ENGINE WORKSHOP BANK 3

Question 363/702 The oil system primarily aims to cool engine internal drives and gears. True. False.

Question 364/702 The oil tank can be refilled using a pump from an external source. True. False.

Question 365/702 The pressure pump in the oil system increases pressure to supply oil to the AOHE. True. False.

Question 366/702 The primary function of the FOHE is to cool the fuel. True. False.

Question 367/702 The AOHE and FOHE have relief valves to bypass excessive pressure. True. False.

Question 368/702 The oil flows to the LP turbine bearing chamber after passing through the FOHE. True. False.

Question 369/702 The AOHE is controlled by the Flight Control Primary Computers (FCPC). True. False.

Question 370/702 The EEC uses the oil temperature as the primary control parameter for the AOHE. True. False.

Question 371/702 The AOHE modulating valve can only be deactivated manually. True. False.

Question 372/702 The oil system has a total capacity of 20.7 litres. True. False.

Question 373/702 What is the function of the engine nacelle?. Engine protection, ventilation, noise reduction, reverse thrust. Controls engine speed and thrust. Supplies fuel to the engine. Monitors engine performance.

Question 374/702 How is the inlet cowl anti-iced?. Hot engine bleed air. Electric heating elements. Hydraulic heating system. Heated fuel.

Question 375/702 What type of material is used to manufacture the fan cowls?. Aluminum. Carbon fiber reinforced plastic. Titanium alloy. Stainless steel.

Question 376/702 Where is the fan cowl chine located?. On the outboard fan cowl. On the inboard fan cowl. At the 12:00 position. At the 6:00 position.

Question 377/702 How many quick-release hinge pins attach the fan cowls to the engine strut?. Two. Four. Six. Eight.

Question 378/702 What is the purpose of the chevrons on the thrust reverser sleeves?. Improve aerodynamic performance. Reduce engine noise. Increase engine thrust. Decrease fuel consumption.

Question 379/702 Which system operates the fan cowls and thrust reversers for maintenance access?. Manual lever system. Electrical motor system. Powered Door Opening System (PDOS). Pneumatic system.

Question 380/702 What position is the access panel for the P20/T20 probe located on the inlet cowl?. 0,125. 0,25. 0,375. 0,5.

Question 381/702 What should you not do in wind speeds of more than 40 knots?. Start the APU. Open the fan cowls. Remove the engine mounts. Perform engine maintenance.

Question 382/702 What type of thrust reverser does the system use?. Blocker door. Clamshell. Cascade. Pivoting door.

Question 383/702 The power plant cowls give the engine an ____. aerodynamic shape. aerodynamic lift. increased thrust. reduced weight.

Question 384/702 The fan cowl attaches to the engine strut with ____. quick-release hinge pins. bolts. rivets. clamps.

Question 385/702 The fan cowl latches hold the ____. fan case closed. inlet cowl closed. thrust reverser closed. nacelle closed.

Question 386/702 The PDOS is used to ____. open fan cowls and thrust reversers. increase engine thrust. reduce engine noise. start the engine.

Question 387/702 Engine vents and drains are inspected as part of ____. routine tasks. emergency procedures. engine overhaul. flight operations.

Question 388/702 Engine mounts attach the engine to the ____. wing pylon. fuselage. landing gear. tail section.

Question 389/702 The RR Trent 1000 engine is designed to power the ____. Boeing 787. Airbus A380. Boeing 737. Airbus A320.

Question 390/702 The strut (pylon) ensures all interfaces between the ____. aircraft wing and the power plant. fuselage and the power plant. landing gear and the power plant. tail section and the power plant.

Question 391/702 The nacelle supplies a smooth airflow around the ____. engine and its accessories. landing gear. fuselage. tail section.

Question 392/702 The nacelle also supplies ____. engine protection and ventilation. landing gear retraction. fuselage protection. tail section stabilization.

Question 393/702 Noise reduction is a function of the ____. nacelle. fuselage. landing gear. tail section.

Question 394/702 Reverse thrust is achieved by the ____. nacelle. fuselage. landing gear. tail section.

Question 395/702 The nacelle components attach to the ____. engine or the pylon. landing gear. fuselage. tail section.

Question 396/702 The nacelle includes the ____. air inlet cowl, fan cowl doors, thrust reverser cowls, and exhaust system. landing gear doors, fuselage panels, tail section, and wings. engine mounts, control surfaces, flaps, and slats. cockpit, passenger cabin, cargo bay, and tail section.

