Escalafon 2025

The Ground and Auxiliary Power Control Unit (GAPCU) interfaces only with the Centralized Fault Display Interface Unit (CFDIU). True. False.

The GAPCU can transmit GCU fault data to the CFDIU via ARINC 429 data bus. True. False.

Maintenance tests on the GAPCU and GCUs can be initiated in-flight for diagnostic purposes. True. False.

The Constant Speed Motor/Generator (CSM/G) operates at 50 Hz frequency. True. False.

The Emergency Generator is activated via the blue hydraulic system only if the ________________. landing gear is compressed. landing gear is extended. aircraft is on the ground. landing gear is NOT compressed.

If AC BUS 1 and 2 are lost above a given airspeed, the Ram Air Turbine (RAT) will automatically ________________. retract. extend. turn off. decrease speed.

In the case of Generator 1 LINE OFF, which component opens?. Generator Line Contactor (GLC) 1. Battery Contactors. External Power Contactor (EPC). Generator Control Unit (GCU).

The emergency generator is powered by the ________________. blue hydraulic system. green hydraulic system. yellow hydraulic system. red hydraulic system.

What is the priority sequence for supplying the two normal AC BUSes (AC BUS 1 & AC BUS 2)?. Onside generator (IDG), external Power, APU GEN, offside generator. External Power, APU GEN, offside generator, onside generator (IDG). APU GEN, offside generator, onside generator (IDG), external Power. Offside generator, onside generator (IDG), external Power, APU GEN.

What is the purpose of the 115/26V AUTO TRANSFORMER in the AC distribution system?. Convert AC power to DC power. Supply power to the APU GEN. Connect AC ESS BUS to AC BUS 1. Convert 115V AC to 26V AC.

How is DC generation achieved in the aircraft's electrical system?. By Transformer Rectifiers (TRs). Through a generator driven by the APU. By converting AC power to DC power. Through an external power unit.

Which power source replaces a faulty main TR to supply the DC ESS BUS?. APU GEN. Battery 1. Battery 2. External Power.

What is the role of the Emergency Generator in the aircraft's electrical system?. Replace the main engine generators. Supply power during normal flight operations. Connect AC BUS 1 and AC BUS 2 in parallel. Provide power in case of failure of all main generators.

Which component is responsible for converting 115 volts to 26 volts for the sub-busbar?. Transformer Rectifiers (TRs). AC ESS SHED BUS. 115/26VAC Auto Transformer. Static Inverter.

What is the purpose of the Static Inverter in the electrical system?. Supply AC BUS 1 and AC BUS 2. Replace faulty main TR units. Convert DC to AC power. Supply power to the galley circuits.

The STATIC INVerter connected to battery 1 supplies the AC __________ BUS. AC BUS 1. DC ESS BUS. AC ESS BUS. AC STAT INV BUS.

The AC transfer circuit allows generators to be connected in parallel on the same bus. True. False.

The AC ESSential BUS can be supplied by AC BUS 2 if AC BUS 1 fails. True. False.

What is the purpose of the red manual inflation handle for the escape slide?. To open the door. To attach the survival kit. To initiate automatic inflation. To manually inflate the slide.

The inflation and deployment of the escape slide start automatically when the cabin door opens in the _____ mode. armed. open. locked. closed.

On the A319, A320, and A321, the forward and aft cargo compartments can have an optional _____ cargo loading system. automated. semi-automatic. manual. automated and manual.

The lower deck of the A318 is divided into three cargo compartments: the forward cargo compartment, the aft cargo compartment, and the _____ cargo compartment. central. bulk. rear. side.

To open a cockpit sliding window from the inside, push down the black push button on top of the _____ handle. locking. opening. closing. emergency.

The inflation and deployment sequence of the slide raft for the FWD and rear cabin doors is automatically initiated when the door is opened in the _____ configuration. closed. locked. armed. open.

The red manual inflation handle for the escape slide is located on the _____ side of the girt bar. left hand. right hand. top. bottom.

In case of a ditching, the survival kit must be connected to the slide raft before opening the _____. cockpit window. cabin door. overhead bin. emergency exit.

One or more Escape Slide/Slide Raft Cabin Passenger Door may be inoperative provided the associated door is considered _____. operational. closed. locked. inoperative.

The lower deck of the A318 is divided into three cargo compartments: the forward cargo compartment, the aft cargo compartment, and the bulk _____ compartment. storage. cargo. overhead. passenger.

The inflation and deployment of the escape slide for the forward and aft cabin doors are manually initiated. True. False.

The manual inflation handle for the escape slide is located on the left-hand side of the girt bar. True. False.

The emergency exit escape slides on the A319, A320, and A321 are stowed in containers in the aft cargo compartment. True. False.

The slide raft is pneumatically pushed open as soon as the cabin door handle is lifted. True. False.

