ERJ-190 TEST UAEAC

What is the maximum capacity of the water potable tank. 120 Lt. 100 Lt. 110 Lt.

How many hyd systems are there in the ERJ – 190 and where are located: 2; 1 and 2 located in the rear fuselage. 4; 2 and 4 located in the left side of fuselage and 1 and 3 in the right side. 3 ; 1 in the LH center fuselage bay, 2 in the RH center fuselage bay, 3 in the aft fuselage.

What is the function of PTU: Transfer hyd power from sys 1 to sys 2 if EDP fails and assist landing gear. Transfer hyd power from sys 3 to sys 1 if ACMP fails and assist pilot. Transfer hyd power from sys 2 to sys 3 if ECS fails and assist brakes.

How many hyd EDP are installed in the aircraft: 4 in the AGB. 2 ; either in the LH AGB and RH AGB. 3; in the LH AGB , RH AGB and APU AGB.

Where is installed the two engine fire extinguisher bottles: R/H rear wing to fuselage fairing. L/H rear wing to fuselage fairing. Mid. E-Bay.

What is the maximum differential of pressure in the aircraft: 9.6 PSI up to 41,000 ft. 8.6 PSI up to 41,000 ft. 6.5 PSI up to 41,000 ft.

What is the maximum angle of the nose wheel with the steering engaged: 76 degrees LH and 76 degrees RH. 170 degrees LH and 170 degrees RH. 90 degrees LH and 80 degrees RH.

What module processes all landing gear proximity sensors information: NWSCM. PSEM. EDPM.

What is the function of BCV: Modulate Hyd press for the brakes. Control Hyd press for the brakes. Monitor the Hyd press for the brakes.

What areas are monitored and protected by the fire protection system: Brakes, cockpit , purses and pockets. Engines and pylons, APU, 2 cargo compartments and lavatories. Fwd e-bay. Mid e- bay and aft e-bay.

What does mean AMS and what system comprise: Aircraft Main System ( Hyd – Elec – Pneumatic – Ice and rain protection). Air Module System ( Air Conditioning – Landing gear – Pressurization ). Air Management System (Air Conditioning – Pressurization – Pneumatic – Ice and Rain Protection).

What areas are protected to prevent icing by pneumatic bleed: Windshield – Horizontal Stabilizer – ADSP. TAT sensors, ADSP, Windshield and Water lines. Slats, Engine.

What is the function of the torque motor: Give a suitable torque to wheel assy. Monitor the slats anti – ice pneumatic press. Controls servo air pressure to the HPSOV and NPRSOV.

What is the function of precooler: Cools air from lavatories and cargo compartment. Cools oil from engine. Cools bleed air by fan when the fan air valve is open.

What is the capacity of lavatory water heater: 2 Lt. 3 Lt. 1.5 Lt.

Where is located the lavatory water heater : Fwd e-bay. Fwd RH side of the fuselage. Fwd and Aft lavatories cabinet underneath the sink.

What does mean CPCS, Where is located, How many are there and function. Cabin Press Controller System, Mid e-bay, 2, control pressurization. Cabin Pressure Control System, Fwd e-bay, 1 (two channels), control max differential press. Cabin Press Control System, Aft e-bay, 1(two channels), control stress cabin.

What is the max speed cruise of the ERJ - 190: 850 km / h. 1003 km / h. 910 m / s.

How many slat panels are there in E-190: 4 each wing. 3 each wing. 5 each wing.

What is the total capacity of the fuel tanks: 18,000 Lt (4520GaI). 17,000 Lt (4320Gal). 16,000 Lt (4220Gal).

The vent systems are designed to: Keep the pressure in the tank. Out the pressure. Keep the pressure differential (tank / ambient).

How many scavenge ejector pumps is installed. Five each wing. Four each wing. Three each wing.

In the event of failure of the fuel EDP, what type of pump supplies fuel: Backup fuel flow to the engine. DC backup flow to the engine. AC backup.

What is the max ceiling certified in the ERJ – 190: 41000 ft. 42000 ft. 43000 ft.

How many level sticks are installed in aircraft: 6 per wing. 4 per wing. 3 per wing.

When a exceeding is annunciated on the EICAS "Fuel imbalance": 380 Kg. (802) Lbs. 490 Kg. (798) Lbs. 360 Kg. (792) Lbs.

