CN code 9014 20 80 Other

TARIC codes (10 digits): 1

Origin, preferential duty and next steps ›

Examples from the EU database of Binding Tariff Information (BTI). A ruling binds only its holder and many have expired — read them as guidance, not as a decision for your product.

• A CONTROL DISPLAY UNIT (CDU) THAT PROVIDES AN INTERFACE TO THE FLIGHT MANAGEMENT COMPUTER SYSTEM (FMCS) WHICH HOLDS THE NAVIGATION DATABASE. THE FILGHT CREW USE THE CDU TO ENTER ROUTE AND PERFORMANCE DATA FOR THE FLIGHT. IT HAS THE ADDITIONAL CAPABILITY TO FUNCTION AS AN INDEPENDENT SOURCE OF NAVIGATION. IN THIS MODE THE CDU PROVIDES LATERAL NAVIGATION FROM THE FMC. THIS ALLOWS THE CREW TO…

  9014 20 80 · GB 2017 · GB503556073

• A VERTICAL GYROSCOPE THAT IS AN ELECTRICALLY DRIVEN GYRO THAT SPINS ABOUT A VERTICAL AXIS. IT SUPPLIES THE REFERENCE FOR THE AUTOMATIC FLIGHT CONTROL AND FLIGHT INSTRUMENTS OF AN AIRCRAFT ABOUT THE ROLL (AILERON) AND PITCH (ELEVATOR) AXIS. THE ELECTRICALLY DRIVEN GYRO HAS FULL FREEDOM IN ROLL. IT HAS -85 TO +85 DEGREES FREEDOM OF PITCH. THERE IS AN ERECTION SYSTEM TO KEEP THE ROTOR SPIN AXIS…

  9014 20 80 · GB 2016 · GB502823183

• A PRIMARY FLIGHT DISPLAY THAT DISPLAYS AIRSPEED, ALTITUDE AND INFORMATION TO THE PILOT ON AN AIRCRAFT. THE DISPLAY UTILIZES FIVE PUSH BUTTONS AND TWO SCROLL KNOBS FOR CONTROL OF THE UNIT. THERE IS NO ON/OFF BUTTON AND POWER IS SUPPLIED THROUGH THE AIRCRAFTS DC BUSSING SYSTEM. THE SYSTEM INCLUDES THREE ACCELEROMETERS, THREE RATE SENSORS AND A PILOT/STATIC SYSTEM.

  9014 20 80 · GB 2016 · GB502833277

• AN AIRCRAFT DISPLAY UNIT, USED TO SUPPLY FORMATS FOR FLIGHT, NAVIGATION AND ENGINE INFORMATION. IT IS A FULL COLOUR FLAT-PANEL DISPLAY LOCATED IN THE AIRCRAFT COCKPIT.. THE UNIT COMPRISES OF A FRONT ELECTRONIC ASSEMBLY AND A REAR ELECTRONIC ASSEMBLY AND IS RACK MOUNTED. THREE CONNECTORS ON THE REAR ELECTRONIC ASSEMBLY MATE TO CONNECTORS IN THE RACK. THE FUNCTION OF THE REAR ELECTRONIC ASSEMBLY…

  9014 20 80 · GB 2016 · GB502796053

• PANEL CONTROL ASSEMBLY FOR BOEING 737 CIVIL AIRCRAFT. THE AUTOMATIC FLIGHT CONTROL SYSTEMS (AFCS) CONSIST OF THREE SYSTEMS: DIGITAL FLIGHT CONTROL SYSTEM (DFCS), YAW DAMPER SYSTEM & AUTOTHROTTLE SYSTEM. THE DFCS INCORPORATES TWO SPERATE CHANNELS. EACH CHANNEL CONTROLS THE PITCH AND ROLL AXES AND PROVIDES MACH TRIM AND SPEED TRIM CONTROL. THE MODE CONTROL PANEL IS MOUNTED ON THE GLARE SHIELD…

  9014 20 80 · GB 2016 · GB502823281

• AN ACCELEROMETER WHICH IS USED FOR TACTICAL NAVIGATION APPLICATIONS INCLUDING TACTICAL MISSILE AND SMART BOMB PROGRAMS. THE ACCELERATION IS MEASURED AS A FUNCTION OF THE FREQUENCY DIFFERENCE BETWEEN TWO VIBRATING QUARTZ BEAMS. FREQUENCY OUTPUT FOR THE DIRECT INTERFACE TO DIGITAL ELECTRONICS. INTEGRAL TWO MOUNTING FLANGE. HERMETICALLY SEALED CASE. INTERNAL TEMPERATURE SENSOR FOR THERMAL…

  9014 20 80 · GB 2011 · GB120319421

• A VISUAL GUIDANCE SYSTEM (VGS). THE FUNCTION OF THE VGC IS TO PRESENT AIRCRAFT PERFORMANCE AND CONTROL INFORMATION TO THE PILOT WITHIN THE FORWARD FIELD OF VIEW. THIS IS DONE BY PROJECTING A CRT GENERATED IMAGE INTO THE FIELD OF VIEW VIA A REFLECTING COMBINER, SHEET OF GLASS. THE VGS CONSISTS OF A MODULAR AVIONICS UNIT (MAU), OVERHEAD UNIT AND COMBINER. THE MAU IS THE COMPUTER THAT RECEIVES AND…

  9014 20 80 · GB 2006 · GB115729373