Question 397/702 The inlet cowl is a ____. four-piece composite structure with an aluminum lip skin. two-piece metal structure with a plastic lip skin. single-piece composite structure with a titanium lip skin. multi-piece metal structure with a composite lip skin.

Question 398/702 The leading edge of the inlet cowl uses ____. engine bleed air for Engine Anti-Icing (EAI) protection. hydraulic fluid for de-icing. electrical heaters for de-icing. fuel for anti-icing.

Question 399/702 The PDOS control switches are located on ____. each side of the inlet cowl and the aft bulkhead. the engine pylon and the fuselage. the tail section and the wings. the landing gear doors and the cockpit.

Question 400/702 The inboard fan cowl on each engine has a ____. chine to control airflow direction. strut for structural support. flap for airflow control. notch for weight reduction.

Question 401/702 The fan cowl latch assemblies hold the ____. left and right fan cowl panels closed. upper and lower fan cowl panels closed. inner and outer fan cowl panels closed. front and rear fan cowl panels closed.

Question 402/702 The fan cowls give access to the ____. engine oil tank and the Variable Frequency Starter Generators (VFSG). landing gear and the control surfaces. fuselage panels and the cockpit. tail section and the wings.

Question 403/702 The inner barrel surface of the inlet cowl is an ____. acoustic panel that decreases engine noise. aerodynamic panel that increases thrust. thermal panel that reduces heat. structural panel that provides support.

Question 404/702 The fan cowls overlap the ____. inlet cowl and the thrust reverser. landing gear and the wings. fuselage and the tail section. cockpit and the cargo bay.

Question 405/702 The area below the fan cowl is designated as ____. zone 1, a fire compartment. zone 2, an aerodynamic compartment. zone 3, a thermal compartment. zone 4, a structural compartment.

Question 406/702 The fan cowls are manufactured from ____. carbon fiber reinforced plastic. aluminum alloy. titanium composite. stainless steel.

Question 407/702 The fan cowl chine improves ____. aerodynamic airflow over the wing inner portion. structural support for the engine. thermal insulation of the engine. noise reduction of the engine.

Question 408/702 The right fan cowl door includes the ____. engine oil tank access door and the VFSG service door. hydraulic fluid access door and the fuel access door. electrical system access door and the control surface access door. landing gear access door and the tail section access door.

Question 409/702 The VFSG service door on the left fan cowl door is used for ____. service access only. cooling airflow only. structural support only. aerodynamic improvement only.

Question 410/702 The fan cowls must be opened before the ____. thrust reverser cowls. landing gear doors. fuselage panels. tail section panels.

Question 411/702 The thrust reverser is a ____. cascade type of thrust reverser. pivot type of thrust reverser. clamshell type of thrust reverser. bucket type of thrust reverser.

Question 412/702 The thrust reverser assemblies are located ____. aft of the fan cowls. forward of the fan cowls. below the fan cowls. above the fan cowls.

Question 413/702 The thrust reverser system uses ____. 5,000 psi hydraulic power to move the translating sleeves. 3,000 psi pneumatic power to move the translating sleeves. 2,000 psi electrical power to move the translating sleeves. 4,000 psi mechanical power to move the translating sleeves.

Question 414/702 The chevrons on the thrust reverser ____. decrease noise levels. increase thrust levels. reduce fuel consumption. improve structural integrity.

Question 415/702 Translating sleeves move aft and deploy the thrust reversers to ____. help in airplane braking. increase engine thrust. reduce engine weight. improve fuel efficiency.

Question 416/702 The thrust reverser attaches to the ____. engine strut. wing pylon. fuselage. landing gear.

Question 417/702 The thrust reverser can be opened for ____. maintenance. flight operations. fuel refilling. cargo loading.

Question 418/702 The power plant drains system collects and discards fluids from ______, engine shutdown or start attempts, and engine accessories with internal leaks. the fuel tank. the oil tank. areas of the power plant where fluids could collect. the fuel injectors.

Question 419/702 The ______ connects to the drains collector tank to supply fuel during engine shutdown. fuel manifold. oil tank. external gearbox. tail bearing housing.

Question 420/702 If the fuel drains tank ejector is defective, a drain tube lets the fuel go overboard at the ______. tail bearing housing. engine zone 2. wing pylon. drain mast.