The ‘’ Fuel Imbalance’ message disappears when the difference is: 35 Kg. (77 Lbs). 55 Kg. (121 Lbs). 45 Kg. (99 Lbs).

How many probes have in total all of the tanks: 16 units each wing and one dual unit compensator/probe. 36 unit total wing. 34 probe in each wing.

What type of smoke detector is installed in the cargo compartment: Electric type. Electric type. Photoelectric type sensor.

The ice detector systems include: Four ice detector. Two ice detector. Two for each side.

How many TRU are installed on the 190: 3 TRU . 4 TRU . 5 TRU .

What is the minimum power of the batteries: 28 VDC. 22.5 VDC. 15 KV A.

What is the function of MRC: To accommodate the Navigation Radios. To accommodate the Communications Radios. Answers A and B are correct.

Where is located the MRC # 1 : In the Aft Electronic Bay. In the Aft Electronic Bay. In the Forward Electronic Bay.

What is the maximum angle of nose steering with control pedals. 7 degrees RH and 7 degrees LH. 76 degrees RH and 76 degrees LH. 170 degrees RH and 170 degrees LH.

The flight control system is comprised of the: Primary, aileron, spoiler. Secondary, rudder on yaw axis control. Primary and the secondary flight control surfaces.

The primary flight control system consists of: Aileron, elevator, rudder, mfs. Flap, aileron, rudder. Spoiler, aileron, rudder.

Which of the following flight control are controlled by FBW: Rudder, elevator, roll spoiler, and all secondary FCS including HS, flaps, slats, ground spoiler and speed break. Rudder, elevator, multifunctional spoiler, flap and ailerons. Primary and secondary surface.

Which is the unit provides artificial feel: Control yoke. Feel and centering unit. Trim control and feeling.

S/F motion is sequenced such that: Slat extends first. Flap extends first. Both at the same time.

The actuator control electronic (ACE) module is the primary component in the flight control system a total: One unit installed. Six unit installed. Four unit installed.

The primary – ace units control: Rudder, elevator. Rudder, flap. Slap/ flap.

The secondary S/F- ace unit control the: Slat, spoiler. Slat /flap. Flap/spoiler.

The HS- ace unit controls: HS (horizontal stabilizer). Slat. Primary/ secondary surface.

The flap PDU is located in the: Pressurized forward e- bay. Pressurized center electronic bay. Pressurized aft e- bay.

How many accelerometers are installed in CF 34- 10e5 engine and function: 5 , give engine velocity information. 2, give engine vibration information. 3, give engine trim information.

What is the function of the SPDA: a. Monitor, control and distribution of the dc and ac power. b. Operate and control of the electrical power of the aircraft. c. Distribution and control of the ac and dc power.

What is the function of the MAU and how many are there in the ERJ – 190: a. To distribute the signal of water lines / 4. b. To management the light system in ERJ – 190 / 2. c. To interface the different systems of the aircraft / 3.

How many DVDR are installed in the aircraft, where and parameters of recording: a. 3 in aft – mid – and fwd e-bay / 10 hours voice – 18 hours flight data. b. 1 in aft – e – bay / 2 hours of voice – 20 hours flight data. c. 2 in fwd and aft e- bay / 2 hours voice – 25 hours flight data.

How many IRS are there in the ERJ – 190, what does mean, and function: a. 3 / internal reversionary system / give position of the aircraft. b. 2 / inertial reference system / give attitude, heading and position of the aircraft. c. 2 / internal reference system / give attitude and position of the aircraft.

The ignition exciters provide: a. 12000 to 16000 vac at two pulses per second to the igniters. b. 14000 to 19000 vdc at one pulse per second to the combustion chamber. c. 14000 to 18000 vdc at one pulse per second to the igniters.

The APU operation is limited up to: a. 31.000 ft. b. 32.000 ft. c. 33.000 ft.

What does mean ESC, location and function: Environmental System Control , Synoptic page, controls pneumatic sys. Electronic System Control ,Fwd E-bay, controls electrical sys. Electronic Starter Controller, Apu compartment, with FADEC controls APU start.

How many igniters are there in the APU: 4. 6. 2.

