Banco preguntas b-737 tla parte 2

Which equipment management the logic of the lights in the electrical panel : SPCU. GCU. AGCU. SCU AND SPU.

Illumination of the DRIVE light indicates: IDG failure. IDG automatic disconnect due to high oil temperature. IDG disconnected through the drive disconnect switch. Any of the above.

The TR UNIT will illuminate in flight if: Any TR unit fails. TR1 fails or TR2 and TR3 fail. TR2 fails. TR3 fails.

The ELEC light will illuminate in flight if: A fault exists in the AC or Standby power system. A fault exists in the DC or Standby system. A fault exists in the AC, DC or the Standby system. The ELEC light only operates on the ground.

With external DC power connected to the external DC power receptacle: The APU can be started using DC external power. The battery is paralleled with the DC External power source. All circuits normally powered by the battery are powered. There is no external DC power receptacle.

The main battery charger is powered through: DC bus 1. AC ground service bus 2. AC ground service bus 2. Transfer Bus 1.

The electrical system incorporates an automatic load shedding feature. What is the first bus that is shed?. Galleys on transfer bus 1 are shed first. Galleys on transfer bus 2 are shed first. The AC standby bus is shed first. None of above.

The electrical system incorporates an automatic load shedding feature. What is the second bus that is shed?. Galleys on transfer bus 1. Galleys on transfer bus 2. The AC ground service bus. The AC standby bus.

After an overload situation has been resolved, how do you recover the galley buses?. It happens automatically. Move the galley power switch to OFF then ON. A ground engineer should reselect the appropriate switch in the E/E.

Once disconnected, the IDG can be reconnected in flight. True. False.

There is no fluid transfer at the PTU between system A and B. TRUE. FALSE.

What is the indication that the PTU is operating?. PTU LOW PRESSURE light goes out. System B EDO LOW PRESSURE light comes on. There is no indication for PTU operation.

What are not indicating on Hydraulic System. Hydraulic fluid quantity. Hydraulic press. Hydraulic low press. Hydraulic low temperature.

You can service the main and standby hydraulic systems from a single point: TRUE. FALSE.

What is the purpose of the Proximity Switch Electronic Unit?. Monitors the takeoff configuration warning. Monitors the landing configuration warning. Monitors the landing gear. All of the above.

The start lever controls ignition system power to the: FMC. DEU. EEC. CDS.

What is not a component of ignition system. Fuel manifold. Ignition exciter. Air manifold. Spark igniter.

Where is located the ignition selector switch. P61. P5. P3. P18.

What electrical source supply power to LH ignition system. 28 VDC DC Bus. 115 AC Standby bus. 115 AC Transfer bus. 28 VDC Standby bus.

What is the purpose of turbine clearance control. Prevent an engine stall. Blades tips do not rub against the case. Engine use less fuel. To have air flow to all power condition.

HPTACC controls air from what stage. 8 AND 9 STAGE. 13 AND 8 STAGE. 9 AND 4 STAGE. 5 AND 9 STAGE.

VSV Actuator follow position by: RVDT. Piston actuator. Pressure rod. LVDT.

To increase the compressor efficiency and stall margin is used. VBV. VSV. TVB. LVDT.

Engine control system supplies: Deploys reverse control. Supply electrical signal to engine. Control the engine thrust. Lock thrust solenoid.

What type of signal is send to EEC from resolvers. Electrical. Mechanical. Digital. Pressure.

What is the purpose of the air conditioning system?. To provide cold air for the passengers and crew. To provide pressure and temperature controlled air to the cabin areas. To control the amount of temperature controlled air entering and exiting the airplane. To compensate for turbulence and anomalous characteristics of atmospheric conditions.

The recirculation system has these components: Two fans, two filters, and a collector shroud. One filter, one fan, one check valve, and a collector shroud. One filter, two fans, one check valve, and a collector shroud. One fan bypass check valve, one fan, two filters, and a collector shroud.

