Second

(ATA 30)What is type of engine anti-ice valve? (page 46). Pneumaticaly-operated piston type valve. Torque motor controlled, flapper type valve. solenoid-controlled, pneumaticaly-operated valve.

(ATA 30) Which anti-ice system gets the icing signal from ice detectors if it is detected for short period of time: Engine anti-ice (EAl), or Wing anti-ice (WAl)? (Pag 12). Wing anti-ice system first. Engine anti-ice system first. Both systems simultaneously.

(ATA 30) What must be done if one window temperature sensor fails? (Pag115). Replace with new sensor. Switch to spare sensor with burndy block. Select the spare sensor with backup switch.

(ATA 30) When do pitot probes get the low heating power? (Pag 74). After engine starts. The airplane is in the air. The airspeed is more than 50 knots.

(ATA 30) RR RB211 Trent 800. Where is power for the heater in the P20/T20 probe supplied from? (Pag 102). Power control unit (PCU). AC standby bus. Left or right De bus.

(ATA 30) Which window (s) are heated with the LEFT FWD WINDOW HEAT Switch ON? (page 114). L2, L4, L5. L1 only. L1, L2, L3.

(ATA 30) What is the power source for the Drain masts heating? (page 148). 28V AC or 115V AC. 28V AC. The warm air.

(ATA 30) What is indicated by four amber window OVERHEAD lights on the windows anti-ice panel? (page 115). Four amber OVERHEAD lights give the crew visual indication of apply current to the window heat system when necessary. They give indication of overheat condition on No.1 & No.2 windows. Four amber OVERHEAD lights give the crew visual indication of overheat conditions for the No.1, 2 and 4 windows.

(ATA 30) GE 90-What stage if air is used for engine cowl anti ice? (page 40). HP7. P6. HP3.

(ATA 30) RR. RB211 trent 800. What stage of air is used for Engine cowl anti-ice? (pag 40). HP7. P6. HP3.

(ATA 30) PW 4000 What stage of air used for enigine cowl anti-ice? (pag 40). HP15. HP3. HP6.

(ATA 30) where is EAI valve controller on the GE 90 enigine? (Page50). on the left side of the fan case at the 7:00 position. on the right side of the enigine fan case at 3:30 position. on the right side of the fan hub at the 1:30 position.

(ATA 30) Where is engine anti-ice (EAI) valve controller on the RR RB211 Trent 800 engine? (page 50). On the left side of the fan case at the 07:00 position next to the PRSOVC. On the right side of the fan hub at the 1:30 position inside the fan hub above the engine core. On the right side of the engine fan case at the 3:30 position between the PRSOVC and HPFAC.

(ATA 30) Where is EAl pressure sensor on the GE 90 engine? (pag 54). On the right side of the engine fan case. On the left side of the fan case. Inside of a cooling air shrouded.

(ATA 30) To what pressure does the WAI valve regulate? (Page 11). APPX 38 PSI. APPX 20 PSI. APPX 65 PSI.

(ATA 30) How is WAI position sensing achieved? (page 28). An RVDT on the WAI valve. A thermostat unit on slats 2 and 15. A pressure sensor aft of the WAI valve.

(ATA 30) Which of the following statements is correct? WAI is available for: (page 30). All slats. Slats 2-6 and 11-15 only. Outboard slats only.

(ATA 30) Where does the WAI valve receives command signals from? (page32). The ASCPCs. ACIPS cards. The ADIRU.

(ATA 30) How is Anti fogging control for the number 1 window disabled? (page 115). Connecting the wiring at the E1 rack Burndy block. Using the back up window heat system on the P61 panel. Using thr FWD window heat control switches on the P5 panel.

(ATA 30) Where are the Waste tank and galley drain line heaters controlled from? (page146). A separate temp sensor in the wing to body fairing. The ACIPS cards. The back up detection cards.

(ATA 30) Where can WAI and EAI flow rates be observed? (page 10). On the EICAS secondary page. On the ice protection maintenance page. There is no indication of flow rate.

