[ { "ch": "How many shafts does the RR T7000 have? (B2)", "ansGr": [ { "ans": [ "1", "false" ] }, { "ans": [ "2", "false" ] }, { "ans": [ "3", "true" ] } ], "part": "Engine T7000 CAT B2", "title": "ATA 70:", "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 2" }, { "ch": "What does the LP system consists of? (A, B2)", "ansGr": [ { "ans": [ "A single stage compressor (Fan) assembly driven by a four-stage turbine.", "false" ] }, { "ans": [ "A single stage compressor (Fan) assembly driven by a five-stage turbine.", "false" ] }, { "ans": [ "A single stage compressor (Fan) assembly driven by a six-stage turbine.", "true" ] } ], "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 6" }, { "ch": "What does the IP system consists of? (A, B2)", "ansGr": [ { "ans": [ "An eight-stage axial compressor driven by a single-stage turbine.", "true" ] }, { "ans": [ "Annine-stage axial flow compressor driven by a two-stage turbine.", "false" ] }, { "ans": [ "Anten-stage axial flow compressor driven by a two-stage turbine.", "false" ] } ], "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 6" }, { "ch": "What does the HP system consist of? (A, B2)", "ansGr": [ { "ans": [ "A six-stage axial flow compressor driven by a single-stage turbine.", "true" ] }, { "ans": [ "A five-stage axial flow compressor driven by a single-stage turbine.", "false" ] }, { "ans": [ "A four-stage axial flow compressor driven by a single-stage turbine.", "false" ] } ], "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 6" }, { "ch": "The description of the fuel system on engine Trent T7000 is as follow: (A, B2)", "ansGr": [ { "ans": [ "18 fuel spray nozzles are equally spaced around the combustion chamber", "true" ] }, { "ans": [ "24 fuel spray nozzles are equally spaced around the combustion chamber", "false" ] }, { "ans": [ "30 fuel spray nozzles are equally spaced around the combustion chamber", "false" ] } ], "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 158" }, { "ch": "A” CRACKED” damage type to metal parts is define as:(A, B2)", "ansGr": [ { "ans": [ "A linear opening that can cause the material to break.", "true" ] }, { "ans": [ "Damage to the surface of a part when it is hit with an object.", "false" ] }, { "ans": [ "A damage that changes the initial shape or contour of a material.", "false" ] } ], "ref": "Ref : A330 AMM 70-00-62-PB401" }, { "ch": "What is true regarding the cotter pin installation? (A, B2)", "ansGr": [ { "ans": [ "If you cannot align the nut slots with the hole for the split cotter pin (unless you apply a higher than maximum torque load value), then replace the nut", "true" ] }, { "ans": [ "Continue to tighten the nut(s) to align the nut(s) slots with the hole for the pin(s) if max torque is not", "false" ] }, { "ans": [ "Loosen the the nut(s) to align the nut(s) slots with the hole for the pin(s) .", "false" ] } ], "ref": "Ref : A330 AMM 70-00-62-PB401" }, { "ch": "Engine oil tank is located on (A, B2)", "ansGr": [ { "ans": [ "Fan case (right side)", "true" ] }, { "ans": [ "Fan case (left side)", "false" ] }, { "ans": [ "Intermediate case", "false" ] } ], "title": "ATA 71:", "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 334" }, { "ch": "Which system drives the external gearbox on RR T7000? (A,B1,B2)", "ansGr": [ { "ans": [ "HP system", "false" ] }, { "ans": [ "IP system", "true" ] }, { "ans": [ "LP system", "false" ] } ], "title": "ATA 72:", "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 14 (WXB HP System drives External Gearbox)" }, { "ch": "How many fuel spray nozzles (FSN) are there? (A,B2)", "ansGr": [ { "ans": [ "18", "true" ] }, { "ans": [ "24", "false" ] }, { "ans": [ "30", "false" ] } ], "title": "ATA 73:", "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 158" }, { "ch": "During start how do you know which ignition system is operating? (A, B2)", "ansGr": [ { "ans": [ "By indication on Engine Warning Display", "false" ] }, { "ans": [ "By indication on SD Engine page", "true" ] }, { "ans": [ "This can not be known.", "false" ] } ], "title": "ATA 74:", "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 222" }, { "ch": "What is the location of the two ignition exciter units? (A,B2)", "ansGr": [ { "ans": [ "On the Fan case (left side)", "true" ] }, { "ans": [ "On the Fan case (right side)", "false" ] }, { "ans": [ "In zone 2 under Gas Generator Fairing", "false" ] } ], "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 356" }, { "ch": "What is the location of the ignitor plugs? (A,B2)", "ansGr": [ { "ans": [ "On the engine core around the combustion chamber (one on each side)", "true" ] }, { "ans": [ "On the engine core around the combustion chamber (left side)", "false" ] }, { "ans": [ "On the engine core around the combustion chamber (right side)", "false" ] } ], "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 356" }, { "ch": "How many IP8 handling bleed valves are there? (A,B2)", "ansGr": [ { "ans": [ "3", "true" ] }, { "ans": [ "5", "false" ] }, { "ans": [ "6", "false" ] } ], "title": "ATA 75:", "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 226" }, { "ch": "How many HP3 handling bleed valves are there? (A,B2)", "ansGr": [ { "ans": [ "2", "true" ] }, { "ans": [ "5", "false" ] }, { "ans": [ "6", "false" ] } ], "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 226 XWB have 3 HP Handling Bleed Valve" }, { "ch": "What burst ducts is the zone 1 temperature sensor likely to detect? (A,B2)", "ansGr": [ { "ans": [ "IPTCC duct", "false" ] }, { "ans": [ "Starter or anti-ice ducts", "true" ] }, { "ans": [ "ESS", "false" ] } ], "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 272" }, { "ch": "What type