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TEST BORRADO, QUIZÁS LE INTERESE: Examen 2

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Título del Test: Examen 2 Descripción: Segundo examen Autor: Lío OTROS TESTS DEL AUTOR Fecha de Creación: 27/03/2025 Categoría: Personal Número Preguntas: 81

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Do you remember which sensor turns ON de PTU? A System B EDP low press switch A System B EMDP low press switch. The PTU hydraulic pressure is delivered to All the components on the System B Only for Leading edge flaps and slats. The purpose of the Current Transformer (CT) is to Monitor the electric current for the EMDP Monitor the hydraulic pressure for the EMDP. The Ground Fault Detector may turn OFF the EMDP because of fluctuations on the frequency Fire on the engine. May Rudder actuator receive standby hydraulic system pressure? Yes No. OIL/FUEL heat exchangers are in the pump case drain lines? Yes No. What components are between Standby Reservoir and Left Thrust Reverser System? Left Heat Exchanger Standby Hydraulic Pressure Module Left Hydraulic Pressure Module Full Flow Filter PTU Standby EMDP. The ground fault detector turns off the EMDP because of fluctuation on the frequency fire on the engine. The PTU turns ON if System B EDP pressure decrease System B EMDP pressure decrease System A EMDP pressure decrease. Where are the hydraulic Pumps Ground Fault Detectors located? Engine's Bay Main Wheel Well Electronic/Equipment Compartment P91/P92. Let's match data of the flight control function Roll Left and Roll Right: Its movement is using the Control Wheel from left to right Pitch Up and Pitch Down: Its movement is using the Control Column move aft and foward Aileron, elevators and rudder controls: Give inputs to each feel and centering Rudder: Help the airplane with the yaw Flaps and Slats: Help the aircraft lift, extending the wing area Elevators: When the stabilizer trim moves. t also moves to a neutral position. What is the main purpose of the trailing edge flaps? Trailing-edge flaps are wing devices used to increase the roll movement coefficient. Trailing-edge flaps are wing devices used to increase the maximum lift Coetficient that a wing can generate. How the TE flaps work normally? Hydraulic Power Electrical Power. What are the main faults related with trailing edge system? Load relief UCM Detection Asymmetry detection Skew detection Spoiler Load Relief Leading Edge EXT. It is posible to retract the Trailing edge flaps in the alternate mode? Yes. No. The Flap drive unit operates Electically Hydraulically Manually All are correct. Match Trailing Egde System Concepts Skew detection refers to: If the TE flaps are not aligned in the same wing Load relief refers to: If the airspeed is more than a limit can cause structural damage Asymmetry detection refers to: If the TE flaps are not aligned in both wing UCM Detection refers to: If the TE flaps move from their commanded position Who is in charge of monitoring TE function: FSEU Flap Slat Electronic Unit: Sends data to the flap position indicator In the flight compartment Flap Skew sensors: There are 8 to indicate the Trailing Edge Position TE Flap Bypass valve: Commanded by the Alternate Flaps arm switch directly. If there is a fault in the Flap and Slat System, you will need to find a cause of the problem. Which computer will you use? Don 't use acronym to write your answer! Flap Slat Electronic Unit Apréndete bien el nombre 🙄. Which menu option let you see sensor data? Fault History Ground Test Other Function. Select which tests are available with this computer. TE flap asymmetry-skew-indication test TE flap load relief test. TE flap load relief test FSEU BITE display test Slat proximity sensor test. How many proximity sensors does the LE Flap and Slat indication system have? 15 20 30 None of the above . After MEL, in a B737-700 what slat indications cannot be deferred? Slats 2,3, 6 and 7 Slats 4 and 5 No Slat indication may be deferred All Slat indications may be deferred. During alternate operation the bypass valve is moved to the bypass position to Change hydraulic source Prevent hydraulic lock Return flaps to initial position All of the above. Program specific for landing and takeoff in low visibility conditions. It needs to downgrade the aircraft. CATII / CATIII RVSM RNAV/RNP. Program that keeps vertical separation in 1000ft between FL290 to FL410 RVSM CATII/CATIII RNAV/RNP. Landing Difficulty Match CAT II: CATI : CAT IIIA: RNAV: RNP Navigation: AR RNP: Conventional Navigation:. Match Trailing Egde System Concepts Skew detection refers to: Load relief refers to: Asymmetry detection refers to: UCM Detection refers to: Who is in charge of monitoring TE function: Flap Slat Electronic Unit: Flap Skew sensors: TE Flap Bypass valve: . Why RNP is a better option for the operation? Operational efficiency Capacity (Acces to the airports with bad weather and increase airport capacity) Safety ( predefined flight) Reduce Noise and save fuel causing reduce de CO2 to the enviroment Reduce Maintenance Action Improve the RVSM program. Accuracy means (RNAV X or RNP X): Lateral separation in nautical miles Vertical separation in nautical miles. Required Navigation Performance is an Area Navigation procedure with on board monitoring and alerting system. Yes No. The main information of operation, power, speed, reverser usage comes from: ADIRUs Engine control levers Engine strut . What is the reason you should put both engines switches in ALTN hard mode? Posible difference of thrust One engine may stop A reverser may be opened . One engine is in hard ALTN mode. May that engine EEC change from hard mode back to normal mode by itself? YES NO. Where is EEC box located? Fan cowl left side EE Compartment, E1 Fan cowl right side. Where is HMU located? Engine AGB left-hand side Engine AGB right-hand side EE Compartment rack E3-3. How can you access EEC BITE? By opening right fan cowl and connecting a laptop to ECP port By using the CDU, Maintenance pages, Engine By making a BITE in EAU in Electronic Equipment Compartment. When does the EEC goes to Soft Alternate mode? TAT is not valid PO is not valid PT is not valid All of the above. The ENGINE CONTROL light is energized by? DEU EEC FMC. When is the EEC in NORMAL mode? Total pressure is valid and EEC switch is in the ON position Total temperature is valid and the EEC switch is in the ON position EEC switch is in the ON position All of the above. Is the left ignition system of an engine dispatchable without maintenance action? No Yes I need to verify in MEL. The Ignition Exciters change 115V AC to 15,000V - 20,000V DC 10,000V - 12,000V DC 15.000V-20.000V AC None of the above. The Right Ignition Exciter normally receives power from? 28V DC 115V AC XFER bus 115V AC StandBy bus All of the above. NORMAL CONFIGURATION - NO PROBLEMS Transfer Bus 115 VAC Standby Bus 115 V AC Ground Service Bus 115 VAC. What is the main function of the Thrust Reverser System? The flight crew uses reverse thrust to help the ground spoilers stop the aircraft and avoid excesive heat in the brakes. The flight crew uses reverse thrust to slow the airplane after landing or during a rejected takeoff (RTO). The flight crew uses reverse thrust to help stop the aircraft and make shorter the distance during landing. All are true. What hydraulic system is used for normal thrust operation? Multiple response Stand by Hydraulic System Hydraulic B Hydraulic A. How many actuator per traslating sleeve reverser has? 3 2 4. The thrust reverser has a low thrust reverse power and a maximun thrust power of operation. This stament is true. This stament is false. What is the component in charge of keeping the T/R in place with no movement? The proximity sensors The Sync Lock A/T switch pack . Conditions to operate the reverser are: Aircraft on ground and below 20 ft of radio altitude Aircraft on ground and below 10ft of radio altitude In flight, better in cruise. Match some concepts: Thrust reverse emergency system for landing Hydraulic A Hydraulic B Controls the hydraulic fluid to the reverser Flight Control Computer Engine Accessory Unit Sync Lock . Could a BITE procedure indicate if the fault was during stow or deploy direction? Yes No. Can BITE show which engine has a problem with the reverser? Yes, but you also need to interrogate the EEC. Yes, during the EEC BITE test this data is present. Yes, the EAU show a red light below the affected engine. . Which light illuminate in a T/R fail? REVERSER light on the Aft Overhead Panel REVERSER light on the CDS REVERSER light on the Master Caution Anunciator . Each T/R Traslating Sleeve has a LVDT