Wright Aviation Services LLC Presents Piper Meridian Systems Training Program PT6A-42A Click Mouse to Advance Wright Aviation Services LLC Meridian – PA46-500TP Power Plant and Fuel Pratt & Whitney Canada PT6A-42A Click.
Download ReportTranscript Wright Aviation Services LLC Presents Piper Meridian Systems Training Program PT6A-42A Click Mouse to Advance Wright Aviation Services LLC Meridian – PA46-500TP Power Plant and Fuel Pratt & Whitney Canada PT6A-42A Click.
Slide 1
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 2
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 3
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 4
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 5
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 6
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 7
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 8
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 9
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 10
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 11
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 12
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 13
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 14
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 15
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 16
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 17
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 18
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 19
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 20
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 21
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 22
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 23
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 24
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 25
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 26
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 2
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 3
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 4
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 5
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 6
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 7
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 8
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 9
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 10
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 11
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 12
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 13
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 14
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 15
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 16
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 17
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 18
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 19
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 20
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 21
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 22
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 23
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 24
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 25
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
Click Mouse to Advance
Wright Aviation Services LLC
Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
Click Mouse to Advance
Wright Aviation Services LLC
Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
Click Mouse to Advance
Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
Click Mouse to Advance
Wright Aviation Services LLC
Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
Click Mouse to Advance
Wright Aviation Services LLC
Slide 26
Wright Aviation Services LLC
Presents
Piper Meridian
Systems Training
Program
PT6A-42A
Click Mouse to Advance
Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant and Fuel
Pratt & Whitney Canada
PT6A-42A
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Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
500 shaft horse power SHP
Turbine Speed: 38100 RPMs
Geared to 2000 rpm propeller speed
Reverse flow, free turbine
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
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Wright Aviation Services LLC
Meridian – PA46-500TP
Power Plant
Pratt & Whitney Canada
PT6A-42A
Terms:
Np – Propeller speed
Ng – Gas generator speed
ITT – Inter-stage Turbine Temp
Tg – Shaft Torque
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Meridian – PA46-500TP
Power Plant
The PT6A engine consists of two main sections:
Gas generator section
Power section.
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Meridian – PA46-500TP
Power Plant
The gas generator section
takes outside air,
compresses it and delivers it
to the combustion chamber.
The gas generator is
separated from the power
turbine in the Meridian
application.
The gas generator drives
accessories mounted at the
rear of the power plant.
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Meridian – PA46-500TP
Power Plant
The Power or Turbine
section is separated
from the Gas
Generator in the
Meridian PT6A-42A.
The separation occurs
between the forward
most component of the
gas generator (the
compressor turbine)
and the beginning of
the power turbines.
The Power Section
shaft is connected to a
gear reduction unit
which, in turn, is
connected to the
propeller shaft.
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Meridian – PA46-500TP
Power Plant
External air is drawn in through a duct section, through screens, turned 180
degrees into the gas turbine or compressor that consists of three axial stages
and one centrifugal stage.
From there, the compressed air leaving the compressor passes through
diffuser pipes which turn the flow 90 degrees, reduce its speed and direct the
air into the combustion chamber.
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Meridian – PA46-500TP
Power Plant
In the annular combustion chamber the air is mixed with fuel and burned.
Initially, two igniter plugs are used to light the fuel/air mixture when the
engine is started.
Once started, the igniter are not required to maintain the combustion process
and can be shut off once the engine has reached idle speed.
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Meridian – PA46-500TP
Power Plant
The expanding hot gases are directed first through the compressor turbine
and then through the power turbine.
After passing through the power turbine, the gases are exhausted through
ports on each side of the engine.
The exhaust stubs fitted to the engine are normally directed to utilize the
remaining energy of the gases in the form of thrust for additional aircraft
propulsion.
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Meridian – PA46-500TP
Power Plant
The expanding hot gases are
directed first through the Gas
Generators’ forward
compressor turbine, which
provides the ongoing power to
spin the Gas Generator.
Expanded gases then pass
through the Power Turbines,
rotating the forward shaft
which is connected to the gear
box and on to the propeller
shaft.
Gases are exhausted through
ports on each side of the
engine. These exhaust stubs
fitted to the engine are
designed to utilize remaining
energy of the gases in the form
of thrust for additional aircraft
propulsion.
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Meridian – PA46-500TP
Power Plant
Two bleed air systems
are incorporated in the
PT6A engine.
Automatic bleed air from
the compressor prevents
compressor stall during
acceleration from low
engine speeds or
deceleration from high
engine speeds.
For aircraft use, air may
be bled for heating or
pressurizing aircraft
cabins.
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Meridian – PA46-500TP
Power Plant
These valves are located on
the sides of the compressor at
the 3 and 9 o’clock positions.
During acceleration and
deceleration of the engine,
the Gas Generator produces
more air than the Power
section can consume, which
could lead to compressor
stall.
Simply put, to prevent this,
low and high pressure valves
are installed that allow excess
pressure to be vented
overboard.
When Ng is at 69%, the low
pressure valve is closed and
at 91%, both valves are
closed.
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Meridian – PA46-500TP
Power Plant
A shaft connects the power turbine to the Bevel gears, located forward of the
two-stage planetary reduction gearbox. second stage planetary gears, drive the
The first stage reduction ring gear floats following accessories that are mounted
on the forward reduction gearbox case:
axially against a hydraulic torquemeter
· propeller governor or constant speed unit
cylinder.
· propeller over-speed governor
The oil pressure in this cylinder is
· tachometer-generator
proportional to output torque. That
pressure is used to provide data for the
torque indicator in the cockpit.
