ECCN 7E004

• a."Technology" for the "development" or "production" of any of the following:
• 2. Air data systems based on surface static data only, i.e., which dispense with conventional air data probes;
• 3. Three dimensional displays for "aircraft";
• 5. Electric actuators (i.e., electromechanical, electrohydrostatic and integrated actuator package) specially designed for 'primary flight control';
• 6. 'Flight control optical sensor array' specially designed for implementing "active flight control systems"; or
• 7. "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;
• b."Development" "technology", as follows, for "active flight control systems" (including "fly-by-wire systems" or "fly-by-light systems"):
• 1. 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";
• 3. Real-time algorithms to analyze component sensor information to predict and preemptively mitigate impending degradation and failures of components within an "active flight control system";
• 4. Real-time algorithms to identify component failures and reconfigure force and moment controls to mitigate "active flight control system" degradations and failures;
• 5. Integration of digital flight control, navigation and propulsion control data, into a digital flight management system for "total control of flight";
• 7. "Technology" "required" for deriving the functional requirements for "fly-by-wire systems" having all of the following:
• 7.a. 'Inner-loop' airframe stability controls requiring loop closure rates of 40 Hz or greater; and
• 7.b. Having any of the following:
• 7.b.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;
• 7.b.2. Couples controls in two or more axes while compensating for 'abnormal changes in aircraft state';
• 7.b.3. Performs the functions specified in 7E004.b.5; or
• 7.b.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 of "fly-by-wire systems" to achieve all of the following:
• 8.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
• 8.b. Probability of loss of control of the "aircraft" being less (better) than 1 × 10−9 failures per flight hour;
• 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:
• 1.a. Collective controls;
• 1.b. Cyclic controls;
• 1.c. Yaw controls;
• 2. "Circulation-controlled anti-torque or circulation-controlled direction control systems";
• 3. Rotor blades incorporating 'variable geometry airfoils', for use in systems using individual blade control.

4 items reserved by BIS (not shown)