7 - Engine, APU Flashcards
APU Selector - ON (4)
- opens APU fuel valve and inlet door
- arms APU bleed air isolation valve
- activates DC or AC fuel pump
The APU drives ___ generator(s) capable of supplying the entire electrical load of the airplane for normal ground operations. Electrical power __(is/is not)__ available in flight.
2
is NOT
An APU start requires both the ______ and _____
main and APU batteries
Rotating the APU selector momentarily to START begins the start sequence. The ____ and _____ open simultaneously. Starter engagement occurs when _______ is fully open. The start sequence continues with ignition, lightoff, and engine acceleration to rated speed
fuel valve
inlet door
inlet door
The EICAS memo message ______ is displayed when the APU selector is ON and APU N1 RPM exceeds ____ N1
APU RUNNING
95% N1
Rotating the APU selector to OFF begins the shutdown cycle by closing the ______. The APU continues running unloaded for a ______ cooldown period. When the cooldown period finishes, the APU shuts down.
APU bleed air valve
60 sec
If the Battery switch is positioned OFF prior to _____, the APU will shut down immediately
completion of the cooldown period
A complete shutdown sequence with fire detection capability can be assured by waiting at least _______ after the APU selector is rotated to OFF before placing the battery switch OFF.
If a limit is exceeded or a fire detected, the APU
_____
2 mins
shuts down immediately
TO 1
D-TO 2
derate one takeoff thrust
derate two assumed temperature derated takeoff thrust
Thrust Reverser Indication:
REV (amber) -
REV (green) -
in transit
fully deployed
EGT indication:
- (white) -
- (amber) -
- (red) -
normal operating range
continuous limit reached
start or takeoff limit reached
During TO or GA, EGT indication remains white for ______, or for ______ if one engine fails or is shut down, when continuous EGT limit is reached or exceeded
5 min
10 min
EGT Red Line: displayed (red) - ______ or _____
takeoff EGT limit
multiple engine in-flight start limit
EGT Start Limit Line
displayed (red): ________ until _________
with Fuel Control switch in CUTOFF
N2 reaches a predetermined RPM
Secondary Engine Exceedance Cue on Primary EICAS displayed (cyan) - VVVVVV
• ____________
• ____________
• ____________
- secondary engine parameter exceedance is occurring
- no longer displayed when exceeding parameter returns to normal operating range
- replaces status cue if displayed
The In-Flight Start Envelope displays on Primary EICAS (magenta) showing _______ when ______
airspeed range for an in-flight start at the current flight level or maximum flight level, whichever is lower
the respective Engine Fire switch is in and a Fuel Control switch is in CUTOFF
When the Fuel Control Switch is in CUTOFF, Fuel-on Indicator on Secondary EICAS (magenta) indicates _______
minimum N2 RPM to move Fuel Control switch to RUN during engine manual start
Engine Vibration Source with the highest vibration displays on Secondary EICAS:
FAN -
LPT -
N2 -
BB -
Fan
Low Pressure Turbine
N2 rotor
broad band (source is unknown and average vibration displayed)
Crossbleed (X-BLD) Start Indication on Secondary EICAS indicates crossbleed air is recommended for in-flight start (magenta) if: ______ and _____
in-flight start envelope displayed
airspeed lower than required for a windmilling start
Partial secondary engine indications will be displayed when the secondary engine
display is not selected and _______
a limit or operating parameter has been reached
an oil quantity differential is exceeded
What happens; FUEL CONTROL Switch RUN
Autostart switch ON) - (2/3
- opens spar fuel valve
- opens engine fuel valve
- EEC sequences start valve, fuel metering valve, and igniter operation
What happens; FUEL CONTROL Switches RUN
Autostart switch OFF) - (3
- opens spar and engine fuel valves
- opens fuel metering valve
- energizes igniters
What happens; FUEL CONTROL Switches - Cutoff (4)
- closes fuel valves
- removes igniter power
- commands respective hydraulic demand pump to operate when Demand Pump selector in AUTO
- unlocks Engine Fire switch
Engine START Switches (bleed/start valves):
Pull (Autostart switch ON) - (2)
Pull (Autostart switch OFF)- (2)
Releases at ___ N2 RPM - (2)
(ON) -
• arms start valve
• opens engine bleed air valve
(OFF)-
• opens start valve
• opens engine bleed air valve
50%
• closes start valve
• closes engine bleed air valve
Engine START Switches release at ______
50% N2 RPM
- start valve closes
- engine bleed air valve closes
Standby (STBY) IGNITION Selector NORM -
What is the power source?
What is the backup source?
