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31 Cards in this Set
- Front
- Back
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The purpose of antiskid generators is to A - monitor hydraulic pressure applied to brakes B - indicate when a tire skid occurs C - measure wheel rotational speed and any speed changes |
C - measure wheel rotational speed and any speed changes |
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In a brake antiskid system, when an approaching skid is sensed, an electrical signal is sent to the skid control valve which A - acts as a bypass for the debooster cylinders B - relieves the hydraulic pressure on the brake C - equalize the hydraulic pressure in adjacent brakes |
B - relieves the hydraulic pressure on the brake |
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An antiskid system is A - a hydraulic system B - an electrohydraulic system C - an electrical system |
B - an electrohydraulic system |
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Antiskid braking systems are generally armed by A - a centrifugal switch B - a switch in the cockpit C - the rotation of the wheels above a certain speed |
B - a switch in the cockpit |
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A typical takeoff warning indication system, in addition to throttle setting, monitors the position of which of the following? A - ailerons, elevators, speed brake, and steerable fuselage landing gear B - elevators, speed brake, flaps, and stabilizer trim C - aerodynamically actuated slats, elevators, flaps, and speed brake |
B - elevators, speed brake, flaps, and stabilizer trim |
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The primary purpose of a takeoff warning system is to alert the crew that a monitored flight control is not properly set prior to takeoff. The system is activated by A - an 80 know airspeed sensor B - an ignition system switch not set for takeoff C - a thrust lever |
C - a thrust lever |
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(1) An airspeed indicator measures the differential between pitot and static air pressures surrounding the aircraft at any moment of flight (2) An airspeed indicator measures the differential between pitot and cabin air pressures at any moment of flight Regarding the above statements, A - both No. 1 and No. 2 are true B - only No. 2 is true C - only No. 1 is true |
C - only No. 1 is true |
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The angle-of-attack detector operates from differential pressure when the airstream A - is parallel to the longitudinal axis of the aircraft B - is not parallel to the true angle of attack of the aircraft C - is parallel to the angle of attack of the aircraft |
B - is not parallel to the true angle of attack of the aircraft |
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(1) When an airplane is slowed below approximately 20 MPH, the antiskid system automatically deactivates to give the pilot full control of the brakes for maneuvering and parking (2) An antiskid system consists basically of three components; wheel speed sensors, control box, and control valves Regarding the above statements, A - only No. 1 is true B - only No. 2 is true C - both No. 1 and No. 2 are true |
C - both No. 1 and No. 2 are true |
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In an antiskid system, wheel skid is detected by A - an electrical sensor B - a discriminator C - a sudden rise in brake pressure |
A - an electrical sensor |
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Which of the following functions does a skid control system perform? 1. normal skid control 2. normal braking 3. fail safe protection 4. locked wheel skid control 5. touchdown protection 6. takeoff protection A - 1, 2, 3, 4 B - 1, 3, 4, 5 C - 1, 2, 5, 6 |
B - 1, 3, 4, 5 |
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In the air with the antiskid armed, current cannot flow to the antiskid control box because landing gear A - squat switch is open B - down and lock switch is open C - antiskid valves are open |
A - squat switch is open |
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At what point in the landing operation does normal skid control perform its function? A - when wheel rotation deceleration indicates an impending skid B - when wheel rotation indicates hydroplaning condition C - anytime the wheel is rotating |
A - when wheel rotation deceleration indicates an impending skid |
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(1) Antiskid system is designed to apply enough force to operate just below the skid point (2) A warning lamp lights in the cockpit when the antiskid system is turned off or if there is a system failure Regarding the above statements, A - only No. 1 is true B - only No. 2 is true C - both No. 1 and No. 2 are true |
C - both No. 1 and No. 2 are true |
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When an airplane's primary flight control surfaces are set for a particular phase of flight, such as landing or takeoff, the corresponding control-surface indicating system will show A - flap/slat position B - speed break position C - trim position |
C - trim position |
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The pneumatic (reed) type stall warning system installed in some light aircraft is activated by A - static pressure B - positive air pressure C - negative air pressure |
C - negative air pressure |
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Stall warning systems are generally designed to begin warning the pilot when a stall A - is imminent B - is starting to occur C - first affects the outboard portions of the wings |
A - is imminent |
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Which of the following conditions is most likely to cause the landing gear warning signal to sound? A - landing gear locked down and throttle advanced B - landing gear locked down and throttle retarded C - landing gear not locked down and throttle retarded |
C - landing gear not locked down and throttle retarded |
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Where is the landing gear safety switch usually located? A - on the main gear shock strut B - on the landing gear drag brace C - on the pilot's control pedestal |
A - on the main gear shock strut |
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What safety device is actuated by the compression and extension of a landing gear strut? A - unlock switch B - down lock switch C - ground safety switch |
C - ground safety switch |
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Which repair would require a landing gear retraction test? A - landing gear safety switch B - red warning light bulb C - gear downlock microswitch |
C - gear downlock microswitch |
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Landing gear warning systems usually provide which of the following indications? A - red light for unsafe gear, no light for gear down, green light for gear up B - green light for gear up and down, red light for unsafe gear C - red light for unsafe gear, green light for gear down, no light for gear up |
C - red light for unsafe gear, green light for gear down, no light for gear up |
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In most modern hydraulically actuated landing gear systems, the order of gear and fairing door operation is controlled by A - sequence valves B - shuttle valves C - microswitches |
A - sequence valves |
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What landing gear warning device(s) is/are incorporated on retractable landing gear aircraft? A - a visual indicator showing gear position B - a light which comes on when the gear is fully down and locked C - a horn or other aural device and a red warning light |
C - a horn or other aural device and a red warning light |
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When a landing gear safety switch on a main gear strut closes at liftoff, which system is deactivated? A - landing gear position system B - antiskid system C - aural warning system |
B - antiskid system |
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The rotor in an autosyn remote indicating system uses A - an electromagnet B - a permanent magnet C - neither an electromagnet nor a permanent magnet |
A - an electromagnet |
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The basic difference between an autosyn and a magnesia indicating system is the A - rotor B - transmitter C - receiver |
A - rotor |
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The rotor in a magnesia remote indicating system uses A - a permanent magnet B - an electromagnet C - an electromagnet and a permanent magnet |
A - a permanent magnet |
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Microswitches are used primarily as limit switches to A - limit generator output B - control electrical units automatically C - prevent overcharging of a battery |
B - control electrical units automatically |
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Which of he following are some uses for a DC-selsyn system? 1. indicates position of retractable landing gear 2. indicates the angle of incidence of an aircraft 3. indicates the altitude of an aircraft 4. indicates cowl flaps or oil cooler door position 5. indicates fuel quantity 6. indicates the rate of climb of an aircraft 7. indicates position of wing flaps A - 1, 4, 5, 7 B - 2, 3, 4, 5 C - 2, 3, 5, 6 |
A - 1, 4, 5, 7 |
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(1) A DC-selsyn system is a widely used electrical method of indicating a remote mechanical movement or position (2) A synchro-type indicating system is an electrical system used for transmitting information from one point to another Regarding the above statements, A - only No. 1 is true B - only No. 2 is true C - both No. 1 and No. 2 are true |
C - both No. 1 and No. 2 are true |
