 561 435 715 759

Available Fuel w/Max Payload 159 NA 209 188

Limits

VNE 175 NA 205 182

VNO 140 NA 176 149

VA 110 NA 140 125

AirportPerformance

TO (SL elev./ISA Temp.) 1,385 1,385 1,517 1,740

TO (5,000 elev.@25C) 1,928 NA 2,268 2,470

VSO 50 NA 64 57

VX 64 NA 88 69

VY 84 NA 103 89

ClimbTime to Climb (min.)/Altit ude 10/FL 100 NA/FL 100 7/FL 100 11/FL 100

Initial Gradient (ft./nm) 743 NA 782 724

Ceilings (ft.)Certificated 20,000 20,000 25,000 25,000

Service 20,000 20,000 25,000 27,000

Cruise

Long

Range

TAS 132 NA 171 137

Fuel Flow 62 NA 76 85


Specific Range 2.129 NA 2.250 1.612

Recommended

TAS 158 NA 201 155




High Speed

TAS 165 156 213 164




Ranges

Seats Full

Nautical Miles 547 NA 1,021 200

Average Speed 134 NA 171 139

Fuel Used 304 NA 486 185

Specific Range/Altitude 1.799/FL 200 NA/NA 2.101/FL 250 1.081/FL 200

Tanks Full

Nautical Miles 915 1,025 1,021 618

Average Speed 134 NA 171 137


Specific Range/Altitude 1.922/FL 200 NA/FL 140 2.101/FL 250 1.346/FL 240


200 nm

Runway 1,385 NA 1,405 1,743

Block Time 1+24 NA 1+08 1+25



500 nm

Runway 1,385 NA 1,699 1,743

Block Time 3+14 NA 2+28 3+21



Remarks

Suggested Base Price $443,500 $515,000 $544,900 $597,500

Certification BasisFAR 23, 2001

Includes Garmin G1000with GFC700 autopilot.

FAR 23 pending

All data preliminary;includes Garmin G1000with GFC700 autopilot.

FAR 23, 2010

Includes Perspective GlobalConnect worldwide weather;

200-lb. MTOW increase.

FAR 23, 1998Includes Garmin G1000with GFC700 autopilot.


12/25



SINGLE-ENGINE PISTONS TURBOCHARGEDManufacturer Mooney Cessna GA8 Airvan (Pty) Ltd.

ModelAcclaim Type S

MO-20TNCorvalis TTX

LC41-550-FGGA8 Airvan TCGA8-320 TC

BCAEquipped Price $635,000 $733,950 $761,030

Characteristics

Seating 1+3/3 1+3/3 1+6/7

Wing Loading 19.2 25.5 20.7

Power Loading 12.03 11.61 13.13

Noise (dBA) 78.0 81.5 85.4

ExternalDimensions

(ft.)

Length 26.9 25.2 28.3Height 8.3 9.0 9.3

Span 36.4 36.0 36.0

InternalDimensions

(ft.)

Length 8.1 7.9 11.6

Height 3.7 4.1 3.7

Width 3.6 4.0 4.2

Power

EngineCont

TSIO-550-GCont

TSIO-550-CLyc

TIO-540-AH1A

Output (hp) 280 310 320

Inspection Interval 2,000t 2,000t 1,800t

Weights (lb.)

Max Ramp 3,374 3,600 4,214

Max Takeoff 3,368 3,600 4,200

Max Landing 3,200 3,420 4,000

Zero Fuel 3,173b 3,300c 4,053b

EOW 2,378 2,600 2,349

Max Payload 795 700 1,704

Useful Load 996 1,000 1,865Max Baggage 120 120 180

Max Fuel 612 612 540

Available Payload w/Max Fuel 384 388 1,325

Available Fuel w/Max Payload 201 300 161

Limits

VNE 195 230 185

VNO 174 181 143

VA 127 158 121

AirportPerformance

TO (SL elev./ISA Temp.) 2,100 1,900 1,840

TO (5,000 elev.@25C) 3,100 2,460 2,788

VSO 60 61 61

VX 80 82 71

VY 105 110 81

ClimbTime to Climb (min.)/Altit ude 7/FL 100 7/FL 100 13/FL 100

Initial Gradient (ft./nm) 770 701 825

Ceilings (ft.)Certificated 25,000 25,000 20,000

Service 25,000 25,000 20,000

Cruise

Long

Range

TAS 215 208 125

Fuel Flow 99 78 68

Altitude FL 250 FL 250 FL 200

Specific Range 2.172 2.667 1.838

Recommended

TAS 227 227 130

Fuel Flow 128 130 78



High Speed

TAS 242 235 135

Fuel Flow 130 152 98



Ranges

Seats Full

Nautical Miles 500 450 233

Average Speed 178 199 125

Fuel Used 259 262 220

Specific Range/Altitude 1.931/FL 160 1.718/FL 250 1.059/FL 200

Tanks Full

Nautical Miles 1,122 1,189 618


Fuel Used 539 539 459



200 nm

Runway 1,300 1,900 1,743

Block Time 1+05 1+05 1+35

Fuel Used 139 150 125


500 nm

Runway 1,380 1,900 1,743

Block Time 2+54 2+24 3+30

Fuel Used 259 336 373


Remarks

Suggested Base Price $635,000 $733,950 $597,500

Certification Basis CAR 3, 1955/89/2006Includes Garmin G1000.

FAR 23Includes Garmin G2000with GFC700 autopilot.

FAR 23, 1998

All data preliiminary;includes Garmin G1000with GFC700 autopilot.

During recent years, the U.S.Federal Trade Commission hasconducted investigations intothe practice of certain indus-tries in fixing and advertisinglist prices. It is the position ofthe FTC that it is deceptive tothe public and against the lawfor list prices of any product tobe specified or advertised ina trade area if the majority ofsales are made at less thanthose prices.

