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ATPL INS

ATPL INS

A PARTIALLY BLOCKED AIR FILTER WILL CAYTE THE AIR DRIVEN TURN INDICATOR TO

. UNDER READ THE CORRECT RATE OF TURN
. OVERREAD THE CORRECT RATE OF TURN
. READ IN THE REVERSE SENSE
. INDICATE ZERO RATE OF TURN
THE VALUES OF COEFFICIENT A,B,C IN ORDER ARE

. +2. 0. +2
. -2. +2. -2
. -3. 0. -2
. +2. +2. +2
THE GYRO IS SET TO READ 356 IN AN AIRCRAFT WHICH IS STATIONARY ON THE GORUND IN THE LATITUDE 50N, THE READING AFTER 1 HOUR AND 45 MIN IS ?

. 357.45
. 354,55
. 358.50
. 353,50
THE GYRO IS SET TO READ THE CORRECT MAGNETIC HEADING WHEN THE AIRCRAFT IS HEADING 090 T VARIATION 10E THE GYRO HEADING AFTER 45 MINYTES FLIGHT ON TRACK OF 090 T WITH NIL DRIFT ALONG THE PARALLEL OF 62 N AT 545 KT IS

. 064.80
. 100.50
. 075.00
. 089.60
THE ROTOR AIR DRIVEN AH ROTATES ANTI CLOCKWISE WHEN VIEWED FROM ABOVE,

ON THE AIRCRAFT ACCELERATING........... WILL CAUSE THE BOTTOM OF THE ROTOR AXIS TO LAG, RESULTING IN A ......WING.......INDICATION.
THE CORRECT WORDS TO COMPLETE THE ABOVE STATEMEN

. INERTIA, PORT, UP
. INERTIA STARBOARD UP
. PRECESSION PORT DOWN
. PRECESSION STARBOARD DOWN
AN AIRCRAFT IS CLIMBING AT A CONSTANT MACH NO, BELOW THE TROPOPAUSE IN ISA CONDITONS DURING THE CLIMB THE RAS WILL

. DECRESE DUE TO DECREASING DENSITY ERROR
. INCREASE DUE TO FALLING TEMPERATURE
. DECREASE DUE TO INCREASING DENSITY ERROR
. INCREASE DUE TO THE LSS DECREASING
AN AIRCRAFT IS FLYING AT FL390 TEMPERATURE 207 A AT MACH 0.85 THE TAS OF THE AIRCRAFT IS

. 561
. 476
. 485
. 472
THE RATE OF PRECESSION OF A GYRO VARIES:

. DIRECTLY INVERSELY INVERSELY
. DERECTLY INVERSELY DIRECTLY
. INVERSELY DIRECTLY INVERSELY
. INVERSELY DIRECTLY DIRECTLY
AN AIRCRAFT FLYING AT A CONSTANT FL AND MAINTAINING A CONSTANT TAS FLIES INTO AN AREA OF WARMER AIR THE AIR DENSEITY IS........CAUSING THE RAS TO

. INCREASING DECREASE
. DECREASING INCREASE
. DECREASING DECREASE
. INCREASING INCREASE
REFERRING TO THE TURN AND SLIP INDICATOR SHOWN ABOVE THE INDICATONS ARE A 90 DEGREE TURN WILL BE COMPLETE IN ------ SECS AND THERE IS -----------BANK FOR THE -----------

. 15 SECS TOO MUCH G FACTOR
. 30 SECS TOO LITTLE RADIUS OF TURN
. 15 SECS TOO LITTLE TAS
. 30 SECS TOO MUCH IAS
IN A CLIMB THE PITOT BECOMES BLOCKED, THE VERTICAL SPEED INDICATOR(VSI) WILL INDICATE:

. THE ORIGINAL RATE OF CLIMB
. TOO HIGH OF A RATE OF CLIMB
. TOO LOW A RATE OF CLIMB
. ZERO
AN AIRCRAFT ACCELERATES ON A WESTERLY HEADING IN THE N HEMISPHERE THE COMPASS NEEDLE ROTATES000000INDICATING A TURN TOWARDS--------

. CLOCKWISE NORTH
. ANTICLOCKWISE NORTH
. CLOCKWISE SOUTH
. ANTICLOCKWISE SOUTH
AN AIRCRAFT PASSIN 6500 FT IN A DESCENT WHEN THE STATIC LINE BECOMES BLOCKED. THE ALTIMETER THEN READS:

