TEST BORRADO, QUIZÁS LE INTERESE:
BOEING02
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Título del Test:
BOEING02 Descripción: CONOCIMIENTOS Autor: COMPRASONLINE OTROS TESTS DEL AUTOR Fecha de Creación: 02/05/2024 Categoría: Otros Número Preguntas: 51 |
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WHICH HYDRAULIC SYSTEM PROVIDES NORMAL PRESSURE TO OPERATE THE LANDING GEAR? CENTER LEFT. IF THE LEFT SYSTEM PUMPS ARE NOT PRODUCCING PRESSURE, BUR FLUID REMAINS AVAILABLE BELOW THE STANDPIPE, IS ANY PORTION OF THE LEFT HYDRAULIC SYSTEM PRESSURIZED? NO YES, THE COMPONENTS POWERED BY THE PTU. WHICH CENTER HYDRAULIC PUMP IS NORMALLY INHIBITED WHEN ONLY ONE ELECTRICAL SOURCE OF POWER IS AVAILABLE? 1 2. WHICH HYDRAULIC SYSTEM PROVIDES NORMAL PRESSUE TO OPERATE THE HYDRAULIC DRIVEN GENERATOR? CENTER LEFT. THE POWER TRANSFER UNID IS USED TO AUGEMENT THE ELECTRIC MOTOR-DRIVEN PUMP IN CASE THE ______ PUMP OUTPUT IS LOW OR THE LEFT ENGINE FAILS. IT IS BASICALLY DRIVEN BY RIGHT SYSTEM PRESSURE. LEFT MOTOR PUMP LEFT ENGINE DRIVEN. WHAT IS THE MINIMUM AIRSPEED FOR SUCCESSFUL RAT OPERATIONS? 100 KTS 130 KTS. CAN THE RAT BE MANUALLY DEPLOYED? NO- AUTOMATIC OPERATION IS REQUIRED YES- SWITCH IS POWERED BY THE HOT BATTERY BUS. IF THE FLUID LEVEL IN THE RESERVOIR HAS LEAKED DOWN TO THE TOP STANDPIPE, FLUID REMAINS AVAILABLE FOR OPERATION OF THE_______ MOTOR DRIVE PUMP PTU. THE RSVR LIGHT SERVES AS A MONITORING LIGHT FOR ________ HYDRAULIC FLUID QUANTITY ONLY BOTH THE QUANTITY OF HYDRAULIC FLUID IN THE RESERVOIR AND PNEUMATIC HEAD PRESSURE OF THE RESERVOIR. WHICH HYDRAULIC SYSTEM PROVIDES THE PRESSURE TO THE NORMAL BRAKE SYSTEM? CENTER RIGTH. WHICH COCKPIT WINDOWS HAVE ONLY ANTI-FOGGING PROTECTION? SIDE FORWARD. WHICH PROBE IS ONLY HEATED WHEN IN FLIGHT? THE TAT PROBE THE CAPTAINS PILOT PROBE. CAN ENGINE ANTI-ICE OPERATE ON THE GROUND AND IN FLIGHT? YES NO. ENGINE ANTI-ICE MUST BE ON DURING ALL GROUND AND FLIGHT OPERATIONS WHEN ICING CONDITIONS EXIST TRUE FALSE. ELECTRICAL POWER TO THE PROBE HEATERS IS APPLIED ANY TIME AN ENGINE RUNNING ANY TIME ELECTRICAL POWER IS ON THE AIRCRAFT. WHAT PART OF THE ENGINE IS ANTI-ICED? THE LEADING EDGE OF THE ENGINE NOSE COWL THE LEADING EDGE OF THE ENGINE NOSE COWL AND THE INLET GUIDE VANES. DOES THE OPERATION OF THE STANDBY FLIGHT ISNTRUMENTS REQUIRE AN OPERATING AIR DATA COMPUTER? YES NO. The standby altitude indicator is a self-contained instrument that also incorporates an ILS display. ILS information is supplied by the left ILS reciver center ILS