TAA 27-29-32 NEW

Related to the operation of the primary Flight Controls, the system: Is a Fly by Wire System: a mechanical input, electrical control, hydraulic operation. Is a fully electrical system. Receives only mechanical inputs and hydraulic pressure.

In the center reservoir, the suction shutoff valve stops hydraulic flow to the: Electric motor pump (EMP) C1. Right engine driven pump (EDP). Electric motor pump (EMP) C2.

Why is necessary to set in IRU ON before you operate the Electric Motor Pump (EMP). To do a better control of the electrical power if you operate any EMP using external power. To reduce the output pressure at 3000 psi during APU maintenance program only. To increase the speed at 5500 RPM.

Park and adjust control mode of the BSCU means. Adjust option for maintenance purpose only (CMCF). Keep moving EBAs(for 1 hour) to keep clamping force during brake cooling period. Release the clamping force due thermal changes.

In the high lift alternate mode, the flaps and slats use. Hydraulic power to extend and electrical power to retract. Electrical or hydraulic power to extend and retract. Electrical power to extend and retract only.

The BSCUs have two channels: Fwd and Aft brakes. Nose and main wheels. Inboard and Outboard brakes.

How are the AFT door of the nose landing gear operated?. Mechanically operated. Electrically operated. Hydraulically operated.

Flight control electronic (FCE) batteries supply power to related FCE cabinet for: 10 minutes. 30 minutes. 60 minutes.

The Horizontal Stabilizer is actuated by: Hydraulic actuators. Hydraulic motors. Electrical motors.

How can the engine driven pump (EDP) be depressurized?. Manually (EDP Sw or Fire handle) or automatically (HYDIF). Manually from EDP Sw only. Manually from EDP Sw or Fire handle.

How many hydraulic system isolation valves are there?. Three isolation valves in the center hydraulic system. Three isolation valves, one in each hydraulic system. Two isolation valves in the center hydraulic system.

The Roll channel is controlled by: Aileron and Flaperon. Only Ailerons. Flaps.

The spoilers 4,5,10,11 are: Operate by EMA´s. Operate by EMCU´s. Operate by PCU´s.

What is the main function of electrical brake actuator controller (EBAC)?. It monitors the brake temperature. It controls the associated hydraulic brake actuators. It controls the electrical brake actuators (EBA).

Which is the function of the hydraulic system heat exchangers?. To cool the hydraulic fluid and warm the engine oil. To warm the hydraulic fluid and cool the engine oil. To cool the hydraulic fluid and warm the tank fuel.

When is the ´Brake Temp´advisory message shown on EICAS?. If a brake temperature indication has 5.0 or more. If a brake temperature indication has low pressure. If a brake temperature indication has lower than 5.0.

which fligth control electronic (FCE ) cabinet does not have flight control module (FCM). flight control electronic ( FCE)cabinet C1. flight control electronic (FCE) cabinet C2. flight control electronic (FCE) cabinet right.

Autobrake control is part of: Right BSCU. left BSCU. CCS.

Related to the Hydraulic system, the aircraft has: Three independent; one main, one secondary and an auxiliary system. Three independent system; left, right and center system. Two main system; left and right, and an auxiliary system.

The purpose of the EDAS/HLFC system, in flight controls on the B 787-9 is to provide: Increase riding characterictics and a better and comfortable flight experience for the passanger. Better handling characterictics from the flight controls point of view. Reduce drag and fuel burn in cruise flight.

The 787-9 Flap control laver module has: 9 positions. 30 positions. 10 positions.

The engine driven pump is: An axial piston, variable displacement, output pressure 5000 psi and 25 gpm maximum. An axial piston, variable displacement, output pressure 3000 psi and 25 gpm maximum. Gear pump, output pressure 5000 psi and 25 gpm maximum.

In the landing gear, the Main Brake System is: An Hydraulically operated system. An High Air pressure system. An electrically operated system.

Which unit is used to pressurize the landing gear alternate system?. Dedicated electrical/hydraulical power. C1 EMP (Electrical motor pump). C2 EMP (Electrical motor pump).

The Spoilers EMA´s are controlled by: SREU´s. REU´s. EMCU´s.

Where is NWS remote electronic unit located?. Forward EE bay. B-787 does not have NWS remote electronic unit. Internal of P40.

During the approaching procedures: The spoilers droop to increase the wing lift with the lift system. The spoilers doesnt move, because the airplane is in the final approach. Only the spoilers help to the high lift system.

For controlling the nose Wheel Steering, the system uses: Two hydraulically operated actuators. Two electrically operated actuators. A mechanically controlled and electrically operated actuator.

To operate high lift in alternate mode, you need select: Arm switch to arm position and control selector to retract or extend position. Flap lever to desired position. Arm switch to arm position and flap lever to retract or extend position.

How many flight control electronic (FCE) batteries does the B-787 have?. Two FCE batteries. One FCE battery. FCE system use the main and APU betteries.

For wich function are used the flight control surface lock switches?. To return from direct to normal flight control mode. To reset the flight controls in flt. To lock the wing or/and tail flight control surfaces during maintenance.

Where is the left hydraulic EMP located?. On the engine strut. On the LH main wheel well. On the trent gearbox.

The LVDT in the hydraulic reservoir sends Qty information to: CDU pages. Eicas page. Status page, synoptics page and maintenance page.

How many control mode does the high lift function (HLF) have?. Two control mode; primary and backup. Three control mode; primary, secondary and alternate. Three control mode; normal, secondary and alternate.

When the RAT (Ram Air Turbine) operates in emergency, it supplies hydraulic pressure to: Right system Flight Controls. Center system Flight Controls. Left System Flight Controls.

The inboard and outboard spoilers PCUs are: Fulle interchangeable. The spoilers havent PCUs. Not interchangeable.

The Nose landing Gear ARDC monitors: Tire pressure only. Air/Gnd signal. Wheel speed.

What do you use to remove power from the horizontal stabilizer in a run-away condition?. Opposite elevator movement. Horizontal stabilizer cutout switches. Primary flight control disconnect switch.

If all FCE´s fail: Limited roll control is possible (Spoilers 4 y 11). Roll control is lost. Mechanical back-up must be used.

How many channels does the NWS remote electronic unit have?. Two chennels, one active other standby and changes every gear retraction. Two channels, both active and changes every gear retraction. One channel.