BCA is not in a position toknow the prices for most of

the sales in each trading areain the United States for eachof the products in this issue.Therefore, the prices shown inthe tables and text in the Pur-chase Planning Handbook arebased on suggested list pricesfurnished to us by the manu-facturers or distributors, or onprices estimated by the editors.It may be possible to purchasesome items in your trading areaat prices less than those report-ed in this issue of BCA. Also,almost all manufacturers anddistributors caution that prices

are subject to change withoutnotice.

NOTICE TO READERS


13/25



SINGLE-ENGINE PISTONS PRESSURIZEDManufacturer Piper Aircraft Piper Aircraft

ModelMalibu MatrixPA-46R-350

Malibu MiragePA-46-350P

BCAEquipped Price $1,014,950 $1,178,875

Characteristics

Seating 1+4/5 1+4/5

Wing Loading 24.8 24.8

Power Loading 12.40 12.40

Noise (dBA) 81.0 81.0

ExternalDimensions

(ft.)

Length 28.9 28.9Height 11.3 11.3

Span 43.0 43.0

InternalDimensions

(ft.)

Length 12.4 12.4

Height 3.9 3.9

Width 4.2 4.2

Power

EngineLyc

TIO-540-AE2ALyc

TIO-540-AE2A

Output (hp) 350 350

Inspection Interval 2,000t 2,000t

Weights (lb.)

Max Ramp 4,358 4,358

Max Takeoff 4,340 4,340

Max Landing 4,123 4,123

Zero Fuel 4,123c 4,123c

EOW 2,969 3,146

Max Payload 1,154 977

Useful Load 1,389 1,212

Max Baggage 200 200

Max Fuel 720 720

Available Payload w/Max Fuel 669 492

Available Fuel w/Max Payload 235 235

Limits

VNE 198 198

VNO 168 168

VA 133 133

PSI 5.5 5.5

AirportPerformance

TO (SL elev./ISA temp.) 2,090 2,090

TO (5,000 elev.@25C) 2,977 2,977

VSO 58 58

VX 81 81

VY 110 110

ClimbTime to Climb (min.)/Altit ude 8/FL 100 8/FL 100

Initial Gradient (ft./nm) 703 703

Ceilings (ft.)

Certificated 25,000 25,000

Service 25,000 25,000

Sea-Level Cabin 12,300

Cruise

Long

Range

TAS 156 156

Fuel Flow 66 66

Altitude FL 250 FL 250

Specific Range 2.364 2.364

Recommended

TAS 203 203

Fuel Flow 108 108



High Speed

TAS 213 213

Fuel Flow 120 120



Ranges

Seats Full

Nautical Miles 867 535

Average Speed 151 138

Fuel Used 457 312

Specific Range/Altitude 1.897/FL 200 1.715/FL 120

Tanks Full

Nautical Miles 1,343 1,343


Fuel Used 658 670



200 nm

Runway 2,090 2,090

Block Time 1+07 1+06

Fuel Used 168 167


500 nm

Runway 2,090 2,090


Fuel Used 350 350


Remarks

Suggested Base Price $939,950 $1,078,875

Certification Basis

FAR 23,

1983/88Includes GarminG1000; FIKI

optional.

FAR 23,

1983/88Includes GarminG1000 with SVS

and FIKI.

MULTIENGINE PISTONS NORMALLY ASPIRATEDManufacturer Vulcanair SpA Vulcanair SpA

ModelP.68CP 68C

VictorP 68R

BCAEquipped Price $960,000 $978,000

Characteristics

Seating 1+5/6 1+5/6



Noise (dBA) 74.7 74.7

External

Dimensions(ft.)

Length 31.3 31.3

Height 11.2 11.2Span 39.4 39.4

InternalDimensions

(ft.)

Length 10.6 10.6

Height 3.9 3.9

Width 3.8 3.8

Power

Engines2 Lyc

IO-360-A1B62 Lyc

IO-360-A1B6

Output (hp each) 200 200


Weights (lb.)

Max Ramp 4,630 4,357



Zero Fuel 4,167c 4,147b

EOW 3,153 3,197



Executive Payload 1,020 1,020

Max Fuel 1,063 1,063

Payload Max Fuel 415 98

Available Fuel w/Max Payload 463 210

Available Fuel w/Executive Payload 457 140

Limits

VNE 194 193

VNO 154 153

VA 132 125

AirportPerformance

TO (SL elev./ISA Temp.) 1,312 1,260

TO (5,000 elev.@25C) 4,000 4,000

A/S (SL elev./ISA) 2,149 2,300

A/S (5,000 elev.@25C) 2,854 4,025

VMCA 60 60

VDEC 70 70

VXSE 82 82

VYSE 88 88

Climb

Time to Climb (min.)/Altit ude 12/FL 100 12/FL 100

Initial Engine-Out Rate (fpm) 217 217

Initial All-Engine Gradient (ft./nm) 1,100 920

Initial Engine-Out Gradient (ft./nm) 147 147

Ceilings (ft.)

Certificated - -

All-Engine Service 18,000 20,000

Engine-Out Service 5,000 5,650

Cruise

Long

Range

TAS 144 144

Fuel Flow 94 94



Recommended

TAS 155 155

Fuel Flow 108 108



High Speed

TAS 162 162

Fuel Flow 116 116



Ranges

Executive Payload


Average Speed 145 145Trip Fuel 395 395


Ferry



Trip Fuel 561 561



200 nm

Runway 1,450 1,450


Fuel Used 140 140


500 nm

Runway 1,500 1,500


Fuel Used 375 375


Remarks

Suggested Base Price $960,000 $978,000

Certification BasisFAR 23,

1976/80Garmin G950;STEC 55X DFCS.

EASA 23, 2009Garmin G950;

STEC 55X DFCS.


14/25



MULTIENGINE PISTONS TURBOCHARGEDManufacturer Vulcanair SpA Piper Aircraft

Model P 68C-TCSeneca V

PA-34-220T


Characteristics

Seating 1+5/5 1+4/5



Noise (dBA) 74.7 75.6

External

Dimensions(ft.)

