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CATEGORY 7 — NAVIGATION AND AERO-ELECTRONICS
7 A - Equipment, assemblies and components
NB: |
For automatic pilots for submersible vehicles, see category 8. For radars, see category 6. |
7A001 - Accelerometers, as follows, and specially designed components therefor:
NB: |
For angular or rotating accelerometers, see 7A001.b. |
a. | linear accelerometers having any of the following characteristics: 1. | specified to operate at linear acceleration levels less than or equal to 15 g and having any of the following characteristics: a. | “bias” “stability” less than (better) than 130 micro g relative to a fixed calibration value over a period of one year; Or |
b. | “scaling factor” “stability” less than (better) than 130 ppm relative to a fixed calibration value over a period of one year; |
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2. | specified to operate at linear acceleration levels greater than 15 g but less than or equal to 100 g, and having all of the following characteristics: a. | “Repeatability” of “bias” less than (better) than 1,250 micro g over a period of one year; And |
b. | “repeatability” of “scale factor” less than (better) than 1250 ppm over a period of one year; Or |
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3. | designed for use in inertial navigation systems or guidance systems and to operate at acceleration levels above 100 g; |
Note: |
Paragraphs 7A001.a.1. and 7A001.a.2. do not cover accelerometers used only to measure vibrations or shocks. |
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b. | Angular or rotating accelerometers specified to operate at acceleration levels greater than 100 g. |
7A002 - Gyroscopes or angular velocity sensors having any of the following characteristics and specially designed components therefor:
NB: |
For angular or rotating accelerometers, see 7A001.b. |
a. | specified to operate at linear acceleration levels less than or equal to 100 g and having any of the following characteristics: 1. | measuring range less than 500 degrees/second and having one of the following characteristics: a. | “bias” “stability” of less (better) than 0.5 degrees/hour, measured in a 1 g environment over a period of one month, and relative to a fixed calibration value; Or |
b. | “random angular path” less than (better than) or equal to 0.0035 degrees per square root of hour; Or Note: |
Paragraph 7A002.a.1.b. does not cover “gyroscopes having a rotating mass”. |
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2. | measuring range greater than or equal to 500 degrees/second and having one of the following characteristics: a. | “bias” “stability” measured in a 1g environment over a three-minute period, and relative to a fixed calibration value, of less (better) than 4 degrees/hour; Or |
b. | “random angular path” less (better than) or equal to 0.1 degree per square root of hour; Or Note: |
Paragraph 7A002.a.2.b. does not cover “gyroscopes having a rotating mass”. |
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b. | specified to operate at linear acceleration levels greater than 100g. |
7A003 - 'Inertial navigation equipment or systems' (INS) having any of the following characteristics:
Note 1: |
'Inertial measuring equipment or systems' incorporate accelerometers or gyroscopes to measure changes in velocity and orientation in order to determine or maintain a heading or position without the need for an external reference after alignment. 'Inertial measuring equipment or systems' includes: — | heading and attitude reference systems (AHRS); |
— | inertial measurement units (IMU); |
— | inertial navigation systems (INS); |
— | inertial reference systems (IRS); |
— | inertial navigation units (IRU); |
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Note 2: |
7A003 does not control 'inertia measuring equipment or systems' which are approved for use on 'civil aircraft' by the civil aviation authorities of one or more EU Member States or participating States to Wassenaar's arrangement. |
Technical note: 'Positioning aid references' indicate position independently, and include: a. | global navigation satellite systems (GNSS); |
b. | “database referenced navigation” (“DBRN”) systems. |
a. | designed for "aircraft", land vehicles or ships, indicating position without the use of "positioning aid references", and having any of the following "accuracies" after normal alignment: 1. | nominal “circular error probable” (“CEP”) equal to or less (better) than 0.8 nautical miles per hour (min/h); |
2. | “ECP” equal to or less (better) than 0.5% of the distance traveled; Or |
3. | total drift with “ECP” equal to or less (better) than 1 nautical mile in a 24-hour period; |
Technical note: The performance parameters specified in 7A003.a.1., 7A003.a.2. and 7A003.a.3. generally apply to 'inertia measuring equipment or systems' designed for 'aircraft', vehicles and ships, respectively. These parameters are linked to the use of specialized reference aids other than for positioning (eg altimeter, odometer, log). Therefore, the performance values shown cannot be directly converted between these parameters. Equipment designed for multiple platforms is evaluated against each applicable entry in 7A003.a.1., 7A003.a.2. or 7A003.a.3. |