reciver. WHICH OF THE FOLLOWING POSITIONS OF THE EHSI MODE SELECTOR WILL CAUSE THE VOR TO OPERATE IN THE AUTOMATIC TUNING MODE? FULL VOR MAP. THE OPPOSITE ADC CAN BE AS A ALTERNATE SOURCE OF AIR DATA INFORMATION THROUGH THE INSTRUMENT SOURCE SELECTOR PANEL _____ SWITCH IRS AIR DATA. WHN THE VORs ARE TUNED BY THE FMCs, THE VOR PANEL FREQ WINDOWS DISPLAY THE _______ FREQUENCIES MANUALLY SELECTED FMC TUNED. WHIT THE HEADING REFERENCE SWITCH IN NORM THE HSI COMPASS ROSE IS AUTTOMATICALLY REFERENCED TO MAGNETIC NORTH WHEN BETWEEN ______ AND 60 DEGREES SOUTH LATITUDE AND TO TRUE NORTH ABOVE THOSE LATITUDES. 60 DEGREES NORTH 73 DEGREES NORTH. THE CAPTS VSI NORMALLY RECIVES IRU INPUTS FROM THE ____ IRU AND THE F/Os VSI RECIVES IRU INPUTS FROM THE ___ IRU RIGHT: LEFT LEFT: RIGHT. THE LEFT SYMBOL GENERATOR NORMALLY GENERATES THE CAPTAINS DISPLAYS, AND THE RIGHT SG NORMALLY GENERATES THE FIRST OFFICERS DISPLAYS. THESE DISPLAYS APPEAR ON THE _______ EAD, EHSI, ANS EICAS SCREENS EADI AN EHSI. THE ________OPERATES TWO BRAKE SYSTEMS THAT, ALTHOUGH SEPARATE, SHARE THE ACTUAL WHEEL BRAKE COMPONENTS. RIGHT HYDRAULIC SYSTEM RIGHT AND LEFT HYDRAULIC SYSTEMS. FOLLOWING ALTERNATE GEAR EXTENSION, THE GEAR DOORS _____ WITHOUT HYDRAULIC PRESSURE BEING AVAILABLE WILL CLOSE REMAIN OPEN. THE RESERVE BRAKE SYSTEM GETTS ITS HYDRAULIC PRESSURE FROM THE _____ ELECTRIC PUMP LEFT HYDRAULIC SYSTEM RIGHT HYDRAULIC SYSTEM. AIRGROUND SENSING SYSTEMS ARE OPERATED ON THE MAIN GEAR ONLY THE MAIN GEAR AND THE NOSE GEAR. THE PARKING BRAKES CAN BE SET WITH THE ___ BRAKE SYSTEM NORMAL, STANDBY AND ACCUMULATOR NORMAL, RESERVE, AND ACCUMULATOR. THE ALTERNATE LANDING GEAR EXTENSION SYSTEM INCLUDE A SMALL ____ PUMP POWERED BY THE ____ A SYSTEM HYDRAULIC: LEFT ENGINE ELECTRIC HYDRAULIC: HOT BATTERY BUS. WHERE IS THE CREW OXYGEN BOTTLE LOCATED? AFT CARGO COMPARTMENT- LEFT SIDE FORWARD CARGO COMPARMENT- RIGHT SIDE. WHERE IS THE CREW OXYGEN BOTTLE GREEN BLOW OUT DISC? BEHIND THE F/Os SEAT RIGHT SIDE OF THE FUSELAGE. HP BLEED AIR IS USED DURING HIGH POWER ENGINE OPERATIONS LOW POWER ENGINE OPERATIONS. AN ILUMINATED BLEED LIGHT INDICATES THE AIR TEMPERAURE IS HIGH AND THE BLEED AIR VALVE HAS CLOSED. IS THIS SITUATION RESETTABLE BY THE CREW? NOT IT MUST RESET BY MAINTENANCE YES AFTER THE DUCT HAS COOLED. THE BLEED LIGHT ILUMINATES BECAUSE THE BLEED AIR TEMPERATURE IS EXCESSIVE HIGH,PROBABLY BECAUSE OF A PRE-COOLER FAILURE. AS A RESULT THE CORRESPONDING ENGINE BLEED VALVE CLOSES AND THE ___ LIGHT ILUMINATES. EICAS DISPLAYS A CAUTION