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WorksheetsHHH - CFM56 Engine
Total questions: 66
Worksheet time: 33mins
Electronic Centralized Aircraft Monitoring (ECAM) gives the information to flight crew are:
Navigation Parameters.
Aircraft System Displays, Faults, Checklists and the current operational status of the aircraft.
Flight path information
Engine Warning Display (EWD) is divided into how many main areas:
The upper area is used for Main Engine parameters, Fuel on Board, and Slat/Flap position, and lower part not used.
The upper area is used for Main Engine parameters, Fuel on Board, and Slat/Flap position, and lower part is used for warning, caution and memo messages.
Upper and lower part used only for Engine parameters.
The engine forward mount is carrying the:
Anti-torque mount
Thrust, Vertical and side loads.
Thermal expansion loads.
The engine drain mast is used to collect the:
Unburnt fuels
Unused engine oil
Waste fluids and vaporise from engine systems and accessories.
The Drains are provided at the pylon rear part is to:
Remove any residual fluid like water, hydraulic, fuel.
Remove air.
Evacuate and vent overboard air and any residual fluids.
Fluids drained from the power plant are:
Fuel, oil or hydraulic
Fuel, oil or water
Fuel, oil, hydraulic or water
The FADEC system consists of :
A single Channel ECU with its peripherals for both engines
Dual channel ECU with its peripherals per engine.
Two computer for each engines
The function of the deactivation lever located on the HCU is to:
De-energize the isolation valve solenoid.
Isolate hydraulic supply.
Energized the isolation valve solenoid.
The System that controls the Engines at all operating conditions is:
Full Authority Digital Engine control (FADEC).
Engine Vibration Monitoring Unit (EVMU).
Engine Interface Unit (EIU).
The Engine Starter oil level checked by:
Multipurpose Control& Display unit (MCDU).
System Display Engine (SD-ENG) page.
Detailed Visual Inspection (DVI).
The CFM56-5B/P LP rotor (N1) is made of:
The fan and the booster compressor are driven by the five stage LP turbine.
Four stage compressor driven by a two-stage turbine.
Fan and a four-stage compressor driven by a four-stage turbine.
The CFM56-5B/P HP (N2) rotor is made of
9-stage compressor driven by a single stage turbine.
10-stage HP compressor driven by a 2-stage HP turbine.
12-stage compressor driven by a single stage turbine.
The CFM56-5B/P, the LP rotor assembly supported by:
N0 1, N0 2 and N0 3 (dual bearing).
N0 3 (dual bearing) and N0 4.
N0 1, N0 2 and N0 5.
The FADEC automatically selects a continuous relight:
In case of Engine Interface Unit (EIU) failure only.
If engine anti-icing is detected ON or EIU failure or engine flame-out.
In case of Electronic Control Unit (ECU) failure.
The purpose of the ENGINE MASTER SWITCH is:
To open or close the HP fuel Shut-Off Valve.
To command and reset the FADEC functions.
To open or close the HP fuel Shut-Off Valve and to command and reset the FADEC functions.
The ENGine MANual START push buttons to operate the corresponding start valves in:
The manual start mode or during an engine cranking.
The manual start mode.
During an engine cranking.
The compressor airflow control of the CMF56-5B/P includes:
The Variable Bleed Valve (VBV) system and the Variable Stator Vane (VSV) system.
The BSBV system, a VSV system and bleed valves at the 7th and 10th stages of the HPC.
The booster stage bleed valve system and a Variable Stator Vane (VSV) system.
Prior to performing maintenance on the thrust reverser:
The yellow hydraulic system must be depressurized.
Deactivate the thrust reverser by placing the lever in the inhibition position on the Hydraulic Control Unit (HCU).
Deactivate the thrust reverser by disconnecting the hydraulic supply lines.
The eng FADEC GND PWR is used to:
Enable the pilots to start the engines automatically.
Supply the computers dedicated to the engines when the engines are not running.
Enable the pilots to start the engines manually.
The purpose of the Fuel Return Valve (FRV) in the re-circulation system is:
To maintain engine oil, IDG oil and fuel temperature within limits.
To provide better fuel filtering.
To depressurize the fuel system at engine shutdown.
In maintenance, if the Inboard cowl opened for engine removal/Installation, the safety precaution to be followed is:
The slats must be retracted, and slat operation must be inhibited.
The slats may be extended.
Aircraft Electrical power must be removed.
The master chip detector used for ground inspection which is of an.
Electrical type and also has a visual pop-out indicator.
Operates only in differential pressure type.
The A320/321 engines throttle control levers:
Only be moved manually.
Automatically in auto-thrust mode
Can be moved manually or automatically.
The Reverse Thrust is available only on the:
Flight
Ground after landing.
Flight or Ground
The Engine Vibration Monitoring Unit function (EVMU) are:
Collects Vibration data from both engines and displayed on the ECAM.
Collects Vibration data from both engines and displayed on the MCDU.
Collects Vibration data from both engines, and displays it on the PFD.
The annular combustion chamber has:
1- igniter plug
4-igniter plugs known as A1, A2 and B1, B2
2-ignitor plugs known as A & B.
The annular combustion chamber has:
20 fuel nozzles
18 fuel nozzles
12 fuel nozzles
The main source of aircraft bleed comes from:
LP compressor.
HP compressor.
LP or HP as per customer demand
CFM 56-5B designed using modular concept, advantage of this concept is:
This engine is made of 4 primary modules.
