System Review PTM CH-07 (Powerplant) Flashcards
What type of engine does the latitude have?
2 Pratt & Whitney PW306D1 Producing 5907 pounds of thrust
Ignition buttons in Normal position causes ignition to be controlled by what?
The FADEC.
If the N1 shaft fails, what automatically shuts down the engine?
Mechanical emergency fuel shutoff valve
The FADEC is powered by what during normal operations?
PMA (permanent magnet alternator).
What is the N1 gauge indication of cruise (CRU) setting?
An inward pointing white line.
What is the N1 gauge indication of max continuous thrust (MCT)?
An outward pointing white line.
What does the T bug indicate?
Current throttle position as N1%
The T bug determines where FADEC sets which bug?
The V bug.
Battery power should not be turned off for how long to allow data transfer from the EEC to the EDU?
30 seconds.
Is engine sync automatic or manual?
It is automatic.
What does the green ignition indicators (IGN) indicate?
Indicates power to the exciter boxes, not actual ignition firing.
The EVENT MARKER records data for how long?
It records 4 minutes before the event and 1 minute after.
At what % N2 is the Run button pushed?
9% N2
Inflight engine starts are aborted by?
The pilot.
Inflight engine start should be aborted if stabilized flight idle of what and when?
Of 65% N2 within 90 seconds of ITT rise.
What signifies engine start sequence has been completed?
The ENGINE SHUTDOWN (White) EICAS message clears.
When does ground idle occur after touchdown?
8 seconds.
Automatic engine shutdown by the FADEC occurs if N1 or N2 reaches what?
110%
An inflight engine failure causes the halo around what button to flash?
The respective RUN/STOP button.
How long of a wait at idle power should be obtained prior to shutting down an engine on the ground?
2 minutes for the ITT to stabilize.
To cool the generators, idle thrust with a load of less than 75 amps for how long prior to shutdown?
4 minutes.
If an adequate time for cooling the generators cannot be obtained prior to shutdown, how long must that aircraft sit prior to a restart?
35 minutes.
The thrust reversers are controlled by what system?
The electrical system.
The thrust reversers are actuated by what system?
The hydraulic system.
The thrust reversers will not operate without how many squat switches indicating WOW?
3
Throttles aft of idle inflight has what effect on thrust reversers?
No effect.
Throttles aft of idle on landing has what effect on thrust reversers?
Thrust reversers deploy.
What does the T/R EMER STOW button do?
It opens the thrust reverser isolation valve and directs the control valve to the stow position which causes the T/R ARM indication to be displayed until EMER STOW is deselected.
Thrust reverser deployment inflight causes the FADEC to command the engine to what power setting?
Idle.
Thrust reverser deployment inflight causes the T/R EMER STOW button to illuminate how?
Flashing till pushed, then steady.
The maximum speed with a thrust reverser deployed inflight is what?
150KIAS. It allows aerodynamic forces to stow it.
Is the thrust reverser check required before every flight?
No only required once per day unless thrust reverser credit is used for performance calculations or after maintenance has been performed.
Idle reverse by must be selected by what speed?
65KIAS.
Thrust reverser deployment is limited to how long with the APU operating?
30 seconds.
Thrust reverser deployment is limited to how long without the APU operating?
5 minutes
When should the pilot abort an engine start?
When no oil pressure within 20 seconds of ITT rise.
When no N1 by 40% N2.
When stable idle is not achieved within 90 seconds of ITT (57% N2 on the ground).
If ITT Limit is going to be exceeded (950 degrees C)
When does the FADEC abort an engine start?
If insufficient ITT rise within 15 seconds after fuel flow.
If the ITT Limit is exceeded. (1000 degrees C)
Powerplant General
Two rear-mounted Pratt & Whitney PW306D1 engines.
High bypass ratio turbofan engines that develop 5907 pounds of thrust at sea level.
Controlled by a dual-channel full authority digital engine control (FADEC) unit.
Forced mixer exhaust nozzle reduces noise levels and increases performance.
Fan
An inner shaft (N1) consists of a fan assembly that is driven by a three-stage low pressure (LP) turbine.
Compressor
The outer-shaft (N2) consists of four axial stages and one centrifugal stage of the compressor driven by a two-stage high pressure (HP) turbine.
Fan Section
Consists of individual titanium blades.
Bypass air passes through single-stage stators and the full-length bypass duct before exiting through a forced mixing nozzle.
The modified outer bypass duct splits into a two-piece assembly to accommodate a vectored outboard thrust of 4 degrees.
Core Airflow
Passes through variable inlet guide vanes and first-stage variable stator vanes, allowing optimum flow into the high pressure (HP) compressor.
