First

(ATA 27)Which slgnal is used by elevator PCU as actuator position feedback (page 331). RVDT to PFC. LVDT to PFC. LVDT to ACE.

(ATA 27) During normal operation with one hydraulic motor operating, the speed of stabilizer movement will be: (page390). 50% of the both motors operation. 25% of the both motors operation. The same as two motors operation.

(ATA 27) Which signal is PFCS using to control elevator feel actuator in secondary mode (page 358). PFC calculates feel commands as a function of flaps and slats position. ACE calculates feel commands as a function ot airspeed. ACE calculates feel commands as a function of flaps and slats position.

(ATA 27) What Is the Indication for sheared primary pin of the inboard support flap? (Page 516). Flaps caution message shows on the status display. Flaps status message shows on the status display. Spring loaded door at inboard flap outboard fairing opens.

(ATA 27) Which access is required to replace pitch rate sensor? (Page 327). Fwd cargo aft end wall remaval. Access to E/E compartment. Aft cargo aft bulkhead panel removal.

(ATA 27) What cockpit indication is available when single pitch rate sensor fails? (Page 327). FLIGHT CONTROL light comes on. FLIGHT CONTROL SYS caution message. PFCS INTERFACE status message.

(ATA 27) Airplane on the ground. Which conditions are required for the flaps/slat secondary mode becomes active? (Page 446). Override function on the MAT. One lane is faulty. Secondary mode not available on ground.

(ATA 27) What positions of the valves will you get by replacing tail flight control SOVs to OFF position in the air? (Page 57). Left SOV closed, right SOV open, centre SOV closed. Left SOV closed, right SOV closed, centre SOV open. Left SOV closed, right SOV closed, centre SOV closed.

(ATA 27) In which modes flaperon PCU may operate? (Page 126). Normal and bypass only. Normal, bypass and blocking/damped. Normal and damped only.

(ATA 27) Which PFCS function(s) is(are) designed to improve the quality of the passenger ride in aft section of cabin? (Page 275). Gust supression function only. Modal supression function and gust supression function. Rudder ratio function only.

(ATA 27) During normal aircraft operation rudder tab will move: (page268). Same direction as rudder with twice angle in relation to airplane centerline. Opposite direction as rudder with twice angle in relation to airplane centerline. Opposite direction with same angles in relation to airplane centerline.

(ATA 27) Which of the listed flight controls surfaces skin is reinforced graphite/epoxy bonded to a core of Nomex honeycomb? (Page 266 & 342). Elevators and slats. Elevators and rudder. Slats and rudder.

(ATA 27) Which spoilers have a lockout function if no faults exists in spoiler system? (Page 202). A. 4 and 11. 1 and 14. 5 and 10.

(ATA 27) Which spoilers have mechanical signal for roll control? (Page153). 4 and 11. 5 and 10. 6,7,8 and 9.

(ATA 27) PFCS in direct mode, speedbrake lever placed to UP position. Which spoiler will move to UP position? (Page 199). All, except 4 and 11. All, except 4, 5, 10, 11. All, except 5 and 10.

(ATA 27) What action is necessary to unlatch autoshutdown relay? (Page 402). No action required, relay will auto reset after fault correction. Perform stabilizer system ground test. Reset PFC DISC switch at P5.

(ATA 27) Which flight control surface is used for roll control at cruise speed? (Page 85). Flaperons normally and ailerons using limited trim control only. Flaperons only, ailerons locked in fair position. Ailerons and flaperons.

(ATA 27) What happens with ailerons/flaperons during flaps extension? (Page 85). Flaperons droop to increase lift, ailerons only used for roll control. Flaperons and ailerons droop to increase lift and stays available for roll control. Flaperons and ailerons only used for roll control, both stay independent from flap position.

(ATA 27) During autopilot operation, the aileron trim does not work. What is the problem? (Page 87). No fault - its normal operation of the system. The actuator control electronics (ACE) is faulty. The Ailerons trim actuator is faulty.

(ATA 27) Which action must be taken to complete elevator PCU replacement? (Page 347). Full elevator system adjustment/tests must be performed. Actuator null LVDT required adjustment. Elevator cables adjustment must be checked.

(ATA 27) Which information is required to have elevator speed stability function available in flight, during autopilot operation? (Page 349). Computed air speed from ADIRU or SAARU and pitch trim signal from ACE and AIMS. Speed stability function is not available during autopilot operation. Computed air speed from ADIRU and SAARU and pitch trim signal from ACE or AIMS.

(ATA 27) The elevator off-load function automatically sets the position of which flight controls? And in wich flight mode? (Page362). Stabilizer, during manual flight orin autoflight. Stabilizer, during an autoflight mode. Elevator, during manual flight or in autoflight.

(ATA 27) When is auto speedbrake function not available? (Page 219). If R ACE defective only. If center hydraulic system is failed only. If R ACE defective or center hydraulic system is failed.

(ATA 27) When does PFCS select secondary mode? (Page 42). When PFC disconnects switch in DISC position. When two ACEs are in direct mode. When on ACE is in direct mode.

(ATA 27) Control Surface pointer does notshows on synoptic display. When: (page 60). Control Surface position unknown. Control Surface does not operate. Control Surface operates normally.

(ATA 27) Is it posible to put ACEs to direct mode? (Page 283). Yes, using ACE mode select switch. No, only automatic mode selection available. Yes, using PFC disconnect switch.

(ATA 27) What is the function of the auto slat priority valve during landing gear operation? (Page 566). It gives priority of the centre hydraulics to the flaps ans slats. It has no effect during landing gear operation. It gives priority the left hydraulic system to the slats.