(ATA 30) Which of the following statements is correct? The ice detection probe sends: (page 66). Vibration signals to the ACIPS cards. Temperature signals to the ice detection cards. Resistance signals to the ECSMC cards.

(ATA 30) How are the AOA sensors heated? (page 96). a. Pneumatically from the centre manifold. Electrically from ELMS. electrically when no Pneumatics are available.

(ATA 33) Which of the following is NOT tested by the master dim and test system? (Page 64). Rudder trim indicator. Engine fire switches. External power AVAIL lights.

(ATA 33) What controls the level of light from the landing lights? (Page 250). Proximity electronics unit (PSEU). Electrical load management system (ELMS). Overhead panel ARINC system (OPAS).

(ATA 33) What happens to the wing landing lights when the landing gear is up and locked? (Pag 264). The lights switch after. The lights operate DIM. The lights operate Bright.

(ATA 33) Cabin lighting tests are conducted through which of the following? (Page 89). The CSCP área control panel. FWD attendants panel. MAT only.

(ATA 33] What power the backup lights in the overhead flight attendants rest (OFAR)? (Page 168). Main Aircraft Battery. Standby bus. Battery packs.

(ATA 33] The engines are running and the flight deck door is opened. What happens to the Direct ceiling light immediately aft of the door? (Pag 101). it's already out as engines are running. It iluminates full bright. It goes out.

(ATA 33) How are the cockpit chart lights re-lamped? (Pag 60). Open the cockpit window to access the bulb. The panel must be replaced as the they are integral. By removing the lens cover over the bulb.

(ATA 33) What happens if a single channel fails on MD&T card? (Page 71). Status message is generated. All Flight deck annunciators fail. maintenance message is generated.

(ATA 33) What are the 4 modes of dome light operation? (Pag 26). Normal, Backup, Standby & storm. Bright, Dim, Night & Storm. Ground, Flight, Emergency & Storm.

(ATA 33} Which power source is required for the environmental control system (ECS) bay lights to work? (Pag210). Battery bus. Ground service bus. Ground handling bus.

(ATA 33) Where does the ZMU receives signals from? (Page 91). The PSUD’s to adjust the lighting brightness. The OEU’s to operate the lights. The ZMU controller for emergency exit operations.

(ATA 33) The master Dim and Test card files can be found? (Page 67). P29, card files in the flight deck. In the MEC. P74 panel, above the L2 galley ceiling.

(ATA 32) When do the Cargo door mounted lights illuminate? (Page 216). The door is fully opened. The door access panel is opened. When the door is fully opened and the switch is selected.

(ATA 33) When will the lights automatically illuminate with the Emergency Light Switch? (Page 324). When the L & R Main DC busses have lost power. When the transfer busses are powered. When the Utility busses have lost power.

(ATA 45) How is data transfered from the AIMS to the MAT (Maintenance Access Terminal)? (Page 25). Over the AVLAN on a fibreoptic bus. On an ARINC 629 data bus. On an ARINC 429 data bus.

(ATA 45) In the engine balancing system of the MAT, how many weight partnumbers and locations can the existing balance weight data list for the fan contain? (Page 243). 30 weight partnumbers and 30 locations. 15 weight partnumbers and 15 locations. 1 part number and 1 location.

(ATA 45) What is the function of the AVLAN system? (Page 25). Provides high speed communications between CMCS and aircraft systems. Allows external devices such as laptop to communicate with the aircraft systems. provides high speed comunication between AIMS and MAT or PMAT.

(ATA 45) Which CMC function is normally the Primary?. L/H CMCF. R/H CMCF. Alternates each Air/Grnd transition.

(ATA 45) The engine balancing function of the MAT allows which type of balancing? (Page 255). Fan and high pressure turbine. Fan balancing only. Fan and low pressure turbine.

(ATA 45) When perfoming a MAT test, the test condition shows INHIBITED. How can you find out why the test was inhibited and how to proceed? (Page 109). By selecting the TO TEST control button. By selecting the maintenance message data button. By selecting ATA 31 on the FMS CDU.