The pack heat exchangers: Receive cooling air from the engine bleed air precooler system. Remove heat from the pneumatic supply source and the air cycle machine compressor discharge air. Control air through the ram air system d. All of the above.

PACKTRIP OFF light will illuminate when which of the following overheat switches or temperature sensors detects an overheat condition?. Compressor discharge overheat switch, turbine inlet overheat switch, 190F/88C duct overheat switch, or 250F/121C duct overheat switch. Compressor discharge overheat switch, turbine inlet overheat switch, duct limit sensor, or 210F/99C duct overheat switch. Compressor discharge overheat switch, turbine inlet overheat switch, or 190F/88C duct overheat switch. Compressor discharge overheat switch, turbine inlet overheat switch, or 250F/121 C duct overheat switch.

How many doors have the main landing gear. 2. 3. 4.

If you disconnect the torsion link to permit the landing gear to move. More of 78 grades. 87 grades. 50 grades.

Hydraulic system B supplies pressure for retraction only through the landing gear transfer valve. True. False.

The landing gear control lever has these three positions with detents. Up, off , down. On , off , In. Up, down, Lock.

You can also manually operate the landing gear transfer valve with the BITE of the proximity switch electronic unit (pseu). True. false.

The landing control level is locked out of the UP position by a mechanical level. 28V dc battery bus. 115V ac. 28V dc power.

How many up lock actuators are installed in each MLG. 1. 3. 2.

When the Landing Gear Lever is positioned DOWN, the landing gear extends by: Hydraulic pressure. Gravity. Air loads. All the above.

What is the purpose of the landing gear transfer unit?. If hydraulic B fluid is lost the landing gear can be extended by automatic activation of the transfer unit. In case of No1 engine failure/separation, the gear can be retracted after takeoff. In case of engine failure the gear can be retracted in order to reduce drag for the cruise segment. If hydraulic A fluid is lost, the transfer unit must be manually selected to B fluid when the gear lever is selected up.

Normal hydraulic brake pressure is: 2000 psi. 3000 psi. 3500 psi.

Which are the parameters of recording of the flight recorder: 25 hours. 2 hours. 24 hours. 30 minutes.

What is the function of the service interphone?. Controls communication between the forward and aft flight attendant stations. Supplies intercommunication between the flight deck, flight attendants and ground personnel. Connects the external jacks used by maintenance personnel to the service interphone system. Disconnects the cabin attendant stations from the flight interphone system.

What is the total fuel capacity of the Boeing 737 NG : 43.000 pounds. 40.000 pounds. 46.000 pounds. 42.000 pounds.

The imbalance message appears when the difference between tanks is greater than: 200 pounds. 800 pounds. 1000 pounds. 1500 pounds.

How is the aileron trim system controlled: By electric control with hydraulic operation. By Hydraulic control and actuators. Manual through the trim wheel. Electronic control and electric operation.

How the flight spoilers help the airplane in a turn?. The spoilers come up to kill lift on the wing with the up aileron. The spoilers come down to kill lift on the wing with the up aileron. The spoilers increase drag in approach. The spoilers keep down in a turn.

What is the meaning of the ADIRU: Air Data Inertial Reference Unit. Auto Digital Input Regulated Unit. Ac Digital Interface Reference Unit. Actuator Data Internal Reference Unit.

The Boeing 737 – 700 has tail bump: True. False.

The Boeing 737 – 800 has one overwing emergency exit per side. True. False.

The elevators has pitot probes for control its movement: True. False.

Who is the manufacturer of the engines in the Boeing 737 NG: A: Snecma. B: General Electric. C: Rolls Royce. A and B are correct.

Placing the TEST switch in the FAULT / INOP position tests: The engines overheat detectors. The fault detection circuits for both engines and the APU. The APU DET INOP light, FAULT light and APU BOTTLE DISCHARGE.