Easy maintenance
As in A &B and Quicker return-to service
The ONLY engine powers complete SA Family(A318/319/320/321) is:
V2500
CFM56-5B
PW1100G
What is the one of the safety precautions observed during Engine Ground Run:
The entry corridor will be open when engine power is above the minimum.
The entry corridor will be open/closed when engine power is above the minimum.
The entry corridor will be closed when engine power is above the minimum.
What is the one of the safety precautions observed on Engine ignition system:
Do not do maintenance on the ignition system while the engines operate.
You can do maintenance on the ignition system while the engines operate.
Do not do maintenance on the ignition system while the engines operate, wait more than >5 minutes after shutdown.
What is the safety precautions observed during opening the engine cowls:
Always secure cowls with the hold-open rads and follow AMM wind limitations.
Make sure that the slats are retracted and install Warning notices in cockpit.
As in A & B follow AMM for additional information.
The Engine Fuel system is designed to supply Fuel Flow into the:
Combustion chamber, servo fuel for airflow control, engine clearance control and IDG cooling.
Directly to Engines only.
APU & Engines.
When Engine Master S/W is set to off:
HP and LP fuel shut off valves are closed.
HP, LP and Fuel Return Valve (FRV) closed.
HP/LP/closed and FRV closed by ECU.
If the engine is running Above 15% (>15%) then the FADEC powered by:
Aircraft Power supply.
The PMA (Permanent Magnet Alternator) supplies only channel A of ECU.
The PMA also called Control Alternator supplies ECU channels A & B
For Maintenance FADEC Gnd Power P/B on in the Maintenance panel will supply the power for:
Five minutes.
20 Minutes.
As long as the GND PWR P/B is in the ON position.
During Engine Dry cranking or wet cranking sequences:
Ignition Inhibited.
Ignition Available.
Only Ignitor A is available.
The Variable Stator Vane (VSV) is located at:
Rear of HP compressor.
Front of the HP compressor.
Middle of the HP compressor.
The Electronic Control Unit (ECU) is cooled by:
By a cooling fan built in.
By Ram Air cooling.
By Fan air cooling.
The N1 rotational Speed indication is shown in the ECAM-EWD by a:
Needle
Digital Indication.
Needle and an N1 digital display.
The EGT is sensed and averaged by:
Four thermocouple probes.
Six Thermocouple probes
Nine Thermocouple probes.
The oil quantity XMTR is located in the:
Oil Tank.
Oil line.
Oil filter assembly.
The PS 12 sensor measures the:
Dynamic pressure
Static pressure from the fan inlet.
Compressor pressure.
The Thrust reverser system is of the:
Static blockage type.
Aerodynamic blockage type.
Electrical blockage type.
The directional valve in T/R system is operated to:
Deploy only.
Stow only.
Deploy& Stow operation.
To command the thrust reverser, the ECU needs an A/C on ground signal supplied by:
Main Landing Gears.
LGCIUs
FMGC.
The Engine oil system includes:
A supply circuit.
A vent circuit.
A supply/Scavenge and Vent circuits.
If Fluid leaks are found during transit operations:
Clean it.
Refer AMM ATA 70-00 & ATA 29-00 for allowable limits.
Refer MEL.
The good practice in maintenance for Fan cowl doors:
Must remain either fully opened or fully closed and latched.
Never open the cowls in transit.
Never open the latches in transit.
If an Engine was ferried or subjected to an In-Flight Shutdown (IFSD) then:
That engine must be dried out.
Re-lubricated within 7 days.
The engine must be dried out and re-lubricated within 24 hours as per engine dry out procedure
The engine anti-ice air overboard discharge grill is located?
On the right-side fan cowl door.
On the lower right side of the inlet cowl.
At the bottom (5 o’clock position) of fan cowling
The engine oil servicing panel is located?
On the outboard side of the inlet cowl.
On the left side fan cowl door.
On the left side of the inlet cowl.
When the engine is running:
No person is allowed to get access to the engine.
Access to the engine is permitted within the Entry/ Exit corridor if power do not exceed min idle.
Access to the engine is permitted within the Entry/Exit corridor at all power rating.
The engine run up at Min idle can be carried out with:
Fan cowls opened and secured.
Both Reverser and Fan cowls opened and secured.
Non engine cowl opened.
Features of CFM-56-5B4 engine are:
Two spools, radial flow, high fan bypass ratio and mixed exhaust.
Two spools, axial flow, high fan bypass ratio and separated exhaust.
Two spools, axial flow, high fan bypass ratio and mixed exhaust.
Select the correct type of combustion chamber for CFM-56-5B4 engine?
Annular combustor.
Tubular combustor.
Reverse flow combustor.
The number of fan blades in one engine fan set?
Thirty-six (36)
Twenty-two (22)
Thirty-two (32)
The engine gear boxes are driven by which shaft?
N1 rotor.
N2 rotor via the transfer gear box.
N2 rotor.
CFM-56-5B4 engine comprise of:
9 HPC stages and 1 HPT stage
9 HPC stages and 2 HPT stage
10 HPC stages and 2 HPT stage
The hand cranking drive connects to?
LP rotor.
HP rotor.
Both LP and HP rotors.
How does the starter operate?
Electrically
Hydraulically
Pneumatically
The type is Engine ignition system?
Low voltage, high energy.
High voltage, low energy.
High voltage, high energy.
Which component provides the selection of ignition channel A/B?
The ECU.
The engine control panel.
The ECAM control panel.
Each engine equipped with?
One ignition system with two igniters.
Two ignition systems, each has two igniters.
Two ignition systems with two igniters.
Ignition system power supply is?
115 V from the aircraft.
115 V from engine generator.
28 V from the FADEC PMA.
