ESTRUCTURAS DE LA 600-687

What is the primary function of the rubbing strip on the outer surface of the top skin of the flaps?. To enhance aerodynamics. To provide additional support. To prevent corrosion. To protect from damage.

The fixed Leading Edge (LE) assembly is located behind the front spar of the wing-box. TRUE. FALSE.

The bottom surface access panels are made of Carbon Fiber Reinforced Plastic (CFRP) and are attached with screws. TRUE. FALSE.

The wing leading edge is fitted with five slats. TRUE. FALSE.

The trailing edge devices consist of three flaps, one aileron, and six spoilers. TRUE. FALSE.

Two flaps are installed on the TE of the outer wing, and they are connected by an interconnection strut. TRUE. FALSE.

The inboard flap of A318-A319-A320 is supported by three tracks. TRUE. FALSE.

The outboard flap of A318-A319-A320 has a leading edge made of stainless steel. TRUE. FALSE.

The A321 flaps are fowler flaps without any tabs on the trailing edge. TRUE. FALSE.

There are six spoilers on the upper surface of the wing trailing edge. TRUE. FALSE.

Where is the center wing located in the aircraft's fuselage?. Between the main frames Fr 36 and 42. Between the main frames Fr 20 and 30. Between the main frames Fr 1 and 10. In the rear fuselage.

How is maintenance access to the center wing box typically achieved?. Through two rectangular openings in the rear spar. Through triangular openings in the rear spar. Through circular openings in the rear spar. Through the top skin panels of the center wing box.

What fittings ensure the junction between the center wing box and the outer wing box?. Upper cruciform fitting and lower triform fitting. Upper triangular fitting and lower square fitting. Upper circular fitting and lower rectangular fitting. Upper hexagonal fitting and lower oval fitting.

What does the upper cruciform fitting make the junction between?. Center wing box top skin panels, outer wing box top skin panels, fuselage, and Rib 1. Center wing box top skin panels and bottom skin panels. Center wing box and outer wing box bottom skin panels. Outer wing box top skin panels and fuselage.

What part of the outer wing contains the top and bottom skin panels, ribs, and stringers?. Outer wing box. Wing tip. Leading edge and leading edge devices. Trailing edge and trailing edge devices.

How many top skin panels are there in the outer wing box?. Two. Three. Four. Five.

How many top skin panels are there in the outer wing box?. Two. Three. Four. Five.

What do the wing spars extend from in the outer wing?. Rib 1 to Rib 27. The center wing box. The fuselage. Rib 22 to Rib 27.

How many load-carrying access panels are there in the outer wing box between Rib 14 and Rib 27?. Fourteen. Seven. Three. Twenty-one.

How are the non load-carrying access panels between Rib 1 and Rib 13 attached to the wing?. Clamped on the wing skin. Bolted through the skin panel. Welded to the fuselage. Riveted to the center wing box.

What parts of the wing require reinforcement when sharklets are installed?. Wing front spar, fixed leading edge structure, wing rear spars, fixed trailing edge structure, wing covers, wing ribs. Wing tip, wing root, winglets, winglet ribs. Center wing box, winglet attachment points, ailerons. Wing stringers, wing skin panels, trailing edge devices.

How is Rib 27 modified when sharklets are installed on the aircraft?. It becomes a box Rib instead of a traditional single-sided Rib. It is removed from the wing. It is strengthened with additional materials. It is shifted to a different location on the wing.

What is the composition of the D-nose assembly in the fixed leading edge?. Made of aluminum alloy parts. Made of Carbon Fiber Reinforced Plastic. Made of stainless steel. Made of honeycomb core.

Which component holds the pylon shroud panels?. D-nose assembly. Support ribs. Sub spar. Pylon ribs.

What is the composition of the D-nose assembly in the fixed leading edge?. Made of aluminum alloy parts. Made of Carbon Fiber Reinforced Plastic. Made of stainless steel. Made of honeycomb core.

Which component holds the pylon shroud panels?. D-nose assembly. Support ribs. Sub spar. Pylon ribs.

How many tracks support Slat 1?. 2. 4. 5. 3.

Which slats receive de-icing through the bleed air system?. Slats 1 and 2. Slats 3 to 5. Slats 1 to 3. Slats 4 and 5.

Where is the fixed trailing edge located?. Forward of the wing front spar. Aft of the wing rear spar. Between the wing box and LE spar. On the wing leading edge.

