AM.III.B.K5 - Turbine Engines

The blending of blades and vanes in a turbine engine

Should be performed parallel to the length of the blade using smooth counters to minimize stress points.

Which of the following may be used to mark turbine engine components exposed to high temperatures?

Layout dye.

When starting a turbine engine, a hung start is indicated if the engine

Fails to reach idle RPM.

What must be done after the fuel control unit has been replaced on an aircraft gas turbine engine?

Retrim the engine.

If, during inspection at engine overhaul, ball or roller bearings are found to have magnetism but otherwise have no defects, they

Must be degaussed before use.

Who establishes the recommended operating time between overhauls (TBO) of a turbine engine used in general aviation?

The engine manufacturer.

(1) Welding and straightening of a turbine engine rotating airfoils does not require special equipment.

(2) Welding and straightening of turbine engine rotating airfoils is commonly recommended by the manufacturer.

Neither 1 nor 2 is true.

Turbine engine components exposed to high temperatures generally may not be marked with

Wax, grease pencil, or a graphite lead pencil.

Who establishes the mandatory replacement times for critical components of turbine engines?

The engine manufacturer.

Where do stress rupture cracks usually appear on turbine blades?

Across the leading or trailing edge at a right angle to the edge length.

When the leading edge of a first-stage turbine blade is found to have stress rupture cracks, which of the following should be suspected?

Overtemperature condition.

Turbine blades are generally more susceptible to operating damage than compressor blades because of

Exposure to high temperatures.

The recurrent ingestion of dust or other fine airborne particulates into a turbine engine can result in

Erosion damage to the compressor and turbine sections.

Jet engine turbine blades removed for detailed inspection must be reinstalled in

The same slot.

When aircraft turbine blades are subjected to excessive heat stress, what type of failures would you expect?

Stress rupture.

Compressor field cleaning on turbine engines is performed primarily in order to

Prevent engine performance degradation, increased fuel cost, and damage or corrosion to gas path surfaces.

Hot section inspections for many modern turbine engines are required

On a time or cycle basis.

What should be done initially if a turbine engine catches fire when starting?

Turn off the fuel and continue engine rotation with the starter.

A weak fuel to air mixture along with normal airflow through a turbine engine may result in

A lean die-out.

Which of the following is a good indication of a malfunctioning fuel nozzle when inspecting the exhaust section of an aircraft turbine engine?

Hotspots on the tail cone.

Anti-icing of jet engine air inlets is commonly accomplished by

Engine bleed air ducted through the critical areas.

The procedure for removing the accumulation of dirt deposits on compressor blades is called

Field cleaning.

Which of the following may be used to accomplish internal inspection of an assembled turbine engine?

A borescope.

What is the possible cause when a turbine engine indicates no change in power setting parameters, but oil temperature is high?

Engine main bearing distress.

A turbine engine hot section is particularly susceptible to which kind of damage?

Cracking.

Dirt particles in the air being introduced into the compressor of a turbine engine will form a coating on all but which of the following?

Turbine blades.

Sever rubbing of turbine engine compressor blades will usually cause

Galling.

Continued and/or excessive heat and centrifugal force on turbine rotor blades is likely to cause

Creep.

Wat term is used to describe a permanent and cumulative deformation of the turbine blades of a turbojet engine?

Creep.

(1) Accumulation of contaminates in the compressor of a turbojet engine reduces aerodynamic efficiency of the blades.

(2) Two common methods for removing dirt deposits from turbojet engine compressor blades are a fluid wash and abrasive grit blast.

Both 1 and 2 are true.

Hot spots in the combustion section of a turbojet engine are possible indicators of

Malfunctioning fuel nozzles.

Which of the following can cause fan blade shingling in a turbofan engine?

Engine overspeed and/or FOD.

Compressor stall is caused by

A high angle of attack airflow through the first stages of compression.

A condition known as "hot streaking" in a turbine engine is caused by

A partially clogged fuel nozzle.