b. | designed for 'aircraft', land vehicles or vessels, with an integrated 'positioning aid reference' and indicating position after all 'positioning aid references' have been lost for a period of up to 4 minutes, and having an “accuracy” less than (better than) 10 meters of “ECP”; Technical note: Paragraph 7A003.b. covers systems in which 'inertia measuring equipment or systems' and other independent 'positioning aid references' are integrated into a single element (i.e. on-board) for the purpose of improving performance . |
c. | designed for "aircraft", land vehicles or ships, for determining heading or true north and having any of the following characteristics: 1. | a maximum operating angular velocity less than (lower than) 500 deg/s and a heading 'accuracy' without the use of 'positioning aid references' equal to or less (better than) 0.07 deg/s s (lat.) (equivalent to 6 arc minutes RMS at a latitude of 45 degrees); Or |
2. | a maximum operating angular velocity equal to or greater than (greater than) 500 deg/s and a heading 'accuracy' without the use of 'positioning aid references' equal to or less (better than) 0.2 deg/s (lat.) (equivalent to 17 arc minutes RMS at a latitude of 45 degrees); |
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d. | providing measurements of acceleration or angular velocity, in more than one dimension, and having any of the following characteristics: 1. | performance specified in paragraph 7A001 or 7A002 along any axis, without the use of any aiding reference; gold |
2. | being "space-qualified" and providing angular velocity measurements with a "random angular course" along any axis less than (better than) or equal to 0.1 degrees per square root of hour. Note: |
Paragraph 7A003.d.2. does not control 'inertia measuring equipment or systems' having 'gyroscopes having a rotating mass' as the only type of gyroscope. |
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7A004 - 'Stellar trackers' and their components, as follows :
a. | 'star trackers' with azimuth 'accuracy' equal to or less (better) than 20 arcseconds throughout the expected life of the equipment; |
b. | components specially designed for equipment specified in 7A004.a., as follows: 1. | optical heads or acoustic screens; |
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Technical note: 'Star trackers' are also known as star attitude sensors or gyro-astro-compasses.
7A005 - Global navigation satellite systems (GNSS) receiving equipment having any of the following characteristics and their specially designed components:
NB: |
For equipment specially designed for military use, see the list of war materials. |
a. | employing a decryption algorithm specially designed or modified for government use to access the code for location and time; Or |
b. | employing 'adaptive antenna systems'. Note: |
7A005.b does not control GNSS receiving equipment that uses only components intended to filter, switch, or combine signals from multiple omnidirectional antennas that do not implement adaptive antenna techniques. |
Technical note: For the purposes of 7A005.b, 'adaptive antenna systems' dynamically generate one or more zeros of radiation in an antenna array by signal processing in the time domain or frequency domain. |
7A006 - On-board altimeters operating on frequencies not between 4.2 and 4.4 GHz and having one of the following characteristics:
a. | “radiated power control”; Or |
b. | using discrete phase modulation. |
7A008 - Underwater navigation sonar systems using Doppler or correlation logs incorporating a heading source and having a positioning “accuracy” equal to or less (better) than 3% of the distance traveled “Probable circular error” (“Circular error probable” (“Circular error probable”) ECP") and their specially designed components.
Note: |
Paragraph 7A008 does not control systems specially designed for installation on surface ships or systems requiring acoustic beacons or buoys to transmit positioning data to them. |
NB: |
See 6A001.a. for acoustic systems and 6A001.b. for correlation and Doppler sonar logs. See paragraph 8A002 for other marine systems. |
7A101 - Linear accelerometers, other than those specified in 7A001, designed for inertial navigation systems or for guidance systems of all types, usable in 'missiles', having all of the following characteristics, and specially designed components therefor:
a. | “bias” “repeatability” less than (better) than 1250 micro g; And |
b. | “Scale factor” “repeatability” less than (better) than 1250 ppm; |
Note: |
Paragraph 7A101 does not control accelerometers specially designed and developed as a MWD (measurement while drilling technique) sensor for use in drilling operations. |
Technical notes: 1. | In paragraph 7A101, the term 'missile' means complete rocket systems and unmanned aerial vehicle systems with a range of at least 300 km. |
2. | In paragraph 7A101, the measurement of "bias" and "scale factor" refers to a standard deviation of one sigma from a fixed calibration over a period of one year. |
7A102 - Gyroscopes of any type, other than those specified in 7A002, usable in "missiles", having a 'precession rate' 'stability' of less than 0.5° (1 sigma or RMS) per hour in an environment of 1 g, and their specially designed components.
