pepsi o cocaa

the electro-mechanical brake system consists of: eight electric brake actuator controllers (EBAC) and thirty-two electric brake actuator (EBA), four per brake. four electric brake actuator controllers (EBAC) and thirty-two electric brake actuator (EBA), four per brake. four electric brake actuator controllers (EBAC) and eight electric brake actuator (EBA), one per brake.

the 787-9 MLG upper and lower side are made of: steel. a composite material. titanium.

in the hydraulic system, the priority valves are: mechanical divices, and they are used to ensure primary fight control flow. electrical divices, using input from HYDIF during engine fire condition. mechanical diveces, and they are controlled from dedicated flight deck rotary selector.

in which primary flight control function (PFCF) mode operate autopilot?. normal mode only. normal and secondary modes. autopilot is available in all three control modes.

how many hyd accumulators are there?. five, one in each reservoir and two for NLG. three, one in each hyd reservoir. four, one in each hydraulic reservoir and one for NLG.

the hydraulic reservoir bootstrap type uses: engine bleed pipe to pressurize the reservoir during takeoff phase only. hyd pressure to pressurize the reservoir. pneumatic pressure from LH CAC to pressurize the reservoir.

autobake control is part of: right BSCU. CCS. left BSCU.

the hight lift system is working in alternate mode, the extension is limited to: flap 20 position and full slats. extension is not limited. flap 20 and slats to middle positions.

what is the purpose of the 4 modal supression accelerometer (2 fwd, 2 aft ), in the flight comtrol system?. to monitor pitch and roll movement for flight envelope protection. to monitor lateral and vertical movement to make ride quality better. to monitor vertical and lateral acceleration in orden not to exceed "G" forces on the fuselage: load limitation.

during secondary and direct primary flight function (PFCF) modes the elevator feel position command is calculate from: flap position. pitot impact pressure. elevator feel positions is inhibited in this modes.

how can you retract the RAT ?. during final approach with P5 sw. during ground, center hyd sys ON, GDN test sw in ENABLE and P57 stow in ON position. during ground, center hyd sys ON, GDN test sw in NORMAL and P57 stow in ON position.

the spoilers droop improves: lift by control of the gap between trailing edge and spoilers. lift by control of the gap between leanding edge and spoilers. drag by flight control laws.

when is the EDP depressurization valve energized ?. when the onside demand pump sw is set to off position. when the EDP control sw in the P5 is set to off position. when the onside demand pump sw is selected to auto position.

which is the function that controls the hyd system?. HYDIF. ADRF. DECAF.

The main landing gear ARDC monitors. tire pressure only. brake life, EBA force. wheel speed, tire pressure, brake temp.

if the door unsafe lights are off. the door is in safe condition to enter the wheel well. the door is moving to the close or open position. the door is in unsafe condition to enter the wheel well.

when is the engine supply shutoff valve closed. when engine driven pump (EDP) has an internal malfunction. when associated hydraulic system quantity is low. when the engine fire handle is pulled.

why the spoilers 6 and 9 reise slightly during tekeoff?. to decrease pilot workload during high lift operations. to decrease drag during first takeoff phase. to increase cooling of brake remote data concentrator (RDC).

during normal landing gear retract or extend sequences: each control proximity sensor in a pair must show the same condition. control proximity sensors are not monitoring during landing gear extend or retract sequences. at least one control proximity sensor in a pair show near.

during engine high power test, the clamping force changes to. run-way hold mode. park and adjust mode. 100%.

if the is a total failure of the fly-by-wire system, a direct path from control wheels is provides for spoilers numbers. 4 and 11. 1 and 14. 5 and 10.

in interface to NWS, the tiller turns: up to 70 independently of aircraft speed. up to 70 at low speed and as speed increases, the tiller allowable turn angle decreases. up to 70 at high speed and as speed decrease, the tiller allowable turn angle decreases.

the fail safe position for the EDAS system doors in 787-9 is: close. open. intermediate position.

in the center hyd sys, the B787 has two EMP (C1 and C2) pumps, wich is primary pump?. C1 is the primary. C1 or C2 operate as primary pump depending on calendar day. C2 is the primary.

the landing gear alternate extension system is used to: extend and retract the lading gear during normal operation. extend the landing gear during abnormal operation and close the landing gear doors on ground for maintenance. extend the landing gear during abnormal operation and open the landing gear doors on ground for maintenance.

on the 787-9, the landing gear doors will go the close position after 30 seconds if the pilot does not move the landing gear lever to the UP position, which system/component/function is in charge of this operation ?. the MLG door safety valve module. the LGA/NWS function. the MLG bypass/Off relay.

why is it recommended that a minimun of one FCE must be installed at all times?. to keep the best fuel consumption airplane configuration. to keep the rigging data for data the current airplane configuration. to decrease pilot workload.

which flight control electronic (FCE) cabinet has FCE batteries?. FCE left and right. FCE left only. FCE C2 and C1.

the suction shutoff valves in each reservoirs are used to. stop the hyd fluid if engine fire handle is pulled. stop the engine driven pump (EDP) operation during abnormal conditions. stop the flow of hyd fluid from the reservoir when it is low.

the variable camber trim unit is used to. move the flap during skew conditions. prevent spoilers contact during retract conditions. move independently inboard and outboard flaps.

the auto bleed valve is used to: manually bleed the air from hyd reservoir. bleed the air from hyd reservoir during cruise. bleed the air from hyd reservoir on ground only.

how many control modes does the primary flight control function (PFCF) have?. two control modes; normal and direct. three control modes; primary, secondary and direct. three control modes; normal, secondary and direct.

if you turn both nose wheel steering tiller in the same direction then: LGA/NWS control function sends EICAS message and NWS no turn. LGA/NWS control function adds the tiller positions together. LGA/NWS control function subtracts the tiller positions together.

the proximity sensor data concentrators (PSDC) are used to. send the electrical request to all EBA motors. monitor the near or far conditions of many proximity sensors. control the landing gear bypass/auto off valve module.

the alternate pitch trim switches signals goes: directly to remote electronic unit (REU). directly to electrical motor control unit (EMCU). flight control electronic (FCE) and then to electrical motor unit (EMCU).

How can you return from secondary control mode to normal control mode?. automatically if the failures go away. manually, setting the PFC disconnect sw to DISC position. manually, setting the PFC disconnect sw to DISC position and then to AUTO position.

MLG truck positioner actuator is in stowed position if. MLG is 12 nose down. MLG is weight of wheel. MLG is 12 nose up.

how many channels does the NWS remote electronic unit have?. two channels, both active and changes every gear retraction. one channel. two channels, one active other standby and changes every gear retraction.

where are the air/ground sensor located ?. strut compressed and truck tilt proximity sensor are located in left main landing gear only. strut compressed and truck tilt proximity sensor are located in both main landing gear. strut compressed proximity sensor in nose landing gear and truck tilt proximity sensor in both main landing gear.

how many hyd power control units (PCU), for the spoilers system are in the B787?. 10. 14. 12.