7E004 Category 7E

Other “technology” as follows (see List of Items Controlled).

Category 7: Navigation and Avionics

Reasons for control

• NS: National security
• MT: Missile technology
• AT: Anti-terrorism

Country chart

List-based license exceptions

Items

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

Related controls

(1) See also 7E001, 7E002, 7E101, and 7E994. (2) In addition to the Related Controls in 7E001, 7E002, and 7E101 that include MT controls, also see the MT controls in 7E104 for design “technology” for the integration of the flight control, guidance, and propulsion data into a flight management system, designed or modified for rockets or missiles capable of achieving a “range” equal to or greater than 300 km, for optimization of rocket system trajectory; and also see 9E101 for design “technology” for integration of air vehicle fuselage, propulsion system and lifting control surfaces, designed or modified for unmanned aerial vehicles capable of achieving a “range” equal to or greater than 300 km, to optimize aerodynamic performance throughout the flight regime of an unmanned aerial vehicle.

Notes

Technical Note: For the purposes of 7E004.a.5, 'primary flight control' is “aircraft” stability or maneuvering control using force/moment generators, i.e., aerodynamic control surfaces or propulsive thrust vectoring.

Technical Note: For the purposes of 7E004.a.6, a 'flight control optical sensor array' is a network of distributed optical sensors, using “laser” beams, to provide real-time flight control data for on-board processing.

Note: 7E004.b.3 does not include algorithms for purpose of off-line maintenance.

Note: 7E004.b.4 does not include algorithms for the elimination of fault effects through comparison of redundant data sources, or off-line pre-planned responses to anticipated failures.

Note: 7E004.b.5 does not apply to: 1. “Technology” for integration of digital flight control, navigation and propulsion control data, into a digital flight management system for 'flight path optimization'; 2. “Technology” for “aircraft” flight instrument systems integrated solely for VOR, DME, ILS or MLS navigation or approaches.

Technical Note: 'Flight path optimization' is a procedure that minimizes deviations from a four-dimensional (space and time) desired trajectory based on maximizing performance or effectiveness for mission tasks.

Technical Note: For the purposes of 7E004.b.7.a, 'inner-loop' refers to functions of “active flight control systems” that automate airframe stability controls.

Technical Note: For the purposes of 7E004.b.7.b.2, 'abnormal changes in aircraft state' include in-flight structural damage, loss of engine thrust, disabled control surface, or destabilizing shifts in cargo load.

Note: 7E004.b.7.b.3 does not apply to autopilots.

Note: 7E004.b does not apply to “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.

Technical Note: For the purposes of 7E004.c.3, 'variable geometry airfoils' use trailing edge flaps or tabs, or leading edge slats or pivoted nose droop, the position of which can be controlled in flight.

Source: eCFR, version 2026-08-01, retrieved 2026-08-20T04:04:59+00:00.