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CHAPTER FIVE
ENGINE INSTRUMENTATION AND FIRE DETECTION SYSTEMS
500.
INTRODUCTION
As student aviators, it is necessary for you to become familiar with the T-34C instrumentation
and fire detection system. You must also become familiar with the location and operation of
various components in order to ensure your capability to operate the aircraft safely and
efficiently.
501.
LESSON TOPIC LEARNING OBJECTIVES
Terminal Objective
5.0  Upon completion of this chapter, the student will demonstrate knowledge of the PT6A-25
instrumentation and fire detection systems characteristics.
Enabling Objectives
5.1
State the purpose of the interstage turbine temperature (ITT) sensing system.
5.2 Describe the location and purpose of the interstage turbine temperature sensing system,
indicators and system limitations.
5.3
Describe the location, purpose and display indications of the turbine tachometer.
5.4
Explain the compressor turbine (N1) limitations.
5.5
Explain the purpose of the fire detection system.
5.6  Describe the location and method of operation of the components of the fire detection
system.
502.
ENGINE INSTRUMENATION
Interstage Turbine Temperature
The ITT sensing system provides an accurate indication of engine operating temperature. Eight
thermocouples are attached to a harness in the engine interior and protrude into the area between
the compressor and power turbines. Each thermocouple is a bi-metallic metal probe that creates
an electrical current proportional to the temperature detected. The current operates the ITT
indicator in each cockpit.
The ITT indicators, located on the instrument panels in both cockpits, are powered by the
electrical signal from the thermocouples. The gauge is graduated in 20 C increments between
200 and 1200 degrees Centigrade.
ENGINE INSTRUMENTATION AND FIRE DETECTION SYSTEMS
5-1


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