ENGINE Flashcards by Laura Hofherr

ENGINE

General Electric CF34-8E5
High-bypass
Dual rotor turbofan, fully integrated with a nacelle and thrust reverse.
1 stage fan driven from 4 stage LP turbine (1/4) represents N1
10 stage axial flow compressor with variable geometry driven from 2 stage HP
turbine (10/2) represents N2
engine oil qty max and usable?

Engine Oil

max: 10.5 qts
usable: 7.2 qts

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What types of engines are on the aircraft?

How much thrust do the CF-34-8E5 engines produce?

What types of engines are on the aircraft?
Two General Electric CF-34-8E5
Hi-bypass, 2-spool, axial-flow, turbo-fan

How much thrust do the CF-34-8E5 engines produce?
13,000-14,200 lbs. (ISA)

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Describe N1 spool

Describe N2 spool

How many igniters per engine?

Describe N1 spool
Single-stage fan
4-stage LP turbine

Describe N2 spool
10-stage compressor (gas generator)
2-stage HP turbine

How many igniters per engine?
2 per engine

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How many igniters activate for engine start?

How many igniters activate for engine start?
Ground 1 igniter ( switch in AUTO )
Flight 2 igniters ( switch in AUTO )

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What happens when the ignition switch is selected to OVRD?

Can the igniters be turned off during flight?

What happens when the ignition switch is selected to OVRD?
Activates both igniters on the ground or in flight

Can the igniters be turned off during flight?
The switch may be moved to the OFF position but the FADEC disregards the command
The OFF position is used for dry motoring on the ground only

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What controls the engine?

Engine FADEC Electrical Power?

Is only one FADEC channel used every flight?

What controls the engine?
A two-channel FADEC
One channel is active and the other channel remains in standby as a backup

Engine FADEC Electrical Power
DC ESS Bus powered below 50% N2
Above approximately 50%N2 the FADEC is powered by thePermanent Magnet Alternator (PMA).

Is only one FADEC channel used every flight?
No. They automatically alternate with each engine start

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What does the cyan line on the N1 gauge represent during approach? When does it appear?

What does the cyan line on the N1 gauge represent during approach? When does it appear?
The minimum N1 for bleed requirements in icing conditions
Configured for landing < 1200’ RA (when anti-ice is ‘ON’)

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What sources are available for engine starting?

What sources are available for engine starting?
APU
Ground source (huffer cart or air bottle)
Opposite engine (crossbleed start)
Windmill start

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Does the FADEC provide engine start protection?

Only on the ground for a

Does the FADEC provide engine start protection? 
Only on the ground for a 
Hot start, 
Hung start 
No light-off

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Engine Starter Limits attempts

1 90 sec ON, 10 SEC OFF
2 90 sec ON, 10 SEC OFF

3 90 sec ON, 5 MIN OFF
4 90 sec ON, 5 MIN OFF
5 90 sec ON, 5 MIN OFF

120 sec ON IN FLIGHT

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Dry Motoring Duty Cycle Limits

1 90 sec ON / 5 min OFF

2 30 sec ON / 5 min OFF (1)
3 “
4 “
5 “

Note: (1) After 5 sequential motorings, cycle may be repeated following a 15 min cool down

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APU Starter Duty Cycle

1 1 min ON / 1 min OFF
2 1 min ON / 1 min OFF

3 1 min ON / 5 min OFF

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What will the FADEC automatically do in case of a hot start on the ground?

What will the FADEC automatically do in case of a start on the ground?
FADEC will not allow FF if ITT >120°C
FADEC will automatically dry motor engine and introduce fuel when ITT <120°C

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Describe the engine start sequence • Start switch momentarily to START:

Describe the engine start sequence • Start switch momentarily to START: 
7%   N2Ignition 
20% N2Fuel flow 
20% N2+ 5 sec Light-off 
50% N2  Ignition off 
50% N2  Engine stabilizes: Starter cutout 
N1  	 
27% 
ITT  	 
460°C 
N2  	 
62% 
FF  	 
550 lbs/hour
Oil Pressure  
>25 psi

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What does WML mean on the engine indications?

What does WML mean on the engine indications?
Windmilling engine
The FADEC has detected a flame-out and is attempting an auto re-light, or
An assisted start has been commanded

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What provides underspeed and overspeed protection? •

What provides underspeed and overspeed protection? •
The FADEC via the FMU
Approximately 52% N2 and 102% N2 respectively

What happens after 3 overspeed detection events?

FADEC will not relight the engine

What heats the fuel and cools the engine oil?

Fuel/Oil heat exchanger

What is ATTCS? What controls it?

What is ATTCS? What controls it?
Automatic Take-off Thrust Control System
Provides max thrust reserve (RSV) according to current rate previously selected via the MCDU
FADEC controlled

What will trigger an ATTCS event?

What will trigger an ATTCS event?
N1 difference >15% between engines
Engine failure during TOGA
Windshear detected

When is thrust reverse available?

