The specifications were prepared in accordance with the requirement of Jaguar Aircraft. The CTS was designed & developed and manufactured in coordination with M/s Prudent Communication System Pvt Ltd, Bangalore. The indigenous CTS had undergone all the stringent qualification testing as recommended by the certification agencies and met all the specification and qualification requirements. The LRU has been cleared by Regional Centre for Military Airworthiness, CEMILAC for using on Jaguar aircraft.

The following specification particularly describes the nature of invention and the manner in which it is to be performed.
BACKGROUND OF INVENTION:
Cockpit Temperature Sensor a line replaceable unit used in air-conditioning system of jaguar aircraft.This item has become obsolete.The spares and specification were not available to service this item.This items is essential for clearance of aircraft for flight or engine ground run.This item is developed with new design and architecture to suit the air condition system requirement on aircraft.This invention ensures to maintain the serviceability of jaguar fleet and fulfils 'Make in India *initiative.
OBJECTIVE OF INVENTION:
The main objective of the invention is to improve the effectiveness of airconditioning system of jaguar aircraft.This solid state Cockpit Temperature Sensor with system defined architecture comprising reliable and precise military grade components is designed to improve the comfort of the pilot. This invention was initiated to achieve considerable foreign exchange savings and broaden the technology base of our country.
DETAIL DESCRIPTION OF INVENTION:
The Cockpit Temperature Sensor consists of one front plate and base cover made Aerospace grade material. Front plate consist of thermistor sensor positioned in a cylindrical stem and base cover has one PCB with processing electronics circuitry. CTS Unit provides all the termination on a rugged DBC-54-H10-6PN to MIL-C 26482 G series 2 circular connector. The finishing for CTS unit will be black anodizing as per MIL-A-8625 REV F. Cockpit Temperature Sensor unit is a part of Air-conditioning System of Jaguar Aircraft and installed in the air conditioning delivery pipelines for foot pedal and HUD/Windscreen. It will automatically control the operation of by-pass valve when the outlet air temperature from the pipeline is less than 19°C or greater than 25°C and prevents the misting of the wind screen when the engines are throttled back after high speed low level flight. When the air temperature is above 25°C, the sensor gives signal to the ball

valve to divert the air to windscreen of the aircraft to demist the fog deposited over the windscreen. When the air temperature is below 19°C/ the sensor allows the pilot to divert the airflow either to windscreen or foot pedal by demist lever selection.
This new Cockpit Temperature Sensor is designed to suit the aircondition system requirement of jaguar. This newly invented cockpit temperature sensor maintains the serviceability requirement of jaguar military aircraft fleet of IAF. Moreover,this invention also strenghtened the self-reliance in Defense sector production in line with "Make in India" concept.The specifications were defined in accordance with Jaguar military Aircraft build standard. The Cockpit Temperature Sensor was designed & developed and manufactured in coordination with M/s Prudent Communication System Pvt Ltd, Bangalore. The indigenous Cockpit Temperature Sensor had undergone all the stringent military qualification testing as recommended by the certification /regulatory agencies to meet the airworthyness requirement of Jaguar aircraft.
QUALIFICATION TEST CARRIED OUT:
The newly designed cockpit temperature sensor was subjected to the following environmental and functional tests.
1. Power supply Test
2. EMI/EMC Test
3. Random Vibration Test
4. High Temperature Test
5. Low Temperature Test
6. Thermal shock Test
7. Humidity Test
8. Altitude Test
9. Acceleration test

10. Mechanical Shock Test
11. Toppling Test

12. Transit Drop Test
13. Corrosion Salt Mist Test
After above qualification testing, the unit was fitted and tested on the aircraft. Performance of the temperature sensor was found satisfactory.
CLAIMS:
Self-reliance and sufficient foreign exchange saving are achieved.
Cycle time for servicing is reduced.