Beechcraft King Air C90

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.

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.

Max Range as indicated by the manufacturer under optimal conditions.

See Cruise & Mission performance for examples of range capabilities.

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.

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).

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.

Is computed using the Max Takeoff Weight (MTOW) divided by the total wing area.

Power Loading is calculated using the Max Takeoff Weight (MTOW) divided by total rated thrust / horsepower.

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.

(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.

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.

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.

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.

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.

Volume of internal baggage compartment and typical weight capacity.

Cabin pressure differential expressed in PSI.

Is the maximum cruise altitude at which a 14.7-psi, sea level cabin altitude can be maintained in a pressurized aircraft.

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.

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.

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.

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.

Max Range as indicated by the manufacturer under optimal conditions.

See Cruise & Mission performance for examples of range capabilities.

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.