Length 37.6 28.6

Height 11.2 9.9Span 39.4 38.9

InternalDimensions

(ft.)

Length 10.6 10.4

Height 3.9 3.6

Width 3.8 4.1

Power

Engines2 Lyc

TIO-360-C1A6D2 Cont

TSIO-360-RB

Output (hp each) 210 220


Weights (lb.)

Max Ramp 4,442 4,773



Zero Fuel 4,140b 4,479c

EOW 2,976 3,491



Executive Payload 1,020 850

Max Fuel 1,146 732

Payload Max Fuel 320 550Available Fuel w/Max Payload 302 294

Available Fuel w/Executive Payload 446 432

Limits

VNE 193 204

VNO 153 164

VA 126 139

PSI

AirportPerformance

TO (SL elev./ISA temp.) 1,260 1,707

TO (5,000 elev.@25C) 2,200 2,435

A/S (SL elev./ISA) 2,300 2,510

A/S (5,000 elev.@25C) 3,000 3,117

VMCA 63 66

VDEC NA 73

VXSE NA 83

VYSE NA 88

Climb

Time to Climb (min.)/Altit ude 10/FL 100 7/FL 100

Initial Engine-Out Rate (fpm) 240 253

Initial All-Engine Gradient (ft./nm) 1,400 996Initial Engine-Out Gr adient (ft./nm) NA 173

Ceilings (ft.)



Engine-Out Service 11,500 16,500

Sea-Level Cabin -

Cruise

Long

Range

TAS 144 167

Fuel Flow 100 108



Recommended

TAS 155 196

Fuel Flow 125 144



High Speed

TAS 162 200

Fuel Flow 150 156



Ranges

Executive Payload

Nautical Miles 1,050 449


Trip Fuel 942 348


Ferry

Nautical Miles 1,100 866


Trip Fuel 950 648



200 nm

Runway NA 1,520


Fuel Used 260 213


500 nm

Runway NA 1,610


Fuel Used 485 476


Remarks

Suggested Base Price $1,015,000 $972,400

Certification BasisFAR 23, 1982Data BCAestimate;

Garmin G950, glasscockpit, STEC 55X DFGS.

FAR 23, 1971/80/97Includes Garmin G600.

MULTIENGINE PISTONS NORMALLY ASPIRATEDManufacturer Beechcraft Corp.

ModelBaron G58

G58

BCAEquipped Price $1,373,900

Characteristics

Seating 1+4/5

Wing Loading 27.6

Power Loading 9.17

Noise (dBA) 77.6

External

Dimensions(ft.)

Length 29.8

Height 9.8Span 37.8

InternalDimensions

(ft.)

Length 12.6

Height 4.2

Width 3.5

Power

Engines2 Cont

IO-550-C

Output (hp each) 300

Inspection Interval 1,700t

Weights (lb.)

Max Ramp 5,524

Max Takeoff 5,500

Max Landing 5,400

Zero Fuel 5,215b

EOW 4,030

Max Payload 1,185

Useful Load 1,494

Executive Payload 850

Max Fuel 1,164

Payload Max Fuel 330

Available Fuel w/Max Payload 309

Available Fuel w/Executive Payload 644

Limits

VNE 223

VNO 195

VA 165

AirportPerformance

TO (SL elev./ISA Temp.) 2,345

TO (5,000 elev.@25C) 4,144

A/S (SL elev./ISA) 3,009

A/S (5,000 elev.@25C) 4,335

VMCA 84

VDEC 85

VXSE 100

VYSE 101

Climb

Time to Climb (min.)/Altit ude 10/FL 100

Initial Engine-Out Rate (fpm) 390

Initial All-Engine Gradient (ft./nm) 988

Initial Engine-Out Gradient (ft./nm) 232

Ceilings (ft.)

Certificated -

All-Engine Service 20,688

Engine-Out Service 7,284

Cruise

Long

Range

TAS 185

Fuel Flow 144

Altitude FL 080

Specific Range 1.285

Recommended

TAS 192

Fuel Flow 174

Altitude FL 080


High Speed

TAS 200

Fuel Flow 190

Altitude FL 080


Ranges

Executive Payload

Nautical Miles 668

Average Speed 177Trip Fuel 561

Specific Range/Altitude 1.191/FL 040

Ferry

Nautical Miles 1,480

Average Speed 180

Trip Fuel 1,081



200 nm

Runway 2,878

Block Time 1+02

Fuel Used 227


500 nm

Runway 2,957

Block Time 2+31

Fuel Used 531


Remarks

Suggested Base Price $1,367,000

Certification Basis

CAR 31957/69/83/2005

Restyled Interior;new, lightweight A/C;Garmin G1000

with SVS.


15/25



SINGLE-ENGINE TURBOPROPSManufacturer Quest Aircraft Cessna Piper Aircraft Cessna Socata Pilatus

ModelKodiak

Kodiak 100CaravanCE-208

MeridianPA-46-500TP

Grand Caravan EXCE-208B

TBM 850TBM 700 N

PC-12 NGPC-12/47E

BCAEquipped Price $1,960,125 $2,133,350 $2,276,325 $2,407,520 $3,414,655 $4,581,742

Characteristics

Seating 1+5/9 1+9/13* 1+4/5 1+9/13* 1+5/6 1+7/10

Wing Loading 30.2 28.6 27.8 31.3 38.2 37.6

Power Loading 9.67 11.85 10.18 10.16 10.56 8.71

Noise (dBA) 84.4 79.0 76.8 84.1 76.2 79.3

External

Dimensions(ft.)

Length 33.8 37.6 29.6 41.6 34.9 47.3

Height 15.3 14.9 11.3 14.8 14.3 14.0Span 45.0 52.1 43.0 52.1 41.6 53.3

InternalDimensions

(ft.)

