A I R C R A F T S P E C I F I C A T I O N S

1 . G e n e r a l D e s c r i p t i o n

1.1. Number of Crew Placesthe basic aircraft shall have accommodation for a pilot and copilot.

1.2. Number of Passengersthe aircraft shall be designed to accommodate a maximum of five passengers and two crew members in the standard interior configuration; and six passengers and two crew members in the air taxi configuration.

1.3. Number and Type of Enginestwo Ge Honda HF120 turbofan engines

1.4. Certificationthe aircraft will be certified to the requirements of U.s. Far part 23, including: Day, night, VFr, iFr, single pilot operation, flight into known icing conditions, and rVsM certification.

1.5. Approximate Dimensions

overall Height ............................................. 13.21 ft (4.03 m)

overall length ............................................41.70 ft (12.71 m)

Wing

span (overall) ..............................................39.87 ft (12.15 m)

cabin

Height (overall) ...............................................4.94 ft (1.51 m)

length—Fwd. pressure Bulkhead

to aft pressure Bulkhead ................................ 17.80 ft (5.43 m)

Width .............................................................5.00 ft (1.52 m)

1.6. Approximate Weights

Useful load ...............................................3,378 lb (1,532 kg)

Maximum payload ...................................... 1,400 lb (635 kg)

figure 1 HondaJet Exterior Dimensions

41.70 ft

13.21 ft

39.87 ft

H o n D a J e t aircraft Description september 2007

I N T R O D u C T I O N

HondaJet employs numerous advancements

in aircraft technology and design to achieve

far better fuel efficiency, more available cabin

space, and higher cruise speed than conven-

tional aircraft in its class.

This document is published for the purpose of providing general information

for the evaluation of the design, performance and equipment of the Aircraft.

HondaJet carries with it Honda’s legendary commitment to world-class quality

in design and manufacture. Key HondaJet innovations include a unique over-

the-wing engine-mount (OTWEM) configuration, a natural-laminar flow (NLF)

wing and fuselage nose, and an all-composite fuselage.

H o n D a a i r c r a F t c o M p a n y, i n c .

6423-B Bryan Blvd.Greensboro, North Carolina 27409

hondajet.com

2 . P E R F O R M A N C E

all performance data mentioned below are based on a standard aircraft configuration, international standard atmosphere (isa) conditions and zero wind. addition-ally, take-off and landing performance data are based on level, hard surface, and dry runways. production air-craft performance will depend on actual flight condi-tions and vary from that described below.

Cruise

cruise speed at Fl300

(Maximum cruise thrust, isa conditions) .................................... 420Ktas

Limitations

service ceiling ............................................................. Fl430

Pressurization (Differential) ...........................................................8.7 psi

Range

iFr range **

(1 pilot plus 3 passengers at 200 lb each) ............................ 1180 nm

(**includes take-off, climb, cruise at Fl410,

100nm alternate, descent, and 45 minute reserve)

Airport Performance

take-off Distance***...................................................3120 ft

(***the distance required to climb to 35 feet above the runway plus

a 15% factor, all engines operating condition)

landing Distance ....................................................... 2500 ft

Engines

Manufacturer/Model .............................Ge HonDa / HF120

output ..................................... 1880 lb/each (Max take-off)

Bypass ratio ..................................................................... 2.9

3 . s t r U c t U r a l D e s i G n c r i t e r i a

the fuselage will be constructed entirely of graphite composites. the wing and the empennage will be con-structed of aluminum. the cabin will be pressurized up to 8.7 psi. all structural limit speeds will be defined to allow for cruise at maximum cruise thrust at normal cruise altitudes as well as efficient descent profiles.

4 . F u S E L A G E G R O u P

the all-composite fuselage structure will consist of a combination of honeycomb sandwich structure and co-cured stiffened panels. an integrally stiffened panel structure will be employed for the constant cross-section portion of the cabin to maximize the cabin volume.

5 . W I N G G R O u P

5.1. Winga newly designed natural-laminar flow airfoil, the sHM-1, will be employed for the wing. the wing will be constructed in two sections: the left and the right wing. the torque box will contain three spars, the ribs, and the skin with integrated stringers forming integral fuel tanks.