of temperature sensor is in zone 3? (A,B2)", "ansGr": [ { "ans": [ "A thermocouple (TC)", "true" ] }, { "ans": [ "A resistance temperature device (RTD)", "false" ] }, { "ans": [ "TC and RTD type", "false" ] } ], "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 276" }, { "ch": "Which sensor is used for NAC temperature indications in the cockpit? (A, B2)", "ansGr": [ { "ans": [ "Zone 1 temperature sensor", "false" ] }, { "ans": [ "Zone 2 temperature sensor", "false" ] }, { "ans": [ "Zone 3 temperature sensor", "true" ] } ], "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 276" }, { "ch": "What is the purpose of the Turbine-Cooling Control System? (A,B2)", "ansGr": [ { "ans": [ "To cool the core engine IP and LP turbine cases", "false" ] }, { "ans": [ "To cool the core engine HP and IP turbine cases", "false" ] }, { "ans": [ "To cool the core engine HP, IP and LP turbine cases", "true" ] } ], "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 22" }, { "ch": "What electrical supplies are provided to the EEC? (A,B2)", "ansGr": [ { "ans": [ "A/C 230VAC Emergency, A/C 230VAC Normal, PMA above 6.46% N3", "false" ] }, { "ans": [ "A/C 115VAC Emergency, A/C 230VAC Normal, PMA above 6.46% N3", "false" ] }, { "ans": [ "A/C 115VAC Emergency, A/C 115VAC Normal, PMA above 6 % N2", "true" ] } ], "title": "ATA 76:", "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 204 XWB above 6,46% N3" }, { "ch": "What is the location of the PMA? (A, B2)", "ansGr": [ { "ans": [ "On the rear face of the accessory gearbox", "false" ] }, { "ans": [ "On the front face of the accessory gearbox", "true" ] }, { "ans": [ "On the R/H side of the accessory gearbox", "false" ] } ], "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 205" }, { "ch": "What provides the primary N3 signal from the PMA?", "ansGr": [ { "ans": [ "A single phase winding within the PMA, signals to both channel A and B", "false" ] }, { "ans": [ "No, N3 Speed provide by Two dual winding speed sensor", "true" ] }, { "ans": [ "A dual phase windings within the PMA, signals to both channel A and B", "false" ] } ], "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 301 XWB using PMA Winding calculate the N3 Speed Signal, T7000 provide Speed Sensor for 3 shaft." }, { "ch": "What is the EMU used for? (A, B2)", "ansGr": [ { "ans": [ "Engine Health Monitoring", "true" ] }, { "ans": [ "Control on engine operation", "false" ] }, { "ans": [ "Electrical power management", "false" ] } ], "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 308" }, { "ch": "From which zone is the nacelle temperature indication obtained? (A, B2)", "ansGr": [ { "ans": [ "Zone 1", "false" ] }, { "ans": [ "Zone 2", "false" ] }, { "ans": [ "Zone 3", "true" ] } ], "title": "ATA 77:", "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 276" }, { "ch": "How many LP speed sensors are located in the Front Bearing Housing(FBH)? (B2)", "ansGr": [ { "ans": [ "1", "false" ] }, { "ans": [ "2", "false" ] }, { "ans": [ "4", "true" ] } ], "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 296" }, { "ch": "How many IP speed sensors are located in the Front Bearing Housing (FBH)? (B1)", "ansGr": [ { "ans": [ "4", "true" ] }, { "ans": [ "2", "false" ] }, { "ans": [ "1", "false" ] } ], "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 298" }, { "ch": "The main thrust parameter is … speed? (A, B2)", "ansGr": [ { "ans": [ "N1", "true" ] }, { "ans": [ "N2", "false" ] }, { "ans": [ "N3", "false" ] } ], "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 282" }, { "ch": "State the location of the P20/T20 probe? (A, B2)", "ansGr": [ { "ans": [ "The P20/T20 probe is attached to the fan case struts", "false" ] }, { "ans": [ "The P20/T20 probe is attached to the inlet cowl at the engine top dead center position", "true" ] }, { "ans": [ "The P20/T20 probe is attached to the intermediate case", "false" ] } ], "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 90" }, { "ch": "What is the location of the TGT thermocouples? (B1,B2)", "ansGr": [ { "ans": [ "TBH struts", "false" ] }, { "ans": [ "IP Turbine Case", "false" ] }, { "ans": [ "LPT stage 1 NGV", "true" ] } ], "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 302 RR XWB TGT Thermocouple located in IP Turbine Case." }, { "ch": "Where is T/R HCU inhibit lever location? (A, B1, B2)", "ansGr": [ { "ans": [ "L/H Fan Case", "false" ] }, { "ans": [ "R/H Fan Case", "true" ] }, { "ans": [ "On Pylon", "false" ] } ], "title": "ATA 78:", "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 375" }, { "ch": "The T/R actuators are driven by: (A, B2)", "ansGr": [ { "ans": [ "Dedicated hydraulic power", "true" ] }, { "ans": [ "Pneumatic power", "false" ] }, { "ans": [ "Electric power", "false" ] } ], "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 314, A350 XWB TR Actuator are driven by Electrical power" }, { "ch": "Thrust reversers actuators are powered by? (A,B1,B2)", "ansGr": [ { "ans": [ "Green hydraulic system for engine 1 and Yellow system for engine 2", "false" ] }, { "ans": [ "Blue hydraulic system for engine 1 and Yellow system for engine 2", "true" ] }, { "ans": [ "Green hydraulic system for engine 1 and Blue system for engine 2", "false" ] } ], "ref": "Ref: Technical Training Manual ATA 70-80 T7000 Page 315" }, { "ch": "The locking proximity switch which send the T/R feedback to EEC are on? (B1, B2)", "ansGr": [ { "ans": [ "Center and lower actuators", "true" ] }, { "ans": [ "Center and upper actuators", "false" ] }, { "ans": [ "Upper actuator only  ", "false" ] } ], "ref": "Ref: Technical Training Manual ATA 70-80 T7000 Page 315" }, { "ch": "The T/R position feedback is sent to EEC