Crear Oportunidades Para Aviones - Systems

Which of the following conditions must exist to arm the RTO mode prior to takeoff?. AUTO BRAKE select switch position to ON. Wheel speed greater than 60n knots. Forward thrust levers positioned to IDLE. Position ANTISKID switch to RTO.

Pulling the engine fire warning switch up,. Closes both the engine fuel shutoff valve and spar fuel shutoff valve. Closes both the engine fuel shutoff valve and spar fuel shutoff valve only if the battery switch is ON. Closes the hydraulic fluid shutoff valve and disables the thrust reverser for the related engine. Both A & C are correct.

During normal operation as a dual loop system, with the OVHT DET switch at the NORMAL position, a fire alert is initiated by both detector loops sensing a fire condition,. True. False.

How are the Engine Bleed Air valves powered?. They are AC activated and pneumatically operated. They are DC activated and pneumatically operated. They are pressure activated and AC operated. They are pressure activated and AC operated.

What is the main source of conditioned air for the flight deck?. The Right Pack. The Left Pack. Both Packs. Ground Air Cart.

What is position of the isolation valve when the ISOLATION VALVE Switch is in AUTO. The isolation valve is always open. The isolation valve is always closed. The isolation valve automatically modulates between open and closed, depending on the pneumatic load. Open when any Engine Bleed Air Switch or Air Conditioning Pack Switch is OFF.

The recirculation fan: Is driven by a DC motor. Increase airflow at greater cabin differential press. Reduces Air Conditioning Pack load and the engine bleed air demand. Provides overheat detection downstream of the pack.

When the amber OFF SCHED DESCENT light illuminates,. The pressurization controller is unable to maintain cabin pressure. The pressurization controller has failed and will automatically shift to ALT mode. The aircraft has begun descending before reaching the planned cruise altitude set in the FLT ALT indicator. All of the above are correct.

If an IDG automatically disconnects from the accessory gearbox inflight due to a high oil temperature, it can be reset with a switch on the overhead panel?. False. True.

What is the source of power for the engine overheat and fire detection systems?. Static Inverter. The battery bus. Battery Charger. None all the above.

After the APU is started and select ¨ON¨, the external power must be turned ¨OFF¨ in order for the APU to provide power to the system. True. False.

When the engine is started, the IDG automatically comes on line and powers the respective side of the electrical system?. False. True.

With both flight control switches in the Standby Rudder position and the yaw damper switch reset ON, the _____ hydraulic system will provide pressure for the yaw damper. A. B. Standby. Impossible to get yaw damper.

The FSEW (Flap Slat Electronic Unit) also monitors the LE devices for asymmetry, and skew conditions on slats __________. 2 through 7. 1 and 8. 2,3 and 7,8. All of them.

Which trim method provides the largest of trim?. Main Electric with flaps extended. Standby trim. Mail Electric with landing gear retracted. Manual.

If the stabilizer has been manually trimmed passed the range of the Main Electric Trim, can the Main Electric Trim be used to trim back within range?. No. Yes.

What is the source of power for the bleed air isolation valve?. AC Power. DC Power. The system doesn´t use electrical power. The bleed valves open with the air pressure from the APU duct.

If the IRS loses both AC and DC power, the alignment is lost?. Yes. No.

What is the purpose of the Landing Gear Transfer Unit?. It supplies hydraulic fluid to raise the landing gear at the normal rate when the system A engine driven pump volume is lost. It supplies hydraulic fluid to raise the landing gear at the normal rate when the system B engine driven pump volume is lost. It supplies hydraulic fluid to raise the landing gear at the normal rate when the system B electric driven pump volume is lost. It supplies hydraulic fluid to raise the landing gear at the normal rate when the system A electric driven pump volume is lost.

What is the main feature of the center tank pumps?. Feed the APU on ground. They produce less pressure that the main tank pumps. They produce more pressure that the main tank pumps. All six pumps operate with the same pressure.

There are ____ flight spoiler panels and ____ ground spoiler panels on each wing. 4; 4. 2; 4. 6; 3. 4; 2.

The PSEU system on the ground monitors which of the following?. Take off/landing configuration warnings. Landing Gear. Air/ground sensing. All of the above.

The stall management yaw damper (SMYD) computer determines when the stall warning is required based on which of the following?. Anti-Ice controls. ADIRU output. FMC outputs. All of the above.