What does mean FADEC, and function in the engine: a. Fault Analysis Digital Engine Controller, analysis of engine stalls. b. Fill Apu Demand Electronic Control, monitor apu. c. Full Authority Digital Electronic/Engine Control, provides flexible engine operation, reduced pilot workload and improved safety, maintenance and reliability.

What does mean TGB and function: a. Transformer generator Buit, transforms energy. . Transfer Gear Box, provides power transmission between inlet gearbox and accessory gear box. Transformer Generator Bus ,supplies electrical power to the aircraft..

The AGB provides mounting pad for : a. Jacks, HPSOV, NAPRSOV, MCC, mainly. b. IDG, fuel pump, oil tank and air starter mainly. c. Fuel pump, oil pump, oil filter manifold, Hyd pump, PMA, air turbine starter and IDG mainly.

The LPTACC-HPTACC-VSV-TBV-VBV are controlled by: a. Fuel press engine. b. Bleed air press engine. c. Oil press engine.

How many fuel nozzles are there in the CF 34-10E5 engine: 20. 25. 30.

What does mean IDG, location and function: a. Internal Digital Gauge, Aft E – Bay, measure the wingspan. b. International Drive Golf, cockpit, select the best golf players in the world. c. Integrated Drive Generator, Engine, provides electrical power for the aircraft.

Where is located and function of the T 1.2 sensor: a. Compressor – provides pressure air data. b. Fan case – Provides oil pressure data. c. Inlet cowl – Provides engine inlet air temperature.

What is the maximum capacity of the waste tank. a. 85 Lt. b. 95 Lt. c. 75 Lt.

What is the function of the ACMP: Powers the AMS system. Powers the CPCS system. Backup of the EDP.

What is the function of the priority valve: Allows transfer air bleed between engine 1 and engine 2. b. Allows transfer hyd power from system 1 to system 2. c. Allows transfer hyd power from system 2 to system 1.

What is the main feature of the bootstrap reservoir: a. Avoid the hyd pumps cavitation. b. Avoid overpress in the hyd pumps. c. Avoid overheat in the hyd fluid.

How many extinguisher bottles are installed in the ERJ 190: 4 : 2 for engines and 2 for the apu. 7 : 2 for engines 2 for cargo compartments, two for lavatories and 1 for APU. 2: for the engines.

What type of smoke detector is installed in the lavatories: a. Electric type. b. Ionized principle type. c. Photoelectric type sensor.

What areas are protected to prevent icing by electrical system. a. Wheels, brakes and slats.. b. ADSP, SAT sensors, windshield. c. ADSP,TAT sensors, windshield ,water lines, static port.

What is the function of the low pressure check valve: a. Avoid reverse flow of the low pressure bleed air. b. Avoid reverse hyd flow into the pump. c. Prevent reverse flow of the high pressure bleed air.

How many slat anti-ice temperature sensors are installed in the ERJ 190. 4 ; 2 per wing. b. 8; 2 each slat panel. c. 6; 1 each slat panel #2 and 2 each slat panel # 4 (inboard and outboard).

What is the function of BCM: . Modulate Hyd press for the brakes. b. Control Hyd press for the brakes. c. Monitor the Hyd press for the brakes.

What module controls the nose wheel steering: a. PSEM. b. NWPSEM. c. NWSCM.

How many modes are there for the landing gear operation: a. 4, Electric, Hyd, Pneumatic and manual. b. 3, Mechanic, hyd and pneumatic. c. 3, Electronic, Electric and manual.

What tube distribute hot air to prevent icing in the slat : a. Lip tube. b. D - Duct. c. Piccolo tube.

Vacuum generator operates up to: a. 17.000 Ft. b. 18.000 Ft. c. 19.000 Ft.

Where is located the waste service panel : Aft LH side of the fuselage. b. Aft RH side of the fuselage. c. Aft LH and RH side of the fuselage.

What LRU monitor the water lines ice protection: a. WWSC. b. WMSV. c. WNPM.

Where is located the potable water service panel : a. Aft LH side of the fuselage. b. Aft RH side of the fuselage. c. Aft LH and RH side of the fuselage.

Which are the pneumatic sources of the aircraft : a. Engine air bleed, APU air bled and external cart HP air bleed. b. Anti – ice air bleed, wheel air bleed and 5 stage air bleed. c. 5 th and 9 th air bleed, fan air bleed valve and HPSOV.