What are the trailing edge devices?. Two flaps, one aileron, five spoilers. Three flaps, two ailerons, four spoilers. Two flaps, two ailerons, six spoilers. One flap, one aileron, four spoilers.

How many flaps are installed on the TE of the outer wing?. 1. 2. 3. 4.

What is the function of the rubbing strip on the inboard flap?. To enhance aerodynamics. To provide additional support. To prevent corrosion. To protect the top skin from damage.

How many wing tracks support and drive the outboard flap in the A318-A319-A320?. 1. 2. 3. 4.

What is the unique feature of the A321 flaps compared to the A318-A319-A320?. They have a tab on the trailing edge. They are made entirely of aluminum alloy. They are larger in size. They have no leading edge.

How many spoilers are connected to the middle and outer sections of the rear spar?. 1. 2. 3. 4.

Which spoilers have a rubbing strip attached to their trailing edge?. Spoilers 1 & 2. Spoilers 3 & 4. Spoilers 4 & 5. all spoilers.

What is the primary material used for the top and bottom skins of the spoilers?. Aluminum alloy. Carbon Fiber Reinforced Plastic (CFRP). Stainless steel. Honeycomb core.

Where is the aileron located in relation to the outer flap?. Inboard. Outboard. Above. Below.

What material is primarily used for the aileron's skin?. Aluminum alloy. Carbon Fiber Reinforced Plastic (CFRP). Stainless steel. Honeycomb core.

What is the primary material used for the sides and trailing edge profile of the spoilers?. Aluminum alloy. Carbon Fiber Reinforced Plastic (CFRP). Stainless steel. Honeycomb core.

The CFM56-5B engine is a single-rotor, fixed stator, low-bypass-ratio turbo-fan power plant. TRUE. FALSE.

The power plant installation includes the engine, the engine inlet, the exhaust, and the fan cowls only. TRUE. FALSE.

The reverse thrust is controlled manually by the flight crew without any involvement of the ECU. TRUE. FALSE.

The thrust reverser uses 4 hydraulically operated pivoting blocker doors to redirect the engine fan airflow. TRUE. FALSE.

The FADEC alternator is located on the LH side of the gearbox. TRUE. FALSE.

The air starter is located on the LH side of the gearbox rear face. TRUE. FALSE.

The primary components of the fuel system are installed on the RH side of the fan compartment. TRUE. FALSE.

What is the primary function of the programming plug on the Electronic Control Unit (ECU) of the CFM56-5B engine?. To change the engine type. To adjust the fuel consumption. To change the available thrust. To monitor the engine temperature.

How is the engine attached to the pylon?. By the exhaust system. By forward and aft mounts. By the fan cowls. By the reverser assemblies.

Who manually selects the reverse thrust?. The ECU. The Engine Interface Unit (EIU). The flight crew. The Hydraulic Control Unit (HCU).

What is the primary role of the Hydraulic Control Unit (HCU) in the thrust reverser system?. To control the ECU. To supply hydraulic power to operate the thrust reverser. To control the throttle control levers. To monitor the engine's thrust.

Where is the ECU located?. On the LH side of the fan case. On the gearbox. On the RH side of the fan case. Inside the engine core.

Where is the air starter located?. On the LH side of the gearbox rear face. On the RH side of the engine core. On the RH side of the gearbox rear face. Inside the engine core.

Which component of the fuel system is operated by the gearbox?. The Hydro-Mechanical Unit (HMU). The filter. The fuel pump. The fuel nozzle.

Where is the oil tank located?. On the RH side of the fan case. On the LH side of the fan case. Inside the engine core. On the gearbox.

Where is the hydraulic shut-off valve located?. On the rear part of the pylon. On the forward part of the pylon. On the forward part of the RH 'C' duct. Inside the engine core.

What is the primary function of the drain system?. To supply fuel to the engine. To cool the engine. To collect and drain waste fluids and vapors from engine systems and accessories. To provide air to the engine.

What happens to the LP and HP fuel shut-off valves during a normal shutdown?. They are opened. They remain in a neutral state. They are closed. They are partially opened.

What drives the LP SOV to the closed position when the ENGine MASTER control switch is set to OFF?. The ECU. Both electrical motors. The HMU. The EIU.

What happens to the LP SOV when the ENGine FIRE P/B is released out?. It is driven to the open position. It remains in a neutral state. Both electrical motors drive it to the closed position. It sends a signal to the EIU.

What changes the available thrust in the CFM56-5B engine?. The power plant installation. The pylon. The programming plug on the Electronic Control Unit (ECU). The fan cowls.