from? (B1, B2)", "ansGr": [ { "ans": [ "The two proximity switches on 2 actuators of each sleeve", "false" ] }, { "ans": [ "LVDT on each upper actuator", "true" ] }, { "ans": [ "LVDT on each TLS actuator", "false" ] } ], "ref": "Ref: Technical Training Manual ATA 70-80 T7000 Page 315" }, { "ch": "What is the location of the oil tank? (A, B2)", "ansGr": [ { "ans": [ "Fan case R/H side", "true" ] }, { "ans": [ "Fan case L/H side", "false" ] }, { "ans": [ "On the external gearbox.", "false" ] } ], "title": "ATA 79:", "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 379" }, { "ch": "How is the oil flow in the scavenge line maintained if the oil scavenge filter is fully clogged? (B2)", "ansGr": [ { "ans": [ "Through a by-pass valve", "true" ] }, { "ans": [ "Through a standby pump", "false" ] }, { "ans": [ "Through a back-up pump", "false" ] } ], "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 340" }, { "ch": "The engine oil vent system consists of? (A, B1, B2)", "ansGr": [ { "ans": [ "FBH vent valve and centrifugal breather", "false" ] }, { "ans": [ "A de-aerator side the oil tank and a centrifugal breather", "true" ] }, { "ans": [ "FBH vent valve and vent pump", "false" ] } ], "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 334" }, { "ch": "On oil pressure filter replacement how tight should the filter bowl be tightened? (A, B2)", "ansGr": [ { "ans": [ "Hand tight only", "true" ] }, { "ans": [ "By proper torque wrench", "false" ] }, { "ans": [ "By using the chain wrench", "false" ] } ], "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 379" }, { "ch": "What is the caution when opening the T/R Cowl Door for maintenance? (A, B1, B2)", "ansGr": [ { "ans": [ "Slat must be retracted", "true" ] }, { "ans": [ "Slat must be Deactivated", "false" ] }, { "ans": [ "Not relate to slat position", "false" ] } ], "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 386" }, { "ch": "The pressurized air necessary to operate the starting components is supplied from these sources", "ansGr": [ { "ans": [ "Other running engine, APU, Ground based air compressor connected to the aircraft", "true" ] }, { "ans": [ "APU", "false" ] }, { "ans": [ "Other running engine", "false" ] } ], "title": "ATA 80:", "ref": "A. Ref: REF: A330 RR Trent 7000 T1+T2 Page 630" }, { "ch": "How many positions do the engine master switches have and what are they? (A,B1,B2)", "ansGr": [ { "ans": [ "3: On, Normal and OFF", "false" ] }, { "ans": [ "3: Cranking, Normal and Ignition/Starting", "false" ] }, { "ans": [ "2: On and Off", "true" ] } ], "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 204" }, { "ch": "Where are primary engine parameters displayed? (A, B2)", "ansGr": [ { "ans": [ "On the ED", "true" ] }, { "ans": [ "On the SD Engine Page", "false" ] }, { "ans": [ "On both the ED and SD Engine Page", "false" ] } ], "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 42" }, { "ch": "Can the starter control valve (SCV) be opened manually? (A,B1,B2)", "ansGr": [ { "ans": [ "Can not", "false" ] }, { "ans": [ "Yes, through a manual opening lever", "false" ] }, { "ans": [ "Yes, using a standard tool with an extension through a dedicated hole in the fan cowling", "true" ] } ], "ref": "Ref : A330 RR Trent 7000 T1+T2 Page 400" }, { "ch": "How is the starter valve controlled and operated? (B1, B2)", "ansGr": [ { "ans": [ "It is electrically controlled and operated", "false" ] }, { "ans": [ "It is pneumatically controlled and operated", "false" ] }, { "ans": [ "It is electrically controlled and pneumatically operated", "true" ] } ], "ref": "Ref:: A330 RR Trent 7000 T1+T2 Page 224" }, { "ch": "Where does the EEC receive feedback information from the Starter Control Valve? (B1, B2)", "ansGr": [ { "ans": [ "No feedback signal", "false" ] }, { "ans": [ "From the solenoid’s energized or de-energized status", "false" ] }, { "ans": [ "From a micro-switch on the valve", "true" ] } ], "ref": "Ref:: A330 RR Trent 7000 T1+T2 Page 338" }, { "ch": "How does the EEC monitor the open/close position of the Engine Section Stator Anti-Ice Valve? (B1, B2)", "ansGr": [ { "ans": [ "By a pressure transducer downstream of the valve", "true" ] }, { "ans": [ "By the solenoid’s energized or de-energized status", "false" ] }, { "ans": [ "By a micro-switch on the valve", "false" ] } ], "ref": "Ref: A330 RR Trent 7000 T1+T2 Page 274" }, { "ch": "Where is the pneumatic starter installed? (B1, B2)", "ansGr": [ { "ans": [ "On the right-hand side of the gearbox", "false" ] }, { "ans": [ "On the rear side of the gearbox", "false" ] }, { "ans": [ "On the front side of the gearbox", "true" ] } ], "ref": "Ref: A330 RR Trent 7000 T1+T2 Page 363" }, { "ch": "Where is the IDG installed? (B1, B2)", "ansGr": [ { "ans": [ "On the right-hand side of the gearbox", "false" ] }, { "ans": [ "On the rear side of the gearbox", "true" ] }, { "ans": [ "On the front side of the gearbox", "false" ] } ], "ref": "Ref: A330 RR Trent 7000 T1+T2 Page 365" }, { "ch": "Which parts of the T7000 engine can be separated for transportation? (B1, B2)", "ansGr": [ { "ans": [ "The entire engine needs to be built up before transportation", "false" ] }, { "ans": [ "Only the fan blades and the exhaust nozzle", "false" ] }, { "ans": [ "The engine core and fan case (with the external gearbox)", "true" ] } ], "ref": "Ref: A330 RR Trent 7000 T1+T2 Page 360" }, { "ch": "What is the function of the PMA on the T7000 engine? (B1, B2)", "ansGr": [ { "ans": [ "A single winding provides power to both EEC channels.", "false" ] }, { "ans": [ "One of the dual windings provides power to each EEC channel.", "true" ] }, { "ans": [ "Each of the dual windings provides