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| For Sale |
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| Ratings & Reviews |
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| Model Website |
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Weights & Dimensions |
| Weights: |
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Basic Operating Weight  Empty Weight (EW) is shown for Piston powered airplanes.
Basic Operating Weight (BOW) is shown for turbine powered airplanes. BOW is the empty weight of the aircraft, plus 200 lbs for each required crewmember. This does not include unusable fuel and oil.
BOW is based on the average EW for current production aircraft and is interpolated as accurate as possible for out of production aircraft. For Ultra Long Range aircraft, Crew = 3 pilots and 1 cabin attendant.
Please see the Guide To Specifications for more detail. |
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| Max Payload Jet & Turboprop Aircraft - Zero Fuel Weight(ZFW)minus Basic Operating Weight(BOW).
For Piston Engine airplanes, the weight shown here is calculated by subtracting 200 pounds from the Useful Load for the pilot and supplies. (Useful Load minus Pilot @ 200 lbs = Max Payload). |
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| Passenger Payload The amount of payload allowed for occupants or cargo and is based on 180 pounds per occupant for Piston aircraft and 200 pounds per occupant for Turbine aircraft.
If the passenger payload exceeds the maximum payload, we use the maximum payload weight.
Pilot(s) and crew are not counted as occupants. Please see the Guide To Specifications for more detail. |
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| Useful Load |
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| Avail. Payload/Max Fuel The maximum ramp weight minus the tanks full weight, (not to exceed zero fuel weight) minus Basic Operating Weight.
For light aircraft, it is the Max Payload minus the full fuel weight. |
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| Avail. Fuel/Max Payload Jet & Turboprop Aircraft - Maximum Ramp Weight minus Basic Operating Weight, not to exceed Zero Fuel Weight. |
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| Avail. Fuel/Seats Full The amount of fuel available with the seats full calculation is based on passenger weights of 180 lbs for piston aircraft and 200 lbs for turbine aircraft. The crew for larger turbine aircraft is already calculated in the BOW. For lighter and piston aircraft, the seats full includes the pilot at 200 lbs. |
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| Max Fuel |
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| Usable Fuel |
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| Wing Loading Is computed using the Max Takeoff Weight (MTOW) divided by the total wing area. |
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| Power Loading Power Loading is calculated using the Max Takeoff Weight (MTOW) divided by total rated thrust or horsepower. |
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| Max Ramp Weight The maximum allowable weight of the aircraft to be considered airworthy including fuel required for taxi.
Max ramp, takeoff and landing weights may be the same for light aircraft that may only have a certificated max takeoff weight. |
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| Max Takeoff Weight (MTOW) The maximum weight that the aircraft has shown to meet all airworthiness requirements. MTOW is fixed and does not vary with altitude or air temperature.
Max ramp, takeoff and landing weights may be the same for light aircraft that may only have a certificated max takeoff weight. |
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| Max Landing Weight Max Landing Weight is determined by structural limits and is the maximum weight for an aircraft to land.
Max ramp, takeoff and landing weights may be the same for light aircraft that may only have a certificated max takeoff weight. |
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| Max Zero Fuel Weight (ZFW) The maximum total weight of the aircraft less the weight of fuel required to fly 1.5 hours at high-speed cruise for turbine powered aircraft. |
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| Seating & Dimensions: |
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| Seating Capacity Crew + Typical Seating / Maximum Seating. For example, 2 + 6 / 9 indicates that the aircraft requires two pilots, there are six seats in the typical cabin configuration and the aircraft is certified for up to 9 passenger seats.
A six place single or multi-engine is shown as 1 + 5 / 5 indicating that one pilot is required and there are five other seats available for passengers. |
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| Internal: |
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| Cabin Length For airplanes other than cabin class models, the length is measured from the forward bulkhead ahead of the rudder pedals to the back of the rearmost passenger seat in its normal, upright position.
