Boeing 737 90 preguntas azules

The flight spoilers augment the Aileronoperation when the control wheel is rotated more than... Eight. Ten. Fifteen. Five.

Tha Ground Service Bus is powered by a Ground Power Source. It powers the Battery Charger, the cabin lighting circuits,and utility outlets that may be needed for cabin servicing. True. False.

Inflight or on the Ground with normalconditions, the Standby Power switch in the AUTO position allows the AC Standby Busto be normally powered by.... Transfer Bus 1. Transfer Bus 2.

Where are the control switches for the NO SMOKING and FASTEN SEAT BELT signs?. Center of the overhead panel. Center of the Control Stand.

A flight deck switch and a switch on the ......................... Attendant station control the Emergency Light system. Forward. aft.

A flight deck switch on the .....................Attendant station control the Emergency Light system. forward. aft.

Inflight or on the Ground with normal conditions, the Standby Power switch in the AUTO position allowsthe AC Standby Bus to be normally powered by............... Transfer Bus 1. Transfer Bus 2. Both Transfer Bus 1 and 2.

How much fluid remains in the hydraulic reservoir when a leak associated with the engine driven pump occurs in System "B" ?. 1/4. 1/8. 3/4. 1/2.

The RF (refill) indication appears if the quantity is below .............. with both engines shut down or after landing with flaps up during the taxi in. 75%. 60%. 76%. 80%.

The "A" hydraulic system is considered full with ............... gallons indicated on the fluid quantity gauge. 3. 4.5. 5. 4.

The External AC Bus is powered when the .................... light is on. The External AC Bus provides power to fuel gauges and the re-fueling panel. GEN BUS OFF. GRD POWER AVAILABLE.

For high performance takeoffs, the ......................... turned Off, and the APU is used to operate one pack until after takeoff. left engine bleed only is. engine bleeds are.

The Anti-collision lights are turned on before ............................ receiving Checklist. engine start or aircraft movement.

On the ground, the APU may be used to power both the Left and Right Electrical systems. Inflight, the APU generator can power ............. the left or right electrical system(s). either. both.

If the exterior switch for the nose gear wheel well is on, can the nose gear wheel well light be turned off by use of the cockpit Wheel Well Light switch?. Yes. NO.

The Standby hydraulic pump LOW PRESS light is inhibited when the Standby system is off. True. False.

Inflight when operating on one generator , the ........................ load is automatically shed. This reduces the load on the operating generator. galley. water system. windshield heat. galley and water system.

The A and B hydraulic systems are each pressurizedby an engine driven hydraulicpump and ............................. a pneumatic pump. none of these. an electric motor driven hydraulic pump. a manual emergency pump.

How is the "A" hydraulic system normally pressurized?. By an engine driven pump only. None of these. By an electric motor pump only. By an engine driven pump and an electric motor pump.

Takeoff flaps are set to Flaps 1,5, or 15, while Flaps 30 or 40 are used for a normal landing . Note: The 500 series aircraft does not use ............... for takeoff. Flaps 5. Flaps 1.

If a leak occurs in system "B" that is associated with the electric motor pump, how much fluid will remain in the reservoir?. An electric motor pump leak will not effect the reservoir. None. Just enough to operate the PTU. 15 qts.

The Standby reservoir is pressurized and receives fluid from an interconnectingbalance line from ....................reservoir(s). the A. both. the B.

With an inoperative engine driven generator,the aircraft can dispatch with the APU as the second source of electrical power. True. False.

If the exterior switch for the nose gear wheel well light is on, can the nose gear wheel well light be turned off by use of thecockpit Wheel Well Light switch?. Yes. No.

Which cockpit light illuminates with the Emergency Exit lights??. Captain's Floods. The extra bukb in the dome light.

If the battery is less than ........................ the APU will not start and the fueling valves cannot be powered by the DC External Bus. 28 volts. 26 volts. 23 volts. 24 volts.

TR1 and TR2 provide .......... power to the ........ busses. AC:AC. DC:DC. DC:AC. AC:DC.

Rudder pedal steering provides a maximumsteering angle of ...................... 18 degrees. 7 degrees.

The External AC Bus is powered when the ........................ light is on. The External AC Bus providespower to fuelgauges and the re-fueling panel. GEN BUS OFF. GRD POWER AVAILABLE.

A red indicator is installed for indication of door arming. With the girt bar ............ the Flight Attendant will move the red indicator from across the door window as a signal that the slide is................. disarmed: disarmed. armed: armed.