Technical notes: 1. |
In paragraph 7A102, the term 'missile' means complete rocket systems and unmanned aerial vehicle systems with a range of at least 300 km. |
2. |
In paragraph 7A102, the term 'stability' means the measure of the ability of a particular mechanism or coefficient of performance not to vary when continuously exposed to fixed operating conditions (IEEE Standard 528- 2001, paragraph 2 247). |
7A103 - Instrumentation, navigation and cueing equipment and systems, other than those specified in 7A003, as follows, and specially designed components therefor:
a. | inertial or other equipment using accelerometers or gyroscopes as follows, and systems comprising such equipment: 1. | accelerometers specified in 7A001.a.3. and 7A001.b. or 7A101 or gyroscopes specified in 7A002 or 7A102; Or |
2. | accelerometers specified in 7A001.a.1. or 7A001.a.2., designed for use in inertial navigation systems or in guidance systems of all types and for use in 'missiles'; |
Note: |
Paragraph 7A103.a.2. does not control equipment containing accelerometers specified in 7A001.a.1. or 7A001.a.2. where these are specially designed and developed as MWD (measurement while drilling) sensors for use in drilling operations. |
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b. | integrated flight instrument systems, including gyroscopic stabilizers or autopilots, designed or modified for use in 'missiles'; |
c. | 'integrated navigation systems' designed or modified for 'missiles' and capable of providing navigation accuracy of 200 m probable circular error or less; Technical note: An 'integrated navigation system' normally consists of the following: 1. | an inertial measurement device (e.g., a heading and altitude reference system, an inertial reference unit or an inertial navigation system); |
2. | one or more external sensors used to correct position and/or speed, either periodically or continuously throughout the flight (e.g. satellite navigation receiver, radar altimeter and/or Doppler radar); And |
3. | integration hardware and software. |
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d. | three-axis magnetic heading sensors, designed or modified for integration into flight control and navigation systems other than those specified in 6A006, and having all of the following characteristics and specially designed components therefor: 1. | internal tilt compensation on the pitch (±90 degrees) and roll (±180 degrees) axes; |
2. | capable of providing azimuth accuracy greater than (better) than 0.5 degrees RMS at a latitude of ±80 degrees, relative to the local magnetic field. |
Note: |
Flight control and navigation systems specified in 7A103.d. include gyroscopic stabilizers, autopilots and inertial navigation systems. |
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Technical note: In paragraph 7A103, the term 'missile' means complete rocket systems and unmanned aerial vehicle systems with a range of at least 300 km.
7A104 - Gyro-astro-compass and other devices, other than those specified in 7A004, for determining the position or orientation by automatic tracking of celestial bodies or satellites, and specially designed components therefor.
7A105 - Receiving equipment for global navigation satellite systems (GNSS; e.g. GPS, GLONASS or Galileo) other than those specified in 7A005, and having any of the following, and specially designed components therefor:
a. | designed or modified for use in space launch vehicles specified in 9A004, sounding rockets specified in 9A104, or unmanned aerial vehicles specified in 9A012 or 9A112.a; Or |
b. | designed or modified for on-board aeronautical use and having one of the following characteristics: 1. | capable of providing navigation information at speeds above 600 m/s; |
2. | using decryption, designed or modified for military or state services, to gain access to secure GNSS signals/data; Or |
3. | specially designed to use anti-jam features (e.g. self-adaptive antenna or electronically pointing antenna) to operate in an active or passive countermeasures environment. |
Note: |
Paragraphs 7A105.b.2. and 7A105.b.3. are not applicable to commercial, civil or 'safety of life' (e.g. data integrity, flight safety) GNSS services. |
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7A106 - Altimeters, other than those specified in 7A006, of the radar or laser-radar type, designed or modified for use in launch vehicles and space vehicles specified in 9A004 or in sounding rockets specified in 9A104.
7A115 - Passive sensors for determining the bearing of specific electromagnetic sources (direction finding equipment) or terrain features, designed or modified for use in launchers and space vehicles specified in 9A004 or in sounding rockets specified in 9A104.
