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Airplane Flying Handbook
Turbo-propeller Powered Airplanes
TURBOPROP ENGINE TYPES

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Airplane Flying Handbook

Preface

Table of Contents

Chapter 1,Introduction to Flight Training
Chapter 2,Ground Operations
Chapter 3,Basic Flight Maneuvers
Chapter 4, Slow Flight, Stalls, and Spins
Chapter 5, Takeoff and Departure Climbs
Chapter 6, Ground Reference Maneuvers
Chapter 7, Airport Traffic Patterns
Chapter 8, Approaches and Landings
Chapter 9, Performance Maneuvers
Chapter 10, Night Operations
Chapter 11,Transition to Complex Airplanes
Chapter 12, Transition to Multiengine Airplanes
Chapter 13,Transition to Tailwheel Airplanes
Chapter 14, Transition to Turbo-propeller Powered Airplanes
Chapter 15,Transition to Jet Powered Airplanes
Chapter 16,Emergency Procedures

Glossary

Index

Powerplant controls—split shaft/free turbine
Figure 14-6. Powerplant controls—split shaft/free turbine engine.

Powerplant (engine and propeller) operation is
achieved by three sets of controls for each engine: the
power lever, propeller lever, and condition lever.
[Figure 14-6] The power lever serves to control engine
power in the range from idle through takeoff power.
Forward or aft motion of the power lever increases or
decreases gas generator r.p.m. (N1) and thereby
increases or decreases engine power. The propeller
lever is operated conventionally and controls the
constant-speed propellers through the primary
governor. The propeller r.p.m. range is normally from
1,500 to 1,900. The condition lever controls the flow
of fuel to the engine. Like the mixture lever in a
piston-powered airplane, the condition lever is located
at the far right of the power quadrant. But the condition
lever on a turboprop engine is really just an on/off
valve for delivering fuel. There are HIGH IDLE and
LOW IDLE positions for ground operations, but condition
levers have no metering function. Leaning is not
required in turbine engines; this function is performed
automatically by a dedicated fuel control unit.

Engine instruments in a split shaft/free turbine engine
typically consist of the following basic indicators.
[Figure 14-7]
• ITT (interstage turbine temperature) indicator.
• Torquemeter.
• Propeller tachometer.
• N1 (gas generator) tachometer.
• Fuel flow indicator.
• Oil temperature/pressure indicator.

Engine instruments—split shaft/free turbine engine.
Figure 14-7. Engine instruments—split shaft/free turbine engine.

 

14-6