test b777

where is the broadband antenna located ?. at top of aircraft external fuselage. at cabin ceiling. at aft cargo bay.

what happens when the engine fire switch is puller ?. hydraulic pump depresurised. hydraulic fluids return to reservoir. hydraulic pump continue operation.

where is the auto throttle disscinect caution displayed?. on the primary flight displays (PFD). on the navigation displays (ND). on EICAS display.

which components decrease interference with the radio receiver antennas by reducing the amount of static electricity. the airplane surface static dischargers. the audio management unit (AMU) filter selector. the antennas self mounted filters.

what hazard are necessary to consider when working with fiber optics on the B777?. the fiber optics strand when transmitting. may produce electro static discharge. the light from the optical fiber is invisible and intense enough to cause eye damege. the light circulating inside the fiber optic strands produces heat that may cause skin damage.

which component changes 115VAC/400Hz power to 110VAC/60Hz for providing personalelectronic devices (PEDs) power. the in-seat power sulpply (ISPS). the master control unit (MCU). the outlet units (OUs).

what is the purpose of the overhead panel ARINC 629 system (OPAS). to send flight deck switch position data to the ARINC 629 systems buses and receive data to turn on and off some flight deck panel ligh. to control the master dim and test fuction on the overhead panel when commanded by the remote light sensors (RLSs). To control the overhead panel light and switched lights of the LRUs connected to the ARINC 629 data bus only.

in the cabin interphone system (CIS) , when performing a test from the cabin system control panel (CSCP) , which test can we select to collect major fault of the address/cabin interphone (PA/CI) controller and the zone management units(ZMUs) only: the engineering tests. the Quick test. the All Test.

where does the cockpit voice recorder (CVR) receive the sound signal from. from the captain , first officer and first observe channel of the audio management unit (AMU) and the cockpit microphone. from each captain , first officer and first observe audio control panels (ACPs) , and the cockpit microphone. from the captain ,first officer and service intephone channel of the audio management unit (AMU) and the cockpit microphone.

to reset the ELT after accidental activation. select DISARMED position of guarded switch in the ELT control panel. select off position of guarded switch in the ELT control panel. select RESET position of guarded switch in the ELT control panel.

if there is an internal failure on the audio management unit (AMU) that affects the captain's audio , how can the captain maintain comunication ?. by selecting the Observer audio selector from NORM to CAPT. by selectingthe observer Audio selector from NORM o ALTN. by plugging the headset prong from the captain's jack to the observer's jack.

wich of the following components are part of the HF system. Audio manangement unit. left and right HF transcelvers , decoder and antenna. Audio manangement unit.left and right HF transcelvers, coupler and antenna. Audio manangement unit.left and right HF transcelvers ,left and right couplers and antenna.

How can the SATCOM system be controlled. by the satellite data unit (SDU) display. By the control display units (CDUs). by the maintenance access terminsl (MAT).

An LRU connected to the ARINC 629 data bus is in monitor or transmit mode ; what occurs when there is a fault on he monitor fuction. the transmitter will continue operating. the trasmit fuction will stop too. the LRU switches to alternate monitor mode.

how can the flight deck communication system (FDCS) main menu be displayed. By select the COMM switch on the display select panel ( DSP). By the data uplink control switches on the glaresshield panel p7. By selecting the FMC COMM switch on the control display Unit (CDU).

how can the printer be tested ?. by pushing the momentary TEST button on the printer. by the printer menu on the data comunication management system (DCMS). by accessing the printer menu on the maintenance access terminal (MAT).

the emergency locator trasnmiter (ELT) uses power from. airplane 28 DC power. its own batteries 14 DC. airplane 14 DC power.

how is the view direction adjusted on the cockpit video survellance cameras. the control of the view angle is achieved from the LCD monitor controlswiches. he cameras are installed on the housing with a fixed predefined angle. the housing where they are mounted allows the cameras to swivel in any direction.

which flight management system CDU is used as the interfas of the passenger addres/cabin interphone (PA/CI) controller?. center CDU. all CDUs. none.

whatis displayed on the integrated standby flight display?. altitude and speed. attitude, airspeed , altitude. attitude and speed.

alternate landing gear extension system consist of. push/pull cables. hydraulic pump operated by electric motor. hydraulic motor operated by the alternate motor.

what is the purpose of semi-levred gear (SLG). lock landing gear in the stow position. assist in landing gear steering. pust truck in proper position for takeoff and landing.

primary flight control system (PFCS) mode are. direct ,secundary and normal. primary , secundary and stanby. normal , secondary and stanby.

when pilots move the aileron trim switches, the aileron trim actuator operates to move. Aileron only. Aileron and spoilers. Aileron and flaperons.

which galleys have their air chillers above the galley. All the galleys. he galleys aft of the aft cabin doors. The galleys forward of the aft cabin doors.

how do the chillers work?. using cold air from he airconditioning packs. on the vapour -cycle principle. using ambient cold air.

when does the cargo system controller (CSC) turn on the power to the cargo handing system. when the cargo door is fully open. when the ground service bus is powered. when the control joystick is moved.

what is the function of the stowage bin snubbers?. control the rate at which the stowage bins open and close. dampen out airframe vibrtions. dampen the movement of the suitcases inside the stowage bin.

which of the following statements is NOT TRUE regarding captain /first officer seats?. The emergency stop switch removes power from the seat. The emergency stop switch removes power from the vertical control circuits. The emergency stop switch removes power from he horizontal control circuits.

cual es la potencia del capitan de los asientos. trifacica 115-400Hz utility bus. none.

how many pumps are used for the hydraulic system?. 4 pump hydraulic and 4 man. none.