Question 421/702 Drain tubes from the ______ give an indication of defective internal seals. fuel injectors. VSV actuators. oil tank. airplane wing pylon.

Question 422/702 The dump valve in the ______ starts and stops the flow of fuel to the tank. VSV actuator. hydraulics EDP. HMU. VFSG.

Question 423/702 Excess oil from the oil tank spills into the ______ and goes overboard at the drain mast. scupper drain. fuel ejector. IP compressor. HP turbine.

Question 424/702 The drains mast is primarily used to ______. collect fluid. discharge fluids overboard. store fluids. pump fluids.

Question 425/702 The Trent 1000 engine has ______ external electrical harnesses. 15. 20. 25. 30.

Question 426/702 The external electrical harnesses do not include the ______ and TGT thermocouple harnesses. LP pump cables. VFSG power feeder cables. IP rotor cables. HP turbine cables.

Question 427/702 The electrical harnesses are considered ______. non-replaceable units. permanent fixtures. line replaceable units. integral units.

Question 428/702 The role of the TGT thermocouple harnesses is to ______. measure oil levels. measure fuel flow. measure turbine gas temperature. measure compressor speed.

Question 429/702 External electrical harnesses are used to ______. monitor engine thrust. connect various engine sensors. supply fuel. control air flow.

Question 430/702 Each VFSG power feeder cable is a part of the ______. electrical harnesses. external gearbox. oil system. fuel system.

Question 431/702 The primary function of electrical harnesses is to ensure ______. fluid transfer. data communication between engine components. oil circulation. fuel efficiency.

Question 432/702 The LP compressor rotor consists of a ______ and LP compressor shaft. fan disc. turbine blade. combustor. annulus filler.

Question 433/702 The titanium fan disc has ______ dovetail slots. 10. 15. 20. 25.

Question 434/702 The annulus fillers are positioned between each pair of ______. turbine blades. compressor blades. guide vanes. exhaust nozzles.

Question 435/702 The primary function of the LP compressor module is to increase the ______. fuel flow. oil pressure. air pressure. exhaust temperature.

Question 436/702 The LP compressor divides the air into ______. two airflows. three airflows. four airflows. five airflows.

Question 437/702 Most of the air in the LP compressor goes through the ______. core airflow. bypass airflow. nozzle guide vanes. combustion chamber.

Question 438/702 The ______ at the bottom of the airfoil surfaces of the blade engages in the dovetail slot on the LP compressor disc. root key. fan disc. dovetail root. annulus filler.

Question 439/702 The IP compressor is an ______ assembly with four primary sections. two-stage. four-stage. six-stage. eight-stage.

Question 440/702 The IP compressor rotor is made of ______ titanium discs welded together. six. eight. ten. twelve.

Question 441/702 The IP front stub-shaft bolts to the ______ disc. stage 1. stage 3. stage 5. stage 8.

Question 442/702 The IP compressor case 1-4 is positioned between the ______ and the stage 5-8 case. oil tank. combustor. LP compressor. front bearing housing (FBH).

Question 443/702 The FBH holds the ______ and oil sump. LP and IP compressor roller bearings. HP turbine. external gearbox. IP turbine.

Question 444/702 The primary function of the IP compressor module is to ______. decrease air pressure. increase air pressure. circulate oil. reduce fuel consumption.

Question 445/702 The IP compressor case divides ______ into two halves. horizontally. vertically. diagonally. radially.

Question 446/702 The HP compressor module consists of a ______ axial flow compressor. four-stage. six-stage. eight-stage. ten-stage.

Question 447/702 The HP shaft is supported by a front ball bearing and a ______ bearing. rear ball. rear roller. front roller. front thrust.

Question 448/702 The HP compressor rotor turns ______. clockwise. counter-clockwise. horizontally. vertically.

Question 449/702 The primary function of the HP compressor is to increase the ______ before combustion. oil flow. air pressure. fuel flow. exhaust gas.

Question 450/702 The HP compressor stages 1 to 3 are integrated bladed rotors called ______. turbines. vanes. blisks. discs.

Question 451/702 The combustor controls and mixes the compressed air and ______ for combustion. water. fuel. oil. nitrogen.

Question 452/702 The hot exhaust gases go out of the combustion chamber through the ______. inlet guide vanes. exhaust nozzle. Nozzle Guide Vanes (NGV). fan blades.

