Hawker 400XP

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).

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.

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.

Jet & Turboprop Aircraft - Maximum Ramp Weight minus Basic Operating Weight, not to exceed Zero Fuel Weight or maximum fuel capacity.

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.

(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.

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.

Volume of external 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.

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.

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.

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.

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.

Maximum allowable operating altitude determined by airworthiness authorities.

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.

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.