The Wassenaar Arrangement - Dual-Use and Munitions Lists - July 1996
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7.A. SYSTEMS, EQUIPMENT AND COMPONENTS
N.B. For automatic pilots for underwater vehicles, see Category 8. For radar, see Category 6.
7.A.1. Accelerometers designed for use in inertial navigation or guidance systems and having any of the following characteristics, and specially designed components therefor:
a. A "bias" "stability" of less (better) than 130 micro g with respect to a fixed calibration value over a period of one year;b. A "scale factor" "stability" of less (better) than 130 ppm with respect to a fixed calibration value over a period of one year; or
c. Specified to function at linear acceleration levels exceeding 100 g.
7.A.2. Gyros having any of the following characteristics, and specially designed components therefor:
a. A "drift rate" "stability", when measured in a 1 g environment over a period of three months and with respect to a fixed calibration value, of:1. Less (better) than 0.1° per hour when specified to function at linear acceleration levels below 10 g; or2. Less (better) than 0.5° per hour when specified to function at linear acceleration levels from 10 g to 100 g inclusive; or
b. Specified to function at linear acceleration levels exceeding 100 g.
7.A.3. Inertial navigation systems (gimballed or strapdown) and inertial equipment designed for "aircraft", land vehicle or "spacecraft" for attitude, guidance or control having any of the following characteristics, and specially designed components therefor:
a. Navigation error (free inertial) subsequent to normal alignment of 0.8 nautical mile per hour (50% Circular Error Probable (CEP)) or less (better); orNote 1 The parameters of 7.A.3.a. are applicable with any of the following environmental conditions:1. Input random vibration with an overall magnitude of 7.7 g rms in the first half hour and a total test duration of one and one half hour per axis in each of the three perpendicular axes, when the random vibration meets the following:
a. A constant power spectral density (PSD) value of 0.04 g2/Hz over a frequency interval of 15 to 1,000 Hz; andb. The PSD attenuates with frequency from 0.04 g2/Hz to 0.01 g2/Hz over a frequency interval from 1,000 to 2,000 Hz; or
2. A roll and yaw rate of equal to or more than +2.62 radian/s (150 deg/s); or
3. According to national standards equivalent to 1. or 2. above.
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b. Specified to function at linear acceleration levels exceeding 10 g.Note 2 7.A.3 does not control inertial navigation systems which are certified for use on "civil aircraft" by civil authorities of a "participating state".
7.A.4. Gyro-astro compasses, and other devices which derive position or orientation by means of automatically tracking celestial bodies or satellites, with an azimuth accuracy of equal to or less (better) than 5 seconds of arc.
7.A.5. Global navigation satellite systems (i.e. GPS or GLONASS) receiving equipment having any of the following characteristics, and specially designed components therefor:
a. Employing decryption; orb. A null-steerable antenna.
7.A.6. Airborne altimeters operating at frequencies other than 4.2 to 4.4 GHz inclusive, having any of the following characteristics:
a. "Power management"; orb. Using phase shift key modulation.
7.A.7. Direction finding equipment operating at frequencies above 30 MHz and having all of the following characteristics, and specially designed components therefor:
a. "Instantaneous bandwidth" of 1 MHz or more;b. Parallel processing of more than 100 frequency channels; and
c. Processing rate of more than 1,000 direction finding results per second and per frequency channel.
(For inertial navigation equipment for ships and submersibles, see Item 9.e on the Munitions List.)*
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* France and the Russian Federation view this list as reference drawn up to help in the selection of dual-use goods which could contribute to the indigenous development, production or enhancement of conventional munitions capabilities.
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7.B. TEST, INSPECTION AND PRODUCTION EQUIPMENT
7.B.1. Test, calibration or alignment equipment specially designed for equipment specified in 7.A.
Note 7.B.1. does not control test, calibration or alignment equipment for Maintenance Level I or Maintenance Level II.Technical Notes
1. Maintenance Level IThe failure of an inertial navigation unit is detected on the aircraft by indications from the control and display unit (CDU) or by the status message from the corresponding sub-system. By following the manufacturer's manual, the cause of the failure may be localised at the level of the malfunctioning line replaceable unit (LRU). The operator then removes the LRU and replaces it with a spare.
2. Maintenance Level II
The defective LRU is sent to the maintenance workshop (the manufacturer's or that of the operator responsible for level II maintenance). At the maintenance workshop, the malfunctioning LRU is tested by various appropriate means to verify and localise the defective shop replaceable assembly (SRA) module responsible for the failure. This SRA is removed and replaced by an operative spare. The defective SRA (or possibly the complete LRU) is then shipped to the manufacturer.
N.B. Maintenance Level II does not include the removal of controlled accelerometers or gyro sensors from the SRA.
7.B.2. Equipment, as follows, specially designed to characterize mirrors for ring "laser" gyros:
a. Scatterometers having a measurement accuracy of 10 ppm or less (better);b. Profilometers having a measurement accuracy of 0.5 nm (5 angstrom) or less (better).