1/2 -
- AC power system supplies power to selected igniters
- standby power system supplies power continuously to all igniters if AC power system is not powered
1 or 2 - standby power system supplies power continuously to respective igniters
What happens; Continuous (CON) IGNITION Switch - ON (2)
- selected igniters operate continuously
* commands approach idle minimum
AUTO IGNITION Selector - SINGLE, which igniter(s) is used for start?
Ground -
Inflight -
- EEC alternates igniter 1 and igniter 2 after every second ground start
- EEC selects both igniters for in-flight start or flameout
AUTO IGNITION - Selected igniters operate when any of the following occur: (4)
- during start when N2 RPM less than 50%
- trailing edge flaps out of up position
- nacelle anti-ice ON
- engine flameout
Engine Start Lights : Illuminated -
start valve is open
What primary engine indications always display on primary EICAS ?
N1 and EGT
EGT indications are inhibited from changing color to amber during takeoff or go-around for ______ after the TO/GA switch is pushed, even though EGT reaches the continuous limit.
The amber color change is inhibited for ______ if one engine fails or is shutdown
5 min
10 min
The EGT indicator has a ______ displayed by a red line. The indication changes color to red if EGT reaches the ______
takeoff limit
takeoff limit
An engine indication changes color back to white when the parameter returns to the normal operating range. The box enclosing the digital indicator remains red as a reminder of the exceedance. The red box color can be selectively canceled to white or recalled to red by _______
pushing the cancel or recall switch on the EICAS Display Select panel
The oil quantity indication changes color to amber if _____ or if _____
low oil quantity is detected
the oil quantity differential is exceeded
N1 Operating Limit Line - Maximum N1 Line - Reference N1 - Target N1 - Command N1 Indicator -
Red Amber Green - (thrust ref selected by FMC) Magenta - (commanded by FMC) White - (commanded by thrust lever position)
Secondary engine indications display in partial format if _______ when the secondary engine display is not selected
a secondary engine parameter exceeds the normal operating range
The EEC has two control modes: ____ and ____
In both modes, the EEC uses _____
as the controlling parameter for setting thrust.
normal and alternate
N1 RPM
Electrical power for each EEC is provided by ______ mounted on the engine accessory gearbox
an alternator
What corrections must the pilot make for OAT and pressure in order to maintain constant thrust?
What corrections must the pilot make when using NAI and or WAI?
When the engine is stabilized, the EEC keeps thrust constant independent of outside air temperature and pressure.
The EEC adjusts thrust for changes in nacelle and wing anti-ice and airplane pressurization bleed requirements.
The EEC continuously computes maximum N1. Maximum thrust is available during ____ phase of flight by moving the Thrust lever to _____
any
the full forward position
Alternate mode __(does/does not)__ provide thrust limiting at maximum N1. Maximum N1 is reached at a Thrust lever position ______
does not
less than full forward
Do thrust levers need to be adjusted to maintain desired thrust as environmental conditions and bleed requirements change?
EEC normal mode -
EEC alternate mode -
No
Yes
Does thrust change when EEC automatically transfers control from normal mode to alternate mode?
Does thrust change when alternate mode is selected
manually?
no change
thrust increases
(When thrust is greater than idle, the Thrust lever should be moved aft prior to manually selecting alternate mode so thrust does not exceed maximum
N1)
If the EECs are in the alternate mode, advancing the Thrust levers full forward
______
provides some overboost and should be considered only during emergency situations when all other actions have been taken and terrain contact is imminent
If control for any EEC transfers from normal to alternate, the autothrottle ______
Can autothrottle be activated after all EECs are manually transferred to alternate mode?
disconnects
Yes
Approach idle is selected in flight when: (3)
- nacelle anti-ice is ON
- flaps are in landing position
- Continuous Ignition switch is ON
Approach idle decreases acceleration time for go-around
The start limit remains displayed until _____
N2 reaches a predetermined RPM (idle)
An in-flight start envelope displays (where) when a Fuel Control switch is moved to CUTOFF in flight.
The in-flight start envelope displays (what)
to ensure an in-flight start at the current flight level.
on primary EICAS
the airspeed range
If the current flight level is greater than the maximum start altitude on the in-flight start envelope, ______ display
X-BLD displays next to _____ if crossbleed air is necessary for start
the maximum start altitude and related airspeed range
the N2 indication
During Auto Start the EEC opens the start valve and the Start light illuminates. At a predetermined N2, the EEC _____.
