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MACHINES AND APPARTUS, FOR THE AUTOMATIC TESTING OF THE INTEGRITY OF INK-JET CARTRIDGE HOUSINGS. THIS BTI REPLACES IE 02NT-14-326-5A
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 meusuring 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 are for use in civil aircrafts.
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 are not for use in civil aircrafts.
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.