FUSELAGE
- The fuselage has a slightly oval cross-section at floor level to improve foot room, with a dropped aisle running the cabin’s length. The keyed cabin door, located on the forward left side, uses eight locking pins and a pressure seal, and is equipped with a folding two-step entry stair. A plug-type emergency exit is positioned on the right side between the fore and aft seats. Windshields meet bird-strike resistance standards of 14 CFR Part 23. Structural framing surrounds the main door, emergency exit, and windshields.
- The nose compartment contains the forward baggage area and the radar assembly behind the composite radome.
- The tailcone houses the environmental and electrical components, engine fire-extinguishing system, and an aft baggage compartment accessible through an external door, providing space for skis or other long items.
WING SECTION
- The aircraft incorporates a high-lift airfoil designed for low stall speeds. It has a low-drag and pitching moment, optimized for high-speed cruise. 3-degrees dihedral contributes to lateral stability.
- Leading edge is equipped with pneumatic de-ice boots.
- Control surfaces includes ailerons, flaps and upper/lower speed-brakes.
- All fuel is carried inside the wing.
TAIL SECTION
- The aircraft features a T-tail configuration with aluminum spars and skins, and composite fairings and strakes. The fixed horizontal stabilizer carries two elevators with trim tabs and a 27° leading-edge sweep. The vertical stabilizer, swept 52° at the leading edge, includes a single rudder with a trim tab and a red LED ground recognition light at the top.
- Both stabilizers are equipped with pneumatic de-ice boots for ice protection.
LANDING GEARS - GENERAL
- Landing gears are retractable, tricycle system that is electrically controlled and hydraulically actuated.
- Each landing gear unit is retracted by its own hydraulic actuator.
- When the gear is retracted, the nose gear and main gear struts are enclosed by mechanically actuated doors linked to the gear struts. The trailing-link main gear wheels remain exposed within the wheel wells.
- Gear position and warning indications are provided through colored indicator lights and an aural warning system.
- The landing gear can be extended and flown up to VMO or 250 KIAS, and retracted at or below 185 KIAS.
BRAKES
- The main gear assemblies are equipped with disc brakes. These brakes normally function as anti-skid power brakes, but they can also operate as power brakes without anti-skid protection if necessary.
- Braking is initiated by the crew pressing the tops of the rudder pedals, which are mechanically linked by cables to operate the brake metering valve.
ANTI-SKID SYSTEM
- With the ANTI SKID switch ON, the system optimizes braking efficiency on all runway surfaces. It can only reduce brake pressure, never exceed that commanded by the crew.
- Each wheel’s speed transducer sends signals to the anti-skid control box, which reduces pressure to any wheel showing rapid deceleration (impending skid) until normal speed returns.
- The system also provides touchdown protection, preventing brake application while airborne; pressure is released until 3 seconds after touchdown or wheel spin-up.
- A locked-wheel crossover feature prevents yaw by reducing pressure to both wheels if one decelerates 70% faster than the other. This protection disables below 12 knots to allow tight taxi turns.
CONTROLS AND INDICATIONS
Landing Gear Control Handle
The LANDING GEAR handle, mounted on the left side of the center tilt panel, commands all normal gear retraction and extension operations. Its position directly determines hydraulic sequencing: handle UP = gear retraction, handle DOWN = gear extension.
Gear Position Indication & Aural Warning
Three green lights confirm all gear down and locked.
A single red light indicates gear in transit or unsafe condition.
The aural gear warning will not let you forget the gear:
- If power is reduced below ~85% N1 and airspeed is under 130 KIAS with gear UP, a warning horn sounds.
- You can silence it with the HORN SILENCE push button.
System Test
A rotary TEST knob, located at the top of the copilot panel, provides full system verification of both gear and anti-skid warning circuits.
Nosewheel Steering
- The rudder pedals are mechanically linked to the nosewheel, providing 20° of steering either side of center. A spring-loaded mechanism allows an additional ±55° of free-castering (total ±75°) using differential braking or asymmetric thrust.
- When the gear retracts, the nosewheel is automatically centered and steering disengaged.
- When extended, steering re-engages automatically regardless of flight or ground state.
Parking Brake
- The parking brake locks brake pressure by trapping hydraulic fluid in the lines.
- Release is immediate once pressure is released from the pedals.