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

The Passenger Oxygen is supplied by ................... an oxygen bottle. chemical oxygen generating canisters.

Wich bus powers the Dome lights?. Battery bus. Hot Battery bus.

The Power Transfer Unit automatically operateswith the flaps between 1 and 5 and with reduced output pressure of the ..................... system engine driven pump. A. B.

The Oxygen Blow Out disc is located on the .......................... side of fuselage. If this disc is missing - the crew oxygen bottle requires servicing. left. right.

The Hydraulic System "B" electric motor pump is powered by ........................ Generator bus #2. the Emergency DC bus. Generator bus #1. the APU.

Lights on the foward overhead panel indicate if a door is not locked, however there are no indicating lights for the...............doors. overwing exit. entrance.

The individual emergency nicad batteries are all charged by 28 Volt. D.C. Bus #2. D.C. Bus #1.

Where is the Cockpit Dome light switch?. Control Stand. Aft overhead panel.

The PTU provides a backup source of hydraulic pressure to assist the....system electric motor pump to operate the leading edge devices and the autoslat system when the....system engine driven pump output is below normal. B : B. A : A.

The Ground Service Power switch is located at the Forward Flight Attendants' station. True. False.

The water pressure for the lavatories is normally provided by the................. hydraulic system. electrical system. pneumatic system.

When normal power is available, the AC Standby Bus is powered by .................. the inverter. Main AC Bus. switched Hot Battery Bus. Transfer Bus 1.

The nickel-cadmium battery located in the Electronics Compartment is: 26 volt. 48 volt. 28 volt. 24 volt.

When normal power is available, the AC Standby Bus is powered by .............................. the inverter. Main AC Bus. switched Hot Battery Bus. Transfer Bus 1.

In general, the APU GEN OFF BUS light indicates the APU is running but its generator is not applied to either system. The APU GEN OFF BUS light is inhibited when the APU control switch is ....... OFF. ON.

With the #2 generator failed, the Bus Transfer Relay allows the #1 generator to provide power to the .......................... #2 Generator Bus. #2 Transfer Bus.

The potable water tank is normally pressurized by the pneumatic system with pressure regulated at ............... 35 psi. 60 psi. 30 psi. 20 psi.

The Standby hydraulic system can be activated .............................. manually only. automatically only. automatically or manually. only while in flight.

A fully charged battery can provide Standby Power for a minimum of ................, including one APU start. 30 minutes. 20 minutes. 45 minutes. 15 minutes.

There is a white strobe light on each wingtip and ................................ top of the Vertical Stabilizer. on the fuselage tail cone.

In case of an overload condition, the gallery power on ................. is shed first. Transfer Bus 1. Transfer Bus 2.

In te event system A or B fails, the Standby system may be pressurized by a motor driven pump that is powered by the ................... #1 AC Transfer Bus. #2 AC Transfer Bus. DC ESS BUS.

The aircraft is equipped with an Inertial Reference System (IRS) and are operationally limited ................................................... This restriction is because the IRS only has stored magnetic variation for this operating area. from 90 degrees North Latitude to 70 degrees South Latitude. from 73 degrees North Latitude to 60 degrees South Latitude.

RTO or Landing Autobrakes are Disamed by: All of these. Positioning the Autobrake select switch to OFF of Applying manual brakes. Moving the Speed Brake Handle to the Down detent. Advancing either or both Thrust levers after touchdown.

What action will activate an oxygen generating canister?. Pull down any mask in a seat row to pull the release firing pin. The both red release levers to the left. They activate when the masks are released. Squeeze both red release levers.

TAI displays in......... if the cowl anti-ice valve is not the position commmanded by the cowl anti-ice switch. red. amber. geen. blue.

What is the normal preflight charge for a full crew oxygen bottle (in PSI)?. 2000. 1900. 1800. 1850.

For landing, the Autobrakes will apply the selected deceleration rate when main wheel spin up is detected and..................................................... the trusth levers are not retarded to near ride. the thrust levers are retarded to near idle.

What is the maximum nosewheel turning angle that can be commanded by the rudder pedals?. 10. 13. 7. 9.

what device automatically stops the spin of the main gear wheels during gear retraction?. Emergency brakes. Wheel brakes. Air Brakes. Wheel spin is not actively stopped.