power to one EEC channel, and the third single winding supplies the N2 speed signal.", "false" ] } ], "ref": "Ref:: A330 RR Trent 7000 T1+T2 Page 212" }, { "ch": "A330 GE CF6 – The connections between the fan electrical harnesses and the pylon: (Level B2)", "ansGr": [ { "ans": [ "On the LH side pylon near to the engine front mount", "false" ] }, { "ans": [ "On the LH side of the fan case upper part", "true" ] }, { "ans": [ "On the RH side of the fan case upper part", "false" ] } ], "part": "GE-CF6 CAT B2", "title": "ATA 70 – INTRO – Standard practice – Constructional arrangement and Engine performance & operation", "ref": "Ref Airbus A330 (GE CF6) B1+B2 Technical Training Manual – Power Plant installaton D/O page 16" }, { "ch": "A330 GE CF6 – What is the main parameter of the engine thrust: (Level B2)", "ansGr": [ { "ans": [ "N1 fan speed", "true" ] }, { "ans": [ "N2 core speed", "false" ] }, { "ans": [ "EPR", "false" ] } ], "ref": "Ref Airbus A330 (GE CF6) B1+B2 Technical Training Manual – Engine thrust page 270" }, { "ch": "A330 GE CF6 – How can the TR be de-activated for maintenance task: (Level B2)", "ansGr": [ { "ans": [ "Remove the lock plate on the CDU, of each half, and install again inverted", "true" ] }, { "ans": [ "Remove the connector from the directional control valve", "false" ] }, { "ans": [ "Install 3 locking plates on the leading edge of each TR sleeve", "false" ] } ], "ref": "Ref Airbus A330 (GE CF6) B1+B2 Technical Training Manual – Power plant system line maintenance page 384" }, { "ch": "A330 GE CF6 – The HP system includes: (Level B2)", "ansGr": [ { "ans": [ "8 stages HPCs, 1 stage HPT, and the bleed ports", "false" ] }, { "ans": [ "11 stage HPCs, 2 stage HPTs, and the compressor stator vane control system", "false" ] }, { "ans": [ "14 stage HPCs, 2 stage HPTs, and the combustion chamber", "true" ] } ], "title": "ATA 71 – Power plant", "ref": "Ref Airbus A330 (GE CF6) B1+B2 Technical Training Manual – Engine D/O page 53" }, { "ch": "A330 GE CF6 – Variable Bleed Valve (VBV) provide: (Level B2)", "ansGr": [ { "ans": [ "An optimum angle of attack of the air for the high pressure compressure in all speed", "false" ] }, { "ans": [ "Proper operation of the low pressure compressure in all speed", "true" ] }, { "ans": [ "Proper operation of the low pressure compressure in high speed or during engine shutdown", "false" ] } ], "title": "ATA 72 – Engine modules", "ref": "Ref Airbus A330-200/300 GE CF6 Line and Base Maintenance – Variable Bleed Valves page 50" }, { "ch": "A330 GE CF6 – What is the primary purpose of the Fuel Filter Δ Pressure Switch: (Level B2)", "ansGr": [ { "ans": [ "To identify to the crew the filter is blocking or blocked with a CLOG indication on the SD and an ECAM message", "true" ] }, { "ans": [ "To provide a signal to the ECU to increase the fuel flow through the FOHE", "false" ] }, { "ans": [ "To provide a class 2 CMS message that a Fuel Filter is blocked with no associated ECAM message", "false" ] } ], "title": "ATA 73 – Engine Fuel and Control", "ref": "Ref Airbus A330 (GE CF6) B1+B2 Technical Training Manual – Engine Fuel System indicating page 95" }, { "ch": "A330 GE CF6 – Where is fuel flow indicated to the crew: (Level B2)", "ansGr": [ { "ans": [ "Fuel Metering Unit (FMU) signal to EEC for indication on the ECAM Engine page", "false" ] }, { "ans": [ "Fuel Flow transmitter transmits signal to ECU for indication on the ECAM Engine page", "true" ] }, { "ans": [ "Fuel Distribution transmitter transmits signal to EIVMU for indication on the Engine SD page", "false" ] } ], "ref": "Ref Airbus A330 (GE CF6) B1+B2 Technical Training Manual – Engine Fuel System inputs/outputs page 122" }, { "ch": "A330 GE CF6 – How many fuel nozzle installed: (Level B2)", "ansGr": [ { "ans": [ "24 fuel nozzles", "false" ] }, { "ans": [ "26 fuel nozzles", "false" ] }, { "ans": [ "30 fuel nozzles", "true" ] } ], "ref": "Ref Airbus A330-200/300 GE CF6 Line and Base Maintenance – Engine general page 54" }, { "ch": "A330 GE CF6 – Which component control fuel flow to the engine’s combustion system: (Level B2)", "ansGr": [ { "ans": [ "Fuel Metering Unit (FMU)", "false" ] }, { "ans": [ "Hydromechanical Unit (HMU)", "true" ] }, { "ans": [ "Pressurizing and Shutoff Valve (PSOV)", "false" ] } ], "ref": "Ref Airbus A330-200/300 GE CF6 Line and Base Maintenance – Fuel system description page 102" }, { "ch": "A330 GE CF6 – The fuel distribution system including: (Level B2)", "ansGr": [ { "ans": [ "Fuel pump, fuel filter, Fuel Metering Unit (FMU), fuel flow transmitter, fuel nozzlees", "false" ] }, { "ans": [ "Fuel pump, fuel/oil heat exchanger, Hydromechanical Unit (HMU), fuel manifold, fuel nozzles", "true" ] }, { "ans": [ "Fuel pump, servo fuel heater, Hydromechanical Unit (HMU), fuel distribution valve, fuel nozzles", "false" ] } ], "ref": "Ref Airbus A330-200/300 GE CF6 Line and Base Maintenance – Fuel system description page 102" }, { "ch": "A330 GE CF6 – The fuel flow transmitter: (Level B2)", "ansGr": [ { "ans": [ "Provide an electrical pulse signal to both the ECU, and electrically self energized when driven by the flowing fuel", "true" ] }, { "ans": [ "Provide an electrical discrete signal to both the ECU, and power supply by the Permanent Magnetic Alternator (PMA)", "false" ] }, { "ans": [ "Provide an electrical signal to both EEC, and power supply by the active EEC", "false" ] } ], "ref": "Ref Airbus A330-200/300 GE CF6 Line and Base Maintenance – Fuel indication components page 104" }, { "ch": "A330 GE CF6 – What happen if CLOG indication is displayed at", "ansGr": [ { "ans": [ "USED indication on Engine SD page: (Level B2)", "false" ] }, { "ans": [ "The supply Fuel filter is clogged and bypassed", "false" ] }, { "ans": [ "The Strainer of Fuel Metering Unit (FMU) is clogged and bypassed", "false" ] }, { "ans": [ "The actual filter bypass might not occuring", "true" ] } ], "ref": "Ref Airbus A330-200/300 GE CF6 Line and Base Maintenance – Engine fuel system page 108" }, { "ch": "A330 GE CF6 – The fuel filter differential pressure switch signal: (Level B2)", "ansGr": [ { "ans": [ "Sent to ECU via EIVMU", "false" ] }, { "ans": [ "Hardwired into both ECU channels A and B", "true" ] }, { "ans": [ "Sent to DMC via EIVMU for CLOG indication", "false" ] } ], "ref": "Ref Airbus A330-200/300 GE CF6 Line and Base Maintenance – Engine fuel system page 108" }, { "ch": "A330 GE CF6 – The Fuel Metering Valve: (Level B2)", "ansGr": [ { "ans": [ "Located within Fuel Metering Unit (FMU), electrically driven by 2 Torque Motors (TMs), each TM contains an electrically isolated coil controlled by one dedicated ECU channel", "false" ] }, { "ans": [ "Located with Integrated Fuel Pump and Control (IFPC), hydraulically driven by Dual channel Torque Motors, one channel to EEC channel A, the other to channel B", "false" ] }, { "ans": [ "Located within Hydromechanical Unit (HMU), hydraulically driven by a Torque Motor/servo valve, TM control by 2 coils, one to ECU channel A, the other to channel B", "true" ] } ], "ref": "Ref Airbus A330-200/300 GE CF6 Line and Base Maintenance – Hydromechanical Unit page 110" }, { "ch": "A330 GE CF6 – The engine fuel nozzle is equipped with: (Level B2)", "ansGr": [ { "ans": [ "There are 10 single pipe manifolds, which each supply 3 fuel injectors loacted inside the combustor", "false" ] }, { "ans": [ "30 fuel spray nozzles installed at equal distance, 15 LH and 15 RH nozzles grouped in adjacent pairs. 2 different part numbers (P/N) for even and odd fuel spray nozzles", "false" ] }, { "ans": [ "28 Standard nozzles with aluminum identity bands and 2 pilot light nozzles with blue identity bands", "true" ] } ], "ref": "Ref Airbus A330-200/300 GE CF6 Line and Base Maintenance – Engine fuel nozzles page 122" }, { "ch": "A330 GE CF6 – The Pilot light nozzle: (Level B2)", "ansGr": [ { "ans": [ "Installed on the secondary manifold. The nozzles fit with a distributor weight assembly allowed control the fuel distribution during engine start and relight", "false" ] }, { "ans": [ "At position #5 and #6 in the Compressor Rear Frame (CRC) provide a richer than normal fuel flow on primary circuit for altitude relights", "true" ] }, { "ans": [ "Installed next to ignitor plugs. The nozzles have additonal secondary flow supplements primary flow to provide a higher rates and preventing possible flameouts", "false" ] } ], "ref": "Ref Airbus A330-200/300 GE CF6 Line and Base Maintenance – Engine fuel nozzles page 122" }, { "ch": "A330 GE CF6 – Moving master switch lever from “ON” to “OFF” position: (Level B2)", "ansGr": [ { "ans": [ "Cut off power supply to ECU, memory reset function of the ECU", "false" ] }, { "ans": [ "All data stored in the ECU RAM memory will be cleared", "true" ] }, { "ans": [ "Closes channel reset discrete contact, resetting active ECU channel", "false" ] } ], "title": "ATA 73A – FADEC", "ref": "Ref Airbus A330 (GE CF6) B1+B2 Technical Training Manual – Engine Master control D/O page 288" }, { "ch": "A330 GE CF6 – How to perform memory reset function of the ECU: (Level B2)", "ansGr": [ { "ans": [ "ENG MASTER lever is directly hardwired to the ECU to satisfy the reset function", "true" ] }, { "ans": [ "EIVMU send signal to reset ECU each time engine shutdown", "false" ] }, { "ans": [ "ON then OFF the ENG FADEC GND PWR P/B on MAINTENANCE PANEL", "false" ] } ], "ref": "Ref Airbus A330 (GE CF6) B1+B2 Technical Training Manual – Engine Master control D/O page 288" }, { "ch": "A330 GE CF6 – FADEC system including: (Level B2)", "ansGr": [ { "ans": [ "3 potentiometers in Throttle Control Unit, send throttle control lever position to the Flight Control Primary Computers (FCPCs) for control of the thrust reverser independent locking system (disk brakes)", "false" ] }, { "ans": [ "Dual resolver in Throttle Control Unit, transmits the throttle control lever position signal back to the ECU", "true" ] }, { "ans": [ "3 Potentiometers and Dual resolver in Throttle Control Unit", "false" ] } ], "ref": "Ref Airbus A330 (GE CF6) B1+B2 Technical Training Manual – Throttle Control lever assembly page 272" }, { "ch": "A330 GE CF6 – Which signal is used for thrust reverser deployment control: (Level B2)", "ansGr": [ { "ans": [ "Dual Resolver in Throttle Control Unit (TCU) sends Throttle Resolver Angle (TRA) to the ECU for thrust reverser deployment control", "false" ] }, { "ans": [ "Microswitch in Thrust Reverser Control Levers sends a \"thrust reverse selected\" signal to the ECU for thrust reverser deployment control", "false" ] }, { "ans": [ "Microswitch in Throttle Control Unit (TCU) sends a \"thrust reverse selected\" signal to the EIVMU for thrust reverser deployment control", "true" ] } ], "ref": "Ref Airbus A330 (GE CF6) B1+B2 Technical Training Manual – Throttle Control lever assembly page 272" }, { "ch": "A330 GE CF6 – ECU receives information from Air Data and Inertial References Unit (ADIRU): (Level B2)", "ansGr": [ { "ans": [ "Each channel of the ECU has inputs from Air Data Inertial Reference Unit (ADIRU 1 & 2). Each ADIRU supplies data to both channels of ECU 1 and ECU 2", "false" ] }, { "ans": [ "Each ECU channel receives digital data bus from two ADIRUs, data crosswired internally to the other channel", "true" ] }, { "ans": [ "Each Air Data Inertial Reference Unit (ADIRU) is wired to the Engine Relay