A/C SYS 2017

airframe, engine and systems

Structure, vehicle system, avionic system

- complex and integrated set of structural components
- supports the mass of systems and PAX
- carries loads and stresses
- also known as the “platform”

- also known as general or utility system
- enables the A/C to fly safely
- provides an adequate environment for crew and PAX

provides information, control and communication functions that enable the aircraft to fulfil its operational role

- nowadays usually a Fly-by-Wire (FBW) system
- pilot control input is elaborated on the basis of air data, A/C attitude etc. to issue the proper control surface deflections that will effect the desired aircraft motion

in most recent aircraft a Full Authority Digital Engine Control (FADEC) system

provides airspeed, altitude, air temperature, rate of climb or descent information

provides information on pitch, yaw and roll angles, rates and accelerations

provides electrical power for flight and engine control computers, air data system, attitude systems, hydraulic servo-valves and (on some A/C) electrically driven hydraulic pumps

provides motive power for the actuators that move the flight control surfaces, or the engine thrust reversers

The functions whose loss would reduce the capability of the A/C or its crew to cope with adverse operating and environmental conditions (i.e. loss of cabin pressurization or loss of the anti-icing system)

Functions which could cause the loss of the aircraft or fatal injuries to the occupants (i.e. a complete loss of engine power)

The severity of a failure condition must be inversely proportional to ist probability

- Effects on the airplane
- Effects on the crew members
- Effects on the occupants