The vanes are controlled by the FADEC.
Accessory Gearbox
All Engine-driven accessories.
Direct drive tower shaft geared to the N2 section.
Compressor Bleed Off Valves
Prevent compressor surge and stall during start, low rpm operations, and during transient power conditions.
The solenoid-operated valves allow compressor air into the bypass ducts.
Four bleed off valves are controlled by the FADEC.
Engine Oil System Schematic
Lubricating System Overview
Lubricates, cools, and cleans the bearings, and carries foreign material to the oil filter.
Consists of an oil filter and tank, a pressure pump, scavenge pumps, and a fuel/oil heat exchanger.
Oil Chip Detector
Oil passes over a chip detector on the accessory gear box to detect metal particles and post a crew alerting system (CAS) message.
Oil Supply
From the tank through a gear pump, and sent to the filter.
A portion of oil is recirculated back to the pump inlet through the pressure adjustment valve to regulate oil pressure.
Oil passes through the fuel oil heat exchanger and is sent to the No. 1, No. 2, No. 3, and No. 4 bearings and the N2 tower shaft bushing.
Accessory Gearbox Oil
Lubricates the starter-generator gear shaft. Accessory gear box gears and bearings are continuously lubricated by oil from the accessory gear box sump.
Oil Tank
Located inside the intermediate case.
A sight glass next to the filler tube provides a visual indication of oil quantity.
When oil quantity is low prior to engine start on the ground, the OIL LEVEL LOW L and/or R CAS message is displayed.
Oil Pump
Located on the accessory gear box.
Three elements: one pressure pump and two scavenge pumps.
Pump housing has a tank oil drain receptacle.
Oil Filter
Oil filter housing contains a cartridge-type 10-micron filter element.
Filter housing has a check valve allowing filter replacement without draining the oil tank.
Oil Filter Bypass Valve
If oil filter becomes contaminated, restricting the flow of oil through the filter, a bypass valve opens, allowing unfiltered oil to flow to the engine.
When OIL FLTR BYPASS L and/or R CAS message displays, indicating an impending bypass situation. For extremely low oil temperatures during engine start the CAS message is inhibited.
Oil Pressure Transducer
A pressure transducer and differential pressure switch monitor oil pressure.
Transducer provides input to the EIS for analog indication.
The differential pressure switch activates the OIL PRESSURE LOW L or R CAS message.
Oil Pressure EIS Display
Fuel/Oil Heat Exchanger
Oil is cooled through the fuel oil heat exchanger by using fuel to cool engine oil.
Elevates fuel temperature, preventing ice crystals from forming.
Ignition System
Two exciter box units on the right side of each engine and two spark igniters in the engine combustion chamber.
Power for the ignition system comes from the emergency buses and is controlled with buttons on the GTC Propulsion page.
With the buttons in the NORM position, the FADEC controls ignition operation.
Two green IGN indicators on the EIS show that power has reached at least one of the igniter boxes.
Fuel System
Delivered from the fuel tanks to a hydromechanical fuel control unit (HMU) on the accessory gear box. A fuel pump receives the fuel and boosts the pressure before sending it through the fuel-oil heat exchanger into the fuel filter.
Fuel Filter Bypass
If the fuel filter becomes blocked due to contamination, a bypass valve opens, allowing fuel to bypass the filter.
A differential pressure switch triggers the FUEL FLTR BYPASS L and/or R CAS message,
High pressure (HP) Engine Driven Pump
Boosts the pressure for atomization in the fuel nozzles.
Delivers Fuel to the FADEC-controlled HMU.
Hydromechanical Fuel Control Unit (HMU)
Delivers metered fuel to the fuel nozzles.
Provides HP fuel for motive flow, engine starting and shutdown, and controls thrust, idle speed, acceleration/deceleration, and variable guide vane positioning.
Waste Fuel Ejector
Collects and stores fuel from the fuel manifold at engine shut down.
On subsequent engine operations, it draws fuel from the waste tank and returns it to the fuel pump.
Fuel Nozzles
24 fuel nozzle adapters are equally spaced around the combustion chamber outer case.
22 secondary nozzles and 2 primary nozzles.
Fuel Flow Transmitter
Sends fuel flow information to the EIS (FUEL PPH) and flight management system (FMS) for fuel flow monitoring.
Emergency Fuel Shutoff Valve
Provides a mechanical means of automatic engine shutdown in the event of an N1 shaft failure.
A plunger at the rear of the N1 shaft senses movement of the shaft and causes the shutoff valve to close and stop fuel flow to the fuel manifold.
FADEC
Full Authority Digital Engine Control (FADEC)