Length 15.8 12.7 12.3 16.7 15.0 16.9

Height 4.8 4.5 3.9 4.5 4.1 4.8

Width 4.5 5.3 4.1 5.3 4.0 5.0

Power

Engine P&WC

PT6A-34P&WC

PT6A-114AP&WC

PT6A-42AP&WC

PT6A-140P&WC

PT6A-66DP&WC

PT6A-67P

Output (shp)/Flat Rating 750/ISA+7C 675/ISA+31C 500/ISA+55C 867/ISA+24C 700*/ISA+49C 1,200/ISA+35C

Inspection Interval 4,000t 3,600t 3,600t 3,600t 3,500t 3,500t

Weights (lb.)

Max Ramp 7,305 8,035 5,134 8,842 7,430 10,495

Max Takeoff 7,255 8,000 5,092 8,807 7,394 10,450

Max Landing 6,690 7,800 4,850 8,500 7,024 9,921

Zero Fuel 6,490c 7,432b 4,850c 8,150b 6,032c 9,039c

BOW 4,428 4,925 3,644 5,305 4,780 6,782

Max Payload 2,062 2,507 1,206 2,845 1,252 2,257

Useful Load 2,877 3,110 1,490 3,537 2,650 3,713

Executive Payload 1,000 1,800 800 1,800 1,000 1,400

Max Fuel 2,144 2,224 1,140 2,246 2,017 2,704

Available Payload w/Max Fuel 733 886 350 1,291 633 1,009

Available Fuel w/Max Payload 815 604 284 692 1,398 1,456

Available Fuel w/Executive Payload 1,877 1,310 690 1,737 1,650 2,313

Limits

VMO 180 175 188 175 266 240

VA 143 150 127 148 160 163

PSI 5.5 6.2 5.8

AirportPerformance

TO (SL elev./ISA temp.) 1,468 2,055 2,438 2,160 2,840 2,650

TO (5,000 elev.@25C) 2,396 2,973 3,691 3,661 4,282 4,450

VSO 60 61 69 61 65 67

VX 73 90 95 86 100 120

VY 101 107 125 108 124 130

ClimbTime to Climb (min.)/Altit ude 9/FL 100 9/FL 100 19/FL 250 9/FL 100 14/FL 250 21/FL 250

Initial Gradient (ft./nm) 915 771 753 816 990 833

Ceilings (ft.)

Certificated 25,000 25,000 30,000 25,000 31,000 30,000

Service 25,000 25,000 30,000 25,000 31,000 30,000

Sea-Level Cabin 12,300 14,390 13,100

Cruise

LongRange

TAS 139 157 179 163 255 208

Fuel Flow 229 281 135 324 260 248Altitude FL 100 FL 100 FL 280 FL 100 FL 310 FL 300

Specific Range 0.607 0.559 1.326 0.503 0.981 0.839

High

Speed

TAS 171 186 257 195 320 280

Fuel Flow 326 379 241 438 436 491

Altitude FL 100 FL 100 FL 280 FL 100 FL 260 FL 200

Specific Range 0.525 0.491 1.066 0.445 0.734 0.570

NBAA IFRRanges(100-nmalternate)

Executive Payload

(w/available fuel)

Nautical Miles 1,079 455 699 599 1,150 1,402

Average Speed 139 155 180 161 301 256

Trip Fuel 1,907 876 649 1,255 1,490 2,020

Specific Range/Altitude 0.566/FL 100 0.519/FL 100 1.077/FL 280 0.477/FL 100 0.772/FL 310 0.694/FL 300

Max Fuel

(w/available

payload)

Nautical Miles 1,079 965 953 857 1,450 1,544

Average Speed 139 156 180 162 253 257

Trip Fuel 1,907 1,795 841 1,768 1,677 2,207


Ferry

Nautical Miles 1,181 970 1,072 865 1,452 1,582

Average Speed 142 156 220 162 253 263

Trip Fuel 1,907 1,800 978 1,777 1,677 2,215Specific Range/Altitude 0.619/FL 160 0.539/FL 100 1.096/FL 280 0.487/FL 100 0.866/FL 310 0.714/FL 300

Missions(4 passengers)

300 nm

Runway 937 1,468 2,250 1,345 1,880 1,650

Flight Time 1+49 1+40 1+22 1+37 1+01 1+11

Fuel Used 583 648 379 713 480 520


600 nm

Runway 975 1,675 2,400 1,659 2,100 1,850

Flight Time 3+38 3+17 2+32 3+09 1+59 2+18

Fuel Used 1,166 1,260 661 1,392 900 947


1,000 nm

Runway 1,467 NP 2,438 NP 2,450 2,100

Flight Time 5+54 NP 4+34 NP 3+15 3+49

Fuel Used 1,907 NP 920 NP 1,430 1,489

Specific Range/Altitude 0.524/FL 100 NP 1.087/FL 280 NP 0.699/FL 280 0.672/FL 280

Remarks

Suggested Base Price $1,750,000 $1,866,550 $2,276,325 $2,149,000 $3,251,795 $3,810,000

Certification Basis

FAR 23, 2007Normal category;

includes GarminG1000.

FAR 23, 1984/98*Export only;

Garmin G1000 withGFC700 autopilot.

FAR 23 A 52*1,000-nm,

3 passengermission; GarminG1000 with SVS.

FAR 23, 1986/2012*Export only;

Garmin G1000 withGFC700 autopilot.

FAR 23,1990/2003/06/07*850-shp max cont.;

Elite config. with6 to 4 seats; RVSM;G1000; SVT; 5-yearsystem warranty.

FAR 23,1996/2005/08

Honeywell Primus

APEX SmartView;BMW Designworks

interior.


