Trans GK Engines Flashcards
What following components are driven by the accessory gearbox?
DC starter/generator
N2 speed sensor
Oil pump
Hydromechanical metering unit (HMU)
Hydraulic pump
Engine-driven fuel pump
N1 is the measure of:
Low pressure compressor fan speed
N2 is the measure of:
High pressure compressor speed
At sea level and up to 27*C, the engine will develop:
2,900 pounds of takeoff rated thrust (TRT)
An integral oil tank in each engine has a capacity of:
2.03 gallons
Maximum oil consumption per engine?
8.5 ounces per hour
What happens when the oil filter becomes clogged?
The pressure relief valve opens and some of the oil is bypassed and ducted externally through a second check valve to the oil pressure pump inlet
When the oil filter bypass valve is in use, what is illuminated?
The amber L or R O FLTR BYPASS annunciator on the main annunciator panel
When does the L or R OIL PRESS LO annunciators illuminate?
When system oil pressure decreases below 40 psi
Where can a pilot add oil to the engine?
Oil can be added to the system through the filler neck opening in the dipstick oil check panel
How is fuel flow to the engine controlled and regulated?
Mechanically controlled by throttle movement and regulated by the engine fuel control system (this is why we check for binding throttles during before starting engines checklist)
Engine fuel control system determines what?
Fuel scheduling to provide engine starting, steady operation, acceleration and deceleration, and N2 governing under all conditions of speed, altitude, and temperature
How would a pilot shut down an engine stuck at a high power setting due to a throttle linkage cable breaking?
Shut down the engine using the Fuel/Hydraulic valve close switch, then accomplish the Engine Shutdown During Flight checklist (assumption is acft is in the air)
The high-pressure fuel pump is installed on, and driven by:
The engine accessory gearbox
The high-pressure fuel pump provides:
Positive fuel pressure to the hydromechanical metering unit, while a portion of the fuel pump output in used as motive flow fuel to the respective primary jet pump
The HMU also acts as a shutoff valve, bypassing the fuel back to the pump during windmilling operation. When the throttle is closed:
Fuel flow is terminated at the HMU
Electronic fuel control (EFC) is provided to better establish:
Fuel scheduling to the engines as functions of engine air inlet temperature, ambient pressure, and throttle demand
Each EFC is powered by the respective:
Left or right DC LOAD BUS and is protected by the respective left or right EFC C/B
EFCs will be on whenever the engines are running unless:
Indications of a malfunction exist (operation of the engines with the EFCs off can result in fuel coking on the fuel nozzles)
EFC failure will result in what?
A loss of scheduled fuel flow (maximum thrust loss could be 40% depending on ambient conditions and altitudes)