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Meridian – PA46-500TP
Power Plant
The accessory gearbox, mounted on
the rear of the engine, is used to drive
the following engine accessories:
· High-pressure fuel pump
· Fuel control unit
· Oil scavenge and oil pressure pumps.
Space is also provided for aircraft
manufacturer provided accessories
such as the starter-generator, gas
generator tachometer-generator, fuel
boost pumps or hydraulic pumps.
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Meridian – PA46-500TP
Power Plant – Fuel System
The fuel system is designed to deliver clean fuel to the engine at the pressure and
flow that are necessary for all engine operating conditions.
The airframe fuel system contains the necessary boost pumps, transfer pumps,
selector/shutoff valves, strainers and filters required to supply fuel to the engine and
to manage the fuel load distribution in the airplane.
The engine is equipped with a fuel system which consists of a fuel heater, highpressure fuel pump, fuel filter, fuel control unit, start control or flow divider unit and
a manifold with fuel injection nozzles.
The fuel control unit is either a hydro-pneumatic or a hydro-mechanical system
which meters the correct amount of fuel to the engine to maintain the gas generator
speed selected by the pilot via the power control lever. It also controls fuel flow
scheduling during engine starting, acceleration and deceleration.
The PT6A engine is approved for operation with all commercial jet fuels, JP-4, JP-5
and for a maximum of 150 hours during any overhaul period with all grades of
aviation gasoline. Specific grades of diesel fuel are approved as alternate fuels for
restricted use. No engine adjustments are required in changing from one fuel to
another, nor is it necessary to purge the fuel system when changing fuels, except
when using alternate fuels.
For listings of approved fuels and fuel additives refer to the appropriate Service
Bulletins for each PT6A engine model.
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Meridian – PA46-500TP
Power Plant – Engine Instrumentation
Incorporated into the design of the PT6A engine are accurate and
reliable torque and ITT measuring systems that give the pilot an
accurate indication of the primary engine operating parameters.
Torque Pressure is sensed by a torque pressure transducer mounted
on the reduction gearbox, to indicate the torque being developed by
the engine. Torque is the primary parameter used to set power for
takeoff and cruise operation for specified propeller speeds.
ITT is monitored to ensure that combustion gas temperature limits of
the engine are not exceeded.
Two tachometer-generators are installed on the engine: one on the
reduction gearbox monitors propeller speed (Np), and the other on the
accessory gearbox monitors gas generator speed, (Ng).
Pressure and temperature gauges monitor the oil system.
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Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
Torque Gauge
ITT Temp Gauge
Np - Propeller RPMs
Ng – Gas Turbine
Percent RPMs
Oil Pressure
Oil Temp
Vacuum
Electrical
Rudder Trim
Fuel Information
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Meridian –
PA46-500TP
Power Plant –
Engine
Instrumentation
OAT Toggle: F or C
OAT
Fuel Gauges
Fuel Totalizer
FUEL FLOW DATA
Current FLOW
Fuel USED
Fuel REMAINING
ENDURANCE
Reset Initial Fuel
NOTES:
Fuel Flow data is based on fuel
consumed by the engine which is
a very accurate measure.
However, the Fuel Remaining
and Endurance Remaining
numbers rely upon accurate
INITIAL FUEL information input
by the pilot.
Fuel Gauges report fuel as
measured in the tanks by the
fuel transducers.
Exceedances
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Meridian – PA46-500TP
Power Plant – Engine Controls
Prop Lever & Governor
Power Lever Cam Assembly
(opposite side)
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Fuel Lever
Meridian – PA46-500TP
Power Plant – Engine Controls
• Condition Lever
• Power Lever
• Manual Override
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Meridian – PA46-500TP
Power Plant – Engine Controls
Condition Lever
Cut-OFF/Feather
Run
Power Lever
Power range
Idle
Beta
Reverse
MOR Lever (manual override)
Stored
Power range
Friction Lever
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Meridian – PA46-500TP
Power Plant – Engine Controls
Notes
Warnings
Power lever not to be moved
into reverse when engine is off
– may cause damage to
linkages.
Moving power below idle in flight is
PROHIBITED. Doing so may cause
loss of aircraft control, engine
overspeed leading to loss of engine
power.
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Meridian – PA46-500TP
Power Plant - Review
Pratt & Whitney Canada
PT6A-42A
Oil is synthetic turbine oil
500 shaft horse power (SHP)
Reverse flow, free turbine
Turbine Speed: 38100 rpms
Maximum allowable torque – 1313 ft pounds
Geared to 2000 rpm propeller speed
Site gauge on left side of engine
Check quantity within 15 minutes of shut
down
Quantity within green on site gauge – OK
Qty below green, use dipstick to determine
qty to add
Major Components
Compressor – Gas Generator
Hot Section – Power Section
Reduction gear section
Fuel : Aviation JetA or JetA-1
Accessories:
Starter Generator
Alternator
AC Compressor
Controls consist of
Power lever
Condition lever
Manual Overide lever
Friction lever
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Wright Aviation Services LLC
Meridian Power Plant - PT6A-42A
THE END
Presentation
By
Wright Aviation Services LLC
www.WrightAviation.net
480-203-0599
©Copyright 2010/2011 Wright Aviation Services, all right reserved
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Presented by
Wright Aviation Services LLC
Scottsdale/Phoenix AZ
Copyright 2010/2011 – Wright Aviation Services
All rights reserved
Website: www.wrightaviation.net
Email: [email protected]
Phone: 480-203-0599
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