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Category 7 - _

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Category 7 - _

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    DUAL-USE LIST - CATEGORY 7 NAVIGATION AND AVIONICS ____________________________________________________________________

    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 as follows and specially designed components therefor:

    N.B. For angular or rotational accelerometers, see 7.A.1.b.

     a. Linear accelerometers having any of the following:

     1. Specified to function at linear acceleration levels less than or equal to

    15 g and having any of the following:

     a. A "bias" "stability" of less (better) than 130 micro g with respect

    to a fixed calibration value over a period of one year; or

     b. A "scale factor" "stability" of less (better) than 130 ppm with

    respect to a fixed calibration value over a period of one year;

     2. Specified to function at linear acceleration levels exceeding 15 g and

    having all of the following:

     a. A "bias" "repeatability" of less (better) than 5,000 micro g over a

    period of one year; and

     b. A "scale factor" "repeatability" of less (better) than 2,500 ppm

    over a period of one year; or

     3. Designed for use in inertial navigation or guidance systems and

    specified to function at linear acceleration levels exceeding 100 g;

     b. Angular or rotational accelerometers, specified to function at linear

    acceleration levels exceeding 100 g.

7. A. 2. Gyros or angular rate sensors, having any of the following and specially designed

    components therefor:

    N.B. For angular or rotational accelerometers, see 7.A.1.b.

     a. A "bias" "stability", when measured in a 1 g environment over a period of

    one month, and with respect to a fixed calibration value of less (better) than

    0.5 degree per hour when specified to function at linear acceleration levels

    up to and including 100 g;

     b. An "angle random walk" of less (better) than or equal to 0.0035 degree per

    square root hour; or

    Note 7.A.2.b. does not apply to 'spinning mass gyros'.

    Technical Note

    ‘Spinning mass gyros’ are gyros which use a continually rotating mass to

    sense angular motion.

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7. A. 2. c. A rate range greater than or equal to 500 degrees per second and having any

    of the following:

     1. A "bias" "stability", when measured in a 1 g environment over a period of

    three minutes, and with respect to a fixed calibration value of less (better)

    than 40 degrees per hour; or

     2. An "angle random walk" of less (better) than or equal to 0.2 degree

    per square root hour; or

     d. Specified to function at linear acceleration levels exceeding 100 g.

7. A. 3. Inertial systems and specially designed components, as follows:

     a. Inertial Navigation Systems (INS) (gimballed or strapdown) and inertial

    equipment, designed for "aircraft", land vehicles, vessels (surface or

    underwater) or "spacecraft", for navigation, attitude, guidance or control and

    having any of the following and specially designed components therefor:

     1. Navigation error (free inertial) subsequent to normal alignment of

    0.8 nautical mile per hour (nm/hr) 'Circular Error Probable' ('CEP') or

    less (better); or

     2. Specified to function at linear acceleration levels exceeding 10 g;

     Technical Note

     'Circular Error Probable' ('CEP') - In a circular normal distribution, the

    radius of the circle containing 50% of the individual measurements being

    made, or the radius of the circle within which there is a 50% probability of

    being located.

     b. Hybrid Inertial Navigation Systems embedded with Global Navigation

    Satellite System(s) (GNSS) or with "Data-Based Referenced Navigation"

    ("DBRN") System(s) for navigation, attitude, guidance or control,

    subsequent to normal alignment and having an INS navigation position

    accuracy, after loss of GNSS or "DBRN" for a period of up to 4 minutes, of

    less (better) than 10 meters 'CEP';

     c. Inertial Measurement equipment for heading or True North determination

    and having any of the following and specially designed components

    therefor:

     1. Designed to have heading or True North determination accuracy equal

    to or less (better) than 0.07 deg sec(Lat) (equivalent to 6 arc minutes

    rms at 45 degrees latitude); or

     2. Designed to have a non-operating shock level of 900 g or greater at a

    duration of 1 msec or greater;

     d. Inertial measurement equipment including Inertial Measurement Units

    (IMU) and Inertial Reference Systems (IRS), incorporating accelerometers

    or gyros specified by 7.A.1. or 7.A.2., and specially designed components

    therefor.

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7. A. 3. cont.

    Note 1 The parameters of 7.A.3.a. and 7.A.3.b. are applicable with any of the

    following environmental conditions:

    a. Input random vibration with an overall magnitude of 7.7 g rms in

    the first 0.5 hour and a total test duration of 1.5 hour per axis in

    each of the 3 perpendicular axes, when the random vibration meets

    all of the following: 21. A constant Power Spectral Density (PSD) value of 0.04 g/Hz

    over a frequency interval of 15 to 1,000 Hz; and 22. The PSD attenuates with frequency from 0.04 g/Hz to 20.01 g/Hz over a frequency interval from 1,000 to 2,000 Hz;

    b. An angular rate capability about one or more axes of equal to or

    more than +2.62 rad/s (150 deg/s); or

    c. According to national standards equivalent to a. or b. above.

