BANCO PREGUNTAS B-737 TLA PARTE 1

Illumination of an amber COWL ANTI ICE light indicates. An overpressure condition. An over temperature or overpressure condition. The respective cowl anti-ice valve is open. The respective cowl anti-ice valve is in transit, the cowl anti-ice valve position disagrees with the respective engine anti-ice switch position.

Windshield wipers of are provided to maintain a clear area on the cockpit No.1 windows. Which of the following statements is correct?. Each wiper is operated by a separate system. Windshield wipers are hydraulically operated & electrically controlled. Windshield wipers may be operated on a dry windshield. None of the above.

Both windshield wipers are controlled with a common switch. True. False.

Which pitot probes and static ports are not heated?. Elevator pitot probes. Alternate static ports. No.1 Aux pitot probe and static port. No.2 Aux pitot probe and static port.

Which portion of the wings does the wing anti-ice system heat?. Leading flaps. Outboard leading edge slats. Three inboard leading edge slats. All of the above.

With the CONTROL PANEL select switch on the DISPLAYS Source Panel in the BOTH ON 2position: The First Officer's EFIS Control Panel is supplying identical inputs to the captain's & First Officer's displays. Both pilots displays are using the No.2 symbol generator. DEU 2 controls all six display units. ADIRU inputs for both the L & R ADIRU are being received from the First Officer's pitot probe.

The Slip/Skid indication of the Attitude Indicator will turn amber if bank angle is 35 degrees or more. True. False.

The Glide Slope Pointer is not displayed when the track and the front course on the Mode Control Panel differ by more than 90 degrees (backcourse). True. False.

Concerning Navigation Display Information, Heading is supplied by Air Data Inertial Reference System (ADIRS) & Track is supplied by the FMC during normal operation. True. False.

If you select the 'BOTH ON 1' switch of the CONTROL PANEL: The Left EFIS control panel controls both pilots' outboard & inboard display units. The Right EFIS control panel controls both pilots' outboard & inboard display units. The Left ADIRS controls both pilots' outboard & inboard display units. The Right ADIRS controls both pilots' outboard & inboard display units.

The Mach digital counter indicates current Mach number & it is displayed when airspeed increases above Mach. 0.30. 0.40. 0.50. 0.60.

The display SOURCE selector also allows the crew to manually select either DEU1 or DEU2 for all 6 display units. If the displays are automatically or manually switched to a single DEU source, a 'DSLPY SOURCE' annunciation illuminates above both pilot's altimeters. True. False.

If the Upper Display fails: The engine display automatically moves to the Inboard display and the Upper display blanks. The engine display automatically moves to the Outboard display and the Upper display blanks. The engine display automatically moves to the Lower display and the Upper display blanks. The engine display automatically moves to the Inboard or Outboard display and the Upper display blanks.

What is the purpose of the Air Data Modules (ADMs)?. The ADMs convert pneumatic pressure to electrical signals and send these data to the ADIRUs. The ADMs provide only pitot & static pressure to the standby instruments. The ADMs provide inertial position & track data to the displays thru the ADIRUs. The ADMs measure thru the Alpha vanes the airplane angle-of-attack.

The Weather Radar Annunciation 'WXR ATT' indicates: The Weather radar has failed. The Weather radar Attitude calibration has been lost. The Attitude stabilization for antenna has been lost. The Display unit cooling has been lost or an overheat condition has occurred.

The ND Wind direction/speed and wind arrow is: Displayed in only in ND MAP mode. Blanked if wind speed becomes less than 6 knots. Displayed if wind speed is greater than 6 knots. Displayed only in ILS mode.

During an ILS approach the Captain observes his BARO minimum reference/ altitude turns from green to flashing amber for three second. What does it mean?. Radio altitude data is unreliable. The aircraft has descended below the Captain's selected minimum altitude (DA). A windshear has been encountered. The aircraft has descended below 1000 feet.

The First Officer observes the word PITCH displayed in amber in the lower portion of the PFD during an ILS approach. What does it mean?. The autopilot has defaulted to CWS pitch. Glide slope is not being tracked. The Captain's and First Officer's pitch displays differ by 5 degrees or more. The First Officer's pitch display is more than 3 degrees in error.

The decision height (DH) display on the CDS is set: Automatically when APPROACH is selected on the MCP panel. Independently by each pilot using his/her EFIS control panel. By entering the desired DH on the FMC CDU APPROACH REFERENCE page. By using the DH selector knob on the forward instrument panel.

The aircraft is on the ground and the Flight Recorder Switch is in NORMAL: The Flight Recorder operates anytime electrical power is available. The Flight Recorder operates when electrical power is available and either engine is operating. The Flight Recorder operates whenever the Battery Switch is ON. The Flight Recorder operates anytime electrical power is available and start switch in GROUND position.

