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BLEED AND OVERHEAT MONITORING SYSTEM. FOR USE IN AIRCRAFT. THE MAIN FUNCTION OF WHICH IS TO PREVENT DAMAGE FROM TOO MUCH HEAT AND PRESSURE, PREVENTS ICE BUILD UP (ON WINGS), MONITORS THE SYSTEM TO CREW OR MAINTENANCE PERSONNEL.

Fibre optic gyroscope is opto-electronic sensor for measuring angular rate based on the sagnac effect. Each fibre optic gyroscope consists of the following main components: fibre optic winding on a bobbin, light source in the form of a super luminescent diode, optic couplers, optical polarizer, piezoceramic modulator photo-diode and processing electronics. The gyroscope is normally packed individually and is not for use in civil aircrafts.

THIS TORQUE SENSOR IS DESIGNED FOR BOTH STATIC AND DYNAMIC MEASUREMENTS ON NON-ROTATING APPLICATIONS. SHEAR STRAINS IN THE TORSION SHAFT ARE MEASURED BY MEANS OF METAL FOIL STRAIN GAUGES CONNECTED ON THE SENSOR ELEMENT. APPLYING A SUPPLY VOLTAGE GENERATES AN ELECTRICAL OUTPUT SIGNAL THAT IS DIRECTLY PROPORTIONAL TO THE APPLIED MECHANICAL TORQUE. MEASUREMENT RANGES FROM 0 - 0.005 NM TO 0 - 5000 NM.

A LEAK METERING SYSTEM PRIMARILY USED TO METER AND INVESTIGATE LEAKS IN DOWNHOLE BARRIERS SUCH AS TUBING, CASING, CEMENT OR DOWNHOLE VALVES USED IN OIL AND GAS WELLS. THE LMS IS ALSO CAPABLE OF IDENTIFYING FLUID COMPOSITION AND HYDROCARBON STORAGE VOLUMES WHICH IS IMPORTANT FOR RISK ASSSESSMENT AND RISK RANKING STUDIES. IT HAS A MAXIMUM OPERATING TEMPERATURE OF 200 DEGREE C. MAXIMUM OPERATING PRESSURE OF 5000 psi. THE SUPPLY VOLTAGE IS 85-260 VAC. DIMENSIONS: 120 MM L X 600 MM D X 850 MM H. WEIGHT: Ca. 200 KG.

A PROCESSOR/DIGITAL FUEL GAUGE TO COMPUTE AND DISPLAY THE DATA RELATED TO FUEL LEVEL AND STATUS OF THE MEASURING COMPONENTS AND FUELING VALVES WITHIN AN AIRCRAFT. THE PROCESSOR ALSO TESTS IF THE COMPONENTS IN THE FUEL TANK (MEASURING COMPONENTS AND FUELING VALVES) ARE WORKING PROPERLY.