7.B.3. Equipment specially designed for the "production" of equipment specified in 7.A.
Note 7.B.3. includes:a. Gyro tuning test stations;b. Gyro dynamic balance stations;
c. Gyro run-in/motor test stations;
d. Gyro evacuation and fill stations;
e. Centrifuge fixtures for gyro bearings;
f. Accelerometer axis align stations.
7.C. MATERIALS - None.
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7.D. SOFTWARE
7.D.1. "Software" specially designed or modified for the "development" or "production" of equipment specified in 7.A. or 7.B.
7.D.2. "Source code" for the "use" of any inertial navigation equipment or Attitude and Heading Reference Systems (AHRS) including inertial equipment not controlled by 7.A.3. or 7.A.4.
Note 7.D.2. does not control "source code" for the "use" of gimballed AHRS.Technical Note
AHRS generally differ from inertial navigation systems (INS) in that an AHRS provides attitude and heading information and normally does not provide the acceleration, velocity and position information associated with an INS.
7.D.3. Other "software", as follows:
a. "Software" specially designed or modified to improve the operational performance or reduce the navigational error of systems to the levels specified in 7.A.3. or 7.A.4.;b. "Source code" for hybrid integrated systems which improves the operational performance or reduces the navigational error of systems to the level specified in 7.A.3. by continuously combining inertial data with any of the following navigation data:
1. Doppler radar velocity;2. Global navigation satellite systems (i.e., GPS or GLONASS) reference data; or
3. Terrain data from data bases;
c. "Source code" for integrated avionics or mission systems which combine sensor data and employ "expert systems";
d. "Source code" for the "development" of any of the following:
1. Digital flight management systems for "total control of flight";2. Integrated propulsion and flight control systems;
3. Fly-by-wire or fly-by-light control systems;
4. Fault-tolerant or self-reconfiguring "active flight control systems";
5. Airborne automatic direction finding equipment;
6. Air data systems based on surface static data; or
7. Raster-type head-up displays or three dimensional displays;
e. Computer-aided-design (CAD) "software" specially designed for the "development" of "active flight control systems", helicopter multi-axis fly-by-wire or fly-by-light controllers or helicopter "circulation controlled anti-torque or circulation-controlled direction control systems" whose "technology" is specified in 7.E.4.b., 7.E.4.c.1. or 7.E.4.c.2.
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7.E. TECHNOLOGY
7.E.1. "Technology" according to the General Technology Note for the "development" of equipment or "software" specified in 7.A., 7.B. or 7.D.
7.E.2. "Technology" according to the General Technology Note for the "production" of equipment specified in 7.A. or 7.B.
7.E.3. "Technology" according to the General Technology Note for the repair, refurbishing or overhaul of equipment specified in 7.A.1. to 7.A.4.
Note 7.E.3. does not control maintenance "technology" directly associated with calibration, removal or replacement of damaged or unserviceable LRUs and SRAs of a "civil aircraft" as described in Maintenance Level I or Maintenance Level II.N.B. See Technical Notes to 7.B.1.
7.E.4. Other "technology", as follows:
a. "Technology" for the "development" or "production" of:1. Airborne automatic direction finding equipment operating at frequencies exceeding 5 MHz;2. Air data systems based on surface static data only, i.e., which dispense with conventional air data probes;
3. Raster-type head-up displays or three dimensional displays for "aircraft";
4. Inertial navigation systems or gyro-astro compasses containing accelerometers or gyros specified in 7.A.1. or 7.A.2.;
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";
b. "Development" "technology", as follows, for "active flight control systems" (including fly-by-wire or fly-by-light):
1. Configuration design for interconnecting multiple microelectronic processing elements (on-board computers) to achieve "real time processing" for control law implementation;2. Control law compensation for sensor location or dynamic airframe loads, i.e., compensation for sensor vibration environment or for variation of sensor location from the centre of gravity;
3. Electronic management of data redundancy or systems redundancy for fault detection, fault tolerance, fault isolation or reconfiguration;
Note 7.E.4.b.3. does not control" technology" for the design of physical redundancy.4. Flight controls which permit inflight reconfiguration of force and moment controls for real time autonomous air vehicle control;
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5. Integration of digital flight control, navigation and propulsion control data into a digital flight management system for "total control of flight";Note 7.E.4.b.5. does not control:1. "Development" "technology" for integration of digital flight control, navigation and propulsion control data into a digital flight management system for "flight path optimisation";2. "Development" "technology" for "aircraft" flight instrument systems integrated solely for VOR, DME, ILS or MLS navigation or approaches.
6. Full authority digital flight control or multisensor mission management systems employing "expert systems";
N.B.: For "technology" for Full Authority Digital Engine Control ("FADEC"), see 9.E.3.a.9.
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.
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