An amber DSPLY SOURCE annunciation below each speed tape indicates: The altimeter is receiving inputs from a source other than the ADIRU and should be considered unreliable unless verified by another source. A single DEU has been manually or automatically selected to drive all six display units. A non-dispatchable CDS fault has occurred. A single EFIS control panel has been manually or automatically selected as the source for all six display units.

If an outboard display unit fails, the PFD is automatically displayed: Never. It can only be displayed manually with the MAIN PANEL DU selectors. On the ENGINE PRIMARY display. On the ENGINE SECONDARY display. On the inboard display unit.

An amber CDS FAULT annunciation below each speed tape indicates: The altimeter is receiving inputs from a source other than the ADIRU and should be considered unreliable unless verified by another source. A single DEU has been manually selected to drive all six display units. A non-dispatchable CDS fault has occurred. Single EFIS control panel has been manually or automatically selected as the source for all six display units.

The Air Data Inertial Reference System (ADIRS) produces following flight data: Position and speed only. Attitude and speed only. Altitude and speed only. Position, attitude, altitude and speed.

When Max range is selected on the EFIS Control Panel, weather radar returns are limited to: 80 NM. 160 NM. 320 NM. 640 NM.

With the weather radar in WX/TURB mode, turbulence will be shown within: 160 NM. 120 NM. 80 NM. 40 NM.

The power source for Engine Fire Extinguishing is: Transfer Bus No.1. The Switched Battery Bus. The Hot Battery Bus. None of the above.

Main wheel well fire protection consists of fire detection powered by the: Battery bus. No.1 AC Transfer bus. Switched hot battery bus.

A dual fire detector loop is installed in the main wheel well. True. False.

Cargo compartment smoke detection is powered by: Hot battery bus. Switch hot battery bus. Transfer bus No.1. DC bus 1 and DC bus 2.

The cargo compartment blowout panels: Allow air to flow into or out of the cargo compartments. Prevent cargo movement in flight. Prevent damage to the airplane structure during sudden decompression. Is just forward of the FWD cargo compartment and AFT of the nose wheel well.

The escape slide can be armed and disarmed: Automatically when you close the door. Manually from a switch at the FWD attendant panel. Manually securing the girt bar in the escape slide floor brackets. Manually securing the girt bar to the girt bar retainer hooks.

The volume and pressure of the air is sufficient to inflate the escape slide within: Six seconds. Four seconds. Ten seconds. Twenty seconds.

What is the meaning of the IDG?. Inertial Drive Generator. Integrated Drive Ground. Integrated Drive Generator.

What is the meaning of HPTACC?. High pressure turbine. High pressure turbine active clearance control. High pressure relive valve clearance control.

How many fan cowl latch has each engine?. Three. One. Two.

The IDG access door is on the right fan cowl panel for each engine?. False. True.

The purpose of the AC ground service bus is to power: The cabin lighting. The utility outlets. The battery charger. All the above.

The TR´s (Transformer rectifier) convert: 115 volts DC to 28 volts AC. 115 volts AC to 28 volts AC. 115 volts AC to 28 volts DC. 115 volts DC to 28 volts DC.

Which is the power source for the AC standby bus?. Transfer bus 1 under normal conditions. Transfer bus 2. AC main bus 1. Battery Bus through the Static Inverter under normal conditions.

A high oil temperature in the IDG would cause an automatic disconnect of the IDG. True. False.

The cross bus tie relay: Must be manually opened using the BUS TRANSFER Switch during a Flight Director approach. Normally powers the Battery Charger and backs-up TR units 1 and 2 through a diode. Opens up if BUS TRANSFER switch is moved to OFF. Will trip off when AC volts reaches 26 volts (plus or minus 4 volts) as displayed on the AC voltmeter.

Illumination of the GND POWER AVAILABLE light indicates: Ground power is connected and meets airplane power quality standards. Ground power is connected however no airplane power quality is measured. The Ground Service Bus is powered by a ground power supply. The external power bus is powered by a ground power supply.

For ground service, a ground service switch is placed: On aft overhead panel on the Flight Deck. On aft attendant´s panel. On forward attendant´s panel. On external receptacle on the right side of the aircraft exterior.

One basic rule of operation for the B737 electrical system is: All generator bus sources can be automatically connected by the Standby Power System. There is no paralleling of the AC power sources. The aircraft must be on ground and GPU connected. An AC power source may be used in parallel with a DC power source.

Illumination of the BAT DISCHARGE light indicates: The battery is being overcharged. Excessive battery discharge is detected with the battery switch ON. The DC meter is in the BAT position with the battery switch ON. The battery bus is not powered.

In the event that the airplane battery is depleted, the APU can be started using DC external power. True. False.

Illumination of the blue GEN OFF BUS light indicates: The associated generator bus is not powered. The associated transfer bus is not powered. The IDG is not supplying power to its associated transfer bus. The generator is not supplying power to its associated generator bus.