(ATA 45) Where can Onboard engine balancing be carried out? (Page 61). At the AVM unit on the E6 shelf. Cannon plug on the AIMS cabinet. Using the OEBS through the MAT.

(ATA 45) Where can Maintenance Memo's and Scheduled Maintenance Tasks messages be found on the MAT (Maintenance Access Terminal)? (Page63). Fault History. Inbound FDE's. Maintenance Planning.

(ATA 45) Existing flightdeck effects are: (page 69). Not flight phase screened. Flight phase screened. Only faults from the last flight.

(ATA 45) The central maintenance computing system (CMCS) is; (page 11). Built into the ELMS. A computing function in AIMS. A stand-alone computing system.

(ATA 45) What is the purpose of the ground test switch? (Page 21). at is required for all ground test. Overrides air/ground system to simulate air mode. Lets some ground tests operate.

(ATA 45) Where is the CMC function? (Page 27). CPM/COMM in AIMS. CPM/GG in AIMS. E2 Rack MEC.

(ATA 45) A condition that requires repair or deferral is known as: (page 9). Maintenance message. Status message. Flight deck effect (FDE).

(ATA 32) What controls the MLG extension speed? (Page 68). Flow restrictor in the actuator retract port internal structure. Actuator rod end snubber by the end of the extension stroke. Alternate extension system pressure in retract actuator.

(ATA 32) When do the normal end alternate brake metering valves get pressure together? (Page 269). During normal braking. During alternate braking. During gear retract braking.

(ATA 32) Can tail skid be retracted after tail strike? (Page 236). Yes, if just the fuse pin is broken. No, due to tail skid cartrige being crushed. Yes, if just tail skid cartrige is crushed.

(ATA 32) The MLG drag brace operated sequence valve controls the: (page 77). MLG door close operation during landing gear extension. MLG side brace down lock actuator during landing gear extension. MLG drag brace down lock actuator during landing gear retarction.

(ATA 32) What does Weigh-ON-Wheels (WOW) system monitor for air/ground indication (page 220). MLG beam bending. MLG shock struct compression. MLG truck tilt.

(ATA 32) When are the semi-levered gear hydraulic structs commanded to unloack (page 48). The airplane on the ground. The airplane are in a takeoff position. The airplane are in the air.

(ATA 32) How is the hottest brake on each main gear truck indicated on the synoptic page? (Page 384). Flashing brake symbol. Solid white brake symbol. Brake temperature indication in red.

(ATA 32) What does the ELMS auto-off relay execute? (Page 56). Operate the control lever lock solenoid on the ground to lock lever in down position. Operate the control lever lock solenoid during the air/ground changeover. Removes the power of the UP solenoid and the selector moves to OFF to remove the pressure.

(ATA 32) MLG steering operates: (page400). Simultaneously with NLG steering. When NLG turns more than 13 degrees. Independently from NLG steering.

(ATA32) Which sensor is using by PFCs for auto speedbrake operation? (page 198). MLG down proximity sensor. MLG truck tiltsensor. Weight-On-Wheel system sensor.

(ATA 32) What gives gear door unsafe condition indication? (Page 139). Amber light at NLG and MLG door manual extension panels. Red light each landing gear wheel well. Red light above alternate extension switch in cockpit.

(ATA 32) What type of sensors are the Weigh-ON-Wheels (WOW)? (page216). Variable inductance type sensors. Variable reluctance strain measurement sensors. Magnetic proximity type sensors.

(ATA 32) What hydraulic pressure can be used for parking brake aplication? (page 285). Only normal and accumulator brake pressure. Any available brake pressure. Only alternate and accumulator brake pressure.

(ATA 32) What controls the tailskid actuator? (page 234). The taild skid dedicated hydraulic system. The MLG actuation system. The gear alternate extension system.

(ATA 32) When is the anti-skid control available? (page 342). When wheel speed is less than eight knots. At airplane touchdown during landing. When wheel speed is greater than eight knots.

(ATA 32) The “GEAR INDICATION SYS” status message indicates the failure of? (page 206). One gear UP sensors on each gear. Either NLG not-compressed sensor. One door sensor on each gear.

