This module sets the fault condition and the related FAULT AREA light comes on. This module supplies overheat or fire indication in the flight compartment.If the pressure in the sense tube decreases, the FAULT switch opens, This causes a large change in resistance which sends the fault signal to the Engine and APU fire detection control module. The other two pressure switches close when the gas pressure increases because of an overheat or fire condition.The overheat and fire signals go to the Engine and APU fire detection control module. Gas pressure in the sense tube holds the FAULT pressure switch in the normally closed position. The three pressure switches sense for these conditions:. Locations of the Engine detector elements:-Two on the upper fan case section.Two on the lower fan case section.Two on the left core section.Two on the right core section.If one loop fails, the entire loop assembly has to be replaced. The detector elements have these components:. There are four fire detection loop assemblies in each engine.Each assembly has two detector elements, two gas charged sense tubes and a support tube. Major components of the Engine fire detection system:-ī] Engine and APU fire detection control module.
System shock 2 engine core code portable#
The Airplane has these fire extinguishing systems:-A] Lavatory fire extinguishing bottles.B] Engine fire-extinguishing bottles.C] APU fire extinguishing bottle.D] Portable fire extinguishers.įire warn and master caution lights. The Airplane has these fire/overheat detection systems:. The Fire protection system monitors the airplane for these conditions:.
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