Primary Systems 1 Exam | Questions and Answers (Complete Solutions)

Primary Systems 1 Exam | Questions and Answers (Complete Solutions) The primary flight controls are manually controlled using _______________ linkage. A. Direct B. Hydraulic C. Electrical D. Mechanical The secondary flight controls are __________________ controlled and operated. A Hydraulically B. Electrically C. Electromechanically D. Aerodynamically Which of the following is NOT a secondary flight control? A. Control sticks B. Elevator trim tab C. Rudder trim tab D. Trim aid device (TAD) What is the purpose of the elevator system? A. Controls movement of the aircraft about the roll axis B. Changes the center of gravity of the aircraft to allow for climbs and descents C. Controls movement of the aircraft about the pitch axis D. Controls movement of the aircraft about the yaw axis Moving the control stick aft causes the trailing edge of the elevator to move ___________ and the nose of the aircraft to move _____________. A. Up; up B. Down; down C. Down; up D. Up; down The purpose of the elevator bobweight is to ________________. A. Provide a balanced control feed B. Aerodynamically balance the elevator C. Assist the trim aid device (TAD) D. Enhance control feedback and help prevent overstressing of the airframe under high G loading The ailerons control movement of the aircraft about the _______________ axis. A. Yaw B. Vertical C. Pitch D. Roll Which of the following is NOT true concerning the ground adjustable trim tabs? A. Tabs are located on each aileron B. Tabs are adjusted by maintenance personnel C. Tabs can be used as a backup trim system in flight D. Tabs adjust for stick neutral trim input to controls Pilot control inputs cause the ailerons to deflect ___________________. A. In the same direction B. Upwards only C. In first one, then the other direction D. In opposite directions The purpose of the rudder is to rotate the aircraft about the _______________ axis. A. Longitudinal B. Yaw C. Pitch D. Roll When the pilot applies pressure to the left rudder pedal, the trailing edge of the rudder moves ________________ and the nose of the aircraft moves ____________________. A. Left; right B. Right; left C. Left; left D. Right; right Rudder centering springs provide a tendency for the rudder to return to neutral and _______________. A. Reduce pilot workloads B. Enhance control feedback C. Prevent opposing control inputs D. Provide inputs to the trim aid device (TAD) In the event of conflicting pilot aileron/elevator trim inputs, which cockpit trim switch has priority? A. The switch that is depressed first has priority B. The front cockpit C. The rear cockpit D. Neither cockpit; the trim system will not work in the case of simultaneous inputs Where is the rudder trim switch located? A. On the power control lever in each cockpit B. On the control stick C. On the power control lever in the aft cockpit only D. On the trim control panel The aileron trim actuator causes deflection of _____________________________. A. The right aileron only B. Both ailerons C. The aileron trim tabs D. The left aileron only The TAD computes input to the rudder trim system based on __________________________. A. Engine torque, airspeed, altitude, and pitch angle B. Altitude, airspeed, pitch rate, and propeller RPM C. Engine torque, rudder pedal, control forces, and altitude D. Engine torque, airspeed, altitude, and pitch rate The TAD preset takeoff settings will remain constant until __________________________. A. Weight on wheels after landing B. 40 KIAS and weight on wheels C. 80 KIAS and weight on wheels D. 80 KIAS and weight off wheels What happens to the trim aid switch when the trim interrupt button is pressed? A. Power to the system is interrupted and the electromagnetic switch automatically moves to the OFF position B. It will reset after running a self-test C. It remains in the TRIM AID position until it is reset D. Nothing What kind of hydraulic system does the T-6B use? A. An engine-driven, fluid pressurized system charged to 3000 +/- 120 psi B. An electrically operated system charged to 2400 +/- 50 psi C. An engine-driven, fluid pressurized system charged to 3000 +/- 150 psi D. An electrically operated, hydraulically controlled system charged to 3500 +/- 225 psi The engine driven hydraulic pump pressurizes the hydraulic system to which of the following? A. 1800 +/- 120 psi B. 1800 +/- 150 psi C. 3000 +/- 120 psi D. 3000 +/- 150 psi The T-6B has a hydraulic system that uses fluid pressurized to 3000 +/- 120 psi. A. True B. False What are the devices operated by the primary hydraulic system under normal operations? A. Landing gear, flaps, speed brake, and flight controls B. Landing gear/main gear doors, flaps, speed brake, and trim aid device C. Landing gear/main gear inboard doors, flaps, speed brake, and nose wheel steering D. Landing gear, main gear inboard doors, flaps, speed brake, and wheel brakes What is true about the reservoir piston located within the power package? A. It keeps the reservoir pressurized using compressed helium gas B. Protects the engine driven hydraulic pump by reducing the return side of the reservoir to 50 psi C. It keeps the reservoir pressurized using compressed nitrogen gas D. It releases excess pressure at 1790 psi What component in the power package isolates hydraulic pressure coming from the engine driven pump from the rest of the system when the emergency system is activated? A. Slide valve B. Reservoir piston C. Firewall shutoff handle D. 3500 psi pressure relief valve The emergency hydraulic system operates which of the following? A. Landing gear, flaps, main gear doors, speed brake B. Landing gear, main