Orlican M-8 EAGLE 2022, Pilots Operating Manual

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ORLI Č AN M-8 EAGLE
PILOT'S OPERATING
REVISION NO. 05
DATE OF ISSUE: MAY 02,
5.4. AIRCRAFT DESCRIPTION
1. CHARACTERISTICS
The M-8 EAGLE aircraft is a two-seat, strut high-wing monoplane of all-composite structure designed for
sport or recreational flying. Favorable flight characteristics make the aircraft suitable for flight training.
The aircraft features spacious crew and baggage compartments. Large doors provide for comfortable
boarding of crew and loading of baggage. Adjustable seats allow the pilots of all heights to find
comfortable position. A stiff Kevlar cabin and three- point seat harnesses system provide maximum safety
of crew in emergency situations.
2. AIRFRAME
The fuselage is made of carbon-kevlar composite. Bulkheads are bonded into integrally stiffened skin to
receive forces from the landing gear, stabilizer, rudder, safety harnesses and wings. There are two doors
with a central-lock system mounted on flush hinges on the sides of fuselage, opening upwards.
Sandwich-type single-spar wings made of carbon-composite house two fuel tanks within leading section.
Wings are fitted with slotted Fowler flaps. Wings have rectangular center section with trapezoidal tips.
MS 313 wing profile is used. Roll along the longitudinal axis is controlled by ailerons with differentiated
deflection 12° down and 17° up. With aileron deflection up, a nose rises from profile, providing favorable
yawing moment. The wing strut is made of a steel strength tube with fittings and a laminate cover.
Trapezoidal horizontal tail unit is fixed into the fuselage bulkheads by pins and screws. Aerodynamically
balanced elevator has electrically servo-actuated trim tab. The elevator deflection is 19° up and 14° down.
Trapezoidal swept vertical tail. The rudder deflection is approximately 25°.
Rudder has dual cable control, ailerons are connected in the wings by a system of rods and controlled
through cables, elevator is rod-operated. Control yokes are used for hand-operated control. Rudder and
nose landing gear are operated by pedals with top-mounted shafts, which greatly improve the kinematics
of controls. Engine and landing gear brakes are controlled by appropriate controllers. The flaps are driven
by central actuator through a system of rods. The actuator control is located on the center panel.
Tricycle landing gear with steerable nose wheel. Main wheels - size 14x4-6 - are provided with hydraulic
disc brakes. These are carried on an all-composite leg. The nose wheel is fitted with spring and hydraulic
shock absorber. The front wheel has size 12x4-4. All wheels provided with fairings. Tire inflation of all
wheels is 2,5 bar (36psi).
3. CONTROLS
PEDALS pressing left pedal turns aircraft left both on the ground and in the air, and vice
versa.
HAND
CONTROLS
pulling the yoke backwards, towards the pilot, raises the nose of aircraft (the
angle of attack increases) and the aircraft climbs. Pushing the yoke forward
dives the aircraft. Turning the yoke to the left banks the aircraft to the left,
turning the yoke to the right banks the aircraft to the right.
ENGINE
THROTTLE
pushing (or turning right) controller located on the middle-panel increases
engine output, and vice versa.
BRAKE
CONTROL
moving lever backwards, in the opposite direction of taxiing, brakes the aircraft.
The parking brake is controlled by separate valve.
GENERAL INFORMATION PAGE 16 OF 99