16/25



MULTIENGINE TURBOPROPS 12,500-LB. MTOW OR LESSManufacturer Evektor Vulcanair SpA Beechcraft Corp. GECI Aviation Beechcraft Corp. Piaggio Aero

ModelOutback

EV-55

ViatorAP68TP-600

King Air C90GTxC90GTi

Caravan IIF406

King Air 250B200GT

Avanti IIP180


Characteristics

Seating 1+9/14 1+7/10 1+7/8 1+8/13 1+8/10 1+7/9

Wing Loading 37.4 31.4 34.4 38.9 40.3 70.3

Power Loading 9.46 9.58 9.53 9.85 7.35 7.12

Noise (dBA) NA 71.7 76.0 69.9 TBD 75.0

ExternalDimensions

(ft.)

Length 46.6 37.0 35.5 39.1 43.8 47.3

Height 16.8 11.9 14.3 13.2 14.8 13.0

Span 53.2 39.4 50.3 49.5 57.9 46.0Internal

Dimensions(ft.)

Length:OA/Net 20/16.5 17.2/11.9 12.4/12.4 14.2/12.8 16.7/16.7 17.5/17.5

Height 4.5 4.1 4.8 4.3 4.8 5.8Width:Max/Floor 5.3/4.7 3 .7/3.7 4.5/4.1 4.7/4.7 4.5/4.1 6.1/3.5

Power

Engines 2 P&WC

PT6A-212 RR

250 B17C2 P&WC

PT6A-135A2 P&WC

PT6A-1122 P&WCPT6A-52

2 P&WCPT6A-66B

Output (shp each)/Flat Rating 536/ISA+15C 328/ISA+25C 550/ISA+30C 500/ISA+22C 850/ISA+37C 850/ISA+28C


Weights (lb.)

Max Ramp 10,207 6,338 10,545 9,925 12,590 12,150

Max Takeoff 10,141 6,283 10,485 9,850 12,500 12,100

Max Landing 10,141 6,283 9,832 9,360 12,500 11,500

Zero Fuel 9,810c 5,621c 9,378c 8,500c 11,000c 9,800c

BOW 5,965 3,770 7,235 5,732 8,780 8,375

Max Payload 3,845 1,851 2,143 2,768 2,220 1,425

Useful Load 4,242 2,568 3,310 4,193 3,810 3,775

Executive Payload 1,800 1,400 1,400 1,600 1,600 1,400

Max Fuel 3,413 1,487 2,573 3,183 3,645 2,802

Available Payload w/Max Fuel 829 1,081 737 1,010 165 973

Available Fuel w/Max Payload 397 717 1,167 1,425 1,590 2,350

Available Fuel w/Executive Payload 2,442 1,168 1,910 2,593 2,210 2,375

Limits

VMO 205 200 226 213 260 260

VA 140 157 169 160 182 202

PSI 5.0 6.5 9.0

AirportPerformance

TO (SL elev./ISA temp.) 1,378 2,034 2,552 2,964 2,111 3,262

TO (5,000 elev.@25C) 1,837 2,950 3,648 4,106 3,099 4,700

A/S (SL elev./ISA temp.) 1,722 2,887 3,666 4,746 3,687 5,750

A/S (5,000 elev.@25C) 2,395 3,740 4,779 6,215 4,859 7,400

VMCA 66 77 80 90 86 100

VDEC 79 85 97 101 94 106

VXSE 92 90 100 105 115 132

VYSE 95 105 108 115 121 140

Climb

Time to Climb (min.)/Altit ude 6/FL 010 7/FL 100 17/FL 250 6/FL 100 13/FL 250 10/FL 250

Initial Engine-Out Rate (fpm) 290 270 474 310 682 670

Initial All-Engine Gradient (ft./nm) 1,107 1,500 1,953 910 1,170 1,106

Initial Engine-Out Gradient (ft./nm) 219 180 259 170 364 287

Ceilings (ft.)

Certificated 24,000 25,000 30,000 30,000 35,000 41,000

All-Engine Service 24,000 25,000 30,000 30,000 35,000 39,400

Engine-Out Service 15,420 11,400 19,170 14,550 26,000 23,800

Sea-Level Cabin 11,065 15,293 24,000

Cruise

Long

Range

TAS 180 169 208 184 256 318

Fuel Flow 432 261 332 412 430 408


Specific Range 0.417 0.648 0.627 0.447 0.595 0.779

High

Speed

TAS 220 214 270 234 310 400

Fuel Flow 610 375 612 605 750 792


Specific Range 0.361 0.571 0.441 0.387 0.413 0.505


Max Payload

(w/available fuel)

Nautical Miles NP 543 275 427 330 1,070

Average Speed NP 180 226 179 267 315

Trip Fuel NP 781 648 1,009 864 1,715

Specific Range/Altitude NP/NP 0.695/FL 100 0.424/FL 270 0.423/FL 100 0.382/FL 330 0.624/FL 390

Max Fuel

(w/available

payload)

Nautical Miles 1,046 837 1,040 1,188 1,412 1,450

Average Speed 217 179 252 180 292 311

Trip Fuel 3,008 1,220 2,069 2,767 2,958 2,167


Full Fuel

(w/4 passsengers)

Nautical Miles 1,046 837 1,005 1,201 1,074 1,510

Average Speed 217 179 251 180 288 317

Trip Fuel 3,008 1,220 2,006 2,770 2,293 2,167Specific Range/Altitude 0.348/FL 100 0.686/FL 100 0.501/FL 270 0.434/FL 100 0.468/FL 330 0.697/FL 410

Ferry

Nautical Miles 1,051 837 1,060 1,228 1,430 1,530

Average Speed 218 179 255 176 293 318

Trip Fuel 3,008 1,220 2,077 2,787 2,960 2,167



300 nm

Runway 3,163 1,247 3,163 3,815 3,495 2,350

Flight Time 1+26 1+35 1+14 1+21 1+03 0+53

Fuel Used 943 419 747 807 868 688


600 nm

Runway 1,289 1,558 3,362 4,075 3,578 2,550

Flight Time 2+22 3+18 2+22 2+39 2+03 1+44

Fuel Used 1,773 866 1,351 1,609 1,493 1,144


1,000 nm

Runway 1,565 NP 3,660 NP 3,667 2,700

Flight Time 4+36 NP 3+56 NP 3+28 3+02

Fuel Used 2,881 NP 1,996 NP 2,146 1,603

Specific Range/Altitude 0.347/FL 100 NP/NP 0.501/FL 270 NP/NP 0.466/FL 330 0.624/FL 390

Remarks

Suggested Base Price NA $2,772,000 $3,813,500 NA $5,995,000 $7,195,000

Certification BasisEASA/FAR 23

pendingCMC SmartDeck.