The automatic inflation of the escape slide can be manually initiated by pulling the manual inflation handle. True. False.

On the A318, the lower deck is divided into two cargo compartments. True. False.

The emergency exit escape slides are installed above each door in the overhead stowage compartment. True. False.

The escape slide is of dual-lane type for the A318, A319, and A320. True. False.

The containers of the emergency exit escape slides are in the wing root fairing. True. False.

The manual inflation handle for the escape slide is used to open the cockpit sliding windows. True. False.

What is the function of the Fire Detection Unit (FDU) in the engine and APU fire detection system?. Monitors flight crew actions. Monitors engine thrust. Monitors fire extinguishing agents. Monitors detection loops.

How are the FIRE and FAULT signals from the fire detection system displayed to the flight crew?. On the engine control panel. On the flight deck alerts sounds. On the ECAM. On the overhead panel.

How many fire bottles are installed in each engine's pylon for fire extinguishing?. One. Two. Three. Four.

What is the purpose of the AGENT P/BSW switches for the engine fire extinguishing system?. Arm the extinguishing system. Control the aircraft's thrust. Monitor the engine's temperature. Test the fire detection system.

Each system in the FIRE detection has __________ detection loops. one. two. three. four.

The guarded FIRE P/B switches are used to give FIRE indication and __________ the related systems. arm. disarm. monitor. activate.

The discharge of each fire extinguisher bottle for the engine is controlled by a related __________ switch. FIRE P/B. FIRE warning. AGENT P/BSW. discharge.

On the A320, how many fire extinguisher bottles are installed in the AFT cargo compartment as part of the optional system?. one. two. three. four.

Lavatory smoke detection is monitored by the SDF integrated in the __________. AEVC. FWC. CIDS. fire extinguisher.

The lavatory smoke detector sends __________ warnings to the FWC. FIRE. SMOKE. FAULT. ALERT.

Each fire detection loop for the CEO engine contains __________ detector elements. one. two. three. four.

The cargo compartment fire-extinguishing agent is discharged into the FWD compartment through __________ nozzles. one. two. three. four.

What causes the engine or APU to shut down when the FIRE pushbutton is released?. Loss of fuel supply. Electrical failure. Fire extinguishing. Thrust reduction.

What are the roles of the AGENT P/BSW switches in the fire extinguishing system?. Control extinguisher discharge. Control engine thrust. Monitor cabin temperature. Monitor avionics equipment.

What action is taken on the ground when an APU FIRE warning occurs?. APU is automatically shut down. APU continues normal operation. APU fire bottles are discharged. APU is restarted immediately.

What does the avionics SMOKE detector specifically detect?. Fire in the cabin. Smoke from the engines. Overheating of avionics equipment. Smoke from the lavatories.

How is the cargo compartment smoke detection system monitored?. By the AEVC. By the FWC. By the AGENT P/BSW switches. By SDF (Smoke Detection Functions) on CIDS.

How many smoke detectors are installed in each cavity of the cargo compartments?. One. Two. Three. Four.

What triggers the automatic discharge of the fire extinguisher in the lavatory waste bin?. Fire in the adjacent lavatory. High cabin temperature. Presence of smoke. Fire.

How does the FDU generate a fire warning signal in case of a flame or hot gas detected?. Closes the INTEGRITY switch. Opens the ALARM switch. Closes the ALARM switch. Generates a fault signal.

How many detection loops does the engine Fire Detection Unit (FDU) have?. One. Two. Three. Four.

What does the FDU do if both loops are broken due to a torching flame?. Generates fire warning signal. Generates fault warning signal. Shuts down the engine. Sends inert gas.

In which situations is the detection fault logic based on a dual loop failure activated?. Fire on loop A, fault on loop B. Fire on loop B, fault on loop A. Total loss of detection system. Both loops working properly.

What components are responsible for fire detection in the engines and APU?. FIRE switches and P/B switches. FWC and ECAM. ALARM and INTEGRITY switches. Detectors and loops.

What must be done if an engine or APU LOOP A or LOOP B fault is detected?. Disregard the fault and continue operations. Perform a fire test. Isolate the fault loop. Shut down the engines.

How does the FDU generate an inoperative signal for loop A or loop B fault logic?. By releasing helium gas. By opening the ALARM switch. By detecting electrical failure. By detecting core gas.

The _____________ fire detection system includes two identical detection loops (A and B) installed in parallel. engine. cargo. avionics. APU.

The ____________ generates fire and fault signals to the Flight Warning Computer (FWC) for display on ECAM. APU MASTER SWITCH. FDU. CFDIU. FWC.

The extinguishing system for the engine fire bottles is controlled by ___________ switches on the FIRE panel. FIRE. ENGINE. AGENT. EXTINGUISHER.

What is the primary function of the Trimmable Horizontal Stabilizer (THS)?. Short-term pitch control. Long-term pitch control. Roll control. Yaw control.