Unit (ERU) where it is split into both channels of the ECU", "false" ] } ], "ref": "Ref Airbus A330-200/300 GE CF6 Line and Base Maintenance – ECU interfaces page 126" }, { "ch": "A330 GE CF6 – Each ECU channel has its own set of sensors and feedback signals, except: (Level B2)", "ansGr": [ { "ans": [ "T49 and T5", "true" ] }, { "ans": [ "T3 and PS3", "false" ] }, { "ans": [ "T25 and Engine Oil Temp (TEO)", "false" ] } ], "ref": "Ref Airbus A330-200/300 GE CF6 Line and Base Maintenance – FADEC Basic system schematic page 127" }, { "ch": "A330 GE CF6 – How can ECU be power supplied if EIVMU power failed: (Level B2)", "ansGr": [ { "ans": [ "The ECU directly supplied by 115V AC EXT BUS 901XP for limited engine operation mode if mode selector is set to IGN/START or CRANK position", "false" ] }, { "ans": [ "The ECU directly supplied by 115V AC ESS BUS 401PP for limited engine operation mode if MASTER LEVER is set to ON", "false" ] }, { "ans": [ "The EIVMU failsafe powers the ECU even when its not powered itself", "true" ] } ], "ref": "Ref Airbus A330-200/300 GE CF6 Line and Base Maintenance – FADEC power supply page 140" }, { "ch": "A330 GE CF6 – Where can we have CMS FUEL USED information: (Level B2)", "ansGr": [ { "ans": [ "From MCDU ECU/CHAN – SPECIFIC DATA menu", "true" ] }, { "ans": [ "From MCDU FADEC/CHAN – TROUBLE SHOOTING DATA menu", "false" ] }, { "ans": [ "From MCDU EEC/CHAN – GROUND SCANNING menu", "false" ] } ], "ref": "Ref Airbus A330-200/300 GE CF6 Line and Base Maintenance – Engine FADEC tests page 164" }, { "ch": "A330 GE CF6 – How is the ignition systems powered: (Level B2)", "ansGr": [ { "ans": [ "One AC normal power supplies normal bus to ECU channel A and one AC emergency power supplies essential bus to ECU channel B", "false" ] }, { "ans": [ "One AC emergency power supplies essential bus to ECU channel A and one AC normal power supplies normal bus to ECU channel B.", "true" ] }, { "ans": [ "Both ignition systems are powered by the emergency busbar for redundancy", "false" ] } ], "title": "ATA 74 – Ignition", "ref": "Ref Airbus A330 (GE CF6) B1+B2 Technical Training Manual – Ignition system description page 189" }, { "ch": "A330 GE CF6 – What is the correct sentence: (Level B2)", "ansGr": [ { "ans": [ "Each exciter (A and B) is electrical wired to ECU channel A and B. At each start, the ECU selects alternatively one ignition system (A or B)", "false" ] }, { "ans": [ "Exciter A is electrically wired to the ECU channel A and exciter B to ECU channel B. The ECU can use internal switching relays to command the two exciters.", "true" ] }, { "ans": [ "Ignition system supplied by 115V AC ESS BUS through ECU and EIVMU", "false" ] } ], "ref": "Ref Airbus A330 (GE CF6) B1+B2 Technical Training Manual – Ignition system description page 189" }, { "ch": "A330 GE CF6 – Variable Startor Vanes (VSV): (Level B2)", "ansGr": [ { "ans": [ "5 stages, operated by 2 hydraulic actuators via fuel", "false" ] }, { "ans": [ "6 stages, operated by 1 hydraulic actuators via fuel", "false" ] }, { "ans": [ "6 stages, operated by 2 hydraulic actuators via fuel", "true" ] } ], "title": "ATA 75 – Air", "ref": "Ref Airbus A330 (GE CF6) B1+B2 Technical Training Manual – Air flow control system D/O page 252" }, { "ch": "A330 GE CF6 – How is feedback from the Variable Bleed Valves (VBV) to the Engine Control Unit (ECU) carried out: (Level B2)", "ansGr": [ { "ans": [ "Each VBV actuator integrated one Linear Variable Differential Transformers (LVDT) provides positon feedback to both ECU channels", "false" ] }, { "ans": [ "Each VBV actuator integrated one Linear Variable Differential Transformers (LVDT). Left actuator feedback to the ECU-CHA, and right actuator to the ECU-CHB", "true" ] }, { "ans": [ "Each VBV actuator integrated two Linear Variable Differential Transformers (LVDTs). Each actuator LVDT provides positon feedback to one ECU channel", "false" ] } ], "ref": "Ref Airbus A330-200/300 GE CF6 Line and Base Maintenance – Compressor control (VBV) page 202" }, { "ch": "A330 GE CF6 – Bore Cooling Valve position feedback: (Level B2)", "ansGr": [ { "ans": [ "A dual Linear Variable Differential Transducer (LVDT) sends feedback signals to each ECU", "false" ] }, { "ans": [ "The ECU receives valve positon feedback from LVDTs mechanically linked to the valve actuator. Valve also has visual O/C positon indicator on the valve body", "false" ] }, { "ans": [ "No feedback positon for the ECU. Manual check valve position by inspecting wire length putting in the positon indication hole on the outlet flange of the valve", "true" ] } ], "ref": "Ref Airbus A330-200/300 GE CF6 Line and Base Maintenance – Bore Cooling System page 182" }, { "ch": "A330 GE CF6 – How does the Variable Stator Vane (VSV) system operate: (Level B2)", "ansGr": [ { "ans": [ "Movement of 2 hydraulic actuators connected to a bellcrank that drives a unison ring, which in turn connected to twelve other bellcranks that position the Stator Vane", "false" ] }, { "ans": [ "Movement of 2 hydraulic actuators raises or lowers the forward end of the actuator levers and linkage causing the actuation rings to rotate circumferentially around compressor case", "true" ] }, { "ans": [ "The torque motor will position the actuator pilot valve to move the actuator piston shaft. Actuator movement is transmitted by mechanical linkage and a series of cams and rollers to position the Stator Vane", "false" ] } ], "ref": "Ref Airbus A330-200/300 GE CF6 Line and Base Maintenance – VSV control schemetic page 200" }, { "ch": "A330 GE CF6 – What is the power supply source of Electronic Control Unit (ECU) power: (Level B2)", "ansGr": [ { "ans": [ "The