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.

‘Technology’ for the ‘development’, ‘production’ and ‘use’ of equipment or ‘software’, specified in IX.A7.

‘Technology’ for the ‘development’, ‘production’ and ‘use’ of equipment or ‘software’, specified in IX.A7.

Program information