Which components achieve roll control on the Airbus A320 family aircraft?. Ailerons and spoilers. Elevators and THS. Rudder and yaw damper. Speed brakes and ground spoilers.

What is the purpose of the speed brake function?. To decrease aircraft drag. To increase aircraft drag. To control engine thrust. To improve fuel efficiency.

How many slats are there on each wing of the Airbus A321?. 2. 5. 4. 7.

What is the function of the Slats and Flaps Control Computers (SFCCs)?. To control and monitor slats and flaps. To control the THS. To control ailerons. To control the rudder.

How are the slat and flap systems powered?. Electrically and hydraulically. Manually. Pneumatically. Mechanically.

What locks the transmission when the slat and flap surfaces reach the selected position?. Power Control Unit (PCU). Torque shafts. Pressure Off Brake (POB). Wing Tip Brakes (WTBs).

What is the purpose of the Alpha/speed lock function in relation to slats?. To prevent slats from extending at high angles of attack or low speeds. To prevent slats from retracting during low speeds. To increase slat extension speed. To improve overall aircraft performance.

How many positions does the FLAPS lever have?. 3. 4. 5. 6.

Which computers are responsible for pitch and roll control on the Airbus A320 family aircraft?. Elevator Aileron Computers (ELAC). Spoiler Elevator Computers (SEC). Flight Augmentation Computers (FAC). Flight Control Data Concentrators (FCDC).

In case of a double ELAC failure, what happens to aileron actuators?. They switch to damping mode. They become inoperative. They disconnect from the aircraft. They lock in their current position.

What is the role of the sidestick in the aircraft's control system?. It controls the rudder. It sends electrical orders to ELACs and SECs. It operates the ailerons. It controls the THS.

The Flight Management Guidance Computer (FMGC) sends roll commands directly to the SECs. True. False.

Spoilers 1 are used for roll control. True. False.

In case of a hydraulic power loss, spoiler surfaces remain extended. True. False.

What is the purpose of the ground spoiler function?. To increase lift during landing. To decrease lift during landing. To increase lift during take-off. To decrease drag during flight.

Which components control the slat and flap systems on the A320 family aircraft?. Slats. Flaps. Slat Flap Control Computers (SFCCs). Landing Gear Control and Interface Units (LGCIUs).

How many positions are there for the FLAPS lever on the aircraft?. 2. 3. 4. 5.

A computer failure can engage a lateral ___________ configuration. Abnormal. Normal. Direct. Alternate.

In case of loss of both ELevator Aileron Computers (ELACs) only ___________ are available. Elevators. Ailerons. Spoilers. Rudder.

If the normal law of both ELACs fails, the ___________ law takes over. Normal. Direct. Alternate. Mechanical.

In this example Slat Flap Control Computer (SFCC) 2 flap channel is inoperative and SFCC 1 operates normally. Each flap channel lane of SFCC 1 generates ___________ signals. Pitch. Command. Drive. Hydraulic.

Two flap disconnect sensors are fitted on the interconnecting strut between inner and outer flaps on each wing. The flap disconnect sensors are ___________ sensors. Pressure. Proximity. Hydraulic. Temperature.

In case of total electrical loss, induced roll is obtained by using the ___________, which have a mechanical control. Throttle levers. Rudder pedals. Joysticks. Elevator levers.

In case of loss of both servo controls of the same aileron, the other aileron is still operated. True. False.

If the alternate law is lost, the direct law computed in ELAC 1 or 2 becomes active. The pitch direct law is active in case of ___________. Dual IR failure. Triple IR failure. Failure of the RA. Dual FAC failure.

How are the wing tanks in the A318/A319/A320 divided?. Into inner cells and outer cells. They are not divided. Into left and right tanks. Into upper and lower cells.

In the A321, are the wing tanks divided like in the A318/A319/A320?. No, they are not divided. Yes, into inner and outer cells. Yes, into upper and lower cells. Yes, into left and right tanks.

What is the first source of fuel supplied to the engines in the A318/A319/A320?. Center tank. Wing inner cells. Wing outer cells. Direct feed from outer cells.

How is fuel transferred from the outer cells to the inner cells in the A318/A319/A320?. Via inter cell transfer valves. Automatically when outer cells are empty. Through a cross feed valve. By gravity flow.

What happens to the LP valve when an engine stops in the A318/A319/A320?. It closes. It remains open. It switches to manual control. It triggers the APU.

What is the purpose of the cross feed valve in the A318/A319/A320?. To connect or isolate the left and right sides. To regulate fuel temperature. To transfer fuel to the APU. To prevent fuel leaks.

Where is the Refuel/Defuel coupling located on the RH wing of the aircraft?. On the lower surface, near the leading edge. On the upper surface, near the trailing edge. Inside the cockpit. On the APU.