What does the thrust reverser use to redirect the engine fan airflow?. 2 hydraulically operated pivoting blocker doors. 4 hydraulically operated pivoting blocker doors. 6 hydraulically operated pivoting blocker doors. 8 hydraulically operated pivoting blocker doors.

Which system controls the turbine clearance?. The compressor airflow control system. The transient bleed valve system. The turbine clearance control system. The FADEC system.

The engine fuel system is designed only to supply Fuel Flow (FF) into the combustion chamber. TRUE. FALSE.

The fuel coming from the A/C tanks is driven by the HP stage of the fuel pump. TRUE. FALSE.

The fuel from the fuel pump goes directly to the nozzles without passing through any filter. TRUE. FALSE.

The FADEC is not repowered when the engine start selector is selected to CRANK. TRUE. FALSE.

The ECU is supplied from the aircraft electrical power when N2<60%. TRUE. FALSE.

The Control Alternator does not supply the ECU when the engine is running above 58% of N2. TRUE. FALSE.

The FADEC is automatically de-powered in the air, through the EIU, after engine shutdown. TRUE. FALSE.

Releasing the ENGine FIRE P/B out does not affect the ECU power. TRUE. FALSE.

Where is the ECU of the FADEC system located?. On the engine fan case left hand side. Inside the cockpit. On the engine fan case right hand side. On the aircraft's tail.

What does the FADEC system consist of?. A single channel Electronic Control Unit (ECU). A dual channel Electronic Control Unit (ECU) without peripherals. A dual channel Electronic Control Unit (ECU) with its associated peripherals. Only its associated peripherals.

Which of the following is NOT a function of the FADEC system?. Power management control. Variable Stator Vanes (VSVs) control. Fuel tank monitoring. Transient Bleed Valve (TBV) control.

What happens to the ECU power supply when the engine N2 is below 58%?. It is supplied by the aircraft's battery. It is supplied by the aircraft's 28 VDC through the Engine Interface Unit (EIU). It is supplied by the Control Alternator. It is not supplied power.

What does the FADEC system manage?. Only the engine thrust. Only the performance optimization. Both the engine thrust and performance optimization. Neither the engine thrust nor the performance optimization.

When is continuous ignition manually selected?. When the APU is off. When IGNition START is deselected with an engine running. When the aircraft is on the ground. When the ECU detects a malfunction.

What does the FADEC do when it detects an ignition delay during start?. It shuts down the engine. It provides continuous relight. It aborts the start sequence. It switches to manual mode.

What is the aircraft configuration for engine CRANK modes?. APU off and APU BLEED off, FADEC 1 and 2 unpowered. APU running and APU BLEED on, FADEC 1 and 2 powered. APU running and APU BLEED off, FADEC 1 and 2 unpowered. APU off and APU BLEED on, FADEC 1 and 2 unpowered.

What happens when CRANK is selected on the ground?. The ENGINE page disappears from the ECAM. The ECU initiates a shutdown sequence. The ECU initiates a motoring sequence after action on the MANual START P/B. The ECU cuts off the ignition.

For how long should you motor the engine with the MASTER CONTROL SWITCH in the ON position during a wet crank?. 5seconds. 15seconds. 30seconds. 60seconds.

What should you do after a wet crank of 15 seconds maximum?. Continue to dry crank the engine for 30 seconds. Set the selector back to MODE NORMal position immediately. Continue to dry crank the engine for 60 seconds. Release the MANual START P/B switch immediately.

How is the fan case and its accessories cooled?. By air entering two flush inlet scoops located on the inlet cowl outer barrel. By using engine oil. By using coolant fluid. By using fan air from the core compartment.

Where does the air exit after cooling the fan compartment?. Through an outlet port located in the lower aft section of the right-hand fan cowl door. Through the engine exhaust. Through the core compartment. Through the engine intake.

How is the core compartment cooled and ventilated?. By fan air entering flush inlets located at the forward section of the core cowl. By using engine oil. By using coolant fluid. By using air from the fan compartment.

Where does the air exit after cooling the core compartment?. Through the annular vent located at the interface between the core cowl and the primary nozzle. Through the engine exhaust. Through the fan compartment. Through the engine intake.

What does the engine provide sources for?. TO feed the Active Clearance Control subsystems and to supply the inlet cowl anti-ice and the engine bleed system. To cool the engine. To provide continuous ignition to the engine. To regulate airflow in the engine.