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Beechcraft King Air F90

Aircraft Specs & Performance


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Aircraft Specs
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General Info
Category Turboprop
Seating
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 in a normal cabin configuration.

See Guide To Specs for more info.
1 + 7 / 9
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.
265 kts
Max Range
Max Range as indicated by the manufacturer under optimal conditions.

See Cruise & Mission performance for examples of range capabilities.
1330 NM
URL www.hawkerbeechcraft.com
Weights & Dimensions
Weights:
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.
7,169 lbs 3,251.80 kg
Passenger Payload
Based on 180 pounds per occupant for Piston aircraft and 200 pounds per occupant for turbine engine airplanes.

If the passenger payload exceeds the maximum payload, we use the maximum payload weight.

Pilots and crew are not counted as occupants.
1,400 lbs 635.03 kg
Useful Load 3,861 lbs 1,751.32 kg
Max Fuel 4700.00 gal / 31490 lbs 17791.44 L / 14283.62 kg
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 only have a certificated max takeoff weight.
10,950 lbs 4,966.84 kg
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 on may only have a certificated max takeoff weight.
10,950 lbs 4,966.84 kg
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 on may only have a certificated max takeoff weight.
10,950 lbs 4,966.84 kg
Internal Dimensions
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.
12 ft 4 in 3.76 m
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. Some aircraft have dropped aisles of varying depths, resulting in less available interior height in certain sections of the cabin.
4 ft 10 in 1.47 m
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.
4 ft 6 in 1.37 m
Cabin Volume 227.00 ft3 69.19 m3
External Dimensions
External length, height and span dimensions are provided for use in determining hangar and or tie-down space requirements.
Length 35 ft 6 in 10.82 m
Height 14 ft 4 in 4.37 m
Wingspan 50 ft 3 in 15.32 m
Wing Area 293.94 ft2 89.59 m2
Baggage Capacity
Interior Volume
Volume of internal baggage compartment and typical weight capacity.
48 ft3 14.63 m3
Pressurization
Differential
Cabin pressure differential expressed in PSI.
5.00 psi
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.
11,065 ft 3,372.61 m
Engine / Propeller
Engine Info
Manufacturer Pratt & Whitney Canada
Model PT6A-135A
Engine turboprop
Fuel Type JetA
Thrust / Horse Power
Is the takeoff rated pounds of thrust for jet/turbofan aircraft and horsepower for propeller driven aircraft.

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.
550 shp ISA + 30'C
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. On Condition repair or replacement parts maintenance is performed when an inspector deems it necessary rather than after a pre-specified hourly use.
3,500 TBO

Performance Specs
Speeds
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.
265 kts
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.
252 kts
Max Range
Max Range as indicated by the manufacturer under optimal conditions.

See Cruise & Mission performance for examples of range capabilities.
1330 NM
V Speeds:
Speed Va 169 kts
Speed Vmo 250 kts
Takeoff Distances
Is the shortest ground distance, measured in feet, for an aircraft to accelerate and liftoff. Where applicable, takeoff distance is computed for airplanes to clear a 50' obstruction.

Aviation regulations, (for large aircraft) require the takeoff distance to be less than, or equal to the available runway length, both with and without an engine failure assumed.
Sea Level, ISA 2,808 ft 855.88 m
Landing Distances
Is the shortest distance an aircraft can descend, land and come to a complete stop. Where applicable, landing distance is computed for airplanes to clear a 50' obstruction. For larger aircraft, a mid-weight mission is used for computation.
Sea Level, ISA 2,275 ft 693.42 m
5000 ft elev 25'C 5,200 ft 1,584.96 m
Climb Performance / Ceilings
Climb 2,380 fpm 725.42 mpm
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.

We provide the all engine time to climb to specific altitudes based on the type of aircraft.

10,000 feet for normally aspirated (non turbocharged) single and multi engine piston aircraft, pressurized single engine piston and non pressurized turboprop; 25,000 feet for pressurized single and multiengine turboprops; 37,000 feet for turbofan powered aircraft.

The data is published as time-to-climb in minutes to the designated altitude. Exp: If it takes 9 minutes to climb to 10,000 feet, it will be shown as 9 / 10,000.
14 min / 25,000 ft 14 min / 7,620.00 m
Engine Out Rate
The One Engine Inoperative (OEI) rate of climb for multi-engine aircraft at Max Takeoff Weight (MTOW). OEI is derived from the Airplane Flight Manuel and is based on landing gear retracted and wing flaps in the takeoff configuration used to compute the published takeoff distance.
600 fpm 182.88 mpm
Certified Ceiling
Maximum allowable operating altitude determined by airworthiness authorities.
30,500 ft 9,296.40 m
Ceiling w/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.
14,420 ft 4,395.22 m
Cruise Performance
Speed / Power 0 kts / 0 %

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