Engine and APU Flashcards
EGT display color indications
White - normal operating range
Amber - continuous (CON) limit reached
Red - start/TO limit reached
- indication will remain white for 5 mins when CON limit is reached or exceeded during TO or GA
When is the Secondary Engine Indications displayed?
- when EICAS first receives power
- in flight, with a fuel control switch moved to CUTOFF
What happens when FUEL CONTROL switch is placed in RUN?
- opens spar fuel valve
- opens engine fuel valve
- EEC sequences start valve, fuel metering valve, and igniter operation (auto start)
- energizes igniter(s) (manual start)
What happens when FUEL CONTROL switch is selected CUTOFF?
- closes fuel valves
- removes igniter power
- commands respective hydraulic demand pump to operate when Demand Pump selector in AUTO
- unlocks Engine Fire switch
When do igniters AUTOMATICALLY turn on?
- during start when N2 RPM less than 50%
- trailing edge flaps out of up position
- nacelle anti-ice ON
- engine flameout
What happens when you place APU selector to OFF position?
- closes APU bleed air isolation valve
- initiates normal shutdown
- resets auto shutdown fault logic except when shutdown due to APU bleed duct leak
Describe Engine Types
4 x GE CF6-80C2-B1F - each produce 56,500 lbs of takeoff thrust
4 x GE CF6-80C2-B5F - each produce 62,100 lbs of takeoff thrust
- dual axial flow, high compression, high bypass turbofans
- N1 rotor——> Fan, low pressure compressor, and low pressure turbine
- N2 rotor——> High pressure compressor and high pressure turbine - drives accessory gearbox
Primary and Secondary Engine Indications
Primary:
- N1
- EGT
Secondary:
- N2
- FF
- Oil Temp
- Oil Press
- Oil Qty
- Eng vibration
What calculates N1 and fuel flow for the engines?
Each engine has its respective Electronic Engine Control (EEC)
Each EEC:
- uses thrust lever movements to control forward and reverse thrust
- calculate N1
- commands fuel metering to adjust actual N1 to calculated N1
- powered by alternator in accessory gear box
Electronic Engine Control (EEC) modes?
Normal:
- thrust is set by controlling N1 based on thrust lever position
- adjust N1 based on pressurization and anti-ice bleed requirements
- continuously computes maximum N1
- thrust is limited to max computed N1 with thrust lever full forward
Alternate:
- back up to normal mode
- automatically or manually selected with EEC mode switch
- provide equal or greater thrust at selected thrust lever position
- does not provide thrust limiting and maximum N1
- Max N1 is reached at thrust lever position less than full forward
- thrust levers must be adjusted to maintain desired thrust as environmental condition and bleed requirements change
When does EEC command Approach Idle?
- nacelle anti-ice is ON
- flaps are in landing position
- Continuous Ignition switch is ON
- thrust reverser operation
*maintained until 5 mins after touchdown
How does EEC protect again Overspeed?
- monitors N1 and N2 RPMs
- commands fuel metering unit to control fuel flow to rotor speeds from exceeding limits
What is the meaning of the Fuel-On indication on N2?
- displayed when Fuel Control switch is in CUTOFF
- displays the minimum N2 RPM at which the Fuel Control switch should be moved from CUTOFF to RUN during a manual start
Indication provided to help in flight restart
- In Flight Start Envelope is displayed on the Primary EICAS when Fuel Control switch is moved to CUTOFF in flight
- envelope displays airspeed range to ensure restart at current flight level
- X-BLD is displayed next to N2 if crossbleed start is needed
Primary source of bleed air for engine start
Primary source: APU
Secondary source: ground source and engines
AUTOSTART Sequence
- EEC monitors start and sequences start valve, fuel valve, and igniter operation
- AUTOSTART switch ON arms the AUTOSTART
- pulling the START switch out opens ENG BLEED VALVE and arms START VALVE
- AUTOSTART sequence is started when FUEL CONTROL switch is moved to RUN
1) EEC opens START VALVE
2) As N2 rises EEC determines when to open FUEL VALVE and energized igniters
* one igniter for ground start and two for in-flight start
3) STARTER CUTOUT at 50% N2 - EEC monitors EGT and N2 until engine stabilizes at idle
Autostart system abort parameters
EEC monitors EGT and N2, does not monitor oil pressure or N1 rotation
ECC with abort start for:
- Hung Start
- Hot Start
- no EGT rise
- malfunction in the Autostart system
“Immediate Action Items”
What happens if EEC detects Hung, Hot, or no rise in EGT
No Rise in EGT:
- fuel and ignition cutoff
- engine motors for 30 sec
- fuel and ignition (both igniters) are reapplied
- 3 attempts are made before autostart is aborted
- engine will motor for 30 sec before start valve and bleed valve are closed
Hung or Hot before starter cutout
- fuel is cutoff and fuel schedule readjusted
- fuel reapplied
- 3 attempts are made before abort
- engine will motor for 30 sec before start valve and bleed valve are closed
Hung or Hot after starter cutout
- autostart sequence aborted immediately
- engine does not motor
When is auto relight activated?
- EEC activates both igniters when a flameout is detected
- detected with rapid decreases of N2 or N2 drops below idle
Normal and backup power source for the engine igniters
Primary power - AC power system
Back up power - Standby power system
Which valves open when FUEL CONTROL switch it selected to RUN?
- spar valve
- fuel metering valve
- engine fuel valve
*Engine Fire switch must be in
How are engine thrust reversers actuated?
- with forward thrust levers in closed position an interlock mechanism is released allowing thrust reverse levers to be raised
- with reverse thrust levers raised to idle detent respective engine bleed air is used to unlock and deploy reversers
- engine bleed air is also used to stow and lock reversers in case of inadvertent deployment
Which areas are monitored by the engine vibration system?
- Fan (N1)
- Low Pressure Turbine (LPT)
- N2
- Broadband (BB) is used to indicate if source cannot be determined
APU Operation limit
- ground to 20,000’
- can only be started on the ground
- Electrical power only avail on the ground
- Bleed air avail in flight for one pack up to 15,000’
How many APU Generators?
2 APU Generators (can supply entire electrical load on the ground)
How long is normal APU Shutdown sequence?
- 60 seconds (for cool down)
- Batt switch should remain on until APU shutdown is complete
APU Start sequence
When APU selector is momentarily selected to start:
- APU Fuel Valve and Inlet Door open simultaneously
- ignition
- light-off
- engine acceleration