Note: |
Paragraph 7A115 includes sensors used in the following equipment: a. | equipment for producing contour maps; |
b. | imaging sensor equipment (active and passive); |
c. | passive interferometer equipment. |
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7A116 - Flight control systems and servo valves, as follows, designed or modified for use in launch vehicles and space vehicles specified in 9A004, in sounding rockets specified in 9A104, or in "missiles."
a. | pneumatic, hydraulic, mechanical, electro-optical or electromechanical flight control systems (including fly-by-wire flight control systems and fiber optic flight control systems); |
b. | attitude control systems; |
c. | Flight control servovalves designed or modified for systems specified in 7A116.a. or 7A116.b., and designed or modified to operate in a vibration environment of more than 10 g RMS between 20 Hz and 2 kHz. |
7A117 - “Guidance subassemblies”, usable in “missiles”, giving the system an accuracy equal to or less than 3.33% of the distance (for example, a “probable circular error” of 10 km or less at a distance of 300 km).
7 B - Testing, inspection and production equipment
7B001 - Testing, calibration or alignment equipment specially designed for equipment covered by subcategory 7A .
Note: |
7B001 does not control 'Maintenance Level I' or 'Maintenance Level II' testing, calibration or alignment equipment. |
Technical notes: 1. 'Level I maintenance' The failure of an inertial navigation unit is detected on the “aircraft” by the indications of the control and display unit (CDU) or by the status message of the corresponding subsystem. By following the manufacturer's user manual, the cause of the failure can be located at the faulty track replaceable unit (URP). The operator then removes this unit (URP) and replaces it with spare equipment. 2. 'Level II maintenance' The faulty track replaceable unit (URP) is sent to the maintenance workshop (that of the manufacturer or that of the operator responsible for level II maintenance). In the workshop, the faulty equipment is tested by various suitable means to locate the faulty workshop replaceable unit (FRU) module responsible for the fault. This module is removed and replaced with a working replacement module. The faulty module [or possibly the complete track replaceable unit (URP)] is then sent to the manufacturer. 'Level II maintenance' does not include the dismantling or repair of the accelerometers or gyroscopes subject to control.
7B002 - Equipment specially designed for the qualification of mirrors for ring gyro-lasers, as follows:
a. | scatterometers having a measurement “accuracy” equal to or less (better) than 10 ppm; |
b. | profilometers having a measurement “accuracy” equal to or less (better) than 0.5 nm (5 angstroms). |
7B003 - Equipment specially designed for the production of equipment covered in subcategory 7A.
Note: |
Paragraph 7B003 includes:
— | test stations for developing gyroscopes; |
— | dynamic gyroscope balancing stations; |
— | test stations for running in gyroscope drive motors; |
— | gyroscope evacuation and filling stations; |
— | centrifugation devices for gyroscope bearings; |
— | accelerometer axis alignment stations; |
— | fiber optic gyroscope winders. |
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7B102 - Reflectometers specially designed for the qualification of mirrors for gyro-lasers, having a measurement accuracy equal to or less (better) than 50 ppm.
7B103 – “Production support equipment” and “production equipment” as follows:
a. | “production support equipment” specially designed for equipment specified in paragraph 7A117; |
b. | "production equipment", and other testing, calibration and alignment equipment, other than that specified in paragraphs 7B001 to 7B003, designed or modified for use with equipment specified in subcategory 7A. |
7C - Materials
Nothing.
7D - Software
7D001 - “Software” specially designed or modified for the “development” or “production” of equipment specified in subcategories 7A or 7B.
7D002 - “Source code” for the operation or maintenance of any inertial navigation equipment, including inertial equipment not specified in 7A003 or 7A004, or heading and attitude reference systems ('AHRS') .
Note: |
7D002 does not control "source code" for the "use" of gimbal heading and attitude reference systems. |
Technical note: Heading and attitude reference systems ('AHRS') generally differ from inertial navigation systems because they provide heading and attitude information and do not usually provide acceleration information. , speed and position associated with inertial navigation systems.