Where is located the Central Maintenance Computer (CMC) : a. In the MAU 2. b. In the MAU 3. c. In the MAU 1.

What is the total length of the E-190: a. 45 m. b. 55 m. c. 36 m.

What is the height of the E -190: a. 12 m. b. 10 m. c. 13 m.

What is the wing span of the E -190: a. 26 m. b. 36 m. c. 28 m.

What is the max thrust of CF 34-10E: a. 16.000 pounds in ISA condition. b. 18.820 pounds in ISA condition. c. 17.500 pounds in ISA condition.

What is the range of the E-190: a. 3200 nautical miles with standard reserves. b. 2300 nautical miles with standard reserves. c. 4200 nautical miles with standard reserves.

How many fuselage jack points has E-190: a. 4. b. 3. c. 2.

What is the function of yaw damper: a. Absorb landing gear vibrations . b. Assist nose wheel steering. c. Avoid Dutch roll.

How many sources of AC are there in the E – 190: a. Five. b. Three. c. Four.

How many sources of DC are there in the E-190. a. Two. b. three. c. Four.

How many ICC are there in the ERJ – 190: 5. 7. 4.

What is the function of ICC: a. Control,protection and distribution of primary AC/DC electrical power. b. Monitor and protection of primary DC electrical power. c. Cooling and distribution of primary AC electrical power.

How many inverters are there in ERJ-190: 2. 1. 3.

Where is located the inverter: a. Fwd E - bay. b. Mid E - bay. c. Aft E - bay.

Where is located the point of plumb: a. RH main landing gear wheelwell. b. LH main landing gear wheelwell. c. Nose landing gear wheelwell.

How many ACE’S are there in the ERJ-190: 6. 8. 5.

Where is located the waste tank: a. Aft cargo compartment. b. Aft E - bay. c. Mid E - bay.

. Where is located the potable water tank: a. Under floor of the fwd cargo compartment. b. Under floor of the cockpit. c. Under floor behind the rear bulkhead of the aft cargo compartment.

. How many safety valves are there and names: a. 3 / relief valve-pressure valve and cabin press valve. b. 2 / positive valve and negative valve. c. Answers A and B are correct.

How many recirculation fans are there in ERJ - 190: 3. 2. 4.

Control of the cockpit or cabin ambient temperature is between: a. 25 – 40 C degrees. b. 22 – 38 C degrees. c. 19 – 30 C degrees.

The total airflow entering the flight deck and cabin is made up of: a. 50 % fresh air and 50 % recirculated air. b. 25 % fresh air and 75 % recirculated air. c. 40 % fresh air and 60 % recirculated air.

What is the function of the outflow valve: a. Modulates the cabin press controller. b. Modulates the airflow from the cabin into ambient. c. Monitor the recirculation fan.

What valves control temperature ambient. a. Outflow valve. b. Safety valves. c. Pack bypass valve.

Pax cabin receives air from: a. Forward cargo compartment. b. Pack RH and LH. c. Recirculation fans.

Cockpit receives air from: a. Only LH pack. b. Only RH pack.Flap extends first. c. Both at the same time.

How many modules comprise the AFCS ( Automatic Flight Control System) and name: a. One module \ ACM (Autopilot Control Module). b. Six modules \ ADA (Autopilot Data Aplication). c. Four modules \ AIOP (Actuator Input Output Processor).

How many servos comprise the AFCS in ERJ – 190 (Aerorepublica): a. 3 servos. b. 4 servos. c. 2 servos.

What servo hasn’t AFCS in ERJ – 190 ( Aerorepublica): a. Rudder servo. b. Aileron servo. c. Elevator servo.

How many digital audio panel (DAP) has the ERJ - 190: a. 2 DAP. b. 3 DAP. c. 4 DAP.

What is the primary means of tuning the radios : a. PFD (Primary Flight Display). b. MCDU (Multifunctional Control Display Unit). c. MFD ( Multifunctional display).

The slat PDU is located in the: a. Unpressurized area inside the wing fairing. b. Pressurized center electronic bay. c. Pressurized aft e- bay.

What is the secondary means of tuning radios: a. PFD (Primary Flight Display). b. MCDU (Multifunctional Control Display Unit). c. MFD (Multifunctional display).