(ATA 27) What will happen when the aircraft is in the air with the autopilot engaged at the pilot operates the control column pitch trim switches? (Page 404). Stab trim will be corrected and autopilot takes control after trim correction. The trim signal is ignored and the autopilot stays engaged. Pilot will take take full control of the aircraft.

(ATA 27) What is the necessary condition for right STCM operation? (Page 400). R and L2 ACEs available. R and C ACEs available. C and L1 ACEs available.

(ATA 52) Where on the aircraft have Battery packs been become larger ON THE -300 AIRCRAFT (page 52). Cargo handling doors. Passenger entry doors. Over wing escape doors.

(ATA 52) When are the Passenger Door Flight Locks Released? (Page 62). When the Aircraft Airspeed is below 80 Knots. Initial movement of the door handle from the closed to open position. Initial movement of the door handle from the open to closed position.

(ATA 52) What is the purpose of the Safety Switch on the Door Battery Pack? (Page 67). To prevent inadvertent operation of the emergency escape slide on opening door. To prevent external opening of the door with the door armed from inside. To prevent EPAS (Emergency Power Assist System) operation during Door maintenence.

(ATA 52) What is the purpose of the programme mechanism? (Page 22). Correctly align the door when it opens and closes. Allow for the door to open fully when the lift raft has deployed. Disconnect the escape rafts when the aircraft sinks in the water.

(ATA 52) What is the purpose of the programme chain in the entry door? (Page 12). To keep the door parallel to the longitudinal axis of the aircraft when opening. To allow for the git bar to be disarmed when opening the door from the outside. To signal EICAS that the door is not fully closed.

(ATA 52) What is the purpose of the Linear Lift piston. (Page 20). to assist the power door opening in an emergency. To connect the battery pack to the exit signs when the door is armed. To assist the door in an upward movement when opening.

(ATA 52) During manual cargo operation which of the following protects the shafts and motors against over torque (page 190). The inboard safety clutch. a mechanical shear pin. There is no safety device fitted.

(ATA 52) When removing the bulk cargo door, which of the following safety precaution is required. (Page 176). The door must be fully opened before removal eliminating any pressure in the counterbalance mechanism. The spring cartridge must be full depleted of nitrogen. A safety pin is fitted in the counterbalance mechanism.

(ATA 52) What does the flight lock mechanism do? (Page 9). Pervents the opening of the passenger doors when the airspeed is more than 80 knots. Prevents anyone opening the flight deck door from outside when the airspeed is more than 80 kts. Pervents the opening of the passenger doors when the aircraft is pressurised.

(ATA 52) The EPAS battery pack squib test light is showing a continuous amber colour. What does this indicate? (Page 53). There is airplane power to the battery pack. The safety switch is in ARM position. The Passenger entry door handle is in CLOSED position.

(ATA 52) What type of switches are used by the Emergency power assist system (EPAS)? (Page 12). Magnetic switches. Mechanical switches. Proximity switches.

(ATA 52) What prevents you from opening the lower cargo door when there is too much pressure inside the aircraft? (Page 12). Vent door mechanism. Lock handle mechanism. Pressure differential switch.

(ATA 52) In the event of a rapid decompression of the flight deck, what happens? (Page 208). A pressure sensor controls an electric actuator that disengages the flight deck door hinges and allows the door to open inwards. A pressure sensor controls the electric strike and allows the flight deck door to open inwards. Blowout panels will open inwards to equalize the pressure in the flight deck.

(ATA 52) What is used to control the rate at which the door opens or closes? (Page 24). Snubber. Spring. Bungee.

(ATA 52) How do you engage the hold open latch of the forwards equipment door? (Page 198). Turn the handle. Push the latch button. Push in the handle.

(ATA 52) What allows the Emergency door assist system (EPAS) to open the passenger door in an emergency? (Page22). Door hold-open mechanism. Snubber piston. Programming mechanism chain.

(ATA 51) How is "Allowable Damage" defined? (Page 14). As damage that is permitted with no other flight restrictions. Is defined as damage that must be repaired. Is defined as damage that must be reworked.

(ATA 51) A region of ultrafine cracks, which may extend in a network on or under the surface of a resin or plastic material is known as? (Page 11). Crazing. Crease. Delamination.

(ATA 56) Which of the following components will generate an advisory message WINDOW FLT DECK? (Page 13). The switch on the cam plunger is NOT closed. The proximity sensor on the Latch handle is in the FAR position. The power to the number 2 window film has failed.

(ATA 56) What alternate indication is available that the number 2 window has been closed correctly? (Page 15). A red Tag is visible on the fwd edge of the window. A caution message will be shown on EICAS, and the door warning light is illuminated. The yellow indication stripe on the latching handle is NOT visible.

(ATA 56) When does WINDOW FLT DECK L(R) advisory message come on? (Page 13). When alert switch closes. When proximity sensor shows FAR signal. When proximity sensor shows NEAR signal.

(ATA 56) What type of coating is applied to the number 1 flight compartment window? (Page 8). Ultra-violet prevention coating. Light sensitive auto shade coating. Rain protection hydrophobic coating.

(ATA 57) What access available for internal wing structure inspection? (Page 6). Through fuel tank and wing access doors at the bottom of the wings. Through fuel tank access doors only at the bottom of the wings. Through fuel tank and wing access doors at the top of the wings.

(ATA 55) How many panels are you allowed to remove from the horizontal stabiliser at the same time? (Page 8). No more than 2 adjacent panel. Any 2 panels on the same surface area. All panels may be removed as they are not support structure.

(ATA 53) What element does not give structural support to the fuselage? (Page 4). Nose Radome. Keal Beam. Floor beams.

(ATA 54) Before doing any maintenance on the strut, what must you do? (Page 9). Remove electrical power from the aircraft. Deactivate the engine starting system. Deactivate the thrust reverser system.