inboard gear doors, flaps C. Landing gear, flaps, speed brake D. Landing gear, main inboard doors, flaps, and nose wheel steering If there is a loss of engine power, the primary system fails, or a failure of the battery bus the emergency hydraulic system is used to operate the ________________. A. Landing gear, landing gear doors, flaps, and speed brake B. Landing gear, main gear inboard doors, and flaps C. Landing gear, main gear doors, nose gear doors, and flaps D. Landing gear, flaps, and speed brake The emergency hydraulic system _______________________________. A. Provides 3000 +/- 120 psi to raise the landing gear and flaps B. Has separate and independent hydraulic lines that ensure gear/flap operation if primary system fails C. Shares the hydraulic lines leading to the actuators with the primary hydraulic system D. Uses an engine-driven pump to produce pressure Power for the landing gear controls is provided through a circuit breaker placarded LDG GR CONT, located on the ____________________. A. Battery bus circuit breaker panels in the front and rear cockpit B. Generator bus circuit breaker panels in the front and rear cockpit C. Battery bus circuit breaker panel in the front cockpit only D. Generator bus circuit breaker panel in the front cockpit only The purpose of the normal landing gear extension/retraction system is to ___________________________. A. Extend and retract the landing gear and retract gear doors only B. Operate as a back up to the primary hydraulic system C. Extend and retract the landing gear and extend doors only D. Extend and retract the landing gear and all gear doors The detent on the landing gear selector handle serves what purpose? A. Prevents the slide valve assembly from "hammering" B. Prevents the gear from being raised accidentally C. Activates the red light in the handle D. Prevents activation of the emergency gear selector The normal indication that the gear and doors are fully retracted is _______________________. A. Only the main gear door lights are illuminated B. Three green lights C. Three green lights and no red lights D. No lights illuminated The aural landing gear position warning safe guards against a gear up landing under which conditions? A. Gear handle not down (regardless of gear conditions), PCL below mid-range position (~87% N1), airspeed below 120 KIAS and flaps up or takeoff B. All gear not indicating down and locked with flaps LDG (regardless of gear door position, power setting, or airspeed) C. There is weight on the wheels with the gear handle not DOWN D. All of the above Prior to raising or lowering the landing gear, ensure airspeed is below _____________________. A. 140 KIAS B. 120 KIAS C. 150 KIAS D. 180 KIAS The device responsible for activating the emergency hydraulic package's selector valve is the __________________________. A. Emergency accumulator B. Helium pre-charge C. 3500 psi pressure release valve D. Landing gear emergency extension handle When extending the gear using the emergency system, ______________________. A. The power package slide valve routes fluid to the accumulator B. The emergency system gear extension actuators are pressurized C. The primary hydraulic system lines are pressurized to 3000 +/- 120 psi D. Hydraulic pressure from the emergency lines activates the normal landing gear actuators What happens when using the emergency system to extend the gear? A. The gear position indicator panel will show two green and three red lights B. The gear position indicator panel will show three red lights C. The main gear inboard doors will remain open D. The main gear inboard doors will remain closed One of the major functions of the flaps is to _______________________. A. Increase sink rate and increase airspeed during landing B. Decrease airspeed needed for approach and decrease landing roll C. Maintain sink rate, decrease drag, and increase airspeed during landing D. Decrease sink rate and increase airspeed during landing What is the purpose for flaps set to takeoff? A. Decrease drag and lift to shorten ground run for takeoff B. Increase lift with maximum increase in drag to shorten ground run for takeoff C. Decrease drag to shorten ground run for takeoff D. Produce the greatest lift with minimal drag to shorten ground run for takeoff The T-6B utilizes a four-segmented split flap concept which are hydraulically operated and electrically controlled. A. True B. False In normal operation, T-6B flaps are ______________ controlled and ________________ operated. A. Mechanically; hydraulically B. Electrically; hydraulically C. Mechanically; electrically D. Electrically; electrically When using the emergency hydraulic system to extend the flaps, the pilot must ________________. A. Ensure the landing gear are down and use the emergency flap extension handle B. Lower the flaps before pulling the emergency landing gear handle and extending the gear C. Pull the emergency landing gear handle to extend the landing gear before extending the flaps D. Ensure the speed brake is extended before moving the flap lever The flaps are operated using ___________________. A. A three-position switch on the PCL quadrant front cockpit only B. A spring-loaded three-position switch on the left instrument panel C. A spring-loaded two-position switch located on the left instrument panel D. A three-position switch on the PCL quadrant in front or rear cockpit The __________________ has the primary purpose of allowing you to decelerate and/or increase your descent rate without increasing your airspeed. A. Flaps system B. Landing gear C. Speed brake D. Wheel brake The speed brake will retract if you perform the following: A. The speed brake switch