7E004

Collective controls;

Cyclic controls;

Yaw controls; 2. "Circulation-controlled anti-torque or circulation-controlled direction control systems"; 3. Rotor blades incorporating 'variable geometry aerofoils', for use in systems using individual blade control.

Not used;

Air data systems based on surface static data only, i.e., which dispense with conventional air data probes;

Three dimensional displays for "aircraft";

Not used;

Electric actuators (i.e., electromechanical, electrohydrostatic and integrated actuator package) specially designed for ‘primary flight control’;

‘Flight control optical sensor array’ specially designed for implementing "active flight control systems"; or

"DBRN" systems designed to navigate underwater, using sonar or gravity databases, that provide a positioning "accuracy" equal to or less (better) than 0,4 nautical miles;

Photonic-based "technology" for sensing "aircraft" or flight control component state, transferring flight control data, or commanding actuator movement, "required" for "fly-by-light systems""active flight control systems";

Not used;

Real-time algorithms to analyse component sensor information to predict and preemptively mitigate impending degradation and failures of components within an "active flight control system";

Real-time algorithms to identify component failures and reconfigure force and moment controls to mitigate "active flight control system" degradations and failures;

Integration of digital flight control, navigation and propulsion control data, into a digital flight management system for "total control of flight";

Not used;

"Technology""required" for deriving the functional requirements for "fly-by-wire systems" having all of the following: a. ‘Inner-loop’ airframe stability controls requiring loop closure rates of 40 Hz or greater; and b. Having any of the following: 1. Corrects an aerodynamically unstable airframe, measured at any point in the design flight envelope, that would lose recoverable control if not corrected within 0,5 seconds; 2. Couples controls in two or more axes while compensating for ‘abnormal changes in aircraft state’; 3. Performs the functions specified in 7E004.b.5.; or 4. Enables "aircraft" to have stable controlled flight, other than during take-off or landing, at greater than 18 degrees angle of attack, 15 degrees side slip, 15 degrees/second pitch or yaw rate, or 90 degrees/second roll rate;

"Technology""required" for deriving the functional requirements for "fly-by-wire systems" to achieve all of the following: a. No loss of control of the "aircraft" in the event of a consecutive sequence of any two individual faults within the "fly-by-wire system"; and b. Probability of loss of control of the "aircraft" being less (better) than 1 × 10^-9 failures per flight hour;

Multi-axis fly-by-wire or fly-by-light controllers, which combine the functions of at least two of the following into one controlling element: a. Collective controls; b. Cyclic controls; c. Yaw controls;

"Circulation-controlled anti-torque or circulation-controlled direction control systems";

Rotor blades incorporating ‘variable geometry aerofoils’, for use in systems using individual blade control.