Aircraft Systems

Question 0

Fuel system

Answer 0

Two 28 gallon fuel tanks (one in each wing) gravity fed to a 3 position selector valve to the reservoir tank through the electric fuel pump, through the shut-off valve, the fuel strainer to the engine driven fuel pump which is then delivered to the fuel/air control unit on the bottom of the engine

Question 1

Engine

Answer 1

Textron-lycoming IO-360-L2A
Normally aspirated, direct drive, fuel injected, horizontally opposed, air cooled, 4 cylinder engine w/ 360 cubic inch displacement

Question 2

Electrical system

Answer 2

28v DC powered by a belt driven 60 ampere alternator and a 24v main storage battery controlled by the master switch. Standby battery supplies power to essential BUS if alternator and main battery fail. Avionics switch supplies power to BUS1 and BUS2. Circuit breakers protect the system.

Question 3

Brake system

Answer 3

Hydraulic actuated single disk brake on each of the main landing gear wheels connected to a master cylinder attached to each rudder pedal by a hydraulic brake line. Applying pressure to the top of each rudder pedal engages the brake on the corresponding wheel. Parking brake engages both brakes simultaneously.

Question 4

Maximum weight (ramp)

Answer 4

2558 lbs

Question 5

Maximum takeoff weight

Answer 5

2550 lbs

Question 6

Maximum fuel capacity

Maximum usable fuel

Answer 6

56 gallons

53 gallons

Question 7

Maximum oil

Minimum oil

Answer 7

8 quarts

6 quarts

Question 8

Maximum engine RPM

Answer 8

2700 RPM

Question 9

AHRS

Answer 9

Attitude & Heading
Reference System
Accelerometers, tilt sensors & rate sensors replace spinning mass gyros. Magnetometer in wing

Question 10

ADC

Air Data Computer

Answer 10

Information provided by pitot static system / outside temp probe / calculates pressure altitude, airspeed, true airspeed, vertical airspeed & outside air temperature