primary source of ECU electrical power when engine is in operation is Permanent Magnet Alternator (PMA)", "true" ] }, { "ans": [ "The ECU is supplied by Permanent Magnet Alternator (PMA) when N2 >12%, and by the number 1 AC ESSENTIAL BUS when N2 <= 12%", "false" ] }, { "ans": [ "The ECU is supplied by Permanent Magnet Alternator (PMA) when N1 >15%, and by the number 1 AC ESSENTIAL BUS when N1 <= 15%", "false" ] } ], "title": "ATA 76 – Engine Controls", "ref": "Ref Airbus A330 (GE CF6) B1+B2 Technical Training Manual – FADEC power supply D/O page 140" }, { "ch": "A330 GE CF6 – The Permanent Magnet Alternator (PMA) supplies power to ECU by: (Level B2)", "ansGr": [ { "ans": [ "One PMA supplies power to both ECU", "false" ] }, { "ans": [ "One PMA, each have two independent coils provide the power to the two separate ECU channels", "true" ] }, { "ans": [ "Two PMAs, each PMA provide the power to the two separate ECU channels", "false" ] } ], "ref": "Ref Airbus A330-200/300 GE CF6 Line and Base Maintenance – Electronic Control Unit (ECU) page 134" }, { "ch": "A330 GE CF6 – What would be the effect on the Engine Thrust Control, for an acceptable Take-Off power setting, if there is an ENG 1(2) EIU FAULT: (Level B2)", "ansGr": [ { "ans": [ "Only DERATE power settings are lost (TOGA and FLEX available only)", "false" ] }, { "ans": [ "TOGA and DERATE power settings are lost (FLEX available only)", "false" ] }, { "ans": [ "The FLEX and DERATE power settings are lost (TOGA available only)", "true" ] } ], "ref": "Ref Airbus A330 (GE CF6) B1+B2 Technical Training Manual – EIVMU interfaces page 138" }, { "ch": "A330 GE CF6 – ECU receives Throttle control lever positon signal from: (Level B2)", "ansGr": [ { "ans": [ "Two Linear Variable Differential Transformers (LVDT) in the Throttle Control Unit, each LVDT send signal to each ECU channel", "false" ] }, { "ans": [ "Dual resolver in the Throttle Control Unit, each resolver send signal to each ECU channel", "true" ] }, { "ans": [ "Two potentiometer in the Throttle Control Unit, each potentiometer send signal to both ECU channel", "false" ] } ], "ref": "Ref Airbus A330 (GE CF6) B1+B2 Technical Training Manual – Throttle Control lever assembly page 272" }, { "ch": "A330 GE CF6 – Target thrust limitation in automatic thrust setting mode: (Level B2)", "ansGr": [ { "ans": [ "FMGE computes the target thrust parameter and target thrust limit", "false" ] }, { "ans": [ "FMGE computes the target thrust parameter, and ECU computes target thrust limit", "false" ] }, { "ans": [ "Target thrust parameter is limited by the actual position of the throttle control lever", "true" ] } ], "ref": "Ref Airbus A330-200/300 GE CF6 Line and Base Maintenance – Thrust control page 270" }, { "ch": "A330 GE CF6 – Engine thrust parameter computation in automatic thrust setting mode: (Level B2)", "ansGr": [ { "ans": [ "ECU computes the target thrust parameter, and engine thrust is limited by the actual position of the throttle control lever except when an alpha floor protection is activated", "false" ] }, { "ans": [ "ECU computes the target thrust parameter and FMGE computes the engine thrust limit parameter", "false" ] }, { "ans": [ "FMGEC computes the target thrust parameter and ECU computes the engine thrust limit parameter", "true" ] } ], "ref": "Ref Airbus A330 (GE CF6) B1+B2 Technical Training Manual – Thrust setting phylosophy page 278" }, { "ch": "A330 GE CF6 – What is the bypass condition indicating of the lube supply filter in Lube & Scavenge pump: (Level B2)", "ansGr": [ { "ans": [ "By a red popout indicator (DPI) on the top of the filter case", "false" ] }, { "ans": [ "CLOG indication on EWD sent by an external differential pressure switch through pressure port located on the filter head", "false" ] }, { "ans": [ "No indication is provided", "true" ] } ], "title": "ATA 77 – Engine Indicating systems", "ref": "Ref Airbus A330-200/300 GE CF6 Line and Base Maintenance – Engine Oil system page 86" }, { "ch": "A330 GE CF6 – The N1 speed sensor signals: (Level B2)", "ansGr": [ { "ans": [ "Generated by two electrically isolated coils. 1 coils signal to both channel of ECU, and the remaining coil signals to EIVMU", "false" ] }, { "ans": [ "Generated by three electrically isolated coils. 2 coils signal to each channel of ECU, and the third coil signals to EIVMU", "true" ] }, { "ans": [ "Generated by four electrically isolated coils. 2 coils signal to both channel of ECU, and the remaining 2 coil signal to EIVMU", "false" ] } ], "ref": "Ref Airbus A330-200/300 GE CF6 Line and Base Maintenance – Power and Speed indication page 236" }, { "ch": "A330 GE CF6 – For Engine monitoring, EIVMU receives these speed signals: (Level B2)", "ansGr": [ { "ans": [ "Two N1&N2 speed signal from ECU", "false" ] }, { "ans": [ "Two analog N1&N2 speed signal from N1&N2 speed sensor, and two N1&N2 speed signal from ECU used as back-up", "false" ] }, { "ans": [ "Two N1&N2 speed signal from ECU, and a analog N1 speed signal from N1 speed sensor used as a back-up", "true" ] } ], "ref": "Ref Airbus A330 (GE CF6) B1+B2 Technical Training Manual – Vibration monitoring system D/O page 292" }, { "ch": "A330 GE CF6 – Does the ECU have authority to deploy and stow the thrust reverser: (Level B2)", "ansGr": [ { "ans": [ "Yes, the ECU directly deploys and stows the thrust reverser", "false" ] }, { "ans": [ "Yes, the ECU via EIVMU send signal to Thrust Reverser Pressurizing Valve (TRPV), and unlock signal from LGCIUs and FCPCs, to deploys and stows the thrust reverser", "false" ] }, { "ans": [ "No, the ECU monitors reverser position and limits engine thrust during deployment but can not directly