FLIGHT CONTROLS AND SYSTEMS, AIRCRAFT LIMITATIONS Flashcards
Airframe
The mechanical structure of an aircraft
Fuselage
The main body of the helicopter.
Semi-rigid Rotor System
Blades flap together as a unit.
Rigid Rotor System
Blades fixed to the rotor hub.
Fully Articulated Rotor System
Allows independent leading/lagging, flapping, and feathering.
Tandem Rotor System
Two large horizontal rotor assemblies.
Coaxial Rotors
Two main rotors rotating in opposite directions.
Intermeshing Rotor
Two rotors that overlap but don’t touch.
Swash plate Assembly
Converts stationary Control input into rotating inputs on a uniball sleeve
Freewheeling Unit
Allows rotor to spin freely when the engine stops
Anti-torque System
Counteracts the main rotor’s torque.
Fenestron
Fan-in-tail anti-torque system
NOTAR
No Tail Rotor system using a jet of air
Engines
Power the helicopter’s rotors. Reciprocating(Piston) and Turbine.
Main Rotor Transmission
Transmits power from the engine to the main rotor.
Clutch
Connects/disconnects the engine from the main rotor.
Fuel System
Stores and delivers fuel to the engine
Electrical Systems
Power avionics and other systems (14 volt system, 12 volt battery, 60 amp alternator)
Hydraulics
amplify the pilot’s input, making it easier to control the aircraft.
Stability Augmentation Systems
Enhance helicopter stability
Environmental Systems
Control temperature and pressure.
Anti-ice and De-ice Systems
Prevent ice buildup on critical surfaces.
Airspeed Limitations
3,000ft DA: 102 KIAS, Above 3,000ft DA see placards
Power Plant Limitations
O-360-J2A: Max cont. 104%
Max transient 106%
CHT Max: 500F
Oil Temp Max: 245F
Mini idle: 25psi
Mini flight: 55psi
Max flight: 95
Max start & warm up: 115psi