FAR 23, 1986BCAcomputed data;G950; STEC 2100.

CAR 3 1959/2007Pro Line 21; STC

SA10747SC wt. inc.SFAR 41C, 1986

FAR 23,1973/80/2008/11STC SA02131SE.

FAR 23, 1990Pro Line 21; TCAS I,Iridium; RVSM appd.


17/25



MULTIENGINE TURBOPROPS >12,500-LB. MTOWManufacturer Beechcraft Corp. Beechcraft Corp. Beechcraft Corp.

ModelKing Air 350i

B300King Air 350HW

B300King Air 350iER

B300ER

BCAEquipped Price $7,312,700 $7,484,525 $8,353,100

Characteristics

Seating 1+9/11 1+9/14 1+9/11Wing Loading 48.4 53.2 53.2

Power Loading 7.14 7.86 7.86Noise (dBA) 72.1 81.5 81.5

ExternalDimensions

(ft.)

Length 46.7 46.7 46.7

Height 14.3 14.3 14.3

Span 57.9 57.9 57.9Internal

Dimensions(ft.)

Length:OA/Net 19.5/19.5 19.5/19.5 19.5/19.5Height 4.8 4.8 4.8

Width:Max/Floor 4.5/4.1 4.5/4.1 4.5/4.1

Power

Engines 2 P&WC

PT6A-60A2 P&WC

PT6A-60A2 P&WC

PT6A-60A

Output (shp each)/Flat Rating 1,050/ISA+10C 1,050/ISA+10C 1,050/ISA+10CInspection Interval 3,600t 3,600t 3,600t

Weights (lb.)

Max Ramp 15,100 16,600 16,600Max Takeoff 15,000 16,500 16,500

Max Landing 15,000 15,675 15,675

Zero Fuel 12,500c 13,000c 13,000c

BOW 10,070 9,340 10,385

Max Payload 2,430 3,660 2,615Useful Load 5,030 7,260 6,215

Executive Payload 1,800 1,800 1,800Max Fuel 3,611 3,611 5,192

Available Payload w/Max Fuel 1,419 3,649 1,023Available Fuel w/Max Payload 2,600 3,600 3,600

Available Fuel w/Executive Payload 3,230 3,611 4,415

Limits

MMO 0.58 0.58 0.58

Trans. Alt. FL FL 210 FL 240 FL 240VMO 263 245 245VA 182 182 182

PSI 6.6 6.6 6.6

AirportPerformance

TO (SL elev./ISA temp.) 3,300 4,598 4,473TOFL (5,000 elev.@25C) 5,376 6,003 7,588

Hot/High WAT Limit 14,196 14,491 15,830NBAA IFR Range 1,551 1,403 2,080

V2 109 111 111

VREF 100 104 104

Landing Distance 2,390 2,720 2,728

Climb

Time to Climb (min.)/Altitude 15/FL 250 23/FL 250 18/FL 250*FAR 25 Initial Engine-Out Rate (fpm) 552 274 337

FAR 25 Initial Engine-Out Gradient (ft./nm) 304 172 182

Ceilings (ft.)

Certificated 35,000 35,000 35,000All-Engine Service 35,000 35,000 35,000

Engine-Out Service 21,500 17,100 17,100

Sea-Level Cabin 15,293 15,293 15,293

Cruise

Long

Range

TAS 235 232 238Fuel Flow 362 392 402

Altitude FL 330 FL 330 FL 330Specific Range 0.649 0.592 0.592

High

Speed

TAS 312 303 303Fuel Flow 773 766 764




Max Payload

(w/available fuel)

Nautical Miles 899 1,255 1,336


Trip Fuel 1,897 2,840 2,886


Max Fuel

(w/available

payload)

Nautical Miles 1,489 1,261 2,239Average Speed 280 258 268

Trip Fuel 2,951 2,886 4,528


Full Fuel

(w/4 passengers)

Nautical Miles 1,532 1,395 2,273


Trip Fuel 2,956 2,908 4,530


Ferry

Nautical Miles 1,560 1,429 2,340Average Speed 288 276 274

Trip Fuel 2,962 2,920 4,539



300 nm

Runway 2,608 3,432 3,463

Flight Time 1+02 1+07 1+05

Fuel Used 883 967 908Specific Range/Altitude 0.340/FL 250 0.310/FL 250 0.330/FL 250

600 nm

Runway 2,724 3,568 3,597Flight Time 2+02 2+10 2+07

Fuel Used 1,472 1,581 1,511Specific Range/Altitude 0.408/FL 290 0.380/FL 290 0.397/FL 290

1,000 nm

Runway 2,851 3,720 3,745

Flight Time 3+27 3+39 3+36Fuel Used 2,106 2,262 2,176


Remarks

Suggested Base Price $7,275,000 $7,484,525 $8,315,400

Certification Basis

FAR 23, 1989Commuter category;

Pro Line 21; new interior with RockwellCollins Venue CMS; RVSM approved.

FAR 23, 1989/2007Commuter category;

Installation by HBS; slick interior availablefor special missions; RVSM approved.

FAR 23, 1989/2007Commuter category;

Pro Line 21; new interior with RockwellCollins Venue CMS; RVSM approved.


18/25



JETS LESS THAN 20,000-LB. MTOWManufacturer Embraer Honda Aircraft Co.

ModelPhenom 100

EMB-500HondaJetHA-420


Characteristics

Seating 1+5/7 1+5/6

Wing Loading 51.9 NA

Power Loading 3.09 NA

Noise (EPNdB):TO/Sideline/APR 70.4/81.4/86.1 NA/NA/NA

ExternalDimensions

(ft.)