    Note 2 7.A.3. does not apply to inertial navigation systems which are certified

    for use on "civil aircraft" by civil authorities of a participating state.

    Note 3 7.A.3.c.1. does not apply to theodolite systems incorporating inertial

    equipment specially designed for civil surveying purposes.

    Technical Note

     7.A.3.b. refers to systems in which an INS and other independent navigation

    aids are built into a single unit (embedded) in order to achieve improved

    performance.

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 (GNSS) receiving equipment having any of

    the following and specially designed components therefor:

     N.B. For equipment specially designed for military use, see ML11.

     a. Employing a decryption algorithm specially designed or modified for

    government use to access the ranging code for position and time; or

     b. Employing 'adaptive antenna systems'.

     Note 7.A.5.b. does not apply to GNSS receiving equipment that only

    uses components designed to filter, switch, or combine signals

    from multiple omni-directional antennae that do not implement

    adaptive antenna techniques.

    Technical Note

     For the purposes of 7.A.5.b 'adaptive antenna systems' dynamically

    generate one or more spatial nulls in an antenna array pattern by signal

    processing in the time domain or frequency domain.

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7. A. 6. Airborne altimeters operating at frequencies other than 4.2 to 4.4 GHz inclusive

    and having any of the following:

     a. "Power management"; or

     b. Using phase shift key modulation.

7. A. 7. Not used since 2004

7. A. 8. Underwater sonar navigation systems using doppler velocity or correlation

    velocity logs integrated with a heading source and having a positioning accuracy

    of equal to or less (better) than 3% of distance travelled 'Circular Error Probable'

    ('CEP') and specially designed components therefor.

    Note 7.A.8. does not apply to systems specially designed for installation on

    surface vessels or systems requiring acoustic beacons or buoys to

    provide positioning data.

    N.B. See Category 6.A.1.a. for acoustic systems, and 6.A.1.b. for correlation-

    velocity and Doppler-velocity sonar log equipment.

    See Category 8.A.2. for other marine systems.

7. B. TEST, INSPECTION AND PRODUCTION EQUIPMENT

7. B. 1. Test, calibration or alignment equipment, specially designed for equipment

    specified by 7.A.

    Note 7.B.1. does not apply to test, calibration or alignment equipment for

    'Maintenance Level I’ or 'Maintenance Level II'.

    Technical Notes

     1. ‘Maintenance Level I’

     The 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. ‘Maintenance Level

    II’ does not include the disassembly or repair of specified accelerometers

    or gyro sensors.

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7. B. 2. Equipment specially designed to characterize mirrors for ring "laser" gyros, as

    follows:

     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 by 7.A.

    Note 7.B.3. includes:

    - Gyro tuning test stations;

    - Gyro dynamic balance stations;

    - Gyro run-in/motor test stations;

    - Gyro evacuation and fill stations;

    - Centrifuge fixtures for gyro bearings;

    - Accelerometer axis align stations;

    - Fibre optic gyro coil winding machines.

7. C. MATERIALS - None

7. D. SOFTWARE

7. D. 1. "Software" specially designed or modified for the "development" or

    "production" of equipment specified by 7.A. or 7.B.

7. D. 2. "Source code" for the "use" of any inertial navigation equipment, including

    inertial equipment not specified by 7.A.3. or 7.A.4., or Attitude and Heading

    Reference Systems ('AHRS').

    Note 7.D.2. does not apply to "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 by 7.A.3., 7.A.4. or 7.A.8.;

     b. "Source code" for hybrid integrated systems which improves the

    operational performance or reduces the navigational error of systems to the

    level specified by 7.A.3. or 7.A.8. by continuously combining heading data

    with any of the following:

     1. Doppler radar or sonar velocity data;

     2. Global Navigation Satellite Systems (GNSS) reference data; or

     3. Data from "Data-Based Referenced Navigation" ("DBRN") systems;

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7. D. 3. 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 by 7.E.4.b., 7.E.4.c.1. or 7.E.4.c.2.

7. E. TECHNOLOGY

7. E. 1. "Technology" according to the General Technology Note for the "development" of

    equipment or "software", specified by 7.A., 7.B. or 7.D.

    7. E. 2. "Technology" according to the General Technology Note for the "production" of

    equipment specified by 7.A. or 7.B.

    7. E. 3. "Technology" according to the General Technology Note for the repair,

    refurbishing or overhaul of equipment specified by 7.A.1. to 7.A.4.

    Note 7.E.3. does not apply to 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 any of the following:

     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 by 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"; 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;

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    DUAL-USE LIST - CATEGORY 7 NAVIGATION AND AVIONICS ____________________________________________________________________

7. E. 4. 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 apply to "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;

     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 apply to:

    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

    Systems ("FADEC Systems"), see 9.E.3.h.

7. E. 4. 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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