Aircraft Overview: HondaJet
Aircraft Overview: HondaJet
The HondaJet is a twin-engine business jet produced by Greensboro, North Carolina-based Honda Aircraft Co. An experimental HondaJet first flew on Dec. 3, 2003, with the HA-420 type receiving FAA approval on Dec. 8, 2015, and the first delivery taking place on Dec. 23, 2015.
Improved versions of the HondaJet were introduced in 2018 (HondaJet Elite), 2021 (HondaJet Elite S) and 2022 (HondaJet Elite II), all of which are commercial designations for the HA-420 type.
A larger HondaJet that is “capable of nonstop transcontinental flight across the United States” was announced on Oct. 12, 2021, an airframe that was designated at the time as the HondaJet 2600 Concept.
Subsequently given the HondaJet Echelon name in October 2023, it is expected that this HondaJet—which the company has said will be “offered alongside the HondaJet Elite II”—will make its first flight in 2026.
Cabin
Based on the serial number, the HA-420 can accommodate as many as six or seven passengers, in addition to one or two pilots.
Airframes in the Serial No. range 42000011 to 42000125 (those marketed as the HondaJet) are limited to seven seats for the passengers and pilot(s), while Serial Nos. including and subsequent to 42000126 (the HondaJet Elite, Elite S, and Elite II) increase the number of seats to eight.
The HondaJet Elite II’s interior has a length of 17.8 ft., width of 5 ft., and height of 4.83 ft., as well as 62 ft.3 of combined stowage volume (9 ft.3 in the nose compartment and 53 ft.3 in the aft compartment).
Comparatively, the HondaJet Echelon will increase the interior length to 25.38 ft., height to 5.21 ft. and width to 5.08 ft., with the combined stowage volume also being raised to 120 ft.3
Avionics
Pilots operate all commercial designations of the HA-420 using avionics that are based on Garmin’s G3000 integrated flight deck, an avionics system that is also planned for the HondaJet Echelon.
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Variants
Two GE Honda Aero Engines HF120-H1A turbofan engines power the HA-420, have an over-the-wing engine mount configuration and have an uninstalled thrust output of 2,050 lbf.
HA-420 airframes marketed as the HondaJet Elite II are limited to an 11,100-lb. maximum takeoff weight (MTOW) and 10,360-lb. maximum landing weight, with the usable fuel capacity being 471.62 gal.
In contrast to the HA-420 commercial designations, the HondaJet Echelon will be powered by two Williams International FJ44-4C engines that have a total output of 3,450 lbf.
Beyond increased baggage and passenger capacity, the Echelon is also expected to have an 17,550-lb. MTOW.
Mission and Performance
Regardless of the commercial designation, the performance limitations of the HA-420 type include a 43,000-ft. maximum operating altitude and a 10,000-ft. maximum takeoff field elevation, as well as a maximum operating limit speed (VMO) of 270-kt. indicated airspeed (KIAS) and a maximum operating limit Mach (MMO) 0.72 Mach.
Beyond those certified limitations, the HondaJet Elite II is capable of a maximum cruise speed—at flight level (FL) 300 and in International Standard Atmosphere (ISA) conditions—of 422-kt. true airspeed (KTAS).
When carrying four occupants and National Business Aviation Association (NBAA) instrument flight rules (IFR) reserves, the range of the HondaJet Elite II is 1,547 nm.
That HA-420 commercial designation is capable of a takeoff distance of 3,699 ft. in ISA conditions, at the airframe’s MTOW and at sea-level altitude. Assuming the same criteria that is used to determine the range noted above, a 2,717-ft. unfactored landing distance is also possible.
In comparison to the HondaJet Elite II, the HondaJet Echelon will be capable of an increased range of 2,625 nm, assuming a standard aircraft, NBAA IFR reserves (100 nm) and four passengers and one pilot.
The maximum cruise speed and maximum cruise altitude will also be increased to 450 KTAS and 47,000 ft., respectively.
The Echelon’s expected 3,300-ft. takeoff distance assumes ISA conditions, the airplane’s MTOW and sea-level altitude, and the 2,550-ft. landing distance is based on ISA conditions, the maximum landing weight and sea-level altitude.
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