5.2. Nacelles and Pylonsthe aircraft engines will be enclosed by nacelles and shall be pylon-mounted over the wing. the pylons will be integrated with reinforced ribs. access will be pro-vided to the interior of the pylon for inspection and maintenance. Ventilation and drainage provisions shall be provided.

H o n D a J e t aircraft Description september 2007

26 in.

145.8 in. (3704 mm)

84 in. (2133.6 mm)

(660 mm)

figure 2 Interior Dimensions

H o n D a J e t aircraft Description september 2007

9 . s y s t e M s

9.1. Flight Controlsthe aircraft will have dual flight controls with column-mounted control wheels and adjustable rudder pedals. a combination of cable and push-pull rod mechanisms will be used to actuate the primary control surfaces. trim in all three axes will be provided by trim tabs.

9.2. Flapsa linkage mechanism will be used for the flap system. the flap system will have two positions: takeoff and landing. the flap system will be deployed by two elec-tric actuators: one for each wing and each installed at the wing root.

9.3. Environmental Systemthe environmental control system will provide control of the aircraft environment, with dual-zone control for cabin and cockpit. the cabin altitude will be maintained below 8,000 ft up to 44,000 ft.

9.4. Ice Protection Systemthe ice protection system will be certified for known icing. icing protection will be provided for the wing, horizontal tail, windshield, and engine inlets.

9.5. Electrical SystemDual high-output starter generators will feed an automated electric power distribution system via separate busses. a standby battery will provide an additional source of electrical power for emergency operation.

9.6. Hydraulic Systeman electric motor operated hydraulic power pack will supply 3000 psi hydraulic power. the hydraulic system will provide power for the following systems during all flight phases:

1. landing Gear actuation system – landing gears and doors

2. steering system – nose Wheel steering3. Braking system

9.7. Fuel Systemthe aircraft will be refueled through a single point. During flight, the fuel will be transferred from the carry-through tank to the right and left wing integral tanks by transfer pumps located in the carry-through tank. an automatic cross-feed function will be incorporated to correct fuel imbalance between the left and right wings.

60 in.(1525 mm)

59 in.(1505 mm)

64 in

.(1

635

mm

)

6 . e M p e n n a G e G r o U p

the empennage will be a t-tail configuration. the horizontal tail will be a conventional, two-spar, aluminum structure. the fin will also be a conventional, two-spar structure.

7 . p o W e r p l a n t s

Ge Honda HF120 turbofan engines mounted over the wing will be controlled by the Full authority Digital engine control (FaDec) system.

8 . l a n D i n G G e a r

the landing gear will be a typical tricycle-type layout with a steerable nose wheel. the nose gear will be of the shock-absorber strut type. the main landing gear will be of the trailing-link type. a side-brace actuator will be used to extend and retract the landing gear. the main gear will be equipped with an anti-lock braking system.

11. i n t e r i o r

the standard cabin will be separated from the cockpit by a refreshment center, which will also serve as a divid-er and storage area. the cabin area will be a constant cross-section. a dropped aisle provides for a 4.9 ft (59 in) aisle height throughout the cabin area. the cabin will feature four seats in a spacious club arrangement with a forward side facing seat (subject to certification).

the aft lavatory will be separated from the rest of the cabin by solid panel doors. in addition to a flushing toi-let, it will be equipped with a vanity, a sink and a stor-age cabinet.

external baggage areas are provided. a nose baggage compartment (approx. 9 ft3) will be located just forward of the forward pressure bulkhead, and an aft baggage compartment (approx. 57 ft3) will be located in the tail-cone.

12 . W a r r a n t y

seller expressly warrants the aircraft (and new equip-ment and accessories except as noted below) to be free from defects in material and workmanship under normal use and service for a period of 3 years or 1500 hours (whichever first occurs) after delivery to the origi-nal retail purchaser or first user except that the war-ranty period for the aircraft interior and exterior paint shall be 1 year. the foregoing warranty shall extend to any other person or entity to which title to the aircraft is transferred during the applicable warranty term. en-gines, engine accessories, and avionics are specifically excluded from this warranty and are covered by their re-spective manufacturer’s warranty, the applicable terms and conditions of which are provided at Delivery time.

