Engines Flashcards
What type engine:
B787-9
B787-8
B787-9 GEnx-1B74/75 engines rated at 74,100 lbs thrust each
B787-8 GEnx-1B70 engines
rated at 69,800 lbs thrust each
Is it normal for the EICAS to display an EGT amber difference between engines?
Yes…in the event of engine replacement, the new engine may be derated to match the installed engine
What is the indication for loss of engine data?
Is there an associated EICAS message?
The associated engine indication blanks
There is no EICAS message
When is the reference/target N1 displayed in magenta?
Target N1 commanded by FMC when:
VNAV is engaged and A/T in THR or THR REF
OR
AT not engaged
When is commanded N1 sector filled in amber?
A difference between engine N1 and commanded N1 exists and engine N1 is not closing toward commanded N1
ENG THRUST EICAS displayed
When reverse thrust is activated, the following N1 indications are not displayed:
Maximum N1 line
Commanded N1
Reference/Target N1 indications
Reference N1
Red line on EGT gauge?
Maximum takeoff EGT
Amber line on EGT gauge?
Normal maximum continuous EGT limit
EGT indication in white?
In amber?
Time limits?
In red?
White=operating in normal band
Amber=max continuous limit reached
Inhibited for 5 min during takeoff and go around
Inhibited for 10 minutes during single engine operations
Red=max start or takeoff limit is reached
When is engine start limit line displayed?
Engine fire switch is IN and:
FUEL CONTROL switch in CUTOFF
OR
N2 RPM below idle
Can you cancel des EGT box color?
Yes…can be canceled to white or recalled to red by pressing the CANCL/RCL switch on the display panel
Green ICA indication on N1 gauge?
Ice Crystal Anti-Ice function
Automatic feature providing protection against ice crystal icing
Activates only above 30,000 feet and will activate for at least 30 minutes
Continues in 15 minute increments as conditions warrant
Will terminate as aircraft descends below 28,500 feet
Inflight start envelope?
Displayed in magenta
Only displayed when:
Respective fire handle in and
Either the engine’s FUEL CONTROL is in CUTOFF
OR
Engine N2 RPM below IDLE
Secondary engine indications display automatically when: (7)
Initially receive power
FUEL CONTROL -> CUTOFF in flight
Engine fire switch pulled in flight
Secondary engine parameter is exceeded
N2 RPM below idle in flight
Start selector is in START
FUEL FLOW ENG L/R advisory
If secondary indications have been automatically displayed, how can they be cleared?
Only by resolving the issue, then pushing the ENG display switch
Green RUNNING indication atop N2 gauge?
Fuel control switch in RUN position and the engine is at or above idle
Will blank 30 seconds after engine reaches idle
White AUTOSTART indication on N2 gauge?
EEC in autostart mode
Will blank when system no longer attempting an engine start
AUTORELIGHT on N2 gauge?
EEC is in auto-relight mode
Will blank when EEC is no longer attempting an auto-relight
What is the green idle target indication on N2 gauge?
Approximate RPM where the engine can maintain self-sustained running operation
Fuel control must be in RUN position and engine below idle
Magenta X-START indication below N2 gauge?
Current altitude and airspeed are outside of the windmilling start envelope
Starter assist is recommended for an inflight start
OIL PRESS amber band?
Indicates the caution range and is only displayed on the ground below 80 knots
OIL PRESS red line?
Oil pressure operating limit
Vertical position of red line will vary with N2 RPM
OIL QTY indication?
Usable oil quantity in quarts
White numbers on black background for normal quantity
Black numbers on white background for low quantity
LO displayed in white when low
Engine VIB display?
Normal is white numbers on a black background
If high vibration, displayed as black numbers on a white background
If vibration source unknown?
BB displayed and the number refers to the average vibration
Engine VIB high band?
Level at which automatic display of the secondary engine indications will occur
Briefly describe the EECs
Each engine controlled by a separate full authority EEC
The EECs monitor thrust lever position to automatically control the engines
The EECs use N1 to set thrust and operate in normal or alternate modes
How are the EECs powered?
During the engine start, the EECs are powered by aircraft power
At a certain RPM the Permanent Magnetic Alternators (PMAs) are able to provide sufficient power
EEC Normal Mode?
EEC sets N1 according to thrust lever position
EEC switch in ALTN?
EEC switch is OFF, EEC switch sets thrust using N1 RPM as the controlling parameter
Alternate modes of the EEC?
What will make the EEC automatically shift to alternate mode?
The alternate mode operates in either soft (automatic) or hard (manually selected) mode
The EEC will shift to soft alternate if required signals to operate in normal mode are lost
NORM and ALTN both illuminated in EEC switch?
Soft alternate mode
At a fixed thrust lever position, the thrust will not change
ALTN (amber) in EEC switch
Hard alternate mode selected manually by pressing EEC switch
Thrust may change to set the commanded N1 when ALTN is manually selected
Will the autothrottles remain engaged in either alternate EEC modes?
Yes, in both
How does switching between normal and alternate mode affect thrust level?