deploy or stow it", "true" ] } ], "title": "ATA 78 – Exhaust", "ref": "Ref Airbus A330 (GE CF6) B1+B2 Technical Training Manual – Thrust Reverser system D/O page 297" }, { "ch": "A330 GE CF6 – Which sensor provides the signal for thrust reverser position indication (REV) on the ECAM display: (Level B2)", "ansGr": [ { "ans": [ "Pressure switch on the Directional Control Valve (DCV)", "false" ] }, { "ans": [ "Position Switch Module (PSM) of Center Drive Unit (CDU)", "true" ] }, { "ans": [ "Dual Position Feedback Sensor (Rotary Variable Differential Transformer RVDT) of Center Drive Unit (CDU)", "false" ] } ], "ref": "Ref Airbus A330 (GE CF6) Line and Base Maintenance – Center Drive Unit (CDU) page 302" }, { "ch": "A330 GE CF6 – The Thrust Reverser Independent locking system interfaces with which computer: (Level B2)", "ansGr": [ { "ans": [ "FCPC 1 and FCPC 3", "true" ] }, { "ans": [ "FCPC 2 and FCPC 3", "false" ] }, { "ans": [ "FCPC 1 and FCPC 2", "false" ] } ], "ref": "Ref Airbus A330 (GE CF6) Line and Base Maintenance – Thrust reverser schematic page 297" }, { "ch": "A330 GE CF6 – The bypass valve of Fuel Oil Heat Exchanger (FOHE) open if: (Level B2)", "ansGr": [ { "ans": [ "Hot fuel or contaminated fuel", "false" ] }, { "ans": [ "Hot oil or contaminated fuel", "false" ] }, { "ans": [ "Very cold oil or contaminated oil", "true" ] } ], "title": "ATA 79 – Oil", "ref": "Ref Airbus A330-200/300 GE CF6 Line and Base Maintenance – Engine oil system page 88" }, { "ch": "A330 GE CF6 – The oil pressure transmitter: (Level B2)", "ansGr": [ { "ans": [ "Has 1 oil pressure transmitter, send signal to both channels of ECU", "false" ] }, { "ans": [ "Has 2 oil pressure transmitters, one for each channel of ECU", "true" ] }, { "ans": [ "Has 2 oil pressure transmitters, each of one send signal to both channels of ECU for redundancy", "false" ] } ], "ref": "Ref Airbus A330-200/300 GE CF6 Line and Base Maintenance – Engine oil indicating page 92" }, { "ch": "A330 GE CF6 – The IDG oil temperature sensor: (Level B2)", "ansGr": [ { "ans": [ "Mounted in the IDG oil-out tube just aft of the IDG, dual themocouples sensor provide signal to each ECU channel", "false" ] }, { "ans": [ "Mounted in the IDG oil-in tube just aft of the IDG, single sensor provides signal to channel A of the ECU", "true" ] }, { "ans": [ "Mounted in the IDG Air/Oil Cooler oil-out tube at the lower, single sensor provides signal to both ECU channel", "false" ] } ], "ref": "Ref Airbus A330-200/300 GE CF6 Line and Base Maintenance – IDG oil inlet temperature sensor page 224" }, { "ch": "A330 GE CF6 – The air starter operating duty cycle: (Level B2)", "ansGr": [ { "ans": [ "Three starter crank attempts and 35-second cooling period between each starter crank attempt. After 15-minute cumulative cranking followed by a 15-minute minimum period when the N2 speed is zero RMP", "false" ] }, { "ans": [ "5 mins ON with a 2 mins cooling period. After the first cycle, repeat operation requires a 10 mins cooling period between each ON cycle", "true" ] }, { "ans": [ "Three starter crank cycles or 5 minutes maximum of continuous cranking. A 30 mins cool down period is necessary for additional use", "false" ] } ], "title": "ATA 80 – Starting", "ref": "Ref Airbus A330-200/300 GE CF6 Line and Base Maintenance – Starter page 346" }, { "ch": "A330 GE CF6 – Which sensor give IDG LOW OIL LEVEL message: (Level B2)", "ansGr": [ { "ans": [ "The Remote Oil Level Sensor (ROLS) is installed in the IDG", "true" ] }, { "ans": [ "The IDG Low Oil Level (LOL) switch installed on the bottom of the IDG", "false" ] }, { "ans": [ "There is no sensor gives IDG LOW OIL LEVEL message. Visual check the IDG oil level through the oil level sight-glass", "false" ] } ], "title": "ATA 24 – Electrical System", "ref": "Ref Airbus A330 (GE CF6) B1+B2 Technical Training Manual – IDG oil level page 47" }, { "ch": "A330 GE CF6 – AFECU actives the APU fire extinguishing sequence if have APU fire signal and: (Level B2)", "ansGr": [ { "ans": [ "Receives a flight/ground signal discrete input from LGCIU 1", "true" ] }, { "ans": [ "Receives a flight/ground signal discrete input from current active LGCIU", "false" ] }, { "ans": [ "Receives a flight/ground signal discrete input from LGCIU 1 or the signal from the GAPCU indicates ground power power connection", "false" ] } ], "title": "ATA 26 – Fire protection", "ref": "Ref Airbus A330 (GE CF6) B1+B2 Technical Training Manual – APU Fire protection D/O page 67" }, { "ch": "A330 GE CF6 – The Engine anti-ice valve: (Level B2)", "ansGr": [ { "ans": [ "Pneumatically operatrd, electrical controlled and spring loaded close", "false" ] }, { "ans": [ "Pneumatically operated, electrical controlled and spring loaded open", "true" ] }, { "ans": [ "Electrical controlled and operated, spring loaded open", "false" ] } ], "title": "ATA 30 – Ice and Rain protection", "ref": "Ref Airbus A330-200/300 GE CF6 Line and Base Maintenance – Engine control page 268" }, { "ch": "A330 GE CF6 – Cross bleed isolation valve operation during engine starting: (Level B2)", "ansGr": [ { "ans": [ "Opens automatically if using bleed air from APU, Opens manually if using bleed air from HP ground air supply or outer engine", "true" ] }, { "ans": [ "Opens automatically if using bleed air from APU or outer engine, Opens manually if using bleed air from HP ground air supply", "false" ] }, { "ans": [ "Opens automatically if using bleed air from outer engine, Opens manually if using bleed air from HP ground air supply or APU", "false" ] } ], "title": "ATA 36 – Bleed system", "ref": "Ref Airbus A330-200/300 GE CF6 Line and Base Maintenance – Starter duct page 348" } ]