If both FMCs fail, the FMC/CDU fail alert light will appear on both CDUs and both CDUs will display failure modes?. True. False.

Flashing ALIGN lights on the IRS MSU indicate: Alignment cannot be completed until the present position is entered. The IRSs are in the shutdown cycle. The IRSs are in the ALIGN mode. B and C are correct.

When the IRSs are operating in the normal navigation mode they provide: Attitude and true and magnetic heading. Acceleration, vertical speed. And ground speed. Track, present position, and wind data. All of the above are correct.

If alignment is lost inflight, the navidation mode: Selecting ATT position. After 5 minutes shows again. Can be aligning again. Is inoperative for the remainder of the flight.

Normal IRS alignment is initialed by rotating the MSU switch from OFF to: ALIGN. NAV. ATT. ON.

What information is available with the IRS mode selector is ATT?. Only position and ground speed information. Only heading information. Only attitude and heading information. Only altitude information.

What is the source of power for the main battery charger?. AC Ground Service bus 2. DC bus 1. AC Galley 1. TR 1.

The autopilot automatically disengages when?. Aircraft above 3000 feet RA. G/S engaged. APU Shutdown. None of the above.

The Standby altimeter receives static pressure from the alternate static port?. True. False.

The taxi light will automatically turn off when the gear is retracted for safety purpose. True. False.

When the battery switch is off an external electrical power is connected to the aircraft, the entry and the lavatory mirror lights will automatically illuminate,. True. False.

The aircraft is equipped with an air data inertial reference unit (ADIRU) and is there for limit to operate from north latitude to south latitude. 82°; 70°. 80°; 130°. 70°; 120°. 82°; 82°.

A flight deck switch and a switch on the _________ attendance station control the emergency light system. AFT. FWD.

The APU is normally supplied by the?. Left fuel tank. Center fuel tank. Right fuel tank. None of the above.

To start the APU the electrical power comes from?. Number 2 Transfer Bus or Battery. Number 2 Transfer Bus. Number 1 Transfer Bus or Battery. AC Main Bus number 2.

Moving the APU switch to ¨OFF¨, the APU shutdown automatically after,. 20 seconds. 30 seconds. 60 seconds. 120 seconds.

N1 & N2 redline overspeed protection in both normal and alternate mode by,. The PTU. EGT. EEC. HMU.

The Thrust Reverser can be deployed when,. Radio Altimeter sense less than 20 feet altitude, or when the air/ground sensor is in ground mode. Radio Altimeter sense less than 10 feet altitude, or when the air/ground sensor is in ground mode. Radio Altimeter sense less than 20 feet altitude, or when the air/ground sensor is in air mode. Radio Altimeter sense less than 10 feet altitude, or when the air/ground sensor is in air mode.

The EEC automatically selects,. Approach Idle. Flight Idle. Ground Idle. A, B, & C are correct.

Fuel from which tank(s) is used first?. All tanks equally. Both wing tanks equally. The left wing tank. The Center tank.

What is the purpose of the fuel vent lines?. To prevent positive or negative overpressure within the center tank. To prevent positive or negative overpressure within the fuel tanks. To prevent positive overpressure within the fuel tanks. To prevent negative overpressure within the fuel tanks.

The fuel temperature indicator displays the temperature of the fuel in the ___________ tank,. Left Tank. Right Tank. Central Tank. Reservoir Tank.

When is the passenger oxygen system automatically activated?. At 15,000 feet. When the cabin altitude exceeds 14,000 feet. When the cabin altitude is bellow 14,000 feet. At 13,000 feet.

The Oxygen generators are activated when,. All four mask drop from stowage. Is activated by the switch at the aft galley. Any mask in the unit is pulled down. None all the above.

Which pitot probes and sensors are not heated?. Elevator pitot probes. Static Ports. Captain´s pitot probe. First Officer´s pitot probe.

How are the alpha vanes heated?. By actuating the LEFT or RIGHT FWD window heat switch. Whenever wing anti-ice is being used. Whenever the alternate static ports are heated. By actuating the A or B PROBE HEAT switch.

The Power Transfer Unit (PTU) provides an alternate source of power for the auto slat system if: A loss of hydraulic system A pressure is sensed. The hydraulic system A engine driven pump is inoperative. The Alternate Flaps position switch is momentarily held down. Pressure from the hydraulic system B engine driven pump drops below limits.