Question 453/702 The HP turbine is a ______ stage turbine. single. two. three. four.

Question 454/702 The HP turbine blades are ______ air cooled. externally. internally. both internally and externally. not.

Question 455/702 The HP turbine blades have an external ______ coating. titanium. ceramic. aluminum. stainless steel.

Question 456/702 The HP turbine section extracts mechanical energy from the ______ to drive the compressors. fuel flow. exhaust gas. oil pressure. bypass air.

Question 457/702 The primary function of the HP turbine is to ______. increase air pressure. decrease fuel flow. extract mechanical energy. increase oil pressure.

Question 458/702 The HP turbine module is an integral part of the ______ module. LP compressor. IP compressor. HP system. LP turbine.

Question 459/702 The exhaust gas goes through and turns the ______ HP turbine rotor. single-stage. two-stage. three-stage. four-stage.

Question 460/702 The LP turbine module has a ______ stage turbine. single. two. four. six.

Question 461/702 The LP turbine blades are ______. hollow. solid and welded in pairs. made of ceramic. replaceable.

Question 462/702 The LP turbine module bolts to the ______ support structure. combustor. tail bearing housing (TBH). IP compressor. fuel pump.

Question 463/702 The LP turbine shaft attaches to the stage 5 disc with a ______ and a curvic coupling. drive arm. fan disc. rotor. bearing.

Question 464/702 The primary function of the LP turbine is to extract mechanical energy from the ______. oil flow. air pressure. exhaust gas. fuel flow.

Question 465/702 The LP turbine section turns in the ______ direction as its associated compressor. opposite. same. vertical. horizontal.

Question 466/702 Before the LPT stage, a set of ______ directs the gas flow correctly into the turbine blades. fan blades. compressor blades. Nozzle Guide Vanes (NGV). oil pumps.

Question 467/702 The engine indicating system parameters are shown on the ______ display. Flight Control. Engine Indication and Crew Alerting System (EICAS). Primary Flight. Multi-Function.

Question 468/702 Primary engine indications include TPR, N1, and ______. N2. N3. Exhaust Gas Temperature (EGT). Oil Pressure.

Question 469/702 Secondary engine indications include N2, N3, and ______. Exhaust Gas Temperature (EGT). Turbine Inlet Temperature (TIT). Oil Pressure. Thrust.

Question 470/702 The Turbofan Power Ratio (TPR) indicating subsystem includes the P20/T20 probe and ______. Pressure Transducer. Turbine Gas Temperature (TGT) thermocouples. Fuel Flow Sensor. Oil Pressure Sensor.

Question 471/702 The components of the shaft speed indication include LPC, IPC, and ______ speed probes. Fuel Flow. Oil Temperature. High Pressure Compressor (HPC). Engine Vibration.

Question 472/702 The Engine Electronic Controller (EEC) calculates TPR using inputs from P20, T20, and ______. P30. P50. N2. Oil Pressure.

Question 473/702 TPR uses the temperature corrected overall compressor pressure ratio of ______ to P20. T20. P30. N2. N1.

Question 474/702 The Turbofan Power Ratio (TPR) indication system interfaces with the ______. Fuel Control System. Hydraulic System. Common Core System (CCS). Environmental Control System.

Question 475/702 The EEC calculates engine TPR from inputs including TGT and ______. N2. P30. N1. Oil Pressure.

Question 476/702 TPR indications include the ______ line. Minimum TPR. Average TPR. Maximum TPR. Intermediate TPR.

Question 477/702 One of the advantages of TPR is that it is less sensitive to ______ than EPR or N1 indications. Humidity. Altitude. Fuel Flow. Oil Pressure.

Question 478/702 The temperature correction in TPR calculations is from TGT and ______ data. P30. N2. T20. N1.

Question 479/702 The ______ component is part of the shaft speed indication system. Oil Temperature Sensor. Low Pressure Compressor (LPC) speed probe. Fuel Flow Sensor. Exhaust Gas Temperature (EGT) probe.

Question 480/702 Shaft speed indication interfaces with the EEC and ______. Aircraft Hydraulic System. Permanent Magnet Alternator (PMA). Oil Pressure Sensor. Fuel Pump.

Question 481/702 The TGT thermocouples sense the temperature of airflow downstream of the ______. Engine Exhaust. Combustion System. Intake Valve. Fan Blades.

Question 482/702 TGT thermocouples provide EGT indications on EICAS including ______. EGT blue line. EGT green band. EGT red line. EGT white band.