How many ramp interphone panels are there in ERJ - 190: a. 3 \ Fwd section – mid – e - bay – Dc external power panel. b. 2 \ Aft section – mid – e - bay. c. 1 \ AC External power receptacle.

What is the function of the RAT: a. Provide electrical power in the event of a lost of all AC and DC sources. b. Provide electrical power in the event of a lost of all AC sources. c. Provide electrical power in the event of a lost of all DC sources.

Where is located the RAT: a. In a bay in the RH side of the main landing gear wheelwell section.. b. In a bay in the LH side of the aircraft nose section. c. In a bay in the RH side of the aircraft nose section.

. SSPC are controlled by means of : a. MAU. ICC. c. MCDU.

Where is located the ELT unit : a. Aft avionics compartment. b. Fwd avionics compartment. c. Mid avionics compartment..

What frequencies transmit the ELT: a. 118.10 Mhz – 121.8 Mhz – 130.10 Mhz. b. 121.5 Mhz – 243 Mhz – 406 Mhz. c. 110.70 Mhz – 109.90 Mhz. – 113.90 Mhz.

Where is located the antenna of ELT: a. In top of the rear fuselage. b. In top of the vertical stabilizer. c. In top of the Fwd fuselage..

How many FCM (Flight Control Module) are there in ERJ - 190: 6. 4. 3.

What is the max angle of spoilers deployment: a. 25 degrees. b. 27 degrees. c. 40 degrees.

Hyd system 1 and 2 are cooling by means of: a. Radiation and convection. b. fluid to fuel heat exchanger. c. Conduction.

Hyd system 3 is cooling by means of: a. Radiation and convection. b. fluid to fuel heat exchanger. Conduction.

Engine anti-ice system works with airflow from: a. 4 th engine stage. b. 6 th engine stage. c. 5 th engine stage.

FDR begins recording when: a. Engines are turned on or aircraft in the air. b. As soon as power is applied. c. Weight on wheels is true.

CVR begins recording when: a. Engines are turned on or aircraft in the air. b. As soon as power is applied. c. Weight on wheels is true.

What does mean ADSP: a. Aircraft Download System Protection. b. Air Data Smart Probe. c. Airborne Display Supply Power.

How many ADSP are there in aircraft: 6. 4. 2.

What is the function of ADSP: a. Sense total press, static press ,local angle of attack and process total air temperature. b. Sense total press and static press only. c. Sense Static Air Temperature and pitot press .

How many doors type I has ERJ - 190: 3. 2. 4.

How many doors type III has ERJ – 190: 2. 3. 4.

How many fuel injectors has the APU. 18. 20. 12.

Fire extinguisher agent contain: a. 3.96 Lbs, Halon 1301. b. 3.86 Lbs, Halon BOl. c 3.98 Lbs, Halon 1301.

What is the pressure used as primary source: a. 30 TO 40PSI. b. 40 TO 50PSI. c. 35 TO 45PSI.

How many positions have the drain valve and location in the airplane: a. Close, open. b. Close, open, service. c. Open, close.

How ensure a continuous supply of pressurized fuel to the Engine: a. Engine feed systems. b. APU feed. c. Refuel /Defuel.

During operation of the airplane in ground for start the engine used: a. Both fuel pump. b. Each wing supply along. c. Ejectors pump.

138. All of the pump is installed in the: a. Wing area. b. Collector bay. c. Pylon Area.

The ejectors pump is a: a. Convergent pump. b. Divergent pump. c. Ventury with no moving parts.

How many scavenge ejector pumps is installed: a. Five. b. Three. c. Three each wing.

The scavenge ejector pump installed in the: a. Lowest point of the rear spar. b. Lowest point of the front spar. c. Lowest point of the wing tank outboard of the rib 1.

The mode of operation of primary ejector pump is indicated: a. MFD. b. MFD,CMC. c. EICAS.

Where is located the DC pump: a. RH collector tank. b. LH collector tank. c. APU area.

DC pump fail annunciates. a. EICAS. b. MFD. c. PFD.

What is the monitor the pressure switch: a. Input of the electrical pumps. b. Output of the electrical pumps. c. Both at the same time.

How many pressure switches have for each pump: a. One. b. One for each pump. c. Four in total in each wing.

How monitor the status of the AC pump 1/ AC pump 2: a. MAU 1 and MAU 2. b. MAU 1 and MAU 3. c MAU 1 and SPDA 1.