used for: Sending position feedback direct to the DEU, then to the CDS; the indication will turn on amber, or green when it is deployed. Sending position feedback to the EEC and then to the DEU to show REV indication transition on the CDS; the indication turns on amber(transit) or green (deployed). ENGINE CONTROL light turns on to show us: Critical failure in the ENG, with no dispatch condition. Critical failure in the ENG, due to a loss of performance data on the EEC Critical failure in the ENG, with dispatch condition. . ALTN light turns on to show us: Critical failure in the ENG, with no dispatch condition Critical failure in the ENG, due to a loss of performance data on the EEC. Critical failure in the ENG, with dispatch condition . You can deploy the Thrust Reversers when the airplane is less than 15 feet from the ground 10 feet from the ground 20 feet from the ground Only wheels on the ground . Can the REVERSER light be turned ON during AIR mode? YES NO. Can the REVERSER light be turned ON during AIR mode? 50% to deploy position 75% to deploy position 90% to deploy position . The High Stage Valve + High Stage Regulator work together to supply 9th stage air for low engine speed operation prevent reverse flow into the 9th stage regulate 9th stage air pressure shut off 9th stage air during high engine speed operation . The PRSOV + the Bleed Air Regulator work together to Regulate bleed air pressure to 42psi Prevent over pressure in the system With the 450° sensor prevent runaway over-temperature . At low engine speed, with the HSV regulating the air pressure, the PRSOV is modulating Wide open Almost close . The pressure tolerance for the PRSOV is 32 psi ‡ 6 42 psi +8 52 psi +10 . According to this test, if you get a low pressure indication while you are testing the BAR it is because normal pressure on the system there is a component failure You are performing a wrong procedure . If you are testing the HSR with the TEST CAP and the pressure is still low it is because The HSV has a failure The HSR has a failure You are performing a wrong procedure . The temperature for the PCCV operation 390 F 450 F 490 F None of the above All of the above. The over pressure sensor activates at 50 psi 120 psi 220 psi none of the above all of the above. At low engine RPM, how system pressure is controlled? Bleed air regulator 450C sensor High stage regulator None of the above All of the above . The main valves of the system are Electrically controlled Neumatically controlled Electro-pneumaticallycontrolled All of the above None of the above . With the thrust levers above idle, how system temperature is controlled? 450C sensor High stage valve PCCV All of the above None of the above . The main valves of the system are Electrically controlled neumatically controlled Electro-pneumaticallycontrolled All of the above None of the above . With the thrust levers above idle, how system temperature is controlled? 450C sensor High stage valve PCCV All of the above None of the above . What information is important to determine if one or both engine pneumatic systems have high duct pressure. Bleed pressure Engine N1 speed Airplane altitude All of the above. What's the main computer in the Air Conditioning System? Pack Zone Temperature Controller Air Conditioning Accessory Unit Temperature Control Valve . What's the purpose of the Zone Trim Air Modulating Valves? (ZTAMV) To bring cool air to the airplane To remove hot air from the airplane To bring hot air to the airplane . What's the purpose of the ACM compressor section? to reduce the air temperature to reduce the air pressure to increase the air pressure . The system is protected against overheat temperature with: Three (3) overheat switches An Air Cycle Machine The Primary and Secondary heat exchanger . Looking at the schematic. What are the switches that turn on the PACK light? Compressor overheat sw Turbine overheat sw RAM air sensor PACK temperature sensor Turbine overheat sw Pack discharge overheat sw Pack temperature Bulb . If an OVHT condition is detected, what automatically happens? First: Second: Third: . How many Controller do the B737-700/800 has for the Air Conditioning system? 3 2 4. What temperature triggers the Zone TEMP light to come ON? 220 F 210 F 190 F NONE OF THE ABOVE .

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