Note: 7E004.b.5. does not control: a. “Development”“technology” for integration of digital flight control, navigation and propulsion control data, into a digital flight management system for “flight path optimisation”; b. “Development”“technology” for “aircraft” flight instrument systems integrated solely for VOR, DME, ILS or MLS navigation or approaches. 6. Not used; 7. “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 Technical Note: ‘Inner-loop’ refers to functions of “active flight control systems” that automate airframe stability controls. 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’; Technical Note: ‘Abnormal changes in aircraft state’ include in-flight structural damage, loss of engine thrust, disabled control surface, or destabilizing shifts in cargo load. 3. Preforms the functions specified in 7E004.b.5.; or Note: 7E004.b.7.b.3. does not control autopilots. 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; 8. “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; Note: 7E004.b. does not control technology associated with common computer elements and utilities (e.g., input signal acquisition, output signal transmission, computer program and data loading, built-in test, task scheduling mechanisms) not providing a specific flight control system function. c. “Technology” for the “development” of helicopter systems, as follows: 1. 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; 2. “Circulation-controlled anti-torque or circulation-controlled directional control systems”; 3. Rotor blades incorporating “variable geometry airfoils”, for use in systems using individual blade control.