7D003 - Other “Software”, as follows:
a. | “software” specially designed or modified to improve operational performance or reduce navigation error of systems to the levels defined in 7A003, 7A004 or 7A008; |
b. | “Source codes” for hybrid integrated systems improving operational performance or reducing navigation error of systems to the level defined in 7A003 or 7A008, by continuously combining heading data with one or more of the following data:
1. | speed data from radar or Doppler sonar; |
2. | global positioning satellite (GNSS) references; Or |
3. | data from “database referenced navigation” (“DBRN”) systems; |
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e. | Computer-aided design (CAD) “software” specially designed for the “development” of “active flight control systems”, multi-axis electric or fiber-optic flight controls or “anti-torque control systems”. circulation or circulation-controlled steering control systems” for helicopters, the “technology” of which is specified in 7E004.b., 7E004.c.1. or 7E004.c.2. |
7D004 - “Source codes” incorporating “development” “technology” specified in 7E004.a.1. at 7E004.a.6. or 7E004.b., for one of the following systems:
a. | digital flight management systems for “total flight control”; |
b. | integrated propulsion and flight control systems; |
c. | “electric flight control systems” or “fiber optic flight control systems”; |
d. | fault-tolerant or self-reconfiguring “active flight control systems”; |
f. | aerodynamic power plants using static surface measurements; Or |
g. | three-dimensional visuals. |
Note: |
Paragraph 7D004. does not cover "source code" related to traditional computing elements and functionalities (e.g., input signal acquisition, output signal transmission, loading of computer programs and data, embedded testing, task scheduling mechanisms) which do not offer any specific function of a flight control system. |
7D005 – “Software” specially designed to decipher global navigation satellite systems (GNSS) code designed for government use.
7D101 - “Software” specially designed or modified for the “use” of equipment specified in 7A001 to 7A006, 7A101 to 7A106 and 7A115, 7A116.a. and 7A116.b., as well as paragraphs 7B001, 7B002, 7B003, 7B102 or 7B103.
7D102 – Integration “Software” as follows:
a. | Integration “software” for equipment specified in 7A103.b.; |
b. | Integration “software” specially designed for equipment specified in 7A003 or 7A103.a.; |
c. | Integration “software” designed or modified for equipment specified in 7A103.c. |
Note: |
A common form of integration "software" uses Kalman filtering. |
7D103 - “Software” specially designed for the modeling or simulation of “guidance subassemblies” specified in 7A117 or for the design of their integration with launchers and space vehicles specified in 9A004 or sounding rockets specified in 9A104 .
Note: |
“Software” specified in paragraph 7D103 remains under control when combined with specially designed hardware specified in paragraph 4A102. |
7D104 - “Software” specially designed or modified for the operation or maintenance of “guidance subassemblies” specified in 7A117.
Note: |
Paragraph 7D104 includes "software" specially designed or modified to increase the performance of "guidance subassemblies" so that they meet or exceed the accuracy specified in paragraph 7A117. |
7E - Technology
7E001 - “Technology”, within the meaning of the General Technology Note, for the “development” of equipment or “software” specified in subcategories 7A, 7B, and paragraphs 7D001, 7D002, 7D003, 7D005, and 7D101 to 7D103.
Note: |
7E001 only includes key management “technology” exclusively intended for equipment specified in 7A005.a. |
7E002 - “Technology”, within the meaning of the general technology note, for the “production” of equipment covered in subcategories 7 A or 7 B.
7E003 - “Technology”, within the meaning of the General Technology Note, for the repair, overhaul or renovation of equipment specified in paragraphs 7A001 to 7A004.