is moved aft, flaps are extended, or the PCL is moved to MAX B. The speed brake switch is moved forward, flaps are extended, or the PCL is moved to MAX C. The speed brake switch is moved forward, flaps are extended, or the PCL is reduced to MIN D. The speed brake switch is moved forward or airspeed increases above 150 KIAS The speed brake is extended and retracted by a single actuator which is operated by ______________________. A. Electric motors B. Pneumatic pressure C. Hydraulic pressure D. Tie rods Which method(s) are used to steer the aircraft on the ground? A. Nose wheel steering and differential thrust B. Nose wheel steering only C. Rudder and/or differential braking only D. Nose wheel steering, differential braking, and rudder The T-6B is maneuvered on the ground during taxi, takeoff, and landing using the following EXCEPT ____________________. A. By moving control stick in the desired direction of turn B. Through the use of rudder (with sufficient propwash or airflow) C. Operation of the hydraulic nose wheel steering system (NWS) D. Through the application of differential braking The three methods for steering the aircraft during ground operations are differential braking, nose wheel braking, control stick placement in direction of turn. A. True B. False Which method(s) are used to steer the aircraft on the ground? A. Nose wheel steering only B. Nose wheel steering and differential thrust C. Nose wheel steering, differential braking, rudder D. Rudder and differential braking only The nose wheel steering is activated _______________________. A. By pushing either rudder pedal B. By pushing the NWS switch on the instrument panel C. Automatically after landing D. By pushing the nose wheel steering button on the control stick During ground operations involving high taxi speed, nose wheel steering should ________________ used, due to ___________________. A. Not be; increased sensitivity B. Be; better control C. Not be; decreased responsiveness D. Be; reduced wear on the brakes Which statement is true regarding the parking brake? A. It is activated by first pulling and turning the handle 90 degrees clockwise or counterclockwise B. The parking brake will operate partially using the emergency system C. The parking brake will not operate if the hydraulic system fails D. The parking brake is applied by applying the toe brakes while simultaneously pulling and turning the parking brake handle 90 degrees clockwise The brake system is considered inoperative if the primary hydraulic system fails. A. True B. False The fluid which provides pressure to the wheel brakes is supplied by ________________________________. A. The master cylinders and the power package B. The master cylinders and the brake reservoir C. Cylinders at the tops of the brake pedals D. The master cylinders and the brake units The UFCP is the primary means of system control functions including __________________________. A. Communication and navigation radio selection and turning B. Navigation waypoint entry C. Execution of pre-planned waypoints and flight plans D. All of the above Select the FALSE statement concerning the UFCP. A. The UFCP provides data entry functionality and control of a wide variety of displays and subsystems B. The UFCP upper panel provides communication and navigation radio frequency setting functionality C. The hard keys provide access to various UFCP pages D. The UFCP alphanumeric keyboard is the only method to change frequency settings The purpose of the up front control panel (UFCP) is to provide data entry functionality and control of a wide variety of displays and subsystems. A. True B. False The UFCP persistent display is the ____________ presentation and displays after ______________ seconds of inactivity. A. Advanced; 20 B. Default; 20 C. Basic; 10 D. Primary; 10 Invalid frequency data in the UFCP is indicated by what symbol? A. Right-facing chevron B. Asterisk C. Left-facing filled triangle D. Left-facing chevron A filled circle (left justified) in a UFCP data display window indicates the window __________________. A. Has a press and hold function B. Is inactive for data entry C. Is active for data entry D. Has toggle capability for two or more options The UHF radio operates in one of three active modes, set normally through the UFCP. They include ________________. A. Mode A, mode C, mode S B. Transmit/receive and monitor Guard, Transmit/receive, Guard C. Transmit, receive, monitor Guard D. Preset, manual, automatic The data entry knob on the lower portion of the up front control panel ________________. A. Increments numerical values (clockwise rotation) B. Decrements numerical values (counter clockwise rotation) C. Has a push-to-select function D. All of the above From the up front control panel (UFCP) persistent display, the ___________________ can be viewed or changed. A. UHF communication frequency B. VHF communication frequency C. Barometric altimeter D. Both A and B The following statements describe MFD/UFCP REPEAT functionality. Which statement is false? A. When NORM is selected in both cockpits, the MFDs and UFCP pages communicate with respective integrated avionics computer (IACs) B. When MFD/UFCP REPEAT is selected in the rear cockpit, the RPT FWD status advisory appears in the crew alerting system (CAS) display C. When MFD/UFCP REPEAT is selected in the forward cockpit, the RPT FWD status advisory appears in the crew alerting system (CAS) display D. With REPEAT is selected, the MFDs/UFCP in the cockpit where REPEAT is selected duplicate the displays of the other cockpit When REPEAT mode is initiated from the rear cockpit, display control inputs from both cockpits communicate with IAC1.