\_\_\_ igniter(s) is/are normally selected for ground start, while \_\_\_ igniter(s) is/are selected for in-flight start.
opens the fuel metering valve and energizes the selected igniter
one
two
Starter cutout occurs at ______
50% N2
During autostart, the EEC monitors _____ and ______ until the engine stabilizes at idle
EGT
N2 RPM
During ground start, the autostart system monitors engine parameters and aborts
the start for any of the following malfunctions: (3)
- hot start
- hung start
- no EGT rise
The autostart system does not monitor ______ or _______
oil pressure
N1 rotation
If the EEC detects no EGT rise, it _______
The engine motors for ______ and then _______
cuts off fuel and ignition
30 seconds
applies fuel and ignition to both igniters for another attempt
If the EEC detects no EGT rise, it makes ___ attempts before aborting the autostart sequence.
The engine motors for ______ before the start and engine bleed air valves close
3
30 sec
If there is an EGT rise, but the EEC detects an impending hot start or a hung start before starter cutout, it ______
The EEC makes ___ attempts before aborting the autostart sequence
The engine motors for ____ before the start and engine bleed air valves close
cuts off fuel, adjusts the fuel schedule, then reapplies fuel for another attempt
3
30 secs
If the EEC detects an impending hot start or a hung start AFTER starter cutout, _______
the autostart sequence is aborted immediately
The engine does not motor
During IN-FLIGHT flameout and/or start, the EEC ________
The EEC allows the EGT to _______ before cutting off fuel
cuts off and then reapplies fuel.
increase past the start limit to the takeoff limit
During in-flight flameout and/or start the autostart sequence is not automatically aborted. The EEC continues making start attempts until ________
the engine stabilizes at idle or the Fuel Control switch is moved to CUTOFF
Auto relight is provided if _______
a flameout is detected
A rapid decrease in N2 occurs, or N2 is less than idle RPM. Both igniters are used
Manual Start: Pulling the Start switch out (2) ______
When N2 RPM reaches ______, the Fuel Control switch is moved to RUN
opens the start and engine bleed air valves
the fuel-on indicator
During a manual start what happens when the Fuel Control switch is moved to RUN? (4)
the fuel metering, spar and engine fuel valves open and the selected igniter(s) energizes
(one igniter is normally selected for ground start while two igniters are selected for in-flight start)
Ignition is selected for each engine when _______, _______, or _______
related Start switch is OUT
nacelle anti-ice is on
flameout is detected
Ignition is selected for all engines when
_______ or ______
trailing edge flaps are out of the up position
Continuous Ignition switch is ON
The ______ is the normal power source for ignition
The ______ provides a backup source
AC power system
standby power
When the Standby Ignition selector is in 1 or 2, the _______ system supplies power continuously to the related igniter regardless of Auto Ignition selector position or EEC selection
standby power system
Fuel is supplied under pressure from pumps located in the fuel tanks. The ______ add additional pressure to the fuel when _____
first and second stage engine fuel pumps
the N2 rotor is turning
_______ heats the fuel as it flows through the _______ heat exchanger
Engine oil
fuel/oil
The oil is cooled by _____ as it flows through the ______
fuel
fuel/oil heat exchanger
An oil filter removes contaminants. If the
filter becomes saturated with contaminants, _______
oil bypasses the filter
During cruise, oil quantity displays on EICAS whenever _______
oil quantity on one engine differs from any other engine by a predetermined amount
(when this occurs, the lowest oil quantity is shown in magenta)
During cruise if there is an increase in oil
quantity during cruise caused by ________ or ________ the EICAS oil partial engine indications display may appear.
indicator malfunction
leaking fuel/oil heat exchanger
(however, for this condition the low quantity displays in magenta, even though that oil quantity may
be normal
Each thrust reverser is powered by ______ from _____
bleed air
the related engine
(only on the ground)
What unlocks and extends the reversers aft to the deployed position?
bleed air from the related engine
Is thrust reverse available when associated Engine Bleed Switch is OFF?
Yes
HP bleed valve and PRV open for thrust reverse, unless PRV closed by:
• prior or present bleed air overheat, or
• start valve not closed
N 1 lines:
Red - Amber - Green - Magenta - White -
operating limit max limit reference target (FMC) thrust lever position
EGT lines:
Red -
Amber -
Red -
takeoff/multiple engine inflight start
continuous
start limit (fuel control switch in cutoff)
At what speed does the A/T engage in HOLD?
When does it return to THR REF?
65 kts
400 ft
APU Battery supplies power to ____ (5)
MAIN Battery supplies power to ____ (3)
- Starting
- Controller
- DC Fuel pump
- Air inlet door
- Fire detection
- Controller back up power
- Fuel valve
- Fire extinguishing
Maximum altitude for APU Bleed for one pack ____ ?
Maximum altitude for APU usage ____ ?
15,000 ft
20,000 ft