10 . a V i o n i c s a n D i n s t r U M e n t a t i o n

the aircraft employs an all-glass flightdeck, which is an integrated design having open architecture. all in-formation, from flight and engine instrumentation to navigation, communication, terrain, and traffic data is integrated and digitally presented on the dual, large-format, high-resolution primary Flight Displays (pFDs) and the Multi-Function Display (MFD). the pFD contains the airspeed indicator, vertical-speed indi-cator, adjustable altimeter, direction indicator, pitch and bank indicator (artificial horizon), slip/skid indica-tor, and navigation information. the MFD contains the engine indication Display, fuel flow, fuel quantity, generator current, and the Global positioning system moving map. this integrated cockpit configuration provides for situational awareness, functionality, ease of operation, and redundancy to assist flight safety.

the avionics suite will provide the following functions:

Dual VHF coM

Dual VHF naV/loc/Gs

Gps

Mode s transponder

Marker beacon

slip and skid indication

Flight Director

3-axis autopilot

Weather overlay

traffic awareness (tcas i)

audio control

artificial horizon indication

airspeed indication

Directional gyro and Hsi indication

Vertical speed indication

terrain awareness

standby instruments

outside air temperature

clock/elapsed time

crew alerting system

propulsion system indications included:

n1

n2

itt

oil temperature

Fuel Quantity

oil pressure

Fuel Flow

H o n D a J e t aircraft Description september 2007

figure 3 Standard Interior Dimensions Configuration (Preliminary)

• Maintenance Manual

• Illustrated Parts Catalog

• Wiring Diagram Manual

• Structural Repair Manual

• Component Maintenance Manual

• Nondestructive Testing Manual

• illustrated tool and equipment Manual

• Airplane Flight Manual

13 . t r a i n i n G

seller shall make available at its designated training facility a ground and simulator flight training program for 2 qualified pilots, and a ground maintenance pro-gram for 1 mechanic. purchaser shall be responsible for all travel and living expenses of purchaser’s per-sonnel.

14 . t e c H n i c a l p U B l i c a t i o n s

the aircraft will be delivered with the following technical publications and a revision service for 1 year at no charge:

15. M a i n t e n a n c e p l a n n i n G a n D t r a c K i n G s y s t e M

seller shall provide a subscription to an automated Maintenance planning and tracking system for 1 year at no charge.

seller’s obligation under this warranty is limited to the repair or replacement, at its option, of any part or parts which within the applicable period as set forth above shall be returned to seller or authorized service facility designated by seller and, which upon examination, shall be determined by seller to be defective. any replacement parts are warranted for the remainder of the applicable original warranty period.

the repair or replacement of defective parts under this warranty shall be made without charge for parts or labor for removal, installation and/or actual repair of such de-fective parts, except shipping and, if applicable, import duties and sales/use taxes on replacement parts, which are the responsibility of the owner/operator. purchaser shall be responsible for any costs related to items sub-mitted under this warranty which are later determined to have no defect (no Fault Found).

the provisions of this warranty do not apply to a) the aircraft and its equipment, accessories or service parts manufactured or sold by seller which have been subject to misuse, negligence or accident or which shall have been repaired or altered by anyone other than seller or seller’s authorized service facility in any way so as to af-fect adversely its performance, stability or reliability; b) normal maintenance services (such as cleaning, control rigging, brake and other mechanical adjustments) and mechanical inspections or the replacement of service items (such as light bulbs, brake linings, filters, hoses and tires) made in connection with such services or re-quired as maintenance; c) normal deterioration of soft trim and appearance items (such as paint, upholstery and rubber-like items) due to wear and exposure; and d) aircraft equipment, accessories or service parts sold separately which have been improperly installed.

H o n D a J e t aircraft Description september 2007

H O N D A A I R C R A F T C O M P A N y

hondajet.com

© 2007 Honda Aircraft Company, Inc. In the event of any conflict or discrepancy between this document and the basic purchase agreement to which

it is incorporated, terms specified in the basic purchase agreement govern. Due to the time span between the date of this Aircraft Description and the

scheduled delivery date of the aircraft, Seller reserves the right to revise the Aircraft Description document wherever occasioned by product modifications,

U.S. Federal Aviation Administration (FAA) regulations (or those of such other applicable governmental body), or other manufacturing and/or vendor cause.