Fire Detection System - P-307

T-34C AIRCRAFT SYSTEMS FAMILIARIZATION

CHAPTER FIVE

WORKBOOK

NOTE

N1 below 62%, but no lower than 60% will allow one-time flight.

With N1 below 60% or above 65% flight is prohibited.

Figure 5-2 Turbine Tachometer (N1 Speed)

503.

FIRE DETECTION SYSTEM

The engine fire detection system is a flame surveillance system installed in the engine

compartment to provide a visual warning to the pilot. Three infrared-sensitive detectors monitor

the compartment.

Normal engine heat will not be sensed by these detectors. One detector monitors the top of the

engine above the combustion chamber housing, a second monitors the upper accessory area, and

a third the lower accessory area. Infrared radiation from a fire (or sunlight) will be sensed by a

detector and will cause a 28-VDC current to be transmitted to the red flashing FIRE warning

light in both cockpits. The fire warning test switch is a four-position rotary switch, located on

the front instrument panel only, which allows the pilot to test the fire warning system. Both

warning lights should be flashing in all three numbered positions, and be off in the OFF position.

The fire warning light cannot be dimmed or reset by pushing and will return to the standby state

when a fire is no longer present.

ENGINE INSTRUMENTATION AND FIRE DETECTION SYSTEMS

5-3