. 6500 FT
. LESS THAN 6500 FT
. MORE THAN 6500 FT
. ZERO
IN A HIGH SPEED FLIGHT AT HIGH ALTITUDE THE STATIC SOURCE WILL SUFFER

. BAROMETRIC ERROR
. LAG
. TEMPERATURE ERROR
. POSITION ERROR
A FLIGHT PLANNNED ALONG A TRACK OF 235(M) WHICH PASSES OVER A MOUNTAING HAVING AN ELEVATION OF 3900 METERS...THE REGIONAL QNH is 998 MB ASSUME 1 MB EQUALS 30 FT. THE LOWEST USUBLE FLIGHT LEVEL ACCORDING TO THE QUADRANT RULE SYSTEM WHICH WILL PROVIDE MINIM

. FL140
. FL155
. FL170
. FL160
AN INCREASE OF A 0.15 IN A MACH NUMBER RESULTIS IN A NA INCREASE OF 93 KTS IN TAS. IF THE TEMPERATURE DEVIATION FROM ISA IS 9+ C THE FL IS

. FL200
. FL220
. FL170
. FL090
IN A STABLE PLATAFORM NORH REFERECEND INS THE MEAN GROUNDSPEED IS 550 KTAFTER 21.1 MINS THE INDICATED GROUNDSPEED WAS OVERREADING BY 5 KTS THE INDICATED GROUNDSPEED AFTER 63.3 MINUTES WAS:

. 550
. 545
. 555
. 565
A VSI METERING UNIT INCORPORATES A CAPILLARY TUBE TO COMPESATE FOR

. BAROMETRIC ERROR
. POSITION ERROR
. TEMPERATURE AND PRESSURE CHANGES WITH HEIGHT
. VISCOSITY CHANGES
IN THE ABOVE DIAGRAM OF A GYRO MAGNETIC COMPASS THE COMPONENTS LABELLED B,H AND D IN ORDER ARE

. FLUXVALVE ,INDUCTIVE PICK OFF, SERVO MOTOR
. SIGNAL SELSYN, ROTOR , AMPLIFIER
. STATORS ROTOR TWO
. SERVO MOTOR, STATOR, AMPLIFIER
IF THE PITOT LINE BECOMES BLOCKED IN THE DESCENT THE ASI WILL INDICATE:

. AN INCREASING RAS
. A DECREASING RAS
. A STEADY RAS
. ZERO
AFTER AN 8,5 HR FLIGHT AN AIRCRAFT IS PARKED ON RAMP POSITION N47 59 4 E011 20.0 IF THE INS POSITION READOUT WAS N48 08 0 E011 40.5 THE HOURLY RADIAL ERROR RATE WAS

. 2.6 NM HR
. 1.9 NM.HR
. 2.07 NM/ HR
. 3.25 NM/HR
A GYROSCOPE WHICH UTILISES GRAVITY TO CONTROL A VERTICAL REFERENCE IS TERMED A

. TIED GYRO
. SPACE GYRO
. EARTH GYRO
. RATE GYRO
THE PRODUCT OF THE FIRST INTEGRATION OF THE E/W ACCELERATON SENSED BY AN INS SYSTEM IS

. DEPARTURE
. SPEED ALONG THE LOCAL PARALLEL
. SPEED ALONG THE LOCAL VERTICAL
. DISTANCE
IN THE ABOVE DIAGRAM OF A SERVO ALTIMETER THE COMPONENTS LABELLED B,C,D IN ORDER ARE

. TORQUE MOTRO, INDUCTIVE PICK OFF, AMPLIFIER
. TORQUE MOTOR, AMPLIFIER, TANSDUCER
. TWO WAY MOTOR, AMPLIFIER, INDUCTIVE PICK OFF
. TWO WAY MOTOR, INDUCTIVE PICK OFF,TRANSDUCER
WITH REFERENCE TO THE ABOVE DIAGRAM OF A MACHMETER THE CORRECT DESCRIPTIONS OF THE COMPONENTS LABELLED A,B AND C IN ORDER ARE

. AIRSPEED CAPSULE, PITOT PRESSURE ENTRU, RATIO ARM
. AIRSPEED CAPSULE, DYNAMIC PRESSURE ENTRY, RANGING ARM
. ALTITUDE CAPSULE, STATIC PRESSURE ENTRY, RANGING ARM
. ALTITUDE CAPSULE, STATIC PRESSURE ENTRY, RATIO ARM


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