How is the crew oxygen mask harness inflated?. By turning the red mask release levers to the right. By squeezing the red mask release levers. By turning the red mask release levers to the left. By pressing the red mask release levers.

Nosewheel steering pressure is normally provided by the ............... "A" system. "B" system.

The PSU doors are released by ................... hydraulic pressure. manual levers. pneumatic pressure. electrical activation.

Normally - during flight - the gear are locked in the up position and all Landing Gear Indicating lights are ....... out. in.

The engine start valve is ............. controlled, and...............operated. pneumatically : electrically. electrically : hydraulically. electrically : pneumatically. hydraulically : pneumatically.

Fuel leaves the Fuel/Oil Heat Exchanger and passes by two pressure sensors and through a fuel filter. If this filter becomes clogged, a .................. light will come on, and fuel can bypass the filter. FILTER BYPASS. FUEL ICE BYPASS. FUEL/OIL BYPASS. OIL BYPASS.

If the RTO is initiated at speeds between 60 - 90 knots, the AUTOBRAKING .........................., and the AUTOBRAKE DISARM light will come on. does not initiate. initiates.

A ........................light (between the PMC switches) Illuminates whenever the engines should be in the high idle mode - but at least one engine is operating in low idle. HI IDLE INOP. LO IDLE INOP. LOW IDLE. HI IDLE.

The 737-300/500 is powered by two CFM 56-3-B1 high bypass turbofan engines rated at..................thrust at sea level on a standard day. 20,800 lbs. 19,500lbs. 25,000 lbs. 20,000 lbs.

The PSU doors are released by ..................... . electrical activation. hydraulic pressure. temperature. pneumatic pressure.

The EEC is a ............... computer. 1 channel. 4 channel. 2 channel. 3 channel.

Are any cockpit indicating lights installed to monitor the position of the nose gear doors?. Yes. No.

An amber ENG FAIL alert appears on the EGT display if the N2 rpm below ...... with the start lever in idle. 40%. 55%. 50%. 60%.

Are any cockpit indicating lights installed to monitor the position of the main gear doors?. No - the doors are mechanically connected to the landing gear assemblies. Yes- the main gear door information is available.

The LOW OIL PRESSURE light will come on if the engine oil pressure is at or below the ................... on the Oil Pressure Indicator - wich is approximately 13 psi. green band. yellow band. normal band. red band.

Accumulator pressure operates the brakes as a last resort. The Brake Pressure gauge in the cockpit will indicate .................. when the accumulator depleted. 1000 psi. 0 psi. 1500 psi. 500 psi.

Where is the control panel for the Anti-Skid and the AutoBrake Systems?. To the right of the Landing Gear Lever. To the left of the Landing Gear Lever. To the right of the First Officer's seat. To the left of the Captain's seat.

Where is the switch located in the cockpit that allows the flight crew to manually activate the solenoids to open all PSU doors?. Aft overhead panel. Right side of the fuselage. Left side of the fuselage. Forward overhead panel.

The hydraulic pressure for gear retraction/extension is normally delivered by the............., however, the..................can provide the pressure to raise the gear through the Landing Gear Transfer Unit. "B" system : "A" system. "A" system : "B" system.

The primary airflow continues to flow normally during reverse operations. True. False.

At what cabin altitude will the PSU door solenoids be automatically activated?. 14,000'. 10,000'.

Before the scavenge filter becomes clogged, the pressure sensors will illuminate the ........................ light. HI BYPASS TEMP. OIL FILTER BYPASS. LO OIL PRESS. HI OIL TEMP.

The RTO mode disarms automatically when the right main gear lifts off during takeoff, however ............................. the AUTO BRAKE DISARM light Illuminates. the AUTO BRAKE DISARM light does not illuminate.

What other lights comes on when the LOW IDLE light illuminates?. EGT LO. MASTER CAUTION lights and the ENG annunciator light. ENG annunciator light. MASTER WARNING and the ENG annunciator light.

the PANEL knob on the F/O's panel can adjust the integral lights in the First Officer's instruments and the AFDS mode control panel edge lighting. True. False.

When the cockpit door is locked with the control stand switch, entry from the cabin requires ........................ use of a key. electrical power.

When the cockpit lights are tested, wich lights will flash continuously?. The autoflight MCP segmented lights. AFDS flood.

With the coockpit Emergency Light switch OFF, the NOT ARMED light illuminates and the batteries ............................ will not be charged. continue to be charged.