When is thrust reverse available?
Weight-on-wheels (ground use only)
Upon Landing, if thrust reversers have been used, reverser should be set to MIN REV at 60 KIAS, and be closed by 30 KIAS.
A Go-Around Maneuver should not be attempted after Thrust Reversers have been deployed

What happens if a thrust reverser inadvertently deploys?

FADEC limits respective engine thrust to IDLE

What engine thrust rating(s) may only be used for 10 minutes?

What engine thrust rating(s) may only be used for 10 minutes?
TO-1
TO-1 RSV (TL beyond TOGA)
GA (two-engine go-around)
GA-RSV (one-engine go-around or windshear)

What is FLEX?

What is FLEX?
Reduced takeoff thrust based on assumed temperature (telling the FADEC that it is warmer than it actually is so it will reduce the thrust)

Can the FLEX thrust be reduced lower than CLB thrust?

Can the FLEX thrust be reduced lower than CLB thrust? | No

START/STOP SELECTOR KNOB STOP:

START/STOP SELECTOR KNOB STOP: STOP: commands the FADEC to shut down the engine, provided the associated thrust lever is in the IDLE

FUEL/OIL HEAT EXCHANGER

FUEL/OIL HEAT EXCHANGER The fuel-cooled oil cooler (FCOC) maintains the oil temperature within an acceptable range and heats the engine fuel to prevent freezing. Each engine has an independent lubrication system.

STARTING SYSTEM

STARTING SYSTEM (1) The engine starting system consists of: (a) Air Turbine Starter (ATS). (b) Starter control valve (SCV). (2) The pneumatic system provides bleed air to the ATS to rotate the rotor speed and start the engine. (3) The FADEC opens the Starter Control Valve (SCV), providing bleed air from the APU, a ground source, or the opposite engine. The Air Turbine Starter (ATS) is a turbine that accelerates the engine to a self-sustaining rpm level. (4) The FADEC closes the SCV when the starter cutout speed is reached.

Ignition System

Ignition System (1) The ignition system provides an electrical spark for fuel combustion during ground/in-flight start attempts and for automatic re-light. (2) The FADEC energizes one igniter for on-ground engine starts and both igniters for in-flight engine starts. (3) When the ignition selector knob is placed on the OVRD position, both igniters on each engine are energized. Igniters 1B that is correct and 2B are connected to SPDA 2. In case of SPDA 2 failure, setting the selector knob to OVRD energizes at least the igniter A.

ATTCS Activation Logic Controlled by the FADEC Automatically provides max engine thrust RSV whenever it is armed, TL in TOGA, and one of following conditions occurs:

ATTCS Activation Logic Controlled by the FADEC Automatically provides max engine thrust RSV whenever it is armed, TL in TOGA, and one of following conditions occurs: (1) The RSV mode is manually activated by moving the thrust levers to MAX position whenever the ATTCS is engaged. (2) Whenever the ATTCS is activated, the green ATTCS indication on the EICAS disappears and the cyan thrust mode will be displayed with an additional “RSV” indication. (3) Difference between both engine N1 values is greater than15%; (4) One engine failure during takeoff; (5) One engine failure during go-around; (6) Windshear detection.

FLEXIBLE TAKEOFF

FLEXIBLE TAKEOFF A. Flexible takeoff is a reduced takeoff thrust based on assumed temperature. B. All takeoff modes are eligible for a flexible takeoff.

Overspeed Protection

Overspeed Protection (1) Whenever N2 reaches 102% the FADEC automatically commands an engine shutdown. (2) In the event of 3 consecutive overspeed detection events within 30 s the FADEC will not relight the engine.

ITT Over Limit Protection During engine start if the ITT reaches its limit the FADEC automatically shuts off the fuel flow aborting the start sequence. In this case the start control valve is not automatically closed. Pilot intervention is needed to close the SCV by selecting the START/STOP switch to STOP.

Engine Start High ITT Prevention/OVER TEMPERATURE | DRY MOTORING

Engine Start High ITT Prevention/OVER TEMPERATURE (a) To improve the ITT control on engine ground starts the FADEC will not allow fuel flow if ITT is above 120. (b) In this case when the pilot sets the START/STOP selector to START the start control valve is commanded open but the fuel flow only starts when the ITT drops below 120. Automatic dry motoring occurs.

Fuel control system consists of

``` Fuel control system consists of FADEC FUEL METERING UNIT (FMU) PERMANENT MAGNET ALTERNATOR (PMA) ENGINE SENSORS VARIABLE GEOMETRY ACTUATORS (VG) OPERABILITY BLEED VALVE (OBV) ```

Fuel distribution system consists of

``` Fuel distribution system consists of Fuel pump Fuel filter Fuel manifold 18 fuel injectors ```

The FADEC will prevent fuel flow during ground start until ITT is at or Below_____? 120*C

Dry motor start until | Below 120C