How transmits the data on the ASCB for EICAS: a. SPDA 1. b. SPDA 2 and Mau 3. c. Each Mau.

For the start the APU what pump is used: a. L/H AC pump. b. R/H DC Pump. c. DC pump.

In what position on the cockpit have to be the switch before to Selecting the APU ON. a. ON. b. AC pump 2. c. Auto.

If the fire detected in the APU compartment on ground APU shutdown after: a. Ten minutes. b. 10 seconds. c. 5 seconds.

The adapter pressure receives pressure between. a. 45 and 50 PSI. b. 35 and 50 PSI. c. 25 and 45 PSI.

The fuel can be transferred from wing to wing to maintenance Purpose only: a. In flight DC - power available. b. In ground AC - power available. c. In both conditions.

To transfer fuel from the right hand tank to the left hand tank the first step that you need to do is: a. Power off. b. Connected external power. c. LH tank refuel C/B pulled.

When appears the EICAS message "fuel tank lo temp”: a. If the fuel temperature drop - 47° C (-35° F). b. If the fuel temperature drop - 37° C (-35° F). c. If the fuel temperature drop - 87° C (-55° F).

Where is installed the two (ECS) pack: a. Behind the fairing. b. Wing to fuselage fairing. c. In both spar rear.

How many fans have the forward e-bay: a. One. b. Four. c. Three.

How many fans have middle e- bay: a. One. b. Four. c. Three.

In which compartment I can put animals: a. Forward E- Bay. b. Mid E-Bay. c. Forward cargo Compartment.

If the fan forward cargo fails i will have message in the. a. EICAS. b. PFD. c. MFD.

The fan of the forward E-bay and aft -E-Bay are monitoring by AMS: a. Four minutes before to T/O. b. Two minutes after each aircraft landing. c. Four minutes after each aircraft landing.

The pressurization control panel is installed: a. Left hand side of the overheat panel in the cockpit. b. Right hand side of the overhead panel in the cockpit. c. Below the windshield panel.

The outflow valve is driven at rate of the: a. 4 degrees per minutes. b. degrees per seconds. c. 2 degrees per seconds.

How many channels have the cabin pressurization controller: a) Two. b) Four. c) Six.

Outflow valve is installed on: a. Forward fairing. b. Lower fairing. c. Forward fairing bulkhead.

What is the function of the dual potentiometers: a. Sends position to each control outflow valve. b. Sends position signal to each to each channel. c. Send position signal to each control channel.

If CPCS software logic fails if the outflow valve if the cabin pressure altitude reaches: a. 18,500 Ft. b. 14,500 Ft. c. 13,000 Ft.

The primary operation of the CPCS systems is: a. Manual. b. Automatic. c. Electrical/manual.

Windshield ice and rain protection consist of two systems: a. Windshield heating, windshield wiper. b. Anti-ice, rain protection. c. Heating.

The drain mast has ice protection: a. Heating. b. Heating, and cooling. c. Ice-protection.

The ice detection systems operate fully: a. Heating. b. Automatic. c. Cooling.

This ice detection is mounted: a. Forward and above the windshield. b. After and below the windshield. c. Forward and below the windshield.

In override position engine and wing anti-ice will be activated by: a. Auto switch. b. Proximity sensor. c. Weight on wheel signal.

When the windshield heating will be operational: a. When the anti-ice open. b. When the engine running. c. Wow condition.

The ice and rain protection system status indications are shown on: a. CMC, EICAS, MFD. b.CMC, MFD,IESS. c.CMC, PFD, EICAS.

The slat anti-ice system utilized hot air from the engine to: a. Supply thermal energy through the slat anti-ice. b. Supply heating to the wing. c. Supply hot air to the leading edge.

The telescoping duct sends thermal energy through the: a. Slat 2, 3, and 4 piccolo tube. b. Slat 1, 2, and 3 piccolo tube 3. c. Slat/Flat, 1, 2, 4 piccolo tubes.

The slat anti-ice valve located: a. Pylon. b. Forward spar. c. Left wing.

The anti-ice flow is based on: a. Altitude, ambient temp, Mach number. b. Slat position, ambient temp, and mach. c. Altitude, ambient temp, Mach number and slat position.