MESSAGE OF LEFT OR RIGHT HI STAGE: ENG HI STAGE BLEED: ENG BLEED VAL. THE ISOLATION VALVE IS ___ EXCEPT WHEN ON THE GROUND... NORMALLY OPEN NORMALLY CLOSED. FOR ENGINE ANTI-ICING TO OPERATE, THE ASSOCIATED ENGINE BLEED AIR SWITCH MUST BE ON TRUE FALSE. IN FLIGHT, APU BLEED AIR IS AVAILABE ONLY UP TO ___ FEET 12,500 17,500. THE ENGINE BLEED AIR VALVES ARE ELECTRICALLY CONTROLLED AND ELECTRICALLY OPERATED ELECTRICALLY CONTROLLED AND PNEUMATICALLY OPERATED. PILOT AND AUTHOTHROTTLE INPUTS ARE PREVENTED FROM EXCEEDING MAXIMUN THRUST LIMITS BY ___ THE EFCs THE ELCs. THE EFCs MAIN FUNCTION IS TO ______ AS A FUNCTION OF THRUST LEVER POSITION SET ENGINE THRUST MAINTAIN OIL TEMPERATURE. THE OIL PASSES THROUGH THE MAIN OIL FILTER, THEN THE OIL COOLER WHERE___ IS USED TO COOL THE OIL, AND IS THEN DISTRIBUITED TO THE BEARINGS FUEL WATER. EXCEPT DURING TAKEOFF OR GO AROND, IF THE NORMAL OPERATING RANGE OF ENGINE PARAMETERS IS EXCEEDED THE INDICATORS CHANGE FROM_________ WHITE TO AMBER OR RED - AS APPROPIATE ROUND DIAL DISPLAY TO VERTICAL SCALE DISPLAY. THE REVERSE ARE CONTROLLED ___ AND ACTUATED____ BY THE REVERSE THRUST LEVERS AND THE CORE ENGINE EXHAUST___ REVERSED ELECTRICALLY :HYDRAULICALLY: IS NOT PNEUMATICALLY: HYDRAULICALLY: IS. THE LETTERS CON ON THE THRUST MANAGEMENT COMPUTER STAND FOR MAXIMUM CONTINUOS THRUST CONTINUOUS IGNITION MODE. UPON FAILURE OR BOTH AUTOMATIC CONTROLLERS, WILL THE CREW RECIVE AN IMMEDIATE WARNING? MO THE SAME STATUS MESSAGE APPEARS AS FOR A SINGLE CONTROLLER FAILURE YES THE AMBER AUTO INOP LIGH ILUMINATE AND EICAS MESSAGE OF CABIN AUTO INOP. WHEN THE AIRPLANE DESCENDS MORE THAN _____ IN THE CRUISE MODE, THE PRRESSURIZATION SYSTEM ENTERS A DESCENT TO THE LND ALT ALTITUDE 2,000 FEET 1,000 FEET. THE PRESSURIZATION SYSTEM ENTERS THE CRUISE MODE WHEN THE AIRPLANE ALTITUDE REMAINS CONSTANT FOR FIVE MINUTES FOR ONE MINUTE. THE ____ ALTIMETER PROVIDES THE BAROMETRIC CORRECTION TO THE LANDING ALTITUDE SETTING FIRT OFFICERS CAPTAINS. IF AN AUTUMATIC SWITCHOVER TO THE ALTERNATE AUTOMATIC CONTROLLER OCCURS, HOW IS THE CREW ALERTED? STATUS PROMP ON THE UPPER EICAS SCREEN AND A MESSAGE OF CABIN ALT AUTO 1 OR 2 STATUS PROMT ON THE LOWER EICAS SCREEN AND A MESSAGE OF CABIN ALT OUTO 1 OR 2. AT ABOUT____ FEET THE PRESSURIZATIONS SYSTEM IS AT THE MAXIMUM CABIN DIFFERENTIAL PRESSURE (8.6+-.10PSI DURING CLIMB). ABOVE THAT ALTITUDE, THE CABIN CLIMBS AT THE 8.6 PSI RATE UNTIL LEVELING OFF AT THE CRUISE ALTITUDE 37,000 35,000. |
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