Note: |
7E003 does not control maintenance "technology" directly related to the calibration, removal and replacement of damaged or inoperable Line Replaceable Units (RPUs) and Shop Replaceable Units (AURs) of " civil aircraft", as described by 'level I maintenance' or 'level II maintenance'. |
NB: |
See technical notes in paragraph 7B001. |
7E004 - Other “technologies”, as follows:
a. | “technology” “necessary” for the “development” or “production” of any of the following:
2. | aerodynamic power plants using exclusively static skin grip measurements, i.e. which eliminate the need for conventional aerodynamic sensors; |
3. | three-dimensional visuals for “aircraft”; |
5. | electric actuators (namely, electromechanical, electrohydrostatic and integrated actuator assemblies) specially designed for “primary flight control”; |
6. | “optical flight control sensor array” specially designed for the implementation of “active flight control systems”; Or |
7. | “database-referenced navigation” systems designed to navigate underwater using sonar or gravity databases providing positioning “accuracy” equal to or less (better) than 0.4 miles nautical; |
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b. | “development” “technology”, as follows, for “active flight control systems” (including “fly-by-wire flight control systems” or “fiber optic flight control systems”):
1. | photonic “technology” for sensing the status of “aircraft” or flight control components, transferring flight control data, or controlling actuator movements, “required” for “active control systems” flight” which are “fiber optic flight control systems”; |
3. | real-time algorithms for analyzing component sensing information to prevent and preemptively mitigate impending degradation and failure of components of an “active flight control system”;
Note: |
Paragraph 7E004.b.3. does not target algorithms intended for offline maintenance. |
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4. | real-time algorithms to identify component failures and reconfigure force and moment controls to mitigate “active flight control system” degradation and failures;
Note: |
Paragraph 7E004.b.4. does not target algorithms intended to eliminate the effects of failures by comparing redundant data sources, nor to pre-programmed offline responses to anticipated failures. |
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5. | integration of digital flight control, navigation control and propulsion data into a digital flight management system for “total flight control”;
Note: |
Paragraph 7E004.b.5. do not aim:
a. | the “development” “technology” for the integration of digital flight control, navigation control and propulsion data into a digital flight management system for “flight path optimization”; |
b. | “technology” for the “development” of aeronautical flight instrument systems integrated exclusively for VOR, DME, ILS or MLS navigation or approaches. |
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7. | “technology” “necessary” to establish operational requirements for “fly-by-wire flight control systems” having all of the following characteristics:
a. | internal loop aircraft airframe stability controls requiring loop closure frequencies equal to or greater than 40 Hz; And Technical note: 'Inner loop' refers to functions of "active flight control systems" that automate the stability controls of the aircraft airframe. |
b. | having one of the following characteristics:
1. | corrects, at any point in the planned flight envelope, an aerodynamically unstable airframe which would no longer respond to commands if a correction does not occur within 0.5 seconds; |
2. | couples controls on two or more axes, while compensating for 'abnormal changes in aircraft state'. Technical note: By 'abnormal changes in the state of the aircraft' we mean in particular structural damage in flight, loss of engine thrust, rudder failure or load movements leading to destabilization. |
3. | performs the functions specified in 7E004.b.5.; Or
Note: |
Paragraph 7E004.b.7.b.3. does not target autopilots. |
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4. | allows the “aircraft” to achieve stable and controlled flight, apart from takeoff and landing, with an angle of attack greater than 18 degrees, a slip on the wing of 15 degrees, a pitch angle or yaw of 15 degrees/second or a roll angle of 90 degrees/second; |
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8. | “technology” “necessary” to establish operational requirements for “fly-by-wire flight control systems” in order to fulfill all of the following conditions:
a. | no loss of control of the “aircraft” following two consecutive “fly-by-wire flight control system” anomalies; And |
b. | probability of loss of control of the “aircraft” less than (better) than 1 × 10 – 9 failure per flight hour; |
Note: |
Paragraph 7E004.b. does not cover technology related to traditional computing elements and functionalities (e.g., input signal acquisition, output signal transmission, loading of computer programs and data, embedded testing, task scheduling mechanisms) that does not offer no specific function of a flight control system. |
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c. | “technology” for the “development” of helicopter components, as follows:
1. | multi-axis electric or fiber optic flight controls which combine in a single control element two or more of the following functions:
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2. | “traffic-controlled anti-torque systems or traffic-controlled steering control systems”; |
3. | Helicopter rotor blades having “variable geometry aerodynamic surfaces” for systems using individual blade control. |
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7E101 - "Technology", within the meaning of the General Technology Note, for the "use" of equipment specified in paragraphs 7A001 to 7A006, 7A101 to 7A106, 7A115 to 7A117, 7B001, 7B002, 7B003, 7B102, 7B103, and 7D101 to 7D103.
7E102 - “Technology” for the protection of aero-electronic and electrical subsystems against electromagnetic pulse (EMI) and electromagnetic disturbance hazards from external sources, as follows:
a. | protection system design “technology”; |
b. | “technology” for designing the layout of radiation-resistant electrical circuits and subsystems; |
c. | design “technology” for determining radiation enhancement criteria for technologies specified in 7A102.a. and 7A102.b. |
7E104 - “Technology” for the integration of flight control, guidance and propulsion data into a flight management system for optimizing the trajectory of a rocket system.
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