For Cabin Class aircraft, the overall length of the passenger cabin is shown, measured from the aft side of the forward cabin divider (wall/door behind the pilots) to the aft-most bulkhead of the cabin. The aft-most point is defined by the rear side of a baggage compartment that is accessible to the passengers in flight or the aft pressure bulkhead.The overall length is reduced by the length of any permanent mounted system or structure that is installed in the fuselage ahead of the aft bulkhead. |
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| Cabin Height Interior height is measured at the center of the cabin cross section. It may be based on an aisle that is dropped several inches below the main cabin floor that supports the passenger seats. |
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| Cabin Width Width shown is measured at the widest part of the cabin. The dimensions may not be completely indicative of the usable space in a specific aircraft because of individual variances of interior furnishings. |
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| Cabin Volume |
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| External: External length, height and span dimensions are provided for use in determining hangar and or tie-down space requirements. |
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| Aircraft Length |
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| Aircraft Height |
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| Wingspan |
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| Wing Area |
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| Baggage Capacity: |
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| Interior Volume |
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| Interior Weight |
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| Exterior Volume |
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| Exterior Weight |
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| Pressurization: |
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| Differential |
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| Sea Level Cabin to FT Is the maximum cruise altitude at which a 14.7-psi, sea level cabin altitude can be maintained in a pressurized aircraft. |
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| Cabin Altitude Max Cert. Is the pressure altitude inside the cabin when the aircraft is at its maximum certified operating altitude. |
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Engine(s) & Prop(s) |
| Engine(s): |
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| Engine Type |
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| Fuel Type |
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| Thrust / Horse Power If an engine is flat rated, enabling it to produce take off rated output at higher than International Standard Day Atmospheric conditions (ISA) ambient temperature, the flat rating limit is shown as ISA +XX'C. Highly flat rated engines, typically provide substantially improved high-density altitude and high-altitude cruise performance. |
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| Turbocharged |
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| Cylinders |
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| Inspection Interval The longest scheduled hourly major maintenance interval for the engine, either Time Before Overhaul (TBO), or Compressor Zone Inspection (CZI). OC (on condition) is shown only for engines that have "on condition" repair or replacement parts maintenance. |
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| Propeller(s): |
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| Pitch |
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| Diameter |
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| Number of Blades |
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Performance Specs |
| Top Speed The top speed as determined by the manufacturer under optimal conditions and flown by an expert test pilot.
This speed will vary from aircraft to aircraft based on equipment, flight conditions and pilot abilities. |
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| Cruise Speed Crusie Speed as determined by the manufacturer under optimal conditions and flown by an expert test pilot.
This speed will vary from aircraft to aircraft based on equipment, flight conditions and pilot abilities. |
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| Max Range Max Range as indicated by the manufacturer under optimal conditions.
See Cruise & Mission performance for examples of range capabilities. |
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| Range With Seats Full Range is calculated using performance charts with avail fuel with seats full and IFR reserves for Piston aircraft and NBAA IFR reserves for Turbine aircraft. |
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| Take Off Distances: Is the shortest ground distance, measured in feet, for an aircraft to accelerate and liftoff. Where applicable, takeoff and landing distance is computed for airplanes to clear a 50' obstruction. |
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| Sea Level, ISA |
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| 5000 ft elev 25'C |
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| Accelerated Stop Distance: The distance of runway length needed for an aircraft to accelerate to rotation speed and then come to a complete stop if unable, or the decision is made to abort the takeoff. The distance is shown for multi-engine piston and turboprop airplanes.
Takeoff Field Length (TOFL), which is the greater of the one-engine inoperative (OEI) takeoff distance or the accelerated stop distance is shown for Part 23 and 25 airplanes. If the accelerated stop and the OEI are equal, the TOFL is the balanced field length. |
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| Sea Level, ISA |
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| 5000 ft elev 25'C |
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| Landing Distances: Is the shortest distance an aircraft can descend, land and come to a complete stop. Where applicable, the distance is computed for airplanes to clear a 50' obstruction. |
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| Sea Level, ISA |
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| 5000 ft elev 25'C |
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| Climb Performance: |
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| Climb (SL, ISA) |
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| Min. To Altitude Provides an indication of overall climb performance, especially if the aircraft has an all-engine service ceiling well above sample top-of-climb altitudes shown here and in the cruise section of performance specs. The all-engine time to climb to a specific altitude is shown, based on type of aircraft, departing at Max Total Operating Weight (MTOW) from a sea level, standard day airport.
The data is published as time-to-climb in minutes to a designated altitude. Exp: If it takes 9 minutes to climb to 10,000 feet, it will be shown as 9 / 10,000. |
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| Engine Out Rate |
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| Engine Out Gradient |
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| Ceilings: |
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| Certified Maximum allowable operating altitude determined by airworthiness authorities. |
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| All-Engine Maximum altitude at which at least 100-fpm rate of climb can be attained, assuming the aircraft departed a sea-level, standard-day airport at Max Total Operating Weight (MTOW) and climbed directly to altitude. |
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| Engine-Out Maximum altitude at which a 50-fpm rate of climb can be attained, assuming the aircraft departed a sea-level, standard-day airport at Max Total Operating Weight (MTOW) and climbed directly to altitude. |
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| V Speeds: |
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| Speed Vs |
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| Speed Vso |
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| Speed Vx |
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| Speed Vxse |
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| Speed Vy |
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| Speed Vyse |
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| Speed Vsse |
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| Speed Vmcg |
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| Speed Vmca |
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| Speed Va |
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| Speed Vmo |
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| Speed V1 |
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| Speed Vno |
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| Speed Vne |
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Cruise & Mission Performance |
| Cruise Performance: Please see the "Guide To Specifications" link at the top of this comparison to get detailed information about how these Cruise Performances are calculated. |
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| Mission Ranges: The range distances are in Nautical Miles using NBAA IFR Range Profile constraints for turbine aircraft and normal IFR of 45 minutes for piston aircraft. |
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