Length 42.1 42.6

Height 14.3 14.9

Span 40.4 39.8

InternalDimensions

(ft.)

Length:OA/Net 11.0/11.0 12.1/12.1

Height 4.9 4.8

Width:Max/Floor 5.1/3.6 5.0/NA

BaggageInternal:Cu. ft./lb. 11/99 5/NA

External:Cu. ft./lb. 60/418 66/NA

Power

Engines 2 P&WC

PW 617F-E2 GE Honda

HF-120

Output (lb. each)/Flat Rating 1,695/ISA+10C 2,050/NA

Inspection Interval 3,500t NA

Weights (lb.)

Max Ramp 10,516 NA

Max Takeoff 10,472 NA

Max Landing 9,766 NA

Zero Fuel 8,444c NA

BOW 7,132 NA

Max Payload 1,312 NA

Useful Load 3,384 NA

Executive Payload 1,000 NA

Max Fuel 2,804 NA

Available Payload w/Max Fuel 580 NA

Available Fuel w/Max Payload 2,072 NA

Available Fuel w/Executive Payload 2,384 NA

Limits

MMO 0.700 0.720

Trans. Alt. FL/VMO 280/275 FL 300/NA

PSI 8.3 8.7

AirportPerformance

TOFL (SL elev./ISA temp.) 3,040 4,000

TOFL (5,000 elev.@25C) 6,384 NA

Hot/High Weight Limit 10,472 NA

NBAA IFR Range 1,065 NA

V2@SL ISA, MTOW 98 NA

VREFw/4 Pax, NBAA IFR Res. 94 NA

Landing Distance w/4 Pax, NBAA IFR Res. 2,441 3,000

Climb

Time to Climb/Altitude 23/FL 370 NA/NA

FAR 25 Engine-Out Rate (fpm) 579 NA

FAR 25 Engine-Out Gradient (ft./nm) 310 NA

Ceilings (ft.)



Engine-Out Service 25,918 NA

Sea-Level Cabin 21,280 NA

Cruise

Long

Range

TAS 333 NA

Fuel Flow 524 NA

Altitude FL 410 NA

Specific Range 0.635 NA

High

Speed

TAS 390 420

Fuel Flow 852 NA


Specific Range 0.458 NA

NBAA IFRRanges

(FAR Part 23,100-nm

alternate;

FAR Part 25,200-nmalternate)

Max Payload

(w/available fuel)

Nautical Miles 710 NA

Average Speed 321 NA

Trip Fuel 1,418 NA

Specific Range/Altitude 0.501/FL 410 NA/NA

Max Fuel

(w/available

payload)

Nautical Miles 1,194 1,180


Trip Fuel 2,167 NA


Four Passengers(w/available fuel)

Nautical Miles 1,044 NA

Average Speed 324 NATrip Fuel 1,940 NA


Ferry

Nautical Miles 1,242 NA


Trip Fuel 2,187 NA



300 nm

Runway 2,717 NA

Flight Time 0+54 NA

Fuel Used 761 NA


600 nm

Runway 2,784 NA

Flight Time 1+46 NA

Fuel Used 1,259 NA


1,000 nm

Runway 3,273 NA

Flight Time 3+05 NA

Fuel Used 1,866 NA


Remarks Certification Basis FAR 23, 2008 FAR 23 pending

All data preliminary.

JETS LESS THAN 10,000-LB. MTOWManufacturer Cessna

ModelCitation Mustang

CE-510

BCAEquipped Price $3,430,000

Characteristics

Seating 1+5/5

Wing Loading 41.2

Power Loading 2.96Noise (EPNdB):TO/Sideline/APR 73.9/85.0/86.0

ExternalDimensions

(ft.)

Length 40.6

Height 13.4

Span 43.2

InternalDimensions

(ft.)

Length:OA/Net 9.8/9.8

Height 4.5

Width:Max/Floor 4.6/3.1

BaggageInternal:Cu. ft./lb. 6/98

External:Cu. ft./lb. 57/620

Power

Engine(s) 2 P&WC

PW615F

Output (lb. each)/Flat Rating 1,460/ISA+10C

Inspection Interval 3,500t

Weights (lb.)

Max Ramp 8,730

Max Takeoff 8,645

Max Landing 8,000

Zero Fuel 6,750c

BOW 5,590

Max Payload 1,160

Useful Load 3,140

Executive Payload 1,000

Max Fuel 2,580

Available Payload w/Max Fuel 560Available Fuel w/Max Payload 1,980

Available Fuel w/Executive Payload 2,140

Limits

MMO 0.630

Trans. Alt. FL/VMO FL 271/250

PSI 8.3

AirportPerformance

TOFL (SL elev./ISA temp.) 3,110

TOFL (5,000 elev.@25C) 6,600

Hot/High Weight Limit 8,645

NBAA IFR Range 991

V2@SL ISA, MTOW 97

VREFw/4 Pax, NBAA IFR Res. 88

Landing Distance w/4 Pax, NBAA IFR Res. 2,137

Climb

Time to Climb/Altitude 20/FL 370

FAR 25 Engine-Out Rate (fpm) 432

FAR 25 Engine-Out Gradient (ft./nm) 267

Ceilings (ft.)

Certificated 41,000

All-Engine Service 41,000

Engine-Out Service 26,900

Sea-Level Cabin 21,280

Cruise

Long

Range

TAS 319

Fuel Flow 498

Altitude FL 390


High

Speed

TAS 339

Fuel Flow 609

Altitude FL 350



Max Payload

(w/available fuel)

Nautical Miles 716

Average Speed 294

Trip Fuel 1,300


Max Fuel

(w/available

payload)


Average Speed 305

Trip Fuel 1,948


Four Passengers

(w/available fuel)

Nautical Miles 970

Average Speed 301

Trip Fuel 1,674Specific Range/Altitude 0.579/FL 410

Ferry


Average Speed 315

Trip Fuel 1,965



300 nm

Runway 2,495

Flight Time 1+00

Fuel Used 670


600 nm

Runway 2,691

Flight Time 1+56

Fuel Used 1,134


1,000 nm

Runway 3,109

Flight Time 3+19

Fuel Used 1,717


Remarks Certification Basis

FAR 23, 20061,000-nm missionflown with 758-lb.

payload.