Alternate mode will provide equal or greater thrust than the normal mode for the same thrust lever position
Thrust protection in alternate EEC mode?
No. Max rated thrust is reached at less than full forward thrust lever position. Overboost is therefore a possibility
In this case, ENG LIMIT PROT L/R EICAS will appear
Are N1 and N2 overspeed protection available in alternate mode?
Yes
Where is ALTN mode overspeed protection located?
How does it work?
What happens if RPM limiting fails and overspeed condition persists?
The overspeed protection is provided on the N2 shaft. N1 protection is indirect, from the N2 location.
As the N2 approaches the red line limit, the EEC will command a reduced fuel flow
If the RPM limiter fails, the EEC will close the fuel valve and shut down the engine
ENG RPM LIMITED L/R?
ENG LIMIT EXCEED?
RPM limiting in effect
The RPM red line limit has been exceeded
Is there a provision to overboost the engines?
Yes, advancing the engine thrust levers to full forward in alternate mode provides some over boost
Only to be considered in emergency situations when all other options failed and terrain contact is imminent
What is thrust ramping?
Is it available in ALTN mode?
EEC slowly increases thrust up to takeoff seeding, to compensate for high stress loads on fan blades due to crosswinds and low ground speed
No
Thrust control malfunction accommodation?
On ground, EEC shuts down engine if thrust lever is at idle and the engine is not decelerating normally
What is Thrust Assymetry Protection (TAP)?
Provides assymetric thrust protection during takeoff or go around by limiting thrust on the higher thrust engine
Also available in alternate mode of the EEC
How does TAP work?
Reduces thrust on operating engine, ensuring there is enough rudder for directional control
Reduces thrust when airspeed drops below V2 on a takeoff or below VREF on a go-around
Will increase the thrust again once airspeed has increased
Does TAP only function at speeds below VREF on go-around?
Only exception is during a light weight go-around at weights < 335,000#. TAP will reduce thrust slightly right at VREF
Does TAP degrade aircraft performance when operating?
No. The climb gradient actually increases when TAP is active, because the additional thrust assymetry increases drag
Do the thrust levers move during TAP operation?
No. The N1 tic marks decrease, but the thrust lever stays constant
THRUST ASYM PROT EICAS?
Thrust Asymmetry Protection function is inoperative
What is the transient bleed system?
Unloads the compressor during engine acceleration for increased engine stall margin
What is the TBV?
Transient Bleed Valve
A fuel operated valve controlled by the EEC, based on N2 speed
Unloads the compressor during acceleration to increase stall margin
ENG TBV CLOSED L/R
The TBV fails to open when commanded
ENG TBV OPEN L/R EICAS?
TBV remains open when commanded to close
Occurs on the ground below 80 kts
Accompanied by ENG TBV OPEN L/R status message
If the TBV fails to open prior to thrust reverser deployment?
If it fails to open during thrust reverser deployment?
The associated thrust reverser will be inhibited
The associated thrust reverser will be limited to idle
ENG REV LIMITED L/R?
The associated TBV has failed to open during reverser operations
What could happen if TBV fails in OPEN position?
May lead to an EGT exceedance and associated flight deck alerts
When is approach idle commanded?
Selected inflight when flaps 25 or greater
OR
Landing gear selected down
When is icing idle commanded?
When engine anti-ice is on
ICI function?
Ice Crystal Icing
The EEC contains a function to accommodate for ICI conditions
It will operate for at least 30 minutes and then 15 minute additions if ice crystals conditions still exist
Where is ICI function commanded?
Only above 30,000 feet
Turns off descending through 28,500 feet
At cruise levels above 30,000 feet and the engines seem to be fluctuating a bit. Is this normal on a 787-9?
Yes, it could be the ICI function of the 787-9 EEC. Each EEC ICI function independently changes engine parameters, so the engines might fluctuate independently
What is the power requirement for simultaneous engine start?
APU must be running with both APU generators operational. If power is inadequate, the second command start will be ignored
Load shedding during engine start
Is there load shedding during every start?
How do you view load shedded systems?
Yes, loads shed during every engine start.
Items can be viewed on their respective synoptic, as well as a majority of items spread on the electrical synoptic
ENG STARTERS L/R EICAS?
Both starters on the respective engine have failed
When is a red maximum start limit line indicated on the EGT gauge?
FUEL CONTROL switch moved to CUTOFF
The engine N2 RPM is below idle and the respective fire switch is not pulled
How do you initiate the autostart sequence?
Rotate the L START selector to START
Move the L FUEL CONTROL switch to RUN
Rotate the R START selector to START
Move the R FUEL CONTROL switch to RUN
During a ground start, what errors does the autostart monitor and correct for?
Compressor stall
High EGT
Hot start
Hung start
Loss of one starter
No EGT riSe
Start time exceeded
On the ground, the EEC will outright abort an autostart for (3 items):
What will be the indication?
Loss of both starters
No N1 rotation
No oil pressure rise
Indication is ENG AUTOSTART EICAS
On the ground, If EEC unable to correct for ___ ____ or ____ ______, the EEC will cancel the autostart.