What is the pressure in the wing anti-ice pressure sensor: a. 0-1 00 PSI. b. 0-150 PSI. c. 0-75 PSI.

How many anti-icing leak detector sensors have mounted in the wing: a) Six. b)Four. c) 3 in each wing.

Where are installed each one (anti-ice leak): a. Both side of the wing. b. Both LH/RH wing anti-icing areas. c. LH/RH wing, leak, slat areas.

The desire skin temperature is calculated: a) Slat position, ambient temperature, mach, and altitude. b) Slat position, mach airspeed. c) Mach, attitude, altitude, airspeed.

The slat anti-ice protection system can be operated in: a. Four mode. b. Two different modes. c. One mode.

Anti-ice wing leak appears in the EICAS message in which status: a) Caution (red). b) Amber (yellow). c) Advisory message.

What is the temp of the loop for send signal to the EICAS: a. 130° C. -- 150° C. b. 130° C. - (30 Sec) --- 150° C (2 Sec). c. 130° C. - (30 Min) --- 15° C (2 Minute).

The AMS receives signals from the: a. Pressure switch. b. Pressure switch and transducer. c. NAl, proximity switch.

Where is mounted the T2 sensor: a. Inlet anti-ice valve. b. lnlet of telescopical duct. c. lnlet cooling.

How transmits temperature signal to the FADEC: a. T2 Sensor. b. PT2 Sensor. c. T3 Sensor.

Provide signals to modulate the left and right engine NAI valve: a. SPDA 1 and SPDA 2. c. FMC- MAU 2. d. MAU l-MAU3.

When the selector switch is in low/high position the wiper operates at: a. 80 cyc1es per minutes low and 135 cycles per minute in high. b. 80 cyc1es per minutes low and 135 cycles per minutes in high. c. 80 cycles low /125 cycles high.

What is interval time between the cycles: a. 7 minutes. b. 7.5 seconds. c. 7. seconds.

How many channels has the AMS: a) Two channels. b. Four channels. c. One or two stand by.

If in the EICAS APPEAR message “ice detector fail” the Aircraft can be dispatched: a. One inoperative. b. Both inoperative. c. Two and stand by inoperative.

What unit controls the AC EXT PWR: a. The EPM. b. The GCU. c. The AGCU.

Where is the EPM located: a. In the EICC. b. In the LICC. c. In the AICC.

When are the batteries charged: a. When the Ground Service is in use. b. When the AC Bus 1 and 2 are powered. c. When the Batteries Charge are powered.

What precaution should be take when removing a card from the SPDA: a. You have to use static discharge wrist strap equipment. b. The SPDA cards not require any special precaution when is removing. c. Only require to remove the AC and DC power.

Where is the location of the AC 1 bus. a. In front of the LICC. b. In the AICC. c. At the Back of the LICC.

What CB'S are displayed on the MCDU CB page: a. The push out Circuit Breakers. b. The LICC and RICC virtual Circuit Breakers. c. The SPDA 1 and 2 virtual Circuit Breakers.

What happens if any PTT button gets stuck: a. In three seconds disconnect and restore the normal communication. b. You have to release manually. c. These are not possible.

How does the MCDU communicate with VHF comm module: a. Throw the MAU via ASCB. b. Direct to the MRC. c. Direct to the MRC via ASCB.

How many pages or radio information are there in the MCDU: a. Two Radios pages. b. One Radio Page. c. Three Radios pages.

Where you can see the CMC: a. On the MFD 2 screen. b. In a Laptop using the LAN connection. c. A and B answer are correct.

You can load the software using the MFD 2: a. YES. b. Yes if you using the reversionary panel. c. NO.

If the MFD 2 screen was change how you load the software: a. Using the same screen. b. Using the MFD 2 screen. c. Using a laptop with the load software on the LAN connections.

Where is the Pilot Reversionary Panel located: a. On the overhead panel. b. At left side of the control quadrant panel. c. On the left and right lower side of the front panel.

If the Aircraft is on the ground with one engine running which probes will be heated: a. Only the left probes. b. Only the right probes. c. All the probes and the TAT sensors.

How can the barometric altimeter correction be performed: a. By the MCDU panels. b. By the Guidance Panels. c. By the CCD controls.

Where is the VHF Nav unit # 1 located: a. In the MRC 1. b. In the MAU 1. c. In the SPDA 1.