Question 483/702 The two elements in a thermocouple are nickel aluminum (alumel) and ______. Copper. Nickel Chromium (chromel). Steel. Brass.

Question 484/702 The TGT thermocouple is on the ______ case. High Pressure Turbine (HPT)/Intermediate Pressure Turbine (IPT). Low Pressure Compressor (LPC). High Pressure Compressor (HPC). Fuel Pump.

Question 485/702 The thermocouple elements go into the related ______. Fuel Injector. Low Pressure (LP) Nozzle Guide Vane (NGV). Exhaust Pipe. Air Intake.

Question 486/702 The ______ connections on the terminal block are for the alumel and chromel TGT harness connections. Parallel. Electrical. Mechanical. Different-sized.

Question 487/702 There are ______ TGT thermocouples evenly positioned around the turbine case. 6. 8. 10. 12.

Question 488/702 The analyzer system components include the Engine Monitoring Unit (EMU) and ______. Fuel Pump. Intermediate Case Vibration Transducer. High Pressure Turbine Blade. Fan Blades.

Question 489/702 The analyzer system interfaces include the EEC and ______. Engine Control Lever. Engine Start Switch. Common Data Network (CDN). Fuel Injectors.

Question 490/702 The ______ monitors critical engine operation. EMU. PMA. CCS. EEC.

Question 491/702 Sensors in the analyzer system monitor temperature, vibration, and ______. Fuel Flow. Pressure. Oil Level. Fuel Quantity.

Question 492/702 The EMU calculates engine vibration and balance solutions and sends vibration data to the ______. EICAS. LPC. HPC. Oil Pump.

Question 493/702 The EMU consists of a single channel of electronics that connects to the ______. EEC Channel A. Fuel Pump. LPC. HPC.

Question 494/702 EHM data is recorded by the EMU and sent to the ______. Aircraft Health Monitoring Function (AHMF). Airplane Condition Monitoring Function (ACMF). Engine Control Unit (ECU). Flight Management System (FMS).

Question 495/702 The engine fuel and control system supplies conditioned and metered fuel to the ______. Fuel pump. Combustion chamber. Oil cooler. Air intake.

Question 496/702 The throttle lever position sends a command signal for a specified ______. Altitude level. Airspeed. Engine power level. Hydraulic pressure.

Question 497/702 The Thrust Management Function (TMF) can set the ______ automatically. Airspeed. Fuel flow. Throttle lever position. Oil pressure.

Question 498/702 The throttle levers connect to ______ that measure their position. Resolvers. Sensors. Actuators. Transmitters.

Question 499/702 The EEC sends a signal to the ______ to control the quantity of fuel going to the combustion chamber. Fuel pump. Hydro-Mechanical Unit (HMU). Fuel nozzle. Fuel tank.

Question 500/702 A fuel flow transmitter measures the quantity of fuel going to the ______. Oil cooler. Combustion chamber. Air intake. Fuel tank.

Question 501/702 Fuel flow data goes to the EEC and ______ indications. Crew. Airspeed. Altitude. Oil pressure.

Question 502/702 The engine fuel and control system supplies ______ and metered fuel to the combustion chamber. unmetered. unconditioned. conditioned. high-pressure.

Question 503/702 The throttle lever position sends a command signal for a specified ______. fuel flow rate. engine power level. EGT level. N1 speed.

Question 504/702 The throttle levers connect to throttle ______ that measure the position of the throttle lever. actuators. sensors. resolvers. controllers.

Question 505/702 The EEC sends a signal to the ______ to control the quantity of fuel going to the combustion chamber. fuel pump. Fuel Flow Meter. Hydro-Mechanical Unit (HMU). Fuel Temperature Sensor.

Question 506/702 A fuel flow transmitter measures the quantity of fuel going to the ______. fuel tanks. fuel manifold. combustion chamber. injectors.

Question 507/702 The EEC uses the throttle lever position signal to set the engine ______. temperature. pressure. thrust. fuel flow.

Question 508/702 Fuel flow data goes to the EEC and ______. fuel pump. fuel manifold. crew indications. throttle resolvers.

Question 509/702 The fuel distribution system interfaces with the ______. Low Pressure (LP) compressor. Engine Fuel/Oil Heat Exchanger (FOHE). EICAS display. throttle resolvers.