_______ ________will be displayed
Hung start
Compressor stall
ENG AUTOSTART (L/R)
What is the ground limit for engine start attempts?
The EEC will limit it to three start attempts
In flight, will the EEC abort start attempts?
No. It will temporarily discontinue a start, or take corrective action, but it will not abort a start
In flight, what will the EEC discontinue the start temporarily for?
If a preset EGT between start EGT and takeoff EGT is reached
A hung start is detected
When is the inflight start envelope information displayed on the EICAS?
An engine is not running (N2 is below idle)
An engine is shutdown in flight and the engine fire switch is not pulled
What does the inflight start envelope indicate?
The airspeed range necessary to ensure an inflight start at the indicated flight level
What prompts the secondary engine indications to be displayed automatically in flight?
Engine is not running (N2 below idle)
OR
FUEL CONTROL switch moved to CUTOFF
Magenta X-START below N2 indication?
X-START is the starter assist indication
Airspeed is below that for a windmilling start
Autostart will continuously attempt inflight starts until:
The engine starts
Pilot aborts by placing FUEL CONTROL switch in CUTOFF (and placing START switch in NORMAL if starter assisted attempt)
How many igniters are in each engine?
How many fire during inflight starts?
How are they powered?
What is the backup power source?
There are 2 igniters in each engine
The EEC controls which ignited
Both igniters fire during an inflight start
Normally powered by DC power
Backup power is standby power
When does auto-relight system activate?
Anytime on the ground or in flight whenever an engine is at or below idle with FUEL CONTROL switch in RUN
What scenarios will the EEC automatically switch on both igniters?
Engine flameout
Engine rollback
Igniters switch off when RPM back at idle
What happens in event of sub-idle engine stall?
Fuel is shut off for one second
Fuel schedule then reduced to help engine return to idle
At idle, fuel schedule returns to normal
When is fuel spar valve open?
When fire switch is in and either
START selector in START
OR
FUEL CONTROL switch in RUN
When is Engine Fuel Valve open?
When commanded by EEC, provided the Engine Fire Switch is in and the Fuel Control Switch is in RUN
Are there crew procedures based on low oil quantity?
No. There is no minimum oil quantity limit
Low oil quantity display?
Will cause automatic secondary engine display
Will show reverse indication: black numbers on a white background
Can thrust reverser be deployed without engine running?
No. Requirements are:
Engine has to be running
Aircraft must be on ground
What ancillary actions are caused by pulling up the thrust reverser?
The autothrottle disengages
The auto speed brakes deploy
REV in amber?
In green?
REV (amber) indicates the thrust reversers are in transit
REV (green) indicates the thrust reversers are fully deployed
ENG REV LIMITED L/R?
Reverser cannot deploy when commanded
OR
Can only deploy with reverse limited to idle
ENG REVERSER L/R
Only displayed on ground,
Indicates system fault
ENG REV AIR/GND
Air/ground logic that prevents inflight reverser deployment has failed
ENG REV COMMANDED L/R
In flight and associated reverse lever not in down position
When a vibration value of ____ units is reached, the secondary engine parameters are automatically displayed
4 units
Engine failure alert system?
What is the indication?
Provides alerts when actual engine performance is less than commanded during all phases of flight
Red ENG FAIL on both PFDs and HUDs
Voice annunciation: “ENGINE FAIL”
Master Warning lights
What are the takeoff speed parameters for the engine failure alert system?
Airspeed between 65 kts and 6 kts prior to V1
ENG FAIL L/R EICAS?
An engine unexpectedly decelerated to less than idle speed
Message will remain until engine recovers or FUEL CONTROL to CUTOFF
ENG THRUST L/R
Engine is producing less than commanded thrust and actual thrust is not increasing
Engine is producing more than commanded thrust and actual thrust is not decreasing
Current airspeed greater than V1-6 knots
Accompanied by master caution light and aural chime
Is there a manual start option for the engines?
No. Only autostart.
What provides engine rotation during start?
The two starter/generators are energized and drive the N2 shaft through the accessory gearbox
The START selectors control:
They control the starter motors
The FUEL CONTROL switches control:
They control the ignition and the fuel flow during start
Simultaneous engine start is only possible with:
Both APU generators on line
When doing a simultaneous engine start, how long should one delay in selecting the second START selector to STATT?
Minimum of five seconds
What indications on EGT and N2 gauges during engine start?
A red start limit line is indicated on the EGT gauge while N2 is below idle
White AUTOSTART is indicated above the N2 value until engine is at idle, when it changes to a green RUNNING indication, lasting 30 seconds
ENG STARTERS L/R EICAS?
Both starters on an engine failed
THRUST ASYM PROT EICAS?
TAP is inoperative
When N1, N2 or EGT exceeded, what are the indications when return to normal range?
Only the box remains red
The red box can be cancelled by pressing the CAC/RCL switch on a DSP
(It can also be recalled by pressing the switch again)