(ATA 32) What must be removed in main electronic compartment to get accessto NLG steering broken cable compensator? (page 411). Crew oxygen bottle. Main battery. ADIRU with its cover.

(ATA 32) Which proximity sensor electronic unit (PSEU) ha the flight lock and cargo control functios? (page 167). PSEU 1 only. Both PSEU simultaneously. PSEU 2 only.

(ATA 32) What type of sensors is used for tire pressure measurement? (Page389). Piezo-electric device. Strain gauge device. Aneroid device.

(ATA 32) Where do the weight on wheel, (WOW), cards receive their information from?. Weight On Ground switches on the shock struts. Load sensors on each MLG structure beams. Truck Levelling sensors.

(ATA 32) Which of the following statements is correct? The Nose Gear steering tiller inputs turn the Nose Gear up to: (page 402). 70 degrees in each direction, the rudder pedals up to 7 degrees in each direction. 65 degrees in each direction and rudder pedals up to 15 degrees in each direction. 72 degrees in each direction and NO rudder pedal input is available.

(ATA 32) How can the MLG steering system be disabled: (page 428). An action through the MAT. A manual shutoff valve handle on the main landing gear steering PCA. Inserting a pin in the MLG steering torsion bar.

(ATA 32) Where is the MGSCU, (Main Gear Steering Control Unit), located? (Page426). On the E5 rack in the MEC. In the RH MLG Bay. On the E6 rack in the Aft Cargo Hold.

(ATA 32) What hydraulic pressure is used for gear retract braking? (Page 259). Landing gear retract pressure. Alternate brake system pressure. Reserve brake system pressure.

(ATA 32) With centre hydraulic system low quantity, how is the reserve brakes and Nose wheel steering systems protected? (Page 281). The hydraulic system control isolates the output of C1 ACMP for brakes and steering only. Reserve brakes and Nose wheel steering uses brake accumulator pressure. The RAT will auto deploy.

(ATA 32) What does the P1 amber brake source indication show? (page 279). The braking system is in the alternate mode of operation. Brake accumulator pressure low. Normal and alternate brake system pressures low.

(ATA 32) What is the purpose of the brake accumulator pressure transducer? (page271). For brake accumulator pressure indication on the P1 panel indicator. To inform AIMS that the parking brake is applied. To illuminate the brake source indicator light on the P1 panel.

(ATA 32) How are tiller position signals to signal MLG steering system initiated? (Page 422). Tiller position transducers through the MGSCU. Cable position drums on the tiller interconnect unit. Switches on the Interconnect bell crank arms.

(ATA 32) Which of the following statements is correct? The MLG steering manual shut of valve permits the system to be: (page428). Hydraulically powered on the ground. Hydraulically unpowered. Electrically disabled on the steering control valves.

(ATA 30) The function of the alternate extend hydraulic pressure switch is to: (page137). turn on the alternate extend power pack when there is a failure in the center hydraulic system. supply pressure indication to the Airplane information management system (AIMS). turn off the alternate extend power pack after the completion of the alternate extend cycle.

(ATA 32) During Landing Gear Gear up operation... (Page 259). the normal Brake Metering Valve supplies Brake pressure to reduce the wheel speed. the accumulator pressure is used to reduce the Wheel speed. gear retract pressure goes through the Alternate braking system to reduce the wheel speed.

(ATA 32) The signal of the pedal position switches... (Page 299). make the red "BRAKE ON" light come on when the brake pedals are applied. deactivate the alternate anti skid system on ground. make the "BRAKE OFF" light come on.

(ATA 32) What is the function of the lockup solenoid?. Will lock the SLG in alternate extension. To will lock the floating piston in the SLG actuator. Hold the gear in the retracted position and release hyd pressure to the up actuator.

(ATA 32) What does the status message SEMI LEVER GEAR LOCKS indicate? (Page 206). The locks have failed. One of the gear up lock proximity sensors has failed. Un-commanded SLG lock solenoid operation.