Question 510/702 Fuel from the fuel tanks goes through the engine fuel shutoff valve to the ______. High Pressure (HP) fuel pump. fuel manifold. LP centrifugal fuel pump. combustion chamber.

Question 511/702 The pressurized fuel from the LP centrifugal boost pump goes through the engine FOHE and the ______. HP fuel pump. LP fuel filter. Fuel Flow Meter. combustion chamber.

Question 512/702 From the FOHE, the fuel goes to the ______ elements and to the HMU. LP fuel pump. HP gear type fuel pump. Fuel Flow Meter. HP turbine.

Question 513/702 The EEC operates these valves in the HMU to control the flow of fuel: Fuel Metering Valve (FMV) and ______. Pressure Raising Shutoff Valve (PRSOV). Fuel Shutoff Valve. Variable Stator Vane (VSV). thrust control valve.

Question 514/702 Servo-fuel from the HMU goes to the HP/IP Turbine Case Cooling (TCC) actuators and the ______. combustion chamber. LP fuel filter. Variable Stator Vane (VSV) actuators. thrust control valve.

Question 515/702 The fuel control system has components such as the EEC and the ______. Permanent Magnet Alternator (PMA). Fuel Temperature Sensor. Fuel Pump. Low Pressure (LP) compressor.

Question 516/702 The EEC uses data from airplane systems and engine sensors to control the ______. fuel flow. engine. fuel pressure. engine temperature.

Question 517/702 The EEC uses the throttle resolver angle (TRA) along with data such as altitude, Mach number, and ______ to calculate the required thrust setting. fuel temperature. ambient conditions. fuel flow rate. N1 speed.

Question 518/702 Thrust Control Malfunction Accommodation (TCMA) software in the EEC prevents ______ on the ground. engine overspeed. asymmetric thrust. fuel leakage. engine shutdown.

Question 519/702 Overspeed protection software in the EEC protects the engine from overspeed conditions that could cause ______. fuel overflow. high EGT. uncontained failure. fuel starvation.

Question 520/702 The CCS Integrated Propulsion Application (IPA) software provides logic for supply of power to the ______ system functions. fuel control. hydraulic. air conditioning. electrical.

Question 521/702 EEC power is supplied from the ______. fuel pump. airplane. EICAS display. throttle resolvers.

Question 522/702 The fuel control system has components including the EEC, PMA, and ______. Fuel Shutoff Valve. Data Entry Plug (DEP). Thrust Control Valve. Fuel Flow Meter.

Question 523/702 The fuel and control indicating system provides data on the ______ display and engine maintenance pages. Flight Control. EICAS. Multi-Function. Primary Flight.

Question 524/702 The fuel and control indicating system has components such as the LP fuel filter differential pressure transducer and the ______. High Pressure (HP) fuel pump. LP centrifugal fuel pump. Fuel Flow Meter. fuel injectors.

Question 525/702 The fuel and control indication system interfaces with the EEC for control and ______. fuel distribution. power management. display. thrust control.

Question 526/702 The fuel and control indication system interfaces with the EEC for control and display using parameters such as P20/T20 and ______. P40. P50. P30. P60.

Question 527/702 The fuel and control indication system interfaces with the EEC using the Low Pressure (LP) fuel filter impending ______ signal. failure. blockage. clog. leakage.

Question 528/702 The fuel and control indication system interfaces with the EEC using the LP fuel filter ______ signal. bypass. flow rate. temperature. pressure.

Question 529/702 The only component in the power control system is the ______. Engine Control Module (ECM). Thrust Control Module (TCM). Fuel Control Module (FCM). Thrust Management System (TMS).

Question 530/702 The power control system interfaces with the EEC, CCS through RDC, and ______. spar valve start switch relays. fuel pumps. flight control system. navigation system.

Question 531/702 The thrust control module includes components such as thrust levers and ______. fuel injectors. fuel flow sensors. auto throttle electronics. speed sensors.

Question 532/702 The thrust levers supply thrust commands to the EEC through the ______. throttle actuators. thrust lever (TL) resolvers. fuel control switches. throttle sensors.

Question 533/702 When a thrust lever moves, the ______ also moves and sends TRA data to the EEC and CCS. thrust lever. resolver. fuel control module. throttle actuator.

Question 534/702 The thrust control module has redundant components in the linkage between each thrust lever, reverse thrust lever, and ______. resolvers. EEC. CCS. RDC.