19/25



JETS LESS THAN 20,000-LB. MTOWManufacturer Cessna Cessna Syberjet Cessna Embraer Cessna

ModelCitation M2

CE-525Citation CJ2+

CE-525ASJ30-2SJ30-2

Citation CJ3CE-525B

Phenom 300EMB-505

Citation CJ4CE-525C


Characteristics

Seating 1+7/7 1+8/9 1+5/6 2+7/8 1+7/10 2+8/9

Wing Loading 44.6 47.4 73.2 47.2 58.6 51.8

Power Loading 2.72 2.51 3.03 2.46 2.67 2.36

Noise (EPNdB):TO/Sideline/APR NA/NA/NA 75.5/86.1/89.7 78.5/86.2/91.8 74.0/88.7/88.6 69.9/88.8/88.5 75.4/92.8/89.5

ExternalDimensions

(ft.)

Length 42.6 47.7 46.8 51.2 51.2 53.3

Height 13.9 14.0 14.2 15.2 16.7 15.3

Span 47.3 49.8 42.3 53.3 52.2 50.8

InternalDimensions

(ft.)

Length:OA/Net 11.0/11.0 13.6/13.6 12.5/12.5 15.7/15.7 17.2/17.2 17.3/17.3

Height 4.8 4.8 4.4 4.8 4.9 4.8

Width:Max/Floor 4.8/3.1 4.8/3.1 4.8/2.8 4.8/3.1 5.1/3.6 4.8/3.3

BaggageInternal:Cu. ft./lb. / / 6/100 / 11/77 7/40

External:Cu. ft./lb. 46/725 65/1,000 53/500 65/1,000 74/573 71/1,000

Power

Engines 2 Wms Intl

FJ44-1AP-212 Wms IntlFJ44-3A-24

2 Wms IntlFJ44-2A

2 Wms IntlFJ44-3A

2 P&WCPW 535E

2 Wms IntlFJ44-4A

Output (lb. each)/Flat Rating 1,965/ISA+7C 2,490/ISA+7C 2,300/ISA+8C 2,820/ISA+11C 3,360/ISA+15C 3,621/ISA+11C


Weights (lb.)

Max Ramp 10,800 12,625 14,050 14,070 18,078 17,230

Max Takeoff 10,700 12,500 13,950 13,870 17,968 17,110

Max Landing 9,900 11,525 12,725 12,750 16,865 15,660

Zero Fuel 8,400c 9,700c 10,500c 10,510c 13,999c 12,500c

BOW 6,991 8,010 8,917 8,760 11,583 10,430

Max Payload 1,409 1,690 1,583 1,750 2,416 2,070

Useful Load 3,809 4,615 5,133 5,310 6,495 6,800

Executive Payload 1,400 1,600 1,000 1,400 1,400 1,600

Max Fuel 3,309 3,930 4,850 4,710 5,353 5,828

Available Payload w/Max Fuel 500 685 283 600 1,142 972

Available Fuel w/Max Payload 2,400 2,925 3,550 3,560 4,079 4,730

Available Fuel w/Executive Payload 2,409 3,015 4,133 3,910 5,095 5,200

Limits

MMO 0.710 0.737 0.830 0.737 0.780 0.770

Trans. Alt. FL/VMO FL 305/263 FL 291/278 FL 295/320 FL 293/278 FL 263/320 FL 279/305

PSI 8.5 8.9 12.0 8.9 9.4 9.0

AirportPerformance

TOFL (SL elev./ISA temp.) 3,250 3,360 3,939 3,180 3,138 3,190

TOFL (5,000 elev.@25C) 5,720 5,180 8,784 4,750 5,114 5,130

Hot/High Weight Limit 10,700 12,500 13,125 13,870 17,968 16,938

NBAA IFR Range 1,145 1,543 1,915 1,726 2,019 1,943

V2@SL ISA, MTOW NA 116 112 114 112 117

VREFw/4 Pax, NBAA IFR Res. NA 102 104 99 104 99

Landing Distance w/4 Pax, NBAA IFR Res. 2,354 2,655 2,657 2,422 2,220 2,277

Climb

Time to Climb/Altitude 18/FL 370 15/FL 370 16/FL 370 15/FL 370 14/FL 370 14/FL 370

FAR 25 Engine-Out Rate (fpm) NA 611 312 808 911 839

FAR 25 Engine-Out Gradient (ft./nm) NA 316 167 425 462 430

Ceilings (ft.)

Certificated 41,000 45,000 49,000 45,000 45,000 45,000

All-Engine Service 41,000 45,000 44,000 45,000 45,000 45,000

Engine-Out Service NA 23,800 25,800 26,250 30,137 28,200

Sea-Level Cabin 22,027 23,586 41,000 23,586 25,560 23,984

Cruise

Long

Range

TAS 317 357 436 351 383 376

Fuel Flow 501 589 684 620 757 809


Specific Range 0.633 0.606 0.637 0.566 0.506 0.465

High

Speed

TAS 398 413 475 415 444 442

Fuel Flow 944 1,096 1,188 1,196 1,312 1,470


Specific Range 0.422 0.377 0.400 0.347 0.338 0.301

NBAA IFRRanges

(FAR Part 23,100-nmalternate;

FAR Part 25,200-nmalternate)

Max Payload

(w/available fuel)

Nautical Miles 768 993 1,635 1,172 1,247 1,425

Average Sp

2013 BCA Purchase Planning Handbook

Documents

Transcript of 2013 BCA Purchase Planning Handbook