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Beechcraft King Air C90GTx

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 / 8
URL www.hawkerbeechcraft.com/beechcraft/king_air_c90gtx/
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.
7,235 lbs 3,281.74 kg
Max Payload
Jet & Turboprop Aircraft - Zero fuel weight minus Basic Operating Weight (BOW).

For piston engine airplanes, 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).
2,743 lbs 1,244.20 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 3,310 lbs 1,501.39 kg
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.
737 lbs 334.30 kg
Avail. Fuel/Max Payload
Jet & Turboprop Aircraft - Maximum Ramp Weight minus Basic Operating Weight, not to exceed Zero Fuel Weight or maximum fuel capacity.
84.63 gal / 567 lbs 320.35 L / 257.19 kg
Max Fuel 384.03 gal / 2573 lbs 1453.71 L / 1167.09 kg
Wing Loading
Is computed using the Max Takeoff Weight (MTOW) divided by the total wing area.
34.40 lbs / ft2 51.19 kg / m2
Power Loading
Power Loading is calculated using the Max Takeoff Weight (MTOW) divided by total rated thrust / horsepower.
9.53 lbs / hp 4.32 kg / hp
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.
10,545 lbs 4,783.13 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.
10,485 lbs 4,755.92 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.
9,700 lbs 4,399.85 kg
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.
9,978 lbs 4,525.94 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 7 in 3.84 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 53 ft 8 in 16.36 m
Baggage Capacity
Interior Volume
Volume of internal baggage compartment and typical weight capacity.
48 ft3 14.72 m3
Interior Weight 350 lbs 158.76 kg
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
V Speeds:
Speed Va 169 kts
Speed Vmo 226 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 2,552 ft 777.85 m
5000 ft elev 25'C 3,648 ft 1,111.91 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 2,363 ft 720.24 m
5000 ft elev 25'C 3,071 ft 936.04 m
Climb Performance / Ceilings
Climb 1,950 fpm 594.36 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.
17 min / 25,000 ft 17 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.
474 fpm 144.48 mpm
Engine Out Gradient
The initial engine-out feet per nautical mile gradient, for multi-engine (mainly turboprop) aircraft with MTOW of 12,500 pounds or less. One Engine Inoperative (OEI) climb rate and gradient are based on the landing gear retracted and wing flaps in the takeoff configuration used to compute the takeoff distance. The climb gradient is obtained by dividing the climb rate (feet per minute) in the Airplane Flight Manual, times 60 by the best single engine rate of climb speed (Vyse) as appropriate.
259 ft/nm 78.94 m/nm
Certified Ceiling
Maximum allowable operating altitude determined by airworthiness authorities.
30,000 ft 9,144.00 m
Ceiling All Engines
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.
30,000 ft 9,144.00 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.
19,170 ft 5,843.02 m
Cruise Performance at 25,000 ft
Recomended
Speed / Power 251 kts / 0 %
Fuel Flow 73.13 gal / 490 lbs 276.84 L / 222.26 kg
Range 823 NM
Altitude 25,000 ft 7,620.00 m
Payload / Fuel
740 lbs / 335.66 kg / 0.00 lb/gal 0.00 kg/L
High Speed
Speed / Power 263 kts / 0 %
Fuel Flow 91.34 gal / 612 lbs 345.77 L / 277.60 kg
Range 710 NM
Altitude 25,000 ft 7,620.00 m
Payload / Fuel
740 lbs / 335.66 kg / 0.00 lb/gal 0.00 kg/L
Cruise Performance at 26,000 ft
Long Range
Speed / Power 208 kts / 0 %
Fuel Flow 49.55 gal / 332 lbs 187.58 L / 150.59 kg
Range 981 NM
Altitude 26,000 ft 7,924.80 m

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